WEIGHT AND BALANCE. ** Equipment List (Form ) TABLE OF CONTENTS SECTION 6. REPORT: VB i .ENCLOSED WTIH THIS HANDBOOK

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1 TABLE OF CONTENTS Paragraph N s 6.7 General Airplane Weighing Prcedure Weight and Balance Data and Recrd Weight and Balance Determinatin fr Flight Page N ** Equipment List (Frm ).ENCLOSED WTH THS HANDBOOK 6-i

2 P , ARCHER 6.1. GENERAL n rder t achieve the perfrmance and flying characteristics which are designed int the airplane, it must be flwn with the weight and center f gravity (C.G.) psitin within the apprved perating range (envelpe). Althugh the airplane ffers flexibility f lading, it cannt be flwn with the maximum number f adult passengers, full fuel tanks and maximum baggage. With the flexibility cmes respnsibility. The pilt must ensure that the airplane is laded within the lading envelpe befre he makes a takeff. Mislading carries cnsequences fr any aircraft. An verladed airplane will nt take ff, climb r cruise as well as a prperly laded ne. The heavier the airplane is laded, the less climb perfrmance it will have. Center f gravity is a determining factr in flight characteristics. f the C.G. is t far frward in any airplane, it may be difficult t rtate fr takeff r landing. f the C.G. is t far aft, the airplane may rtate prematurely n takeff r tend t pitch up during climb. Lngitudinal stability will be reduced. This can lead t inadvertent stalls and even spins; and spin recvery becmes mre difficult as the center f gravity mves aft f the apprved limit. A prperly laded airplane, hwever, will perfrm as intended. Befre the airplane is licensed, a basic empty weight and C.G. lcatin is cmputed (basic empty weight cnsists f the standard empty weight f the airplane plus the ptinal equipment). Using the basic empty weight and C.G. lcatin, the pilt can easily determine the weight and C.G. psitin fr the laded airplane by cmputing the ttal weight and mment and then determining whether they are within the apprved envelpe. SSUED: JALY 12, "1'

3 PA , ARCHER The basic empty weight and C.G. lcatin are recrded in the Weight and Balance Data Frm (Figure 6-5) and the Weight and Balance Recrd (Figure 6-7). The current values shuld always be used. Whenever new equipment is added r any mdificatin wrk is dne, the mechanic respnsible fr the wrk is required t cmpute a new basic empty weight and C.G. psitin and t write these in the Aircraft Lg Bk and the Weight and Balance Recrd. The wner shuld make sure that it is dne. A weight and balance calculatin is necessary in determining hw much fuel r baggage can be barded s as t keep within allwable limits. Check calculatins prir t adding fuel t insure against imprper lading. The fllwing pages are frms used in weighing an airplane in prductin and in cmputing basic empty weight, C.G. psitin, and useful lad. Nte that the useful lad includes usable fuel, baggage, carg and passengers. Fllwing this is the methd fr cmputing takeff weight and C.G. 6.3 ARPLANE WEGHNG PROCEDURE At the time f licensing, Piper prvides each airplane with the basic empty weight and center f gravity lcatin. This data is supplied by Figure 6-5. The remval r additin f equipment r airplane mdificatins can affect the basic empty weight and center f gravity. The fllwing is a weighing prcedure t determine this basic empty weight and center f gravity lcatin: (a) Preparatin (l) Be certain that all items checked in the airplane equipment list are installed in the prper lcatin in the airplane. (2) Remve excessive dirt, grease, misture, freign items such as rags and tls frm the airplane befre weighing. (3) Defuel airplane. Then pen all fuel drains until all remaining fuel is drained. Operate engine n each tank until all undrainable fuel is used and engine stps. Then add the unusable fuel (2.0 gallns ttal, 1.0 gallns each wing). 6-2 SSUED: JALY 12,1995

4 PA , ARCHER (b) Leveling CAUTON Whenever the fuel system is cmpletely drained and fuel is replenished it will be necessary t run the engine fr a minimum f 3 minutes at 1000 RPM n each tank t ensure n air exists in the fuel supply lines. (4) Fill with il t full capacity. (5) Place pilt and cpilt seats in furth (4th) ntch, aft f frward psitin. Put flaps in the fully retracted psitin and all cntrl surfaces in the neutral psitin. Tw bar shuld be in the prper lcatin and all entrance and baggage drs clsed. (6) Weigh the airplane inside a clsed building t prevent errrs in scale readings due t wind. (l) With airplane n scales, blck main gear le pistns in the fully extended psitin. (2) Level airplane (refer t Figure 6-3) deflating nse wheel tire, t center bubble n level. (c) Weighing - Airplane Basic Empty Weight (1) With the airplane level and brakes released, recrd the weight shwn n each scale. Deduct the tare, if any, frm each reading.. 6-3

5 PA , ARCHER Scale Psitin and Symbl Scale Reading Tare Net Weight Nse Wheel (N) Right Main Wheel (R) Left Main Wheel (L) Basic Empty Weight" as Weighed (T) WEGHNG FORM Figure 6-1 (d) Basic Empty Weight Center f Gravity (1) The fllwing gemetry applies t the PA airplane when it is level. Refer t Leveling paragraph 6.3 (b). rvel 4\ WinglcadingEdge N R+L A+ A = 31.0 B LEVELNG DAGRAM Figure 6-3 B = 1(D.7 REPORft V

6 PA , ARCHER (2) The basic empty weight center f gravity (as weighed including ptinal equipment, full il and unusable fuel) can be determined by the fllwing frmula: C.G. Arm = N (A) + (R + L) ß) T inches Where: T=N+R+L 6.5 DATA AND RECORD The Basic Empty Weight, Center f Gravity Lcatin and Useful Lad listed in Figure 6-5 are fr the airplane as licensed at the factry. These figures apply nly t the specific airplane serial number and registratin number shwn. The basic empty weight f the airplane as licensed at the factry has been entered in the Weight and Balance Recrd (Figure 6-7). This frm is prvided t present the current status f the airplane basic empty weight and a cmplete histry f previus mdificatins. Any change t the permanently installed equipment r mdificatin which affects weight r mment must be entered in the Weight and Balance Recrd. SSUED: JULY L2,L

7 PA , ARCHER r MODEL PA ARCHER Airplane Serial Number Registratin Number_ Date ARPLANE BASC EMPTY WEGHT tem C.G. Arm Weight x (nches Aft = Mment (Lbs) f Datum) (n-lbs) Actual Standard Empty Weight* Cmputed Optinal Equipment Basic Empty Weight *The standard empty weight includes full il capacity and 2.0 gallns f unusable fuel. ARPLANE USEFUL LOAD (Ramp Weight) - (Basic Empty Weight) = Useful Lad Nrmal Categry (25581bs) - ( lbs) = Utility Categry (2l38lbs) - ( lbs) = lbs. lbs. THS BASC EMPTY WEGHT, C.G. AND USEFUL LOAD ARE FOR THE ARPLANE AS LCENSED AT THE FACTORY. REFER TO APPROPRATE ARCRAFT RECORD WHEN ALTERATONS HAVE BEEN MADE. DATA FORM Figure

8 PA , ARCHER tr 3 z a, a 6A..9ä ä.8 tq!f -.5> E ir. äe cel.t F 8.cl g "8 E z c 'll6t.e 6 a, ü ä0 c3 ql ä0 F cl Hg x- E i!t F J (, pc utcu (+) pppv "B E3zcl ü v, ct N a g. -9. (, 'E cl t.9, t5 eg $a A 'Nureu d ö RECORD Figure 6-7 SSUED: JALY 12, E

9 PA , ARCHER r 6 E z a, öo cl O. ä6 T"*.E> :t cl ter trrq 2 a) tr., B 8 ri J EE z E G ts ta öl t) cl O ä t) F c EA g= E t c d Ẹ1 (-) pa,ruax (+) peppv 3 =z c (, (t) N 0. c. C'.r.9 q8 8.3> 8ö (l' a 'Nursll a, ql a RECORD (cnt) Figure 6-7 (cnt) 6-8 SSUED: JALY 12,1995

10 PA , ARCHER 6.7 DETERMNATON FOR FLGHT (a) Add the weight f all items t be laded t the basic empty weight. (b) Use the Lading Graph (Figure 6-13) t determine the mment f all items t be carried in the airplane. (c) Add the mment f all items t be laded t the basic empty weight mment. (d) Divide the ttal mment by the ttal weight t determine the C.G. lcatin. (e) By using the figures f item (a) and item (d) (abve), lcate a pint n the C.G. range and weight graph (Figure 6-15). f the pint falls within the C.G. envelpe, the lading meets the weight and balance requirements. Weight (Lbs) Arm Aft Datum (nches) Basic Empty Weight Pilt and Frnt Passenger Passengers (Rear Seats)* Fuel (48 Galln Maximum) Baggage (200 Lbs. Maximum)* Ramp Weight (2558 Lbs. Nrmal, 2138 Lbs. Utility Maximum) r Fuel Allwance Fr Engine Start, Taxi and Run Up -8 9s TakeffWeight (2550 Lbs. Nrmal, 2130 Lbs. Utility Maximum) The center f gravity (C.G.) f this sample lading prblem is at 9l.5 inches aft f the datum line. Lcate this pint (91.5) n the C.G. range and weight graph. Since this pint falls within rhe weight - C.G. envelpe, this lading meets the weight and balance requirements. T S THE RESPONSBLTY OF THE PLOT AND ARCRAFT OWNER TO ENSURE THAT THE ARPLANE S LOADED PROPERLY. *Utility Categry Operatin - N baggage r rear passengers allwed. Mment (n-lbs) SAMPLE LOADNG PROBLEM (NORMAL CATEGORY) Figure

11 PA , ARCHER rr Weight (Lbs) Arm Att Datum (nches) Mment (n-lbs) Basic Empty Weight Pilt and Frnt Passenger Passengers (Rear Seats)* Fuel (48 Galln Maximum) Baggage (200 Lbs. Maximum)* Ramp Weight (2558 Lbs. Nrmal, 2138 Lbs. Utility Maximum) Fuel Allwance Fr Engine Start, Taxi and Run Up TakeffWeight (2550 Lbs. Nrmal, 2130 Lbs. Utility Maximum) Ttals must be within apprved weight and C.G. limits. t is the respnsibility f the airplane wner and the pilt t insure that the airplane is laded prperly. The Basic Empty Weight C.G. is nted n the Weight and Balance Data Frm (Figure 6-5). f the airplane has been altered, refer t the Weight and Balance Recrd fr this infrmatin. *Utility Categry Operatin - N baggage r rear passengers allwed LOADNG FORM Figure

12 P , ARCHER 450 t 350 3n H ,/ /. /t 7 7 a / A?53035{04550 MOMENT/1OOO (POUNDS. NCHES LOADNG GRAPH Figure rt

13 PA , ARCHER WEGHT vs. C.G. ENVELOPE 2550 L8S. MAX. GROSS WT.- NORMAL CATEGORY a4 83 l a J F u u z J L G c.g. LOCATTON (NCHES AFT DATUM) 1 C.G. RANGE AND WEGHT Figure