EASA AD No.: 2015-0055

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0055

Date: 31 March 2015

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 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 accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with th e 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 Monitori ng System – Installation

Manufacturer(s): Technify Motors GmbH (TMG), former ly Thielert Aircraft Engines (TAE).
Applicability: TAE 125-02-99 (commercial designatio n CD-135, formerly Centurion 2.0) and TAE 125-02-114 (commercial designation CD-155, form erly Centurion 2.0S) engines, all serial numbers (S/N), if a Dual Mass F lywheel is installed, and if the engine is installed on one of the following aeropla ne types: - Cessna 172 and (Reims-built) F172 series with eng ine 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 ins talled 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 dur ing aeroplane manufacture), or any other S/N with engine installe d through STC EASA 10036328. - DAI DA 42 and DA42 M models, S/N 42.004 through 4 2.427, S/N 42.AC001 through 42.AC151 and S/N 42.M001 through 42.M027 (e ngine installed during aeroplane manufacture), or any other S/N wit h engine installed through STC EASA 10048730. Engines having a Dual Mass Flywheel installed can b e identified by marking on the fuel rail (sticker “Dual Mass Flywheel installe d”), or record in the engine log book (“Dual Mass Flywheel” listed as engine compone nt on page 4 “Main Engine Components”).EASA AD No.: 2015-0055

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Reason: Cases of a broken gearbox drive shaft have been reported on aeroplanes equipped with TAE 125-02 engines that have a Dual M ass Flywheel installed. Investigations results showed a possible overload o f 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 eng ine power loss during flight, possibly resulting in loss of control of the aeropl ane. To address this unsafe condition, TMG has developed an improved software mapping and a start phase monitoring system. See TM G Service Bulletin (SB) TM TAE 125-1018 P1 for further details. For the reason described above, this AD requires th e installation of the improved software mapping and of the start phase mo nitoring system.

Effective Date: 14 April 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
(1) Within 110 flight hours or at the next schedule d maintenance event, whichever occurs first after the effective date of this AD, install the software mapping specified in Appendix 1 of this AD, as appl icable to engine model and aeroplane type, in accordance with the instruct ions of TMG SB TM TAE 000-0007, Revision 28.
(2) Concurrent with the software mapping installati on as required by paragraph (1) of this AD, install a start phase monitoring sy stem 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 Sy stem

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 aeropl ane 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 soft ware mapping version as required by this AD or later.EASA AD No.: 2015-0055

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Ref. Publications: TMG SB TM TAE 125-1018 P1 Revisi on 1, dated 05 February 2015. TMG SB TM TAE 000-0007 Revision 28, dated 05 Februa ry 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 Februar y 2015. TMG SB TMG 651-1004 P1 Revision 2, dated 05 Februar y 2015. TMG SB TMG 691-1002 P1 Revision 2, dated 05 Februar y 2015. CEAPR SB n° 141201 Revision 1, dated 05 February 20 15. 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 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. This AD was posted on 24 February 2015 as PAD 15 -015 for consultation until 24 March 2015. No comments were received duri ng the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification 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: 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

.EASA AD No.: 2015-0055

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 4/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

### 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