A flight control system for an aircraft, the flight control system comprising: one or more computer processors; a plurality of pitot tubes in communication with the one or more computer processors, wherein the plurality of pitot tubes are configured to measure a total pressure; static ports configured to measure a static pressure; and a memory coupled to the one or more computer processors, the memory storing data comprising a database and program code that, when executed by the one or more computer processors, causes the flight control system to: receive as an input a measured dynamic pressure (Q bar(m)) and an estimated angle of attack (α est), wherein the measured dynamic pressure is based on the total pressure and the static pressure, and wherein the estimated angle of attack is based on the total pressure; determine a rate of change of the measured dynamic pressure (Q̇ bar(m)); compare the rate of change of the measured dynamic pressure (Q̇ bar(m)) with a dynamic pressure threshold value, wherein the dynamic pressure threshold value is representative of the rate of change of the measured dynamic pressure (Q̇ bar(m)) when a majority of the plurality of pitot tubes experience a failure; determine a rate of change of the estimated angle of attack (α̇ est); compare the rate of change of the estimated angle of attack (α̇ est) with an estimated angle of attack threshold value, wherein the estimated angle of attack threshold value is representative of the rate of change of the estimated angle of attack (α̇ est) when a majority of the plurality of pitot tubes experience a failure; and in response to determining that the rate of change of the measured dynamic pressure (Q̇ bar(m)) is less than the dynamic pressure threshold value and the rate of change of the estimated angle of attack (α̇ est) is greater than the estimated angle of attack threshold value, determine that a first common mode pneumatic event has occurred. one or more computer processors; a plurality of pitot tubes in communication with the one or more computer processors, wherein the plurality of pitot tubes are configured to measure a total pressure; static ports configured to measure a static pressure; and a memory coupled to the one or more computer processors, the memory storing data comprising a database and program code that, when executed by the one or more computer processors, causes the flight control system to: receive as an input a measured dynamic pressure (Q bar(m)) and an estimated angle of attack (α est), wherein the measured dynamic pressure is based on the total pressure and the static pressure, and wherein the estimated angle of attack is based on the total pressure; determine a rate of change of the measured dynamic pressure (Q̇ bar(m)); compare the rate of change of the measured dynamic pressure (Q̇ bar(m)) with a dynamic pressure threshold value, wherein the dynamic pressure threshold value is representative of the rate of change of the measured dynamic pressure (Q̇ bar(m)) when a majority of the plurality of pitot tubes experience a failure; determine a rate of change of the estimated angle of attack (α̇ est); compare the rate of change of the estimated angle of attack (α̇ est) with an estimated angle of attack threshold value, wherein the estimated angle of attack threshold value is representative of the rate of change of the estimated angle of attack (α̇ est) when a majority of the plurality of pitot tubes experience a failure; and in response to determining that the rate of change of the measured dynamic pressure (Q̇ bar(m)) is less than the dynamic pressure threshold value and the rate of change of the estimated angle of attack (α̇ est) is greater than the estimated angle of attack threshold value, determine that a first common mode pneumatic event has occurred. receive as an input a measured dynamic pressure (Q bar(m)) and an estimated angle of attack (α est), wherein the measured dynamic pressure is based on the total pressure and the static pressure, and wherein the estimated angle of attack is based on the total pressure; determine a rate of change of the measured dynamic pressure (Q̇ bar(m)); compare the rate of change of the measured dynamic pressure (Q̇ bar(m)) with a dynamic pressure threshold value, wherein the dynamic pressure threshold value is representative of the rate of change of the measured dynamic pressure (Q̇ bar(m)) when a majority of the plurality of pitot tubes experience a failure; determine a rate of change of the estimated angle of attack (α̇ est); compare the rate of change of the estimated angle of attack (α̇ est) with an estimated angle of attack threshold value, wherein the estimated angle of attack threshold value is representative of the rate of change of the estimated angle of attack (α̇ est) when a majority of the plurality of pitot tubes experience a failure; and in response to determining that the rate of change of the measured dynamic pressure (Q̇ bar(m)) is less than the dynamic pressure threshold value and the rate of change of the estimated angle of attack (α̇ est) is greater than the estimated angle of attack threshold value, determine that a first common mode pneumatic event has occurred.