ICE AND RAIN PROTECTION TABLE OF CONTENTS CHAPTER 14

DESCRIPTION

General 14−10−1

Bleed/Anti-Ice Synoptic 14−10−2

Components 14−10−2

Anti-Ice Panel 14−10−3

Ice Detection 14−10−4

Ice Detection Indication 14−10−5

Pneumatic Anti-Icing 14−10−6

Cowl Anti-Icing (CAI) 14−10−6Engine Spinner 14−10−6Cowl Anti-Ice Valves 14−10−6

CAI Operation 14−10−7

Wing Anti-Icing (WAI) 14−10−8Wing Anti-Ice Valves (WAIV) 14−10−8

WAI Operation 14−10−9Crossbleed Valve (CBW) 14−10−9

WAI Failure Indications 14−10−10Wing Anti-Ice Overheat 14−10−10Wing Anti-Ice Fail 14−10−10Wing Anti-Ice Low Heat 14−10−11

Slat Anti-Icing 14−10−12

Slat Anti-Ice Operation 14−10−12

Electrical Anti-Icing 14−10−13

Air Data Probes and Sensors 14−10−13HBMU 14−10−13Probes 14−10−15

Windshield Heat 14−10−16Windshield Temperature Controller 14−10−16Windshield Heat Panel 14−10−17

Modes of Operation 14−10−17Warm-Up Mode 14−10−17Normal Regulating Mode 14−10−17

Windshield/Window Failure Indication 14−10−17

EICAS Philosophy 14−10−18

Ice and Rain EICAS Messages 14−10−19

ICE AND RAIN PROTECTION

TABLE OF CONTENTS

CHAPTER 14

14−00−1

Rev 3, Apr 25, 2005 Flight Crew Operating Manual

CSP 700−5000−6

Volume 214−00−1

Page

TABLE OF CONTENTS

EMS CIRCUIT PROTECTION

CB − Ice System 14−20−1


TABLE OF CONTENTS

Rev 2A, Apr 11, 2005Flight Crew Operating Manual

CSP 700−5000−6

Volume 214−00−2

Page

GENERAL

Thermal anti-icing, electrical anti-icing, ice detection and alerting systems are provided for airplaneice and rain protection. Selections for anti-ice functions are made on the ANTI-ICE panel, located onthe overhead panel.

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AUTOOFF ON

AUTOOFF ON

AUTOOFF ON

R COWLWINGL COWL

ANTI−ICE

AUTOFROM L FROM R

WING XBLEED

Ice Detection

Independent ice detection probes (2), located on the fuselage, sense the formation of ice. If ice isdetected, the ice detectors automatically turn on the electrical heat to the various probes, signallingthe Bleed Management Controllers (BMC) to activate wing anti-ice and operate a relay in theANTI-ICE Control panel to activate cowl anti-ice.

Pneumatic Anti-Icing

Hot air anti-icing, provided by engine bleed air, through piccolo ducting, wing anti-ice valves and cowlanti-ice valves, prevents the formation of ice on the wing leading edge, slats and the engine intakecowls.

Electrical Anti-Icing

Electrical anti-icing is provided for Pitot Static Probes, Ice Detectors, Total Air Temperature (TAT)Probes, Heater/Brake Temperature Monitoring Units (HBMUs) and Angle of Attack (AOA) Vanes.

Selections for the Pilot’s and Copilot’s Windshields and Side Windows heating, are made on theWINDSHIELD HEAT panel, located on the overhead panel.

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R

WINDSHIELD HEAT

ONOFF/RESET

LONOFF/

RESET

Anti-ice system data is displayed on the BLEED /ANTI-ICE synoptic page and any faults or failuresare displayed on EICAS and CAIMS.



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BLEED/ANTI-ICE SYNOPTIC

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WING ANTI-ICE CROSS BLEED VALVE (CBW)

WING ANTI-ICE VALVE (WAIV)

COWL ANTI-ICE VALVE(CAIV)

For more information on BLEED System, refer to Chapter 2, AIR CONDITIONING and PRESSURIZATION.

LP

HP

L R

APU

HP

LP

CONDAIR

BLEED/ANTI-ICE

40PSI

40PSI

COMPONENTS

CBW

CAIV

WAIV

BMC

ANTI-ICINGTEMPERATURE SENSORS

ICE DETECTORS PICCOLO

DUCTS GF

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TO EICAS


Rev 3, Apr 25, 2005Flight Crew Operating Manual

CSP 700−5000−6

Volume 214−10−2

ANTI-ICE PANEL

Controls are provided on the ANTI-ICE panel, located on the overhead panel.

L & R COWL Selectors

associated valves.

operation, when ice is detected by the ice detector.

detector signals.

WING Selector

and closes the associated valves.

to enable automatic operation, when ice is

System inhibited on the ground until 400 feet

above take-off field elevation.

independent of ice detector signals.

WING XBLEED Selector

the CBW, independent of BMC commands.

operation in the event of a failure in one WAIV.

the CBW, independent of BMC commands.G

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05

− Disarms the cowl anti-ice system and closes the

− Arms the cowl anti-ice system, to enable automatic

− Activates cowl anti-ice operation, independent of ice

OFF

AUTO

ON

FROM L

AUTO

FROM R

− Closes the RH WAIV and opens

− Closes the LH WAIV and opens

OFF

AUTO

− Activates wing anti-ice operation,

− Disarms the wing anti-ice system

− Arms the wing anti-ice system,

ON

detected by the ice detector.

− Arms the CBW to enable automatic

AUTOOFF ON

AUTOOFF ON

AUTOOFF ON

R COWLWINGL COWL

ANTI−ICE

AUTOFROM L FROM R

WING XBLEED



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ICE DETECTION

The airplane is fitted with two ice detectors, one on each side of the front fuselage.

VIBRATING

MOUNTING FLANGE

ELECTRICAL

STRUT

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CONNECTORPROBE

The ice detector incorporates a vibrating probe, that maintains a preset frequency (40 KHz), to detecticing conditions. As the ice detector enters an icing environment, ice collects on the vibrating probe.The added mass of ice causes the frequency of the probe to decrease, .010 inch thickness of iceequals a 65 HZ decrease and immediately the ice detector de-ices the strut and the probe throughinternal heaters. Heater power is applied until the frequency rises to a predetermined set point, plus atime delay factor (60+/− 5 seconds) to ensure complete de-icing. If an additional icing/de-icing cycleoccurs during that time interval, the 60 seconds cowl and wing anti-ice activation period is begunagain.

VIBRATING PROBE

STRUT HEATERS

PROBE HEATERSECTIONAL VIEW

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The ice detectors emit icing signals to the following:

• ANTI-ICE panel (cowl anti-ice relay), for activation of the cowl anti-icing system (AUTO).• BMC for activation of the wing anti-icing system (AUTO). The AUTO operation of WING

ANTI-ICE is inhibited during take-off until the airplane is >400 feet above field elevation.• Stall protection system, to change stick shaker control, if an ice detector has failed and to the

BMC for fault indication. For more information on Stall Protection, refer to Chapter 10 FLIGHTCONTROLS.

Once de-iced, the probe cools within a few seconds and is ready to sense ice buildup again. Thiscycling process is repeated as long as the ice detector remains in an icing environment.

The ice detectors are not capable of operating at low airspeeds of less than 29 knots IAS, thereforethey cannot be used to detect icing when the airplane is on the ground.



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ICE DETECTION INDICATION

If ice is detected and the ANTI-ICE system is turned OFF, a message is displayed on EICAS.

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ICE

AUTOAUTOOFF ON

AUTOR COWLWINGL COWL

ANTI−ICE

OFF ON OFF ON

If ice is detected and the ANTI-ICE system is turned to ON or AUTO, the following message isdisplayed on EICAS.

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OR ICE

AUTOAUTOOFF ON


ANTI−ICE

AUTOAUTOOFF ON


ANTI−ICE

OFF ON

OFF ONAUTO

OFF ON

OFF ON

If both ice detectors are failed, a message is displayed on EICAS and the crew must revert to manualselection of cowl and wing anti-ice.

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ICE DETECTOR FAIL

AUTOAUTOOFF ON


ANTI−ICE

OFF ON OFF ON

If a single ice detector fails, a message is displayed on EICAS. If ice is detected by the other icedetector, the Stall Protection system enables a change in stick shaker control and a message isdisplayed on EICAS.

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ICEICE DETECTOR FAULTSTALL WARN ADVANCE



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PNEUMATIC ANTI-ICING

Engine bleed air is used for the following systems:

COWL ANTI-ICING (CAI)

The cowl anti-icing system is used to prevent formation of ice on the nose cowl of the engine. Thecowl leading edge uses hot engine bleed air from the low pressure compressor 5th stage to heat thenose cowl. The bleed air is ducted through a spray ring and exhausts to atmosphere, through an exitgrill.

Engine Spinner

The engine spinner point is made of soft rubber which will distort during engine running and iceaccumulation and will shed any ice buildup. The rear of the spinner and the fan blades usecentrifugal force to shed ice after start up, to prevent ice accumulation during engine running.

X

SPRAY RING

EXHAUST DUCT

EXHAUST

NOSE COWL LIP

SPINNER

FAN BLADES

AIR INLET COWL

SPINNER POINT

BLEED AIRSUPPLY DUCT

NOSE COWL LIP

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AND SPINNER

Cowl Anti-Ice Valves

There are two Cowl Anti-Ice Valves (CAIV), which control the flow of engine bleed air to the cowlducting. The CAIVs are spring-loaded open, pneumatically operated, electrically controlled,pressure regulating and shutoff valves, that are controlled by signals from the ice detectingsystem. They are either fully open or fully closed.



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CAI OPERATION

When the L and/ or R COWL selector is selected to AUTO and ice is detected, the ice detectionsystem sends a signal to a relay in the ANTI-ICE panel, that commands the anti-ice valves open. Ifan ice detector fails, the other detector will activate both cowl anti-ice valves in AUTO mode. A statusmessage is displayed on EICAS.

RH ICE DETECTOR

LH ICE DETECTOR

LOW PRESS PORT

HIGH PRESS PORT

CAIV

SPRAY RING

SYNOPTIC

LP

HP

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HP

LP

L−R COWL A/ICE AUTO

AUTOOFF ON

R COWL

AUTOOFF ON

L COWL

Cowl anti-icing can be manually selected to ON, in which case the CAIVs will open, independent ofthe ice detection system and a status message is displayed. Whenever cowl anti-ice is activated(AUTO or ON), a CAI icon will be displayed on the EICAS page.

73.373.3

789789

N1

ITT

CAICAI

INDICATIONCAI

LP

HP

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L−R COWL A/ICE ON

EICAS

AUTOOFF ON

L COWLAUTO

OFF ON

L COWL



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WING ANTI-ICING (WAI)

The wing anti-icing system is used to prevent formation of ice on the leading edge of the wing. Thewing leading edge uses hot engine bleed air from either the 5th stage or the high pressurecompressor 8th stage, of the bleed air system.

HPGROUND AIR SUPPLY

R WINGA/I VALVE

CROSSBLEEDVALVE

L WINGA/I VALVE

WING CROSSBLEED VALVE

TEMPERATURE SENSORS

ICE DETECTOR

LOWPRESSPORT

HIGHPRESS PORT

L ATSVALVE

HIGHPRESS VALVE

PRSOV

COWL ANTI−ICE

L COWLA/I VALVE

R ATS VALVE

R COWL A/I VALVE

R AIRTURBINESTARTER

APU

L AIRTURBINESTARTER

BMC 1 BMC 2CONT

CHMONCH

CONTCH

MONCH

DAUDAU

L AIR CONDITIONING

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Wing Anti-Ice Valves (WAIV)

Two wing anti-ice valves are electrically controlled, pneumatically operated, spring loaded closed,modulating shutoff valves. The ice detector system will send a signal to the BMC to activate thewing anti-ice system. The temperature sensor, located in the fixed leading edge, provides a signalto the control channel of the BMC, which drives the WAIVs open or closed. The other temperaturesensors, located in the fixed leading edge, provide a signal to a monitoring channel in the BMC.One channel controls and the other channels act as a monitor but can assume control in the eventof a failure of the control sensor. In the event of complete failure of sensors on one side, theserviceable control sensor on the opposite side, will control the WAIVs.



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WAI OPERATION

The ice detectors will send a signal to the BMC to activate the wing anti-ice system when selected toAUTO. Wing anti-ice can be manually selected to ON, in which case the WAIVs will open,independent of the ice detection system. Whenever wing anti-ice is activated (AUTO or ON), a WAIicon will be displayed on the EICAS page. The ICON colour will vary from amber, green or white,depending on the temperature in the wing and/or its status.

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LP

HP

L R

APU

HP

LP

CONDAIR

BLEED/ANTI-ICE

WING A/ICE AUTO

789789

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ITT

WAIWAI

40PSI

WING A/ICE ON

AUTOOFF ON

WING

WINGAUTO

OFF ONAUTO

OFF ON40PSI

Crossbleed Valve (CBW)

The left and right hand anti-ice systems normally operate independently from one another. In theevent of a single engine failure, bleed failure or a failure of wing anti-ice air supply on one side, theleft and right systems are interconnected by a CBW. This allows both wings to be fed from a singleengine. In case of a failure in AUTO operation, the CBW will automatically open and the affectedWAIV will automatically be closed by the BMC. Manual operation of the CBW is provided on theANTI-ICE panel.

73.373.3

789789

N1

ITT

WAIWAIG

F14

10_0

17a

LP

HP

L R

APU

HP

LP

CONDAIR

BLEED/ANTI-ICE

0PSI

WING XBLEED FROM R

40PSI

WING A/ICE AUTO

OR

AUTOOFF ON

WING XBLEED

AUTOWING XBLEED

OFF ON



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WAI FAILURE INDICATIONS

The WAI failure indications are as follows:

Wing Anti-Ice Overheat

If there is an overheat in the wing anti-ice system, a message is displayed on EICAS.

Turn WING ANTI-ICE OFF789789

N1

ITT

WAIWAI

GF

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_018

a

BLEED/ANTI-ICE

WING A/ICE OVHT

AUTOOFF ON

WING

AUTOOFF ON

WING

Wing Anti-Ice Fail

If wing anti-ice is failed, a message is displayed on EICAS. If ice is detected during this failurecondition, the stall warning trigger points are advanced automatically. Ensure rpm (N2) is above76% may make this amber message diappear.

NOTEIf ice is detected, the stall warning trigger points are advanced automatically. For more information on stall protection, see Chapter 10, FLIGHT CONTROLS. G

F14

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19

ICEL−R WING A/ICE FAILSTALL WARN ADVANCE



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WAI FAILURE INDICATIONS (CONT'D)Wing Anti-Ice Low Heat

If there is insufficient heat in the wing leading edge duct, a message is displayed on EICAS.

789789

N1

ITT

WAIWAI

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AIR

BLEED/ANTI-ICE

ICEWING A/ICE LO HEAT



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SLAT ANTI-ICING

The sections of slat leading edge that are heated, are as follows:

• Inboard fixed leading edge.• Slat 1, 2, 3 and 4.

Only the short, fixed section outboard of slat 4 and the leading edge of the winglet are not heated.

SLAT ANTI-ICE OPERATION

Air is ducted into the fixed section of the wing leading edge from the forward part of the wing root.From there, it is directed into the wing leading edge slats via a telescopic duct which extends as theslats move to the extend position. Piccolo tubes in both inboard fixed leading edge and outboard ateach slat, distribute the air into the inside surface of the wing leading edge for ice protection. Air isthen extracted overboard between the slat and main wing.

TEMPERATURE SENSOR

FIXED LEADING EDGE

WING CROSSBLEED VALVE

WING ANTI-ICE VALVES (WAIV)

SLATEXTENDED

PICCOLO TUBE

TELESCOPIC JOINT

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ELECTRICAL ANTI-ICING

Electrical power is used to operate the following:

AIR DATA PROBES AND SENSORS

The air data probes and sensors anti-ice system prevents ice accumulation on the probes andsensors, which could lead to incorrect data transmission to the Air Data Computers (ADC).

The air data probes and sensors anti-ice system is controlled automatically by two Heater/BrakeTemperature Monitoring Units (HBMU).

TAT1

TAT2BTMS3

BTMS1

BTMS4

BTMS2

YD HEATER 1

YD HEATER 2

PS 1PS 3

PS STANDBY PS 2

AOA 2

AOA 1

TAT 3

PS − PITOT/STATICAOA − ANGLE OF ATTACKBTMS − BRAKE TEMPERATURE MONITOR SYSTEMTAT − TOTAL AIR TEMPERATUREYD −YAW DAMPER

HBMU1

HBMU2

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HBMU

HBMU 1 controls AOA 1, PS 1, PS 3, TAT 1 and YD Heater 1 and monitors BTMS 1 and BTMS 2.

HBMU 2 controls AOA 2, PS 2, PS Standby, TAT 2, TAT 3 and YD Heater 2 and monitors BTMS3 and monitors BTMS 3 and BTMS 4.

The HBMUs also monitor brake temperature data. The data sent by the Brake TemperatureMonitoring System (BTMS), which incorporates four sensors, installed in the brake housings,provides excessive brake temperature warning to EICAS (For more information see Chapter 15,LANDING GEAR). The HBMU also controls heat to Yaw Damper (YD) actuators, to ensure thatthe standby YD actuator is heated. (For more information see Chapter 10, FLIGHT CONTROLS).



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AIR DATA PROBES AND SENSORS (CONT'D)HBMU (Cont’d)

The HBMU receives data from various airplane systems via the Data Acquisition Units (DAU) tocontrol the heaters. The systems that send data to the DAUs are:

• Electronic Engine Controllers (EEC), for the “all heaters off” logic and for TAT probe on/offlogic.

• Fault Warning Computer (FWC), regarding which ADC is selected for cockpit display.• Automatic Flight Control System (AFCS), regarding which Yaw Damper is in use, for YD

heater control logic.• Air Data Computers (ADC) to provide TAT information to control heat to the Yaw Dampers

and airspeed information for “all heaters off” logic.• Electrical Load Management System (EMS), provides BUS status and ADG information for

heater control logic.• Weight On Wheels (WOW), for “all heaters off” logic and for TAT probe on/off logic.

The heaters are driven to the indicated ON/OFF state based on the following logic:

• AOA 1 Heater Off − AC ESS BUS unpowered and WOW.• AOA 2 Heater Off − AC ESS BUS unpowered and AC BUS 1 unpowered and WOW.• PS 1 Heater Off − ADG deployed and ADC 1 not selected or AC ESS BUS unpowered

and AC BUS 1 unpowered.• PS 2 Heater Off − AC BUS 2 unpowered.• PS 3 Heater Off − ADG deployed and ADC 3 not selected or AC ESS BUS unpowered.• PS STBY Heater Off − AC ESS BUS unpowered.• TAT 1 Heater Off − WOW and LH engine Off.• TAT 2 Heater Off − WOW and RH engine Off.• TAT 3 Heater Off − WOW or AC BUS 3 unpowered.• YD 1 Heater On − TAT <−40°C and Yaw Damper 1 not engaged.• YD 2 Heater On − TAT <−40°C and Yaw Damper 2 not engaged.

The “all heaters off” control function, turns OFF all heaters and overrides the above heater on/offlogic equations when :

• L and R engine not running and/or,• WOW and/or,• airspeed less than 50 knots.



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AIR DATA PROBES AND SENSORS (CONT'D)Probes

There are four Pitot-Static (PS) probes on the side of the fuselage. They supply pitot and staticpressure to the air data computers and standby instruments. Heater elements are installed in thePS heads and mounting bases.

There are three Total Air Temperature (TAT) probes, one on the fuselage and one each in theengine inlets.

There are two AOA probes, mounted on the fuselage, one on either side.

PS STANDBY

PS 1

PS 3PSSTANDBY

PS 2

TAT 3

TAT 3PS 2

TAT 2

TO

P V

IEW

ENGINE INLET

TAT 1/2

AOA 2AOA 1

AOA 2

PS 3

PS 1TAT 1

AOA 1

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PROBE

The current being drawn by the heater is measured and a heater fault is generated if the currentdrawn is less than the minimum required by the particular probe. The fault is then transmitted toEICAS.

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L−R AOA HEAT FAILPITOT 1−2−3 HT FAILSTBY PITOT HT FAILTAT 1−2 FAIL



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WINDSHIELD HEAT

The Windshield Temperature Control System provides defog and anti-icing for the Pilot’s andCopilot’s windshield and side window. The system continuously monitors the temperature of eachwindshield and side window and maintains the temperature within specified limits.

Windshield Temperature Controller

There are two dual channel Windshield Temperature Controllers (WTC). The left hand WTCcontrols the left windshield heater and the left side window heater. The right hand WTC controlsthe right windshield heater and the right side window heater. Both WTCs are interfaced withEICAS via different DAUs.

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EICAS

LEFTWINDOWHEATER

LEFTWINDSHIELDHEATER

RIGHTWINDSHIELDHEATER RIGHT

WINDOWHEATER

98F

98F 98F

98F

CONTROLLER CONTROLLER

R

WINDSHIELD HEAT

ONOFF/RESET

LONOFF/

RESET

The windshield construction is laminated, stretched acrylic mainplies, which incorporate a goldconductive film as the de-icing heater element. The windshield also includes three temperaturesensor elements, one for controlling and monitoring and two spares.

The side window construction is similar to the windshield, except that the stretched acrylicmainplies are thinner. The side window also includes a heating element for defog and threetemperature sensor elements, one for control and monitoring and two spares.



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WINDSHIELD HEAT (CONT'D)Windshield Heat Panel

Selections for the Pilot’s and Copilot’s Windshields and Side Windows heating, are made on theWINDSHIELD HEAT panel, located on the overhead panel.

− Resets the system, in the event of a failure. − Inhibits all windshield and window fail messages.

Left and Right Windshield Heat selectors

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ON

− Turns windshield/window heat OFF.

− Activates the windshield/window temperature control system.

R

WINDSHIELD HEAT

ONOFF/RESET

LONOFF/

RESET

MODES OF OPERATION

The windshield modes of operation are as follows:

Warm-Up Mode

The warm-up mode is provided to avoid the effect of thermal shock on the windshield. While in thewarm-up mode, the windshield heater generates only 33% of nominal heat and lasts forapproximately 4 minutes, then is terminated. The warm-up mode is activated on WTC power-up,when the following conditions are met:

• Heat was not applied to the windshield for more than 5 seconds.• The airplane is Weight On Wheels.

If the airplane is Weight Off Wheels, the warm-up mode is terminated. Once the warm-up mode isterminated, it automatically switches to normal regulating mode.

Normal Regulating Mode

On WTC power-up both channels controlling the windshield and respective side window areenergized. Each channel continuously monitors the temperature through its sensor element. If thetemperature decreases below a specified low limit, the heater is turned on. If the temperatureexceeds a specified limit, the heater is turned off.

WINDSHIELD/WINDOW FAILURE INDICATION

In the event of a system failure or being turned off, a message is displayed on EICAS.

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L−R WINSHLD FAILL WSHLD HEAT OFFR WSHLD HEAT OFF



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EICAS PHILOSOPHY

The following represents the EICAS symbols and logic for the BLEED/ANTI-ICE synoptic page. Thesymbols are shown in serviceable and failure conditions.

BLEED/ANTI − ICE SYSTEM LOGIC

VALVE AND FLOW LINE

OPEN

VALVE

NOT FAILED

CLOSED

TRANSIT

INVALID

VALVE FAILED

DIRECTION OF FLOW

LOW TEMPERATURE

WAI OFF

WING LEADING EDGE

OVERHEAT

SUFFICIENT HEAT

ENGINE COWL

CAI OFFCAI ON

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ICE AND RAIN EICAS MESSAGES

L−R WINDOW HEAT FAILIndicates that the respective window heater temperature controller has failed.

ICEIndicates that ice has been detected and one or the other system is OFF.

WING A/ICE OVHTIndicates that an overtemperature has been detected in the wing anti-ice system.

L−R WING A/ICE FAILIndicates that the wing anti-ice valve is not in the selected position.

PITOT 1−2−3 HT FAILIndicates that the respective pitot heater has failed.

WING A/ICE LEAKIndicates that a bleed leak has been detected in the wing anti-ice system.

STBY PITOT HEAT FAILIndicates that the standby pitot heater has failed.

ICE DETECTOR FAILIndicates the loss of both ice detectors.

L−R COWL A/ICE FAILIndicates that the cowl anti-ice valve is not in the selected position.

L−R WSHLD HEAT FAILIndicates that the respective windshield heater temperature controller has failed.

L−R AOA HEAT FAILIndicates that respective AOA has failed.

WING A/ICE LO HEATIndicates that there is insufficient heat in the wing leading edge duct.

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a

R AOA HEAT FAIL

ICE DETECTOR FAIL L AOA HEAT FAIL

ICE

L WINDOW HEAT FAIL

L COWL A/ICE FAILR COWL A/ICE FAIL

R WING A/ICE FAIL

R WINDOW HEAT FAILL WING A/ICE FAIL

L WSHLD HEAT FAILR WSHLD HEAT FAILPITOT 1 HT FAIL

WING A/ICE OVHT

PITOT 2 HT FAILPITOT 3 HT FAILSTBY PITOT HT FAILWING A/ICE LEAKWING A/ICE LO HEAT



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ICE AND RAIN EICAS MESSAGES (CONT'D)

ICE DETECTOR FAULTIndicates that there is a loss of one ice detector.

L−R PROBE MON FAILIndicates that the heater status of the probes and associated systems is not verified.

TAT HT 1−2−3 FAILIndicates that the respective TAT heater has failed.

WING A/ICE FAULTIndicates loss of redundancy on wing anti-ice system.

ICEIndicates that cowl or wing anti-icing has been detected with anti-ice systems ON.

WING A/ICE SENSORIndicates loss of both outboard wing anti-ice temperature sensors.

L−R COWL A/ICE FAULTIndicates that there is a loss of the affected cowl anti-ice.

YD HEAT 1−2 FAILIndicates that the respective yaw damper heater has failed.

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a

R PROBE MON FAILL PROBE MON FAIL

TAT HT 3 FAIL

TAT HT 1 FAILTAT HT 2 FAIL

WING A/ICE FAULTWING A/ICE SENSOR

R COWL A/ICE FAULT

TAT 3 FAIL

TAT 1 FAILTAT 2 FAIL

ICE DETECTOR FAULT L COWL A/ICE FAULT

ICE

YD HEAT 1 FAILYD HEAT 2 FAIL

TAT 1−2−3 FAILIndicates that the respective TAT has failed.



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ICE AND RAIN EICAS MESSAGES (CONT'D)

L−R COWL A/ICE ONIndicates that the respective cowl anti-ice has been selected ON.

L−R WSHLD HEAT OFFIndicates that the respective temperature controller selector is selected to OFF/RESET.

WING XBLEED FROM L − R Indicates that wing anti-ice isbeing supplied from theselected side.

WING A/ICE AUTOIndicates that wing anti-ice has been selected to AUTO.

WING A/ICE ONIndicates that wing anti-ice has been selected ON.

L−R COWL A/ICE AUTOIndicates that the respective cowl anti-ice has been selected to AUTO.

GF

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_031

L COWL A/ICE AUTOR COWL A/ICE AUTOL COWL A/ICE ONR COWL A/ICE ONL WSHLD HEAT OFFR WSHLD HEAT OFFWING A/ICE AUTOWING A/ICE ONWING XBLEED FROM LWING XBLEED FROM R



CSP 700−5000−6

Volume 214−10−21



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CB - ICE SYSTEM

GF

1420

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STAT SYS BUS PREV CNTL TESTPAGE

NEXTPAGE

EMERCNTL

BUS

CIRCUIT BREAKER − SYSTEM 2/2

SYSTEMCIRCUIT BREAKER

HYD

ICE

IND/RECORD

LDG GEAR

LIGHTS

NAV

OIL

OXYGEN

THRUST REV

BRT

BATT

HBMU 2

L AOA HEAT

L WINDOW HEAT

INHBMU 1

IN

IN

IN

IN

BATT

DC ESS

AC ESS

L COWL A/ICE VLV

AC ESS

AC ESS

IN

AC 1

L WIING A/ICE CTL

L WISHLD HEAT 1

PITOT 1 HT A

PITOT 1 HT B

INL WINDOW HEAT CTL

IN

IN

IN

IN

DC ESS

DC ESS

AC 1

L WSHLD HEAT 2

AC 1

AC ESS

IN

PITOT 3 HT

R AOA HEAT A

R COWL A/ICE VLV

R ICE DETECTOR

INPITOT 2 HT

IN

IN

IN

IN

AC 2

AC ESS

AC 1

AC ESS R AOA HEAT B

BATT

AC 1

IN

L ICE DETECTOR

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

1/5CB − ICE SYSTEM



R WINDOW HEAT CTL

R WING A/ICE CTL

R WSHLD HEAT 1

R WSHLD HEAT 2

STBY PITOT HT

INR WINDOW HEAT

IN

IN

IN

IN

AC 2

DC 1

DC ESS

AC 3

AC 3

AC ESS IN

TAT HT 2

TAT HT 3

WAI XBLEED CTL

WAI XBLEED VLV

INTAT HT 1

IN

IN

IN

IN

AC ESS

AC ESS

AC 3

DC ESS

DC ESS

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CB − ICE SYSTEM 4/5

CB − ICE SYSTEM 5/5



Rev 2A, Apr 11, 2005 Flight Crew Operating Manual

CSP 700−5000−6

Volume 214−20−1



Rev 2A, Apr 11, 2005Flight Crew Operating Manual

CSP 700−5000−6

Volume 214−20−2

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ICE AND RAIN PROTECTION TABLE OF CONTENTS CHAPTER 14

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Transcript of ICE AND RAIN PROTECTION TABLE OF CONTENTS CHAPTER 14