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APU Inflight Operation - ELWS (Loadmeter) /
ASC 420 Procedures ...............................................................EA-29
APU Alternator Failure ................................................................EA-31
Display Unit Failure .....................................................................EA-31
Symbol Generator Failure ...........................................................EA-32
Traffic and Collision Avoidance System (TCAS) Failure.............EA-33
Enhanced Ground Proximity Warning Sys. (EGPWS) Failure....EA-33
DADC Failures ............................................................................EA-33
Related Topics In QRH
Electrical Smoke / Fire: Source Unknown............................... ED-6
Landing With Standby Electrical Power System Operating ..........EF-6
Circuit Breakers Listed By Bus and Group.................................... S-13
Alphabetical List of Circuit Breakers ............................................. S-31
Battery Charging Using APU or External AC Power ....................NG-4
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EA - 2 May 30/02
Electrical Power System Diagram
CHGR
CONT
RLY
CHGR
CONT
RLY
L
ALT
APU
ALT
R
ALT
EXT AC
AUX AC
LAC 2 RAC 2
AC ESS 1
AC ESS 2
ESS AC
E
INV
E INV
ON RLY
R MAIN AC
LAC 1 RAC 1
DC AC AC DC
L CONV R CONV
TRU 1
STBY GEN
AC PWR RLY
TRU
ABEX
HYD
SYS
AUX DC
LDC 2 RDC 2
LDC 1 RDC 1
AC DC
EXT
DC
L MAIN DC R MAIN DC
DC ESS 1
DC ESS 2
ESS DC
NO. 2
BATTERY
L MAIN AC
NO. 2
BATT BUS
BATT
CONT
RLY
BATT
CONT
RLY
BATT TIE
BUS
NO. 2
CHGR
NO. 1
BATTERY
NO. 1
CHGR
NO. 1
BATT BUS
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 Page EA - 3
Alternator / Converter Failure - Dual AFM 4-07-10
After verifying that neither Alternator / Converter can be regained
by use of "Alternator / Converter Failure - Single" checklist
proceed as follows:
1. Crossflow............................................................................... OPEN
2. Fuel Boost Pump (One Main only) .........ON (ALL OTHERS - OFF)
3. "L or R FUEL PRESS LOW" Messages................... CHECK / OUT
If combined hydraulic pressure and the Standby Electrical Power
system are available, proceed as follows. If not, proceed to Step 13.
NOTE: Approximately twenty (20) minutes of electrical power is available if
both batteries are fully charged and Standby Electrical Power System cannot
be used.
4. All Normal Electrical Power Sources (Except Batteries) .......... OFF
5. Standby Electrical Power Switch ................................................ON
6. Standby Electrical E-INVERT Switch .........................................ON
7. Standby Electrical TRU Switch...................................................ON
CAUTION: UNLOAD ELECTRICAL SYSTEM TO STAY AT OR
UNDER 100% AC AND DC POWER AS INDICATED ON STANDBY
ELECTRICAL POWER PANEL. TURN OFF DC ITEMS IF AC
PERCENTAGE IS OVERRANGE, AND VICE VERSA.
NOTE: Speed Brakes may be used, however, operation should be slow
(approximately five [5] seconds for full range movement).
8. Utility Pump .................................................. OFF / AS REQUIRED
NOTE: The Utility Pump, if left in the ARM position, will run continuously.
If both FGCs indicate FAILED, to regain FGC 1:
9. FGC 1 and 2 Circuit Breakers (CPO: A-7, B-7).......................PULL
10. FGC 1 Circuit Breaker Only (CPO: A-7).............................. RESET
NOTE: The Standby Electrical Power system is powered by a
hydraulically driven motor and is therefore sensitive to hydraulic
pressure changes. As long as the limitations in GIV AFM Section 1 are
observed, the Standby Electrical Power system should operate normally.
If the system drops off line, as result of hydraulic pressure transients, it
will be necessary to cycle Standby Electrical Power switch from ON to
OFF and back to ON.
Continued on next page →
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EA - 4 May 30/02
Alternator / Converter Failure – Dual, ctd… AFM 4-07-10
NOTE: The Standby Electrical monitor panel indicates percent power from
the source. The airplane subsystem takes standby AC power and converts it
to DC through the TRU. Standby DC power is converted through the "E"
　
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