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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 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 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 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 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).
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 specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
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 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.
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.
This document defines the test procedures and performance limits of steady state and transient voltage characteristics for 12 V, 24 V, or 48 V electrical power generating systems used in commercial ground vehicles.
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 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 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 SAE J3161/1. For the purposes of this report, “vehicle-level requirements” primarily consist of those requirements which can be verified external to the vehicle. The IUT for these procedures is a configured LTE-V2X vehicle-to-vehicle (V2V) device as defined in SAE J3161/1 and is installed on a vehicle of class 2, 3, 4, or 5. 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 J3161/1 is satisfied. This document also includes a Traceability Matrix to
This document applies to safety observers or spotters involved with the use of outdoor laser systems. It may be used in conjunction with AS4970.
This document describes a process that may be used to perform the ongoing safety assessment for (1) GAR aircraft and components (hereafter, “aircraft”), and (2) commercial operators of GAR aircraft. The process described herein is intended to support an overall safety management program. It is associated with showing compliance with regulations and also establishing and meeting internal company safety standards. The process described herein identifies a systematic means, but not the only means, to assess continuing airworthiness. Ongoing safety management is an activity dedicated to assuring that risk is identified and properly eliminated or controlled. The safety management process includes both safety assessment and economic decision-making. While economic decision-making (factors related to scheduling, parts, and cost) is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. This ongoing safety assessment process
This SAE Standard provides minimum requirements and performance criteria for devices to prevent runaway snowmobiles due to malfunction of the speed control system.
Fulfillment of the intended purpose requires testing as follows:
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, and forging stock.
This specification covers the specific requirements for seamless tube drawn from aluminum alloy 7075.
This test plan defines the requirements of data bus components which comply with the requirements of MIL-STD-1553B, Digital Time Division Command/Response Multiplex Data Bus.
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