Abstract: A retractable fuselage mounted landing gear assembly is disclosed. The landing gear assembly includes a main strut, a drag stay and a landing gear main fitting. A first end of the drag stay is attached to the main strut and a second end of the drag stay is connected to the fuselage. A first end of the landing main fitting is attached to the main strut and a second end of the main fitting is connected to the fuselage. When the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.

Abstract: A retractable fuselage mounted landing gear assembly is disclosed. The landing gear assembly includes a main strut, a drag stay and a landing gear main fitting. A first end of the drag stay is attached to the main strut and a second end of the drag stay is connected to the fuselage. A first end of the landing main fitting is attached to the main strut and a second end of the main fitting is connected to the fuselage. When the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.

Abstract: An aircraft landing gear bay roof, the roof forming a pressurization barrier between a pressurized upper compartment and a landing gear bay for the housing of a landing gear, comprising a roof wall forming the pressurization barrier. The roof wall is held by longitudinal gantries to which it is linked, and which extend over the entire length of the roof wall. The roof wall comprises a lower face configured to be installed inside the landing gear bay and an upper face configured to be installed outside the landing gear bay. At least one of the gantries is installed against the lower face of the roof wall.

Abstract: An aircraft landing gear bay roof for forming a pressurization barrier between an upper pressurized compartment and a landing gear bay for the housing of a landing gear. The roof comprises a main bulkhead extending in a longitudinal direction, an inclined forward bulkhead, rigidly connected to a forward edge of the main wall, and an inclined aft bulkhead, rigidly connected to an aft edge of the main bulkhead. The forward bulkhead and the aft bulkhead each form an obtuse angle with the main bulkhead. This configuration enables a better absorption of loads by the landing gear bay roof and a shorter and optimized path for transmission of the mechanical loads, in particular to the fuselage member to which the aft bulkhead is configured to be connected.