EASA AD No.: 2010-0042-E 

EASA Form 111 Page 1/3 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0042-E 

Date: 12 March 2010 

Note: This Emergency 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 : None 

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, -341, -342 and -343, all 

manufacturer serial numbers on which Airbus modification 

56966MP16199 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 

contributory factor. 
EASA AD No.: 2010-0042-E 

EASA Form 111 Page 2/3 

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, this AD requires 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. 

Effective Date: 16 March 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated : 

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

embodied in production:

Unless accomplished previously, no later than 10 days after the 

effective date of this AD, 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:

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 the effective date of this AD 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. 

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 paragraph 

(2) 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. 
EASA AD No.: 2010-0042-E 

EASA Form 111 Page 3/3 

Remarks : 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The safety assessment has requested not to implement the full 

consultation process and an immediate publication and notification. 

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 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.