Text in force at CS29-12: from CS29-0, effective 14 Nov 2003.
(a) Attitudes. Under each of the loading conditions prescri bed i n sub-paragraph (b) , the rotorcraft is assum ed to be in each of the following level landing attitudes:
(1) An attitude in which each wheel contacts the ground simultaneously.
(2) An attitude in wh ich th e aft wh eels contact the ground with the forward wheels just clear of the ground.
(b) Loading conditions. The rotorcraft m ust be desi gned for t he fol lowing l anding loading conditions:
(1) Vertical l oads appl ied under CS 29.471.
(2) The loads resulting from a combination of t he l oads applied under sub-paragraph (b) (1) with drag loads at each wheel of not less than 25% of t he vertical load at that wheel.
(3) The vertical load at the instant of peak drag load com bined with a drag component si mulating t he forces requi red t o accelerate the wheel rolling assem bly up to the specified ground speed, with:
(i) The ground speed for determination of the spi n-up l oads bei ng at l east 75% of t he opt imum forward flight speed for m inimum rat e of descent in autorotation; and
(ii) The loading conditions of sub-paragraph (b) appl ied t o t he l anding gear and its attaching structure only.
(4) If there are two wheels forward, a distribution of the loads applied to those wheels under sub-paragraphs (b)(1) and (2) i n a rat io of 40:60.
(c) Pitching moments. Pi tching m oments are assumed to be resisted by:
(1) In the case o f th e attitu de in su b-paragraph (a)(1), the forward landing gear; and
(2) In the case o f th e attitu de in su b-paragraph (a)(2), the angular inertia forces.
ED Decision 2003/016/RM · Source