A method comprising, by a flight control computer: receiving a time series of control inputs in relation to a control axis of an aircraft, wherein the flight control computer comprises a filter system and control logic arranged to transform control outputs of the filter system into a control signal sent to an actuator to cause actuation in response to each control input in the time series as the control input is received to control motion of a controllable element in the aircraft; determining aircraft oscillation over a sample period corresponding to the time series; evaluating information related to the determined aircraft oscillation using engagement settings associated with a control filter in the filter system; and engaging the control filter responsive to the information satisfying the engagement settings, wherein the engaged control filter systematically attenuates future control inputs in relation to the control axis prior to the control logic sending a control signal to cause actuation responsive thereto; characterized by the method further comprising: receiving a subsequent time series of control inputs in relation to the control axis of the aircraft; determining aircraft oscillation over a subsequent sample period corresponding to the subsequent time series; evaluating information related to the determined aircraft oscillation over the subsequent sample period using escalation settings, wherein the escalation settings specify an arrangement of control filters (314 -314(n)) in an ascending order of criticality, and wherein the arrangement comprises the control filter; responsive to a determination that the information related to the determined aircraft oscillation over the subsequent period satisfies specified criteria for escalated signal attenuation: disengaging the control filter; and engaging a next control filter in the arrangement according to the ascending order of criticality. receiving a time series of control inputs in relation to a control axis of an aircraft, wherein the flight control computer comprises a filter system and control logic arranged to transform control outputs of the filter system into a control signal sent to an actuator to cause actuation in response to each control input in the time series as the control input is received to control motion of a controllable element in the aircraft; determining aircraft oscillation over a sample period corresponding to the time series; evaluating information related to the determined aircraft oscillation using engagement settings associated with a control filter in the filter system; and engaging the control filter responsive to the information satisfying the engagement settings, wherein the engaged control filter systematically attenuates future control inputs in relation to the control axis prior to the control logic sending a control signal to cause actuation responsive thereto; characterized by the method further comprising: receiving a subsequent time series of control inputs in relation to the control axis of the aircraft; determining aircraft oscillation over a subsequent sample period corresponding to the subsequent time series; evaluating information related to the determined aircraft oscillation over the subsequent sample period using escalation settings, wherein the escalation settings specify an arrangement of control filters (314 -314(n)) in an ascending order of criticality, and wherein the arrangement comprises the control filter; responsive to a determination that the information related to the determined aircraft oscillation over the subsequent period satisfies specified criteria for escalated signal attenuation: disengaging the control filter; and engaging a next control filter in the arrangement according to the ascending order of criticality. receiving a subsequent time series of control inputs in relation to the control axis of the aircraft; determining aircraft oscillation over a subsequent sample period corresponding to the subsequent time series; evaluating information related to the determined aircraft oscillation over the subsequent sample period using escalation settings, wherein the escalation settings specify an arrangement of control filters (314 -314(n)) in an ascending order of criticality, and wherein the arrangement comprises the control filter; responsive to a determination that the information related to the determined aircraft oscillation over the subsequent period satisfies specified criteria for escalated signal attenuation: disengaging the control filter; and engaging a next control filter in the arrangement according to the ascending order of criticality. disengaging the control filter; and engaging a next control filter in the arrangement according to the ascending order of criticality.