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|  MIL-T-6396E
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d. -l5 F (-26 C) soak: The tank shall then be filled with the applicable test
fluid specified in0 4.5.1, containing a satisfactory staining agent, cooled to a
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temperature of -15 F + 5 F (-26 C + 3C), and allowed to remain at this
temperature for a minimum period of 3 days. The outside layer of water-alcohol
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shall have reached -15 F (-26 C) prior to start of the 3-day period.
e. Examination: The tank shall then be drained and examined externally and
internally for any unsatisfactory conditions or indications of fluid leakage.
4.6.23 Stand test (phase II). Upon completion of the low temperature leakage
test (4.6.22) for type II tanks, the cavity shall be completely lined with
brown paper. For type III tanks, the tanks shall be prepared as specified by
the acquisition activity for the detection of leakage. The tank shall be
emptied and refilled with the applicable test fluid, as specified in 4.5.1,
containing a satisfactory staining agent. The tank shall be allowed to stand
at ambient temperature for a period of 30 days at which time the tank shall be
drained and examined for any unsatisfactory condition or indication of fluid
leakage. All joints, seams, and fittings shall be covered with brown paper to
aid in determining leakage. An alternate method of detecting leakage during
this test is acceptable, if approved by the acquisition activity.
Only type II, class B tanks which exceed 150
4.6.24 Gunfire (phase II).
gallons in capacity shall undergo the phase II gunfire test. For this test,
the tank shall be mounted in the actual structure for which it is designed.
The tank shall then be filled three-fourths-full with water. The number of
rounds of .50 caliber AP ammunition to be fired will be determined on the basis
of one round for each 30 gallons of tank capacity up to a maximum of 6 rounds.
In addition to the .50 caliber gunfire, one round of 20 mm AP shall be fired.
All shots shall be so placed as to be compatible with the aircraft installation
and the combat ability of the aircraft. No bursts shall be fired and the test
shall be conducted at ambient temperatures. This test shall produce no larger
than a 4-inch-diameter tear for each entry and exit. There shall be no tears
which do not radiate from a bullet hole which cannot be accounted for by
shrapnel or structure.
4.6.25 Accelerated loads test. The tank assembly, consisting of the tank and
tank structure shall be mounted in a support jig that provides support
equivalent to the aircraft structure for which it is designed and subjected to
the applicable dynamic load tests specified herein to simulate the aircraft
design accelerations including the. appropriate magnification factors. The tank
shall be tested at fill levels of 25, 50, 75, and 100 percent of the rated
capacity. anks of pressurized systems shall be subjected to the normal
operating pressures for the condition being tested, except where unpressurized
conditions are considered more critical. Deflections on various parts of the
tank structure including the areas surrounding components within the cell shall
be measured during the test.
4.6.25.1 Accelerated loads test to desire limit load. The tank assembly shall
be subjected to 100 percent design limit accelerations at the four fill levels
and pressurized conditions to determine the most critical condition. Then the
tank shall be subjected to 100 load applications at this critical condition
applicable to Navy Aircraft only. For Air Force and Army aircraft one
application at each fill level is required. There shall be no evidence of
failure, leakage or chaffing of the cell or components. Further, the
deflection of the cell shall be such that there will be no contact with the
tank or aircraft components.
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