A fault in an auxiliary power unit (APU) (10, Figure 2) of an aircraft (50, Figure 2) may be predicted by receiving a sensor signal from at least one of multiple APU sensors, and preferably also an altitude signal, speed signal or engine performance parameters, defining a sensor output 102 that is compared to a reference value 104. A fault in the auxiliary power unit is predicted based on the comparison 106. Predictions of faults may be displayed to a pilot on a primary flight display. Sensor output may be aggregated over multiple flights and statistically analysed, and pre-flight and post-flight phases may be separately analysed. Faults may be predicted if, for example, post-flight exhaust gas temperature or pre-flight median inlet temperature are above thresholds, if the APU takes longer than expected to start or if a surge control valve is further than expected from a central position post-flight.
Method for predicting an auxiliary power unit fault
2015-04-15
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |