| 摘要 |
The invention relates to a pylon (14) for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge (16), as well as a first hot air distribution channel (30) passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel (36) belonging to a system for supplying pressurised air to the aircraft. According to the invention the second channel (36) is housed inside the first channel (30).
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