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
These formulae shall be used to determine drop dimensions for simple bend tube fittings utilizing flare and flareless end connection designs from 0° to 90° used in aircraft and aerospace applications. Individual design standards shall specify parameters, such as centerline bend radius (R), straight tangent length to accommodate bending equipment (X1 and X2), and nut to be used.
This specification defines the requirements for A286 CRES T-bolts and eye bolts, with room temperature tensile strength of a minimum of 160000 psi, for use with clamps and V-band couplings at 1000 °F maximum ambient temperature.
This SAE Aerospace Standard (AS) establishes the requirements for 24 degree cone flareless fluid connection fittings and nuts, internally or externally swaged, preset, or welded sleeves for use in aircraft fluid systems at nominal operating pressures up to and including 3000 psi.
This specification covers the design requirements and test procedures for separable beam seal fittings which includes end fittings (see 2.3.4), fitting bodies (see 2.3.7), and boss fittings (see 2.3.2) for use in aerospace fluid systems. Design requirements are for class 3000 in corrosion resistant steel (15-5 PH, 17-4 PH CRES) only and for class 4000 in titanium alloy (Ti) and corrosion and heat-resistant steel (nickel alloy 718 CRES) only. Definition of fittings and related terms are defined in 2.3.
This SAE Aerospace Information Report (AIR) presents reference information for use in preparing detailed specifications and other documents. The intent is to have a master reference document containing frequently required tabulations of information, such as the meaning of abbreviations, the spelled out wording of acronyms, the definition of terms, etc. so that such tabulations need not be repeated in recommended practice documents describing how to prepare technical documents. This document is intended to provide references in the field of fluid system components for space applications. Space applications include spacecraft, such as satellites, space stations, launch vehicles and space shuttles, and servicing equipment and components used for ground systems and launching and for servicing in space. Fluid system components include couplings, fittings, hose and tubing assemblies.
This SAE Aerospace Information Report (AIR) contains information relative to stresses and loads developed in tubes caused by tube deflections encountered in misaligned installations. Users are advised that when calculating the stresses and loads of a tubing system, the yield strength of existing loop clamp material is significantly lower than the tubing materials specified herein and should be considered.
This document covers flexible and semiflexible, reinforced and unreinforced air hoses fabricated from laminated and impregnated fabric, intended for use in aircraft heating, air conditioning, ventilating, defrosting, and/or deicing systems.
This SAE Aerospace Information Report (AIR) presents flexure fatigue strength of tube fitting joints in the form of graphs showing applied deflection D and total calculated axial stress S versus number of cycles to failure N. The graphs have been prepared from data obtained by actual testing conducted in accordance with ARP1185.
This specification covers the requirements for aircraft, hydraulic, self-sealing, quick disconnect couplings, for use in Type II hydraulic systems (-65 to +275 °F temperature range) as defined by AS5440.
This SAE Aerospace Standard (AS) establishes the requirements for externally swaged titanium tube fittings on titanium and CRES tubing with flareless separable fitting for use in hydraulic supply and return aerospace fluid systems up to operating pressure of 5080 psig (35 000 kPa) maximum and an operating temperature range of -65 to +275 °F (-54 to +135 °C). This specification covers a common 5080 psi pressure titanium fitting that may be used for a range of operating pressures up to 5080 psi with different tubing materials and tubing wall thicknesses, and is assembled with the same tooling in accordance with AS5959. The fitting operating pressure is based on the fitting thread pitch. Extra fine pitch for 5080 psi operating pressure and fine pitch for operating pressures 3000 psi and less. Table 12 shows applicable aerospace fitting part number standard and tubing materials and operating pressures.
This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, high conductive, self-bonding coupling assembly which, when installed on defined ferrules, provides a flexible connection for joining ducting and components in pressurized fluid systems. The assembled coupling is designed to provide interchangeability of parts and components between qualified manufacturers for use from -65 to +265 °F at 130 psi nominal operating pressures and for the service life of the aircraft system. FAR 23.954, FAR 25.603, FAR 25.605, FAR 25.609, FAR 25.613, FAR 25.901, FAR 25.954, and FAR 25.981 certification requirements have identified the need for high current capable flexible fluid assembled couplings. The coupling assembly does not require inspection or maintenance to remain current capable for the life of the aircraft.