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Standard

Temperature Instruments (Reciprocating Engine Powered Aircraft)

1969-12-01
CURRENT
AS413B
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.
Standard

TURN AND BANK INDICATOR

1947-07-01
CURRENT
AS395
This specification covers three basic types of instruments as follows: TYPE I - Air Driven TYPE II - D-C Operated TYPE III - A-C Operated
Standard

TEMPERATURE INDICATOR

1954-12-01
HISTORICAL
AS413A
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.
Standard

TEMPERATURE INDICATOR

1948-11-01
HISTORICAL
AS413
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.
Standard

Single-Degree-of-Freedom Spring-Restrained Rate Gyros

1969-12-31
CURRENT
AS1104
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.
Standard

SMOKE DETECTORS

1947-07-01
HISTORICAL
AS400
This specification covers two basic types as follows: Type I Carbon Monoxide Type II Photo-Electric Cell
Standard

Rate of Climb (Vertical Speed) Indicator, Pressure Actuated (Turbine Powered Subsonic Aircraft)

1963-08-01
CURRENT
AS429
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
Standard

PRESSURE INSTRUMENTS - FUEL, OIL, AND HYDRAULIC

1954-12-15
HISTORICAL
AS408A
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.
Standard

PRECISION MOTOR TACHOMETER GENERATOR

1970-04-15
CURRENT
ARP667
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.
Standard

MINIMUM PERFORMANCE STANDARD STALL WARNING EQUIPMENT

1986-09-08
CURRENT
AS8014
This Aerospace Standard covers two basic Stall Warning Systems, one measures air flow and pressure distribution on the airfoil and the other measures the angle of airflow with respect to an arbitrary reference line. Each type of system includes, as a minimum, a sensor and the means for activating a device which warns the pilot of an impending stall.
Standard

MINIMUM PERFORMANCE STANDARD FOR FUEL AND OIL QUANTITY INDICATING SYSTEM COMPONENTS

1983-06-01
CURRENT
AS8029
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.
Standard

MINIMUM PERFORMANCE STANDARD FOR BANK & PITCH INSTRUMENTS

1975-09-01
CURRENT
AS8001
This Standard covers Bank and Pitch Instruments which measure and display the angular displacement of bank and pitch from a gyroscopic vertical reference. This reference may be pneumatically or electrically driven and be contained within the instrument display case or located remotely. Unless otherwise specified, whenever the term "Instrument" is used, it is to be understood to be the complete system of gyro component, any auxiliary equipment and display.
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