E ASA AD No.: 20 1 5

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- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 15

- 0 049 [Correction: 07 May 2015]

Date: 17 March 201 5

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 ope rate an aircraft to which an AD applies, except in accordance w ith 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) exemp tion]

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### Design Approval Holder’s Name:

TURBOMECA Type/Model designation(s):
ARRIUS 2F engines

TCDS Number: France n°M22

F oreign AD: Not applicable

Supersedure: No ne



### ATA 7 9 Oil

– O il Pump D rive L ink / Lubricating D evice

– 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 i n

- flight shut

- d own (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 los s 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 o n findings, accomplishment of applicable corrective actions.
This AD is republished to correct a typographical error in paragraph (5).

Effect ive Date: 31 March 2015E ASA AD No.: 20 1 5

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- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 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) F or engines equipped with a n oil pump having Part Number (P/N) 0319155050 , w ithin 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 ver sion A , is acceptable to comply with the requirements of paragraphs (1) and (2) of this AD.
(4) An engine that is equipped with a n oil pump P/N 0319155050

, which was overhauled in a Turbomeca repair centre after 01 January 2013, is not affected by the require ments of this AD.
(5) An engine that has a serial number higher than 34 77 5 is not affected by the require ments of this AD, provided it is determined that, since first flight of that engin e on a helicopter, the oil pump has not been replaced on that engine

. E H s ince n ew, or s ince last

o verhaul , or s ince last i nstallation of an affected oil
pump , whichever occurred later Compliance Time

Less than 250 EH Before exceeding 300 EH since

n ew, or since o verhaul, or since last i nstallation of an affected oil
pump , as applicable

250 EH or m ore , 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

M ore than 800 EH During the next scheduled 500 EH inspection

Ref. Public ations: Turbomeca SB N° 319 79 483 4 version A dated 25 November 2013, or Version B dated 2 1 October 201 4

. 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 co nsultation 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

.E ASA AD No.: 20 1 5

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TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 4. For any question concerning the technical content of the requirements in thi s 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

.