Abstract: This invention relates to a hard landing indication system that will provide a quantitative assessment that a hard landing did or did not occur at the last landing of an airplane. A hard landing can cause structural damage to an airplane. An airplane that has been declared to have a hard landing must be grounded until an inspection of the structure has been made to determine if repairs are required.

Abstract: This invention relates to a hard landing indication system that will provide a quantitative assessment that a hard landing did or did not occur at the last landing of an airplane. A hard landing can cause structural damage to an airplane. An airplane that has been declared to have a hard landing must be grounded until an inspection of the structure has been made to determine if repairs are required.

Abstract: An aircraft cargo loader is provided including a platform having a plurality of rollers for supporting cargo thereon. A base member is disposed below the platform and a plurality of telescoping jacks are disposed between the platform and the base member for lifting the platform. A supply of pressurized gas is connected to the plurality of telescoping jacks. An automatic load balancing system is provided for balancing the load on the platform. The cargo loader is designed to be lightweight and portable so that it can be loaded onto the aircraft and transported therewith.

Abstract: A method and the resulting structure for attaching a doubler to the skin of an airplane, using the original fastener holes, where the fastener countersinks are filled with interference fitted washers and the new fasteners have an interference fit with the airplane skin, doubler and washers.

Abstract: A method and the resulting structure for attaching a doubler to the damaged skin of an airplane, using the original fastener holes, where the fastener countersinks are filled with interference fitted washers and the new fasteners have an interference fit with the airplane skin, doubler and washers.

Abstract: A fail-safe zero-load hinge or pivot-joint having a first load primary support path comprising a sleeve and nut combination and a secondary or redundant load support path comprising a shaft, sized to be inserted axially through the sleeve with diametrical clearance, for threaded engagement with a nut providing axial clearance from said primary members. The secondary shaft and nut combination holds the joint intact after the primary load members have failed permitting the joint assembly to perform its normal designed function of load carrying with the continued full range of movement without the risk of restricted operation seizure or jamming.A locking cap is provided for simple, safe holding of the nuts of primary and secondary member from disengagement, or even partial back off.A dye indicator may be used to indicate failure of the primary load carrying members.