SECTION V. FLIGHT CONTROL SYSTEM
2-35. FLIGHT CONTROL SYSTEM.
The aircraft s primary light control systems consist of conventional rudder, elevator, and aileron control surfaces.
These surfaces are manually operated from the cockpit through mechanical linkage using a control wheel for the
ailerons and elevators, and adjustable rudder/brake pedals for the rudder. Both the pilot and copilot have light
controls. Trim control for the rudder, elevator, and ailerons is accomplished through a manually actuated cable-drum
system for each set of control surfaces. The autopilot has provisions for controlling the position of the ailerons,
2-36. CONTROL WHEELS.
Elevator and aileron control surfaces are operated by manually actuating either the pilot or the copilot s control wheel.
These control wheels (Fig. 2-29) are installed on each side of the instrument panel. Switches are installed in the
outboard grip of each wheel to operate the elevator trim tabs. A microphone switch, CHAFF DISPENSE switch, and
an autopilot/yaw damp/electric trim disconnect switch are also installed in the outboard grip of each control wheel.
A FLARE DISPENSE switch is installed on top of the inboard grip of each control wheel. In addition, a transponder
Ident switch is installed on the forward side of each control wheel. A map light switch, and touch control steering
(TCS) switch are located on the faceplate of each control wheel.
2-37. RUDDER SYSTEM.
a. Rudder Pedals. Aircraft rudder control and nose wheel steering is accomplished by actuation of the rudder
pedals from either pilot s or copilot s station (Fig. 2-14). The rudder pedals may be individually adjusted, in either
a forward or an aft position, to provide adequate legroom for the pilot and copilot. Adjustment is accomplished
by depressing the lever alongside the rudder pedal arm and moving the pedal, forward or aft, until the locking pin
engages in the selected position.
b. Yaw Damper System. A yaw damper system is provided to aid the pilot in maintaining directional stability
and increase ride comfort. The system may be used at any altitude, but is required for light above 17,000 feet. It
must be deactivated for takeoff and landing. The yaw damp system is a part of the autopilot. A YAW DAMP switch
located on the autopilot control head controls the system. Operating instructions for this system are contained in
c. Rudder Boost System. The rudder boost system is a torque sensing, linear actuating system. The system
utilizes a pressure transducer on each engine to sense engine torque oil pressure, a stability augmentation computer
to monitor torque levels and the rudder servo to apply boost to aid the pilot. The stability augmentation computer
monitors torque levels and airspeed to determine if boost is required. The level of boost is proportional to the differ-
ence in torque between each engine and inversely proportional to airspeed. Boost commences at about 50% torque
differential and increases to maximum at 100% torque differential. The level of boost available is inversely propor-
tional to airspeed such that maximum rudder boost is obtained at 100% differential and low airspeed (80 knots),
while no rudder boost is available at high airspeeds (above 180 knots). The rudder boost system is controlled by a
switch, placarded RUDDER BOOST-OFF-YAW CONTROL TEST , located on the pedestal extension (Fig. 2-19).
The rudder boost system is powered through a 5-ampere circuit breaker, placarded RUDDER BOOST , located on