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This SAE Aerospace Information Report (AIR) discusses past and present approaches for monitoring the landing gear structure and shock absorber (servicing), opportunities for corrosion detection, methods for transient overload detection, techniques for measuring the forces seen by the landing gear structure, and methods for determining the fatigue state of the landing gear structure. Landing gear tire condition and tire pressure monitoring are detailed in ARP6225, AIR4830, and ARP6137, respectively. Aircraft Brake Temperature Monitoring Systems (BTMS) are detailed in AS1145.
This test method provides a procedure for measuring no-load rotational breakaway torque of self-lubricating spherical bearings.
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, and forging stock.
This specification covers the requirements for six alloy compositions, four inspection classes, four radiographic quality grades and six classes of mechanical properties of high strength aluminum-alloy castings.
This SAE Standard was developed to provide a method for indicating the direction of engine rotation and numbering of engine cylinders. The document is intended for use in designing new engines to eliminate the differences which presently exist in industry.
Most signal and marking lighting devices have light sources (bulbs), which can be based on either filament or LED technology. To assure field replacement, it is important that light source types employed be readily available in normal service channels. This document defines the physical, electrical, and photometric characteristics necessary to achieve a proper replacement for popular types of signal and marking light sources. Some of the design characteristics in this document are listed solely for the sake of standardization and are not intended to describe the performance of lighting devices (lamp assemblies) on the vehicle. Halogen filament light sources suitable for signal and marking lighting are specified in SAE J2560.
This specification establishes the requirements for various types of identification sleeving that will shrink to a predetermined size upon the application of heat after it has been marked. Continuous operating temperature ratings range from -55° to 175°C (-67° to 347°F). (See 6.1).
This SAE Aerospace Recommended Practice (ARP) provides the industry agreed methods to keep the center of gravity (C.G.) location of loaded air cargo Unit Load Devices (ULDs) within the maximum horizontal and vertical limits allowed by their airworthiness approval.
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
This specification covers a phenol/formaldehyde-resin-impregnated, cotton fabric laminate in the form of sheet.
The turbine-engine inlet flow distortion methodology addressed in this document applies only to the effects of inlet total-pressure distortion. Practices employed to quantify these effects continue to develop and, therefore, periodic updates are anticipated. The effects of other forms of distortion on flow stability and performance, and of any distortion on aeroelastic stability are not addressed. The guidelines can be used as necessary to create a development method to minimize the risk of inlet/engine compatibility problems. The degree to which guidelines for descriptor use, assessment techniques, and testing outlined in this document are applied to a specific program should be consistent with the expected severity of the compatibility problem.
This SAE Standard sets forth the requirements for the attachment of three-point hitch implements or equipment to the rear of agricultural wheeled tractors equipped with quick-attaching couplers.
This AS defines instruments which use inputs of static and pitot pressure equal to those which are utilized to establish the pressure altitude and speed of that aircraft. These pressures are applied to the instrument ports to provide means for generation of an aural warning whenever the aircraft reaches or exceeds the maximum operating limit speed. This Over Speed Warning Instrument function may be incorporated as part of an Air Data Computer, or an Air Speed Indicator, or an Air Speed/Mach Number Indicator, or other instruments. In those cases where the Over Speed Warning Instrument is part of another instrument, the standards contained herein apply only to the Over Speed Warning Instrument function. Each aircraft type and model has a defined maximum operating limit speed curve or curves which are a part of the airframe manufacturer's type certification approval data; this limit speed data shall be available from the subject airframe manufacturer as published in the operating manual
This specification covers a nitriding grade of aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock. AMS6497 and AMS6498 cover UNS K23280 having other quality levels.
This specification covers an aluminum alloy in the form of sheet laminated with two or more layers of unidirectional aramid fiber/epoxy prepreg.
This slash sheet specifies the operational parameters and characteristics of a particular implementation of the SAE Linear, Token Passing Bus (LTPB) Interface Unit. This slash sheet defines the following: a The physical media interface: This slash sheet specifies the characteristics of the electrical interface to the physical bus media. b The minimum and maximum timing requirements for operation of this implementation of the LTPB. c The data coding used to encode and decode the data for transmission. d The default values to be loaded into the timers of the LTPB interface at power-up prior to intervention by the host processor.
This specification covers the requirements for electrodeposed lead on metal parts.
This specification covers an adhesive compounded from modified epoxy resins in ready-to-use film, supplied in rolls or sheets, either supported by mat or by woven monofilaments or unsupported.
This specification establishes hardness and electrical conductivity acceptance criteria for finished or semifinished parts made from wrought aluminum alloys after heat treatment (see 8.6).
The tow vehicle should be designed for towbarless push-back and/or maintenance towing of regional type aircraft as specified in 1.3. The design will ensure that the unit will safely secure the aircraft nose landing gear within the coupling system for any operational mode. The purpose of this towing procedure is to achieve a safer and faster operation than is possible with conventional towing equipment.
This specification covers an adhesive compounded from modified epoxy resins in ready-to-use film supplied in rolls or sheets, either supported by mat or by woven monofilaments or unsupported.
Electric, Fuel Cell and Hybrid vehicles may contain many types of high voltage systems. Adequate barriers between occupants and the high voltage systems are necessary to provide protection from potentially harmful electric current and materials within the high voltage system that can cause injury to occupants of the vehicle during and after a crash. This SAE Recommended Practice is applicable to Electric, Fuel Cell and Hybrid vehicle designs that are comprised of at least one vehicle propulsion voltage bus with a nominal operating voltage greater than 60 and less than 1,500 VDC, or greater than 30 and less than 1,000 VAC. This Recommended Practice addresses post-crash electrical safety, retention of electrical propulsion components and electrolyte spillage.
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