Abstract: An aircraft landing gear door assembly has a plurality of doors. The doors include a first door (1) mounted for rotational movement between closed and open positions about a first generally longitudinal axis (11) and a transverse door (3) mounted for rotational movement between closed and open positions about a generally horizontal axis (13) that is transverse to the longitudinal axis (11). The provision of the transverse door (3) can allow the length of the first door (1) to be reduced from that which would otherwise be required to allow passage of the landing gear.

Abstract: An aircraft, aircraft fuselage, aircraft wing and aircraft landing gear are provided. The landing gear (10) comprises a wheeled leg (12) and a series of mounting members (14, 15, 16, 17) to attach the leg to an airframe of the aircraft via respective attachments (14a, 15a, 18, 19). The leg is pivotably movable between a first stowed position within the aircraft and a second deployed position for movement of the aircraft along the ground, and at least one of the attachments (18) is configured to allow retraction movement of the leg to occur about an angularly variable pivot axis and thus avoid obstacles that would be encountered in a conventional retraction path, and also to alleviate forces in the gear that can be caused by four point location of the gear leg.

Abstract: An aircraft landing gear comprises four mounting members 14, 15, 18, 19 attached to an airframe of the aircraft via attachments 14a, 15a, 16a. One of the attachments 16a is in the form of a leaf spring 30 which can flex upwards and downwards but is non-displaceable in a side-to-side direction thereby reducing induced loading in the mounting members resulting from airframe deflection.