MIL-DTL-6484D
3.7.1 Environmental. The cockpit light assemblies shall be capable of operating under the following
environmental conditions:
a.
A temperature range of -54º to +71ºC.
b.
Exposure to atmosphere containing salt-laden moisture.
c.
Exposure to airborne sand and dust particles encountered in normal and desert operation.
d.
A relative humidity of 95 percent at a temperature of 49ºC.
e.
Vibration incident to use on aircraft.
f.
Rough handling incident to storage and use on aircraft.
3.7.1.1 Low-temperature storage. The light assemblies shall withstand storage at a low temperature of -62ºC.
3.8 Details of components. The components of cockpit light assemblies shall be as stated in the following
paragraphs, unless otherwise stated in the applicable specification sheet or MS drawing.
3.8.1 Housing assembly. The housing assembly shall consist of the outer case, rheostat, lamp socket,
momentary switch, mounting provisions, and means for selecting either red or white color spot or flood or either red
or white color flood only as specified in the applicable specification sheet or MS drawing.
3.8.1.1 Housing. The lamp and lamp focusing mechanism, the color filter and filter selector mechanism, and
the momentary switch and the light intensity rheostat shall be mounted in non-corrosive or corrosive resistant metal or
impact resistant plastic housing.
3.8.2 Focusing device. If required in the applicable specification sheet or MS drawing, a means shall be
provided so that the light emitted may be adjusted to a small spot or to a wide flood of light as selected by the
operator. The focusing device shall be so designed that it will not get out of adjustment and so that the lens and lens
housing will not become detached from the light assembly by the vibration normally encountered in aircraft.
3.8.3 Rheostat. If required in the applicable specification sheet or MS drawing, a rheostat control with an
"off " position shall be installed in the housing and connected into the lamp circuit to control the light output. The
rheostat shall have a maximum resistance of 200 to 250 ohms, unless otherwise specified in the applicable
specification sheet or MS drawing, and shall be of sufficient size to handle the current required for the lamp specified.
Rotation of the rheostat in a clockwise rotation from the detented "off " position shall increase the lamp intensity until
it reaches the mechanical stop position. The rheostat knob shall be of a serrated or indented configuration and large
enough for ease of operation. The rheostat shall be connected in such a manner that the protective shell around the
rheostat, if metal, is in the ground side of the circuit. The rheostat shall have mechanical stops to prevent damage to
the control portion of the unit. Optional locations for the rheostat are at the rear of the light or on the side of light
adjacent to the mounting and to the rear of the mounting.
3.8.4 Lamp socket. The cockpit light assembly shall be designed with a lamp socket to accommodate a lamp
as specified in the applicable specification sheet or MS drawing.
3.8.5 Filter assembly. If required in the applicable specification sheet or MS drawing, a filter assembly
consisting of a filter of plastic or glass and suitable mechanism for color selection shall be securely fastened within
the cockpit light assembly. The filter assembly shall be an integral part of the light, and so designed as to be readily
adjusted to emit white light or colored light in accordance with SAE-AS25050. A positive lock of a type to prevent
accidental change from colored light to white light or white light to colored light shall be provided. The filter shall be
identification red unless otherwise specified in the applicable specification sheet or MS drawing.
3.8.6 Switch. If required in the applicable specification sheet or MS drawing, a spring-loaded momentary "on"
switch shall be provided at the rear of the cockpit light assembly. The switch shall be so connected that when it is
closed, the lamp will be energized with the rheostat cut out of the circuit.
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