§3.245 Level landing—.

(a) Tail wheel type.Normal level flight attitude. (b) Nose wheel type. Two cases shall be considered: (1) Nose and main wheels contacting the ground simultaneously, (2) Main wheels contacting the ground, nose wheel just clear of the ground. (The angular attitude may be assumed the same as in subparagraph (1) of this paragraph for purposes of analysis.) (c) Drag components. In this condition, drag components simulating the forces required to accelerate the tires and wheels up to the landing speed shall be properly combined with the corresponding instantaneous vertical ground ontacting ground simultaneously. reactions. The wheel spin-up drag loads may be based on vertical ground reactions, assuming wing lift and a tire-sliding coefficient of friction of 0.8, but in any case the drag loads shall not be less than 25 percent of the maximum vertical ground reactions neglecting wing lift. LIMIT PILOT LOADS Control Maximum loads for design weight W equal to or less than 5,000 lbs.1 Minimum loads.2 Aileron: Stick 67 pounds 40 pounds. Wheel3 53 D in-pounds4 40 D in-pounds Elevator: Stick 167 pounds 100 pounds. Wheel 200 pounds 100 pounds. Rudder 200 pounds 130 pounds. 1For design weight W greater than 5,000 pounds the above specified maximum values shall be increased linearly with weight to 1.5 times the specified values at a design weight of 25,000 pounds. 2If the design of any individual set of control systems or surfaces is such as to make these specified minimum loads inapplicable, values corresponding to the pertinent binge moments obtained according to §