SAE AS94 Snap Ring, Non-Controllable Propeller Hub (NONCURRENT Aug 1973)
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Product Code:SAE AS94
Title:Snap Ring, Non-Controllable Propeller Hub (NONCURRENT Aug 1973)
Issuing Committee:E-25 General Standards For Aerospace And Propulsion Systems
Scope:The purpose of Section I of this document is to specify the requirements for minimum safe performance of an altimeter system in its normal mode of operation on subsonic aircraft. Compliance with this section is a means of assuring that the altimeter system will satisfactorily perform its intended function when exposed to conditions encountered in routine aeronautical operations (normal operation). 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
Title:Snap Ring, Non-Controllable Propeller Hub (NONCURRENT Aug 1973)
Issuing Committee:E-25 General Standards For Aerospace And Propulsion Systems
Scope:The purpose of Section I of this document is to specify the requirements for minimum safe performance of an altimeter system in its normal mode of operation on subsonic aircraft. Compliance with this section is a means of assuring that the altimeter system will satisfactorily perform its intended function when exposed to conditions encountered in routine aeronautical operations (normal operation). 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
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