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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 antiice
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 antiice
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 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 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
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.
· 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/off
logic equations when :
· L and R engine not running and/or,
· WOW and/or,
· airspeed less than 50 knots.
ICE AND RAIN PROTECTION
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
14−10−14
AIR DATA PROBES AND SENSORS (CONT'D)
Probes
There are four PitotStatic
(PS) probes on the side of the fuselage. They supply pitot and static
pressure to the air data computers and standby instruments. Heater elements are installed in the
PS heads and mounting bases.
There are three Total Air Temperature (TAT) probes, one on the fuselage and one each in the
engine inlets.
There are two AOA probes, mounted on the fuselage, one on either side.
PS STANDBY
PS 1
PS 3
PS
STANDBY
PS 2
TAT 3
TAT 3
PS 2
TAT 2
TOP VIEW
ENGINE INLET
TAT 1/2
AOA 1 AOA 2
AOA 2
PS 3
PS 1
TAT 1
AOA 1
GF1410_023
PROBE
The current being drawn by the heater is measured and a heater fault is generated if the current
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