MIL-DTL-6396F
3.5 Design.
3.5.1 General. Tanks shall be compatible with the fuel for which they are intended and shall
perform in conjunction with the containing structure to avoid load concentration on splices,
seams, fittings, or concentrated flexure locations. The tank assembly and aircraft structure in
which it is mounted shall possess the necessary strength to provide for the stresses caused by the
following:
a. Flexing resulting from vibration.
b. Impact loads incident to take-off, taxiing, and landing (including catapulting and
arresting).
c. Positive and negative pressures associated with fluid surge incident to all
dynamic conditions of flight, including catapult and arrested landing, if applicable.
d. Pressure loads imposed by:
1. Hydrostatic head of fluids during level flight or maneuvers.
2. Pressurizing or inerting gases.
3. Proof and ultimate pressures as designated by the procuring activity.
4. Fluid surge incident to gunfire, where type II, class B, tank constructions are used.
e. Handling loads associated with removal, transportation and installation.
3.5.2 Capacity. The capacity of the tank(s) shall be such that the aircraft is capable of
completing the requirements as specified by the procuring activity. The capacity of types I and
III cells shall be within 1.5 percent of the total volume of the average capacity of the first 10
production cells manufactured after design approval of the cells. For cells in production, the fuel
level versus volume curve shall be within 1.5 percent of the calibrated fuel level versus volume
curve.
3.5.3 Weight. Emphasis shall be placed on creating the lowest weight cell that will meet the
requirements of this specification. The weight of production cells shall be within the following
percentages of the average weight of the first 10 production cells manufactured after design
approval of the cell:
a. Type I cells:
± 2 percent
b. Types II and III cells:
± 5 percent
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