EASA AD No.: 2015

- 0014

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3

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

- Internet/Intranet. 

## 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 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 engine s

TCDS Number: EASA.E.070

F oreign AD: Not applicable

Supersedure: None



### ATA 72 Engine

– Reduction Gear Box Quill S haft and S upporting 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 t o

, 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 S ervice B ulletin

( 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 2015EASA AD No.: 2015

- 0014

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3

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:

(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 R evision 0 2

.

(2) If, du ring 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) Inspecti on 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. Public ations: GE Aviation Czech SB M601D/44 original issue dated 27 June 2014 , or

R evision 01 dated 23 December 2014, or R evision 0 2 dated 23 January 201 5

.

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

T el. : +420 222 538 111 ; F ax : +420 222 538 222EASA AD No.: 2015

- 0014

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3

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

- Internet/Intranet. 

### 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