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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0012R1

Date: 24 January 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.

In accordance with the EASA Continuing Airworthiness Procedures, the Executive Director is proposing the issuance of an EASA 

Airworthiness Directive (AD), applicable to the aeronautical product(s) identified below.

All interested persons may send their comments, referencing the PAD Number above, to the e-mail address specified in the 

‘Remarks’ section, prior to the consultation closing date indicated.

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

Revision: This AD revises EASA AD 2014-0012 dated 10 January 2014, which superseded

EASA AD 2007-0284 dated 12 November 2007.

ATA 53 Fuselage – Longitudinal Doubler at Vertical Tail Plane Attachment Cut 

Out – Inspection / Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-243 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) on which 

Airbus modification 44205 has been embodied in production, except those on 

which Airbus modification 52974 or 53223 has been embodied in production, 

and

Airbus A340-311, A340-312 and A340-313 aeroplanes, all MSN on which 

Airbus modification 44205 has been embodied in production, except those on 

which Airbus modification 52974 or 53223 has been embodied in production.

Reason: During fatigue tests (EF3) on the A340-600, damage was found in the 

longitudinal doubler at the Vertical Tail Plane (VTP) attachment cut out

between Frame (FR) 80 and FR86. This damage occurred between 58 341 

and 72 891 simulated flight cycles (FC).

Due to the higher Design Service Goal and different design of the affected 

structural area (e.g. doubler thickness) for A330-200/-300 and A340-300 

aeroplane series, the damage assessment concluded that these aeroplanes 

may be also potentially affected.

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

integrity of the upper shell structure between FR80 and FR86.

Prompted by these findings, EASA issued AD 2007-0284 to require 

implementation of an inspection programme of this structural area using a high 

frequency eddy current (HFEC) method and a modification to improve the 
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upper shell structure.

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

evaluation, taking into account the aeroplane utilisation, the inspection

threshold and intervals have been reassessed and the conclusion was that the 

thresholds and intervals for inspection, as well as the threshold for modifying 

the aeroplane, must be reduced.

For the reason described above, this AD retains the requirements of EASA AD 

2007-0284, which is superseded and introduces redefined thresholds and 

intervals.

This AD is revised to clarify that, under some conditions, accomplishment of a 

repair constitutes terminating action for the repetitive inspections. One of the 

outcome of this clarification is the deletion of paragraph (5) of this AD.

Effective Date: Revision 1 (same as original issue): 24 January 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Part A – A330-300 and A340-300 aeroplanes

(except Weight Variant (WV) 027 – see Part C of this AD):

(1) For aeroplanes that, before the effective date of this AD, have never

been inspected in accordance with the instructions of Airbus SB

A330-53-3168 or SB A340-53-4174, as applicable to aeroplane type:

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

and, thereafter, at intervals not to exceed the values, whichever occurs 

first as defined in Airbus SB A330-53-3168 Revision 02 or Airbus SB 

A340-53-4174 Revision 02, depending on aeroplane type, configuration 

and utilisation, accomplish a HFEC inspection of the upper shell structure 

between FR80 and FR86 in accordance with the instructions of Airbus SB 

A330-53-3168 Revision 02 or Airbus SB A340-53-4174 Revision 02, as 

applicable to aeroplane type.

Table 1 – Threshold

Compliance time (whichever occurs later, A or B)

A

Within the inspection threshold defined in Airbus SB 

A330-53-3168 Revision 02 or Airbus SB A340-53-4174 Revision 

02, as applicable to aeroplane type, configuration and utilisation, 

since aeroplane first flight

B

Within 12 months after the effective date of this AD, but without 

exceeding the previous inspection threshold, whichever occurs 

first, as defined in Airbus SB A330-53-3168 Revision 01 or 

Airbus SB A340-53-4174 Revision 01, as applicable to aeroplane 

type, configuration and utilisation, since aeroplane first flight

(2) For aeroplanes that, before the effective date of this AD, have 

already been inspected in accordance with the instructions of 

Airbus SB A330-53-3168 or Airbus SB A340-53-4174, as applicable 

to aeroplane type:

Within the compliance time defined in Table 2 of this AD, as applicable, 

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

SB A330-53-3168 Revision 02 or Airbus SB A340-53-4174 Revision 02,

whichever occurs first, depending on aeroplane type, configuration and 

utilisation, accomplish a HFEC inspection of the upper shell structure 

between FR80 and FR86 in accordance with the instructions of Airbus 

SB A330-53-3168 Revision 02 or Airbus SB A340-53-4174 Revision 02,

as applicable to aeroplane type.
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Table 2 – First inspection after the effective date of this AD

Compliance time (whichever occurs later, C or D)

C

Within the new interval, as defined in Airbus SB A330-53-

3168 Revision 02 or Airbus SB A340-53-4174 Revision 02, 

depending on aeroplane type, configuration and utilisation to 

be counted from the last inspection

D

Within 12 months after the effective date of this AD but 

without exceeding the previous value as defined in Airbus SB

A330-53-3168 Revision 01 or Airbus SB A340-53-4174 

Revision 01, depending on aeroplane type, configuration and 

utilisation to be counted from the last inspection

(3) If, during any HFEC inspection as required by paragraph (1) or (2) of this 

AD, a crack less than 10 mm in length is detected, depending on crack 

length, aeroplane configuration and utilisation, accomplish the following 

actions:

(3.1) Amend the interval of repetitive HFEC inspection, as required by 

paragraph (1) or (2) as applicable, as defined in Airbus SB 

A330-53-3168 Revision 02 or Airbus SB A340-53-4174 Revision 

02, as applicable to aeroplane type, configuration and utilisation,

and

(3.2) Contact Airbus for approved repair instructions and within the next

[or second] reduced interval as defined in Airbus SB A330-53-

3168 Revision 02 or Airbus SB A340-53-4174 Revision 02, as 

applicable to aeroplane type, configuration and utilisation,

accomplish those instructions accordingly. Accomplishment of a 

repair for a specific area, as required by this paragraph, 

constitutes terminating action for the repetitive HFEC inspections, 

as required by paragraph (1) or (2) of this AD, as applicable, for 

that specific repaired area only. The need and definition of 

subsequent repetitive inspections (if any) for that specific repaired 

area are defined in the applicable Airbus Repair Design Approval 

Sheet (RDAS).

(4) If, during any HFEC inspection as required by paragraph (1) or (2) of this 

AD, a crack equal to or more than 10 mm in length is detected, before

next flight, contact Airbus for approved repair instructions and 

accomplish those instructions accordingly. Accomplishment of a repair 

for a specific area, as required by this paragraph, constitutes terminating 

action for the repetitive HFEC inspections, as required by paragraph (1) 

or (2) of this AD, as applicable, for that specific repaired area only. The 

need and definition of subsequent repetitive inspections (if any) for that 

specific repaired area are defined in the applicable Airbus RDAS.

(5) [Deleted]

(6) Modification of an aeroplane in accordance with the instructions of 

Airbus SB A330-53-3159 (at any revision) or Airbus SB A340-53-4165

(at any revision) constitutes terminating action for the repetitive HFEC 

inspections as required by paragraph (1) or (2) or (3.1) of this AD, as 

applicable for that aeroplane.

Part B – A330-200 aeroplanes:

(7) Within the compliance time as defined in Table 3 of this AD, inspect and 

modify the aeroplane upper shell structure between FR80 and FR86 in 

accordance with the instructions of Airbus SB A330-53-3160 Revision 
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03.

Table 3

Compliance time (whichever occurs later, E or F)

E

Within the threshold defined in Airbus SB A330-53-3160 

Revision 03, depending on WV and aeroplane utilisation, since 

aeroplane first flight

F

Within 12 months after the effective date of this AD, but without 

exceeding the previous threshold as defined in Airbus 

SB A330-53-3160 Revision 02, since aeroplane first flight

(8) If, during the inspection as required by paragraph (7) of this AD, any 

crack is detected, before next flight, contact Airbus to obtain approved 

repair instructions and accomplish those instructions accordingly, 

concurrent with the modification as required by paragraph (7) of this AD.

(9) Inspection and modification of an aeroplane upper shell structure 

between FR80 and FR86, accomplished before the effective date of this 

AD in accordance with the instructions of Airbus SB A330-53-3160 at 

original issue or Revision 01 or Revision 02, are acceptable to comply 

with the requirements of paragraph (7) of this AD for that aeroplane.

Part C – A340-300 aeroplanes, only WV 027:

(10) Before accumulation of 14 200 FC from aeroplane first flight, inspect and 

modify the aeroplane upper shell structure between FR80 and FR86 in 

accordance with the instructions of Airbus SB A340-53-4172.

(11) If, during the inspection as required by paragraph (10) of this AD, any 

crack is detected, before next flight, contact Airbus to obtain approved

repair instructions and accomplish those instructions accordingly, 

concurrent with the modification as required by paragraph (10) of this 

AD.

Ref. Publications: Airbus SB A330-53-3159 original issue dated 19 September 2007, or Revision 

01 dated 15 June 2009, or Revision 02 dated 29 March 2010.

Airbus SB A330-53-3160 original issue dated 09 July 2007, or Revision 01 

dated 28 April 2009, or Revision 02 dated 29 March 2010, or Revision 03 

dated 06 January 2012.

Airbus SB A330-53-3168 original issue dated 19 September 2007, or Revision 

01 dated 15 February 2008, or Revision 02 dated 21 December 2011.

Airbus SB A340-53-4165 original issue dated 19 September 2007, or Revision 

01 dated 17 June 2009, or Revision 02 dated 29 March 2010.

Airbus SB A340-53-4172 original issue dated 10 July 2007, or Revision 01 

dated 08 July 2009.

Airbus SB A340-53-4174 original issue dated 19 September 2007, or Revision 

01 dated 15 February 2008, or Revision 02 dated 21 December 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. The original issue of this AD was posted on 04 December 2013 as PAD 

13-180 for consultation until 01 January 2014. 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.
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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.