Vertical Drop Test of a Narrow-Body Transport Fuselage Section with a Conformable Auxiliary Fuel Tank Onboard

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Vertical Drop Test of a Narrow-Body Transport Fuselage Section with a Conformable Auxiliary Fuel Tank Onboard

A. Abromowitz / T. G. Smith / T. Vu

A narrow-body transport airplane fuselage section was subjected to a vertical impact drip test at the Federal Aviation Administration (FAA) William J. Hughes Technical Center located at the Atlantic City International Airport, New Jersey. The objective of the test was to determine the intersection between a typical transport airplane fuselage, particularly its floor structure, and a comfortable auxiliary fuel tank under severe, but survivable, impact conditions. The fuel tank used in this test is representative of tanks being installed in narrow-body transport airplanes. A 10-foot airframe section from a Boeing 737-200 airplane was dropped from a height of 14 feet, generating a vertical impact velocity of 30 ft/sec. The airframe test section, at a weight of 8780 pounds, simulated the load density at the maximum takeoff weight condition. The weight included cabin seats, dummy occupants, and simulated fuel in the 500-gallon fuel tank. Structural response data were obtained during the impact from instrumentation installed on the fuselage structure, floor structure, and the fuel tank. The fuselage test section sustained severe damage after the test. Portions of the cabin floor were damaged due to the impact with the auxiliary fuel tank located in the cargo compartment. The bottom of the fuel tank was punctured in numerous locations resulting in fuel spillage. The strength and rigidity of the fuel tank limited the inherent ability of the fuselage structure to absorb energy crushing during the impact.