EASA AD No.: 2010-0068-E 

EASA Form 110 Page 1/2

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0068-E 

[corrected: 13 April 2010] 

Date: 12 April 2010 

Note: This Emergency 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 EC 1702/2003, Part 21A.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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness 

Directive 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]. 

Type Approval Holder’s Name : 

TURBOMECA 

Type/Model designation(s) : 

MAKILA 2A and MAKILA 2A1 turboshaft 

engines 

TCDS Number : EASA.E.006 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2010-0055 dated 25 March 2010. 

ATA 73 Engine Fuel & Control – Digital Engine Control Unit – 

Replacement 

Manufacturer: TURBOMECA 

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

required to operate on replacement fuels (the list of approved normal and 

replacement fuels is contained in the MAKILA 2 Installation and Operating 

Manual), and equipped with a Digital Engine Control Unit (DECU) having a 

serial number (S/N) listed in TURBOMECA Mandatory Service Bulletin A298 

73 2815 Version A, which has not been returned to an approved repair 

centre since 01 January 2010. 

These engines are known to be installed in, but are not limited to, 

EUROCOPTER EC225 LP helicopters. 

Reason: Some DECUs used to control MAKILA 2A and MAKILA 2A1 engines have an 

ambient pressure (P0) sensor with a measurement accuracy that may be 

outside the range required for satisfactory functioning of the engines 

throughout the entire operating envelope. In certain extreme flight conditions, 

the lack of P0 measurement accuracy could potentially cause an engine 

flameout if the engine is operating on a replacement fuel. 

The issue is limited to a batch of 24 DECUs, of which 23 are known to be still 

in service. Since 01 January 2010, any such DECU returned to an approved 

repair centre has had its P0 sensor checked and replaced as necessary. 

EASA AD 2010-0055 was issued to reduce the risk of complete loss of power 

due to engine flameout and required the replacement of the affected DECU. 
EASA AD No.: 2010-0068-E 

EASA Form 110 Page 2/2

This AD, which supersedes EASA AD 2010-0055 while retaining its 

requirements, is issued to extend the applicability of the AD to 2 other DECU 

(S/N 201 & S/N 234) and to delete 2 DECU (S/N 141 & S/N 266) from the 

applicability of the AD. S/N 141 & S/N 266 are serviceable parts. 

This AD has been republished to correct several typographic mistakes on the 

superseded AD number. 

Effective Date: 14 April 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

1. For any engine controlled by a DECU whose S/N is listed in 

TURBOMECA Mandatory Service Bulletin A298 73 2815 Version A 

and which is paired with another DECU with a S/N listed in 

TURBOMECA Mandatory Service Bulletin A298 73 2815 Version A on 

the same helicopter, before the next flight after the effective date of this 

AD, replace one affected DECU with a serviceable part, and, within the 

next 75 Flight Hours (FH), replace the second DECU with a 

serviceable part. 

2. For any engine controlled by a DECU whose S/N is listed in 

TURBOMECA Mandatory Service Bulletin A298 73 2815 Version A 

and which is paired with a DECU with a S/N not listed in TURBOMECA 

Mandatory Service Bulletin A298 73 2815 Version A on the same 

helicopter, within 75 FH after the effective date of this AD, replace the 

affected DECU with a serviceable part.

3. After the effective date of this AD, do not install in an aircraft any DECU 

listed in TURBOMECA Mandatory Service Bulletin A298 73 2815 

Version A unless it has been returned to an approved repair centre and 

had its P0 sensor checked and replaced as necessary.

Ref. Publications: TURBOMECA Mandatory Service Bulletin A298 73 2815 Version A. 

MAKILA 2 Installation and Operating Manual X 298 N7 001 2. 

The use of later approved revisions of these documents 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. The safety assessment has requested not to implement the full 

consultation process and an immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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: Operator Support MAKILA – TURBOMECA 

40220 TARNOS – FRANCE, Phone: +33 (0)5 59 74 40 00, Fax: +33 

(0)5 59 74 45 15, or refer to your nearest TURBOMECA field 

representative at http://www.turbomeca-support.com