This　paper　focuses　on　the　fatigue　performances　and　reliability　analysis　of　fatigue　life　for　scarf-repaired　carbon　fiber　composite　laminates,　which　plays　an　important　role　in　ensuring　the　safety　of　repaired　aircraft.　Tension-tension　fatigue　tests　at　constant-load　amplitude　were　conducted　to　determine　the　fatigue　limit　and　mechanism　of　scarf-repaired　composite　laminates.　Experimental　results　show　that　the　fatigue　limit　of　scarf-repaired　composite　laminates　is　about　34%　of　the　static　tensile　strength　and　the　failure　modes　of　speicmens　under　different　stress　levels　are　similar.　The　dominated　failure　mode　is　cohesive　failure　of　adhesive,　accompanied　by　partial　45　degrees　and　90　degrees　matrix　cracks　of　composite　patch.　Meanwhile,　the　stiffness　degradation　and　crack　observation　indicate　that　the　crack　initiation　stage　occupies　a　large　proportion　(92　+/-　5%)　of　fatigue　life.　In　additon,　the　distribution　of　fatigue　life　data　was　discussed.　Based　on　the　best　fitting　distribution,　a　new　approach　incorporating　both　reliability　and　con?dence　level　was　proposed　to　predict　the　fatigue　life　of　scarf-repaired　composites.