- Author
-
Asad, N. N.
- Title
- Carbon/Graphite Fiber Risk Analysis and Assessment Study. Volume 1. A Statistical Assessment of Fire Damage to Airframe Components.
- Coporate
- Lockheed-California Co., Burbank, CA
- Sponsor
- National Aeronautics and Space Administration, Hampton, VA
- Report
-
NASA CR-159030; LR 29075,
April 20, 1979,
71 p.
- Distribution
- AVAILABLE FROM National Technical Information Service (NTIS), Technology Administration, U.S. Department of Commerce, Springfield, VA 22161. Telephone: 1-800-553-6847 or 703-605-6000; Fax: 703-605-6900; Rush Service (Telephone Orders Only) 800-553-6847; Website: http://www.ntis.gov
- Contract
- NAS1-15509
- Keywords
-
commercial aircraft
|
carbon
|
graphite
|
risk analysis
|
risk assessment
|
fire damage
|
fire statistics
|
fibers
|
composite materials
|
aircraft accidents
|
jet transports
|
aircraft fires
|
airframes
|
fire statistics
- Abstract
- This report was prepared under contract to NASA in support of their charter to evaluate the national risk associated with the accidental release of free carbon/graphite fibers from composite material used in commercial aircraft. The purpose of the report is to prepare a statistical assessment of damage to aircraft in accidents with fire. The scope of the assessment is limited to jet transport aircraft fire accidents related to operations at airports and involving airframe components that are potential applications of carbon/graphite fiber composites. Government furnished data of accident statistics were reviewed and data that fall beyond the scope of this assessment were excluded. Data were divided into operational phases: take-off, landing and static. The extent of damage to each airframe component is assessed by the probability exceedance function of the percentage consumed by fire in each operational phase. The correlation among the extent of damage to different components is treated by a methodology that retains the highly irregular distribution of damage for each component. Accident data were divided into seven damage categories; wing, fuselage, tail, and all possible combinations thereof; within each operational phase. The proposed methodology will produce the maximum posible correlation of extent of damage among the different components within a damage category and operational phase, extending the range of extreme cases.