EASA AD No.: 2015-0223 

EASA . Airworthiness Directive 

AD No.: 2015-0223 

European Aviation Safety Agency 

Issued: 16 November 2015 

Note: This Airworthiness Directive (AD) Is issued by EASA, acting In accordance with Regulation 

(EC) 216/2008 on behalf or the European Union, its M ember States and or the European third 

countries that participate In the activities or EASA under Article 66 or that Regulation. 

This AD is issued in accordance with Regulation (EU) 748/2012, Part 21A3B. In accordance with Regulation (EU) 1321/2014 Annex I, Part M.A.301, the 

continuing airworthiness oran 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 (Regulation (EU) 1321/2014 Annex I, 

Part M .A.303) or agreed with the Authority of the State of Registry (Regulation (EC) 216/2008, Article 14(4) exemption). 

Design Approval Holder's Name: Type/Model designation(s): 

TURBOMECA ASTAZOU XIV engines 

Effective Date: 30 November 2015 

TCDS Number(s): EASA.E.075 

Foreign AD: None 

Supersedure: Not applicable 

ATA 72- Engine- Third Stage Turbine Wheel-Inspection 

Manufacturer(s): 

Turbomeca 

Applicability: 

ASTAZOU XIV Band XIV H engines, all serial numbers, if fitted with a third stage turbine wheel part 

number (P/N) 0 265 25 700 0 or 0 265 25 706 0, and incorpor(!te Turbomeca modification (mod) AB 

173 or mod AB 208. 

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

Aerospatiale, Sud Aviation) SA 319 B (Aiouette Ill) and SA 342 J (Gazelle} helicopters. 

Reason: 

During the overhaul of an ASTAZOU XIV engine, a crack was detected on the front face of the third 

stage turbine wheel between two balancing plugs. The cause of the crack is probably linked to a 

geometric singularity, likely caused by the transformation operation aimed at introducing expansion 

slots between the blades during embodiment ofTurbomeca mod AB 173. Although there is only 

one known case of this type of crack, and although it was detected, the possibility exists that 

additional parts have the same geometric singularity. 

CJ . 

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An •c•tw!'¥ ol ttl• (t.ll'opu.n Union 
EASA AD No.: 2015-0223 

This condition, if not detected and corrected, may lead to failure of a turbine blade and its 

associated piece of rim, possibly resulting in an uncommanded in-flight shut-down and/or release of 

high energy debris. 

Prompted by these findings, Turbomeca issued Service Bulletin {SB) 283 72 0811 to provide 

inspection instructions to detect any potential geometric singularity. 

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

stage turbine wheel, and, depending on findings, accomplishment of the applicable corrective 

actions. 

Required Action(s) and Compliance Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 1 000 engine hours (EH) after the effective date of this AD, accomplish an in-shop 

inspection of the front face of the third stage turbine in accordance with the instructions of 

Turbomeca SB 283 72 0811. 

(2) If, during the inspection as required by paragraph (1), a discrepancy (as defined in Turbomeca 

SB 283 72 0811) is detected, before release to service of the engine, accomplish the applicable 

corrective action(s) in accordance with the instructions of Turbomeca SB 283 72 0811. 

Ref. Publications: 

Turbomeca SB 283 72 0811 Version A dated 25 August 2015. 

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 October 2015 as PA.D 15-132 for consultation until 09 November 

2015. No comments were received during the consultation period. 

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

Certification Directorate. 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 

Telephone: +33 (0)5 59 74 40 00 Fax: +33 (0)5 59 74 45 15 

CJ . 

. 

or refer to your nearest TURBOMECA technical representative on 

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

'· 

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