MIL-DTL-6396F
TABLE IV. Test fluid temperature.
Test fluid
Temperature
Fuel
135 +10 °F (57 +6 °C)
Oil
275 +5 °F or 325 +5 °F (135 +3 °C or 163 +3 °C)
Water
Ambient
Water-alcohol
135 +10 °F (57 +6 °C)
4.5.6 Simultaneous slosh and vibration. (Mandatory for Types I and III, and Type II, Class C.)
4.5.6.1 Test conditions.
4.5.6.1.1 Vibrator and rocker assembly. These tests shall be conducted on a simultaneous
vibrator and rocker assembly acceptable to the procuring activity.
4.5.6.1.2 Vibration speed. Unless otherwise specified by the procuring activity, for testing a
tank intended for installation in an aircraft propelled entirely or partially by a reciprocating
engine(s), the rotational speed of the eccentric weights shall be 87 to 90 percent of the normal
rated crankshaft speed of the engine used. Unless otherwise specified by the procuring activity,
for testing all other aircraft tanks, the rotational speed of the eccentric weights shall be 1,940 to
2,000 revolutions per minute.
4.5.6.1.3 Vibration displacement. Unless otherwise specified by the procuring activity, the
throw of the eccentric weights on the vibration machine shall be adjusted to produce a total
displacement of 0.032 to 0.042 inch, measured at points of inherent rigidity on the tank (such as
points along the seams or near mounting points). Where the above frequencies and
displacements are not applicable, the tank shall be vibrated at a frequency and displacement
specified by the procuring activity.
4.5.6.1.4 Mounting axis. Unless otherwise specified by the procuring activity, the tank shall
be mounted in such a manner as to simulate pitching in the actual aircraft. Special fixtures, such
as baffles, may also be tested, if applicable, by mounting in another position for a portion of the
test time.
4.5.6.1.5 Slosh rocking angle. Unless otherwise specified by the procuring activity, the
slosh rocking angle shall be 30 degrees total, approximately 15 degrees on either side of the
horizontal position.
4.5.6.1.6 Type I tanks. The test tank, complete with all caps, vents, gages, fittings and other
parts or accessories that will be mounted on or in an aircraft, shall be mounted in the support jig
and installed on the vibrator and rocker assembly. In addition, all lines attached to the tank in the
actual aircraft installation shall be included. The minimum length of these lines shall be that
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