EASA AD No.: 2010-0132R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0132R1

Date: 10 June 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 European third countries that participate in the activities of EASA under Article 66 of that 

Regulation.

This AD is issued in accordance with EU 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, 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 aeroplanes

TCDS Number: EASA.A.004

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2010-0132 dated 28 March 2010, which superseded 

EASA AD 2010-0042-E dated 12 March 2010.

ATA 28 Fuel – Main Fuel Pump System Water Scavenge System –

Deactivation

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-243, A330-243F, A330-341, A330-342 and A330-343

aeroplanes, all manufacturer serial numbers on which Airbus modification

56966H16199 has been embodied in production, or Airbus Service Bulletin 

(SB) A330-28-3105 has been embodied in service, except those on which 

Airbus modification (mod) 200801 has been embodied in production.

Reason: During an in-service event, the flight crew of a Trent 700 powered A330 

aeroplane reported a temporary Engine Pressure Ratio (EPR) shortfall on 

engine 2 during the take-off phase of the flight. The ENG STALL warning was 

set. The flight crew followed the standard procedures which included reducing 

throttle to idle. The engine recovered and provided the demanded thrust level 

for the remainder of the flight.

Data analysis confirmed a temporary fuel flow restriction and subsequent 

recovery, and indicated that also engine 1 experienced a temporary fuel flow 

restriction shortly after the initial event on engine 2, again followed by a full 

recovery. The engine 1 EPR shortfall was insufficient to trigger any associated 

warning and was only noted through analysis of the flight data. No flight crew 

action was necessary to recover normal performance on this engine. The 

remainder of the flight was uneventful.

Based on industry-wide experience, the investigation of the event has focused 

on the possibility for ice to temporarily restrict the fuel flow. While no direct 

fuel system fault has been identified, the operation of the water scavenge 
EASA AD No.: 2010-0132R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

system at Rib 3 is considered to have been a contributory factor.

The scenario of ice being shed and causing a temporary blockage in the 

engine fuel system may lead to a temporary restriction of fuel flow to the 

engine. This may result in a possible engine surge or stall condition, and in 

the engine not being able to provide the commanded thrust.

As a precautionary measure to reduce the possibility of ingesting ice into the 

engine fuel feed system, EASA issued Emergency AD 2010-0042-E to require

deactivation of the automatic Standby Fuel Pump Scavenge System, which 

operates during Taxi and Take-off by removing relays Functional Item 

Numbers (FIN) 80QA1 and 80QA2 (this will not affect normal standby pump 

operation) and prohibition of dispatch with one MAIN Fuel Pump inoperative.

The deactivation was introduced in production through Airbus mod 200801.

Subsequently, EASA issued AD 2010-0132 which superseded EASA AD 

2010-0042-E, retaining its requirements, to expand the applicability to the 

newly certified model A330-243F.

Since AD 2010-0132 was issued, testing and analysis have continued to 

identify the root cause of the event and recent rig tests on the aeroplane fuel 

system have been conducted to evaluate the worst icing scenario.

These test results concluded that the water scavenge system at Rib 3 cannot 

be considered as a significant contributor on ice build-up and subsequent 

release of ice into the fuel system. Consequently, the temporary MMEL 

restriction for ATA28-21 (Main Fuel Pump System) is no longer applicable and 

the dispatch restriction required by the original issue of this AD can be 

removed.

For the reason described above, this AD is revised to remove the dispatch 

restriction related to A330 MMEL TR 01-28/01Z Issue 01. In addition, some 

editorial changes have been made to improve the AD readability.

Effective Date: Revision 1: 10 June 2013

Original issue: 12 July 2010

Required action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) No later than 26 March 2010, deactivate the water scavenge automatic 

operation by removing relays FIN 80QA1 (LH) and 80QA2 (RH) in 

accordance with the instructions of Airbus All Operators Telex (AOT) 

A330-28A3114.

(2) Deleted.

(3) Deleted.

Ref. Publications: Airbus All Operators Telex A330-28A3114 dated 10 March 2010, or Rev.1 

dated 24 March 2010.

The use of later approved revisions of this 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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

3. Enquiries 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 requirements in 

this AD, please contact:

AIRBUS SAS – Airworthiness Office – EIAL, Fax: + 33 5 61 93 45 80, or

+ 33 5 61 93 44 51. E-mail: airworthiness.A330-A340@airbus.com.