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a If the START/VALVE caution light illuminates
after the ENG CRANK switch is
off, select AIR SOURCE to OFF to prevent
starter overspeed.
. When attempting a crossbleed or normal
ground start, do not attempt to reengage
the ENG CRANK switch if the engine is
spooling down and rpm is greater than
46 percent. Between 30- and 46-percent
rpm, the ENG CRANK switch may not
stay engaged because of normal variations
in starter cutout speed.
Note
During cold starts, oil pressure may exceed
65 psi. This pressure limit should not be exceeded
for more than 1 minute.
7. Right throttle -IDLE at 20-Percent Rpm.
If an idle crossbleed start is attempted with
high-residual engine EGT and/or throttles
are advanced from OFF to IDLE prior to 20-
percent rpm, higher than normal EGT readings
may occur. If the EGT appears to be
rising abnormally, increasing the supply engine
to 80-percent ‘pm may yield a normal
start temperature.
Note
l Advancing the R throttle Tom OFF to IDLE
automaticallya ctuatest he ignition system.
An immediate indication of fue.1fl ow (300
to 350 pph) will be exhibited and light-off
(EGT rise) should be achieved within 5 to
15s econdsP. eaks tartingt emperaturews ill
he achieved in the 40- to 50-percent tpm
range.A tler a slight hesitation,t heE GT will
return to normal. Exceeding 890 “C constitutes
a hot start. During the initial starting
phase, the nozzle should expand to a fullopen
(100 percent) position.
l If the START VALVE caution light is
illuminated after the ENG CRANK
switchisoffor ifthe ENG CRANKswitch
does not automatically return to off, ensure
that the ENG crank switch is off by
60-percent rpm and select AIR SOURCE
to OFF to prevent starter overspeed.
ORIGINAL 7-12
NAVAIR 0%F14AAD-1
Note
Loss of electrical power may result in smoke
entering the cockpit via the ECS.
8. R GEN light - OFF.
The right generator should automatically pick up
the load on the left and right main ac buses as
indicated by the R GEN light going out at approximately
59-percent ‘pm.
9. R FUEL PRESS light -OFF.
The fuel-pressureli ghts should go off by the time
the engine achieves idle ‘pm.
10. Idle engine instrument readings - Check.
a. RPM - 62 to 78 Percent.
b. EGT - 350 to 650 “C (nominal).
c. FF - 950 to 1,400 Pph (nominal).
d. NOZ position - 100 Percent.
e. OIL-25to35Psi (nominal) (15 psiminimum).
f. FLT HYD PRESS - 3,000 Psi.
11. External power - Disconnect.
Ground engine operation without electrical
power supplied by either the generators or
external power may cause 20-mm ammunition
detonation because of excessive heat in
the gun ammunition drum.
12. ENG CRANK switch-L (let? engine).
When combined hydraulic pressure reaches 3,000
psi, tetum switch to neutral (center position).
13. HYD TRANSFER PUMP switch-NORMAL
Hydraulic transfer pump will operate from flight
side to maintain the combined side between 2,400
to 2,600 psi.
If the transfer pump does not pressurize the
combined system within 5 seconds, immediately
set HYD TRANSFER PUMP switch to
SHUTOFF.
14. HYII TRANSFER PUMP switch - SHUTOFF.
15. Repeat steps 6 through 10 for left engine.
16. Starter air - Disconnect.
17. AIR SOURCE - L ENG, R ENG, then BOTH
ENG.
Verify cockpit airflow in each position.
18. OBOGS master switch - ON.
Ensure ECS service air is available to
OBOGS prior to selecting the OBOGS
master switch ON.
19. HYD TRANSFER PUMP switch-NORMAL.
20. Ground safety pins -Remove and Stow.
Plane captain should remove landing gear pins and
stow them.
7.4.4 Poststart - Pilot
1.
2.
3,
STAB AUG switches -All ON.
MASTER TEST switch - EMERG GEN.
Check that NO GO light illuminates for about 1
second until emergency generator power is connected
to essential buses and GO light illuminates.
When disconnecting this test, the resultant power
interruption causes the standard attitude heading
reference system light to illuminate momentarily,
VMCU operation - CHECK.
Following disengagemento f the emergencyg enerator.
a oroner check of the VMCU is indicated
by illummaiion of the PITCH STAB 1 and 2,
ROLL STAB 1 and 2, YAW STAB OP and OUT,
SPOILERS, HZ TAIL AUTH, RUDDER AUTH,
7-13 ORIGINAL
NAVAIR 01.F14AAD-1
AUTO PILOT, and MACH TRIM lights during
the power transient (approximately 1.25 seconds).
Once normal power is restored, all lights go out
except the RUDDER AUTH light (resettablew ith
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F-14D 飞行手册 Flight Manual 2(19)
