EASA AD No.: 20 12 - 0188

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## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 12 - 0188 Date: 19 September 2012 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 i ssued 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]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A310 aeroplanes TCDS Number: France TCDS N o 145 F oreign AD: Not applicable Su persedure: This AD supersedes EASA AD 2011 - 0005 dated 17 January 2011 

### 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 ensure s insufficient segregation betw een fuel quantity indication wires and the 115 Volts Alternating Current (VAC) wires of route 2S which could, under certain conditions, lead to a short circuit an d subsequent arcing, creating a potential ignition source in the fuel tank vapour space

. This condition, if not detected, could result in a fuel tank explosion and consequent loss of the aeroplane

. To address this potential unsafe condition, D GAC France issued AD 2002 - 578 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 super seded DGAC France AD 2002 - 578 , required those same actions, plus additional work 1 , as defined in Airbus SB A310 - 28 - 2148 Revision 02. Since EASA AD 2007 - 0230 was issued, an ope rator reported the possibility of chafing between the new routing of the wire bundle 2S in the RH wing pylon area and the wire bundle of No.2 engine generator . The modification of this zone was introduced by Airbus SB A310 - 28 - 2148 Revision 02 as additional work 1. Investigation results 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 o f SB A310 - 28 - 2148 to implement these changesEASA AD No.: 20 12 - 0188

CAP.0011 0 - 001 © European Aviation Safety Agency. All rights reserved. 2 / 3 P roprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. as additional work 2

. Subsequently, a new potential interference due to insufficient clearance was found , which prompted Airbus to issue SB A310 - 28 - 2148 Revision 04. Prompted by these findings and actions, EASA issue d AD 2011 - 0005 , retain ing the requirements of EASA AD 2007 - 0230 , which was superseded, and required the additional work 2 as specified in Revision s 03 and 04 of Airbus SB A310 - 28 - 2148. Since EASA AD 2011 - 0005 was issued, several operators of aeroplanes not having been modified in - service through Airbus SB A310 - 36 - 2015 , or without having Airbus modification 07633 applied in production , reported to have embodied Airbus SB A310 - 28 - 2148 at Revision 02 or Revision 03 on the aeroplane

. However, t he adequate instr uctions to avoid the new interferences were only introduced in Airbus SB A310 - 28 - 2148 Revision 04. For the reasons described above, this new AD retains the requirements of EASA AD 2011 - 0005 , which is superseded , and requires , for certain aeroplanes, the ad ditional work 3 as defined in Airbus SB A310 - 28 - 2148 Revision 06. As SB A310 - 28 - 2148 R evision 0 7 was issued to clarify the additional work 1, 2 and 3 for aeroplanes that have previously embodied th at SB at original issue , Revision 01 or Revision 02, this A D also clarifies the required additional work. Effective Date: 03 October 2012 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) For aeroplanes not yet modified in accordance with the accomplishment ins tructions of Airbus SB A310 - 28 - 2148 (at any revision level) w ithin 4 000 flight hours (FH) after 07 December 2002 [the effective date of DGAC France AD 2002 - 578], modify the aeroplane by isolat ing the route 2S of the fuel system in accordance with the inst ructions of Airb us SB A310 - 28 - 2148 Revision 07. (2) For aeroplanes already modified in accordance with the instructions of Airbus SB A310 - 28 - 2148 at o riginal issue or Revision 01 , and without having Airbus SB A310 - 36 - 2015 applied in - service, or without Air bus modification 07633 applied in production , w ithin 6 000 FH or 30 months after 31 January 2011 [the effective date of EASA AD 2011 - 0005] whichever occurs first, accomplish the additional work identified as “additional work 1, 2 and 3 ” in accordance with the instructions of Airbus SB A310 - 28 - 2148 Revision 07. (3) For aeroplanes already modified in accordance with the instructions of Airbus SB A310 - 28 - 2148 at Revision 0 2 and having had Airbus SB A310 - 36 - 2015 applied in - service, or Airbus modification 07633 applied in production, w ithin 1 000 FH after 31 January 2011 [the effective date of EASA AD 2011 - 0005], accomplish the additional work identified as “additional work 2” in accordance with the instructions of Airbus SB A310 - 28 - 2148 Revision 07. (4) For aer oplanes already modified in accordance with the instructions of Airbus SB A310 - 28 - 2148 at Revision 02 and without having Airbus SB A310 - 36 - 2015 applied in - service, or Airbus modification 07633 applied in production, w ithin 1 000 FH or 12 months , whichever occurs first after the effective date of this AD, accomplish the additional work identified as “additional work 2 and 3” in accordance with the instructions of Airbus SB A310 - 28 - 2148 Revision 07. (5) For aeroplanes already modified in accordance with the i nstructions of Airbus SB A310 - 28 - 2148 at Revision 03 and without having Airbus SB A310 - 36 - 2015 applied in - service or Airbus modification 07633 applied in production, w ithin 1 000 FH or 12 months , whichever occurs first after the effective date of this AD, accomplish the additional work identified asEASA AD No.: 20 12 - 0188

CAP.0011 0 - 001 © European Aviation Safety Agency. All rights reserved. 3 / 3 P roprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. “additional work 3” in accordance with the instructions of Airbus SB A310 - 28 - 2148 Revision 07. (6) For aeroplanes modified in - service through Airbus SB A310 - 36 - 2015 or modified in production through Airbus modif ication 07633 , and already modified in accordance with the instructions of Airbus SB A310 - 28 - 2148 Revision 03 or a later revision , no additional work is required. (7) For aeroplanes without having Airbus SB A310 - 36 - 2015 applied in - service, or Airbus modif ication 07633 applied in production, and already modified in accordance with the instructions of Airbus SB A310 - 28 - 2148 at original issue or Revision 01 and further modified by accomplishment of the “additional work 3” in accordance with the instructions o f Airbus SB A310 - 28 - 2148 at Revision 06, w ithin 6 000 FH or 30 months , whichever occurs first after 31 January 2011 [the effective date of EASA AD 2011 - 0005], accomplish the additional work identified as “additional work 1 and 2 ” in accordance with the ins tructions of Airbus SB A3 1 0 - 28 - 2148 R evision 0 7. Ref. Public ations: Airbus SB A3 1 0 - 28 - 2148 revision 07 dated 13 February 2012. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD. Remarks: 1. I f requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 26 July 2012 as PAD 12 - 090 for consultation until 23 August 2012 . No comments were received during the consultation period

. 3. E nquiries 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 I AW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).