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The heated surfaces are each monitored by two RTDs. The fairing, being cyclically heated and not
controlled to a given temperature, has two overheat detection RTDs. The IRW is controlled to a
specific temperature set point, has one control and one overheat RTD. In the case of a single
sensor failure, the remaining sensor will assume both functions.
Status information is displayed to the pilot by means of the EICAS. The EVSHC communicates
with the CAIMS, IAC and the DAU to provide failure indication and maintenance information.
IRW Demisting Control
The IRW is controlled by the EVSHC to a temperature sufficient to prevent condensation. The
EVSHC controls the activation of the demisting based on a demist set point as calculated by the
HUD based on SAT and is only active while the ISU is ON. This set point is transmitted from the
HUD to the EVSHC via the DAU on the ARINC bus. When both deice and demist conditions are
required, the higher window temperature is utilized to ensure both clear view and ice protection are
maintained.
FLIGHT INSTRUMENTS
Flight Crew Operating Manual Rev 7, Dec 01, 2005
CSP 700−5000−6
Volume 2
11−10−100
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Ice Protection System Architecture
GF1110_111
HFDC
Control
ASCB (Chanel A & B)
DAU 4 IAC EICAS
MADC
AntiIce
AntiIce
DAU 2
Right Cowl Left Cowl
Switch Switch
EVS HEATER
CONTROLLER
ARINC 429
ARINC 429
115 Vac AC Bus 1
1 , 5A CB
IR Window
Sensor
OVHT
Sensor
OVHT
115 Vac AC Bus 1
3 , 7.5A CB
EVS FAIRING
Sensor
OVHT
Sensor
Temp
Sensors
Heater
Power Temp
Sensors
Heater
Power
28 VDC Essential Bus
SSPC 2.5 ACB
Window Power Input,
115 Vac 1
Fairing Power Input,
115 Vac 3
EVS ISU
ON
EVS Control Panel
The EVS control panel is located on the left pilot’s glareshield. The EVS control panel includes the
following functions:
· HUD OFF/BRT control
· EVS OFF/MAX control
· EVS Calibration (CAL) push button
GF1110_105b
MASTER
WARNING/CAUTION
ROLL SPLRS
PLT CONT
OFF BRT
WARNING
CAUTION
ROLL
SEL
PLT
ROLL
OFF MAX
PUSH/CAL
EVS
EVS Control Knob
HUD Control Knob
HUD
Push button (short press)
− 6 sec CAL
Push button (long press)
− 22 sec CAL
FLIGHT INSTRUMENTS
Rev 7, Dec 01, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
11−10−101
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Clear Switch
An EVS image clear switch is incorporated into the left pilot handwheel outboard of the horizontal
stabilizer trim switches. The EVS Clear Switch can be activated at any time to remove the EVS IR
image and the raster symbology from the combiner while maintaining the aircraft flight symbology
by reverting to the stroke mode. The function of removing the IR image is an aide in obtaining or
verifying the normal vision without IR enhancement or to deal with any malfunction of the EVS that
could impair the pilot’s normal view through the combiner and windshield.
GF1110_106
EVS IMAGE
CLEAR SWITCH
Brightness Control
The HUD OFF/BRT control is used to control the overall projector brightness affecting symbology
and image brightness, but not image contrast. The HUD OFF/BRT control and EVS OFF/MAX
control interact in order to make it impossible to provide an EVS image that is brighter than the
symbology brightness. This ensures that symbology is always available in various lighting
conditions.
The EVS image brightness and contrast are controlled by a single contol knob (EVS OFF/MAX).
The 12 O’clock position is the recommended EVS control seting for IMC operations. The EVS
control position may be adjusted to obtain the optimum image in VMC conditions. Turning the EVS
OFF/MAX control knob clockwise increases the IR image illumination. Turning the EVS OFF/MAX
control knob counterclockwise decreases the IR image illumination.
Both EVS brightness and contrast affect only the video signal transmitted by the HUD computer to
the HUD projector.
The EVS OFF/MAX control uses two independent brightness/contrast tables, one for night and
one for day conditions. The HUD ambient light detector provides a voltage, based on sensor
illumination, to the HUD computer to determine which table will be used. This operation is
transparent to the pilot.
　
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