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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0010R1

Date: 05 May 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 A340-200/-300 aeroplanes

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

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2014-0010 dated 08 January 2014, which superseded

EASA AD 2010-0024 dated 12 February 2010.

ATA 57 Wings – Centre Wing Box Keel Beam Fastener Holes at Frame 40 

– Inspection

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), except 

those on which Airbus modification (Mod) 55306 or 55792 has been 

embodied in production.

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

aeroplanes, all MSN, except those on which Airbus Mod 55306 or 55792 has 

been embodied in production and except those on which Airbus Repair 

Drawing R57115053 or R57115051 or R57115047 has been embodied in 

service on both right-hand (RH) and left-hand (LH) sides.

Reason: During A330 and A340 aeroplanes fatigue tests, cracks were detected on the 

RH and LH sides between the crossing area of the keel beam fitting and the 

front spar of the Centre Wing Box (CWB).

This condition, if not detected and corrected, could lead to keel beam rupture 

which would affect the structural integrity of the area.

Prompted by this potential unsafe condition, EASA issued AD 2006-0315

(later revised to R1) to require repetitive special detailed inspections (SDI) on 

the horizontal flange of the keel beam in the area of first fastener hole aft of 

Frame (FR) 40 in order to maintain the structural integrity of the aeroplane.

After that AD was issued, EASA issued AD 2010-0024, retaining the 

inspection requirements of EASA AD 2006-0315R1, which was superseded, 

extending the applicability to aeroplanes with Airbus Mod 49202 embodied, 
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and reducing the inspection thresholds and intervals.

Since that AD was issued, a new fatigue and damage tolerance evaluation

has been conducted by Airbus, which concluded that due to the aeroplane 

utilisation, the current inspection threshold and intervals have to be modified.

In addition, it was determined that the rototest inspection of fastener hole Nr 

6, necessary to ensure that no crack was left unrepaired at the time of 

fastener hole cold working, was inadvertently not included in Revisions 01 and 

02 of both Airbus Service Bulletin (SB) A330-57-3098 and SB A340-57-4106.

Prompted by these findings, EASA issued AD 2014-0010, retaining the 

requirements of EASA AD 2010-0024, which was superseded, and redefined

the inspection thresholds and intervals, and added a one-time ultrasonic 

inspection of fastener hole Nr 6 in the junction keel beam fitting at FR40 on 

both LH and RH side.

Following issuance of EASA AD 2014-0010, it was identified that there was a 

need for clarifications, by amending paragraph (1), with the introduction of a 

statement and adding paragraphs (10) and (11).

Effective Date: Revision 1: 12 May 2014

Original issue: 22 January 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Re-statement of EASA AD 2010-0024 requirements:

(1) For aeroplanes already modified before 26 February 2010 [the effective 

date of EASA AD 2010-0024] in accordance with the instructions of 

Airbus SB A330-57-3098 at original issue or Airbus SB A340-57-4106 at 

original issue, as applicable to aeroplane type, and on which a crack was 

detected at hole Nr 5 before oversizing of the keel beam (in accordance 

with instructions in paragraph 3.B (1)(b) step 3 of Airbus SB A330-57-

3098 at original issue or Airbus SB A340-57-4106 at original issue), 

within 30 days after 26 February 2010 [the effective date of EASA AD 

2010-0024], contact Airbus for further instructions (additional work) and 

apply the associated instructions within the compliance time defined in 

these instructions.

The new requirements of this AD do not apply to aeroplanes affected by 

this paragraph and do not apply also to aeroplanes that were already 

modified before 26 February 2010 [the effective date of EASA AD 2010-

0024] in accordance with the instructions of Airbus SB A330-57-3098 at 

original issue or Airbus SB A340-57-4106 at original issue, as applicable 

to aeroplane type, and on which no crack was detected at hole Nr 5 

before oversizing of the keel beam (in accordance with the instructions in 

paragraph 3.B (1)(b) step 3 of Airbus SB A330-57-3098 at original issue 

or Airbus SB A340-57-4106 at original issue).

New requirements of this AD:

(2) For aeroplanes that have never been inspected in accordance with 

the instructions of Airbus SB A330-57-3081 or SB A340-57-4089, 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 defined in Airbus SB A330-57-3081 Revision 05 or SB 

A340-57-4089 Revision 05, as applicable to aeroplane type, depending 

on aeroplane configuration and utilisation, accomplish a SDI of the 

fastener hole(s) of the horizontal flange of the keel beam located on 

FR40 datum on RH and/or LH side of the fuselage, in accordance with 

the instructions of Airbus SB A330-57-3081 Revision 05 or SB A340-57-

4089 Revision 05, as applicable to aeroplane type.
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Table 1 – Inspection threshold for

pre-SB A330-57-3081/SB A340-57-4089 aeroplanes

Compliance time (whichever occurs later, A or B)

A

Before exceeding the threshold(s) as defined in Airbus SB A330-

57-3081 Revision 05 or SB A340-57-4089 Revision 05 since 

aeroplane first flight, as applicable to aeroplane type, depending 

on aeroplane configuration and utilisation.

B

Within 12 months after 22 January 2014 [the effective date of 

this AD at original issue], but without exceeding the previous 

threshold as defined in Airbus SB A330-57-3081 Revision 04 or 

SB A340-57-4089 Revision 04, as applicable to aeroplane type.

(3) Inspections, accomplished before the effective date of this AD in 

accordance with the instructions of Airbus Technical Disposition 

Reference F57D03012810 or 582.0651/2002 (either with no findings, or 

with discrepancies corrected), are acceptable to comply with the initial 

rotating probe inspection, which is part of the actions as required by 

paragraph (2) of this AD.

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

inspected in accordance with the instructions of Airbus SB A330-57-

3081 or SB A340-57-4089, as applicable to aeroplane type: Within the 

compliance time defined in Table 2 of this AD, and, thereafter, at intervals 

not to exceed the values defined in Airbus SB A330-57-3081 Revision 05

or Airbus SB A340-57-4089 Revision 05, as applicable to aeroplane type,

depending on aeroplane configuration and utilisation, accomplish a SDI

of the fastener hole(s) of the horizontal flange of the keel beam located 

on FR40 datum on RH and/or LH side of the fuselage, in accordance with 

the instructions of Airbus SB A330-57-3081 Revision 05 or Airbus SB 

A340-57-4089 Revision 05, as applicable to aeroplane type.

Table 2 – Inspection threshold for

post-SB A330-57-3081/SB A340-57-4089 aeroplanes

Compliance time (whichever occurs later, C or D)

C

Within the new interval(s) as defined in Airbus SB A340-57-4089 

Revision 05 or Airbus SB A330-57-3081 Revision 05, since the 

previous inspection, as applicable to aeroplane type, depending 

on aeroplane configuration and utilisation.

D

Within 12 months after 22 January 2014 [the effective date of 

this AD at original issue], but without exceeding the previous 

value(s) as defined in Airbus SB A340-57-4089 Revision 04 or 

Airbus SB A330-57-3081 Revision 04, as applicable to 

aeroplane type.

(5) If, during any SDI as required by paragraph (2) or (4) of this AD, as 

applicable, no crack is detected, within the compliance time defined in

Airbus SB A330-57-3081 Revision 05 or Airbus SB A340-57-4089 

Revision 05, as applicable to aeroplane type, accomplish the corrective 

actions as indicated (or incorporated by reference) in the applicable SB.

(6) For aeroplanes in configuration 2 as defined in Airbus SB A330-57-3098 

Revision 01 or Revision 02, or Airbus SB A340-57-4106 Revision 01 or 

Revision 02, as applicable to aeroplane type, that have already been 

modified, before the effective date of this AD, in accordance with the 

instructions of Airbus SB A330-57-3098 Revision 01 or Revision 02, or 

Airbus SB A340-57-4106 Revision 01 or Revision 02, as applicable to 

aeroplane type, and on which the hole Nr 5 has already been bushed 

before embodiment of Airbus SB A330-57-3098 or Airbus SB A340-57-
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4106, as applicable to aeroplane type, or on which a crack has been 

found on hole Nr 5 during embodiment of Airbus SB A330-57-3098 or

Airbus SB A340-57-4106, as applicable to aeroplane type, within the 

compliance time specified in Table 3 of this AD, accomplish an ultrasonic 

inspection at hole Nr 6 in the junction keel beam fitting at Frame 40 LH 

and RH side, in accordance with the instructions of Airbus SB A330-57-

3117 or Airbus SB A340-57-4126, as applicable to aeroplane type.

Table 3 – One-time ultrasonic inspection

Compliance time (whichever occurs later, E or F)

E

Within the threshold defined in Airbus SB A330-57-3117 or 

Airbus SB A340-57-4126, as applicable to aeroplane type, 

depending on aeroplane configuration and utilisation. 

F

For A330: within 2 400 flight cycles (FC) or 24 months after 22 

January 2014 [the effective date of this AD at original issue],

whichever occurs first.

For A340: within 1 300 FC or 24 months after 22 January 2014 

[the effective date of this AD at original issue], whichever occurs 

first.

(7) If, during any inspection as required by paragraph (2), (4) or (6) of this 

AD, as applicable, any crack is detected, before next flight, contact Airbus 

for approved repair instructions and, within the defined compliance time,

accomplish those instructions accordingly. The need and definition of any 

subsequent repetitive inspections can be defined in the relevant repair 

instructions.

Note: Inspection and, depending on findings, accomplishment of corrective 

action(s) as required by paragraphs (6) and (7) of this AD, are equal to the 

additional work as specified in Airbus SB A330-57-3098 Revision 03, or 

Airbus SB A340-57-4106 Revision 03, as applicable to aeroplane type. See 

also paragraph (11) of this AD.

(8) For aeroplanes on which a rototest at hole Nr 6 has been accomplished 

before cold working during accomplishment of Airbus SB A330-57-3098 

Revision 01 or Revision 02 or Airbus SB A340-57-4106 Revision 01 or 

Revision 02, as applicable to aeroplane type, the ultrasonic inspection of 

paragraph (6) of this AD is not required.

(9) Modification of an aeroplane in accordance with the instructions of Airbus 

SB A330-57-3090 (any revision), or Airbus SB A340-57-4098 (any 

revision), or Airbus SB A330-57-3098 Revision 03, or Airbus SB A340-

57-4106 Revision 03, as applicable to aeroplane type, constitutes 

terminating action for the requirements of this AD for that aeroplane.

(10) For aeroplanes that have been modified before 22 January 2014 [the 

effective date of this AD at original issue] in accordance with the 

instructions of Airbus SB A330-57-3098 Revision 01 or Revision 02, or 

Airbus SB A340-57-4106 Revision 01 or Revision 02, as applicable to 

aeroplane type, no actions are required by this AD, except for aeroplanes

that are affected by the requirements of paragraph (6) of this AD.

(11) Accomplishment on an aeroplane of the inspection as required by 

paragraph (6) and, depending on findings, corrective action as required 

by paragraph (7) of this AD, constitutes terminating action for the 

requirements of this AD for that aeroplane.

Ref. Publications: Airbus SB A330-57-3081 original issue dated 30 October 2003, or Revision 

01 dated 18 May 2004, or Revision 02 dated 24 January 2006, or Revision 03 

dated 31 July 2009, or Revision 04 dated 31 May 2011, or Revision 05 dated 

13 November 2012.
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Airbus SB A340-57-4089 original issue dated 30 October 2003, or Revision 

01 dated 02 March 2004, or Revision 02 dated 24 January 2006, or Revision 

03 dated 31 July 2009, or Revision 04 dated 31 May 2011, or Revision 05 

dated 13 November 2012.

Airbus SB A330-57-3098 original issue dated 30 August 2007, or Revision 

01 dated 31 July 2009, or Revision 02 dated 15 June 2011, or Revision 03 

dated 24 September 2012.

Airbus SB A340-57-4106 original issue dated 30 August 2007, or Revision 01 

dated 31 July 2009, or Revision 02 dated 15 June 2011, or Revision 03 dated 

24 September 2012.

Airbus SB A330-57-3090 original issue dated 27 March 2006, or Revision 

01 dated 15 June 2011.

Airbus SB A340-57-4098 original issue dated 27 March 2006, or Revision 

01 dated 15 June 2011.

Airbus SB A330-57-3117 original issue dated 25 January 2013.

Airbus SB A340-57-4126 original issue dated 25 January 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. The original issue of this AD was posted on 26 November 2013 as PAD 

13-174 for consultation until 24 December 2013. No comments were 

received during the 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.