An air vehicle power and thermal management system comprising an aircraft controller, a cooling system comprising a fluid control device (46, 48) and an electrically powered load: the aircraft controller structured to distribute power provided by a gas turbine engine between the cooling system to cool an engine fuel cooling medium and the electrically powered load to drive the electrically powered load; the aircraft controller being configured to: direct the power to create a first duration cooling power from the gas turbine engine to the cooling system to cool the engine fuel cooling medium, wherein the first duration cooling power is directed over a first power time period, and shift the power to reduce the first duration cooling power to create a load electrical power to the electrically powered load to drive the electrically powered load over a second power time period that follows the first power time period, and wherein by operation of the aircraft controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period by the first duration cooling power, and wherein by operation of the aircraft controller the second duration cooling power is provided to the fluid control device (46, 48) of the cooling system to transfer the cooled engine fuel cooling medium to the electrically powered load. the aircraft controller structured to distribute power provided by a gas turbine engine between the cooling system to cool an engine fuel cooling medium and the electrically powered load to drive the electrically powered load; the aircraft controller being configured to: direct the power to create a first duration cooling power from the gas turbine engine to the cooling system to cool the engine fuel cooling medium, wherein the first duration cooling power is directed over a first power time period, and shift the power to reduce the first duration cooling power to create a load electrical power to the electrically powered load to drive the electrically powered load over a second power time period that follows the first power time period, and wherein by operation of the aircraft controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period by the first duration cooling power, and wherein by operation of the aircraft controller the second duration cooling power is provided to the fluid control device (46, 48) of the cooling system to transfer the cooled engine fuel cooling medium to the electrically powered load. direct the power to create a first duration cooling power from the gas turbine engine to the cooling system to cool the engine fuel cooling medium, wherein the first duration cooling power is directed over a first power time period, and shift the power to reduce the first duration cooling power to create a load electrical power to the electrically powered load to drive the electrically powered load over a second power time period that follows the first power time period, and wherein by operation of the aircraft controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period by the first duration cooling power, and wherein by operation of the aircraft controller the second duration cooling power is provided to the fluid control device (46, 48) of the cooling system to transfer the cooled engine fuel cooling medium to the electrically powered load.