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Airframe Static Test article successfully demonstrated its ability to withstand the application of 150% design limit Load for the wing maximum up bending design condition which produced approximately 22.5 inches of wing tip deflection.

 

 

 

 

 

 

 

 

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The MLG Support Structure should have the capability to meet the static strength certification requirements. There shall be no permanent detrimental deformation of the MLG SS below or at 100% DLL. And the MLGSS shall withstand loading up to 150% DLL without failing.

 

 

 

 

 

 

 

 

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The objective of the NLG Support Structure is to meet the static strength certification requirements. There shall be detrimental deformation of structure at 100% DLL or below and withstand up to 150% DLL without catastrophic failure(rupture). Failure test also is conducted up to 200%DLL or failure, whichever occurs first.

 

 

 

 

 

 

 

 

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The objective of the test is to demonstrate the T-50 horizontal tail meet the static strength requirements. There shall be no detrimental deformation or delamination at any point at design limit load and no global buckling or catastrophic failure at design ultimate load (150%DLL).

 

 

 

 

 

 

 

 

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The Pylon static test is conducted on structurally complete T-50 pylons, supported by a test fixture that provides hard-point attachment areas identical in geometry to the T-50 wing and fuselage.

 

 

 

 

 

 

 

 

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The objective of the test is to verify the static strength of the T-50 speed brake assembly with design limit loads(100% DLL with casting factor) and design ultimate loads(150% DLL with casting factor). Failure test is also conducted to 200%DLL with casting factor.

 

 

 

 

 

 

 

 

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T-50 Engine Door Lower Pin Joint Fitting is designed as a aircraft primary structure for safety. The objective of this test is to demonstrate that the T-50 Engine Door Lower Pin Joint Fittings meet the static strength requirements. There is no detrimental deformation at any point at design limit load, and no buckling or catastrophic failure at design ultimate load(150%DLL). Failure test also is conducted up to 200%DLL or failure, whichever occurs first.