EASA AD No.: 2016

- 0025

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TE.CAP.0011 1

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

Proprietary document. Copies are not controlled. Confirm revision status through the EASA

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An agency of the European Union Page 1 of 4 

# Emergency Airworthiness Directive

AD No.: 2016

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[ C orrection : 27 January 2016]

I ssued : 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

Re gulation

.

This AD is issued in accordance with Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 Ann ex I, Part M.A.301, the

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Con sequently, 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 (E U) 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: 2 8 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, M60 1 D

- 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 i nstalled 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:

D uring engine shop visit s or overhaul s , certain p ower t urbine ( PT ) d isc s may have been damaged in
the area of the balance weights

. Additional PT disc s with non conforming geometry of the slot

ra dius 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, po ss i b ly resulting in damage to, and/or red u ced control of

, the aeroplane

.EASA AD No.: 2016

- 0025

- E

TE.CAP.0011 1

- 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 Ale r t Service Bulletin (SB)

SB

- 2016

- 72

- 50

- 00

- 1 (hereafter referred to as “the SB”) to provide inspection instructions f or 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 A pplicability 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 instruc tions of the SB

.

Table 1

– Affected engines and Compliance Time

Engine Model s/n Compliance time

( after the effective date of this AD)

M601 D

- 1 833027 30 days

M601 E

- 11 833244 3 months

M601 D 842066 3 months

M601 D

- 1 852052 30 days

M601 E 862003 3 months

M601 D

- 2 864005 14 days

M601 E 864204 3 months

M601 E 871001 3 months

M601 E 871016 3 months

M601 E 872013 30 days

M601 E 873039 3 months

M601 E 873041 3 months

M601 D 874004 2 months

M601 D 874006 2 months

M601 E 874025 3 months

M601 E 881012 3 months

M601 E

- 11 881020 3 months

M601 E 881021 3 months

M601 E 882035 3 months

M601 E 882046 3 months

M601 E 882049 3 months

M601 E 883017 3 months

M601 E 883025 3 months

M601 E 883037 3 monthsEASA AD No.: 2016

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TE.CAP.0011 1

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An agency of the European Union Page 3 of 4

Engine Model s/n Compliance time

( after the effective date of this AD)

M601 E 883061 3 months

M601 E 883065 3 months

M601 E 884029 3 months

M601 E 891022 3 months

M601 E 891033 3 months

M601 E 891042 3 months

M601 E 894010 3 months

M601 D

- 1 894019 30 days

M601 E 894031 14 days

M601 E 901043 3 months

M601 E 903001 2 months

M601 E

- 21 904022 3 months

M601 E 904032 3 months

M601 E 911001 3 months

M601 E 911031 3 months

M601 D 912006 3 months

M601 D 912018 2 months

M601 E 913006 30 days

M601 E 913009 3 months

M601 E 914004 3 months

M601 E 914017 3 months

M601 E 922003 3 months

M601 E

- 11 922009 14 days

M601 Z 931002 3 months

M601 D

- 2 932002 14 days

M601 E 941014 3 months

(2) If, during the inspection as re q ui r ed by par a graph (1) of this A D

, a ny damage is found, or a

non

- conforming slot radiu s , exceeding the acceptability criteria as defined in the applicable SB,

before next flight, rep lace 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 an y aeroplane an engine, having a s/n as listed in Table 1 of this AD, unless it has passed an inspection in accordan ce 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.0011 1

- 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 4 of 4 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 p rocess.

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 requ irements 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.