This study comprehensively covers the structure, operation, and field testing processes of the pitot-static system, which directly affects flight safety in aircraft. The types of dynamic, static, and back pressures that the pitot-static system perceives during flight are defined in detail, and the effects of these pressures on the indicators are explained schematically. Deviations in the airspeed, altitude, and vertical speed indicators that may be caused by failures in any of the system components are analysed for each indicator. In the literature review, current studies on pitot-static systems were summarized and it was determined that these studies mostly focused on system design, modelling, and fault simulations, but field applications were not given enough space. Based on this deficiency, traditional and modern leakage test methods are compared in detail, the test device used is introduced, and the practical leakage test on a Sikorsky S-70 type helicopter is explained step by step. The presented sample test process aims to provide an educational and guiding resource for technical personnel, engineering teams and educational institutions involved in pitot-static system maintenance.
Kazan et al. (Thu,) studied this question.