MIL-DTL-5578D
support. (For testing of tanks which incorporate reticulated foam or similar materials, see
4.5.9.8.) The test specimen shall be filled two-thirds full with water and simultaneously slosh
and vibration tested in accordance with applicable conditions specified in 4.5.9.1 through 4.5.9.5
and 4.5.9.8. The temperature of the test fluid shall be as specified in table II. This test shall be
conducted with the test specimen subjected to a pressure equivalent to the maximum operating
pressure encountered in any prescribed flight conditions. At the conclusion of this test, the test
specimen shall be filled with the applicable test fluid and thoroughly inspected for leakage or
other evidence of failure such as sagged panels or buckled plates which is cause for rejection.
TABLE II. 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)
4.5.9.7 Type II tanks (jet 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 support.
The interior of each compartment shall be completely lined with brown paper and held in place
with a suitable adhesive. (For testing the tanks which incorporate reticulated foam or similar
materials, see 4.5.9.8.) The test specimen shall be filled two-thirds full with the applicable test
fluid containing a suitable dye. The tank shall be simultaneously slosh and vibration tested in
accordance with the applicable conditions specified in 4.5.9.1 through 4.5.9.5 and 4.5.9.8. The
temperature of the test fluid shall be 135 +10 °F (57 +6 °C). This test shall be conducted with
the test specimen subjected to a pressure equivalent to the maximum operating pressure
encountered in any prescribed flight conditions. At the conclusion of this test, the test specimen
shall be filled with the applicable test fluid as specified in ASTM-D471 Ref Fuel A or B and
thoroughly inspected for leakage or other evidence of failure.
4.5.9.8 Special baffling materials. Tanks incorporating reticulated foam or similar materials
for fire and explosion protection shall have the material removed during the slosh, vibration or
slosh and vibration tests described herein. If deemed necessary by the procuring activity, a
second slosh test with the foam installed shall be conducted.
4.5.10 Test duration. Unless otherwise specified by the procuring activity, test duration and
procedure shall be:
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