EASA AD No.: 2015-0049

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0049

[Correction: 07 May 2015]

Date: 17 March 2015

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 EU 1321/2014 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 

[EU 1321/2014 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 – Oil Pump Drive Link / Lubricating Device – Inspection

Manufacturer(s): Turbomeca S.A.

Applicability: ARRIUS 2F engines, all serial numbers.

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

Helicopters (formerly Eurocopter, Eurocopter France) EC 120 B helicopters.

Reason: A risk of an in-flight shut-down (IFSD) has been identified on an ARRIUS 2F 

engine, due to deterioration of gas generator front bearing. This could be the

result of lack of lubrication, due to a link loss between pump driver and oil 

pump shaft.

This condition, if not detected and corrected, could lead to cases of IFSD, 

possibly resulting in forced landing with consequent damage to the helicopter 

and injury to occupants.

To address this potential unsafe condition, Turbomeca published Mandatory 

Service Bulletin (MSB) No 319 79 4834 to provide inspection instructions. 

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

the oil pump drive shaft, and, depending on findings, accomplishment of 

applicable corrective actions. 

This AD is republished to correct a typographical error in paragraph (5).

Effective Date: 31 March 2015
EASA AD No.: 2015-0049

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Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) For engines equipped with an oil pump having Part Number (P/N) 

0319155050, within the compliance time specified in Table 1 of this AD, 

as applicable, depending on the engine hours (EH) accumulated on the 

effective date of this AD, inspect the pump driver assembly on the oil 

pump shaft, the pump driver splines and the oil pump splines, in 

accordance with the instructions of Turbomeca MSB N° 319 79 4834 

version B.

Table 1 – One-time Inspection

(2) If, during the inspection as required by paragraph (1) of this AD, a 

discrepancy is detected, before next flight, replace the oil pump driver 

assembly and/or the oil pump shaft, or replace the affected oil pump, in 

accordance with the instructions of Turbomeca MSB N° 319 79 4834 

version B.

(3) Inspection (of the oil pump driver assembly on the oil pump shaft and of 

the pump driver splines and the oil pump splines) and corrective action,

accomplished before the effective date of this AD in accordance with the 

instructions of Turbomeca MSB N° 319 79 4834 version A, is acceptable 

to comply with the requirements of paragraphs (1) and (2) of this AD.

(4) An engine that is equipped with an oil pump P/N 0319155050, which was

overhauled in a Turbomeca repair centre after 01 January 2013, is not 

affected by the requirements of this AD.

(5) An engine that has a serial number higher than 34 775 is not affected by 

the requirements of this AD, provided it is determined that, since first flight 

of that engine on a helicopter, the oil pump has not been replaced on that 

engine.

EH since new, or since last 

overhaul, or since last 

installation of an affected oil 

pump, whichever occurred later

Compliance Time

Less than 250 EH Before exceeding 300 EH since 

new, or since overhaul, or since 

last installation of an affected oil 

pump, as applicable

250 EH or more, but less than 

300 EH

Within 50 EH after the effective 

date of this AD

300 EH or more but less than 

800 EH

Within 100 EH after the effective 

date of this AD

More than 800 EH During the next scheduled 500 EH

inspection

Ref. Publications: Turbomeca SB N° 319 79 4834 version A dated 25 November 2013, or 

Version B dated 21 October 2014.

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 12 February 2015 as PAD 15-012 for consultation 

until 12 March 2015. No comments were received during the consultation 

period.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu.
EASA AD No.: 2015-0049

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4. For any question concerning the technical content of the requirements in 

this AD, please contact:

Turbomeca, S.A., ARRIUS Customer Support, 40220 TARNOS, FRANCE. 

Fax: +33 5 59 74 45 15 or contact your usual or nearest technical 

representative at www.turbomeca-support.com.