2.65.4 Position Lights. Position lights (Figure 2-1) are outboard of the left and right landing gear support and top tail pylon. The lights are red on the left, green on the right, and white on the tail. Control of the position lights is through the upper console panel containing two switches, marked POSITION LIGHTS, DIM, OFF, BRT, and STEADY, FLASH. When the intensity switch is placed to DIM or BRT, all three lights go on at once. If the STEADY-FLASH switch is placed to FLASH, the three lights will .ash. The STEADY position causes the lights to remain on continuously. Power to operate the position lights is provided by No. 2 dc primary bus through a circuit breaker, marked POS LTS. Infrared position lights are installed within close proximity of the standard position lights. NVG operation is selected through a toggle switch on the upper console (Figure 2-6) marked NAV LTS, with switch positions NORM and IR. Position lights are to be selected through a switch marked POSITION LIGHTS, DIM, OFF,or BRT, and mode of operation through a switch markedSTEADYor FLASH. Power for control of the IR lights is from the No. 2 dc primary bus through a circuit breaker marked IR LTS.
2.65.5 Formation Lights. These lights (Figure 2-1) are on top of the main pylon cowling, tail drive shaft cover, and horizontal stabilator. The system consists of four green electroluminescent lights. The lights are controlled by a single rotary selector switch, marked FORMATION LT, with marked positions OFF and 1 through 5. Position 5 is the brightest. When NVG operations are required, IR lights may be used to enhance viewing outside the helicopter. IR lights are selected through a toggle switch on the upper console (Figure 2-6) marked, NAV LTS, NORM, and IR. This switch shares operation with the IR position lights when operating in a NVG environment. Dimming of the IR lights is done with the FORMATION LT control, as used with the electroluminescent formation lights. Selection of position 1 through 4 causes the IR formation lights to illu-minate at the same intensity. Position 5 causes the lights to illuminate brighter. Power to operate the formation lights is provided from the No. 2 ac primary bus through two circuit breakers, marked LIGHTS, FORM LV and HV.
Section XIV FLIGHT INSTRUMENTS
2.66 PITOT-STATIC SYSTEM.
Two electrically-heated pitot tubes with static ports are aft and above the pilot’s and copilot’s cockpit doors. The right pitot tube is connected to the pilot’s instruments and the left pitot tube is connected to the copilot’s instruments. Tubing connects the pitot tube static pressure ports to the airspeed indicators and the altimeters. In addition to stan-dard instrumentation, airspeed data is sensed for operation of stabilator, .ight path stabilization, and command instru-ment system. Refer to Section IX for pitot tube heater sys-tem.
2.67 ATTITUDE INDICATING SYSTEM.
Helicopter pitch and roll attitudes are sensed by the pi-lot’s and copilot’s vertical displacement gyroscopes, that apply attitude signals to the vertical situation indicators (VSI) for visual display (Figure 2-8). Signals are applied through the VERT GYRO select switches to the remote indicator on the vertical situation indicators. Helicopter pitch and roll attitudes are shown on the pilot’s and copi-lot’s vertical situation indicators. The indicator face con-tains a .xed bar, representing the helicopter, a movable sphere with a white horizon line dividing the two colors, white above and black below, a .xed bank angle scale and a bank index on the moving sphere. Relative position of the .xed bar (helicopter) and the horizon line indicates the he-licopter’s attitude referenced to the earth horizon. A ROLL trim knob on the lower left of the VSI permits adjustment of the roll index about 14°66° right and left from zero. A PITCH trim knob on the lower right of the VSI permits adjustment of the indicator sphere 14°66° for dive and 7°63° for climb from zero index. If a power failure or unbalance occurs in the pilot’s or copilot’s vertical dis-placement gyroscope, a gyroscope power failure .ag will appear, indicating ATT, warning the pilot or copilot that pitch and roll attitude signals are not being sent to his in-dicator. To restore attitude information to the indicator, the pilot or copilot should press his VERT GYRO select switch on the MODE SEL panel so that ALTR appears in the switch window. This causes the ATT .ag on the indi-cator to disappear, and pitch and roll signals are supplied from the operating gyro, restoring attitude information dis-play. Refer to Chapter 3 for description of VERT GYRO select switch.
　
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