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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 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.

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 Standard covers two basic types of manifold pressure instruments:

This Aeronautical Standard covers the capacitance sensor type of instrument.

This Aeronautical Standard covers two basic types of instruments as follows: Type I - Float Instruments Type II - Capacitance Instruments

This Aeronautical Standard covers two basic types of instruments as follows: Type I - Float Instruments Type II - Capacitance Instruments

This Aeronautical Standard covers two basic types of instruments, or combinations thereof, intended for use in indicating fuel consumption of aircraft engines as follows: TYPE I - Measure rate of flow of fuel used. TYPE II - Totalize amount of fuel consumed or remaining.

This specification covers the following basic types of instruments, or combinations thereof, intended for use in indicating fuel consumption of aircraft engines.

This aeronautical standard covers two basic types of instruments, or combinations thereof, intended for use in indicating fuel consumption of aircraft engines.

This Aeronautical Standard covers two basic types of instruments as follows: Type I - Float Instruments Type II - Capacitance Instruments

This Aeronautical Standard covers two basic types of instruments as follows: Type I - Float Instruments Type II - Capacitance Instruments

This specification covers: Type I - Float Gages Type II - Capacitance Gages

This Aeronautical Standard covers Flight Directors for use on aircraft to indicate to the Pilot, by visual means, the correct control application for the operation of an aircraft in accordance with a pre-selected flight plan.

These recommendations cover the mechanical and electrical installation and installation test procedures for Compass Systems of the type normally used in transport type aircraft. The recommendations in the ARP do not supersede any airworthiness requirements in Civil Air Regulations.

These recommendations cover the mechanical and electrical installation and installation test procedures for Compass Systems of the type normally used in transport type aircraft. The recommendations in the ARP do not supersede any airworthiness requirements in Civil Air Regulations.