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 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 aeroplanes

TCDS Number: France N° 145 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA AD 2007-0230 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 System Safety Program (FSSP), analyses of the 

wire routing showed that the route 2S of the fuel electrical circuit in the Right 

Hand (RH) wing must be modified in order to ensure better segregation 

between fuel quantity indication wires and the 115 Volts Alternating Current 

(VAC) wires of route 2S. 

This condition, if not corrected, could result 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superseded DGAC France AD 2002-578(B), required those same actions, 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 wire 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 chafing, 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 found 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 after 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 & 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 93 36 96, Fax: + 33 5 61 93 44 51).