Weight & Balance for the Piper PA-34 Seneca V

The following geometry applies to the PA-34-200 airplane when airplane is level. (See Item 2) C. G. ARM Level Points 78.4 + N * REPORT: VB-424 PAGE 4-4 MODEL: PA-34-200 m R+L (Fuselage Left Side Below Window) Full 200 2827 1373 570 3028 40.8 8420 * The datum is 78.4 inches ahead of the wing leading edge at the inboard edge of the inboard fuel tank ank Less ISSUED: March 10, 1972 SENECA b. C. d. Obtain measurement "A" by measuring from a plumb bob dropped from the wing leading edge, at the intersection of the straight and tapered section, horizontally and parallel to the airplane centerline, to the main wheel centerline. Obtain measurement "B" by measuring the distance from the main wheel centerline, horizontally and parallel to the airplane centerline, to each side of the nose wheel axle. Then average the measurements. The empty weight center of gravity (as weighed including optional equipment and undrainable oil) can be determined by the following formula: C.G. Arm = 78.4 + AB(N) T C. G. Arm = 78.4 + ( )-( ) ( )= inches 5. LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY Empty Weight (as weighed) Unusable Fuel (5.0 gallon) Licensed Empty Weight Weight Empty m Weight Arm Moment +30 103.0 +3090 74.9- WEIGHT & BALANCE ABOVE SUPERSEDED 12-18-72: New aircraft empty weight New useful load Superceded 11/20/90 MAL ISSUED: March 10, 1972 2827.2 1172.8 84.87" 239936.47 REPORT: VB-424 PAGE 4-5 MODEL: PA-34-200 SENECA Airplane Serial Number 34- Registration Number Date WEIGHT AND BALANCE DATA MODEL PA-34-200 SENECA AIRPLANE BASIC WEIGHT C. G. Arm Item Weight (Lbs) (Inches Aft = Moment of Datum) (In-Lbs) Standard Empty Weight* Actual Computed Optional Equipment Unusable Fuel (5 gallon) 30 103.0 3090 Licensed Empty Weight = Total of above items Oil (16 quarts) 30 49.0 1470 = Basic Weight Licensed Empty Weight Plus Oil *Standard Empty Weight includes paint, hydraulic fluid and undrainable engine oil. AIRPLANE USEFUL LOAD - NORMAL CATEGORY OPERATION (Gross Weight) - (Licensed Empty Weight) - Useful Load (4200 lbs) - ( lbs) Ibs THIS LICENSED EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY. REEER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. REPORT: VB-424 PAGE 4-6 MODEL: PA-34-200 ISSUED: March 10, 1972 C. G. RANGE AND WEIGHT INSTRUCTIONS SENECA 1. Add the weight of all items to be loaded to the licensed empty weight. 2. Use the loading graph to determine the moment of all items to be carried in the airplane. 3. Add the moment of all items to be loaded to the licensed empty weight moment. 4. Divide the total moment by the total weight to determine the C.G. location. 5. By using the figures of Item 1 and Item 4, locate a point on the C.G. range and weight graph. If the point falls within the C.G. envelope, the loading meets the weight and balance requirements. SAMPLE LOADING PROBLEM (Normal Category) Arm Aft Weight Datum (Lbs) (Inches) Moment (In-Lbs) Licensed Basic Weight Pilot and Front Passenger 340.0 85.5 29070 Passengers (Center Seats) 340.0 118.1 40154 Passengers (Rear Seats)* 155.7 Passenger (Jump Seat)* 118.1 Fuel (93 Gallon Maximum) Baggage (Forward) Baggage (Aft) 93.6 22.5 178.7 Total Loaded Airplane The center of gravity (C.G.) of this sample loading problem is at datum line. Locate this point ( inches aft of the ) 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 INSURE THAT THE AIRPLANE IS LOADED PROPERLY. *Optional Equipment ISSUED: March 10, 1972 REVISED: May 30, 1975 REPORT: VB-424 PAGE 4-7 MODEL: PA-34-200 LOAD (POUNDS) SENECA 600 550 500 450 400 350 300 250 200 150 100 50 Forward Baggage- Pilot and Front Passenger Aft Baggage 0 5 10 15 20 25 30 35 REPORT: VB-424 PAGE 4-8 MODEL: PA-34-200 LOADING GRAPH 40 40 MOMENT/1000 (POUND-INCHES) Fuel (6 lb/gal) 45 45 Center Passengers Aft Passengers 50 55 60 60 ISSUED: March 10, 1972 SENECA IT IS THE RESPONSIBILITY OF THE OWNER AND PILOT TO ASCERTAIN THAT THE AIRPLANE ALWAYS REMAINS WITHIN THE ALLOWABLE WEIGHT VS. CENTER OF GRAVITY ENVELOPE WHILE IN FLIGHT. 88 90 92 94 4200 Max. Take-Off Wt. 4000 Max. Landing - Wt. 3800 84 3600 82 3400 3200 3000- 2800 2600 2400 2200 Fwd. limit 80.7 Aircraft Weight - lbs 82 84 86 88 90 92 94 C.G. Location (Inches Aft Datum) Aft Limit 94.6 Weight Vs C.G. Envelope Moment change due to retracting Landing Gear = -32 in. -lbs. ISSUED: March 10, 1972 REPORT: VB-424 PAGE 4-9 MODEL: PA-34-200 SENECA INSTRUCTIONS FOR USING THE WEIGHT AND BALANCE PLOTTER This plotter is provided to enable the pilot quickly and conveniently to: (1) Determine the total weight and C.G. position. (2) Decide how to change his load if his first loading is not within the allowable envelope. Heat can warp or ruin the plotter if it is left in the sunlight. Replacement plotters may be purchased from Piper dealers and distributors. When the airplane is delivered, the basic weight and basic C.G. will be recorded on the computer. These should be changed anytime the basic weight or C.G. location is changed. The plotter enables the user to add weights and corresponding moments graphically. The effect of adding or disposing of useful load can easily be seen. The plotter does not cover the situation where cargo is loaded in locations other than on the seats or in the baggage compartments. Brief instructions are given on the plotter itself. To use it, first plot a point on the grid to locate the basic weight and C.G. location. This can be put on more or less permanently because it will not change until the airplane is modified. Next, position the zero weight end of one of the six slots over this point. Using a pencil, draw a line along the slot to the weight which will be carried in that location. Then position the zero weight end of the next slot over the end of this line and draw another line representing the weight which will be located in this second position. When all the loads have been drawn in this manner, the final end of the segmented line locates the total load and the C.G. position of the airplane for take-off. If this point is not within the allowable envelope it will be necessary to offload fuel, baggage, or passengers and/or to rearrange baggage and passengers to get the final point to fall within the envelope. Fuel burn-off and gear movement do not significantly affect the center of gravity. SAMPLE PROBLEM A sample problem will demonstrate the use of the weight and balance plotter. Assume a basic weight and C.G. location of 2615 pounds at 82.0 inches respectively. We wish to carry a pilot and 5 passengers. Two men weighing 180 and 200 pounds will occupy the front seats, two women weighing 115 and 135 pounds will occupy the middle seats and two children weighing 80 and 100 pounds will ride in the rear. Two 25 pound suitcases will be tied down in the front baggage compartment and two suitcases weighing 25 pounds and 20 pounds respectively will be carried in the rear compartment. We wish to carry 60 gallons of fuel. Will we be within the safe envelope? REPORT: VB-424 PAGE 4-10 MODEL: PA-34-200 ISSUED: March 10, 1972 SENECA 1. 2. Place a dot on the plotter grid at 2615 pounds and 82.0 inches to represent the basic airplane. (See illustration.) Slide the slotted plastic into position so that the dot is under the slot for the forward seats, at zero weight. 3. Draw a line up the slot to the 380 pound position (180 + 200) and put a dot. 4. 5. 6. 7. Move the slotted plastic again to get the zero end of the middle seat slot over this dot. Draw a line up this slot to the 250 pound position (115 + 135) and place the 3rd dot. Continue moving the plastic and plotting points to account for weight in the rear seats (80+ 100), forward baggage compartment (50), rear baggage compartment (45), and fuel tanks (360). As can be seen from the illustration, the final dot shows the total weight to be 3880 pounds with the C.G. at 89.52. This is well within the envelope. 8. There will be room for more fuel. As fuel is burned off, the weight and C.G. will follow down the fuel line and stay within the envelope for landing. ISSUED: March 10, 1972 REPORT: VB-424 PAGE 4-11 MODEL: PA-34-200 SENECA ーで、 ག 72 372 46 ابه f SAMPLE PROBLEM 88 90 90 4200 Max. Take-Off Wt. 4000 Max. Landing Wt. 3800 84 3600 3400 3200 3000 2800 2600 2400 2200 82 62 Fwd. limit 80.7 Aircraft Weight - lbs 920 # Plus 80zal провод 92 -TAKE-OFF WEIGHT AND C.G.. FUEL REAR BAGGAGE FORWARD BAGGAGE REAR SEATS MIDDLE SEATS FRONT SEATS BASIC WEIGHT Aft Limit 94.6 94 Weight Vs 82 84 86 88 90 92 94 C.G. Location (Inches Aft Datum) C.G. Envelope Moment change due to retracting Landing Gear = -32 in.-lbs. REPORT: VB-424 PAGE 4-12 MODEL: PA-34-200 ISSUED: March 10, 1972