EASA Cancellation Notice No : 2010
- 0132
- CN

TE. CAP.0011 6
- 00 2 © European Aviation Safety Agency. All rights reserved
. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE CANCELLATION NOTICE AD No
. : 2010 - 0132 - CN

Date: 1 4 October 2013
Note: This Airworthiness Directive (AD) Cancellation Notice (CN) 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

. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A330 aeroplanes
TCDS Number: EASA A.004
F oreign AD: Not applicable
Cancellation: This Notice cancel s EASA AD 2010
- 0132R1 dated 10 June 2013.



### ATA 28 CANCELLED: 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 A330
- 28
- 3105 has been embodied in service , except those on which Airbus modification 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 st andard 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 focused on the possibility for ice to tempora rily restrict the fuel flow. While no direct fuel system fault was identified, the operation of the water scavenge system (WSS) at Rib 3 wa s considered to have been a contributory factor. P rompted by these findings , EASA issued Emergency AD 2010
- 0042
- E toEASA Cancellation Notice No : 2010
- 0132
- CN

TE. CAP.0011 6
- 00 2 © European Aviation Safety Agency. All rights reserved
. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. require deactivation of the automatic Standby Fuel Pump Scavenge System and to prohibit dispatch of an aerop lane with one main fuel pump inoperative

. Subsequently, EASA issued AD 2010
- 0132 which superseded EASA AD 2010
- 0042
- E, retaining its requiremen ts, to expand the applicability to the newly certified model A330
- 243F. EASA AD 2010
- 0132 was later revised to remove the dispatch restriction with one main fuel pump inoperative

. Since EASA AD 2010
- 0132 R1 wa s issued , extensive fuel system icing risk investigations testing was conducted by Airbus and Rolls
- Royce, the results of which confirmed that the Rib 3 WSS operation does not induce any risk of fuel feed system (including the engine) blockage by ice accreted on the pipework and/or pump inlets. In addition, it was demonstrated that the risk of fuel flow restriction by ice at the Fuel Oil Heat Exchanger (FOHE) interface on aeroplanes equipped with Trent 700 engines is now adequately addressed by introduc tion of a re - designed FOHE , more tolerant to the release of ice (modification 200218). The modified FOHE (incorporating enhanced anti
- icing and de
- icing performance) is required to be installed on all Trent 700 engines through EASA AD 2009
- 0257. Previously , the operation of the WSS at Rib 3 wa s no longer considered as a main contributory factor on ice build
- up and subsequent release of ice into the fuel system. Based on the latest information , the deactivat ion of the automatic Sta ndby Fuel Pump Scavenge System is no longer required

. For the reasons described above, this Noti c e cancel s EASA AD 2010
- 0132R1

. Effective Date: 1 4 October 2013 Required A ction(s) and Compliance Time(s) : Not applicable

Ref. Public ations: Airbus All Operators Telex A330
- 28A3114 dated 10 March 2010, or Rev.1 dated 24 March 2010. Remarks: 1. This AD
- CN was posted on 27 September 2013 as PAD 13
- 151
- CN for consultation until 11 October 2013

. No comments were received during the consultation period

. 2. Enquiries regarding this AD
- CN should be referred to the Safety Information Section, Executive Directorate, EASA. E
- mail: ADs@easa.europa.eu

. 3. For any question concerning the technical content of this AD
- CN , 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

.