Patent ID: 6595714
Filing Date: 2003-07-22
Classification: F16B,F16C,Y10T

Abstract:
A control rod for an aircraft actuator system, comprising:a swivel insert including a tubular member having a longitudinally extending bore, external screw threads, and at least one radially extending bore through the tubular member; a rod end including a shaft, the shaft including a circumferential groove; at least one ball bearing; and a tube including an internally threaded bore, the tube adapted to be connected to the swivel insert; wherein the shaft is located in the longitudinally extending bore, the radially extending bore and circumferential groove substantially aligned; wherein the tube is threadably coupled to the swivel insert, the ball bearing captured substantially within the radially extending bore between the circumferential groove and the tube; wherein the swivel insert further includes a plurality of longitudinally extending grooves, the tube located in the longitudinally extending grooves to prevent rotation between the swivel insert and the tube.