National Space Development Agency of Japan (NASDA) started to develop H-II launch vehicle in 1983 and succeeded in the 1st flight on February in 1994. Meanwhile, several troubles were experienced in the development of LE-7 which is the 1st stage engine of H-II. The LE-7 is a staged combustion cycle engine with high pressure and high Isp like SSME. Therefore, high delivery pressure and high performance were required for LH₂ turbopump, which is the main key component, and caused several troubles in the development. This paper describes the development of LH₂ turbopump containing the design description, the contents of some troubles and their counterplans. In addition, some activities to solve turbopump life and endurance will be introduced.