Goodrich Actuation Systems Limited

Daniel Foster

Jonathan A Darby

Graham James Burgess

A system for detecting a fault in a locking pin for use in an aircraft includes the locking pin; means for receiving a static air temperature; and a controller; wherein said locking pin comprises an internal heater element and at least one internal temperature sensor provided therein. The system also includes means for transmitting said measured temperature sensor information from said at least internal temperature sensor and said static air temperature information to said controller. The controller is configured to compare the static air temperature information with said locking pin temperature sensor information and determine if a difference between the measurements is above a static v. internal temperature threshold value.

Anti-icing and de-icing heated lock pin system

An apparatus configured to measure the output of a rotary actuator unit includes a rotary actuator unit. The unit includes a stationary portion, a rotating portion, and a main rotational axis (L) that runs in an axial direction from a first end of the rotary actuator unit to a second end of the rotary actuator unit. The first end is opposite the second end. The apparatus also includes a linear position sensor comprising a follower, a sensor, and a sensor arm, wherein the follower is attached to the sensor by sensor arm; and wherein the sensor is attached to the stationary portion. The apparatus also includes a follower track attached or formed in, or on, to the rotating portion. The follower track is aligned in the circumferential direction that is perpendicular to axial direction of the main rotational axis (L). The follower is configured to follow the follower track.

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Pelsall, United Kingdom

Daniel Foster