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engine compartment tire.
2.7.1 Engine In-Flight Ventilation. In-flight cooling
of the engine compartment is accomplished by nacelle
ram-air scoops, circulating boundary-layer air
through the length of the compartment and expelling the
air overboard through louvered exits, just fonvard ofthe
engine nozzle shroud.
2.7.2 Engine Ground Ventilation. With weight on
wheels, cooling airflow through the engine compartment
is inducedb y the hydraulic heate xchangere jector in the
forward end of the compartment. Air enters through the
nacellem m-air scoopo n the left side,p assesth rought he
hydraulich eate xchangera, ndi s dischargedin to thee ngine
compartment.T he air flows throught he full lengtho f the
nacelle to discharge overboard through a louvered port
atop the nacelle on the outboard side ofthe vertical tail.
2.8 ENGINE IGNITION SYSTEM
There are three electrical ignition circuits, each utilizing
a dedicated igniter, for each engine: main high
energy, afterburner, and backup.
ORIGINAL 2-30
I I EXT ENVIRONMENT I I
NOMENCLATURE a ANTI-ICE switch
02 INLET ICE caution light
0
BLEED DUCTcaution light
,
,
I
i
FUNCTION
DRIDE/ON - Overrides ice detector system to turn on INLET ICE caution
light, and acttvaie external probe heaters and engine anti-ice.
Commands the anti-ice mode to the AICS programmers.
AUTO/OFF - When icing is sensed, Ice detector activates engine anti-ice
system and turns on INLET IcE cactlon light. External probe
heaters activated with weight off wheels. Disables antl-ice
mode to AICS programmers.
OFF/OFF - Engine anti-ice system and probe heaters shut off. INLET ICE
caution light disabled. Disables anti-ice mode to AICS
programmers.
Illuminates when ice accumulates on ice detector with ANTI-ICE switch in
AUTO/OFF or if ORIDE/ON is selected. Does not illuminate with switch in
OFF/OFF.
Illuminates when bleed air leak sensing elements detect temperatures greater
than 575°F between the left and right firewalls, past the primary heat exchanger
and up to the right diverter area. An additional sensor, detecting temperatures
of 255O or greater, senses from the right diverter area, along the 400” manifold
and into the bootstrap turbine compartment.
Figure 2-23. Anti-Ice Control
2-31 ORIGINAL
NAVAIR 01-Fl4AAD-1
2.8.1 Main High-Energy Ignition. The main highenergy
ignition provides ignition in the combustion
chamber for ground and air starts. It is powered by one
of the four windings in the engine-driven ac alternator.
The AFTC provides logic to control main high-energy
ignition automatically. Ignition is available when N2
rpm is 10 percent or greater and is automatically provided
from lo- to 59-percent rpm when the throttle is
abovec utoff. Ignition is secured0 .5 seconda fterN2 ‘pm
rises above 59 percent. At ‘pm above 59 percent, ignition
is provided if Nz deceleration exceeds a 5 percent
‘pm per second rate. Ignition continues for 20 seconds
after N2 deceleration falls below the 5 percent ‘pm per
second rate. Main high-energy ignition is provided continuously
when the engine is in the secondary (SEC)
mode.
2.8.2 Afterburner Ignition. The AB ignition provides
ignition for AB light-offs, and relights in the event
of an AB blowout. It is powered by the same winding in
the engine-driven alternator that powers the main energy
ignition. The AFTC provides logic to control AB ignition
automatically and prevents simultaneous powering
of the main high-energy and AB ignitions. In the event
of an AB blowout, relight is normally provided within
1.5 seconds. AB ignition is not powered ifthe engine is
in SEC mode.
2.8.3 Backup Ignition. The backup ignition provides
ignition in the combustion chamber for ground and
air starts when the BACK UP IGNITION switch on the
THROTTLE CONTROL panel is set to ON. It is powered
by the essential No. 1 ac bus and provides less
power than main high-energy ignition. After use, the
BACK UP IGNITION switch should be set to OFF. To
allow ground checkout of backup ignition, main highenergy
ignition is disabled when the BACK UP IGNITION
switch is ON and weight is on wheels.
pii-1
The BACK UP IGNITION switch shall be
selected to OFF prior to applying external
electrical power to prevent ignition of fuel
puddled in the engine.
2.9 ENGINE STARTING SYSTEM
Each engine is provided with an airturbine starter that
may be pressurized from an external ground starting cart
or by crossbleeding high-pressure bleed air from the
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F-14D 飞行手册 Flight Manual 1(71)
