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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

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

Exhaust Gas Temperature Instruments

1966-06-01
CURRENT
AS428
The exhaust gas temperature instruments covered by this standard are of the electrical servo null balance type, actuated by a varying emf output of one or more parallel connected Chromel-Alumel thermocouples.
Standard

FLIGHT DIRECTOR EQUIPMENT

1984-09-01
CURRENT
AS8008
This Aerospace Standard covers Flight Director Equipments which display to the pilot a computed command for the operation of an aircraft in accordance with selected Mode(s). The term “Equipment” may include controls, displays, computers, etc. and may include sensors if furnished as a part of the Flight Director.
Standard

Overspeed Warning Instrument (Turbine Powered Subsonic Aircraft)

1967-07-01
CURRENT
ARP435
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.
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

Altitude Alerting Devices and Systems

2020-04-14
CURRENT
ARP1061B
This SAE Aerospace Recommended Practice (ARP) provides performance criteria for Altitude Alerting Devices and Systems. These devices can be self-contained or receive remote altitude information and can have integral or remote barometric corrections. Only the generation of the alerting signals is covered by this recommended practice and not the details of the visual or audio alerts operated by these signals. It is recommended that the system’s operational correspondence between the selected altitude settings of the Altitude Alerting Device and the Altitude Level Indication normally used to control the aircraft should not exceed ±250 ft RSS throughout the operating range of the device.
Standard

ALTITUDE ALERTING DEVICES AND SYSTEMS

1971-11-01
HISTORICAL
ARP1061
This ARP provides performance criteria for Altitude Alerting Devices and Systems. These devices can be self-contained or receive remote altitude information and can have integral or remote barometric corrections. Only the generation of the alerting signals is covered by this recommended practice and not the details of the visual or audio alerts operated by these signals. It is recommended that the system's operational correspondence between the selected altitude settings of the Altitude Alerting Device and the Altitude Level Indication normally used to control the aircraft should not exceed ±250 ft RSS throughout the operating range of the device.
Standard

Altitude Alerting Devices and Systems

1999-04-01
HISTORICAL
ARP1061A
This SAE Aerospace Recommended Practice (ARP) provides performance criteria for Altitude Alerting Devices and Systems. These devices can be self-contained or receive remote altitude information and can have integral or remote barometric corrections. Only the generation of the alerting signals is covered by this recommended practice and not the details of the visual or audio alerts operated by these signals. It is recommended that the system’s operational correspondence between the selected altitude settings of the Altitude Alerting Device and the Altitude Level Indication normally used to control the aircraft should not exceed ±250 ft RSS throughout the operating range of the device.
Standard

PRESSURE ALTIMETER SYSTEM MINIMUM SAFE PERFORMANCE STANDARD

1996-09-01
CURRENT
AS942A
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.
Standard

Pressure Altimeter System, Minimum Safe Performance Standard

1971-06-01
HISTORICAL
AS942
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 mechansim, 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.
Standard

Indicator, Pressure, 1 1/2-Inch, Integrally Lighted

2012-08-22
CURRENT
AS23479A
This specification covers design requirements and all performance requirements for the procurement of single and dual hermetically sealed, integrally lighted, remote indicating, pressure indicators.
Standard

Indicator, Pressure, 1 1/2-Inch, Integrally Lighted

1999-05-01
HISTORICAL
AS23479
This specification covers design requirements and all performance requirements for the procurement of single and dual hermetically sealed, integrally lighted, remote indicating, pressure indicators.
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