EASA AD No.: 2013-0163

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0163

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 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

Airbus A300, A300-600, A300-600ST and 

A310 aeroplanes

TCDS Numbers: France No. 145, EASA.A.014

Foreign AD: Not applicable

Supersedure: None

ATA 28 Fuel – Fuel Pumps / Power Supply Circuit Breakers – Functional 

Test / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus model A300 series, A300-600 series, A300-600ST 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 2052Cxx 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.

Investigations 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, would 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 described 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.: 2013-0163

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

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Effective Date: 07 August 2013

Required Action(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 intervals 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 Table 1 of this AD, as 

applicable to aeroplane model, in accordance with the instructions of 

Airbus (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,

A300-600ST 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 instructions of Airbus AOT 

A28W002-13.

(3) The replacement of one or more circuit breakers as required by paragraph 

(2) of this AD does not constitute terminating action for the repetitive 

functional tests required by paragraph (1) of this AD.

Ref. Publications: Airbus AOT A28W002-13 dated 23 July 2013.

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 – EIAW (Airworthiness Office)

Email: continued.airworthiness-wb.external@airbus.com