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TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
No ac or dc standby power  Relay R36 or 37  If STANDBY PWR OFF light is on If STANDBY PWR OFF light is off  Replace R36 Replace R37 

C.  Place STANDBY POWER switch on P5 panel to AUTO.
D.  Close STBY BUS PWR circuit breaker on P6-5 panel and DC STANDBY POWER TR circuit breaker on P6-4 panel.
TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
No ac standby power (dc standby power OK) or no dc standby power (ac standby power OK)  Relay R37  None required  Replace R37 
No ac or dc standby power (airplane on ground condition only)  Relay R37 not actuating  Check that STBY PWR OFF light is on  Replace ac voltage sensor. If not OK - Replace relay R37.  If not OK - Replace standby power module 
Failure of system to go to battery standby power with loss of 115Vac (flight condition simulated – GRD SENSING TEST switch actuated)  AC Volt Sensor  Open STBY BUS PWR circuit breaker on P6-4 panel. Press GRD SENSING TEST switch. System should go to battery power. If not, place STANDBY POWER switch on pilot’s fwd overhead panel to BAT. 

CAUTION:  MAKE SURE LANDING GEAR PINS ARE IN PLACE AND AVOID PROLONGED ACTUATION OF TEST SWITCH OR DAMAGE TO PITOT OR DRAIN MAST HEATERS MAY RESULT. DISENGAGE YAW DAMPER USING P5 OVERHEAD PANEL SWITCH TO PREVENT INADVERTENT RUDDER MOVEMENT.
If system goes to battery
Replace ac voltage standby power.
sensor. If system does not go to
Replace R37 battery power.
4.  Restore System to Normal

A.  Check that STANDBY POWER switch is set to AUTO.
B.  Remove electrical power if no longer required (Ref. 24-22-0, MP).
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

STANDBY POWER SYSTEM -ADJUSTMENT/TEST
EFFECTIVITY
AT CN-RMI THRU CN-RML CA B2501 THRU B2503 IDO 601
1.  General

A.  Major components of the standby power system are the static inverter, standby power transfer relays No. 1 and 2, ac voltage sensor, and the standby power switch. The standby power system should be tested after component replacement or after any other maintenance has been performed on the system.
B.  There are two standby power system tests: an expanded procedure and a short procedure. The expanded procedure tests the standby power system circuitry, the normal and battery supplies to the system, the ac voltage sensor, and the lights and annunciators on the P7 pilot shield and on the M238 annunciator lights module. The short procedure tests the system circuitry and the normal and battery supplies to the system.
NOTE: Anytime the generator drive and standby power module (P5-5) is replaced, the standby power system must be tested per the expanded procedure.
Test Standby Power System (Expanded Procedure)
A.  Verify EMER EXIT LIGHTS switch on P5 overhead panel is in OFF position.
CAUTION:  EMERGENCY EXIT LIGHTING CONTROL SWITCH MUST BE IN OFF POSITION BEFORE REMOVING POWER FROM AIRPLANE. IF LEFT IN ARMED POSITION ALL EMERGENCY LIGHTS WILL COME ON AND BATTERIES WILL DISCHARGE.
B.  Provide 3-phase, 400-Hz, 115-volt power to external power receptacle.
C.  Set GROUND POWER switch on P5-4 to ON.
D.  Set BATT switch on P5-13 to ON.
E.  Open GENERATOR DRIVE OIL LOW PRESS circuit breaker on P6-4.
F.  Press MASTER CAUTION light to reset all caution and annunciator lights.
G.  Set STANDBY POWER switch on P5-5 to OFF and check:
(1)  
STANDBY POWER OFF light on P5-5 illuminates

(2)  
ELEC and MASTER CAUTION lights on P7 illuminate

H.  Press MASTER CAUTION light and check that MASTER CAUTION and ELEC lights
extinguish.

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I.  Set STANDBY POWER switch to AUTO and check that:
(1)  
STANDBY POWER OFF light extinguishes.

(2)  
STANDBY AC light on M238 illuminates.

(3)  
STANDBY DC light on M238 illuminates when INDICATE-TEST switch is set to INDICATE.

(4)  
ELEC light does not illuminate when ELEC light is pressed.

J.  Set AC and DC meter selector switches to STBY PWR and check that:
(1)  
DC voltmeter reads 26 + 4 volts dc.

(2)  
AC voltmeter reads 115 + 5 volts ac.

(3)  
Frequency meter reads 400 + 10 Hz.
　
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