| 摘要 |
FIELD: aeronautical engineering. SUBSTANCE: method consists in assembly of front spar with nose section, rear spar with tail section, torsion box frame-work with ribs, installation of panels, sealing-up of them by means of vertical assembly jig where front spar with nose section, rear longeron with tail section and one of panels are mounted preliminarily. Preparation of mating surfaces of panels and spars for final assembly is effected in general assembly jig; panels are moved away from framework at retained space orientation. Ribs are secured to upper and lower panels through compensators mounted on panels preliminarily. EFFECT: reduce consumption of labor; improved quality of final assembly. 3 cl, 10 dwg
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