An assembly comprising a flight control member of an aircraft , the assembly comprising: a hydraulic actuator operatively connected to the flight control member and comprising a piston , a first chamber on a first side of the piston , and a second chamber on a second side of the piston ; a boost pump ; a supply line and a boost line ; a receiving manifold connected to the supply line and to the boost line to receive hydraulic fluid from both the supply line and the boost line , and configured to move hydraulic fluid to an output line , wherein the boost line receives hydraulic fluid from the boost pump ; a dual spool valve including a first port connected to the output line to receive the hydraulic fluid from the output line and a second port configured to discharge hydraulic fluid to a return line , the dual spool valve further comprising: first and second manifolds each including a supply port to receive hydraulic fluid from the first port , a return port to move hydraulic fluid to the return line via the second port , and an actuator port to move hydraulic fluid to the actuator ; and a first spool movably positioned in the first manifold and a second spool movably positioned in the second manifold , the first and second spools being independently movable between a first position and a second position; in the first position, the first and second spools blocking the supply ports to prevent hydraulic fluid from moving from the supply line to the actuator and being away from the return ports to allow hydraulic fluid to move from the actuator to the return line; in the second position, the first and second spools positioned away from the supply ports to allow hydraulic fluid to move from the first port to the actuator and blocking the return ports to prevent hydraulic fluid from moving from the actuator to the second port ; the first and second spools being positioned away from the actuator ports in each of the first and second positions to allow hydraulic fluid to flow into and out of the actuator . a hydraulic actuator operatively connected to the flight control member and comprising a piston , a first chamber on a first side of the piston , and a second chamber on a second side of the piston ; a boost pump ; a supply line and a boost line ; a receiving manifold connected to the supply line and to the boost line to receive hydraulic fluid from both the supply line and the boost line , and configured to move hydraulic fluid to an output line , wherein the boost line receives hydraulic fluid from the boost pump ; a dual spool valve including a first port connected to the output line to receive the hydraulic fluid from the output line and a second port configured to discharge hydraulic fluid to a return line , the dual spool valve further comprising: first and second manifolds each including a supply port to receive hydraulic fluid from the first port , a return port to move hydraulic fluid to the return line via the second port , and an actuator port to move hydraulic fluid to the actuator ; and a first spool movably positioned in the first manifold and a second spool movably positioned in the second manifold , the first and second spools being independently movable between a first position and a second position; in the first position, the first and second spools blocking the supply ports to prevent hydraulic fluid from moving from the supply line to the actuator and being away from the return ports to allow hydraulic fluid to move from the actuator to the return line; in the second position, the first and second spools positioned away from the supply ports to allow hydraulic fluid to move from the first port to the actuator and blocking the return ports to prevent hydraulic fluid from moving from the actuator to the second port ; the first and second spools being positioned away from the actuator ports in each of the first and second positions to allow hydraulic fluid to flow into and out of the actuator . <EOS>