EASA AD No.: 2015

- 0162

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2 0 1 5

- 0162

Date: 0 6 August 2015

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 E U 748/2012 , Part 21

. A.3B. In accordance with EU 1321/2014 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 [ EU 1321/2014 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) :

A RRIEL 2 e ngines

TCDS Number: EASA

. E.001

F oreign AD: Not applicable

Supersedure: None



### ATA 7 2 E ngine

– Accessory Gear Box Module M01

– Inspection / Replacement

Manufacturer(s): T urbomé ca

Applicability: ARRIEL 2B, 2B1, 2B1A, 2B1B, 2C, 2C1, 2C 2, 2D, 2E, 2N, 2S 1 and 2S2 engines , all serial numbers

. These engines are k nown to be installed on, but not limited to, Airbus Helicopter s AS350B3, EC130B4, EC130T2, AS 365N3, EC155B and EC155 B1

, Airbus Helicopters Deutschland MBB

- BK 117 D

- 2 ( EC145T2 or H145), Avic international AC311 and Sikorsky S

- 76C helicopters.

Reason: A n uncommanded in

- flight shut

- down (IFSD) of an ARRIEL 2 engine was reported, caused by rupture of the 41

- tooth gear, which forms part of the bevel gear of the accessory gearbox (module M01). The subsequent i nvestigation revealed that wear on the housing of the front bearing of this gear was a major contributor to this rupture

. In addition, the investigation showed that this wear mechanism had r esulted in positive Spectrometric Oil Analysis (SOA) indications before the event.
This condition, if not detected and corrected, could potentially lead to further cases of IFSD, possibly resulting in a n emergency landing

. To address this potentially unsafe condition, Turbomé ca issued Mandatory Service Bulletin ( MSB ) 292 72 2861 to provide SOA check instructions

. For the reasons described above, this AD requires repetitive SOA checks and, depending on the results, replacement of the module M01.EASA AD No.: 2015

- 0162

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: 20 August 2015

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:
( 1 ) W ithin the compliance time specified in Table 1 of this AD , p erform a visual inspection in accordance with the instructions of Turbomé ca MSB 292 72 2861 to identify

, if a machined front casing Part Number ( P/N ) 0292120650 is installed on that engine.
( 2 ) For engines equipped with a module M01 fitted with a machined front casing P/N 0292 120650 (as identifi ed in Turbomé ca MSB 292 72 2861)

, within the compliance time specified in Table 1 of this AD, and, thereafter, at intervals not to exceed 100 EH, unless otherwise required by paragraph (3) and (4) of this AD, accomplish a SOA check in accordance with the instructions of Turbomé ca MSB 292 72 2861

.

Table 1

– Initial SOA check

Engine Hours (EH) accumulated by the Module M 01 ( since first installation on an engine or since last over hau l ) Compliance Time

Less than 80 0 EH Before exceeding 850 EH since first installation of the Module M01 on an engine

, or since last Module M01 overhaul, as applicable

800 EH or more , or EH not known Within 50 EH after the effective date of this AD

(3) If

, during any SOA check as required by paragraph ( 2 ) of this AD

, an aluminium concentration has value between 0.8 ppm and 1.4 ppm (inclusive), accomplish further SOA checks at intervals not to exceed 50 EH to comply with paragraph (2) of this AD.
( 4 ) If

, during any SOA check

, as required by paragraph ( 2 ) or ( 3 ) of this AD

, the aluminium concentration is above 1.4 ppm, within 50 EH after that SOA check

, replace the module M0 1 with a serviceable module M 01 (refer to paragraph ( 5 ) of this AD)

, in accordance with the instructions of Turbom é ca MSB 292 72 2861.
( 5 ) For the purpose of this AD, a serviceable module M01 is either a module M01 fitted with a machined front casing P/N 0292120650 , that is subjected to SOA checks in accordance with paragraph ( 2 ) and ( 3 ) of this AD, or a module M01 fitted with a casted front casing P/N 0292127020
( 6 ) From the effective date of this AD

, it is allowed to install a module M01 fitted with a machined front casing P/N 0292120650 , provided it is subjected to SOA checks in accordance with paragraph ( 2 ) and ( 3 ) of this AD.

Ref. Public ations: Turbomé ca MSB 292 72 2861 version A dated 24 April 2015.
The use of later approved revisions of th is 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 23 June 2015 as PAD 15

- 0 79 for consultation until 21 July 2015. No comments were received during the consultation period.

3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E

- mail: ADs@easa.europa.eu

.EASA AD No.: 2015

- 0162

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 4. For any question concerning the technical content of the requirements i n 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

- su pport.com ).