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.

Abstract: A connector assembly mounted on a printed wiring board allowing modifications to be made to the connectivity using simple wiring techniques. The connector assembly contains special contacts providing three connections. One end of the contact mates with the source or destination of the signals in a modular electronic device. The other end accepts a wired contact for making additional connections not contained in the printed wiring board. The middle section of the contact makes a compliant connection to the printed wiring board. A signal can be disconnected from the printed wiring board by removing the contact and replacing it with a contact that is insulated from the printed wiring board.