Patent ID: 8172551

Claim:
A pump arrangement for a fuel system for use in an aircraft, the pump arrangement comprising: an actuation pump having an actuation pump outlet having an actuation pump discharge flow at an actuation pump discharge pressure; a pressure regulating valve comprising: first, second and third ports; a regulator valve member selectively adjusting a flow path from the first port to the second port; wherein the first port is operably fluidly coupled to the actuation pump outlet such that a first portion of the actuation pump discharge flow operably biases the regulator valve member in a first direction; wherein the third port is operably fluidly coupled to the actuation pump outlet such that a second portion of the actuation pump discharge flow operably biases the regulator valve member in a second direction opposite the first direction; wherein movement of the regulator valve in either of the first or second directions operably adjusts a pressure of the first portion of the actuation pump discharge flow to correspondingly adjust the actuation pump discharge pressure; and a control valve operably interposed between the actuation pump outlet and the third port selectively adjusting the amount of biasing applied by the second portion of the actuation pump discharge flow.