EASA AD No : 2010-0013

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0013

Date: 26 January 2010

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 a pplicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance wi th 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) :
A340-500/-600 aeroplanes

TCDS Number : EASA.A.015

Foreign AD : Not applicable

Supersedure : None



### ATA 28 Fuel – Main and Standby Fuel Pump Wiring – Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A340-541, A340-542 , A340-642 and A340-643 aeroplanes, all manufacturer serial numbers.

Reason: An A340-642 operator reported a Ma in Fuel Pump 4 fault that occurred during descent. Afterwards it was followed by a 2 times Eng 4 Stall/Surge Message and finally the engine had an auto shutdown with Message Engine 4 Fail. Analysis of the A340-500/600 aircraft fuel-pump electrical-circuit design has shown that when a main fuel pump becomes unserviceable and the fuel pressure indication system indicates abnormal High (HI) pressure, these unwanted conditions occur:
- There is no Electronic Centralized Aircraft Monitor (ECAM) caution or

fault light of the unserviceable fuel pump. - The crew cannot manually set the standby fuel pump to ’ON’ because

of the main pump pressure abnormal HI condition. Simultaneous loss of at least two Main Pumps along with other potential failures related to the in-service event may lead to a dual engine loss. This AD mandates the modification of the main and standby pump wiring logic which will let the related standby fuel pump be set ’ON’ irrespective of the status of the main fuel pum p pressure switch in each of theEASA AD No : 2010-0013

EASA Form 110 Page 2/2 conditions that follow: - After the main fuel pump becomes unserviceable; - When the push-button switch of the related main fuel pump is set to

’OFF’, even if the fuel pump pressure indicates abnormally HI.

Effective Date: 09 February 2010

Required action(s) and Compliance Time(s): Required as indicated, unless already accomplished: Within 13 500 Flight Hours after the effective date of this AD, modify the electrical circuit associated to the main and standby pumps in the Left Hand (LH) and Right Hand (RH) wing in accordance with the instructions of Airbus Service Bulletin A340-28-5050.

Ref. Publications: Airbus Service Bulle tin A340-28-5050 at original issue. The use of later approved revisions of this document is acceptable for compliance with the requirements of the AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 24 November 2009 as PAD 09-132 for consultation until 22 December 2009. No comments were received during the consultation period. 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 questions concerning the technical content of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EAL; E-mail: airworthiness.A330-A340@airbus.com

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