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The test procedure applies to the refueling manifold system connecting the receiver aircraft fuel tanks to the refueling source fuel pump(s) for both ground and aerial refueling. The test procedure is intended to verify that the limit value for surge pressure specified for the receiver fuel system is not exceeded when refueling from a refueling source which meets the requirements of AS 1284 (reference 2). This recommended practice is not directly applicable to surge pressure developed during operation of an aircraft fuel system, such as initiating or stopping engine fuel feed or fuel transfer within an aircraft, or the pressure surge produced when the fuel pumps are first started to fill an empty fuel manifold.

The test procedure applies to the refueling manifold system connecting the receiver aircraft fuel tanks to the refueling source fuel pump(s) for both ground and aerial refueling. The test procedure is intended to verify that the limit value for surge pressure specified for the receiver fuel system is not exceeded when refueling from a refueling source which meets the requirements of AS1284 (reference 2). This recommended practice is not directly applicable to surge pressure developed during operation of an aircraft fuel system, such as initiating or stopping engine fuel feed or fuel transfer within an aircraft, or the pressure surge produced when the fuel pumps are first started to fill an empty fuel manifold.

This document defines design, performance, and test criteria for self-sealing breakaway valves for use in crash-resistant aircraft fuel systems.

This document defines design, performance, and test criteria for self-sealing breakaway valves.

MIL-STD-1290, 14 CFR 27.952, and 14 CFR 29.952 provide crash resistant fuel system design and test criteria that significantly minimize fuel leaks and occurrence of post-crash fire in survivable impacts. This document does not change and does not authorize changes in or deviations from MIL-Standard or regulatory requirements. This document provides guidance for the design, performance, and test criteria for self-sealing breakaway valves.

This document defines design, performance, and test criteria for self-sealing breakaway valves.

This report is intended to identify the various errors typically encountered in capacitance fuel quantity measurement systems. In addition to identification of error sources, it describes the basic factors which cause the errors. When coupled with appraisals of the relative costs of minimizing the errors, this knowledge will furnish a tool with which to optimize gauging system accuracy, and thus, to obtain the optimum overall system within the constraints imposed by both design and budgetary considerations. Since the subject of fuel measurement accuracy using capacitance based sensing is quite complex, no attempt is made herein to present a fully-comprehensive evaluation of all factors affecting gauging system accuracy. Rather, the major contributors to gauging system inaccuracy are discussed and emphasis is given to simplicity and clarity, somewhat at the expense of completeness. An overview of capacitive fuel gauging operation can be found in AIR5691.

It is intended to provide capacitance gaging system "specifiers" with the necessary tools to make value judgements concerning the various errors typically encountered in systems of this type. Thus, in addition to merely identifying the error-causes, descriptions are given concerning the basic factors from which these error-causes derive. This knowledge, when complemented with appraisals of the relative costs of minimizing the error-causes, will furnish the system specifier with a powerful tool with which to optimize gaging system accuracy, and thus, to obtain the "best possible" overall system within the constraints imposed by both design and budgetary considerations. Since the subject of capacitance gaging accuracy is quite extensive, and in some instances very complex, no attempt is made herein to present an all-inclusive and fully comprehensive evaluation of the subject. Rather, the major contributors to gaging system inaccuracy are discussed.

This report is intended to identify the necessary analytical tools to enable making value judgments for minimizing the various errors typically encountered in capacitance systems. Thus, in addition to identification of error sources, it describes the basic factors which cause the errors. When coupled with appraisals of the relative costs of minimizing the errors, this knowledge will furnish a tool with which to optimize gauging system accuracy, and thus, to obtain the optimum overall system within the constraints imposed by both design and budgetary considerations. Since the subject of capacitance accuracy is quite complex, no attempt is made herein to present a fully-comprehensive evaluation of all factors affecting gauging system accuracy. Rather, the major contributors to gauging system inaccuracy are discussed and emphasis is given to simplicity and clarity, somewhat at the expense of completeness. An overview of Capacitive Fuel Gauging operation is provided in the Appendix.

Applications include specifications, reports, ratings, texts etc., where fluid leakage rates are treated.

Applications include specifications, reports, ratings, texts etc., where fluid leakage rates are treated.

The scope of this document is to provide pertinent information on demonstrating the performance of Flame Arrestors, also known as Fuel Vent Protectors (FVPs), in preventing the propagation of a deflagration when the arrestors are subjected to aerospace-representative flames produced by the venting of flammable gas through the arrestor. Test procedures for two separate combustion-loading profiles are presented herein: The flame hold test condition, and the flame propagation test condition. For the flame hold test condition, the applicability of two separate critical flows is discussed in which one flow results in the greatest flame arrestor temperature and a second flow results in the greatest temperature of the surrounding structure.

The test procedure applies to the refueling manifold system connectingn the receiver aircraft fuel tanks to the refueling source fuel pump(s) for both ground and aerial refueling. The test procedure is intended to verify that the limit value for surge pressure specified for the receiver fuel system is not exceeded when refueling from a refueling source which meets the requirements of AS1284 (reference 2). This recommended practice is not directly applicable to surge pressure developed during operation of an aircraft fuel system, such as initiating or stopping engine fuel feed or fuel transfer within an aircraft, or the pressure surge produced when the fuel pumps are first started to fill an empty fuel manifold.

This SAE Aerospace Information Report (AIR) reviews performance testing parameters for noncleanable, often referred to as disposable, aircraft gas turbine engine lubricant filter elements.

This SAE Aerospace Standard (AS) defines the maximum allowable free opening dimensions for airframe fueling ports on civil aircraft that require the exclusive use of gasoline as an engine fuel and the minimum free opening dimensions for airframe fueling ports on civil aircraft that operate with turbine fuels as the primary fuel type. In addition, this document defines the minimum fuel nozzle tip dimensions for turbine fuel ground service equipment and the maximum fuel nozzle tip diameter for gasoline ground service equipment.

This SAE Aerospace Standard (AS) defines the maximum allowable free opening dimensions for airframe fueling ports on civil aircraft that require the exclusive use of gasoline as an engine fuel, and the minimum free opening dimensions for airframe fueling ports on civil aircraft that operate with turbine fuels as the primary fuel type and with gasoline as the emergency fuel type. This SAE Aerospace Standard (AS) also defines the features and dimensions for airframe refueling ports on civil aircraft that require the exclusive use of turbine fuel as an engine fuel. In addition, this document defines the minimum fuel nozzle spout dimensions for turbine fuel ground service equipment, and the maximum fuel nozzle spout diameter for gasoline ground service equipment.

This SAE Aerospace Standard (AS) defines the maximum allowable free opening dimensions for airframe fueling ports on civil aircraft that require the exclusive use of gasoline as an engine fuel, and the minimum free opening dimensions for airframe fueling ports on civil aircraft that operate with turbine fuels as the primary fuel type and with gasoline as the emergency fuel type. This SAE Aerospace Standard (AS) also defines the features and dimensions for airframe refueling ports on civil aircraft that require the exclusive use of turbine fuel as an engine fuel. In addition, this document defines the minimum fuel nozzle spout dimensions for turbine fuel ground service equipment, and the maximum fuel nozzle spout diameter for gasoline ground service equipment.

This SAE Aerospace Information Report presents a glossary of terms commonly used in the ground delivery of fuel to an aircraft and pertinent terms relating to the aircraft being refueled.