Fuel actuated bleed air system

A gas turbine engine bleed air system includes one or more fuel-actuated bleed air supply valves (114-2,114-3,142) and, in some cases, a pneumatically actuated overpressure valve (116). Each fuel-actuated bleed air supply valve is mounted on a bleed air supply conduit (104) and is coupled to a source of pressurized aircraft fuel (130). Each fuel-actuated bleed air supply valve is responsive to the pressurized aircraft fuel to move to a plurality of valve positions and to regulate compressed air pressure in the bleed air supply conduit, downstream of the fuel-actuated bleed air supply valve. The pneumatically actuated overpressure valve (116) is mounted on the bleed air conduit (104) downstream of each of the fuel-actuated bleed air valves and pneumatically regulates or shuts off pressure independent of fuel pressure or electrical signals.