EASA AD No.: 2010-0132 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0132 

Date: 28 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 aeroplanes 

TCDS Number : EASA.A.004 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2010-0042-E dated 12 March 2010 

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

Deactivation / Dispatch Restriction 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

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

manufacturer serial numbers on which Airbus modification 56966H16199 

has been embodied in production or Airbus Service Bulletin A330-28-3105 

has been embodied in service. 

Reason: During a recent in-service event the flight crew of a Trent 700 powered 

A330 aircraft 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 previous 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 system at Rib 3 cannot be excluded as being a 
EASA AD No.: 2010-0132 

EASA Form 110 Page 2/3 

contributory factor. 

Testing and analysis are continuing to identify the root cause of the event. 

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

engine fuel system may lead to a temporary fuel flow restriction 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. 

Therefore, as a precautionary measure to reduce the possibility of 

ingesting ice into the engine fuel feed system, EASA EAD 2010-0042-E 

required to: 

- deactivate 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) for aeroplanes identified in the applicability section of this 

AD and on which this deactivation has not been performed in production 

through the modification 200801, and 

- Prohibit the dispatch with one MAIN Fuel Pump inoperative on all 

aeroplanes identified in the applicability section of this AD. 

This AD, which supersedes EASA AD 2010-0042-E retaining its 

requirements, is issued to extend the applicability to the newly certified 

model A330-243F. 

Effective Date: 12 July 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated after 16 March 2010 [effective date of AD 

2010-0042-E]: 

(1) For aeroplanes on which Airbus modification 200801 has NOT been 

embodied in production:

Unless accomplished previously, no later than 26th March 2010, 

deactivate the water scavenge automatic operation by removing relays 

FIN 80QA1 (LH) and 80QA2 (RH) in accordance with the instructions 

defined in Airbus All Operators Telex (AOT) A330-28A3114. 

(2) For all aeroplanes identified in the applicability section of this AD, 

except A330-243F aeroplanes:

Before further flight after accomplishment of paragraph (1) of this AD 

for aeroplanes on which Airbus modification 200801 has NOT been 

embodied in production, or 

After 16 March 2010 [effective date of EASA AD 2010-0042-E] for 

aeroplanes on which Airbus modification 200801 has been embodied 

in production: 

Dispatch restriction :

Dispatch with any Main Fuel Pump inoperative (item numbered 28-21-

01 in the associated Master Minimum Equipment List (MMEL)) is 

prohibited. 

The following operational limitation is required as indicated from the 

effective date of this AD: 

(3) For A330-243F aeroplanes: 

Dispatch restriction :

Dispatch with any Main Fuel Pump inoperative (item numbered 28-21-

01 in the associated Master Minimum Equipment List (MMEL)) is 

prohibited. 
EASA AD No.: 2010-0132 

EASA Form 110 Page 3/3 

Note: This dispatch restriction is included in the MMEL Temporary 

Revision (TR) A330 TR 01-28/01Z Issue 01. 

Incorporation of this MMEL TR or inserting the above dispatch restriction 

or a copy of this AD into the Aircraft Operations Manual (AOM) and strict 

adherence to the above dispatch restriction by the flight crew is acceptable 

to comply with the requirements of paragraphs (2) and (3) of this AD. 

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

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

Airbus A330 MMEL TR 01-28/01Z Issue 01 EASA accepted on 10 March 

2010. 

The use of any later EASA accepted revision of this MMEL TR or of any 

general MMEL revision including this dispatch restriction is acceptable to 

comply 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 required actions and the risk allowance have granted the 

issuance of a Final AD with Request for Comments, postponing the 

public consultation process after publication. 

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 

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