EASA AD No.: 2013

- 0118

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 3

- 0 118

Date: 03 June 201 3

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 EC 7 48 /20 12 , Part 21

. A.3B. In accordance with EC 2042/2003 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 requirements of that AD
, unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]

.



### D e sign Approval Holder’s Name :
AGUSTA

WESTLAND S.p.A. Type/Model designation(s) :

A109 and A119 helicopters

TCDS Number: EASA. R .0 05

F oreign AD : Not applicable

Supersedure: None



### ATA 63 Main Rotor Drive

– Main Gear Box / Gleason Crown

– In spection /

Replacement

Manufacturer(s): AgustaWestland S.p.A (formerly Agusta S.p.A.), AgustaWestland Philadelphia Corporation (formerly Agusta Aerospace Corporation).

Applicability: A109K2, A109E , A119 and A W 1 1 9 MK II helicopters, all serial numbers ( s / n )

.

Reason: D uring the overhaul of a n A119 helicopter main transmission
, Part Number ( P/N ) 109

- 0400

- 05

- 103, a crack on Gleason crown P/N 109

- 0403

- 07

- 103 was found

. The investigation of th is occurrence carried out by AgustaWestland revealed that the crack was originated from the bottom of one of 40 threaded holes in the Gleason crow n

. The Gleason crown P/N 109

- 0403

- 07

- 103 is also eligible for installation on A109 helicopters. This condition, if not detected and corrected, could cause damage to, or loss of, the main rotor drive
, possibly resulting in loss of control of the helicopter

. To address this potential unsafe condition, AgustaWestland published Bollettino Tecnico ( BT ) 109K

- 57 Rev. A , BT 1 1 9

- 058 Rev. A and BT 109EP

- 128 Rev. A (hereafter called “ the applicable BT ” )
, provid ing instructions for additional i nspections of the Gleason crown and, depending on findings, replacement of the affected part with a new support assembly Gleason crown (welded to the mast support, which does not have the 40 threaded holes).EASA AD No.: 2013

- 0118

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. For the reasons described above, this AD requires repetitive inspections of the Gleason c rown and
, depending on findings, accomplishment of the applicable corrective actions.

Effective Date: 1 7 June 2013

Required A ction(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within the compliance time specified in the applicable BT, depending on the time in service o f the affected main transmission on the effective date of this AD, accomplish repetitive magnetic particle inspection s of the Gleason
c rown in accordance with the instructions of the applicable BT

. Note 1: For the purpose of this AD, the affected main transmission s are listed in Table 1 of this AD.
Table 1

– Affected Main Transmission

Helicopter Model (s) P/N S/N
A109K2 109

- 0400

- 03

- 10 3 Defined in the applicable BT A119 and AW119MK II 109

- 0400

- 05

- 103
A109E 109

- 0400

- 03

- 109

( 2 ) If, during any inspection a s required by paragraph (1) of this AD
, any crack is identified, before next flight
, replace the affected Gleason c rown with a n improved part in accordance with the instructions of the applicable BT

. (3) An inspection
, accomplished before the effective date of this AD in accordance with the instructions of the applicable AgustaWestland BT at
o riginal issue, is acceptable to comply with the init ial inspection as required by paragraph (1) of this AD. ( 4 ) Replacement of a Gleason c rown as required by paragraph (2 ) of this AD constitute s terminating action for the repetitive inspections as required by paragraph (1) of this AD. ( 5 ) From the effective date of this AD, do not install on any helicopter a Gleason crown P/N 109

- 0403

- 07

- 103 and do not install on any helicopter a Gleason crown ass embl y P/N 109

- 0401

- 27

- 101 or
- 109 ( Gleason c rown P/N 109

- 0403

- 07

- 103 is part of these assemblies)

.
Ref. Public ations: AgustaWestland BT 109K

- 57 Rev. A dated 28 May 201 3

. AgustaWestland BT 1 1 9

- 058 Rev. A dated 28 May 201 3

. AgustaWestland BT 109EP

- 128 Rev. A dated 28 May 201 3

. The use of later approved revisions of th e s e 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. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments, postponing the public consultation process until after publication.
3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: Agusta S.p.A. Customer Support Via del Gregge, 100

- 21015 Lonate Pozzolo (VA)

– Italy Telephone + 39 0331 664600 ; Fax: + 39 0331 664684 E

- mail: custserv@agustawestland.com

.