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 parti cipate in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EC 1702/2003, Part 21A.3 B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any a pplicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance wi th 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. Investigat ion has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed t hat 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 lo ss 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 effect ive date of this AD for rudders listed in Appendix A to this AD, or
- within 24 months after the effect ive 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 associ ated 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, restor e the vacuum loss holes as per the option selected (temporary restorat ion 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 a pply 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 Bu lletin 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 & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the te chnical 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