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This supplement forms a part of SAE Aerospace Specification AS85421. It shall be used to identify fitting standards citing this procurement specification.
This SAE Standard establishes the test procedure, environment, and instrumentation for determining the sound levels of snowmobiles in the stationary test mode. This test method is intended to provide an accurate measurement of exhaust and other engine noise and may be used to evaluate new and in-use snowmobiles to determine compliance with noise control regulations. Sound level measurements obtained with this test method are not intended as an engineering determination of overall machine noise. For this purpose, the use of SAE J192 is recommended.
This SAE Recommended Practice is applicable to two- or three-wheel motorcycles intended for highway use. Unless noted, requirements apply to both metallic and nonmetallic tanks. Accessory or aftermarket tanks as well as original equipment tanks are covered.
This SAE Recommended Practice describes the equipment and procedure for determining the truck cab interior sound level over the upper half of the engine speed range. This practice applies to motor trucks and truck-tractors and does not include construction and industrial machinery.
This SAE Standard applies to the application of ultraviolet leak detection to service mobile air-conditioning systems.
This document presents design and application information which will allow optimized utilization of filter line wire and cable purchased to AS85485. Filter line wire is defined and design information is presented. The electrical and mechanical performance characteristics of the wire, along with recommended harnessing methods and techniques, are also presented.
This document applies to regulatory/approving authorities involved with decisions regarding the use of high-intensity light (HIL) directed into the navigable airspace. For the purpose of this document, lights greater than 0.25 million candlepower meet the minimum threshold of an HIL. Lights not directed or reflected into the navigable airspace are not usually considered to interfere with aircraft operations. HILs include laser-derived light sources; other laser systems are beyond the scope of this document. This document addresses adverse effects of HILs on humans, such as visual interference. HIL effects on Unmanned Aircraft Systems (UASs) are beyond the scope of this document.
This report investigates the use of single and multi-layer coatings on replaceable headlamp bulbs and how such coatings can affect the performance of bulbs in terms of light scattering, which can contribute to glare, and spectral separation in headlamps. Tests were developed to investigate the effects of absorptive and interference (multi-layer) coatings on bulbs, and on bulbs in headlamp systems. These tests provide validation for a proposed bulb color separation test, which establishes limits for spectral separation within the boundaries of SAE J578 white color requirements. The bulb color separation test provides a definitive selection criterion to identify bulbs that cause excessive light scatter (glare) and/or spectral separation in an optical system.
This SAE Information Report prescribes dummies, procedures, and configurations that can be used for investigating the interactions that might occur between a deploying airbag and a child restrained by a child restraint system (CRS). During the inflation process, airbags generate a considerable amount of kinetic energy which can result in substantial forces being applied to a child who is restrained in a CRS in the front seat of a vehicle. Field data collected by the special crash investigation team of the National Highway Traffic Safety Administration (NHTSA) indicate that fatal forces can be developed. In response to these field data, NHTSA added a series of airbag/child interaction tests and limits to the Code of Federal Regulations (CFR 571.208) that deal with occupant protection, commonly known as Federal Motor Vehicle Safety Standards (FMVSS 208). The bases for NHTSA tests are the various test procedures that were developed by the International Standards Organization (ISO) and the
The SAE International task force on headlamp mounting height has considered the ramifications of reducing the maximum mounting height of headlamps on highway vehicles. The task force has concluded that it is in the best interest of the driving public to make a substantial reduction in the recommended maximum height at which headlamps, particularly low-beam headlamps, may be mounted. Heights as low as 36 to 40 in (90 to 100 cm) have been considered. New tractor vehicles are in fact being designed with headlamps mounted in this range. Further recommendations were withheld in anticipation of tests to demonstrate the effect of mounting height on the legibility of certain overhead signs.
This SAE Recommended Practice defines test methods and general requirements at all phases of development, production, and field analysis of electrical terminals (including sense pins), connectors, and components that constitute the jump-start connection for road vehicles having 42 V (nominal) electrical systems. The 42 V jump start connector is always remote from the vehicle battery and may take the form of an in-line or Header Connection, either of which is in an accessible location for attachment of a jumper cable from an assist vehicle or battery charger. WARNING—The Jump Start Connector requires environmental protection. This specification assumes that such protection is in place and remains effective for the life of the vehicle. The level of protection depends on the vehicle packaging environment and duty cycle. Appendix B of this document contains the physical specification for the Jump Start Connector.
This document applies to the requirements of a device used in the field and inspection stations to aim and check aim of mechanically aimable headlamp units. The purpose of this document is to provide a laboratory test procedure to determine whether the devices under test are capable of accurately positioning headlamp units from their aiming pads and maintaining their accuracy in service within the tolerances designated in this document.
This SAE Aerospace Standard (AS) provides minimum design, installation (by manual and power methods) and removal requirements for AS3504 and AS3505 thin wall inserts and is applicable when specified on engineering drawings or in procurement documents.
This SAE Aerospace Standard (AS) establishes general requirements and descriptions of specific activities for the performance of LORA during the life cycle of products or equipment. When these requirements and activities are performed in a logical and iterative nature, they constitute the LORA process.
This document is for establishing and addressing anomalies on appearance of new and newly retreaded tires prior to installation on aircraft. It is intended to use cosmetics as well as functionality to make a determination of acceptability. However, if cosmetic appearance is not a requirement, use the inspection criteria from ARP6225. This ARP does not supersede (E)TSO-C62 minimum requirements, including marking requirements.
This SAE standard applies to any and all additives and chemical solutions intended for aftermarket use in the refrigerant circuit of vehicle air-conditioning systems with belt-driven compressors, except as noted below. This standard provides testing and acceptance criteria for determining the stability and compatibility of additives and flushing materials (solutions) with A/C system materials and components, that may be intended for use in servicing or operation of vehicle air conditioning systems. This standard does not provide test criteria for additive, compressor lubricant, or flushing solution effectiveness; such testing is the responsibility of the additive and/or solution manufacturer/supplier. This standard does not cover additives or flushing materials for electrically driven compressors. The use of additives with electrically driven compressors might cause electrical shorting and compressor failure. It is not the intent of this document to identify the requirements for
This Aerospace Recommended Practice (ARP) establishes uniform requirements and procedures to determine the torsional strength of permanent hydraulic tube joints. It also establishes testing equipment and apparatus for torsion testing.
This SAE Aerospace Information Report (AIR) provides general guidance for design considerations and qualification in endurance, strength, and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107B.
This SAE Aerospace Standard (AS) covers the requirements for polytetrafluoroethylene (PTFE) hose assemblies for use in aerospace fuel and lubricating oil systems at temperatures between -67 and 450 °F and at operating pressures per Table 1. The hose assemblies are also suitable for use within the same temperature and pressure limitations in aerospace pneumatic systems, where some gaseous diffusion through the wall of the PTFE liner can be tolerated. Standard hose assembly configurations are defined in AS7051 through AS7056. The use of these hose assemblies in pneumatic storage systems is not recommended. In addition, installations in which the limits specified herein are exceeded, or in which the application is not covered specifically by this document, for example oxygen, shall be subject to the approval of the purchaser.
This SAE Standard covers dimensional, material, and general specifications and methods of test for two types of general purpose conical spring washers, designated type L and type H, for use as loose washers over screws and bolts, and also for use as pre-assembled washers in screw and washer assemblies.
This test method outlines the recommended procedure for performing the no-load rotational starting torque test on airframe rolling bearings. Bearings covered by this test method shall be antifriction ball bearings and spherical roller bearings.
This SAE Standard establishes a test method and a definition for disclosing the performance of suction/blower fans when applied to self-propelled sweepers that solely use a pneumatic conveyance means for the collection and transfer of “sweepings” into a collection hopper.
This SAE Recommended Practice incorporates a track-based test procedure that produces a representative value for vehicle top speed when operating on a level paved road with a fully charged battery.
This specification covers an aluminum alloy in the form of sheet and plate.
This specification covers a copper-beryllium alloy in the form of sand, investment, or centrifugal castings.
This SAE Standard defines a minimum set of acceptable safety criteria for a lithium-based rechargeable battery system to be considered for use in a vehicle propulsion application as an energy storage system connected to a high voltage power train. While the objective is a safe battery system when installed into a vehicle application, this Standard is primarily focused, wherever possible, on conditions which can be evaluated utilizing the battery system alone. As this is a minimum set of criteria, it is recognized that battery system and vehicle manufacturers may have additional requirements for cells, modules, packs and systems in order to assure a safe battery system for a given application. A battery system is a completely functional energy storage system consisting of the pack(s) and necessary ancillary subsystems for physical support and enclosure, thermal management, and electronic control.
The landing gear system is a major and safety critical airframe system that needs to be integrated efficiently to meet the overall aircraft program goals of minimizing the penalties of weight, cost, dispatch reliability and maintenance. As the landing gear system business develops and large-scale teaming arrangements and acquisitions become increasingly common, it may be desirable in some instances to procure an Integrated Landing Gear System. This document provides guidelines and useful references for developing an integrated landing gear system for an aircraft. The document structure is divided into four sections: Landing Gear System Configuration Requirements (Section 3) Landing Gear System Functional Requirements (Section 4) Landing Gear System Integrity Requirements (Section 5) Landing Gear System Program Requirements (Section 6) The landing gear system encompasses all landing gear structural and subsystem elements. Structural elements include shock struts, truck beams, torsion
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