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the LIGHTING EMER EXIT circuit breaker on the No.1 PDP.
2-13-27. EMER EXIT Switch.
CAUTION
If the EMER EXIT switch is left in ARM or
DISARM with the helicopter shutdown and
the battery connected, the charging circuit
of the emergency exit light system will
discharge the helicopter battery.
Prior to turning the BATT switch OFF, place the EMERG
EXIT switch to DISARM then set to TEST. The EMER EXIT
switch is located on the INTR LTG panel of the overhead
switch panel (fig. 2-13-2). The three-position switch is
labeled DISARM, TEST, and ARM. When the switch is
placed to ARM, the emergency exit lights stay off, the
batteries are charging, and the charge indicator lights come
TM 1-1520-240-10
2-13-7
on. The circuit monitors electrical failures and landings in
excess of 3 to 4g’s. The light from the charge indicator
lamps can be seen emitting through two pin holes at the
base of the main light reflector. When the switch is set
from ARM to TEST, the main light comes on, powered by
the batteries. When the switch is set to DISARM, the
indications are the same as for the ARM position, except
the circuit does not monitor electrical or failures hard
landing.
Figure 2-13-3. Emergency Exit Light
TM 1-1520-240-10
2-13-8
Figure 2-13-4. Cabin Lighting and Controls
TM 1-1520-240-10
2-13-9/(2-13-10 blank)
2-13-28. Forward Transmission Oil Level Check
Lights.
The forward transmission floodlight provides light to
check the oil level of the transmission. The floodlight is
near the sight gage on the transmission. Power to operate
and control the oil level check light is supplied by the
switched battery bus through the LIGHTING OIL LEVEL
CHECK circuit breaker on the No. 1 PDP.
2-13-29. Oil Level Check Light Switch.
The OIL LEVEL CHECK LT SW is inside the cockpit on
the canted bulkhead at sta. 95 above the pilot seat. it is
a two-position switch labeled ON and OFF. When placed
to ON, the oil check light turns on by the forward transmission.
2-13-30. Cargo Hook Lights.
Three NVG compatible lights are mounted on the bottom
of the fuselage at stations 244, 313, and 404. These
lights are directed towards the forward, center, and aft
cargo hooks and provide lighting during night external
load operations. The lights are controlled by the cargo
hook lighting panel switches marked FWD, CTR, and
AFT located in the center hook cargo by at station 360
(fig. 2-13-4). The two position switches (ON and OFF)
receive power from the NO. 1 DC bus through the LIGHTING
CARGO HOOK circuit breaker located on the NO. 1
power distribution panel.

TM 1-1520-240-10
Change 3 2-14-1
SECTION XIV. FLIGHT INSTRUMENTS
2-14-1. General.
The following paragraphs contain information on the
flight instruments. Information on the navigation instruments
will be found in Chapter 3, Avionics. All other instruments
directly related to one of the helicopter systems
are found under the appropriate system heading in
this chapter. Refer to fig. 2-1-5 thru 2-1-14 for illustrations
of the instrument panels, canted and center consoles,
and overhead switch panel.
2-14-2. Cruise Guide indicator System.
The cruise guide indicator (CGI) system gives the pilot a
visual indication of actual loads imposed on critical components
of the helicopter dynamic system. The system
allows the pilot to achieve maximum helicopter utilization
under various conditions of payload, altitude, airspeed,
ambient temperature, and center-of-gravity. The system
consists of strain gages bonded to fixed links in the forward
and aft rotor controls, an indicator, a signal processor
unit in the aft pylon, a signal conditioner unit in the
forward pylon, and interconnecting wiring. The system
measures alternating stress loads at each rotor and displays
the larger of the two signals. Power to operate the
cruise guide indicator system is supplied by No. 2 DC bus
through the CRUISE GUIDE circuit breaker on the No. 2
PDP.
2-14-3. CRUISE GUIDE Indicator.
The CRUISE GUIDE indicator is on the pilot instrument
panel (fig. 2-14-1). Three bands are colored green, yellow,
and striped red-and-yellow. Refer to figure 5-2-1 for
limitations. Immediate corrective action must be taken to
reduce stress when in the red-and-yellow striped band.
This can be accomplished by lowering THRUST CONT
lever, reducing airspeed, releasing back pressure on the
cyclic stick, or by reducing the severity of the maneuver.
2-14-4. CGI TEST Switch.
The CGI TEST switch is on the pilot instrument panel, on
the left side of the indicator (fig. 2-14-1). It is a three-position
　
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