A fuel system for an aircraft can include one or more airframe fuel lines configured to transfer fuel from one or more fuel tanks to an engine, one or more engine fuel pumps in fluid communication with the one or more airframe fuel lines and configured to pressurize fuel from a main stage boost pressure to a combustor pressure to be injected into a combustor of an engine, one or more airframe fuel pumps configured to pressurize fuel within the one or more airframe fuel lines to the main stage boost pressure used by the engine fuel pump. For example, the main stage boost pressure can be about 250 psi.