majuro15
Well Known Member
I'm working through my electrical design and contemplating failure modes analysis. My question is when using the EFII injection and ignition system, what would an inflight complete power failure look like of the bus manager after an E-buss switch is thrown?
For example, stable flight, primary power distribution device (Bus Manager) fails. Switch the 30A rated switch which would then connect the ECU's/coils/fuel pumps directly to a battery. Will the engine immediately restart? ECU's have to reset? Fuel pump reset? What would the restart procedure be?
I am aware of the functions of the bus manager and triple redundancy, but considering not using the bus manager switch and wiring in an independent switch.
For example, stable flight, primary power distribution device (Bus Manager) fails. Switch the 30A rated switch which would then connect the ECU's/coils/fuel pumps directly to a battery. Will the engine immediately restart? ECU's have to reset? Fuel pump reset? What would the restart procedure be?
I am aware of the functions of the bus manager and triple redundancy, but considering not using the bus manager switch and wiring in an independent switch.