EASA AD No : 2011-0005

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0005

Date: 17 January 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 participat e in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EC 1702/2003, Part 21A.3 B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft s hall be ensured by accomplishing any applicable ADs. Consequently, no person may opera te 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) exemptio n]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A310 aeroplanes

TCDS Number: France N° 145

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2007-02 30 dated 15 August 2007.



### ATA 28 Fuel – Electric / Electronic Common Installation Fuel System Route 2S – Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A310 aeroplanes, all certified models, all serial numbers.

Reason: Within the scope of the Fuel Syst em Safety Program (FSSP), analyses of the wire routing showed that the route 2S of the fuel electr ical circuit in the Right Hand (RH) wing must be modified in order to ensure better segregation between fuel quantity indication wires a nd the 115 Volts Alternating Current (VAC) wires of route 2S. This condition, if not corrected, could resu lt in short circuits leading to arcing, and possible fuel tank explosion. To address this unsafe condition, DGAC France issued AD 2002-578(B) to require improvements of the design as specified in Airbus Service Bulletin (SB) A310-28-2148 original issue or Revision 01. EASA AD 2007-0230, which superseded DGAC France AD 2002-578(B), required those same actions, plus additional work as defined in Airbus SB A310-28-2148 Revision 02.
Since EASA AD 2007-0230 was issued, an operator reported the possibility of chafing with the new routing of the wi re bundle 2S in the RH wing pylon area to the generator wire bundle of engine 2. The modification of this zone was introduced by A310-28-2148 Revision 02 as additional work. Investigation showed that, to avoid the risk of chafi ng, the affected wiring harnesses must be installed at a higher position to provide sufficient clearance with the newly routed wire bundle 2S conduit. Airbus published Revision 03 of SB A310-28-2148 to describe these changes,EASA AD No : 2011-0005

EASA Form 110 Page 2/2 but a new interference has been foun d and requires updating SB A310-28- 2148 to Revision 04. For the reasons described above, this new AD retains the requirements of EASA AD 2007-0230, which is superseded, and requires the additional work as specified in Revision 04 of Airbus SB A310-28-2148.

Effective Date: 31 January 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless previously accomplished: (1) For aeroplanes not yet modified in accordance with the instructions of Airbus SB A310-28-2148 Original issue, Revision 01, or Revision 02: Within 4 000 flight hours (FH) after 07 December 2002 [the effective date of DGAC France AD 2002-578], isolate the route 2S of the fuel system in accordance with the instructions of Airbus SB A310-28-2148 Revision 04. (2) For aeroplanes already modified in accordance with the instructions of Airbus SB A310-28-2148 Revision 02 and not having SB A310-36-2015 or production modification 07633 embodied:
Within 6 000 FH or 30 months a fter the effective date of this AD, whichever occurs first, accomplish Airbus SB A310-28-2148 Revision 04. (3) For aeroplanes already modified in accordance with the instructions of Airbus SB A310-28-2148 Revision 02 and having SB A310-36-2015 or production modification 07633 embodied: Within 1 000 FH after the effective date of this AD, accomplish the additional work identified “additional work 2” as defined in Airbus SB A310-28-2148 Revision 04. (4) For aeroplanes having SB A310-36-2015 or production modification 07633 embodied and already modified in accordance with the instructions of Airbus SB A310-28-2148 Revision 03, no further action is required.

Ref. Publications: Airbus SB A310-28-2148 Revision 04. The use of later approved revisions of this document is acceptable for compliance with 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 06 January 2010 as PAD 10-004 for consultation until 03 February 2010. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA E-mail: ADs@easa.europa.eu

. 4. For any question concerning the tec hnical content of the requirements in this AD, please contact: AIRBUS SAS – EAW (Airworthiness Office, Telephone: + 33 5 61 93 36 96, Fax: + 33 5 61 93 44 51).