Honeywell SPZ-8000 Maintenance Manual page 58

The system data communication is split between the
private-line paths provided for specific sensitive
main system bus (ASCB) and
data for which fault
isolation is required. These specific private-line paths include the
following:
. IRS attitude and headinq data to SG-884 Symbol Generators (~rivate-line
serial bus)
. FZ-820 Flight
(private-line
GP-820 Flight
(private-line
. .
Guidance Computer to GP-820 Flight Guidance Controller
serial bus)
Guidance Controller to FZ-820 Flight Guidance Computer
serial bus)
AZ-81O Air Data Computer to SG-884 Symbol Generators (private-line
serial bus)
SG-884 Symbol Generators to DU-880 EDS displays (private-line serial
bus)
. ADF, NAV, and ILS data to SG-884 Symbol Generators (private-line serial
bus)
Information from navigation receivers is not interfaced directly to the
SPZ-8000 DAFCS but is pre-processed by the EDS and/or the FMS. The EDS shall
function as data concentrator and switcher for basic navigation and heading
data and shall provide to the DAFCS source identification logic for currently
displayed data. The DAFCS shall receive lateral navigation (roll steering
commands) and vertical navigation (vertical targets) directly via ASCB from
both FMS subsystems. However, the DAFCS shall use the FMS navigation data
only if selected for display by the EDS.
The system displays heading, course, radio bearing, pitch and roll attitude,
barometric altitude, selected alert altitude, radio altitude, IAS/MACH
targets, lateral and vertical deviation, to-from indications, DME
indications, engine parameters, and advisory and caution indications.
Annunciators denote selected flight mode, altitude alert, decision height,
and go-around mode engagement. Pitch and roll steering commands developed by
the FZ-820 Flight Guidance Computer in conjunction with the GP-820 Flight
Guidance Controller are displayed by steering pointers to enable the pilot to
reach and/or maintain the desired flightpath or attitude.
2. A. LASEREF@ II Inertial Reference System (IRS)
The IRS is comprised of the following components:
Inertial Reference Units
. Attitude Heading Reference Unit
Mode Select Unit
Inertial System Display Unit (Optional)
I
22-14-00
Page 10
Apr 15/93
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