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STUDENT GUIDE FOR T-1A AIRCRAFT SYSTEMS
CHAPTER SIX
External Power Limitations
Reference Miscellaneous Limitations - Ground Power Unit Limitations, Section V, T.O. 1T-1A-
1, for specific limitations of the external power system.
DC Standby Power
The DC standby power system consists of a standby battery power subsystem, an Altitude
Heading Reference System (AHRS) battery power subsystem, and an emergency supply
subsystem. The systems supply 24 VDC to selected aircraft systems in case of aircraft electrical
power failure. In the event of total electrical failure (including the aircraft battery) the standby
bus supplies electrical power to the standby attitude indicator, other selected standby
instruments, and the CP's lights for approximately 30 minutes.
DC Standby Battery Power
The DC standby power subsystem consists of a standby battery, and a DC power distribution
channel. The standby battery is located in the nose electronics compartment and supplies power
to the following:
1.
Standby attitude indicator
2.
Ultra High Frequency (UHF) radio
3.
Remote Terminal Unit (RTU) #1
4.
No. 1 ITT indicator
5.
Electronic fuel control - start
6.
CP instrument light power supply
7.
Standby altimeter vibrator
DC Standby Power Source
1.
A 24 VDC lead-acid battery
2.
The STBY PWR switchlight
The STBY PWR switchlight controls and indicates standby battery power subsystem status.
When power is applied to the aircraft electrical system, the white STBY PWR indicator
illuminates and remains illuminated. When the switchlight is pressed, the green ARM indicator
illuminates, indicating the standby battery is connected to the standby bus. With the system
armed, loss of all primary (or main) electrical power will illuminate the ON indicator, which
ELECTRICAL POWER SYSTEMS
6-3


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