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 A

APPENDIX A

HELICOPTER SLING LOAD MATERIEL LIFT POINT LOAD FACTOR A.1  GENERAL

A.1.1 Scope. This appendix provides the procedures for calculating the helicopter

HSL materiel lift point load factor (LF).

A.2  APPLICABLE DOCUMENTS.

Department of Defense

Standards

MIL-STD-913        Requirements for the Certification of Sling Loaded Military Equipment for External Transportation by Department of Defense Helicopters.

A.3 REQUIREMENTS

A.3.1 Determine the helicopter sling load (HSL) materiel lift point LF. The HSL materiel lift point LF is used to calculate the design limit load for all materiel with a HSL requirement. The LF is calculated using the Table A-1 (page A-2). The LF is a function of the HSL weight (HSLWT) and the helicopter HSLWT/maximum projected frontal area (MPFA) ratio, in accordance with the table below. The MPFA for a single-point load is the maximum area projected on a vertical plane as the item is rotated about a vertical axis through the aircraft hook; for dual-point or tandem loads, the maximum projected area on a vertical plane is in the direction of flight (see figure A-1).

A.3.2 Cargo equipment. For items of equipment with cargo-carrying capability, the materiel lift point LF shall be calculated for the minimum and maximum possible helicopter HSLWTs. Depending upon the weights, the lesser weight could have higher design limit load requirements. Thus, the design limit load shall be the greater value of the HSLWT multiplied by the lift point LF. Consult MIL-STD-913 for detailed information on determining design limit load for HSL.

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