EASA AD No : 2010-0178R1 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0178R1 

Date: 20 May 2011 

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 EC 1702/2003, Part 21A.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 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]. 

Type Approval Holder’s Name : 

AIRBUS 

Type/Model designation(s) : 

A310, A300-600 and A300-600ST aeroplanes 

TCDS Number : France N° 145 and EASA.A.014 

Foreign AD : Not applicable 

Revision : This AD revises EASA AD 2010-0178, dated 23 August 2010. 

ATA 24, 92 Electrical Power – Wiring Installation at Pylon/Wing Interface - 

Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: A310, A300-600 aeroplanes, all serial numbers and A300F4-608ST 

aeroplanes, all serial numbers. 

Reason: An operator reported several cases of wire damages at the pylon/wing 

interface. Analysis revealed that wire damages are due to installation quality 

issue resulting from lack of information in installation drawings and job cards. 

Moreover detailed analysis has highlighted that the Low Pressure Valve (LPV) 

wires were not segregated by design. 

Due to design similarities, A310, A300-600 and A300-600ST aeroplanes can 

be affected, depending on the wire installation in the concerned area. 

If left uncorrected, the wire chafing could impact fire protection and detection 

system. It may also induce dormant failure on LPV preventing its closure 

leading to a permanent and uncontrolled fire (in case of fire ignited upstream 

the High Pressure Valve (HPV)). 

For the reasons explained above, this AD required the modification of the 

electrical installation in the pylon/wing interface to avoid wire damages. 

Shortly after this AD was issued, it was discovered that Airbus Service Bulletin 

(SB) A310-24-2106, associated to Airbus modification 13541, contained wrong 

Low Pressure Valve installation drawings. This makes it impossible for the 

operators to accomplish the SB instructions. Consequently, Airbus have 
EASA AD No : 2010-0178R1 

EASA Form 110 Page 2/2 

revised the SB to correct the error. 

Revision 1 of this AD is issued to require modification 13541 to be 

incorporated in accordance with the instructions of Airbus SB A310-24-2106 at 

Revision 1. 

Effective Date: Revision 1: 03 June 2011 

Original issue: 06 September 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Within 30 months or 4 000 Flight Hours (FH) after 06 September 2010 [the 

effective date of the original issue of this AD], whichever occurs first, modify 

the electrical installation in the pylon/wing interface on left-hand (LH) and righthand (RH) side by : 

- replacing cable tie by lacing tape, 

- improving the electrical installation at the level of the electrical ramp, 

- improving the segregation of both routes of the LPV channels 1 and 2 

between LPV connector and ramp, 

in accordance with the instructions of Airbus Service Bulletin (SB) A310-24-

2106 Revision 1, or Airbus SB A300-24-6106 original issue or Airbus SB 

A300-24-9015 original issue, as applicable to aeroplane models. 

Ref. Publications: Airbus Service Bulletin A310-24-2106 Revision 1. 

Airbus Service Bulletin A300-24-6106 original issue. 

Airbus Service Bulletin A300-24-9015 original issue. 

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. The original issue of this AD was posted on 20 July 2010 as PAD 10-076 

for consultation until 17 August 2010. No comments were received during 

the consultation period. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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 SAS – EAW (Airworthiness Office, 

Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).