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Figure 10-1 depicts the areas which are anti-
iced on the Challenger.
ICE DETECTION
SYSTEM
GENERAL
An ice detector is mounted on each side of the
forward fuselage (Figure 10-2). These identi-
cal ice detectors consist of an aluminum hous-
ing containing electronic components and an
aerodynamic strut and probe extending into
PROBE
FWD
HOUSING
Figure 10-2. Ice Detectors
CL-600-2B16 PILOT TRAINING MANUAL
HEATERS
STRUT
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
the slipstream. The strut and probe contain
heating elements which deice the detectors
after ice is detected.
OPERATION
The probe in each ice detector is 1/4 inch
(0.635 cm) in diameter and 1 inch (2.54 cm)
long. Each probe is electronically vibrated at
its natural frequency of 40 kHz. When ice ac-
cumulates on the probe, its frequency de-
creases slightly due to the increase in mass.
Due to the high frequency of the probe, only
ice will adhere; other materials, such as dirt
or oil, will not.
During icing conditions, an internal micro-
computer detects probe frequency drops of
more than 133 Hz and activates an associated
flashing, red ICE light (amber on Canadian
airplanes) on the ice detector panel located
on the center instrument panel. (See Figure
10-3 and Annunciator.)
ICE DETECTOR
PUSH TO TEST
ICE
FAIL
SYS 1
ICE
FAIL
SYS 2
Figure 10-3. ICE DETECTOR Panel
Lt é e
Lt d .
ICE
SYS 1
ICE
SYS 2
CL 601-3A/R 10-3
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