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This recommended practice covers a stand that may be used for assembly, disassembly, and maintenance. The stand incorporates the following design criteria: complete interchangeability of any and all components, collapsible frame construction, envelope dimensions (marked with an asterisk on the attached drawings), attachment pad configuration, and gearbox and caster specifications
This specification and its supplementary detail specifications cover a chemically or mechanically expanded polyether urethane (EU) elastomeric foam material in the form of ready-to-use sheet
This specification covers a low-alloy steel in the form of welding wire
This specification covers a dry film lubricant in the form of lubricating solids dispersed in a resin binder and suitable solvents to produce a sprayable liquid
This specification covers three classes of fuel-resistant polysulfide (T) sealing compound with high strength and temperature characteristics, supplied as a two-component system which cures at room temperatures
This interface standard applies to fuzes/fuzing systems (referred to as fuzing system hereafter) in airborne weapons that use a MIL-STD-1760 type interface. It defines the powers, the discrete signals and the serial data interface for the communications at the interface between the fuzing system and the remainder of the weapon, including the weapon control unit. The Class 1 interface is an electrical only interface that facilitates use of MIL-STD-1760 type platform store interfaces for the fuze to monitor intentional release and defines the fuze interface bus communications protocol to allow sending and receiving data from fuzing systems. Class 2 interfaces add a defined connector and additional interfaces to facilitate the exchange of compatible fuzing systems. Class 3 interfaces add further interface definitions to facilitate the exchange of AS5680A compatible fuzing systems components. The bus communications protocol provides a means by which the weapon may set mission parameters
This Recommended Practice is intended to outline the design, installation, testing, and field maintenance criteria for a high temperature metal pneumatic duct system, for use as a guide in the aircraft industry. These recommendations are to be considered as currently applicable and necessarily subject to revision from time to time, as a result of the rapid development of the industry
This specification covers one grade of glass-fiber-filled polytetrafluoroethylene (PTFE) in the form of molded billets
This report provides information on the design and use of aircraft oxygen systems. It explains the physiological oxygen requirements of the human body in both a normal environment and in an hypoxic environment. It includes an overview of the continuous flow, demand and pressure demand, and liquid oxygen systems. A basic understanding of how each system operates is then specifically addressed in its own titled section. The charts, tables, and schematics provide a specific example of a theoretical oxygen system design and the calculations showing how that system would meet the regulations established by the FAR’s. A comprehensive overview of the theoretical oxygen requirements of the human body at altitude is also provided. A detailed list of specifications and standards applicable to aircraft oxygen systems is included
This SAE Aerospace Information Report (AIR) establishes a positive identification of the functions and, if applicable, the hazards and direction of flow of pipe, hose, tube, or electrical conduit lines
It is intended that the scope of this information report be limited to electrical heating of passenger, crew, and cargo compartments only. No attempt has been made to develop the complete electrical circuitry associated with the electrical heating components; however, the electrical circuitry required for heating component operation, safety, and monitoring will be included as available. Specific design information is given for various modern aircraft utilizing electrical heating. Each aircraft discussed will be identified by alphabetical letter designation and included in the appropriate appendix
This recommended practice covers a self-contained detection system which is capable of pressurizing a closed system up to 70 psig with halogen (tracer) gas and up to 3500 psig with nitrogen
This SAE Aerospace Recommended Practice (ARP) addresses the design, installation, and testing of coiled tube assemblies using Ti-3Al-2.5V cold worked, stress relieved (CWSR) tubing per AMS4945. It specifically details five different configurations of coiled tubing. The configurations detailed herein should be compatible with pressure levels up to 8000 psi (55.2 MPa) upon completion of analysis for the actual stress and life requirement of the intended application. Formal qualification tests are recommended to verify satisfactory installation, clamping, and the life of each unique design. NOTE: For information on design of coiled tube assemblies using CRES steel tubing, see ARP584
The purpose of this document is to establish the requirements for sensor/video interconnect subsystems. These requirements have been driven predominantly, but not exclusively, by aerospace-type military platforms and commercial aircraft. These requirements are intended to be used as the criteria to establish a sensor/video interconnection standard that will foster the development of common hardware to simplify the total interconnectivity of future avionics platforms
This SAE Aerospace Information Report (AIR) identifies Propulsion Engineer’s recommendations for the instrumentation that is required for the safe operation and maintenance of turbine engines as installed in helicopters. It should be used as a guide for cockpit layout, as well as a reference for maintenance considerations throughout the propulsion area. Propulsion instruments should receive attention early in the design phase of the helicopter. Maintenance and diagnostics recorders are not considered within the scope of this document. (See ARP1587, “Aircraft Gas Turbine Engine Monitoring System Guide
The report presents air conditioning data for aircraft cargo which is affected by temperature, humidity, ventilation rate and atmospheric pressure. The major emphasis is on conditioning of perishable products and warm-blooded animals. The report also covers topics peculiar to cargo aircraft or which are related to the handling of cargo
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