Lever 1 is connected by turning pairs B and C to link 8, turning about fixed axis A, and to rod a of piston 9 which reciprocates in fixed pump cylinder 2. Rod b of piston 10, reciprocating in fixed cylinder 5, is linked to the mechanism of the aircraft landing flaps (not shown). When lever 1 is oscillated, pump 2 draws in fluid from tank 3 and delivers it to power cylinders 4 of the landing gear or to power cylinder 5 of the landing flaps. Two rotary directional valves, 6 and 7, connected in parallel, enable the landing gear and landing flap mechanisms to be separately controlled. Landing gear control valve 6 is shown turned on.
$3966$LHP,Co$