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ALTN ALTN2 ALTN1 ALTN
ALTN3
MINIMUMS NAV SCR BARO SET RAD BARO IN HPa
PFD1 EICAS PFD2
PUSH STD
PFD1 PFD2
PFD Control Panel
IRS ADC ADC IRS
ADC
NORM NORM NORM
ALTN ALTN ALTN
SG1 SG3 SG2
Reversion Control Panel MFD Control Panel
In the event of a PFD failure, the PFD format may be displayed on the adjacent MFD by actuation of the reversionary mode switch (PFD1 or PFD2) on the reversion control panel. MFD format can also be replaced by EICAS page and/or SYSTEMS page. For more information, see Chapter 3.
PFD format can be changed by actuation of HSI button on the PFD control panel. MFD format can be changed by actuation of the MAP/PLAN button, MENU button and/or checklist buttons (NORM, ABN and EMER) on the MFD control panel.
GF1110_001
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
FLIGHT INSTRUMENTS
EFIS NETWORK
GUIDANCE PANEL
PFD PFD CONTROLLER
TO IAC 1,2,3 CONTROLLER #1
#2
REVERSION
CONTROLLER
LIMLIM 0.881.65 1.65 CKPT (°C) FWD AFT CAB ALT 13000.88
TRU FMS1TRU FMS1
CABIN (°C) CABIN (°C)1.54 1.54 P 0.00
N
2022 22 N
2020 20 CAB RATE 500
CRZ
1 2 TOC
TOC EPR OXYGEN 90 %
OUTFLOW VALVES KSRPKSRP KDVTKDVT 73.3 73.3 12 0 KLAX
KLAX 0OPEN OPEN
KPHX 50 50
KPHX 50 50 13% 13% 12
N1 OIL QTY (QTS)
12.3 ENG 12.3 KLAX 789 789 APU 4.5
KLAX LUFLUF
RES 5.0
0.856M BARO0.856M BARO 23.4NM
23.4NM
12.5NM12.5NM
ITT APU FMS1 SRPFMS1 SRP
KDVT NN KDVT
DTK 360 24 W 30 33 3 6 E 12 4000 KPHX FL180 KDVT 4000 TOC SAT TAT ETE TAS GSPD KSRP ET .56 .40 234 345 00:10 WX T5.0% 1+36 NU TRIMS 7.2 N2 FF (PPH) OIL TEMP OIL PRESS 93.4 5750 115 81 93.4 5750 115 81 AIL RPM EGT100 650 BRAKE TEMP 04 05 04 04 4000 KPHX FL180 KDVT 4000 TOC SAT TAT ETE TAS GSPD KSRP ET .56 .40 234 345 00:10 WX T5.0% 1+36 DTK 360 24 W 30 33 3 6 E 12
15S21 LX TOTAL FUEL (LBS) 41550 LWD RWD LX 15S21
14600 1460010000 2350 ND STAB RUDNL DER NR
IRU 3
EGPWS
IRU 2
IAC 2IRU 1 IAC 1 IAC 3
WX RADAR WX RADAR CONTROLLER 1
CONTROLLER 2
RX/TX ANTENNA
EICAS CONTROLLER
FMS 1 FMS 22
IRS MODE SELECTOR MFD
MFD CONTROLLER
CONTROLLER 1
TO IRU 1,2,3
NAVIGATION DISPLAY ADC 1 UNIT
ADC 2
DAU 2DAU 1 DUAL SERVO’S YAW DAU 3 DAU 4 ADC 3DAMPERS
AILERON ELEVATOR 1 2
SYSTEMS AND
SYSTEMS SENSORS
AND
THROTTLE SENSORSQUADRANT ASSEMBLY
GF1110_002
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
11.10.2 CSP 700.5000.6
Three pitot-static (PS) systems designated PS 1, PS 2 and PS 3 are provided to supply variable pressure inputs to the 3 Air Data Computers (ADC) and to the Mach transducer (if installed). A standby PS source is also provided to supply inputs to the standby instruments.
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