Patent ID: 7984880
Filing Date: 2011-07-26
Classification: B64C

Abstract:
1. A rudder assist mechanism for operable interconnection with a rudder control system by which manual pilot inputs cause an aircraft rudder control surface to be moved through right and left deflection angles, the rudder assist mechanism comprising: a control spring assembly; and a linkage assembly which operably connects the control spring assembly to the rudder control system, the linkage assembly including a null position which defines a dead zone of rudder control surface deflection within a selected range of right and left rudder control surface deflection angles whereby substantially no spring force of the control spring assembly is transferred to the rudder control system, and an actuator unit which is operably capable of moving the control spring assembly and the linkage assembly connected thereto between a thrust symmetrical mode (TSM) condition and into a thrust asymmetrical mode (TAM) condition in response to receiving a signal from an engine monitoring system of an abnormal engine thrust condition, wherein