EASA AD No.: 2010-0101R2

EASA Form 110 Page 1/4 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0101R2

Date: 24 March 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an 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 EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD unless other wise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Type Approval Holder’s Name :
Turboméca Type/Model designation(s) : ARRIEL 1 series turboshaft engines

TCDS Number : EASA.E.073

Foreign AD : Not applicable

Revision : This AD revises EASA AD 2010-0101R1 dat ed 04 August 2010.



### ATA 72 Engine – Module M03 (Gas Generator) – Post-TU347 S econd Stage Turbine Disc – Reduced Life Limit

Manufacturer(s): Turboméca S.A.
Applicability: Arriel 1A, 1A1, 1B, 1C, 1C1, 1C2, 1D , 1D1 and 1S1 turbo-shaft engines, all serial numbers if modified by TU347. These engines are known to be installed on, but not limited to, the following helicopters: Eurocopter AS350 series, AS365 and SA365 series, Si korsky S-76A series and C series.
Reason: Metallurgical non-conformities have been fo und when performing quality inspections during production of Arriel 1 Gas Gener ator (GG) second Stage Turbine Discs introduced by Turboméca Modification TU347 (P/N 0 292 25 040 0). Analysis has concluded that the approved li fe limit of the post-TU347 GG second Stage Turbine Disc needs to be reduced to 2 500 GG cycles. Exceeding the revised approved life limit could res ult in a GG second Stage Turbine Disc burst with uncontained high energy deb ris. To address this unsafe condition, this AD requires compliance with the revised life limit of the GG second Stage Turbine D isc by removing the module M03 (Gas Generator) or the GG second Stage T urbine fitted with a GG second stage Turbine Disc which has reached or e xceeded the new life limit. After issuance of AD 2010-0101-E, Turboméca has int roduced a reinforced Eddy-current inspection which provides a lower (imp roved) detection threshold of the metallurgical non-conformities. Th is reinforced Eddy-currentEASA AD No.: 2010-0101R2

EASA Form 110 Page 2/4 inspection, named “CFR”, combined with a revised an alysis, allowed to increase the life limit of the post-TU347 GG second Stage Turbine Discs identified as “CFR” over the 2 500 GG life cycles o f the “non-CFR” Discs, as specified in AD 2010-0101R1.
The revision 2 of this AD is issued to increase fur ther the life limit of the post-TU347 GG 2 nd stage turbine discs identified as “CFR” and the li fe limit of the post-TU347 GG 2 nd stage turbine discs identified as “non-CFR”. This is possible as, since issuance of AD 2010-0101R1, T urboméca has carried out further analysis and testing on those discs.
Effective Date: Revision 2: 07 April 2011 Revision 1: 18 August 2010 Original Issue: 06 June 2010
Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) For “non-CFR” (see Note [a]) second Stage Turbi ne Discs, within the compliance time as indicated in Table 1, as applica ble, replace the module M03 (Gas Generator) or the GG second Stage T urbine, in accordance with Turboméca Mandatory Service Bulleti n (MSB) A292 72 0831 version C.
Table 1:

“non-CFR” [a] Second Stage Turbine Disc Accumulated GG cycles at the effective date of this AD: Compliance time:

4 000 or more 20 GG cycles after the effective date of this AD Less than 4 000 Upon accumulating 4 000 GG cycles Note [a]: “non-CFR” second Stage Turbine Discs were not subject to the reinforced Eddy-current inspection. These parts are not marked with “CFR”. P/N may only be 0 292 25 040 0. (2) For “CFR” (see Note [b]) GG second Stage Turbin e Discs, the approved life is defined in the latest update of the Airwort hiness Limitation Section of the Engine Maintenance Manual Chapter 05 – INSPE CTIONS – FREQUENCIES, Chapter 05-10-03, Task 05-10-03-900-80 1-A01, Par. Service Life Limits – Life Limit Values. The refere nces of the Engine Maintenance Manuals are in Appendix of this AD (Fre nch / English versions). At the issue date of this AD, the approv ed life of the “CFR” GG second Stage Turbine Disc is 6 500 GG cycles. Note [b]: “CFR” second Stage Turbine Discs were sub ject to the reinforced Eddy-current inspection. These parts are permanently marked with “CFR” next to the Part Number (P/N). P/N may b e 0 292 25 040 0 or 7 292 25 040 1. (3) In a Repair Center, a “non-CFR” second Stage Tu rbine Disc removed from service may be sent to an approved facility to be subject to a reinforced Eddy-current inspection in accordance wi th Paragraph 2.B.(2) of Turboméca MSB A292 72 0831 version C. The discs that will pass the inspection will be marked “CFR” and the remaining l ife will be the approved life defined in Paragraph (2) of this AD m inus the number of consumed cycles of the part, in accordance with Par agraph 2.D.(3) of Turboméca MSB A292 72 0831 version C. (4) Compliance with the requirements of paragraph ( 1), (2) and (3) of this AD can be demonstrated by: (4.1)Revising as follows, unless accomplished previ ously, the approvedEASA AD No.: 2010-0101R2

EASA Form 110 Page 3/4 Aircraft Maintenance Programme from which the Opera tor or the Owner ensures the continuing airworthiness of each operated helicopter, as well as the Engine log book and Modu le M03 log card: Incorporate the new life limits of the GG second S tage Turbine Disc specified in Turboméca MSB A292 72 0831 versio n C.
and (4.2) Complying with the approved Aircraft Maintena nce Programme as described in paragraph (4.1) of this AD. (5) After the effective date of this AD, do not ins tall a post-TU347 GG second Stage Turbine Disc unless in compliance with the re quirements of this AD.
Ref. Publications: Turboméca Mandatory Service Bull etin A292 72 0831 version C dated 03 March 2011. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication. 3. Enquiries regarding this AD should be referred t o the Airworthiness Directives, Safety Management & Research Section, C ertification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Turboméca, S.A., ARRIEL 1 Customer Support, 40220 T ARNOS, FRANCE. Fax: +33 5 59 74 45 15 or contact your near est technical representative at www.turbomeca-support.com

.EASA AD No.: 2010-0101R2

EASA Form 110 Page 4/4 

### APPENDIX

Maintenance Manuals according to Engine Variant:

Maintenance Manual Engine Variant French Version English Version

ARRIEL 1A 292 01 931 n/a

ARRIEL 1A1 X 292 B3 452 1 X 292 B3 452 2

ARRIEL 1B X 292 65 452 1 X 292 65 452 2

ARRIEL 1C X 292 B0 452 1 X 292 B0 452 2

ARRIEL 1C1 X 292 C3 452 1 X 292 C3 452 2

ARRIEL 1C2 X 292 G1 452 1 X 292 G1 452 2

ARRIEL 1D X 292 E5 452 1 X 292 E5 452 2

ARRIEL 1D1 X 292 G2 452 1 X 292 G2 452 2

ARRIEL 1S1 X 292 H4 452 1 X 292 H4 452 2