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conditioning pack) is excessive.
Pilot’s Manual
PM-132A 6-15
AIR CYCLE MACHINE CONTROLS
Control of the air cycle machine is through the use of the PACK and HI
FLOW switches located on the PRESSURIZATION panel. These
switches control the Pressure Regulating Shutoff Valve (PRSOV). The
PRSOV controls inlet air to either 18 (normal) or 26 (HI FLOW) psig.
The air cycle machine is always On (not illuminated) for normal operations.
PACK Switch — When set to OFF (illuminated), the bleed air supply to
the ACM is shut off (PRSOV closed). When set to On (not illuminated),
bleed air is allowed to pass through the ACM and enter the air distribution
system at 18 psig.
HI FLOW Switch — When set to ON (illuminated), the bleed air coming
out of the ACM compressor section must pass through the cooling
turbine and enter the air distribution system at 26 psig.
The following CAS illuminations are specific to PACK control:
AIR CYCLE MACHINE SYSTEM SCHEMATIC
Figure 6-4
CAS Color Description
ECS FAIL Amber Both channels of the Pack have failed.
ECS FAULT Amber
or
White
A fault has been detected in the appropriate
(L or R ECS) channel of the ECS controller.
(Amber on the ground or White during flight)
PACK HIGH FLOW White HI FLOW is selected on the air conditioning
pack.
1
SECONDARY HEAT
EXCHANGER
PRIMARY HEAT
EXCHANGER
WATER SPRAY
ASPIRATOR
RAM/FAN
AIR IN
RAM/FAN
EXHAUST
WATER
SEPARATOR
TO COCKPIT/
CABIN
TURBINE
COMPRESSOR
AIR CYCLE
MACHINE (ACM)
PRE COOLER
TO COCKP T/CABIN
TEMP CONTROL VALVES
FAN
P
B
BLEED AIR
FROM
ENG NE
RAM/FAN AIR
LP/HP BLEED AIR
WATER
CONDITIONED AIR
LEGEND
LOW LIMIT TEMP CONTROL VALVE
PACK BYPASS SHUTOFF VALVE
ACM BYPASS CHECK VALVE
PACK OVERTEMP SENSOR
LOW LIMIT TEMPERATURE SENSOR
PRESSURE REGULATED SHUTOFF VALVE
B
P
CAS MESSAGES
1 PACK OVHT
Pilot’s Manual
6-16 PM-132A
TEMPERATURE CONTROL SYSTEM
The temperature of the environmental air is controlled by mixing bleed
air upstream of the air cycle machine with refrigerated air downstream
of the air cycle machine. The resulting conditioned air is ducted into the
cabin and cockpit. Separate controls are provided for the cockpit and
cabin creating two temperature zones. Each temperature control system
consists of a temperature control valve, torque motor, temperature
controller, duct temperature sensor, air temperature sensor, and a
COLD-HOT selector. A MANUAL TEMP switch allows the temperature
control valves to be operated manually by rotation of the temperature
selector knobs.
Temperature control valve position, thus, temperature regulation, is
pneumatically controlled by the electrically operated temperature control
system. During normal operation, the respective system temperature
controller will automatically maintain the temperature set with the
(COCKPIT or CABIN) COLD-HOT selector on the ENVIRONMENTAL
CONTROL panel. The controllers maintain the selected temperature
by comparing input signals from various temperature sensors and
then electrically controlling the torque motors that provide pneumatic
pressure (servo air) to the temperature control valves. The cockpit and
cabin air temperature sensors have small blowers that draw air past the
sensing elements to assure rapid sensing of temperature changes.
Whenever the MANUAL TEMP switch is ON, the respective temperature
control valve will respond directly to movement of the (COCKPIT
or CABIN) COLD-HOT selector.
Each system has duct temperature sensors and limiters to provide for
duct temperature indication and protection. The temperature sensors
signal the ECS integrated controller of temperature information during
normal operation. Temperature is displayed on the ECS page as digital
CAB and CKPT indications.
If excessively high temperatures are reached in the cabin or cockpit
supply duct, the overtemp limiter will signal the ECS integrated controller
to close the respective cabin or cockpit temperature control
valve. In this event, a CAB DUCT OVHT or CKPT DUCT OVHT amber
CAS will illuminate. These CAS are primarily for protection during
emergency pressurization (EMER PRESS) operation.
Electrical power for the temperature control system is 28-vdc supplied
by the R MAIN bus for the automatic mode or the R essential bus for
the manual mode. Power is supplied through the respective 1-amp
AUTO or MAN circuit breaker located on the copilot’s ENVIR panel
　
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