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This SAE Aerospace Standard (AS) establishes the minimum performance requirements for an angle of attack (AOA) system.

This AS covers subsonic and supersonic Mach meter instruments which, when connected to sources of static (Ps), and total (Pt), or impact (Pt-Ps), pressure provide indication of Mach number. These instruments are known as Type A. This AS also covers servo-operated repeater or digital display instruments which indicate Mach number when connected to the appropriate electrical output of a Mach transducer of Air Data Computer. These instruments are known as Type B.

This SAE Aerospace Standard (AS) specifies minimum performance requirements for primary pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components. The test procedures specified herein apply specifically to analog type instruments. Digital instruments or automatic test instrumentation may require other test procedures.

This AS defines instruments which use inputs of static and pitot pressure equal to those which are utilized to establish the pressure altitude and speed of that aircraft. These pressures are applied to the instrument ports to provide means for generation of an aural warning whenever the aircraft reaches or exceeds the maximum operating limit speed. This Over Speed Warning Instrument function may be incorporated as part of an Air Data Computer, or an Air Speed Indicator, or an Air Speed/Mach Number Indicator, or other instruments. In those cases where the Over Speed Warning Instrument is part of another instrument, the standards contained herein apply only to the Over Speed Warning Instrument function.

This SAE Aerospace Standard (AS) specifies minimum performance requirements for pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. This document does not address RVSM requirements because general RVSM requirements cannot be independently detailed at the component level. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components.

This Aeronautical Standard covers two (2) basic types of instruments as follows: TYPE I - Range 35,000 feet. Barometric Pressure. Scale range at least 28.1 - 30.99 inches of mercury (946-1049 millibars). May include markers working in conjunction with the Barometric Pressure Scale to indicate pressure altitude. TYPE II- Range 50,000 feet. Barometric Pressure. Scale range at least 28.1 - 30.99 inches of mercury (946-1049 millibars). May include markers working in conjunction with the Barometric Pressure Scale to indicate pressure altitude.

This SAE Aerospace Standard (AS) covers air data computer equipment (hereinafter designated the computer) which when connected to sources of aircraft electrical power, static pressure, total pressure, outside air temperature, and others specified by the manufacturer (singly or in combination) provides some or all of the following computed air data output signals (in analog and/or digital form) which may supply primary flight instruments: Pressure Altitude Pressure Altitude, Baro-Corrected Vertical Speed Calibrated Airspeed Mach Number Maximum Allowable Airspeed Overspeed Warning Total Air Temperature In addition, the computer may supply one or more of the following signals: Pressure Altitude, Digitized Equivalent Airspeed True Airspeed Static Air Temperature Altitude Hold Airspeed Hold Mach Hold Angle of Attack Flight Control Gain Scheduling Others

This standard covers the following basic types: