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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0016

Date: 16 January 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 aeroplanes

TCDS Number: EASA A.004

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2006-0266 dated 30 August 2006.

ATA 53 Fuselage – Frame 53.3 Circumferential Joint – Reinforcement

Manufacturer(s): Airbus

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-243, A330-301,

A330-321, A330-322, A330-323, A330-341, A330-342 and A330-343 

aeroplanes, all manufacturer serial numbers, except those on which Airbus

modification 49202 has been embodied in production.

Reason: During the fatigue tests (EF2) of the Airbus A330 test fuselage, initiation and

development of cracks were evidenced at the circumferential joint of frame 

53.3.

This condition, if not corrected, could lead to a reduction in the structural 

integrity of the fuselage.

EASA issued AD 2006-0266, which took over the requirements of DGAC 

France AD F-2003-415 for A330-300 pre-mod 41652S11819, and required

reinforcement of the circumferential joint of frame 53.3 by application of Airbus 

Service Bulletin (SB) A330-53-3143 on A330-300 post modification

41652S11819 and pre-mod 49202, and all A330-200 pre-mod 49202 in order to 

improve the fatigue life.

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

evaluation taking into account the aeroplane utilisation, the thresholds for the 

reinforcement were reassessed and the conclusion is that some thresholds 

must be reduced. 

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

2006-0266, which is superseded, and requires reinforcement of structure of the 

centre fuselage at the upper circumferential joint of frame 53.3 within the new 
EASA AD No.: 2013-0016

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thresholds.

Effective Date: 30 January 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) For A330-301, A330-321, A330-322, A330-323, A330-341, A330-342 and 

A330-343 aeroplanes on which Airbus modification 41652S11819 has 

NOT been embodied in production: 

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

structure of the centre fuselage at the upper circumferential joint of frame 

53.3 (between Left Hand (LH) stringer 13 and Right Hand (RH) stringer 13)

in accordance with the instructions of SB A330-53-3127 Revision 02.

Table 1 – Compliance Time

Compliance time (whichever occurs later between A and B)

A

Within the threshold defined in Airbus SB A330-53-3127 Revision 

02, depending on aeroplane configuration and utilisation and to be 

counted from the aeroplane first flight

B

Within 24 months after the effective date of this AD but without 

exceeding 14 700 Flight Cycles (FC) or 51 400 Flight Hours (FH) 

(the previous threshold defined in SB A330-53-3127 Revision 01) to 

be counted from the aeroplane first flight, whichever occurs first

Note: Modification of an aeroplane in accordance with Airbus SB A330-53-3127 

at original issue is not acceptable to comply with the requirement of paragraph 

(1) of this AD.

(2) For all A330-200 and A330-300 aeroplanes [as listed in the

applicability of this directive] on which Airbus modification 

41652S11819 has been embodied in production:

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

structure of the centre fuselage at the upper circumferential joint of frame 

53.3 (between LH stringer 13 and RH stringer 13) in accordance with the 

instructions of SB A330-53-3143 Revision 05.

Table 2 – Compliance Time

Compliance time (whichever occurs later between C and D)

C Within the threshold defined in Airbus SB A330-53-3143 Revision 

05, depending on aeroplane configuration and utilisation and to be 

counted from the aeroplane first flight

D Within 24 months after the effective date of this AD but without 

exceeding 17 600 FC or 61 600 FH (the previous threshold defined

in SB A330-53-3143 Revision 03) to be counted from the aeroplane 

first flight, whichever occurs first

(3) Reinforcement of the structure of the centre fuselage at the upper 

circumferential joint of frame 53.3 (between LH stringer 13 and RH stringer 

13) accomplished on an aeroplane, before the effective date of this AD, in 

accordance with Airbus SB A330-53-3127 at Revision 01 or SB A330-53-

3143 from original issue to Revision 04, is acceptable to comply with the 

requirements of paragraph (1) or (2) of this AD, as applicable.

Ref. Publications: Airbus SB A330-53-3127 Revision 01 dated 21 November 2003, or Revision 02 

dated 07 December 2011.

Airbus SB A330-53-3143 at original issue 24 December 2004, or Revision 01 

dated 29 June 2006, or Revision 02 dated 31 August 2010, or Revision 03 
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dated 03 March 2011, or Revision 04 dated 06 December 2011, or Revision 05 

dated 29 May 2012.

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. This AD was posted on 13 November 2012 as PAD 12-143 for consultation 

until 11 December 2012. 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.