EASA AD No.: 2010-0144 

EASA Form 110 Page 1/4 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0144

Date: 16 July 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 : None 

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 rudders having a Part 

Number (P/N) and serial number (s/n) as listed in Appendix A, B, C or D to 

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 2010-0002, superseding 

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 addresses the rudder population that has also been reworked 

in production but not included in the applicability of EASA AD 2010-0002.
EASA AD No.: 2010-0144 

EASA Form 110 Page 2/4 

Effective Date: 30 July 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated: 

(1) For rudders as identified in Appendix A and B to this AD, apply 

the following actions for the locations defined in Airbus Service 

Bulletin (SB) A310-55-2049, or Airbus SB A300-55-6048, as 

applicable:

(1.1) “Area 1” location : 

Unless already accomplished, 

- within 8 months after the effective date of this AD for rudders 

listed in Appendix A to this AD, or 

- within 24 months after the effective date of this AD, for rudders 

listed in Appendix B to this AD, 

perform Vacuum Loss inspection on the “area 1” in accordance 

with instructions defined in Airbus SB A310-55-2049, or Airbus SB 

A300-55-6048, as applicable to aeroplane model. 

(1.2) Trailing edge area location: 

(1.2.1) Unless already accomplished, within 24 months after the 

effective date of this AD, perform Elasticity Laminate Checker 

inspection on the rudder trailing edge area in accordance with 

instructions defined in Airbus SB A310-55-2049, or Airbus SB 

A300-55-6048, as applicable to aeroplane model. 

(1.2.2) Repeat two further times the inspection 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. 

(2) For rudders as identified in Appendix C to this AD

(2.1) Unless already accomplished, within 4500 FC but not less than 

4 000 FC from the last sampling inspection, perform an Elasticity 

Laminate Checker inspection on the rudder trailing edge area in 

accordance with instructions defined in Airbus SB A310-55-2049, 

or Airbus SB A300-55-6048 as applicable to aeroplane model. 

(2.2) Repeat once the inspection defined in paragraph (2.1) of this AD 

within 4 500 FC but not less than 4 000 FC from the last 

inspection. 

(3) For rudders as identified in Appendix D to this AD

Within 8 months after the effective date of this AD, replace the affected 

rudder with a serviceable unit. 

(4) In case of findings during the inspections defined in paragraph (1) or 

(2) of this AD, before next flight, contact Airbus to get further 

instructions and apply these associated instructions and corrective 

actions in accordance with the approved data provided. 

(5) In case of no findings during the inspection defined in paragraph (1.1) 

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 Airbus SB A310-55-2049, or Airbus SB A300-55-6048, 

as applicable to aeroplane model, and apply the associated instructions 

until performance of permanent restoration. 

(6) Within 10 days after accomplishment of each inspection in accordance 

with paragraph (1) or (2) of this AD, report to Airbus the inspection 

results, including no finding. 
EASA AD No.: 2010-0144 

EASA Form 110 Page 3/4 

(7) After the effective date of this AD, no person shall install any affected 

rudder listed in Appendix A or B or C to this AD on an aeroplane, 

unless in compliance with the requirements of this AD. 

(8) After the effective date of this AD, no person shall install any affected 

rudder listed in Appendix D to this AD. 

Ref. Publications : Airbus Service Bulletin A310-55-2049 at original issue. 

Airbus Service Bulletin A300-55-6048 at original issue. 

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 11 June 2010 as PAD 10-042 for consultation 

until 09 July 2010. No comments were received during the consultation 

period. 

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 – Airworthiness Office – EAS Fax 

+33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com. 
EASA AD No : 2010 – 0144 Appendix 

EASA Form 110 Page 4/4 

Appendix A 

Rudder P/N Affected rudder S/N 

A554-71710-000-00 TS-2010 

A554-71710-000-00 TS-2027 

A554-71710-000-00 TS-2030 

A554-71710-002-00 TS-2043 

A554-71710-004-00 TS-2048 

Appendix B 

Rudder P/N Affected rudder S/N 

MSN-scrapped TS-1362 

A554-71710-000-00 TS-2006 

A554-71710-000-00 TS-2008 

A554-71710-002-00 TS-2033 

A554-71710-004-00 TS-2054 

A554-71710-004-00 TS-2061 

A554-71710-004-00 TS-2071 

A554-71710-004-00 TS-2072 

A554-71710-004-00 TS-2073 

A554-71730-000-00-0000 TS-2082 

A554-71730-000-00-0000 TS-2084 

A554-71730-000-00-0000 TS-2085 

A554-71730-000-00-0000 TS-2086 

A554-71730-000-00-0000 TS-2087 

Appendix C 

Rudder P/N Affected rudder S/N 

A554-71500-016-30 HF-1254 

A554-71710-004-00 TS-2049 

A554-71710-004-00 TS-2055 

A554-71710-004-00 TS-2059 

Appendix D 

Rudder P/N Affected rudder S/N 

A554-71500-016-91 HF-1044 

A554-71500-014-00 HF-1116 

A554-71500-016-00 HF-1183 

A554-71500-016-00 HF-1184 

A554-71500-026-00 TS-1402