This subject is connected with the structural health monitoring (SHM) of aircraft. Progressive methods and means of the monitoring over use of ultrasonic technology are developed. The final stage provides carrying out of full-scale fa-tigue tests on components of real aviation structures. One of the objects of full-scale testing is the helicopter MI-8 tail beam. The methods of dynamic analysis of elastic system and the methods of fracture mechanics were used for planning of full-scale test, designing local experimental system of SHM, processing of test re-sults and predicting of remaining strength and remaining lifetime. The dynamic properties of object were analyzed by the method of concentrated weights and the result of dynamic stresses calculation was compared with the result of measurement. The fatigue cracks initiation and their growing in skin was observed at dynamic loading on second natural frequency 61 Hz during about four hundreds thousands of cycles. There were estimated the parameters of Paris’ law for the fatigue crack growth in a skin. A procedure of prediction of a crack growth was performed. Plural measurements of ultrasonic response were made and the stable correlation “signal-damage size” applicable for SHM of aircraft primary elements was established. It allows designing and building the integrated continuous system of monitoring of an aircraft structure and under the received information to define the fatigue cracks of a structure, to predict its remaining strength and remaining lifetime with accuracy sufficient for practical purposes. Results of monitoring can be used also for an estimation of the generalized parameters of fatigue crack resistance under loading in real operation.