C. Standby Power System (24-33-00)
(1)
AIRPLANES WITH 30-MINUTE STANDBY POWER; The standby power system includes the main battery and static inverter. The standby power system provides 28-volt dc and/or 115-volt, single phase, 400 Hz ac power to critical flight loads in case of a loss of main ac and/or dc power. The system can supply these loads for 30 minutes. The standby system also serves as an independent power source for the autoland system center channel during a category III autoland.
(2)
AIRPLANES WITH EXTENDED STANDBY POWER; The standby power system includes the main battery and static inverter. The standby power system provides 28-volt dc and/or 115-volt, single phase, 400 Hz ac power to critical flight loads in case of a loss of main ac and/or dc power. The system can supply these loads for 90 minutes. The standby system also serves as an independent power source for the autoland system center channel during a category III autoland.
(3)
AIRPLANES WITH HYDRAULIC MOTOR GENERATOR; Hydraulic motor generator is an independent non-time-limited backup power source which is installed on the extended range airplanes. The hydraulic motor generator is activated automatically when power is lost at both main ac buses. The hydraulic motor generator provides both ac and dc power.
D. Battery/Battery Charger System (24-31-00)
(1)
The main battery/charger system provides 28-volt dc power for loads on the hot battery bus, supplies power to the APU controller during APU starting, and serves as the primary source for the standby power system.
(2)
The APU battery/charger system provides 28-volt dc power for APU starting and for the loads on the APU hot battery bus.
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MAINTENANCE MANUAL
HYD GEN
HYD GEN
DC POWER
DC POWER
AIRPLANES WITH HYDRAULIC MOTOR GENERATOR AIRPLANES WITH APU START TRU AIRPLANES WITH 90-MINUTE STANDBY POWER
DC Generation Block Diagram
Figure 1
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MAINTENANCE MANUAL
(3) AIRPLANES WITH EXTENDED STANDBY POWER; The main and APU batteries are paralleled when left main 28-volt dc power is lost to provide a 90-minute standby power source.
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DC GENERATION - ADJUSTMENT/TEST
_______________________________
1. General_______
A. This procedure has these tasks:
(1)
An Operational Test of the DC Generation System and Battery Charger Failure Detection Circuit.
(2)
An Operational Test of the Battery Charger and Current Monitor.
(3)
An Operational Test of the DC Tie Control Unit and DC Tie Relay.
TASK 24-30-00-705-048
2. Operational Test - DC Generation System and Battery Charger Failure___________________________________________________________________ Dectection Circuit__________________
A. References
(1)
AMM 24-22-00/201, Electrical Power - Control
(2)
AMM 27-61-00/201, Spoiler/Speedbrake Control System
(3)
AMM 31-41-00/201, EICAS
B. Access
(1) Location Zones
211 Control Cabin - section 41 (LH side)
212 Control Cabin - section 41 (RH side)
C. Prepare for the Operational Test 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：757 AMM 飛機(jī)維護(hù)手冊(cè) 電源 ELECTRICAL POWER 2(20)
