EASA AD No.: 2013-0109

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0109

Date: 22 May 2013

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 EU 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

THIELERT AIRCRAFT ENGINES GmbH

Type/Model designation(s):

TAE 125-01 engines

TCDS Number: EASA.E.055

Foreign AD: Not applicable

Supersedure: None

ATA 72 Engine – Crankcase Assembly Opening – Sealing

Manufacturer(s): Thielert Aircraft Engines (TAE)

Applicability: TAE 125-01 (commercial designation Centurion 1.7) engines, all serial 

numbers. These engines are known to be installed on, but not limited to, the 

following aeroplane types, mostly through application of a Supplemental Type 

certificate (STC):

- Cessna 172 and (Reims-built) F172 series (STC EASA.A.S.01527), 

- Piper PA-28 series (STC EASA.A.S.01632), 

- CEAPR (APEX, Robin) DR 400 series (STC EASA.A.S.01380), and 

- Diamond DA 40 and DA 42 series.

Reason: A power loss event was reported on an aeroplane equipped with a TAE 125-01

engine. The investigation results showed that the probable cause was

contamination of the engine clutch by coolant spillage during the last 

maintenance operation. The contamination penetrated the clutch housing 

through an opening located under the coolant tank that was only closed by a 

not fluid-tight plastic cover.

This condition, if not corrected, could lead to further engine power loss events, 

possibly resulting in loss of control of the aeroplane.

To address this potential unsafe condition, TAE have issued Technische 

Mitteilung (TM) / Service Bulletin (SB) No. TAE 125-0022.

For the reasons described above, this AD requires sealing of the crankcase 

assembly opening.

Effective Date: 05 June 2013
EASA AD No.: 2013-0109

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

Within 110 flight hours, or during the next scheduled engine maintenance, 

whichever occurs first after the effective date of this AD, seal the crankcase 

assembly opening in accordance with the instructions of TAE TM/SB No. TAE 

125-0022.

Ref. Publications: TAE TM/SB No. TAE 125-0022, Initial Issue, dated 08 August 2012.

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 18 April 2013 as PAD 13-056 for consultation until 

16 May 2013. No comments were received during the consultation period.

3. Enquiries regarding this AD should be referred to the Safety Information 

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

4. For any question concerning the technical content of the requirements in 

this AD, please contact:

Thielert Aircraft Engines GmbH

Platanenstraße 14

D-09350 Lichtenstein, Germany

Telephone +49-37204-696-0; Fax +49-37204-696-55;

E-mail info@centurion-engines.com.