A method of producing a gas turbine engine fan blade having a geometric configuration, the method comprising: plastically deforming an initial substrate comprised of a first metallic material into a formed substrate that has a first face surface , a second face surface , which first face surface is opposite the second face surface , a first end surface and a second end surface , which second end surface is opposite the first end surface ; and depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface , to form a root portion ; depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion ; depositing second metallic material to the first face surface of the formed substrate between the root portion and the airfoil portion , and to the second face surface of the formed substrate between the root portion and the airfoil portion to form a platform portion ; and shaping the blade blank into the geometric configuration of the gas turbine engine fan blade . plastically deforming an initial substrate comprised of a first metallic material into a formed substrate that has a first face surface , a second face surface , which first face surface is opposite the second face surface , a first end surface and a second end surface , which second end surface is opposite the first end surface ; and depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface , to form a root portion ; depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion ; depositing second metallic material to the first face surface of the formed substrate between the root portion and the airfoil portion , and to the second face surface of the formed substrate between the root portion and the airfoil portion to form a platform portion ; and shaping the blade blank into the geometric configuration of the gas turbine engine fan blade . depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface , to form a root portion ; depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion ; depositing second metallic material to the first face surface of the formed substrate between the root portion and the airfoil portion , and to the second face surface of the formed substrate between the root portion and the airfoil portion to form a platform portion ; and shaping the blade blank into the geometric configuration of the gas turbine engine fan blade . <EOS>