EASA AD No.: 2015

- 0097

TE. CAP.00110

- 00 4 © 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

. : 2015

- 0097

Date: 01 June 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 E U 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 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 : AGUSTAWESTLAND S.p.A. Type/Model designation(s) : A109A and A109AII helicopters

TCDS Number: EASA.R.005

F oreign AD: Not applicable

Supersedure: None



### ATA 65 Tail Rotor Drive

– Slider Assembly Pitch Control

– Inspection

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

Applicability: A109A and A109A II helicopters, all serial numbers

.

Reason: During a scheduled 100 flight hour (FH) inspection on an A109AII helicopter

, unusual play was detected on the s lider ass embl y pitch control Part Number ( P/N ) 109

- 0130

- 11

- 7. Further investigation identified an excessive wear of the broaching of the slider assembly pitch control at the point of contact with the tail rotor shaft. The reason for this excessive play and wear has not yet been determined and investi gations are still ongoing.
This condition, if not detected and corrected, could lead to reduced control of the helicopter

. To address this unsafe condition, AgustaWestland issued Bollettino Tecnico (BT) 109

- 149 to provide instructions for inspection.
For the reason described above, this AD requires repetitive inspections of the slider assembly pitch control P/N 109

- 0130

- 11

- 7 at reduced intervals, and, depending on findings, accomplishment of corrective action (s)

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

Effective Date: 15 June 2015EASA AD No.: 2015

- 0097

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 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 25 flight hours (FH) after the effective date of this AD and, thereafter, at intervals not to exceed 25 FH, inspect the slider assembly pitch control P/N 109

- 0130

- 11

- 7 for play in accordance with the instructions of AgustaWestland BT 109

- 149

. (2) If, during any inspection as required by paragraph (1) of this AD, unusual play is detected, before next flight, accomplish the applicable corrective action(s) in accordance with approved maintenance instructions.
(3) Accomplishment of corrective action(s) on a helicopter as required by
par agraph ( 2 ) of this AD does not constitute terminating action for the repetitive inspections required by paragraph (1) of this AD for that helicopter

.

Ref. Public ations: AgustaWestland BT 109

- 149 original issue dated 29 May 2015.

The u se of later approved revisions of th is 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. Based on t he 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 A D 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: AgustaWestland S.p.A., Customer Support & Services

– Italy, Product Support Engineering DPT, via Indipendenza, 2 21018 Sesto Calende (VA)

– Italy Tel.: +39 0331 915874, Fax: +39 0331 664680 E

- mail: cu stserv@agustawestland.com

.