EASA AD No.: 2013

- 0008R1

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

. : 2013
- 0008 R1

Date: 22 January 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) exempt ion]. 

### Design Change Approval Holder’s Name : AIRBUS Type/Model designation(s) : A 300

- 600 aeroplanes

TCDS Number: France No.145

F oreign AD: Not applicable

Revision : T his AD revises EASA AD 2013

- 000 8 dated 10 January 2013



### ATA 5 7 Wings

– Outer W ing Stringer R un - O uts at Rib 14

– Modification

Manufacturer(s): Airbus ( f ormerly Airbus Industrie)
Applicability: Airbus A300 B4

- 601, A300B4

- 603, A300B4

- 605R, A300 B4

- 620, A300 B4

- 622, A300 B4

- 622R , except aeroplanes on which Airbus Modification 10324 or 10325 has been embodied in production

. Note: This AD applies only to aeroplanes that are operate d beyond the Extended Service Goal (ESG 1 ) : 42 500 F light C ycles (FC ).

Reason: During full

- scale fatigue testing, cracks were detected in the bottom wing skin stringers at rib 14. In addition, A300 aeroplane operators have also reported finding cracks in the same area. This condition , if not detected and corrected , could impair the structural integrity of the wings. Additional analysis results showed that the improve d design of the stringer run

out is necessary for aeroplanes operating beyond the ESG 1

. For the reasons described above, this AD requires the removal of the stringer end run

- out plate at stringer 19 on the bottom wing skin and the re

- profiling modification of the stringers 10, 11, 12, 17 and 19. This AD is revised to incorporate the correct Modification number and to clarify the Applicability.

Effective Date: 24 January 2013EASA AD No.: 2013

- 0008R1

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 previously accomplished: (1) Upon accumulation of 42 500 Total FC , or within 2 000 FC after the effective date of this AD, whichever occurs later, modify the profile of stringer run

- outs at rib 14 of both wings in accordance with the a ccomplishment Instructions of Airbus Service Bulletin ( SB ) A300

- 57

- 6 046 Revision 01. (2) Modification of an aeroplane before the effective date of this AD , in accordance with the instructions of Airbus SB A300

- 57

- 6046 (MOD 10326) at original issue , is acceptable for compliance with the requirements of paragraph (1) of this AD for that aeroplane.

Ref. Public ations: Airbus SB A300

- 5 7

- 60 46 at original issue dated 18 January 1994 , or Revision 01 dated 18 April 2011. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. Th e original issue of this AD was posted on 27 November 2012 as PAD 12

- 152 for consultation until 25 December 2012

. No comments were received during the consultation period. 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

– E I AW (Airworthiness Office), Telephone: + 33 (0)5 6118

- 4139, Fax: + 33 (0)5 6193

- 4451.