EASA AD No : 2015-0211

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0211

Date: 15 October 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) :

ASTAZOU XIV engines

TCDS Number: EASA.E.075

Foreign AD : Not applicable

Supersedure : This AD supersedes EASA AD 2010-0004 dated 5 January 2010.

ATA 72 Engine – Third Stage Turbine Wheel – Inspection

Manufacturer(s): Turbomeca

Applicability: ASTAZOU XIV B and XIV H engines, all serial numbers, if fitted with a third 

stage turbine wheel that incorporates modification AB 173 or modification AB 

208, except those engines that have been reworked in accordance with the 

instructions of Turbomeca Service Bulletin (SB) 283 72 0805.

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

Helicopters (formerly Aerospatiale, Sud Aviation) Alouette III SA 319 B and 

GAZELLE SA 342 J helicopters.

Reason: Investigation of an uncommanded in-flight shut down (IFSD) event revealed that 

a third stage turbine wheel rupture was not contained by the turbine casings. 

The released portion consisted of a turbine blade together with the rim piece 

immediately below the blade. The rim piece was bounded by two adjacent axial 

slots and a fatigue crack that had developed between the holes in which the 

slots terminate. The slots and holes, which are closed by riveted plugs, were 

introduced by modification (MOD) AB 173 in order to improve the vibration 

characteristics of the turbine wheel. MOD AB 208 introduced an improvement to 

MOD AB 173 by changing only the riveting detail. Turbomeca issued SB 

283 72 0805 to provide instructions for re-boring the holes (at overhaul or 

repair) in order to improve their surface condition. A manufacturing process 

modification has been introduced to improve the surface condition of these 

holes in third stage turbine wheels. Wheels subject to the improved 

manufacturing process have serial numbers (S/Ns) outside the range specified 

in Turbomeca Mandatory SB (MSB) 283 72 0804 Version C.

Although only one event has been reported which resulted in an uncommanded 
EASA AD No : 2015-0211

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IFSD and no damage to the affected helicopter, this condition, if not detected 

and corrected, could lead to an emergency autorotation landing.

To address the unsafe condition, EASA issued AD 2009-0136 to require

inspection of certain third stage turbine wheels and removal of any damaged 

wheel. The wheels to be inspected were those that would exceed 2 000 cycles 

since new (CSN) by 01 February 2011.

Following additional research by Turbomeca on crack initiation and growth, 

EASA issued AD 2010-0004, which superseded AD 2009-0136, to require new

inspections, based on new criteria, and removal from service of any damaged 

wheels.

Since EASA AD 2010-0004 was issued, a new case of cracking on a third stage 

turbine wheel was detected during engine overhaul in a repair center. This 

turbine had previously been inspected in accordance with MSB 283 72 0804 

Version C but the crack, if present at that time, was not detected.

Prompted by these findings, Turbomeca, issued MSB 283 72 0804 Version D in 

order to expand the population of potentially affected turbines and to introduce 

repetitive inspections.

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

affected third stage turbine wheels, as specified in MSB 283 72 0804 Version D,

and, depending on findings, accomplishment of the applicable corrective 

actions.

Effective Date: 29 October 2015

Required Action(s) 

and Compliance 

Time(s):

Required as indicated unless accomplished previously:

Note 1: For the purpose of this AD, an affected third stage turbine wheel has a 

P/N and S/N as listed in Turbomeca MSB 283 72 0804 Version D.

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

and, thereafter, at intervals not to exceed 400 engine cycles (EC), 

accomplish a dye penetrant inspection on the rear face of each affected

third stage turbine wheel in accordance with the instructions of Turbomeca

MSB 283 72 0804 Version D.

Table 1 – Initial dye penetrant inspection

Engine condition

(on the effective date of this AD)

Compliance Time

Third stage turbine wheel installed, not 

affected by Turbomeca MSB 283 72 

0804 Version C

Within 150 EC after the effective 

date of this AD

Third stage turbine wheel installed, 

listed in Turbomeca MSB 283 72 0804 

Version C, and accumulated 300 EC or 

more since last inspection, or since new, 

or since last overhaul, or repair, as 

applicable

Third stage turbine wheel installed, 

listed in Turbomeca MSB 283 72 0804

Version C, and accumulated less than 

300 EC since the last inspection, or 

since new, or since last overhaul, or 

repair, as applicable

Before exceeding 400 EC since

the last inspection, or since new, 

or since the last overhaul, or 

since repair, as applicable

Note 2: A non-cumulative tolerance of 50 EC may be applied only to the 

inspection interval as specified in paragraph (1) of this AD.

(2) If, during any inspection as required by paragraph (1) of this AD, a crack is 
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detected, before next flight, remove the engine from the helicopter and 

contact Turbomeca for approved instructions.

(3) In-shop rework of a third stage turbine on an engine in accordance with the 

instructions of Turbomeca SB 283 72 0805 constitutes a terminating action

for the repetitive inspections as required by paragraph (1) of this AD for 

that engine.

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

third stage turbine wheel is allowed, provided that, following installation, 

the engine is inspected as required by this AD.

Ref. Publications : Turbomeca MSB 283 72 0804 Version C dated 23 October 2009, or Version D

dated 24 July 2015.

Turbomeca SB 283 72 0805 Version B dated 15 December 2010.

The use of later approved revisions of these documents 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 15 September 2015 as PAD 15-124 for 

consultation until 13 October 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.

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

this AD, please contact:

Operator Support ASTAZOU - TURBOMECA 40220 TARNOS – FRANCE

Phone: +33 (0)5 59 74 40 00 Fax: +33 (0)5 59 74 45 15 or refer to your 

nearest TURBOMECA technical representative on

http://www.turbomeca-support.com.