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electrical signal is converted into a pneumatic signal and the
pneumatic signal positions the temperature control valve
accordingly.
(4) Cabin/Cockpit Temperature Controllers:
The cabin/cockpit temperature controller receives and interprets
various inputs in order to derive an output signal. These inputs are:
• Two cabin/cockpit temperature sensors, for ambient
temperature
• One cockpit temperature sensor, for ambient temperature
• Two cabin/cockpit duct temperature anticipators, for duct
temperature and exhausted air temperature
These inputs are compared to the desired ambient temperature
commanded by the TEMP CONTROL panel knob and an output
signal is then sent to the servo air pressure regulator and torque
motor to position the temperature control valve.
The cabin/cockpit temperature controller receives power from the
28V Right Main DC bus (aircraft 1000 through 1143, excluding
1034) or the Essential DC bus (aircraft 1034, and aircraft 1144 and
subsequent).
(5) Cabin/Cockpit Temperature Sensors:
The cabin/cockpit temperature sensors are dual elements consisting
of two separate sections. One section provides temperature
information to the cabin temperature controllers, while the other
element is actually a temperature bulb for the digital cabin air
temperature indicator located on the cockpit overhead panel. On
airplanes SN 1437 and subsequent and SN 1000 through 1436
having ASC 162A, a second cabin temperature sensor is also
installed. It is used for temperature indication only.
(6) Cockpit Temperature Sensor:
The cockpit temperature sensor is a single thermistor sensing
element. It is used with the compartment thermostat to provide
temperature information to the cockpit temperature controller.
(7) Crossover Function:
Airflow and temperature control capability is maintained in the event
of failure of either engine or either ECS pack.
In the event of an engine failure, the BLEED AIR switch for the
OPERATING MANUAL
2A-21-00 PRODUCTION AIRCRAFT SYSTEMS
Page 22
May 30/02
Revision 7
operative engine is left ON while the BLEED AIR switch for the
inoperative engine is selected OFF. The ISOLATION valve would be
opened to allow operative engine bleed air to both ECS packs. Both
PACK switches are left ON for full airflow and temperature control
capability.
In the event of an ECS pack failure, the PACK switch for the
operative pack is left ON while the PACK switch for the inoperative
pack is selected OFF. The BLEED AIR switch for the operative
pack’s engine is left ON for full airflow and temperature control
capability.
Depending on flight conditions and mission requirements, problem
ECS packs should be managed as necessary. Airplane Flight
Manual limitations should be consulted if an ECS pack is to be shut
down in flight.
NOTE:
Do not select both ECS packs OFF at altitude.
C. Distribution System:
(See Figure 6 and Figure 7.)
Exiting the temperature control valves, the hot bleed air is joined with the
cooled air from the refrigeration unit to become temperature-controlled air.
This air is then introduced into the cabin and cockpit distribution systems,
each having separate temperature control valves and ductwork.
The cockpit distribution system consists of ducting from the cockpit
temperature control valve, the refrigerated air duct, an air duct check valve
and a silencer. Final distribution is from four outlets in the cockpit: a
controllable side (or shoulder) outlet and a non-adjustable foot outlet, for
each pilot.
The cabin distribution system consists of ducting from the cabin
temperature control valve, a air duct check valve and a silencer. Final
distribution is through two louvered baseboard ducts running most of the
cabin’s length, one on each side.
Cabin and cockpit check valves are installed in the compartment ducting
allowing air to flow only in a forward direction. Should the air attempt to
reverse flow, the check valve closes to prevent backflow.
Cabin and cockpit silencers are installed in the ducting under the floor to
silence air noise from the bleed air ducts.
D. Refrigeration System:
(See Figure 7.)
Bleed air which does not bypass the cabin and cockpit temperature control
valves is routed into the refrigeration unit (ECS pack). The ECS pack
consists of the following major components:
• Primary Heat Exchanger
• ACM and ACM Overtemperature Thermal Switch
• Secondary Heat Exchanger
• Water Separator System
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-21-00
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