EASA AD No.: 2010-0142-E 

EASA Form 111 Page 1/2 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0142-E 

Date: 05 July 2010 

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 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 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]. 

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 locking 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 corrected, 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 2010 
EASA 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 instructions 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 flight 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 Bollettino 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 immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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: 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 .