Aircraft turbine engine

The invention concerns an aircraft turbine engine (1), comprising a gas generator comprising at least one annular gas flow duct (2), the duct (2) being defined by two annular housings, respectively an external housing (3b) and an internal housing (3a), extending one around the other and connected together by at least one tubular arm (5) for the passage of a lubricating oil line (7). According to the invention, the line (7) comprises a first fixed section (14) secured to the external housing (3b), a second fixed section (16) secured to a piece of equipment (4) of the turbomachine capable of moving or vibrating during operation relative to the housings (3a, 3b), and an intermediate section (18) connecting the first and second sections (14, 16), this intermediate section (18) having a generally elongate shape and comprising longitudinal ends engaged and capable of swiveling and/or sliding in ends of the first and second sections (14, 16).