FIELD: transport.
SUBSTANCE: invention relates to method of fitting aircraft window in window hole, outer transparent window element, and to aircraft with such window. Proposed window comprises outer transparent element and inner transparent element. In compliance with proposed method blunt cutout is made in aircraft sidewall to window opening outline to fit outer transparent element in said opening from fuselage outer side. Outer transparent element has first part with diameter larger than that of said opening. Said first part features shape interacting with sidewall section to lock outer transparent element in said opening in lateral and lengthwise directions. Said outer transparent element has second section with recess extending inside fuselage. Outer and inner transparent elements are rigidly secured by means of ring fastener. Said ring fastener presses gasket to fuselage and recess inner wall.
EFFECT: reduced weight.
11 cl, 3 dwg
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