EASA AD No.: 2013-0210

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/4

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0210

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 EU 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 operate an 

aircraft to which an AD applies, except in accordance with the requirements 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

Foreign AD: Not applicable

Supersedure: None

ATA 32, 36 Landing Gear / Pneumatic – Life Limits – Implementation

Manufacturer(s): Airbus (formerly 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.

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

Nevertheless, failure 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 requires 

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 Revision 00.

EASA AD 2007-0293, which required compliance with the actions specified in 

ALS Part 1, will be superseded by a new AD, requiring compliance with ALS 

Part 1 at Revision 1.

Effective Date: 18 September 2013
EASA AD No.: 2013-0210

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/4

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) From the effective date of this AD, replace 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) Life 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. Publications: None

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

Alternative Methods of Compliance for this AD.

2. Based on the 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 content of the requirements in 

this AD, please contact:

AIRBUS SAS – EIAW (Airworthiness Office),

Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51. 
EASA AD No.: 2013-0210

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/4

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

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 B4-2CB4-1xx B4-2xx C4-203F4-203

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 X
EASA AD No.: 2013-0210

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/4

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

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 B4-2CB4-1xx B4-2xx C4-203F4-203

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