EASA AD No : 2012-0005 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0005 

Date: 10 January 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 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, A340-200/-300 aeroplanes 

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

Foreign AD : Not applicable 

Supersedure : None 

ATA 53 Fuselage – Belly Fairing Rods – Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, 

A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, 

A330-323, A330-341, A330-342 and A330-343 aeroplanes, all 

manufacturer serial numbers (MSN). 

Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313, 

all manufacturer serial numbers. 

Reason: A rod manufacturing process defect has been identified at the supplier, 

Technical Airborne Components Industries (TAC), which could lead to 

cracks at the crimped end of the rod.

A design review of all affected rods has demonstrated that rupture of rods 

which attach the belly fairing can lead to separation of the belly fairing from 

the airframe, which would constitute an unsafe condition. 

For the reasons described above, this AD requires detailed visual 

inspections of the 21 affected rods installed in the belly fairing for 

manufacturer identification, and if TAC is identified as manufacturer, or if 

the manufacturer cannot be identified, to further inspect the rods to find 

any crack, using a high frequency eddy current (HFEC) method and, 

depending on findings, accomplishment of the applicable corrective 

actions, to ensure structural integrity of the belly fairing rods. This AD also 

prohibits installation of an affected TAC rod as replacement part in the 

belly fairing to all aeroplanes. 
EASA AD No : 2012-0005 

EASA Form 110 Page 2/2 

Effective Date: 24 January 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) For Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, 

A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, 

A330-322, A330-323, A330-341, A330-342 , A330-343, A340-211, 

A340-212, A340-213, A340-311, A340-312, and A340-313 aeroplanes, 

from MSN 0002 to 1113 inclusive, except MSN 0996, 1039, 1054, 

1059, 1105, 1107, 1108 and 1112: 

Within 72 months after the effective date of this AD, accomplish the 

following actions in accordance with the instructions of Airbus Service 

Bulletin (SB) A330-53-3186 Revision 01 or SB A340-53-4185 Revision 

01, as applicable to aeroplane type: 

(1.1) Perform a detailed visual inspection of the 21 affected rods of 

the belly fairing, listed in SB A330-53-3186 Revision 01 or SB 

A340-53-4185 Revision 01, as applicable to aeroplane type, for 

rod manufacturer identification. 

(1.2) If the rod manufacturer, identified as required by paragraph (1.1) 

of this AD, is TAC, or if the manufacturer cannot be identified, 

perform a HFEC inspection of the crimped end of the rod body 

and, if any crack is found, before next flight following the HFEC 

inspection, do the applicable corrective actions. 

(1.3) Inspections and corrective actions accomplished before the 

effective date of this AD, in accordance with Airbus SB 

A330-53-3186 original issue or SB A340-53-4185 original issue, 

as applicable to aeroplane type, are acceptable to comply with 

the requirements of paragraphs (1.1) and (1.2) of this AD. 

(2) For all aeroplanes identified in the Applicability section of this AD: 

From the effective date of this AD, do not install any affected TAC rod, 

listed in SB A330-53-3186 Revision 01 or SB A340-53-4185 Revision 

01, as applicable to aeroplane type, in the belly fairing unless the rod 

has passed the inspection as required by paragraph (1.2) of this AD. 

Ref. Publications : Airbus Service Bulletin A330-53-3186 Revision 01 dated 07 April 2011; 

Airbus Service Bulletin A340-53-4185 Revision 01 dated 07 April 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 25 November 2011 as PAD 11-056R1 for 

consultation until 09 December 2011. The original issue of PAD 11-

056 was closed for consultation on 29 June 2011. The Comment 

Response Document can be found at http://ad.easa.europa.eu/. 

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 questions concerning the technical content of the 

requirements in this AD, please contact: AIRBUS – Airworthiness 

Office – EAL; E-mail: airworthiness.A330-A340@airbus.com .