AS8860A Landing Gear Structural Requirements as Listed in the MIL-886X Series of Specifications
Stabilized
10/03/2012
- Features
- Issuing Committee
- Content
- 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:
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a
General Specifications
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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.
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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.
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3
The strength of anchor-line clamps, and the airplane strength for hoisting, jacking, towing, tie-down, and other ground- or deck-handling conditions.
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4
Structural design, analysis, and test data.
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5
Laboratory and flight tests performed to obtain information regarding strength rigidity and loads.
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6
Definitions.
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1
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b
Landing and Ground Handling Loads
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c
Ground Loads for Navy Acquired Airplanes
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d
Miscellaneous Loads
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e
Reliability Requirements, Repeated Loads, Fatigue and Damage Tolerance
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a
- Content
- 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.
- Pages
- 66
- Citation
- SAE International Technical Standard, Landing Gear Structural Requirements as Listed in the MIL-886X Series of Specifications, SAE Standard AS8860A, Stabilized October 2012, Reaffirmed May 2012, Issued April 2006, https://doi.org/10.4271/AS8860A.