A fuel control system for an aircraft comprising: a first electric motor controlled fuel pump having an outlet operatively connected to output pressurized fuel to a fuel line, and an inlet configured to receive fuel supplied from an aircraft fuel tank; a second electric motor controlled fuel pump having an outlet operatively connected to output pressurized fuel to the fuel line, and an inlet configured to receive fuel supplied from the aircraft fuel tank, wherein the first and second electric motor controlled fuel pumps connect in parallel with one another to the fuel line; a plurality of fuel nozzles connected to the fuel line to issue pressurized fuel from the fuel line, wherein at least one fuel nozzle in the plurality of fuel nozzles includes a respective sensor system; and a fuel controller operatively connected to receive input from the respective sensor system of the at least one fuel nozzle, and operatively connected to control the first and second electric motor controlled pumps based on input from the respective sensor system of the at least one fuel nozzle; wherein each of the fuel nozzles in the plurality of fuel nozzles includes internal valving operatively connected to the controller so the controller can control fuel flow through the plurality of fuel nozzles by throttling the plurality of fuel nozzles and by controlling the first and second electric motor controlled pumps (104, 110); wherein the controller is operatively connected to receive input from an engine controller, and is configured to control the first and second electric motor controlled pumps (104, 110) based on input from the respective sensor system of the at least one fuel nozzle and from the engine controller; and wherein the sensor system of the at least one fuel nozzle includes a pressure sensor on an outlet portion of the respective nozzle and is configured to produce an input signal indicative of nozzle outlet pressure. a first electric motor controlled fuel pump having an outlet operatively connected to output pressurized fuel to a fuel line, and an inlet configured to receive fuel supplied from an aircraft fuel tank; a second electric motor controlled fuel pump having an outlet operatively connected to output pressurized fuel to the fuel line, and an inlet configured to receive fuel supplied from the aircraft fuel tank, wherein the first and second electric motor controlled fuel pumps connect in parallel with one another to the fuel line; a plurality of fuel nozzles connected to the fuel line to issue pressurized fuel from the fuel line, wherein at least one fuel nozzle in the plurality of fuel nozzles includes a respective sensor system; and a fuel controller operatively connected to receive input from the respective sensor system of the at least one fuel nozzle, and operatively connected to control the first and second electric motor controlled pumps based on input from the respective sensor system of the at least one fuel nozzle; wherein each of the fuel nozzles in the plurality of fuel nozzles includes internal valving operatively connected to the controller so the controller can control fuel flow through the plurality of fuel nozzles by throttling the plurality of fuel nozzles and by controlling the first and second electric motor controlled pumps (104, 110); wherein the controller is operatively connected to receive input from an engine controller, and is configured to control the first and second electric motor controlled pumps (104, 110) based on input from the respective sensor system of the at least one fuel nozzle and from the engine controller; and wherein the sensor system of the at least one fuel nozzle includes a pressure sensor on an outlet portion of the respective nozzle and is configured to produce an input signal indicative of nozzle outlet pressure.