Weight & Balance for Piper Pilot 100i

new equipment is added or any modification work is done, the mechanic responsible for the work is required to compute a new basic weight and basic C.G. position and to write these in the aircraft log book. The owner should make sure that it is done. A weight and balance calculation is necessary in determining how much fuel or baggage can be boarded so as to keep within allowable limits. Check calculations prior to adding fuel to insure against improper loading. The following pages are forms used in weighing an airplane in production and in computing basic weight, basic C.G. position, and useful load. Note that the useful load includes fuel, oil, baggage, cargo and passengers. Following this is the method for computing takeoff weight and C.G. ISSUED: MAY 14, 1973 REVISED: APRIL 6, 1979 REPORT: VB-535 PAGE 5-1 MODEL: PA-28-151 CHEROKEE WARRIOR WEIGHT AND BALANCE DATA WEIGHING PROCEDURE At the time of delivery, Piper Aircraft Corporation provides each airplane with the licensed empty weight and center of gravity location. This data is on Page 5-7. The removal or addition of an excessive amount of equipment or excessive airplane modifications can affect the licensed empty weight and empty weight center of gravity. The following is a weighing procedure to determine this licensed empty weight and center of gravity location: 1. PREPARATION a. b. C. Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane. Remove excessive dirt, grease, moisture, foreign items such as rags and tools from the airplane before weighing. Defuel airplane. Then open all fuel drains until all remaining fuel is drained. Operate engine on each tank until all undrainable fuel is used and engine stops. 2. CAUTION Whenever the fuel system is completely drained and fuel is re- plenished it will be necessary to run the engine for a minimum of 3 minutes at 1000 RPM on each tank to insure no air exists in the fuel supply lines. d. e. f. Drain all oil from the engine, by means of the oil drain, with the airplane in ground attitude. This will leave the undrainable oil still in the system. Engine oil temperature should be in the normal operating range before draining. Place pilot and copilot seats in fourth (4th) notch, aft of forward position. Put flaps in the fully retracted position and all control surfaces in the neutral position. Tow bar should be in the proper location and all entrance and baggage doors closed. Weigh the airplane inside a closed building to prevent errors in scale readings due to wind. LEVELING a. With airplane on scales, block main gear oleo pistons in the fully extended position. ISSUED: MAY 14, 1973 REVISED: APRIL 6, 1979 REPORT: VB-535 PAGE 5-3 MODEL: PA-28-151 CHEROKEE WARRIOR 3. b. Level airplane (see diagram) deflating nose wheel tire, to center bubble on level. WEIGHING - AIRPLANE EMPTY WEIGHT a. With the airplane level and brakes released, record the weight shown on each scale. Deduct the tare, if any, from each reading. Scale Position and Symbol Nose Wheel (N) Right Main Wheel (R) Left Main Wheel (L) Airplane Empty Weight, as Weighed (T) A = B = 4. Scale Reading Tare Net Weight EMPTY WEIGHT CENTER OF GRAVITY a. The following geometry applies to the PA-28-151 airplane when airplane is level (See Item 2). C. G. Arm. -78.4 REPORT: VB-535 PAGE 5-4 MODEL: PA-28-151 C. G. Level Points (Fuselage) R+L Wing Leading Edge The datum is 78.4 inches ahead of the wing leading edge at the intersection of the straight and tapered section. ISSUED: MAY 14, 1973 REVISED: APRIL 6, 1979 CHEROKEE WARRIOR b. C. d. Obtain measurement "A" by measuring from a plumb bob dropped from one wing leading edge, at the intersection of the straight and inboard 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 = 78.4A B(N) - T C. G. Arm 78.4 +( = )- ) inches 5. LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY Weight Arm Moment Empty Weight (as weighed) | Unusable Fuel (2.0 gal.) 12 lb 103.0 1236 Licensed Empty Weight ISSUED: MAY 14, 1973 REVISED: JUNE 14, 1974 REPORT: VB-535 PAGE 5-5 MODEL: PA-28-151 Airplane Serial Number_ Registration Number Date WEIGHT AND BALANCE DATA MODEL PA-28-151 CHEROKEE AIRPLANE EMPTY WEIGHT CHEROKEE WARRIOR C. G. Arm Weight (Lbs) X (Inches Aft = of Datum) Moment (In-Lbs) Item Actual Computed 12 103 1236 *Empty Weight Unusable Fuel (2 gal.) Standard Empty Weight Optional Equipment Licensed Empty Weight *Empty weight is defined as dry empty weight (including paint and hydraulic fluid) plus 1.8 lbs undrainable engine oil. Normal category: Utility category: AIRPLANE USEFUL LOAD (Gross Weight) - (Licensed Empty Weight) = Useful Load (2325 lbs) (1950 lbs) lbs) lbs) = lbs = lbs THIS LICENSED EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. ISSUED: MAY 14, 1973 REVISED: JUNE 14, 1974 REPORT: VB-535 PAGE 5-7 MODEL: PA-28-151 CHEROKEE WARRIOR C. G. RANGE AND WEIGHT INSTRUCTIONS 1. Add the weight of all items to be loaded to the licensed empty weight. 2. 3. 4. 5. Use the loading graph to determine the moment of all items to be carried in the airplane. Add the moment of all items to be loaded to the licensed empty weight moment. Divide the total moment by the total weight to determine the C.G. location. 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) Weight (Lbs) Arm Aft Datum (Inches) Moment (In-Lbs) Licensed Empty Weight Oil (8 quarts) 15 27.5 413 Pilot and Front Passenger 340 80.5 27370 Passengers, Aft* (Rear Seat) 340 118.1 40154 Fuel (48 Gal. Maximum) 95.0 Baggage* 142.8 Total Loaded Airplane inches aft of the The center of gravity (C.G.) of this sample loading problem is at datum line. Locate this point ( ) 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. *Utility Category Operation - No baggage or aft passengers allowed. REPORT: VB 535 PAGE 5-8 MODEL: PA-28-151 ISSUED: MAY 14, 1973 REVISED: AUGUST 30, 1973 LOAD WEIGHT (POUNDS) 450 400 350 300 250 200 150 100 50 LOADING GRAPH Pilot and Front Passenger CHEROKEE WARRIOR Fuel (6 lb/gal). Aft Passengers. Baggage 0 5 10 15 20 25 30 35 40 45 50 50 ISSUED: MAY 14, 1973 MOMENT/1000 (POUNDS - INCHES) REPORT: VB-535 PAGE 5-9 MODEL: PA-28-151 CHEROKEE WARRIOR WEIGHT - IN LBS 2800 2600 2400 2200 C. G. RANGE AND WEIGHT 2000 UTILITY CATEGORY I 1800 1600 1 1400 + NORMAL CATEGORY 1200 82 84 86 88 90 92 94 REPORT: VB-535 PAGE 5-10 MODEL: PA-28-151 DATUM ISSUED: MAY 14, 1973 REVISED: JANUARY 25, 1974