EASA AD No.: 2011-0071 

EASA Form 110 Page 1/2

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0071 

Date: 18 April 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) : 

A310 aeroplanes 

TCDS Number : France N° 145 

Foreign AD : Not applicable 

Supersedure : None 

ATA 29 Hydraulic Power – Electrical Motor Pump Feeder Cables and 

Pressure Hoses – Inspection / Repair / Placard Installation 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: A310 aeroplanes, all certified models, all serial numbers. 

Reason: An operator reported an electrical arc and a large hydraulic haze in the left 

hand Main Landing Gear (LH MLG) wheel bay that occurred during ground 

operation. The analysis revealed that this occurrence is likely the result of 

chafing between hydraulic high pressure hose and electrical wiring of the 

Green Electrical Motor Pump (EMP). 

This condition, if not detected and corrected, and in combination with a 

system failure leading to the use of the Green EMPs in flight, could lead to an 

uncontrolled and undetected fire in the MLG bay. 

For the reasons explained above, this AD temporarily prohibits the in-flight 

use of green EMPs, by mandating an update of the Aeroplane Flight Manual 

(AFM) limitations section and installation of a placard in the cockpit overhead 

panel. This AD requires also a one-time visual inspection of hydraulic 

pressure hoses and electrical wiring of Green EMPs and corrective action(s), 

depending on findings. 

Effective Date: 02 May 2011 
EASA AD No.: 2011-0071 

EASA Form 110 Page 2/2

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) From the effective date of this AD, the in-flight use of green EMPs is 

prohibited. For that purpose, before next flight, do the following actions: 

(1.1) Install in the cockpit on the HYDRAULIC POWER overhead panel 

427VU, a locally manufactured self-adhesive placard prohibiting the 

in-flight use of the Green EMPs in accordance with instructions of 

the Airbus All Operator Telex (AOT) A310-29A2101 Revision 01, as 

applicable for aeroplanes equipped with EATON (formerly 

VICKERS) hydraulic EMPs, or Airbus AOT A310-29A2102, as 

applicable for aeroplanes equipped with PARKER (formerly ABEX) 

hydraulic EMPs. 

(1.2) Update the Limitations section of the applicable AFM to prohibit the 

in-flight use of green EMPs. 

 

Insertion of a copy of this AD into the AFM Limitations section is 

acceptable to comply with the requirement of paragraph (1.2) of this 

AD. 

(2) Within 500 flight hours or 4 months after the effective date of this AD, 

whichever occurs first, perform a one-time visual inspection of the 

hydraulic pressure hoses, of the electrical conduits, feeder cables and of 

the associated clamping devices at frame 54 as well as the electrical 

conduits, feeder cables underneath the clamps (this inspection requires 

removal of the concerned clamps) in accordance with the instructions of 

Airbus AOT A310-29A2101 Revision 01, or Airbus AOT A310-29A2102, 

as applicable to the installed EMP. 

(3) If any damage is found during the visual inspection as required by 

paragraph (2) of this AD, before further flight, replace or repair the 

affected parts (hydraulic pressure hoses, electrical conduits, feeder 

cables, clamps and spacer, if installed), in accordance with the 

instructions of Airbus AOT A310-29A2101 Revision 01, or Airbus AOT 

A310-29A2102, as applicable to the installed EMP. 

(4) After compliance with the requirements of paragraph (2) and (3), as 

applicable, the placard as required by paragraph (1.1) and the update of 

the Limitations section as required by paragraph (1.2) of this AD must be 

removed from the aeroplane and from the AFM, respectively. 

Ref. Publications: All Operator Telex A310-29A2101 Revision 01, dated 12 April 2011. 

All Operator Telex A310-29A2102 Original issue, dated 12 April 2011. 

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. The required actions and the risk allowance have granted the issuance of a 

Final AD with Request for Comments, postponing the public consultation 

process after publication. 

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 18 41 

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