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 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) : 

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 the defects reported on both rudders 

corresponded to areas that had been reworked in production. The 

investigation confirmed that the surface 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 loss 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 inspections 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 effective 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 required 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 associated 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, restore the vacuum loss holes as per the 

option selected (temporary restoration 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 Bulletin 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 & 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 – 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-4031 
EASA 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-3069 
EASA 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-4083 
EASA 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