R.B. Jones

Utilizing principles previously established by the National Advisory Committee for Aeronautics and the Walter Kidde & Company, Inc., an aircraft crash-fire prevention system was designed, developed and flight tested. The object of the program was to demonstrate, through the use of pre-production type equipment, the feasibility of providing an airworthy and reliable aircraft crash-fire prevention system. A transport type airplane, the USAF C-119G, was used as test medium for the system. The system was designed to eliminate, in the event of a survivable type crash, the potentially dangerous crash-fire hazards usually found in an airplane. This was accomplished by providing for -'the inerting of all possible sources of ignition, as well as the shutoff of combustibles in nacelles and de-energizing of the airplane's electrical system. The system also included crash damage sensing devices coordinated by a control unit to automatically initiate the inerting and shutoff equipment in the event of crash. Circuitry for semi-automatic checkout of the system was incorporated in the control unit. The flight tests which concluded the program, demonstrated that an aircraft crash-fire prevention system can be made airworthy and reliable

Damiel Gross

Flame-spread data, as measured by the radiant panel method, have been obtained for a wide variety of materials including representative composite assemblies of interior finishes applied to common wall base materials.

Jack H. Cohen

Tests were conducted to investigate the degree of hazard resulting from fuel entering aircraft turbojet engines with the engine primary-air supply. The J35-A-13D and J47-GE-25 series engines were used for the tests. During engine operation, measured quantities of JP-4 fuel were released and carried by engine primary air into the engine compressor. Each engine failed when the quantity of ingested fuel approached approximately 1 per cent by weight of the normal quantity of engine primary air with actual failures occurring between 0.8 and 1.1 per cent. However, each engine failed in a different manner; the J35 engine failed as a result of components becoming overheated and the J47 engine failed as the result of a compressor stall.

G.W. Birdsall

This book explains the principles and procedures for heat treating the aluminum alloys. You do not need to be a metallurgist to understand the simple concepts used to provide the reader with a clear picture of what happens when aluminum is heat treated.

Paul R. Dierdorf & James E. Demaree

As a result of request by Region 3 of the Civil Aeronautics Administration, Kansas City, Missouri, a modified PBY aircraft, designation N19Q, was flown to the Technical Development Center, Indianapolis, Indiana, on August 19, 1957, for evaluation tests of the fire extinguishing system. Two flight tests were conducted, one under takeoff power and the other under cruise power conditions. Extinguishing agent concentrations were measured by means of the Statham Model GA-2A portable gas analyzer. This instrument is capable of recording the concentrations and duration of the discharge of the extinguishing agent while the aircraft is in flight. A recorded agent concentration of at least 15 per cent, for duration of ½ second or longer, is required to assure that the extinguishing system is adequate.