Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.

A system for displaying the state of an aircraft cargo door. The cargo door is configured pivot between a closed position and an open position, the closed and open positions defining a pivoting range. The cargo door is lockable both in the closed position and in the open position. The cargo door is in a regular state when locked in the closed position or the open position. The cargo door is in a warning state when in the pivoting range between the closed position and open position. The cargo door is in a faulty state when unlocked in the closed position or unlocked in the open position or when there is an obstacle in the pivoting range. The cargo door comprises at least one indicator configured to display the respective state of the cargo door, the indicator being detectable from a distance of at least 7.5 m.

An emergency exit system comprising a first primary structure frame, a second primary structure frame extending substantially parallel to the first primary structure frame, a door opening arranged between the first primary structure frame and the second primary structure frame, and a door shiftable substantially parallel to the first primary structure frame and the second primary structure frame between a closed position and an open position. In the closed position, the door closes the door opening. In the open position, the door opens up the door opening. At least one of the primary structure frames comprises a primary structure guide element for guiding the door when the door is shifted between the closed position and the open position.

A drain configured to evacuate leaks of fluid, such as fuel, from a leak collecting system of an aircraft, the drain comprising a rigid tube secured to a plate, the plate being configured to be attached to an external wall of the aircraft, a flexible pipe configured to join the collecting system to the rigid tube, one end of the flexible pipe being received within the rigid tube. The rigid tube comprises a channel, the channel being configured to allow separation of the rigid tube from the plate at the location of the channel.

A door arrangement for an aircraft segment, which door arrangement comprises a passenger door, a fuselage portion accommodating the passenger door, and a girt bar for arming and disarming an emergency slide. The passenger door is movable relative to the fuselage portion between a raised position and a lowered position. The girt bar is connectable by means of a connecting arrangement to the passenger door and/or to the fuselage portion. The connecting arrangement comprises a mechanism which is configured to, during arming of the emergency slide, actuate a locking mechanism of an engagement device fastened to the fuselage portion, such that the girt bar is fixed in a decouplable manner to the engagement device.

A seal is disclosed having a pair of side walls, a base extending between the side walls, a first concave surface extending inwardly from one of the side walls, a second concave surface extending inwardly from the other side wall, and a convex surface extending between the first concave and second concave surface to form a rounded peak having an apex. The seal has a seal width defined between the seal side walls, and a seal height defined between the apex of the rounded peak and the base. The width is at least twice the height of the seal. The seal is located in a channel recess of a first component opposite a second component to seal between the first component and the second component, the channel recess having a floor and a height defined between the floor and a surface of the first component in which the channel recess is formed.

A seal is disclosed having a pair of side walls, a base extending between the side walls, a first concave surface extending inwardly from one of the side walls, a second concave surface extending inwardly from the other side wall, and a convex surface extending between the first concave and second concave surface to form a rounded peak having an apex. The seal has a seal width defined between the seal side walls, and a seal height defined between the apex of the rounded peak and the base. The width is at least twice the height of the seal. The seal is located in a channel recess of a first component opposite a second component to seal between the first component and the second component, the channel recess having a floor and a height defined between the floor and a surface of the first component in which the channel recess is formed.

A time-delay latch for securing a structure in a specified position includes a housing, a fluid chamber contained within the housing for holding fluid, a pin that extends through the fluid chamber and is axially movable within and through the fluid chamber, and a release frame movably secured within the housing. When the pin is in a latched position, the release frame engages with the pin to prevent axial movement of the pin. When the pin is in an unlatched position, the release frame disengages from the pin to allow axial movement of the pin. The axial movement of the pin between the latched position and the unlatched position requires a prescribed duration of time to elapse. During operation, the axial movement of the pin between the unlatched position and the latched position can occur faster than the prescribed duration of time.

A rapidly disassembled hinge suitable for use in an aircraft includes a first attachment plate attached to a supported structure, a second attachment plate attached to a supporting structure, and a pin with a notch in an outer surface thereof, which is insertable into portions of the first and second attachment plates for pivotably connecting the first and second attachment plates together. The pin is inserted so that the notch is positioned within the second attachment structure when the hinge is in an assembled state. A key includes a main body and a distal end extending from the main body, the distal end being insertable within the notch of the pin. The key is movable such that the distal end of the key can be inserted into and removed from engagement with the notch of the pin to provide for toolless disassembly of the hinge.

The invention relates to an aircraft door having a support arm (6) connected to a support forearm (9) by a first pivot connection (7) about a first pivot axis (8), the support forearm (9) being connected to the leaf (5) by a second pivot connection (10) about a second pivot axis (11) parallel to the first pivot axis (8). The support arm (6) is connected to the door frame (4) by two hinges (13, 14) each having a pivot (26, 27) for rotating the support arm (6) about a third pivot axis (12) which is parallel to the first pivot axis (8) and to the second pivot axis (11), this pivot (26, 27) being connected to the door frame (4) by an attachment (22, 23) that is translatably adjustable in two directions (35, 37, 43, 47) orthogonal to one another and orthogonal to the third pivot axis (12).