integrated into the skin 8 and has a strip like oblong shape and extends at least in portions substantially parallel to the longitudinal direction 12 of the aircraft it is not necessary at least in the barrel construction method for the aircraft window 10 to extend over the entire length of a fuselage portion barrel depending on requirements any length of the aircraft window 10 can be selected in the configuration regardless of predefined fuselage portions the aircraft window 10 is realised as a transparent pane element produced from a composite material the composite material is preferably a fibre composite material with fibres and a matrix material the fibres are transparent and have substantially the same refractive index as the matrix material due to the identical and constant refractive index within the entire material the fibres can no longer be detected in the material itself when selecting the transparent fibres for example glass fibres or polymer fibres which in an optimum case have an appropriate sizing and or appropriate finish and an appropriate matrix material based on synthetic polymer plastics materials purely by way of example these could be epoxy resin phenol resin or another type of resin among many other possible plastics materials the composite material has transparency characteristics suitable for window panes the fibre material can be in any form whether as individual fibre strands braiding or mats with random fibres regarding the usability of phenol resins it is noted here that although cured phenol resin frequently becomes friable or brittle when loaded mechanically its behaviour in fire in respect of melting resistance and similar parameters is however more favourable compared to epoxy resins therefore the use of phenol resin for the production of aircraft windows according to the invention should not be ruled out.