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CITATION MUSTANG OPERATING MANUAL INTRODUCTION This chapter describes the flight controls of the Cessna Model 510 Citation Mustang. The aircraft has fixed and moveable surfaces that provide stability and control during flight. The primary flight controls are ailerons, rudder, and elevators. Secondary flight controls include trim devices, flaps, and speedbrakes. Control locks are also described. GENERAL The flight control systems consist of the control surfaces, trim control surfaces, trim indicating systems, and the related mechanical and electrical systems that control the airplane during flight. The primary flight controls (elevators, ailerons, and rudder) directly control aircraft movement around the three axes of flight (pitch, roll, and yaw). They are manually actuated through cables by dual conventional control yokes and dual sets of rudder pedals in the cockpit. They can be immobilized by control locks when on the ground to prevent damage to the control surfaces and systems from wind gusts striking the aircraft. The secondary flight controls include trim, flaps, and speedbrakes. Trim tabs, electrically or mechanically adjusted through controls on the cockpit pedestal or control yoke, assist flight control on all three axes. Mechanical elevator trim, adjusted through a cockpit pedestal wheel, is also provided. CHAPTER 15 FLIGHT CONTROLS 20 20 20 10 5 5 10 10 5 5 L O C G S Flaps and speedbrakes directly adjust airplane lift and drag. Both controls are electrically actuated. Flaps are operated by a handle on the cockpit pedestal. Speedbrakes are operated by a switch on the throttle. All flight control surfaces are shown in Figure 15-1. PRIMARY FLIGHT CONTROLS DESCRIPTION The primary flight controls (ailerons, rudder, and elevators) are manually operated by either the pilot or the copilot through a conventional control yoke and rudder pedal arrangement. Control inputs are transmitted to the control surfaces through cables, bellcranks, and pushrods. The rudder pedals also operate the nosewheel steering and wheel brakes (see Chapter 14—“Landing Gear and Brakes”). A flexible mechanical interconnect between the rudder and ailerons provides improved lateral stability. The primary flight controls can also be controlled by the autopilot and yaw damper (see Chapter 16—“Avionics”). The rudder, both elevators, and the left aileron are each equipped with a trim tab that is electrically actuated from the cockpit. The elevator tabs can also be mechanically positioned by the pitch trim wheel on the control pedestal. AILERON SYSTEM Two ailerons (one on the outboard trailing edge of each wing) provide roll control. Neutral aileron position is 2° up. The ailerons are controlled through cables connected to the cockpit control yokes and the autopilot aileron electric servo. The control yoke rotates 70° in each direction to provide maximum aileron deflection. 15-2 510OM-00 CITATION MUSTANG OPERATING MANUAL FLAP ELEVATOR TRIM TAB TRIM TAB TRIM TAB RUDDER SPEEDBRAKE AILERON STRAKE Figure 15-1. Flight Control Surfaces 510OM-00 15-3 CITATION MUSTANG OPERATING MANUAL Operation When the pilot rotates the control yokes counterclockwise, the right aileron rotates down and the left aileron rotates up, causing the aircraft to roll left. By turning the control yokes clockwise, the opposite is true. When the autopilot is operating, the autopilot roll servo provides inputs to the aileron control system. A single autopilot roll servo is mechanically connected to the aileron cable system. When the autopilot is engaged, the autopilot servo provides autopilot input to the aileron system in response to the automatic flight control system (AFCS) commands. Disengaging the autopilot can be accomplished by three normal means: • The AP or YD button on the AFCS controller • The AP TRIM DISC switch on either control yoke • By commanding pitch trim Either pilot can manually override the servo motor by applying force to the control yoke. For information on the AFCS (including autopilot), refer to Chapter 16—“Avionics.” Aileron-Rudder Interconnect A flexible mechanical interconnect between rudder and ailerons provides improved lateral stability. Movement of the ailerons results in www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：CITATION MUSTANG OPERATING MANUAL 2
