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This standard covers oronasal type masks which use a continuous flow oxygen supply. Each such mask comprises a facepiece with valves as required, a mask suspension device, a reservoir, or rebreather bag (when used), a length of tubing for connection to the oxygen supply source, and a means for allowing the crew to determine if oxygen is being delivered to the mask. The assembly shall be capable of being stowed suitably to meet the requirements of its intended use.
This SAE Recommended Practice covers the safety alert symbol intended for use on construction and industrial equipment as defined in SAE J1116 and on agricultural tractors and machinery as defined in ASABE S390.
This SAE Aerospace Information Report (AIR) provides an orientation regarding the general technology of chemical oxygen generators to aircraft engineers for assistance in determining whether chemical oxygen generators are an appropriate oxygen supply source for hypoxia protection in a given application and as an aid in specifying such generators. Information regarding the details of design and manufacture of chemical oxygen generators is generally beyond the scope of this document.
This SAE Aerospace Information Report (AIR) outlines a recommended procedure for evaluation of the vibration environment to which the gas turbine engine powerplant is subjected in the helicopter installation. This analysis of engine vibration is normally demonstrated on a one-time basis upon initial certification, or after a major modification, of an engine/helicopter configuration. This AIR deals with linear vibration as measured on the basic case structure of the engine and not, for example, torsional vibration in drive shafting or vibration of a component within the engine such as a compressor or turbine airfoil. In summary, this AIR discusses the engine manufacturer’s "Installation Test Code" aspects of engine vibration and proposes an appropriate measurement method.
This SAE Aerospace Recommended Practice (ARP) identifies and defines a method of measuring those factors affecting installed power available for helicopter powerplants. These factors are installation losses, accessory power extraction, and operational effects. Accurate determination of these factors is vital in the calculation of helicopter performance as described in the RFM. It is intended that the methods presented herein prescribe and define each factor as well as an approach to measuring said factor. Only basic installations of turboshaft engines in helicopters are considered. Although the methods described may apply in principle to other configurations that lead to more complex installation losses, such as an inlet particle separator, inlet barrier filter (with or without a bypass system), or infrared suppressor, specialized or individual techniques may be required in these cases for the determination and definition of engine installation losses. Some rotorcraft may use an
This SAE Aerospace Information Report (AIR) provides details of how to perform hydraulic system calculations using equations that incorporate the metric International System of Units (SI).
This SAE Aerospace Standard (AS) specifies scarf-cut polytetrafluoroethylene (PTFE) retainers (backup rings) for use in static glands in accordance with AS5857. They are usually for use in hydraulic and pneumatic systems as anti-extrusion devices in conjunction with O-rings and other seals.
The turbine-engine-inlet flow distortion descriptors summarized in this document apply to the effects of inlet total-pressure, planar-wave, and total-temperature distortions. Guidelines on stability margin, destabilizing influences, types and purposes of inlet data, AIP definition, and data acquisition and handling are summarized from AIR5866, AIR5867, ARP1420, and AIR1419. The degree to which these recommendations are applied to a specific program should be consistent with the complexity of the inlet/engine integration. Total-pressure distortion is often the predominant destabilizing element that is encountered and is often the only type of distortion to be considered, i.e., not all types of distortion need to be considered for all vehicles.
The present SAE Aerospace Information Report (AIR) provides a list of the main government regulations, SAE and international standards, and standing industry recommendations applying to air cargo unit load devices (pallets, nets, and containers) to be loaded with either baggage or freight on board civil transport aircraft.
This specification covers an aluminum alloy in the form of die forgings, hand forgings, and forging stock.
This specification covers a corrosion and heat resistant nickel alloy in the form of sheet, strip, and plate.
This specification has previously been widely used and may be required for production or processing of existing designs in the future. The Aerospace Materials Division, however, does not recommend this specification for future use in new designs (See 6.7).
This specification covers the general requirements for aluminum and aluminum alloy bar, rod, wire, or special shapes; rolled, drawn, or cold finished. Specific requirements for these products are covered by the applicable detail specification (See 6.3).
This specification covers balls made of a low-chromium, high-carbon steel.
This specification covers a polytetrafluoroethylene (PTFE) resin filled with 10% mineral and 2.5% molybdenum disulfide in the form of extruded or molded rods or tubes which are sintered after molding or, in the case of extrusions, sintered during the extrusion process.
This specification covers an aluminum alloy in the form of sheet and plate supplied in the - T861 temper.
This specification covers an irradiated, thermally-stabilized, flame-resistant, modified-polyvinylidene-fluoride plastic in the form of extra-thin-wall tubing.
This specification covers a perfluoroether elastomer in the form of molded rings.
This specification covers an aluminum alloy in the form of pre-alloyed powder.
This specification covers a corrosion and heat resistant nickel alloy in the form of sheet and strip.
This specification presents requirements for thin-walled (inside diameter greater than four times the wall thickness and outside diameter 1/4 inch and larger) corrosion-resistant steel tubing in approximately the 1/8 hard condition, of special quality, suitable for use in high-pressure hydraulic systems.
This specification covers discontinuously reinforced aluminum alloy (DRA) metal matrix composites (MMC) made by mechanical alloying of the 2124A powder and SiC particulate, which is then consolidated by hot isostatic pressing (HIP) into shapes less than 62 square inches (0.04 m2) in cross-sectional area (see 8.12).
This specification covers a corrosion and heat-resistant steel in the form of bars, wire, forgings, mechanical tubing, flash welded rings, and stock for forging or flash welded rings.
This specification covers a one-part fluorosilicone (FVMQ) adhesive/sealant, supplied in cartridges, suitable for extrusion and curing to an elastomeric material upon exposure to air. It also covers a compatible primer.
This specification covers a low-alloy steel in the form of welding wire.
This specification covers bearings of a tin alloy cast on one or both faces of a steel or bronze backing.
This specification covers a 100% homopolymer of polychlorotrifluoroethylene (PCTFE) in the form of film and film tape 0.010 inch (0.25 mm) and under in nominal thickness.
This specification covers polyurethane systems consisting of an isocyanate component and other components containing a polyol and other ingredients which, when mixed and cured, produce thermosetting, rigid, cellular products.
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, profiles, and tubing produced with cross-sectional area of 32 square inches (206 cm2), maximum (see 8.6).
This specification covers an aluminum alloy in the form of sheet.
This specification covers a corrosion and heat resistant work strengthened nickel alloy in the form of bars and wire, 1½ inches (38 mm) and under in nominal diameter (See 8.2).
This SAE Aerospace Standard (AS) covers automatic pilots intended for use on aircraft to automatically operate the primary and trim aerodynamic controls to maintain stable flight and/or to provide maneuvering about any of the three axes through servo control. Automatic control functions essential for primary or augmented flight control are excluded.
This specification covers a chloroprene (CR) rubber sponge in the form of sheet, strip, molded shapes, or other forms, as ordered.
This specification covers an aluminum alloy in the form of plate 0.250 to 3.000 inch (6.35 to 76.20 mm) inclusive, in nominal thickness (see 8.7).
This specification covers the specific requirements for seamless tube drawn from aluminum alloy 5086.
This specification covers the general requirements for aluminum and aluminum alloy tube; drawn, seamless (see 6.1.1). Specific requirements for these products in a particular alloy are covered by the applicable detail specification (see 6.3).
This specification covers epoxy-resin-impregnated carbon-fiber broadgoods and tape in the form of multi-plied unidirectional layers constructed from the same or uniform fibers and supplied as broadgood rolls, tape, or cut sheet. The individual ply orientation shall be as ordered.
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