Abstract: A hybrid support rail for receiving fixtures in a cabin of a vehicle includes a support rail base, first attachment elements, second attachment elements formed so as to be complementary to the first attachment elements, and a support rail upper part. The support rail base has a lower side and an upper side. The upper side has a receiving housing extending along a main extension direction of the support rail base for sliding in first attachment elements and, on a side facing away from the lower side, a support surface having at least one recess. The receiving housing is formed so as to prevent the first attachment elements from sliding out towards the support surface. The support rail upper part has a contact surface for placement on the support surface. The contact surface has recesses through which the second attachment elements are guided for insertion in the first attachment elements.

Abstract: A hybrid support rail for receiving fixtures in a cabin of a vehicle includes a support rail base, first attachment elements, second attachment elements formed so as to be complementary to the first attachment elements, and a support rail upper part. The support rail base has a lower side and an upper side. The upper side has a receiving housing extending along a main extension direction of the support rail base for sliding in first attachment elements and, on a side facing away from the lower side, a support surface having at least one recess. The receiving housing is formed so as to prevent the first attachment elements from sliding out towards the support surface. The support rail upper part has a contact surface for placement on the support surface. The contact surface has recesses through which the second attachment elements are guided for insertion in the first attachment elements.

Abstract: A method for coating a surface of an aircraft is provided. The method comprises the steps of cutting to size at least one film section from a shrinkable film material in such a manner that the film section relative to a surface section of the aircraft, which surface section is to be coated with the film section, comprises an overmeasure that is determined by the degree of shrinkage of the film material; applying the film section and a functional coating to the surface section so that the functional coating is arranged between the surface section and the film section; and shrinking the film section by heating it to a temperature that corresponds at least to the shrinkage temperature of the film section and at least to the flow temperature of the functional coating until the contours of the film section largely conform to the contours of the surface section.

Abstract: An aircraft landing flap includes a flap member having an abrasion-resistant coating coated on an abrasion region exposed to mechanical rubbing contacts with an aircraft spoiler. The coating comprises a polyurethane matrix based on aliphatic components and fillers embedded in the polyurethane matrix so as to increase resistance to abrasion.

Abstract: The present invention relates to a chromate-free composition, to the use thereof for corrosion protection, and to a corrosion protection coating for the inside surfaces of fuel tanks, wherein the composition comprises binding agents, hardening agents, corrosion inhibitors and quaternary ammonium compounds in a quantity of at least 0.1% by weight.

Abstract: A method for coating a surface of an aircraft is provided. The method comprises the steps of cutting to size at least one film section from a shrinkable film material in such a manner that the film section relative to a surface section of the aircraft, which surface section is to be coated with the film section, comprises an overmeasure that is determined by the degree of shrinkage of the film material; applying the film section and a functional coating to the surface section so that the functional coating is arranged between the surface section and the film section; and shrinking the film section by heating it to a temperature that corresponds at least to the shrinkage temperature of the film section and at least to the flow temperature of the functional coating until the contours of the film section largely conform to the contours of the surface section.

Abstract: A coating material includes: (A) a compound of formula (I) Ra4-nSiXan??(I), wherein: Xa is a hydrolysable radical; Ra is a non-hydrolysable radical; n is 2, 3 or 4; (B) a compound of formula (II) wherein: Xb is a hydrolysable radical; Rb is a non-hydrolysable radical without an epoxide function, an acryloxy function, a methacryloxy function and an isocyanate function; Yb is a non-hydrolysable radical with a crosslinkable function; p is 2 or 3; q is 1 or 2; the sum of p and q is less than or equal to 4; (C) a crosslinking agent; (D) an organozirconium, organotitanium or organoaluminum compound containing hydrolysable organic radicals; (E) a hydrolysis catalyst; (F) crosslinkable prepolymers of epoxy and epoxysiloxane resins, (G) optional corrosion inhibitors; (H) optional compounds for reducing the reactivity of component (D); wherein n and the sum of p +q are not at the same time each 4.

Abstract: The present invention relates to a chromate-free composition, to the use thereof for corrosion protection, and to a corrosion protection coating for the inside surfaces of fuel tanks, wherein the composition comprises binding agents, hardening agents, corrosion inhibitors and quaternary ammonium compounds in a quantity of at least 0.1% by weight.

Abstract: The use of a lacquer is described, comprising a polyurethane matrix based on aliphatic components and fillers which are embedded in the polyurethane matrix and increase the resistance to abrasion as an abrasion-resistant coating of (a) aircraft landing flaps 2 in the contact region with the spoilers 4 or (b) in the abrasion region of the cargo doors or (c) in the abrasion region of other aircraft parts mechanically rubbing on one another during operation. Corresponding landing flaps and lacquers are also described.

Abstract: A coating material includes: (A) a compound of formula (I) Ra4-nSiXan, ??(I) wherein: Xa is a hydrolysable radical; Ra is a non-hydrolysable radical; n is 2, 3 or 4; (B) a compound of formula (II) wherein: Xb is a hydrolysable radical; Rb is a non-hydrolysable radical without an epoxide function, an acryloxy function, a methacryloxy function and an isocyanate function; Yb is a non-hydrolysable radical with a crosslinkable function; p is 2 or 3; q is 1 or 2; the sum of p and q is less than or equal to 4; (C) a crosslinking agent; (D) an organozirconium, organotitanium or organoaluminum compound containing hydrolysable organic radicals; (E) a hydrolysis catalyst; (F) crosslinkable prepolymers of epoxy and epoxysiloxane resins, (G) optional corrosion inhibitors; (H) optional compounds for reducing the reactivity of component (D); wherein n and the sum of p+q are not at the same time each 4.