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adjust the display in the same way. The DT flag is lit
• By depressing the MODE button once, the LT minutes’s digits are flashing and
you can adjust the display in the same way. The LT flag is lit
• By depressing the MODE button once, the LT hours’s digits are flashing and you
can adjust the display in the same way. The LT flag is lit
• One more press on MODE button will lead to GMT minutes adjustment
• Press the MODE button for more than two seconds to start the clock operation
The default time and date for the SET mode at initialization of the clock will be: The
1st of January 2002 at 00 hr and 00 min.
Set after Synchronization by GPS or Manual Starting
If the GPS data is valid, only the LT mode can be set.
The setting is obtained by means of the SET function which is available by pressing
the MODE pushbutton for a minimum of two seconds.
• By depressing the MODE button, the setting roll in LT time if the LT setting is
chosen
• By depressing the MODE button, the setting roll in DATE if the DT setting is
chosen
• By depressing the MODE button, the setting roll in the INT time if the INT setting
is chosen
For Training Purposes Only
Sept 04
7-107
P I LOT T R A I N I N G GU I D E
ELECTRONIC DISPLAY SYSTEM
STANDBY AIRSPEED/ALTITUDE/ALTIMETER (IF INSTALLED)
Incorporated in the indicator is a light sensor that provides ambient light level data to
the automatic lighting system.
A navigation (NAV) button is selected to display ILS (localizer and glideslope)
deviation information. The ATT button is used to erect the display.
GX_07_079
20
20
10
10
20
20
10
10
1300
360 200
340 000
300
NAV ATT
600
290 400
320 26800
M.789 1013 HP
29.92 IN
Light Sensor
Attitude Barometric Set
Altimeter
Setting Inches
Attitude
Indicator
Altitude
Tape
Altimeter Setting
Hectopascals
Navigation
MACH Number
Airspeed
Tape
P I LOT T R A I N I N G GU I D E
ELECTRONIC DISPLAY SYSTEM
7-108 For Training Purposes Only
Sept 04
PFD COMPARISON MONITOR ANNUNCIATIONS
Comparison monitor annunciations are displayed when the difference between the
data received by the pilot’s and copilot’s PFD, exceeds the predetermined trip
thresholds.
If both PFDs have misleading data, CHECK PFD message will be displayed on the
EICAS display.
SYSTEM INTEGRATION
The Electronic Flight Instrument is tightly coupled with both the Automatic Flight
Control and Navigation Systems. This is the case as it reflects the output of these
systems for pilot consumption and action while providing the source data upon which
it is based. The three-sided, interdependent relationship between these systems can
make fault determination difficult in the event of a failure in one. Aircrew need to be
cognizant of this fact and address such eventualities in a disciplined, step-by-step
manner.
GX_07_080
20 20
10 10
10 10
20 20
HDG
29.92 IN
AP1 ASEL
CRS
030
HDG
030
1000
VS 1000
200 10400
10000
80
20
9500
10500
220
210
200
190
180
170
160
150
185
6
4
0
1
2
3
1
2
3
LOC
LOC
FWC
HDG
FWC
EICAS
ALT
RAD
RAD
ATT
G
S
G
S
IAS
IAS
PIT
ALT
ROL
ATT
HDG
EICAS
Indicates a
miscompare of
± 20 knots.
Indicates a
miscompare of
± 5° of pitch.
Indicates a
miscompare of
± 0.24°.
Indicates a
miscompare
of ± 10 feet.
Indicates a
miscompare
of ± 1/2 dot.
Indicates CAS
message
miscompare
(warnings, cautions
and advisories) for
more than 7
seconds.
Indicates a
miscompare of
± 200 feet.
Indicates a
miscompare of
± 6° of roll.
Indicates a
miscompare of ± 5°
of pitch and ± 6° of
roll.
Indicates a
miscompare
of ± 10°.
Indicates engine data
miscompare between the
sensors (DAU) and the
engine parameters for
more than 3 seconds.
N
33
30
W
24
21
S
15
12
E
6
3
For Training Purposes Only
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航空翻译 www.aviation.cn
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