Abstract: In an individual rotor blade control device for a helicopter main rotor with a rotor shaft that can be driven by a main drive, with an even number of rotor blades that are arranged on the periphery of a rotor hub, with primary control mechanisms for collective and sinusoidal, cyclic rotor blade adjustment, which include a transfer element for the control movements from a non-rotating system to a rotating system and with actuators that are individually allocated to the rotor blades, wherein the actuator control movement is superimposed onto the control movement of the primary control mechanisms and each actuator is equipped with a safety device in order to bring the actuator into its final position and keep it there, if necessary, it is suggested that the setting angle change of one half of the rotor blades have an opposed direction due to the securing of the actuators in their final positions, like the setting angle change of the other half of rotor blades, and that the rotor blades of each half be distribute