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 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) : 

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 Main 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 pump pressure switch in each of the 
EASA 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 Bulletin 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 & Research 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.