Using the loading graph [Figure 19-2], the moment/1000 of the pilot is found to be 9.1 pound- inches, and the passenger has a moment/1000 of 13.4 pound-inches.  CENTER OF GRAVITY ENVELOPE Gross Moment in Thousands of LBS-IN. Gross Weight in Pounds (x100) 160 180 190 200 170 15 16 17 18 1. Total Aircraft WeightGLYPH<.notdef> (Less Fuel) ...............................GLYPH<.notdef> GLYPH<.notdef> 3. Fuel........................................... TOTALS GLYPH<.notdef> WeightGLYPH<.notdef> (lbs.) MomentGLYPH<.notdef> (lb.-ins.GLYPH<.notdef> /1,000) 176.4 1,650 11.9 108 188.3 1,758 A f t F o $_{r}$w a $_{r}$d 0 2 4 6 8 10 12 14 16 18 20 1 2 3 Load Weight in P ounds (x100) Load Moment in Thousands of LBS - IN LOADING GRAPH A B C D A = Pilot B = Passenger C = Fuel D = Baggage Figure 19-4. Center of gravity envelope chart. Figure 19-2. A loading graph is used to determine the load moment for weights at various stations. Figure 19-3. Loading of the sample aircraft, less fuel. The maximum gross weight for the sample aircraft is 1,800 pounds, which allows up to 150 pounds to be car- ried in fuel. For this flight, 18 gallons of fuel is deemed sufficient. Allowing six pounds per gallon of fuel, the fuel weight on the aircraft totals 108 pounds. Referring again to the loading graph [Figure 19-2], 108 pounds of fuel would have a moment/1000 of 11.9 pound-inches. This is added to the previous totals to obtain the total aircraft weight of 1,758 pounds and a moment/1000 of 188.3. Locating this point on the center of gravity enve- lope chart [Figure 19-4], shows that the loading is within the prescribed weight and balance limits. For this example, a gyroplane at its maximum gross weight (1,800 lbs.) needs to perform a short field take- off due to obstructions in the takeoff path. Present weather conditions are standard temperature at a pres- sure altitude of 2,000 feet, and the wind is calm. Referring to the appropriate performance chart [Figure 19-5], the takeoff distance to clear a 50-foot obstacle is determined by entering the chart from the left at the pressure altitude of 2,000 feet. You then proceed hori- zontally to the right until intersecting the appropriate temperature reference line, which in this case is the dashed standard temperature line. From this point, descend vertically to find the total takeoff distance to clear a 50-foot obstacle. For the conditions given, this particular gyroplane would require a distance of 940 feet for ground roll and the distance needed to climb 50 feet above the surface. Notice that the data presented in this chart is predicated on certain conditions, such as a running takeoff to 30 m.p.h., a 50 m.p.h. climb speed, a 19-2 The performance section of the flight manual contains data derived from actual flight testing of the aircraft. Because the actual performance may differ, it is pru- dent to maintain a margin of safety when planning operations using this data. Adding these figures, the total weight of the aircraft for this flight (without fuel) is determined to be 1,650 pounds with a moment/1000 of 176.4 pound-inches. [Figure 19-3] PERFORMANCE SECTION SAMPLE PROBLEM Weight MomentGLYPH<.notdef> (pounds) (lb.-in./1,000) Basic Empty WeightGLYPH<.notdef> PilotGLYPH<.notdef> PassengerGLYPH<.notdef> BaggageGLYPH<.notdef> Total Aircraft (Less Fuel) 1,315GLYPH<.notdef> 175GLYPH<.notdef> 160GLYPH<.notdef> 0 1,650 153.9GLYPH<.notdef> 9.1GLYPH<.notdef> 13.4GLYPH<.notdef> 0 176.4 Max Gross Weight =  1,800 lbs .