FAA Approved Airplane Flight Manual Supplement

Hawker Beechcraft B300 and B300C King Air 190-00716-03 Rev.4
Page 132 of 173
FLIGHT CONTROLS
AFCS, AUTOPILOT, FLIGHT DIRECTOR AND RUDDER BOOST
The GFC 700 is a digital Automatic Flight Control System (AFCS), fully integrated within the G1000
System avionics architecture. The GFC 700 is a three-axis autopilot and flight director system which
provides the pilot with the following features:
Autopilot (AP) — Autopilot operation occurs within the pitch, roll, and pitch trim servos. It also provides
servo monitoring and automatic flight control in response to flight director steering commands, AHRS
attitude and rate information, and airspeed.
Flight Director (FD) - Two flight directors, each operating independently within their respective GIA and
referred to as pilot-side and copilot-side. Commands for the selected flight director are displayed on both
PFDs.
The flight director provides:
 Command Bars showing pitch/roll guidance
 Vertical/lateral mode selection and processing
 Autopilot communication
Yaw Damper (YD) — The yaw servo is self-monitoring and provides Dutch Roll damping and turn
coordination in response to yaw rate, roll angle, vertical acceleration, and airspeed.
Rudder Boost — The GFC 700 incorporates the rudder boost capabilities. The rudder boost is enabled
by setting the pedestal mounted control switch, placarded RUDDER BOOST – OFF, to the RUDDER
BOOST position. The system senses engine torque from both engines. When the difference in these
torques exceeds a preset level, the yaw servo is activated and deflects the rudder to assist pilot effort in
maintaining directional control. The servo contribution is proportional to the engine torque differential.
Trimming of the rudder must be accomplished by the pilot. The rudder boost system is disabled if the
RUDDER BOOST switch is OFF and is interrupted when the AP/YD DISC/TRIM INTRPT button is
pressed.
The amber caution annunciator, [RUD BOOST OFF], is retained from the original caution/advisory/status
annunciator panel to indicate that the rudder boost system is unavailable due to the rudder boost control
switch being in the OFF position, the AP/YD DISC/TRIM INTRPT has been pressed on either yoke, or if a
fault in the rudder boost system has rendered it inoperative.
Electric Pitch Trim — The pitch trim servo provides manual electric pitch trim capability when the autopilot
is not engaged.
Pilot commands to the AFCS are entered through the GMC 710 Autopilot Mode Controller mounted in the
center of the cockpit under the airplane’s glareshield. The GMC 710 controller also controls the heading
bug, navigation course selector on each PFD, and the altitude preselect.
Other components of the autopilot include four servos that also contain autopilot processor, control
wheel-mounted elevator trim switches (copilot’s side optional), control wheel-mounted autopilot/yaw
damper disconnect and trim interrupt switch (AP/YD DISC/TRIM INTRPT), control wheel-mounted CWS
(Control Wheel Steering) switch, and a Go-Around switch mounted in the left power lever knob.