Vibration and temperature measurement tests were conducted on a CH-54B helicopter to define the vibration and temperature environment for instruments, avionics, pilot station, and other component parts for representative flight conditions. The testing consisted of 16 flights totaling 18.5 productive test hours. Vibration data were recorded from 70 accelerometer locations for 55 flight conditions, and narrow band spectral analyses were performed on the vibration data. The results of the spectral analyses were summarized by use of statistical methods. Forward fuselage vibrations were primarily low frequency and were caused by the main rotor. Aft fuselage vibrations were primarily high frequency and were caused by gearbox and other rotating component vibration sources. The highest vibration levels were recorded at the auxiliary power plant at main transmission gear mesh frequencies. There were two shortcomings: amplification of main rotor-induced vibrations by avionics vibration isolation mounts, and excessively high Wet Bulb Globe Temperature index at the pilot station under certain environmental conditions.


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