EASA AD No : 2010-0002 

EASA Form 110 Page 1/5 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0002 

Date: 05 January 2010 

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 EC 1702/2003, Part 21A.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]. 

Type Approval Holder’s Name : 

AIRBUS

Type/Model designation(s) : 

A310 and A300-600 aeroplanes 

TCDS Number: France N°145 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2009-0166 dated 31 July 2009. 

ATA 55 Stabilizers – Rudder Side Shell Skin – Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: 

Airbus A310 and A300-600 aeroplanes, all certified models, all manufacturer 

serial numbers, if equipped with a Carbon Fibre Reinforced Plastic (CFRP) 

rudder having a Part Number (P/N) and serial number (s/n) as listed in 

Appendix A of this AD. 

Reason: 

Surface defects were visually detected on the rudder of an A319 and an A321 

in-service aeroplane. Investigation has determined that the defects reported on 

both rudders corresponded to areas that had been reworked in production. The 

investigation confirmed that the defects were as a result of de-bonding between 

the skin and honeycomb core. Such reworks were also performed on some 

rudders fitted on A310 and A300-600 aeroplanes. 

An extended de-bonding, if not detected and corrected, may degrade the 

structural integrity of the rudder. The loss of the rudder leads to degradation of 

the handling qualities and reduces the controllability of the aeroplane. 

To address this unsafe condition, EASA issued AD 2009-0166 to require 

inspections of specific areas and, depending on findings, the application of 

corrective actions for those rudders where production reworks have been 

identified. 

This new AD retains the requirement of EASA AD 2009-0166, which is 

superseded, and requires for the vacuum loss hole restoration : 

- a local ultrasonic inspection for reinforced area instead of the local 

thermographic inspection, which is maintained for non-reinforced areas, and 

- additional work performance for rudders on which this thermographic 

inspection has been performed in the reinforced area.
EASA AD No : 2010-0002 

EASA Form 110 Page 2/5 

Effective Date: 19 January 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated: 

(1) For rudders with a honeycomb core density of 24 kg/m3 as identified in 

Appendix A to this AD, apply the following actions for the locations defined 

in Airbus All Operators Telex (AOT) A310-55A2048 Revision 02 or AOT 

A300-55A6047 Revision 02, as applicable: 

(1.1) Reinforced area location: 

 Unless already accomplished, within 8 months from 14 August 2009 

[the effective date of AD 2009-0166], perform Vacuum Loss 

inspection on the rudder reinforced area in accordance with the 

instructions defined in Airbus AOT A310-55A2048 Revision 02 or 

AOT A300-55A6047 Revision 02, as applicable. 

(1.2) Trailing edge area location: 

(1.2.1) Unless already accomplished, within 24 months from 14 

August 2009 [effective date of AD 2009-0166], perform 

Elasticity Laminate Checker inspection on the rudder trailing 

edge area in accordance with instructions defined in Airbus 

AOT A310-55A2048 Revision 02 or AOT A300-55A6047 

Revision 02, as applicable. 

(1.2.2) Repeat two further times the inspection as defined in 

paragraph (1.2.1) of this AD at intervals not to exceed 4 500 

flight cycles (FC) but not less than 4 000 FC from the last 

inspection. 

(1.3) Other areas locations (lower rib/upper edge/leading edge/other 

locations): 

(1.3.1) Unless already accomplished, within 8 months from 14 

August 2009 [the effective date of AD 2009-0166], perform 

Elasticity Laminate Checker inspection on the other areas 

(lower rib/upper edge/leading edge/other locations) in 

accordance with instructions defined in Airbus AOT A310-

55A2048 Revision 02 or AOT A300-55A6047 Revision 02, as 

applicable. 

(1.3.2) Repeat the inspection defined in paragraph (1.3.1) of this AD 

at intervals not exceeding 8 months from the last inspection. 

(1.3.3) Unless already accomplished, within 24 months from 14 

August 2009 [the effective date of AD 2009-0166], perform 

Vacuum Loss inspection on these areas (lower rib/upper 

edge/leading edge/other locations) in accordance with the 

instructions defined in Airbus AOT A310-55A2048 Revision 

02 or AOT A300-55A6047 Revision 02, as applicable. 

(1.3.4) Accomplishment of the inspection required by paragraph 

(1.3.3) cancels the initial and repetitive inspections required 

by paragraph (1.3.1) and (1.3.2) of this AD. 

(1.4) In case of findings during the inspections as required by paragraphs 

(1.1), (1.2) or (1.3) of this AD, before next flight, contact Airbus to get 

further instructions and apply the associated instructions and 

corrective actions in accordance with the approved data provided. 

(1.5) In case of no findings during the inspections as required by 

paragraphs (1.1) or (1.3.3) of this AD, before next flight, restore the 

vacuum loss holes as per the option selected (temporary restoration 

with self adhesive patches, temporary restoration with resin or 

permanent restoration), in accordance with AOT A310-55A2048 

Revision 02 or AOT A300-55A6047 Revision 02, as applicable, and 

apply associated instructions until performance of permanent 
EASA AD No : 2010-0002 

EASA Form 110 Page 3/5 

restoration. 

(1.6) Within 10 days after accomplishment of each inspection as required 

by paragraphs (1.1), (1.2) and (1.3) of this AD, report the inspection 

results, including no findings, to Airbus. 

(2) For rudders not having a honeycomb core density of 24 kg/m3

 as 

identified in Appendix A to this AD, apply the following actions for the 

locations defined in Airbus AOT A310-55A2048 Revision 02 or AOT 

A300-55A6047 Revision 02, as applicable: 

 For the purpose of this AD a “Reference Date” is 14 August 2009 [the 

effective date of AD 2009-0166] or the date when the rudder will 

accumulate 13 000 FC from its first installation on an aeroplane, whichever 

occurs later.

(2.1) Reinforced area location: 

 Unless already accomplished, within 8 months from the Reference 

Date, perform Vacuum Loss inspection on the rudder reinforced area 

in accordance with instructions defined in Airbus AOT A310-55A2048 

Revision 02 or AOT A300-55A6047 Revision 02, as applicable. 

(2.2) Trailing edge area location: 

(2.2.1) Unless already accomplished, within 24 months from the 

Reference Date, perform Elasticity Laminate Checker 

inspection on the rudder trailing edge area in accordance with 

instructions defined in Airbus AOT A310-55A2048 Revision 

02 or AOT A300-55A6047 Revision 02, as applicable. 

(2.2.2) Repeat two further times the inspection defined in paragraph 

(2.2.1) of this AD at intervals not to exceed 4 500 FC but not 

less than 4 000 FC from the last inspection. 

(2.3) Other areas locations (lower rib/upper edge/leading edge/other 

locations) : 

(2.3.1) Unless already accomplished, within 8 months from the 

Reference Date, perform Elasticity Laminate Checker 

inspection on the other areas (lower rib/upper edge/leading 

edge/other locations) in accordance with instructions defined 

in Airbus AOT A310-55A2048 Revision 02 or AOT A300-

55A6047 Revision 02, as applicable. 

(2.3.2) Repeat the inspection defined in paragraph (2.3.1) of this AD 

at intervals not exceeding 8 months from the last inspection. 

(2.3.3) Unless already accomplished, within 24 months from the 

Reference Date, perform Vacuum Loss inspection on these 

areas (lower rib/upper edge/leading edge/other locations) in 

accordance with instructions defined in Airbus AOT 

A310-55A2048 Revision 02 or AOT A300-55A6047 Revision 

02, as applicable. 

(2.3.4) Accomplishment of the inspection required by paragraph 

(2.3.3) of this AD cancels the initial and repetitive inspections 

required by paragraph (2.3.1) and (2.3.2) of this AD. 

(2.4) In case of findings during the inspections as required by paragraphs 

(2.1), (2.2) or (2.3) of this AD, before next flight, contact Airbus to get 

further instructions and apply the associated instructions and 

corrective actions in accordance with the approved data provided. 

(2.5) In case of no findings during the inspections as required by 

paragraphs (2.1) or (2.3.3) of this AD, before next flight, restore the 

vacuum loss holes as per the option selected (temporary restoration 

with self adhesive patches, temporary restoration with resin or 

permanent restoration), in accordance with AOT A310-55A2048 

Revision 02 or AOT A300-55A6047 Revision 02, as applicable, and 
EASA AD No : 2010-0002 

EASA Form 110 Page 4/5 

apply associated instructions until performance of permanent 

restoration. 

(2.6) Within 10 days after accomplishment of each inspection as required 

by paragraphs (2.1), (2.2) and (2.3) of this AD, report the results, 

including no findings, to Airbus. 

(3) All rudders that have passed the inspection, before 14 August 2009 [the 

effective date of AD 2009-0166], in accordance with the instructions of 

Airbus AOT A310-55A2048 at original issue or AOT A300-55A6047 at 

original issue, as applicable, or through Sampling campaign for Rudder 

P/N A554-71500-016-91 (s/n HF-1059) and Rudder P/N A554-71500-014-

00 (s/n HF-1087), are compliant with the associated requirements of 

paragraphs (1) or (2) of this AD for the areas inspected. Additional areas 

requiring inspection are defined in Airbus AOT A310-55A2048 Revision 01 

or AOT A300-55A6047 Revision 01. For these additional areas the 

requirements of paragraphs (1) or (2) of this AD are applicable. For all 

areas, the repetitive inspections required by paragraphs (1) or (2) of this 

AD remain applicable. 

(4) All rudders that have passed the inspection, before the effective date of 

this AD, in accordance with the instructions of Airbus AOT A310-55A2048 

Revision 01 or AOT A300-55A6047 Revision 01, as applicable, are 

compliant with the associated requirements of paragraphs (1) or (2) of this 

AD for the areas inspected. The repetitive inspections required by this AD 

remain applicable. 

(5) For rudders on which temporary restoration with resin or permanent 

vacuum loss hole restoration has been performed before the effective date 

of this AD in reinforced area as per paragraph (1.5) or (2.5) of this AD and 

in accordance with the instructions of Airbus AOT A310-55A2048 at 

original issue or Revision 01 or AOT A300-55A6047 at original issue or 

Revision 01, as applicable, within 4 500 FC from restoration date, perform 

an ultrasonic inspection in accordance with the instructions of Airbus AOT 

A310-55A2048 Revision 02 or AOT A300-55A6047 Revision 02, as 

applicable. 

(6) After the effective date of this AD, do not install any rudder listed in 

Appendix A to this AD on an aeroplane, unless in compliance with the 

requirements of this AD.

Ref. Publications : 

AIRBUS All Operators Telex A310-55A2048 original issue, Revision 01 or 

Revision 02. 

AIRBUS All Operators Telex A300-55A6047 original issue, Revision 01 or 

Revision 02. 

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 27 November 2009 as PAD 09-134 for consultation 

until 25 December. The Comment Response Document can be found at 

http://ad.easa.europa.eu/. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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 93 36 96, Fax: + 33 5 61 93 44 51). 
EASA AD No : 2010-0002 

EASA Form 110 Page 5/5 

Appendix A 

 

Rudder Part 

Number

Affected rudder 

Serial Number

Core density 

24kg.m-3

A554-71500-016-91 HF-1017 X

A554-71500-016-91 HF-1020

A554-71500-016-91 HF-1059

A554-71500-016-91 HF-1061

A554-71500-016-91 HF-1064

A554-71500-014-00 HF-1087 X

A554-71500-014-00 HF-1119 X

A554-71500-016-00 HF-1189 X

A554-71500-016-00 HF-1203 X

A554-71500-016-00 HF-1266 X

A554-71500-026-00 TS-1405

A554-71710-000-00 TS-2001

A554-71710-000-00 TS-2004

A554-71710-000-00 TS-2007

A554-71710-000-00 TS-2009

A554-71710-000-00 TS-2011

A554-71710-000-00 TS-2012

A554-71710-000-00 TS-2013

A554-71710-000-00 TS-2014

A554-71710-000-00 TS-2016

A554-71710-000-00 TS-2017

A554-71710-000-00 TS-2018

A554-71710-000-00 TS-2020

A554-71710-000-00 TS-2021

A554-71710-000-00 TS-2022

A554-71710-000-00 TS-2024

A554-71710-000-00 TS-2025

A554-71710-000-00 TS-2026

A554-71710-000-00 TS-2028

A554-71710-000-00 TS-2029

A554-71710-002-00 TS-2031

A554-71710-002-00 TS-2032

A554-71710-002-00 TS-2035

A554-71710-002-00 TS-2040

A554-71710-002-00 TS-2041

A554-71710-002-00 TS-2044

A554-71710-002-00 TS-2046

A554-71710-004-00 TS-2050

A554-71710-004-00 TS-2056

A554-71710-004-00 TS-2058

A554-71710-004-00 TS-2060

A554-71710-004-00 TS-2062

A554-71710-004-00 TS-2065

A554-71710-004-00 TS-2066

A554-71710-004-00 TS-2074

A554-71710-004-00 TS-2075

A554-71710-004-00 TS-2076

A554-71710-004-00 TS-2079