A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

An aircraft fuselage includes a structure, considered in respect of all or part of the fuselage, with fuselage upper sub-structure constituting an upper part of the fuselage and a fuselage bottom sub-structure constituting a lower part of the fuselage. Openings in the structure of the fuselage are intended for the installation of windows or doors for exiting the fuselage. Furthermore, the fuselage upper sub-structure and the fuselage bottom sub-structure form fuselage sub-structures that are assembled with one another via at least one lintel in which all or some of the openings intended for installing the exit doors or windows are formed.

A structural assembly includes a support structure and an elongate structure intersecting the support structure. The elongate structure has a length and a mass. The mass of the elongate structure varies along the length of the elongate structure. A localized mass of the elongate structure decreases toward the support structure and increases away from the support structure.

An alignment jig (10) configured to support and orient a load (500). The alignment jig (10) may form part of an alignment system (300). The alignment jig (10) comprises a first base unit (100) configured to carry a first support unit (200), the first support unit (200) being configured to support the load (500) and to space the first base unit (100) apart from the load (500). The first support unit (200) is moveable relative to the first base unit (100). The first base unit (100) comprises a first base unit actuation system (110) operable to act on the first support unit (200) along a first base unit operational axis X1. The first support unit (200) comprises a first support unit actuation system (210) operable to act on the load (500) along a first support unit operational axis Y1.

An aircraft having a systems cabinet positioned in an avionics bay to the rear of a landing gear compartment and connected to the fuselage by at least one lower connecting system. The systems cabinet and/or the lower connecting system comprises at least one longitudinal beam, which has a front end connected by a front connection to a wall separating the avionics bay and the landing gear compartment, the front connection comprising a sliding connection sliding in a direction substantially parallel to the longitudinal axis.

An aircraft body section comprises a first layer of composite material, a first group of conductive traces, a second layer of composite material, and a first group of conductive connectors. The first layer of composite material has an upper surface and a lower surface, with the lower surface forming an exterior surface of a body of the aircraft. The first group of conductive traces are formed on the upper surface of the first layer of composite material. The second layer of composite material is positioned on the first layer of composite material and has an upper surface and a lower surface, with the upper surface forming an interior surface of a body of the aircraft. The first group of conductive connectors is formed on the upper surface of the second layer of composite material and is configured to provide electrical connection from external conductors to the conductive traces.

A conductive composite includes a first layer of elastomeric polymer, a layer of conductive fluorofluid on the first layer of elastomeric polymer, and a second layer of elastomeric polymer on the layer of conductive fluorofluid.

A conductive composite includes a first layer of elastomeric polymer, a layer of electrically conductive paste on the first layer of elastomeric polymer, and a second layer of elastomeric polymer on the layer of electrically conductive paste. A reinforcement mesh is in contact with the layer of electrically conductive paste.

An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.

Embodiments for aircraft keel beam assembly. One embodiment is a keel beam assembly of an aircraft. The keel beam assembly includes a keel attach chord to connect to a wing center section of the aircraft, the keel attach chord extending in a longitudinal direction between a rear spar and front spar of the aircraft. The keel beam assembly also includes a lower chord disposed underneath the keel attach chord and extending in the longitudinal direction between an aft wheel well bulkhead and a forward bulkhead of the aircraft. The keel beam assembly further includes a forward web to couple the keel attach chord and the lower chord, the forward web including a front edge extending in a diagonal direction from the keel attach chord that is downward and aft toward the lower chord to create an open area forward from the front edge.