EASA AD No.: 2013-0118

TE.CAP.00110-003 © 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.: 2013-0118

Date: 03 June 2013

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 748/2012, 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 operate 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].

Design Approval Holder’s Name :

AGUSTAWESTLAND S.p.A.

Type/Model designation(s) :

A109 and A119 helicopters

TCDS Number: EASA.R.005

Foreign AD: Not applicable

Supersedure: None

ATA 63 Main Rotor Drive – Main Gear Box / Gleason Crown – Inspection / 

Replacement

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

Corporation (formerly Agusta Aerospace Corporation).

Applicability: A109K2, A109E, A119 and AW119MKII helicopters, all serial numbers (s/n).

Reason: During the overhaul of an 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 this occurrence carried out by AgustaWestland revealed 

that the crack was originated from the bottom of one of 40 threaded holes in the 

Gleason crown. 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 119-058 Rev. A and BT 109EP-128 Rev. A

(hereafter called “the applicable BT”), providing instructions for additional 

inspections 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.00110-003 © 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 crown and, depending on findings, accomplishment of the applicable 

corrective actions.

Effective Date: 17 June 2013

Required Action(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 of the affected main transmission on the effective date of 

this AD, accomplish repetitive magnetic particle inspections of the Gleason 

crown in accordance with the instructions of the applicable BT.

Note 1: For the purpose of this AD, the affected main transmissions are listed in 

Table 1 of this AD.

Table 1 – Affected Main Transmission

Helicopter Model(s) P/N S/N

A109K2 109-0400-03-103

Defined in the 

applicable BT A119 and AW119MKII 109-0400-05-103

A109E 109-0400-03-109

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

is identified, before next flight, replace the affected Gleason crown with an

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

original issue, is acceptable to comply with the initial inspection as required 

by paragraph (1) of this AD.

(4) Replacement of a Gleason crown as required by paragraph (2) of this AD 

constitutes 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 assembly P/N 109-0401-27-101 or -109 (Gleason crown 

P/N 109-0403-07-103 is part of these assemblies).

Ref. Publications: AgustaWestland BT 109K-57 Rev. A dated 28 May 2013.

AgustaWestland BT 119-058 Rev. A dated 28 May 2013.

AgustaWestland BT 109EP-128 Rev. A dated 28 May 2013.

The use of later approved revisions of these documents 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.