E ASA AD No.: 20 1 4

- 0034

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 1 4 - 0034

Date: 05 February 201 4

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 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) exemption]

. 

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

- 600 , A300

- 600ST and A310 aeroplanes

TCDS Number s : France No. 145 and EASA.A.014
F oreign AD: Not applicable Supersedure: None



### ATA 24 Electric al Power

– Wing Electrical Installation

– Modification

Manufacturer(s): Airbus ( formerly Airbus Industrie) Applicability: Airbus A300

- 600, A300

- 600ST and A310 aeroplanes, all certified models , all manufacturer serial numbers

. Reason: Following publication of FAA SFAR 88 (Special Federal Aviation Regulation 88) , EASA issued AD 2006

- 0076 requiring inspection and c orrective action to improve the explosion risk protection system for the left hand (LH) and right hand (RH) wings on A300, A300

- 600, A300

- 600ST and A310 aeroplanes. For A300

- 600, A300

- 600ST and A310 aeroplanes, the required detai led visual inspections of electrical bundles located in the leading and trailing edges of the RH and LH wings and a review of the wing electrical installation on the f inal assembly line have shown that the wing electrical installation does n o t comply with the minimum distance inspection criteria to the surrounding structure in a few wing locations

. This condition, if not detected and corrected, could lead to damage on the electrical harness e s and on the surrounding structure. To address this unsafe condition, Airbus developed an improvement of the wing electrical installation to prevent possible chafing and subsequent damage to the electrical harnesses and surrounding structure

. For the reasons described above, this AD requires installation of new bracket assemblies to ensure the clearance between the wiring and the structure , and installation of protective split sleeve s as mechanical protection to the electrical harnesses

. Effective Date: 19 February 2014E ASA AD No.: 20 1 4

- 0034

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. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously : (1) Within 30 months after the effective date of this AD, modify the electrical installation in the RH side and LH side wing s in accordance with the instructions of Airbus Service Bulletin (SB) A300

- 24

- 6103 Revision 02 , or SB A300

- 24

- 9014 Revision 01 , or SB A310

- 24

- 2105 Revision 01 , as applicable to aeroplane model. (2) Modifications, accomplished before the effective date of this AD in accordance with the instructions of Airbus SB A300

- 24

- 9014 or SB A310

- 24

- 2105 at original issue, as applicable to aeroplane model, are acceptable to comply with the requirements of paragraph (1) of this AD

. Ref. Public ations: Airbus SB A300

- 24

- 6103 Revision 02 dated 07 February 2013

. Airbus SB A300

- 24

- 9014 original issue dated 17 June 2010, or Revision 01 dated 23 April 2013

. Airbus SB A310

- 24

- 2105 original issue dated 20 March 2013 or Revision 01 dated 11 December 2013

. The u se of later approved revisions of these documents 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. This AD was posted on 11 October 2013 as PAD 13

- 157 for consultation until 08 November 2013

. 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 conte nt of the requirements in this AD, please contact: AIRBUS SAS

– E IAW (Airworthiness Office) E

- mail: continued.airworthiness

- wb.external@airbus.com

.