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The problem of determining the transien ts in an airplane following the landing impact has become important during recent years with the advent of large transport airpla{les. It became apparent, a~ a result of several failures in service, that the stresses deVeloped during the landing of large transport airplanes could be far in excess of those computed from the characteristics of the landing gear on the assumption that the airplane was decelerated a a rigid body during the landing impact. I t was obvious that an adequa te str ess analysis of the airplane wo uld have to take into account the transients excited by the landing impact. Several methods were soon proposed for computing these transients, notably the statistical method of Biot and Bisplinghoff [1],2 in which the response of the airplane for impacts of standard shapes is resolved in terms of the normal modes of vibration of the airplane, and the method of David Williams 12], in which

Transient vibration in an airplane wing obtained by several methods