E ASA AD No.: 2013

- 0 165

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 13

- 0165

Date: 2 5 July 2013

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 Euro pean third countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with E U 748/2012 , Part 21

. A.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, Pa rt M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].



### Design Approval Holder’s Name:

AIRBUS Type/Model designation(s): A310 aeroplanes

TCDS Number: France n° 145

F oreign AD: Not applicable

Supersedure : None



### ATA 29 Hydraulic P ower
– Electrical Motor Pump E lectrical R outing and H ydraulic P ipes

– Modification

Manufacturer(s): Airbus (Formerly Airbus Industries)

Applicability: Airbus A310 aeroplanes

, all certified model s, all m anufacturer s eri a l n um bers on which Airbus Modification No 04797 has been embodied in production or those on which Airbus Service B ulletin (SB) A310

- 29

- 2091 has been embodied in service

.

Reason: An A310 operator reported an electrical arc and a large hydraulic haze in the Left Hand (LH) Main Landing Gear ( M LG) wheel bay that oc curred during ground operation. The analysis of the occurrence revealed that this was likely caused by chafing between a hydraulic high pressure hose and electrical wiring of the Green Electrical Motor Pu mp (EMP).
This condition, if not detected and corrected, could result in an undetected an d uncontrolled fire in the LH MLG wheel bay

. For the reaso n described above, this AD requires modification of the electrical routing and installation of reinforced hydraulic pipes.

Effective Date: 0 8 August 2013E ASA AD No.: 2013

- 0 165

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless a ccomplished previously:

Within 36 months after the effective date of this AD, modify the e lectrical r outing of the EMP p ower s upply in the h ydraulic b ay at frame 5 4 and replace the union elbows to re

- route the delivery pipe of the upper EMP in accordance w ith the instructions of Airbus SB A310

- 29

- 2103.

Ref. Public ations: Airbus SB A310

- 29

- 2103 original issue dated 21 December 2012. The use of later approved revisions of th is document 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 08 July 2013 as PAD 13

- 071 for consultation until 08 July 2013

. No comments were received during the consultation period

. 3. En quiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirement s in this AD, please contact: AIRBUS SAS

– E I AW

- Airworthiness Office,

E

- mail: continued.airworthiness

- wb.external@airbus.com

.