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zones of dual loops. The four zones are divided as follows:
- Right pylon dual loops: includes the powerplant interface to the right intermediate pressure valve (IPV) and right
high pressure valve (HPV)
- Left pylon dual loops: includes the powerplant interface to the left (IPV) and left (HPV)
- Right anti-ice ducting dual loops: includes all the ducting downstream of the right HPV to the end of the right wing
bleed-air tubing
- Left anti-ice ducting dual loops: includes all the ducting downstream of the left HPV to the end of the left wing
bleed-air tubing
When a leak is detected in the pylon zone (upstream of the HPV), a L (R) PYLON BLEED LEAK (W) message is displayed
on the EICAS. The pilot must reduce the corresponding engine throttle and if the leak persists, shut down the corresponding
engine.
When a leak is detected downstream of the HPV, a WING ANTI-ICE LEAK (W) CAS message is illuminated and the IASC
will automatically close both wing anti-ice valves to isolate the failure and stop the leakage. If the leak stops after the automatic
shutdown, the warning message will be replaced by a L (R) WING ANTI-ICE FAIL (C) CAS message. The pilot
should then complete the shutdown of the wing anti-ice system
WING TEMPERATURE SENSORS
Dual temperature sensors provide feedback temperature data to the integrated air system controller (IASC). Two dualtemperature
sensors are installed in the outboard section of each wing and two in the inboard section. Channel B of each
IASC receives data from one sensor at each of the four wing positions.
Each outboard sensor monitors the leading edge of its associated wing for insufficient temperature. A L (R) WING ANTIICE
FAIL (C) message will illuminate if there is insufficient heat.
The inboard sensor supplies the temperature data used to modulate the wing anti-icing valves. The sensor also monitors the
wing for overheat and will display L (R) WING OVHT (W) CAS message if the condition exists.
ICE AND RAIN PROTECTION
Volume 2 Flight Crew Operating Manual May 06/2005
14-01-04 CSP 100-6 REV 2
WING ANTI-ICE SYSTEM (Cont)
WING ANTI-ICING VALVES
The left and right wing anti-icing valves are installed on the bleed-air manifold in the aft equipment bay.
When the WING switch is selected to ON, the wing anti-icing valves modulate as a function of the wing temperature.
The valves are spring-loaded to the closed position. The valve will close when:
- Bleed-air supply pressure is removed
- Loss of electrical power at the valve
- Anti-ice duct failure is detected by the IASC
- Anti-ice system is operated in either FROM L or FROM R mode
The high pressure valves limit the high stage engine bleed pressure to 36 ± 3 psi. If a valve fails and pressure exceeds 46 psi,
a caution (L) R WING A/I PRESS HI CAS message is displayed.
WING ANTI-ICE DUCTS
The aft equipment bay and center fuselage anti-icing ducts provide bleed-air to the wing anti-icing ducts. The hot air enters
the wing via the piccolo tube in the leading edges.
In the wing leading edges, dual sensing loops and dual temperature sensors are used to detect the failure of a wing anti-ice
duct (piccolo tube) or duct connector. The detectors can discriminate between overheat condition caused by a leaking duct
and the normal temperatures associated with wing anti-icing. The wing anti-icing piccolo ducts uniformly spray hot bleedair
onto the inner surfaces of the leading edges.
The bleed-air used to anti-ice the leading edges is dissipated to the atmosphere through vent holes located on the bottom
side of the wing surface.
WING OVERHEAT
When the anti-icing system overheats, a L (R) WING OVERHEAT (W) CAS illuminates, and the pilot shuts off the wing
anti-ice system, selects FROM L or FROM R and selects the system ON. Bleed flow is modulated by the sensor on the
same side as the bleed source when FROM L or FROM R is selected.
On the ANTI-ICE synoptic page, the overheated leading edge will be identified in red.
WING ISOLATION VALVE
A crossbleed duct bridges the two anti-ice lines and contains the wing isolation valve.When opened, bleed air can be supplied
to the wings by one engine. This function is automatic in case of engine failure. In normal operation, the isolation
valve is closed.
The wing isolation valve is pneumatically actuated and electrically controlled. The valve is controlled from the ANTI-ICE
control panel. When FROM L is selected at the WING SOURCE rotary switch, the right wing anti-ice and high pressure
valves are closed and the crossbleed valve opens to permit bleed-air from the left engine to anti-ice both wings.
When the FROM R is selected, the left wing anti-ice and high pressure valves are closed and the crossbleed valve opens
allowing bleed-air from the right engine to anti-ice both wings.
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