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An attempt has been made to consider all features of seal ring design including configuration, materials, hardness, dimensions, surface finishes, surface treatment, leak testing, and general quality. In addition to this, allowable cylinder breathing and general quality requirements of mating hardware are discussed. Also, at the end of this report, there is a brief paragraph on other types of seal rings.

An attempt has been made to consider all features of seal ring design including configuration, materials, hardness, dimensions, surface finishes, surface treatment, leak testing, and general quality. In addition to this, allowable cylinder breathing and general quality requirements of mating hardware are discussed. Also, at the end of this report, there is a brief paragraph on other types of seal rings.

The SLIPPER SEAL is defined and the basic types in current use are described. Guide lines for selecting the type of Slipper Seal for a given design requirement are covered in terms of friction, leakage, service life, installation characteristics and interchangeability.

This SAE Aerospace Information Report (AIR) provides basic information on the use of slipper seal sealing devices when used as piston (OD) and rod (ID) seals in aerospace fluid power components such as actuators, valves, and swivel joints, including: The definition of a slipper seal and the description of the basic types in use. Guidelines for selecting the type of slipper seal for a given design requirement are provided in terms of friction, leakage, service life, installation characteristics, and interchangeability.

This SAE Aerospace Standard (AS) is applicable to military and commercial aircraft. It specifies the dimensions, tolerances and size codes (dash numbers) for use in glands per MIL-G-5514 where squeeze at low temperature is often insufficient to provide a leak-tight seal. The dimensions and tolerances specified in this standard are suitable for any elastomeric material. This standard should not be used as a part standard, therefore no part numbers like AS5798-001X shall be created. Each dash number, which should be appended to an appropriate drawing or standard number, identifies one size O-ring only. An AS5798 sized O-ring is intended to replace an AS568 sized O-ring of the same dash number. An X suffix is part of the dash number to signify oversize. Temperature limitations of 275 °F (135 °C) and coefficient of thermal expansion of 9.0 × 10-5 unit length per °F (1.6 × 10-4 unit length per °C) were used for swell calculations.

This SAE Aerospace Standard (AS) specifies the dimensions, tolerances and size codes (dash numbers) for O-rings with a larger cross-section than those to AS568, for use in glands per MIL-G-5514 where squeeze at low temperature is often insufficient to provide a leak-tight seal.

This SAE Aerospace Recommended Practice (ARP) provides an overview of the various types of polytetrafluoroethylene (PTFE) backup rings for hydraulic and pneumatic fluid power applications, including their advantages and disadvantages.

The backup ring is defined. The various types designed for use with O-rings in MIL-G-5514 packing glands, and MS33566 and MS21344 universal fitting installations are described. Guidelines are included for selecting backup rings and backup ring materials. Backup ring installation procedures and precautions are described.

The backup ring is defined. The various types designed for use with O-rings in MIL-G-5514 packing glands, and MS 33566 and MS 21344 universal fitting installations, are described.

This SAE Aerospace Recommended Practice (ARP) provides an overview of the various types of polytetrafluoroethylene (PTFE and TFE) back up rings for hydraulic and pneumatic fluid power applications, including their advantages and disadvantages.

This standard establishes the dimensional and visual quality requirements, lot requirements and packaging and labeling requirements for O-rings molded from AMS7601 butyl rubber. It shall be used for procurement purposes.

This SAE Aerospace Information Report (AIR) contains a description of the design approach, the calculations, some comparisons to alternate SAE Aerospace Recommended Practice (ARP) documents, and the background information used to generate the standard face seal gland dimensions specified in AS6235. NOTE: This AIR should be read in conjunction with AS6235. In some instances, the information contained within AS6235 is repeated for clarity.

This AIR documents the methodologies used to calculate the dimensions and tolerances used in the following backup rings standards: AS5781 AS5782 AS5860 AS5861 In addition, an appendix is provided which provides details of gland and backup ring design practices.

This AIR documents the methodologies used to calculate the dimensions and tolerances used in the following backup rings standards: AS5781 AS5782 AS5860 AS5861 In addition, an appendix is provided which provides details of gland and backup ring design practices.

This document recommends general gland design criteria for static and dynamic O-ring seal applications specifically for engines and engine control systems.

This document recommends standard gland design criteria and dimensions for dynamic radial O-ring seal applications specifically for engine and engine control systems operating at pressures up to a maximum of 1500 psi (10342.14 kPa) and provides recommendations for modifying these glands in special applications. There are no provisions in this document for anti-extrusion devices. NOTE: The criteria set forth here are similar to but not identical with those in MIL-G-5514 and AS4716. This document is not intended to replace MIL-G-5514 or AS4716 for hydraulic applications.