EASA AD No.: 2016-0025-E

TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

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Emergency Airworthiness Directive

AD No.: 2016-0025-E

[Correction: 27 January 2016]

Issued: 26 January 2016

Note: This Emergency Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) 216/2008 on behalf of the European Union, 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 Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (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 [Regulation (EU) 1321/2014 Annex I, 

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

Design Approval Holder’s Name:

GE AVIATION CZECH

Type/Model designation(s):

M601 Engines 

Effective Date: 28 January 2016

TCDS Number(s): EASA.E.070 

Foreign AD: Not applicable

Supersedure: None

ATA 72 – Engine – Power Turbine Disc – Inspection / Replacement

Manufacturer(s):

GE Aviation Czech S.R.O. (formerly Walter Engines a.s.)

Applicability:

M601D, M601D-1, M601D-2, M601E, M601E-11, M601E-21, and M601Z engines, having a serial 

number (s/n) as listed in Table 1 of this AD.

These engines are known to be installed on, but not limited to, Thrush Aircraft Inc. (formerly 

Quality, Ayres, Rockwell) S-2R, PZL "Warszawa-Okęcie" PZL-106 (Kruk), RUAG (formerly Dornier) 

Do 28 and Aircraft Industries (formerly LET) L-410 aeroplanes.

Reason:

During engine shop visits or overhauls, certain power turbine (PT) discs may have been damaged in 

the area of the balance weights. Additional PT discs with non conforming geometry of the slot 

radius may have also been released to service as a result of incorrect machining of the PT disc slot.

This condition, if not corrected, could lead to a PT disc failure, with subsequent release of 

high-energy debris, possibly resulting in damage to, and/or reduced control of, the aeroplane. 
EASA AD No.: 2016-0025-E

TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

Page 2 of 4

To address this unsafe condition, GE Aviation Czech issued Alert Service Bulletin (SB) 

SB-2016-72-50-00-1 (hereafter referred to as “the SB”) to provide inspection instructions for the 

affected engines.

For the reasons described above, this AD requires inspection of the PT disc and, depending on 

findings, replacement with a serviceable part. 

This AD was republished to correct typographical errors in the Applicability and in Table 1 (column 

“Engine Model”).

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time as specified in Table 1 of this AD, as applicable to engine model and 

serial number, inspect the PT disc in accordance with the instructions of the SB.

Table 1 – Affected engines and Compliance Time

Engine Model s/n Compliance time

(after the effective date of this AD)

M601D-1 833027 30 days

M601E-11 833244 3 months

M601D 842066 3 months

M601D-1 852052 30 days

M601E 862003 3 months

M601D-2 864005 14 days

M601E 864204 3 months

M601E 871001 3 months

M601E 871016 3 months

M601E 872013 30 days

M601E 873039 3 months

M601E 873041 3 months

M601D 874004 2 months

M601D 874006 2 months

M601E 874025 3 months

M601E 881012 3 months

M601E-11 881020 3 months

M601E 881021 3 months

M601E 882035 3 months

M601E 882046 3 months

M601E 882049 3 months

M601E 883017 3 months

M601E 883025 3 months

M601E 883037 3 months
EASA AD No.: 2016-0025-E

TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

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Engine Model s/n Compliance time

(after the effective date of this AD)

M601E 883061 3 months

M601E 883065 3 months

M601E 884029 3 months

M601E 891022 3 months

M601E 891033 3 months

M601E 891042 3 months

M601E 894010 3 months

M601D-1 894019 30 days

M601E 894031 14 days

M601E 901043 3 months

M601E 903001 2 months

M601E-21 904022 3 months

M601E 904032 3 months

M601E 911001 3 months

M601E 911031 3 months

M601D 912006 3 months

M601D 912018 2 months

M601E 913006 30 days

M601E 913009 3 months

M601E 914004 3 months

M601E 914017 3 months

M601E 922003 3 months

M601E-11 922009 14 days

M601Z 931002 3 months

M601D-2 932002 14 days

M601E 941014 3 months

(2) If, during the inspection as required by paragraph (1) of this AD, any damage is found, or a 

non-conforming slot radius, exceeding the acceptability criteria as defined in the applicable SB, 

before next flight, replace that PT disc with a serviceable part in accordance with the 

instructions of the SB.

(3) From the effective date of this AD, do not install on any aeroplane an engine, having a s/n as 

listed in Table 1 of this AD, unless it has passed an inspection in accordance with the 

instructions of the SB.

Ref. Publications:

GE Aviation Czech SB-2016-72-50-00-1, original issue, dated 21 january 2016.

The use of later approved revisions of this document is acceptable for compliance with the 

requirements of this AD.
EASA AD No.: 2016-0025-E

TE.CAP.00111-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

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Remarks:

1. If requested and appropriately substantiated, EASA can approve Alternative Methods of 

Compliance for this AD.

2. The results of the safety assessment have indicated the need for immediate publication and 

notification, without the full consultation process.

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

Certification Directorate. 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 

Telephone: +420 222 538 111; Fax: +420 222 538 222.