EASA AD No.: 201 6

- 0016

TE.CAP.00110

- 005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet.

An agency of the European Union Page 1 of 2 

# Airworthiness Directive

AD No.: 201 6

- 0 016

Issued : 15 January 2016

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) 216/2008 on behalf of the European Union , 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 Regulation ( EU ) 748/2012, Part 21.A.3B. In accordance with Regulation ( 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 [ Regulation ( EU ) 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [ Regulation ( EC ) 216/2008, Article 14(4) exemption]

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### Design Approval Holder’s Name:

TURBOMECA Type/Model designation(s):

MAKILA 2 engines

Effective Date: 20 January 2016

TCDS Number (s) : EASA.E.0 0 6

Foreign AD: Not applicable

Supersedure: None



### ATA 72

– Engine

– Power Turbine Module 04 Bearing Supply Swivel Union

– Check of Tightening Torque

Manufacturer(s): Turbomeca, S.A.

Applicability: MAKILA 2A and MAKILA 2A1 engines, all serial numbers

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These engines are known to be installed on, but not limited to, Airbus Helicopters (formerly Eurocopter) EC 225 LP helicopters

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Reason:
Two occurrences of commanded in

- flight shut down following low oil pressure warning were reported. In both cases the nut attaching the swivel union to the power turbine module 04 was found completely loose. Aft er further investigation, it was determined t hat the application of
Turbomeca S ervice B ulletin (SB) N° 298 79 2831 may have led to incorrect torque application or loosening of the nut.

This condition, if not detected and corrected, could lead to an engine fire, possibly resulting in an emergency landing.EASA AD No.: 201 6

- 0016

TE.CAP.00110

- 005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet.

An agency of the European Union Page 2 of 2 Prompted by these occurrences, Turb omeca published Mandatory Service Bulletin (MSB)

N° 298 72 2835 to provide instructions to check the tightening torque on the nut attaching the swivel union to the power turbine module 04

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For the reasons described above, this AD requires a one

- time torq ue control of the affected nut.

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:

Note 1: For the purpose of this AD, an affected engine is an engine on which Turbomeca SB

N° 298 79 2831 is embodied.

( 1 ) For an affected engine, within 7 days or 30 engine hours, whichever occurs first after the
effective date of this AD

, apply the torque on the nut attaching the swivel union to the power
turbine module 04 in accordance with the instructions of Turbomeca MSB N° 298 79 2835.

Condition for installation of an affected engine on a helicopter: ( 2 ) From the effective date of this AD, it is allowed to install an affected engine on a helicopter, provided that, before installation of that engine, the nut attaching the swivel union to the power turbine module 04 of that engine is torqued in accordance with the instructions of
Turbomeca MSB N° 298 79 2835

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Ref. Publications:
Turbomeca MSB N° 298 72 2835 Version A dated 15 January 2016

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The use of later appro ved revisions of this document is acceptable for compliance with the requirements of this AD

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Remarks:

1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.

2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments, postponing the public consultation process until after publication

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

- mail: ADs@easa.europa.eu

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4. For any question concerning the technical content of the requirem ents in this AD, please

contact : Turbomeca, S.A., MAKILA Customer Support, 40220 TARNOS, FRANCE. Fax: +33 5 59 74 45 16; or contact your nearest technical representative at www.turbomeca

- support.com

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