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|  MIL-T-18847C(AS)
3.5.1 .4.1 Tank center of gravity. The center of gravity location and
travel with varying quantities of fuel within the tank shall be such that
there shall be no adverse effects on the aircraft structure or aerodynamic
characteristics that depend on center of gravity location at all attitudes of
the aircraft that are otherwise allowable.
3.5.1.5 Fuel tank design loads.
3.5.1 .5.1 Rotary wing crashworthiness application. The tank must be able
to withstand survivable or marginally survivable crash areas (see Figure 1)
without leakage. The tank shall be in any fuel condition from empty to full.
3.5.1 .5.2 Strength. Strength shall be provided in the tank and suspension
for the loads in accordance with MIL-A-8591 at the following weights:
a. Flight conditions: tank 3/4 full and tank empty
b. Catapulting conditions: tank full
c. Landing conditions: tank 1/4 full
The critical combination to be used for design shall be selected by the
contractor and approved by the Naval Air Systems Command.
3.5.1. 5.3 Tank ejection load. The tank shall be capable of withstanding
the ejection loads without rupture In accordance with MIL-A-8591.
3.5.1. 5.4 Cradling and handling areas. As a minimum, all tanks shall have
cradling and handling areas capable of withstanding loads equal to three times
the weight of the tank without permanent deformation.
3.5.1.6 Suspension. Tanks shall be provided with means of suspending the
tank from the applicable aircraft. The location of the suspension system
shall be in accordance with MIL-A-8591. The suspension lugs shall be
removable.
3.5.1 .6.1 Sway brace area. The bomb rack sway brace pad areas shall be
provided in accordance with MIL-A-8591.
3.5.1.7 Ejection area.
The ejection area shall conform to the requirements
of MIL-A-8591.
3.5.1.8 Pressures.
The tank shall withstand
the following pressures.
3.5.1 .8.1 Internal pressure.
The internal pressure loads are as follows:
Operating:
15 psig
Proof:
75 psig
Burst:
112 psig
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