Charles Middlesworth

A mathematical model was formulated which permits a calculation to be made of the time required for damage to occur to the aluminum skin covering an aircraft fuselage when it is exposed to maximum spill fire conditions. The damage time was defined as the time required for the aluminum skin to melt.

The model was developed through consideration of the heat transfer rates by convection and radiation across a simplified aircraft fuselage configuration. The resulting differential equation was solved using a numerical technique. The results indicate that the minimum time required for skin damage to occur to the largest commercial aircraft now in service through the use of the mathematical model, correspond closely with measurements made on simulated aircraft skin configuration employing a 40-fott, stainless-steel-covered section of a four-engine jet aircraft fuselage.

U.S. Department Of Commerce

Generation of HC occurs when PVC cable insulation is heated, externally or by internal heating induced by electric overload. The HC vapor my be present in the atmosphere, at hazardous levels, prior to the generation of black smoke – so that fire-fighting personnel may not be readily cognizant of the danger.

American Instrument Company

Government regulations now under study may bring drastic changes in the type of materials specified for the interiors of the new jets.

Dsavid W. Voyls

A series of static and dynamic tests of representative aircraft passenger seats was conducted. The static tests utilized the procedures of Technical Standard Orders C-22 and C-39 which embody the test standards for certifying passenger seats for commercial aircraft. The dynamic tests utilized, in part, test procedures developed specifically for this project and, in part, test procedures developed from experience in the testing of Navy aircrew seats.

A significant difference between static and dynamic test results was found, thus warranting further investigation of the validity of utilizing static tests alone for the type certification of aircraft passenger seats for a dynamic or crash load requirement. The fact that static test results, in themselves, cannot be related to crash environments is demonstrated and cited as a definite limitation of static tests. Dynamic test results are demonstrated as having the capability of being related to crash environments and are considered to be the more meaningful in definjng the behavior of seat/occupant systems when subjected to crash phenomena.

vDynamic test criteria for the type certiftcation of aircraft seats were established and used to analyze the static and dynamic test results. A relationship between the static and dynamic test load conditions was devised as part of the criteria. Relatively simple methods for dynamic testing are suggested, and the procedure for analyzing test results is presented. _ _

Eugene P. Klueg

To present information on the standard burner used in fire resistance testing of aircraft power plant components and the effect of engine size on fire resistance requirements