EASA AD No.: 2013-0111R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0111R1

Date: 03 June 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):

ASTAZOU XIV engines

TCDS Number: EASA.E.075

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2013-0111 dated 27 May 2013.

ATA 72 Engine – Second Stage Turbine Disc – Replacement

Manufacturer(s): TURBOMECA

Applicability: ASTAZOU XIV B and XIV H engines, all serial numbers.

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

(formerly Sud Aviation, Aerospatiale) SA 319 B (Alouette III) and SA 342 J 

(Gazelle) helicopters.

Reason: Some cracks have been reported on the second stage turbine disc of 

ASTAZOU XIV engines inducted into a Repair Centre. These cracks are 

located in the serrations of the disc. The results of the technical investigation 

concluded that the cracks were present on non-shot peened second stage 

turbine discs (discs on which AB 138 modification was not incorporated), and 

on second stage turbine discs that were shot peened during their service life 

(discs on which AB 138 modification was incorporated after initial service use

without shot peening). Until now, no crack has been reported on second stage 

turbine discs shot peened since new, these discs accounting for more than half 

of all ASTAZOU XIV flight hours. It was not possible to clearly identify what 

caused the cracks.

This condition, if not corrected, could lead to some events of disc serrations 

rupture, possibly resulting in uncontained second stage turbine blade release 

with consequent damage to, and reduced control of, the helicopter.

To address these occurrences, TURBOMECA published Mandatory Service 

Bulletin (MSB) A283 72 0808 and MSB A283 72 0809, which provides second 

stage turbine disc replacement instructions.

For the reasons described above, this AD requires replacement of the affected

second stage turbine discs with serviceable second stage turbine discs.
EASA AD No.: 2013-0111R1

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This AD is revised to clarify the compliance time for the second stage turbine 

disc replacement for certain engines.

Effective Date: 10 June 2013

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

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

applicable to engine Model and configuration, replace each non-shot 

peened second stage turbine disc (AB 138 modification was not 

incorporated), and any affected second stage turbine disc that was shot

peened during its service life (AB 138 modification was applied after initial 

service use without shot peening) with a serviceable part in accordance 

with the instructions of Turboméca MSB A283 72 0808 or Turboméca MSB 

A283 72 0809, as applicable.

(2) After replacement of an affected second stage turbine disc with a 

serviceable second stage turbine disc on an engine, do not install a second

stage turbine disc on that engine, unless the disc is a serviceable part as 

defined in Turboméca MSB A283 72 0808 or Turboméca MSB A283 72 

0809, as applicable.

Ref. Publications: TURBOMECA MSB A283 72 0808 version A dated 16 May 2013.

TURBOMECA MSB A283 72 0809 version A dated 16 May 2013.

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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

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:

Operator Support & Sales ASTAZOU - TURBOMECA 40220 TARNOS –

FRANCE

Phone: +33 (0)5 59 74 40 28 Fax: +33 (0)5 59 74 45 16 or refer to your 

nearest TURBOMECA field representative on

www.turbomeca-support.com.
EASA AD No.: 2013-0111R1

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Table 1 – Appendix: Replacement Second Stage Turbine Discs

Affected Engine Configuration Compliance Time

ASTAZOU XIV B

Engine not incorporating 

AB 138 modification

Engine has, at the effective date 

of this AD, accumulated 1 800 

engine cycles (EC) or more since 

last engine overhaul (or since 

new if the engine has never been 

overhauled):

Within 10 operating hours after 

the effective date of this AD

Engine has, at the effective date 

of this AD, accumulated less than 

1 800 EC since last engine 

overhaul (or since new if the 

engine has never been 

overhauled):

Within 300 operating hours after 

the effective date of this AD or 

within 1 800 EC since last engine 

overhaul (or since new if the 

engine has never been 

overhauled), whichever occurs 

first

Engine incorporating AB 

138 modification

Within 1 800 EC since last 

engine overhaul (or since new if 

the engine has never been 

overhauled) or within 10 

operating hours after the effective 

date of this AD, whichever occurs 

later

ASTAZOU XIV H Engine not incorporating

AB 138 modification

Within 300 operating hours after 

the effective date of this AD