FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft gas turbine engines. Unit comprises gas turbine engine and engine to aircraft mounting system. Attachment system comprises support, rear fasteners and support rear closing element. Rear closing element has two side walls. Every wall has first part (42a) passing along and next to support and passing rearward, and second part (42b), which protrudes in lateral direction relative to wall first part to its outer side so, that to close rear fasteners. Each second part (42b) of closing element rear side wall has essentially bulge shape and connected to side wall first part.
EFFECT: invention allows to reduce specific fuel consumption.
5 cl, 5 dwg
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