MIL-STD-209 Lifting And Tiedown ProvisionsThis standard establishes dimensional limits, design considerations, positioning requirements, and strength requirements for lifting to include helicopter sling load HSL and tiedown provisions for lifting or tying down tanks and other tracked vehicles, tactical wheeled vehicles, helicopters, and other military equipment shipped assembled or disassembled in unboxed or uncrated condition, and for restraining cargo or accessories to such equipment. The lifting and tiedown requirements in this standard are necessary to permit compatibility between military equipment and the transportation systems used for deployments.

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MIL-STD-209K

5.5.3.1  Ultimate design load.

The ultimate load each large cargo tiedown provision can withstand shall not be less than 1.5 times the design limit load determined in paragraph 5.5.3.

5.5.3.2  Transport on Navy/Marine Corps aircraft.

Internal transport on Navy/Marine Corps aircraft require restraint above that

required for other modes of transport.  See appendix D for further guidance in designing for restraint aboard these transportation assets.

5.5.4    Provision dimensions.

Largo cargo tiedown provisions shall meet the dimensional requirements of Figure

3.  If two large cargo tiedown provisions are in each row (front, rear, and center (if required), then use the maximum payload capability of the cargo area as the "Gross Weight of the Equipment."  If four large cargo tiedown provisions are in each row, then use half the maximum payload capability of the cargo area as the "Gross Weight of the Equipment."

5.5.5  Testing.

Testing shall meet the following requirements:

a.  A static independent pull to the required design limit load shall be conducted on all tiedown provisions; however, all provisions do not have to be tested at the same time.

b.  Loads applied to each provision shall be measured with an appropriate measuring device, such as a load cell or dynamometer.

c.  Since testing of the provisions includes testing of the connecting structure around the provisions, the points used to restrain the equipment during testing shall be located such that  they do not interfere with or reduce the loading on the connecting structure around the provisions.

d.  Loads applied in the longitudinal, vertical, and lateral directions shall be applied statically and independently for not less than 6.0 seconds and shall be not less than the required design limit load in each direction.

e.  Failure is defined as any visible permanent deformation, yielding, or bending of the provision or other structural component.  A possible failure indication during the initial material analysis shall be justification to use more detailed analysis and testing methods (for example, calibrated measurements, finite element analysis, magnetic particle inspection, X-ray, fatigue testing, ultimate testing, and so forth).  Cracks in welds will constitute test failure.

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