By Federal Aviation Administration (FAA)/Aviation Supplies & Academics (ASA)
Basic airplane weight and stability keep watch over rules and approaches for the education, and the particular weighing of an plane begin the dialogue, together with the equipment of choosing the positioning of the empty weight middle of gravity. Loading computations with loading graphs and tables of weight and second indexes stick with, together with directions on choosing the burden and middle of gravity alterations as a result of upkeep and adjustments or removing and set up of apparatus. Chapters are devoted to light-sport airplane, single-engine plane, multi-engine airplane, and commuter and big plane, in addition to helicopter weight and stability regulate and identifying 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 variation displays the most recent aviation approaches, gear, strategies, laws, and is a key reference within the FAA Airman Certification criteria (ACS). Illustrated all through with specified, full-color drawings, and encompasses a word list and index.
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Extra info for Aircraft Weight and Balance Handbook: FAA-H-8083-1A
The pages should be signed by the person making the revision and his or her certificate type and number must be included. The computations for a weight and balance revision are included on a weight and balance revision form. The date those computations were made is shown in the upper right-hand corner of Figure 5-2. ” Appropriate fore-and-aft extreme loading conditions should be investigated and the computations shown. Weight Changes Caused by a Repair or Alteration A typical alteration might consist of removing two pieces of radio equipment from the instrument panel, and a power supply that was located in the baggage compartment behind the rear seat.
Cargo Forward hold.............................. 1,500 lbs Aft hold...................................... 2,500 lbs Fuel Tank 1 & 3...................... 10,500 lbs each Tank 2...................................... indd 2 3/13/07 11:03:11 AM Figure 7-2. Loading schedule for determining weight and CG. indd 3 3/13/07 11:03:13 AM Determining the Correct Stabilizer Trim Setting It is important before takeoff to set the stabilizer trim for the existing CG location. There are two ways the stabilizer trim setting systems may be calibrated: in % MAC, and in Units ANU (Airplane Nose Up).
The CG is determined by dividing the total moment by the total weight. 8 inches behind the datum. Two Ways to Express CG Location Figure 3-3. The datum is located at the firewall. Determine the CG by adding the weight and moment of each weighing point to determine the total weight and total moment. Then divide the total moment by the total weight to determine the CG relative to the datum. The location of the CG may be expressed in terms of inches from a datum specified by the aircraft manufacturer, or as a percentage of the MAC.
Aircraft Weight and Balance Handbook: FAA-H-8083-1A by Federal Aviation Administration (FAA)/Aviation Supplies & Academics (ASA)