A Short Brothers PLC, Model SD 3-30, airplane was subjected to a vertical impact drop test at the Federal Aviation Administration (FAA) William J. Hughes Technical Center, Atlantic City International Airport, New Jersey. The objective of the test was to determine the impact response of the fuselage, seat tracks, seats, and anthropomorphic test dummies on a high-wing, commuter type airplane. The test was conducted to simulate the vertical velocity component of a severe, but survivable, crash impact. A final impact velocity of 30 feet per second was therefore selected. The airplane was configured in a typical maximum gross weight flight condition, including seats, simulated occupants, fuel, and cargo. The Shorts 3.30 is a twin turboprop, 30-passenger regional transport airplane. The total test weight of the airplane was 21,210 pounds. The internal seating arrangement consisted of pilot and copilot seats, eight rows of standard passenger seats, and two nonstandard seats mounted in the aisle. Twentyone of the 28 seats were occupied by mannequins; the remaining seven seats were occupied by instrumented anthropomorphic test dummies. The Shorts 3-30 fuel system is unique insofar as the two fuel tanks are located on top of the fuselage as opposed to the more conventional location in the wings. During the drop test, a massive amount of simulated fuel spilled into the passenger compartment. The stiff structure of the airplane allowed for only small amounts of airframe crushing. As a result, the fuselage experienced high G(max) levels of approximately 90 g's with an impact pulse duration of 15 ins. The stiff structure also prevented fuselage crushing which allowed the airplane to maintain a protective shell. The seat tracks remained attached to the fuselage. However, 23 of the 26 passenger seats experienced structural failure. The crew seats were undamaged.
Vertical Drop Test of a Shorts 3-30 Airplane
1999
121 pages
Report
Keine Angabe
Englisch
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