EASA AD No : 2010 – 0199 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0199 

Date: 30 September 2010 

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) : 

A310 aeroplanes 

TCDS Number : France N° 145 

Foreign AD : Not applicable 

Supersedure : None 

ATA 28 Fuel System – Fuel Tank Electrical Bonding – 

Inspection/Modification [Fuel Tank Safety] 

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE) 

Applicability: - A310-203, A310-203C, A310-204, A310-221 and A310-222 

aeroplanes (without trim tank) models, all serial numbers, except 

aeroplanes on which AIRBUS Service Bulletins (SB) A310-28-2143 

and A310-28-2142 Revision 3 have been embodied in service. 

- A310-304, A310-308, A310-322, A310-324 and A310-325 aeroplanes 

(fitted with trim tank) models, all serial numbers, except aeroplanes on 

which SB A310-28-2143, A310-28-2142 Revision 3 and A310-28-

2153 have been embodied in service. 

Reason: Further to the accident of a Boeing 747-131 (flight TWA800), the FAA has 

published SFAR 88 (Special Federal Aviation Regulation 88). 

In their letters referenced 04/00/02/07/01-L296, dated March 4th, 2002, 

and 04/00/02/07/03-L024, dated February 3rd, 2003, the JAA 

recommended the application of a similar regulation to the National 

Aviation Authorities (NAA). 

Under this regulation, all holders of type certificates for passenger 

transport aircraft with either a passenger capacity of 30 or more, or a 

payload capacity of 3,402 kg (7,500 lb) or more which have received their 

certification since January 1st, 1958, are required to conduct a design 

review against explosion risks. 
EASA AD No : 2010 – 0199 

EASA Form 110 Page 2/2 

The replacement of some types of P-clips and improvement of the 

electrical bonding of the equipment in the fuel tanks have been required 

by EASA AD 2006-0325. Thereafter, AD 2006-0325 has been revised 

twice to remove respectively AIRBUS A300-600 and A310 aeroplanes 

from its applicability paragraph. 

As a result, this new AD retains the requirements of EASA AD 2006-325 

R1 (corrected on 26th July 2007) applicable to A310 aeroplanes and 

requires the additional work introduced by Airbus SB A310-28-2142 at 

revision 3.

Effective Date: 14 October 2010 

Required action(s) 

and Compliance 

Time(s): 

Required before 31 December 2010, unless previously accomplished: 

(1) Remove NSA5516-XXND or NSA5516-XXNJ type P-clips, used in the 

wing and centre fuel tanks to retain wiring and pipes, and replace them by 

NSA5516-XXNF type P-clips in accordance with the instructions of Airbus 

SB A310-28-2143; and 

(2) Check the electrical bonding points in the centre tank, and install 

additional bonding leads, electrical bonding points in the wing and centre 

fuel tanks and the bonding of the bolt with the over wing refuel caps, in 

accordance with the instructions of Airbus SB A310-28-2142 Revision 3. 

(3) For aeroplanes in compliance with the requirements of EASA AD 2006-

325 R1, do only the additional work in accordance with the instructions of 

Airbus SB A310-28-2142 Revision 3. 

(4) For aeroplanes fitted with a trim tank, in addition to the actions defined in 

paragraphs (1) and (2) of this AD, install bonding leads and electrical 

bonding points in the trim tanks in accordance with the instructions of 

Airbus SB A310-28-2153. 

Ref. Publications: AIRBUS Service Bulletins A310-28-2142 Revision 3, A310-28-2143 and 

A310-28-2153 original issue. 

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. The required actions and the risk allowance have granted the 

issuance of a Final AD with Request for Comments, postponing the 

public consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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 – EAW (Airworthiness Office, 

Telephone: + 33 5 61 93 36 96, Fax: + 33 5 61 93 44 51).