E ASA AD No.: 2013

- 0013 R1

TE. CAP.0011 0

- 003 © 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

- 0013 R1

Date: 2 0 February 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 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) exempt ion]. 

### Design Approval Holder’s Name:
Airbus Type/Model designation(s):
A300

- 600 aeroplanes

TCDS Number: France No.145

F oreign AD: Not applicable

R e v i sion : This AD revises EASA AD 2013

- 0013 dated 15 January 2013, which

supersede d DGAC France AD 1997

- 375

- 239 (B) R3 dated 12 July 2000.



### ATA 57 Wings

– Rear S par Build Slot b etween Rib s 1 and 2

– Inspection

Manufacturer(s): Airbus (Forme r ly Airbus Industries)
Applicability: Airbus A300B4

- 601, A300B4

- 6 03, A300 B4

- 605R, A300B4

- 620, A300B4

- 622, A300B4

- 622R, A300C4

- 605R/F, A300C4

- 620 , and A300F4

- 605R aeroplanes, all manufacturer serial numbers.

Reason: Wing fatigue tests carried out by Airbus revealed cracks on the vertical web of the rear spar between Ribs 1 and 2

. S imilar cracks in the same area were reported ly found by A3 00 aeroplane operators. In all cases, the cracks ran from the tip of the build slot to the nearest adjacent bolt hole. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, DGAC France issued AD 1 997

- 375

- 239 (later revised, now at R evision 3 ) to require an eddy current inspection of the aft face of the wing rear spar in the area adjacent to the build slot on Left Hand (LH) and Right Hand (RH) wings. Since that AD was issued, a fleet survey and upda ted f atigue and d amage t olerance analysi s were performed in order to substantiate the second A300

- 600 Extended Service Goal (ESG2) exerci se. The results of th e survey and analysis showed that the inspection threshold and interval must be reduced to allow timely detection of cracks and accomplishment of an applicable corrective action. Prompted by these findings, Airbus issued Airbus Service Bulletin (SB) A300

- 57

- 6059 Revision 04

.E ASA AD No.: 2013

- 0013 R1

TE. CAP.0011 0

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

- Internet/Intranet. For the reasons described abo ve, this AD retains the requirements of DGAC France AD 1997

- 375

- 239 (B)R 3
, which is superseded, but redefines the t hresholds and intervals. This AD also expands the applicability to aeroplanes on which Airbus modification (mod) 12102 has been embodied in production and to aeroplanes on which Airbus SB A300

- 57

- 6063 (Airbus mod 11130) has been embodied in service.
This AD is re

- published for cl arification of the inspection thresholds and intervals.

Effective Date: Revision 1: 06 March 2013 Original issue: 29 January 2013
Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the compliance times (threshold s and intervals , flight hours or flight cycles, whichever occurs first ) defined in Table 1, Table 2, T able 3 and T able 4 of Airbus SB A300

- 57

- 6059 Revision 4
, as applicable to the aeropl ane configuration and aeroplane utilization , accomplish repetitive eddy current inspection s of the aft face of the wing rear spar web in the area adjacent to the build slot in accordance with the instructions of Airbus SB A300

- 57

- 6059 Revision 04. (2) If, during any inspecti on as required by paragraph (1 ) of this AD, discrepancies are detected, before next flight, accomplish the applicable corrective actions in accordance with the instructions of Airbus SB A300

- 57

- 6059 Revision 04. (3) Corrective actions, as required by paragraph ( 2 ) of this AD do not
con stitute terminating action for the repetitive inspection requirements of paragraph ( 1 ) of this AD. (4) Inspections and corrective actions
, accomplished before the effective date of this AD, in accordance with the instructions of Airbus SB A3 0 0

- 57

- 6059 at original issue up to Revision 0 3
, are acceptable to comply wit h the initial requirements of paragraph s (1) and (2) of this AD (initial and repetitive inspection s ). After the effective date of this AD, repetitive inspection s and, depending on findings, corrective actions must be accomplished in accordance with the instructions of Airbus SB A340

- 57

- 6059 at Revision 0 4.

Ref. Public ations: Airbus SB A300

- 57

- 6059 Revision 0 4 dated 22 February 2011.
The use of la ter approved revisions of th i s 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 th is AD was posted on 26 November 2012 as PAD 12

- 148 for consultation until 24 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 conte nt of the requirements in this AD, please contact: AIRBUS SAS

– EIAW (Airworthiness Office), Telephone: + 33 (0)5 6118

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

- 4451.