E ASA AD No.: 20 1 4

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TE. CAP.0011 0

- 00 3 © 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 1 4

- 0 059

Date: 10 March 2014

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 EC 2042/2003 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 Age ncy [EC 2042/2003 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

F oreign AD: Not applicable

Supersedure: None



### ATA 7 7 Fuel System

– H igh P ressure F uel P ump D rive S plines

– Inspection

Manufacturer(s): Turbom e ca , S.A.

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

. These engines are known to be installed on, but not limited to, A i rbus
Hel i copters ( formerly Euro copter ) EC 225 LP helicopters.

Reason: T wo uncommanded in

- flight shutdowns on MAKILA 2A/2A1 engines have been reported . The results of the technical investigations concluded that these

eve nts were caused by deterioration of the splines on the High Pressure (HP) fuel pump drive link, which eventually interrupted the fuel supply to the engine.

This condition, if not detected and corrected, could lead to further cases of
uncommanded engine in

- flight shutdown, and may ultimately lead to an emergency landing

. To address these occurrences, T urbomeca publish ed Service Bulletin (SB) N° 298 73 2818 (Version s A through D) , to recommend inspection of the specific spline coupling area and report ing any damage. Turbomeca ’s understanding of the damage of HP fuel pump drive link splines improved and, consequently, a new fuel pump drive shaft was developed ( Turbomeca modification TU 59 ).
This modification

, available for in

- service application via SB N° 298 73 2059, improves lubrication and limits axial displacement of the HP pump drive shaft in the Module 01 drive gear. Turbomeca subsequently published Mandatory Service Bulletin (MSB) N° 298 73 2818 version E, applicable to engines fitted with pre

- mod TU 59 fuel pumps, to repetitively inspect the HP fuel pump drive
links.

For the reasons described above, t his AD requires repetitive inspections ofE ASA AD No.: 20 1 4

- 0 059

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. engines equipped with H P fuel pump with part number (P/N) 0 298 91 806 0 and P/N 0 298 91 805 0, and , depending on findings, accomplishment of the applicable corrective actions.

Effective Date: 24 March 2014

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

(1) For engines equipped with an HP fuel pump with P/N 0 298 91 806 0 or P/N 0 298 91 805 0 , within 25 f light h ours (FH) or 6 months, whichever

occurs first after the effective date of this AD, and thereafter, at intervals
not to exceed 1 00 FH, inspect the HP fuel pump/ metering valve and the module M01 drive gear in accordance with the instructions of Turbomeca
M SB N° 298 73 2818 Version E

.
Note: A non

- cumulative tolerance as defined in Turbomeca MSB N°
298 73 2818 may be applied to the actions specified in pa ragraph (1) of this
AD.

(2) If, during any inspection as required by paragraph (1) of this AD , a ny discrepancy (as defined in MSB N° 298 73 2818 ) is detected, before next flight, accomplish the applicable corrective actions in accordance with the instructions of Turbomeca MSB N° 298 73 2818 Version E

. (3) Inspections and corrective actions

, accomplished before the effective date of this AD in accordance with the instructions of Turbomeca SB
N° 298 73 2818 (all previous versions until Version D inclusive) are acceptable to comply with the initial requirements of paragraphs (1) and (2), as applicable.

( 4 ) From the effective date of this AD, for an engine equipped with an HP fuel

pump with P/N 0 298 91 806 0 or P/N 0 298 91 805 0

, install ation on an engine of an HP fuel pump drive shaft or an HP fuel pump or a module 01 or a module 01 77

- tooth gear is allowed, provided that upon installation of one of these parts, that engine passes the inspection of the HP pump/metering valve and t he module M01 drive gear , and thereafter , it is inspected as required by paragraph (1) of this AD

. ( 5 ) From the effective date of this AD, do not install an HP fuel pump on an engine, or an engine on a helicopter, unless it is in compliance with the requirements of this AD

.

Ref. Public ations: T urbomeca M SB N° 298 73 2818 Version E dated 11 February 201 4

. 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 14 February 2014 as PAD 1 4

- 040 for consultation
until 28 February 2014. No comments were received during the consultation period

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

- mail: ADs@easa.europa.eu

.
4. For any question concerning the technical content of the requirements in
this AD, please contact: Turboméca, 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

.