| 摘要 |
A turbojet engine nacelle comprising a secure lock for the rear half-portions. A turbojet engine nacelle comprising two rear half-portions (24, 26) arranged downstream from front half-covers (20, 22), the two rear portions and the two covers closing against each other in a same axial junction plane (P), a lock provided at the junction between the two rear portions (24, 26), on the upstream side, and tangentially clamping these two portions together, comprises a manoeuvring handle (28) that pivots in a transverse plane, characterised in that, with the lock locked and the front covers (20, 22) closed, the handle (28) is fully fitted into a transverse external cutout that extends over the two covers, apart from a shoulder formed at the free end of same that is below one of the covers (20). |
