EASA AD No : 2011-0112 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0112 

Date: 15 June 2011 

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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directive 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) : 

A300 aeroplanes 

TCDS Number : France N° 145 

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 A300 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 and corrected, 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: 29 June 2011 
EASA AD No : 2011-0112 

EASA Form 110 Page 2/2 

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 Accomplishment 

Instructions of AIRBUS Service Bulletin A300-27-0204 original issue. 

Ref. Publications: Airbus Service Bulletin A300-27-0204 at original issue. 

The use of later approved revisions of this document is acceptable for 

compliance with 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 13 May 2011 as PAD 11-055 for consultation until 

10 June 2011. 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 18 41 39, Fax: + 33 5 61 93 44 51).