E ASA AD No.: 20 14 - 0 149

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 1 4 - 0 149

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 E U 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 ope rate 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 Number s : EASA.A.004 and EASA.A.015 F oreign 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 A irbus 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 R ight H and (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 a n 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 faste n ersE ASA AD No.: 20 14 - 0 149

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. and repetitive rototest inspection s 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 A ction(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, a nd thereafter , at intervals not to exceed the values defined in Airbus Service Bulletin ( SB ) A3 3 0 - 5 7 - 3114 , or SB A330 - 57 - 3115 , or SB A330 - 57 - 3116 , or SB A340 - 5 7 - 4123 , or SB A340 - 57 - 4124 Revision 01 , or SB A340 - 57 - 4125 , as applicable, depending on aeroplane configuratio n and utilisation , remove the fasteners and accomplish a spe cial 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 A3 3 0 - 57 - 3114 , or SB A3 3 0 - 57 - 3115 , or SB A3 3 0 - 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 utili s ation

. B For A330 aeroplanes : Within 2 400 F light C ycles (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 4436 0 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 AboveE ASA AD No.: 20 14 - 0 149

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. (2) If, during any inspection as required by paragraph (1) of this AD, no crack is detected, before next flight , install new fastener s in transit ion 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 inspection s ) 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 R epair Design Approval Sheet (RDAS) and accomplish th at repair accordingly, including post - repair follow - on action(s), if any are specified in that RDAS

. (4) Installation of new fastener s as required by paragraph (2) of this AD does not constitute terminating action for the repetitive insp ection s 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 LR57 D 11023270 , or LR57D1102917 1 , 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 inspection s and corrective actions as required , respectively, by paragraph s (1) and (3) of this AD

. After the effective date of this AD , inspections , corrective actions and fastener replacements must be accomplishe d as required by this AD. Ref. Public ations: 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 u se 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 atE ASA AD No.: 20 14 - 0 149

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 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 t h is AD, please contact: Airbus

– Airworthiness Office

– E I AL; E - mail: airworthiness.A330 - A340@airbus.com

.