Aerodynamic drag associated with a flap hinge assembly (30) used to pivotally mount a flap (17) to the trailing edge (22) of an aircraft (10) wing (14) can be reduced when the cross-sectional area of the hinge fairing (24) which surrounds the flap hinge assembly is reduced in size. The reduction in cross-sectional area of the hinge fairing is enabled when the flap hinge assembly attachment footprint to the underside of the flap box is also reduced. The flap hinge assembly has an internal support rib (66) positioned between spars of the flap box structure internal to the skin, a hinge fitting (44) exhibiting an actuation point (50) and a hinge point (52) positioned proximate a front spar (60) of the flap box structure external to the skin, and a link (68) passing through an aperture (70) in the lower skin (46) of the flap and coupling the internal support rib to the hinge fitting.