Technical data

13773-001
24-30
Page 1
DC GENERATION
1. DESCRIPTION
This section covers the systems to generate, regulate, control, and indicate DC electrical power. The DC
generation portion of the system includes the batteries, alternators (with internal rectifiers), and regulator.
Two batteries (battery 1 and battery 2) and two alternators (alternator 1 and alternator 2) are used in the
power generation system on this airplane. Both batteries are used for power storage. The two alternators
are very similar in design to each other.
The alternators and the batteries are designed to function in parallel or independently. Both alternators are
self-exciting which means the alternators become energized as soon as either battery switch is moved to
the “on” position. If an alternator becomes disconnected, the remaining alternator will still function properly,
as long as the opposing alternator received initial excitation. If the alternators were initially excited from the
batteries, they will continue to generate electrical power if either battery should fail. Because the alterna-
tors are self-exciting (not self-starting), the battery switches should never be turned off during flight.
CAUTION: Never turn the battery switches off during normal flight.
During normal operation, the alternators feed their respective distribution bus independently (ALT 1 feeds
the main distribution bus and ALT 2 feeds the essential distribution bus). The distribution buses are inter-
connected by two 50-amp fuses and diodes. The diodes prevent ALT 2 from feeding the main distribution
bus. Additionally, since ALT 2 / essential bus voltage is slightly higher than ALT 1 / main distribution bus
voltage, ALT 1 will not feed the essential distribution bus unless ALT 2 fails.
The alternators are three-phase AC generator type; each alternator has an internal rectifier, which limits
current output to 28 VDC. Each alternator uses two diodes for each phase to rectify the output. In addition,
these diodes will block reverse current. If a single output diode were to fail, the winding junction will be held
to the output potential, reducing the quantity of current the alternator can produce.
The alternators are regulated by the MCU and power the MCU via 6 AWG tin plated copper wires. Alterna-
tor 1 is protected by an 80-amp fuse within the MCU while alternator 2 is protected by a 40-amp fuse within
the MCU. ALT 1 is connected to the main distribution bus and ALT 2 is connected to the essential distribu-
tion bus. Each alternator system has its own 5-amp alternator circuit breaker located in the circuit breaker
panel. Each alternator is individually protected against overvoltage generation by the voltage regulator,
located within the MCU. ALT 1 is regulated to 28 volts and ALT 2 is regulated to 28.75 volts.
Voltage output of each alternator is a function of engine RPM, alternator design, and load on the alternator.
During low RPM operation, the alternator will require higher engine RPM to provide the same voltage to
increased electrical loads. With nominal loads on the electrical system, alternator 2 will drop off at approxi-
mately 1700 - 2200 RPM and alternator 1 will drop off at approximately 600 - 900 RPM. Alternator 2 drops
off before alternator 1 because alternator 2 spins half as fast as alternator 1.
The drop off RPM for each alternator will change whenever the electrical system loads are altered from
nominal. Any time an alternator drops off line, it will be indicated by illumination of the corresponding ALT 1
or ALT 2 annunciators. If an alternator drops off line due to low engine RPM, the alternator(s) can be
restarted by simply increasing engine RPM. When alternator 2 drops off line, the ALT 2 annunciator will
illuminate and alternator 1 will provide electrical power to the entire electrical system, including charging
both batteries. When alternator 1 drops off line, the ALT 1 annunciator will illuminate and alternator 2 will
provide electrical power to only the essential bus and BAT 1 will provide power to the main bus. Alternator
2 will then allow continued operation of only the flight critical instruments and charging of battery 2.
30 Nov 2000