Accession Number : AD0431309

Title :   THEORY, DEVELOPMENT AND TEST OF A CRASH FIREINERTING SYSTEM FOR RECIPROCATING ENGINE HELICOPTERS

Corporate Author : AVIATION SAFETY ENGINEERING AND RESEARCH PHOENIX AZ

Personal Author(s) : Robertson, S H ; Turnbow, James W ; Carroll, Donald F

PDF Url : AD0431309

Report Date : Dec 1963

Pagination or Media Count : 84

Abstract : This report describes the theory, development, and test of a fire- inerting system for helicopters powered with reciprocating engines. The feasibility of constructing a lightweight system capable of operating under typical crash conditions is demonstrated. Areas requiring additional development are discussed. It is concluded that: (1) a fire-inerting system for helicopters should be in operation within 0.20 second or less after first impact; (2) a time to operate of 0.20 second can be attained in an operational fire-inerting system; (3) a fireinerting system can be installed in a 10,000pound aircraft with as little as 80 pounds increase in overall weight including coolant; and (4) the construction and installation into service aircraft of a combination manual-automatic fire-inerting system meeting the above weight and time-to- operate limitations is possible with the present state of the art.

Descriptors :   *AIRCRAFT FIRES, *FIRE SAFETY, *HELICOPTER ENGINES, AVIATION ACCIDENTS, AVIATION FUELS, AVIATION SAFETY, CARBON DIOXIDE, COOLANTS, COUNTERMEASURES, FIRE EXTINGUISHERS, HELICOPTERS, IGNITION, INTERNAL COMBUSTION ENGINES, NITROGEN, SPRAYS, WATER

Subject Categories : Military Aircraft Operations
      Helicopters

Distribution Statement : APPROVED FOR PUBLIC RELEASE