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## EASA AIRWORTHINESS DIRECTIVE

AD No : 2008-0018

Date: 24 January 2008

No person may operate an aircraft to which an Airworthines s Directive applies, except in accordance with the requirements of that Airworthiness Directive unless otherwi se 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 2B 1A, ARRIUS 2B2, ARRI US 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 over speed electronic protection,

- non-direct activation of the electroni c overspeed protection by lowering of

the threshold,

- spurious activation of the starting sequence; or

- loss of power control with no free ze 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 be come 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, i dentify 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, within2/2 the next 100 FH or 2 months, whicheve r 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, whiche ver 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 s hall 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 Bullet in 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 appropria tely 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 tec hnical 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