are the body bending vibrations and body twisting torsional modes the present invention is an active system for suppressing the body bending modes and the torsional modes 0054 fig1 depicts the sensors required to feed into the control law algorithm of the preferred embodiment of the multi axis modal suppression system as shown in fig2 a 2 b amp 2 c the feedback sensors include an inertial reference unit 60 a hereinafter iru located at the electronics equipment hereinafter ee bay 52 at the front belly of the aircraft 50 along with the iru 60 a an air data computer 60 b hereinafter adc is also required a pitch rate gyro 61 located in the vicinity of the wing box front spar 50 c is also used in the present invention finally dedicated forward accelerometers 62 a and aft galley accelerometers 62 b at the forward 50 a and aft 50 b airplane body locations respectively are also deployed in general the wing box front spar pitch rate gyro 61 and the iru sensors 60 a together provide the attitude and acceleration signals for the rigid body mode stability augmentation the adc 60 b provides the speed and or dynamic pressure for control law gain scheduling such that proper amount of surface deflection can be applied at different speed dynamic pressure conditions even though similar vibration levels are sensed for modal suppression the dedicated accelerometers 62 a 62 b and the iru rate gyro and accelerometer sensors usually provide the necessary structural mode contents it is understood that the location of the ee bay 52 has been a matter of historical convention wherein all electronics were situated in the vicinity of the flight deck.