Method for diagnosing an auxiliary power unit fault
A method of diagnosing an auxiliary power unit fault in an aircraft having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, including receiving a sensor signal from at least one of the multiple sensors to define a sensor output, comparing the sensor output to a reference value and diagnosing a fault in the auxiliary power unit based on the comparison.
1. A method of diagnosing an auxiliary power unit fault in an aircraft having an auxiliary power unit (APU) and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, the method comprising:
receiving, during at least one of pre-flight or post-flight, a sensor signal from at least one of the multiple sensors to define a sensor output;
comparing, by a controller, the sensor output to a reference value for the sensor output;
diagnosing, by a controller, a fault associated with the auxiliary power unit based on the comparison between the sensor output and the reference value; and
providing, by a controller, an indication of the diagnosed fault.
2. The method of claim 1 , further comprising receiving at least one of an altitude signal, a speed signal, and performance parameters outputted by an engine of the aircraft.
3. The method of claim 2 , further comprising determining when the aircraft is in pre-flight or post-flight.
4. The method of claim 2 , wherein the received sensor signal comprises sensor signals for a number of flights.
5. The method of claim 2 , wherein the diagnosing the fault comprises diagnosing the fault when the comparing indicates thresholds are satisfied over multiple flights.
6. The method of claim 1 , further comprising determining when the aircraft is in pre-flight or post-flight.
7. The method of claim 1 , wherein the received sensor signal comprises sensor signals for a number of flights.
8. The method of claim 1 , wherein the diagnosing the fault comprises diagnosing the fault when the comparing indicates thresholds are satisfied over multiple flights.
9. The method of claim 1 , wherein the diagnosing the fault comprises diagnosing the fault with a temperature sensor when the comparing indicates a threshold related to the sensor signal is satisfied over multiple flights.
10. The method of claim 1 , further comprising determining from the sensor output a time taken for the APU to start and wherein the determined time is compared to the reference value.
11. The method of claim 10 , wherein the diagnosing the fault is based on multiple comparisons.
12. The method of claim 11 , wherein the diagnosing the fault comprises diagnosing the fault with a starter motor when the comparing indicates that the time taken for the APU to start up satisfies a threshold and an exhaust gas temperature is greater than the reference value.
13. The method of claim 11 , wherein the diagnosing the fault comprises diagnosing the fault with a generator of the APU when: 1) the comparing indicates that the time taken for the APU to start up satisfies a threshold, 2) the comparing indicates that an exhaust gas temperature is greater than the reference value, and 3) the comparing indicates that the load compressor flow satisfies a threshold.
14. The method of claim 1 , wherein the received sensor output is aggregated over time to define aggregated sensor data, and the comparison comprises comparing the aggregated sensor data to the reference value.
15. The method of claim 14 , wherein the aggregating the received sensor output over time comprises aggregating the received sensor output over multiple flights.
16. The method of claim 14 , wherein the aggregated sensor data comprises at least one of a median value, a running median value, or a historical median value.
17. The method of claim 1 , wherein the providing the indication comprises providing the indication on a PFD in a cockpit of the aircraft.
18. The method of claim 12 , wherein the diagnosing the fault comprises diagnosing the fault with a generator of the APU when: 1) the comparing indicates that the time taken for the APU to start up satisfies a threshold, 2) the comparing indicates that an exhaust gas temperature is greater than the reference value, and 3) the comparing indicates that the load compressor flow satisfies a threshold.
19. The method of claim 15 , wherein the aggregated sensor data comprises at least one of a median value, a running median value, or a historical median value.
20. A method of diagnosing an auxiliary power unit fault in an aircraft having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, the method comprising:
receiving, during at least one of pre-flight or post-flight, a sensor signal from at least one of the multiple sensors to define a sensor output;
comparing, by a controller, the sensor output to a reference value for the sensor output;
diagnosing, by a controller, a fault associated with the auxiliary power unit based on the comparison; and
providing, by a controller, an indication of the diagnosed fault;
wherein the received sensor signal comprises sensor signals for a number of flights.