A system for monitoring health of an electrical heater of an air data probe, the system comprising: an electrical power source configured to electrically couple to the electrical heater so as to provide electrical power thereto, the electrical heater having an electrical property that changes in response to a thermal load of the electrical heater, wherein the thermal load of the electrical heater, in turn, depends upon aircraft flight parameters and/or environmental conditions; wherein the electrical property that changes in response to the thermal load of the electrical heater is an electrical resistance of the electrical heater or a leakage current between a resistive heating element and a conductive member of the air data probe; an aircraft interface configured to communicate with an aircraft so as to receive the aircraft flight parameters and/or the environmental conditions therefrom; an electrical-property calculator configured to calculate a thermal load of the electrical heater based on the received aircraft flight parameters and/or the environmental conditions, the electrical-property calculator further configured to calculate an expected value of the electrical property of the electrical heater based on the provided electrical power and further based on the aircraft flight parameters and/or environmental conditions; an electrical measurement circuit configured to electrically couple to the electrical heater so as to measure electrical parameters indicative of the electrical property of the electrical heater; and a health monitor configured to determine health of the electrical heater based on a comparison between the calculated expected value and the electrical property as indicated by the measured electrical parameters. an electrical power source configured to electrically couple to the electrical heater so as to provide electrical power thereto, the electrical heater having an electrical property that changes in response to a thermal load of the electrical heater, wherein the thermal load of the electrical heater, in turn, depends upon aircraft flight parameters and/or environmental conditions; wherein the electrical property that changes in response to the thermal load of the electrical heater is an electrical resistance of the electrical heater or a leakage current between a resistive heating element and a conductive member of the air data probe; an aircraft interface configured to communicate with an aircraft so as to receive the aircraft flight parameters and/or the environmental conditions therefrom; an electrical-property calculator configured to calculate a thermal load of the electrical heater based on the received aircraft flight parameters and/or the environmental conditions, the electrical-property calculator further configured to calculate an expected value of the electrical property of the electrical heater based on the provided electrical power and further based on the aircraft flight parameters and/or environmental conditions; an electrical measurement circuit configured to electrically couple to the electrical heater so as to measure electrical parameters indicative of the electrical property of the electrical heater; and a health monitor configured to determine health of the electrical heater based on a comparison between the calculated expected value and the electrical property as indicated by the measured electrical parameters.