§3.267 Local bottom pressures—.

(a) Maximum local pressure. The maximum value of the limit local pressure shall be determined from the following equation: where P = pressure in pound per square inch. Vs0 = stalling speed, flaps down, power off, in miles per hour (to be calculated on the basis of wind tunnel data or flight tests on previous airplanes). W = design weight. (b) Variation in local pressure. The local pressures to be applied to the hull bottom shall vary in accordance with Figure 3-13. No variation from keel to chine (beamwise) shall be assumed, except when the chine flare indicates the advisability of higher pressures at the chine. Tail wheel hype Nose wheel Iype Level Tailedown Level landing Level landing wilh Tail-dewn Condition landing landing wilh inclined nese Wheel jis clear landing roneclions of sro Relérenes soelinn----- 38.24Mai gA.24aC $2245 (hihi y A245 Chi i) $ A246 chifes VYenical component al Pe aif if iF iF Uhbemen cn eee ee eeee cece ee Fore aid all component Kit ni Rae Rae hn WD Da eeen en ene eee eee eee Laleral component in n ni i i TY cilher direction ale. Shock whsorher extension Chydranlic shock absaor hert--------- Mole (21 Mule 124 Nolew24 Mule 124 Nolo .24 Shock ahsorher delleclion inibher or Spring shock absorber t------ ---------- [os, pny. LH. [nny Pan. Tire defleclion------------ Stal iv Stalic Shalic Stalic Shalic Main wheel leads fholli whoels)------------- “1¥, vik hd ait had vit nit 11, Ky hi Ky. Kv. ni Tail tnoser whee! loads wen nee nee ee eee eee eee PY n Rac vifaad "i " Dy " "i Kye tt "i Mul ts-- ----- ---- ----------- tliaml saa | -------------- tli Cliand (34 34 Mele la— may be determined as fellows: Ae 28 for P23 20 pounds or less; R33 for 6 ponds ar sreader silh linear vanialion oh K bebeesen tess weiglils. Neale t 23.—Por the puceose of design, the maxiniin load Melor shall be assuined fe eecur throng taut the shock absorber slroke [ram 25 pereen! defection lo 10 percent deflection unless demonstrated otherwise, aid the load factor shall be rrsed wilh whatever shock absorber extension is mest erilicnl for cach element of the binding gear. Nelo (24—Lnhalaneed montents shall be balanesd ber a ration! ar conservaire inethed. PEG. A-L2tu pee BASE! LANBDENC? CONBTFIONS ot “nn kK VSEe NOTE T LEVEL LANDING HOSE WHEEL TYPE - Tan x REVEL CaNdi4G WITH ACLIGED KLatTrONS nk. . se nose Ss ROTUS F< F1G. BASIC LANDING CONDITIONS %- §2¢b) NOTE. CLEAR OF ORGIND SCG OTE > LEVEL LANDIND WITH NWOSE WHEEL dUST FIG. 3-13 OLSTRIBUTION OF LOGAL PRESSURES {BOAT SEAPLANES} consideration of the inertia loads which resist the linear and angular accelerations involved. To avoid excessive local shear loads, the water reaction may be distributed over the hull bottom, using pressures not less than those specified in § 3.268.