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- 0210

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# EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 13

- 0210

Date: 11 September 2013

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation

(EC) No 216/2008 on behalf of the European Community, its Member States and of the

European third countries that participate in the activities of EASA under Article 66 of that

Regulation.

This AD is issued in accordance with E U 748/2012 , Part 21

. A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an

aircraft to which an AD applies, except in accordance with the requ irements of that AD

, unless otherwise specified by the Agency [EC

2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]

.



### Design Approval Holder’s Name:

AIRBUS Type/Model designation(s):

A300 aeroplanes

TCDS Number: France n° 145

F oreign AD: N ot applicable

Supersedure: None



### ATA 32, 36 Landing G ear / Pneumatic

– Life L imits

– I mplementation

Manufacturer(s): Airbus ( f ormerly Airbus Industrie)

Applicability: Airbus A300 aeroplanes

, all certified models

, all Manufacturer Serial Numbers.

Reason: Some life limits previously defined in Revision 00 of A300 ALS Part 1 have

been removed form that document at Revision 01 and should normally be

included in an ALS Part 4.

A t this time, there are no plans to issue an ALS Part 4 for A300 aeroplanes

.

Nevertheless, f ailure to comply with these life limits could result in an unsafe

condition

.

For the reasons described above, it has been decided to require the application

of these life limits through a separate AD . Consequently, this AD r e quires

application of life limits applicable to Main Landing Gear (MLG) barrel

assembly, retraction actuator assembly linkage assembly and flanged duct

which were previously contained in Airbus ALS Part 1 Revi sion 0 0

.

EASA AD 2007

- 0293, which required compliance with the actions specified in

ALS Part 1, will be superseded by a new AD, requiring complianc e with ALS

Part 1 at Revision 1

.

Effective Date: 18 September 2013E ASA AD No.: 20 13

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### Required A ction(s)

and Compliance

Time(s) : Required as indicated, unless accomplished previously:

(1) From the effective date of this AD, r eplace each component before or upon

reaching the applicable life limit, as specified in Appendix 1 of this AD.

( 2 ) Compliance with the requirements of paragraph (1) of this AD can be

demonstrated by :

(2.1) Revising as follows, the approved Aircraft Maintenance Programme

(AMP) on the basis of which the operator or the owner ensures the

continuing airworthiness of each operated aeroplane:

Incorporate all the airworthiness limitations as specified in Appendix

1 of this AD

, as applicable to aeroplane model and configuration

,

and

(2.2) Complying with the approved AMP described in paragraph (2.1) of

this AD.

(3) L ife limits specified in Appendix 1of this AD supersede any life limits

referenced in EASA AD 2007

- 0293 for the parts listed in Appendix 1 of this

AD

.

Ref. Public ations: None

Remarks: 1. If requested and appropriately substantiated, EASA can approve

Alternative Methods of Compliance for this AD.

2. Based on t he required actions and the compliance time, EASA have

decided to issue a Final AD with Request for Comments, postponing the

public consultation process until after publication.

3. Enquiries regarding this AD should be referred to the Safety Information

Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

.

4. For any question concerning the technical conte nt of the requirements in

th is AD, please contact:

AIRBUS SAS

– E I AW (Airworthiness Office )

, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51.E ASA AD No.: 20 13

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## Appendix 1

(*) Whichever occurs first. LIFE LIMITS (*) LIFE LIMITS APPLICABILITY Notes are located under the assy title.

Part Number FH LDG Cal. B2

- 1A

B2

- 1C B2K

- 3C

B2

- 20x B2

- 320 B4

- 2C

B4

- 1xx B4

- 2xx C4

- 203

F4

- 203

ATA 32

- 10

- 00 MAIN LANDING GEAR

BARREL ASSEMBLY

Stirrup C66277

- 10 N/A 66600 N/A X X X X

C66277

- 12 N/A 76600 N/A X X X X

C66277

- 14 N/A 76600 N/A X X X X

D58303

- 1 N/A 76600 N/A X X X X

Stirrup pin C66457 N/A 76600 N/A X X X X

D48939 N/A 76600 N/A X X X X

D48939

- 1 N/A 76600 N/A X X X X

D58314

- 1 N/A 76600 N/A X X X X

Universal joint C66279 N/A 76600 N/A X X X X

C66279

- 2 N/A 76600 N/A X X X X

C66279

- 6 N/A 76600 N/A X X X X

D58313

- 1 N/A 76600 N/A X X X X

Plate (Upper end) C61637

- 10 N/A 76600 N/A X X

C61637

- 11 N/A 76600 N/A X X

C61637

- 12 N/A 76600 N/A X X

Plate (Rear head end) C61638

- 10 N/A 53300 N/A X X

C61638

- 11 N/A 53300 N/A X X

C61638

- 20 N/A 76600 N/A X X

Tie rod C68523

- 3 N/A 76600 N/A X XE ASA AD No.: 20 13

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## Appendix 1 (continued)

(*) Whichever occurs first. LIFE LIMITS (*) LIFE LIMITS APPLICABILITY Notes are located under the assy title.

Part Number FH LDG Cal. B2

- 1A

B2

- 1C B2K

- 3C

B2

- 20x B2

- 320 B4

- 2C

B4

- 1xx B4

- 2xx C4

- 203

F4

- 203

RETRACTION ACTUATOR ASSEMBLY

(1) When SB A300

- 32

- 0123 embodied before SB A300

- 32

- 0113.

(2) When SB A300

- 32

- 0123 embodied after SB A300

- 32

- 0113.

Sliding rod C69028

- 1 N/A 34 000 N/A X X

C69028

- 4 N/A 34 000 N/A X X

C69029

- 1 (1) N/A 32 000 N/A X X X X

C69029

- 2 N/A 32 000 N/A X X X X

C69029

- 3 N/A 32 000 N/A X X X X

C69029

- 4 (2) N/A 22 000 N/A X X X X

Piston C67078 N/A 33 000 N/A X X X X

C67078

- 1 N/A 33 000 N/A X X X X

End fitting C61342

- 4 N/A 36 700 N/A X X

C66510

- 4 N/A 32 000 N/A X X X X

LINKAGE ASSEMBLY

Upper multiple link pin

(Multiple link/Upper

link) C61505 N/A 76 600 N/A X X

C61505

- 1 N/A 76 600 N/A X X

C61505

- 20 N/A 76 600 N/A X X

ATA 36

- 11

- 05 PNEUMATIC

(1) “xx” at the end of the P/N stands for any number between 00 and 99.

Duct flanged (1) A21274063000xx N/A 24 000 N/A X X X