Results
This method is intended to evaluate the thermal and oxidative stability of synthetic, ester-based aviation lubricants under defined conditions of time and temperature. This method is applicable to lubricants meeting the compositional and performance requirements of AS5780.
Long wave ultraviolet or UV-A irradiation (between 320 and 400 nm) is used for fluorescent inspections in magnetic particle and liquid penetrant examinations. UV-A irradiation is obtained from either LED, fluorescent, or high intensity discharge lamps that are stationary or portable. Commercially available UV-A lamps possess a large variation in intensity output that may introduce a legitimate concern for possible health hazards. This document reviews the nature of UV-A irradiation emitted by lamps and acceptable UV dosage limits adopted by the American Conference of Governmental Industrial Hygienists (ACGIH®) and European Union and recommendation of proper practices when working with UV-A irradiation.
This specification covers the installation of aircraft interior lighting for military aircraft.
This specification covers the engineering requirements for finishing aircraft parts and assemblies with an engine gray enamel.
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 specification covers a two-component adhesive compound, an epoxy resin base and a hardener, in the form of a paste.
Recent field experience has indicated significant problems with some types of wire and cables as routed on aircraft landing gear. This SAE Aerospace Information Report (AIR) is intended to identify environmental concerns the designer should consider, materials that appear to be most suitable for use in these areas, routing, clamping, and other protection techniques that are appropriate in these applications. In recent years aircraft certification regulatory agencies introduced new regulations regarding Electrical Wiring Interconnection Systems (EWIS) to further enhance safety of the associated systems and aircraft overall.
This specification covers the specific requirements for aluminum alloy 7178 bar, rod, shapes, tube, and wire produced by extrusion.
The technical architecture defined in this document outlines mandatory, emerging, and needed standards to provide interoperability at key interfaces in the aircraft/store system (including an associated NATO Network Enabled Capability environment), as required to support a future plug-and-play aircraft/store integration capability. These standards relate to services and protocols associated with the subject interfaces. Modeling standards to facilitate the Model Driven Architecture® (MDA®) approach to system definition and implementation are also included. Note that the status of referenced standards as reflected in this document is as of August 2007, and document users should check to see if there has been a subsequent change of status relative to applicable standards.
This specification covers a two-component compound, an epoxy resin base and a hardener, in the form of a paste.
This specification covers a corrosion and heat-resistant steel in the form of sheet, strip, and plate.
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.
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.
The supplier shall use the following process to respond to a customer request for corrective and preventive action.
Primarily to provide recommendations concerning minimizing stress-corrosion cracking in wrought titanium alloy products.
This document provides a recommended electrical performance testing guideline for LIBM, which makes up an xEV (Battery Electric Vehicles and Hybrid Electric Vehicles) battery pack system. This testing guideline may also be used for other applications, such as stationary, vessel, and aircraft. However, using the guideline for other applications should be determined by the users of this document. Users of this document may also be interested in conducting tests on battery cells and/or battery packs. To avoid conducting potentially redundant tests between cells, modules, and packs, this document does not specify which tests need to be conducted. Determination of which tests need to be conducted is at the user’s discretion and should be based on individual module applications. Rather than specifying which tests need to be conducted, this document describes how each test is to be conducted. This document provides a matrix of tests that can be selectively picked for the application
This SAE Aerospace Recommended Practice (ARP) defines the test set-up requirements, general analysis procedures, and test report documentation for impact tests where photometric analysis of the high speed film or digital video will be required to obtain target paths (typically the Anthropomorphic Test Dummy (ATD) head path and knee path). Such tests support the requirements of AS8049 - Performance Standard for Seats in Civil Rotorcraft, Transport Aircraft and General Aviation Aircraft. These setup and analysis procedures are applicable to conventional, geometry based, two-dimensional analysis. If a more sophisticated technique that allows cameras to be installed at oblique angles for two or three-dimensional analysis is used, then the specific procedures required by that technique supersede any conflicting procedures contained herein. Some of the requirements that could be superseded include camera placement, optical data channel evaluation, camera to subject measurements, and scaling
This specification covers a two-component silicone rubber sealant and compatible primers.
This SAE Recommended Practice covers a procedure for evaluating plastic and multiple-layer coatings exposed to gravelometer testing (as defined in SAE J400) with an optical imaging and analysis system. The intent of the procedure is to detect, count and characterize instances of damage in the coated surface that fracture the top coat layer or penetrate through multiple layers of the coating system. It may be possible to extend this methodology of coating damage evaluation to specimens that have undergone test procedures or exposures that produce similar, discrete damage sites in the coating system. If so applied, evaluation results must be interpreted with respect to the limitations and intent implied by the original evaluation procedure and its associated rating system, if applicable.
This specification covers an adhesive compounded from modified epoxy resins in ready-to-use film supplied in rolls or sheets, either supported by mat or by woven monofilaments or unsupported.
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 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.
This specification covers the specific requirements for 2124 aluminum alloy plate for intended use in the -T851 temper; the general requirements are covered in AMS-QQ-A-250.
Items per page:
50
1 – 50 of 222094