SPZ--8000 Digital Integrated Flight Control System
A28--1146--055
REV 2
2-3
System Description
Pitch and roll steering commands developed by the flight guidance
computer in conjunction with the flight guidance controller are displayed
as steering pointers that direct the pilot to reach and/or maintain the
desired flightpath or attitude.
With very few exceptions, most of this system is powered f rom 28 V dc.
The air data displays and radar antenna stabilization require 26 V ac.
AIR DATA SYSTEM (ADS)
The ADS consists of the following components:
D DADC
D Altitude transducer
D Mach/airspeed indicator
D Vertical speed indicator
D Barometric altimeter.
NOTE: Some installations with TCAS installed remove the VS--200
VSI. TCAS installations display vertical speed on the
electronic attitude director indicator (EADI).
The DADC is a microprocessor--based digital computer that accepts
both digital and analog inputs, performs computations, and supplies
both digital and analog outputs. It receives pitot--static pressures and
total air temperature (TAT) inputs that are used to compute the standard
air data functions. The DADC outputs information to the following:
D Barometric altimeter
D Mach/airspeed indicator
D VSI
D T ransponder
D Flight recorder
D Flight director
D Autopilot.
The altitude transducer inputs altitude levels to the aircraft stall
protection system.
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