Simulated bleed air impingement tests were conducted to explore the possibility that an engine bleed air leak contributed to the loss of an F-16 aircraft. A data base of the results of hot engine bleed air impinging on engine compartment walls was established for selected aircraft aluminum materials. Testing indicated the specific F-16 conditions could not have caused panel burnthrough; however, substituting other conditions did result in panel burnthrough. The results provide information which will assist in future mishap investigations. Keywords: Electrical conductivity.
Effects of Aircraft Engine Bleed Air Duct Failures on Surrounding Aircraft Structure
1987
122 pages
Report
Keine Angabe
Englisch
Aircraft , Bleed systems , Burnthrough , Ventilation ducts , Aircraft panels , Compartments , Data bases , Electrical conductivity , Engines , High temperature , Materials , Panels , Walls , Air , Aluminum , Air leakage , Bleed air , F-16 Aircraft
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