Patent ID: 8544176

Claim:
A method of forming a panel assembly of a ventral fairing of an aircraft, comprising: mounting first and second panels on a support structure to form at least a portion of the panel assembly of the ventral fairing the aircraft, with a variable width interstice being provided between adjacent longitudinal edges of the mounted first and second panels, wherein the width of the variable width interstice varies as a maximum and a minimum dimension between the adjacent edges of the first and second panels according to mounting constraints of the first and second panels on the support structure and compression and expansion forces encountered during use of the aircraft; and sealing adjacent edges of the first and second panels with a sealing joint configured to minimize aerodynamic drag on the aircraft generated by movement of the first and second panels, wherein the sealing joint comprises: a central part housed in the variable width interstice, an external part facing an exterior of the panel assembly and configured to cover an external face of the longitudinal edges of the mounted first and second panels, with the external part being provided with an aerodynamic profile to minimize the aerodynamic drag at a location between the first and second panels, and an internal part facing an interior of the assembly and configured to cover an internal face of the longitudinal edges of the mounted first and second panels.