EASA AD No.: 2015

- 0190

- E

TE. CAP.0011 1

- 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 EMERGENCY AIRWORTHINESS DIRECTIVE

AD No

. : 2015

- 0190

- E

Date: 18 September 2015

Note: This Emergency 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 2 1

. 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 wi th 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 62 Main Rotor

– Blades

– Inspection

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

Applicability: A109A and A109A II helicopters, all serial numbers

.

Reason: A bnormal vibrations were reported during flight on an A109AII helicopter. During post flight inspection, a crack was found on a main rotor blade (MRB) part number (P/N) 109

- 0103

- 01

- 9.
This condition, if not detected and corrected, could affect the st ructural integrity of the blade, possibly resulting in blade failure and loss of control of the helicopter. Prompted by this finding, AgustaWestland issued Bollettino Tecnico (BT) 109

- 150, providing instructions for pre

- flight and repetitive inspections o f the affected MRB

. Due to similar ity of design, the inspections also apply to MRB P/N 109

- 0103

- 01

- 7 and P/N 109

- 0103

- 01

- 115.

For the reason describe d above, this AD requires pre

- flight inspections and repetitive inspections on affected MRB

.

Effective Date: 2 2 September 2015EASA AD No.: 2015

- 0190

- E

TE. CAP.0011 1

- 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:

Note 1: F or the purpose of this AD, an affected MRB is identified by P/N 109

- 0103

- 01

- 7, or P/N 109

- 0103

- 01

- 9, or P/N 109

- 0103

- 01

- 115

. (1) Upon accumulating 500 flight hours (FH) by an affected MRB (see Note 1 of this AD) since first installation on a helicopter , o r before next flight

, whichever occurs later after the effective date of this AD, and

, thereafter

, before each flight, visual ly inspect that MRB in accordance with Part I of the compliance instructions of AgustaWestland BT 109

- 1 50. Note 2: The inspections required by paragraph (1) of this AD may be performed by appropriately trained and authorized flight crew members and/or pilot owner, in accordance with Commission Regulation (EU) 1321/2014 Part M and Part 145 provisions. (2) Upon accumulating 500 FH by a n affected MRB (see Note 1 of this AD) since first installation on a helicopter , or before first flight of any day

, whichever occurs later after the effective date of this AD, and, thereafter, before first flight of each day, inspect that MRB in accordance with Part II of the compliance instructions of AgustaWestland BT 109

- 1 50. (3 ) If, during any inspection as required by paragraph ( 1 ) or (2) of this AD, as applicable, any crack is found, before next flight, replace the affected MRB with a serviceable MRB in accordance with the applicable maintenance manual. ( 4 ) Replacement of a MRB on a helicopter as required by paragraph ( 3 ) of this AD does not constitute terminating action for the repetitive inspections required by paragraph (1) and ( 2 ) of this AD for that helicopter. (5) Amendment of the applicable Rotorcraft Flight Manual (RFM) by inserting a copy of this AD, and thereafter, operatin g the helicopter acco rdingly

, is an acceptable way to show compliance with paragraph (1) of this AD. After revising the RFM it is not necessary that accomplishment of individual inspection s is recorded for demonstration of AD compliance on a continued basis

.

Ref. Public ations: AgustaWestland BT 109

- 1 50 original issue dated 17 September 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. The results of the safety assessment ha ve indicated the need for immediate publication and notification , without the full public consultation process

. 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: custserv@agustawestland.com

.