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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.
The following schematic diagrams reflect various methods of illustrating automotive transmission arrangements. These have been developed to facilitate a clear understanding of the functional interrelations of the gearing, clutches, hydrodynamic drive unit, and other transmission components. Two variations of transmission diagrams are used: in neutral (clutches not applied) and in gear. For illustrative purposes, some typical transmissions are shown.
This specification covers beryllium in the form of bars, rods, tubing, and machined shapes fabricated from vacuum hot-pressed powder.
This specification covers an aromatic nylon fabric in the form of cloth.
This specification covers a liquid oxygen compatible gas-leak detecting compound in the form of a liquid.
This specification covers two types of virgin, unfilled polytetrafluoroethylene (PTFE) in the form of molded rods, tubes, and shapes. This specification does not apply to product over 12 inches (305 mm) in length, rods under 0.750 inch (19.05 mm) in diameter, and tubes having wall thickness under 0.500 inch (12.70 mm).
This specification covers a corrosion- and heat-resistant nickel alloy in the form of investment castings.
This SAE Aerospace Recommended Practice (ARP) establishes the method for qualification testing of tube joints and fitting attachments, using the flexure test method described in ARP1185. This qualification test method allows the determination of S-N type stress versus cycles or D-N type deflection versus cycles curves, as illustrated in ARP1418 as an alternate to flexture testing to a minimum endurance stress level.
This specification covers a corrosion-resistant steel in the form of investment castings.
This specification covers a plasticized, polyether-type, urethane (EU) resin and hardener which, when mixed and cured, produces elastomeric polyurethane products.
This specification covers epoxy-resin-impregnated glass laminates in the form of sheets clad on one or both sides with electrolytic copper foil.
This specification covers virgin, unfilled polytetrafluoroethylene (PTFE) in the form of molded rods, tubes, and shapes. This specification does not apply to product over 12 inches (305 mm) in dimension parallel to the direction of applied molding pressure, rods under 0.750 inch (19.05 mm) in diameter, and tubes having wall thickness under 0.500 inch (12.70 mm).
This specification covers a high-humidity-resistant, modified epoxy adhesive in the form of film supplied as rolls or sheets.
This specification covers a silver-brazing flux in the form of a paste.
This specification covers one grade of polytetrafluoroethylene (PTFE) resin in the form of film and film tape.
This specification covers dielectrically-loaded syntactic foam tiles having a polyimide resin matrix.
This specification covers one grade of glass-fiber-filled polytetrafluoroethylene (PTFE) in the form of molded billets.
This specification covers an anti-galling compound remover in the form of a water-soluble powder, a concentrated liquid for dilution with water, or a ready-to-use liquid.
This specification covers an aluminum alloy in the form of sheet and plate from 0.006 to 3.000 inches (0.15 to 76.20 mm), inclusive, in nominal thickness (see 8.5).
This specification covers an aluminum alloy in the form of sheet and plate 0.020 to 0.499 inch (0.51 to 12.67 mm), inclusive, in nominal thickness alclad two sides (see 8.5).
The product shall consist of 5-ply yarn having 720 continuous filaments per ply and a maximum of 4 turns per inch (25.4 mm).
This specification covers a corrosion- and heat-resistant steel in the form of sheet, strip, and plate.
This specification covers an aluminum alloy in the form of sheet and plate over 0.039 to 4.000 inches (over 0.991 to 101.60 mm), inclusive, in thickness (see 8.6).
This aerospace recommended practice is applicable to the design of a reusable locking device for cylindrical nuts which are generally tightened with a spanner wrench. Nuts of this type are commonly used to pre-load, and/or position, anti-friction bearings.
This SAE Aerospace Recommended Practice (ARP) covers the requirements for the types of glass to be utilized in the fabrication of cover glasses and lighting wedges used in aerospace instruments. It defines the maximum extent of physical defects and recommends standard methods of inspection and evaluation. Definitions of terminology used in this document are covered in 2.2.
This specification and its supplementary detail specifications cover interleaf carrier materials in the form of polyethylene film or coated paper tape or sheeting.
This specification establishes requirements for a corrosion-removing compound in the form of a liquid concentrate.
This specification covers a water-base cleaner in the form of a concentrated liquid.
This SAE Aerospace Recommended Practice (ARP) establishes flexure test procedures to determine and classify the fatigue strengths of reconnectable or permanent hydraulic tube joints. The procedure is intended for conducting flexure tests of fittings and joints for hydraulic tubing materials such as AMS 5561 (21Cr-6Ni-9Mn) steel or AMS 4944 (3AL-2.5V) titanium. A mean stress is applied by holding system pressure in the specimens and flexing in a rotary or planar bending test machine.
This specification covers a corrosion- and heat-resistant cobalt alloy in the form of investment castings.
This SAE Aerospace Information Report (AIR) identifies and explains the meaning of various ratings and terms used to describe the physical characteristics of liquid filter elements. The significance of various filter parameters is discussed. In addition, a number of filter test methods are briefly described. This AIR and the data presented are only applicable where the system liquid wets the filter elements.
This SAE Aerospace Recommended Practice (ARP) defines and establishes a standard presentation of data for gas turbine propulsion engine starter characteristics in graphs and curves. The data presentation applies to both pneumatic and hydraulic energy source starting systems.
This test method describes a procedure for measuring the largest pore or hole in a filter or similar fluid-permeable porous structure. A standard referee test method for precise determination or resolution of disputes is specified. A simpler inspection test procedure for quality assurance “go-no-go” measurement is also given. Bubble-point testing physics, analysis of bubble-point test data, and correlation with other methods of pore size determination are separately discussed in the appendix.
This specification covers balls made of high-carbon corrosion-resistant steel of three carbon ranges.
This specification covers a corrosion and heat-resistant steel in the form of sand or centrifugal castings.
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