Development of a Laboratory-Scale Test for Evaluating the Decomposition Products Generated Inside an Intact Fuselage During a Simulated Postcrash Fuel Fire

Marker, Timothy R.; Speitel, Louise

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Development of a Laboratory-Scale Test for Evaluating the Decomposition Products Generated Inside an Intact Fuselage During a Simulated Postcrash Fuel Fire

2008-08-01
By Marker, Timothy R. ; Speitel, Louise

File Language:

English

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Creators:

Marker, Timothy R. ; Speitel, Louise
Corporate Creators:

United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center. Airport and Aircraft Safety Research and Development Division.
Corporate Contributors:

United States. Department of Transportation. Federal Aviation Administration. Office of Aviation Research and Development
Subject/TRT Terms:

Burnthrough Combustion Composite Materials Gases Heat-stabilized Polyacrylonitrile Fiber Heat Insulating Materials Insulation Batting Lower Explosive Limit Postcrash Phase Prototypes Spectroscopy Structural Models Toxicity
Publication/ Report Number:

DOT/FAA/AR-TN07/15
Resource Type:

Tech Report
Geographical Coverage:

United States
Edition:

Technical Notes
Corporate Publisher:

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

This report summarizes the research effort undertaken by the Federal Aviation Administration to develop a laboratory-scale test method for evaluating the products of combustion inside an intact transport category fuselage during exposure to a simulated external fuel fire. An oil-fired burner, configured in accordance with Title 14 Code of Federal Regulations Part 25.856(b) Appendix F Part VII, was used to simulate the fuel fire, and a 4- by 4- by 4-foot steel cube box was used to mount representative test samples. The cube box simulated an intact fuselage and served as an enclosure to collect emitted gases during fire exposure. Test samples representing a variety of fuselage constructions were evaluated, including a noncontemporary prototype structural composite material (without thermal acoustic insulation). A typical cross section consists of a 40- by 40-inch aluminum panel representing the fuselage skin and the accompanying thermal acoustic insulation blanket behind the skin. Two thermal acoustical configurations were also tested. The first contained a heat-stabilized polyacrylonitrile fiber blanket. The second contained a ceramic paper barrier sandwiched under a fiberglass blanket. Each was encased by a thin metallized polyvinylfluoride moisture barrier. These burnthrough-resistant configurations were primarily run to provide a baseline for comparing the emitted gas concentrations with that of the prototype structural composite material.
Format:

PDF
Collection(s):

FAA William J. Hughes Technical Center for Advanced Aerospace
Main Document Checksum:

urn:sha-512:35247d9d8d05846d4dcc89ab63e9336517bf6565ca78fd04018937594e1da2fc6cb21a44bbe3c954ded6de11e82e3975323ba09ad580531172e8bd616f06889c
Download URL:

https://rosap.ntl.bts.gov/view/dot/90169/dot_90169_DS1.pdf
File Type:

[PDF - 793.23 KB ]

File Language:

English

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