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.
This standard covers all types of oxygen breathing equipment used in non-military aircraft. It is intended that this standard supplements the requirements of the detail specification or drawings of specific components or assemblies (e.g., regulators, masks, cylinders, etc.). Where a conflict exists between this standard and detail specifications, detail specifications shall take precedence.
This SAE Recommended Practice establishes a uniform fluid specification for reference usage in specific documents, such as fluid power component test procedures, where a fluid designation is required.
This SAE Recommended Practice establishes a uniform fluid specification for reference usage in specific documents, such as fluid power component test procedures, where a fluid designation is required.
This document defines the requirements for polytetrafluoroethylene (PTFE) lined, para-aramid reinforced, hose assemblies suitable for use in 275 °F (135 °C), 5080 psi (35000 kPa) aircraft hydraulic systems.
This SAE Aerospace Recommended Practice (ARP) provides information and guidance for the control of hazardous laser exposure in the navigable airspace. This ARP does not address techniques that pilots can apply to mitigate laser illuminations during a critical phase of flight. Such mitigation strategies are described in ARP6378.
SCOPE IS UNAVAILABLE.
This specification, in conjunction with the general requirements for steel heat treatment covered in AMS2759, establishes the requirements and procedures for three classes of gas, vacuum, liquid, and low-pressure carburizing (LPC) and related heat treatment of parts fabricated from carburizing-grade steels. Parts made from steels other than those specified in the detail specifications may be heat treated in accordance with the applicable requirements using processing temperatures, times, and other parameters recommended by the material producer. This specification does not cover pack carburizing.
This SAE Aerospace Standard (AS) aims at identifying the design criteria and testing methods adequate to guarantee the ultimate load and operational dependability of cargo restraint strap assemblies with a typical 22250 N (5000 lbf) rated ultimate tension load capability, as used by the airline industry in order to restrain cargo on board civil transport aircraft during flight: a cargo loaded and tied down onto airworthiness certified air cargo pallets, themselves restrained into aircraft lower deck or main/upper deck cargo systems and meeting the requirements of NAS 3610 or AS36100, or b non-unitized individual pieces of cargo, or pieces of, cargo placed onto an unrestrained (“floating”) pallet into either lower deck or main deck containerized cargo compartments of an aircraft.
This document and the EUROCAE equivalent, ED-107, provides detailed information, guidance, and methods in support of the Federal Aviation Administration (FAA) Advisory Circular (AC) 20-158 and to the European Union Aviation Safety Agency (EASA) AMC 20-158. AC 20-158 provides a means, but not the only means, for demonstrating compliance with Title 14 of the Code of Federal Regulations (14 CFR) 23.1308 (Amendment 57 and lower), 23.2520 (Amendment 64 and higher), 25.1317, 27.1317, 29.1317, and applicable FAA HIRF special conditions addressing HIRF Protection. AMC 20-158 is applicable to Certification Specifications CS 23.1308 (Amendment 4 and lower), 23.2520 (Amendment 5 and higher), 25.1317, 27.1317, and 29.1317. It should be noted that this document is neither mandatory nor regulatory in nature and does not constitute a regulation or legal interpretation of the regulation. Therefore, an applicant may elect to establish an alternative method of compliance that is acceptable to the
This specification covers metric bolts and screws made from a corrosion and heat resistant, nickel-base alloy of the type identified under the Unified Numbering System as UNS N07001. The following specification designations and their properties are covered: MA3378 1210 MPa minimum ultimate tensile strength at room temperature 520 MPa stress-rupture strength at 730 °C MA3378-1 1210 MPa minimum ultimate tensile strength at room temperature 726 MPa minimum ultimate shear strength at room temperature
This standard establishes the dimensional and visual quality requirements, lot requirements, and packaging and labeling requirements for O-rings machined from AMS3668 material. It shall be used for procurement purposes.
This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, high conductive, self-bonding coupling assembly which, when installed on defined ferrules, provides a flexible connection for joining ducting and components in pressurized fluid systems. The assembled coupling is designed to provide interchangeability of parts and components between qualified manufacturers for use from -65 to +265 °F at 130 psi nominal operating pressures and for the service life of the aircraft system. FAR 23.954, FAR 25.603, FAR 25.605, FAR 25.609, FAR 25.613, FAR 25.901, FAR 25.954, and FAR 25.981 certification requirements have identified the need for high-current capable flexible fluid assembled couplings. The coupling assembly does not require inspection or maintenance to remain current capable for the life of the aircraft. This specification provides two test philosophies necessary for low-pressure couplings: 1 Electromagnetic effects/lightning testing of assembled couplings to
This specification covers a magnesium alloy in the form of sand castings.
This specification covers silicone (VMQ) rubber sheet reinforced with glass cloth.
This SAE Recommended Practice describes the test procedure for conducting a rollover test using a dolly fixture designed to laterally trip a vehicle into a roll. Its purpose is to establish a recommended test procedure which will standardize the procedure between different test facilities. A description of the test procedure, test instrumentation, photographic/video coverage, and the rollover fixture is included.
This SAE Recommended Practice establishes minimum requirements for electric hourmeters for general vehicular applications.
This specification covers the specific requirements for aluminum alloy 5454 bar, rod, shapes, tube, and wire produced by extrusion.
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