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| Title: | Friction Effects Of Runway Grooves, Runway 18-36 Washington National Airport | ||||
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| Author: | William A. Hiering, Charles R. Grisel | ||||
| Abstract: | Wet and dry runway friction tests were conducted on bituminous concrete Runway 18-36 at Washington National Airport using a Fixed Slip Runway Friction Tester. These tests were conducted to determine if significantr friction changes were generated at a result of grooving the runway surface with 1/8 by 1/8 inch tranverse grooves spaced on 1-inch centers. Data analysis indicates that at test speeds of 10 to 60 mph, no appreciable increase or decrease in overall runway friction values was obtained for this series of tests. The treatment of the runway surface, however, by the cutting of uniformly spaced grooves markedly smoothed the resultant wet runway firction values. It is hypothesized that these smoother wet runway friction values result in a surface that affords more efficient operation of aircraft antiskid braking devices and more effective manual braking. | ||||
| Report: | FAA-NA-68-31 | Pages: | 82 | Size: | 39.2 MB |
| Title: | Evaluation Of Experimental Flight Data Recorders In An Aircraft Crash Environment | ||||
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| Author: | Paul M. Rich | ||||
| Abstract: | Two types of experimental 20-channel flight data recorders were evaluated to determine their resistance to an aircraft crash environ mente This crash environment was simulated by a series of four test a shock test. a crushing test, a penetration test, and a fire test. The first flight data recorder tested was an oscillographic .recorder enveloped in a 1/2 ATR (Air Transport Radio) casej the recording medium being stainless steel tape. This recorcter survived all the tests except the shock test in the longitudinal direction. A minor modification to the recorder would correct this fault. The second type of recorder was a magnetic tape recorder. This recorder was also destroyed in the longitudinal shock test. A major redesign would be required for this recorder to survive this test.. It was concluded that the series of four crash survivability tests are poorly defined and recommendations are made herein to correct this problem. | ||||
| Report: | NA-68-24 | Pages: | 38 | Size: | 89.2 MB |
| Title: | Supplementary Radiant Panel Test Data | ||||
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| Author: | J.F. Marcy | ||||
| Abstract: | To update Report NA-68-30, Flaming and Self Extinguishing characteristics of aircraft cabin interior materials to include data on additional materials tested of particular interest to the formulation of new standards. To present comparative flame-spread index data from several different laboratories on the same materials using the Radiant Panel Test Apparatus |
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| Report: | FSR-0130 | Pages: | 10 | Size: | 422 KB |
| Title: | Flaming And Self Extinguishing Characteristics Of Aircraft Cabin Interior Materials | ||||
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| Author: | John F. Marcy, Richard Johnson | ||||
| Abstract: | A study was made of the burning characteristics of some 140 different material for the purpose of obtaining technical data and criteria needed to support current efforts to improve existing Federal Air Regulations governing the use of cabin interior materials in aviation. Comparative tests were conducted on two groups of materials; one consisting of materials now in use in air transport, and the second materials proposed for future use with superior fire resistance. Measurements were made of ignition time, burn and char lengths, flame-out time, burn rate, heat of combustion, flame-spread index, etc. Two standard laboratory test methods were employed; namely, (1) Federal Standard CCC-T-19Ib, Test Method 5902, Results of the tests were analyzed to indicate major flammability trends for different material classifications. Practical allowable flammability limits based on available materials technology were recommended for increasing the present fire protection requirements of interior materials. |
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| Report: | NA-68-30 | Pages: | 100 | Size: | 19.1 MB |
| Title: | The Cleveland Aircraft Fire Tests | ||||
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| Author: | Captain Donald A. Heine | ||||
| Abstract: | In Phase I of the Cleveland Fire Tests, June 30 and July 1, 1966, a control burn of an aircraft was done to determine the free burn characteristics of an average aircraft cabin interior. Full instrumentation and gas analysis was accomplished to give baseline data for comparison with future tests. Also, in Phase I, a second aircraft was accomplished to determine whether high expansion foam could be used successfully to extend survival time in an aircraft cabin beyond previously known limits. This test was not successful since it was determined that ingestion of air contaminated with products of combustion/pyrolysis into foam generator prevented formation of the foam. This has been further documented by research done by Williams and reported in Fire Journal (September 1968). |
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| Report: | FSR-0176 | Pages: | 23 | Size: | 927 KB |
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