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 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) : 

A310, A300-600 and A300-600ST aeroplanes 

TCDS Number : France 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 upper 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 result 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 of 
EASA 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 substantiated, 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 & 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 SAS – EAW (Airworthiness Office, 

Telephone: + 33 5 61 93 36 96, Fax: + 33 5 61 93 44 51).