Patent ID: 6659399
Filing Date: 2003-12-09
Classification: F15B,Y10T

Abstract:
An aircraft control surface actuator assembly comprising:a flight control surface; a mechanical drive mechanism in communication with said flight control surface, said mechanical drive mechanism controlling movement of said flight control surface; at least one actuator rod assembly mounted to said mechanical drive mechanism, said at least one actuator rod assembly comprising: a first segment having a first control mounting end mounted to said mechanical drive mechanism and a first segment adjustment end, said first segment adjustment end including a first segment outer diameter comprising a plurality of first segment outer threads; a second segment including a second segment inner diameter having a plurality of second segment inner threads and a second segment outer diameter having a plurality of second segment outer threads, said second segment inner threads engaging said first segment outer threads; at least one second segment split sleeve passage formed in said second segment, said at least one second segment split sleeve passage allowing said second segment inner diameter to be reduced under a compression force; a third segment including a third segment adjustment end and a third segment mounting end, said third section adjustment end including a third segment inner diameter having a plurality of third segment inner threads engaging said second segment outer threads; at least one third segment split sleeve passage formed in said third segment adjustment end to allow said third segment inner diameter to be reduced under said compression force; and a clamped sleeve portion formed as a portion of said third segment, said clamped sleeve portion including a clamp actuator, said clamp actuator applying said compression force to said second segment inner diameter and said third segment inner diameter to prevent rotational movement of said second segment.