Honeywell SPZ-8000 - 30 EHSI Displays and Annunciators

SPZ--8000 Digital Integrated Flight Control System
A28--1146--055
REV 2
Electronic Flight Instrument System (EFIS)
4-39/(4-40 blank)
BEARING
POINTER
NO. 2
AD--12798@
T
T
CRS
OR
DTK
MAG
OR
TRU
FMS
OR
DME
NAV SOURCE
ANNUNCIATOR
VOR1
VOR2
LOC1
LOC2
FMS1
FMS2
COURSE
PRESELECT
ANNUNCIATOR
LOC1
LOC2
BEARING
SOURCE
ANNUNCIATOR
A(ADF)
V(VOR)
F(FMS)
ELAPSED
TIME, TIME
GROUND
SPEED
DISPLAY
ET
59:59
ET
H9:59
TTG
399.9 MIN
GSPD
999 KTS
4
3
2
1
HEADING
DIAL
COURSE/DESIRED
TRACK DISPLAY
COURSE
SELECT/DESIRED
TRACK POINTER
COURSE
PRESELECT
POINTER (FMS ONLY)
GLIDESLOPE
DEVIATION
POINTER
TO- -FROM
ANNUNCIATOR
AIRCRAFT
SYMBOL
COURSE PRESELECT
DEVIATION BAR
(FMS ONLY)
TIME--TO--GO
DISPLAY
FMS APPROACH
ANNUNCIATOR
DISTANCE
DISPLAY
WAYPOINT/DME
IDENTIFIER
NAVIGATION
SOURCE
ANNUNCIATOR
COURSE
PRESELECT
ANNUNCIATOR
(FMS ONLY)
BEARING
POINTER NO. 1
BEARING
POINTER
SOURCE
ANNUNCIATOR
COURSE
DEVIATION BAR
AND LATERAL
DEVIATION SCALE
HEADING
SELECT BUG
FORE
LUBBER
LINE
FMS
MESSAGE
ANNUNCIATOR
HEADING
SOURCE
ANNUNCIATOR
WIND
VECTOR
DISPLAY
FMS
DRIFT
BUG
TARGET ALERT
ANNUNCIATOR
HEADING
SELECT
DISPLAY
RECIPROCAL
COURSE
PRESELECT
POINTER
AFT
LUBBER
LINE
RECIPROCAL
COURSE
POINTER
NOTES:
1. DISTANCE IS PROVIDED BY THE FMS:
TO THE NEXT WAYPO I NT WITH
FMS AS THE NAVIGATI ON SOURCE.
TO THE VOR STATI ON IN THE VOR
MODE IF DME IS NOT CO- -LOCA TED
WTH THE VOR, OR IF DME IS NOT VALID.
IF ANNUNCIA TOR IS FMS.
2. GROUND SPEED IS PROVIDED BY:
THE FMS IN THE FMS MODE.
THE IRS IN ALL OTHER MODES.
3. T I M E -- TO-- G O IS P R O VIDED B Y:
THE FMS IN THE FMS MODE.
THE FMS IN THE VOR MODE WITH
NO CO- -LOCA TED DME.
THE DME AND IRS WITH CO--LOCA TED
DME.
4. ELAPSED TIME IS COMPUTED BY THE
EFIS SYMBOL GENERATOR.
5. WITH FMS SELECTED AND DURING
COURSE PRESELECT , THE CRS DISPLA Y
APPEAR S DURING AND FOR 5 SECONDS
AFTERROTATIONOFTHECRSKNOBAND
THEN REVERTS BACK TO THE DTK DISPLAY.
5
5
EHSI Displays and Annunciators
Figure 4--30