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equipment. Generator operation is controlled from the
pilot ELEC PWR control panel (fig 2-37). When a
generator control switch is in GEN 1 or GEN 2 position,
the selected generator(s) are brought on-line. When the
switch is placed to OFF/RESET, the generator is taken
off-line and fault sensing is reset. Two caution lights,
GEN 1 and GEN 2 on the pilot caution/ warning panel
illuminate whenever the generator control unit senses a
fault. These lights receive 28 vdc from the emergency
dc bus through the CAUT circuit breaker on the pilot
overhead circuit breaker panel (fig
2-39).
b. External Power Receptacle. The external
power receptacle is located aft of the aft avionics bay. It
provides a means of connecting external power to the
helicopter. A micro switch, which is actuated by opening
the
external power access door, informs the pilot when the
door is open by illuminating the EXT PWR caution lamp
on his caution/warning panel. The system is controlled
from the ELEC PWR control panel. When the
BATT/EXIT PWR switch is at EXT PWR position, the
external power monitor checks the GPU for proper
phase sequence, voltage, and frequency. The power
monitor also inhibits connecting and charging of the
battery. The EXT PWR caution light receives 28 vdc
from the emergency dc bus through the CAUT circuit
breaker on the pilot overhead circuit breaker panel (fig 2-
39).
Figure 2-37. Pilot Electrical Power Control
Panel
Change 3 2-67
TM 1-1520-238-10
Figure 2-38. Electrical Power Distribution System (Sheet 1 of 2)
2-68
TM 1-1520-238-10
Figure 2-38. Electrical Power Distribution System (Sheet 2 of 2)
2-69
TM 1-1520-238-10
Figure 2-39. Pilot Overhead Circuit Breaker Panels (Sheet 1 of 2)
2-70 Change 5
TM 1-1520-238-10
CENTER CIRCUIT BREAKER PANEL
CENTER CIRCUIT BREAKER PANEL (LASER DETECTING SET MODIFICATION)
Figure 2-39 Pilot Overhead Circuit Breaker Panels (Sheet 2 of 2)
Change 5 2-70.1/(2-70.2 blank)

TM 1-1520-238-10
CPG NO. 2 CIRCUIT BREAKER PANEL
CPG NO. 1 CIRCUIT BREAKER PANEL
M01-019
Figure 2-40. CPG Circuit Breaker Panels (Typical)
2-71
TM 1-1520-238-10
Section
2.48 AUXILIARY POWER UNIT (APU).
XII. AUXILIARY POWER UNIT
To prevent an accidental APU start,
the APU circuit breaker in the aft
avionics bay and the APU HOLD circuit
breaker on the pilot overhead
circuit breaker panel shall be out
when battery or external electrical
power is connected to the helicopter
and unqualified personnel are in or
around the pilot crew station.
The APU indirectly provides hydraulic, pneumatic, and
electrical power for the operation of helicopter systems
whenever the engines are not driving the main transmission
accessory section. The APU provides the means
of engine starting without the need for an aircraft
ground power unit (AGPU). It is located just inboard of
the right engine nacelle in the aft equipment bay. The
APU consists of a gearbox, a compressor, and a turbine
section, together with associated fuel, lubrication, and
electrical systems. The APU controller and the APU
control panel are installed separately from the APU.
The utility hydraulic accumulator, located on the deck
of the aft equipment bay below the APU, provides hydraulic
pressure to the APU hydraulic starter through
a solenoid-operated hydraulic start valve. The start
valve opens when the APU START switch is positioned
to START and closes automatically at 60% APU speed.
The utility hydraulic accumulator is discussed in more
detail in Section VI of this chapter.
2.48.1 Fuel System. The aft fuel cell provides fuel for
APU operation and is discussed in more detail in Section
IV of this chapter. The APU fuel control automatically
regulates fuel flow. The APU burns approximately
135 pounds of fuel per hour.
2.48.2 Lubrication System. The APU has a self-contained
oil system. An oil filler cap is located on the left
side of the unit. Oil cooling is provided by airflow over
cooling fins at the compressor inlet. The oil level sight
gage (fig 2-45) is located on the right side and is an integral
part of the oil sump. The sight gage can be inspected
through an opening just below the right engine
nacelle.
2.48.3 Electrical System. The APU electrical system
requires dc power which is normally delivered by the
helicopter battery when the APU control switch is set to
RUN. This switch will apply dc power to energize the
APU boost pump, open the APU fuel shutoff valve, and
at the same time, send a signal to open the utility accumulator
　
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