CS 27.479 Level landing conditions

• ED Decision 2003/15/RM found in: CS-27 Amdt 10 - Small Rotorcraft (Feb 2023)

CS 27.479 Level landing conditions ED Decision 2003/15/RM (a) *Attitudes*. Under each of the loading conditions prescribed in sub-paragraph (b), the rotorcraft is assumed to be in each of the following level landing attitudes: (1) An attitude in which all wheels contact the ground simultaneously. (2) An attitude in which the aft wheels contact the ground with the forward wheels just clear of the ground. (b) *Loading conditions*. The rotorcraft must be designed for the following landing loading conditions: (1) Vertical loads applied under [CS 27.471](#_DxCrossRefBm8893858). (2) The loads resulting from a combination of the loads applied under sub-paragraph (b)(1) with drag loads at each wheel of not less than 25% of the vertical load at that wheel. (3) If there are two wheels forward, a distribution of the loads applied to those wheels under sub-paragraphs (b)(1) and (2) in a ratio of 40:60. (c) *Pitching moments*. Pitching moments are assumed to be resisted by: (1) In the case of the attitude in sub-paragraph (a)(1), the forward landing gear, and (2) In the case of the attitude in sub-paragraph (a)(2), the angular inertia forces. CS 27.479 Level landing conditions ED Decision 2003/15/RM (a) *Attitudes*. Under each of the loading conditions prescribed in sub-paragraph (b), the rotorcraft is assumed to be in each of the following level landing attitudes: (1) An attitude in which all wheels contact the ground simultaneously. (2) An attitude in which the aft wheels contact the ground with the forward wheels just clear of the ground. (b) *Loading conditions*. The rotorcraft must be designed for the following landing loading conditions: (1) Vertical loads applied under [CS 27.471](#_DxCrossRefBm472493289). (2) The loads resulting from a combination of the loads applied under sub-paragraph (b)(1) with drag loads at each wheel of not less than 25% of the vertical load at that wheel. (3) If there are two wheels forward, a distribution of the loads applied to those wheels under sub-paragraphs (b)(1) and (2) in a ratio of 40:60. (c) *Pitching moments*. Pitching moments are assumed to be resisted by: (1) In the case of the attitude in sub-paragraph (a)(1), the forward landing gear, and (2) In the case of the attitude in sub-paragraph (a)(2), the angular inertia forces.