EASA AD No.: 2014-0059

TE.CAP.00110-003 © 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.: 2014-0059

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 Agency [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

Foreign AD: Not applicable

Supersedure: None

ATA 77 Fuel System – High Pressure Fuel Pump Drive Splines – Inspection

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 uncommanded in-flight shutdowns on MAKILA 2A/2A1 engines have been 

reported. The results of the technical investigations concluded that these 

events 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, Turbomeca published Service Bulletin (SB) N° 

298 73 2818 (Versions A through D), to recommend inspection of the specific 

spline coupling area and reporting 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, this AD requires repetitive inspections of 
EASA AD No.: 2014-0059

TE.CAP.00110-003 © 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 HP 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 flight hours (FH) or 6 months, whichever 

occurs first after the effective date of this AD, and thereafter, at intervals 

not to exceed 100 FH, inspect the HP fuel pump/metering valve and the 

module M01 drive gear in accordance with the instructions of Turbomeca 

MSB 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 paragraph (1) of this 

AD.

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

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, installation 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 the 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. Publications: Turbomeca MSB N° 298 73 2818 Version E dated 11 February 2014.

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 14-040 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 16; or contact your nearest technical representative at 

www.turbomeca-support.com.