| 摘要 |
The invention relates to a lining (1) for an aircraft. The lining (1) separates an intermediate space 6 from an interior space (7) of the aircraft in a pressuretight manner. The lining panels (3-5, 44, 45, 66) extend either substantially horizontally or are fastened approximately vertically on a lining framework formed by profiles (47, 67), for connection to the fuselage cell (2). According to the invention, at least one of the lining panels (3-5, 44, 45, 66) allows automatic pressure equalization between the interior space (7) and the intermediate space (6) in the event that the pressure in the interior space (7) drops to something in the order of 0 hPa (known as "rapid decompression"). This pressure corresponds to the air pressure prevailing at an altitude above 10,000 m. For this purpose, mounts (46, 68) of the lining panels (3-5, 44, 45, 66) are provided with predetermined breaking points (30, 59, 70). The predetermined breaking points (30, 59, 70) are formed in particular by plastic nuts (28, 58, 69), the thread of which tears away when a critical load-bearing capacity is exceeded. |
