A decompression assembly (10; 10') for an aircraft comprises a first cabin lining element (12; 12') having a boundary area (14; 14') and a second cabin lining element (20; 20') having a boundary area (22; 22'), wherein the boundary area (22; 22') of the second cabin lining element (20; 20') is disposed at a smaller distance from an aircraft outer skin (24; 24') than the boundary area (14; 14') of the first cabin lining element (12; 12'). An air discharge opening (28; 28') is disposed between the boundary area (14; 14') of the first cabin lining element (12; 12') and the boundary area (22; 22') of the second cabin lining element (20; 20') for discharging air from a cabin (18; 18') of the aircraft into an area (30; 30') of the aircraft located between the cabin lining elements (12, 20; 12', 20') and the aircraft outer skin (24; 24'). A decompression element (32; 32') is adapted to release a pressure compensation opening (36; 36') between the cabin (18; 18') of the aircraft and the area (30; 30') of the aircraft located between the cabin lining elements (12, 20; 12', 20') and the aircraft outer skin (24; 24') in the event of decompression and is disposed in an area of the aircraft that is shielded from an interior of the cabin (18; 18') of the aircraft by the first and/or the second cabin lining element (12, 20; 12', 20').