diff --git a/docs/documentation/analysis/weight_and_balance_analysis/basic-concepts.md b/docs/documentation/analysis/weight_and_balance_analysis/basic-concepts.md
index b015448c0b120ef27e63eac4f26c1dddff9a19e6..fb10b53995cd12515527db679a1abbc521d96d92 100644
--- a/docs/documentation/analysis/weight_and_balance_analysis/basic-concepts.md
+++ b/docs/documentation/analysis/weight_and_balance_analysis/basic-concepts.md
@@ -163,13 +163,19 @@ Where:
 - $f_{xx}$ and $f_{yy}$: Technology factors set to $1.25$ respectively $1.15$   
 - $ R_x, R_y, R_z $: Nondimensional radii of gyration. The following values are implemented:
 
-| **Aircraft Configuration**                      | $ R_x $ | $ R_y $ | $ R_z $ |
-|-----------------------------------------|-----------|-----------|-----------|
-| Fuselage-mounted engines                | 0.24      | 0.34      | 0.42      |
-| 2 wing-mounted engines                  | 0.23      | 0.33      | 0.45      |
-| 4 wing-mounted engines                  | 0.24      | 0.36      | 0.44      |
-| Blended wing body                       | 0.28      | 0.40      | 0.46      |
+| **Aircraft Configuration**                    | $ R_x $ | $ R_y $ | $ R_z $ |
+|---------------------------------------------|-----------|-----------|-----------|
+| Single prop engine                          | 0.25      | 0.38      | 0.39      |
+| Twin prop engine                            | 0.30      | 0.40      | 0.44      |
+| 2 fuselage-mounted jet engines              | 0.24      | 0.34      | 0.42      |
+| 2 wing-mounted jet engines                  | 0.23      | 0.33      | 0.45      |
+| 4 wing-mounted jet engines                  | 0.24      | 0.36      | 0.44      |
+| Blended wing body                           | 0.28      | 0.40      | 0.46      |
 
+The aircraft configuration is determined based on the data from the TLARs. For this, the information about the possible propulsion types, mounting positions and number of engines are used.
+
+!!! note 
+    If no matching radii of gyration are found, a critical message is shown and the values for the radii are set to the ones for a jet with two wing mounted engines to keep the workflow running. It is the user's responsability to check the validity of the chosen calculation methods and the results.
 
 #### 2. Using the LTH Tables (*Luftfahrttechnisches Handbuch*) 
 The LTH provides tabulated values and empirical methods specific to various aircraft configurations. These tables account for typical mass distributions and structural layouts. They are more accurate than Raymer’s approach but require knowledge of the specific aircraft class and design. The `calculate_inertia_by_lth_method` function is tailored specifically for conventional tube-and-wing configurations. This method uses aircraft mass properties like the OEM, the payload mass ($m_{payload}$) and the fuel mass ($m_{fuel}$) and geometric dimensions such as wing span $b$ and fuselage length $l$. All cross-product terms ($I_{xy}$, $I_{xz}$, etc.) are set to $0$, assuming symmetry.