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Infrared Sensor Unit (ISU)
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Infrared Window (IRW)
The Infrared Sensor Unit (ISU) is mounted inside the aircraft TRU bay, aft of the radome. The ISU provides a monochrome video image in RS170 standard to the HUD Computer and FMS CDU.
The Infrared Window (IRW) consists of sapphire glass mounted in an EVS heated fairing. The IRW has a heating element to protect against ice build up from the outside environment, and to prevent condensation from the inside of the TRU bay. The EVS Heater Controller (EVSHC) controls the IRW and fairing heating.
The IRW allows the ISU to see the forward scene of the aircraft, while protecting the ISU from the outside environment.
The HUD displays the IR image via the projector onto the combiner and generates the raster symbology that overlays the IR image. When the EVS image clear switch is selected to CLR or EVS is turned off, the HUD operates in the basic HUD mode.
The HUD interfaces with the ISU and the aircraft systems through ARINC 429 buses and discrete signals. All communication between the EVS and the aircraft systems are conducted via the HUD computer.
The EVS controls are located with those for the HUD on the aircraft glare shield panel.
Volume 2 Flight Crew Operating Manual Rev 7, Dec 01, 2005
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Architecture
Legend
Existing Signal
New or modified signal or data
Existing EVS components
New EVS components
Other sub.system
EVS Ice Protection System Overview
The EVS Ice Protection System (EVS IPS) is comprised of the following units:
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EVS Heater Controller (EVSHC)
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EVS Heated Fairing (EVSHF)
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Infrared Window (IRW)
The EVSHC is located in the nose TRU bay and provides regulation and control of AC current to the EVS Heated Fairing and Infrared Window.
The power distribution of the EVSHC is controlled using zero-crossed Heater Power Switches (HPS) and redundant Fail Safe Relays. To ensure adequate power is distributed to the heater mats, the controller performs current monitoring and is able to detect both over and undercurrent faults.
Temperature sensors for control and monitoring are kept in separate channels for redundancy and the controller can utilize a single sensor to perform both functions in case of failure. This degraded mode is not annunciated to the pilots, but is logged as a maintenance item in CAIMS.
Rev 7, Dec 01, 2005 Flight Crew Operating Manual Volume 2
FLIGHT INSTRUMENTS
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Ice Protection System Overview (Cont’d)
The EVS Heated Fairing is a cast body of aluminium with a heater mat bonded to the inner surface. The heater mat has 3 zones of differing watt densities to account for the variation of accretion and heat transfer rates along the body of the fairing.
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