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maintains a constant cockpit pressure altitude of 8,000
feet. At altitudes above 23,000 feet, the cockpit pressure
regulator maintains constant 5-psi pressure differential
greater than ambient pressures. An illustration of the
cabin pressure schedule is shown in Figure 2-78.
2.30.4.1 .I Cockpit Pressure Indicators. A cockpit
pressure altimeter (Figure 2-76) is provided for the
pilot. In the rear cockpit, the RIO has a low-pressure
caution light on the CAUTION and ADVISORY light
panel. This low-pressure caution light, placarded
CABIN PRESS, illuminates when cockpit pressure
drops below S psi absolute pressure or cockpit altitude
is above 27,000 feet.
2.30.4.1.2 Cockpit Pressure MalRnwtlons. Ifthe
cockpit pressurere gulatorm alfunctions,t he cockpit safety
valve will opent o preventa cockpit pressured ifferential
fmm exceedinga positive 5.5~psoi r a negatived ifferential
of 0.25 psi. The cockpit pressurere gulatora nd the safety
valve are pneumatically operated and timction indo
pendemlyt hroughs eparatep ressures ensingl ines.
2.30.4.1.3 Cockpit Pressure Dump. Cockpit pressurization
can be dumped by the pilot by selecting DUIvlP
with the CABIN PRESS switch. When DUh4P is selected
the safety valve is immediately opened and the cockpit is
dt?pRSSurized
ORIGINAL 2-136
NAVAIR Of-F14AAD-1
I NOMENCLATURE FUNCTION
a RADAR COOLING switch OFF - Deactivates the radar cooling pumps.
ON - Activates the radar cooling pump for ground and airborne thermal
conditioning.
@ ;;A$AR ENABLE caution Indicates that radar operation on the ground is possible.
0 COOLING AIR advisory
light
Illuminates afler a delay of 25 to 40 seconds when insufficient cooling is
provided to the electronic forced air cooling system. Degraded cooling may
result from cooling system failure, turbine failure, or ECS duct failure.
@
SENSOR COND advisory
iigm
lllumlnates when coolant exiting the heat exchanger is greater than lC!PF, or
pump output pressure is too low, or when the overtemperature switch shuts
down the radar, television camera Set (KS), and the infrared search and
track (IRST).
Figure 2-77. Avionic F,quipment Liquid Cooling Controls and Lights (Sheet 1 of 2)
2-137 ORIGINAL
0 GND CLG switch
c3 C & D HOT caution light IIn dicates DD or TID overheat condltlon.
APG-71 - Cockpit low flow sensor Is overridden.
CAUTION
l Servo air required to atiuate servo operated valves.
l Use RADAR only when engines are shut down.
OFF - Cockpit low flow interlock Is operationaLOFF shall be selected
when engines are operating.
NAVAIR 0%FlUAD-I
NOMENCLATURE FUNCTION
Figure Z-77. Avionic Equipment Liquid Cooling Controls and Lights (Sheet 2 of 2)
2.30.4.2 Canopy Seal Pressurization. Pressurized
air from the air-conditioning system is ducted through
the cockpit to the canopy seal. The seal is automatically
inflated when the canopy actuator is moved to the closed
position. A check valve in the canopy pressurer egulating
valve prevents the loss of canopy seal pressurization
if the conditioned air manifold is depressurizedI.n itial
movement ofthe canopy actuator automatically deflates
the seal.
2.30.5 Windshield Air and Anti-Ice. Compressor
bleed air at approximately 340 “F and at high pressure
is directed over the outside of the windshield through a
fixed-area nozzle. This blast of hot air over the windshield
will evaporate rain and ice and prevent its fiuther
accumulation. It is activated by selecting ON with the
WSHLD AIR switch. A temperature overheat sensor
at the base of the windshield protects the windshield
from overheating. When the sensor detects overheating
(300 OF), a signal closes the pressure regulating
valve and illuminates the WSHLD HOT advisory light
on the pilot CAUTION ADVISORY light panel (Figure
2-79).
9 Selecting WSHLD AIR ON prior to entering
rain or icing conditions may cause
windshield cracking because of the rapid
cooling effects ofprecipitation.
l Extended operations in clear air with the
windshield air on may cause windshield
cracking and discoloration.
2.30.6 Gun-Gas Purging. External airflow is used
to ventilate the gun compartment for gun-gas purging.
A flush air inlet on the fuselage gun bump and an at?
louvered door containing a FOD screen provide a continual
flow of air to purge gun gases. Gun tiring is limited
to 200-round bursts.
2.30.7 Degraded ECS Operation. There are various
temperature and pressure safeguard systems that cause
the ECS system to shut down if an unsafe situation is
detected. A complete failure of the dual valve will cause
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F-14D 飞行手册 Flight Manual 1(133)
