Weight & Balance for Piper PA-28R Arrow IV

loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope. The licensed empty weight and C.G. location for a particular airplane are recorded in the weight and balance section of the Airplane Flight Manual. The current values should always be used. Whenever new equipment is added or any modification work is done, the mechanic respon- sible for the work is required to compute a new basic empty weight and 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 empty weight, 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: FEBRUARY 29, 1984 REPORT: VB-549 PAGE 5-1 MODEL:PA-28R-200 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-549 PAGE 5-2 MODEL: PA-28R-200 ISSUED: MAY 14, 1973 WEIGHT AND BALANCE DATA WEIGHING PROCEDURE ARROW At the time of licensing. 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. 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. 2. LEVELING a. With airplane on scales, block main gear oleo pistons in the fully extended position. ISSUED: MAY 14, 1973 REVISED: FEBRUARY 29, 1984 REPORT: VB-549 PAGE 5-3 MODEL: PA-28R-200 DATUM A = B = ARROW 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) Scale Reading Tare Weight Airplane Empty Weight, as Weighed (T) 4. EMPTY WEIGHT CENTER OF GRAVITY a. The following geometry applies to the PA-28R-200 airplane when airplane is level (See Item 2). N C. G. ARM 78.4*. R + L A B REPORT: VB-549 PAGE 5-4 MODEL: PA-28R-200 Level Points (Fuselage Left Side) -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 13, 1979 ARROW 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 + A- B(N) Τ C. G. Arm = 78.4 + ( )-( ) ( inches 5. LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY Empty Weight (as weighed) Weight Arm Moment Unusable Fuel (13 1/3 Pints) +10.0 103.0 +1030 Licensed Empty Weight ISSUED: MAY 14, 1973 REPORT: VB-549 PAGE 5-5 MODEL: PA-28R-200 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-549 PAGE 5-6 MODEL: PA-28R-200 ISSUED: MAY 14, 1973 WEIGHT AND BALANCE DATA MODEL PA-28R-200 CHEROKEE Airplane Serial Number 28R-7535001 Registration Number N44443 Date 10/6/2005 AIRPLANE EMPTY WEIGHT ARROW Item Weight (Lbs) C. G. Arm (Inches Aft of Datum) Moment (In-Lbs) *Empty Weight Actual Computed Unusable Fuel (13-1/3 pints) 10.0 103.0 1030 Standard Empty Weight Optional Equipment Licensed Empty Weight 1721.97 87.42 150538.35 *Empty weight is defined as dry empty weight (including paint and hydraulic fluid) plus 1.8 lbs undrainable engine oil. AIRPLANE USEFUL LOAD - NORMAL CATEGORY OPERATION (Gross Weight) - (Licensed Empty Weight) = Useful Load (2650 lbs) - ( lbs) = lbs THIS LICENSED 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. ISSUED: MAY 14, 1973 REPORT: VB-549 PAGE 5-7 REVISED: FEBRUARY 29, 1984 MODEL: PA-28R-200 ARROW C. G. RANGE AND WEIGHT INSTRUCTIONS 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) Max Wt. = 2650# Arm Aft Weight (Lbs) Datum (Inches) Moment (In-Lbs) Licensed Empty Weight Oil (8 quarts) 1721.97 87.42 150,538.35 15 24.5 368 Pilot and Front Passenger 80.5 Passengers, Aft (Rear Seat) 118.1 Fuel (48 Gal. Maximum) 95.0 *Baggage 142.8 Moment due to Retracting of Landing Gear 819 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. *Check Aft C.G. between 150 lbs and 200 lbs. Cument as q of OLMAY 2013 M REPORT: VB-549 PAGE 5-8 MODEL: PA-28R-200 ISSUED: MAY 14, 1973 REVISED: OCTOBER 29, 1973 48288 36g=216