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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 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 SAE Aerospace Recommended Practice (ARP) provides design guidelines for aircraft mechanical control systems and components. Topics contained in this document include design requirements, system design and installation guidelines, and component design practices for primary flight controls, secondary flight controls, and utility controls.
This SAE Aerospace Information Report (AIR) addresses many of the significant issues associated with effects of inlet total-pressure distortion on turbine-engine performance and stability. It provides a review of the development of techniques used to assess engine stability margins in the presence of inlet total-pressure distortion. Specific performance and stability issues that are covered by this document include total-pressure recovery and turbulence effects and steady and dynamic inlet total-pressure distortion.
This document provides background information, rationale, and data (both physical testing and computer simulations) used in defining the component test methods and similarity criteria described in SAE Aerospace Recommended Practice (ARP) 6330. ARP6330 defines multiple test methods used to assess the effect of seat back mounted IFE monitor changes on blunt trauma to the head and post-impact sharp edge generation. The data generated is based on seat and IFE components installed on type A-T (transport airplane) certified aircraft. While not within the scope of ARP6330, generated test data for the possible future development of surrogate target evaluation methods is also included.
This procurement specification covers aircraft quality solid rivets and tubular end rivets made from a corrosion- and heat-resistant nickel base alloy of the type identified under the Unified Numbering System as UNS N06600.
This SAE Recommended Practice applies to all trucks that are equipped with armlift bodies, carrier bodies, wheel lift bodies, wrecker, and underlift bodies. Additional rating methods are provided for tow slings, truck hitches, and chain assemblies.
AIR5317 establishes the foundation for developing a successful APU health management capability for any commercial or military operator, flying fixed wing aircraft or rotorcraft. This AIR provides guidance for demonstrating business value through improved dispatch reliability, fewer service interruptions, and lower maintenance costs and for satisfying Extended Operations (ETOPS) availability and compliance requirements.
This document lists definitions that are commonly used in describing aircraft reciprocating engine performance.
This SAE Aerospace Recommended Practice (ARP) is written to establish tire removal criteria of on-wing civil aircraft tires only. This document is primarily intended for use with commercial aircraft, but may be used on other categories of civil aircraft, as applicable. The criteria are harmonized with the care and service manuals (CSMs) of the tire manufacturers for both radial and bias tires.
This section presents the basic equations for computing ice protection requirements for nontransparent and transparent surfaces and for fog and frost protection of windshields. Simplified graphical presentations suitable for preliminary design and a description of various types of ice, fog, frost, and rain protection systems are also presented.
This SAE Aerospace Information Report (AIR) provides various graphical displays of atmospheric variables related to aircraft icing conditions in natural clouds. It is intended as a review of recent developments on the subject, and for stimulating thought on novel ways to arrange and use the available data. Included in this Report is FAR 25 (JAR 25) Appendix C, the established Aircraft Icing Atmospheric Characterization used for engineering design, development, testing and certification of civilian aircraft to fly in aircraft icing conditions.
This specification covers sealed, self-aligning, anti-friction, rod end roller bearings operating in the temperature range of −65 to +300 °F (−54 to +149 °C) and intermittent spikes to 350 °F (177 °C).
This document outlines a standard practice for conducting system safety. In some cases, these principles may be captured in other standards that apply to specific commodities such as commercial aircraft and automobiles. For example, those manufacturers that produce commercial aircraft should use SAE ARP4754 or SAE ARP4761 (see Section 2 below) to meet FAA or other regulatory agency system safety-related requirements. The system safety practice as defined herein provides a consistent means of evaluating identified risks. Mishap risk should be identified, evaluated, and mitigated to a level as low as reasonably practicable. The mishap risk should be accepted by the appropriate authority and comply with federal (and state, where applicable) laws and regulations, executive orders, treaties, and agreements. Program trade studies associated with mitigating mishap risk should consider total life cycle cost in any decision. This document is intended for use as one of the elements of project
The recommendations of this document apply to such aircraft as are able to perform both normal angle and steep IMC approaches, the latter being defined as those approaches having a final approach segment angle greater than 4°. Such aircraft can include both conventional and STOL fixed-wing aircraft, commercial air transport and/or utility and normal category helicopters, compound helicopters and powered lift vehicles (tiltrotors, tiltfans, tiltwings, etc.).
This procurement specification covers split cotter pins with optional ends (see Figure 1), made to metric dimensions and made from a corrosion and heat resistant steel of the type identified under the Unified Numbering System as UNS S32100.
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