EASA AD No.: 2015-0223 

# EASA

.Airworthiness Directive AD No.: 

### 2015-0223 European Aviation Safety Agency 

### Issued: 

### 16 November 

### 2015 Note: This Ai rworthi ness Directive (AD) Is issued by EASA, acting In accordance with Regulation (EC) 216/2008 on behalf or t he European Union, its M ember S tates and or the European third countries that participate Inthe activities or EASA under Article 66 orthat Regulation
. This AD is issued in accordance with R egulation (EU) 748/2012, Part 21A3B. In accordance with Regulation (EU) 1 321/2014 Annex I, Part M.A.301, the continuing airworthiness oran aircraft shall be ensured byaccomplishing any applicable ADs. Consequently , no person mayoperate an ai rcraft to which an AD applies, except I n accordance w ith the requirements of that AD, unless otherwise specified by the Agency (Regulation (EU) 1321/2014 Annex I, Part M .A .303) or a g reed with the Authority ofthe State of Registry (Regu lation (EC) 2 16 /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 Helicopter s (fo rmerly 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 ofthe third stage turbine wheel between two balancing plugs. The ca use ofthe crack is probably linked to a geometric singularity, likely caused bythe transformation operation aimed at introducing expansion slots between the blad es during embodiment ofTurbomeca mod AB 173. Although there is only one known case ofthis type of crack, and although it was detected, the possibility exists that additional parts have the sa me geometric singularity. 

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An •c•tw!'¥ olttl• (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 ofthird stage turbine wheel, and, depending on findings, accomplishment ofthe 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 ofthe 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 

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. or refer to your nearest TURBOMECA technical representative on http://www.turbomeca-support.com. '·

TE.CAP.OOllO·OOS © European Aviation Safety Agency. All rights reserved. 1509001 Certified. Page 2 of 2

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