A system for supplying the combustion chamber in an aircraft turboshaft engine with fuel, comprising injectors comprising a first pilot stage, a second pilot stage, and a main stage. The pilot stages being configured to deliver a permanent flow rate of fuel and the main stage being configured to deliver an intermittent flow rate of fuel. A device for distributing (2) fuel into the injectors comprising a primary circuit, a secondary circuit, and a valve configured to distribute the fuel between the primary circuit and the secondary circuit. The primary circuit being connected to the first pilot stage and the main stage, the secondary circuit being connected to the second pilot stage, and a member for controlling the valve.