EASA AD No : 2010-0224

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0224

Date: 04 November 2010

Note: 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 participat e 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 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, A300-600 and A300-600ST aeroplanes

TCDS Number : Fran ce N° 145 and EASA.A.014

Foreign AD : Not applicable

Supersedure : None



### ATA 27 Flight Controls – Trimmable Horizontal Stabilizer Actuator (THSA) Upper Attachment - Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A310, A300-600 and A300- 600ST aeroplanes, all certified models, all manufacturer serial numbers.

Reason: A specific failure case of the THSA uppe r primary attachment, which may result in a loading of the upper secondary attachment, has been identified by analysis. Primary load path failure can be caused by bearing migration from the upper attachment gimbal by failure or loss of a retention bolt. In case of failure of the THSA upper primary attachment, the THSA upper secondary attachment would engage. Because the upper attachment secondary load path can only withstand the loads for a limited period of time, the condition where it would be engaged could lead, if not detected, to the failure of the secondary load path, which would likely resu lt in loss of control of the aeroplane. For the reasons explained above, this AD requires installation of three secondary retention plates for the gimbal bearings on the THSA upper primary attachment.

Effective Date: 18 November 2010

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:
Within 30 months after the effective date of this AD, install three retention plates on THSA upper primary attachment in accordance with the instructions ofEASA AD No : 2010-0224

EASA Form 110 Page 2/2 AIRBUS Service Bulletins A300-27-6066 or A310-27-2103 or A300-27-9019 as applicable to aeroplanes model.

Ref. Publications: Airbus Service Bulletins : A300-27-6066 at Original issue, A310-27-2103 at Original issue, A300-27-9019 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 subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 28 September 2010 as PAD 10-083 for consultation until 26 October 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 tec hnical content of the requirements in this AD, please contact: AIRBUS SAS – EAW (Airworthiness Office, Telephone: + 33 5 61 93 36 96, Fax: + 33 5 61 93 44 51).