In order to achieve reasonable induction of landing shock data of aero-engine， the energy spectrum density and the shock response spectrum（SRS） are used to filter the shock data samples， and combined with the relevant standards and mathematical statistics methods， then measured SRS and the normalized SRS are given. By measuring the landing shock data of aero-engine casing， the measured SRS and the normalized SRS of two types of aero-engines installed on the same aircraft are obtained. The differences of shock characteristics in different directions at the same position and in two different aero-engines are analyzed respectively. The results show that the shock characteristics in different directions at the same position may vary greatly， and it is possible to reduce the risk of shock damage by changing the installation direction of equipments or structures. Moreover， shock characteristics of different aero-engines may vary greatly as well. Thus， to ensure that the shock environmental testing of structures could contain actual shock dangerous loads as soon as possible ， the excitation in shock testing can combine the normalized SRS with 3 dB or 6 dB margin increase with maximum value of actual shock. The conclusions of this study provide some guidance for shock absorption design of aero-engines and installation of airborne equipments.