EASA AD No: 2012

- 0 231

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through th e EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 2

- 0231

Date: 02 Novem ber 201 2

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 i s issued in accordance with E U 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 1 A2 engine s

TCDS Number : EASA.E.072

F oreign AD : Not applicable

Supersedure : None



### ATA 7 7 Engine Indicating

– N2 Sensor H arness

– Replacement

Manufacturer(s): TURBOMECA

Applicability: MAKILA 1A2 engines, all serial numbers

. These eng ines are known to be installed i n, but are not limited to, Eurocopter
AS 332 L2 helicopters.

Reason: An event occurred in which , during start of a MAKILA 1A2 engine , a fluctuation was observed in the N2 spe ed. Event analysis led to remov al and investigation of th e N2 harness . D uring the investigation, c orrosion w as detected i n the h arnes s , inside the cable sheath at the splices with the sensor

coils.

Further quality investigations performed with the harness supplier led to the
conclusion that this occurrence was due to a manufacturing error. N2 sensor

harness es Part Number (P/N) 0 30 1 52 001 0 having Serial Number (S/N)

691 through 705 inclusive

, or S/N 707 through 728 inclusive

, or S/N 813 through 844 inclusive

, are potentially affected by the same manufacturing discrepancy.

This condition, if not corrected, could lead to the inadver tent activation of the
65% N1 (gas generator rating) back up mode and consequently to a significant power loss on one or both engine s i nstalled on the same helicopter, potentially resulting in an emergency landing of the helicopter.

For the reasons describ ed above, this AD requires replacement of affected N2 sensor harnesses with serviceable parts. This AD also prohibits theEASA AD No: 2012

- 0 231

TE. CAP.00110

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

- Internet/Intranet. installation of an affected N2 sensor harness on an engine.

Effective Date: 16 November 2012

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

(1) For engines equipped with N2 sensor harnesses P/N 0 301 52 001 0 having S /N 691 through 705 inclusive

, or S/N 707 through 7 28 inclusive

, or S/N 813 through 844 inclusive , accomplish the followi ng actions, in accordance with the instructions of Turbomeca Mandatory Service

Bulletin (MSB) 298 77 0821:

(1.1) Affected P/N is installed on each of the 2 (two) engines of the helicopter: within 10 Flight Hours (FH) after the effective date of this AD, re place one N2 sensor harness with a serviceable part, and within 50 FH after the effective date of this AD, replace the second harness with a serviceable part.

(1.2) Affected P/N is installed only on 1 (one) engine of the helicopter:
within 50 FH after the effective date of this AD, replace the affected N2 sensor harness with a serviceable part.

Note : For the purpose of this AD, a serviceable N2 sensor harness P/N 0 301
52 001 0 is defined as a part not having S /N 691 through 705 inclusive

, or S/N

707 throug h 728 inclusive

, or S/N 813 through 844 inclusive.

(2) After modification of an engine as required by paragraph (1) of this AD, do not install in an engine an N2 sensor harnesses P/N 0 301 52 001 0 having S /N 691 through 705 inclusive

, or S/N 707 through 7 28 inclusive

, or S/N 813 through 844 inclusive

. (3) After the effective date of this AD, do not install in a helicopter an engine equipped with an N2 sensor harnesses P/N 0 301 52 001 0 having S /N

691 through 705 inclusive

, or S/N 707 through 728 inclusive

, or S/N 813 through 844 inclusive

.

Ref. Public ations: TURBOMEC A MSB 2 98 7 7 0821 Version A

. 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 subst antiated, EASA can approve Alternative Methods of Compliance for this AD

.

2. Based on t he required actions and the compliance time, EASA have

decided to issue a Final AD with Request for Comments, postponing the public consultation process until after publica tion

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 questions concerning the technical conte nt of the requirements

in this AD, please contact:

Operator Support & Sales MAKILA
TURBOMECA 40220 TARNOS

– FRANCE Phone: +33 (0)5 59 74 40 28 Fax: +33 (0)5 59 74 45 16 or refer to your
nearest TURBOMECA fie l d representative on : http://www.turbomeca

- support.com

.