EASA AD No.: 2014-0033

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0033

Date: 04 February 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 aeroplanes

TCDS Number: EASA.A.04, EASA.A.15

Foreign AD: Not applicable

Supersedure: None

ATA 55 Stabilizers – Rudder Side Shell Sandwich Repair – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

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

A330-243F, 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).

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

A340-541, A340-542, A340-642 and A340-643 aeroplanes, all MSN.

Reason: A case of skin disbonding was reported on a composite side panel of a rudder 

installed on an A310 aeroplane. 

The investigation results revealed that this disbonding started from a skin panel 

area previously repaired in-service in accordance with the Structural Repair 

Manual (SRM).

The initial damage has been identified as a disbonding between the core and 

skin of the repaired area. This damage may not be visually detectable and likely 

propagates during normal operation due to the variation of pressure during 

ground-air-ground cycles.

Composite rudder side shell panels are also installed on A330 and A340

aeroplanes, which may have been repaired in-service using a similar method.

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

of the rudder, possibly resulting in reduced control of the aeroplane.

For the reasons described above, this AD requires a one-time thermography

inspection of a repaired rudder or a rudder whose maintenance records are 

incomplete and, depending on findings, accomplishment of applicable 
EASA AD No.: 2014-0033

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corrective and follow-up actions.

Effective Date: 18 February 2014

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 24 months after the effective date of this AD, check the available 

maintenance records of the rudder to determine if any composite side shell 

panel repair has been accomplished on the rudder since first installation on 

an aeroplane, e.g. in accordance with an Airbus Repair Approval Sheet, 

SRM instructions or any other approved repair solution.

(2) If, based on available maintenance record analysis, a repair is identified as 

affected in accordance with figure A-GBBAA (Sheet 01 and 02) or figure AGBCAA (Sheet 02) of Airbus Service Bulletin (SB) A330-55-3043, Airbus 

SB A340-55-4039 or Airbus SB A340-55-5007, as applicable, within 24 

months after the effective date of this AD, accomplish a thermography 

inspection limited to the repaired area(s) in accordance with the 

instructions of Airbus SB A330-55-3043, SB A340-55-4039 or SB A340-55-

5007, as applicable.

(3) For a rudder, where maintenance records are not available or incomplete, 

within 24 months after the effective date of this AD, accomplish a 

thermography inspection on complete side shells to identify and mark the 

repair(s) in accordance with the instructions of Airbus SB

A330-55-3043, SB A340-55-4039 or SB A340-55-5007, as applicable.

Not later than 3 months before accomplishment of the thermography 

inspection, as required by this paragraph, report the undocumented rudder 

by serial number (s/n) to Airbus to obtain related rudder manufacturing 

reworked data.

(4) After the inspection, as required by paragraph (2) or (3) of this AD, as 

applicable, depending on findings, within the compliance times and 

intervals defined in Tables 3, 4A, 4B, 4C, 4D and 5 of Airbus SB

A330-55-3043, SB A340-55-4039 or SB A340-55-5007, as applicable, 

accomplish supplemental inspections and / or applicable corrective actions 

and terminating actions in accordance with the instructions of Airbus SB

A330-55-3043, SB A340-55-4039 or SB A340-55-5007, as applicable, or in 

accordance with Airbus approved specific instructions, as applicable.

(5) Aeroplanes fitted with a rudder having s/n which is not in the range s/n 

TS-1001 to TS-1043 inclusive, s/n TS-2001 to TS-2074 inclusive, s/n

TS-3000 to TS-3525 inclusive, s/n TS-4001 to TS-4170 inclusive, s/n

TS-6001 to TS-6246 inclusive or s/n TS-5001 to TS-5138 inclusive, are not 

affected by the requirements of paragraphs (2), (3), (4) of this AD provided

that it is determined that no repair, in accordance with SRM procedures as 

identified in paragraph (2) of this AD, has been accomplished on the 

composite side shell panel of that rudder since first installation on an 

aeroplane.

(6) From the effective date of this AD, in case of rudder replacement, it is 

allowed to install a rudder on an aeroplane, provided that, prior to 

installation, it is determined that the rudder is compliant with the 

requirements of paragraphs (2), (3), (4) and (5) of this AD.

(7) From the effective date of this AD, do not accomplish a side shell repair on 

any rudder using an SRM procedure as identified in figure A-GBBAA 

(Sheet 01 and 02) or figure A-GBCAA (Sheet 02) of Airbus SB A330-55-

3043, Airbus SB A340-55-4039 or Airbus SB A340-55-5007, as applicable.

Ref. Publications: Airbus SB A330-55-3043 original issue dated 07 February 2013.

Airbus SB A340-55-4039 original issue dated 07 February 2013.

Airbus SB A340-55-5007 original issue dated 07 February 2013.
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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 18 September 2013 as PAD 13-143 for consultation 

until 16 October 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.