Results
This SAE Aerospace Recommended Practice (ARP) recommends a methodology to be used for the design, analysis and test evaluation of modern helicopter gas turbine propulsion system stability and transient response characteristics. This methodology utilizes the computational power of modern digital computers to more thoroughly analyze, simulate and bench-test the helicopter engine/rotor system speed control loop over the flight envelope. This up-front work results in significantly less effort expended during flight test and delivers a more effective system into service. The methodology presented herein is recommended for modern digital electronic propulsion control systems and also for traditional analog and hydromechanical systems.
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 document establishes the requirements for screw-on type reattachable couplings for use in low temperature hose assemblies.
This SAE Surface Vehicle Technical Information Report, SAE J2836/4, establishes diagnostic use cases between plug-in electric vehicles (PEV) and the electric vehicle supply equipment (EVSE). As PEVs are deployed and include both plug-in hybrid electric (PHEV) and battery electric (BEV) vehicle variations, failures of the charging session between the EVSE and PEV may include diagnostics particular to the vehicle variations. This document describes the general information required for diagnostics and SAE J2847/4 will include the detail messages to provide accurate information to the customer and/or service personnel to identify the source of the issue and assist in resolution. Existing vehicle diagnostics can also be added and included during this charging session regarding issues that have occurred or are imminent to the EVSE or PEV, to assist in resolution of these items.
The primary objective of this document is to describe the systematic and random measurement uncertainties which may be expected when testing gas turbine engines in a range of different test facilities. The documentation covers a "traditional" method for estimating pretest uncertainties and a "new" method for computing and comparing posttest uncertainties. To determine these posttest uncertainties, data generated during the AGARD Uniform Engine Test Program (UETP) were analyzed and compared to the pretest estimates. The proposed procedure provides a mechanism for determining the expected accuracy of test results obtained from facilities which were not previously cross calibrated. Furthermore, the method can be used to assist in making cost-effective management decisions on the level of validation/cross calibration necessary when bringing a test facility on line. This document is also intended to act as a guide for improving uncertainty analyses in a broad spectrum of related industries
The primary purpose of the shipping closure is to protect the aircraft parts or system from damage and foreign material ingress/egress (e.g., dust, dirt or other contaminants) during transport and storage. Shipping closures are not airworthy items. Therefore, their usage is defined as preventative for the parts to be protected as opposed to operational. Military and commercial customer requirements for the prevention of damage or contamination to stored parts are generally limited to the generic instructions “all openings should be sufficiently covered to prevent the entrance of dust, dirt, moisture or other foreign contaminants”. This recommended practice outlines basic minimum parameters for suggested item construction and usage. Additionally, this recommended practice provides instruction on how to apply these closures to various openings.
This procurement specification covers tubular-shaped, coiled spring pins made of a corrosion resistant nickel base alloy of the type identified under the Unified Numbering System as UNS N07718.
This specification defines the requirements for a grooved clamp coupling and flanges suitable for joining intermediate pressure and temperature ducting in aircraft air systems. The rigid coupling joint assembly, hereafter referred to as "the joint", shall operate within the temperature range of -65 °F to +800 °F.
This specification covers a corrosion-resistant steel in the form of sheet, strip, and plate 4.0 inches (102 mm) and under in nominal thickness (see 8.5).
This SAE Aerospace Information Report (AIR) provides information on aircraft cabin air quality, including: Origins of chemical airborne contaminants during routine operating and failure conditions. Exposure control measures, including design, maintenance, and worker training/education. This AIR does not deal with airflow requirements.
This specification covers a fluorocarbon (FKM) rubber in the form of O-rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications. For sheet, strip, tubing, extrusions, and molded shapes use the AMS3353 specification which is intended for that use.
Scope is unavailable.
This specification covers coated round rods fabricated by the pultrusion process from aramid fibers and a weather-resistant polyester resin binder in the form of straight lengths or in coils.
The focus of this SAE Aerospace Standard (AS) is the integration of thermally actuated pressure release devices, hereafter referred to as fuse plugs, with the wheel and brake assembly. It does not address the manufacturing, quality or acceptance test requirements pertaining to the production of these fuse plugs. It establishes minimum design, installation, qualification, and operational requirements for fuse plugs which are used only in tubeless tire type aircraft braked wheels. Fuse plugs are designed to completely release the contained inflation pressure from a tubeless tire and wheel assembly when brake generated heat causes the tire or wheel to exceed a safe temperature level. The objective is to prevent tire or wheel rupture due to brake generated heat that could cause an unsafe condition for personnel or the aircraft. (Reference: U.S. Department of Transportation FAA Advisory Circular No. 23-17C; Title 14, Code of Federal Regulations (14 CFR) Part 25.735 (j); U.S. Department of
This specification covers a 100% homopolymer of polychlorotrifluoroethylene, (PCTFE) in the form of thin wall tubing.
This specification covers a silicone rubber in the form of a two-component liquid compound.
This SAE Standard presents a test procedure for determining the airborne sound insulation performance of materials and composite layers of materials commonly found in mobility, industrial, and commercial products under conditions of representative size and sound incidence so as to allow better correlation with in-use sound insulator performance. The frequency range of interest is typically 100 to 10000 Hz 1/3-octave band center frequencies. This test method is designed for testing flat samples with uniform cross section, although in some applications the methodology can be extended to evaluate formed parts, pass-throughs, or other assemblies to determine their acoustical properties. For non-flat parts or assemblies where transmitted sound varies strongly across the test sample surface, a more appropriate methodology would be ASTM E90 (with a reverberant receiving chamber) or ASTM E2249 (intensity method with an anechoic or hemi-anechoic receiving chamber).
This specification covers coated round rods manufactured by the pultrusion process from glass fiber roving and a weather-resistant polyester resin binder in the form of straight lengths or in coils.
SCOPE IS UNAVAILABLE.
This specification covers a corrosion and heat-resistant alloy in the form of sheet, strip, and plate 2.00 inch (50.8 mm) and under in thickness (see 8.4).
This SAE Aerospace Standard (AS) covers the general requirements for the design, manufacture, and test of 28 VDC, 270 VDC, and 115 VAC solid-state power controllers (SSPCs) for use in electrical power systems. SSPCs conforming to this standard are intended for use in controlling the making and breaking of power circuits for electrically operated equipment and devices, and for providing overload and short-circuit protection. Applications that require SSPCs to have a high level of performance in some areas or may be exposed to harsher electrical or environmental conditions are designated as CLASS A. Applications that utilize SSPCs in moderate level of performance or are exposed to a controlled environment are designated as CLASS C. Applicability of both MIL-STD-704 and RTCA DO-160G have been considered when determining the performance standards for the designated classes of SSPCs. To support older aircraft platforms, legacy versions of these specifications were also considered as
This document establishes the Rotorcraft Industry Technology Association (RITA) Health and Usage Monitoring System Data Interchange Specification. The RITA HUMS Data Interchange Specification will provide information exchange within a rotorcraft HUMS and between a rotorcraft HUMS and external entities.
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