EASA AD No.: 2009-0027 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0027 

Date: 18 February 2009 

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 : 

EUROCOPTER 

Type/Model designation(s) : 

AS 350 and EC 130 helicopters 

TCDS Number : EASA.R.008 

Foreign AD : Not applicable 

Supersedure : This AD supersedes and cancels EASA AD 2009-0004 dated 12 January 2009. 

ATA 80 Engine Starting – Starter-Generator Damping Assembly –

Adjustment 

Manufacturer(s): EUROCOPTER (formerly Eurocopter France, Aerospatiale) 

Applicability: AS 350 B, BA, BB, B1, B2, B3 and EC 130 B4 helicopters, all serial numbers, 

if equipped with ARRIEL engines where Aircraft Parts Corporation (APC) 

starter-generators with Part Number (P/N) 150SG122Q or P/N 200SGL130Q 

without “004” marking on their name plates are installed. 

Reason: EUROCOPTER has received several reports of engine flame-outs, all of which 

involved the failure of the 41-tooth pinion in the engine accessory gear box. All 

the concerned helicopters were equipped with starter-generators 

manufactured by the APC company (currently UNISON). In each case, it was 

found that the torque damping system of the starter-generator was inoperative. 

Further investigations have been conducted to assess the efficiency of the 

damping system of starter-generators with P/N 150SG122Q and 

200SGL130Q, which have revealed that the non-operation of the torque 

damping system was due to an incorrect adjustment. If the damping system is 

incorrectly adjusted, torque oscillations may not be limited and can induce 

bending stress on the 41-tooth pinion of the accessory gear box, contributing 

to the pinion failure. Such pinion failure causes the fuel pump to stop which 

results in an engine flame-out. 

Pending additional investigations, EASA AD 2009-0004 required an inspection 

of the alignment and torque of the APC starter-generator damping assembly 

and, in case of discrepancies, the accomplishment of corrective actions. 

This AD, superseding EASA 2009-0004, requires the accomplishment of a 

new adjustment procedure, which has proven to be more reliable and 

optimizes the performance of the APC starter-generator damping assembly. 
EASA AD No.: 2009-0027 

EASA Form 110 Page 2/2 

Effective Date: 04 March 2009 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

1. Within 110 flight hours or 3 months, whichever occurs first after the 

effective date of this AD, adjust and mark the APC starter-generator in 

accordance with the instructions of paragraph 2.B.2 of EUROCOPTER 

AS350 Alert Service Bulletin (ASB) No. 80.00.07 Revision 1 or EC130 ASB 

No. 80A003 Revision 1, as applicable to the helicopter version. 

2. After the effective date of this AD, no person shall install on a helicopter a 

starter-generator with P/N affected by this AD unless it has been adjusted 

and marked as required in the relevant ASB. 

Ref. Publications: EUROCOPTER AS350 ASB No. 80.00.07 Revision 1 dated 06 February 2009. 

EUROCOPTER EC130 ASB No. 80A003 Revision 1 dated 06 February 2009. 

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 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: EUROCOPTER (STDI) – Aéroport de Marseille 

Provence 13725 Marignane Cedex – France. 

Telephone: +33 (0)4 42 85 97 97, Fax: +33 (0)4 42 85 99 66 

E-mail: Directive.technical-support@eurocopter.com.