Abstract: A landing gear actuation system comprising a motive force system, such as an actuator and/or a piston to move the landing gear from a first position to a second position is disclosed herein. The landing gear actuation system may also comprise a spring system configured to counterbalance the weight of the landing gear and/or assist the motive force system in moving the landing gear from a first position to a second position. The landing gear actuation system may further comprise a camming mechanism to distribute the direction and/or location of the force applied to the landing gear.

Abstract: A ballscrew assembly may comprise a ballscrew having an axially distributed ballscrew groove about an interior circumference of the ballscrew, an extended top plate having an axially distributed extended top plate groove disposed on an outer circumference of the extended top plate, and an axially distributed thrust bearing. Further, a ballnut assembly may comprise a ballnut having an axially distributed ballnut groove about an interior circumference of the ballnut, an extended top plate having an axially distributed extended top plate groove disposed on an outer circumference of the extended top plate, and an axially distributed thrust bearing. Further still, a ballnut assembly may comprise a ballnut having an axially distributed ballnut groove about an outer circumference of the ballnut, an extended top plate having an axially distributed extended top plate groove disposed on an interior circumference of the extended top plate and an axially distributed thrust bearing.

Abstract: A method is disclosed that comprises severing an I/O channel between a brake system controller and an aircraft component; sending a test signal to the brake system controller; receiving, from the brake system controller, a feedback signal to the test signal; and determining an appropriateness of the feedback signal. A system is disclosed that comprises a brake system controller wrapped in a BITE region, wherein the BITE region comprises a testing module, a safety interlock region having an I/O channel between the brake system controller and another system, and a testing module capable of sending a test signal to the brake system controller.

Abstract: A system for securing objects in an aircraft can comprise a structure in an aircraft having a plurality of receiving holes and a tie down. The tie down can comprise a housing and a fitting. The housing can have at least one engagement pin for selective positioning wherever the receiving holes are located. The fitting can be capable of receiving and securing a restraint to the housing and configured to rotate about the engagement pin to facilitate securing objects in an aircraft.

Abstract: An aircraft cargo restraint has a base configured for attachment to a cargo deck. A housing is rotatably mounted to the base about a first axis and is movable between an erect position and a stowed position. A head is movably disposed in the housing, and is movable between an extended position and a contracted position in directions that are substantially parallel to the first axis. The restraint includes a lock configured to releasably secure the housing in the erect position when the head is in the contracted position, and to permit movement of the head from the erect position to the stowed position when the head is in the extended position.