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The water separator anti-ice sensor/controller is a pneumatic
thermostat, installed on the discharge side of the water separator.
The thermostat is set to maintain anti-ice valve position so that air
moving through the water separator is held at a temperature of
approximately 37° F. The sensor/controller remains function
throughout all altitude, temperature and humidity ranges.
One cockpit indication that a water separator may be frozen is an
absence of cool air in all modes of operation. To determine whether
the water separator is merely frozen or the ACM is faulty, the
affected PACK switch is selected OFF and a ten minute time period
is allowed to elapse. The affected PACK switch is then selected ON
and the air temperature is checked. If cool air returns, the water
separator was most likely frozen, thus a warmer temperature should
be selected. If warm or hot air returns, the ACM is most likely faulty.
(6) Cooling Fan:
Ground cooling places additional requirements on the air
conditioning system. As there is no ram air flow, the possibility exists
that the air conditioning equipment would overheat unless a source
of cooling air is supplied.
A turbofan is installed downstream of the ACM in the dorsal fin ram
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-21-00
Page 25
May 30/02
Revision 7
air duct. The fan assembly provides airflow across the primary and
secondary heat exchangers whenever the air conditioning system is
in operation on the ground. Fan air leaving the heat exchangers is
then exhausted overboard.
(7) Cooling Air Distribution:
Dehumidified, refrigerated air from the discharge side of the water
separator is ducted forward, joining that portion of the hot bleed air
having passed through the cabin/cockpit temperature control valves
to become temperature-controlled air. Also, dehumidified,
refrigerated air from the ECS pack is ducted into one line which
supplies cabin and cockpit eyeball ducts installed by the operator’s
completion agency. A check valve is installed in each line to prevent
backflow.
E. Ram Air Ventilation System:
In the event of an emergency, the flight crew can ventilate the aircraft with
ram air from the ram air dorsal fin inlet. A line is installed in the ram air duct
just upstream of the primary heat exchanger. The line is routed to the ram
air check valve and then to the downstream side of the left water separator
refrigerated air duct. If ram air duct pressure is greater than refrigerated air
duct pressure, the ram air check valve opens, allowing ram air into the
refrigerated air line. The ram air then moves forward through the cabin duct
check valve, into the distribution system.
The ram air check valve allows airflow to move only from the ram air duct
into the air conditioning system ducting. During normal operations with the
air conditioning system running, system pressure is always greater than
ram air pressure, thus the ram air check valve is held closed.
Selection of ram air ventilation is accomplished using the RAM AIR switch
located on the cockpit overhead panel. Selection of the switch to RAM
supplies 28V Essential DC bus power to close both air conditioning shutoff
and flow regulating valves, shutting off the air conditioning system. As air
conditioning system duct pressure falls below ram air duct pressure, the
ram air check valve opens, allowing ram air into the distribution system.
Conversely, selection of the RAM AIR switch to OFF allows both air
conditioning shutoff and flow regulating valves to open, restoring the air
conditioning system. As air conditioning system duct pressure rises above
ram air duct pressure, the ram air check valve closes, allowing air
conditioning system air into the distribution system.
NOTE:
Selection of the RAM AIR switch to RAM results in the
cabin altitude climbing, eventually causing the
pressurization system outflow valve to close.
Consideration should be given to manually opening
the outflow valve to ensure adequate airflow for radio
rack cooling.
NOTE:
During use of ram air ventilation, the flight crew has no
control of cabin air pressure or temperature.
OPERATING MANUAL
2A-21-00 PRODUCTION AIRCRAFT SYSTEMS
Page 26
May 30/02
Revision 7
F. Temperature Indication System:
(See Figure 8.)
A digital cabin/cockpit air temperature indicator is installed on the TEMP
CONTROL panel on the cockpit overhead panel. The CABIN temperature
display is provided ambient temperature information from the cabin
temperature sensor. The CKPT temperature display is provided ambient
temperature information from the cockpit temperature sensor. Both sensors
　
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