CS 25.519 Jacking and tie-down provisions

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

CS 25.519 Jacking and tie-down provisions ED Decision 2003/2/RM (a) *General*. The aeroplane must be designed to withstand the limit load conditions resulting from the static ground load conditions of sub-paragraph (b) of this paragraph and, if applicable, sub-paragraph (c) of this paragraph at the most critical combinations of aeroplane weight and centre of gravity. The maximum allowable load at each jack pad must be specified. (b) *Jacking*. The aeroplane must have provisions for jacking and must withstand the following limit loads when the aeroplane is supported on jacks: (1) For jacking by the landing gear at the maximum ramp weight of the aeroplane, the aeroplane structure must be designed for a vertical load of 1·33 times the vertical static reaction at each jacking point acting singly and in combination with a horizontal load of 0·33 times the vertical static reaction applied in any direction. (2) For jacking by other aeroplane structure at maximum approved jacking weight: (i) The aeroplane structure must be designed for a vertical load of 1·33 times the vertical reaction at each jacking point acting singly and in combination with a horizontal load of 0·33 times the vertical static reaction applied in any direction. (ii) The jacking pads and local structure must be designed for a vertical load of 2·0 times the vertical static reaction at each jacking point, acting singly and in combination with a horizontal load of 0·33 times the vertical static reaction applied in any direction. (c) *Tie-down.* If tie-down points are provided, the main tie-down points and local structure must withstand the limit loads resulting from a 120 km/h (65-knot) horizontal wind from any direction.