TM 1-1520-240-102-5-1SECTION V. FLIGHT CONTROLS2-5-1. Flight Control System.The helicopter is controlled by changing the pitch of theblades either collectively or cyclically. Pitch changes aremade by the pilot’s movement of the flight control whichinclude a THRUST CONT (control) lever, a cyclic controlstick, and directional pedals. The pilot’s controls are in-terconnected with the copilot’s controls.Flight control movements are transmitted through a sys-tem of bellcranks, push-pull tubes, and actuators to amixing unit just aft of the cockpit, next to the forwardtransmission. The control movements are mixed to givethe correct lateral cyclic and collective pitch motions tothe rotors through dual hydraulic actuators. These dualboost actuators are under each swashplate. Each set ofdual boost actuators is normally powered by both flightcontrol hydraulic systems.The helicopter is vertically controlled with the THRUSTCONT lever through application of equal pitch to all bla-des. Directional control is obtained with the directionalpedals by imputting equal but opposite lateral cyclic pitchto the blades. Lateral control is obtained by applicationof equal lateral cyclic pitch to the blades with the cycliccontrol stick. The helicopter is controlled longitudinallywith the cyclic stick through application of differentialcollective pitch.In addition, the helicopter has an advanced flight controlsystem (AFCS). AFCS provides the following features:a.Rate damping in all axes and sideslip stability.b.Pitch and roll attitude hold and heading hold.c.Airspeed hold.d.Improved control response in pitch, roll, andyaw.e.Barometric and radar altitude hold.f.Automatic coupled turns.g.Longitudinal cyclic trim scheduling.THRUST CONTROL LEVER(ON HELICOPTER WITHTHRUST CONTROL LEVER(ON HELICOPTER WITH714A ENGINE712 ENGINE2Figure 2-5-1. Thrust Control Lever
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