Method for adjusting the doors of a landing gear bay, and associated door
The aim of the invention is to allow the set of doors to be adjusted without increasing the number of landing gear retraction/extension maneuvers, by incorporating a specific entrance in the fairing ( 2 ) of the landing gear bay ( 4 ) that provides access to the different accessories ( 14, 17 a, 17 b ) used to adjust the doors ( 21 - 25 ). The method of the invention consists in: providing a removable bodywork element ( 5 ) which is inserted into the fairing ( 2 ) of a landing gear bay, surrounded by a stiffening structure ( 7 ) and of sufficient dimension such that the adjustment levers ( 14, 17 a, 17 b ) can be reached from the outside; accessing the inside of the bay ( 4 ) by retracting the removable bodywork element ( 5 ); and using the levers ( 14, 17 a, 17 b ) to adjust the different doors ( 21 to 25 ) in a flush aerodynamic position, as well as the clearances between said doors. In one embodiment of the invention, one door ( 25 ) comprises a central bodywork portion ( 5 ) and a peripheral portion ( 7 ) including stiffening means ( 70 ). The peripheral portion ( 7 ) is surrounded by a seal ( 30 ) that bears on the other doors ( 21 - 24 ) via the stiffening means ( 70 ) and the central portion ( 5 ) is coupled to the peripheral portion ( 7 ) by removable separation means ( 6 ).
1. A method for providing adjustable doors of a bay for landing gear of an aircraft having an overall fuselage, the landing gear being able to deploy out of the bay via doors formed in the fuselage and the doors being adjusted using position-adjustment handles that are inaccessible from outside the bay, the method comprising:
providing a removable bodywork in at least one door,
applying a stiffening structure to a surface of the removable bodywork, and
positioning the position-adjustment handles proximate to the removable bodywork, wherein the position-adjustment handles are configured to be accessed from outside of the fuselage by removing the removable bodywork and reaching through an opening formed by removing the bodywork and reaching into the bay, such that the position-adjustment handles are reachable from outside of the fuselage to adjust positions of the doors.
2. The method for adjusting doors as claimed in claim 1 , in which the removable bodywork is formed in an unpressurized zone of the fuselage or in a fairing formed on the fuselage.
3. The method for adjusting doors as claimed in of claim 1 , in which the removable bodywork is formed in a fixed door and the adjustment of the position-adjustment handles adjusts a relative position between the fixed door and the other doors.
4. A landing gear bay door assembly comprising:
a door including a central bodywork part including a peripheral part extending around the central bodywork;
a stiffener mounted to a surface of the peripheral part,
the door configured to open while a landing gear extends from or retracts into a bay of a fuselage;
a seal bearing extending around the peripheral part and configured to form a seal between the door and other doors while all of the doors are closed, and
the central bodywork part being coupled by removable fastener to the peripheral part.
5. The door as claimed in claim 4 , wherein the door is mounted to a wheel strut.
6. The door as claimed in claim 5 , wherein the central body work is a panel.
7. The door as claimed in claim 4 , in which the stiffener includes at least one of metal ribs and a composite material.
8. The door as claimed in claim 7 , wherein the central bodywork part is coupled removably to the peripheral part of the door by at least one of screw/nut assemblies, a magnetic lock.
9. A landing gear bay door assembly for an aircraft fuselage comprising:
a first door including a central bodywork panel and a peripheral door part extending around the perimeter of the central bodywork panel, wherein the central bodywork panel is removable from the peripheral door part;
a stiffing rib mounted to a surface of the peripheral door part;
second and third doors pivotably attached to the aircraft fuselage, wherein the second and third doors each have an edge adjacent an edge of the first door while the first, second and third doors are closed;
an adjusting mechanism configured to spatially the first doors relative to the second and third doors, wherein the adjusting mechanism is accessible through an opening formed by removal of the central bodywork panel;
a seal bearing extending around the peripheral part and configured to form a seal between the central bodywork and the edges of the second and third doors.
10. The landing gear bay door assembly of claim 9 wherein the first door is fixed to a wheel strut of a landing gear.
11. The landing gear bay door assembly of claim 9 wherein a thickness of the first door is smaller than a thickness of the peripheral part.
12. The landing gear bay door assembly of claim 9 wherein the edges of the second and third doors are opposite to hinged edges of the second and third doors.