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24
W
30
33 N DTK
360
LIM
0.856M
0.88
FMS1 SRP
23.4NM
BARO
3
6
E
12
15
21 S
24
W
30
33 N DTK
360
LIM
0.856M
CKPT (°C) FWD
CABIN (°C)
AFT
CABIN (°C)
20
90
22
20
22
20
1300
0.00
500
OXYGEN
CAB ALT
P
20 CAB RATE
%
OIL QTY (QTS)
ENG
APU
RES
12.3
4.5
5.0
12.3
APU
RPM 100 EGT 650
BRAKE TEMP
04 05 04 04
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
1
0
13 %
OPEN
13
OPEN
OUTFLOW VALVES
1 2 0
% 1 2
2
KPHX
4000
KDVT
50 50
KLAX
KPHX
FL180
KSRP
KDVT
4000
TOC SAT
TAT
ETE
TAS
NM
GSPD
KSRP
ET
TOC
KLAX
−56
−40
234
LX
345
00:10
WX
T5.0%
LUF
1+36
12.5
KDVT
TRU
N
FMS1
KPHX
4000
KDVT
50 50
KLAX
KPHX
FL180
KSRP
KDVT
4000
TOC SAT
TAT
ETE
TAS
NM
GSPD
KSRP
ET
TOC
KLAX
−56
−40
234
LX
345
00:10
WX
T5.0%
LUF
1+36
12.5
KDVT
TRU
N
FMS1
FLIGHT INSTRUMENTS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
11−10−2
PITOT-STATIC SYSTEM
Three pitotstatic
(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.
Use and distribution of these pitotstatic
probes are as follows:
Source Use
PS 1 Normal pitot/static input to the pilot’s side Mach transducer (if installed) and ADC 1.
PS 2 Normal pitot/static input to the copilot’s side Mach transducer (if installed) and ADC
2.
PS 3 Normal pitot/static input to ADC 3.
PS Standby Normal pitot/static input to standby instruments.
Three Total Air Temperature (TAT) probes are provided to supply temperature input to the ADCs. Ice
protection is provided by electric heating elements for the PS probes and TAT probes (refer to
Chapter 14, Ice and Rain Protection).
GF1110_004
PS STANDBY
PS 1
PS 3
PS
STANDBY
PS 2
TAT 3
TAT 3
PS 2
TAT 2
TOP VIEW
ENGINE INLET
TAT 1/2 PROBE
PS 3
PS 1
TAT 1
FLIGHT INSTRUMENTS
Rev 5, Jul 21, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
11−10−3
PITOT-STATIC SCHEMATIC
GF1110_005a
TEMPERATURE
PROBE NO. 1
LEFT ENGINE
ADC 1
UPPER LEFT
PITOT/STATIC
NO. 1
UPPER RIGHT
STANDBY
PITOT/STATIC
COPILOT
VALVE
MACH TRANSDUCER
SELECTOR VALVE
S1
S2
P1 S1
S2
P1
S1
S2
P1 S1
S2
P1
TEMPERATURE
PROBE NO. 3
FUSELAGE
TEMPERATURE
PROBE NO. 2
ADC 3 ADC 2 RIGHT ENGINE
MACH TRANSDUCER
(on airplane 9002 thru 9158)
LOWER LEFT
PITOT/STATIC
NO. 3
LOWER RIGHT
PITOT/STATIC
NO. 2
(on airplane 9002 thru 9158)
STANDBY
INSTRUMENT
FLIGHT INSTRUMENTS
Flight Crew Operating Manual Rev 5, Jul 21, 2005
CSP 700−5000−6
Volume 2
11−10−4
AIR DATA SYSTEM
The air data system provides computed air data (speed, altitude and temperature data) to various
systems:
· Integrated Avionics Computers (IAC).
· Data Acquisition Units (DAU).
· Inertial Reference System (IRS).
· Stall Protection Computer (SPC).
· Electronic Display System (EDS) − EFIS and EICAS.
· Automatic Flight Control System (AFCS).
Pitot and static pneumatic inputs and total air temperature provide raw air data information to the
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