SAE AS8860B

This SAE Aerospace Standard (AS) contains landing gear strength and rigidity requirements which, in combination with other applicable specifications, define the structural design, analysis, test, and data requirements for fixed wing piloted airplanes. These requirements include, but are not limited to, the following: a General specifications: 1 The shock-absorption characteristics and strength of landing-gear units and the strength and rigidity of their control systems and of their carry-through structures. Requirements for wheels, tires, and brakes as they affect air vehicle ground loads are also included. 2 The strength of structures integral with the airplane provided for transmitting catapulting forces to the airplanes, and for engaging shipboard and shore-based arresting gear, and barricades. 3 The strength of anchor-line clamps, and the airplane strength for hoisting, jacking, towing, tie-down, and other ground- or deck-handling conditions. 4 Structural design, analysis, and test data. 5 Laboratory and flight tests performed to obtain information regarding strength rigidity and loads. 6 Definitions. b Landing and ground handling loads. c Ground loads for Navy acquired airplanes. d Miscellaneous loads. e Reliability requirements, repeated loads, fatigue and damage tolerance. This SAE Aerospace Standard (AS) has been revised to correct an error in Table 6, along with other minor errors that were introduced when the previous MIL-A-886X documents were digitized.