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Chapter 14, Ice and Rain Protection.
TAT PROBE
RIGHT PITOT/
STATIC PROBE
LEFT PITOT/
STATIC PROBE
LEFT STANDBY
STATIC PORT
CFO1101002_003
RIGHT STANDBY
STATIC PORT
STANDBY PITOT
PROBE
REV 5
FLIGHT INSTRUMENTS
Volume 2 Flight Crew Operating Manual Feb 22/2006
11-01-14 CSP 100-6 REV 5
AIR DATA SYSTEM (Cont)
TOTAL AIR TEMPERATURE PROBE
An electrically heated total air temperature (TAT) probe is mounted on the right forward fuselage. The TAT probe has two
independent temperature sensors. One sensor is connected to ADC 1 and the other to ADC 2.
The ADCs use the total air temperature to calculate the static air temperature (SAT) and the true airspeed (TAS).
The use and distribution of the pitot and static sources are as follows:
- P1 is the normal pitot input to ADC 1
- S1 is the normal static input to ADC 1
- P2 is the normal pitot input to ADC 2
- S2 is the normal static input to ADC 2
-S3 is the static input to the integrated standby instrument
CFO1101002_028
LEGEND
PITOT
STATIC
MANIFOLD
ADC
2
ADC
1
P2 S1 S2
P1 S1 S2 STBY STANDBY
STATIC
STANDBY
STATIC
STANDBY
INSTRUMENT
V 5
FLIGHT INSTRUMENTS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 11-01-15
ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS)
INTRODUCTION
The aircraft attitude and heading reference system (AHRS) is a strapped gyro reference system that generates angular rate
and linear acceleration information about the aircraft axes.
Combining the acceleration gyro information with heading data from the flux detector provides highly accurate three-axes
AHRS information.
The AHRS interfaces with the following systems:
- EFIS
- Weather radar
- Autoflight control system (AFCS)
- Flight data recorder (FDR)
- Integrated avionics processor system (IAPS)
- Terrain awareness warning system (TAWS)
- Traffic alert and collision avoidance system (TCAS)
- Stall protection system
The AHRS consists of two computers, two flux detector units and two external compensator units. Both Attitude Heading
Reference Systems are active permanently. AHRS mode selections are carried out through the COMPASS HEADING and
COMPASS SLEW switches. The AHRS normally operates in magnetic mode (MAG). Directional gyro mode (DG) may
be selected in areas where magnetic field disruptions exist.
The AHS-3000/3000A system is not designed for use as a polar navigator. Flying in or around the fringe of low magnetic
flux areas can cause temporary dropouts in required flux levels for the system to operate properly.
Initialization and operation of the AHRS occurs automatically when electrical power is established and the aircraft is stationary.
Initialization takes approximately 40 seconds in MAG mode and 4.5 minutes in DG mode.
REV 1
FLIGHT INSTRUMENTS
Volume 2 Flight Crew Operating Manual Sep 13/2004
11-01-16 CSP 100-6 REV 1
ATTITUDE AND HEADING REFERENCE SYSTEM (Cont)
COMPONENTS AND OPERATION
AHRS COMPUTERS
Each AHRS computer has a dual-sensor assembly. Each sensor assembly has four pairs of piezoelectric accelerometer sensors
mounted on a rotating wheel. These sensors provide the rate and acceleration data.
The sensor data combined with ADC and heading information is processed by the AHRS computers and transmitted for
use by the adaptive flight displays (AFD), and by the integrated avionics processor system (IAPS), which itself interfaces
with the flight guidance computer (FGC) and flight management system (FMS).
MAGNETIC FLUX DETECTORS
Each of the two magnetic flux detectors senses the earth’s magnetic field and provides corrected heading information to its
respective attitude heading computer.
External compensator units store corrections for any north/south, east/west or misalignment of the flux detectors.
COMPASS CONTROL AND SLEW SWITCHES
There are two COMPASS HEADING switches and SLEW switches located on either side of the main flight instrument
panel. There are two modes of operation, magnetic heading (slaved) mode, and directional gyro (DG or free gyro) mode.
The HEADING switches are used to select the mode.
In the magnetic heading mode, heading computations are slaved to the attitude heading computer and the flux detectors. In
DG mode, magnetic flux detector data is removed. DG mode is not intended for long term heading reference.
In DG mode, the selection of the SLEW switch causes the heading to slew in the selected direction.
ATT/HDG REVERSION SWITCH
The ATT/HDG switch is located on the center pedestal. When NORM is selected, the left PFD and MFD receive data from
　
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