A gas turbine engine comprising: a compressor section configured to rotate about an axis (A-A); a combustor aft of the compressor section and in fluid communication with the compressor section; a turbine section aft of the combustor and configured to extract energy from combusted gas; an engine case disposed about a high pressure compressor of the compressor section, the engine case comprising: a first half having a first semiannular geometry, with a first flange located at a first circumferential edge of the first half; a second half having a second semiannular geometry, with a second flange located at a second circumferential edge of the second half, wherein the second flange is aligned with the first flange and mechanically coupled to the first flange using fasteners; a third flange located at a third circumferential edge of the first half; and a fourth flange located at a fourth circumferential edge of the second half, wherein the third flange is aligned with the fourth flange and mechanically coupled to the fourth flange using fasteners; a first seam defined by the first flange and the second flange; and a second seam defined by the third flange and the fourth flange, wherein the first seam is substantially vertically aligned with the second seam, wherein the engine case comprises an annular geometry; and wherein the first flange and the second flange extend axially along the first half and the second half respectively to define corresponding first mating surfaces that extend the axial length of the first half and the second half, respectively; characterised by an engine mounting point disposed on the gas turbine engine; wherein the engine mounting point is axially forward of the engine case; and wherein the engine mounting point is substantially aligned with the same vertical plane as the first and second seams. a compressor section configured to rotate about an axis (A-A); a combustor aft of the compressor section and in fluid communication with the compressor section; a turbine section aft of the combustor and configured to extract energy from combusted gas; an engine case disposed about a high pressure compressor of the compressor section, the engine case comprising: a first half having a first semiannular geometry, with a first flange located at a first circumferential edge of the first half; a second half having a second semiannular geometry, with a second flange located at a second circumferential edge of the second half, wherein the second flange is aligned with the first flange and mechanically coupled to the first flange using fasteners; a third flange located at a third circumferential edge of the first half; and a fourth flange located at a fourth circumferential edge of the second half, wherein the third flange is aligned with the fourth flange and mechanically coupled to the fourth flange using fasteners; a first seam defined by the first flange and the second flange; and a second seam defined by the third flange and the fourth flange, wherein the first seam is substantially vertically aligned with the second seam, wherein the engine case comprises an annular geometry; and wherein the first flange and the second flange extend axially along the first half and the second half respectively to define corresponding first mating surfaces that extend the axial length of the first half and the second half, respectively; characterised by an engine mounting point disposed on the gas turbine engine; wherein the engine mounting point is axially forward of the engine case; and wherein the engine mounting point is substantially aligned with the same vertical plane as the first and second seams. a first half having a first semiannular geometry, with a first flange located at a first circumferential edge of the first half; a second half having a second semiannular geometry, with a second flange located at a second circumferential edge of the second half, wherein the second flange is aligned with the first flange and mechanically coupled to the first flange using fasteners; a third flange located at a third circumferential edge of the first half; and a fourth flange located at a fourth circumferential edge of the second half, wherein the third flange is aligned with the fourth flange and mechanically coupled to the fourth flange using fasteners; a first seam defined by the first flange and the second flange; and a second seam defined by the third flange and the fourth flange, wherein the first seam is substantially vertically aligned with the second seam, wherein the engine case comprises an annular geometry; and wherein the first flange and the second flange extend axially along the first half and the second half respectively to define corresponding first mating surfaces that extend the axial length of the first half and the second half, respectively; characterised by an engine mounting point disposed on the gas turbine engine; wherein the engine mounting point is axially forward of the engine case; and wherein the engine mounting point is substantially aligned with the same vertical plane as the first and second seams.