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(1) Unit weight for weight and balance purposes. Gasoline ----------- 6 pounds per U.S. gal. Turbine Fuel ------ 6.7 pounds per U.S. gal. Lubricating oil ---- 7.5 pounds per U.S. gal. Crew and passengers ----- 170 pounds per person. (2) It is important to retain the proper algebraic sign (+ or -) through all balance computations. For the sake of uniformity in these computations, visualize the aircraft with the nose to the left. In this position any arm to the left (forward) of the datum is “minus” and any arm to the right (rearward) of the datum is “plus.” Any item of weight added to the air craft either side of the datum is plus weight, any weight item removed is a minus weight. When multiplying weights by arms, the answer is plus if the signs are the same, and minus if the signs are different. The following combi nations are possible: Items added forward of the datum ( + ) weight x ( - ) arm = ( - ) moment. Items added to the rear of the datum (+)weight x(+)arm=(+)moment. Items removed forward of the datum (-)weightx(-)arm=(+)moment. Items removed rear of the datum (-)weightx(+)arm=(-)moment. (3) The total weight of the airplane is equal to the weight of the empty aircraft plus the weight of the items added minus the weight of the items removed. (4) The total moment of the aircraft is the algebraic sum of the empty weight moment of the aircraft and all of the individual mo ments of the items added and/or removed. 10-17. WEIGHT AND BALANCE EX- TREME CONDITIONS. The weight and balance extreme conditions represent the maximum forward and rearward c.g. position for the aircraft. Include the weight and balance data information showing that the c.g. of the aircraft (usually in the fully loaded condition) falls between the extreme conditions. a. Forward Weight and Balance Check. When a forward weight and balance check is made, establish that neither the maximum weight nor the forward c.g. limit listed in the TCDS and Aircraft Specifications are ex ceeded. To make this check, the following in formation is needed: (1) The weights, arms, and moment of the empty aircraft. (2) The maximum weights, arms, and moments of the items of useful load that are located ahead of the forward c.g. limit. (3) The minimum weights, arms, and moments of the items of useful load that are located aft of the forward c.g. limit. A typical example of the computation necessary to make this check, using this data, is shown in fig ure 10-10. b. Rearward Weight and Balance Check. When a rearward weight and balance check is made, establish that neither the maximum weight nor the rearward c.g. limit listed in the TCDS and Aircraft Specifications are exceeded. To make this check, the fol lowing information is needed: (1) The weight, arms, and moments of the empty aircraft. (2) The maximum weights, arms, and moments of the items of useful load that are located aft of the rearward c.g. limit.PDF Image | AFS-640
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