b.
In the air conditioning mode, air is circulated through the evaporator pallet where it is cooled and dried, and di-rected to the cabin through ducts. The major components of the air conditioning system are started in spaced intervals to prevent power surges, which results in a delay of up to 30 seconds between turning the system on and feeling cooler air at the vents. Load shedding (Table 2-2) protects the electrical system from overload when the air conditioning
is operated and the main generators are not supplying power.
b. In the ventilation mode, air is circulated through the evaporator pallet, and directed to the cabin through ducts. No heating, cooling, or drying occurs in the evaporator in this mode.
2.56.3 Normal Operation.
1. Heating Mode.
a.
Mode switch -HEAT. HEAT ON light will illuminate.
b.
COOLER g WARMER knob -Adjust to a comfortable temperature.
2. Air Conditioning Mode.
a.
Mode switch -AC. AC ON light will illu-minate.
b.
COOLER g WARMER knob -Adjust to a comfortable temperature.
2. Ventilation Mode.
a. Mode switch -VENT.
Table 2-2. Air Conditioning System Power Source Priority
POWER SOURCE AIR CONDITIONING SYSTEM OPERATION
APU GENERATOR (AIRCRAFT ON GROUND) vAIR CONDITIONING INTERRUPTED IF: (1) BACKUP PUMP IS ON. OR (2) WINDSHIELD ANTI-ICE IS ON. vWINDSHIELD ANTI-ICE INTERRUPTED WHEN BACKUP PUMP IS ON.
APU GENERATOR (AIRCRAFT IN FLIGHT) vAIR CONDITIONING INTERRUPTED WHILE AIRCRAFT IN AIR. vWINDSHIELD ANTI-ICE INTERRUPTED WHEN BACKUP PUMP IS ON.
DUAL MAIN GENERATOR (NO. 1 AND NO. 2) (AIRCRAFT IN FLIGHT OR ON GROUND) vAIR CONDITIONING, BACKUP PUMP, AND WINDSHIELD ANTI-ICE CAN OPERATE SIMULTANEOUSLY.
SINGLE GENERATOR OR EXTERNAL AC POWER (WEIGHT ON OR OFF WHEELS) vAIR CONDITIONING INTERRUPTED IF: (1) BACKUP PUMP IS ON.
ANY POWER SOURCE OR COMBINATION vECS POWER (AIR CONDITIONING AND HEATER) INTERRUPTED WHEN HOIST POWER IS ON.
Section XI ELECTRICAL POWER SUPPLY AND DISTRIBUTION SYSTEMS
2.57 ELECTRICAL POWER SYSTEMS.
Alternating current (ac) is the primary source of power. The primary electrical system consists of two independent systems, each capable of supplying the total helicopter power requirements. The prime source of each system is a 115/200 vac generator. A subsystem feeds two independent ac primary buses and an ac essential bus. A portion of each ac primary bus load is converted to 28 volts direct current (vdc) by two 200 ampere ac/dc converters. The 28 vdc is distributed by two independent dc primary buses and a dc essential bus. Emergency power is provided by a generator driven by the auxiliary power unit (APU). The APU gen-erator is capable of supplying all .ight-essential ac and dc bus loads. In addition, the APU generator can supply power to the blade deice system (when installed) if one main gen-erator should fail. Should a second generator fail, the blade deice load will be dropped and the APU generator will power the remaining ac bus loads. An electric power prior-ity feature allows either the No. 1 or No. 2 main generator to automatically supersede the APU generator, which, in turn, automatically supersedes external power. A 24-volt battery provides backup dc power when the #1 generator fails or is turned off.
2.58 DC POWER SUPPLY SYSTEM.
Primary dc power is obtained from two converters (transformer-recti.ers) with a battery as the secondary power source. There is no external dc power connector (Figure 2-17).
2.58.1 Converters. Two 200-ampere converters, each normally powered by the No. 1 and No. 2 ac primary buses respectively, turn ac power into dc power and reduce it to 28 volts. The converter output is applied to the No. 1 and No. 2 dc primary buses whenever ac power is applied to the ac primary buses. If one converter’s output is lost, the con-verter load will be transferred to the operating system, and a caution legend, marked #1 CONV or #2 CONV will go on. Power to light the caution legend is provided by the battery bus through a circuit breaker marked, AC CONV WARN.
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