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This standard covers heat and corrosion resistant steel loop clamps with a woven steel wire cushion that is attached to the clamp by spot welding and is intended for use in applications up to 1200 °F (649 °C).

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 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 document establishes the requirements for aircraft, hydraulic couplings, self-sealing one side only, for use in Type II hydraulic systems (-65 to +275 °F temperature range) as defined by MIL-H-5440. The purpose being to connect a hose or tube to a standard MS33656, MS33514, or MIL-F-85421, or MIL-F-85720 fitting, and to provide the self-sealing feature on the hose or tube side of the connection.

This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, self-bonding coupling assembly which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent or other systems. This assembled coupling, hereafter referred to as the assembly, and is designed for use from −65 to +400 °F and at 125 psig nominal operating pressure. AS1650 was not designed for the new certification requirements for flammable leakage zones and fuel tanks for lightning protection and assembly redundancy. As such their use and installation may require additional efforts and equipment to support new FAA CFR compliance. The AS7510 flexible coupling should be the preferred coupling for use in flammable leakage zones and fuel tanks that require service life and functionality for lightning protection and part redundancy.

This SAE Aerospace Standard (AS) covers the requirements for a flexible, lightweight, low pressure, self-extinguishing, integrally heated silicone hose assembly. The hose has a fully fluorinated fluoropolymer inner liner and is primarily intended for use in aircraft potable water systems with an environmental operating temperature range of -65 °F (-54 °C) to +160 °F (+71 °C).

This SAE Aerospace Standard (AS) covers the requirements for a flexible, lightweight, low pressure, self-extinguishing, silicone hose assembly. The hose has a fully fluorinated fluoropolymer inner liner and is primarily intended for use in aircraft potable water systems.

This specification covers the requirements for aircraft hydraulic, self-sealing, quick disconnect couplings for use in 8000 lbf/in2 (gage) lightweight hydraulic systems.

This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, self-bonding coupling assembly which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent or other systems. This assembled coupling, hereafter referred to as the assembly, and is designed for use from −65 to +400 °F and at 125 psig nominal operating pressure.

This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, self-bonding coupling assembly which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent or other systems. This assembled coupling, hereafter referred to as the assembly, and is designed for use from 65 to +400 °F and at 125 psig nominal operating pressure.

This document specifies performance and quality requirements for the qualification and manufacture of 24° 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 document defines the requirements for a threadless, flexible, self-bonding coupling assembly, which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent, or other systems. This assembled coupling, hereafter referred to as the assembly, is designed for use from -54 to 204 °C and at 862 kPa operating pressure. AS coupling components referenced herein have been qualified to AS1650. Ferrules referenced herein are inch ferrules adapted to metric tubing.

This Aerospace Specification establishes the requirements for a threaded flexible coupling assembly, hereafter referred to as the assembly, which utilizes ferrules or machined tube end fittings to join tubing and components in aircraft fuel, vent, or other systems. This coupling assembly is designed for use from -54 to 93 °C and at 862 kPa peak working pressure. AS coupling components referenced herein have been qualified to AS1710. Ferrule referenced herein are inch ferrules adapted to metric tubing.

This SAE Aerospace Standard (AS) specifies test methods for fitting assemblies used in aircraft fluid systems in the pressure classes B, D, and E, and in temperature Types I, II, and III of MA 2001. This document applies each time that it is referred to in a procurement specification or other definition document. Fluids and materials used for the tests are listed in Section 2.

This SAE Metric Aerospace Recommended Practice (MAP) establishes the requirements for preparing a specification for fluid couplings for spacecraft servicing. The objective of this document is to provide design, development, verification, storage, and delivery requirement guidelines for the preparation of specifications for fluid couplings and the ancillary hardware for use with serviceable spacecraft designed for use in the space environment. The couplings shall be capable of resupplying storable propellants, cryogenic liquids, and gases to a variety of spacecrafts.

This specification covers the detail requirements for aircraft hydraulic self-sealing quick disconnect couplings, for use in types I and II hydraulic systems (-65°F to +275°F temperature range) as defined by Specification MIL-H-5440.

This specification covers the requirements for aircraft hydraulic, self-sealing, quick disconnect couplings for use in 5000 and 8000 lbf/in2 (gage) lightweight hydraulic systems.

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) covers medium-pressure, high-temperature, flexible, metal-hose assemblies suitable for operation in pneumatic systems up to 800 °F with excursion to 1200 °F for Class “B” and “N” and primarily for use on jet aircraft power plants. Refer to 1.2.1 for recommended usage.

This SAE Aerospace Standard (AS) covers the requirements for a flexible, lightweight, low pressure, self-extinguishing, integrally heated silicone hose assembly. The hose has a fully fluorinated fluoropolymer inner liner and is primarily intended for use in aircraft potable water systems with an environmental operating temperature range of −65 °F (−54 °C) to +160 °F (+71 °C).