EASA AD No.: 2015-0142

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0142

Date: 17 July 2015

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 EU 1321/2014 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 Agency [EU 

1321/2014 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):

A330 and A340 aeroplanes

TCDS Number: EASA.A.004, EASA.A.015

Foreign AD: Not applicable

Supersedure: None

ATA 92 Electric / Electronic Common Installation – Feeder Cable Routing 

Attachment – Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, 

A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, 

A330-341, A330-342 and A330-343 aeroplanes, all manufacturer serial 

numbers (MSN), except those on which Airbus modification 203672 has been 

embodied in production, and

Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313,

A340-541, A340-542, A340-642 and A340-643 aeroplanes, all MSN.

Reason: Two events have been reported of feeder cable chafing at the pylon-wing 

junction on A330 aeroplanes. Inspection of the affected area for the first event 

revealed that the bracket supporting the cables G-route, made in plastic, was 

broken. The second event was due to clamp damage. Failure of support 

bracket and/or damage of clamp led to the feeder cables gradually chafing 

away at the cut-out edge by vibration. Due to design similarity, A340 

aeroplanes are also affected by this issue.

This condition, if not corrected, could create a short circuit, in combination with 

fuel vapour on ground, possibly resulting in a fire or explosion.

To address this unsafe condition, Airbus developed modifications to be 

embodied in service through Airbus Service Bulletin (SB) A330-92-3132, SB 

A340-92-4100 or SB A340-92-5066, as applicable to aeroplane type and 

model.

For the reasons described above, this AD requires the embodiment of these 
EASA AD No.: 2015-0142

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modifications at the pylon/wing junction in LH and RH wings.

Effective Date: 31 July 2015

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 18 months after the effective date of this AD, for each inboard pylon, 

modify the cable loom support bracket of the G-route 7701VB LH side and 

7702VB RH side at the pylon/wing junction in accordance with the 

instructions of Airbus SB A330-92-3132 Revision 1, or Airbus SB 

A340-92-4100 Revision 1, or Airbus SB A340-92-5066, as applicable to 

aeroplane type and model.

(2) Modification of an aeroplane, accomplished before the effective date of this 

AD in accordance with the instructions of Airbus SB A330-92-3132 at 

original issue, or Airbus SB A340-92-4100 at original issue, as applicable 

to aeroplane type and model, is acceptable to comply with paragraph (1) of 

this AD for that aeroplane.

Ref. Publications: Airbus SB A330-92-3132 original issue dated 19 June 2014 or Revision 1

dated 21 May 2015.

Airbus SB A340-92-4100 original issue dated 19 June 2014 or Revision 1 

dated 21 May 2015.

Airbus SB A340-92-5066 original issue dated 25 June 2014.

The use 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 17 October 2014 as PAD 14-150 for consultation 

until 14 November 2014 and republished as PAD 14-150R1 on 30 June 

2015 for consultation until 14 July 2015.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, Certification 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 – Airworthiness Office – EIAL;

E-mail: airworthiness.A330-A340@airbus.com.