Heats forward engine components that are subject to icingĮngine Airscoop and Inlet Vanes (4) switches (1 per engine).
Thermostat in the probe opens the circuit at a temp not higher than 121☌Įngine Anti-Ice Each power plant has two separate bleed air anti-ice systems:.
With switch on anti-ice protection is provided w/ a thermostatically controlled electric heating element.
Slotted probed mounted on the right side of the aircraft.
Used: Before Start checklist to Secure checklist (chocks to chocks)
L HTR OUT, R HTR OUT, and master DE-ICING lights if current flow is interrupted or current flow detector is bad.
P/CP (FEAC/28V FLB) heat elements have separate power sources, which ensures pitot static source if one system fails.
One switch (PITOT HEAT) controls power for both P/CP pitot heat.
Pitot tubes (2) mounted symmetrically on either side of the lower fuselage just aft of the radome.
ICING light flash frequency will increase with the severity of icing conditions. The 7 small holes ice first and cause an imbalance. There are 7 small orifices and one large orifice balance the diaphragm. This cycle continues as long as icing condition persist. Ice accumulates on the probe causing a diaphragm actuated pressure switch to energize the ICING light and the probes heating element. Ice Detection System Airfoil shaped probe located on lower right side of aircraft just aft of the radome.
3.2.3 Empennage Switches, Gauges and LightsĪnti-ice: used prior to entering icing conditions (prevents ice formation)ĭe-ice: used when structural icing is evident (removes ice buildup).