Abstract: A shock strut assembly for an aircraft landing gear includes a trunnion fitting, a compressible oleo strut subassembly, a wheel subassembly, an energy dissipating subassembly, and a mechanical load control subassembly. The oleo strut subassembly includes a cylinder member having an upper end mounted in combination with the trunnion fitting by means of the mechanical load control subassembly and a piston member having a lower end affixed in combination with the wheel subassembly and an upper end slidably inserted in the cylinder member. The energy dissipating subassembly includes a cylindrical cutter member secured in combination with the cylinder member and the trunnion fitting and a frangible tube member mounted in concentric combination with the cylinder member so that the lip of the upper end thereof is disposed in abutting engagement with the cutter member.

Abstract: An aircraft landing locking pin (12) automatically repositions from an engage position, wherein a rotating portion (15) of the landing gear is prevented from rotating, to a released position, wherein the rotating portion if free to rotate, in response to excessive side loading on the landing gear. The locking pin comprises a spring loaded actuator (32,34,60) which urges a roller (19) of a lock pin assembly (20) in contact with a bushing (22). In response to a side loading on the landing gear in excess of a predetermined loading, the locking pin is automatically released wherein the roller is expelled from the bushing. The threshold loading is determined as a function of the spring force applied to the lock pin assembly via the actuator linkage. The locking pin automatically reengages when the lock pin assembly is aligned with the bushing.