E ASA AD No : 20 13

- 0 158

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved

. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 13 - 0 158

Date: 22 July 2013

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 Euro pean 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, Pa rt 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

- 300 aeroplanes

TCDS Number : EASA.A.004, EASA.A.015
F oreign AD : N ot applicable Supersedure : This AD supersedes EASA AD 2007

- 0269 R1 dated 15 October 2007

.



### ATA 53 Fuselage
– Cone / Rear Fuselage Section 19

– Inspection /

Modification
Manufacturer(s): Airbus (Forme r ly Airbus Industrie) Applicability: Airbus A330

- 201, A330

- 202, A330

- 203, A330

- 223 and A330

- 243 aeroplanes , all manufacturer serial numbers (MSN) , on which Airbus Modification (Mod) 44205 has been embodied in production , except those on which Airbus M od 52974 or Mod 53223 has been embodied in production. Airbus A340

- 311, A340

- 312 and A340

- 313 aeroplanes, all MSN on which Airbus Mod 44205 has been embodied in production, except those on which Airbus Mod 52974 or Mod 53223 or Mod 45 012 has been embodied in production.
Reason: During fatigue tests (EF3) on an A340

- 600 aeroplane , multiple damage was found in the upper side shell structure at skin and frame (FR) 84 and 85 interface, from stringer 6 to 15 Left

- Hand (LH) and Right Hand (RH) . This da mage occurred between 58 341 and 72 891 simulat ed f light c ycles (FC). Due to the higher Design Service Goal and different design (e.g. skin thickness) for A330

- 200 and A340

- 300 aeroplane s , the damage assessment concluded that these aeroplane s can potential ly be impact ed

. This condition, if not detected and corrected, c ould result in reduced structural integrity of the air frame. Prompted by these findings , EASA issued AD 2007

- 0269 to require a one - time inspectio n and a modification to improve the upper shell structure. EASA AD 2007

- 0269 R1 was issued to clarify the fact t hat the AD was not applicable to A340

- 300 aeroplanes on which both Airbus M od 44205 and Mod 45012 have been embodied in production.E ASA AD No : 20 13

- 0 158

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- 003 © European Aviation Safety Agency. All rights reserved

. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Since that AD was issued, in the frame of a new fatigue and damage tolerance evaluation , taking into account the aeroplane u tilization, the threshold and intervals were reassessed. This reassessment concluded that , in that specific case, the threshold for modifying the aeroplane must be reduced. For the reasons described above, this AD retains the requirements of EASA AD 2007

- 0 269R1, which is superseded, but requires these actions within the new thresholds

. Effective Date: 05 August 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) For A330

- 200 aeroplane s on which Airbus M od 45012 has been embodied in production , w ithin the compliance time defined in T able 1 of this AD , accomplish a High Frequency Eddy Current ( HFEC ) inspection and corrective actions , as applicable , and modify the upper shell structure between FR84 and FR 87 ( LH and RH ) , in accordance with the instructions of Airbus Service Bulletin ( SB ) A330

- 53

- 3152 Revision 0 3. Table 1 Compliance time (whichever occurs later, A or B)

A Within the thresholds defined in Airbus SB A330

- 53

- 3152 Revision 03, depending on aero plane configuration and utilization

B Within 12 months after the effective date of this AD but without exceeding the previous threshold defined in Airbus SB A330

- 53

- 3152 Revision 02, as applicable, depending on aeroplane configuration and utilization

. (2 ) Aeroplanes already inspected and modified, before the effective date of this AD, in accordance with any previous revision of Airbus SB A330

- 53

- 3152 , are compliant with the requirements of paragraph ( 1 ) of this AD. (3) For A330

- 200 and A340

- 300 aeroplane s on which Airbus Mod 45012 has not been embodied in production , w ithin the compliance time defined in T able 2 of this AD, as applicable, modify the upper shell structure between FR84 and FR87 (LH and RH) in accordance with the instructions of Airbus SB A33 0

- 53

- 3157 or Airbus SB A340

- 53

- 4163, as applicable , depending o n the a eroplane type

. Table 2 Aeroplane type Compliance Time ( since aeroplane first flight ) A330

- 200 6 600 FC A340

- 300 14 000 FC

Ref. Publications : Airbus SB A330

- 53

- 3152 original issue dated 10 April 2007 , or Revision 01 dated 5 May 2009 , or Revision 02 dated 27 July 2011 , or R evision 0 3 dated 22 December 2011. Airbus SB A330

- 53

- 3157 original issue dated 05 July 2006. Airbus SB A340

- 53

- 4163 original issue dated 05 Jul y 2006. The use of l ater approved revisions of these documents is acceptable for compliance with the requirements of this AD.E ASA AD No : 20 13

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- 003 © European Aviation Safety Agency. All rights reserved

. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD

. 2. This AD was p osted on 18 June 2013 as PAD 13

- 0 79 for consultation until 16 July 2013 and republished on 24 June 2013 as PAD 13

- 0 79 R1 for additional consultation until 16 July 2013 . No comments were received during the additional consultation period

. 3. Enquiries regarding this A D 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

– Air worthiness Office

– E I AL E

- mail : airworthiness.A330

- A340@airbus.com

.