EASA AD No.: 2013-0039

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0039

Date: 26 February 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):

A300-600 and A310 aeroplanes

TCDS Number: France n° 145

Foreign AD: Not applicable

Supersedure: None

ATA 55 Stabilizers – Rudder Side Panel Along the Z-Profile – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300-600 and A310 aeroplanes, all models, all Manufacturer Serial 

Numbers, except aeroplanes on which mod 08827 has been embodied in 

production. 

Reason: One A310 operator found substantial inner skin disbonding damage on a

rudder that was previously inspected in accordance with the instructions of 

Airbus Service Bulletin (SB) A310-55-2044. The results of the subsequent 

investigation revealed that the most probable cause of this damage was a blunt 

impact with no visible damage from outside during the rudder handling.

Damage like this might grow with pressure variation during ground-air-ground 

cycles, and tests performed with other rudders showed a rapid propagation of 

damage during artificial pressure cycling.

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

of the rudder.

To address this potential unsafe condition, Airbus issued Alert Operators

Transmission (AOT) A55W002-12, pending Aircraft Maintenance Manual 

(AMM) 27-21-21 PB401 revision to update rudder handling procedures.

For the reasons described above, this AD requires ultrasonic test (UT) 

inspections of the affected rudders to detect signs of disbonding and,

depending on findings, accomplishment of applicable corrective action(s).

Effective Date: 12 March 2013
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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 3 months after the effective date of this AD, in accordance with the 

instructions of Airbus Alert Operator Transmission (AOT) A55W002-12,

accomplish the following actions:

(1.1) Identify the Part Number (P/N) and serial number (s/n) of the 

installed rudder assembly. If the P/N and/or s/n cannot be identified, 

contact Airbus for identification advice.

(1.2) For a rudder assembly having P/N A55471500, accomplish an UT

inspection of the rudder side panel along the Z-profile and in the 

booster area.

(2) If, during the inspection as required by paragraph (1.2) of this AD, any 

disbonding is detected, before next flight, differentiate the disbonding from 

other possible damage by accomplishing an Elasticity of Laminate Checker

Inspection to detect external and internal disbonding, and accomplish a

Woodpecker or Tap test inspection to detect external disbonding.

If damage is confirmed as disbonding, accomplish corrective actions as 

required by paragraph (3) or (4) of this AD, depending on the size of the 

disbonding. 

If the detected discrepancies are confirmed as other type(s) of damage 

(e.g. liquid ingress), before next flight, accomplish a repair in accordance 

with the instructions as provided in the applicable Airbus Structural Repair 

Manual.

(3) For disbonding, equal to or less than 50 mm width, and equal to or less 

than 150 mm length, before next flight, vent the core in accordance with an 

approved procedure (which must be requested from Airbus) and, within 10 

days after the inspection as required by paragraph (1.2) of this AD, send a 

detailed damage report to Airbus, request permanent repair instructions 

and, within 100 flight cycles after the UT inspection as required by 

paragraph (1.2) of this AD, accomplish those instructions accordingly.

(4) For disbonding, exceeding 50 mm width, or exceeding150 mm length, 

before next flight, send a detailed damage report to Airbus, request 

approved instructions for corrective actions and accomplish those 

instructions accordingly.

(5) A rudder which has been inspected on an aeroplane, before the effective 

date of this AD, in accordance with the instructions of Airbus SB A300-55-

6043 Revision 01 or SB A310-55-2044 Revision 01, as applicable to 

aeroplane model, but which has been removed and re-installed on an

aeroplane after this inspection, must be inspected, as required by 

paragraph (1) of this AD.

(6) After the effective date of this AD, for each installation of a P/N A55471500

rudder on an aeroplane, before next flight after installation, inspect the 

rudder as required by paragraph (1.2) of this AD and, depending on 

findings, accomplish corrective actions as required by paragraph (3) or (4)

of this AD, depending on the size of the disbonding.

Ref. Publications: Alert Operator Transmission A55W002-12 dated 13 December 2012;

Airbus SB A300-55-6043 Revision 01 dated 03 December 2007;

Airbus SB A310-55-2044 Revision 01 dated 03 December 2007;

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 14 December 2012 as PAD 12-160 for consultation 
EASA AD No.: 2013-0039

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until 11 January 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 SAS – EAW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, 

Fax: + 33 5 61 93 44 51)