Environmental Requirements; Air Conditioning; General; Humidity Control - BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual

primary airflow to the cockpit is from the left
ACU. The right ACU supplies the cabin area.
The ACU delivery ducts are interconnected by
balance ducts to provide a more even distri-
bution to all occupied areas. This also allows
a single ACU to supply both areas.
ENVIRONMENTAL
REQUIREMENTS
The normal environmental requirements of
the Canadair Challenger are to provide for:
ground heating and cooling; in-flight air con-
ditioning; instrument panel cooling and avion-
i c s b a y v e n t i l a t i o n . F o o t w a r m i n g a n d
windshield demisting were discussed under
Chapter 9, "Pneumatics."
A ram-air ventilating system is also provided
for ventilation of the occupied areas in case
of failure or other malfunctions occurring in
the air-conditioning system.

AIR CONDITIONING

GENERAL

Air conditioning is achieved by the controlled
intermixing of hot engine bleed air with the
output of two air-conditioning units (ACUs).
The ACUs cool air by heat exchanging and by
refrigeration (supercooled air supply produced
by the air-cycle machines through expansion
of compressed air).
The cooling medium for the heat exchangers
is ram air. An ejector is provided to induce a
cooling airflow through the heat exchangers
when the airplane is on the ground, or in flight
if temperature tends to increase too high.
11-2 CL 601-3R
CL-600-2B16 PILOT TRAINING MANUAL

HUMIDITY CONTROL

Each ACU has a mechanical water separator
that removes water droplets by swirl action,
resulting in comfortable humidity in the oc-
cupied areas. The water removed from the air-
flow is sprayed onto the heat exchangers to
increase their cooling effectiveness. Ice pre-
vention at the water separator is achieved by
a warm air bleed line that maintains the inlet
nozzle temperature above the freezing point.
A pressure-operated bypass is incorporated
in the water separator in case of blockage. A
water extractor is also used to prevent ice for-
mation in the air-cycle machine. The water is
thrown overboard.
TEMPERATURE
CONTROL
GENERAL
Separate temperature control systems are pro-
vided for the cockpit and cabin areas by two
temperature control valves. These operate in
response to input signals from the associated
temperature control unit. The signals, trans-
mitted from fan sensors, duct sensors, and tem-
perature selectors are computed, and an output
signal is sent to the associated temperature
control valve to produce and maintain the de-
sired temperature in the affected area.
The temperature control panel (Figure 11-1)
for the cockpit and cabin areas is located on
the copilot's side console. It contains two
mode selector switches labeled "NORMAL,"
"STANDBY," and "MANual" for the cockpit
and cabin, respectively. Located below each
mode selector is a rheostat TEMPerature se-
lector with its extreme positions labeled
"COLD" and "HOT." A cabin temperature in-
dicator graduated in degrees Celsius is lo-
cated in the center of the temperature control
panel. Input to the indicator is from the cabin
fan sensor. The power for temperature control
is supplied by DC bus 1 for the cockpit and DC
bus 2 for the cabin.
FOR TRAINING PURPOSES ONLY
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