Vertical Drop Test of a Narrow-Body Transport Fuselage Section with Overhead Stowage Bins

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Vertical Drop Test of a Narrow-Body Transport Fuselage Section with Overhead Stowage Bins

A. Abramowitz / T. G. Smith / T. Vu / J. R. Zvanya

A 10-foot-long fuselage section from a Boeing 737-100 was dropped from a height of 14 feet, generating a final velocity at impact of 30 feet per second. The fuselage section was configured to simulate the load density at the maximum takeoff weight condition. The final weight of 8870 pounds included cabin seats, dummy occupants, overhead stowage bins with contents, and cargo compartment luggage. The fuselage section was instrumented with strain gages, accelerometers, and high-speed cameras. The fuselage section sustained severe deformation of the cargo compartment. The cargo compartment luggage influenced the manner in which the fuselage crushed, affecting the g forces experienced by the fuselage section and the pulse duration. The seat tracks experienced a vertical impact pulse of 15 g and a pulse duration of approximately 135 milliseconds. Although numerous fuselage structural members fractured during the test, a habitable environment was maintained for the occupants, and the impact was considered survivable. Both overhead stowage bins maintained their structural integrity and remained attached to the fuselage. The bins sustained up to 14 g vertical loading. Distribution of the loads among the bin supports was different in the dynamic versus static case.