EASA AD No : 2011-0006

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0006

Date: 17 January 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 parti cipate 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 opera te 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) exemptio n]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :

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

TCDS Number : France No.145 and EASA.A.014

Foreign AD : Not applicable

Supersedure : None



### ATA 29 Hydraulic Power – Hydraulic Accumulator – Inspection / Replacement / Placards Installation

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A300, A310 and A300-600 aerop lanes, all certified models, all serial numbers, and A300F4-608ST aeroplanes, all serial numbers.

Reason: Since 1984, the design of the hydrau lic accumulator installed on all the affected Airbus types has changed. The Part Number (P/N) remained the same, but the manufacturer did not record the serial number of the part that was the first to be manufactured to the changed design specification. The new design hydraulic accumulator is manufactured with 2 pieces unit welded, instead of 4 pieces unit with 3 welds (old design) as pictured in Appendix 1 of this AD. The welding pr ocess of the new design hydraulic accumulator provides a higher strength shell material and more reliability. A recent analysis conducted by the manufacturer showed a particular risk for explosive failure of the old design hydraulic accumulator. This condition, if not detected and corrected, might, for some aeroplane installations, lead to damage to all three hydraulic circuits, possibly resulting in loss of control of the aeroplane or could, for certain other aeroplane installations, lead to an undetected fire in the wheel bay. For the reasons explained above, this AD requires a one time detailed visual inspection to identify the old designed accumulators installed on certain hydraulic systems, the replac ement of those accumulators by new designed accumulators and, irrespective of findings, the installation of warning placards to avoid installation of old designed accumulators on the affected hydraulic systems.EASA AD No : 2011-0006

EASA Form 110 Page 2/3 Effective Date: 31 January 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Within 30 months or 6 000 flight hours (FH), whichever occurs first after the effective date of this AD, accomplish the following actions: (1) Perform a detailed visual inspection of each type 5 hydraulic accumulator, P/N 3059103-1, P/ N 3059103-2, P/N 3059103-8 and P/N 3059103-9, to detect if an old design accumulator is installed on the affected hydraulic circuits indicated in Table 1 of this AD, as applicable to aeroplane model, in accordance with the instructions of Airbus Service Bulletin (SB) A300-29-0126 Revision 01, SB A310-29-2099, SB A300-29-6063, or SB A300-29-9012, as applicable to aeroplane model.
Table 1
Affected Aeroplanes Affected Hydraulic Circuit(s)

A300 PRE mod 02447 Blue and Green

A300 POST mod 2447 Blue

A300-600 and A300F4-608ST Blue

A310 Green
(2) If, during the visual inspection as required by par agraph (1) of this AD, an old design hydraulic accumulator is found installed on any of the affected hydraulic circuits as indi cated in Table 1 of this AD, as applicable to aeroplane model, replace each affected old design accumulator with a new design accumulator in accordance with the instructions of Airbus SB A300-29-0126 Revision 01, SB A310-29- 2099, SB A300-29-6063, or SB A300-29-9012, as applicable to aeroplane model. (3) Irrespective of findings during the visual inspection as required by paragraph (1) of this AD, install plac ards at the designated locations of the affected hydraulic circuits indicated in Table 1 of this AD, as applicable to aeroplane model, in accordance with the instructions of Airbus SB A300-29-0127, SB A310-29-2100, SB A300-29-6064, or SB A300-29-9013, as applicable to aeroplane model.

Ref. Publications: Airbus SB A300-29-0126 Revision 01 and SB A300-29-0127 original issue. Airbus SB A310-29-2099 and SB A310-29-2100, both original issue. Airbus SB A300-29-6063 and SB A300-29-6064, both original issue. Airbus SB A300-29-9012 and SB A300-29-9013, both original issue. 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 15 December 2010 as PAD 10-122 for consultation until 12 January 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, Certification Directorate, EASA E-mail: ADs@easa.europa.eu

. 4. For any question concerning the te chnical content of the requirements in this AD, please contact: AIRB US SAS – EAW (Airworthiness Office, Telephone: + 33 5 61 93 36 96, Fax: + 33 5 61 93 44 51).EASA AD No : 2011-0006

EASA Form 110 Page 3/3 

### Appendix 1