EASA AD No.: 2013-0243

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.: 2013-0243

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 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):

ARRIUS 2F engines 

TCDS Number: France n°M22

Foreign AD: Not applicable

Supersedure: None

ATA 79 Oil – Nozzle Bonding on Ejector Assembly – Inspection

Manufacturer(s): TURBOMECA

Applicability: ARRIUS 2F engines, all serial numbers.

These engines are known to be installed on, but not limited to, Eurocopter

EC 120 B helicopters.

Reason: An in-flight shutdown (IFSD) occurred on an 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 engines 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 (MSB) 319 79 4835 which provides instructions for an 

inspection of the ejector assembly.

For the reasons described above, this AD requires a one-time inspection of the 

nozzle bonding on the ejector assembly and, depending on findings, 

accomplishment of the applicable corrective actions.

Effective Date: 15 October 2013
EASA AD No.: 2013-0243

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.

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 MSB 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 MSB 319 79 4835.

(2) If, during the inspection and the check as required by paragraph (1) of this 

AD, any discrepancy is detected, before next flight, replace the ejector 

assembly of the affected lubricating device with a serviceable part, or 

replace the lubricating 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 an engine containing a lubricating 

device with a S/N as listed in Turbomeca SB 319 79 4835 on a helicopter.

Ref. Publications: Turbomeca 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 content of the requirements in 

this 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.