EASA AD No.: 2010-0127

EASA Form 110 Page 1/7 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0127

Date: 23 June 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 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 b y 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) :

A330 and A340-200/-300 aeroplanes

TCDS Number : EASA.A.004, EASA.A.015

Foreign AD : Not applicable

Supersedure : None



### ATA 55 Stabilizers – Rudder Side Shell Skin – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342 and -343, all manufacturer serial numbers, and Airbus A340 aeroplanes, models -211, -212, -213, -311, -312 and -313, all manufacturer serial numbers, if equipped with rudders having part numbers (P/N) and serial numbers (S/N) as listed in the Appendix A, B or C to this AD.

Reason: Surface defects were visually detected on the rudder of one A319 and one A321 in-service aeroplane during scheduled maintenance. Investigation has determined that t he defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the surf ace defects were a result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A330 and A340-200/-300 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.EASA AD No.: 2010-0127

EASA Form 110 Page 2/7 To address this unsafe condition, EASA issued AD 2010-0021, superseding EASA AD 2009-0156, to require inspec tions of specific areas and, depending on findings, the accomplishment of corrective actions for those rudders where production reworks have been identified. In addition, this AD addresses the rudder population that has also been reworked in production but is not part of EASA AD 2010-0021 applicability.

Effective Date: 07 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) A330-55-3042, or Airbus SB A340-55-4038, as applicable: (1.1) Non ventilated area (“Area 1”) location : Unless already accomplished, - within 1 800 Flight Hours (FH) after the effective date of this AD for rudders listed in Appendix A to this AD, or

- within 21 months after the effect ive date of this AD, for rudders listed in Appendix B to this AD, perform Vacuum Loss inspection on the rudder non ventilated area in accordance with instructions defined in Airbus SB A330-55-3042, or Airbus SB A340-55-4038, as applicable to the aeroplane model. (1.2) Trailing edge area (“Area 2”) location:

(1.2.1) Unless already accomplished, within 21 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 A330-55-3042, or Airbus SB A340-55-4038, as applicable to the aeroplane model. (1.2.2) Repeat two further times the inspection required by 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 4 500 FC but not less than 4 000 FC from the sampling inspection, perform an Elasticity Laminate Checker inspection on the rudder trailing edge area in accordance with instructions defined in Airbus SB A330-55-3042, or Airbus SB A340-55-4038 as applicable to the aeroplane model. (2.2) Repeat once the inspection r equired by paragraph (2.1) of this AD within 4 500 FC but not less than 4 000 FC from the last inspection. (3) In case of findings during the inspections required by 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. (4) In case of no findings during the inspection required by 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 with resin), in accordance with Airbus SB A330-55-3042, or Airbus SB A340-55-4038, as applicable to the aeroplane model, and apply the associated instructions until performance of permanent restoration.EASA AD No.: 2010-0127

EASA Form 110 Page 3/7 (5) Within 10 days after accomplishment of each inspection in compliance with paragraphs (1) or (2) of this AD , report to Airbus the inspection results, including no finding. (6) After the effective date of this AD, do not 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.

Ref. Publications : Airbus Service Bu lletin A330-55-3042 at original issue; Airbus Service Bulletin A340-55-4038 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 19 May 2010 as PAD 10-044 for consultation until 16 June 2010. 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 & 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 – EAL, E-mail: airworthiness.A330-A340@airbus.com

.EASA AD No.: 2010-0127 Appendix A

EASA Form 110 Page 4/7 EASA AD 2010-0127 – Appendix A Rudder P/N Affected rudder S/N F554-70000-000-00 TS-2045 F554-70000-000-00 TS-2046 F554-71000-000-00-0000 TS-3013 F554-71000-000-00-0000 TS-3014 F554-71000-000-00-0000 TS-3020 F554-71000-000-00-0000 TS-3022 F554-71000-000-00-0000 TS-3023 F554-71000-000-00-0000 TS-3027 F554-71000-000-00-0000 TS-3031 F554-71000-000-00-0000 TS-3034 F554-71000-000-00-0000 TS-3036 F554-71000-000-00-0000 TS-3038 F554-71000-000-00-0000 TS-3041 F554-71000-000-00-0000 TS-3046 F554-71000-000-00-0000 TS-3054 F554-70005-000-00-0000 TS-3102 F554-71002-000-00-0002 TS-4018 F554-71002-000-00-0002 TS-4022 F554-71002-000-00-0002 TS-4031EASA PAD No.: 2010-0127 Appendix B

EASA Form 110 Page 5/7 EASA AD 2010-0127 – Appendix B Rudder P/N Affected rudder S/N A554-71500-024-00 TS-1014 A554-71500-030-00 TS-1042 F554-70000-000-00 TS-2004 F554-70000-000-00 TS-2005 F554-70000-000-00 TS-2008 F554-70000-000-00 TS-2009 F554-70000-000-00 TS-2010 F554-70000-000-00 TS-2022 F554-70000-000-00 TS-2023 F554-70000-000-00 TS-2028 F554-70000-000-00 TS-2029 F554-70000-000-00 TS-2030 F554-70000-000-00 TS-2032 F554-70000-000-00 TS-2033 F554-70000-000-00 TS-2034 F554-70000-000-00 TS-2041 F554-70000-000-00 TS-2044 F554-70000-000-00 TS-2048 F554-70000-000-00 TS-2049 F554-70000-000-00 TS-2050 F554-70000-000-00 TS-2057 F554-70000-000-00 TS-2067 F554-70000-002-00 TS-2068 F554-70000-002-00 TS-2071 F554-71000-000-00-0000 TS-3001 F554-71000-000-00-0000 TS-3010 F554-71000-000-00-0000 TS-3012 F554-71000-000-00-0000 TS-3017 F554-71000-000-00-0000 TS-3018 F554-71000-000-00-0000 TS-3019 F554-71000-000-00-0000 TS-3021 F554-71000-000-00-0000 TS-3024 F554-71000-000-00-0000 TS-3025 F554-71000-000-00-0000 TS-3026 F554-71000-000-00-0000 TS-3028 F554-71000-000-00-0000 TS-3029 F554-71000-000-00-0000 TS-3030 F554-71000-000-00-0000 TS-3032 F554-71000-000-00-0000 TS-3035 F554-71000-000-00-0000 TS-3037 F554-71000-000-00-0000 TS-3039 F554-71000-000-00-0000 TS-3040 F554-71000-000-00-0000 TS-3042 F554-71000-000-00-0000 TS-3047 F554-71000-000-00-0000 TS-3049 F554-71000-000-00-0000 TS-3055 F554-71000-000-00-0000 TS-3058 F554-71000-000-00-0000 TS-3062 F554-71000-000-00-0000 TS-3063 F554-71000-000-00-0000 TS-3065 F554-71000-000-00-0000 TS-3067 F554-71000-000-00-0000 TS-3069EASA PAD No.: 2010-0127 Appendix B

EASA Form 110 Page 6/7 F554-71000-000-00-0000 TS-3070 F554-71000-000-00-0000 TS-3077 F554-71000-000-00-0000 TS-3078 F554-71000-000-00-0000 TS-3080 F554-71000-000-00-0000 TS-3081 F554-71000-000-00-0000 TS-3086 F554-71000-000-00-0000 TS-3089 F554-71000-000-00-0000 TS-3092 F554-71000-000-00-0000 TS-3093 F554-71000-000-00-0000 TS-3095 F554-71000-000-00-0000 TS-3096 F554-70005-000-00-0000 TS-3098 F554-70005-000-00-0000 TS-3099 F554-70005-000-00-0000 TS-3101 F554-70005-000-00-0000 TS-3103 F554-70005-000-00-0000 TS-3104 F554-70005-000-00-0000 TS-3105 F554-70005-000-00-0000 TS-3108 F554-70005-000-00-0000 TS-3109 F554-70005-000-00-0000 TS-3110 F554-70005-000-00-0000 TS-3111 F554-70005-000-00-0000 TS-3112 F554-70005-000-00-0000 TS-3114 F554-70005-000-00-0000 TS-3116 F554-70005-000-00-0000 TS-3117 F554-70005-000-00-0000 TS-3120 F554-70005-000-00-0000 TS-3131 F554-70005-000-00-0000 TS-3132 F554-70005-000-00-0000 TS-3212 F554-70005-000-00-0002 TS-3323 F554-70005-000-00-0002 TS-3330 F554-71002-000-00-0002 TS-4009 F554-71002-000-00-0002 TS-4010 F554-71002-000-00-0002 TS-4012 F554-71002-000-00-0002 TS-4013 F554-71002-000-00-0002 TS-4014 F554-71002-000-00-0002 TS-4015 F554-71002-000-00-0002 TS-4016 F554-71002-000-00-0002 TS-4017 F554-71002-000-00-0002 TS-4020 F554-71002-000-00-0002 TS-4023 F554-71002-000-00-0002 TS-4025 F554-71002-000-00-0002 TS-4026 F554-71002-000-00-0002 TS-4027 F554-71002-000-00-0002 TS-4029 F554-71002-000-00-0002 TS-4030 F554-71002-000-00-0002 TS-4038 F554-71002-000-00-0002 TS-4047 F554-71002-000-00-0002 TS-4049 F554-71002-000-00-0002 TS-4066 F554-71002-000-00-0003 TS-4083EASA PAD No : 2010–0127 Appendix C

EASA Form 110 Page 7/7 EASA AD 2010-0127 – Appendix C Rudder P/N Affected rudder S/N F554-71000-000-00-0000 TS-3060 F554-71000-000-00-0000 TS-3068 F554-70005-000-00-0000 TS-3128 F554-71002-000-00-0002 TS-4011