The elevator control system supplies the input for the pitch control of the aircraft. Control column movement is transmitted to the elevator power-control units (PCUs). The PCUs then move the elevator to the correct position. The elevator position transducers supply data on the elevator position to the engine indication and crew alerting system (EICAS).

The left and right elevators surfaces are connected together in the normal condition. In the case of a jam in the left or right elevator control circuit, the control circuits disconnect automatically. Pitch control of the aircraft is possible with only one of the two control circuits in operation.

A stall protection system supplies warnings when the aircraft is near a stall condition. It also makes sure that the aircraft does not go into an angle-of-attack (AOA) where a stall can occur. For fail-safe operation, the system has two identical subsystems.

If the aircraft goes near the stall condition, the stick shaker starts to shake. The vibration continues until the angle-of-attack of the aircraft decreases. If the angle-of-attack does not decrease, the stall protection system operates the stick pusher actuator. The stick pusher actuator automatically moves the control columns forward to decrease the angle-of-attack of the aircraft.

The pitch feel system supplies an artificial feel force at the control columns to help the pilots control the aircraft. The feel force varies with changes in calibrated airspeed, horizontal stabilizer position. Also when the normalized AOA exceeds a specific threshold which is dependent on the flap position, there is an increase in the feel force.