S 014-012

 (2)  
Open the sidewall panels aft of the aft equipment center rack, E6 to get access to the APU start TRU.

 S 714-013

 (3)  
Motor the APU (AMM 49-11-00/201).

 (a)  While the APU is motored, make sure the fan in the APU start TRU operates.
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 (4)  S 864-014Do the shutdown procedure for the APU (AMM 49-11-00/201).
 (5)  S 414-015Close the sidewall panels aft of the aft equipment center rack, E6.
 (6)  S 864-016Remove electrical power if it is not necessary (AMM 24-22-00/201).

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 STANDBY POWER - DESCRIPTION AND OPERATION
_________________________________________
 1.  General_______
 A.  AIRPLANES WITH 30-MINUTE STANDBY POWER; the standby power system supplies power to critical flight loads if main power is lost. System components include static inverter, standby power control panel, AC standby power relay, standby power relay, and standby bus off relays. (See 24-33-00/601 for an operational check of standby power system).
 B.  AIRPLANES WITH EXTENDED STANDBY POWER; the standby power system supplies power to critical flight loads if main power is lost. The standby power system is controlled from a panel in the flight compartment. System components include a static inverter, a standby power control panel, an ac standby power relay, a standby power relay, standby bus off relays, a main/APU battery tie remote control circuit breaker, an extended standby power indication relay, a battery discharge indication inhibit relay, and an APU battery charger detection relay. (See 24-33-00/601 for an operational check of standby power system).
 C.  There are two standby buses: 115v ac and 28v dc. When the left ac and left dc buses are powered the ac standby bus receives power from the left ac bus and the dc standby bus receives power from the left dc bus.
 D.  If the left ac bus loses power, the ac standby bus receives power from the static inverter. If the left dc bus loses power, the dc standby bus receives power from the hot battery bus.
 2.  Component Details (Fig. 1)_________________
 A.  Static Inverter
_______________
 (1)  The static inverter converts 28-volt DC power to nominal 115-volt, single phase, 400 Hz AC power. The inverter can supply rated power of 1 KVA continuously when forced-air cooled. The inverter is located in the forward equipment area.
 B.  Standby Power Control Panel
___________________________
 (1)  AIRPLANES WITH 30-MINUTE STANDBY POWER; the standby power control panel, M10062 is located on the pilots' overhead panel P5. The M10062 panel has switches to control the source of standby bus power. Lights on the M10062 panel monitor power on the standby buses and main battery charge status. The STBY POWER switch must be pushed in before the switch can be moved to OFF.
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MAINTENANCE MANUAL

STANDBY POWER
CONTROL PANEL

SEE A
P6 PANEL . AC STANDBY BUS OFF RELAY . AC STANDBY POWER RELAY . DC STANDBY BUS OFF RELAY . STANDBY POWER RELAY
FLIGHT COMPARTMENT
STATIC INVERTER
SEE B
BAT
STBY POWER
AUTO

ON  OFF  BAT 
w 
D I  OFF  a  O 
S  F 
C  F 
　
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