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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
This SAE Aerospace Information Report (AIR) developed by a broad cross section of personnel from the aviation industry and government agencies is offered to provide state-of-the-art information for the use of individuals and organizations designing new or upgraded turboshaft engine test facilities. This document is also applicable to turboprop engines tested with a dynamometer as load absorption device, as they are basically tested as turboshaft engines. For propeller-equipped turbofan testing facilities design considerations, see 2.1.7.
The intent of this specification is for the procurement of 7781 glass fabric epoxy prepreg product with 250 °F (121 °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).
The purpose of this SAE Aerospace Information Report (AIR) is to provide management, designers, and operators with information to assist them to decide what type of power train monitoring they desire. This document is to provide assistance in optimizing system complexity, performance, and cost effectiveness. This document covers all power train elements from the point at which energy in a turbine or electric engine is converted via a gear train to mechanical energy for propulsion purposes. The document covers aircraft engine driven transmission and gearbox components, their interfaces, drivetrain shafting, drive shaft hanger bearings, and associated rotating accessories, propellers, and rotor systems as shown in Figure 1. For guidance on monitoring additional engine components not addressed herein (e.g., main shaft bearings and compressor/turbine rotors), refer to ARP1839. This document addresses rotary and fixed wing applications for rotor, turboprop, turbofan, prop fan, and lift fan
This document establishes the minimum training and qualification requirements for ground-based aircraft deicing methods and procedures. All guidelines referred to herein are applicable only in conjunction with the applicable documents. Due to aerodynamic and other concerns, the application of deicing fluids shall be carried out in compliance with engine and aircraft manufacturers’ recommendations. The scope of training should be adjusted according to local demands. There are a wide variety of winter seasons and differences of the involvement between deicing operators, and therefore, the level and length of training should be adjusted accordingly. However, the minimum level of training shall be covered in all cases. As a rule of thumb, the amount of time spent in practical training should equal or exceed the amount of time spent in classroom training.
This document presents criteria for flight deck controls and displays for Airborne Collision Avoidance Systems.
This specification covers the requirements for vacuum deposited cadmium.
This document discusses the history and development of endurance requirements, provides an analysis of test contaminant material and includes a discussion of future requirements.
This specification covers quality assurance sampling and testing procedures used to determine conformance to applicable material specification requirements of wrought corrosion- and heat-resistant steel and alloy products and of forging stock.
This specification covers requirements for electrodeposited porous chromium plate.
This specification covers quality assurance sampling procedures which may be used to determine conformance to applicable specification requirements of carbon and low-alloy steel castings.
The scope of this SAE Aerospace Standard (AS) is to define the following dimensional requirements for double hexagon, hexagon head and tee headed bolts, and nuts with AS8879 UNJ inch series threads primarily for use in propulsion systems. Design requirements are based on UNJC threads for sizes 0.1640 and smaller and UNJF threads for sizes 0.1900 and larger.
This specification covers an aluminum bronze alloy in the form of sand castings (see 8.5).
This specification covers an aircraft-quality, low-alloy steel in the form of mechanical tubing.
The test procedure and related limit value are intended to apply to fixed and mobile ground pressure fuel dispensing systems and to aerial refueling tankers.
This specification covers an aluminum alloy in the form of alclad sheet 0.040 to 0.249 inch (1.02 to 6.32 mm), inclusive, in nominal thickness (see 8.5).
This specification covers an alicyclic diepoxy carboxylate prepolymer in the form of a low-viscosity liquid.
This specification covers molded or extruded bar, rod, and shapes produced from a polyamide-imide (PAI) polymer filled with 30% glass fiber. This is designated as Grade 4 material per AMS3670.
This specification covers an aluminum alloy in the form of hand forgings up to 8 inches (203 mm), inclusive, in nominal thickness and a cross-sectional area not over 256 square inches (1652 cm2) and rolled rings up to 3.5 inches (89 mm), inclusive, in nominal thickness and with an OD to wall thickness ratio of 10:1 or greater (see 8.6).
This specification covers columbium in the form of sheet, strip, plate, and foil.
This specification covers two types of refined hydrocarbon compounds in the form of liquids. This specification only covers newly manufactured materials.
This specification covers a polycarbonate resin in the form of extrusions and moldings.
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, flash welded rings, and stock for forging or flash welded rings.
This specification covers a modified vinyl plastic foam in the form of sheet and strip up to 1-1/2 inches (38.1 mm) in nominal thickness.
This specification covers a corrosion-resistant steel in the form of investment castings.
This specification covers an aluminum alloy in the form of extruded or drawn welding wire.
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