GAS TURBINE ENGINE

A gas turbine engine (10) has: an annular gaspath (20) extending around a central axis (11), the annular gaspath (20) defined between a first casing (28) and a second casing (26), the first casing (28) defining pockets (28a); and a variable guide vane assembly (40) having: variable guide vanes (42) circumferentially distributed around the central axis (11), the variable guide vanes (42) having airfoils (42a) extending into the annular gaspath (20) and extending between first and second pivot members (42f, 42g) at respective first and second ends of the airfoils (42a), the variable guide vanes (42) rotatable about respective spanwise axes (A), bushings (46) received within the pockets (28a) of the first casing (28), the first pivot members (42f) of the variable guide vanes (42) rollingly engaged to the bushings (46), and resilient members (50) disposed radially between surfaces of the first casing (28) and the bushings (46) relative to the spanwise axes (A), the resilient members (50) in abutment against both of the surfaces of the first casing (28) and the bushings (46).