BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual page 55

ICE AND RAIN PROTECTION
Ice and rain protection is divided into two cat-
egories, depending on whether they use bleed
air or electrical power as a source of energy.
The anti-iced areas and their sources are:
• Pneumatic (hot bleed air)
• Wing leading edge
• Engine inlet area
• Electric
• Windshields
• Air data sensors
The empennage does not require anti-icing.
The wing leading edges and engine inlet areas
are anti-iced using engine bleed air. This is
drawn from the 14th compressor stage.
The windshields are anti-iced using the AC
electrical power system which also provides
a defog capability to the windshield and side
window panels.
Seven air data sensors are electrically anti-iced
by 115-VAC power heating integral elements
in each sensor.
All anti-icing operations are electrically con-
trolled with switches located in the cockpit.
Rain protection is provided by continuous en-
gine ignition and by an acrylic windshield on
which water beads; therefore, the use of wipers
is not required.
AIR CONDITIONING
The air-conditioning system uses the air cycle
system of cooling. It supplies air to the cabin
and flight compartment for heating, cooling,
ventilation, and pressurization.
CL-600-2B16 PILOT TRAINING MANUAL
The air-conditioning system includes the pres-
sure regulating and shutoff valves, refrigerated
and conditioned air ventilations system, and
separate cabin and flight compartment tem-
perature control systems.
Two identical air-conditioning units (ACUs)
are located in the aft equipment bay. Air drawn
through a ram-air intake at the base of the ver-
tical stabilizer is ducted through the units as
a cooling agent. A ducting system associated
with each air-conditioning unit is responsible
for delivering conditioned air to the cabin area
from the right ACU and to the flight deck and
cabin area from the left ACU. Cabin and flight
compartment temperature is controlled from
the cockpit in an automatic or manual mode.
Normal pressurization of the airplane is
achieved with conditioned air from the ACU's.
On aircraft 5001-5134 emergency pressuriza-
tion is provided if both ACUs are unavailable.
PRESSURIZATION
The pressurized area of the airplane extends
from the bulkhead immediately forward of
the windshield to the pressure bulkhead at the
rear of the cabin, including the baggage com-
partment and the underfloor area. The pressure
in this area is controlled by two outflow valves
in the rear pressure bulkhead. The outflow
valves are operated by an automatic controller
with a manual pneumatic controller provided
as a backup. The pressurized area of the air-
plane is maintained at a selected altitude of
from -1,000 feet to +10,000 feet. Normal cabin
differential pressure is maintained at 8.8 psi.
Failure of the automatic mode necessitates
the use of the manual mode. In this mode, the
outflow is controlled pneumatically without
the need for electrical power. Operation in the
manual mode is accomplished by adjusting a
manual regulator and monitoring the response
on the cabin altitude indicator.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
CL 601-3A/R 1-17
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