EASA AD No.: 2012

- 0229

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## 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 E U 748/2012 , Part 21

. A.3B. In accordan ce 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 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 aeroplane s

TCDS Number: France TCDS No 145

F oreign AD: Not applicable
Supersedure: No n e



### 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 revision s, 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 repa ired due to a crack finding in the area 1 , was not due to be inspected before reaching the post

- re pair inspection threshold, i.e. 45 400 FC , from repair embodiment. It has been determined that the current repairs proposed in Airbus SB A300

- 53

- 6111 and Airbu s 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 existin g 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 Airbu s.
Effective Date: 14 November 2012EASA AD No.: 2012

- 0229

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(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. Public ations: 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 revision s.
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.e asa.europa.eu

. 3. Enquiries regarding this A D 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 requireme nts in this AD, please contact AIRBUS SAS

– E I AW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).