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Fan Speed Protection
If the fan fails to attain 60% or more of its rated speed within two seconds of activation, the fan
and heater will shut down. During operation, if the fan speed drops below 60% for more than
two seconds, the fan and heater will shut down, and a white CKPT HEAT FAN FAIL status
message will be displayed on the EICAS.
Overtemperature Protection
If the temperature in the heater element reaches approximately 65°C (150°F), the thermal
safety switch will deactivate the heater. The fan will continue to operate to dissipate heat and,
as the element cools, the system will reset automatically.
Avionics Cooling System
The underfloor avionics bay is cooled by a combination of cockpit exhaust air and a portion of
the cold air output from each pack. Electronics displays and instruments in the flight
compartment instrument panel, control panels, and display units in the center pedestal, and
some of the electronic units in the underfloor avionics bay (e.g. IRUs, DCUs) are cooled with
recirculated air from their integral fans. In addition, an automatic cooling system, with its own
fan, draws hot air from behind the flight compartment instrument panel and exhausts it under the
copilot’s seat area. All fans activate automatically when AC power is applied to the airplane.
If the cockpit instrument exhaust fan drops to less than 60% of its rated speed when cooling is
demanded, an EXHAUST FAN FAIL status EICAS message will be displayed. This message
extinguishes when fan speed recovers or when cooling is no longer demanded.
The DISPLAY COOL FAIL status EICAS message will be displayed when any individual EFIS or
EICAS display fan has failed. Continued operation of an EFIS or EICAS display with a failed fan
may result in a display overtemperature. This is indicated by the raster image (e.g. PFD
sky/ground color) being removed from the display and a red DISPLAY TEMP annunciation
appearing on the affected display.
Ram Air Valve
If both packs are inoperative (unpressurized flight), the ram air valve can be opened to allow air
from the ram air scoop to enter the mixing manifold and ventilate the cockpit and the passenger
cabin. The ram air valve is controlled by the RAM-AIR switch/light located on the AIR
CONDITIONING panel. The white OPEN legend will illuminate when the valve is opened.
NOTE
An airspeed of 250 KIAS is recommended during cruise to provide
sufficient airflow to passengers within the cabin.
AIR CONDITIONING AND PRESSURIZATION
Description
Vol. 2 02−10−9
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
PRESSURIZATION SYSTEM
Description
Cabin pressurization is achieved by controlling the leakage rate, or outflow, of aircraft cabin air
through two outflow valves. The outflow valves are located on the aft pressure bulkhead and are
normally controlled by the cabin pressure controller (CPC).
During normal operation, the pressurization system automatically maintains cabin pressure
through all phases of flight. The flight crew only needs to set the landing field elevation and
baro-correction input. Controls are provided on the CABIN PRESSURIZATION panel, and
indications are on the EICAS status page and standby cabin altimeter.
Components and Operation
Cabin Pressure Acquisition Module
The cabin pressure acquisition module (CPAM) provides the data concentrator units (DCUs)
with pressurization data for display on the EICAS.
EICAS indications include:
• Cabin Altitude (C ALT);
• Cabin Rate of Climb or Descent (RATE); and
• Differential Pressure (ΔP).
The CPAM also provides the DCUs with data to generate the following EICAS messages:
• CABIN ALT caution message when cabin altitude between 8,500 and 10,000 ft;
On airplanes not incorporating SB 604–21–004:
• CABIN ALT warning message when cabin altitude exceeds 10,000 ft;
On airplanes incorporating SB 604–21–004:
• CABIN ALT warning message when cabin altitude exceeds 10,000 ft during low-altitude
airfield operation or 14,000 ft during high-altitude airfield operation; and
• DIFF PRESS warning message when cabin pressure differential exceeds 9.0 psid.
If PASS SIGNS switches are selected to AUTO, the CPAM will cause the NO SMKG and SEAT
BLTS signs to illuminate when the airplane’s cabin altitude exceeds 10,000 feet.
If the CPAM fails, the CPAM FAIL caution EICAS message will be displayed and all of the above
functions will be lost. The standby cabin altitude indicator located on the center instrument panel
can then be used to monitor the cabin altitude.
NOTE
Failure of the CPAM does not affect the operation of the cabin
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庞巴迪挑战者604操作手册 Operating Manual 3(23)
