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 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 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 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]. 

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 Turbine 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 not 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 had determined 

through “fleet leader” testing and inspection that the published life limit of 

this turbine wheel should be reduced to 9 000 cycles. 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 affected parts and the 

replacement of parts that had exceeded the new limit. 

MICROTURBO has now determined that the life limit of this turbine wheel 

should be further reduced to 4 225 cycles. Use of the turbine wheel 

beyond 4 225 cycles could lead to the release of high energy debris that 

could jeopardize aircraft safety. 

For the reasons described above, this AD, which supersedes EASA AD 

2008-0084, requires the implementation of the new life limit on the 

affected parts and the replacement of parts that had exceeded this new 

limit. This AD also extends the scope to include the P/N 095-01-015-20 
EASA 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 process (approved by 

EASA).

Effective Date: 10 May 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within one month after the effective date of this AD or upon 

accumulating 4 225 APU cycles in service, whichever occurs later, 

and thereafter, at intervals not to exceed 4225 APU 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 with 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 previously, the 

approved Aircraft Maintenance Programme from which the 

Operator or the Owner ensures the continuing airworthiness of 

each operated helicopter: 

Incorporate the new life limits and associated helicopter 

airworthiness limitations specified in the MICROTURBO 

Service Bulletin 095-49-17. 

and 

(2.2) Complying with the approved Aircraft Maintenance 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 acceptable to comply 

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 23 March 2010 and corrected on 24 March 

2010 as PAD 10-029 for consultation until 20 April 2010. No 

comments were received during the consultation period. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail ADs@easa.europa.eu. 

4. For any questions concerning the technical content 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 .