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This AS covers Vertical Velocity Instruments which display the rate of change of pressure altitude of an aircraft, as follows:

This Aerospace Standard covers two basic types of temperature instruments as follows: TYPE I: Ratiometer type, actuated by changes in electrical resistance of a temperature sensing electrical resistance element; the resistance changes being obtained by temperature changes of the temperature sensing resistance element. TYPE II: Millivoltmeter type, operated and actuated by varying E.M.F. output of a thermocouple; the varying E.M.F. input to the instrument being obtained by temperature changes of the temperature sensing thermocouple.

This specification covers three basic types of instruments as follows: TYPE I - Air Driven TYPE II - D-C Operated TYPE III - A-C Operated

This Aeronautical Standard covers two basic types of temperature indicators as follows: TYPE I - Ratiometer type actuated by changes of electrical resistance of a temperature sensing electrical resistance element; the resistance changes being obtained by temperature changes of the temperature sensing resistance element. TYPE II - Millivoltmeter type, operated and actuated by varying e.m.f. output of a thermocouple, the varying e.m.f. input to the instrument being obtained by temperature changes of the temperature sensing thermocouple.

This specification covers two types of instruments. These instruments are for the purpose of measuring temperature, such as those of oil coolant, carburetor air, free air and cylinder head.

This specification covers that gyroscopic instrument normally defined as a "subminiature rate gyro." The rate gyro, when subjected to an angular rate about its input axis, provides an AC output voltage proportional to the angular rate. The subminiature size category generally includes gyro instruments of one (1) inch diameter or less and three and one-half (3 1/2) inches length or less. This specification defines the requirements for a subminiature spring-restrained, single-degree-of-freedom rate gyro for aircraft, missile, and spacecraft applications.

This standard provides minimum performance criteria for air data instruments intended to provide cockpit indication of: a Indicated airspeed (Vi) b Computer airspeed (Vc) c True airspeed (Vt) d Equivalent airspeed (Ve) e Mach number (M) f Altitude (H) g Vertical speed (Hpr) h Maximum operating limit speed (Vmo) i True angle of attack (αt) j Free air temperature (Tfat) k Total temperature (Tt) These functions shall be derived from a central air data computer (AS 417) and through system wiring applied to the respective indicator.

This Aerospace Standard covers four basic types of direct reading pressure actuated rate of climb (vertical speed) indicators as follows: Type I - Range 0-2000 feet per minute climb and descent Type II - Range 0-3000 feet per minute climb and descent Type III - Range 0-4000 feet per minute climb and descent Type IV - Range 0-6000 feet per minute climb and descent

This aeronautical standard covers two basic types of pressure instruments. These are intended for use in measuring fuel, oil or hydraulic pressures as follows: This aeronautical standard does not apply to engine mounted torque meter systems.

The instrument system specified shall accept an input of static pressure and in some equipment other inputs that contribute altitude information to provide a visual indication of pressure altitude. If equipped with an automatic correction mechanism, it shall indicate by a positive means when the automatic correction mechanism is not in use. If the static source pressure error compensating mechanism is operational it shall be functional throughout the required operating envelope of the particular aircraft. Each aircraft type has its own static source error data which shall be obtained from the airframe manufacturer’s certified data. When a Central Air Data Computer is used in the altimeter system, the CADC shall be certified to its own governing document and the altimeter system (CADC and display) shall comply with the requirements of this document. NOTE: The instrument system specified herein does not include the aircraft pressure lines and pressure sources.

All automatic altitude reporting digitizer equipment manufactured under this standard shall comply with the requirements as specified up to its maximum range as indicated on the equipment nameplate.

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 AS defines components in "Capacitance Sensor" and "Non-Capacitance Sensor" type Fuel and Oil Quantity Indicating Systems. "Non-Capacitance" systems may employ any measurement technique current in the art including, but not restricted to, float, ultra-sonic and fiber optic devices. The definition of the individual components contained herein is related to the specified Total Installed System accuracy of the entire Fuel or Oil Quantity Indicating System which is a part of the airframe manufacturer's type certification approval data. This data shall be available from the subject airframe manufacturer as published in the operating manual for the aircraft type, model number and configuration. The Fuel or Oil Quantity Indicating System may incorporate optimum compensation based upon measurement of dielectric constant, temperature or density to correct for variations in fuel or oil characteristics due to temperature grade variations or additives.

This SAE Aerospace Standard (AS) establishes the minimum requirements for design and qualification of equipment identified as Gyroscopically Stabilized Magnetic Direction Instruments.

This document establishes the minimum requirements for design and qualification of equipment identified as Gyroscopically Stabilized Magnetic Direction Instruments.

This Standard covers two basic types of manifold pressure instruments:

This specification covers instruments intended for use in airplanes to indicate engine manifold absolute pressure.