EASA AD No : 2011-0196 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0196 

Date: 07 October 2011 

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 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 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) : 

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 Tank 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, and 

- aeroplanes on which Airbus modification 200242 has 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 aeroplanes, 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 SFAR88 and JAA 

INT/POL 25/12, this AD requires that Ground Fault Interrupters (GFI) are 

installed into the electrical power supply circuits of fuel pumps for which the 

canisters become uncovered during normal operation, taking into account 
EASA AD No : 2011-0196 

EASA Form 110 Page 2/2 

normal fuel reserve or the fuel level, triggering the low fuel level warning. 

The function of this additional system protection is to electrically isolate the 

pump if a ground fault condition occurs downstream of the GFI. The GFI gives 

additional earth leakage protection to the downstream circuit. 

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 AD, accomplish the actions 

specified in paragraph (1) or (2) of this AD, as applicable to aeroplane type 

and model: 

(1) For A330-200 and A340-200/300 aeroplanes, modify the center tank fuel 

pump control circuit, in accordance with the accomplishment instructions 

of Airbus Service Bulletin (SB) A330-28-3113, or Airbus SB A340-28-

4129, as applicable to aeroplane model. 

(2) For A340-500/600 aeroplanes, modify the rear and/or center tank fuel 

pump control circuit, in accordance with the accomplishment 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 July 2011. 

Airbus SB A340-28-5051 original issue, dated 01 September 2011. 

The use of later approved revisions of these documents 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. This AD was posted on 06 September 2011 as PAD 11-096 for 

consultation until 04 October 2011. No comments were received during 

the consultation period. 

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 – EAL, 

E-mail: airworthiness.A330-A340@Airbus.com.