An aircraft flight control system includes a first actuator attached to a wing main body, a horn arm configured to transmit an output of the first actuator to a control surface, and a second actuator that is a rotary actuator and attached to the control surface. At least one of the first actuator and the second actuator is an electromechanical actuator (EMA). A first end of the horn arm is coupled to an output terminal of the first actuator, and a second end of the horn arm is fixed to an output terminal of the second actuator. The second actuator is attached to the control surface such that a turning axis of the output terminal is parallel to or coincides with a fulcrum axis (hinge line) of the control surface.