EASA AD No.: 20 12

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CAP. 0011 0

- 00 1 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 12

- 0 150

Date: 08 August 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 ope rate 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]

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### Design Approval Holder’s Name:

TURBOMECA Type/Model designation(s):
ARRIUS 2F engines

TCDS Number: France n°M22

F oreign AD: Not applicable

Supersedure: This AD supersedes DGAC AD 1999

- 233 (A) dated 12 June 1999

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### ATA 73 Engine Fuel & Control

– P rivilege Injector

– Replacement

Manufacturer(s): Turboméca

Applicability: ARRIUS 2F engines, all serial numbers.
These engines are known to be installed on, but not limited to, Eurocopter EC120B helicopters

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Reason: During inspections carried out at the repair workshop on variants similar to ARRIUS 2F, it was found that some main injectors were totally or partially blocked. Blockage of the injectors may lead to engine flame out during rapid engine deceleration.

This condition, if not corrected, could lead to an uncommanded engine in

- flight shut down and may ultimately lead to an emergency landing

. To address this unsafe condition, DGAC i ssued AD 1999

- 0233 (A) which required periodical replacement of fuel manifolds

. Since issuance of AD 1999

- 0233 (A) , f urther investigations demonstrated that:

a periodic flow rate check (water technology) and the cleaning required by DGAC AD 1999

- 0233 (A) did not meet the expect ed results (wrong indication and non

- sufficient cleaning)

, and, replacement of the privilege injector only ensure s the airworthiness of the engine in case of blockage of the injection manifolds combined with a rapid engine deceleration

. For the reasons described above, this AD requires replacement of the privilege injector before exceeding a defined limit of operating hours as specified in Turboméca Mandatory Service Bulletin (MSB) N° A319 73 4001

.EASA AD No.: 20 12

- 0 150

CAP. 0011 0

- 00 1 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: 22 August 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:
(1) Before exceeding 400 privilege injector operating hours since new or 400 privilege injector operating hours since last accomplishment of Turbom é ca Mandatory Service Bulletin (MSB) N° A 319 73 4001 , as applicable, replace the privilege injector with a serviceable privilege injector

. Note: For the purpose of this AD, a serviceable privilege injector is a part that has accumulated less than 400 operating hours since new or since last accomplishment of Turboméca MSB N° A 319 73 4001

. (2) From the effective date of this A D, do not install a privilege injector on an engine , or an engine on a helicopter, unless in compliance with the requirements of paragraph (1) of this AD.

Ref. Public ations: TURBOMECA MSB N° A319 73 4001 issue K dated 10 February 2012

. T he 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 approve Alternative Methods of Compliance for this AD.

2. This AD was posted on 10 Ju ly 2012 as PAD 1 2

- 0 78 f or consultation until 07 August 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., ARRIUS Customer Support, 40220 TARNOS, FRANCE. Fax: +33 5 59 74 45 15; or contact your nearest technical representative at www.turbomeca

- support.com

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