PIPER AIRCRAFT CORPORATION PA.28RT-2OIT, TURBO ARROW IV WEIGHT AND BALANCE 6.1 GENERAL

Transcription

1 PIPER AIRCRAFT CORPORATION PA.28RT-2OIT, TURBO ARROW IV 6.1 GENERAL In 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 a 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 insure 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. If the C.G. is t far frward in any airplane, it may be difficult t rtate fr takeff r landing. If.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, it is weighed, and 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 determine the weight and C.G. psitin fr the laded airplane by cmputing the ttal weight and mment apd then determining whether they are within the apprved envelpe. ISSUED: NOVEMBER 30, 1978 REVISED: JULY 16, l

2 PIPER AIRCRAFT CORPORATION PA.28RT-2OIT, TURBO ARROW IV 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 equ*ipment is added r any mdificatin wrk is dne, the mechanic reipänsible fr the wrk is required ttl cmpute a new basic empty weight unä C.G. psitin and t write these in the Aircraft Lg Bk and the Weight unä Bulun". 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 calculatiü frir t adding fuel t insure against imprper lading. The fllwing pages are frms used in weighing an airplane in,prductin and in cmpuiing 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 AIRPLANE WEIGHING PROCEDURE At the time f licensing, Piper Aircraft crpratin prvides each airplane with the basic empiy 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- detörmine this basic empty weight and center f gravity lcatin: (a) Preparatin ( l) Be certain that all items checkgd 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 (5.0 gallns ttal, 2.5 gallns each wing). 6-2 ISSUED: NOVEMBER 30, 1978 REVISED: JI.JLY 16, 1984

3 PIPER AIRCRAFT CORPORATION PA.28RT.2OIT, TURBO ARROW IV (b) Leveling CAUTION 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 insure 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 (l) With the airplane level and brakes released, recrd the weight shwn n each scale. Deduct the tare, if any, frm each reading. ISSUED: NOVEMBER 30, 1978 REVISED: SEPTEMBER 14,

4 PIPER AIRCRAFT CORPORATION PA-28RT-201T, TURBO ARROW IV 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) WEIGHING FORM Figure 6-l (d) Basic Empty Weight Center f Gravity (l) The fllwing gemetry applies t the PA-28RT-2017 airplane when it is level. Refer t Leveling paragraph 6.3 (b). C.G. Arm 78.4 Level Pints (Fuselage Left Side) d d A B = A- N R+ Wing Leading Edge B The datum is 78.4 inches ahead f the wing leading edge at the intersectin f the straight and tapered sectin. LEVELING DIAGRAM Figure ISSUED: NOVEMBER 30, l97e REVISED: SEPTEMBER 14, 1979

5 PIPER AIRCRAFT CORPORATION PA-2tRT-ilIT, TURBO ARROW rv (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) (B) T inches Where: f =}l +ft+l 5.5 DATA AND RECORD The Basic Empty Weight, Center f Gravity Lcatin and Useul 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. ISSUED: NOVEMBER 3{1, 197t REYISED: SEPTEMBER 30' l9t5 REPORT: VB-94{l 6-5

6 PIPER AIRCRAFT CORPORATION PA.28RT.2OIT, TURBO ARROW IV S[CTION DETERMINATION FOR FLIGHT (a) (b) (c) Add the weight f ail items t be laded t the basic emprv rveight. LIse the [-ading Graph ( Figure 6-r3) t derermine rt e i,äment t all items t be carried in the airplane. Add the mment f all items t be laded t the basic cmptv wcight mment. (d) Diride rhe tral mmenr b), the rral weight t cietcrminc. the C.G. lcatin. (e) B-"" using the figures l item (a) and item (d) (ab'e). l6care a pinr n the C.G. range and weight graph (Figure 6_15). llthe pinif alls within the c.g. envelpe. the tad-ing möets the u,eight nd buln.. re q uirements. Weight (Lbs) Arm Al't Datunr ( I nches) Mment ( I n-lbs) Basic Empty Weight Pilt and Frnt Passenger Passengers (Rear Seats) I tJ iltt A 40t54 Fuel (72 Callns Maximum) 3t Baggage (200 Lbs. Maximum) Ranrp We ight (2912 Lbs. Maximum) Fucl alklwance lr engine start. taxi and run-up 'fakeft Weight (2900 l-bs. Maximum) The c-e nrer f gravity (C,G.y f this sample lading pr aft l the darum line. Lcare this pint (92.0t ;n weight graph. Since this pint falls within the weighr lading meets the weight and balance requircments e t ill -il40 166{17tl blcm is at 92.0 inches the C.G. range and - C.G. cnvelpe, rhis IT IS I-HE RESPONSIBILITY OFTHE PILOTANDAIRCRAFTOWNER 1'O INSURE THAT THE AIRPLANE IS LOADED PROPER'Y. SAMPLE LOADING PROBLEM (NORMAL CATEGORY) Figure 6-9 ISSUED: NOVEMBER 30, 1978 REVISED: AUGUST 8, t9e3 REPORT: V

7 PIPER AIRCRAFT CORPORATION PA-28RT-201T, TURBO ARROW IV Weight (Lb3) Arm Aft Datum (lnches) Mment (ln-lbs) Basic Empty Weight Pilt and Frnt Passenger 80.5 Passengers (Rear Seats) I l8.l Fuel (72 Gallns Maximum) 95.0 Baggage (200 Lbs. Maximum) t42.8 Ramp Weight (2912 Lbs' Maximum) Fuql allwance fr engine start, taxi, and run-up -t r40 Ttal Laded AirPlane (2900 Lbs. Maximum) Ttals must be within apprved weight and c.g. limits. It is the respnsibility f the airplane *n.t and the pilt t insure that the airplaneis laded ;;;;r;ly. ine üasic Empty Weight.ö.G. is nted n the Weight and Balance 'Ouä fätr (Figure e-t. li ttre a-irplane has been altered, refer t the Weight and Balance Räcrd fr this infrmatin' LOADING FORM Figure 6- l I REPORT: VB' ISSUED: NOVEMBER 30' 1978 REVISED: JULY 15' 19t2

8 PIPER AIRCRAFT CORPORATION PA-28RT-2OIT, TURBO ARROW IV 4S at, z 3 I I (J UI = MOMENT/IOOO (POUNDS- NCHES) LOADING GRAPH Figure 6-13 ISSUED: NOVEMBER 30, 1978 REPORT: vb ll

9 PIPER AIRCRAFT CORPORATION PA-28RT-2OIT, TURBO ARROW IV 29OO LBS. MAX. GROSS WT WEIGHT VS C,G, ENVELOPE I ln t- 2 ) v tr C,G. LOCATION (INCHES AFT DATUM} I -E 100 a (Il ) F 1 T It! F L tr C) 70 E _1600 a C.G. RANGE AND WI'IGHT Figure 6- l 5 RIil'OR'I': Vll ISSUED: NOvIMBER REVISED: AUGUST 22, 1980

10 \ PIPER AIRCRAFT CORPORATION PA-28RT-201T, TURBO ARROW IV 6.9 INSTRUCTIONS FOR USING TIIE WEIGHT AND BAL.{NCE PLOTTER This?ltter.is prvided t enable the pilt quickly and cnveniently t: (a) Determine the ttal weight and C.G. psitin. (b) Decide hw r change his lad if his first lading is nt within rhe allwable envelpe. Heat can warp. r ruin the pltter if it is left in the sunlight. Replacement pltters may be purchased frm piper dealers and distiibutrs. The "Basic Empty weight and center f Gravity" lcatin is taken frm I the weight and Balance Frm (Figure 6-5), the weigtrt and Balance Recrd I (Figure 6-7) r the latest FAA majr repair r altöratin frrn. I The pltter enables the user t add weights and crrespnding mments graphically. The effect f adding r dispsing f useful iad can easily be seen. The pltter des nt cver the situatin where carg is ladeä in lcatins ther than n the seats cr in the baggage cmpartments. Brief instructins are given n the pltter itself. T use it, first plt a pint n the grid t lcate the basic weight and c.g. lcatin. This can be put n mre r less permanently because it will nt change until the airplane is mdified-.next, psitin the zer weight end f any ne f the läding slts ver this pint. using a pencil, draw a line alng ihe slt t the weighl which will be carried in that lcatin. Then psitin the zer weight end f the next slt ver the end fthis line and draw anther line represänting the weight which will be lcated in this secnd psitin. when allihelads have been drawn in this manner, the final end f the segmented line lcates the ttal lad and the c.g. psitin f the airplane fi takeff. If this pint is nt within the allwable envelpe it will be necessary t remve fuel,!ugq3g", r.passengers and/r t rearrange baggage and passengers t get the final pint t fall within the envelpe. Fuel burn-ff and gear mvement d nt significantly affect the center f gravity. ISSUED: AIJGUST 22, l9t0 REVISED: JULY 15, l9t2 6-l2a

11 PIPER AIRCRAFT CORPORATION PA-28RT-201T, TURBO ARROW IV SAMPLE PROBI,EM A sample prblem will demnstrate the use f the weight and balance pltter. Assume a basic weight and C.G. lcatin f 1600 punds at inches respectively. We wish t carry a pilt and 3 passengers. Tw men weighing 180 and 200 punds will ccupy the frnt seats, and tw children weighing 80 and 100 punds will ride in the rear. Tw suitcases weighing 25 punds and 20 punds respectively, will be carried in the rear cmpartment. We wish t carry 60 gallns f fuel. Will we be within the safe envelpe? (a) Place a dt n the pltter grid at I600 punds and inches t represent the basic airplane. (See illustratin.) (b) Slide the sltted plastic int psitin s that the dt is under the slt fr the frward seats, at zer weight. (c) Draw a line up the slt t the 380 pund psitin ( ) and put a dt. (d) Cntinue mving the plastic and pltting pints t accunt fr weight in the rear seats ( ), baggage cmpartment (45), and fuel tanks (360). (e) As can be seen frm the illustratin, the final dt shws the ttal weight t be 2565 punds with the C.G. at This is well within the envelpe (0 There will be rm fr mre fuel. As fuel is burned ff, the weight and C.G. will fllw dwn the fuel line and stay within the envelpe fr landing. 6-l2b ISSUED: AUGUST 22,l9E0

12 PIPER AIRCRAFT CORPORATION PA-2tRT-201T, TURBO ARROW IV WEIGHT AND BALANCf, SAMPLE PROBLEM 2900 tbs. MAX. GROSS WT WEIGHT vs C.G. ENVETOPE l 2900 a7 270I) 85 l I l'p* TAKEOFF WEIGHT AND C.G i / I t' BAGGAGE l I l td 2 ) 7IL FRONT \ EAR TS (',, t J !-r c, l-ra ll. <_17OO E S c.g. LOCATTON ( NCHES AFT DATUMI 1400 ISSUED: AUGUST 22, l2c