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This SAE Aerospace Information Report (AIR) presents safety criteria for pneumatic type engine starting system design and component hardware. Included are safety criteria in design of both starter control valves and starters as well as in design of airframe control systems. Safety topics concern starter valve operation and material application, airframe controls and instrumentation installations and starter rotor integrity and containment.

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.

This specification covers the general requirements for pneumatic control valves for use with the starters on aircraft gas turbine engines. This specification shall be used in conjunction with AS943, ARP949, and AIR1639.

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 recommended practice covers requirements for turbine engine-generators designated as follows:

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.

This Aerospace Recommended Practice describes two performance acceptance test methods to determine the performance acceptability of new production and overhauled air turbine starters. Before a new or overhauled starter is delivered to a customer, the starter is subjected to a performance acceptance test in accordance with an acceptance test procedure. The performance acceptance test is intended to ensure that the customer receives a starter that meets or exceeds minimum starter performance requirements.

This Aerospace Standard establishes the common requirements for hydraulic starters, suitable for use in aircraft and missiles, and the methods to be used for demonstrating compliance with these requirements.

The starters covered by this specification shall be designed to operate on compressed air from ground support equipment, engine interbleed or on board air supply.

The material contained in this report has been simplified to facilitate its use. Specific manufacturers should be contacted for more detailed information. Many of the basic power supplies are available in numerous configurations and some provide shaft power or electrical power in addition to the pneumatic capability. Vehicles for the ground transportation of the power supplies are also varied to fit specific requirements.