EASA AD No.: 2015-0209R1

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Airworthiness Directive

AD No.: 2015-0209R1

Issued: 20 April 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: Revision 1: 27 April 2016

Original issue: 30 October 2015

TCDS Number(s): EASA.E.006

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2015-0209 dated 16 October 2015.

ATA 72 – Engine – Centrifugal Diffuser Ferrule – Inspection

Manufacturer(s):

TURBOMECA

Applicability:

MAKILA 2A and MAKILA 2A1 engines, all serial numbers, if Turbomeca modification (Mod) TU 52 is 

embodied in production, or modified in service by Turbomeca Service Bulletin (SB) 298 72 2052.

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

Eurocopter) EC 225 LP helicopters.

Reason:

Two occurrences were reported of crack initiation on a ferrule of diffuser Part Number (P/N) 

0298210100, which propagated and led to the ferrule rupture. The investigation shows that in both 

cases, the ruptured ferrule contacted and punctured the main fuel supply line, resulting in a fuel 

leak.

This condition, if not detected and corrected, could lead to an engine fire, consequently triggering 

an uncommanded engine in flight shut down, possibly resulting in an emergency landing.
EASA AD No.: 2015-0209R1

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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Prompted by these occurrences, Turbomeca published Mandatory Service Bulletin (MSB) N° 

298 72 2832 to provide repetitive inspection instructions.

Consequently, EASA issued AD 2015-0209 to require repetitive borescope inspections of the 

affected diffuser and, depending on findings, accomplishment of the applicable corrective action(s).

Since that AD was issued, Turbomeca demonstrated that the interval for the repetitive inspection 

could be extended.

For the reason described above, this AD is revised and extends the interval for the borescope

inspection.

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance times specified in the Table of Turbomeca MSB N° 298 72 2832, or 

within 30 engines hours (EH) after 30 October 2015 [the effective date of this AD at original 

issue], whichever occurs later, as applicable, and, thereafter, at intervals not to exceed 300 EH, 

accomplish a borescope inspection of the ferrule of diffuser P/N 0298210100 in accordance 

with the instructions of Turbomeca MSB N° 298 72 2832 Version B (or later).

Note: A non-cumulative tolerance as defined in Turbomeca MSB N° 298 72 2832 may be applied to 

the actions specified in paragraph (1) of this AD.

(2) If, during any inspection as required by paragraph (1) of this AD, any discrepancy, as defined in 

Turbomeca MSB N° 298 72 2832, is detected, before next flight, accomplish the applicable 

corrective actions in accordance with the instructions of Turbomeca MSB N° 298 72 2832 

Version B (or later).

(3) Accomplishment of corrective action(s) on an engine, as required by paragraph (2) of this AD, 

does not constitute terminating action for the repetitive inspections as required by paragraph 

(1) of this AD for that engine.

(4) A borescope inspection of the ferrule of diffuser P/N 0298210100 accomplished, before 

30 October 2015 [the effective date of this AD at original issue], in accordance with the 

instructions of Turbomeca MSB N° 298 72 2832 Version A is acceptable to comply with the 

initial borescope inspection as required by paragraph (1) of this AD.

Ref. Publications:

Turbomeca MSB 298 72 2832 Version A dated 03 September 2015, or Version B dated 12 October 

2015, or Version C dated 15 April 2016.

The use of later approved revisions of this document is acceptable for compliance with the 

requirements of this AD.
EASA AD No.: 2015-0209R1

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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Remarks:

1. If requested and appropriately substantiated, EASA can approve Alternative Methods of 

Compliance for this AD.

2. The original issue of this AD was posted on 11 September 2015 as PAD 15-123 for consultation 

until 09 October 2015. The Comment Response Document can be found at 

http://ad.easa.europa.eu.

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.