Text in force at CS29-12: from CS29-0, effective 14 Nov 2003.
(a) General. Rotorcraft with lan ding g ear with two wheels forward and one wheel aft of the centre of gravi ty m ust be designed for loading conditions as prescribed in this paragraph..
(b) Level landing attitude with only the forward wheels contacting the ground. In th is attitude:
(1) The vertical loads m ust be applied under CS 29.471 to CS 29.475;
(2) The vertical load at each axle m ust be combined with a drag load at that axle of not less than 25% of that vertical load; and
(3) Unbalanced pitching m oments are assumed to be resisted by angular inertia forces.
(c) Level landing attitude with all wheels contacting the ground simultaneously. In this attitude, the ro torcraft m ust b e d esigned fo r landing l oading condi tions as prescri bed in sub-paragraph (b).
(d) Maximum nose-up attitude with only the rear wheel contacting the ground. The attitude for this condition m ust be t he m aximum nose-up attitude ex pected in n ormal o peration, including autorotative landings. In this attitude:
(1) The appropriate ground l oads specified in sub-paragraphs (b)(1) and (2) m ust be det ermined and appl ied, usi ng a rat ional method to account for the moment arm between the rear wheel ground reaction and the rotorcraft centre of gravity; or
(2) The p robability o f lan ding with initial contact on the rear wh eel must be shown to be extremely remote.
(e) Level landing attitude with only one forward wheel contacting the ground. In th is attitude, the ro torcraft m ust b e d esigned fo r ground loads as specified in sub-paragraphs (b)(1) and (3).
(f) Side loads in the level landing attitude. In the attitu des sp ecified in su b-paragraphs (b ) and (c), the following apply:
(1) The side loads m ust be com bined at each wheel with one-half of the m aximum vertical ground reactions obtained for that wheel under sub-paragraphs (b) and (c). In t his condition, the side loads must be:
(i) For the forward wheels, 0.8 times the vert ical react ion (on one si de) acting inward and 0.6 t imes t he vert ical reaction (on the ot her si de) act ing outward; and
(ii) For the rear wheel, 0.8 tim es the vertical reaction.
(2) The loads specified in sub-paragraph (f)(1) must be applied:
(i) At t he ground cont act point with th e wh eel in th e trailin g position (for non-full swi velling l anding gear or for ful l swivelling lan ding g ear with a lock, steering device, or shi mmy damper to keep the wheel in the trailing position); or
(ii) At the centre of the axle (for full swivelling landing gear without a lock, steering device, or shimmy damper).
(g) Braked roll conditions in the level landing attitude. In the attitu des sp ecified in su b-paragraphs (b) and (c), and wi th t he shock absorbers in th eir static p ositions, the rotorcraft must be designed for braked roll loads as follows:
(1) The limit vertical load must be based on a limit vertical load factor of not less than:
(i) 1.0, for the attitude specified in sub-paragraph (b); and
(ii) 1.33, for th e attitu de sp ecified in sub-paragraph (c).
(2) For each wheel with brakes, a drag load must be appl ied, at t he ground cont act point, of not less than the lesser of:
(i) 0.8 times the vertical load; and
(ii) The maximum based on limiting brake torque.
(h) Rear wheel turning loads in the static ground attitude. In the static ground attitude, and with the shock absorbers an d tyres in th eir static positions, the rotorcraft must be desi gned for rear wheel turning loads as follows:
(1) A vertical ground reaction equal to the static load on the rear wheel m ust be combined with an equal side load.
(2) The load specified in sub-paragraph (h)(1) must be applied to the rear landing gear:
(i) Through the axle, i f t here i s a swivel (the rear wheel being assumed to be swiv elled 9 0°, to th e lo ngitudinal ax is of the rotorcraft); or
(ii) At t he ground cont act poi nt i f there is a lock, steering device or shim my damper (t he rear wheel bei ng assum ed t o be in the trailing position).
(i) Taxying condition. The rotorcraft and its landing gear must be desi gned for t he l oads t hat would occur when the rotorc raft is taxied over the roughest ground t hat m ay reasonabl y be expect ed in normal operation.
ED Decision 2003/016/RM · Source