Abstract: An arrangement for monitoring the functionality of a structural adhesive layer to be fabricated between a first surface of a stiffening element and another component. A sensor block is bonded to a second surface of the stiffening component opposite to the first surface. The area of the structural adhesive layer incorporates a plurality of air openings and vacuum openings that vertically extend through the stiffening component and structural adhesive layer and the sensor block. The air openings are interconnected among each other by at least one air channel, and the vacuum openings by at least one vacuum channel. At least one of the channels is connected to an evaluator unit to detect a failure of the structural adhesive layer.

Abstract: The invention relates to a stiffening component (2) for monitoring the functionality of a structural adhesive layer (6) to be fabricated between the latter and another component (4). According to the invention, the area of the structural adhesive layer (6) incorporates a plurality of air openings and vacuum openings that intersperse the stiffening component (2) and structural adhesive layer (6), as well as a sensor block (28), and the air openings are interconnected by at least one air channel (32), and the vacuum openings by at least one vacuum channel (34), wherein the channels (32, 34) run in the sensor block (28), and at least one of the channels (32, 34) can be connected to an evaluator unit (38) to detect a failure of the structural adhesive layer (6).

Abstract: A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal 1 may furthermore comprise elements for detecting cracks. A method for producing a riveted and/or screwed joint between a first and a second component of an aircraft is also provided, with the joint being sealed with the surface seal.

Abstract: A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal 1 may furthermore comprise elements for detecting cracks. A method for producing a riveted and/or screwed joint between a first and a second component of an aircraft is also provided, with the joint being sealed with the surface seal.

Abstract: Vacuum sensor application and method for firmly joining a sensor workpiece to a body component, where a) firstly, an adhesive layer which is provided by a cross-linked transfer contact adhesive is laminated to a sensor contact surface of the sensor workpiece, b) then, by using known radiation methods, the geometric patterns of a plurality of galleries to be arranged in a laminar fashion are transferred to the sensor contact surface by a light beam that penetrates the transfer contact adhesive, are subsequently introduced into the sensor workpiece and, in the process, are removed congruently with the structures of the adhesive layer introduced into the sensor workpiece, c) the adhesive-laminated patterned sensor contact surface is then arranged on a defined surface region of the body component surface, d) after that, a mechanical pressure is exerted on the two joint partners, with which the adhesive-laminated patterned sensor contact surface and the body component surface region (3) are pressed together.

Abstract: Vacuum sensor application and method for firmly joining a sensor workpiece to a body component, where a) firstly, an adhesive layer which is provided by a cross-linked transfer contact adhesive is laminated to a sensor contact surface of the sensor workpiece, b) then, by using known radiation methods, the geometric patterns of a plurality of galleries to be arranged in a laminar fashion are transferred to the sensor contact surface by a light beam that penetrates the transfer contact adhesive, are subsequently introduced into the sensor workpiece and, in the process, are removed congruently with the structures of the adhesive layer introduced into the sensor workpiece, c) the adhesive-laminated patterned sensor contact surface is then arranged on a defined surface region of the body component surface, d) after that, a mechanical pressure is exerted on the two joint partners, with which the adhesive-laminated patterned sensor contact surface and the body component surface region (3) are pressed together.