EASA AD No : 2011-0124

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0124

Date: 30 June 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 t he 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 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) : A300, A310, A300-600 and A300-600ST aeroplanes

TCDS Number : Fran ce N° 145 and EASA.A.014

Foreign AD : Not applicable

Supersedure : None



### ATA 28 Fuel Pump System - Fuel Pump Canister Hood Halves - Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A300, A310, A300-600 aeroplanes, all cert ified models, all serial numbers, and A300F4-608ST aeroplanes, all serial numbers.
Reason: This AD results from findings of cracked fuel pump canister hoods located in fuel tanks. From the analyses, laboratory testing and examinations made so far, it is presently thought that vibration-induce d fatigue can be identified as the root cause for the cracks found on in-service aeroplanes. However, current data does not yet permit to exclude some ot her potential contributing factors. This condition, if not detected and correc ted, could lead to detached canister hood fragments/debris to be ingested into the fuel feed system. Also, the metallic debris inside the fuel tank could result in a potential source of ignition and consequent fire or explosion. For the reasons described above, this AD requires repetitive inspections of all fuel pump canister hood halves and thei r replacement if any damage is found. This AD also requires the inspection results to be reported.
This AD is considered to be an interim action. The reports t hat are required by this AD will enable the manufacturer to obtain better insight into the nature, cause, and extent of the fuel pump c anister hood cracking, and eventually to develop final action to address the unsafe condition. Once final action has been identified, further AD actions could be considered.

Effective Date: 14 July 2011EASA AD No : 2011-0124

EASA Form 110 Page 2/3 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 30 months after the effectiv e date of this AD, do a detailed visual inspection of fuel pump canister hood halves installed on all fuel pump canisters Part Numbers (P/N) 2052C11 and P/N 2052C12 and P/N C93R51-601, in accordance with the Accomplishment Instructions of Airbus Service Bulletin (SB) A300-28-0089 Revision 01, or SB A310-28- 2173 Revision 01, or SB A300-28-6106 Revision 01, or SB A300-28-9020 Revision 01, as applicable to aeroplane model. If any crack is found, before next fligh t, do all necessary corrective actions in accordance with the Accomplishme nt Instructions of Airbus SB A300- 28-0089 Revision 01, or SB A310-28-2173 Revision 01, or SB A300-28- 6106 Revision 01, or SB A300-28-9020 Revision 01, as applicable to aeroplane model. (2) After accomplishment of paragraph (1) of this AD, repeat thereafter at intervals not to exceed 30 months, the detailed visual inspection of fuel pump canister hood halves installed on all fuel pump canisters Part Numbers (P/N) 2052C11 and P/N 2052C12 and P/N C93R51-601, in accordance with the Accomplishment Instructions of Airbus Service Bulletin (SB) A300-28-0089 Revision 01, or SB A310-28-2173 Revision 01, or SB A300-28-6106 Revision 01, or SB A300-28-9020 Revision 01, as applicable to aeroplane model. If any crack is found, before next fligh t, do all necessary corrective actions in accordance with the Accomplishme nt Instructions of Airbus SB A300- 28-0089 Revision 01, or SB A310-28-2173 Revision 01, or SB A300-28- 6106 Revision 01, or SB A300-28-9020 Revision 01, as applicable to aeroplane model. (3) Inspections and corrective actions done before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus SB A300-28-0089, or SB A310-28-2173, or SB A300-28-6106, or SB A300- 28-9020, at original issue, are acceptable for compliance with the requirements of paragraph (1) of this AD. (4) After any inspection done in accordance with paragraphs (1), (2) and (3) of this AD, report all inspection result s (negative or positive) to Airbus at the applicable time specified in paragraph (4.1) and (4.2) of this AD. For that purpose, you may use the inspection finding reporting sheet provided in SB A300-28-0089, or SB A310-28-2173, or SB A300-28-6106, or SB A300-28-9020, as applicable to aeroplane model. (4.1) For inspections done after the effective date of this AD, submit the report within 30 days after the inspection. (4.2) For inspections done before the effective date of this AD, submit the report within 30 days after the effective date of this AD.

Ref. Publications: Airbus Service Bulletin A300-28-0089 Revision 01, Airbus Service Bulletin A310-28-2173 Revision 01, Airbus Service Bulletin A300-28-6106 Revision 01 and Airbus Service Bulletin A300-28-9020 Revision 01. The use of later approved revisions of these 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 May 2011 as PAD 11-057 for consultation until 27 June 2011. 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, CertificationEASA AD No : 2011-0124

EASA Form 110 Page 3/3 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 18 41 39, Fax: + 33 5 61 93 44 51).