Other

The Boeing Company

Jeffrey V Lindstrom

Kevin W Beyer

David C Reusch

Lior Ungar

Bradley E Platin

R David Reed

A linear actuator system including a screw member elongated along a longitudinal axis, the screw member including a threaded portion and an end portion, a nut member coaxially received over the screw member and in threaded engagement with the threaded portion of the screw member, a ring member received over the end portion of the screw member, a flange member connected to the end portion of the screw member, and a threaded member in threaded engagement with the flange member, the threaded member having a distal end protruding toward the ring member.

Linear actuator system with circumferentially and axially adjustable end stop assembly

An accurate and compact flap skew detection system that operates independent of the flap-drive system comprises, in a preferred embodiment, three major elements; a rotary position sensor located on fixed wing structure; a push-pull link and crank arm to convert translational flap motion into rotary sensed motion at the sensor; and a computer processing means to process the rotational sensed information and to compute a flap skew algorithm. Inter-flap and intra- flap translational motion is sensed and compared using a plurality of rotary sensors. Sensors falling outside of predetermined limits or violating control law rules indicate a non-synchronous or asymmetrical &ldquo;skewed&rdquo; condition.

Method and apparatus for detecting skew and asymmetry of an airplane flap

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Seattle, WA, United States of America

Jeffrey V Lindstrom