Airworthiness Directive · Amendment 39-15434 · Eurocopter France Model EC130 B4 Helicopters
Eurocopter France Model EC130 B4 Helicopters
Model EC130 B4 helicopters, with a twist grip assembly, part number (P/N) 350A27520900, 350A27520901, 350A27520902, or 350A27520903, with a serial number below 64, installed on the pilot's side, and a twist grip assembly, P/N 350A27521201, with a serial number below 67, installed on the co-pilot's side, certificated in any category.
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) Model EC 130 B4 helicopters, with certain twist grip assemblies installed, that requires inspecting the pilot and co-pilot collective levers for proper bonding between the twist grip drive tubes and the control pinions and if debonding is present, replacing the collective levers before further flight. This amendment is prompted by one incident in which the engine remained at idle speed although the twist grip had been turned to the flight position. The actions specified by this AD are intended to detect debonding between the twist grip drive tubes and the control pinions on the pilot and co-pilot collective levers to prevent loss of cockpit throttle control of the engine, and subsequent loss of control of the helicopter.
To detect a reduced bonding strength of the control pinion on the pilot and co-pilot collective lever drive tubes, which could lead to failure of a twist grip drive tube and control pinion bonded attachment, resulting in loss of engine throttle control and subsequent loss of control of the helicopter, accomplish the following:
(a) Inspect the pilot and co-pilot collective levers for proper bonding between the twist grip drive tubes and the control pinions in accordance with paragraphs 2.B.1. and 2.B.2. of the Accomplishment Instructions, in Eurocopter, an EADS Company, Alert Service Bulletin EC130 No. 76A001, dated February 10, 2006, except you are neither required to contact the manufacturer nor return a non-compliant collective lever.
(b) If a twist grip turns when applying the 35N load to the twist grip, before further flight, replace the collective lever with an airworthy collective lever that has been inspected in accordance with paragraph (a) of this AD, or a collective lever with a twist grip assembly that is not listed in the Applicability of this AD.
(c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, ATTN: Ed Cuevas, Aviation Safety Engineer, Rotorcraft Directorate, FAA, Fort Worth, Texas 76193-0111, telephone (817) 222-5355, fax (817) 222-5961, for information about previously approved alternative methods of compliance.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
