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enter the ACU if the ACU valve failed to close when the ACU is selected off. The switch
causes the L (R) PACK NOT OFF caution EICAS message to be displayed.
Pack Cooling
Ram air, taken from the air scoop in the base of the vertical fin, is used as the cooling medium
for the heat exchangers. Ram air passes across the precooler and the dual heat exchangers,
extracting heat from the bleed air used by the air-conditioning packs. The ram air is discharged
through exhaust louvers on the upper left and right sides of the aft fuselage.
During ground operations, when airflow through the ram air scoop is inadequate for cooling of
the heat exchangers, an ejector valve opens automatically and draws ambient air from the aft
equipment bay for use in the heat extraction process. The ejector valve may also be
automatically commanded open in flight if insufficient pack cooling is detected.
AIR CONDITIONING AND PRESSURIZATION
Description
Vol. 2 02−10−8
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AIR CONDITIONING SYSTEM (CONT'D)
Cabin Temperature Control Transfer
When the CABIN TEMP CONT XFER switch on the AIR CONDITIONING panel is selected to
CABIN, it transfers the control of the cabin temperature to the cabin electronic system (CES).
When CKPT is selected, the cockpit has control of temperature settings of the cabin.
Foot Warmer Mats
Temperature-regulated, heated mats provide heat for the pilot’s feet. This system is fully
automatic and does not require pilot input for operation. It is also self-monitoring and will shut
down during overtemp.
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. Adaptive flight displays (AFDs) 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 avionics cooling fan drops to less than 60% of its rated speed when cooling is demanded,
a DISPLAY FAN FAIL status EICAS message will be displayed. This message extinguishes when
fan speed recovers, or when cooling is no longer demanded.
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.
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 page and SUMMARY page.
AIR CONDITIONING AND PRESSURIZATION
Description
Vol. 2 02−10−9
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
PRESSURIZATION SYSTEM (CONT'D)
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 (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;
• 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;
• 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
　
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