 |
|||
|
|
|||
| ||||||||||
|
|  MIL-T-6396E
pressure on the bottom of the tank which is mutually satisfactory to both the
tank and the airframe manufactueres. Alternate leakage tests acceptable to the
acquisition activity may also be used.
Type II tanks selected in accordance with
4.6.2 Stand test (sampling).
4.4.2.2 shall be collapsed and held strapped for 30 minutes in a position
comparable to that required for installation in its respective aircraft cavity.
Then the tank shall be adequately supported and filled with the applicable test
fluid as specified in 4.5.1 and stand tested for 15 days. A brown paper liner
in the cavity and a staining agent in the test fluid shall be used for leak
detection. A stand pipe shall be used to insure that all internal surfaces are
in contact with fuel. Upon completion of the tests the tank shall be examined
for evidence of leakage or other failure.
The sectioned portion of each tank selected as
4.6.3 Dissection test.
specified in 4.4.2.3 shall be examined for conditions outlined in MIL-STD-801.
4.6.4 Capacity. The capacity of the finished tank shall be checked to
determine compliance with 3.5.2.
4.6.5 Aging
4.6.5.1 Oil tank, normal system (275F)(135C). For this test, the tank
shall be filled to its normal level with the applicable oil specified in
4.5.l.b, and shall stand at 275F (135C) for 200 hours. At the end of this
period, the tank shall show no signs of deterioration or other unsatisfactory
condition as a result of the test.
O
4.6.5.2 Oil tank, hot oil system (375oF) (l63 C). For this test, the
tank shall be filled to its normal level with the applicable oil specified in
0
4.5.l.b, and shall stand at 325F (163 C) for 200 hours. At the end of this
period, the tank shall show no signs of deterioration or other unsatisfactory
condition as a result of the test.
4.6.6 simultaneous slosh and vibration
4.6.6.1 Test conditions
4.6.6.1.1 Vibrator and rocker assembly. These tests shall be conducted on a
vibrator and rocker assembly of a design acceptable to the acquisition
activity
For testing a tank intended for installation in an
4.6.6.1.2 Vibration speed
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. For testing all other
aircraft tanks, the rotational speed of the eccentric weights shall be 1940 to
2000 revolutions per minute.
4.6.6.1.3 Vibration displacement. 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).
4.6.6.1.4 Alternate vibration frequency and displacement. Where the above
frequencies and displacements are not applicable, the tank shall be vibrated at
a frequency and displacement specified by the contractor or acquisition
activity.
15
|
|
Privacy Statement - Press Release - Copyright Information. - Contact Us |
Click
here for thousands of PDF manuals