A rotary aircraft (101;201), comprising: a rotor system comprising a rotor blade; a nacelle; and a flight control system, having: a first sensor associated with the nacelle, the first sensor being configured to detect an angle of the nacelle; a second sensor associated with the rotary aircraft, the second sensor being configured to detect a first flight parameter of the rotary aircraft; a third sensor associated with the rotor blade (107;205), the third sensor being configured to detect a lateral flapping movement and a longitudinal flapping movement of the rotor blade; a collective pitch parameter; and a subsystem associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the subsystem having: a first loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the first loop being configured to determine a lower longitudinal cyclic limit created by the rotor blade (107;205) during flight; and a second loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the second loop being configured to determine an upper longitudinal cyclic limit created by the rotor blade during flight. a rotor system comprising a rotor blade; a nacelle; and a flight control system, having: a first sensor associated with the nacelle, the first sensor being configured to detect an angle of the nacelle; a second sensor associated with the rotary aircraft, the second sensor being configured to detect a first flight parameter of the rotary aircraft; a third sensor associated with the rotor blade (107;205), the third sensor being configured to detect a lateral flapping movement and a longitudinal flapping movement of the rotor blade; a collective pitch parameter; and a subsystem associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the subsystem having: a first loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the first loop being configured to determine a lower longitudinal cyclic limit created by the rotor blade (107;205) during flight; and a second loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the second loop being configured to determine an upper longitudinal cyclic limit created by the rotor blade during flight. a first sensor associated with the nacelle, the first sensor being configured to detect an angle of the nacelle; a second sensor associated with the rotary aircraft, the second sensor being configured to detect a first flight parameter of the rotary aircraft; a third sensor associated with the rotor blade (107;205), the third sensor being configured to detect a lateral flapping movement and a longitudinal flapping movement of the rotor blade; a collective pitch parameter; and a subsystem associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the subsystem having: a first loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the first loop being configured to determine a lower longitudinal cyclic limit created by the rotor blade (107;205) during flight; and a second loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the second loop being configured to determine an upper longitudinal cyclic limit created by the rotor blade during flight. a first loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the first loop being configured to determine a lower longitudinal cyclic limit created by the rotor blade (107;205) during flight; and a second loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the second loop being configured to determine an upper longitudinal cyclic limit created by the rotor blade during flight.