EASA AD No.: 2015

- 0015

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2015

- 0 0 1 5

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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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

F oreign AD: Not applicable

Supersedure: None



### ATA 72 Engine

– G as 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) b lades 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_3 2 (for engines overhauled prior to 2009) to provide instructions for GGT blade replacement.
For the reason described above, this AD requires replace ment of the non

- shot peened GGT blades.

Effective Date: 13 February 2015EASA AD No.: 2015

- 0015

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(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 S B M601D

- 1_31 or SB M601D

- 1_32 , as applicable to engine s/n.

Ref. Public ations: 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 document s 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 i n this AD, please contact: GE Aviation Czech Beranových 65

, 199 02 Praha 9

– Letňany Czech Republic T el. : +420 222 538 111 ; F ax : +420 222 538 222

.EASA AD No.: 2015

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TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

### Appendix 1

– Affected engine s/n

GE Aviation Czech SB M601D

- 1_31 :

GE Aviation Czech SB M601D

- 1_3 2 :EASA AD No.: 2015

- 0015

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet.