Abstract: A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.

Abstract: The present invention proceeds from an engine brake for a multi-cylinder internal combustion engine with decompression valves actuatable by pressurization of hydraulic pistons outside of the exhaust stroke of the working piston of the internal combustion engine, in particular at the end of the compression stroke. A radial piston pump is provided with internally supported radial pistons. The pump housing has a first housing section with the radial pistons, and a space for the eccentric which controls the radial pistons and a second housing section with the control outputs.