a) The STANDBY PWR OFF light goes off.
b) The dc voltmeter shows 24 | 4 volts
c) The ac voltmeter shows 115 | 5 volts
d) The frequency meter shows 400 | 5 Hz
(j)
Release the GROUND SENSING test switch. 1) Make sure that the STANDBY POWER OFF light comes on.
(k)
Close the forward access door.
(l)
Push the STANDBY POWER switch to BAT. 1) Make sure that the STANDBY PWR OFF light goes off. 2) Make sure that the dc voltmeter shows 24 | 4 volts.
(m)
Put the STANDBY POWER swtich to OFF. 1) Make sure the STANDBY PWR OFF light is ON.
(n)
If the APU is used as the power source, Shut down the APU (AMM 49-11-00/201).
(o)
Put the BAT switch to OFF.
1) Make sure electrical power is removed from the airplane. a) Make sure the STANDBY PWR OFF light is OFF.
(p)
Put the STANDBY POWER switch to BAT. 1) Make sure the STANDBY PWR OFF light is OFF. 2) Make sure the DC voltmeter shows 24 +/- 4 volts. 3) Make sure the AC voltmeter shows 115 +/- 5 volts.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
24-54-00
ALL ú ú 03 Page 503 ú Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(q)
Put the STANDBY POWER switch to OFF. 1) Make sure the STANDBY PWR OFF light remains OFF.
a) Make sure electrical power is removed from the airplane.
(r)
Put the BAT switch to ON. 1) Make sure the STANDBY PWR OFF light is ON.
E. Put the System Back to its Usual Condition.
S 865-006
(1)
Push the STANDBY POWER switch to AUTO.
S 865-007
(2)
Push the GRD PWR switch or the APU GEN No. 1 and No. 2 switches to ON.
S 765-008
(3)
Make sure that the battery is fully charged.
NOTE: For more details about the operation of the battery charger,
____
refer to 24-31-21/501.
S 865-010
(4)
Turn the dc meters switch to TR1.
S 865-011
(5)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
TASK 24-54-00-715-024
3. Standby Power System - Operational Test - (1 mechanic)
______________________________________________________
A. General
(1)
This test uses a deactuators between the ground safety sensor and its target to put the airplane in the air mode. This makes sure the battery will automatically supply power to the standby buses if the ac buses have no power.
(2)
To get accurate results from this test, the ac generation system (AMM 24-21-00) and the dc generation system (AMM 24-31-00) must operate correctly.
B. References
(1)
AMM 24-22-00/201, Manual Control
(2)
AMM 24-31-21/501, Battery Charger
(3)
AMM 32-09-01/501, Main Landing Gear Safety Sensors
(4)
SSM 24-20-04, 24-50-07, 32-31-00
(5)
WDM 24-34-01
C. Access
(1) Location Zone 101 Left Control Cabin - P5 Forward Overhead Panel 102 Right Control Cabin - P6 Load Control Center Panel 202 Lower Nose Compartment - E11 Landing Gear Logic Shelf 217 Main Wheel Well, Right Gear
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
24-54-00
ALL ú ú 04 Page 504 ú Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(2)
Access Panel
1103L Forward Access Door
D.
Procedure
S 865-025
(1) Make sure that the circuit breakers for the dc and standby power systems are closed:
(a)
The circuit breakers on the J9 panel
(b)
The circuit breakers on the P6-4 panel
(c)
The circuit breakers on the P6-5 panel
(d)
The circuit breakers on the P6-6 panel.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300 400 500 AMM 飞机维护手册 电源 ELECTRICAL POWER(171)
