EASA AD No.: 20 15

- 0209

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 15

- 0 209

Date: 1 6 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 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):

M AKILA 2 engines

TCDS Number: EASA. E.006

F oreign AD: Not applicable

Supersedure: None



### ATA 72 Engine

– Centrifugal Diffuser Ferrule

– Inspection

Manufacturer(s): Turbom e ca

Applicability: MAKILA 2A and MAKILA 2A1 engines , all serial numbers , if T urbomeca 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 Euro copter ) EC 225 LP helicopters.

Reason: Two occurrence s 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 ma in fuel supply line , resulting in a fuel leak.

Th is condition, if not detected and corrected, could lead to a n engine fire

, consequently triggering an un commanded engine in flight shut down , po ss i b ly resulting in an emergency landing

. Prompted by these occurrences, T urbomeca publish ed Mandatory Service Bulletin ( M SB) N° 298 7 2 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 2015EASA AD No.: 20 15

- 0209

TE. CAP.0011 0

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

- Internet/Intranet. Required A ction(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 7 2 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 boroscop e inspection o f the ferrule of diffuser P / N 0298210100 in accordance with the instructions of Turbomeca MSB N° 298 7 2 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 7 2 28 32

, is detected, before next flight, accomplish the applicable corrective actions in

accor dance 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

acco mplished , before the effective date of this AD, in accordance with the instructions of Turbomeca MSB N° 298 7 2 2832 Version A is acceptable to comply with the initial boroscope inspection as required by paragraph (1) of this AD.

Ref. Public ations: Turbomeca M SB 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 i n this AD, please contact: Turbome ca, S.A., MAKILA Customer Support, 40220 TARNOS, FRANCE. Fax: +33 5 59 74 45 1 6 ; or contact your nearest technical representative at www.turbomeca

- support.com

.