EASA AD No.: 2015-0055

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0055

Date: 31 March 2015

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 EU 1321/2014 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 [EU 

1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Design Change Approval Holder’s Name:

TECHNIFY MOTORS GmbH

Type/Model designation(s):

TAE 125-02 engines

TCDS Number: EASA.E.055 

Foreign AD: Not applicable 

Supersedure: None 

ATA 80 Starting – Software Mapping / Start Phase Monitoring System – 

Installation 

Manufacturer(s): Technify Motors GmbH (TMG), formerly Thielert Aircraft Engines (TAE). 

Applicability: TAE 125-02-99 (commercial designation CD-135, formerly Centurion 2.0) and 

TAE 125-02-114 (commercial designation CD-155, formerly Centurion 2.0S) 

engines, all serial numbers (S/N), if a Dual Mass Flywheel is installed, and if the 

engine is installed on one of the following aeroplane types: 

- Cessna 172 and (Reims-built) F172 series with engine installed through 

Supplemental Type Certificate (STC) EASA 10014287. 

- Piper PA-28 series with engine installed through STC EASA 10014364. 

- CEAPR (APEX, Robin) DR 400 series with engine installed through STC 

EASA.A.S.01380 or STC EASA 10014219, all aeroplane S/N up to 2674 

(included), with STC installed before December 2014. 

- Diamond (DAI) DA 40 D model, S/N D4.001 through D4.399 and 

S/N 40.DS001 through 40.DS135 (engine installed during aeroplane 

manufacture), or any other S/N with engine installed through STC EASA 

10036328. 

- DAI DA 42 and DA42 M models, S/N 42.004 through 42.427, S/N 42.AC001 

through 42.AC151 and S/N 42.M001 through 42.M027 (engine installed 

during aeroplane manufacture), or any other S/N with engine installed 

through STC EASA 10048730. 

Engines having a Dual Mass Flywheel installed can be identified by marking on 

the fuel rail (sticker “Dual Mass Flywheel installed”), or record in the engine log 

book (“Dual Mass Flywheel” listed as engine component on page 4 “Main 

Engine Components”). 
EASA AD No.: 2015-0055

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Reason: Cases of a broken gearbox drive shaft have been reported on aeroplanes 

equipped with TAE 125-02 engines that have a Dual Mass Flywheel installed. 

Investigations results showed a possible overload of the gearbox drive shaft 

during starting of the engine or during restarting of the engine in-flight. 

This condition, if not corrected, could lead to engine power loss during flight, 

possibly resulting in loss of control of the aeroplane. 

To address this unsafe condition, TMG has developed an improved software 

mapping and a start phase monitoring system. See TMG Service Bulletin (SB) 

TM TAE 125-1018 P1 for further details. 

For the reason described above, this AD requires the installation of the 

improved software mapping and of the start phase monitoring system. 

Effective Date: 14 April 2015 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 110 flight hours or at the next scheduled maintenance event, 

whichever occurs first after the effective date of this AD, install the software 

mapping specified in Appendix 1 of this AD, as applicable to engine model 

and aeroplane type, in accordance with the instructions of TMG SB TM TAE 

000-0007, Revision 28. 

(2) Concurrent with the software mapping installation as required by paragraph 

(1) of this AD, install a start phase monitoring system in accordance with 

TMG Installation Manual IM-02-02, Chapter 13.08.16, Issue 4, Revision 1, 

using the instructions specified in Table 1 of this AD, as applicable to 

aeroplane type and engine installation approval (TC/STC). 

Table 1 – Installation of Start Phase Monitoring System 

Aeroplane type / model 

(TC/STC) 

Instructions 

Cessna 172 

(STC EASA 10014287) 

TMG SB TMG 601-1007 P1 Rev. 3 

Piper PA-28 

(STC EASA 10014364) 

TMG SB TMG 651-1004 P1 Rev. 2 

CEAPR DR 400 

(STC EASA 10014219 or 

 STC EASA.A.S.01380) 

CEAPR SB B.S. n° 141201 Rev. 1 

DAI DA 40 D 

(STC EASA 10036328) 

TMG SB TMG 691-1002 P1 Rev. 2 

DAI DA 40 D 

(TC EASA.A.022) 

DAI MSB D4-097/2 

DAI DA 42 and DA 42 M 

(TC EASA.A.005 or 

EASA.A.513) 

DAI MSB 42-109/1 

DAI DA 42 

(STC EASA 10048730) 

EASA Approved Modification 

(3) From the effective date of this AD, it is only allowed to install a 

TAE 125-02-99 or TAE 125-02-114 engine on an aeroplane type listed in 

the Applicability of this AD provided the engine is equipped with start phase 

monitoring system as required by this AD and a software mapping version 

as required by this AD or later. 
EASA AD No.: 2015-0055

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Ref. Publications: TMG SB TM TAE 125-1018 P1 Revision 1, dated 05 February 2015. 

TMG SB TM TAE 000-0007 Revision 28, dated 05 February 2015. 

TMG Installation Manual IM-02-02, Chapter 13.08.16, Issue 4, Revision 1, 

dated 02 December 2014. 

TMG SB TMG 601-1007 P1 Revision 3, dated 05 February 2015. 

TMG SB TMG 651-1004 P1 Revision 2, dated 05 February 2015. 

TMG SB TMG 691-1002 P1 Revision 2, dated 05 February 2015. 

CEAPR SB n° 141201 Revision 1, dated 05 February 2015. 

DAI MSB D4-097/2 (Issue 2), dated 04 February 2015. 

DAI MSB 42-109/1 (Issue 1), dated 04 February 2015.

The use of later approved revisions of these documents 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 24 February 2015 as PAD 15-015 for consultation 

until 24 March 2015. No comments were received during the consultation 

period. 

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

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

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

this AD, please contact: 

Technify Motors GmbH 

Platanenstraße 14 

D-09356 Sankt Egidien, Germany 

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

E-mail info@centurion.aero. 

 
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Appendix 1 – Instructions for Software Mapping 

TAE 125-02-99 engines 

Software (Firmware) Type Voltage Software Mapping Part Number 

FADEC D48 

TAE-125 m3.30 

P/N 02-7610-55101R14 

Cessna 172 14V O14D330CES 20-7610-E020101 

Cessna 172 28V O28D330CES 20-7610-E021101 

Piper PA28 14V O14D330PIP 40-7610-E020101 

Piper PA28 28V O28D330PIP 40-7610-E021101 

Apex DR400 14 V O14D330APEX 60-7610-E020101 

Diamond DA40 14 V O14D330DA40 50-7610-E020101 

Diamond DA42 28 V O28D330DA42 52-7610-E020501 

FADEC D4 

D4-v1.40 

P/N 05-7610-E001003 

Cessna 172 14 V F14D140CES 20-7610-E012101 

Cessna 172 14 V F14D141CES 20-7610-E012102 

Cessna 172 28 V F28D140CES 20-7610-E013101 

Cessna 172 28 V F28D141CES 20-7610-E012102 

Piper PA28 14 V F14D140PIP 40-7610-E012101 

Piper PA28 28 V F28D140PIP 40-7610-E013101 

Apex DR400 14 V F14D140APEX 60-7610-E012101 

Diamond DA40 14 V F14D140DA40 50-7610-E012101 

Diamond DA42 28 V F28D140DA42 52-7610-E012101 

TAE 125-02-114 engines 

Software (Firmware) Type Voltage Software Mapping Part Number 

FADEC D48 

TAE-125 m3.30 

P/N 02-7610-55101R14 

Cessna 172 14V P14D330CES 20-7610-E022001

Cessna 172 28V P28D330CES 20-7610-E023001

Piper PA28 14V P14D330PIP 40-7610-E022001

Piper PA28 28V P28D330PIP 40-7610-E023001

Apex DR400 14 V P14D330APEX 60-7610-E022001

Diamond DA40 14 V P14D330DA40 50-7610-E022001

FADEC D4 

D4-v1.40 

P/N 05-7610-E001003 

Cessna 172 14 V G14D140CES 20-7610-E012301

Cessna 172 28 V G28D140CES 20-7610-E013301

Piper PA28 14 V G14D140PIP 40-7610-E012301

Piper PA28 28 V G28D140PIP 40-7610-E013301

Apex DR400 14 V G14D140APEX 60-7610-E012301

Diamond DA40 14 V G14D140DA40 50-7610-E012301

Diamond DA42 28 V G28D130DA42 52-7610-E012601