EASA AD No.: 2015-0015

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0015

Date: 30 January 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 Approval Holder’s Name:

GE AVIATION CZECH

Type/Model designation(s):

M601 engines

TCDS Number: EASA.E.070

Foreign AD: Not applicable

Supersedure: None

ATA 72 Engine – Gas Generator Turbine Blades – Replacement

Manufacturer(s): GE Aviation Czech s.r.o (formerly Walter Engines a.s.)

Applicability: M601D-1, M601E, M601E-11, M601E-11A, M601E-21, M601F, M601FS, 

M601F-22, M601F-32, M601T and M601Z engines with a serial number (s/n) 

as listed in Appendix 1 of this AD.

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

 Thrush S2R aeroplanes

 PZL “Kruk” aeroplanes

 Dornier DO 28 aeroplanes

Reason: It has been demonstrated that non-shot peened Gas Generator Turbine (GGT)

blades are susceptible to blade separation in the shank area due to their 

reduced fatigue life. 

This condition, if not corrected, could lead to an in-flight engine shutdown and, 

consequently, reduced control of the aeroplane.

To address this unsafe condition, GE Aviation Czech issued SB M601D-1_31 

(for engines overhauled prior to 2012) and SB M601D-1_32 (for engines 

overhauled prior to 2009) to provide instructions for GGT blade replacement.

For the reason described above, this AD requires replacement of the non-shot 

peened GGT blades.

Effective Date: 13 February 2015
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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Within 300 flight hours or 6 months, whichever occurs first after the effective 

date of this AD, replace the non-shot peened GGT blades with shot peened 

GGT blades in accordance with the instructions of GE Aviation Czech SB

M601D-1_31 or SB M601D-1_32, as applicable to engine s/n.

Ref. Publications: GE Aviation Czech SB M601D-1_31 dated 23 December 2014.

GE Aviation Czech SB M601D-1_32 dated 23 December 2014.

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 23 December 2014 as PAD 14-181 for consultation 

until 09 January 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:

GE Aviation Czech

Beranových 65, 199 02 Praha 9 – Letňany

Czech Republic 

Tel.: +420 222 538 111; Fax: +420 222 538 222.
EASA AD No.: 2015-0015

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Appendix 1 – Affected engine s/n

GE Aviation Czech SB M601D-1_31:

GE Aviation Czech SB M601D-1_32:
EASA AD No.: 2015-0015

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