An airfoil comprising a cooling hole pattern, wherein the cooling hole pattern comprises: a first filmrow comprising: a first radially outward facing portion comprising cooling holes oriented radially outward of an engine central longitudinal axis (x-x) and over a surface of the airfoil; a first radially inward facing portion comprising cooling holes oriented radially inward toward the engine central longitudinal axis (x-x') and over the surface of the airfoil; a first transition boundary comprising a first point equidistant between the first radially outward facing portion and the first radially inward facing portion; and a first transition boundary radial position comprising a first radial distance of the first transition boundary from the engine central longitudinal axis (x-x'); and a second filmrow comprising: a second radially outward facing portion comprising cooling holes oriented radially outward of the engine central longitudinal axis (x-x) and over the surface of the airfoil; a second radially inward facing portion comprising cooling holes oriented radially inward toward the engine central longitudinal axis (x-x') and over the surface of the airfoil; a second transition boundary comprising a second point equidistant between the second radially outward facing portion and the second radially inward facing portion; and a second transition boundary radial position comprising a second radial distance of the second transition boundary from the engine central longitudinal axis (x-x); characterised in that the second transition boundary radial position differs by more than one-half pitch from the first transition boundary radial position, wherein one whole pitch is the radial distance (190-1, 190-2) between individual cooling holes of the first radially outward facing portion or the radially inward facing portion of the first film row. a first filmrow comprising: a first radially outward facing portion comprising cooling holes oriented radially outward of an engine central longitudinal axis (x-x) and over a surface of the airfoil; a first radially inward facing portion comprising cooling holes oriented radially inward toward the engine central longitudinal axis (x-x') and over the surface of the airfoil; a first transition boundary comprising a first point equidistant between the first radially outward facing portion and the first radially inward facing portion; and a first transition boundary radial position comprising a first radial distance of the first transition boundary from the engine central longitudinal axis (x-x'); and a first radially outward facing portion comprising cooling holes oriented radially outward of an engine central longitudinal axis (x-x) and over a surface of the airfoil; a first radially inward facing portion comprising cooling holes oriented radially inward toward the engine central longitudinal axis (x-x') and over the surface of the airfoil; a first transition boundary comprising a first point equidistant between the first radially outward facing portion and the first radially inward facing portion; and a first transition boundary radial position comprising a first radial distance of the first transition boundary from the engine central longitudinal axis (x-x'); and a second filmrow comprising: a second radially outward facing portion comprising cooling holes oriented radially outward of the engine central longitudinal axis (x-x) and over the surface of the airfoil; a second radially inward facing portion comprising cooling holes oriented radially inward toward the engine central longitudinal axis (x-x') and over the surface of the airfoil; a second transition boundary comprising a second point equidistant between the second radially outward facing portion and the second radially inward facing portion; and a second transition boundary radial position comprising a second radial distance of the second transition boundary from the engine central longitudinal axis (x-x); characterised in that the second transition boundary radial position differs by more than one-half pitch from the first transition boundary radial position, wherein one whole pitch is the radial distance (190-1, 190-2) between individual cooling holes of the first radially outward facing portion or the radially inward facing portion of the first film row. a second radially outward facing portion comprising cooling holes oriented radially outward of the engine central longitudinal axis (x-x) and over the surface of the airfoil; a second radially inward facing portion comprising cooling holes oriented radially inward toward the engine central longitudinal axis (x-x') and over the surface of the airfoil; a second transition boundary comprising a second point equidistant between the second radially outward facing portion and the second radially inward facing portion; and a second transition boundary radial position comprising a second radial distance of the second transition boundary from the engine central longitudinal axis (x-x); characterised in that the second transition boundary radial position differs by more than one-half pitch from the first transition boundary radial position, wherein one whole pitch is the radial distance (190-1, 190-2) between individual cooling holes of the first radially outward facing portion or the radially inward facing portion of the first film row.