A method comprising: determining, by a controller comprising a processor, that an aircraft is on a landing surface based on a weight-on wheels sensor reading; setting, by the controller, an initial vibration frequency to be applied to an airframe of the aircraft; commanding, by the controller, one or more force generators to apply a vibratory load to the airframe at the initial vibration frequency based on determining that the aircraft is on the landing surface, in a pre-flight or diagnostic mode, wherein the one or more force generators are components of an active vibration control system that is configured to attenuate vibration of the airframe while in flight and to provide a source of vibration excitation for global airframe health characterization while on the landing surface; determining, by the controller, a vibration response of the airframe at the initial vibration frequency using a plurality of sensors; sweeping, by the controller, through a range of vibration frequencies to be applied to the airframe; commanding, by the controller, the one or more force generators to apply a plurality of vibratory loads to the airframe over the range of vibration frequencies; determining, by the controller, a range of vibration responses of the airframe over the range of vibration frequencies using the plurality of sensors; determining, by the controller, a global stiffness of the airframe based on the vibration response and the range of vibration responses; comparing the global stiffness of the airframe to a threshold value; determining a level of damage to the airframe based on a difference between the global stiffness and the threshold value; and reporting, by the controller, results of determining the global stiffness of the airframe. determining, by a controller comprising a processor, that an aircraft is on a landing surface based on a weight-on wheels sensor reading; setting, by the controller, an initial vibration frequency to be applied to an airframe of the aircraft; commanding, by the controller, one or more force generators to apply a vibratory load to the airframe at the initial vibration frequency based on determining that the aircraft is on the landing surface, in a pre-flight or diagnostic mode, wherein the one or more force generators are components of an active vibration control system that is configured to attenuate vibration of the airframe while in flight and to provide a source of vibration excitation for global airframe health characterization while on the landing surface; determining, by the controller, a vibration response of the airframe at the initial vibration frequency using a plurality of sensors; sweeping, by the controller, through a range of vibration frequencies to be applied to the airframe; commanding, by the controller, the one or more force generators to apply a plurality of vibratory loads to the airframe over the range of vibration frequencies; determining, by the controller, a range of vibration responses of the airframe over the range of vibration frequencies using the plurality of sensors; determining, by the controller, a global stiffness of the airframe based on the vibration response and the range of vibration responses; comparing the global stiffness of the airframe to a threshold value; determining a level of damage to the airframe based on a difference between the global stiffness and the threshold value; and reporting, by the controller, results of determining the global stiffness of the airframe.