A new test method is proposed about fuselage panels under internal pressure load. “D” jig and “Arch” connectors are utilized to simulate the boundary conditions of fuselage panel subjected to internal pressure load. Test fixture and fuselage panel specimen were designed and manufactured. Tests were conducted based on the proposed method. The test results demonstrated that hoop stress and axial stress about transition area were much more lower than it’s about the test area. Hoop stress ,axial stress and displacement about the test area are consistent with theoretic result. The proposed test settle for engineering precision requirements and provides reference for configuration-selection tests of fuselage panel subjected to internal pressure load.