| 摘要 |
A method and apparatus comprising a frame 124, a first linking system 126 connected to the frame, and a second linking system 128 connected to the frame. The frame is configured to be connected to a support structure 108 for an engine 102 of an aircraft 100. The first linking system is configured to be connected to a fan case 116 in the engine. The second linking system is configured to be connected to an engine core case 118 in the engine. |
