EASA AD No.: 2013

- 0 163

TE. CAP.0011 0

- 00 3 © 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

AD No

. : 2013

- 0 1 6 3

Date: 24 July 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 ope rate 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) exempt ion].



### Design Approval Holder’s Name:

AIRBUS Type/Model designation(s) : Airbus A300, A300

- 600, A300

- 60 0 S T and A310 aeroplanes

TCDS Number s : France No. 145, EASA.A.014

F oreign AD: Not applicable

Supersedure: None



### ATA 28 Fuel

– Fuel Pumps / Power Supply Circuit Breakers

– Functional

Test / Replacement

Manufacturer(s): Airbus ( formerly A irbus Industrie)

Applicability: Airbus model A300 series , A300

- 600 series , A300

- 6 00 ST series and A310 series aeroplanes, all manufacturer serial numbers

.

Reason: Two successive failures have been reported of a Right Hand # 1 inner tank fuel pump , Part Number 2052C xx series (with placeholder “xx” indicating numerals ). The fix consisted in the replacement of the pump, the associated circuit breaker and the AC bus load relay.

I nvestigations determined that

, in case of loss of one phase on the pump supply and the associated circuit breaker failing to trip, the fuel pump thermal fuses may not operate as quickly as expected

. This condition , if not detected and corrected, w ould result in an overheat condition of the fuel pump in excess of 200  ̊ C and could lead to a fuel tank explosion.
To address this potential unsafe condition, Airbus issued Alert Operator Transmission ( AOT ) A28W002

- 13 providing instructions for a functional test of circuit breakers and corrective action.

For the reasons descri bed above, as a temporary measure until further notice, this AD mandates functional tests of the affected fuel pump power supply circuit breakers, and , depending on findings, replacement of circuit breakers

. This AD will be followed by further AD action.EASA AD No.: 2013

- 0 163

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: 07 August 2013

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:
(1) Within 6 months or 500 flight hours (FH) after the effective date of this AD, whichever occurs first, and

, thereafter

, at interval s not to exceed 6 months or 500 FH, whichever occurs first, accomplish a functional test of the fuel pump power supply circuit breakers as listed in T able 1 of this AD , as applicable to aeroplane model , in accordance with the instruction s of Ai rbus (AOT) A28W002

- 13

.

Table 1: Circuit breakers to be tested

Aeroplane model Circuit breakers to be tested

A300B2 series - Inner and outer pump, No

. 1 and No

. 2, Left Hand (LH) side and Right Hand (RH) side

A300B4 /C4/F4 series

, A300

- 600 series

, A300

- 6 0 0 S T series

, A310

- 200 series - Inner and outer pump, No

. 1 and No. 2, LH and RH

- Centre pump LH and RH

A300

- 600R series

, A310

- 300 series - Inner and outer pump, No

. 1 and No. 2, LH and RH

- Centre pump LH and RH

- Trim tank pump No

. 1 and No

. 2

(2) If, during any functional test as required by paragraph (1) of this AD, any finding is made, before next flight

, replace the affected circuit breaker with a serviceable part in accordance with the instruction s of Airbus AOT A28W002

- 13

. (3) The replacement of one or more circuit breaker s as required by paragraph (2) of this AD does not constitute terminating action for the repetitive functional test s required by paragraph (1) of this AD.

Ref. Public ations: Airbus AOT A28W002

- 13 dated 23 July 2013.

The u se 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 A D should be referred to the Safety Information Section, Executive Direct orate , 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

– EIAW (Airworthiness Office ) Email: continued.airworthiness

- wb.external@airbus.com