Landing Gear Structural Requirements as Listed in the MIL-886X Series of Specifications(STABILIZED Oct 2012)
This specification 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:
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.
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.
The strength of anchor-line clamps, and the airplane strength for hoisting, jacking, towing, tie-down, and other ground- or deck-handling conditions.
Structural design, analysis, and test data.
Laboratory and flight tests performed to obtain information regarding strength rigidity and loads.
Landing and Ground Handling Loads
Ground Loads for Navy Acquired Airplanes
Reliability Requirements, Repeated Loads, Fatigue and Damage Tolerance
This document has been declared "Stabilized" by SAE A-5B, Gears, Struts and Couplings Committee and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability of technical requirements. Newer technology may exist.