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The first digit in the three-part locator is the alphanumeric
that identities the circuit breaker panel. The second
part is a letter and designates the row in which the
circuit breaker will be found. The top row is designated
A, the next row lower is B, etc. The third part is a number
and designates the column in which the circuit breaker
will be found. The innermost column of each panel 1,2,
$8, and 9 or aft most column on each panel 3,4,6,7 L
and R is designated “1,” the next outboard/forward
column is 2, etc. Figure 2-38 is an alphanumeric listing
of circuit breakers.
Note
l Panel No. 1 row A, the column numbering
is different from rows B to J.
l Panel No. 2 rows A to F, the column
numbering is different from Rows G to I.
2.15.3 Degraded Electrical Operation
2.15.3.1 Emergency Generator. The emergency
generator provides a limited but independent backup
source of ac (5 kVA, 1 IYZOO volts) and dc (50 amperes,
28 volts) power for flight-essential components. It is
driven by combined hydraulic system pressure.
With the normal combined hydraulic system operation,
the emergency generator powers the essential ac
and dc No. 1 and No. 2 buses and the AFCS dc bus.
Operation of the generator is automatically initiated
with the loss of dc left main bus even if other dc buses
remain energized.A pproximately 1 secondelapsesfr om
the time of automatic initiation before the generatordelivers
rated power to flight-essential ac and de buses.
Pilot control of the emergency generator is through
the guarded EMERG switch on the MASTER GEN
control panel. With theswitch inNORM, theemergency
generator is automatically activated when all main ae or
dc power is lost. The switch OFF/RESET provides the
pilot with the capability of isolating emergency electrical
power from the aircraft buses (as in the case of an
electrical fire) or resetting the generator.
2.15.3.1 .l Emergency Power Distribution. An
emergency generator control unit monitors the emergency
generator output. If it senses that the emergency
generator cannot supply power within the proper fiequency
and voltage tolerances, it disconnects the essential
ac and dc essential No. 2 and the dc AFCS buses
from the emergency generator. It is possible that this
could happen if the combined hydraulic system is not
operatingn ormally. Ifcombined hydraulicp ressures ubsequently
recovers, the emergency generator switch
must be cycled through OFF/RESET and back to
NORM to regain the essential No. 2 and AFCS buses.
ORIGINAL 2-62
3F8
3F7
4Fl
4F2
214
3ca
8D8
as1
RC2
LFl
215
aE2
7A8
LGl
218
8El
7A5
RD2
ac2
9B8
985
RBI
4F4
2Hl
2H3
2H8
2H9
788
9F5
9D1
7A3
3F3
4F5
9c2
8Cl
9Aa
lC2
1c4
1C8
ac2
28 VAC BUS FDR
AC ESS BUS NO. 2 FDR PH A
AC ESS BUS NO. 2 FDR PH B
AC ESS BUS NO. 2 FDR PH C
ACM LT/SEAT ADJ/STDY POS LT
ADF AC
ADF DC
AFCS BUS FDR
AFCS/NOSE WHEEL STEER
AICS L
AICS L HTR
AICS L LKUP PWR/EMER GEN TST
AICS L RAMP STOW
AICS R
AICS R HTR
AICS R LKUP PWWANTI SKID
AICS R RAMP STOW
AIR SOURCE CONTROL
AIR/ANTI ICE CONTR HOOK CONT/
WSHLD
ALE-39 CHAFF/FLARE DISP
ALE-39 SEQ 1 & 2 SQUIBS
ALPHA COMP/PEDAL SHAKER
ALPHA HTR
ALR-87 CMPTR
ALR-87 RCVR PH A
ALR-87 RCVR PH B
ALR-87 RCVR PH C
ALT LOW WARN
ALR-87 CONTR
AMC BIT/R DC, TEST
ANGLE OF ATTACK IND DC
ANGLE OF ATTK IND AC
ANL Al-TK/TOTAL TEMP HTR
ANN PNL DIM CONTR
ANN PNL PWR
ANT LOCK EXCIT
ANT SVO HYD PH A
ANT SVO HYD PH B
ANT SVO HYD PH C
ANTI ICE CONTR HOOK CONTiWSHLD/
AIR
8El ANTI SKID/R AICS LKUP PWR
211 ANTICOLUSUPP POS/POB LT
RG2 ANTI-ICE/ENG/PROBE
8C3 ANIAWW 4 PH A
ac2 ANIAWW 4 PH 0
ac1 ANIAVvW 4 PH C
9A2 APG-71 ANT
2G3 APG-71 PUMP PH A
2G8 APG-71 PUMP PH B
2G7 APG-71 PUMP PH C
9A3 APG-71 XMTR DC
111 APG -71 XMTR AC
8E8 APN-154
4D8 APX-1OOAC
7F7 APX-100 DC
7C2 ARC- 182 NO. 1
7Cl ARC-182 NO. 2
aA ARMT GAS/L ENG AFT CONTIRAT IND
9A4 ASC
1D2 ASCPHA
lD5 ASC PH 0
lD8 ASC PH C
IF1 ASPJ AUG PH A
IF3 ASPJ AUG PH 6
IF8 ASPJ AUG PH C
IF2 ASPJ BASIC PH A
IF4 ASPJ BASIC PH B
lF5 ASPJ BASIC PH C
9G5 ASPJ DC
9G8 ASW-27
lJ2 ASW-27 AC
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F-14D 飞行手册 Flight Manual 1(92)
