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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 three basic types of true mass flow indicating instruments. Each may consist of an indicator, transmitter and other auxiliary means such as a power supply or amplifier as required.

This SAE Aerospace Standard (AS) covers three basic types of true mass flow indicating instruments. Each may consist of an indicator, transmitter and other auxiliary means such as a power supply or amplifier as required.

This standard covers three basic types of total-temperature-measuring instruments used as a means of determining the total temperature developed by adiabatic heating of the air due to motion of the aircraft through the air.

This SAE Aerospace Standard (AS) covers tachometer instruments (RPM indicator, 0-110 percent RPM and 0-120 percent RPM indicators and generator) for remote indication of engine speed.

This Aerospace Standard covers tachometer instruments (RPM indicator, 0–110 percent RPM and 0–120 percent RPM indicators and generator) for remote indication of engine speed.

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 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.

This Aeronautical Standard covers two basic types of fuel, oil and hydraulic pressure instruments as follows: Type I - Direct Indicating Type II - Remote Indicating This Aerospace Standard does not apply to engine mounted torque meter systems.

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.

This Aerospace Standard covers two basic types of fuel, oil and hydraulic Pressure instruments as follows: Type I- Direct Indicating Type II- Remote Indicating This Aerospace 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.

This ARP covers an electro-mechanical pneumatic device which is calibrated to provide control contacts that can be made to operate a warning device whenever the indicated airspeed (IAS) reaches a maximum value as defined by the operating limit speed curve for the specific model aircraft.

The purpose of this AIR is to provide recommendations for the minimum dimensions of characters and symbols used in aircraft instrument dials and panel displays as related to the conditions stated in para. 3. Numerous variables influence the legibility of aircraft instrument dial characters. This situation makes it very difficult, if not impossible, to establish an exact act of rules for optimizing all installations. Character size, one of the important considerations, can be optimized where adequate dial space exists. Usually this is not the case and the designer is faced with placing the information in a limited space while continuing to strive for error-free legibility. Appropriate minimum size requirements have been stated herein for guidance in air transport use.

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