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SAE AIR5914

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Omfang

This SAE Aerospace Information Report (AIR) provides guidelines for the development of landing gear fatigue spectra for the purpose of designing and certification testing of Part 25 landing gear. Many of the recommendations herein are generalizations based on data obtained from a wide range of landing gears. The aircraft manufacturer or the landing gear supplier is encouraged to use data more specific to their particular undercarriage whenever possible. Purpose With the ever-increasing length of aircraft operating life, design for good fatigue resistance assumes greater prominence, particularly for civil aircraft with low reaction factors where landing loads are assumed to have little significance. In recent years, the ability to gather field data on actual aircraft landing gear loading has allowed aircraft manufacturers to develop large data sets for use in developing fatigue spectra for new aircraft. This spectrum generally varies with the type of aircraft such as military versus commercial, as well as the various configurations of commercial aircraft from wide body transports to regional aircraft and business jets. In most cases, in the past the aircraft manufacturer has provided the fatigue spectrum in the design specification. This has ranged from block loads for similar maneuvers to the modern flightby- flight spectrum. In cases where the fatigue spectrum is not provided, a standardized method of developing the fatigue spectrum is needed. This methodology can be used by landing gear supplier to develop the fatigue spectrum based on a set of parameters supplied by the aircraft manufacturer. The purpose of this document is to establish guidelines for the landing gear supplier to develop Landing Gear Fatigue Spectra (LGFS) from loads data supplied by the aircraft manufacturer or with no data supplied by the manufacturer. It is the intent to base the recommendations for the various aircraft configurations upon historical data used in landing gear design as well as input from the aircraft manufacturers and in some cases, the aircraft users. Individual landing gear units may be initially designed and qualified to fatigue requirements in excess of those stated in this report. This maybe for a variety of reasons such as: a. Simplifying analysis and testing. b. Ensure adequate life availability for future increased weight versions of the airplane. This report addresses the fatigue load spectrum requirements of the landing gear. Requirements in addition to those of this report may be imposed to verify functional and endurance aspects of the gears.

Dokumentinformasjon

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