Abstract: An aircraft motor includes a bearing assembly including a first plurality of rotor alignment magnets; a magnet support structure fixedly mounted on a shaft of the motor in a spaced apart relation to the bearing assembly, the magnet support structure including a second plurality of rotor alignment magnets such that when the vertical thrust engine is disengaged, attraction between the first and second rotor alignment magnets causes the magnet support structure to rotate relative to the bearing assembly to an alignment position defined by the relative placement of north and south poles of the first and second plurality of rotor alignment magnets.

Abstract: An aircraft decompression assembly, comprising a cabin lining element, an element opening and an air channel adjacent to an element rear face and connected to the opening. A channel outlet, during normal assembly operation, discharges air exiting a cabin region delimited by the element through the opening into a secluded area between the element and an aircraft outer skin. A first decompression opening has a first decompression flap, which during normal operation, closes the first decompression opening and, in the event of a rapid decompression, opens the first decompression opening equalizing a pressure between the cabin region and the secluded area. A second decompression opening in the lining element has a second decompression flap which, during normal operation, closes the second decompression opening and which, in the event of a rapid decompression, opens the second decompression opening equalizing a pressure between the cabin region and the secluded area.

Abstract: An aerodynamic cover panel for a landing gear wheel well in an undercarriage of an aircraft includes at least one embodiment having a peripheral lip that defines a plane. Movements of the cover panel to open and close the wheel well are confined to pivotal rotation within the plane, and occur within an aerodynamic boundary layer of the undercarriage about a pivot axis in one rotational direction to open the wheel well, and in an opposite rotational direction to close the wheel well. The cover panel includes a flange, to which a rotary shaft is secured at one end for rotation about the pivot axis. The other end of the rotary shaft is secured to an actuator fixed within the undercarriage. In one embodiment, the cover panel rotates about an arc of least 75° between fully opened and fully closed positions of the wheel well.

Abstract: An aircraft includes a first structure between a pressure-controlled region of the aircraft and a non-pressure-controlled region of the aircraft and a second structure between the non-pressure-controlled region and an exterior of the aircraft. The aircraft also includes a first door assembly that includes a first door configured to cover a first opening between the pressure-controlled region and the non-pressure-controlled region and a second door configured to cover a second opening between the non-pressure-controlled region and the exterior. The aircraft further includes a spring coupled, via a first member, to the first door assembly and coupled, via a mechanical linkage, to the second door. The spring is configured to apply a first force to the first member and to apply a second force, via the mechanical linkage, to the second door, where the second force is applied based on a state of the first door assembly.

Abstract: An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.

Abstract: The disclosed embodiments relate to an aircraft having an interior door with a self-adjusting door jamb. The self-adjusting door jamb includes a door jamb configured to receive the interior door and a bias mechanism coupled to the door jamb and facilitating movement of the door jamb along an axis. Additionally, an angular translating mechanism coupled to the bias mechanism and facilitating angular displacement of the door jamb relative to the axis.

Abstract: A pressure relief door having a panel with an exterior side and an interior side, a pair of pressure relief latches mounted to the interior side of the panel, and a pair of hinges mounted to the panel and each including a lock mechanism mounted thereto. Each of the lock mechanisms includes a mounting bracket. The door is adapted to be installed within a structure and moveable between a closed position, such that the exterior side of the panel is substantially flush with an exterior surface of the structure, the lock mechanisms are engaged with an interior surface of the structure, and the pressure relief latches are engaged with the interior surface of the structure, and an open position, such that the pressure relief latches are disengaged with the interior surface of the structure, while the lock mechanisms remain engaged with the interior surface of the structure.

Abstract: There is provided a method and a system for controlling an inlet door of an auxiliary power unit provided on an aircraft. Input data indicative of whether the aircraft is on ground or airborne is received. If the aircraft is on ground, a first control signal comprising instructions to command the inlet door to a fully open position is output. If the aircraft is airborne, a second control signal comprising instructions to command the inlet door to a partially open position. When a current value of a rotational speed of the auxiliary power unit reaches a predetermined threshold indicative of an end of a start sequence of the auxiliary power unit, a third control signal comprising instructions to transition the inlet door from the partially open position to the fully open position is output.

Abstract: A signal-initiation device for initiating control signals in an aircraft fuselage, an aircraft fuselage including a signal-initiation device of such a type, an aircraft including such a fuselage, and the use of a signal-initiation device of such a type. The signal-initiation device for initiating control signals in an aircraft fuselage comprises a switching area configured to generate at least one control signal for controlling at least one orifice shutter present in the aircraft fuselage; and an initiating component connected to the switching area, configured to introduce the at least one control signal into the aircraft fuselage.

Abstract: A system for opening a door of an aircraft includes a connection assembly adapted to connect the door to a fuselage section of the aircraft. The connection assembly includes a main hinge pivotally connected to the fuselage section and a link assembly connecting the door to the main hinge and pivotally connected to the fuselage section, the link assembly including one member slidingly and pivotally connected to the door. The system also includes a latch mechanism between the door and the main hinge, the latch mechanism being adapted to be actuated. The system is adapted to move the door upwardly and inwardly along a predetermined path without moving the main hinge through movement of the latch mechanism and, subsequently, to pivot the door around a virtual pivot point located outside of the aircraft by moving the main hinge once the door has reached an end of the predetermined path.

Abstract: A door frame for an aircraft includes first and second beams, each having a first end and a second end. The second beam is substantially parallel to the first beam. A third beam extends from the first end of the first beam to the first end of the second beam. The third beam is substantially perpendicular to the first beam and the second beam. A first flange extends from the second end of the first beam in a direction that is away from the second beam. The first flange is substantially perpendicular to the first beam.

Abstract: Fluid systems are described. An example fluid system has a first body portion, a second body portion, a spacer, and a fluid pressurizer. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. The first body portion defines a cavity that is sized and configured to filter debris that enters the channel during use and provide a mechanism for removing the debris from the system.

Abstract: An access door assembly includes a door panel located at a door opening and a primary hinge having a primary hinge axis and operably connected to the door panel. A guide track is affixed at the door opening and is operably connected to the door panel to guide rotation of the door panel about the first hinge axis. A secondary hinge having a secondary hinge axis is operably connected to the door panel. The secondary hinge allows for rotation of a first portion of the door panel about the secondary hinge axis, while a second portion of the door panel is stationary.

Abstract: A sliding closing element for a sliding closing element arrangement of a vehicle, the sliding closing element arrangement comprising at least one rail that is adapted for slidably supporting the sliding closing element, the sliding closing element comprising at least one fail safe sliding arm assembly with at least one bogie support arm and at least one safety arm, the at least one bogie support arm comprising at least one bogie assembly with at least one guide roller that is adapted for rolling along the at least one rail in operation, and the at least one safety arm being adapted for retaining the at least one fail safe sliding arm assembly on the at least one rail in case of a failure of the at least one bogie support arm.

Abstract: A door retention system includes a housing defining a slot configured to accept the insertion of a door. The slot is deep enough to position a majority of the door within the slot. A sensor is positioned within the slot and configured to detect the presence of the door within the housing.

Abstract: A method for reducing aircraft turnaround time by improving airport ramp safety is provided. The method minimizes the time interval between an aircraft's landing and takeoff by independently moving the aircraft on the ground without the aircraft's engines by eliminating hazards from jet blast, the possibility of engine ingestion, and the time previously required to wait in the gate area upon arrival or at departure until jet blast or engine ingestion did not pose a danger. Turnaround time is further reduced by providing an onboard driver controllable to drive at least one of the aircraft's wheels between landing and takeoff, thereby eliminating the need for a tow vehicle and the time required to move the aircraft with a tow vehicle.

Abstract: An aircraft-side aircraft data retrieval system and method, comprising: a data storage device (14) located in an aircraft (2) adapted to, during a flight, store data acquired during the flight; a transmission element (50), for example a dielectric filled hole or a coaxial transmission line assembly, in an external panel (9) of the aircraft (2); and wireless apparatus (18) adapted to wirelessly transmit, after the aircraft (2) has landed, the stored data to a ground-side data retrieval system (6) via the transmission element (50).

Abstract: Embodiments of a cabin outflow valve having one or more laterally-tapered sealing surfaces are provided, as are cabin pressure controls system including cabin outflow valves. In one embodiment, the cabin outflow valve includes a frame and a first door, which is pivotally coupled to the frame and which is rotated by an actuator between open and closed positions. The first door includes, in turn, a torque input point at which the actuator applies a closing force when rotating the first door into a closed position. A laterally-tapered sealing surface extends along a lateral axis of the cabin outflow valve and has a profile height decreasing with increasing proximity to the torque input point. The laterally-tapered sealing surface helps to ensure the formation of a complete lateral seal when in the first door is rotated into the closed position to significantly reduce or eliminate leakage through the cabin outflow valve.

Abstract: A system for operating an aircraft door includes an operating handle having a lever and a grip, a slide arming means movable between a first position representing an armed state and a second position representing a disarmed state, a control unit coupled with the slide arming means, warning means arranged in the vicinity of the slide arming means and a sensor. The sensor is adapted for detecting the proximity of a hand of a user in a field around the grip, which field covers a distance of at least 10 cm and not exceeding 50 cm to the grip, and for producing a proximity signal representing the proximity of a hand of a person. The control unit is adapted for operating the warning means on receiving the proximity signal of the sensor to attention to the slide arming means when the slide arming means is in the first position.

Abstract: A thrust recovery outflow valve includes a valve frame for mounting on an aircraft exterior skin and a bi-fold valve door that is mounted within the valve frame. The bi-fold valve door includes an aft door section, a forward door section, and a ram air flap. The aft door section is rotatable between an aft door closed position and an aft door full-open position and has a ram air opening formed therein. The forward door section is rotatable between a forward door closed position and a forward door full-open position. The ram air flap is rotationally mounted on the aft door section and is rotatable between a flap closed position, which prevents air flow through the ram air opening, and a flap open position, which allows air flow through the ram air opening.

Abstract: To reliably prevent entrance of electro-magnetic waves in a door that closes an opening portion formed in an airframe of an aircraft. A gasket seal 20 which is arranged between an opening portion 12 formed in an airframe of an aircraft and a door 13 for closing the opening portion 12, includes: a gasket seal body that is made of a rubber material; and conductive fiber 24 that covers a surface of the gasket seal body. When the door 13 is in a closed state, the gasket seal 20 whose surface is made conductive is abutted against a striker 30 provided on a skin 11 side of the airframe and made of a conductive material. The door 13 and the skin 11 of the airframe are electrically connected together via the conductive fiber 24 and the striker 30, and electro-magnetic waves can be reliably shielded.

Abstract: A manufacturing method for passenger door corner components of aircraft or spacecraft includes using additive layer manufacturing, ALM, to form an integral passenger door corner component. The integral passenger door corner component includes a substantially cruciform shape having a frame coupling member with two frame couplings as end pieces. The frame coupling member intersect with a beam coupling member with two beam couplings as end pieces.

Abstract: An aircraft comprising a first door and a second door, each being mobile between an open position and a closed position, and a maneuvering system. The maneuvering system includes an actuation mechanism, a first transmission chain configured to transmit the movements of the actuation mechanism to the first door, a second transmission chain configured to transmit the movements of the actuation mechanism to the second door. Such a maneuvering system uses a single actuation mechanism, which results in a simplification of the mechanism and a weight saving.

Abstract: A device for opening and closing according to the invention relates to an aircraft door (2) hinged around an axis (6) substantially parallel to the longitudinal axis the aircraft comprising a motorized mechanism and a driving system combined with a control device comprising a system for acquisition of the angular position of the door (2) relative to the structure (4) the aircraft, where said angular position acquisition system for the door comprises at least one inclinometer (20) combined with the door (2).

Abstract: A device for opening an aircraft door, comprising: a support arm arranged between the aircraft fuselage and the aircraft door; an opening system for opening the aircraft door; a support arm cover covering the support arm in the closed position of the aircraft door, the support arm cover having a cover element, and a flap element which swivels between being flush with the cover element, and a state in which the flap element overlaps the cover element; and a guide system for guiding the flap element, wherein the guide system has at least one guide arm, one end of which is joined in an articulated manner to the support arm, and the other end of which is joined to at least one guide element, which guide element can be guided along a guide track on the inner side of the flap element, when the aircraft door is opened.

Abstract: A door assembly for mounting on an aircraft includes a rail mounted exteriorly to an outer skin of the aircraft, and a door movably coupled to the rail. The door assembly also includes a motor mountable in an interior of the aircraft, and a shaft extending through a sealed shaft port in the outer skin of the aircraft. The shaft couples the motor to the door, such that the door is movable between a first position and a second position along an outer moldline of the aircraft.

Abstract: An aircraft (1) with jettison mechanism, particularly a helicopter, comprising an airframe (2), at least one door (5) movably mounted to the airframe (2), at least one door lock mechanism (9) at an interface of said at least one door (5) with the airframe (2) to releasable mount the at least one door (5) relative to the airframe (2) and actuation means (11) for the at least one door lock mechanism (9). An emergency jettison button (20, 38) is integrated into handles (11, 12) of said actuation means.

Abstract: Provided is a captured seal assembly that can be positioned between a first surface and a second surface of a structure or vehicle, such as an aircraft. The captured seal assembly includes a geometric-shaped seal such as a bulb-shaped seal that can be secured to an outer perimeter of the first surface and a receiving land capture that can be secured to an outer perimeter of the second surface. The geometric-shaped seal is designed to engage with the receiving land capture, and join the first surface and second surface when the geometric-shaped seal is engaged with the receiving land capture. In addition, the seal assembly can maintain a differential in pressure between a first region adjacent to the first surface and a second region adjacent to the second surface.

Abstract: An apparatus for controlling the movement of a furniture part received movably on a furniture body, including a guide mechanism which acts between the body and the part and with which the part is brought out of a closing state relative to the body, wherein the part is in a position as close as possible to a front side of the body, into an opening state of the part relative to the body, and is moved back into the closing state. In an opening process, the guide mechanism moves the part out of the closing state such that, in a first motion phase, a horizontal distance between the part and the front side of the body increases and, in a subsequent motion phase following the first motion phase, the furniture part is moved linearly onward.

Abstract: The invention provides a damping mechanism which comprises a damper; and a coupling mechanism. The coupling mechanism comprises a coupling member which is pivotally attached to the damper and has a pivot bearing for pivotally connecting the coupling member to a structure when in use; and a fitting which can be engaged with the coupling member to couple the fitting with the damper and disengaged with the coupling member to decouple the fitting from the damper. More, the coupling member has a pair of parallel planar faces which taper outwardly from the pivot bearing to a convex curved edge, an upper edge and a lower edge; and a first and a second recess formed in the convex curved edge, a rib between the first and the second recesses and, a third recess formed in the lower edge.

Abstract: An aircraft having an opening therein, the aircraft including a door member moveable relative to the opening between at least an open position and a closed position, and a biasing assembly operatively connected to the door member to bias the door member to the closed position, the biasing assembly including a torsion spring.

Abstract: Embodiments of an outflow valve are provided for use in conjunction with an actuator. In one embodiment, the outflow valve includes a frame and a first door rotatably coupled to the frame and configured to be moved by the actuator between an open position and a closed position. The first door includes: (i) a main body, (ii) a bellmouth fixedly coupled to the main body, and (iii) a plurality of longitudinally-spaced slots formed through the bellmouth and increasing the flexibility thereof.

Abstract: Described are airbag modules for a passenger door having a door bustle, an airbag positioned adjacent the door bustle, and an inflator positioned adjacent the door bustle. As examples, a pneumatic system is coupled to the inflator and the airbag, wherein the pneumatic system includes a slide lock that is configured to couple a girt bar of an escape slide to a passenger door sill when the inflator is activated. As additional examples, a valve is coupled to an inlet of the airbag, wherein the valve is configured to prevent the pressurized gas from flowing from the inflator to the airbag when the valve is closed and is configured to allow the pressurized gas to flow from the inflator to the airbag when the valve is open.

Abstract: An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

Abstract: The present disclosure provides a hinge, a freight container that includes the hinge and a freight container that includes a locking rod and optionally the hinge. The hinge includes a locking pin, a first wing, a second wing and a first hinge pin that pivotally connects the first wing to the second wing. The hinge further includes a pair of hinge lugs each having a first set of surfaces defining openings through which a second hinge pin passes and at least one of the pair of hinge lugs having a surface defining an opening through which a locking pin reversibly travels. The locking rod is mounted to the door of the freight container, where the locking rod includes a cam that can move between a first predetermined position where the cam can engage the cam keeper and a second predetermined position where the cam is disengaged from the cam keeper and can travel past the end frame of the freight container and the cam keeper as the door travels into the volume of the freight container.

Abstract: An access system (10) for earthmoving equipment to allow a person to move from ground level to an elevated position, said access system having an access means (20) mounted to the earthmoving equipment via a pivot, and a retraction mechanism (50) therefor, said pivot allowing the access means to be retracted through a compound angle from a downwardly and outwardly deployed position to a retracted position generally adjacent and aligned beside the vehicle, the access means may be collapsible, such as with steps (30) pivotably mounted to the sides of the access means via secondary pivots (62).

Abstract: A manufacturing method for passenger door corner components of aircraft or spacecraft includes using additive layer manufacturing, ALM, to form an integral passenger door corner component. The integral passenger door corner component includes a substantially cruciform shape having a frame coupling member with two frame couplings as end pieces. The frame coupling member intersect with a beam coupling member with two beam couplings as end pieces.

Abstract: A multi-purpose hatch system having a removable antenna mounting plug, block or plate for installing multiple configurations of antennas or sensors is disclosed. The system features a hatch having an opening sized to receive the antenna mounting plug, block or plate. The hatch features handles which aid in installation and removal of the hatch. Multiple configurations of antennas or sensors attached to the plate can easily be removed and quickly installed to configure an aircraft for a specific mission. The system also features a billet machined hatch body, field replaceable seals and easily adaptable antenna or sensor mounting configurations which provide unprecedented ruggedness, antenna options, and field supportability.

Abstract: According to some embodiments, a door system includes a door attachment device and a receiver. The door attachment device may be coupled to a door, and the receiver may be coupled to a door frame. A receiving surface of the receiver may be configured to at least partially receive the door attachment device along a first axis. The receiving surface may have a non-planar portion curved relative to the first axis such that the receiving surface responds to movement of the door attachment device in a direction parallel to a second axis, the second axis perpendicular to the first axis, by repositioning the door attachment device in a third direction perpendicular to the plane formed by the first axis and the second axis.

Abstract: The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion (15) is of the O-duct type and is capable of axial sliding between an operational position in which it covers the gas generator (3) of said turbojet engine and defines an annular cold-air jet with said hood, and a maintenance position downstream from said operational position. The downstream portion (15) is conformed so as to be capable of sliding without blocking relative to said gas generator (3), and the inner structure includes an upstream portion (13) that can be separated from the downstream portion (15) and that includes at least two doors (13a, 13b) capable of opening towards the outside.

Abstract: An aircraft hatch emergency opening actuator, includes, a cylinder connected to the hatch at one end to a reference frame at the other end to which the hatch is connected, fluid means feeding the cylinder for emergency opening of the hatch, means for injection of the fluid means at a point of a fluid circuit feeding the cylinder for emergency opening of the hatch, said injection means configured to adopt: a rest position, in which the fluid means are isolated from the cylinder, and an active position, in which the fluid means are injected at the point of the fluid circuit, means for delaying the injection of the fluid means into the cylinder including a mobile element in the fluid circuit, delaying opening of the circuit when the injection means are in the active position, the injection delay being determined by a time of movement of the mobile element.

Abstract: A cargo door arrangement for an aircraft includes a fuselage portion, a cargo door and a locking mechanism. The fuselage portion includes a skin portion, at least one fuselage former and an opening. The cargo door includes at least one door former. The locking mechanism includes a first engagement element, a second engagement element and a connecting means. The first engagement element has a tapered portion and is rigidly connected to the door former. The second engagement element includes a tapered cavity having a shape matching the shape of the tapered portion and is rigidly connected the fuselage former. In the closed position the tapered portion is engageable with the cavity. The connecting means is adapted to rigidly connect in the closed position the door former to the first or second engagement element.

Abstract: An actuating mechanism (1) for a vent door (2) in an aircraft door (3) comprising an electric motor (4) driving the vent door (2) in a closing position towards the aircraft door (3), a control unit (9), controlling said electric motor (4), and a flight lock actuator, driven by the electric motor (4). A return spring biases the vent door (2) to an open position.

Abstract: A quiet landing gear door and methods are presented. A landing gear door comprises a trailing edge and a leading edge and is operable to deploy to a landing gear door deployed position. A door flap comprises the trailing edge and is hinged to the landing gear door. The door flap deflects toward a landing gear strut to a door flap deployed position in response to deployment of the landing gear door. A leading edge section comprises the leading edge and is coupled to the door flap. The leading edge section deflects toward the landing gear strut to a leading edge deployed position in response to deployment of the landing gear door.

Abstract: A method for mounting an aircraft component, which in the mounted state is movable between a first and a second operating position and is taken up in its first operating position in a mounting area, comprises the measuring of the mounting area, in order to obtain data characteristic of the shape and/or the dimensions of the mounting area. The data characteristic of the shape and/or the dimensions of the mounting area are projected onto the aircraft component arranged in its second operating position. Finally, the aircraft component arranged in its second operating position is adjusted with reference to the projection of the data characteristic of the shape and/or the dimensions of the mounting area.

Abstract: A connection assembly for an emergency aircraft door. The assembly includes a first pair of non parallel links pivotally attached to the fuselage and a second pair of non parallel links attached to the door. One of the links of the first pair is pivotally connected to both links of the second pair, and one of the links of the second pair is pivotally connected to both links of the first pair. A compact assembly can be achieved.

Abstract: A monument complex is provided for a rear area of a passenger cabin. The rear contour of the monument complex is adapted to the contour of the bulkhead so that an additional wash basin can be installed without there being any loss of space in the passenger cabin.

Abstract: An emergency opening system (1) of an aircraft cabin door (3) mounted in an aircraft fuselage structure (4) by means of a hinge arm (2). An actuator (7), designed to assist the opening of the aircraft cabin door (3) against the force of gravity by means of a gas operated actuating rod (8) is mounted with its fix end (9) to said hinge arm (2) and said actuating rod (8) is connected to an actuator joint (10). A fork lever (24) is linked to said actuator joint (10). A bell crank (13) is respectively pivotable mounted to said hinge arm (2) and to said actuator joint (10) for the fork lever (24). At least one coupling lever (12) is pivotable joint to said fork lever (24) at at least one coupling joint (14). Said at least one coupling lever (12) is mounted in at least one hinge (18) of the hinge arm (2) by means of a respective bolt (26), said bolt (26) being drivingly connected to said aircraft cabin door (3) for rotation of said aircraft cabin door (3).

Abstract: A method and apparatus for a tracking door centering system. An apparatus may comprise an elongate member, a first centering track, and a second centering track. The elongate member may have a first end and a second end capable of being rotatably mounted to a door along an axis that may be substantially parallel to a horizontal centerline. The first centering track may be mounted on the first end. The second centering track may be mounted on the second end. The first centering track and the second centering track may be movable to reduce rotational movement of the door during movement of the door about a vertical centerline when a first follower is engaged in the first centering track and a second follower is engaged in the second centering track.

Abstract: A shell structure of a fuselage at a door opening of the fuselage comprising a main door frame arranged on a cross-sectional plane of the fuselage. A wall portion of the main door frame extends into the fuselage and forms at least part of a first monument wall.