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This specification covers the installation of aircraft interior lighting for military aircraft.
This specification covers a manganese alloy in the form of powder, preforms, and a viscous mixture (paste) of the powder in a suitable binder.
This document provides recommendations to identify battery group sizes and dimensions for 6 V, 8 V, 12 V, and 24 V lead acid batteries.
This specification establishes the procedures used to produce a hard anodic coating on magnesium alloys and the properties of the coating.
This specification covers a corrosion-resistant steel in the form of sheet, strip, and plate.
This document outlines general requirements for the use of CFD methods for aerodynamic simulation of medium and heavy commercial ground vehicles weighing more than 10000 pounds. The document provides guidance for aerodynamic simulation with CFD methods to support current vehicle characterization, vehicle development, vehicle concept development, and vehicle component development. The guidelines presented in the document are related to Navier-Stokes and Lattice-Boltzmann based solvers. This document is only valid for the classes of CFD methods and applications mentioned. Other classes of methods and applications may or may not be appropriate to simulate the aerodynamics of medium and heavy commercial ground vehicle weighing more than 10000 pounds.
This SAE Standard applies to 12-volt lead-acid storage batteries that are designed specifically for start-stop operations in on-road passenger vehicles or light trucks. Included are definitions of terms, general testing recommendations, key performance characteristics, and life testing. Properties not unique to start-stop batteries should be tested according to SAE J537 or other applicable testing protocols.
This specification covers non-silicone synthetic rubber sealing compounds supplied as a two-component or pre-mixed and frozen (PMF) system that cures at room temperature.
This Purchasing Specification (PS), AMS3970/3, specifies the batch release and delivery requirements for carbon fiber fabric epoxy prepreg used for repair. This specification is applicable only when the carbon fiber fabric epoxy prepreg is used as part of the repair system defined in AMS3970 and AMS3970/1. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials that are qualified against AMS3970 (refer to PRI QPL AMS3970) and shall be carried out within the responsibility of the purchaser and under control of its Quality organization.
The intent of this specification is for the procurement of the material listed on the QPL; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the Quality Assurance section of the base specification, AMS6891.
The purpose of this document is to establish guidelines for determining the critical R134a and R1234yf refrigerant charge for off-road, self-propelled work machines as defined in SAE J1116 and agricultural tractors as defined in ANSI/ASAE S390. It will develop a minimum to maximum refrigerant charge range in which the HVAC system can maintain proper operation. Operating conditions and characteristics of the equipment will influence the optimum charge. Since these conditions and characteristics vary greatly from one application to another, careful consideration should be taken to determine the optimum R134a and R1234yf refrigerant charge for the HVAC system.
This SAE Aerospace Standard (AS) defines the requirements for polytetrafluoroethylene (PTFE) lined, metallic reinforced, hose assemblies suitable for use in aerospace hydraulic, fuel, and lubricating oil systems at temperatures between -67 and 450 °F for Class I assemblies, -67 and 275 °F for Class II assemblies, and at nominal pressures up to 1500 psi. The hose assemblies are also suitable for use within the same temperature and pressure limitations in aerospace pneumatic systems where some gaseous diffusion through the wall of the PTFE liner can be tolerated. The use of these hose assemblies in pneumatic storage systems is not recommended. In addition, installations in which the limits specified herein are exceeded, or in which the application is not covered specifically by this standard (for example, oxygen), shall be subject to the approval of the procuring activity.
This SAE Standard provides general and dimensional specifications for beaded ends and hose fittings. These connections are intended for general applications in low-pressure automotive and hydraulic systems on automotive, industrial, and commercial products. The fittings shown are designed to be used with hoses that are intended to be retained by hose clamps. It is recommended that where step sizes or additional types of fittings are required they be designed to conform with the specifications of this document insofar as they may apply. The following general specifications shall supplement the dimensional data contained in the tables with respect to all unspecified detail.
The intent of this specification is for the procurement of carbon fiber and fiberglass epoxy prepreg products with 350 °F (177 °C) cure for aerospace applications; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the production quality assurance section (see 4.3) of this base specification, AMS6891.
This specification covers a titanium alloy in the form of extruded bars, tubes, and shapes, flash-welded rings up through 4.000 square inches (25.81 cm2) cross section, and stock for flash-welded rings (see 8.6).
This Purchasing Specification (PS) AMS3970/4 specifies the batch release and delivery requirements for film adhesive used for repair. This specification is applicable only when the film adhesive is used as part of the prepreg system as defined in AMS3970 and AMS3970/1. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials which are qualified and shall be carried out within the responsibility of the purchaser and under control of its Quality organization.
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS3970/2B gives specific information about the qualification program for carbon fiber fabric reinforced epoxy structural repair prepreg systems, curing under vacuum at 120 °C (250 °F), and a companion non-structural glass fabric prepreg used for repair of carbon fiber reinforced epoxy structures. The prepreg system shall include an epoxy film adhesive to be applied in a co-curing process with the prepreg for joint solid laminate and sandwich bonding.
This specification covers a corrosion- and heat-resistant nickel alloy in the form of bars, forgings, flash-welded rings under 4 inches (102 mm) in least cross-sectional dimension, and stock of any size for forging or flash-welded rings (see 8.3).
This Purchase Specification (PS), AMS3970/5, specifies the batch release and delivery requirements for the companion non-structural glass fiber fabric prepreg. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials which are qualified and shall be carried out within the responsibility of the purchaser and under control of its Quality organization.
This SAE Aerospace Recommended Practice (ARP) provides recommendations for the development of aircraft and systems, taking into account aircraft functions and operating environment. It provides practices for ensuring the safety of the overall aircraft design, showing compliance with regulations, and assisting a company in developing and meeting its own internal standards. These practices include validation of requirements and verification of the design implementation for safety, certification, and product assurance. The guidelines in this document were developed in the context of U.S. Title 14 Code of Federal Regulations (14 CFR) Part 25 and European Union Aviation Safety Agency (EASA) Certification Specification (CS) CS-25. They may be applicable in the context of other regulations, such as 14 CFR Parts 23, 27, 29, 33, and 35, and CS-23, CS-27, CS-29, CS-E, and CS-P. This document addresses the development cycle for aircraft and systems that implement aircraft and system functions. It
This document establishes training guidelines applicable to fiber optic installer technical training for individuals involved in the manufacturing, installation, support, integration and testing of fiber optic systems. Applicable personnel include: Managers Engineers Technicians Trainers/Instructors Third Party Maintenance Agencies Quality Assurance Production
The purpose of this SAE Aerospace Information Report (AIR) is two-fold: to inform the reader of the extent of effort that went into the development of the Joint Architecture for Unmanned Systems (JAUS); and to capture for posterity the domain analysis that provides the underpinnings for the work by the AS-4 Committee (Unmanned Systems).
This document defines the steps and documentation required to perform a digital fiber optic link loss budget. This document does not specify how to design a digital fiber optic link. This document does not specify the parameters and data to use in a digital fiber optic link loss budget.
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 establishes the requirements for flake or granular cetyl alcohol, solvents for dissolving the cetyl alcohol, preparation and application requirements for use of cetyl alcohol as an installation lubricant on mechanical fasteners, such as pins, bolts, nuts, washers, threaded or nonthreaded fastening devices, and inspection criteria for coated parts.
This specification covers a corrosion-resistant steel in the form of wire.
This SAE Aerospace Standard (AS) establishes the requirements for fluid fittings that combine both flareless and pipe threaded connections for use in all types of fluid systems.
This SAE Standard was developed to provide a method for indicating the direction of engine rotation and numbering of engine cylinders. The document is intended for use in designing new engines to eliminate the differences which presently exist in industry.
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.
This SAE Recommended Practice is intended to cover plastic safety glazing for use in motor vehicles and motor vehicle equipment. Nominal specifications for thickness, flatness, curvature, size, and fabrication details are presented principally for the guidance of body engineers and designers. For additional information on plastic safety glazing materials for use in motor vehicles and motor vehicle equipment, please refer to SAE J673.
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