EASA AD No.: 2010-0239-E 

EASA Form 111 Page 1/2 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010- 0239-E

[Corrected: 23 November 2010] 

Date: 19 November 2010

Note: This Emergency 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) :

A300-600 and A300-600ST aeroplanes

TCDS Number : France N° 145 and EASA.A.014 

Foreign AD : Not applicable 

Supersedure : None 

ATA 27 Flight Control – Elevator Mechanical Control Linkage – Pitch 

Uncoupling Unit - Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: A300-600 aeroplanes, all certified models, all serial numbers, and A300F4-

608ST aeroplanes, all serial numbers, except aeroplanes on which the pitch 

uncoupling functional test has already been performed in service since new. 

Note : The pitch uncoupling functional test is described in A300-600 and 

A300-600ST Aircraft Maintenance Manuals (AMM) under task 27-31-00 

page block 501 section 3.(2) and is scheduled to be performed at intervals 

not to exceed 18 000 Flight Hours (FH) or 120 months, whichever occurs 

first [Maintenance Planning Document (MPD) task 273100-02-1]. 

Reason: During a routine maintenance check on an A300-600 aeroplane, the 

operator found the pitch uncoupling unit installed at an incorrect location. 

The pitch uncoupling unit was inverted with the rod assembly. 

After a complete inspection of all A300-600 aeroplanes of its fleet, the 

operator identified the same incorrect installation on another aeroplane. 

Had this routine maintenance check, which was accomplished for other 

purposes, not been carried out, the incorrect installation could only have 

been detected during the accomplishment of the pitch uncoupling functional 

test. 

Note: Another maintenance task, the pitch uncoupling operational test, 

scheduled at intervals not to exceed 2 000 FH or 36 months, whichever 

occurs first (MPD task 273100-01-1), only validates the condition of the pitch 
EASA AD No.: 2010-0239-E 

EASA Form 111 Page 2/2 

uncoupling solenoid. 

This condition, if not detected and corrected, in combination with particular 

failure modes, could lead to loss of control of the aeroplane during the takeoff phase. 

For the reason described above, this AD requires a one time visual 

inspection, to detect any incorrect installation of the pitch uncoupling unit, 

and, depending on findings, to take corrective actions. 

This AD was republished to correct the compliance time.

Effective Date: 23 November 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 30 days after the effective date of this AD, visually check that the 

pitch uncoupling unit is installed at the correct location in accordance with 

the instructions of Airbus All Operators Telex (AOT) 27A6068 Revision 01, 

or AOT 27A9020 Revision 01, as applicable to the aeroplane model. 

(2) If the pitch uncoupling unit is found inverted with the rod assembly, 

before next flight, remove and re-install the pitch uncoupling unit and the 

rod assembly at their correct locations, and thereafter perform the 

functional test of the pitch uncoupling unit, in accordance with the 

instructions of Airbus AOT 27A6068 Revision 01, or AOT 27A9020 Revision 

01, as applicable to the aeroplane model.

Ref. Publications: Airbus A300-600 AOT 27A6068 Revision 01, dated 18 November 2010, 

Airbus A300-600ST AOT 27A9020 Revision 01, dated 18 November 2010. 

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. The safety assessment has requested not to implement the full 

consultation process and an immediate publication and notification. 

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)