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or MAN modes.
NORM Mode
In normal mode, the temperature controller provides automatic temperature control in the
selected compartment, using inputs from the fan sensor, the duct sensor, and the temperature
selector.
When there is more than a 3°F difference between the actual and selected temperature, the
temperature control valve is commanded to full hot or full cold. When the actual and selected
temperature is within 3°F, the duct temperature is controlled by modulating the temperature
control valve to maintain the selected temperature. The NORM mode temperature control
range is from 16°C to 32°C (60°F to 90°F).
STBY Mode
In standby mode, the temperature controller provides automatic control of the supply air
temperature. The compartment control loop is bypassed and the temperature controller uses
inputs from the temperature selector and the duct sensor. The supply air temperature can be
varied between 2°C (35°F) and 82°C (180°F) through the rotation of the temperature selector.
Man Mode
When manual mode is selected, the flight crew directly commands the temperature control
valve by adjusting the respective temperature selector on the AIR CONDITIONING panel. The
temperature control valve can be positioned anywhere between full closed and full open.
CKPT TEMP and CABIN TEMP Selectors
The temperature selector knobs to control temperature in the CKPT and CABIN are located on
the AIR CONDITIONING Panel. They are rotated to vary the desired cabin or flight
compartment temperature within the selected mode limits.
AIR CONDITIONING AND PRESSURIZATION
Description
Vol. 2 02−10−7
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR CONDITIONING SYSTEM (CONT'D)
Air Conditioning Panel
Figure 02−10−4
Pack Pressure and Temperature Protection
Pack overpressure monitoring is accomplished by an overpressure switch in the output of the
primary heat exchanger. An overpressure condition will cause the affected pack to shut down
(by closing the pressure-regulating ACU valve). During an overpressure condition, the
10th-stage isolation valve and the applicable 10th-stage shutoff valve will also close
automatically. A pack overpressure condition will illuminate the FAIL annunciation in the
affected L (R) PACK switch/light and display the L (R) PACK HI PRESS caution EICAS
message.
Pack overtemperature monitoring is accomplished using a temperature sensor located in the
ducting between the compressor of the air cycle machine and the secondary heat exchanger.
Compressor outlet temperatures above the trip setting cause the pack to shut down
automatically (by closing the pressure-regulating ACU valve), illuminating the fail annunciation
in the affected L (R) PACK switch/light and displaying the L (R) PACK HI TEMP caution EICAS
message. Once the pack has cooled, it can be re-selected.
A thermostatic switch is located in the cold air outlet duct of each ACU. Hot bleed air could
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
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR CONDITIONING SYSTEM (CONT'D)
Cockpit Heat
The cockpit heat (CKPT HEAT) switch on the AIR CONDITIONING panel controls a fan, an
electric heating element, and a duct temperature sensor mounted on the exhaust duct of the
heater. The fan, mounted under the left-hand side of the cockpit floor, forces air through the
heating element. The temperature sensor monitors the duct temperature and controls power to
the heating element to maintain outlet temperature at 38°C to 49°C (100°F to 120°F). The
heated airflow can be distributed to either the foot warmer manifold or the windshield demist
manifold, or at half flow rate to both, by use of the AIR knob on the right side panel.
　
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