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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 bleed-air 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 sup-plied 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.
Volume 2 Flight Crew Operating Manual May 06/2005 CSP 100-6 REV 2
14-01-04
WING ANTI-ICE SYSTEM (Cont) WING ANTI-ICE SYSTEM SCHEMATIC
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
14-01-05 ENGINE ANTI-ICE
DESCRIPTION
Each of the engine nacelle inlets are anti-iced with engine bleed-air. The left and right engine anti-icing systems are con-trolled by L (R) ENG switches on the ANTI-ICE control panel located on the center pedestal.
COMPONENTS AND OPERATION NACELLE ANTI-ICING VALVES
Nacelle anti-icing valves are located on top of each engine downstream of the high pressure duct. The valves are electrically operated and pneumatically controlled and incorporates a fail safe open feature.
ENGINE NACELLE DUCTING
Hot bleed-air is directed to and then sprayed by a piccolo tube onto the inner surface of the nacelle leading edge. The air is then discharged overboard through an exhaust duct located at the bottom of the nacelle inlet.
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