A method for detecting damage to a rotor of an aircraft, wherein the aircraft comprises actuators for active vibration reduction, the method comprising the following steps: determining actuator manipulated variables in a reference flight operation of the aircraft, wherein the determined actuator manipulated variables are used in the reference flight operation of the aircraft for active vibration reduction by means of the actuators; plotting the determined actuator manipulated variables of respective data area tiles (D1, D1-...) in the reference flight operation of the aircraft on first coordinates of a coordinate system, wherein the coordinate system comprises a plurality of closed and non-overlapping data area tiles, wherein, furthermore, the coordinates are assigned to respective data area tiles (D1, D1-...), wherein a plurality of coordinates is representable within one data area tile; detecting a number of the actuator manipulated variables in the reference flight operation of the aircraft, which are arranged in each data area tile (D1, D1-...); eliminating the data area tiles comprising a number of actuator manipulated variables in the reference flight operation of the aircraft which is below a threshold provided for this purpose, whereupon a reference flight signature is generated; determining actuator manipulated variables for a flight-specific signature, wherein the determined actuator manipulated variables are used in the flight operation of the aircraft to reduce vibration by means of the actuators; plotting the determined actuator manipulated variables in the flight operation of the aircraft on second coordinates of the coordinate system, wherein the coordinate system comprises a plurality of data area tiles (D1, D1-...), wherein, furthermore, the coordinates are assigned to respective data area tiles (D1, D1-...), wherein a plurality of coordinates is representable within one data area tile (D1, D1-...), and wherein the data area tiles (D1, D1-...) of the flight-specific signature and the data area tiles (D1, D1-...) of the reference flight signature are embodied identically; detecting the number of the actuator manipulated variables in the flight operation of the aircraft, which are arranged in each data area tile (D1, D1-...); eliminating the data area tiles (D1, D1-...) comprising a number of actuator manipulated variables in the flight operation of the aircraft, which is below a threshold provided for this purpose, whereby the flight-specific signature is generated; comparing the respective data area tiles (D1, D1-... D1-...) of the flight-specific signature and the reference flight signature, wherein a warning signal for a detection of damage is issued if a threshold for the number of divergent data area tiles (D1, D1-... D1-...) between the flight-specific signature and the reference flight signature is exceeded. determining actuator manipulated variables in a reference flight operation of the aircraft, wherein the determined actuator manipulated variables are used in the reference flight operation of the aircraft for active vibration reduction by means of the actuators; plotting the determined actuator manipulated variables of respective data area tiles (D1, D1-...) in the reference flight operation of the aircraft on first coordinates of a coordinate system, wherein the coordinate system comprises a plurality of closed and non-overlapping data area tiles, wherein, furthermore, the coordinates are assigned to respective data area tiles (D1, D1-...), wherein a plurality of coordinates is representable within one data area tile; detecting a number of the actuator manipulated variables in the reference flight operation of the aircraft, which are arranged in each data area tile (D1, D1-...); eliminating the data area tiles comprising a number of actuator manipulated variables in the reference flight operation of the aircraft which is below a threshold provided for this purpose, whereupon a reference flight signature is generated; determining actuator manipulated variables for a flight-specific signature, wherein the determined actuator manipulated variables are used in the flight operation of the aircraft to reduce vibration by means of the actuators; plotting the determined actuator manipulated variables in the flight operation of the aircraft on second coordinates of the coordinate system, wherein the coordinate system comprises a plurality of data area tiles (D1, D1-...), wherein, furthermore, the coordinates are assigned to respective data area tiles (D1, D1-...), wherein a plurality of coordinates is representable within one data area tile (D1, D1-...), and wherein the data area tiles (D1, D1-...) of the flight-specific signature and the data area tiles (D1, D1-...) of the reference flight signature are embodied identically; detecting the number of the actuator manipulated variables in the flight operation of the aircraft, which are arranged in each data area tile (D1, D1-...); eliminating the data area tiles (D1, D1-...) comprising a number of actuator manipulated variables in the flight operation of the aircraft, which is below a threshold provided for this purpose, whereby the flight-specific signature is generated; comparing the respective data area tiles (D1, D1-... D1-...) of the flight-specific signature and the reference flight signature, wherein a warning signal for a detection of damage is issued if a threshold for the number of divergent data area tiles (D1, D1-... D1-...) between the flight-specific signature and the reference flight signature is exceeded.