MIL-DTL-5578D
applied to the sample tank and held for a minimum of 2 minutes. Any evidence of permanent
set, distortion, or failure of any kind is cause for rejection. Water may be used for this test.
4.5.8.2 Burst pressure. All air shall be bled from the tank and the necessary ports plugged.
Hydrostatic pressure shall then be applied to the tank. This pressure shall be at least 2.0 times
the maximum operating pressure. Evidence of permanent set or distortion is permitted, but any
evidence of rupture is cause for rejection. Water may be used for this test.
4.5.9 Slosh or slosh and vibration resistance. Slosh and vibration tests shall be conducted as
follows:
4.5.9.1 Vibrator and rocker assembly. These tests shall be conducted on a simultaneous
vibrator and rocker assembly acceptable to the procuring activity.
4.5.9.2 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.
4.5.9.3 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.
4.5.9.4 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.
4.5.9.5 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.
4.5.9.6 Type I tanks (reciprocating engines). 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 length in the actual aircraft installation from the tank to the first
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