EASA AD No.: 2012-0141

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0141

Date: 31 July 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:

TURBOMECA

Type/Model designation(s):

ARRIEL 2 engines

TCDS Number: EASA E.001

Foreign AD: Not applicable

Supersedure: None

ATA 73 Engine Fuel & Control – Hydro-Mechanical Metering Unit –

Replacement

Manufacturer(s): Turboméca S.A.

Applicability: ARRIEL 2D engines, all serial numbers.

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

350 B3 and EC 130 T2 helicopters.

Reason: During an ARRIEL 2D endurance test, the illumination of the Low Fuel 

Pressure warning light was observed. The investigation of the High Pressure / 

Low Pressure (HP/LP) pump assembly within the Hydro-Mechanical Metering 

Unit (HMU), removed following this occurrence, revealed a deterioration and a 

loss of the LP pump drive function.

This condition, if not corrected, could lead to the illumination of the Low Fuel 

Pressure warning light in flight, possibly resulting in an uncommanded In-flight 

shut-down (if the booster pumps are not switched on or under high load factor 

manoeuvres). For a single-engine helicopter, it may result in an emergency 

autorotation landing.

For the reasons described above, this AD requires replacement of the HMU

before exceeding a defined limit of operating hours.

Effective Date: 14 August 2012
EASA AD No.: 2012-0141

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Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Before exceeding 800 HMU operating hours since new, or within 800 HMU 

operating hours since last application of the Turboméca Mandatory Service 

Bulletin (MSB) A292 73 2847 version A, as applicable, replace the HMU 

with a serviceable HMU in accordance with the instructions of paragraph 2 

of Turboméca MSB A292 73 2847 version A.

Note : For the purpose of this AD, a serviceable HMU is a part that has 

accumulated less than 800 operating hours since new or since last application 

of the Turboméca Mandatory Service Bulletin (MSB) A292 73 2847 version A.

(2) From the effective date of this AD, do not install an HMU on an engine, or 

an engine on a helicopter, unless in compliance with the requirements of 

paragraph (1) of this AD.

Ref. Publications: Turboméca MSB A292 73 2847 version A dated 29 May 2012.

The use of later approved revisions of this 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. This AD was posted on 29 June 2012 as PAD 12-069 for consultation until 

27 July 2012. No comments were received during the consultation period.

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:

Turboméca S.A., ARRIEL 2 Customer Support

40220 Tarnos, France

Fax: +33 5 59 74 45 15, or your usual or nearest TURBOMECA technical 

representative (refer to http://www.turbomeca-support.com).