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This technical report documents three surveys to determine realistic vibration requirements for skid control systems specifications and obtain updated vibration information for locations in aircraft where skid control system components are mounted.
A-5A Wheels, Brakes and Skid Controls Committee
This specification covers the design and performance requirements for a single axis, four load-factor level counting accelerometer group referred to hereafter as “equipment.”
A-4 Aircraft Instruments Committee
This specification established the requirements for a 5 second duration, 4500 pound thrust (when determined at 60°F) solid propellant rocket engine hereinafter specified as 5 S-4500.
Aerospace Council
The complete specification for a pneumatic pressure reducer for high pressure pneumatic systems used in missiles comprises: (1) this standard, which includes many of the general performance requirements, (2) a detailed procurement specification describing envelope and operating conditions, and (3) the "Pneumatic Components, Aeronautical - General Specification For - MIL-P-8564" which covers general requirements common to all components for use in high pressure pneumatic systems.
A-6C5 Components Committee
This specification covers a silicone rubber in the form of a two-component liquid compound.
AMS G9 Aerospace Sealing Committee
This specification covers one type of fuel pressure transmitter designated MS28005-7.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
This document establishes the requirements for aircraft, hydraulic couplings, self-sealing one side only, for use in Type II hydraulic systems (-65 to +275 °F temperature range) as defined by MIL-H-5440. The purpose being to connect a hose or tube to a standard MS33656, MS33514, or MIL-F-85421, or MIL-F-85720 fitting, and to provide the self-sealing feature on the hose or tube side of the connection.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This aerospace standard (AS) defines the requirements of portable protective breathing equipment for use during smoke/fire conditions on board an aircraft.
A-10 Aircraft Oxygen Equipment Committee
This SAE Aerospace Recommended Practice (ARP) covers the general requirements and test procedures for illuminating systems for integrally lighted aircraft instruments in order to provide (a) uniformity of illumination within each instrument, (b) legibility of instrument presentation under daylight or integral light, and (c) uniformity of illumination between instrument displays.
A-20A Crew Station Lighting
This AS defines components in "Capacitance Sensor" and "Non-Capacitance Sensor" type Fuel and Oil Quantity Indicating Systems. "Non-Capacitance" systems may employ any measurement technique current in the art including, but not restricted to, float, ultra-sonic and fiber optic devices. The definition of the individual components contained herein is related to the specified Total Installed System accuracy of the entire Fuel or Oil Quantity Indicating System which is a part of the airframe manufacturer's type certification approval data. This data shall be available from the subject airframe manufacturer as published in the operating manual for the aircraft type, model number and configuration. The Fuel or Oil Quantity Indicating System may incorporate optimum compensation based upon measurement of dielectric constant, temperature or density to correct for variations in fuel or oil characteristics due to temperature grade variations or additives. Examples of the type of components
A-4 Aircraft Instruments Committee
This document specifies dimensional, functional and visual requirements for Automotive grade coaxial cable. This material will be designated AG for general-purpose automotive applications or AG LL for low loss applications. It is the responsibility of the user of this cable to verify the suitability of the selected product (based on dimensional, mechanical, electrical and environmental requirements) for its intended application. It is the responsibility of the supplier to retain and maintain records as evidence of compliance to the requirements detailed in this standard.
USCAR
SAE J1717 is an advisory document suggesting minimum recommended testing, appearance evaluation, and protocol for specifying the recommendations with regard to Singular Unassembled Automotive Interior Trim Parts.
Plastics Committee
The scope of this Recommended Practice encompasses the range of environments which influence the performance and reliability of the electronic equipment designed for heavy duty on and off road vehicles, as well as any appropriate stationary applications which also use these vehicle derived components. A few examples of such vehicles are on and off highway trucks, trailers, buses, construction equipment, and agricultural equipment including implements.
Truck and Bus Electrical Systems Committee
This Aerospace Recommended Practice (ARP) covers a brief discussion of the icing problem in aircraft fuel systems and different means that have been used to test for icing. Fuel preparation procedures and icing tests for aircraft fuel systems and components are proposed herein as a recommended practice to be used in the aircraft industry for fixed wing aircraft and their operational environment only. In the context of this ARP, the engine (and APU) is not considered to be a component of the aircraft fuel system, for the engine fuel system is subjected to icing tests by the engine/APU manufacturer for commercial and specific military applications. This ARP is written mostly to address fuel system level testing. It also provides a means to address the requirements of 14 CFR 23.951(c) and 25.951(c). Some of the methods described in this document can be applied to engine and APU level testing or components of those application domains. This revision does not completely address new
AE-5A Aerospace Fuel, Inerting and Lubrication Sys Committee
This SAE Aerospace Standard (AS) covers the requirements for a flexible, lightweight, low pressure, self-extinguishing, integrally heated silicone hose assembly. The hose has a fully fluorinated fluoropolymer inner liner and is primarily intended for use in aircraft potable water systems with an environmental operating temperature range of -65 °F (-54 °C) to +160 °F (+71 °C).
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This specification covers the general requirements for integrally illuminated information panels.
A-20A Crew Station Lighting
The scope of this document is to define a test method for performing the Compression Stress Relaxation (CSR) Test with the Automotive Standard (ASD) CSR Jig using the appropriate test fixtures, configurations and procedures. This standard defines the equipment needed, guidelines for running the test, and the format for generating the results and analyzing the data.
Committee on Automotive Rubber Specs
All automatic altitude reporting digitizer equipment manufactured under this standard shall comply with the requirements as specified up to its maximum range as indicated on the equipment nameplate.
A-4 Aircraft Instruments Committee
The purpose of this document is to serve as a resource to aerospace designers who are planning to utilize Wavelength Division Multiplexed (WDM) interconnects and components. Many WDM commercial systems exist and they incorporate a number of existing, commercially supported, standards that define the critical parameters to guide the development of these systems. These standards ensure interoperability between the elements within these systems. The commercial industry is motivated to utilize these standards to minimize the amount of tailored development. However, since some of the aerospace parameters are not satisfied by the commercial devices, this document will also try to extend the commercial parameters to those that are necessary for aerospace systems. The document provides cross-references to existing or emerging optical component and subsystem standards. These parameter definitions, test methods, and procedures typically apply to telecommunications application and in some cases
AS-3 Fiber Optics and Applied Photonics Committee
This specification gives general requirements for electric devices for which the detail requirements are given by standards only, as the detail requirements for the devices are not complex enough to warrant issuance of detail specifications for them.
AE-7 Aerospace Electrical Power and Equipment Committee
This specification covers ground type hydropneumatic pressure accumulators for use in ground support hydraulic systems at rated pressures ranging up to 5,000 psi including details pertinent to the design, fabrication, and performance of the accumulators.
A-6C4 Power Sources Committee
This Aerospace Recommended Practice provides general requirements for Electrohydrostatic Module (EHM) that is used in Electrohydrostatic Actuator (EHA) for aerospace applications. This document includes design, performance and test (production and qualification) requirements.
A-6B2 Electrohydrostatic Actuation Committee
This Recommended Practice provides a guide for specifying general design, performance, and test requirements for power drive units (PDUs) for flight controls and other applications.
A-6B3 Electro-Mechanical Actuation Committee
This SAE Standard defines the general requirements and provides a system for the control of quality for conformal coatings suitable for application to printed circuit assemblies.
AMS G8 Aerospace Organic Coatings Committee
This SAE Aerospace Standard (AS) establishes the minimum performance standards for equipment used as secondary alternating current (AC) electrical power sources in aerospace electric power systems.
AE-7B Power Management, Distribution and Storage
This specification covers a silicone rubber in the form of a two-component liquid.
AMS G9 Aerospace Sealing Committee
This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs.
E-36 Electronic Engine Controls Committee
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.
AC-9 Aircraft Environmental Systems Committee
This document provides details of test methods that should be taken into consideration when qualifying fiber optic termini to the product specifications (slash sheets). The product specifications (slash sheets) provide pass/fail criteria, optical and physical intermatability, and interoperability requirements for fiber optic termini in circular, rectangular, and modular type aerospace connectors.
AS-3 Fiber Optics and Applied Photonics Committee
This specification covers the design requirements and all performance requirements for procurement of 1 7/8 inch dial pilot’s standby compasses as specified herein.
A-4 Aircraft Instruments Committee
The AS8050 master document contains general information for qualification of aerospace fiber optic, circular, modular, and rectangular connectors as part of a fiber optic interconnect assembly comprising of a connector, fiber optic cable, and fiber optic terminus. The product specifications (slash sheets) contain dimensional, mechanical, and operating performance requirements for aerospace fiber optic, circular, and rectangular connectors. The product specifications (slash sheets) reference associated aerospace fiber optic termini and cables suitable for use with AS8050 connectors.
AS-3 Fiber Optics and Applied Photonics Committee
This specification establishes the common requirements for variable delivery electric motor driven, hydraulic pump units, suitable for use in aircraft hydraulic systems.
A-6C4 Power Sources Committee
This specification establishes the design, performance, and test requirements for hydraulic flow rate fuses intended to be used for hydraulic circuit protection on aircraft.
A-6C5 Components Committee
This specification covers an optical-quality, transparent, polycarbonate plastic, to which a hard protective surface coating has been applied, supplied in the form of flat sheet or formed parts made from flat sheet.
AMS P Polymeric Materials Committee
The scope of this HIR is to specify general oceanographic environments. Specific environmental requirements shall be specified in a detail specification. Specific requirements are in the state of constant flux because the ocean environment is constantly changing and the changes occur not only on a seasonal basis but also monthly, weekly, daily, and in some cases even hourly. This HIR is to be used as a guide only.
Fluid Power Utilization
This Aerospace Standard (AS) covers the general minimum performance standards for generators/starter-generators and associated voltage regulators for use in direct current (DC) electric systems for civil aircraft.
AE-7A Generators and Controls Motors and Magnetic Devices
This specification establishes the requirements for a probe type self-sealing, self-aligning, non-locking coupling intended for aerospace hydraulic and cooling systems.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This document defines the requirements for a threadless, flexible, self-bonding coupling assembly, which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent, or other systems. This assembled coupling, hereafter referred to as the assembly, is designed for use from -54 to 204 °C and at 862 kPa operating pressure. AS coupling components referenced herein have been qualified to AS1650. Ferrules referenced herein are inch ferrules adapted to metric tubing.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This publication is applicable to liquid cooling systems of the closed loop type and the expendable coolant type in which the primary function is transporting of heat from its source to a heat sink. Most liquid cooling system applications are oriented toward the cooling of electronics. Liquid cooling techniques, heat sinks, design features, selection of coolants, corrosion control, and servicing requirements for these systems are presented. Information on vapor compression refrigeration systems, which are a type of cooling system, is found in Reference 1.
AC-9 Aircraft Environmental Systems Committee
This standard covers oronasal type masks which use a continuous flow oxygen supply. Each such mask comprises a facepiece with valves as required, a mask suspension device, a reservoir, or rebreather bag (when used), a length of tubing for connection to the oxygen supply source, and a means for allowing the crew to determine if oxygen is being delivered to the mask. The assembly shall be capable of being stowed suitably to meet the requirements of its intended use.
A-10 Aircraft Oxygen Equipment Committee
This SAE Aerospace Standard (AS) establishes the general requirements for a miniature probe type self-sealing, self-aligning, non-locking coupling intended for aerospace liquid cooling systems. The AS5072/slash sheets define the specific performance and dimensional requirements.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This Performance Standard covers the Qualification Test Requirements for separable fittings, permanent fittings, and tubing suitable for use in 8000 psi aerospace fluid power systems. The standard treats each of these elements as part of a “system” in which each element has a specific critical relationship one to the other This document is applicable to both the pressure (8000 psi) and the return (4000 psi) portions of an 8000 psi rated system. Rationale for tests, testing philosophy, and key words are covered in Sections 5 and 6.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This specification covers electrical connections made with single, solid, round copper or copper alloy wire wrapped around copper alloy terminals without the use of solder.
AMS B Finishes Processes and Fluids Committee
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