EASA AD No.: 2012-0229

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0229

Date: 31 October 2012

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 and A300-600 aeroplanes

TCDS Number: France TCDS No 145

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Frame Base Fitting between Frames 41 and 46 Area 2 

– Inspection

Manufacturer(s): Airbus (formerly Airbus Industries)

Applicability: A300 and A300-600 aeroplanes, all certified models, all manufacturer serial 

numbers, if repaired in accordance with Airbus Service Bulletin (SB) A300-53-

0337 Revision 01 or earlier revision, or A300-53-6111 Revision 04 or earlier 

revisions, as applicable to aeroplane Model.

Reason: During accomplishment of Airbus SB A300-53-6111, which addresses detailed 

visual inspections of the lower frame fittings between Frame (FR) 41 and FR46, 

on one A300-600 aeroplane a crack was detected in the area 2 of the foot of 

frame FR46 at junction radius level. 

This frame, that was previously repaired due to a crack finding in the area 1,

was not due to be inspected before reaching the post-repair inspection 

threshold, i.e. 45 400 FC, from repair embodiment.

It has been determined that the current repairs proposed in Airbus SB A300-53-

6111and Airbus A300-53-0337 are of limited effect to prevent cracking in the 

area 2 of the lower frame fittings.

Consequently, as a temporary action and until an improvement of the existing 

repairs is made available, this AD requires a one-time detailed visual inspection 

of frame base fittings that were repaired in accordance with Airbus SB A300-

53-0337 original issue or Rev. 1 or Airbus SB A300-53-6111 original issue up to 

Rev.4, and the reporting of findings to Airbus.

Effective Date: 14 November 2012
EASA AD No.: 2012-0229

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 1 000 FH after the effective date of this AD, accomplish the 

following actions concurrently:

(1.1) Check the maintenance records to determine if repairs were 

performed in the area 1 of the frame base fitting as defined in the 

appendix 1 of Airbus Alert Operators Transmission (AOT) A53W001-

12 dated 04 Jul 2012.

(1.2) If it is conclusively determined, as required by paragraph (1.1) of this 

AD, that the affected area has been repaired, accomplish a one-time 

detailed visual inspection of the frame base fittings between FR41 

and FR46 in the area 2 defined in accordance with appendix 2 of 

AIRBUS AOT A53W001-12 dated 04 July 2012.

(2) If, during the inspection as required by paragraph (1.2) of this AD, any 

crack is detected, before next flight, contact Airbus for approved 

instructions for corrective action and accomplish those instructions 

accordingly.

Ref. Publications: Airbus Alert Operators Transmission (AOT) A53W001-12 dated 04 July 2012.

Airbus Service Bulletins:

A300-53-0337 Revision 01 dated 17 March 2003 or earlier revision.

A300-53-6111 Revision 04 dated 25 August 2011 or earlier revisions.

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

Alternative Methods of Compliance for this AD.

2. This AD was posted on 20 July 2012 as PAD 12-082 for consultation until 

17 August 2012. The Comment Response Document can be found at 

http://ad.easa.europa.eu.

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).