MAIN CHARACTERISTICS:
- The aircraft uses conventional flight controls with trim and autopilot on all three axes.
- Dual yokes provide aileron and elevator control, and rudder pedals control rudder, brakes, and nose-wheel steering.
- Flaps have three selectable positions: UP, TAKEOFF/APPROACH, and LAND, and their position is shown on the MFD.
- Speed brakes are electrically actuated and available at any speed, with switches located on the throttle handles.
- Pitch, roll, and yaw trim are electrically operated, with a manual elevator trim wheel on the pedestal.
- Trim positions are displayed on the MFD for aileron and rudder, and mechanically for elevator.
- Aileron-Rudder Interconnect: Flexible mechanical interconnect between the rudder and ailerons provides improved lateral stability. When pilot rolls aircraft, interconnect causes some rudder deflection to the same side (and resultant airplane yawing into better-coordinated flight).
- Three autopilot servos (pitch, roll, and yaw) provide full-axis control.
- The yaw servo also supplies Dutch-roll damping and turn coordination when the autopilot is disengaged.
CONTROL YOKE SWITCHES
- Each control yoke contains three switches that manage key AFCS functions, including disengaging the autopilot and restoring manual control to the crew.
- DOWN–UP trim switches: When operated to adjust pitch, trim also disengages the AP.
- AP TRIM DISC switch: Immediately disconnects both the AP and the YD.
- The CWS (Control Wheel Steering) switch: temporarily disengages the autopilot and aligns the flight director command bars with the aircraft’s current pitch (when not in glide slope or vertical navigation mode) and current roll (when in roll hold mode). A CWS button is installed on each control wheel. When released, the flight director may establish new reference points based on the active vertical and lateral modes.
