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NOTE
If ice is detected, the stall warning trigger points are advanced automatically.
For more information on stall protection, see Chapter 10, FLIGHT CONTROLS.
GF1410_019
ICE
L−R WING A/ICE FAIL
STALL WARN ADVANCE
ICE AND RAIN PROTECTION
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
14−10−10
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.
789 789
N1
ITT
WAI WAI
GF1410_020
AIR
BLEED/ANTI-ICE
ICE
WING A/ICE LO HEAT
ICE AND RAIN PROTECTION
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
14−10−11
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 the
slats move to the extend position. Piccolo tubes in both inboard fixed leading edge and outboard at
each slat, distribute the air into the inside surface of the wing leading edge for ice protection. Air is
then extracted overboard between the slat and main wing.
TEMPERATURE
SENSOR
FIXED LEADING
EDGE
WING CROSSBLEED
VALVE
WING ANTI-ICE
VALVES (WAIV)
SLAT
EXTENDED
PICCOLO
TUBE
TELESCOPIC
JOINT
GF1410_021
ICE AND RAIN PROTECTION
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
14−10−12
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 and
sensors, 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/Brake
Temperature Monitoring Units (HBMU).
TAT1
TAT2
BTMS3
BTMS1
BTMS4
BTMS2
YD HEATER 1
YD HEATER 2
PS 1
PS 3
PS STANDBY
PS 2
AOA 2
AOA 1
TAT 3
PS − PITOT/STATIC
AOA − ANGLE OF ATTACK
BTMS − BRAKE TEMPERATURE MONITOR SYSTEM
TAT − TOTAL AIR TEMPERATURE
YD −YAW DAMPER
HBMU1
HBMU2
GF1410_022
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 BTMS 3
and BTMS 4.
The HBMUs also monitor brake temperature data. The data sent by the Brake Temperature
Monitoring 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 that
the standby YD actuator is heated. (For more information see Chapter 10, FLIGHT CONTROLS).
ICE AND RAIN PROTECTION
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
14−10−13
AIR DATA PROBES AND SENSORS (CONT'D)
HBMU (Cont’d)
The HBMU receives data from various airplane systems via the Data Acquisition Units (DAU) to
control 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/off
logic.
• 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.
　
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