EASA AD No.: 2015-0209

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0209

Date: 16 October 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 EU 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 operate 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):

MAKILA 2 engines

TCDS Number: EASA.E.006

Foreign AD: Not applicable

Supersedure: None

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 incorporated in service 

with Turbomeca Sevice 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 of crack initiation were reported on a ferrule of diffuser Part 

Number (P/N) 0298210100, which propagated and led to the ferrule rupture.

The investigation shows in both cases that 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.

Prompted by these occurrences, Turbomeca published Mandatory Service 

Bulletin (MSB) N° 298 72 2832 to provide repetitive inspection instructions.

For the reasons described above, this AD requires repetitive inspections of the 

affected diffuser and, depending on findings, accomplishment of the applicable 

corrective action(s).

Effective Date: 30 October 2015
EASA AD No.: 2015-0209

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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 the effective date of this 

AD, whichever occurs later, as applicable, and, thereafter, at intervals not 

to exceed 50 EH, accomplish a boroscope 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 boroscope inspection of the ferrule of diffuser P/N 0298210100

accomplished, before the effective date of this AD, in accordance with the 

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

comply with the initial boroscope 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.

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. 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 Safety Information 

Section, Certification Directorate, EASA. 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.