Abstract: The C/D axisymmetrical exhaust nozzle for a gas turbine engine is designed to fit on the engine and STOVL aircraft and includes an hydraulic actuator and a combined load balancing piston/sync ring that is judiciously mounted in the assembly and discretely attached to a fulcrum link and the mechanism is enclosed between concentrically spaced static structure for defining a full-hoop configuration. The actuator is attached to flanges formed on the static structure to allow for access to the attaching bolts. Rollers are mounted on the sync ring to ease the rectilinear movement of the sync ring. Positioning the actuator rectilinearly rotates the fulcrum and connecting links to position the flaps for varying the throat size and C/D configuration for optimum engine performance.