E ASA AD No.: 20 13

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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 13

- 0 243

Date: 01 October 2013

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):
ARRIUS 2F engines

TCDS Number: France n°M22

F oreign AD: Not applicable

Supersedure: None



### ATA 79 Oil

– Nozzle Bonding on Ejector Assembly

– I nspection

Manufacturer(s): TURBOMECA

Applicability: ARRIUS 2F engines , all serial numbers.
These engines are known to be installed on, but not limited to, Euro copter EC 120 B helicopters.

Reason: An i n

- f light s hut d own (IFSD) occurred on a n ARRIEL 1 engine

, as a result of incorrect bonding of the nozzle on the ejector assembly fitted to the engine

. The subsequent technical investigation concluded that ARRIUS 2F engine s are also potentially affected and it was possible to identify a batch of parts that could have this non

- conformity.
This condition, if not detected and corrected, could lead to further cases of IFSD , possibly resulting in forced landing.

To address this potential unsafe condition, Turbomeca published Mandatory Service Bulletin ( M SB) 319 79 4835 which provide s instruction s for an inspection of the ejector assembly.
For the reasons described above, this AD requires a one

- time inspection of the nozzle bondin g on the ejector assembly and, depending on findings, accomplishment of the applicable corrective actions

.

Effective Date: 15 October 2013E ASA AD No.: 20 13

- 0 243

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. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:
(1) For engines equipped with a lubricating device having a Serial Number (S/N) as listed in Turbomeca M SB 319 79 4835 , within 30 days after the effective date of this AD, accomplish a visual inspection of the nozzle of the ejector assembly and a check of the tightening torque in accordance with the instructions of Turbomeca M SB 319 79 4835

. (2) If, during the inspection and the check as required by paragraph (1) of this AD, a ny discrepancy is detected, before next flight, replace the ejector assembly o f the affected lubricati ng device with a serviceable part , or replace the lubricati ng device with a serviceable part in accordance with the instructions of Turbomeca MSB N° 319 79 4835.
(3 ) From the effective date of this AD, do not install on an engine an ejector assembly containing a lubricating device with a S/N as listed in Turbomeca SB 319 79 4835

, and do not install a n engine containing a lubricating device with a S/N as listed in Turbomeca SB 319 79 4835 on a helicopter

.

Ref. Public ations: T urbomeca SB 319 79 4835 original issue A dated 22 May 2013

. 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 16 September 2013 as PAD 13

- 141 for consultation until 30 September 2013. 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 conte nt of the requirements in th is AD, please contact: Turboméca, S.A., ARRIUS Customer Support, 40220 TARNOS, FRANCE. Fax: +33 5 59 74 45 15; or contact your nearest technical representative at www.turbomeca

- support.com

.