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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
This SAE Recommended Practice provides a system for marking thermoset rubber parts to designate the general type of material from which the part was fabricated.
This specification covers crimp-style aluminum lug terminals and conductor splices for aluminum aircraft wire. Lug terminals and conductor splices are hereafter called “terminals.”
This document specifies performance and quality requirements for the qualification and manufacture of 24 degree cone fittings to ensure reliable performance in aircraft hydraulic systems. This document specifies baseline criteria for the design and manufacture of system fittings that are qualification tested on engines. This document covers fittings of temperature types and pressure classes specified in MA2001.
This brief User Guide recaps the content of the AS6518B UCS Architectural Model. The purpose of the UCS Architecture Model is to provide the authoritative source for other models and products within the UCS Architecture as shown in the AS6512B UCS Architecture: Architecture Description.
This SAE Aerospace Information Report (AIR) presents a review of the types and general characteristics of power sources that may be used to provide the power for gaseous or liquid fluidic control systems. Fluidic definitions, terminology, units and symbols are defined in Reference 2.1.1.
This recommended practice covers the requirements and qualification tests for two types of flexible all-metal hose assemblies intended for hydraulic use on missile and rocket applications at rated pressures of 4000 psi. Type I -65° to +650 °F service temperature range Type II -65° to +1000 °F service temperature range
This Aerospace Recommended Practice is applicable to the design of remote indicating magnetic chip detectors installed in the lube systems, hydraulic systems, controls systems, gearboxes, constant speed drives, etc. of Aerospace Power Plants. It is not applicable to the touch-to-test type terminal models.
Much of the available long-term storage test data has been reviewed and topically separated to enable the independent discussion of storage effects on fluids, seals, hydraulic components, and hydraulic systems. Comments are made in Section 4 concerning the applicability of the test results and regarding design practices for storability. Conclusions are drawn in Section 5 regarding inactive storage of hydraulic systems for at least a 7 year period.
This SAE Aerospace Information Report (AIR) has been compiled to provide information on hydraulic systems fitted to commercial aircraft. Data has been provided for following aircraft types: a Wide body jet airliners b Narrow body jet airliners c Turboprop/commuter aircraft d Business jet aircraft The airliners that have been included in this document are generally in operational service with either airlines or cargo operators. Information on aircraft that have been retired from in-service use has been included for reference purposes. No information is presented for aircraft that are currently being developed. The following information is provided for each aircraft Design requirements: Governing airworthiness regulations System pressure: Fluid power system operating pressure Hydraulic fluid: Type of fluid the hydraulic system uses Number of hydraulic systems: Number and identification of independent hydraulic systems System temperature: Minimum and maximum design operating temperatures
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.
SAE TA-HB-0007-1A is an integral part of the following suite of documents, which are meant to be used together: SAE TA-STD-0017A, Product Support Analysis, SAE GEIA-STD-0007C, Logistics Product Data, SAE GEIA-HB-0007B, Logistics Product Data Handbook, and SAE TA-HB-0007-1A. MIL-HDBK-502A, Product Support Analysis provides additional guidance and instruction applicable to United States DoD programs. SAE TA-STD-0017A Product Support Analysis is a standard which prescribes a set of analysis activities for designing support and supporting the design of a product. MIL-HDBK-502A provides DoD users with implementation guidance for SAE TA-STD-0017A. The results of the analysis are Logistics Product Data. SAE GEIA-HB-0007B is a companion handbook to SAE GEIA-STD-0007C. The handbook provides standard guidance (i.e., how to), data population during life cycle phases, tailoring, contracting, data selection, a data map, and detailed information on data development for key and major fields (LCN
This SAE Aerospace Standard (AS) provides a system of graphic symbols and line codings that are intended primarily for usage in hydraulic and pneumatic system schematic diagrams for all types of aircraft.
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 specification establishes the requirements for anodic coatings on aluminum alloys.
This SAE Aerospace Information Report provides a general discussion on gaseous breathing oxygen and oxygen equipment for use on commercial aircraft. Other types of oxygen systems are mentioned to assist in this discussion. For detailed information on systems other than gaseous, refer to the appropriate section of AIR825.
This SAE Aerospace Recommended Practice (ARP) recommends criteria for the design and installation of Head-Up Display (HUD) systems. The recommendations are applicable to HUD systems for transport category aircraft, which display flight information (focused at infinity) in the forward field of view. The HUD total system requirement recommendations shall primarily lead to certifiable fail-passive CAT III characteristics and performance. This document forms a part of these recommendations. This document does not address devices for peripheral vision of displays worn by the pilot, nor the presentation of Enhanced Vision System (EVS) information.
This Aerospace Standard covers two basic Stall Warning Systems, one measures air flow and pressure distribution on the airfoil and the other measures the angle of airflow with respect to an arbitrary reference line. Each type of system includes, as a minimum, a sensor and the means for activating a device which warns the pilot of an impending stall.
This SAE Standard specifies dimensional characteristics of flat blades of single-pole connectors and specific requirements for on-board electrical harnesses of road vehicles, which can be fitted into female connectors such as those given as in Appendix A. This document applies to connectors designed to be disconnected after mounting in the vehicle in the case of repair and/or maintenance only.
This document provides information and guidance material to assist in assessing the need for and feasibility of developing deicing facilities, the planning (size and location) and design of deicing facilities, and assessing environmental considerations and operational considerations associated with de-icing facilities. The document presents relevant information necessary to define the need for a deicing facility and factors influencing its size, location, and operation. The determination of the need for deicing facilities rests with Airports. Although this document intends to provide information to airport operator and deicing facility planner/designer, all stakeholders, including deicing service providers, should be involved in the development process.
This SAE Information Report applies to liquefied natural gas used as vehicle fuel and requires LNG producers to provide the required information on the fuel composition and its “dispense by” date.
This recommended best practice outlines a method for estimating CO2-equivalent emissions using life cycle analysis.
The Class A Task Force of the Vehicle Network for Multiplex and Data Communications Committee is publishing this SAE Information Report to provide insight into Class A Multiplexing. Multiplexed actuators are generally defined as devices which accept information from the multiplexed bus. A multiplexed actuator can be an output device controlled by the operator or an intelligent controller. A Multiplex actuator can also be a display device that reports the status of a monitored vehicle function. This document is intended to help the network system engineers and is meant to stimulate the design thought process. A list of multiplexed actuator examples is provided in Appendix A, Figure A1. Many other examples can be it identified.
This Standard covers Bank and Pitch Instruments which measure and display the angular displacement of bank and pitch from a gyroscopic vertical reference. This reference may be pneumatically or electrically driven and be contained within the instrument display case or located remotely. Unless otherwise specified, whenever the term "Instrument" is used, it is to be understood to be the complete system of gyro component, any auxiliary equipment and display.
This specification covers a copper-beryllium alloy in the form of bars and rods up to 3.000 inches (76.20 mm), inclusive, in nominal diameter or least distance between parallel sides (see 8.7).
This specification, in conjunction with the general requirements covered in AMS2431 establishes the requirements for glass shot to be used for peening of metal parts.
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