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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 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 document establishes the requirements for screw-on type reattachable couplings for use in low temperature hose assemblies.
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 specification covers a corrosion and heat resistant iron alloy in the form of covered welding electrodes.
This SAE Information Report applies to the control circuits and devices associated with the electrical propulsion system used on electric drive dumpers. Dumper is defined in J/ISO 6165. The document does not apply to auxiliary equipment control systems such as: a Battery charging systems b Engine wiring and control c Monitoring and control circuits not directly affecting the operation of the electric propulsion and retarding system d Lighting e Accessory systems (heating, air conditioning, horns, radios, emergency steering, fire protection, and similar functions).
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
Document provides information on how military/commercial/gas turbine engine test cell/system users may benefit from this unique Coanda/Refraction concept.
SCOPE IS UNAVAILABLE.
This specification covers an aluminum alloy in the form of castings (see 8.10).
This SAE Information Report discusses the significant factors which measure the effectiveness of the total occupant restraint system in commonly encountered collision configurations. The total system includes the components which affect occupant injury by influencing the manner in which the collision energy management is accomplished. In addition to the elements that contribute to impact attenuation, consideration must be given to factors that encourage maximum use, such as comfort, reliability, appearance, and convenience. Hence, system evaluation necessarily involves consideration of the complete vehicle.
This specification covers a silver alloy in the form of wire, rod, sheet, strip, foil, pig, powder, shot, and chips and a viscous mixture (paste) of powder in a suitable binder.
This report lists documents that aid and govern the design, development, certification, and utilization of aerospace electronic engine control systems. The report lists the military and industry specifications and standards that are commonly used in electronic engine control system design. Also included are Airworthiness Authority documents and requirements associated with certification. However, these lists are not necessarily complete. The specifications and standards section has been divided into two parts: a master list, and a categorized list that provides a functional breakdown and cross-reference of these documents. For specifications and standards, the issue available during the latest revision to this document is listed. Details of current revisions for many documents are available in the Department of Defense Index of Specifications and Standards (DODISS). It should be noted that not all of these documents are referenced or even recognized by all certification authorities. In
This document provides the specifications of horizontal hard-bearing balancing machines, which make such machines suitable for gas turbine rotor balancing.
This SAE Aerospace Standard (AS) defines the overall requirements applicable to oxygen flow indication as required by Airworthiness Requirements of CS/FAR 25.1449 to show that oxygen is being delivered to the dispensing equipment. Requirements of this document shall be applicable to any type of oxygen system technology and encompass “traditional” pneumatic devices, as well electric/electronic indication.
This standard defines a system for the qualification of standard products for aviation, space, and defense applications. It defines the principles that shall be adhered to when carrying out product qualification; applied in conjunction with the rules and procedures of the CA. The system enables the CA to confirm compliance is achieved and maintained, in accordance with the requirements of its product definition and associated controlling technical specifications by an Original Component Manufacturer (OCM) of standard products. This standard requires an OCM that has been granted product qualification approval to ensure applicable approvals are maintained and renewed in accordance with the CA’s quality system for that qualified product. OCMs and OCM designated Value Added Distributors (VADs) requesting product qualification to this standard, shall as a prerequisite, maintain 9100 standard quality management system certification approval. This certification shall be visible in the Online
This SAE Standard defines a method for evaluating the immunity of automotive electrical/electronic devices to radiated electromagnetic fields coupled to the vehicle wiring harness. The method, called bulk current injection (BCI), uses a current probe to inject RF onto the wiring harness in the frequency range of 1 to 400 MHz. BCI is one of a number of test methods that can be used to simulate the electromagnetic field. The test method refers to ISO 11452-4 (please refer to ISO 11452-4 for test procedures). In addition to ISO 11452-4, this test method also includes a differential bulk current injection (DBCI) test. DBCI is described in Section 4 of this document.
This document provides vehicle-level data collection, data analysis, and data verification procedures that may be used to verify that an instrument under test (IUT) satisfies the vehicle-level requirements specified in the SAE International (SAE) J2945/1 standard. For the purposes of this recommended practice, “vehicle-level requirements” primarily consist of those requirements which can be verified external to the vehicle. The IUT for these procedures is a configured dedicated short range communications (DSRC) vehicle-to-vehicle (V2V) device as defined in SAE J2945/1 and is installed on a light vehicle. While the IUT is conceptually separated from the vehicle it is installed on, the tests outlined in this document are primarily vehicle-level so the terms “vehicle” and “IUT” can generally be considered interchangeable. Additionally, non-vehicle-level complementary tests, not included in this document, are required to verify that the entire set of requirements specified in SAE J2945/1
This document provides guidance concerning the maintenance and serviceability of oxygen cylinders beginning with the quality of oxygen that is required, supplemental oxygen information, handling and cleaning procedures, transfilling, and marking of serviced oxygen assemblies. This document attempts to outline in a logical sequence oxygen quality, serviceability, and maintenance of oxygen cylinders. Content of this document can also be used for refilling oxygen cylinders while installed on aircraft, directly or through an intermediate charging port.
The accompanying mounting and gear locations are applicable for all general installations of power take-off on the transmission gear box of motor trucks and tractors where the size of the transmission permits. The heavy-duty type opening can be adapted to the regular-duty type by the use of an adapter with 6.35 mm (0.25 in) flange thickness with appropriate bolt pattern and thread engagement. (See Figures 1 and 2.)
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