The Boeing Company
POWER SYSTEM CONTROLLER FAILSAFE CYCLING PROTECTION

Abstract:

Examples provide a method and system for inhibiting aircraft electrical power system controller failsafe state cycling in air mode condition. The electrical power system controller can include a bus power control unit (BPCU) or a generator control unit (GCU). A failsafe cycling protection indicator, such as a software flag or hardware electronic latch has a first configuration to indicate failsafe cycling protection is enabled and a second configuration to indicate failsafe cycling protection is disabled. An internal low voltage power source generates an output voltage. If a monitor component monitoring the output voltage detects an undervoltage or overvoltage, the aircraft electrical power system controller goes into a failsafe state. A failsafe cycling component prevents the aircraft electrical power system controller from exiting the failsafe state if the failsafe cycling protection is enabled.