EASA AD No.: 2010-0021 

EASA Form 110 Page 1/5 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0021 

Date: 09 February 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) : 

A330-300 and A340-200/-300 aeroplanes 

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

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2009-0156 dated 17 July 2009 

ATA 55 Stabilizers – Rudder Side Shell Skin – Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -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 Carbon Fiber Reinforced Plastic (CFRP) rudders having 

part numbers (P/N) and serial numbers (S/N) as listed in the Appendix A 

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 A330-300 

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.: 2010-0021 

EASA Form 110 Page 2/5 

 

EASA AD 2009-0156 required inspections of specific areas and, 

depending on findings, the application of corrective actions for those 

rudders where production reworks have been identified. 

This AD retains the requirement of EASA AD 2009-0156, which is 

superseded, and in addition requires for the vacuum loss hole restoration: 

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

thermography inspection, which is maintained for non-reinforced areas, 

and 

- an additional work for aeroplanes on which this thermography 

inspection has been performed in the reinforced area. 

Effective Date: 23 February 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated: 

For the purpose of this AD a Reference Date is 31 July 2009 [effective 

date of EASA AD 2009-0156] or the date when the rudder will accumulate 

13 000 Flight Cycles (FC) from its first installation on an aeroplane, 

whichever occurs later. 

Depending on the locations of the areas to be inspected as defined in 

Airbus All Operators Telex (AOT) A330-55A3040 Revision 02 or AOT 

A340-55A4036 Revision 02, as applicable, do the following actions: 

(1) Reinforced area location: 

Unless already accomplished, within 1 800 Flight Hours (FH) from the 

Reference Date, perform Vacuum Loss inspection on the rudder 

reinforced area in accordance with instructions defined in Airbus AOT 

A330-55A3040 Revision 02 or AOT A340-55A4036 Revision 02, as 

applicable. 

(2) Trailing edge area location:

(2.1) Unless already accomplished, within 21 months from the 

Reference Date, perform Elasticity Laminate Checker inspection 

on the rudder trailing edge area in accordance with instructions 

defined in Airbus AOT A330-55A3040 Revision 02 or AOT 

A340-55A4036 Revision 02, as applicable. 

(2.2) In case of no findings, repeat two further times the inspection 

defined in paragraph (2.1) of this AD at intervals not to exceed 

4 500 FC but not less than 4 000 FC from the last inspection. 

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

locations):

(3.1) Unless already accomplished, within 1 800 FH 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 

A330-55A3040 Revision 02 or AOT A340-55A4036 Revision 02, 

as applicable. 

(3.2) Repeat the inspection defined in paragraph (3.1) of this AD at 

intervals not to exceed 1 800 FH from the last inspection. 

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

(3.1) or (3.2) of this AD, unless already accomplished, within 21 

months from the Reference Date, perform Vacuum Loss 

inspection on these areas (lower rib/upper edge/leading 
EASA AD No.: 2010-0021 

EASA Form 110 Page 3/5 

 

edge/other locations) in accordance with instructions defined in 

Airbus AOT A330-55A3040 Revision 02 or AOT A340-55A4036 

Revision 02, as applicable. 

(3.4) Accomplishment of the inspection required by paragraph (3.3) of 

this AD cancels the initial and repetitive inspections required by 

paragraphs (3.1) and (3.2) of this AD. 

(4) In case of findings during the inspection defined in paragraph (1), 

(2.1), (2.2), (3.1), (3.2) or (3.3) of this AD, before next flight, contact 

Airbus for further instructions and apply the associated instructions 

and corrective actions in accordance with the approved data provided. 

(5) In case of no findings during the inspection defined in paragraphs (1) 

and (3.3) of this AD, before next flight, restore the vacuum loss holes 

as per the selected option (temporary restoration with self adhesive 

patches, temporary restoration with resin or permanent restoration) in 

Airbus AOT A330-55A3040 Revision 02 or AOT A340-55A4036 

Revision 02, as applicable, and apply the associated instructions until 

performance of permanent restoration. 

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

with paragraphs (1), (2) or (3) of this AD, report the results, including 

no findings, to Airbus. 

(7) All rudders that have passed the inspection, before 31 July 2009 

[effective date of AD 2009-0156], in accordance with the instructions 

of Airbus AOT A330-55A3040 at original issue or AOT A340-55A4036 

at original issue, are compliant with the associated requirements of 

paragraph (1), (2), (3) or (5) of this AD for the areas inspected. 

Additional areas requiring inspection are defined in Airbus AOT A330-

55A3040 Revision 01 or AOT A340-55A4036 Revision 01. For these 

additional areas the requirements of this AD are applicable. For all 

areas, the repetitive inspections required by this AD remain applicable.

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

of this AD, in accordance with the instructions of Airbus AOT A330-

55A3040 Revision 01 or AOT A340-55A4036 Revision 01, as 

applicable, are compliant with the associated requirements of 

paragraph (1), (2), (3) or (5) of this AD for the areas inspected. The 

repetitive inspections required by this AD remain applicable. 

(9) For rudders on which temporary vacuum loss hole 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 (5) of this AD and in accordance with the instructions of 

Airbus AOT A330-55A3040 at original issue or Revision 01 or AOT 

A340-55A4036 at original issue or Revision 01, as applicable, within 

21 months from restoration date perform an ultrasonic inspection in 

accordance with the instructions of Airbus AOT A330-55A3040 

Revision 02 or AOT A340-55A4036 Revision 02, as applicable. 

(10) After the effective date of this AD, no person shall install any rudder 

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

with the requirements of paragraph (1), (2), (3), (5) or (9) of this AD. 
EASA AD No.: 2010-0021 

EASA Form 110 Page 4/5 

 

Ref. Publications: Airbus All Operators Telex A330-55A3040 Revision 02, 

Airbus All Operators Telex A340-55A4036 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 published as PAD 09-130 on 09 November 2009 for 

consultation until 07 December 2009. 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 questions 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.: 2010-0021 

EASA Form 110 Page 5/5 

 

EASA AD No. 2010-0021: Appendix A 

Rudder Part Number Rudder Serial Number 

F554-70000-000-00 TS-2013 

F554-70000-000-00 TS-2015 

F554-70000-000-00 TS-2016 

F554-70000-000-00 TS-2017 

F554-70000-000-00 TS-2018 

F554-70000-000-00 TS-2020 

F554-70000-000-00 TS-2021 

F554-70000-000-00 TS-2024 

F554-70000-000-00 TS-2026 

F554-70000-000-00 TS-2035 

F554-70000-000-00 TS-2036 

F554-70000-000-00 TS-2040 

F554-70000-000-00 TS-2042 

F554-70000-000-00 TS-2055 

F554-70000-000-00 TS-2056 

F554-70000-000-00 TS-2058 

F554-70000-000-00 TS-2059 

F554-70000-000-00 TS-2061 

F554-70000-000-00 TS-2062 

F554-70000-000-00 TS-2063 

F554-70000-000-00 TS-2065 

F554-70000-002-00 TS-2074 

F554-71000-000-00 TS-3003 

F554-71000-000-00 TS-3004 

F554-71000-000-00 TS-3005 

F554-71000-000-00 TS-3006 

F554-71000-000-00 TS-3007 

F554-71000-000-00 TS-3008 

F554-71000-000-00 TS-3011 

F554-71000-000-00 TS-3015 

F554-71000-000-00 TS-3033 

F554-71000-000-00 TS-3061 

F554-71000-000-00 TS-3064 

F554-71000-000-00 TS-3066 

F554-71000-000-00 TS-3071 

F554-71000-000-00 TS-3072 

F554-71000-000-00 TS-3075 

F554-71000-000-00 TS-3079 

F554-71000-000-00 TS-3084 

F554-71000-000-00 TS-3087 

F554-70005-000-00 TS-3100 

F554-70005-000-00 TS-3106 

F554-70005-000-00 TS-3107 

F554-70005-000-00 TS-3119 

F554-70005-000-00 TS-3124