A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

A system for use with a landing gear of an aircraft includes a drag brace assembly having an upper end configured to be rotatably coupled to the aircraft and a lower end configured to be rotatably coupled to a shock strut of the landing gear. The system further includes a jury linkage having a brace portion configured to be pivotally coupled to the drag brace assembly and a strut portion pivotally coupled to the brace portion and configured to be rotatably coupled to the shock strut.

A system for use with a landing gear of an aircraft includes a drag brace assembly having an upper end configured to be rotatably coupled to the aircraft and a lower end configured to be rotatably coupled to a shock strut of the landing gear. The system further includes a jury linkage having a brace portion configured to be pivotally coupled to the drag brace assembly and a strut portion pivotally coupled to the brace portion and configured to be rotatably coupled to the shock strut.

A landing gear for an aircraft comprising a truck support strut, a landing gear retract mechanism coupling the truck support strut to a frame of the aircraft, so that the truck support strut is suspended from the frame by the landing gear retract mechanism, at least one wheel support arm rotatably coupled to the truck support strut, a carrier member coupled to the landing gear retract mechanism and to the truck support strut so that the landing gear retract mechanism drives the carrier member along the truck support strut, and at least one shock absorber, each of the at least one shock absorber being coupled to both a respective one of the at least one wheel support arm and the carrier member so that movement of the carrier member effects rotation of the at least one wheel support arm relative to the truck support strut.

A landing gear for an aircraft comprising a truck support strut, a landing gear retract mechanism coupling the truck support strut to a frame of the aircraft, so that the truck support strut is suspended from the frame by the landing gear retract mechanism, at least one wheel support arm rotatably coupled to the truck support strut, a carrier member coupled to the landing gear retract mechanism and to the truck support strut so that the landing gear retract mechanism drives the carrier member along the truck support strut, and at least one shock absorber, each of the at least one shock absorber being coupled to both a respective one of the at least one wheel support arm and the carrier member so that movement of the carrier member effects rotation of the at least one wheel support arm relative to the truck support strut.

A landing gear including an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation, a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder, and a shrink mechanism including a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam (a.k.a. retract actuator beam) of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.

A landing gear including an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation, a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder, and a shrink mechanism including a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam (a.k.a. retract actuator beam) of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.

Landing gear monitoring systems and methods for an aircraft include a landing gear timing analysis control unit that is configured to analyze one or both of landing gear motion of one or more landing gears of the aircraft or door motion of one or more doors proximate to the landing gear(s) to determine an operational status of one or both of the landing gear(s) or the door(s).

Landing gear monitoring systems and methods for an aircraft include a landing gear timing analysis control unit that is configured to analyze one or both of landing gear motion of one or more landing gears of the aircraft or door motion of one or more doors proximate to the landing gear(s) to determine an operational status of one or both of the landing gear(s) or the door(s).