CPC B29C 73/10 (2013.01) [B29C 73/26 (2013.01); B29C 2073/266 (2013.01); B29L 2031/3076 (2013.01); Y10T 156/1066 (2015.01); Y10T 156/1074 (2015.01); Y10T 428/20 (2015.01)] | 7 Claims |
1. A method for repairing a damaged thermal protection covering a nacelle structure for an aircraft turbojet engine, the damaged thermal protection comprising a thermal insulation blanket present between a first sheet and a second sheet, the second sheet being located on the side of the nacelle structure, the thermal insulation blanket and the first sheet each having an area of lack of material, the method comprising:
the cutting of slots through the first sheet, the area of lack of material of the first sheet being present between the slots,
the positioning of a repair thermal insulation blanket in the area of lack of material of the thermal insulation blanket,
the positioning of a repair sheet after positioning of the repair thermal insulation blanket, the repair sheet comprising a central part and lateral tabs, a first sealing adhesive being applied on the lateral tabs, the positioning of said repair sheet being carried out by inserting the lateral tabs into the slots to interpose them between the thermal insulation blanket and the first sheet and to secure them to the first sheet by the first sealing adhesive, the central part covering the repair thermal insulation blanket after insertion of the lateral tabs into the slots, and
the depositing of a second sealing adhesive on the contour of the repair sheet thus positioned.
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