Abstract: A rotor system is provided in one example embodiment and may include a rotor system may be provided and may include a drive link associated with a rotor hub of the rotor system, the drive link comprising an inner member and an outer member; and a sensor system mounted to the drive link, the sensor system to accommodate motions of the drive link to track rotor hub flapping. The sensor system for the rotor system may further include a sensor, the sensor comprising a sensor arm, wherein the sensor is mounted proximate to the inner member of the drive link; and a sensor link, the sensor link comprising a first end portion moveably coupled to the sensor arm, a second end portion coupled to the outer member of the drive link, and an angled portion between the first end portion and the second end portion.

Abstract: A rotor system is provided in one example embodiment and may include a rotor system may be provided and may include a drive link associated with a rotor hub of the rotor system, the drive link comprising an inner member and an outer member; and a sensor system mounted to the drive link, the sensor system to accommodate motions of the drive link to track rotor hub flapping. The sensor system for the rotor system may further include a sensor, the sensor comprising a sensor arm, wherein the sensor is mounted proximate to the inner member of the drive link; and a sensor link, the sensor link comprising a first end portion moveably coupled to the sensor arm, a second end portion coupled to the outer member of the drive link, and an angled portion between the first end portion and the second end portion.

Abstract: A pitch horn assembly for an aircraft including a blade attachment member having a first end, a second end configured to be coupled to a rotor blade; and a blade attachment axis extending between the first end and the second end of the blade attachment member; a moveable arm configured to be coupled to the blade attachment member at a pitch horn axis, the moveable arm having a first end configured to be coupled to a pitch link; a second end; and a moveable arm axis extending between the first end and the second end of the moveable arm; an extendable member configured to be coupled to the blade attachment member and the moveable arm of the pitch horn, wherein the extendable member moves the moveable arm about the pitch horn axis. An embodiment provides a method of adjusting a pitch-flap coupling in an aircraft.

Abstract: A pitch horn assembly for an aircraft including a blade attachment member having a first end, a second end configured to be coupled to a rotor blade; and a blade attachment axis extending between the first end and the second end of the blade attachment member; a moveable arm configured to be coupled to the blade attachment member at a pitch horn axis, the moveable arm having a first end configured to be coupled to a pitch link; a second end; and a moveable arm axis extending between the first end and the second end of the moveable arm; an extendable member configured to be coupled to the blade attachment member and the moveable arm of the pitch horn, wherein the extendable member moves the moveable arm about the pitch horn axis. An embodiment provides a method of adjusting a pitch-flap coupling in an aircraft.