EASA AD No : 2010-0079

EASA Form 112 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0079

Date: 26 April 2010

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 participat e 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 accordance with the requirements of that AD, unl ess 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]. 

### Type Approval Holder’s Name :
MICROTURBO Type/Model designation(s) :
Saphir 20 Model 095 Auxiliary Power Unit

TCDS Number : QAC 150 (letter 53038 SFACT/TC dated 12/01/1990).

Foreign AD : Not applicable.
Supersedure : This AD supersedes EASA AD 2008-0084 dated 06 May 2008 and corrected

on 26 February 2009.



### ATA 49 Airborne Auxiliary Power – Auxiliary Power Unit Tur bine Wheel

Life Limit – Reduction

Manufacturer(s): MICROTURBO

Applicability: Saphir 20 Model 095 Auxiliary Power Units (APU), all serial numbers. These APUs are known to be installed on, but are no t limited to, Eurocopter EC225 and AS332 helicopters.
Reason: The turbine wheel, Part Number (P/N) 095-01 -015-03, of the SAPHIR 20 Model 095 APU is a life-limited part. MICROTURBO ha d determined through “fleet leader” testing and inspection that the published life limit of this turbine wheel should be reduced to 9 000 cycle s. Use of the turbine wheel beyond 9 000 cycles could lead to the release of high energy debris that could jeopardize aircraft safety. For the reasons described above, EASA AD 2008-0084 required the implementation of the new life limit on the affecte d parts and the replacement of parts that had exceeded the new limi t. MICROTURBO has now determined that the life limit o f this turbine wheel should be further reduced to 4 225 cycles. Use of t he turbine wheel beyond 4 225 cycles could lead to the release of hi gh energy debris that could jeopardize aircraft safety. For the reasons described above, this AD, which sup ersedes EASA AD 2008-0084, requires the implementation of the new l ife limit on the affected parts and the replacement of parts that ha d exceeded this new limit. This AD also extends the scope to include th e P/N 095-01-015-20EASA AD No : 2010-0079

EASA Form 112 Page 2/2 turbine wheel, which is physically identical to the P/N 095-01-015-03 turbine wheel but is manufactured using a revised p rocess (approved by EASA).
Effective Date: 10 May 2010

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within one month after the effective date of th is AD or upon accumulating 4 225 APU cycles in service, whichever occurs later, and thereafter, at intervals not to exceed 4225 AP U cycles, replace the turbine wheel P/N 095-01-015-03 or (P/N) 095-01 -015-20, as applicable, with a serviceable unit in accordance w ith the instructions of MICROTURBO Service Bulletin 095-49-17. (2) Compliance with the requirements of paragraph ( 1) of this AD can be demonstrated by: (2.1) Revising as follows, unless accomplished prev iously, the approved Aircraft Maintenance Programme from which the Operator or the Owner ensures the continuing airwor thiness of each operated helicopter: Incorporate the new life limits and associated heli copter airworthiness limitations specified in the MICROTUR BO Service Bulletin 095-49-17.
and (2.2) Complying with the approved Aircraft Maintena nce Programme as described in paragraph (2.1) of this AD.

Ref. Publications: MICROTURBO Service Bulletin 095- 49-17, Original Issue, dated 16 March 2010.
SAPHIR 20 Model 095 Maintenance Manual 49-29-99. Any later approved revision of these documents is a cceptable to comply 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. This AD was posted on 23 March 2010 and correcte d on 24 March 2010 as PAD 10-029 for consultation until 20 April 2010. No comments were received during the consultation peri od. 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 questions concerning the technical conte nt of the requirements in this AD, please contact: MICROTURBO - Support Clients, 8, Chemin du pont de Rupé - BP 62089 31019 Toulouse - Cedex 2 – FRANCE; Telephone +33 (0)5 61 37 55 00; Fax: +33 (0) 5 61 70 74 45; E-mail technical.support@microturbo.fr

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