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

attached to a 20-foot ISO container spreader bar.  If there is sling interference with the equipment, the contact points on the equipment must have sufficient strength to withstand the compressive loads caused by sling contact at the design limit load.

b.  An ultimate load of not less than 1.5 times the design limit load. c.  The lifting provisions shall be tested for validation in accordance

with paragraph 5.1.5 of this standard.

5.1.4  Provision Dimensions.

Lifting provisions shall conform to the dimensions specified in Figure 3.

5.1.5  Testing.

Testing shall meet the following requirements:

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

b.  The angles and loads for the static pull shall be those loads and angles as determined by the methods specified in paragraphs 5.1.3.1.a, 5.1.3.1.b and 5.1.3.2.a.  If evaluations show that the provisions may fail when lifted by a 20-foot ISO container spreader bar, an additional test using the container spreader bar, or equivalent, will be performed.

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 in the sling legs shall be measured with an appropriate measuring device, such as a load cell or dynamometer.

e.  The load applied to each provision shall not be less than the required design limit load and shall be applied for not less than 90 seconds.  (Note:  For helicopter transport, the required design limit load will be based on the highest LF required in appendix A.)

f.  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.

g. The contractor shall provide a material analysis showing the ultimate load is

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