By Federal Aviation Administration (FAA)/Aviation Supplies & Academics (ASA)
Basic plane weight and stability keep an eye on rules and systems for the education, and the particular weighing of an airplane begin the dialogue, together with the tools of deciding on the positioning of the empty weight heart of gravity. Loading computations with loading graphs and tables of weight and second indexes stick with, together with directions on selecting the burden and middle of gravity adjustments as a result of maintenance and changes or elimination and deploy of apparatus. Chapters are devoted to light-sport plane, single-engine plane, multi-engine airplane, and commuter and big airplane, in addition to helicopter weight and stability keep watch over and selecting lateral CG. additionally incorporated are examples of fixing weight and stability difficulties utilizing a handheld digital calculator, E6-B flight desktop, and a devoted digital flight computer.
This 2016 version displays the most recent aviation tactics, gear, concepts, laws, and is a key reference within the FAA Airman Certification criteria (ACS). Illustrated all through with certain, full-color drawings, and encompasses a thesaurus and index.
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Additional resources for Aircraft Weight and Balance Handbook [FAA-H-8083-1A]
If the shift were forward, the CG change would be negative. 59% MAC. 5% MAC. 36 inches, so the new CG is: When cargo is shifted from one cargo hold to another, the CG changes, but the total weight of the aircraft remains the same.
8 inches aft of the datum. 2 inches forward of the main-wheel weighing points which proves the location of the datum has no effect on the location of the CG so long as all measurements are made from the same location. Datum Aft of the Main Wheels Nose Wheel Landing Gear The datum of some aircraft may be located aft of the main wheels. The airplane in this example is the same one just discussed, but the datum is at the intersection of the trailing edge of the wing with the fuselage. The distance (D) between the datum of the airplane in Figure 3-6 and the main-wheel weighing points is 75 inches, the weight of the nose wheel (F) is 340 pounds, and the distance between main wheels and nose wheel (L) is 78 inches.
13 5. Subtract the removed weight and its moment/1,000 from the original weight and moment/1,000. 1. Determine the CG location in inches from the datum before the cargo is onloaded. Do this by first determining the distance of the CG aft of the LEMAC: 6. Determine the location of the new CG by dividing the total moment/1,000 by the total weight and multiplying this by the reduction factor 1,000. 2. Determine the distance between the CG and the datum by adding the CG in inches aft of LEMAC to the distance from the datum to LEMAC: 7.