EASA AD No : 2012-0198

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0198

Date: 26 September 2012

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 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].

Type Approval Holder’s Name :

AIRBUS

Type/Model designation(s) :

A318, A319, and A320 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2012-0133 dated 18 July 2012.

ATA 28 Fuel System – Centre Tank Fuel Pump Control Circuit – Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, A319-

113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, A320-211, 

A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, and A320-233 

aeroplanes, all manufacturer serial numbers.

Reason: Prompted by an accident of a Boeing 747-131 (flight TWA800), the FAA published 

Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities 

(JAA) published Interim Policy INT/POL/25/12.

In the framework of these requirements, EASA have determined that the electrical 

power supply circuits of certain fuel pumps, installed on A320 family aeroplanes, 

for which the canisters become uncovered during normal operation, could, under 

certain conditions, create an ignition source in the tank vapour space.

This condition, if not corrected, could result in a fuel tank explosion and 

consequent loss of the aeroplane.

To address this potential unsafe condition, Airbus developed a modification which 

includes installing Ground Fault Interrupters (GFI) into the centre tank fuel pump 

control circuit, providing additional system protection by electrically isolating the 

pump in case of a ground fault condition downstream of the GFI.

Consequently, EASA issued AD 2012-0133 to require modification of the centre 

tank fuel pump control circuit by installing GFI and thereafter, in case a GFI failed 

an operational test, replacement of the faulty GFI, or deactivation of the 

associated fuel pump in accordance with the provisions of the applicable Master 

Minimum Equipment List (MMEL).

Since that AD was issued, it was noted that, inadvertently, the Applicability of the 
EASA AD No : 2012-0198

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Final AD was incorrect (the preceding PAD 12-051 was correct) by excluding 

aeroplanes on which Airbus modification 150736 has been embodied in 

production. As a result, the required actions when a GFI fails an operational test 

did not apply to those aeroplanes.

For the reasons described above, this AD retains the requirements of EASA AD 

2012-0133, which is superseded, and expands the Applicability to aeroplanes on 

which Airbus modification 150736 has been embodied in production.

Effective Date: 10 October 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless already accomplished:

(1) Within 48 months after 01 August 2012 [the effective date of EASA AD

2012-0133], modify the centre tank fuel pump control circuit by installing GFI,

in accordance with the accomplishment instructions of Airbus Service Bulletin 

(SB) A320-28-1188.

(2) Aeroplanes on which Airbus modification (mod) 150736 has been embodied in 

production, and on which no GFI has been removed since first flight, are not 

affected by the requirement of paragraph (1) of this AD.

(3) From the effective date of this AD, or after modification of the centre tank fuel 

pump control circuit by installation of a GFI, as applicable, each time a GFI 

fails an operational test (Maintenance Review Board Report task number 

28.18.00/10 or AMM task 281800-710-801), before next flight, replace the 

faulty GFI, or deactivate the associated fuel pump, in accordance with the 

provisions of the applicable Master Minimum Equipment List (MMEL), item

28.21.02 "Centre tank fuel pump”.

Ref. Publications: Airbus SB A320-28-1188 at original issue dated 23 March 2012.

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

with the requirements of the 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 – Airworthiness Office – EIAS,

Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com.