A system comprising: an air data sensing probe having a probe head portion and a strut portion that extends between the probe head portion and a mounting plate, each of the probe head portion and the strut portion configured to be exposed to airflow about an exterior of an aircraft, the air data sensing probe including a first self-compensating heater disposed in the probe head portion and a second self compensating heater disposed in the strut portion; a first current monitor configured to produce a first measurement value representing electrical current flow through the first self-compensating heater; a second current monitor configured to produce a second measurement value representing electrical current flow through the second self-compensating heater; one or more processors; and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to: receive aircraft flight condition data; determine one or more parameters of expected electrical current flow through the first self-compensating heater based on the received aircraft flight condition data; determine whether the first measurement value exceeds a first threshold deviation from the one or more parameters of expected electrical current flow; determine whether the first measurement value exceeds a second threshold deviation from the second measurement value; and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data responsive to determining that the first measurement value exceeds the first threshold deviation from the one or more parameters of expected electrical current flow; produce the icing condition signal to include an indication of a liquid water icing condition in response to determining that the first measurement value does not exceed the second threshold deviation from the second measurement value; and produce the icing condition signal to include an indication of a solid water icing condition in response to determining that the first measurement value exceeds the second threshold deviation from the second measurement value. an air data sensing probe having a probe head portion and a strut portion that extends between the probe head portion and a mounting plate, each of the probe head portion and the strut portion configured to be exposed to airflow about an exterior of an aircraft, the air data sensing probe including a first self-compensating heater disposed in the probe head portion and a second self compensating heater disposed in the strut portion; a first current monitor configured to produce a first measurement value representing electrical current flow through the first self-compensating heater; a second current monitor configured to produce a second measurement value representing electrical current flow through the second self-compensating heater; one or more processors; and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to: receive aircraft flight condition data; determine one or more parameters of expected electrical current flow through the first self-compensating heater based on the received aircraft flight condition data; determine whether the first measurement value exceeds a first threshold deviation from the one or more parameters of expected electrical current flow; determine whether the first measurement value exceeds a second threshold deviation from the second measurement value; and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data responsive to determining that the first measurement value exceeds the first threshold deviation from the one or more parameters of expected electrical current flow; produce the icing condition signal to include an indication of a liquid water icing condition in response to determining that the first measurement value does not exceed the second threshold deviation from the second measurement value; and produce the icing condition signal to include an indication of a solid water icing condition in response to determining that the first measurement value exceeds the second threshold deviation from the second measurement value. receive aircraft flight condition data; determine one or more parameters of expected electrical current flow through the first self-compensating heater based on the received aircraft flight condition data; determine whether the first measurement value exceeds a first threshold deviation from the one or more parameters of expected electrical current flow; determine whether the first measurement value exceeds a second threshold deviation from the second measurement value; and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data responsive to determining that the first measurement value exceeds the first threshold deviation from the one or more parameters of expected electrical current flow; produce the icing condition signal to include an indication of a liquid water icing condition in response to determining that the first measurement value does not exceed the second threshold deviation from the second measurement value; and produce the icing condition signal to include an indication of a solid water icing condition in response to determining that the first measurement value exceeds the second threshold deviation from the second measurement value.