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 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 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 aeroplanes, all certified models, all serial 

numbers, and A300F4-608ST aeroplanes, all serial numbers. 

Reason: Since 1984, the design of the hydraulic 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 process 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 replacement 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 paragraph (1) of this AD, 

an old design hydraulic accumulator is found installed on any of the 

affected hydraulic circuits as indicated 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 placards 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 & Research Section, Certification 

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 93 36 96, Fax: + 33 5 61 93 44 51). 
EASA AD No : 2011-0006 

EASA Form 110 Page 3/3 

Appendix 1