Abstract: A locking mechanism for an aircraft door includes a plurality of frame-side fittings and a plurality of door-side fittings. Each frame-side fitting includes a pin with an eccentric rotary cylinder mounted on each pin. Each door-side fitting includes an eccentric rotary latch configured to encompass at least a section of a corresponding rotary cylinder. Also a method of locking a door using the locking mechanism.

Abstract: A locking mechanism for an aircraft door includes a plurality of frame-side fittings and a plurality of door-side fittings. Each frame-side fitting includes a pin with an eccentric rotary cylinder mounted on each pin. Each door-side fitting includes an eccentric rotary latch configured to encompass at least a section of a corresponding rotary cylinder. Also a method of locking a door using the locking mechanism.

Abstract: A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal stabilizer. The horizontal stabilizer has a load-bearing structure which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas which are connected to the load-bearing structure such that they can move and can be moved independently of the elevator in order to trim the horizontal stabilizer by varying the aerodynamic profile.

Abstract: A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal stabilizer. The horizontal stabilizer has a load-bearing structure which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas which are connected to the load-bearing structure such that they can move and can be moved independently of the elevator in order to trim the horizontal stabilizer by varying the aerodynamic profile.

Abstract: A mounting bracket for holding a heat insulating mat in an aircraft cabin has a lower and an upper section configured to conform to a trough-shaped flange of a stringer secured to the fuselage. A holding pin forms part of the lower section and can be connected to the insulating mat. The two sections are onto the stringer (2) as a clip. For this purpose the lower section (4) fits with a trough (10) around the stringer (2) and the upper section (5) formed with a snap-in locking device including an expander pin (9) is arranged with a barrel portion in the trough of the stringer. The upper section (5) has a plate (14) tangentially merging into the barrel portion and extending outside the stringer (2) for the snap-in action.