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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
Rev 5, Jul 21, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
11−10−5
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.
Pilot’s Side
Normally fed as follows:
Copilot’s Side
Normally fed as follows:
PFD Annunciation
Pilots Selected
ADC
Copilots Selected
ADC
PFD1 Source
Annunciation
PFD2 Source
Annunciation
ADC1 ADC1 ADC1 ADC1
ADC1 ADC2
ADC2 ADC1 ADC2 ADC1
ADC2 ADC2 ADC2 ADC2
ADC1 ADC3 ADC3
ADC2 ADC3 ADC2 ADC3
ADC3 ADC3 ADC3 ADC3
ADC3 ADC1 ADC3 ADC1
ADC3 ADC2 ADC3
ADC Source Annunciation
GF1110_007
ADC 1 − if reverted then,
ADC 3 − if reverted then,
ADC 2.
ADC 2 − if reverted then,
ADC 3 − if reverted then,
ADC 1.
HDG AP2 FLC 100 00
VOR ADC2
NORM
ALTN
PFD1
NORM
ALTN1
EICAS
NORM
ALTN
PFD2
ALTN2
ALTN3
PFD1 PFD2
NORM
ALTN
SG1
NORM
ALTN
SG3
NORM
ALTN
SG2
IRS ADC ADC IRS
FLIGHT INSTRUMENTS
Flight Crew Operating Manual Rev 5, Jul 21, 2005
CSP 700−5000−6
Volume 2
11−10−6
INERTIAL REFERENCE SYSTEM
The Inertial Reference System (IRS) provides attitude, directional, position and 3axis
rate/accelerometer data to the following airplane systems:
· PFDs and MFDs
· Weather radar system
· AFCS
· EGPWS
· TCAS
· Stall protection system
· Fuel system
· Flight data recorder
· Air data computer
· FMS
Each IRS computer (IRS 1, IRS 2, IRS 3) receives true airspeed and altitude from the applicable
(onside,
either left or right side) air data system. In the event of a failure of the onside
air data input,
the offside
input is automatically selected.
The IRS mode select panel, located on the pedestal, is used to initialize the IRS and to select NAV or
ATT modes.
IRS Mode Switches
OFF
NAV
ATT
attitude information, in the event of
NAV mode failure.
IRS Mode selector Panel
G08F1110_008
ALN
(time to align will differ with temperature
and latitude).
after ALN completed.
− Removes power from IRS.
− Normal operating mode, selected
− Reversionary mode, used to provide
− Aligns IRS in approximately 7 minutes
IRS1 IRS2 IRS3
NOTE
During IRS initialization the PFD is in a failure mode.
HDG
IN
CRS
0
1
2
3
1
2
3
BARO
NM
HDG
FAIL
VS
TCAS FAIL
GF1110_009
RAD
ATT
FAIL
FLIGHT INSTRUMENTS
Rev 5, Jul 21, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
11−10−7
INERTIAL REFERENCE SYSTEM (CONT'D)
At an IRS internal temperature between −54°C and −40°C, the power supply will turn on, but normal
alignment will not start until IRS temperature is >−40°C. The IRS will not go to NAV mode until the
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