Таблица начальных условий
| Angle of attack | 2,19 |
| Pressure altitude | 15899,67 |
| Indicated airspeed | 288,02 |
| Roll Euler angle | -0,14 |
| Pitch Euler angle | 6,18 |
| Vertical speed indication | 2547,67 |
| Left-right stab trim indicator | -2,78 |
| Engine N1 | 98,49 |
| Elevator deflection | 0,75 |
| Aileron deflection | -0,19 |
| Rudder deflection | 0,00 |
| Absolute value of sideslip angle | 0,00 |
| Speed Brake Position - Variable | 0,00 |
| Windshear active flag | 0,00 |
| Aircraft upset active | 0,00 |
| Roll Rate | 0,05 |
| Pitch Rate | 0,00 |
| Yaw Rate | -0,01 |
| N2RPM Engine N2 | 98,49 |
| N1RPM Engine N1 | 98,49 |
| Vertical deviation from glidepath | 0,00 |
| Horizontal deviation | 0,00 |
| Roll acceleration - Body axis | 0,00 |
| Pitch acceleration - Body axis | 0,00 |
| Yaw acceleration - Body axis | 0,00 |
| Roll Acceleration | 0,00 |
| Pitch Acceleration | 0,00 |
| Yaw Acceleration | 0,00 |