EASA AD No.: 2016-0016

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

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Airworthiness Directive

AD No.: 2016-0016

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 operate 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].

Design Approval Holder’s Name:

TURBOMECA

Type/Model designation(s):

MAKILA 2 engines

Effective Date: 20 January 2016

TCDS Number(s): EASA.E.006

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.

These engines are known to be installed on, but not limited to, Airbus Helicopters (formerly 

Eurocopter) EC 225 LP helicopters.

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. After further investigation, it was determined that the application of 

Turbomeca Service Bulletin (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.: 2016-0016

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, Turbomeca 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.

For the reasons described above, this AD requires a one-time torque 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.

Ref. Publications:

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

The 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. 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.

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

Certification Directorate. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements 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.