MIL-STD-209K APPENDIX D
ample, a windshield can be tested using a dynamic/impact test with a Navy/Marine Corps specified pulse as part of peripheral vehicle equipment test whereas a machine gun instal- lation can be structurally substantiated by hand analysis for a critical static load condition. Loose cargo items within the vehicle may have multiple configurations for carriage and are also required to be restrained to the appropriate conditions in paragraph D.3.1. All con- figurations must be structurally substantiated by analysis or test.
D.3.7 Provision Testing.
Provision testing consists of structurally substantiating each vehicle provision for the vehicle loads generated from the application of load conditions in paragraph D.3.1. A matrix of all possible tiedown patterns shall be submitted as part of the provision testing process, along with provision cone of action. Testing of the provisions and back-up struc- ture shall be of a production representative configuration. The tiedown provisions and back-up structure shall be analyzed through the entire stated cone of action from loads calculated in procedures in paragraph D.3.3. Provision pull testing will be conducted to validate the results of the analysis. The number and direction of pull tests may be deter- mined from a combination of structural analysis and engineering inference based on the actual structure and geometry being tested. In general, a minimum of 4 pull tests will be performed to simulate worst load case vehicle tiedown pattern geometry, for each provi- sion, within the cone of action. If the vendor can show structural substantiation with less than the minimum tests, a complete data package shall be submitted to NAVAIR. A test plan with total number of pulls and directions with substantiating documentation will be submitted to NAVAIR or the appropriate service transportability agent for approval.
D.3.8. Aircraft Restraint Pattern Testing.
The aircraft restraint pattern testing shall structurally substantiate the vehicle tiedown patterns for a specific aircraft platform. The vehicle will be restrained to an aircraft
mockup using the procedures submitted for paragraph D.3.6. The forward restraint criteria will be applied to the vehicle to simulate the tie down geometry in the aircraft. The same
will be performed in the other test directions. At least one complete tiedown pattern pull test shall be performed in the forward, aft and side directions to simulate the worst case load- ing. This test will be performed for each aircraft platform. When performing pattern testing, five items must be considered when developing and executing the aircraft restraint pattern test plan: 1) Local provision strength and influence on strength capability from neighboring provisions, 2) provisions sharing the same backup structure, 3) Combinations of tiedown patterns which simulate worst case loading, 4) simultaneous testing of provisions that
share the same backup structure, 5) influence of suspension system of the vehicle. Atest plan shall be submitted to NAVAIR for approval. The plan shall show the range of tiedown patterns for the vehicle in the aircraft, justification for choosing the test patterns proposed for testing, loads predicted in tiedowns devices, and loads and stresses predicted in vehicle structure for each test condition. A post test report documenting results and how they compare to predicted values shall be submitted to NAVAIR.
Source: https://assist.dla.mil -- DDow-n4loaded: 2014-09-28T23:10Z Check the source to verify that this is the current version before use.
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