Specifications

SECTION I
DESCRIPTION AND SPECIFICATIONS
MODEL 560
HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM
The Honeywell Primus 1000 Display and Flight Guidance System is a comprehensive flight
management system that provides three axis airplane attitude stabilization and path control. Cathode Ray
Tubes (CRTs) are utilized to display many functions traditionally referenced by analog instruments, such as
attitude director indicators, horizontal situation indicators, glideslope indicators, and navigation bearing
indicators.
Standard Electronic Flight Instrument System (EFIS) installation, is a three-tube system. It consists of a
cathode ray tube (primary flight display), installed in left (pilot's) instrument panel, a second cathode ray
tube (multifunction display), installed in center instrument panel and a third cathode ray tube (primary flight
display), installed in right (copilot's) instrument panel. Two Display Guidance Computers (DGCs) are
installed in the nose and act as symbol generators, flight directors, and autopilot computers.
In addition to displays and DGCs, source controllers, display controllers, and annunciator switches are
installed to select information sources, position of displays, and display formats.
The Honeywell IC-600 display guidance computers are integrated computers which are the focal point
of information flow within the system. Computers accept inputs from sensors, including DME, glideslope,
directional gyros, flight management system, micro air data computer, radar, and long range navigation
sources. Symbol generator portions of the display guidance computers convert input information into a
video format for display on respective primary flight displays and multifunction display.
The Honeywell AZ-850 Micro Air Data Computer (MADC) accepts pitot and static pressure and outside
temperature from a temperature probe. This information is used to produce static pressure and differential
pressure signals which are utilized by the IC-600 Display Guidance Computer.
A Honeywell VG-14A Vertical Gyro provides three-wire synchro outputs that are electrical analogs of
aircraft pitch and roll attitudes. Pitch gimbal freedom is +80 degrees to -80 degrees, and roll gimbal
freedom is unlimited.
A Honeywell C-14D Directional Gyro provides three-wire synchro heading information. This component
also includes a remotely mounted Auto/Man switch which controls slaved or unslaved modes of operation.
The Honeywell AG-222 Accelerometer is a self-contained, closed loop, force-balanced device, with DC
signal output in proportion to normal airplane acceleration.
The Honeywell DC-550 Display Controller provides the pilot a method of control display formatting on
the EFIS tubes, as well as data acquisition function for the remote instrument controller, and mode selector.
This Information is then transmitted to the computer.
A Honeywell RI- 553 Remote Instrument Controller provides a method by which the pilot can manually
select heading, course, and preselected altitude.
The Honeywell MS-560 Mode Selector provides push-button controls for Integrated Flight Guidance
system and mode annunciation.
A Honeywell MC-800 Multifunction Display Controller provides a method for pilot selection of display
modes and formats on the Multifunction Display (MFD), as well as interfacing with both IC-600 computers
over a serial digital bus.
A DU-870 Display Unit is the electronic display used to provide Primary Flight Displays (PFDs) and
Multifunction Display (MFD) in the Primus 1000 system. Tubes are driven by video and deflection signals
compiled by the symbol generator function of the display guidance computers.
The Honeywell PC-400 Autopilot Controller provides a method of engaging autopilot and yaw damper,
and manual control of autopilot through Turn knob and Pitch wheel.
Display guidance computers also drive aileron, elevator, rudder, and trim servos. Their description is
covered in Chapter 22, Honeywell Autopilot Servo - Maintenance Practices.
I 1-20 Configuration AA 56OMB-01