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canadair
chaifenqer
OPERATING MANUAL
PSP 606
SECTION 14
ICE/RAIN PROTECTION
Subject
TABLE OF CONTENTS
Page
GENERAL
ICE DETECTION
WING ANTI-ICING
General
Operating Modes
System Monitoring
Lower Isolation Valve
Operation
ENGINE ANTI-ICING
General
Operation
WINDSHIELD AND SIDE WINDOWS ANTI-ICING
General
System Controls and Indicators
Operation
ADS SENSORS ANTI-ICING
General
Operation
9
9
12
12A
Figure
Number
LIST OF ILLUSTRATIONS
Title Page
1 Anti-Iced Areas
2 Ice Detector Panel
3 Anti-Icing Ducts and Components
4 Anti-Icing Panels and Indicators
5 Anti-Ice Control (2 Sheets)
2
4
6
8
10
14-CONTENTS
Page 1
Feb 12/88
canadsur
chanencjer
OPERATING MANUAL
Figure
Number Title Page
6 Overheat and Duct Fail Lights 13
7 ADS Anti-Icing Controls and Indicators 15
14 - CONTENTS
Page 2
Apr 4/83
canadair
chauertQer
OPERATING MANUAL
PSP 606
SECTION 14
ICE/RAIN PROTECTION
GENERAL (Figures 1, 3 and 4)
Anti-icing protection is provided by thermal and electrical anti-icing
systems. Thermal anti-icing, using engine bleed air, 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
trailing vanes of the stall protection system angle-of-attack sensors.
System indicators and controls are located on the centre instrument, ANTI-ICE
and A.D.S. HEATER CONT panels (refer to Figure 4).
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.
The ice detector panel consists of ICE, FAIL and ICE lights for systems 1 (left
ice detection system) and 2 (right ice detection system). The ICE lights at
the left side of the panel receive the ice detector signals and indicate icing
conditions by flashing amber (red on FAA registered aircraft). When the wing
and engine anti-icing systems have been selected, white steady ICE lights come
on at the right side of the panel. At the same time the flashing amber ICE
lights go out. The white ICE lights go out when the ice detectors have failed
to detect ice for 60 seconds. The FAIL lights come on when the built-in-test
circuit detects a fault in the ice detection system or when the switch/light is
pressed to test.
WING ANTI-ICING (Figures 5 and 6)
A. General
The wing leading edge is heated with bleed air tapped from the eighth stage
of each high pressure compressor. The bleed air is routed across the
engine pylons and the bleed air shutoff valves and enters the bleed air
manifold. Two modulating/shutoff valves, one installed on each side of the
manifold, control the flow of bleed air into wing anti-icing ducts running
along each side of the aircraft underfloor area to the wing leading edges.
Piccolo tubes, running the full length of each leading edge, discharge the
bleed air against the inside of the leading edge skin. The spanwise flow
of air exhausts through exits on the lower surface of each leading edge.
SECTION 14
Page 1
Mar 01/85
ctiaiientjer
OPERATING MANUAL
PSP 606
TAT PROBE (RIGHT SIDE ONLY)
PITOT STATIC HEADS
Anti-Iced Areas
Figure 1
SECTION 14
Page 2
Feb 12/88
canadair
chaiienQer
OPERATING MANUAL
Operating Modes
The system can be operated in automatic and manual modes selected by the
three-position WING switch on the ANTI-ICE panel.
In the automatic mode (WING switch set to AUTO), the modulating/shutoff
valves are automatically controlled by an electronic anti-ice controller
located in the accessory compartment on the unpressurized side of the rear
pressure bulkhead. The controller compares the signals from two
temperature sensors, each with temperature control and overheat detection
elements, which are located inside the left and right wing leading edges,
respectively. If the sensed temperature is too low, the controller opens
the modulating shutoff valves to maintain the leading edge skin temperature
at 107 + 8°C (225 + 15°F).
When the system is operated in the manual mode (WING switch set to MAN)>
both of the modulating/shutoff valves are powered to the fully open
position. In this mode, the bleed air flow is not temperature-regulated
and, if an overheat occurs, the modulating/shutoff valves must be closed by
setting the WING switch to OFF.
A separate overheat circuit in the anti-ice controller operates in both
modes and transmits a warning to the flight compartment, if an overheat
condition is detected by one of the overheat detection elements on the
temperature sensors in the leading edge (refer to paragraph 0 .
System Monitoring
The operation of the system i s monitored by the following lights on the
centre instrument and ANTI-ICE panels:
- White L HEAT and R HEAT lights on the ANTI-ICE panel, which come on to
indicate that the temperature of the leading edge i s sufficiently high
to provide efficient anti-icing. The lights are operated by associated
thermal switches, designated sufficient heat switches, inside the left
and right inboard wing leading edges.
- Anber L FAIL and R FAIL lights which come on when a low-pressure
condition exists in the associated wing anti-icing duct. The lights are
controlled by pressure switches in the wing anti-icing ducts downstream
of the modulating/shutoff valves.
In the automatic mode of operation, the flow of bleed air into the ducts
may be reduced sufficiently to lower the duct pressure to the preset
warning level. In this case, a thermal switch located in each wing at
WS 95, senses that the leading edge is s t i l l hot enough for effective
anti-icing and prevents the associated (L or R) FAIL light from coming
on. When the low-pressure condition is a true indication of a system
failure, the sensed temperature is always lower than the thermal switch
trip point and the associated FAIL light comes on.
SECTION 14
Page 3
Apr 4/83
cacnhaadnaeinr Qer
OPERATING MANUAL
PSP 606
1ST
ICE ACCUMULATION WARNING LIGHTS
When ice detector sensor probe senses ice accumulation, a
signal is sent to the warning light circuit which causes the
SYS 1 and SYS 2 amber (red on FAA registered aircraft) ICE
lights to flash. Lights go out when wing and engine anti-icing
is selected on.
r©
ICE
ICE
ICE DETECTOR
PUSH TO TEST
SYS1
SYS2
FAIL
FAIL
SYS1
SYS2
©
ICE
ICE
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 lights are also used as a press-to-test indication. ICE MONITOR LIGHTS
Steady white ICE lights come on when wing and engine
anti-icing is selected and remain on until ice detector fails
to detect ice for 60 seconds.
Ice Detector Panel SECTION 14
Figure 2 pa g e 4
Mar 01/85
canaaair
chanencjer
OPERATING MANUAL
A steady red L EDGE OVHT Tight on the ANTI-ICE panel and a flashing
red WING ANTI-ICE/OVHT light on the centre instrument panel come on
whenever an overheat condition is detected on the left or right wing
leading edge* The overheat condition is detected by the overheat
detection element of the affected dual-element temperature sensor and
the warning signal is transmitted via the anti-icing controller to the
flight compartment.
If a failure occurs in the overheat warning circuits, monitoring of
the leading edge skin temperature is maintained by a backup overheat
sensor mounted inboard from each dual-element temperature sensor.
Each sensor i s wired directly to the L EDGE OVHT and WING
ANTI-ICE/OVHT lights and causes these lights to come on i f an overheat
condition is detected in its associated wing leading edge.
An amber AUTO FAULT light on the ANTI-ICE panel, which comes on when
the anti-icing controller detects a fault in one of the overheat
detection circuits caused by an open overheat detection element.
A steady red DUCT FAIL light on the ANTI-ICE panel and a flashing red
DUCT FAIL light on the centre instrument panel which come on when the
bleed air leak detection system detects a leak in one of the wing
anti-icing ducts (refer to SECTION 17, POWER PLANT for further
information on the bleed air leak detection system).
Lower Isolation Valve
A solenoid-operated pneumatic shutoff valve, designated the lower isolation
valve, is installed on the bleed air manifold downstream from the
modulating/shutoff valves. In normal operation, the valve i s closed to
separate the two sides of the wing anti-icing system. If one of the
modulating/shutoff valves fails closed, the valve is opened when the AUTO
FAULT/ISOL OPEN switch/light on the ANTI-ICE panel is pressed. Bleed air
from both of the engines is then fed through the serviceable
modulating/shutoff valve. The white ISOL OPEN light comes on when the
valve is open.
An upper isolation valve on the bleed air manifold is opened to obtain
bleed air crossfeed into the manifold from the left and right engines
(refer to SECTION 17, POWER PLANT for details of valve operation and bleed
air control).
Operation
When the WING switch i s set to AUTO, the anti-icing controller controls the
position of the modulating/shutoff valves. The amber L FAIL and R FAIL
lights come on briefly until pressure in the wing anti-icing ducts reaches
a preset minimum. The white L HEAT and R HEAT lights come on when the wing
leading edges are heated to the required anti-icing temperature. Operation
continues with the anti-icing controller automatically positioning the
modulating/shutoff valves to maintain a constant leading edge temperature.
SECTION 14
Page 5
Apr 4/83
canadair
chauenQer
OPERATING MANUAL
PSP 606
Anti-Icing Ducts and Components
Figure 3
SECTION 14
Page 6
Feb 12/88
canadair
chaiienper
OPERATING MANUAL
The lower isolation valve is normally left in the closed position (ISOL
OPEN light out) when the system is in the automatic mode.
The system requires only occasional monitoring for overheat conditions (L
EDGE OVHT light on) or overheat detection faults (AUTO FAIL light on). If
either of these abnormal conditions is detected, the system must be
operated in the manual mode (WING switch set to MAN) with the lower
isolation valve open.
In the manual mode, the modulating/shutoff valves are set to the fully open
position and the system must be monitored frequently to prevent prolonged
operation with a leading edge overheat. If an overheat condition occurs,
the WING switch must be set to OFF until the L EDGE OVHT light goes out.
I f a bleed air leak occurs in one of the wing anti-icing ducts, the DUCT
FAIL lights on the ANTI-ICE and centre instrument panels come on. If the
leak in the duct is sufficiently large to reduce the duct pressure below
the preset minimum, the appropriate (L or R) FAIL light also comes on.
ENGINE ANTI-ICING (Figure 5)
A. General
Engine anti-icing is obtained by heating the leading edge of the nose cowl
with compressor eighth-stage bleed air. The bleed air is ducted to the
lower left side of each engine via left and right pressure regulating
valves and enters a ring-shaped piccolo tube inside each nose cowl. The
air discharges from the piccolo tube against the inside surface of the cowl
leading edge and exhausts through slots in the cowl assembly.
The solenoid-operated pressure regulating valves are energized to the
closed position. This feature causes the valves to fail open following an
electrical failure.
The system is controlled by the ENGINES, LEFT and RIGHT switch/lights on
the ANTI-ICE panel. When the switch/lights are pressed in, the pressure
regulating valves are de-energized and forced open under bleed air
pressure.* When the switch/lights are pressed out, the valves are energized
closed.
Each switch/light has a white ON and an amber FAIL light. The ON light
comes on whenever the switch/light is pressed in or whenever the associated
pressure regulating valve fails open. A pressure switch in the duct
downstream from the associated pressure regulating valve, causes the FAIL
light to come on i f the switch/light is pressed in and a low pressure
condition exists. The FAIL light also comes on when the switch/light is
pressed out and the pressure regulating valve fails in the open position.
SECTION 14
Page 7
Apr 4/83
canadair
chaiiencjer
OPERATING MANUAL
PSP 606
EFFECTIVITY
Ujj Aircraft incorporating SB 600-0495.
For other A/C, refer to Figure 5.
o
WING
ANTI-ICE
OVHT
m
WING
MAN
OFF
ANTI-ICE
AUTO
FIF/ML]
11 R FAIL 1
ILHEATI
RHEAT
ENGINES 1
PUSH ON/OFF
LEFT RIGHT
| FAIL I
L°LJ
1 DUCT 1
! FAIL 1
! LEDGE 1
j OVHT 1
i FAIL Ijl
i 0N III
1 AUTO I
FAULT
ISOL
OPEN
L. .JJ
WSHLD—
LOW LOW
HIGH HIGH
NOHT I NOHT !
TEST ; TEST
TEST
Q) PUSH OPEN/CLOSED J I—LEFT—L-RiGHT-J
ANTI-ICE CONTROL PANEL n
WING ANTNCE/OVHT LIGHT
DUCT
FAIL
DUCT FAIL TEST SWITCH
©
PITOT
HEAT
PITOT HEAT LIGHT
ADS HEATER CONTROL PANEL O
Anti-Icing Panels and Indicators
Figure 4 SECTION 14
Page 8
Feb 12/88
canadair
ctiaiiencjer
OPERATING MANUAL
PSP 606
B. Operation
When engine anti-icing is required, the ENGINES, LEFT and RIGHT
switch/lights are pressed in- The white ON lights come on and the pressureregulating
valves open allowing bleed air to enter the nose cowl piccolo
tubes. The valves regulate the air flow to maintain a pressure of
55 ± 3 psi at the piccolo tube inlets. When the switch/lights are pressed
in, the amber FAIL lights come on momentarily until the anti-icing air
pressure increases to above 10 psi.
When engine anti-icing is no longer required, the switch/lights are pressed
out to close the pressure-regulating valves, and the white ON lights go out.
The sixth-stage bleed air system, used to provide anti-icing for the engine
splitter rings and inlet guide vanes, is also controlled by the ENGINES,
LEFT and RIGHT switch/lights and uses the same monitoring and fault
indications (refer to SECTION 17, POWER PLANT, for details of this system).
WINDSHIELD AND SIDE WINDOWS ANTI-ICING (Figure 5)
A. General
The windshields and side windows are of laminated construction and each has
a thin heating element between the two outer laminations for defogging and
anti-icing. Each windshield is also equipped with a windshield icing
detector/indicator.
B. System Controls and Indicators
The left and right sides of the system operate independently and are
controlled by the WSHLD, L and R (WINDSHIELD, LEFT and RIGHT on aircraft
not incorporating Canadair Service Bulletin 600-0495) switches on the
ANTI-ICE panel and temperature controllers located under the left and right
side consoles. The temperature controllers monitor temperature sensors,
one for normal operation and one spare, integral with each windshield and
side window.
Amber NO HT lights on the ANTI-ICE panel indicate system faults and a PRESS
TO TEST pushbutton on the same panel is used to test the temperature
controller circuits.
SECTION 14
Page 9
Feb 12/88
chanerujer
OPERATING MANUAL
PSP 606
WING ANTI-ICE SWITCH
Three-position switch controls mode of operation of
modulating/shutoff valves.
AUTO - Anti-icing controller operates modulating/shutoff
valves to maintain constant wing leading edge temperature.
MAN - Anti-icing controller bypassed and modulating/shutoff
valves set to fully open position. Bleed air flow is not
regulated to maintain a specific leading edge temperature.
OFF - Modulating/shutoff valves closed.
ENGINES - LEFT AND RIGHT SWITCH/LIGHTS
Control operation of pressure regulating valves of engine antiicing
system.
When switch/lights are pressed in, valves de-energize 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 valve fails open.
FAIL light - amber light comes on when switch/light is
pressed in and bleed air pressure is low or when switch/light
is pressed out and associated pressure regulating valve fails
open.
OFF |
L AND R FAIL LIGHTS
Amber L or R FAIL light comes on if low pressure condition
is detected in associated wing anti-icing duct.
L AND R HEAT LIGHTS
White L or R HEAT light comes on to indicate that
temperature of associated leading edge is high enough for
effective anti-icing.
DUCT FAIL AND L EDGE OVHT LIGHTS
Red DUCT FAIL light comes on when overheat condition due
to duct failure is detected in area around wing anti-icing
ducts.
Amber L EDGE OVHT light comes on when overheat
condition is detected on left or right wing leading edge.
AUTO
ANTI-ICE
— ENGINES —
LEFT RIGHT
1 L FAIL!
11 R FAIL 1 1
|| |L HEAT] 1
R HEAT
G
Hi FAIL 1
III ON |
1 FAIL ||
1 °N II
L, PUSH ON/OFF -1
1 DUCT I
FAIL
LEDGE
1 1 0VHT 1
1 AUTO t
FAULT
tSOL
1 OPEN 1
PUSH ON/OFF
03
EFFECTIVITY
I t j j Aircraft incorporating SB 600-0495.
[ 1 1 Aircraft not incorporating SB 600-0495.
AUTO FAULT/ISOL OPEN SWITCH/LIGHT
Split legend switch/light controls operation of lower isolation
valve. Valve opens when switch/light pressed in; closes
when switch/light pressed out.
ISOL OPEN light - white light comes on when lower isolation
valve is open.
AUTO FAULT - amber light comes on when anti-icing
controller detects an open overheat sensor in one of the
overheat detection circuits.
Anti-Ice Control
Figure 5 (Sheet 1) SECTION 14
Page 10
Feb 12/88
cacntiaadnaeinr per
OPERATING MANUAL
PSP 606
ANTI-ICE
AUTO
1 LFAIL 1
R FAIL
[LHEAT
R HEAT
ENGINES 1
PUSH ON/OFF
LEFT RIGHT
| FAIL j
1 ON j
1 DUCT 1
1 FAIL |
1 LEDGE
j OVHT j
1 FAIL 1
i ON III
1 AUTO I
FAULT
ISOL
1 OPEN 1
© PUSH OPEN/CLOSED
NO HT LIGHTS (4)
Amber NO HT light comes on if
associated temperature control unit
detects an electrical fault in heating
circuit.
TEST LIGHTS (4)
Green TEST lights come on during
system test to indicated operation of
associated heating circuit.
WSHLD SWITCHES (2)
Three-position switches control same side
windshield 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 than controlled
temperature at LOW setting. Controlled
temperature of side window is the same
at HIGH or LOW.
WINDSHIELD LEFT AND RIGHT
CONTROL SWITCHES (2)
Control the heating elements for the
windshield and side windows.
ON - Power is supplied to heating
elements via the temperature heat
controllers. Temperature is controlled to
58°C (136°F) for the windshield and 41°C
O06°F) for the side window as sensed by
temperature sensors.
OFF/RESET - System is reset after test
of shutdown.
TEST BUTTON
If WSHLD switches are set to HIGH, all
four heating circuits are tested when
button is pressed. Correct operation of
the system is indicated if all four green
TEST lights come on for at least one
second.
PRESS TO TEST PUSHBUTTON
Used to test all windshield and side
window heating circuits.
EFFECTIVITY
LU Aircraft incorporating SB 600-0495.
^ U Aircraft not incorporating SB 600-0495.
Anti-Ice Control
Figure 5 (Sheet 2) SECTION 14
Page 11
Feb 12/88
canaaair
cftaiiencjer
OPERATING MANUAL
PSP 606
Operation
When the WSHLD switches are set to HIGH or LOW, the temperature controllers
monitor their associated temperature sensors and control power to the
heating elements to maintain the windshields and the side windows at a
constant temperature (HIGH selects a higher controlled temperature for the
windshields only).
On aircraft not incorporating Canadair Service Bulletin 600-0495,
when the WINDSHIELD, LEFT and RIGHT switches are set to ON, the temperature
controllers monitor their associated temperature sensors and control power
to the heating elements to maintain the windshields at 58°C (136°F) and the
side windows at 41°C (106°F).
The affected heating circuit is de-energized and the appropriate NO HT
light comes on if any of the following faults occur:
- A windshield or side window overtemperature
- A shorted temperature sensor
- An overcurrent condition
- No current flow when a controller is commanding power
- Current flow when a controller is commanding no power
- A loss of input power (ac or dc) to the system.
With the WSHLD, L and R (WINDSHIELD, LEFT and RIGHT) switches set to HIGH
(on), when the TEST (PRESS TO TEST) pushbutton is pressed, the circuits in
the temperature controllers are independently tested (each controller has
two control circuits: one for the windshield and one for the side
window). If the circuits are operating correctly, the appropriate green
TEST lights on the ANTI-ICE panel come on for at least one second. After
testing, the WSHLD, L and R (WINDSHIELD, LEFT and RIGHT) switches must be
set to OFF/RESET before normal operation can be restored.
The windshield icing detectors/indicators consist of small, red, light
beams aimed at the bottom of the windshields. These beams pass through the
windshields and are not visible under ice-free conditions. When ice
formation begins, light is reflected and is displayed as a red area of
approximately one-half inch diameter. The detectors/indicators come on
whenever the battery bus is energized.
SECTION 14
Page 12
Feb 12/88
canadair
chauenper
OPERATING MANUAL
PSP 606
ADS SENSORS ANTI-ICING (Figure 7)
A. General
The ADS sensors anti-icing system 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 the total air temperature (TAT) probe.
Power to the elements is controlled by a rotary PWR & METER SELECT switch
located on the ADS HEATER CONT panel. The switch is also provided to test
the individual heater elements in conjunction with a 1 HTR CURRENT
indicator.
B. Operation
When the PWR & METER SELECT switch is moved away from the HTRS OFF
position, power is applied to all the heating elements. If a heater fails
in the left or right AOA vane, the left or right static port, or the TAT
probe, an amber HTR FAIL light on the ADS heater control panel comes on.
If this occurs, the switch must be rotated through all positions until the
fault is detected by the HTR CURRENT indicator indicating a red zone. The
HTR FAIL press to reset switch/light must then be pressed to put out the
warning light. The failure indicating system automatically resets to
indicate further failures if they occur.
SECTION 14
Page 12A
Feb 12/88
canadair
ctianenejer
OPERATING MANUAL
PSP 606
^ W
ZUC Q
ZERO
V
o
WING
ANTI-ICE
) MLG BAY 1
D
OE
V*1"
HE
TC
T
OVHT
loVHT III
WARN
FAIL
PUSH TO TEST
o (r^snj o
WING ANTI-ICE/OVHT LIGHT
Flashing red OVHT light comes on with L EDGE OVHT light on
ANTI-ICE panel when overheat condition exists on left or right
leading edge.
When pushed to test, OVHT light comes on flashing and L EDGE
OVHT light on ANTI-ICE panel comes on.
DUCT FAIL LIGHT
Flashing red DUCT FAIL light comes on if bleed air leak is detected
by sensors of bleed leak detection system (refer to SECTION 17,
Figure 11). If wing anti-icing ducts are affected, red DUCT FAIL
light on ANTI-ICE panel also comes on.
When pushed to test, light comes on flashing and DUCT FAIL lights
on ANTI-ICE and BLEED AIR panels come on.
Overheat and Duct Fail Lights
Figure 6
SECTION 14
Page 13
Mar 01/85
canadair
chaiienQer
OPERATING MANUAL
Amber PITOT HEAT lights, located on the pilot's and copilot's instrument
panels, are provided to indicate a failure of the left (pilot's) or right
(copilot's) pitot static head heater. In this case, the system cannot be
reset.
When the PWR & METER SELECT switch is selected to HTRS OFF, the HTR FAIL
light and the PITOT HEAT lights come on, and the HTR CURRENT indicator
indicates in the red zone.
SECTION 14
Page 14
Apr 4/83
cacnhaatiliaeinr tjer
OPERATING MANUAL
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 any further failures.
PWR & 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, ail heating elements are
supplied. Also used to test individual heater elements.
% HTR CURRENT INDICATOR
indicates heater current in terms of percentage. Red zone
indicates failed system.
PITOT HEAT LIGHTS
Amber PITOT HEAT lights come on to indicate failure of associated
pitot static head, heater. Pilot's light signals failure of left heater;
copilot's light signals failure of right heater.
ADS Anti-Icing Controls and Indicators
Figure 7 SECTION 14
Page 15
Apr 4/83 |
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