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) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the E uropean Community, its Member States and of the European third countries that participat e 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an Airworthiness Direc tive applies, except in accordance with the require ments 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) exemp tion].



### 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 Inst allation and Operating Manual), and equipped with a Digital Engine Control Unit (DECU) having a serial number (S/N) listed in TURBOMECA Mandatory S ervice Bulletin A298 73 2815 Version A, which has not been returned to a n 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 MA KILA 2A1 engines have an ambient pressure (P0) sensor with a measurement acc uracy that may be outside the range required for satisfactory functio ning of the engines throughout the entire operating envelope. In certai n extreme flight conditions, the lack of P0 measurement accuracy could potential ly cause an engine flameout if the engine is operating on a replacemen t fuel.

The issue is limited to a batch of 24 DECUs, of whi ch 23 are known to be still in service. Since 01 January 2010, any such DECU re turned to an approved repair centre has had its P0 sensor checked and rep laced 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 r etaining 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 serv iceable parts.

This AD has been republished to correct several typ ographic mistakes on the superseded AD number.

Effective Date: 14 April 2010

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:

1. For any engine controlled by a DECU whose S/N is listed in TURBOMECA Mandatory Service Bulletin A298 73 2815 V ersion A and which is paired with another DECU with a S/N li sted in TURBOMECA Mandatory Service Bulletin A298 73 2815 V ersion A on the same helicopter, before the next flight after t he effective date of this AD, replace one affected DECU with a serviceable pa rt, 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 li sted in TURBOMECA Mandatory Service Bulletin A298 73 2815 V ersion A and which is paired with a DECU with a S/N not list ed in TURBOMECA Mandatory Service Bulletin A298 73 2815 Version A o n the same helicopter, within 75 FH after the effective date o f 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 approve d repair centre and had its P0 sensor checked and replaced as necessary

.

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

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

The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.

2. The safety assessment has requested not to imple ment the full consultation process and an immediate publication a nd notification.

3. Enquiries regarding this AD should be referred t o the Airworthiness Directives, Safety Management & Research Section, C ertification Directorate, EASA. E-mail ADs@easa.europa.eu

4. For any question concerning the technical conten t 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 TURBOMEC A field representative at http://www.turbomeca-support.com