EASA AD No.: 2013-0082

TE.CAP.00110-003 © 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.: 2013-0082

Date: 02 April 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 2 engines 

TCDS Number: EASA.E.029

Foreign AD: Not applicable

Supersedure: None

ATA 73 Engine Fuel & Control – Hydro-mechanical Metering Unit / DriveLink Splines – Inspection

Manufacturer(s): TURBOMECA

Applicability: ARRIUS 2B1, 2B1A, 2B2, 2K1, 2K2 and 2G1 engines, all serial numbers.

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

Deutschland EC135, Agusta A109 and KAMOV 226T twin-engine helicopters.

Reason: A number of in-flight shutdown occurrences have been reported for ARRIUS 2 

engines. The results of the technical investigations concluded that these events 

were caused by deterioration of the splines on the High Pressure (HP) / Low 

Pressure (LP) pump assembly drive shaft of the Hydro-mechanical Metering 

Unit (HMU), which eventually interrupted the fuel supply to the engine. 

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

engine in-flight shutdown, possibly resulting in forced landing.

To address these occurrences, TURBOMECA published Service Bulletin (SB) 

N° 319 73 2825, which provides inspection instructions. After that SB was 

issued, further similar occurrences prompted TURBOMECA to perform a new 

assessment of the issue. As a result, it was determined that repetitive 

inspections of the HMU, including an additional inspection of the sleeve 

assembly, was necessary to address the issue. Those instructions are provided 

in TURBOMECA Mandatory SB (MSB) N° 319 73 2825 version G.

For the reasons described above, this AD requires repetitive inspections of 

drive gear shaft splines of the HP pump, and depending on findings, 

accomplishment of applicable corrective actions.
EASA AD No.: 2013-0082

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Effective Date: 16 April 2013

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time specified in Table 1 or Table 2 of this AD, as 

applicable, depending on HMU condition, and, thereafter, at intervals not to 

exceed 500 HMU operating hours, accomplish a visual inspection of the 

drive gear shaft splines of the HP pump and, clean and inspect the sleeve 

assembly splines in accordance with the instructions of TURBOMECA

MSB N° 319 73 2825 version G.

Note: a maximum of 10 % tolerance can be applied to the defined 

inspection interval. This tolerance cannot be used accumulatively during 

two successive inspections.

Table 1 - Initial inspection for HMU that have previously been inspected in 

accordance with TURBOMECA SB N° 319 73 2825 (at any version)

HMU condition Compliance Time

HMU has accumulated 500 

operating hours or more since 

last inspection

Within 200 HMU operating hours 

after the effective date of this AD

HMU has accumulated less 

than 500 operating hours since 

last inspection

Before exceeding 500 HMU 

operating hours since the last 

inspection in accordance with 

TURBOMECA SB N° 319 73

2825 (any version)

Table 2 – Initial inspection for HMU that have never been inspected in 

accordance with TURBOMECA SB N° 319 73 2825 (at any version)

HMU condition Compliance Time

HMU has accumulated 200 

operating hours or more since 

new or since last overhaul

Within 50 HMU operating hours 

after the effective date of this AD

HMU has accumulated less 

than 200 operating hours since 

new or since last overhaul

Before exceeding 200 HMU 

operating hours since new or 

since last overhaul

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

discrepancy is detected, before next flight, replace the sleeve assembly on 

the affected HP pump drive gear shaft, or replace the affected HMU in 

accordance with the instructions of TURBOMECA MSB N° 319 73 2825

version G.

(3) Replacement of a sleeve assembly or an HMU, as required by paragraph 

(2) of this AD, does not constitute terminating action for the repetitive 

inspections required by paragraph (1) of this AD for that engine.

(4) From the effective date of this AD, installation of an HMU on an engine, or 

an engine on a helicopter, is allowed, provided that the HMU is inspected 

and, depending on findings, corrected, as required by paragraphs (1) and 

(2) of this AD.

Ref. Publications: TURBOMECA MSB N° 319 73 2825 version G dated 24 January 2013.

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD.
EASA AD No.: 2013-0082

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 04 March 2013 as PAD 13-040 for consultation until 

01 April 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:

TURBOMECA, 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.