EASA AD No.: 2010-0142-E

EASA Form 111 Page 1/2 

## EASA EMERGENCY AIRW ORTHINESS DIRECTIVE

AD No.: 2010-0142-E

Date: 05 July 2010

Note: This Emergency Airworthiness Directive (A D) 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 participat e in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EC 1702/2003, Part 21A .3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Age ncy [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) exemptio n]. 

### Type Approval Holder’s Name :
Agusta S.p.A. Type/Model designation(s) :
A119 and AW119MKII helicopters

TCDS Number : EASA.R.005

Foreign AD : Not applicable

Supersedure : None



### ATA 67 Rotors Flight Control – Pilot and Co-pilot Control Box Assemblies – Inspection / Replacement

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

Applicability: A119 and AW119MKII helicopters, all serial numbers, if equipped with pilot control box assembly part number (P/N) 109-0010-81-103 and co-pilot control box assembly P/N 109-0010-81-107.

Reason: A case of non-conformity has been discovered on an AW119MKII helicopter, in the pilot control box assembly P/N 109-0010-81-103 of the collective pitch control installation, where the gear lo cking pin P/N MS16555-628 fell out of its seat. This caused the loss of the pilot and co-pilot engine throttles synchronicity. This non conformity, if not detected and co rrected, could lead to the loss of the manual engine throttle and consequent loss of control of the helicopter. For the reason mentioned above, this AD requires repetitive inspections of the pilot and co-pilot control box assemblies and the accomplishment of the associated corrective actions, as necessary. A modification to the pilot and co-pilot control box assemblies is currently under development by the TC Holder. Another AD requiring the accomplishment of this modification might be issued later on, once the modification is approved.

Effective Date: 07 July 2010EASA AD No.: 2010-0142-E

EASA Form 111 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 5 flight hours (FH) after the effective date of this AD but no later than 31 August 2010, whichever occurs first, and thereafter at intervals not to exceed 50 FH, inspect the pilot control box assembly P/N 109-0010-81-103 and co-pilot control box assembly P/N 109-0010-81-107 to verify that the gear locking pin is correctly installed in its seat, in accordance with the in structions of Agusta Alert Bollettino Tecnico (BT) 119-39. (2) If the gear locking pin is not present or partially out of its seat, or recessed for more than 2.00 mm, before next fli ght replace the affected control box by a serviceable assembly with the same P/N, in accordance with the instructions of Agusta Alert BT 119- 39. Replacement of the control box does not constitute terminating action for the repetitive inspection requirements of paragraph (1) of this AD. (3) After the effective date of this AD , do not install the pilot control box assembly P/N 109-0010-81-103 and co-pilot control box assembly P/N 109-0010-81-107 on any helicopter, unless in compliance with the requirements of this AD.
Ref. Publications: Agusta Alert Bolle ttino Tecnico 119-39 dated 02 July 2010. 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. The safety assessment has requested not to implement the full consultation process and an immedi ate publication and notification. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the tec hnical 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 664873; Fax: + 39 0331 664680; E-mail: absereng@agustawestland.com

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