EASA AD No : 2013-0158

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0158

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 

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 A340-300 aeroplanes

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

Foreign AD : Not applicable

Supersedure : This AD supersedes EASA AD 2007-0269R1 dated 15 October 2007.

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

Modification

Manufacturer(s): Airbus (Formerly 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 Mod 

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 45012 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 

damage occurred between 58 341 and 72 891 simulated flight cycles (FC).

Due to the higher Design Service Goal and different design (e.g. skin thickness) 

for A330-200 and A340-300 aeroplanes, the damage assessment concluded 

that these aeroplanes can potentially be impacted.

This condition, if not detected and corrected, could result in reduced structural 

integrity of the airframe.

Prompted by these findings, EASA issued AD 2007-0269 to require a one-time 

inspection and a modification to improve the upper shell structure.

EASA AD 2007-0269R1 was issued to clarify the fact that the AD was not 

applicable to A340-300 aeroplanes on which both Airbus Mod 44205 and Mod 

45012 have been embodied in production.
EASA AD No : 2013-0158

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Since that AD was issued, in the frame of a new fatigue and damage tolerance 

evaluation, taking into account the aeroplane utilization, 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 

2007-0269R1, which is superseded, but requires these actions within the new 

thresholds.

Effective Date: 05 August 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) For A330-200 aeroplanes on which Airbus Mod 45012 has been embodied 

in production, within the compliance time defined in Table 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 FR87 (LH and RH), in accordance with the instructions 

of Airbus Service Bulletin (SB) A330-53-3152 Revision 03.

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 aeroplane 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 aeroplanes on which Airbus Mod 45012 has 

not been embodied in production, within the compliance time defined in 

Table 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 A330-53-3157 or Airbus SB A340-53-4163, as applicable, depending 

on the aeroplane 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 Revision 03 dated 22 

December 2011.

Airbus SB A330-53-3157 original issue dated 05 July 2006.

Airbus SB A340-53-4163 original issue dated 05 July 2006.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.
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Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative 

Methods of Compliance for this AD.

2. This AD was posted on 18 June 2013 as PAD 13-079 for consultation until 

16 July 2013 and republished on 24 June 2013 as PAD 13-079R1 for 

additional consultation until 16 July 2013. No comments were received 

during the additional consultation period.

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.