Maintenance BITE Page
You use the MAINT BITE index page to select BITE for these systems:
-Flight management computer system (FMCS)
-Digital flight control system (DFCS)
-Autothrottle system (A/T)
-Air data inertial reference system (ADIRU)
-Common display system (CDS)
-Engines
-Auxiliary power unit (APU)
-Fuel quantity indication system (FQIS).
This shows how to get to the MAINT BITE index page from airplane electrical power up.
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737-600/700/800/900 TRAINING MANUAL 737 GENERAL -- ELECTRICAL POWER INTRODUCTION Purpose
The electrical power system makes, supplies and controls electrical power. The system has automatic and manual control features. Built-in-test equipment (BITE) and alternate source selection make the system reliable and easy to maintain.
Electrical power has these subsystems:
-Generator drive
-AC generation
-DC generation
-External power
-AC electrical load distribution.
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ELECTRICAL
POWER
AC ELECTRICAL
GENERATOR AC DC EXTERNAL
LOAD
DRIVE
GENERATION
GENERATION
POWER
DISTRIBUTION
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737 GENERAL -- ELECTRICAL POWER GENERAL DESCRIPTION
Purpose
The electrical power system makes and supplies AC and DC power to the airplane. The system has automatic and manual controls and protection. A standby AC and DC system gives normal and emergency power.
AC Power
The electrical power system has four main AC power sources and one standby power source. These are the main AC power sources and their supply capacity:
-Left integrated drive generator (IDG 1) - 90 KVA
-Right integrated drive generator (IDG 2) - 90 KVA
-APU starter-generator - 90 KVA below 32,000
feet/9,753 meters, and goes down to 66 KVA at
41,000 feet/12,496 meters)
-External power - 90 KVA.
The IDGs and APU starter-generator supply a 3-phase, 115/200 volts (nominal) at 400 Hz. The AC power system design prevents two sources to the same load at the same time.
The static inverter supplies a single phase, 115v ac output to the AC standby bus.
DC Power
Three transformer rectifier units (TRUs) change 115v ac to 28v dc. The airplane also has these DC power sources:
-Battery
-Battery charger.
The battery is the backup DC source if other sources do not operate. The standby power control unit (SPCU) controls the distribution of dc power.
Standby Power
If there is a loss of normal power, the standby power system supplies a minimum of 30 minutes of AC and DC power to systems necessary to maintain safe flight. The battery supplies DC power. The static inverter uses battery power to make AC power. The SPCU controls the distribution of AC and DC standby power.
Protection
The electrical power system has automatic control to protect the system from source failure or load failure. These line replaceable units (LRUs) supply protection and control logic:
-Left generator control unit (GCU 1)
-Right generator control unit (GCU 2)
-APU generator control unit (AGCU)
-Bus power control unit (BPCU)
-Standby power control unit (SPCU)
-Start converter unit (SCU).
The GCUs monitor the system to control and protect the IDGs. The APU GCU and the starter converter unit (SCU) work together to control and protect the APU starter-
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generator. The bus power control unit (BPCU) controls The modules on the P5 also let you monitor the status
and monitors the use of external power. The BPCU of the electrical power system. The panels have lights
protects the airplane from external power whose quality and an alpha-numeric LED display.
is out of limits.
Control
These modules on the P5 panel give manual control of the electrical power system:
-Electrical meters, battery and galley power module
(P5-13)
-Generator drive and standby power module (P5-5)
-AC systems, generator and APU module (P5-4).
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