This procedure is intended to apply to fuel pumps. This procedure will be defined in terms of recommended test fluid, test setup, test conditions, and test method. This procedure may be used for other fuel system components, by testing in conjunction with the pump, which normally supplies the component inlet flow, or a substitute test pump of similar capacity. This procedure may be used, with variations in test conditions and test fluid for performing pump evaluation tests. Tests at progressively increasing pump speeds and pressures will provide design limitation data. Alternate test periods on a test pump and another pump, of a design for which actual service durability is known, will provide useful comparison data.
The requirements presented in this document address the key considerations for mechanical and electrical safety in aircraft fuel pump design. Document sections focus on understanding safety relative to an electrically motor driven fuel pump assembly acting as an ignition source for explosive fuel vapors within the airplane tank.
This SAE Aerospace Information Report (AIR) discusses the sources of Copper in aviation jet fuels, the impact of Copper on thermal stability of jet fuels and the resultant impact on turbine engine performance, and potential methods for measurement and reduction of the catalytic activity of Copper contamination in jet fuels. This document is an information report and does not provide recommendations or stipulate limits for Copper concentrations in jet fuels.
This procedure is intended to apply to fuel pumps. This procedure will be defined in terms of recommended test fluid, test setup, test conditions, and test method. This procedure may be used for other fuel system components, by testing in conjunction with the pump, which normally supplies the component inlet flow, or a substitute test pump of similar capacity. This procedure may be used, with variations in test conditions and test fluid for performing pump evaluation tests. Tests at progressively increasing pump speeds and pressures will provide design limitation data. Alternate test periods on a test pump and another pump, of a design for which actual service durability is known, will provide useful comparison data.
The requirements presented in this document address the key considerations for thermal safety in aircraft fuel pump design. Document sections focus on understanding safety relative to an electrically motor driven fuel pump assembly acting as an ignition source for explosive fuel vapors within the airplane tank.
The requirements presented in this document cover the design factors which might cause any part of an electrically motor driven fuel pump assembly to act as an ignition source for explosive fuel vapors within the airplane tank.
These recommendations cover only those design factors which might cause the pump motor or pump housing to act as an autogenous or spark-ignition source for explosive fuel vapors within the airplane tank.
These recommendations cover only those design factors which might cause the pump motor or pump housing to act as an autogenous or spark-ignition source for explosive fuel vapors within the airplane tank.
The AIR is limited to a presentation of the historical background, the technical rationale which generated the V/L fuel condition interface requirement in specifications between the aircraft fuel delivery system and the aircraft engine fuel system, and limitations in the usage of the V/L concept.
The AIR is limited to a presentation of the historical background, the technical rationale which generated the V/L fuel condition interface requirement in specifications between the aircraft fuel delivery system and the aircraft engine fuel system, and limitations in the usage of the V/L concept.
This document establishes requirements, test procedures, and acceptance criteria for the fire testing of fluid handling components and materials used in aircraft fluid systems. It is applicable to fluid handling components other than those prescribed by AS1055 (e.g., hoses, tube assemblies, coils, and fittings). It also is applicable to materials, wiring, and components such as reservoirs, valves, gearboxes, pumps, filter assemblies, accumulators, fluid-cooled electrical/electronic components, in-flight fluid system instrumentation, hydromechanical controls, actuators, heat exchangers, and manifolds. These components may be used in fuel, lubrication, hydraulic, or pneumatic systems.
This specification covers the general requirements for aircraft tank mounted, centrifugal type, fuel booster pumps, used for engine fuel feed and/or fuel transfer.
This specification covers the general design, testing, and safety requirements for aircraft tank mounted fuel booster pumps used for engine fuel feed, transfer, and jettison.
This SAE Aerospace Recommended Practice (ARP) addresses the characteristics required for the definition, development, and acquisition of a satisfactory airframe mounted accessory gearbox (AMAG).
This document discusses the history and development of endurance requirements, provides an analysis of test contaminant material and includes a discussion of future requirements.
This document discusses the history and development of endurance requirements, provides an analysis of test contaminant material and includes a discussion of future requirements.
This document discusses the history and development of endurance requirements, provides an analysis of test contaminant material and includes a discussion of future requirements.
This AIR discusses the history and development of endurance requirements, provides an analysis of test contaminant material and includes a discussion of future requirements.