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CABIN HTR circuit breaker (fig. 2-8) installed in the and bleed air to obtain the desired air temperature.
center post console. Operation is as follows:
NOTE
(1) HTR switch HTR.
Noise from an operating heater will degrade
radio and intercom communication and the (2) HEAT control knob Adjust as desired.
2-41
TM 1-1520-248-10
Figure 2-19. Main Rotor System (Typical)
2-42
TM 1-1520-248-10
2-62. VENTILATION SYSTEM. equipment. A three-position COMPT BLWR switch (fig.
2-8) permits the system to be OFF, manually operated
The ventilation system is an integral part of the heating in the ON position, and automatically operated by
and defogging system. VENT PULL control knobs (fig. temperature sensors when in the AUTO position. The
2-6 and 2-7) open and close the fresh air inlets. Pulling temperature sensors automatically turn on the cooling
the control knob out opens the fresh air inlet. The blower whenever the equipment compartment
defogging/defrosting system blowers (para. 2-58) may temperature reaches 100 °F (38 °C). The avionics
be turned on to provide a larger volume of air directed cooling blower can also be utilized to rapidly remove
to the windshield and forward cabin area. smoke and other contaminants from the cabin by
pulling air from the crew and equipment compartments
2-63. EQUIPMENT COOLING. and exhausting the air overboard through the aft equipment bay.
An avionics cooling blower (fig. 2-20) is provided to
cool the electronic/avionics equipment. The blower has
the capacity to adequately cool the electronic/avionics
SECTION XI. ELECTRICAL POWER SUPPLY AND
DISTRIBUTION SYSTEMS
2-64. ELECTRICAL POWER SUPPLY AND producer turbine (Ng). An additional DC bus, power
DISTRIBUTION SYSTEM (FIG. 2-21). assured, is powered from the battery emergency bus.
c. Backup Systems. Backup systems for both DC
WARNING and AC primary power systems are provided. These
backup systems ensure that no single electrical failure
will cause the loss of any system essential to flight.
• (CDS2) Weapons can be inadvertently Automatic switching from primary power to backup is
fired while the aircraft is on the ground provided. Backup power is provided by the starterif
the MASTER switch is in the ARMED generator. In the event the AC generator fails, the
position, electrical power is applied to starter-generator input to an inverter will supply AC
the aircraft and either the Integrated power. A starter-generator failure results in the TRU
System Processor (ISP) has failed or assuming the full load imposed by the DC essential
the ISP circuit breaker is pulled. bus, battery emergency bus, and power assured bus
except for battery charging. In the event of an AC
• Weapons can be inadvertently fired generator failure, the inverter will assume the loads on
while the aircraft is on the ground if the 115 Vac essential bus.
the MASTER switch is in the ARMED
position, electrical power is applied to d. Starting. Electrical power for starting and
the aircraft and either the R MCPU has emergency power supply is provided by a single 24
failed or the R MCPU circuit breaker is volt, 17 ampere battery. This battery is located in the
pulled. nose of the helicopter (fig. 2-1) and is controlled by the
BATT 1 switch in the overhead console. Complete
a. Primary AC Power. Primary AC electrical power provisions are included for the installation of a second
for the helicopter systems is provided by a 120/208 battery. When installed, the second battery is located in
Vac, three-phase, 400 Hz, air cooled AC generator. the aft electrical compartment and controlled through
This generator is driven by the engine power turbine the BATT 2 switch in the overhead console (fig. 2-8). At
(Np) from an engine accessory drive pad. ambient temperatures of +5 °F (-15 °C) or less both
batteries are in parallel at the initiation of a start and
b. Primary DC Power. Primary DC electrical power switch to series when the MCPU signals a transfer
for the helicopter systems is provided by two sources. based on engine Ng. Battery heating at temperatures
The DC essential bus is powered from a 28 volt, 200 below −17° (2 °F) is accomplished by momentarily
ampere transformer rectifier unit (TRU) and the battery positioning the BATT switch, for the battery to be
emergency bus is powered by a 28 volt, 200 ampere heated, to the PREHEAT position and releasing. A
starter-generator. The TRU is located in the aft HEAT ON light, located in the floodlight bracket to the
electrical compartment and the starter-generator is right of the overhead console, will illuminate while the
located on the engine and driven by the engine gas battery is heating. The heating cycle will require 3 to 4
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TECHNICAL MANUAL OPERATOR’S MANUAL FOR ARMY OH-58D HELICOPT(24)
