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ADC 1−2−3 FAIL
Indicates that ADC has
failed.
ADC 1−2−3 DEGRADED
Indicates that ADC is unreliable.
Degraded static error correction.
ASCB BUS FAULT
Indicates ASCB single bus
failure (on ground only).
ASCB CTRL 1−2−3 FAULT
Indicates loss of
communication with one bus
controller.
IRS 1−2−3 SET HDG
Indicates IRS has defaulted
to a heading of 360 degrees
upon entering attitude mode.
GF1110_101a
IRS 1 SET HDG
IRS 2 SET HDG
IRS 3 SET HDG
ADC 1 FAIL
ADC 2 FAIL
ADC 3 FAIL
ADC 1 DEGRADED
ADC 2 DEGRADED
ADC 3 DEGRADED
ASCB BUS FAULT
ASCB CTRL 1 FAULT
ASCB CTRL 2 FAULT
ASCB CTRL 3 FAULT
FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
11−10−54
FLIGHT INSTRUMENTS EICAS MESSAGES (CONT'D)
IRS 1 (2)(3) IN ATT
Indicates that IRS mode
selector has been selected
to ATT.
IRS 1 (2)(3) AUX PWR
Indicates that IRS has lost
its normal power source
and has reverted to
auxiliary DC power.
IRS 1 (2)(3) AUX FAIL
Indicates IRS back-up
power source has failed.
IRS 1 (2)(3) NO ALIGN
Indicates IRS fails to properly
align due to improper position
entry or excessive airplane
motion, while in align mode.
IRS 1 (2)(3) FAIL
Indicates IRS has failed. (IRU
has detected an internal failure).
GF1110_102c
IRS 1 AUX FAIL
IRS 2 AUX FAIL
IRS 3 AUX FAIL
IRS 1 FAIL
IRS 2 FAIL
IRS 3 FAIL
IRS 1 NO ALIGN
IRS 2 NO ALIGN
IRS 3 NO ALIGN
IRS 1 AUX PWR
IRS 2 AUX PWR
IRS 3 AUX PWR
IRS 1 IN ATT
IRS 2 IN ATT
IRS 3 IN ATT
FLIGHT INSTRUMENTS
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−55
HEAD-UP DISPLAY SYSTEM (HUD) (IF INSTALLED)
The HUD is an electronic and optical system which is used to generate and display situational
awareness and guidance to the pilot. The combiner presentation is a repeat of the pilot’s PFD
information (airspeed, altitude, attitude, vertical speed, autothrottle, BARO set, compass, AP/FD
modes, sensor and navigation source annunciation, navigation information and flight guidance). The
combiner will also display specific symbology pertaining to HUD only.
The HUD is composed of:
• Heads-Up Display Computer (HUD Computer)
• Optical Projector Unit
• Combiner Unit
Combiner Unit
GF1110_057
The HUD can be used for full flight operation including:
• Take-off and Go Around with pitch reference,
• Climb, Cruise and Descent with FD guidance,
• Precision (down to CAT 2) and Non-Precision Approach with FD guidance and Visual
Approaches.
FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
11−10−56
HEAD-UP DISPLAY SYSTEM (HUD) (IF INSTALLED) (CONT'D)
HUD Schematic
GF1110_058
NAV
1
NAV
2
RADIO COMMUNICATIONS BUS
SPC
1
IAC
1
IRS
1
ADC
1
RAD
1
EGPWS
TCAS
ADC
3
IRS
3
IAC
3
SPC
2
IAC
2
IRS
2
ADC
2
RAD
2
Channel A
DAU 4
Channel B
PFD EICAS
Optical
Projector
Unit
Combiner
MON
COM
I/O
I/O
0.88
FMS1 SRP
23.4NM
BARO
3
6
E
12
15
21 S
24
W
30
33 N DTK
360
LIM
0.856M
TOTAL FUEL (LBS) 41550
1.54 1.54
73.3 73.3
789 789
14600 10000 14600
2350 ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
5750
115
81
93.4
5750
115
81
EPR
N1
ITT
AIL
1.65 1.65
CRZ
AP1 FLC
2250
HUD
Computer
FLIGHT INSTRUMENTS
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−57
HEAD-UP DISPLAY SYSTEM (HUD) (IF INSTALLED) (CONT'D)
Head-Up Display Computer
The HUD Computer is mounted in the avionics bay and interfaces with the airplanes avionic and
electrical systems. 28 VDC is supplied to the HUD Computer from the DC BUS 2 via the EMS
CDU and is controlled by the HUD BRT/DIM knob located on the glareshield. The HUD Computer
　
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