CS 25.473 Landing load conditions and assumptions

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

CS 25.473 Landing load conditions and assumptions ED Decision 2003/2/RM (a)For the landing conditions specified in [CS 25.479](#_DxCrossRefBm1709820980) to [25.485](#_DxCrossRefBm1709821007), the aeroplane is assumed to contact the ground: (1) In the attitudes defined in [CS 25.479](#_DxCrossRefBm1709820980) and [CS 25.481](#_DxCrossRefBm1709820925). (2) With a limit descent velocity of 3·05 m/sec (10 fps) at the design landing weight (the maximum weight for landing conditions at maximum descent velocity); and (3) With a limit descent velocity of 1·83 m/sec (6 fps) at the design take-off weight (the maximum weight for landing conditions at a reduced descent velocity). (4) The prescribed descent velocities may be modified if it is shown that the aeroplane has design features that make it impossible to develop these velocities. (b) Aeroplane lift, not exceeding aeroplane weight, may be assumed, unless the presence of systems or procedures significantly affects the lift. (c) The method of analysis of aeroplane and landing gear loads must take into account at least the following elements: (1) Landing gear dynamic characteristics. (2) Spin-up and spring back. (3) Rigid body response. (4) Structural dynamic response of the airframe, if significant. (d) The landing gear dynamic characteristics must be validated by tests as defined in [CS 25.723(a)](#_DxCrossRefBm1709821006). (e) The coefficient of friction between the tyres and the ground may be established by considering the effects of skidding velocity and tyre pressure. However, this coefficient of friction need not be more than 0·8.