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

Abramowitz, Allan; Vu, Tong; Smith, Tim; United States. Federal Aviation Administration; William J. Hughes Technical Center (U.S.)

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

2000-09-01
By Abramowitz, Allan ; Vu, Tong ; Smith, Tim

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Creators:

Abramowitz, Allan ; Vu, Tong ; Smith, Tim

Abramowitz, Allan ; Vu, Tong ; Smith, Tim Less -
Corporate Creators:

United States. Federal Aviation Administration ; William J. Hughes Technical Center (U.S.)

United States. Federal Aviation Administration ; William J. Hughes Technical Center (U.S.) Less -
Corporate Contributors:

United States. Department of Transportation
Subject/TRT Terms:

[+]

Airplanes Aviation Safety Cargo Compartments Fuel Tanks Fuselages
Publication/ Report Number:

DOT/FAA/AR-00/56
Resource Type:

Tech Report
Geographical Coverage:

United States
TRIS Online Accession Number:

00967862
Edition:

Final Report July 1999-July 2000
Corporate Publisher:

United States. Department of Transportation. Federal Aviation Administration
Abstract:

A narrow-body transport airplane fuselage section was subjected to a vertical impact drop 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 interaction between a typical transport airplane fuselage, particularly its floor structure, and a conformable 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.
Format:

PDF
Collection(s):

US Transportation Collection
Main Document Checksum:

[+]

urn:sha256:cc41ba97462ce35533fed2f81facafa6a6cde159b693586ba92dab004d80f282
Download URL:

https://rosap.ntl.bts.gov/view/dot/42293/dot_42293_DS1.pdf
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Vertical Drop Test of a Narrow-Body Transport Fuselage Section With a Conformable Auxiliary Fuel Tank Onboard

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