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NORM  Provides a signal path normal operation.  for 
SYNC 1  Provides a signal to the con-troller to verify operation of synchronization check cir-cuitry when POWER switch is at TEST. 
SYNC 2  Provides an open circuit to the controller to verify opera-tion of synchronization check circuitry when POWER switch is at TEST. 
OAT  Short circuits the OAT sensor to check BITE circuit sensing a fault when POWER switch is at TEST. 
EOT  Disables BITE circuits in controller and OAT sensor to simulate a malfunctioning primary EOT timing circuit when POWER switch is ON and MODE select switch is at M (moderate). 
PWR MAIN RTR light  Indicates a malfunction has occurred in the main rotor primary power. 

CONTROL/  FUNCTION 
INDICATOR 
PWR TAIL RTR light  Indicates  a  malfunction has 
occurred in the tail rotor pri-
mary power. 

2.51 BLACKOUT CURTAINS.
Curtains are provided to cover the cabin windows and the opening between the pilot’s compartment and the cabin. Velcro tape is bonded to the cabin structure and the curtains with an adhesive. Loops are attached to the curtains to aid removal.
2.512.52 WIRE STRIKE PROTECTION SYSTEM.
On helicopters equipped with wire strike protection pro-visions, the system (Figure 2-1) is a simple, lightweight, positive system with no motorized or pyrotechnic compo-nents used to cut, break, or de.ect wires that may strike the helicopter in the frontal area between the tires and fuselage, and between the fuselage and main rotor in level .ight. The system consists of nine cutters/de.ectors located on the fuselage and landing gear/support. They are: upper cutter on the rear of the sliding fairing, the pitot cutter/de.ector on the front of the sliding fairing, windshield post and wiper de.ectors, door hinge de.ector, step extension and step de.ector, landing gear joint de.ector, main landing gear cutter/de.ector, and tail landing gear de.ector.
2.53 DATA COMPARTMENTS.
Data Compartments are on each cockpit door (Figure 2-4).

Section X HEATING, VENTILATING, COOLING,
AND ENVIRONMENTAL CONTROL UNIT

2.54 HEATING SYSTEM.
The subsystem consists of a heated air source, cold air source, mixing unit, temperature sensing unit, overtempera-ture sensor, controls, ducting and registers. The heating system is a bleed-air system and bleed-air supplied in .ight by the main engines, and on the ground by the main engines or the APU. An external connector allows connection of an external ground source in to the pneumatic system, that can provide heat when connected. Power to operate electrical components of the heating system is by the No. 1 dc pri-mary bus through a circuit breaker, marked AIR SOURCE HEAT/START.
2.54.1 Heat and Ventilation Controls. A variable control air mixing valve assembly is used to control the temperature of air for cabin heating in the helicopter. Bleed-air from the engine, APU, or external source is mixed with ambient air to obtain the desired temperature deter-mined by the setting of the sensor in the downstream air .ow. Regulation of the diaphragm position is by a solenoid. Should the HEATER control switch (Figure 2-6) be turned OFF, or dc power fail, bleed-air will shut off. The valve also has a thermal protective switch that deenergizes the solenoid if mixed air temperature is over 90° to 96°C (194° to 205°F). The mixture temperature sensor downstream of the mixing valve regulates .ow output temperature. The sensor is regulated from the cockpit through a control link-age at the overhead console. The temperature control is marked HEATER OFF, MED, and HI. Ventilation is con-trolled through a panel on the upper console marked VENT BLOWER. When the switch is placed ON, dc power to the solenoid allows bleed-air to mix with outside air.
2.54.2 Normal Operation.
1.
APU or engine -Start .
　
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