EASA AD No.: 20 14

- 0193

CAP.0011 0

- 00 4 © 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 14

- 0193

Date: 1 5 October 2014

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 EU 748/2012, Part 21.A.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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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 a eroplanes

TCDS Number: EASA.A.172

F oreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2007

- 009 6 R1 dated 02 May 2007

.



### ATA 05 Time Limits and Maintenance Checks

– Airworthiness Limitations Section Part 5

– Fuel Airworthiness Limitations

– Amendment

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A310 aeroplanes, all certifie d models

, all manufacturer serial numbers

.

Reason: Prompted by an accident of a Boeing 747

- 131 (Flight TWA800)

, the Federal Aviation Administration (FAA) published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviati on Authorities (JAA) published I nterim Policy INT/POL/25/12. In response to these regulations, Airbus conducted a design review to develop Fuel Airworthiness Limitations (FAL) for Airbus on A310 aeroplanes.

The FAL were specified in Airbus A310 FAL d ocument ref. 95A.1930/05 at issue 02 a nd in the A310 Airworthiness Limitations Section ( ALS ) v ariation to FAL document issue 02

, ref. 0BVLG110006/C0S issue 01

, for A310 aeroplanes.

EASA issued AD 2006

- 0202 to require compliance with the FAL documents ( comprising maintenance/inspection tasks and Critical Design Configurati on Control Limitations (CDCCL) )

. EASA AD 2006

- 0202 was superseded by EASA AD 2007

- 009 6 (later revised)

, which retained the original requirements and corrected and updated the

co mpliance paragraphs concerning t ask ref

. 28

- 18

- 0 0

- 03

- 1 and CDCCL’s

. Since EASA AD 2007

- 0096R1 was published

, Airbus issued A310 ALS Part 5

, prompted by EASA policy statement (EASA D2005/CPRO) which requ ests design approval holders to integrate Fuel Tank Safety items into an ALS document

. The A310 ALS Part 5 is approved by EASA.EASA AD No.: 20 14

- 0193

CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Failure to comply with the items as identified in Airbus A310 ALS Part 5 could result in a fuel tank explosion and consequent loss of the aeroplane.
For the reasons described above, this AD retains th e requirements of EASA AD 2007

- 009 6 R1, whi ch is superseded, and requires implementation of the new and more restrictive maintenance instructions and/or airworthiness limitations as specified in Airbus A3 10 ALS Part 5.

Effective Date: 2 9 October 2014

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) From the effective date of this AD, accomplish the following actions, as specified in

- A310 ALS Part 5 R evision 00,
or, until 27 May 2015 :

- A310 FAL d ocument ref. 95A.1930/05

, issue 02

, and A310 ALS v ariation to FAL document issue 02

, ref. 0BVLG110006/C0S

, issue 01

, depending on aeroplane configuration: ( 1 .1) Replace each component before or upon reaching the applicable life limit. ( 1 .2) Within the thresholds and intervals, accomplish all applicable maintenance tasks, including any applicable CDCCL items

. ( 1 .3) Within the thresholds (embodiment limit), accomplish all applicable aeroplane modifications.

(2) In case discrepancies are dete cted during accomplishment of any task as required by paragraph (1) of this AD, within the compliance time specified in the Airbus maintenance documentation, accomplish the applicable corrective action(s) in accordance with the instructions specifie d (or incorporated by reference) in the relevant Ai rbus maintenance documentation.
If no compliance time is identified in the Airbus documentation, accomplish the applicable corrective action ( s ) before next flight. If a detected discrepancy is not ident ified in the Airbus documentation, before next flight, contact Airbus for approved instructions and accomplish those instructions accordingly.

(3) Compliance with the requirements of paragraphs (1) and (2) of this AD can be demonstrated by: ( 3 .1) Revising

, as follows, the approved Aircraft Maintenance Programme (AMP) on the basis of which the operator or the owner ensures the continuing airworthiness of each operated aeroplane:
Incorporate all mandatory instructions for continued airworthiness

an d airworthiness limitations as specified in the A3 1 0 ALS Part 5 Revision 00, or (until 27 May 201 5 ) in the A310 FAL d ocument ref. 95A.1930/05

, issue 02

, and the A310 ALS v ariation to FAL document issue 02

, ref. 0BVLG110006/C0S

, issue 01

, and ( 3 .2) Complying with the approved AMP described in paragraph ( 3 .1) of this AD.EASA AD No.: 20 14

- 0193

CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Ref. Public ations: A310 ALS Part 5 Revision 00 dated 27 May 2014

. A310 FAL d ocument ref. 95A.1930/05

, issue 02 dated 11 May 2007

. A310 ALS v ariation to FAL document issue 02

, ref. 0BVLG110006/C0S

, issue 01 dated 05 December 2011

. The use of later approved revisions of th e s e 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. This AD was posted on 30 July 2014 as PAD 14

- 125 for consultation until 27 August 2014

. No comments were received during the consultation period.

3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements i n this AD, please contact: AIRBUS

– EIAW (Airworthiness Office) E

- mail: continued.airworthiness

- wb.external@airbus.com

.