EASA AD No.: 2013-0302

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0302

Date: 19 December 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):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 55 Stabilizers – Composite Rudder Side Shell Sandwich Repair –

Inspection

Manufacturer(s): Airbus (Formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, A319-111, A319-112,

A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-211, 

A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, A320-233, 

A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231

and A321-232 aeroplanes, all manufacturer serial numbers.

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

rudder installed on an A310 aeroplane. Investigation results revealed that this 

disbonding had started from a skin panel area, previously repaired in-service, in 

accordance with Structural Repair Manual (SRM) instructions. The initial 

damage was identified as a disbonding between the core and the skin of the 

repaired area. This damage was not visually detectable and likely propagated

during normal operation due to the variation of pressure during ground-airground cycles.

Composite rudder side shell panels are also installed on A320 family 

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.

To address this potential unsafe condition, Airbus issued Service Bulletin (SB) 

A320-55-1041 to provide instructions to inspect and correct any affected 

composite rudder side shell panels.
EASA AD No.: 2013-0302

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

inspection of each rudder that have received a composite rudder side shell 

panel repair, and, depending on the findings, accomplishment of applicable 

corrective and follow-up actions.

Effective Date: 02 January 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 

maintenance records of each rudder to determine if any composite side 

shell panel repair has been accomplished 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) A320-55-1041, within 24 

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

thermography inspection, limited to the repaired area(s), in accordance 

with the instructions of Airbus SB A320-55-1041.

(3) For each 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 location(s) in accordance with the instructions of Airbus SB 

A320-55-1041. 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 rework 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 A320-55-

1041, accomplish supplemental inspections and/or applicable corrective 

actions and terminating actions in accordance with the instructions of 

Airbus SB A320-55-1041, or in accordance with Airbus approved specific 

instructions, as applicable.

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

TS-1001 to TS-1639 inclusive, TS-2001 to TS-5890 inclusive, or TS-5927, 

are not affected by the requirements of paragraphs (2), (3) and (4) of this 

AD, provided that it is determined that no repairs, in accordance with SRM 

procedures as identified in paragraph (2) of this AD, have 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 composite side 

shell panel 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 A320-55-1041.

Ref. Publications: Airbus SB A320-55-1041 original issue, date 26 November 2012.

The use of later approved revisions of this document 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.
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2. This AD was posted on 02 September 2013 as PAD 13-133 for consultation 

until 30 September 2013. 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.

4. For any question concerning the technical content of the requirements in 

this AD, please contact: AIRBUS-Airworthiness Office-EIAS,

Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com.