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EASA AIRWORTHINESS DIRECTIVE 

AD No : 2008-0018 

Date: 24 January 2008

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.

Type Approval Holder’s Name : 

TURBOMECA 

Type/Model designation(s) : 

ARRIUS 2 turboshaft engines 

TCDS Number: France No. M 20 

Foreign AD: Not applicable 

Supersedure: None 

ATA 73 Engine Fuel & Control – Electronic Engine Control (EEC) Unit – 

Identification / Modification 

Manufacturer(s): Turbomeca 

Applicability: ARRIUS 2B1, ARRIUS 2B1A, ARRIUS 2B2, ARRIUS 2K1 and ARRIUS 2K2 

engines, all serial numbers. 

These engines are known to be installed on, but not limited to, Eurocopter 

Deutschland EC135 and Agusta A109 twin-engine helicopters. 

Reason: A short circuit of some tantalum capacitors inside certain EEC units may lead 

to an in-flight shutdown on one of the two engines resulting from: 

- direct activation of the overspeed electronic protection, 

- non-direct activation of the electronic overspeed protection by lowering of 

the threshold, 

- spurious activation of the starting sequence; or 

- loss of power control with no freeze of the fuel metering-valve. 

For the reasons described above, this Airworthiness Directive (AD) requires 

the identification and modification of EEC units that have the tantalum 

capacitors installed that could have become brittle during their acceptance 

test. 

Effective Date: 07 February 2008 

Compliance: Required as indicated, unless accomplished previously: 

(1) Within the next 100 Flight Hours (FH) or 2 months, whichever occurs first 

after the effective date of this AD, identify the installed EEC units as listed 

in TURBOMECA Service Bulletin (SB) N° 319 73 2835; 

(2) If both EEC units installed on the helicopter’s engines are affected, within 
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the next 100 FH or 2 months, whichever occurs first after the effective 

date of this AD, modify at least one unit in accordance with the 

instructions of TURBOMECA SB N° 319 73 2835; 

(3) Within 300 FH or 12 months, whichever occurs first after the effective 

date of this AD, modify all remaining affected EEC units in accordance 

with the instructions of TURBOMECA SB N° 319 73 2835; 

(4) After 07 February 2009, no person shall install a spare EEC unit with a 

serial number as listed in TURBOMECA SB N° 319 73 2835 on any 

helicopter, unless it has been modified in accordance with the instructions 

of TURBOMECA SB N° 319 73 2835. 

Ref. Publications: TURBOMECA Service Bulletin N° 319 73 2835, Update No.1 dated 21 

December 2006. 

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

compliance with the requirements of this AD. 

Remarks : 1. If requested and appropriately substantiated, EASA can accept Alternative 

Methods of Compliance for this AD. 

2. This AD was posted on 21 December 2007 as PAD 07-229 for 

consultation until 18 January 2008. The Comment Response Document 

can be found at http://ad.easa.europa.eu/ . 

3. Enquiries regarding this AD should be referred to the AD Focal Point - 

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: 

ARRIUS 2 Customer Support 

TURBOMECA - 40220 TARNOS – FRANCE 

Fax: +33 5 59 74 45 15; or contact your nearest technical representative 

at www.turbomeca-support.com