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annunciation will be displayed.
When the EVS failure annunciation is displayed while the EVS is commanded off, the pilot can
remove the annunciation on the HUD by toggling the EVS clear switch (NORM to CLR to NORM).
This procedure will not remove the associated EICAS message.
FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
11−10−106
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EICAS Messages
HUD FAIL
Indicates an internal failure.
Either a loss of HUD or bad
status bit. (no image displayed)
EVS FAIL
Indicates an EVS failure. Either a
loss of ISS or a bad status bits. The
EVS HEAT FAIL
Indicates the IRW and/or fairing not heated.
Loss of heater control. EVS image may
EVS HEAT OVHT
Indicates an IRW or fairing
overheat. Loss of IPS due to
EVS DEFOG FAULT
Indicates that the IRW is not
defogged. EVS image may
become degraded.
HUD MISALIGN
does not detect alignment beam.
GF1110_108a
HUD will revert to stroke mode. become degraded.
relay being switched off. EVS
image may become degraded.
HUD MISCOMPARE
Indicates sensor mispcompare
not detected by IAC.
HUD FAN FAIL
Indicates a loss of fan cooling
in HUD computer tray. When in
approach, HUD reverts after
2 min to stroke mode.
EVS FAIL
EVS HEAT FAIL
EVS HEAT OVHT
HUD FAIL
HUD MISCOMPARE
EVS DEFOG FAULT
HUD FAN FAIL
HUD MISALIGN
HUD ON
HUD ON
EVS ON
HUD ON
EVS CLEAR
HUD ON
EVS CAL
Indicates that the combiner unit
HUD ON
selected ON.
Indicates that the HUD has been
EVS ON
that the EVS image is displayed.
Indicates that the HUD is ON and
HUD ON
EVS CLEAR
Indicates that the EVS is
available but the display
has been cleared using the
CLEAR switch.
HUD ON
EVS CAL
calibration in progress.
Indicates EVS IR sensor
HUD ON
FLIGHT INSTRUMENTS
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−107
FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
11−10−108
THIS PAGE INTENTIONALLY LEFT BLANK
CB - NAV SYSTEM
DC ESS
CB − NAV SYSTEM 1/6
ADF 2
DME 1
FMS 1 CDU
FMS 2 CDU
ADF 1 IN
IN
IN
IN
IN
DC 1
DC ESS
DC 2
DME 2
BATT
DC 2
IN
IRS 3 PWR B
LIGHTNING SENSOR
MFD 1 CTLR
MFD 2 CTLR
RAD ALT 1
IRS 3 PWR A IN
IN
IN
IN
IN
DC 1
DC ESS
DC 1
BATT
DC 2
DC 1 IN
4/6
DC 1
CB − NAV SYSTEM 2/6
GPS 1
GPS 2
HUD
IRS 1 FAN
FMS 3 CDU IN
IN
IN
IN
IN
DC 1
DC 1
DC 2
GPWS
DC 2
DC ESS
IN
STBY ADI
STBY ALT/ASI
TCAS
VOR/ILS 1
VOR/ILS 2
RAD ALT 2 IN
IN
IN
IN
IN
DC 2
AV BATT
DC ESS
DC ESS
DC 2
DC ESS
CB − NAV SYSTEM
IN
5/6
DC 2
CB − NAV SYSTEM 3/6
IRS 1 PWR B
IRS 2 FAN
IRS 2 PWR B
IRS 3 FAN
IRS 1 PWR A IN
IN
IN
IN
IN
DC ESS
BATT
DC 2
IRS 2 PWR A
DC ESS
DC 1
IN
WX RADAR
WX RADAR CTLR 1
WX RADAR CTLR 2
VOR/ILS 3 (OPT) IN
IN
IN
IN
DC 1
DC 1
DC 1
DC 1
CB − NAV SYSTEM 6/6
CB − NAV SYSTEM
CCBP
GF1120_001
STAT SYS BUS PREV CNTL TEST
PAGE
NEXT
PAGE
EMER
CNTL
BUS
CIRCUIT BREAKER − SYSTEM 2/2
CIRCUIT BREAKER SYSTEM
HYD
ICE
IND/RECORD
LDG GEAR
LIGHTS
NAV
OIL
OXYGEN
THRUST REV
BRT
FLIGHT INSTRUMENTS
EMS CIRCUIT PROTECTION
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−20−1
CB - NAV SYSTEM (CONT'D)
Effectivity:
· Airplanes 9002 thru 9122 not incorporating Service Bulletin:
· SB 700−24−045, AC and DC Power Distribution − Unit Change and Activation of Build 4
Electrical System.
DC ESS
CB − NAV SYSTEM 1/6
ADF 2
DME 1
FMS 1 CDU
FMS 2 CDU
ADF 1 IN
IN
IN
IN
IN
DC 1
DC ESS
　
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