main spar cover. Both circuits are protected by a 5-
ampere circuit breaker mounted beneath the battery and
connected to the emergency battery bus. Both lights are
controlled by the switch mounted adjacent to the
threshold light. If the lights are illuminated, closing the
cabin door will automatically extinguish them.
Dome light. A dome light is installed in
the baggage area, in the overhead. The circuit is
protected by a 5-ampere circuit breaker mounted
beneath the battery and connected to the emergency
battery bus. Control is provided by a switch mounted
adjacent to the light.
Cabin utility light. Each mission operator's
position is provided with a utility light adjacent to each
cabin light. Each utility light is individually controlled by
a rheostat placarded OFF ON BRT on the back of the
light. There is a momentary ON switch in the center of
the rheostat. Each light is capable of producing a red or
white spotlight by turning the selector on the front of the
light. To remove the light from the stationary position,
loosen the retaining screw directly below the light
escutcheon and pull down on the light. The light is
connected to the light housing by an 11 inch coiled cord
that extends to approximately 50 inches.
Mission operator's position lights. Each
mission operator's position is illuminated by an
overhead flood. These lights are located adjacent to
each other between the middle and aft cabin lights.
They are positioned to illuminated each operator's
position. A rheostat switch placarded OFF BRT, located
adjacent to each light, is provided to turn the light on
and off, and control its intensity. The mission operator's
position lights are protected by a 5-ampere circuit
breaker, placarded CABIN LIGHTS, located on the
overhead circuit breaker panel (fig. 2-27).
Cabin door latching mechanism light. A
light is provided to check the cabin door latching
mechanism. It is controlled by a red pushbutton switch
located adjacent to the round observation window, which
is just above the second step.
2-77. EMERGENCY LIGHTING.
Description. An independent battery operated
lighting system is installed. The system is actuated
automatically by shock, such as a forced landing. It
provides adequate lighting inside and outside the
fuselage to permit the crew to read instruction placards
and locate exits. An inertia switch, when subjected to a
2 G shock, will illuminate interior lights in the cockpit,
forward and aft cabin areas, and exterior lights aft of the
emergency exit and aft of the cabin door. The battery
power source is automatically recharged by the aircraft
Operation. An emergency lights override
switch, located on the overhead control panel (fig. 212),
is provided to turn the system off, if it is accidentally
actuated. The switch is placarded EMERG LIGHTS
ORIDE -OFF RESET AUTO TEST. Should the system
illuminate. Placing the switch in the momentary OFF
RESET position will extinguish the lights. To test the
system, place the switch in the momentary position.
The lights should illuminate.
Moving the switch to the TEST OFF RESET position will
turn the system off and reset it.
If, while using the emergency
lights. the battery is run down, it
may become impossible to reset
(turn off) the lights.
Change 2 2-71