E ASA AD No : 2012

- 0198

TE.CAP.00110

- 003 © 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.: 20 12 - 0198

Date: 26 September 20 1 2

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 i s issued in accordance with EC 7 48 /20 12 , 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 air craft to which an AD applies, except in accordance with the requ irements 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 sup ersedes EASA AD 2012

- 0133 dated 18 July 2012

.



### ATA 28 Fuel System

– Centre T ank 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 aeropl ane. 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 i n case of a ground fault conditio n 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, rep lace ment of the faulty GFI , or deactivat ion 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 theE ASA AD No : 2012

- 0198

TE.CAP.00110

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

- Internet/Intranet. 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 A ction(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 affecte d 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 fail s an operational test (M aintenance R eview B oard R eport 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. Public ations: Airbus SB A3 2 0

- 28

- 1188 at original issue dated 23 March 201 2

. The use of later approved revisions of th is 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 t he 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 conte nt 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

.