Bombardier-Challenger_01-Ice_and_Rain_Protection
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OPERATING MANUAL
PSP 601A-6
SECTION 14
ICE/RAIN PROTECTION
TABLE OF CONTENTS
1. GENERAL
2. ICE DETECTION
3. WING ANTI-ICING
A. General
B. Operating Modes
4. ENGINE ANTI-ICING
5. WINDSHIELD AND SIDE WINDOW ANTI-ICING
6. ADS SENSOR ANTI-ICING
Page
1
1
1
1
2
LIST OF ILLUSTRATIONS
Figure
Number Title
1 Anti-Iced Areas
2 Ice Detector Panel
3 Anti-Icing Ducts and Components
4 Wing and Engine Anti-Icing - Schematic
5 Anti-Icing Controls and Indicators
6 ADS Anti-Icing Controls and Indicators
Page
3
4
5
6
7
8
14-
Page 1
Apr
OPERATING MMUAL
PS? 6Q1A-6
SECTION 14
ICE/RAIN PROTECTION
1. GENERAL (Figures 1 and 3)
Ice and rain protection is provided by thermal and electrical anti-icing
systems. Thermal anti-icing, using 14th stage engine bleed a i r , protects the
wing leading edges and the engine cowlings- Electrical anti-icing is provided
for the windshield and the various sensors of the air data system (ADS),
including the stall protection system angle-of-attack sensors.
2. ICE DETECTION (Figure 2)
Icing conditions are detected by two externally mounted ice detectors. The ice
detectors consist of aerodynamic struts which hold sensing probes into the
airstream. The sensing probe vibrates at a set frequency until ice accumulates
to a point where the frequency starts to decrease. When the frequency
decreases to a value which indicates the ice has reached a certain thickness,
the ice detector sends a signal to the ice detector panel in the flight
compartment.
3. WING ANTI-ICING (Figures 4 and 5)
A. General
The wing anti-icing system monitors the temperature of the wing leading
edges and automatically controls, through an electronic wing anti-icing
controller, the flow of engine bleed air to the wing leading edges to
prevent icing.
Left and right wing anti-icing modulating/shutoff valves direct 14th stage
bleed air into wing anti-icing ducts running along each side of the
underfloor area of the fuselage to the wing leading edges. Piccolo tubes,
running the full length of each leading edge, discharge the air against the
inside of the leading edge skin. The air then exhausts through louvers
along the underside of the wing leading edge.
The left and right sides of the wing anti-icing system are separated by a
normally closed isolation valve.
A control temperature sensor, a standby temperature switch and a sufficient
heat/overheat sensor are fitted to the inside of each wing leading edge.
These sensors monitor the leading edge skin temperature as required for
automatic or standby control as well as for sufficient heat and overheat
indications.
SECTION 14
Page 1
Apr 02/87
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OPERATING MANUAL
PSP 601A-6
B. Operating Modes
In the NORMAL mode, the wing anti-icing controller uses the higher of the
two temperatures sensed by the control temperature sensors and modulates
both wing anti-icing valves to maintain the leading edge temperature at its
optimum value for anti-icing.
In the STANDBY mode, each standby temperature switch cycles its respective
wing anti-icing valve open or closed to maintain the leading edge
temperature within the maximum and minimum limits for anti-icing.
ENGINE ANTI-ICING (Figures 4 and 5)
Engine anti-icing is obtained by heating the leading edge of the nacelle nose
cowl with 14th stage bleed air. The bleed air is ducted to each engine via
l e f t and right pressure regulating/shutoff valves and enters a ring-shaped
piccolo tube inside the nacelle nose cowl. The air discharges from the piccolo
tube against the inside surface of the nose cowl leading edge, then exhausts
through a louver in the nose cowl lower access panel.
A pressure relief valve protects the engine cowl against bleed air
overpressure. An engine anti-ice blowout plug, which is normally flush with
the engine nacelle skin, extends when the valve operates to indicate that an
overpressure relief has occurred and that maintenance action is required before
the next flight. (Refer to Volume 1, WALKAROUND CHECK LIST for location.)
The pressure regulating/shutoff valves are de-energized open. This feature
causes the valves to fail open following an electrical failure.
WINDSHIELD AND SIDE WINDOW ANTI-ICING (Figure 5)
The windshields and side windows are of laminated construction and each has a
thin heating element between the two outer laminations. The windshield and
side window anti-icing system consists of the heating elements, temperature
sensors, dual-channel temperature control units, and controls and indicators on
the ANTI-ICE panel.
The left and right sides of the system operate independently. Each side of the
system has a dual-channel temperature control unit. Each unit monitors
temperature signals from the same side windshield and side window. Two
temperature sensors are provided for each windshield and side window, one for
normal operation and one spare.
ADS SENSOR ANTI-ICING (Figure 6)
The ADS sensor anti-icing consists of heating elements in the left and right
pi tot heads, left and right static ports, left and right angle-of-attack (AOA)
vanes, and in the total air temperature (TAT) probe. Power to the elements is
controlled by the ADS HEATER CONT panel in the flight compartment.
SECTION 14
Page 2
Apr 02/87
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OPERATING MANUAL
PSP 601A-6
TAT PROBE (RIGHT SIDE ONLY)
PILOT STATIC HEADS
AOA VANES
STATIC PORTS
WINDSHIELDS
SIDE WINDOWS
AIR INTAKES
WING LEADING EDGES
Anti-Iced Areas
Figure 1
SECTION 14
Page 3
Apr 02/87
OPERATING MANUAL
PSP 601A-6
SYS 1 AND SYS 2 FAIL LIGHTS
Steady amber FAIL lights come on when built-in-test
circuit detects fault in ice detection system 1 and/or 2.
FAIL ights are also used K a press-to-test indication.
ICE DETECTOR
PUSH TO TEST
FAIL
FAIL
EFFECTIVITY: NO 5001 TO 5134
ICE ACCUMULATION WARNING LIGHTS
When ice detector sensor probe senses ice accumulation,
SYS 1 and SYS 2 ember ICE fights flash. Lights go out
when wing and engine entMcmg is selected on.
ICE MONITOR LIGHTS
Steady white ICE lights come on when wing ana engine
anti-icing cs selected and remain on until ice detector fails
to detect ice for 60 seconds.
CENTRE INSTRUMENT PANEL
Ice Detector Panel SECTION 14
Figure 2 Page 4
Apr 10/95
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OPERATING MANUAL
PSP 601A-6
Anti-Icing Ducts and Components
Figure 3
SECTION 14
Page 5
Apr 02/87
challenger
OPERATING MANUAL
PSP 601A-6
STANDBY
TEMP
SWITCH
(TYPICAL)
CONTROL
TEMP
SENSOR
(TYPICAL)
SUFFICIENT HEAT/
OVERHEAT
SENSOR
(TYPICAL)
OPEN/CLOSE
SIGNAL
WING
ANTI-ICING
MODULATING/I
SHUTOFF
VALVE
(TYPICAL)
ISOLATION
VALVE
TO ENGINE -
COWL (TYPICAL)
ENGINE ANTI-ICING
REGULATING/SHUTOFF
VALVE (TYPICAL)
TO THRUST
REVERSER
(TYPICAL)
HTH STAGE BLEED
SHUTOFF VALVE
(TYPICAL)
A
NOTE
If open, valves are closed by thrust
reverser operation infer to Section 17).
Wing and Engine Anti-Icing - Schematic
Figure 4
SECTION 14
Page 6
Apr 02/87
WING SWITCH
Three-position switch controls mode of operation
of left and right wing anti-icing
modulatmg/shutoff valves.
STANDBY - Moduiating/shutotf valves cycle
open or dose to maintain wing leading edge
within the minimum and maximum allowable
temperatures.
OFF - Modulating/srurtoff valves dosed.
NORMAL - Anti-icing controller operates
modulating/shutoff valves to maintain a constant
wing leading edge temperature.
L FAIL AND R FAIL LIGHTS
Amber L FAIL or R FAIL light comes on if WING
switch is set to STANDBY or NORMAL and tow
pressure condition is detected in the associated
wing anti-icing manifolds. Each light is inhibited
when its associated HEAT light is on.
L HEAT AND R HEAT SWITCH LIGHTS
White L HEAT or R HEAT light comes on to
indicate that temperature of associated leading
edge is sufficient for effective anti-icing.
When switch/light is pressed to test, correct
operation of system control and monrtonng
circuits is indicated when flashing WING ANTi-
ICE. OVHT »tght on centre ^istrument panel and
L HEAT. R HEAT. L FAIL. R FAIL and OVHT
iights on ANTI-ICE panel ail come on.
DUCT FAIL AND SENSOR FAIL LIGHTS
Red DUCT FAIL light Refer :c Section 16
Amber SENSOR FAIL light comes on when
controller detects an open temperature sensor in
one of the overheat detection circuits.
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OPERATING MANUAL
PSP 601A-6
COWL-LEFT AND RIGHT SWITCH/LIGHTS (2)
Control operation of pressure regulating/shutof?
valves of engine anti-icing system.
When switch/lights are pressed in. valves deenergize
and open. When pressed out. valves are
energized and close.
ON light - white light comes on when
switch/light is pressed in or when associated
pressure regulating/shutoff valve fails open
FAIL light amber light comes on when
switch/iight is pressed m and bleed air
pressure is low or when switch/light is
pressed out and associated pressure
regulating/shutoff vaive fails open.
WSHLD SWITCHES (2)
Three-posit ion switches control same side
wmoshteid and side window heating elements
HIGH or LOW - Temperature control units
maintain windshield and side window at constant
temperature. At HIGH setting, controlled
temperature of windshield is higher tharn
controlled temperature at LOW setting
Controlled temperature of side window >s the
same at HIGH or LOW.
OVERHEAD
PANEL
BUTTON
WSHLD switches are set to HIGH, all four
ircuits are tested when outton is
Correct operation of the system is
if an four green TEST lights come on
s: one second.
OVHT AND ISOL OPEN SWITCH/LIGHTS
When pressed »n. anti-ice isolation valve opens
and white ISOL OPEN light comes on. When
pressed out. valve closes and light goes out.
Red OVHT lignt comes on when an overheat
condition is detected in the left or ngnt wing
leading edge.
NO HT LIGHTS 14)
Amber NO HT hght comes on if associated
temperature control unit detects an electrical
fault m heating circuit.
TEST LIGHTS t4)
Green TEST itgnts come on during system test
to tnoicated correct operation of associated
heating circuit.
WING ANTl-lCE.-OVHT LIGHT
Flashing reC OVHT light comes on with OVHT
light on ANTl-ICT panel when overheat condition
exists on left or right leading eoge.
When pushed to test, light comes on flashing.
DUCT FAIL LIGHT
Refer to Section 17.
CENTRE INSTRUMENT PANEL
Anti-Icing Controls and Indicators
Figure 5
SECTION 14
Page 7
Apr 02/87
OPERATING MANUAL
PSP 601A-6
HTR FAIL SWITCH/LIGHT
Amber HTR FAIL light comes on if a heater fails in the left or right
AOA vane, left or right static port, or the TAT probe. When
pressed in, light goes out and system is reset to receive arty
further failures.
PWR fcr METER SELECT SWITCH
Controls power to heating elements in the left and right pitot
heads, left and right static ports, left and right AOA vanes, and
the TAT probe. When set away from HTRS OFF, all heating
elements are supplied. Also used to test individual heater
elements.
OVERHEAD PANEL
HTR
FAIL
PUSH TO
RESET
% HTR CURRENT INDICATOR
Indicates heater current in terms of percentage. Red zone
indicates faBed system.
PITOT HEAT LtGHTS (2)
Amber PITOT HEAT tights come on to indicate failure of
associated pitot static head heater. Pilot's light signals failure of
left heater: copBot's light signals failure of right heater.
PILOTS AND COPILOT'S INSTRUMENT PANELS
ADS Anti-Icing Controls and Indicators
Figure 6
SECTION 14
Page 8
Apr 02/87
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