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This SAE Aerospace Recommended Practice (ARP) establishes the requirements for the design, manufacture, and qualification of four hydraulic switching valves used in airborne applications. Two are pressure operated, Type IA and IB and two are solenoid/pilot operated, Type IIA and IIB. They are applicable to four pressure classes 3000, 4000, 5000 and 8000 psi. The equipment as designed is intended to be installed in hydraulic systems designed to AS5440 for military applications or ARP4752 and ARP4925 depending on the type of aircraft for commercial applications. Additional or refined requirements shall be contained in the detail (procurement) specification and these shall take precedence over any potentially conflicting requirements of this ARP or documents referenced by this ARP.

This SAE Aerospace Recommended Practice (ARP) establishes the general requirements for spring-loaded, normally closed check valves for use in Type I, Type II, or Type III aircraft and missile hydraulic systems having nominal operating pressure shown in Table 1.

This SAE Aerospace Standard (AS) specifies the general requirements for hydraulic system reservoirs that are installed in commercial and military aircraft and helicopters and also in missile hydraulic systems. This document includes design, test (production and qualification) criteria for various types of reservoirs. Appendix A provides information on hydraulic fluid volume requirements and reservoir sizing. This document also provides a basis for the Procurement Specification to completely define individual reservoir requirements.

This SAE Aerospace Standard (AS) specifies the general requirements for hydraulic system reservoirs that are installed in commercial and military aircraft and helicopters and also in missile hydraulic systems. This document includes design, test (production and qualification) criteria for various types of reservoirs. Appendix A provides information on hydraulic fluid volume requirements and reservoir sizing. This document also provides a basis for the Procurement Specification to completely define individual reservoir requirements

This SAE Aerospace Standard (AS) specifies the general requirements for hydraulic system reservoirs that are installed in commercial and military aircraft and helicopters and also in missile hydraulic systems.This document includes design, test (production and qualification) criteria for various types of reservoirs. Appendix A provides information on hydraulic fluid volume requirements and reservoir sizing.This document also provides a basis for the Procurement Specification to completely define individual reservoir requirements.

This document provides recommended practices for the design and selection of tube, hose, and fitting systems that are used to transmit hydraulic fluid on aircraft. NOTE: Guidance for the sizing of hydraulic tubing is contained in Appendix A.

This document provides recommended practices for the design of tubing systems that are used for the transmission of liquid and gasses in fluid power systems for aerospace vehicles such as aircraft, missiles and boosters. The primary emphasis is given to recommended practices for line sizing, tube routing, supports and clamping, stress considerations and permissible defects, and provisions for flexure through the use of flexible hoses, coiled tubes, swivel joints, and expansion glands. The sections regarding tubing materials and fitting types are included for reference, but particular recommendations are purposely avoided since their selection is dependent upon the specific requirements of each particular vehicle system and many other factors.

This document is a compendium of recommended practices for the design of tubing systems for the transmission of liquid and gasses influid power systems for aerospace vehicles such as aircraft, missiles and boosters, and is considered applicable to the design of future space vehicles and other applications using aircraft technology. Primary emphasis is given to recommended practices for line sizing, tube routing, supports and clamping, stress considerations and permissible defects, and provisions for flexure through the use of flexible hoses, coiled tubes, swivel joints, and expansion glands. Fluid power systems are differentiated from the normal aircraft fuel and oil systems and the various fluid systems used for environmental control and air conditioning systems; however, the practices cited herein will in many cases be applicable to these other systems.