MIL-DTL-6484D
3.11 Dimensions. The light assemblies shall not be larger than the dimensions specified on the applicable
specification sheet or MS drawing.
3.12 Weight. The weight of the light assemblies shall not exceed the value specified on the applicable
specification sheet or MS drawing.
3.13 Color. The color of the housing shall be dull black.
3.14 Finishes and protective coatings.
3.14.1 Aluminum-alloy parts. Aluminum-alloy parts shall be covered with an anodic film conforming to MIL-
A-8625, except as follows:
3.14.1.1 Small holes and case inserts need not be anodized.
3.14.1.2 Aluminum alloys which do not anodize satisfactorily shall be coated with a chemical film in
accordance with MIL-DTL-5541.
3.14.1.3 Where the primary purpose of the treatment is to afford a suitable paint base, chemical treatments in
accordance with MIL-DTL- 5541 may be used in lieu of anodizing.
3.14.1.4 Castings containing non-aluminum-alloy integral inserts may be treated with a chemical film in
accordance with MIL-DTL-5541.
3.14.1.5 When abrasion resistance is a factor, chemical films in accordance with MIL-DTL-5541 shall not be
used in lieu of anodizing.
3.15 Identification of product. Each cockpit utility light assembly shall be marked for identification in
accordance with MIL-STD-130. The nameplate shall contain the following information:
LIGHT, COCKPIT UTILITY, AIRCRAFT
MS Part No. (without base)
MIL-DTL-6484D
National Stock Number (without base)
Manufacturer's name or trademark
Contract or Order No.
U.S.
3.16 Workmanship. Each light assembly, including all parts and accessories, shall be fabricated and finished in
accordance with stand engineering practices.
4. VERIFICATION
4.1 Classification of inspections. The inspections specified herein are classified as follows:
a. Qualification inspection (4.3)
b. Conformance inspection (4.4)
4.2 Test conditions.
4.2.1 Standard atmospheric conditions. Whenever the pressure and temperature at the time of testing are not
definitely specified in the applicable specification sheet or MS drawing, it is to be understood that the test shall be made
at atmospheric pressure (approximately 29.92 inches Hg) and at room temperature(approximately 25ºC). When tests are
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