Consideration for the damaging effects to aircraft from the failure of wheels and tires should be evaluated. This document discusses the types of problems in-service aircraft have experienced and methodology in place to assist the designers when evaluating threats for new aircraft design. The purpose of this document is to provide a history of in-service problems, provide a historical summary of the design improvements made to wheels and tires during the past 40 years, and to offer methodology which has been used to help designers assess the threat to ensure the functionality of systems and equipment located in and around the landing gear and in wheel wells.
This specification covers a direct reading, remote control, pneumatic pressure inflator assembly, for use on aircraft tires and struts having pneumatic pressure requirements up to 600 psi. It includes pressure relief provisions to provide for safe inflation. Also included are dual chuck stem gages for measuring tire pressure.
This specification covers a direct reading, remote control, pneumatic pressure inflator assembly, for use on aircraft tires and struts having pneumatic pressure requirements up to 600 psi. It includes pressure relief provisions to provide for safe inflation. Also included are dual chuck stem gages for measuring tire pressure.
This document categorizes the different types of storage requirements, either on the aircraft or new unused or overhauled on the shelf, for aircraft landing gears/components. Recommendations and examples of proper landing gear storage are outlined. Reclamation recommendations are provided for aircraft landing gear returning from long-term storage.
This document discusses the work done by the U.S. Army Corps of Engineers and the Waterways Experiment Station (WES) in support of SAE A-5 Committee activity on Aerospace Landing Gear Systems. It is an example of how seemingly unrelated disciplines can be combined effectively for the eventual benefit of the overall aircraft system, where that system includes the total airfield environment in which the aircraft must operate. In summary, this AIR documents the history of aircraft flotation analysis as it involves WES and the SAE.
This document discusses the work done by the U.S. Army Corps of Engineers and the Waterways Experiment Station (WES) in support of SAE A-5 Committee activity on Aerospace Landing Gear Systems. It is an example of how seemingly unrelated disciplines can be combined effectively for the eventual benefit of the overall aircraft system, where that system includes the total airfield environment in which the aircraft must operate. In summary, this AIR documents the history of aircraft flotation analysis as it involves WES and the SAE.
This aerospace recommended practice includes the type of lubricant to be used, conditions of lubrication, and torque-tension relationship of lock nut and bolts as required for desired preload.
This SAE Aerospace Recommended Practice (ARP) is intended to document the process of landing gear system development. This document includes landing gear system development plans for commercial/military, fixed wing, and rotary wing air vehicles.
This SAE Aerospace Standard (AS) covers an alternate gland design for the installation of scraper/wiper rings in the lower end of landing gear shock struts for the purpose of contaminant exclusion. The defined scraper gland covered by this document, as shown in Table 1, is a variant of MIL-G-5514, the accepted gland standard for MS28775. Piston diameters, gland internal diameters, and the groove sidewall angles and surface finish are defined by MIL-G-5514, but the gland outer retaining wall diameter is changed. AS4088 is similar to this document, but was developed by SAE A-6 for flight control and general purpose cylinders. It differs from this document primarily by the clearance between the rod (piston) and outer gland wall. Since landing gears are more susceptible to dirt contamination, the additional clearance provides a larger path to allow excessive dirt accumulation to exit the gland.
This SAE Aerospace Information Report (AIR) describes the performance of plating’s and coatings for landing gear that potentially provide environmental compliance benefits versus the current baseline processes. The hazardous systems addressed in this version of the document include cadmium plating, chromated primers, and high VOC (volatile organic compounds) topcoats. The AIR applies to landing gear structures and mechanisms for all types of civil and military aircraft. The potential replacements apply to both Original Equipment Manufacturer (OEM) hardware and overhaul of in-service landing gears.
This SAE Aerospace Information Report (AIR) describes the performance of platings and coatings for landing gear that potentially provide environmental compliance benefits versus the current baseline processes. The hazardous systems addressed in this version of the document include cadmium plating, chromated primers, and high VOC (volatile organic compounds) topcoats. Available data are presented for various standard tests in order to compare the replacement candidates. Conclusions are made as to the best performer(s) for each test section presented. These conclusions are not to be regarded as recommendations for or against any of the candidates. The AIR applies to landing gear structures and mechanisms for all types of civil and military aircraft. The potential replacements apply to both original equipment manufacturer (OEM) hardware and overhaul of in-service landing gears.
This SAE Aerospace Information Report (AIR) describes the performance of platings and coatings for landing gear that potentially provide environmental compliance benefits versus the current baseline processes. The hazardous systems addressed in this version of the document include cadmium plating, chromated primers, and high VOC (volatile organic compounds) topcoats. Available data are presented for various standard tests in order to compare the replacement candidates. Conclusions are made as to the best performer(s) for each test section presented. These conclusions are not to be regarded as recommendations for or against any of the candidates. The AIR applies to landing gear structures and mechanisms for all types of civil and military aircraft. The potential replacements apply to both original equipment manufacturer (OEM) hardware and overhaul of in-service landing gears.
Electrolytically deposited chrome plate is the current standard surface treatment for landing gear component interface surfaces that require good wear resistance and corrosion protection. Chrome plated components are typically plagued by a slight debit in fatigue performance, detrimental mud cracking surface pattern, susceptibility to scoring, wear, and seal leakage. In addition, recent changes in environmental compliance standards place further restrictions on the use of electrolytically deposited chromium. Some commercial applications have already eliminated the use of chrome plate on current and future products. As a result, a substitute for electrolytically deposited chrome plate has been sought for several years. High Velocity Oxygenated Fuel (HVOF) thermal spray coatings have been developed to the point where they are being implemented as an alternative to hard chrome plate on high strength low alloy steels for external surfaces on landing gear applications.
This SAE Aerospace Recommended Practice (ARP) identifies the best practices to reduce damage and promote safety during the storage, handling, and shipping of W/T assemblies.