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it to shut down the pressurization and air-conditioning
system. Should that fail to close, a pressure switch will
close both engine bleed air shutoff valves if an overpressure
(155 psi) situation exists in theoutlet oftheprimary
heat exchangerA. shutdowno fthe bleeda ir supplyd uct,
either automatically or pilot-selected AIR SOURCE
OFF pushbutton, will cause total ECS air shutdown.
Failure of the left or right weight-on-wheels
switches to the in-flight mode can cause loss
of engine ejector air to the IDGs and hydraulic
heat exchangers causing thermal disconnect
and/or heat damage to the generators
and aircraft hydraulic systems.
Note
After an automatic shutdown of the system,
the pilot should select either OFF or RAh4
AIR SOURCE to enable the emergency ramair
door and then hold mm-air switch to
OPEN for approximately 50 seconds to provide
ram-air cooling to electronic equipment
and to the cabin.
ORIGINAL 2-138
NAVAIR Ol-F14AAD-1
Note
l Loss of electrical power with bleed air still
operating will result in smoke entering the
cockpit through the ECS when the aircraft
is on the deck. In flight, only cold air will
be supplied to the cabin and suit. Icing of
the water separator may occur, causing
reduced flow to the cabin. Since the ECS
panel is dependent on electrical power,
selector pushbuttons will be inoperative.
l Retarding throttles to IDLE above 30,M)o
feetm ay result in a considerablere duction
in ECS airflow, leading to a loss of cockpit
pressurization, SENSOR COND light,
and/or COOLING AIR light.
If the 400’ manifold reaches4 75 OF,a 400 “F shutoff
valve closes, stopping the flow of unconditioned engine
bleed air to the 400 OF manifold.
If either compressor inlet or turbine inlet tempemtum
becomes excessive, the refrigeration unit will shut
down. Cockpit indications will be as follows:
1. No cockpit airilow.
2. RIO COOLING AIR advisory light illuminated.
J
-0
Figure 2-78. Cabin Pressure Schedule
3. RIO SENSOR COND advisory light illuminated.
4. If ram-air cooling is not selected, extended flight
with AlR SOURCE OFF could cause an overheating
condition of the converter interface unit
and a subsequenlto ss of primary attitude andn avigational
indications (i.e., multifunction displays,
HUD, NAVAIDs).
The pilot should press the AIR SOURCE RAM pushbutton
and set the RAM AIR switch to OPEN to open
the ram-air door to provide forced-air cooling to the
electronic equipment and to the cabin.
ECS duct failures may be indicated by diminishing
cabin cooling airflow and/or cabin pressurization with
or without COOLING AIR advisory light illumination.
Duct failures may additionally be indicated bypressurixation
loss to the service systems and airflow loss to rain
removal, defog, and heating systems. This cannot be
verified if the system is not in use. Selection of AIR
SOURCE OFF and ram air increasei s appropriatew hen
any indication of duct failure exists. ECS malfunctions
that are not caused by duct failure are usually indicated
by loss of temperaturec ontrol without a cabin or system
airflow/pressurizationd egradation.F ailure of the 400 OF
modulating valve or duct should not cause illumination
of the cooling air light. Any duct failure in this area
2-139 ORIGINAL
NAVAIR Ol-Fl4iUtD-1
NOMENCLATURE FUNCTION
a
WSHLD AIR switch ON- Provides a continuous blast of hot air (34OV) over the exterior
windshield. Used for windshield antl-ice.
OFF - Closes the shutoff valve after a 5-second delay. The system
Is deenerglzed.
0 WSHLD HOT advlsoly Light illuminates when a sensor In the warm air nozzle to the cent&
light wlndshleld lndlcates overheat (3OOOF).
0
CANOPY air diffuser CABIN AIR - 70% of the conditioned alr dlrected through the cookplt alr
lever (both cockpits) diffusers and 30% Is through the canopy defog rails. This Is
normal posltlon.
DEFOQ - Alr flow Is dlrected through the canopy defog rails only.
Figure 2-79. Canopy Defog Controls and Windshield Air
ORIGINAL 2-j40
associatedw ith the COOLING AIR light is mictly coincidentaHl.
owevert,h e ductf aihneb etweenth e primsry
heate xchangearn dt he tmbinec ompmssoars semblyo,r
betweenth e secondarhye ate xchangear ndt he turbine
compressoars semblyc,o uldc aused egradecdo olings irflow
and a COOLING AIK light to illuminate.
Actuationo f the overtemperatumsw itch resultsin
cyclingo f the4 00“ F valve.D uringt hisp eriodt heh eating
capacityo f the4 00O Fm anifoldw ouldb ed egraded.
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F-14D 飞行手册 Flight Manual 1(134)
