E ASA AD No

. : 2013

- 0180

TE. CAP.0011 0

- 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

. : 20 13

- 0180

Date: 09 August 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 Age ncy [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

- 600 aeroplanes

TCDS Number : France No.145

F oreign AD : Not app licable

Supersedure: This AD s upersedes DGAC France AD 94

- 031

- 155 (B) R1 dated 07 May 1997.



### ATA 57 Wings

– Rear S par MLG A ttachment F itting H oles

– Inspection / Repair

Manufacturer(s): Airbus ( formerly Airbus Industrie)

Applicability: A irbus A300

- 600 aeroplane s , all certified models except A300F4

- 622R , all serial numbers.

Reason: During full

- scale fatigue testing , cracks were found on the rear spar from certain bolt holes at the attachment of the Main Landing gear ( MLG ) forward pick

- up fitting and the MLG Rib 5 aft. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane.
DGAC France issued AD 94

- 031

- 155 (later revised) to require High Frequency Eddy Current (HFEC) or Ultraso nic (U/S) inspections of certain fastener holes where the MLG forward pick

- up fitting and MLG Rib 5 aft are attached to the rear spar. Since DGAC France AD 94

- 031

- 155(B) R1 was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300

- 600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the t hreshold and interval must be reduced to allow timely detection of these cracks and accompli shment of an applicable corrective action

. For the reasons described above, this AD retains the requirements of DGAC France AD 94

- 031

- 155 (B) R1 , which is superseded, but reduces the related compliance times

.E ASA AD No

. : 2013

- 0180

TE. CAP.0011 0

- 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. Effective Date: 23 August 2013

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the compliance time s as specified in Airbus Service Bulletin (SB) A300

- 57

- 6017 Revision 04, depending on the aeroplane configuration and Average Flight Time, accomplish repetitive U/S inspection s of the MLG attachment fitting holes on the wing rear spar in accordance with the instruction s of Airbus SB A300

- 57

- 6017 Revision 04. For aeroplanes modified in accor dance with the instructions of Airbus SB A300

- 57

- 6073 at any revision, the threshold of repetitive U/S inspections of the MLG attachment fitting holes on the wing rear spar is counted from the accomplishment of the modification. (2) If
, during any inspection as required by paragraph (1) of this AD cracks are found , before next flight
, accomplish the applicable corrective actions in accordance with the instruction s of Airbus SB A300

- 57

- 6017 Revision 04. (3) Inspections and corrective actions, accomplished before the effective date of this AD in accordance with the instructions of Airbus SB A300

- 57

- 6017 at original issue up to Revision 0 3, are acceptable to comply with the initial requirements of paragraph s (1) and (2) of this AD. After the effective date of this AD, inspections and corrective actions must be accomplished in accordance with the instruction s of Airbus SB A300

- 57

- 6017 at Revision 04. (4) Accomplishment of c orrective action ( s ) on an aeroplane, as required by paragraph (2) of this AD
, do es not constitute terminating action for the repetitive inspections required by paragraph (1) of this AD for that aeroplane

.
Ref. Publications: Airbus SB A300

- 57

- 6017 Revision 04 dated 24 February 2011.
Airbus SB A300

- 57

- 6073 original issue dated 30 September 1997, Revision 01 dated 12 January 1999 or Revision 02 date d 12 September 2011. The use of later approved revisions of th ese document s are acceptable for compliance with the requirement s of this AD.

Remarks : 1. If requeste d and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.
2. This AD was posted on 21 January 2013 as PAD 13

- 015 for consultation until 18 February 2013

. The Comment Response Document can be found at http://ad.easa.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 requirements in this AD, please contact : AIRBUS SAS

– EIAW (Airworthiness Office) E

- mail: continued.airworthiness

- wb.external@airbus.com

.