EASA AD No

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- 0 168

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 12 - 0 168

Date: 31 August 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 Eu ropean 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 a n 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 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) exemption]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A330 and A340 aeroplanes

TCDS Number s : EASA

. A .004, EASA.A.015
Foreign AD: Not applicable Supersedure: This AD supersedes DGAC F rance AD s 98

- 103

- 082 dated 25 February 1998 , 98

- 099

- 066 dated 25 February 1998 and F

- 2005

- 030 dated 16 February 2005 , and EASA AD s 2006

- 0187 dated 05 July 2006 , 20 06

- 0191 dated 10 July 2006 , 2006

- 0205 date d 11 July 2006 , 2007

- 0023 dated 25 January 2007 , 2007

- 0278 dated 05 November 2007 and corrected on 08 November 2007 , 2009

- 0150 dated 09 July 2009 , 2010

- 0089 dated 10 May 2010 , 201 0

- 0232 dated 12 November 2010 and 2011

- 0196 dated 07 October 2011 and corrected on 23 March 2012

.



### ATA 05 Time Limits and Maintenance Checks

– 

### A irworthiness L imitations Section Part 5
– Fuel Airworthiness Limitations


### – Amendment

Manufacturer(s): A irbus (formerly A irbus Industrie )
Applicability: Airbus A330

- 201, A330

- 202, A330

- 203, A330

- 223, A330

- 243, A330

- 223F, A330

- 243F, A330

- 301, A330

- 30 2, A330

- 303, A330

- 321, A330

- 322, A330

- 323, A330

- 341, A330

- 342 and A330

- 343 aeroplanes, all manufacturer serial numbers. Airbus A340

- 211, A340

- 212, A340

- 213, A340

- 311, A340

- 312, A340

- 313, A340

- 541, A340

- 542, A340

- 642 and A340

- 643 aeroplanes, all manufactur er serial numbers.

Reason: Prompted by an accident of a Boeing 747

- 131 (flight TWA800), the FAA published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/25/12. The design review con ducted Airbus to develop Fuel Airworthiness Limitations (FAL) for Airbus on A330 and A340 aeroplanes in response to these regulations

. The FAL were specified in Airbus A330 FAL Document reference 95A.193 2 /05 for A330 aeroplanes and A340 FAL Document refere nceEASA AD No

. : 20 12

- 0 168

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 95A.193 3 /05 for A340 aeroplanes. Those documents have been approved by the European Aviation Safety Agency (EASA) and are now referenced in Airbus A 330 and A340 Airworthiness Limitations Section ( ALS ) Part 5 revision 00 (both approved by EASA on 16 Nov ember 2011) , to comply with EASA policy statement (EASA D 2005/CPRO) which requires Fuel Tank Safety items to be integrated in to ALS Part 5. Failure to comply with items as identified in Airbus A 330 and A340 ALS Part 5 could result in a fuel tank explosion and consequent loss of the aeroplane. To address this condition, EASA issued: EASA AD 2007

- 0023 to require compliance with FAL specified in the Airbus A330 FAL Document reference 95A.1932/05 at Issue 02 (comprising maintenance/inspection tasks and Critica l Design Configuration Control Limitations (CDCCL)) for A330 aeroplanes , and EASA AD 2006

- 0205 to require compliance with FAL specified in Airbus A340 FAL Document reference 95A.1933/05 at Issue 01 (comprising maintenance/inspection tasks and Critical Desi gn Configuration Control Limitations (CDCCL)) for Airbus A340 aeroplanes

. All other EASA ADs specified in the Supersedure section of this AD required accomplishment of aeroplane modification s related to Fuel Tank Safety items , the requirements and complian ce times of which are now integrated in to ALS Part 5. For the reasons described above, this AD retains the requirements of all A D s specified in the Supers e dure section of this AD , which are superseded, and require s the implementation of the new or more res trictive maintenance requirements and/or airworthiness limitations as specified in the revision 00 of the Airbus A330 ALS Part 5 and of the Airbus A340 ALS Part 5.

Effective Date: 14 September 2012
Required A ction(s) and Compliance Time(s): Required as i ndicated, unless previously accomplished: (1) W ithin the compliance times defined in the Record of Revisions (ROR) pages of the Airbus A330 ALS Part 5 or A340 ALS Part 5 (hereafter referred to as ALS Part 5), both at Revision 00, as applicable to aeroplane type , comply with all applicable instructions and airworthiness limitations included by reference in the ROR of ALS Part 5 Revision 00, as applicable to aeroplane type

. ( 2 ) Compliance with the requirements of paragraph s (1) of this AD can be demonstrated by: ( 2 .1) Revising as follows , the approved Aircraft Maintenance Programme (AMP) on the basis of which the o perator or the o wner ensures the continuing airworthiness of each operated aeroplane: Incorporate all maintenance and modification requirements , an d associated airworthiness limitations specified in the ALS Part 5 R evision 00 , as applicable to aeroplane type.
a nd ( 2 .2) Complying with the approved AMP described in paragraph ( 2 .1 ) of this AD.

Ref. Publications: AIRBUS A330 ALS Part 5 R evision 00 , and AI RBUS A340 ALS Part 5 R evision 00 , both approved by EASA on 16 November 2011. The use of later approved variations or revisions of these documents is acceptable for compliance with the requirements of this AD

.EASA AD No

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- 0 168

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Remarks: 1. If requested and appropriately sub stantiated, EASA can approve Alternative Methods of Compliance for this AD

. 2. This AD was posted on 3 1 July 2012 as PAD 12

- 09 6 for consultation until 28 August 2012. No comments were received during the consultation period

. 3. Enquiries 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

– Ai rworthiness Office , E

- mail: airworthiness.A330

- A340@airbus.com

.