PILOT TRAINING GUIDE ICE AND RAIN PROTECTION

Table of Contents

Introduction ....................................................................................................................... 14-1

Wing Anti-Ice System........................................................................................................ 14-2
Description .................................................................................................................. 14-2
Components and Operation ........................................................................................ 14-3
Anti-Ice Ducts ........................................................................................................ 14-3
Wing Anti-Ice Valves ............................................................................................. 14-3
Wing Anti-Ice Controller ........................................................................................ 14-3
14th-Stage Isolation Valve .................................................................................... 14-4
Thrust Reverser Override Function ....................................................................... 14-4
Engine Cowl Anti-Ice System............................................................................................ 14-5
Description .................................................................................................................. 14-5
Components and Operation ........................................................................................ 14-6
Cowl Anti-Ice Valves ............................................................................................. 14-6
Pressure Relief Valves .......................................................................................... 14-6
Thrust Reverser Override Function ....................................................................... 14-6
Windshield/Window Anti-Ice System ................................................................................ 14-7
Description .................................................................................................................. 14-7
Components and Operation ........................................................................................ 14-8
Windshield and Window Construction................................................................... 14-8
Control Switches and Function ............................................................................. 14-8
System Test .......................................................................................................... 14-8
Air Data Probes and Sensors Anti-Icing ........................................................................... 14-9
Description .................................................................................................................. 14-9
Components and Operation ...................................................................................... 14-10
Primary Pitot-Static Probes ................................................................................. 14-10
Standby Pitot Probe ............................................................................................ 14-10
Alternate Static Ports .......................................................................................... 14-10
Angle-Of-Attack (AOA) Vanes............................................................................. 14-10
Auxiliary Angle-Of-Attack Vane........................................................................... 14-10
Total Temperature (TAT) Probe .......................................................................... 14-10
Air Data Sensor Heat Controllers (ADSHCs) ...................................................... 14-10
Probe Switches ................................................................................................... 14-11
Ice Detection System ...................................................................................................... 14-12
Description ................................................................................................................ 14-12
Components and Operation ...................................................................................... 14-12
Ice Detection Test ............................................................................................... 14-12

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Controls and Indicators ................................................................................................... 14-13

ANTI-ICE Panel ........................................................................................................ 14-13
EICAS Messages...................................................................................................... 14-14
EICAS Messages - Wing Anti-Ice System .......................................................... 14-14
EICAS Messages - Engine Cowl Anti-Ice System .............................................. 14-14
EICAS Messages - Windshield/Window Anti-Ice System ................................... 14-15
EICAS Messages - Air Data Probes and Sensors Anti-Icing .............................. 14-15
EICAS Messages - Ice Detection System........................................................... 14-15

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List of Figures
Graphic Title Figure

Wing Anti-Ice System........................................................................................................ 14-1

Wing Anti-Ice Components ............................................................................................... 14-2
Cowl Anti-Ice System ........................................................................................................ 14-3
Windshield/Window Anti-Ice System ................................................................................ 14-4
Air Data Probes and Sensors Anti-Icing System .............................................................. 14-5
Ice Detectors..................................................................................................................... 14-6
ANTI-ICE Panel ................................................................................................................ 14-7

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PILOT TRAINING GUIDE ICE AND RAIN PROTECTION

CHAPTER 14: ICE AND RAIN PROTECTION

Introduction
There are four anti-iced areas on the Challenger 604:
• wing leading edges
• engine cowls
• windshields and windows, and
• air data probes
The wing leading edges and the engine intake cowls are anti-iced using engine 14th-
stage bleed air. The windshields, windows and air data probes are anti-iced using
electrical power. An ice detector system provides EICAS indications of ice
accumulation.
Anti-icing of the aircraft tail surfaces is not required.

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Wing Anti-Ice System

Description
The left and right wing leading edges are anti-iced using pressure-regulated 14th-stage
bleed air, distributed by wing anti-ice ducting and piccolo tubes. The system is
controlled by the WING ANTI-ICE switch located on the ANTI-ICE panel. The
WING ANTI-ICE switch normally controls the left and right wing anti-ice valves via
wing-mounted control sensors and the wing anti-ice controller. An isolation valve
allows both wings to be anti-iced from a single bleed source via a crossover duct.
Panel lights and EICAS messages provide indications of system status during
operation.
Stby Thermal Switch
Control Sensor
Overheat Sensor

WING
ANTI-ICE
CONTROLLER

14th Isol

L Cowl R Cowl
A/Ice A/Ice
L R
Wing Wing
A/Ice A/Ice
Valve Valve
L T/R R T/R
PDU PDU
P604_14_002

L R
14th-Stage 14th 14th 14th-Stage
Bleed Air Port SOV SOV Bleed Air Port

BLEED AIR
14TH STAGE
DUCT DUCT
FAIL FAIL
OPEN
CLOSED CLOSED
L ISOL R
BLEED AIR PANEL

Wing Anti-Ice System

Figure 14-1

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Components and Operation

Anti-Ice Ducts

Bleed air taken from the 14th-stage bleed air manifold is ducted to the wing and
ejected from piccolo tubes onto the inner surfaces of the leading edge. After heating
the leading edges, the air is exhausted overboard through louvers located beneath each
wing leading edge. The piccolo tubes extend the full length of the leading edges.

EXHAUST LOUVERS Exhaust Louvers

(on Lower Surface)

P604_14_001
Leading
Edge Skin

Piccolo
Tube

Sensors
! Overheat/Sufficient Heat
! Control
! Standby Thermal Switch
Shroud

Wing Anti-Ice Components

Figure 14-2

Wing Anti-Ice Valves

The left and right wing anti-ice valves are electrically controlled, pneumatically
operated, pressure-regulating shutoff valves. The valves are spring-loaded to the
closed position when no 14th-stage pressure is available or electrical control power is
lost. The wing anti-ice system is normally operated in the NORM mode. A backup
mode (STBY mode) exists should NORM mode fail.

Wing Anti-Ice Controller

The wing anti-ice controller maintains the temperature of the left and right wing
leading edges when NORM mode is selected. The wing anti-ice controller is bypassed
when STBY mode is selected.

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NORM Mode
When the WING ANTI-ICE switch is selected to the NORM position, the wing
leading edge temperatures are continuously monitored by their respective control
sensor. The wing anti-ice controller modulates both wing anti-ice valves
simultaneously to maintain a constant wing leading edge temperature (88°C/190°F).
The green L HEAT/R HEAT lights located on the ANTI-ICE panel will illuminate
when the respective wing leading edge is sufficiently heated to prevent ice
accumulation.

STBY Mode
When the WING ANTI-ICE switch is selected to the STBY position, the wing anti-ice
controller is bypassed and both wing anti-ice valves are independently controlled by
their respective standby thermal switch. The valves will cycle either fully open or fully
closed to maintain the wing leading edge temperature within a predetermined
temperature range (49°C/120°F and 82°C/180°F).

Wing Overheat
Should a wing leading edge reach a temperature of 130°C/265°F or greater, the WING
OVHT warning EICAS message will appear, accompanied by the “WING
OVERHEAT” voice warning and the flashing MAST WARN lights. Once the
temperature drops below this value, the WING OVHT warning message will be
removed.

14th-Stage Isolation Valve

The isolation valve allows both wings to be anti-iced from a single source by using the
crossover duct. The 14th-stage isolation valve is normally closed during wing anti-
icing. Should a wing anti-ice valve fail, or if an engine is not capable of supplying
14th-stage bleed air, the isolation valve can be selected open by the flight crew,
allowing the operative system to anti-ice both wings.
The 14th-stage isolation valve is pneumatically operated and electrically controlled by
the 14th-stage ISOL switch/light on the BLEED AIR panel. Valve status is indicated
by a switch/light OPEN annunciation (see Figure 14-1).
The isolation valve is spring-loaded to the closed position when no 14th-stage bleed
air is available or electrical power control is lost.

Thrust Reverser Override Function

The 14th-stage bleed air cannot simultaneously supply the demands of the thrust
reverser and the wing anti-ice system. Therefore, the wing anti-ice system is
automatically disabled upon thrust reverser operation. The EICAS caution messages
for wing anti-ice are inhibited during thrust reverser operation.

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Engine Cowl Anti-Ice System

Description
The engine cowl anti-ice system prevents ice formation on the cowl leading edges and
the T2 probe at the engine inlet, using pressure-regulated 14th-stage bleed air.
The bleed air is ducted to the T2 probe and to the cowl leading edges from the cowl
anti-ice valve and the ejector. The ejector circulates the air within the cowl with air
ejected from piccolo tubes onto the inner surfaces of the leading edge. After heating
the cowl leading edges, the air is exhausted overboard through a louvered exit at the
bottom of the engine nacelle.
The L(R) COWL ANTI-ICE switch/lights located on the ANTI-ICE panel control the
left and right engine cowl anti-ice valves respectively.

Cowl Anti-Ice
Piccolo Tube
Ejector

T2
SENSOR Pressure
Relief
Valve

To Wing
ANTI-ICE PRESS
Anti-Ice System
COWL SWITCH

Cowl Wing
HEAT Anti-Ice Anti-Ice
ON ON Pressure Valve
HEAT
Regulating
and SOV
L R T/R
PDU
ANTI-ICE PANEL Exhaust
Louver
(Lower
Nacelle)

14th-Stage
Bleed Air 14th-
Port Stage
Bleed
Air SOV

Note: Generic Cowl

P604_14_004

Anti-Ice System
is Shown

Cowl Anti-Ice System

Figure 14-3

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Components and Operation

Cowl Anti-Ice Valves

The cowl anti-ice valves are electrically controlled, pneumatically operated, pressure-
regulating shutoff valves. The valves reduce the high 14th-stage bleed air pressure to a
level suitable for anti-icing of the engine intake cowl and T2 probe. The valves are
fail-safed to the open position. Therefore, if electrical power is lost and bleed air is
available, the cowl anti-ice valves will move to the open position.
Selecting a COWL switch/light to ON commands the corresponding cowl anti-ice
valve to open. When the valve opens, the COWL switch/light will illuminate (as
sensed by the pressure switch) and the COWL A/ICE ON advisory EICAS message
will appear.
If the cowl anti-ice valve fails to open, the L (R) COWL A/ICE caution EICAS
message will be displayed, indicating insufficient pressure.
When the COWL switch/light is deselected, the cowl anti-ice valve is commanded to
close. Should the cowl anti-ice valve remain in the open position (as sensed by the
pressure switch), the L (R) COWL A/ICE caution EICAS message will be displayed
indicating bleed pressure in the system (valve failed to close).

Pressure Relief Valves

The pressure relief valves provide overpressure protection in the event of cowl anti-ice
valve malfunction. When an overpressure condition occurs, the respective relief valve
plunger extends, dumping excess pressure overboard. When extended, the relief valve
plunger is visible from the ground during the external walkaround.

Thrust Reverser Override Function

The cowl anti-ice system is automatically disabled upon thrust reverser operation,
since the 14th-stage bleed air cannot simultaneously supply the demands of the thrust
reverser and the cowl anti-ice system. The EICAS caution messages for the cowl anti-
ice system are inhibited during thrust reverser operation.

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Windshield/Window Anti-Ice System

Description
The windshield/window anti-ice system provides a dual-temperature heating function
on the windshield (LOW and HI) and a single-temperature heating function on the side
windows (LOW).
When HI is selected, heating of the windshield provides an anti-ice capability on the
outer panel while also providing a moderate defogging function on the inner surface.
The LOW setting provides defogging to the windshield and window.
In addition to electrically heating the windshields/windows, a footwarmer/demist
system is available, using an electric element and fan, to demist the inside of the
windshields. This system uses recirculated airflow and is discussed in Chapter 2 Air
Conditioning and Pressurization.

LEFT RIGHT
WINDSHIELD WINDSHIELD

LEFT SIDE RIGHT SIDE

WINDOW WINDOW

P604_14_005

LEFT RIGHT
CONTROLLER CONTROLLER

WSHLD/WIND
OFF/ TEST OFF/
RESET RESET
LOW LOW
HI HI

L R

Windshield/Window Anti-Ice System

Figure 14-4

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Components and Operation

Windshield and Window Construction

The forward-facing windshields and side windows are constructed of two vinyl layers
separated by a vinyl inner layer. Each windshield and window incorporates electrical
resistance coatings that provide heat for anti-icing the windshields and low heat for
defogging the side windows. Temperature sensors and temperature controllers for each
windshield and window regulate system temperature to maintain a scheduled surface
temperature.

Control Switches and Function

The L and R WSHLD/WIND switches located on the ANTI-ICE panel control the
windshield/window anti-ice system. The L WSHLD/WIND switch controls the left
windshield and window. The R WSHLD/WIND switch controls the right windshield
and window.
When the WSHLD/WIND switch is set to LOW, the corresponding windshield and
side window will be controlled at the low heat level (41°C/106°F).
When the WSHLD/WIND switch is set to HI, the controllers and sensors operate to
maintain a high heat level (58°C/137°F) on the corresponding windshield, and a low
heat level (41°C/106°F) on the corresponding side window.
Overheat protection circuits for each windshield or window remove power from the
affected surface during an overheat condition. The applicable L (R) WSHLD HEAT,
L (R) WINDOW HEAT caution EICAS message will also be displayed. Moving the
WSHLD/WIND switch to the OFF/RESET position de-energizes the applicable
windshield and window and resets the temperature controller.

System Test

The TEST switch is used to test the windshield and window anti-ice systems. With
both WSHLD/WIND switches in the HI position, depressing the TEST switch
performs a test of the windshield and window heat systems. A successful test is
indicated by the L (R) WSHLD HEAT OK and L (R) WINDOW HEAT OK advisory
EICAS messages appearing.
With the WSHLD/WIND switches in the LOW position, only the side window heat
system will be tested.

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Air Data Probes and Sensors Anti-Icing

Description
The air data probes and sensors are located on either side of the aircraft nose and are
electrically heated to prevent ice formation. Two air data sensor heat controllers
(ADSHCs) provide control and monitoring of the probe heaters.
Two probe toggle switches located on the ANTI-ICE panel provide control of AC
power to left side and right side heating elements. Activation of the heating elements is
determined by probe switch positions, engine generator operation, and passenger door
status.

Left Right
Pitot-Static Pitot-Static
Probe Probe

Standby Total Air

Pitot Probe Temp Probe

Left Right
Angle-of-Attack Angle-of-Attack
Vane Vane

Left Static Right Static

Port Port
Auxiliary
Angle-of-Attack
Vane

LEFT RIGHT
CONTROLLER CONTROLLER
(ADSHC) (ADSHC)

WSHLD/WIND PROBES
OFF/ TEST OFF/
RESET RESET
LOW LOW OFF OFF
HI HI
ON ON
P604_14_006

L R L R

Air Data Probes and Sensors Anti-Icing System

Figure 14-5

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Components and Operation

Primary Pitot-Static Probes

There are two pitot-static masts, one on either side of the nose. The pitot static mast
consists of a head and mounting base. The mast has two heaters, one in the head and
the other in the base.

Standby Pitot Probe

There is one standby pitot probe on the left side of the nose which contains one
integral heating element.

Alternate Static Ports

Two flush alternate static ports are located on each side of the aircraft and each
contains an integral heating element.

Angle-Of-Attack (AOA) Vanes

Two angle-of-attack vanes are located on each side of the aircraft and each contains an
integral heating element in the vane.

Auxiliary Angle-Of-Attack Vane

One auxiliary angle-of-attack vane is located on the right side of the nose and contains
two integral heating elements, one for the vane and the other for the base.

Total Temperature (TAT) Probe

One total air temperature sensor is located on the right side of the aircraft and contains
an integral heating element.

Air Data Sensor Heat Controllers (ADSHCs)

The ADSHCs provide control of AC power to respective heating elements and detect
system failures. Should any ADSHC lose control power, all probes connected to the
failed ADHSC will receive full AC power (fail-safe ON). Should a fault condition be
detected by any ADSHC, the applicable EICAS caution message(s) will be displayed.

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PILOT TRAINING GUIDE ICE AND RAIN PROTECTION

Probe Switches

The L and R PROBES switches are used to control AC power to the probe heaters via
the ADHSCs. The L PROBES switch controls the left pitot-static probe, the standby
pitot-probe, the left angle-of-attack vane and the left static port. The R PROBES
switch controls the right pitot-static probe, the total air temperature probe, the right
angle-of-attack vane, the right static port and the auxiliary angle-of-attack probe.
Electrical power is applied to the respective heaters under the following conditions:
• L (R) PROBES switch ON, and
• any one engine generator on-line or PAX door is locked
With the L and R PROBES switches selected ON, all probes are heated and no EICAS
caution messages are displayed.

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Ice Detection System

Description
The ice detection system alerts the flight crew of icing conditions. The system consists
of two independent ice detector/microprocessors, one installed on each side of the
forward fuselage.

P604_14_007
Ice Detectors
Figure 14-6

Components and Operation

Each ice detector consists of a probe and a microprocessor, which operate
continuously (no switch control). The probe extends into the airstream to detect icing
conditions. The microprocessor is a self-contained unit and interfaces with the data
concentrator units (DCUs) to provide the flight crew with a visual indication of icing
conditions.
The ice detector probes vibrate at high frequency. When icing conditions are
encountered, ice accumulation on the probe causes a frequency change in the probe.
The microprocessor detects the frequency change, triggers an ICE advisory or caution
EICAS message on the EICAS and begins the probe’s deicing cycle. During probe
deicing, the probe is electrically heated for 5 seconds followed by 55 seconds with no
heat. The cycle repeats automatically as long as a frequency change is detected. When
no ice accumulation is detected, the heat cycle ceases and the ICE message on the
EICAS is removed.

Ice Detection Test

Selecting the TEST switch on the ANTI-ICE Panel to the DET position checks the
circuitry of the ice detectors.

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Controls and Indicators

The ANTI-ICE Panel provides the system control switches and switch/lights, and the
EICAS Primary and Secondary displays provide the system warning/caution and
advisory messages respectively (see Figure 14-7, Tables 14-1 and 14-2).

ANTI-ICE Panel

Wing HEAT Lights

Illuminated – Indicates
sufficient heat on respective
wing for anti-icing.

WING ANTI-ICE Switch

STBY – Wing anti-ice valves cycle
open and closed at a predetermined
temperature (49°C /120°F open, L and R COWL ANTI-ICE
82°C/180°F closed). Switch/Light (alternate-action)
OFF – Wing anti-ice valves close. Push – Opens or closes respective
NORM – Wing anti-ice controller cowl anti-ice valve.
modulates wing anti-ice valves to Illuminated – Indicates respective
maintain a constant wing leading cowl anti-ice valve is open with
edge temperature (88°C /190°F). sufficient pressure for cowl anti-icing.

ANTI-ICE DET/WING TEST Switch

WING COWL TEST (spring-loaded to center
position)
STBY L HEAT DET
D
DET – Initiates test of the
OFF ON ON ice detectors.
R HEAT
NORM WING
W WING – Initiates test of the
L R wing anti-ice controller and
overheat sensors.

WSHLD/WIND WSHLD/WIND PROBES

TEST Switch OFF/ TEST OFF/
(momentary-action) RESET RESET
Push – Initiates self-test of LOW LOW OFF OFF
windshield and window HI HI
ON ON
heat system.
P604_14_008

NOTE: Both L and R L R L R

WSHLD/WIND switches
must be at the HI position
for a complete test.

L and R WSHLD/WIND Switch L and R PROBES Switch

OFF/RESET – Removes heat from corresponding windshields and OFF – Removes heat from respective
the side window and resets corresponding overheat circuit. side probes and sensors.
LOW – Heats corresponding windshield and side window at a low ON – Respective side probes and
temperature (41°C/106°F). sensors are heated.
HI – Heats corresponding windshield at a high temperature NOTE: Heat is applied to probes and
(58°C/137°F) and side window at a low temperature (41°C/106°F). sensors only if the PAX door is locked
or at least one engine generator is
selected ON.

ANTI-ICE Panel
Figure 14-7

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EICAS Messages

EICAS Messages - Wing Anti-Ice System

AURAL WARNING
MESSAGE MEANING
(IF ANY)
Bleed air leak detected in left and/or right fuselage or
ANTI-ICE DUCT “ANTI-ICE DUCT”
wing anti-ice ducts.
Overheat condition detected in left and/or right wing
WING OVHT “WING OVERHEAT”
leading edge.
L WING A/ICE With wing anti-ice selected on, insufficient pressure and temperature in
R WING A/ICE respective wing leading edge for anti-icing.
WING A/ICE SNSR Wing anti-ice sensor failure detected (control and/or overheat sensor).
WING A/ICE ON Wing anti-ice is selected on with sufficient heat available for anti-icing.
Wing and cowl anti-ice selected on and sufficient heat/pressure available for anti-
WING/COWL A/ICE ON
icing.
WING A/ICE OK Successful test of the wing anti-ice system.

EICAS Messages - Engine Cowl Anti-Ice System

MESSAGE MEANING
L COWL A/ICE Cowl anti-ice valve failure;
- With the cowl anti-ice selected on, respective cowl has insufficient pressure for
anti-icing, or
R COWL A/ICE - With the cowl anti-ice selected off, respective cowl senses pressure (i.e. valve
failed open).
Both cowl anti-ice switches selected on and both cowls have sufficient pressure
COWL A/ICE ON
for anti-icing.
Left cowl anti-ice switch selected on and left cowl has sufficient pressure for anti-
L COWL A/ICE ON
icing.
Right cowl anti-ice switch selected on and right cowl has sufficient pressure for
R COWL A/ICE ON
anti-icing.

EICAS Messages (1 of 2)
Table 14-1

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EICAS Messages - Windshield/Window Anti-Ice System

MESSAGE MEANING
L WINDOW HEAT
Respective side window heat has failed.
R WINDOW HEAT
L WSHLD HEAT
Respective front windshield heat has failed.
R WSHLD HEAT
L WINDOW HEAT OK
Respective side window heat system has passed self-test.
R WINDOW HEAT OK
L WSHLD HEAT OK
Respective front windshield heat system has passed self-test.
R WSHLD HEAT OK

EICAS Messages - Air Data Probes and Sensors Anti-Icing

MESSAGE MEANING
L AOA HEAT
Respective AOA heater has failed.
R AOA HEAT
AUX AOA CASE HEAT AUX AOA vane base heater has failed.
AUX AOA VANE HEAT AUX AOA vane heater has failed.
L PITOT BASE HEAT
Respective pitot-static base heater has failed.
R PITOT BASE HEAT
L PITOT TUBE HEAT
Respective pitot-static heater has failed.
R PITOT TUBE HEAT
L PROBE HEAT OFF On the ground, either all respective side anti-ice heaters have failed or the
R PROBE HEAT OFF respective PROBES switch is selected off.
L STATIC HEAT
Respective static port heater has failed.
R STATIC HEAT
STBY PITOT HEAT Standby pitot probe heater has failed.
TAT PROBE HEAT TAT probe heater has failed.

EICAS Messages - Ice Detection System

MESSAGE MEANING
ICE Ice has been detected and wing and/or cowl anti-ice systems are not selected on.
ICE DETECTORS Both ice detector channels have failed.
Icing has been detected and both wing and cowl anti-ice systems are on and
ICE
sufficient heat/pressure is available for anti-icing.
ICE DETECTOR 1 FAIL Ice detector 1 has failed.
ICE DETECTOR 2 FAIL Ice detector 2 has failed.

EICAS Messages (2 of 2)
Table 14-2

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