BOMBARDIER BD-100-1A10, Operating Manual

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ICE AND RAIN PROTECTION
Volume 2 Flight Crew Operating Manual May 06/2005
14-01-06
CSP 100-6
REV 2
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.
T2 SENSOR
A T2 sensor is installed in the inlet housing of each engine and senses the engine inlet total-air temperature. The T
2
sensor
supplies the inlet total-air temperature to each of the electronic control units (ECU).
The in-control ECU uses the engine inlet total-air temperature for power control. The sensor contains two resistance tem-
perature devices and a heat device for anti-ice. The anti-ice function is controlled from the L or R ENG switches on the
ANTI-ICE panel.
ENGINE SPINNER
The engine spinner is a two-piece, aluminum forging with a conical shape to provide a surface that sheds ice in icing con-
ditions and operates without the need for anti-icing heat.
C
F
O1401002_
010
MANIFOLD
PICCOLO TUBE
NACELLE
LEADING EDGE
NACELLE
ANTI-ICE
RING
T2 SENSOR
FAN
BLADES
SPINNER
EV 2