Abstract: A landing gear system includes landing gear, an uplock that is releasably engageable with the landing gear, an uplock hydraulic actuator operably connected to the uplock, a landing gear hydraulic actuator operatively connected to the landing gear, and a controller operatively connected to the uplock hydraulic actuator and the landing gear hydraulic actuator. In response to receipt of a command to deploy the landing gear, the controller actuates the uplock hydraulic actuator and the landing gear hydraulic actuator to the UP condition and then actuates the uplock hydraulic actuator and the landing gear actuator to the DOWN condition. An alternative embodiment incorporates a piloted check valve upstream of the landing gear hydraulic actuator. The piloted check valve delays operation of the landing gear hydraulic actuator until release of the landing gear by the uplock.

Abstract: A cable support apparatus for an aircraft cable control system comprises at least one cable support unit. The cable support unit includes a pulley adapted to carry a cable of the aircraft cable control system, a support link with a first joint between the pulley and the support link and a second joint between the support link and the structure of the aircraft, and a compensation link connected with the structure of the aircraft. The thermal expansion of the compensation link causes a displacement of the support link. An aircraft and a method for maintaining a tension of a cable of a cable control system of an aircraft are also provided.

Abstract: A method of forming a composite structure having a skin, a plurality of webs and a plurality of flanges includes wrapping each of a plurality of first lay-ups around a corresponding one of a plurality of mandrels such that each first lay-up forms a skin section, a pair of opposed web sections, which extend from the skin section, and a pair of inwardly facing flange sections. The first lay-ups are aligned and a second lay-up is laid over their skin sections. A plurality of third lay-ups are laid over pairs of flange sections. A composite structure detained by this method is also disclosed.