Search Results

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.

This SAE Aerospace Recommended Practice (ARP) describes the multi-pass method for evaluating the filtration performance of fine lube filter elements, commonly utilized in aerospace power and propulsion lubrication systems: gas turbine engines, auxiliary power units (APUs), helicopter transmissions, constant speed drives (CSDs), and integrated drive generators (IDGs).

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 SAE Aerospace Information Report (AIR) reviews performance testing parameters for fuel filter elements utilized in gas turbine engine and APU main fuel systems. The scope is limited to main fuel filter elements rated at 35 μm(c), or finer, which constitute the majority of contemporary engine main fuel system filtration. This document does not address icing tests specific to fuel filter elements since they are only required for certain engine designs and are custom test procedures. General information on icing tests for aircraft fuel system components can be found in ARP1401. This document also does not address fuel filter elements utilized in fuel hydraulic systems since it is outside the scope of this document, This document is confined to laboratory testing of filter element performance to qualify the filtration medium and filter element construction as opposed to qualification of the complete fuel filter assembly.

This SAE Aerospace Information Report (AIR) is intended as a guide toward standardization of descriptions and specifications of fluid contamination products.

This metric SAE Aerospace Information Report (AIR) details a ball-on-cylinder (BOC) test device and specifies a method of rating the relative lubricity of aviation turbine fuel samples. The BOC produces a wear scar on a stationary steel ball by forcing it with a fixed load against a fuel wetted steel test ring in a controlled atmosphere. The test ring is rotated at a fixed speed so its surface is wetted by a momentary exposure to the fluid under test. The size of the wear scar is a measure of the test fluid lubricity and provides a basis for predicting friction or wear problems.

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.

This document discusses descriptions of fluid contamination products. These contaminants are used for design evaluation and formal component qualification/certification testing. Such tests are routinely performed on candidate aircraft engine fuel and pneumatic system components. Typical of these components are fuel pumps, fuel filters, fuel controls, pressurizing valves, flow dividers, selector valves, and combustor nozzles. The purpose of this document is to recommend standard descriptions to be used by specification writers.

This document establishes standard gland dimensions for low pressure static radial O-ring seal applications and provides recommendations for modifying these glands in special applications. No provisions are made in this document for anti-extrusion devices.

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.

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.