Pulling the fire handle?
Did a search , but didn't find anything that thoroughly answered my question. When pulling the fire handle, you isolate fuel, bleed air, hydraulic, electric. But where does the physical dis-connection actually occur? My understanding so far:
1. Electrical - GCB and GCR
2. Bleed air - Bleed air control valve
3. Fuel - Fuel spar valve. I thought I read somewhere that certain designs also pull a valve in the HMU. Would this be the same HP SOV as is controlled by the fuel lever in cockpit for normal start/stop?
4. Hydraulic - this one got me. In case of an Engine Driven Pump, would it be physical disconnection from the gearbox?
I don't fly anything bigger than a MEP!
Thanks in advance