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This SAE Aerospace Recommended Practice (ARP) defines and establishes a standard presentation of data for gas turbine propulsion engine starter characteristics in graphs and curves. The data presentation applies to both pneumatic and hydraulic energy source starting systems.

No scope available.

This document provides a brief description of the auxiliary power equipment that is available with enough description and pertinent comments to enable an engineer to make logical preliminary selection of the appropriate equipment for advanced military aircraft programs. The information has been kept as brief as possible to include the maximum amount of equipment in a relatively short document. It is not intended to replace textbook design analysis or detailed information available from the equipment suppliers. The document describes auxiliary power equipment. Auxiliary power is defined as follows: "Those elements of secondary power [defined as all aircraft nonpropulsive power generation and transmission] related to main engine bleed air and shaft power extraction or power generation separate from the main engines. Included are engine bleed air systems, remote engine driven gearboxes, engine starting systems, auxiliary power units, and emergency power systems."

This SAE Aerospace Information Report includes procedures for the analysis of a gas turbine engine start. It utilizes a standard form for the essential starting characteristics of the gas turbine engine and for the starting power capability of the aircraft battery. This report illustrates the format of the characteristic which is provided by the electric starter to transform the battery electric power (voltage and current) to the mechanical power (torque and speed) required to successfully start the engine. An aircraft engine start battery typically also serves as a backup source for emergency electrical energy. Guidelines are therefore provided for the determination of battery capacity to fulfill the emergency energy requirements of the aircraft.

This SAE Aerospace Information Report (AIR) covers basic aircraft engine start systems fundamentals. It presents various ground power sources and aircraft “on board” starting units. Also included are descriptions of start system components and interconnections which together comprise an engine starting system.

This Aerospace Information Report (AIR) reviews the factors to be considered in determining the location and arrangement for auxiliary power unit (APU) installations for airborne applications and reviews requirements for flight suitability. As treated in this discussion, the APU normally includes a power section (or engine), a starting system, an electronic control unit (ECU), a gearbox with accessory mounting pads, and an oil cooling system. The accessories that are driven by the APU, such as CSD's (constant speed drives), alternating current (AC) generators, hydraulic pumps, or air compressors, are not covered here except insofar as they make demands on the APU. The various installation components and systems that are covered here are outlined by the table of contents. Turbine-type APU's are by far the most highly developed and universally used airborne units, so their installation will dominate the discussion in this document.

This SAE Aerospace Information Report (AIR) presents a discussion of drag torques of engine accessories operating at cold temperature. Various conditions of temperature, speed, and acceleration rates are reviewed showing the merits of each method and recommending a standard test method.

This report lists military and industry specifications and standards which are used in aerospace engine starting and auxiliary power systems. Listings are provided as follows: Section 2. Topic Listing Section 3. Numerical Listing Section 4. Alphabetical Listing Only those hardware standards which have been specifically designed for engine starting systems are listed. Revisions and amendments which are current for these specifications and standards are not listed.

This report lists military and industry specifications and standards which are used in aerospace engine starting systems. Only those hardware standards which have been specifically designed for engine starting systems are listed. Revisions and amendments which are current for these specifications and standards are not listed.

This report lists military and industry specifications and standards which are used in aerospace engine starting and auxiliary power systems. Only those hardware standards which have been specifically designed for engine starting systems are listed. Revisions and amendments which are current for these specifications and standards are not listed.

This specification establishes the requirements for the (TBS) jet fuel starter for the (TBS) gas turbine engine used in the (TBS) aircraft.

This Recommended Practice covers a means of determining the performance acceptability of new production or overhauled starters that will be used for cranking turbine engines and is intended for use where torque measuring equipment is not available or desirable. This method determines acceptability of the overall performance of the starter on a flywheel test stand, rather than the performance at specific speed conditions. It allows a slight variation of output torque outside specified limits, as long as the overall performance is up to standard.