Honeywell SPZ-8000 - System Description

SPZ--8000 Digital Integrated Flight Control System
A28--1146--055
REV 2
2-1
System Description
2. System Description
The SPZ--8000 Digital Integrated Flight Control System, shown in block
diagram form in Figure 2--1, includes the following subsystems:
STANDARD
D Air data system
D Electronic flight instrument system
D Multifunction display system
D Dual flight guidance system
D Flight management system
D Radio altimeter system
D PRIMUS
R
650 or PRIMUS
R
870 Weather Radar (WX) System
D LASEREF
R
II or LASEREF
R
III Inertial Reference System
OPTIONAL
D Lightning sensor system (optional)
D Traffic alert and collision avoidance system
D Enhanced ground proximity warning system (EGPWS) (optional)
D PRIMUS
R
II Integrated Radio System
The DIFCS is a complete automatic flight control system (AFCS) that
has fail--operational flight director, autopilot, yaw damper, and trim
functions. The automatic path mode commands are generated by the
flight guidance computer. The flight guidance computer integrates the
attitude and heading reference system, air data system, and EFIS into
a complete aircraft control system that stabilizes and controls the
aircraft throughout the flight.
A central serial communications network links subsystems within the
system, as shown in Figure 2 --1. The Avionics Standard
Communications Bus (ASCB) consists of two serial synchronous digital
communications buses. Each bus is electrically isolated from the
other bus and each bus communicates bidirectionally.
The ASCB interfaces the AFCS with the IRS, ADS, FMS, EF IS, and the
MFD systems. The bus controller is located in the flight guidance
computer . Each subsystem broadcasts on the ASCB when directed to
transmit by the bus controller, and returns to an off condition when its
time slot expires.