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This can be the one booklet on hand this present day that covers army and advertisement airplane touchdown equipment layout. it's a finished textual content that might lead scholars and engineers from the preliminary ideas of touchdown equipment layout via ultimate element layout. The e-book presents a necessary hyperlink in touchdown apparatus layout know-how from historic practices to trendy layout tendencies, and it considers the mandatory airfield interface with touchdown equipment layout. The textual content is subsidized up by way of calculations, necessities, references, operating examples.
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Extra info for Aircraft Landing Gear Design: Principles and Practices (AIAA Education Series)
In addition to the above, the FAR has the following requirements. ,N i.. < 0 u 0 i-, >. , o. , ~ ~ "-" . ~ 0 ~ ~*'* ¢1 ~ ~'2. 0 :::= o *" ~ ~'~ t'~ ~ =,~ ~ o= ~ ~ . 9. ~, =_ ,~ o. ~, '-~ - ~ . ~ 1 . ,q ~8 L. a . , >,=6 o. r,h A) 35 stops at average i of 10 ft/s 2 e,g,h Source: AS 227. aSea level power-off stalling speed at design landing weight and configuration. bOne change of friction materials is permissible in meeting the 66 stops. For other than friction materials, the assembly shall withstand the 65 stops without failure or impairment of operation.
4 k B-727 \ " . ~4 • Flap, aileron, k ~ nacelle \\\~contact Fig. 11 Pitch and roll limitation diagram. ~ 2 m 0 0 m i 2 4 Aircraft t. / I1. :. , m z..... J ~F--. IF- T¢: 41 I el 42 AIRCRAFT LANDING GEAR DESIGN The following checks are suggested: I) Are the nose and main gear shock struts operating properly and the tires at normal inflation? 2) Is the nose gear shock strut fully compressed and the tire flat? Is the main gear shock strut fully compressed and the tire flat on one side, with static deflection and normal tire inflation on the other side?
G. g. along these lines. g. position is generally of little importance in the determination of aircraft configurations, its position will probably not have been calculated at this stage and a "guesstimate" must be made. , so if the aircraft is, for instance, a high-wing cargo aircraft, an approximate calculation will be made assuming full wing fuel and no cargo. A low-wing passenger aircraft would be critical with no wing fuel and a full load of passengers. In step 4, from observations of wing spar locations and other structure, the main gear is placed in a position that appears to be the most conducive to the efficient transmission of loads.