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cooling is provided by the AB fuel/oil cooler before
returning to the IDG. Should an excessive amount of
heat be developed in an IDG, a thermal (390 “F) actuated
device automatically decouples the input shaft from the
remainder of the CSD, protecting both the CSD and
generator. There are no provisions for recoupling the
IDG unit in flight.
2-59 ORIGINAL
NAVAIR 01.Fl4AAD-1
NOMENCLATURE FUNCTION
a
MASTER GEN switch NORM Connects the generator to the main buses through the line
(lock lever) contactor.
OFF/RESET - Disconnects generators from the buses. Reset the generator If
tripped by an overvoltage, undervoltage, or fault condition.
TEST - The generators are energized but are not connected to the
buses. Provides a means to analyze a system malfunction
indicated by a generator caution light when an attempt to reset a
generator Is unsuccessful.
0
EMERG generator NORM - Safety guard down. Emergency generator Is automatlcally
switch connected to the essential buses lf both dc power sources fail.
OFF/RESET Safety guard must be lifted. Disconnects the emergency
generator from the essential buses. Resets the generator W
trlpped by an undervoltage or underfrequency condition.
GEN caution lights are on the pllot’s caution/advisory light panel. Each light Is
tied to its respective main ac contactor and is powered by the essential bus no.
2. Illumination of the L GEN or R GEN caution light indicates that the
corresponding generator is not supplying power due to a fault in the generator,
generator control unit, or electrical distribution system.
@ light
TRANS/RECT advisory A TRANWRECT advisory light Is on the lower half of the pilot’s caution/advisory
Indicator panel. Illumination of the TRANS/RECT advisory light Indicates either a
single or dual transformer-rectifier failure has occurred.
ORIGINAL 2-60
Figure 2-37. Generator Panel
Failure ofthe weight-on-wheels circuit to the
in-flight mode while on the deck will cause
the loss ofECS engine compartment air ejectorpumps,
c ausinga subsequenItD G disconnect
and illumination of the GEN light.
2.15.1.1.1 Generator Control Units. Generator
output voltage and frequency are individually monitored
by GCUs, mat prevent application of internally
generated power to the aircraft bus system until the
generator output is within prescribed operating limits.
With the main generator switch in NORM, the applicable
generator is self-excited, so that during the engine
start cycle, it automatically comes on the line at approximately
60-percent rpm under normal load conditions.
Likewise, during engine shutdown, the GCU automatically
trips the generatoro ff the line as the power output
decreasesb elow prescribedl imits at approximately 55
percent.
During normal operations, the generator control
switches remain in NORM continuously. However, subsequent
to an engine shutdown, stall, or flameout in
flight where the GCU has tripped the generator off the
line, the reattainment of normal engine operation will
not automatically reset the generator unless the engine
speed decreasesb elow about 30-percentN Z ‘pm, If a
transient malfunction or condition causes the generator
to trip, the generator must be manually reset by cycling
the applicable generator control switch to OFF/RESET
then back to NORM.
When normal reset cannot be accomplished, TEST,
on the generator control switch, allows the generator lo
bee xcitedb ut not connectedt o the aircraAb uses.I n test,
a CSD, generator,o r GCU failure causest he GEN light
to remain illuminated. If the light goes out, the problem
is in the distribution system.
2.15.1.2 Transformer-Rectifiers. Two transformerrectifiers
convert internal or external ac power to 2%Vdc
power. A single TRANS/RECT advisory light on the
pilot advisory panel provides failure indication for one
or bofh transformer-rectifiers. No flightcrew control is
exercised over transformer-rectifier operation aside
from controlling the ac power supply or circuit breakers
for the power converters. The transformer-rectifiers
have a rated output of 100 amperes each. Each unit is
capable of assuming the complete dc electrical load of
the aircraft. Forced air cooling is provided with engines
running to dissipate the heat generated by the power
converters.
NAVAIR Ol-Fl4AAD1
2.15.1.3 External Power. Ground power is applied
through a receptacleju st aft of the nosegear.T he pilot
has control over external power application only
through hand signals to the plane captain. An external
power monitor prevents application of external power
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F-14D 飞行手册 Flight Manual 1(90)
