Flight Guidance System (Fgs) - Honeywell PRIMUS 1000 Pilot's Manual

Essential display information from sensor systems, automatic flight
control, and navigation are integrated into the pilot's prime viewing area.
Critical flight operation information is selected using the display
controller and MFD controller. These controllers are also used to
operate the checklist function. Navigation and aircraft performance
displays are selected using the bezel controllers on the display units.
Each symbol generator can drive the three displays. In case of a DU
failure, the pilot's PFD can be reverted to the MFD.
The symbol generator in the IAC functions as the data processor for the
display system. It receives digital and discrete inputs, organizes the
data into the correct formats as defined by the display controller
settings, and transmits the information to the DUs.
Except for an autopilot function in the No. 1 IAC, the IACs are identical
and directly interchangeable. When the display system is in its normal
(no failure) configuration, IAC No. 1 drives the pilot displays, and IAC
No. 2 drives the copilot displays. Wraparound signals are used for
critical parameters, such as pitch and roll data, indicated airspeed
(IAS), barometric altitude, and baro set.
Reversionary switches substitute operational sensors for failed ones.

FLIGHT GUIDANCE SYSTEM (FGS)

The flight guidance system includes the following LRUs:
D
The IAC, which includes:
— Flight director function
— Autopilot function (No. 1 IAC only, pilot's)
— System monitors
D
Mode selector
D
Autopilot (AP) controller
D
Servo motors (pitch/roll/yaw)
D
Accelerometers
D
Rate gyro.
A28–1146–134
REV 1 Jan/03
R
PRIMUS 1000 Integrated Avionics System
System Description
2-5