AMC 25.147(d) Lateral control: Roll capability

• ED Decision 2003/2/RM found in: CS-25 Amdt 27 - Large Aeroplanes (Jan 2023)

AMC 25.147(d) Lateral control: Roll capability ED Decision 2003/2/RM An acceptable method of demonstrating compliance with [CS 25.147(d)](#_DxCrossRefBm1709820699) is as follows: With the aeroplane in trim, all as nearly as possible,in trim, for straight flight at V2, establish a steady 30° banked turn. It should be demonstrated that the aeroplane can be rolled to a 30° bank angle in the other direction in not more than 11 seconds. In this demonstration, the rudder may be used to the extent necessary to minimise sideslip. The demonstration should be made in the most adverse direction. The manoeuvre may be unchecked. Care should be taken to prevent excessive sideslip and bank angle during the recovery. Conditions: Maximum take-off weight. Most aft c.g. position. Wing-flaps in the most critical take-off position. Landing Gear retracted. Yaw SAS on, and off, if applicable. Operating engine(s) at maximum take-off power. The inoperative engine that would be most critical for controllability, with the propeller (if applicable) feathered. Note: Normal operation of a yaw stability augmentation system (SAS) should be considered in accordance with normal operating procedures.