The flight control system gives control of roll, yaw, and pitch to the pilot or copilot.

The primary flight controls are the ailerons, rudder, and elevator. The flight deck controls are arranged conventionally with a control wheel, rudder pedals, and control column for both pilots. The ailerons are mechanically (cable) operated. The rudder and elevator systems have cable activated power control units (PCUs) that hydraulically move the control surfaces. Manual reversion capability during dual hydraulic system failure is provided. Mechanical inputs from the autopilot system can also operate the system in flight.

The Stall Protection System (SPS) provides the flight crew with aural, visual, and tactile (stick shaker and stick pusher) indications of an impending stall.

A gust lock system, which operates manually through a lever on the center pedestal, protects the ailerons against ground wind. The rudder and elevator systems PCUs protect the rudder and elevator against ground wind.

The secondary flight controls are the flaps, the spoilers, and a horizontal stabilizer which can change its angle of attack. The flaps and spoilers are electrically controlled and hydraulically energized. The horizontal stabilizer is electrically controlled and mechanically operated.

Aircraft trim systems (pitch, roll and yaw) are electrically controlled and operated.