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 APPENDIX B

lifted with equal length slings is proportional to the distance between the provisions and the vertical axis of the CG when the equipment is resting on a level surface. Therefore, the following equations apply:

V = L /(L

+ L ) x D /(D

+ D ) x GW

a r r f

b a b

= 79/(56 + 79) x 17/(16 + 17) x 10,000 = 3,015 lb

V = L /(L

+ L ) x D /(D

+ D ) x GW

b r r f

a a b

= 79/(56 + 79) x 16/(16 + 17) x 10,000 = 2,837 lb

V = L /(L

+ L ) x D /(D

+ D ) x GW

c f r f

d c d

= 56/(56 + 79) x 33/(33 + 34) x 10,000 = 2,043 lb

V = L /(L

+ L ) x D /(D

+ D ) x GW

d f r f

c c d

= 56/(56 + 79) x 34/(33 + 34) x 10,000 = 2,105 lb

B.5.1.6 Determine the static load, R, for each sling leg.

R = V /COS(VA ) = 3,015/COS(23.70) = 3,293 lb

a a a

R = V /COS(VA ) = 2,837/COS(23.90) = 3,103 lb

b b b

R = V /COS(VA ) = 2,043/COS(36.50) = 2,541 lb

c c c

R = V /COS(VA ) = 2,105/COS(36.30) = 2,612 lb

d d d

B.5.1.7 Determine the required design limit load, T. For items of equipment without heli- copter EAT requirements, the materiel lift point LF is 2.3. For items of equipment with helicopter EAT requirements, the materiel lift point LF is calculated using Appendix A. The helicopter EAT materiel lift point LF is a function of helicopter EATWT and the helicopter EATWT/MPFA ratio. If the equipment has a cargo-carrying capability, the materiel lift point LF shall be calculated for the minimum and maximum helicopter EATWTs.

For demonstration purposes, assume that this item of equipment has a helicopter EAT and crane lift requirement and an MPFA of 105 square feet. Thus, the EATWT/MPFA ratio (10,000 , 105) equals 95.24 pounds per square foot. Using Appendix A, we find the

Source: https://assist.dla.mil -- DBow-1nl0oaded: 2014-09-28T23:10Z Check the source to verify that this is the current version before use.