EASA AD No.: 2015-0014

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0014

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 – Reduction Gear Box Quill Shaft and Supporting Cone –

Inspection

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

Applicability: M601D, M601D-1, M601D-11NZ, M601E, M601E-11, M601E-11A, M601E-21

and M601F 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, Aircraft 

Industries L-410 aeroplanes.

Reason: It has been identified that misalignment between the Quill shaft of the engine 

and the Power Turbine (PT) shaft may lead to a rupture of the Quill shaft. 

This condition, if not detected and corrected, could lead to overspeed of the PT

and consequent uncontained engine failure, possibly resulting in damage to the 

aeroplane and injury to occupants and/or persons on the ground.

To address this unsafe condition, GE Aviation Czech issued Service Bulletin

(SB) M601D/44 to provide instructions for inspection.

For the reason described above, this AD requires a one-time inspection of the 

Reduction Gear Box and Supporting Cone and, in case of findings, corrective 

action.

This AD is considered interim action and further AD action may follow.

Effective Date: 13 February 2015
EASA AD No.: 2015-0014

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 300 flight hours or 6 months after the effective date of this AD, 

whichever occurs first, accomplish an inspection of the Reduction Gear Box 

and Supporting Cone in accordance with the instructions of GE Aviation 

Czech SB M601D/44 Revision 02.

(2) If, during the inspection as required by paragraph (1) of this AD, any crack 

is detected on the Quill Shaft, the PT Shaft or the Supporting Cone, or if the 

Quill Shaft or PT Shaft involute spline wear exceeds 0.12 mm, before next 

flight, accomplish corrective action in accordance with the instructions of

GE Aviation Czech SB M601D/44 Revision 02.

(3) Inspection and corrective action, accomplished before the effective date of 

this AD in accordance with the instructions of GE Aviation Czech SB 

M601D/44 at original issue or at Revision 01, is acceptable to comply with 

the requirements of this AD.

Ref. Publications: GE Aviation Czech SB M601D/44 original issue dated 27 June 2014, or 

Revision 01 dated 23 December 2014, or Revision 02 dated 23 January 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 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 23 December 2014 as PAD 14-180 for consultation 

until 09 January 2015. The Comment Response Document can be found 

at http://ad.easa.europa.eu.

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.: 2015-0014

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Appendix 1 – Affected engine s/n

M601D

854037 863010 

M601D-1

832058 843036 851005 852052 852079

M601D-11NZ

903011

M601E

064003 064004 843013 852217 854027 861003

861032 862023 864002 874001 874017 874031

881038 883060 884045 884090 892022 901028

902005 902025 903044 904015 904016 904021

911001 911011 913009 914020 914021 922017

922023 912028 883066 901046 054003 873026

863012 884029 864032

M601E-11

833244 841289 852239 861007 881217 884021

892046 892219 894018 903028 913038 912023

M601E-11A

902004 883046

M601E-21

894029 912031 913037 882052

M601F

912001 924002