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FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
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. A standby PS
source is also provided to supply inputs to the standby instruments.
Use and distribution of these pitotstatic
probes are as follows:
PRESSURE
SOURCE
FROM TO
P1 Pilot/Static Probe No. 1 MADC No. 1
P2 Pilot/Static Probe No. 2 MADC No. 2
P3 Pilot/Static Probe No. 3 MADC No. 3
Ps Standby Pilot/Static Probe Standby Instruments / Mach Transducer
S1/S2 Pilot/Static Probe No. 1 and Standby MADC No. 1
S1/S2 Pilot/Static Probe No. 2 and No. 3 MADC No. 2
S1/S2 Pilot/Static Probe No.3 and No. 2 MADC No. 3
S1/S2 Standby Pilot/Static Probe and No. 1 Standby Instruments / Mach Transducer
FLIGHT INSTRUMENTS
REV 46, Jul 21, 2005 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−3
PITOT-STATIC SYSTEM (CONT'D)
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
Flight Crew Operating Manual REV 46, Jul 21, 2005
CSP 700−6
Volume 2
11−10−4
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
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−5
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
ADCs. Static input to each ADC absolute sensors produces the altitude sensor data. Static and pitot
inputs to each ADC differential sensor produces the airspeed sensor data.
ADC 1
ASC
B
ADC 2
ADC 3
AFCS
IRS
DAU
EDS
FMS
AT
PS 3
TAT 3
FADEC
FCU
EGPWS
FLAP/SLAT CU
STALL PROTECTION COMPUTER
CABIN PRESSURE CU
HUD (OPTION)
STANDBY
INSTRUMENTS
PS 2
TAT 2
PS 1
TAT 1
PS
STANDBY
GF1110_006
FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 46, Jul 21, 2005
CSP 700−6
Volume 2
11−10−6
AIR DATA SYSTEM (CONT'D)
Each ADC computes the following:
· Pressure altitude and barometriccorrected
altitude.
· Vertical speed, indicated airspeed, Mach number and true airspeed (TAS).
· Static air temperature (SAT), TAT and temperature variations from ISA.
· IAS reference (using AFCS or manually using SPD switch on guidance panel).
· Vertical speed reference (VS switch on guidance panel).
· Attitude reference.
· Air speed and altitude trend vector (on PFDs).
· Alerts (preselected on flight level 180).
· Static source error correction.
· Maximum speed values (Vmo at all altitudes and Mmo at a constant).
· Overspeed warning (present airspeed and Vmo).
The reversion control panel, located on the pedestal, is used for pilot input to the air data system.
ADC Switches
Used to select
reversion on
appropriate ADC.
　
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