ICE DETECTION
The ice detection system (Figure 10A-2) in-
cludes an ice detector and interpreter mounted
in the left engine intake at the two o’clock
position as viewed from the front of the intake.
A single detector and one red ICE DETECT
light on the warning panel comprise the warn-
ing system. The system is protected with a
10-ampere NAC ICE DETECT circuit breaker.
Pressure differential provides mechanical power
that allows a three-phase cycling operation.
The phases are neutral, sensing, and deicing.
When the detector probe is subjected to ram air
of 40 knots or more, a pressure differential is
10A-2
FOR TRAINING PURPOSES ONLY
LEARJET 20 SERIES PILOT TRAINING MANUAL
FlightSafety
international
FRONT FRAME
ANTI-ICING
(BLEED AIR)
NACELLE CAP ANTI-ICE
(ELECTRIC BLANKET)
WING LEADING-EDGE
ANTI-ICE (BLEED AIR)
WINDSHIELD ANTI-ICE
(BLEED AIR AND ALCOHOL)
Figure 10A-1. Ice and Rain Protected Areas
LOCATION OF
ICE-DETECTION
PROBE
Figure 10A-2. Ice Detection System
LOCATION OF
ICE-DETECTION
PROBE
