Airworthiness Directive · Amendment 39-14603 · Eurocopter France Model EC130 B4 Helicopters
Eurocopter France Model EC130 B4 Helicopters
Model EC130 B4 helicopters, with a throttle twist grip (twist grip) assembly, part number (P/N) 350A27-5209-00, P/N 350A27-5209-01, or P/N 350A27-5209-02, installed, certificated in any category.
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC130 B4 helicopters. This action requires inspecting the throttle twist grip (twist grip) assembly for any foreign body (chip or debris), any rotating micro-switch, and any micro-switch roller that does not move freely. If any unairworthy condition is found, this action requires that it be corrected before further flight. This amendment is prompted by two reports of a twist grip assembly jamming in the "IDLE" position. The actions specified in this AD are intended to detect and prevent jamming of the twist grip assembly, which, if present, could keep the engine from operating above idle speed and result in subsequent loss of control of the engine power of the helicopter.
To detect jamming of the twist grip assembly, which could keep the engine from operating above idle speed and result in subsequent loss of control of the engine power of the helicopter, accomplish the following:
(a) Within 30 hours TIS, access the twist grip assembly and inspect the cam and micro-switch body and rollers for:
(1) Any foreign chip or debris;
(2) Any friction point while turning the twist grip assembly from “Flight” to “Idle” position;
(3) Any rotating micro-switch body; and
(4) Any micro-switch roller that does not turn freely.
(b) If you find any chip or debris, remove it; if you find a friction point, a rotating micro-switch body, a binding micro-switch roller or any other unairworthy part, repair or replace the part before further flight.
Note 1: Eurocopter Alert Telex No. 05A003, dated June 30, 2005, pertains to the subject of this AD. AMM Task 76-12-00, 6-1, dealing with a repetitive functional check of the twist grip assembly, has been inserted into the current maintenance instructions and is now part of the annual or 100-hour inspection.
(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, Rotorcraft Directorate, FAA, ATTN: Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 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
