EASA AD No : 2011-0196

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0196 [Correction: 23 March 2012]

Date: 07 October 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an 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 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Type Approval Holder’s Name :
AIRBUS Type/Model designation(s) : A330-200 and A340 aeroplanes

TCDS Numbers: EASA.A.004, EASA.A.015

Foreign AD: Not applicable

Supersedure: None



### ATA 28 Fuel / Main Transfer System – Rear and/or Center Ta nk Fuel Pump Control Circuit – Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, and A330-243 aeroplanes, all manufacturer serial numbers (MSN), except those on which Airbus modification 200242 has been embodied in production

. Airbus A330-223F and A330-243F aeroplanes, all MSN, except: - aeroplanes on which Airbus modification 58623 has been embodied in production and on which Airbus modification 200281 has not been embodied in production, or - aeroplanes on which Airbus modification 200242 ha s been embodied in production. Airbus A340-211, A340-212, A340-213, A340-311, A340 -312, A340-313, A340-541, A340-542, A340-642 and A340-643 aeroplane s, all MSN, except aeroplanes on which Airbus modification 200242 has been embodied in production.

Reason: Further to the accident which occurred to a Boeing 747-131 in 1996 (flight TWA800), the FAA issued a set of new rules related to Fuel Tank Safety including Special Federal Aviation Regulation (SFAR ) 88. In line with SFAR88, the JAA issued policy JAA INT/POL 25/12 and recommended to the National Aviation Authorities (NAA) the application of a similar regulation. To ensure compliance with the requirements set by S FAR88 and JAA INT/POL 25/12, this AD requires that Ground Fault I nterrupters (GFI) are installed into the electrical power supply circuits of fuel pumps for which the canisters become uncovered during normal operation, taking into accountEASA AD No : 2011-0196

EASA Form 110 Page 2/2 normal fuel reserve or the fuel level, triggering t he low fuel level warning. The function of this additional system protection i s to electrically isolate the pump if a ground fault condition occurs downstream of the GFI. The GFI gives additional earth leakage protection to the downstre am circuit. This AD has been republished to correct a typograph ic mistake (“or” is correct instead of “and”) in the Applicability section whic h changed the intent of the AD applicability.

Effective Date: 21 October 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless already accomplished:
Within 48 months after the effective date of this A D, accomplish the actions specified in paragraph (1) or (2) of this AD, as ap plicable to aeroplane type and model: (1) For A330-200 and A340-200/300 aeroplanes, modif y the center tank fuel pump control circuit, in accordance with the accomp lishment instructions of Airbus Service Bulletin (SB) A330-28-3113, or Ai rbus SB A340-28- 4129, as applicable to aeroplane model. (2) For A340-500/600 aeroplanes, modify the rear an d/or center tank fuel pump control circuit, in accordance with the accomp lishment instructions of Airbus SB A340-28-5051.
Ref. Publications: Airbus SB A330-28-3113 original issue, dated 19 July 2011. Airbus SB A340-28-4129 original issue, dated 19 Jul y 2011. Airbus SB A340-28-5051 original issue, dated 01 Sep tember 2011. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 06 September 2011 as PAD 1 1-096 for consultation until 04 October 2011. No comments wer e received during the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS – Airworthiness Off ice – EAL, E-mail: airworthiness.A330-A340@Airbus.com

.