EASA AD No.: 2012-0102

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0102

Date: 08 June 2012

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].

Design Approval Holder’s Name:

Airbus

Type/Model designation(s):

A300-600, A310 and A300-600ST aeroplanes

TCDS Number: France TCDS No 145 and EASA.A.014

Foreign AD: Not applicable

Supersedure: None

ATA 25 Equipment and Furnishings – Powered Pilot and Co-pilot Seats –

Inspection

Manufacturer(s): Airbus (formerly Airbus Industries)

Applicability: Airbus A300-600, and A310 aeroplanes, all certified models, all manufacturer 

serial numbers (MSN), and

Airbus A300F4-608ST aeroplanes, all MSN.

Reason: During a steep climb manoeuvre that was flown with a high pitch (25°) for 

training of ground threat avoidance, an Airbus A310 aeroplane experienced an 

uncommanded slide back of the co-pilot seat to the end stop position.

Investigation revealed that on the affected seat, the disc key inside the clutch 

was broken. SOGERMA Service Bulletin (SB) No 2510112-25-813, which

addresses the previous end stop switch issue and which is covered by EASA 

AD 2010-0070, had been accomplished on this seat, but due to seizure, the key 

failure was not detected at time. This broken disc key caused a jamming 

between the gear and the shaft of the clutch. Despite this failure, the torque 

transmission between the gear and the shaft was sufficient for normal 

operation, but not to keep the seat in locked position during climbing, due to the 

high longitudinal loads generated by the high aeroplane incidence.

This condition, if not detected and corrected, could cause the pilot to lose 

contact with the controls, leading to an inadvertent input on the flight control 

commands during take-off or climb, possibly resulting in loss of control of the 

aeroplane.

For the reasons described above, this AD requires a one-time inspection of the 

affected seats and, depending on findings, accomplishment of applicable 

corrective action(s).

Effective Date: 22 June 2012
EASA AD No.: 2012-0102

CAP.00110-001 © European Aviation Safety Agency. All rights reserved. 2/2

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 6 months after the effective date of this AD, accomplish the 

following actions:

(1.1) Inspect each SOGERMA pilot and co-pilot seat installed on the 

aeroplane to identify the Part Number (P/N). A review of aeroplane 

delivery- or maintenance records is acceptable in lieu of the 

inspection as required by this paragraph, provided those records can 

be relied upon for that purpose, and the P/N of each seat can be 

conclusively identified from that review.

(1.2) If the P/N of a seat, identified as required by paragraph (1) of this 

AD, is P/N 2510112 series (all suffixes) or P/N 2510113 series (all 

suffixes), accomplish a tensile test on that seat in accordance with 

the instructions of Airbus Alert Operators Transmission (AOT) No.

A25W001-12.

(2) Affected seats which, before the effective date of this AD, have already 

passed the test, or have been modified, in accordance with the instructions 

of SOGERMA SB 2510112-25-898, are not required to be tested, as these 

are considered to be compliant with the requirements of this AD.

(3) If the tensile test sample does not break-off while performing the test as 

required by paragraph (1) of this AD, before the next flight, accomplish one 

of the following actions in accordance with the instruction of Airbus AOT

No.A25W001-12:

(3.1) Replace the affected seat with a serviceable one,

or

(3.2) Remove the seat from the aeroplane for replacement of the actuator 

P/N RT19H4FX in accordance with the instructions of Airbus AOT

No. A25W001-12, or modify the seat in accordance with the 

instructions of SOGERMA SB 2510112-25-898.

(4) From the effective date of this AD, do not install a SOGERMA pilot or copilot seat P/N 2510112 series or P/N 2510113 series on an aeroplane, 

unless it has passed the test as required by paragraph (1) of this AD, or 

the seat has passed the test in accordance with the instructions of 

SOGERMA SB 2510112-25-898, or has been repaired or modified as 

required by paragraph (3) of this AD.

Ref. Publications: Airbus AOT No. A25W001-12 original issue dated 06 June 2012.

SOGERMA SB 2510112-25-898 original issue dated 24 April 2012.

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 required actions and the risk allowance have granted the issuance of a 

Final AD with Request for Comments, postponing the public consultation 

process after publication.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive 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 – EIAW (Airworthiness Office, 

Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).