An apparatus for detecting an inflight icing condition on an aircraft, the apparatus comprising: a processor unit including a processor and a computer-readable storage medium coupled to the processor and having computer-readable program code stored therein that, in response to execution by the processor, causes the apparatus to perform a number of operations in real-time during flight of the aircraft, including the apparatus being caused to at least: monitor a continuous electrical signal output by a sensor on a surface of the aircraft, a magnitude of the electrical signal being related to an amount of ice buildup on the sensor, wherein the sensor comprises an ice accretion sensor including a magnetostrictive probe whose vibrational frequency is measurable in terms of a continuous electrical voltage signal output by the ice accretion sensor, and wherein the apparatus being caused to monitor the continuous electrical signal includes being caused to monitor the continuous electrical voltage signal output by the ice accretion sensor, wherein the internal circuitry of the sensor is configured to: - continue to monitor the probe's vibrational frequency until it reaches a frequency threshold that indicates a certain thickness of ice to indicate an icing condition; and - at that time turn on a heater of the sensor to deice the sensor's probe; wherein the processor unit is configured to: - calculate a liquid water content "LWC" value as a function of a rate of change of the electrical signal; - maintain the LWC at its most recent value while the heater is on; - iteratively calculate a total water exposure "TWE" value as a function of the LWC value, the TWE value representing a total water exposure of the aircraft from a time of an initial event, and being calculated as a running total over a plurality of iterations as follows: TWE i = TWE i − 1 + TAS ∗ LWC i ∗ K 2 ∗ iRate wherein TWE i - 1 represents the calculated TWE at a prior iteration i - 1, K 2 represents a unit conversion, iRate represents an iteration rate for the TWE calculation, TAS represents the true air speed of the aircraft, and LWC i represents the liquid water content at iteration i; and - perform a remedial or alert action in an instance in which the TWE value reaches a TWE threshold. monitor a continuous electrical signal output by a sensor on a surface of the aircraft, a magnitude of the electrical signal being related to an amount of ice buildup on the sensor, wherein the sensor comprises an ice accretion sensor including a magnetostrictive probe whose vibrational frequency is measurable in terms of a continuous electrical voltage signal output by the ice accretion sensor, and wherein the apparatus being caused to monitor the continuous electrical signal includes being caused to monitor the continuous electrical voltage signal output by the ice accretion sensor, wherein the internal circuitry of the sensor is configured to: - continue to monitor the probe's vibrational frequency until it reaches a frequency threshold that indicates a certain thickness of ice to indicate an icing condition; and - at that time turn on a heater of the sensor to deice the sensor's probe; - continue to monitor the probe's vibrational frequency until it reaches a frequency threshold that indicates a certain thickness of ice to indicate an icing condition; and - at that time turn on a heater of the sensor to deice the sensor's probe; wherein the processor unit is configured to: - calculate a liquid water content "LWC" value as a function of a rate of change of the electrical signal; - maintain the LWC at its most recent value while the heater is on; - iteratively calculate a total water exposure "TWE" value as a function of the LWC value, the TWE value representing a total water exposure of the aircraft from a time of an initial event, and being calculated as a running total over a plurality of iterations as follows: TWE i = TWE i − 1 + TAS ∗ LWC i ∗ K 2 ∗ iRate wherein TWE i - 1 represents the calculated TWE at a prior iteration i - 1, K 2 represents a unit conversion, iRate represents an iteration rate for the TWE calculation, TAS represents the true air speed of the aircraft, and LWC i represents the liquid water content at iteration i; and - perform a remedial or alert action in an instance in which the TWE value reaches a TWE threshold. - calculate a liquid water content "LWC" value as a function of a rate of change of the electrical signal; - maintain the LWC at its most recent value while the heater is on; - iteratively calculate a total water exposure "TWE" value as a function of the LWC value, the TWE value representing a total water exposure of the aircraft from a time of an initial event, and being calculated as a running total over a plurality of iterations as follows: TWE i = TWE i − 1 + TAS ∗ LWC i ∗ K 2 ∗ iRate wherein TWE i - 1 represents the calculated TWE at a prior iteration i - 1, K 2 represents a unit conversion, iRate represents an iteration rate for the TWE calculation, TAS represents the true air speed of the aircraft, and LWC i represents the liquid water content at iteration i; and - perform a remedial or alert action in an instance in which the TWE value reaches a TWE threshold.