Weight & Balance

intersection of the straight and tapered section 109.7 LEVELING DIAGRAM Figure 6-3 ISSUED: JULY 12, 1995 PA-28R-201, ARROW SECTION 6 WEIGHT AND BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE (continued) (2) The basic empty weight center of gravity (as weighed including optional equipment, full oil and unusable fuel) can be determined by the following formula: C.G. Arm=N (A) + (R ÷ L) (B) inches T Where: TN+R+L 6.5 WEIGHT AND BALANCE DATA AND RECORD The Basic Empty Weight, Center of Gravity Location and Useful Load listed in Figure 6-5 are for the airplane as licensed at the factory. These figures apply only to the specific airplane serial number and registration number shown. The basic empty weight of the airplane as licensed at the factory has been entered in the Weight and Balance Record (Figure 6-7). This form is provided to present the current status of the airplane basic empty weight and a complete history of previous modifications. Any change to the permanently installed equipment or modification which affects weight or moment must be entered in the Weight and Balance Record. ISSUED: JULY 12, 1995 REPORT: VB-1612 6-5 SECTION 6 WEIGHT AND BALANCE PA-28R-201, ARROW 6.5 WEIGHT AND BALANCE DATA AND RECORD (continued) MODEL PA-28R-201 ARROW Airplane Serial Number Registration Number Date AIRPLANE BASIC EMPTY WEIGHT C.G. Arm Item Weight x (Lbs) (Inches Aft = Moment of Datum) (In-Lbs) Actual Standard Empty Weight* Computed Optional Equipment Basic Empty Weight *The standard empty weight includes full oil capacity and 5.0 gallons of unusable fuel. AIRPLANE USEFUL LOAD - NORMAL CATEGORY OPERATION (Gross Weight) - (Basic Empty Weight) = Useful Load (2750 lbs) - ( lbs) = lbs THIS BASIC EMPTY WEIGHT, C.G,. AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. · WEIGHT AND BALANCE DATA FORM REPORT: VB-1612 6-6 Figure 6-5 ISSUED: JULY 12, 1995 ISSUED: JULY 12, 1995 PA-28R-201 Serial Number Date Item No. Description of Article or Modification WEIGHT AND BALANCE RECORD Figure 6-7 REPORT: VB-1612 6-7 As Licensed Moment 100 Registration Number Weight Change Page Number Running Basic Empty Weight Added (+) Removed (-). Wt. Arm Moment (Lb.) (In.) 100 Wt. (Lb.) PA-28R-201, ARROW WEIGHT AND BALANCE 6.5 WEIGHT AND BALANCE DATA AND RECORD (continued) SECTION 6 REPORT: VB-1612 6-8 PA-28R-201 Serial Number Date Item No. Description of Article or Modification WEIGHT AND BALANCE RECORD (cont) Figure 6-7 (cont) ISSUED: JULY 12, 1995 Page Number Running Basic Empty Weight SECTION 6 WEIGHT AND BALANCE PA-28R-201. ARROW 6.5 WEIGHT AND BALANCE DATA AND RECORD (continued) Arm (l.b.) (In.) : 100 Wt. (Lb.) Moment 100 Registration Number Wt. Weight Change Moment Removed (-) Added (+) PA-28R-201, ARROW SECTION 6 WEIGHT AND BALANCE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane. (c) Add the moment of all items to be loaded to the basic empty weight moment. (d) Divide the total moment by the total weight to determine the C.G. location. (e) By using the figures of item (a) and item (d) (above), locate a point on the C.G. range and weight graph (Figure 6-15). If the point falls within the C.G. envelope, the loading meets the weight and balance requirements. Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight 1890 84.8 160272 Pilot and Front Passenger 340.0 80.5 27370 Passengers (Rear Seats) 170.0 118.1 20077 Fuel (72 Gallons Maximum) 294 95.0 27930 Baggage (200 Lbs. Maximum) 64 142.8 9139 Ramp Weight (2758 Lbs. Maximum) 2758 88.76 244788 Fuel Allowance For Engine Start, Taxi, and Run-Up -8 95.0 -760 Moment due to Retraction of Landing Gear 819 Takeoff Weight (2750 Lbs. Maximum) 2750 89.04 244847 The center of gravity (C.G.) of this sample loading problem is at 89.04 inches aft of the datum line. Locate this point (89.04) on the C.G. range and weight graph. Since this point falls within the weight - C.G. envelope, this loading meets the weight and balance requirements. IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY. SAMPLE LOADING PROBLEM (NORMAL CATEGORY) Figure 6-9 ISSUED: JULY 12, 1995 REPORT: VB-1612 6-9 SECTION 6 WEIGHT AND BALANCE PA-28R-201, ARROW 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (continued) Basic Empty Weight Pilot and Front Passenger Passengers (Rear Seats) Fuel (72 Gallons Maximum) Baggage (200 Lbs. Maximum) Ramp Weight (2758 Lbs. Maximum) Fuel Allowance For Engine Start, Taxi, and Run-Up Moment due to Retraction of Landing Gear Takeoff Weight (2750 Lbs. Maximum) Weight (Lbs) Arm Aft Datum Moment (Inches) (In-Lbs) 80.5 118.1 95.0 142.8 -8 95.0 -760 819 Totals must be within approved weight and C.G. limits. It is the responsibility of the airplane owner and the pilot to insure that the airplane is loaded properly. The Basic Empty Weight C.G. is noted on the Weight and Balance Data Form (Figure 6-5). If the airplane has been altered, refer to the Weight and Balance Record for this information. WEIGHT AND BALANCE LOADING FORM Figure 6-11 REPORT: VB-1612 5-10 ISSUED: JULY 12, 1995 LOAD WEIGHT (POUNDSĮ PA-28R-201, ARROW SECTION 6 WEIGHT AND BALANCE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (continued) 450 400 150 300 250 200 160 100 50 FUEL (6 LEGALL 1 PASSENGER 10 16 20 MOMENT/1000 [INCH 25 30 POUNDS) 35 40 45 50 ISSUED: JULY 12, 1995 LOADING GRAPH Figure 6-13 REPORT: VB-1612 6-11 WEIGHT - LB. SECTION 6 WEIGHT AND BALANCE PA-28R-201. ARRO 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (continued) 3000 2800 2750 LB MAX. WEIGHT F.S. 88.9 2600 2400 2375 LB 2200 2000 1800 1600 1400 80 REPORT: VB-1612 6-12 FWD LIMIT-82: . 82 84 86 INCHES AFT OF DATUM 88 90 8 C. G RANGE AND WEIGHT Figure 6-15 AFT LIMIT 91. 92 94 ISSUED: JULY 12, 1995