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 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) : 

A300, A310, A300-600 and A300-600ST aeroplanes 

TCDS Number : France 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 certified 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-induced 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 other potential contributing factors. 

This condition, if not detected and corrected, 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 their 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 that are required by 

this AD will enable the manufacturer to obtain better insight into the nature, 

cause, and extent of the fuel pump canister 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 2011 
EASA 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 effective 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 flight, do all necessary corrective actions 

in accordance with the Accomplishment 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 flight, do all necessary corrective actions 

in accordance with the Accomplishment 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 results (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 & Research Section, Certification 
EASA AD No : 2011-0124 

EASA Form 110 Page 3/3 

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 18 41 39, Fax: + 33 5 61 93 44 51).