EASA AD No.: 2014-0149

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0149

Date: 13 June 2014

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 EU 748/2012, 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 

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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A330 and A340 aeroplanes

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

Foreign AD: Not applicable

Supersedure: None

ATA 57 Wings – Center Wing Box Fastener Holes at Frame 40 Vertical Web 

– 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, except those on which Airbus modification (Mod) 55792 or Mod 

55306 has been embodied in production, and except those on which Airbus

Repair Instruction R57115092 has been embodied in service on both Right 

Hand (RH) and Left Hand (LH) sides.

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

aeroplanes, all manufacturer serial numbers except those on which Airbus Mod

55792 or Mod 55306 has been embodied in production, and except those on 

which Airbus Repair Instruction R57115092 has been embodied in service on 

both RH and LH sides.

Reason: During accomplishment of A330 Airworthiness Limitation Item (ALI) task 

57-11-04 on the rear fitting of the Frame (FR) 40 between stringers 38 and 39 

on both LH/RH sides, cracks were found on an adjacent hole. After reaming at 

second oversize of the subject hole, the crack was still present.

Other crack findings on this adjacent hole have been reported on A330 and 

A340-200/-300 aeroplanes as a result of sampling inspections.

This condition, if not detected and corrected, could affect the structural integrity

of the aeroplane.

For the reasons described above, this AD requires removal of the fasteners 
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and repetitive rototest inspections of fastener holes at FR40 vertical web 

located above Center Wing Box (CWB) lower panel reference and/or below 

CWB lower panel reference on both sides and, depending on findings, 

accomplishment of the applicable corrective actions.

Note: These holes affected by this AD are different from the ones affected by 

EASA AD 2009-0001.

Effective Date: 27 June 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time defined in Table 1 of this AD, as applicable,

and thereafter, at intervals not to exceed the values defined in Airbus 

Service Bulletin (SB) A330-57-3114, or SB A330-57-3115, or SB 

A330-57-3116, or SB A340-57-4123, or SB A340-57-4124 Revision 01, or 

SB A340-57-4125, as applicable, depending on aeroplane configuration

and utilisation, remove the fasteners and accomplish a special detailed 

inspection of fastener holes at FR40 vertical web, on both sides, located

above and below CWB lower panel reference in accordance with the 

instructions of applicable Airbus SB, as specified in Table 2 of this AD, 

depending on aeroplane configuration.

Table 1 – Initial Inspection

Compliance time (whichever occurs later, A or B)

A

Within the threshold defined in Airbus SB A330-57-3114, or SB 

A330-57-3115, or SB A330-57-3116, or SB A340-57-4123, or 

SB A340-57-4124 Revision 01, or SB A340-57-4125, as 

applicable, depending on aeroplane configuration and 

utilisation.

B

For A330 aeroplanes: Within 2 400 Flight Cycles (FC) or 24 

months, whichever occurs first after the effective date of this 

AD.

For A340 aeroplanes: Within 1 300 FC or 24 months, whichever 

occurs first after the effective date of this AD.

Table 2 – Applicable Airbus SB

Aeroplane Configuration Airbus SB Location to be 

Inspected

A330-300 pre-mod 44360 A330-57-3114 Below

A340-200/-300 pre-mod 44360 A340-57-4123 Below

A330-200/-300 post-mod 44360 

and pre-mod 49202

A330-57-3116 Below

A340-200/-300 post-mod 44360

and pre-mod 49202

A340-57-4125 Below

A330-200/-300 pre-mod 55306 

and A330-200/-300 pre-mod 

55792

A330-57-3115 Above

A340-200/-300 pre-mod 55306 

and A340-200/-300 pre-mod 

55792

A340-57-4124 Above
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(2) If, during any inspection as required by paragraph (1) of this AD, no crack 

is detected, before next flight, install new fasteners in transition fit in 

accordance with the instructions of Airbus SB A330-57-3114 or SB

A330-57-3115 or SB A330-57-3116 or SB A340-57-4123 or SB 

A340-57-4124 Revision 01 or SB A340-57-4125, as applicable to 

aeroplane type and model.

(3) If, during any inspection as required by paragraph (1) of this AD, a crack is 

detected, before next flight, accomplish the applicable corrective actions

(additional inspection followed by repetitive inspections) in accordance with 

the instructions of Airbus SB A330-57-3114 or SB A330-57-3115 or SB 

A330-57-3116 or SB A340-57-4123 or SB A340-57-4124 Revision 01 or 

SB A340-57-4125, as applicable to aeroplane type and model, or,

depending on findings, contact Airbus to obtain a Repair Design Approval 

Sheet (RDAS) and accomplish that repair accordingly, including post-repair 

follow-on action(s), if any are specified in that RDAS.

(4) Installation of new fasteners as required by paragraph (2) of this AD does 

not constitute terminating action for the repetitive inspections required by 

paragraph (1) of this AD.

(5) Accomplishment of the corrective actions as required by paragraph (3) of 

this AD does not constitute terminating action for the repetitive inspections 

required by paragraph (1) of this AD.

Accomplishment of a repair on an aeroplane, as required by paragraph (3) 

of this AD, does not constitute terminating action for the repetitive 

inspections as required by paragraph (1) of this AD for that aeroplane, 

unless the RDAS indicates otherwise.

(6) Accomplishment of the initial and repetitive inspections as required by this 

AD cancels the need to accomplish Airworthiness Limitation Items tasks 

57-11-04 and 57-11-02.

(7) Inspections, corrective actions, and installation of fasteners accomplished

before the effective date of this AD in accordance with the instructions of 

Airbus Technical Disposition Reference LR57D11023270, or 

LR57D11029171, or LR57D11029173, or LR57D11030741, or 

LR57D11029170, or LR57D11023714, or LR57D11029172, or 

LR57D11030740, or SB A340-57-4124 at original issue, are acceptable to 

comply with the initial inspections and corrective actions as required, 

respectively, by paragraphs (1) and (3) of this AD. After the effective date 

of this AD, inspections, corrective actions and fastener replacements must 

be accomplished as required by this AD.

Ref. Publications: Airbus SB A330-57-3114 original issue dated 12 March 2013.

Airbus SB A330-57-3115 original issue dated 04 April 2013.

Airbus SB A330-57-3116 original issue dated 12 March 2013.

Airbus SB A340-57-4123 original issue dated 12 March 2013.

Airbus SB A340-57-4124 original issue dated 04 April 2013 or Revision 01 

dated 22 August 2013.

Airbus SB A340-57-4125 original issue dated 12 March 2013.

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 March 2014 as PAD 14-058 for consultation 

until 22 April 2014. The Comment Response Document can be found at 
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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 question concerning the technical content of the requirements in 

this AD, please contact: Airbus – Airworthiness Office – EIAL;

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