EASA AD No : 2009-0193R1

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009- 0193R1

Date: 01 December 2009

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 Airworthiness Direc tive applies, except in accordance with the require ments of that Airworthiness Directive 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) exemp tion].


### Type Approval Holder’s Name :
Thielert Aircraft Engines GmbH Type/Model designation(s) :

TAE125-01 piston engines

TCDS Number : EASA E.055

Foreign AD : Not applicable

Revision: This AD revises AD 2009-0193 dated 27 Au gust 2009



### ATA 61 Propellers/Propulsion - Vibration Isolator of the Propeller’s Constant Speed Unit - Inspection/Replacement

Manufacturer(s): Thielert Aircraft Engines GmbH.

Applicability: All TAE125-01 engines that are insta lled on Diamond Aircraft Industries DA 42 aeroplanes.
Remark: TAE125-01 engines installed on other aeropl ane types are not concerned by this AD.

Reason: Engine In-Flight Shutdown (IFSD) incidents have been reported on Diamond Aircraft Industries DA 42 aeroplanes equipp ed with TAE125 engines. The investigations showed that it was main ly the result of failure of the Proportional Pressure Reducing Valve (also k nown as Propeller Control Valve) due to high vibrations. To address this subject, AD 2008-0145 was issued in July 2008 and amended by its revision 1 in July 2009 to mandate a life-limit for the Proportional Pressure Reducing Valve (PPRV). Since the release of AD 2008-0145, the engine gearb ox has been identified as the primary source of vibrations for the PPRV, and it has also been determined that failure of the electrical conn ection to the Proportional Pressure Reducing Valve can have contr ibuted to some power loss events or IFSD.
For the reasons described above, AD 2009-0193, whic h superseded AD 2008-0145 & AD 2008-0145R1, mandated installation o f a vibration isolator between the engine gearbox and the propell er Constant Speed Unit (CSU). In addition, it required an inspection of the electricalEASA AD No : 2009-0193R1

EASA Form 110 Page 2/2 connectors of the PPRV. Installation of the vibrati on isolator entails the replacement of the de-icing nozzle support bracket and replacement of the CSU aluminium pipe with a flexible hose.
This AD 2009-0193R1 specifies compliance time limit and refers to the latest revision of Thielert applicable Service Bull etin (SB). In addition to that, this AD gives credit for Inspection/Replaceme nt done in accordance with the initial issue of the SB.

Effective Date: 15 December 2009

Required Action(s) and Compliance Time(s): Required as indicated unless previously accomplishe d:
1. Within 55 Flight Hours after the effective date of this AD, at the next inspection but no later than 28 February 2010, insp ect and/or replace the electrical connectors of the Proportional Press ure Reducing Valve and install a vibration isolator between the engine gearbox and the propeller’s Constant Speed Unit as instructed in st eps 1 to 27 of the Thielert Service Bulletin TM TAE 125-0020 Rev. 1.
Note 1: If not already been done, step 22 of the Th ielert Service Bulletin TM TAE 125-0020 calls for the initial replacement o f the PPRV in accordance with Thielert Service Bulletin TM TAE 12 5-0018 revision 1.
Note 2: The vibration isolator and the PPRV are par t of the gearbox assembly. They must be inspected regularly in accor dance with the Engine Operation & Maintenance Manual OM-02-01 and the Engine Repair Manual RM-02-01. 2. Inspection/Replacement done in accordance with T M TAE 125-0020 and annexes, initial issue dated 20 August 2009 are acceptable for compliance with the requirements of this AD.

Ref. Publications: Thielert Service Bulletin TM TA E 125-0020 and annexes, Revision 1 dated 25 November 2009;

Thielert Service Bulletin TM TAE 125-0018 revision 1 dated 12 November 2008; The use of later approved revisions of these docume nts 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, p ostponing 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:
Thielert Aircraft Engines Platanenstraße 14 D-09350 Lichtenstein, Germany Telephone +49-37204-696-0 Fax +49-37204-696-55

E-mail info@centurion-engines.com