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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 document is limited to units meeting the definitions of para. 1.3 and covers the following general class of synchros:

This document is limited to units meeting the definitions of para. 1.3 and covers the following general class of synchros:

This standard covers _________________________________________

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.

This recommended practice establishes objectives for high performance control motor tachometer generators to be used with aeronautical and associated equipment in protective enclosures or completely within the shell of the aircraft so that they are subjected only to the internal climatic conditions of heat, cold, shock, vibration, and humidity. Control motor tachometer generators larger than size 23 are not covered in this document.

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.

In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject.

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 specification covers design requirements and all performance requirements for the procurement of single and dual hermetically sealed, integrally lighted, remote indicating, pressure indicators.

This specification covers design requirements and all performance requirements for the procurement of single and dual hermetically sealed, integrally lighted, remote indicating, pressure indicators.

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