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.
The marine environment differs greatly from other environments in which hydraulics are used. This Recommended Practice provides hydraulic design considerations and criteria for the marine environment and is applicable to commercial vessels, military ships, and submersible vehicles. This document may be used for manned and un-manned vehicles.
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 Some of the requirements that could be superseded include camera placement, optical data channel evaluation, camera to subject measurements, and scaling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 Aerospace Recommended Practice (ARP) provides recommendations for the design and test requirements for a hydraulic thermal relief valve. The thermal relief valve is intended for use in a civil or military aircraft hydraulic system with a rated system pressure up to 5000 psi (34500 kPa).
SCOPE IS UNAVAILABLE.
This aerospace recommended practice provides a framework and suggested procedures or values for requirements for the design, performance, and test of hydraulically powered servoactuators for use in aircraft flight control systems. The original version of this document was intended for military usage: consequently, the requirements still often reflect such use. However, the basic requirements of this ARP may and should be applicable to commercial usage as well, provided that appropriate considerations are given for the applicable FAR/JAR 25 regulations, hydraulic fluids, and environmental conditions.
This SAE Standard applies to hydraulic directional control valves as applied to self-propelled work machines referenced in SAE J1116. It describes a laboratory test procedure for evaluating: a Flow versus pressure drop b Leakage rate c Operating effort d Metering characteristics versus spool travel, pilot pressure, or electrical current e Relief valve characteristics The document applies to single and multiple section hydraulic directional control valves. This document illustrates axial, manually operated valves although the test procedure is applicable to other input forms such as rotary actuation, electric current, hydraulic or pneumatic pressure. Performance characteristics such as metering hysteresis or dynamic response may have a significant effect on some of these tests.
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.
This SAE Aerospace Recommended Practice (ARP) describes a method for evaluating the performance of filter elements designed for aerospace hydraulic systems. The performance is measured and reported in terms of filtration ratios and stabilized contamination levels while testing with cyclic flow.
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 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.
This document outlines the most common repairs used on landing gear components. It is not the intention of this AIR to replace overhaul/component maintenance or technical order manuals, but it can serve as a guide into their preparation. Refer to the applicable component drawings and specifications for surface finish, thickness, and repair processing requirements. This document may also be used as a guide to develop an MRB (Material Review Board) plan. The repairs in this document apply to components made of metallic alloys. These repairs are intended for new manufactured components and overhauled components, including original equipment manufacturer (OEM)/depot and in-service repairs. The extent of repair allowed for new components as opposed to in-service components is left to the cognizant engineering authorities. Reference could be made to this document when justifying repairs on landing gears. For repairs outside the scope of this document, a detailed justification is necessary
This SAE Information Report establishes procedures and terminology for measuring, calculating, and referencing the percent vehicle overlap for a case vehicle in real-world or staged end plane collisions where the end plane of the case vehicle is engaged at one of the two bumper corners but not both. This SAE Information Report may be applied to rear or front plane impacts.
This specification covers the engineering requirements and process for brush plating of tin by electrodeposition. It shall be used, in conjunction with AMS2451, for general purpose tin deposits.
This SAE Recommended Practice applies to the boomstop for the main boom of all mobile construction type cranes having rope supported booms, equipped for hook work, clamshell, magnet, grapple, or concrete bucket attachments.
This Aerospace Standard (AS) 5659/4 Physical Layer Specification provides guidance for the physical layer of optical networks which use Wavelength Division Multiplexing (WDM), within the AS5659 WDM LAN specification document family. The physical layer consists of the optical interconnections between the functional components of the network. Performance requirements for general interconnections are described. For guidance, standards are identified, corresponding to each of several environments, which describe physical layer design, installation, maintenance, and training.
This SAE Aerospace Information Report (AIR) provides data and general analysis methods for calculation of internal and external, pressurized and unpressurized airplane compartment pressures during rapid discharge of cabin pressure. References to the applicable current FAA and EASA rules and advisory material are provided. While rules and interpretations can be expected to evolve, numerous airplanes have been approved under current and past rules that will have a continuing need for analysis of production and field modifications, alterations and repairs. The data and basic principles provided by this report are adaptable to any compartment decompression analysis requirement.
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