EASA AD No : 2010-0086R1 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0086R1 

Date: 16 June 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) : 

A330 and A340 aeroplanes 

TCDS Number : EASA.A.004, EASA.A.015 

Foreign AD : Not applicable 

Revision : This AD revises EASA AD 2010-0086 dated 04 May 2010 

ATA 92 Electric and Electronic Common Installation – Hydraulic Pump 

Electrical Motor Connectors – Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -243, -301, -302, -

303, -321, -322, -323, -341, -342 and -343, all manufacturer serial 

numbers, except those on which Airbus modifications 58773 and 45968 

have been embodied in production. 

Airbus A340 aeroplanes, models -211, -212, -213, -311, -312, -313, all 

manufacturer serial numbers, except those on which Airbus modifications 

58773 and 45968 have been embodied in production. 

Airbus A340 aeroplanes, models -541, -542, -642 and -643, all 

manufacturer serial numbers, except those on which Airbus modifications 

58773 and 45968 have been embodied in production. 

Reason: Several A330 and A340 operators have reported in service occurrences of 

hydraulic pump electrical motor connector internal arcing, resulting in: 

- either false hydraulic system overheat Electronic Centralized Aircraft 

Monitoring (ECAM) warnings 

- and / or hydraulic pump electrical motor malfunction. 

Investigations have shown that, due to the manufacturing tolerances of the 

cables and the connectors rear grommet, there is a possible path for fluid 

ingress, resulting in connector internal arcing and hydraulic system 

malfunction. In addition, as the connectors are located in areas adjacent to 

fuel tanks, such arcing associated with the presence of a fuel leakage 

could lead to an uncontrolled fire. 
EASA AD No : 2010-0086R1 

EASA Form 110 Page 2/2 

In order to protect the hydraulic pump electrical motor connectors against 

fluid ingress from the rear of the connector grommet and prevent false 

hydraulic system overheat ECAM warnings and/or hydraulic pump 

electrical motor malfunction, this AD requires modification of the three 

hydraulic pump electrical motor connectors associated to the Blue, Yellow 

and Green hydraulic systems. 

This Revision 1 is issued to delete Airbus modifications 55923S18878 and 

55924S19452 from the applicability of this AD. 

Effective Date: Revision 1: 17 June 2010 

Original Issue: 18 May 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished : 

Within 3 600 flight hours after 18 May 2010 [effective date of this AD at 

original issue], modify the hydraulic pump electrical motor connectors of 

the Blue, Yellow and Green Electric Pumps in accordance with the 

instructions defined in Airbus Service Bulletin (SB) A330-92-3088, or 

Airbus SB A340-92-4081, or Airbus SB A340-92-5053, as applicable to 

the aeroplane model. 

Ref. Publications: Airbus Service Bulletin A330-92-3088 at Original issue, 

Airbus Service Bulletin A340-92-4081 at Original issue, 

Airbus Service Bulletin A340-92-5053 at 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. The original issue of this AD was posted on 19 February 2010 as PAD 

10-019 for consultation until 19 March 2010. 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 – Airworthiness Office - EAL. Fax: +33 5 61 93 45 80. 

E-mail: airworthiness.A330-A340@airbus.com .