MIL-C-5778D
3.4.4 Slits. Slits shall be provided for obstructions such as struts, stay
wires, shafts, or other aircraft parts. Silts shall extend to the nearest free edge,
unless another position is specified. Unless otherwise specified, the edges of each
slit shall be closed by means of an Interlocking fastener installed as shown on
figure 2. Means for attaching and securing covers shall be accomplished by means of
ties, straps, ropes or fasteners on the edge to permit fastening them around
fuselage, wings, or some adjacent fittings. The hardware or fittings used for
securing the cover shall be padded and the padding permanently attached, by sewing
around the periphery, to prevent contact with the aircraft skin.
3.4.5 Patches. The covers shall be provided with reinforcement patches where
they come in contact with sharp corners or projections.
l 3.4.6 Engine or transmission covers.
The engine or transmission cover shall
extend beyond the fire wall and the propeller or rotor hub. Typical designs are
shown on figures 3 through 7.
- 3.4.6.1 Fasteners. Engine covers around the nacelles shall be closed with
interlocking fasteners as specified herein. The interlocking fastener shall be
offset 5° ± 10 from the vertical centerline of the engine.
3.4.6.2. Sleeves for hot air duct.
Two sleeves, each approximately 8 inches long
and 13 inches in diameter, shall be attached to each engine cover to serve as a hot
air duct when the free end of the sleeve is attached to a heater. One sleeve shall
be so located as to coincide with the opening into the accessories compartment of the
The other sleeve shall be located at the nose section of the cowling. A
engine.
piece of type I lightweight webbing conforming to MIL-W-5665, approximately 52 inches
long and 1/2 inch wide, shall be sewn at the midpoint to each sleeve near its open
The color of the webbing shall approximately match the color of the cover.
end
* 3.4.6.3 Sleeve for propeller or rotor blades.
A sleeve approximately 10 inches
long and of sufficient diameter to-fit the proeller or rotor blade shall be attached
to the engine or transmission cover for each propeller blade or rotor.
3.4.6.4 Grommets. Plain grommets conforming to MS20230 shall be placed on the
underside of the cover to permit excess oil drainage
3.4.7 Propeller and rotor blade covers. The propeller and rotor blade covers
shall match the respective engine cover propeller sleeves or rotor head cover blade
sleeves.
A typical design is shown on figure 8.
3.4.8 Fuselage and armament covers. These covers shall be for the bombardier and
pilot compartments, turrets, sight blisters, and all other gun openings.
3.4.9 Miscellaneous covers. Covers for ventilation duct openings, tail and nose
wheel openings, landing gear wells, and any opening too large to be covered with
2-inch masking tape shall be provided, unless justification by the weapon system
manfacturer can be substantiated that covers are not required.
3.4.10 Snap Fasteners (type II). Junctions between cover components, shall be
secured with snap fasteners as shown on figure 9.
3.4.11 Fasting
tapes Fastening tapes conforming to MIL-F-21840, type II, may
be used for fastening or securing flaps, pockets, folds, et cetera, when required,
The tapes shall be of the size and class to match the fabric material being used in
the protective cover.
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