mtom = design_mass_takeoff

weight_and_balance_analysis/src/tube_and_wing/standard/basic/methodbasic.py

@@ -175,10 +175,11 @@ def method_basic(paths_and_names, routing_dict, dict_ac_exchange, dict_mod_confi
     ).print("Design mass takeoff")
 
     # Maximum takeoff mass
-    maximum_takeoff_mass = copy.copy(design_mass)
+    maximum_takeoff_mass = copy.copy(design_mass_takeoff)
     maximum_takeoff_mass.path_to_element = "./analysis/masses_cg_inertia/maximum_takeoff_mass"
     maximum_takeoff_mass.cg_mac = (
-        design_mass.center_of_gravity['x'] - x_leading_edge_mac) / mac * 100
+        design_mass_takeoff.center_of_gravity['x'] - x_leading_edge_mac) / mac * 100
+    maximum_takeoff_mass.print("Maximum takeoff mass")
 
     # Maximum payload + fuel up to MTOW
     mtow_max_payload_mass = calculate_mtow_max_payload(