DESCRIPTION
General 14−10−1
Bleed/AntiIce
Synoptic 14−10−2
Components 14−10−2
AntiIce
Panel 14−10−3
Ice Detection 14−10−4
Ice Detection Indication 14−10−5
Pneumatic AntiIcing
14−10−6
Cowl AntiIcing
(CAI) 14−10−6
Engine Spinner 14−10−6
Cowl AntiIce
Valves 14−10−6
CAI Operation 14−10−7
Wing AntiIcing
(WAI) 14−10−8
Wing AntiIce
Valves (WAIV) 14−10−8
WAI Operation 14−10−9
Crossbleed Valve (CBW) 14−10−9
WAI Failure Indications 14−10−10
Wing AntiIce
Overheat 14−10−10
Wing AntiIce
Fail 14−10−10
Wing AntiIce
Low Heat 14−10−11
Slat AntiIcing
14−10−12
Slat AntiIce
Operation 14−10−12
Electrical AntiIcing
14−10−13
Air Data Probes and Sensors 14−10−13
HBMU 14−10−13
Probes 14−10−15
Windshield Heat 14−10−16
Windshield Temperature Controller 14−10−16
Windshield Heat Panel 14−10−17
Modes of Operation 14−10−17
WarmUp
Mode 14−10−17
Normal 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 2
14−00−1
Page
TABLE OF CONTENTS
EMS CIRCUIT PROTECTION
CB − Ice System 14−20−1
ICE AND RAIN PROTECTION
TABLE OF CONTENTS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
14−00−2
Page
GENERAL
Thermal antiicing,
electrical antiicing,
ice detection and alerting systems are provided for airplane
ice and rain protection. Selections for antiice
functions are made on the ANTIICE
panel, located on
the overhead panel.
GF1410_001
AUTO
OFF ON
AUTO
OFF ON
AUTO
OFF ON
L COWL WING R COWL
ANTI−ICE
AUTO
FROM L FROM R
WING XBLEED
Ice Detection
Independent ice detection probes (2), located on the fuselage, sense the formation of ice. If ice is
detected, the ice detectors automatically turn on the electrical heat to the various probes, signalling
the Bleed Management Controllers (BMC) to activate wing antiice
and operate a relay in the
ANTIICE
Control panel to activate cowl antiice.
Pneumatic AntiIcing
Hot air antiicing,
provided by engine bleed air, through piccolo ducting, wing antiice
valves and cowl
antiice
valves, prevents the formation of ice on the wing leading edge, slats and the engine intake
cowls.
Electrical AntiIcing
Electrical antiicing
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 the
WINDSHIELD HEAT panel, located on the overhead panel.
GF1410_002
R
WINDSHIELD HEAT
OFF/ ON
RESET
L
OFF/ ON
RESET
Antiice
system data is displayed on the BLEED /ANTIICE
synoptic page and any faults or failures
are displayed on EICAS and CAIMS.
ICE AND RAIN PROTECTION
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
14−10−1
BLEED/ANTI-ICE SYNOPTIC
GF1410_003
WING ANTIICE
CROSS BLEED VALVE
(CBW)
WING ANTIICE
VALVE
(WAIV)
COWL ANTIICE
VALVE
(CAIV)
For more information on BLEED System, refer to Chapter 2, AIR CONDITIONING and PRESSURIZATION.
LP
HP
L R
APU
HP
LP
COND
AIR
BLEED/ANTIICE
40
PSI
40
PSI
COMPONENTS
CBW
CAIV
WAIV
BMC
ANTIICING
TEMPERATURE
SENSORS
ICE
DETECTORS PICCOLO
DUCTS
GF1410_004
TO EICAS
ICE AND RAIN PROTECTION
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
14−10−2
ANTI-ICE PANEL
Controls are provided on the ANTIICE
　
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