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5A3
5E2
6F6
6F5
6F4
6F8
STA 1 TYPE I DCDRIREL PWR
STA 1 TYPE II DCDR/REL PWR
STA IA AIM-9 PWR AC
STA IA AIM-9 PWR DC
STA 1 B NO. It2 DC
STAIBPWRPHA
STAIBPWRPHB
STAIBPWRPHC
STA 3 DCDWREL PWR
STA 3 NO. II2 DC
STA 3 PWR PH A
STA 3 PWR PH B
STA 3 PWR PH C
STA 3/S IFOL
STA 4 DCDRIREL PWR
STA 4 NO. 1 I2 DC
STA 4 PWR PH A
BTA 4 PWR PH B
STA 4 PWR PH C
STA 4/5 IFOL
STA 5 DCDR/REL PWR
STA 5 NO. 112 DC
STA 5 PWR PH A
STA 5 PWR PH B
STA 5 PWR PH C
STA 6 DCDR/REL PWR
STA 6 NO. 112 DC
STA 6 PWR PH A
STA 6 PWR PH B
STA 6 PWR PH C
STA a AIM-9 COOL
STA a BOL PWR
STA a IFOL
ETA a TYPE i DCDR~REL PWR
sTA a TYPE ii DCDIUREL PER
STA aA AIM-9 PWR AC
STA aA AIM-9 PWR DC
STA aB NO. II2 DC
STA aB PWR PH A
STA aB PWR PH B
STA aB PWR PH C
STARTER VALVE LT
3A7 STBY ATTD IND PH A
4Al STBY ATTD IND PH B
4A2 STBY ATTD IND PH C
211 SUPP POS/POS LT/ANTICOLL
216 STORM FLOOD LTS
3D6 TAIURUDDER/FLAP IND
3A2 TAXI/FORM LT
lH2 TCS PH A
lH3 TCS PH B
lH6 TCS PH C
9c3 TCS SEL
485 TEMP CONT AC
4F5 TOTAL TEMP HTR/ANL ATTK
8F3 TR ADVSY/PLT ANN PNL AUX PWR
7D3 TURN SLIP/BAR0 ALT
7F6 UHF CONTR/VHF
3A6 UTILITY LTS
7F6 VHF/UHF CONTR
LEI
7D6
216
3F2
7D2
LDl
ac3
ac2
aB6 YAW SAS A
LD3 YAW SAS A PWR SUP
885 YAW SAS B
LC3 YAW SAS B PWR SUP
884 YAW SAS M
LB3 YAW SAS M PWR SUP
3F6 26 VAC BUS FDR
WG SWP DR NO. 2/MANUV FLAP
WHEELS POS IND
WHITE FLOOD LT
WING POS IND AC
WING POS IND DC
WING SWEEP DRIVE NO. 1
WSHLD DEFOG CONTR
WSHLDAIR/ANTI ICE CONTR/HOOK
CONT
N2/97
Figure 2-38. Circuit Breaker Alphanumeric Index (Sheet 5 of 5)
2-67 ORIGINAL
NAVAIR OI-Fl4AAD.I
Theexactpressureat which theemergencygenerator
is unable to power all three buses is dependent on the
load placed on the generator and can vary from 2,000 to
1,100 psi indicated. If the emergency generator is required
and there is a hydraulic emergency that could
lowercombinedsystemoperatingpressure,theessential
ac and dc No. 2 and AFCS buses can be powered with
lowerhydmulicpressurebyreducingtheelectricalload,
such as turning off the HUD and not jettisoning ordnance.
Note
When the emergency generator is operating
with one main hydraulic system inoperative,
large hydraulic flow requirements for flight
controls may cause loss of the essential ac
and dc No. 2 and AFCS buses. To regain
these buses the emergency generator switch
must be cycled through OFF/RESET to
NORM after the hydraulic pressurere covers.
Engine instruments are powered by essential
ac bus No. 1. Engine instruments will be
availableorrestoredat lower enginerpm. The
airspeed at which engine instrumentation is
restored (either automatically or by pilot cycling
the emergency generator switch) could
be higher than minimum airspeed.
2.15.3.1.2 Emergency Generator Test. An operational
check of the emergency generator can be accomplished
anytime the combined systemi s pressurizeda nd
at least one main generator is on the line by selecting
EMERG GEN on the master test switch and depressing
the switch. This provides 28 Vdc to activate the emergency
motor-generatora nd checkst he tie contactorsb y
connecting electrical power to the essential ac and dc
buses. The GO light on the MASTER TEST panel indicates
a satisfactory check. A malfunction in the emergency
generator operation is indicated by the NO GO
light.
2.16 HYDRAULIC POWER SUPPLY SYSTEMS
The aircraft employs two main, independente, nginepowered
hydraulic systems, supplemented by two
electrohydraulicpowermodules,abidirectionaltransfer
unit, and a cockpit handpump. The systems are pressurized
to 3,000 psi and use MIL-H-83282 hydraulic fluid
circulated through stainless steel and titanium lines. Hydraulic
fluid is cooled by heat exchangersth at use ejector
air on deck. Hydraulic power system controls and
indicators are shown in Figure 2-39. The components
serviced by each hydraulic power system are shown on
FO- 10.
2.16.1 Flight and Combined Systems
2.16.1.1 Engine-Driven Pumps. The flight and the
combined systems are each pressurized by enginedriven
pumps. The flight hydraulic system pump is
driven by the right engine and the combined hydraulic
system pump by the left engine. Each of the main systems
　
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