EASA AD No.: 2015-0189

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0189

Date: 21 September 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 05 Time Limits / Maintenance Checks – Airworthiness Limitation 

Section – Amendment

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.

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 or 

EASA 10014287).

- Piper PA-28 series (STC EASA.A.S.01632 or STC EASA 10014364).

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

10014219).

- Diamond DA 40 and DA 42 series.

Reason: In-flight shut down occurrences have been reported on aeroplanes equipped 

with TAE 125-02 engines. The initial results of the investigations showed that a 

defective fuel feed pump was the probable cause of the engine failure.

This condition, if not detected and corrected, could lead to further cases of 

engine power loss, possibly resulting in loss of control of the aeroplane.

To address this potential unsafe condition, TMG has reduced the inspection 

interval of fuel feed pumps P/N 05-7312-K0073xx, 05-7312-K0133xx (where 

“xx” can be any number). The approved Airworthiness Limitation Section (ALS), 

published in the applicable Operation & Maintenance Manual OM-02-02, 
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Chapter 5, Issue 4, Revision 4 (hereafter referred to as ‘the ALS’ in this AD),

has been revised to reflect the new interval.

For the reason described above, this AD requires accomplishment of all 

maintenance tasks and parts replacement as described in the ALS.

Effective Date: 05 October 2015

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) From the effective date of this AD, accomplish the actions required by 

paragraphs (1.1), (1.2) and (1.3) of this AD, as specified in the ALS:

(1.1) Replace each component before exceeding the applicable life limit.

(1.2) Within the thresholds and intervals, accomplish all applicable 

maintenance tasks.

(1.3) Inspect fuel feed pumps, P/N 05-7312-K0073xx and 

P/N 05-7312-K0133xx, which, on the effective date of this AD, have 

reached or exceeded 600 operating hours (OH) since first 

installation on an aircraft or since last inspection, as applicable, 

within 110 OH after the effective date of this AD, and thereafter at 

intervals not exceeding the value as specified in the ALS.

(2) If, during any maintenance task as required by paragraph (1.2) or (1.3) of 

this AD, as applicable, discrepancies are detected, within the compliance 

time specified in the ALS, accomplish the applicable maintenance 

procedures for corrective action(s) in accordance with the approved 

maintenance documentation. If no compliance time is identified in the ALS, 

accomplish the applicable corrective actions before next flight. If a detected 

discrepancy is not identified in the ALS, before next flight, contact TMG for 

approved instructions and accomplish those instructions accordingly.

(3) Within 12 months after the effective date of this AD, revise the approved 

aircraft maintenance programme (AMP), on the basis of which the operator 

or the owner ensures the continuing airworthiness of each operated 

aeroplane, by incorporating the limitations, tasks and associated 

thresholds and intervals described in the ALS.

(4) For an AMP that, on the effective date of this AD, is already updated to 

incorporate the maintenance tasks and life limitations as specified in TMG

OM-02-02, Chapter 5, Issue 4, Revision 3, it is acceptable to incorporate 

the new and more restrictive tasks and limitations, as defined in the ALS, 

into the AMP to comply with paragraph (3) of this AD.

(5) When the AMP of an aircraft has been revised as required by paragraph 

(3) or (4) of this AD, as applicable, that action ensures (see Note 1 of this 

AD) continued accomplishment of the tasks as required by paragraph (1) 

of this AD for that aircraft. Consequently, after revising the AMP, as 

required by paragraph (3) or (4) of this AD, as applicable, it is not 

necessary that accomplishment of individual tasks is recorded for 

demonstration of AD compliance on a continued basis.

Note 1: For affected engines installed on aircraft registered in Europe, 

complying with the approved AMP as specified in paragraph (3) of this AD is 

required by Commission Regulation (EU) No 1321/2014, Part M.A.301, 

paragraph 3.

Ref. Publications: Operation & Maintenance Manual OM-02-02, Chapter 5, Issue 4, Revision 4, 

dated 02 September 2015

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 
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Alternative Methods of Compliance for this AD.

2. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

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.