GULFSTREAM G650ER
SYSTEM DESCRIPTION MANUAL
ENHANCED VISION SYSTEM II — SYSTEM DESCRIPTION
1. General
A. Description
The Enhanced Vision System (EVS) II is a Forward Looking Infrared (FLIR) camera system which
provides a clear image to the flightcrew during low visibility conditions. This allows the flightcrew to
safely continue taxi, takeoff and approach to landing phases of flight in marginal weather conditions.
See Figure 1 , Figure 2 and Figure 3.
2. Component Location
COMPONENT ATA QTY PER A/C LOCATION
Enhanced vision system II
34-29-01 1 Above and behind radome
camera
Enhanced vision system II
34-29-03 1 LEER
processor
Enhanced vision system II
34-29-05 1 Above and behind radome
window assembly
Enhanced vision system II
34-29-07 1 Cockpit overhead panel
window heat switch
3. Component Details
A. Enhanced Vision System II Camera
The EVS II camera incorporates FLIR hardware and software that provides a clear Infrared (IR)
image to the EVS II processor. The EVS II camera also sends status information to the EVS II
processor.
B. Enhanced Vision System II Processor
The EVS II processor receives and processes IR video from the EVS II camera and routes it to the
HUD II for display. The processor also receives status information from both the camera and the
window assembly. Communication between the camera and processor is over an Ethernet fiber
optics bus. The processor then sends this status information to the single generic input / output
module No. 1 located in modular avionics unit No 1 where it is used to display CAS messages to the
flightcrew. The processor performs the following major functions:
• Built-in Test (BIT)
• Communication with the HUD II via ARINC 429
• Communication with the EVS II camera via Ethernet over fiber optic cable
• Monitors video integrity
• Monitors and controls the window heat
• Notifies the HUD II, monitor warning function and Central Maintenance Computer (CMC) of a
failure condition
• Records fault data, system parameters, accumulated operational processor time and
cooldown time of the FLIR sensor in nonvolatile memory
• Sends debug output to the RS-232 serial port
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C. Enhanced Vision System II Window Assembly
The EVS II window assembly is mounted above and behind the radome. It provides the EVS II
camera a clear view while protecting it from the atmospheric and flight conditions. The window is a
¼ in thick synthetically grown sapphire pane with an antireflection coating on both the inner and
outer surfaces. The window assembly incorporates a dual heater grid bonded to the inner surface of
the window to eliminate the formation of condensation or ice on the window. There are also three
thermostats bonded to the inner surface.
The window heat is controlled via the EVS II processor. The window assembly also sends status
information to the EVS II processor.
The EVS II processor monitors the three thermostats on the inner surface of the window assembly.
When the temperature of the window assembly is ≤ 54°F (12°C), the EVS II processor applies
power to the dual heater grid. When the temperature of the window assembly is ≤ 57°F (14°C), the
EVS II processor removes power from the dual heater grid.
D. Enhanced Vision System II Window Heat Switch
The flightcrew may manually apply window heat by selecting the EVS WSHLD HT switch on the
cockpit overhead panel. This momentary switch provides a ground signal to the EVS II processor.
The EVS II processor will then apply power to the dual heater grid for approximately 2 minutes. The
(blue) EVS WSHLD HT switch will come ON anytime power is applied to the dual heater grid.
4. Controls and indications
A. Circuit Breakers
The system is protected by the following solid state power controllers:
NOMENCLATURE IDENTIFICATION NUMBER POWER SOURCE
EVS CAM 3404 L MAIN DC
EVS HTR 3405 L MAIN DC
EVS PROC 3406 L MAIN DC
B. CAS Messages
The CAS messages for the EVS II are shown in the following table:
MESSAGE COLOR MESSAGE DESCRIPTION
Indicates a failure of EVS window system. The EVS
remains operational at the discretion of flightcrew.
The following may cause this message:
• Nonuniformity Correction (NUC) does not occur with
flaps 10° or occurs at some other time
EVS Maintenance Required Blue
• FLIR temperature controller BIT fails
• FLIR processor BIT fails
• EVS processor has detected a fault that prevents
normal control of EVS but valid video is still being
produced
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MESSAGE COLOR MESSAGE DESCRIPTION
Indicates serious failure within the EVS system. The EVS
system is shut down and flightcrew is not allowed to use it.
Any imagery displayed on HUD is immediately removed.
The following may cause this message:
• Sensor assembly BIT fails
• Camera operating below minimum operating
EVS Fail Amber temperature of 41°F (5°C)
• Camera operating above maximum operating
temperature of 131°F (55°C)
• Video misalignment
• Display goes full bright
• Video signal from EVS camera not present
Indicates a maintenance requirement. The message occurs
only if there is a noncritical maintenance issue with EVS
that should be addressed by maintenance.
The following may cause this message:
EVS Window Heat Fail Amber • Window temperature above 158°F (70°C)
• Both heater grids have failed
• Power lost or circuit breaker open
5. Operation
A. Enhanced Vision System II
The EVS II has two modes of operation called flight mode and maintenance mode. These states are
dependent on the following two aircraft conditions: Airspeed and WOW. Anytime the airspeed is >
50 kts or WOW on both main landing gear disappears, EVS II will revert to flight mode. Maintenance
functions are inhibited in flight mode. When WOW on both wheels is present again and airspeed is
< 50 kts, the EVS II operation changes to maintenance mode. The previously inhibited functions are
released for operation. See Figure 4.
If the EVS II is powered on in maintenance mode, a power-up BIT is performed, taking
approximately 15 seconds. When powered on in flight mode, the EVS II skips the power-up BIT and
completes initialization within 5 seconds, given that power-up BIT was performed prior to takeoff.
When initially powered on, the EVS II camera may take up to 15 minutes to cool the FLIR detector
to operating temperature in a moderate climate. When the aircraft is parked overnight in
temperatures below -41°F (-40°C), the EVS II camera may take up to 35 minutes to bring the
electronics and FLIR detector to operating temperature. The EVS II processor will output video from
the EVS II camera during the cooldown process. However, this video is only displayed on the head-
down display during this time. Once the EVS II camera is cooled to temperature, the EVS II
processor will perform a NUC and then enable video to be displayed on the HUD.
The EVS II acquires its imagery with the FLIR assembly located in the camera. The video is sent to
the processor and forwarded from there to the HUD II system. The image activity is projected onto
the HUD II combiner glass in a high resolution combined stroke / raster format. The imagery is
combined with the necessary flight guidance and navigation data normally displayed on the
combiner glass.
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SYSTEM DESCRIPTION MANUAL
An EVS/HUD CLEAR button on the control column yoke functions as an EVS II video toggle button.
If selected while EVS II video is displayed, the video will be immediately removed from the combiner
glass. Subsequently selecting this button will toggle video back on. If the EVS II is off (has not been
through the power on sequence) or the EVS II has been deactivated since the EVS/HUD CLEAR
button was selected, this button will not affect (activate) the EVS II.
(1) Window Heat
The EVS II processor unit controls power application to the dual heater grid to prevent ice
buildup on the window. There are four modes of heat operation; no heat, cyclic, continuous
and manual on.
When the aircraft anti-ice system is active, heat is applied to the window as continuous or
cyclic (1 minute on, 7 minutes off). The following table indicates window heat modes based on
logic inputs:
EVS WSHLD
LEFT COWL RIGHT COWL GEAR WINDOW HEAT
HT SWITCH
A/I A/I POSITION MODE
COMMAND
No ice detected No ice detected X(1) Heat off Heat off
Heat on - Cyclic (7
No ice detected Ice detected Up Heat off minutes off, 1 minute
on)
Heat on - Cyclic (7
Ice detected No ice detected Up Heat off minutes off, 1 minute
on)
Heat on - Cyclic (7
Ice detected Ice detected Up Heat off minutes off, 1 minute
on)
No ice detected Ice detected Down Heat off Cyclic with thermostat
Continuous with
Ice detected No ice detected Down Heat off
thermostat
Continuous with
Ice detected Ice detected Down Heat off
thermostat
Heat on - Continuous
X (1) X(1) X(1) Heat on with thermostat (2
minutes on, then off)
(1)
The X indicates no affect on system.
When one of the heater on modes is selected and the temperature of the window is at or
below 54°F (12°C), power is applied to the heater grid.
When the temperature reaches 57°F (14°C) or more, power to the heater grid is turned off.
When EVS WSHLD HT switch is selected ON, a ground is applied to the EVS II processor. At
this point, the EVS II processor applies power to the window heat grid for approximately 2
minutes.
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If the window temperature rises above 70°F (21°C), it triggers the second thermostat and the
EVS Maintenance Required (blue) message appears on the CAS display. The (blue) EVS
WSHLD HT switch will come ON anytime power is applied to the dual heat grid.
(2) Fault Detection Modes
The EVS II functions either maintenance mode or flight mode.
(a) Maintenance Mode
In maintenance mode only internal faults are recorded to nonvolatile memory; external
faults are not recorded. Faults detected during this mode are reported to the CMC for
recording.
(b) Flight Mode
In flight mode any fault detected is written to nonvolatile memory since maintenance
activities cannot be the cause of any external faults. Faults detected during this mode
are reported to the CMC for recording.
(3) Maintenance mode
Maintenance mode is available when the WOW discrete value is true and the MAINT TEST
switch located on the system monitor and test panel in the REER is selected on. Maintenance
mode allows for adjustment and operational assessment of the EVS II components.
While in maintenance mode, registration of the EVS II image is done through this CMC
interface. The EVS II is successfully registered when the EVS II video depicting the real world
accurately overlays the actual real world view through the cockpit window. The nonvolatile
ram within EVS II processor may also be downloaded via the CMC.
When in maintenance mode, the EVS II cannot be used for other activities. The entire system
is occupied with test functions. Results are displayed on the CMC maintenance pages. When
an EVS Maintenance Required (blue) or an EVS Fail (amber) message is reported on CAS,
the reasons for these messages will usually be ascertained from the CMC system status
pages.
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SYSTEM DESCRIPTION MANUAL
SEE DETAIL A
SEE DETAIL C
SEE DETAIL B
DETAIL A
TIL-008020
Enhanced Vision System II Window and Camera Location
Figure 1
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SYSTEM DESCRIPTION MANUAL
DETAIL B
DETAIL C
TIL-008021
Enhanced Vision System II Window and Camera
Figure 2
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SYSTEM DESCRIPTION MANUAL
SEE DETAIL A
DETAIL A
TIL-008022
Enhanced Vision System II Processor Location
Figure 3
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SYSTEM DESCRIPTION MANUAL
POWER RS-232 / 422
28 VDC MAINTENANCE
SMPTE - 170
ANALOG VIDEO
3 PORTS
EITHERNET
CONTROL ARINC 429
4 PORTS (RX / TX)
DISCRETE INPUTS
24 PORTS
FLIR PROCESSOR
ASSEMBLY ASSEMBLY
DISCRETE OUTPUTS
8 PORTS
EITHERNET
CONTROL IR RS - 232 MAINTENANCE
DATA & STATUS
SMPTE - 259M
DIGITAL VIDEO
2 PORTS
POWER SUPPLY 28 VDC
WINDOW ASSEMBLY
IR WINDOW HEATER MONITOR
ASSEMBLY
TIL-008023
Enhanced Vision System II
Figure 4
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SYSTEM DESCRIPTION MANUAL
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