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Records 461 to 465 of 733
| Title: |
An Overall Review of the Cabin Interior Materials Program |
| Author: |
John F. Marcy |
| Abstract: |
The study of the flammability, smoke, and toxic characteristics of sir plane cabin materials was first initiated at NAFEC in 1963 following the introduction of large jet air transports to commercial aviation. |
| Report: |
NSR-0061 |
Pages: |
2 |
Size: |
126 KB |
| Title: |
Design Calculations for a Halon 1301 Distribution Tube for an Aircraft Cabin Fire Extinguishing System |
| Author: |
Jack Jones & Constantine P. Sarkos |
| Abstract: |
Theoretical calculations were performed to aid in the design of a perforated tube that will uniformly distribute Halon 1301 throughout the unventilated passenger cabin of a commercial air transport. Conditions for the calculations were those of a passenger cabin of a DC-7 fuselage, with a volume of 4000 cubic feet and a length of 72 feet, being used as a test article for evaluating the performance of such a system. Four separate calculations were made to determine the (1) size and number of orifices in the tube required for various Halon 1301 discharge rates; (2) pressure drop as a function of tube diameter and discharge rates; (3) time required to fill the tube with Halon 1301 for various tube diameters; and (4) cabin temperature and pressure after completion of Halon 1301 discharge. The first calculations indicated that for a given discharge time, the required orifice diameter decreased slightly with increasing orifice number for a large number of orifices (about 40-50). The pressure drop was shown to be a strong function of both tube diameter and discharge time; however, practical tube diameter could be selected to assure a negligible pressure loss � a system feature which allows orifices equally spaced with the same diameter. It was demonstrated that the fill time would be less than 10 percent of most normally used discharge times � another desired system feature. Thermodynamic calculations predicted a 38 degree F cabin temperature after complete discharge of agent with an initial cabin temperature of 70 degree F and relatively humidity of 50 percent. |
| Report: |
FAA-RD-73-32 |
Pages: |
31 |
Size: |
|
| Title: |
Jet Engine Burn-Through Investigation Volume I: Sonic Analysis |
| Author: |
Richard W. Schumacker |
| Abstract: |
The work performed during thi program was directed toward determining the acoustic characteristics of simulated burn-through failures. To determine the feasibility of detecting this failure acoustically two types of jet engines (J-47 and J-57) were modified to simulate burn-through failures. Magnetic tape recordings of the modified engines were made to determiine the extent of the acoustic spectrum, the relationship of engine speed to ailure related sound pressure levels and acoustic spectrum, the effect of sensor location to detect the failure acoustically and characteristic acoustic specta at burn-through. The recorded data was analyzed by real time spectrum analysis and mean square techniques. Results indicated that the simulated burn-through failure acoustic spectra consists primarily of broadband random noise above 5 kHz. It was also determined that sensor location is an important factor in detecting burn-through failures. Basd on the results it is concluded that acoustic detection of a burn-through failure is feasible. Recommendations for a monitor and detector based on the results of this program have been included. Volme II contains engine tests raw data and is available on loan from the DOT Library Services Division, TAD-494, 800 Independence Avenue, Washington, D.C. 20591 |
| Report: |
FAA-RD-72-149 |
Pages: |
76 |
Size: |
30.8 MB |
| Title: |
Jet Engine Burn-Through Investigation Volume II, Engine Tests Raw Data |
| Author: |
Richard W. Schumacker |
| Abstract: |
The work performed during this program was directed toward determining the acoustic characteristics of simulated burn-through failures. To determine the feasibility 0 detecting this failure acoustically two types of jet engines (J-47 and J-57) were modified to simulate burn-through failures. Magnetic tape recordings of the modified engines were made to determine the extent of the acoustic spectrum, the relationshi of engine speed to failure related sound pressure levels and acoustic spectrum, the effect of sensor location to detect the failure acoustically and characteristic acoustic spectra at burn-through. The recorded data was analyzed by real time spectrum analysis and mean square techniques. Results indicated that the simulated burn-through failure acoustic spectra consists primarily of broadband random noise above 5 kHz. It was also determined that sensor, location is an important factor in detecting burn-through failures. Based on the results it is concluded that acousti detection of a burn-through failure is feasible. Recommendations for a monitor and detector based on the results of this program have been included. Volume I contains the Sonic Analysis. |
| Report: |
FAA-RD-72-149,II |
Pages: |
301 |
Size: |
138 MB |
| Title: |
DC-9 Safe Bomb Location Study |
| Author: |
R.E> Darling |
| Abstract: |
The DC-9 commercial aircraft structure and systems are reviewed to determine the optomum location to place a discovered explosive device for the best chance of survial of the aircraft and minimization of casualties. The damage that would be caused by the explosion and the structural residual strength are determined.
The study revealed that the best place to put the bomb to do the least damage would be on the ventral stairs for those airplanes so equipped. On other DC-9 airplanes, the bomb should be put in the tail cone. |
| Report: |
FAA-RD-72-88 |
Pages: |
160 |
Size: |
39.3 MB |
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