MAINTENANCE
Honeywell !!!!!!%h.
Prioritization and message suppression under specific circumstances will
be performed in the FWC to improve the effectiveness of each warning/
advisory to the pilots.
The FWC will also function as a continuous
engine trend and limit monitoring system with the capability to store
selective engine parameters for later readout and analysis by maintenance
personnel.
The DP-884 Dimmer Panel provides the CRT brightness control for the six
DU-880 Display units.
2. E. DFZ-820 Dual Flight Guidance System
The DFZ-820 Dual Flight Guidance System is comprised of the following
components:
. FZ-820 Flight Guidance Computers (FGC)
● GP-820 Flight Guidance Controller
● PC-880 Turn
. SM-600 Dual
. TM-260 Dual
Pitch Controller
Servo Drive and SB-600 Bracket (Aileron and Elevator)
Trim Servo and TB-261 Bracket
. Dual-Valve Hydraulic Rudder Actuator (non-Honeywell)
The DFZ-820 Flight Guidance System provides full fail-operational flight
director, autopilot, yaw damper, and trim. Fail-operational capability
is provided by redundant flight control functions.
Existence of dual
attitude/heading and air data sensors is used to full advantage within
the DFZ-820 System through sensor voting and redundancy management
techniques.
The fail-operational characteristic is extended to include
sensor failures.
One servo of each dual servo (aileron, elevator, and trim) and the rudder
actuator is connected to a flight guidance computer.
Only one computer
will be actively controlling the servos and actuator. The servo or
actuator connected to the inactive FGC has a brake applied. Normally,
the pilot’s side will be automatically in control. The copilot’s side
can be manually selected, if desired, or will automatically take control
if there is a disengage type failure in the pilot’s computer. In this
way, fail-operational control is achieved.
If only one FGC is valid, the
system will disconnect if the remaining FGC fails.
The single GP-820 Flight Guidance Controller has dual circuitry that
provides the same outputs to each FGC and is used to engage the system,
select the operating modes, select the PFD in command, arm the
autothrottle system, and set the selected heading, course, vertical
speed, speed targets,
and altitude preselect.
The single PC-880 Turn Pitch Controller provides dual pitch wheel and
turn knob outputs to the FGC.
22-14-00
Page 14
Aug 15/91
Use or disclosure of information on this page is subpct to the restncfions on the title page of this document,
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