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PA-44-180, SEMINOLESECTION 6

WEIGHT AND BALANCE

TABLE OF CONTENTS

SECTION 6

WEIGHT AND BALANCE

ParagraphNo.

PageNo.

6.1 General..... 6-1

6.3 Airplane Weighing Procedure 6-2

6.5 Weight and Balance Data Record 6-5

6.7 Weight and Balance Determination for Flight . 6-9

6-156.9 Instructions for Using the Weight and Balance Plotter .

ISSUED: JULY 12, 1995 REPORT: VB-16166-i


WEIGHT AND BALANCE

SECTION 6

WEIGHT AND BALANCE

6.1 GENERALIn order to achieve the performance and flying characteristics which are

designed into the airplane, it must be flown with the weight and center ofgravity (CO.) position within the approved operating range (envelope).Although the airplane offers flexibility of loading, it cannot be flown with themaximum number of adult passengers, full fuel tanks and maximum baggage.With the flexibility comes responsibility. The pilot must ensure that theairplane is loaded within the loading envelope before he makes a takeoff.

Misloading carries consequences for any aircraft. An overloaded airplanewill not take off, climb or cruise as well as a properly loaded one. The heavierthe airplane is loaded, the less climb performance it will have.

Center of gravity is a determining factor in flight characteristics. If thee.G. is too far forward in any airplane, it may be difficult to rotate for takeoffor landing. If the CO. is too far aft, the airplane may rotate prematurely ontakeoff or tend to pitch up during climb. Longitudinal stability will be reduced.This can lead to inadvertent stalls and even spins; and spin recovery becomesmore difficult as the center of gravity moves aft of the approved limit.

A properly loaded airplane, however, will perform as intended. Thisairplane is designed to provide performance within the flight envelope. Beforethe airplane is delivered, it is weighed, and a basic empty weight and CO.location is computed (basic empty weight consists of the standard emptyweight of the airplane plus the optional equipment). Using the basic emptyweight and e.G. location, the pilot can determine the weight and C.G. positionfor the loaded airplane by computing the total weight and moment and thendetermining whether they are within the approved envelope.

ISSUED: JULY 12, 1995 REPORT: VB-16166-1

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SECTION 6WEIGHT AND BALANCE PA·44.180, SEMINOLE

6.1 GENERAL (Continued)

The basic empty weight and C.G. location are recorded in the Weight andBalance Data Form (Figure 6-5) and the Weight and Balance Record (Figure6-7). The CUITentvalues should always be used. Whenever new equipment isadded or any modification work is done, the mechanic responsible for the workis required to compute a new basic empty weight and CG. position and towrite these in the Aircraft Log Book and the Weight and Balance Record. Theowner should make sure that it is done.

)

A weight and balance calculation is necessary in determining how muchfuel or baggage can be boarded so as to keep within allowable limits. Checkcalculations prior to adding fuel to ensure against overloading.

The following pages are forms used in weighing an airplane in productionand in computing basic empty weight, CG. position, and useful load. Note thatthe useful load includes usable fuel, baggage, cargo and passengers. Followingthis is the method for computing takeoff weight and CO.

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6.3 AIRPLANE WEIGHING PROCEDURE

At the time of licensing, provides each airplane with the basic emptyweight and center of gravity location. This data is supplied by Figure 6-5.

The removal or addition of equipment or airplane modifications can affectthe basic empty weight and center of gravity. The following is a weighingprocedure to determine this basic empty weight and center of gravity location:

(a) Preparation

(I) Be certain that all items checked in the airplane equipmentlist are installed in the proper location in the airplane.

(2) Remove excessive dirt, grease, moisture, and foreign itemssuch as rags and tools, from the airplane before weighing.

(3) Defuel airplane. Then open all fuel drains until all remainingfuel is drained. Operate each engine until all undrainable fuelis used and engine stops. Then add the unusable fuel (2.0gallons total. 1.0 gallon each wing).

REPORT: VB·16166-2

ISSUED: JULY 12, 1995


WEIGHT AND BALANCE

6.3 AIRPLANE WEIGHING PROCEDURE (Continued)

CAUTIONI~

Whenever the fuel system is completely drainedand fuel is replenished it will be necessary to runthe engines for a minimum of 3 minutes at 1000RPM on each tank to ensure no air exists in thefuel supply lines.

(4) Fill with oil to full capacity.

(5) Place pilot and copilot seats in fourth (4th) notch, aft offorward position. Put flaps in the fully retracted position andall control surfaces in the neutral position. Tow bar should bein the proper location and entrance and baggage door closed.

(6) Weigh the airplane inside a closed building to prevent errorsin scale readings due to wind.

(b) Leveling

(I) With airplane on scales, block main gear oleo pistons in thefully extended position.

(2) Level airplane (refer to Figure 6-3) deflating nose wheel tire,to center bubble on level.

(c) Weighing- Airplane Basic Empty Weight

(1) With the airplane level and brakes released, record the weightshown on each scale. Deduct the tare, if any, from eachreading. r

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SECTION 6WEIGHT AND BALANCE PA-44-180, SEMINOLE

Scale NetScale Position and Symbol Reading Tare Weight

Nose Wheel (N)

Right Main Wheel (R)

Left Main Wheel (L)

Basic Empty Weight,(as Weighed) (T)

WEIGHING FORMFigure 6-1

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NacelleU (Top View)

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Fairing (Outboard of Nacelle)

Level Points(Fuselage Left Side)

A= 8.7"B = 109.7"

The datum is 78.4 inchesahead of the wing leadingedge at Wing Station 106.

Wing Leading Edge

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LEVELING DIAGRAMFigure 6-3

REPORT: VB-16166-4

ISSUED: JULY 12, 1995riI

SECTION 6WEIGHT AND BALANCEPA-44-180, SEMINOLE

6.3 AIRPLANE WEIGIDNG PROCEDURE (Continued)

r>. (d) Basic Empty Weight Center of Gravity

(1) The Leveling Diagram geometry (Figure 6-3) applies to thePA-44-180 airplane when it is level. Refer to Levelingparagraph 6.3 (b).

(2) The basic empty weight center of gravity (as weighedincluding optional equipment, full oil and unusable fuel) canbe determined by the following formula:

c.G. Ann = N (A) + CR+ L) (B)T

inches

Where: T = N + R + L

6.5 WEIGHT AND BALANCE DATA AND RECORD

,~ The Basic Empty Weight, Center of Gravity Location and Useful Loadlisted in Figure 6-5 are for the airplane as delivered from the factory. Thesefigures apply only to the specific airplane serial number and registrationnumber shown.

The basic empty weight of the airplane as delivered from the factory hasbeen entered in the Weight and Balance Record (Figure 6-7). TIllS form isprovided to present the current status of the airplane basic empty weight anda complete history of previous modifications. Any change to thepermanently installed equipment or modification which .affects weight ormoment must be entered in the Weight and Balance Record.

ISSUED: JULY 12,1995 REPORT: VB-16166-5

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MODEL PA-44-1S0, SEMINOLE

Airplane Serial Number 4496211

Registration Number N380U

Date 07125/05

I C.G. Ann TWeight x (Inches Aft = Moment

Item (Lbs) of Datum) (In-Lbs)

Actual 2596.9 85.8163 222856.4Standard Empty Weight* Comptttefi

Optional Equipment 55.4 115.2563 6385.2

Basic Empty Weight 2652.3 86.4312 229241.6

AIRPLANE BASIC EIv1PTY WEIGHT

*The standard empty weight includes full oil capacity and 2.0 gallons ofunusable fuel.

AIRPLANE USEFUL LOAD - NORMAL CATEGORY OPERATION

(Gross Weight) - (Basic Empty Weight) = Useful Load

(3800 lbs.) - ( 2652.3 lbs.) = 1147.7 lbs.

THIS BASIC EMPTY WEIGHT, C.G. AND USEFUL LOAD AREFOR THE AIRPLANE AS LICENSED AT THE FACTORY. REFERTO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONSHAVE BEEN MADE.

WEIGHT AND BALANCE DATA FORMFigure 6-5

REPORT: VB-16166-6 ISSUED: JULY 12, 1995

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6-8ISSU

ED:JU

LY12,1995


WEIGHT AND BALANCE

6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT

(a) Add the weight of all items to be loaded to the basic empty weight.(b) Use the Loading Graph (Figure 6-13) to determine the moment of all

items to be carried in the airplane.(c) Add the moment of all items to be loaded to the basic empty weight

moment.(d) Divide the total moment by the total weight to determine the C.G.

location.(e) By using the figures of item (a) and item (d) (above), locate a point on

the C.G. range and weight graph (Figure 6-15). If the point fallswithin the e.G. envelope, the loading meets the weight and balancerequirements.

ISSUED: JULY 12, 1995 REPORT: VB·16166-9

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SECTION 6WEIGHT AND BALANCE PA·44.180, SEMINOLE

6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT(Continued)

Arm AftWeight Datum Moment(Lbs) (Inches) (In-Lbs)

Basic Empty WeightPilot and Front Passenger 340.0 80.5 27370Passengers (Rear Seats) 340.0 118.1 40154Fuel (l08 Gallon Maximum Usable) 95.0Baggage (200 Lb. Limit) 142.8Ramp Weight (3816 Lbs. Max.)Fuel Allowance for EngineStart, Taxi & Runup -16.0 95.0 -1520Take-off Weight (3800 Lbs. Max.)

The center of gravity (e.G.) for the take-off weight of this sample loadingproblem is at inches aft of the datum line. Locate this point ( ) onthe CiG. range and weight graph. Since this point falls within the weight -e.G. envelope, this loading meets the weight and balance requirements.

Take-off WeightMinus Estimated Fuel Burn-off(climb & cruise) @ 6.0 Lbs/Gal. 95.0Landing Weight

Locate the center of gravity of the landing weight on the e.G. range andweight graph. Since this point falls within the weight- e.G. envelope, theloading may be assumed acceptable for landing.

IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNERTO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY AT ALLTIMES. ,.,.--......

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SAMPLE LOADING PROBLEMFigure 6-9

REPORT: VB·16166·10


PA.44.180, SEMINOLESECTION 6

WEIGHT AND BALANCE

6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT(Continued)

Arm AftWeight Datum Moment(Lbs) (Inches) (In-Lbs)

Basic Empty WeightPilot and Front Passenger 80.5Passengers (Rear Seats) 118.1Fuel (108 GaIIon Maximum Usable) 95.0Baggage (200 Lb. Limit) 142.8Ramp Weight (3816 Lbs. Max.)Fuel AIIowance for EngineStart, Taxi & Runup -16.0 95.0 -1520Take-off Weight (3800 Lbs. Max.)

The center of gravity (e.G.) for the take-off weight of this loadingproblem is at inches aft of the datum line. Locate this point ( ) onthe e.G. range and weight graph. If this point falls within the weight -e.G. envelope, this loading meets the weight and balance requirements.

Take-off Weight

Minus Estimated Fuel Burn-off(climb & cruise) @ 6.0 Lbs/Gal. 95.0Landing Weight

Locate the center of gravity of the landing weight on the e.G. range andweight graph. If this point falls within the weight- C.G. envelope, theloading may be assumed acceptable for landing.

IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNERTO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY AT ALLTIMES.

WEIGHT AND BALANCE LOADING FORMFigure 6-11

ISSUED: JULY 12, 1995 REPORT: VB·16166·11


THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: VB-16166-12


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WEIGHT AND BALANCE

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LOADING GRAPHFigure 6-13



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REPORT: VB-16166-14

LANDING WEIGHT V I I I8887/ I I

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MAX. T.O. AND 89 91 9290

84 86 86 87 88 89 90 91 92 93C.G. LOCATION (INCHES AFT DATUM)

c.c. RANGE AND WEIGHTFigure 6-15


93


WEIGHT AND BALANCE

6.9 INSTRUCTIONS FOR USING THE WEIGHT AND BALANCEPLOTTERThis plotter is provided to enable the pilot quickly and conveniently to:

(a) Determine the total weight and CiG. position.(b) 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. Replacementplotters may be purchased from Piper dealers and distributors.

When the airplane is delivered, the basic weight and basic C.G. will berecorded on the computer. These should be changed any time the basic weightor e.G. location is changed.

The plotter enables the user to add weights and corresponding momentsgraphically. 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 otherthan on the seats or in the baggage compartments.

Brief instructions are given on the plotter itself. To use it, first plot a pointon the grid to locate the basic weight and C.G. location. This can be put onmore or less permanently because it will not change until the airplane ismodified. Next, position the zero weight end of anyone of the loading slotsover this point. Using a pencil, draw a line along the slot to the weight whichwill be carried in that location. Then position the zero weight end of the nextslot over the end of this line and draw another line representing the weightwhich will be located in this second position. When all the loads have beendrawn in this manner, the final end of the segmented line locates the total loadand the e.G. position of the airplane for takeoff. If this point is not within theallowable envelope it will be necessary to remove fuel, baggage, or passengersand/or to rearrange baggage and passengers to get the final point to fall withinthe envelope.

Fuel burn-off and gear movement do not significantly affect the center ofgravity.



SAMPLE PROBLEM

A sample problem (Figure 6-17) will demonstrate the use of the weightand balance plotter.

Assume a basic weight and C.O. location of 2364 pounds at 86.14 inchesrespectively. We wish to carry a pilot and 3 passengers. Two men weighing180 and 200 pounds will occupy the front seats, and two children weighing 80and 100 pounds will ride in the rear. Two suitcases weighing 25 pounds and 20pounds respectively, will be carried in the rear compartment. We wish to carry60 gallons of fuel. Will we be within the safe envelope?

(a) Place a dot on the plotter grid at 2364 pounds and 86.14 inches torepresent the basic airplane. (See illustration.)

(b) Slide the slotted plastic into position so that the dot is under the slotfor the forward seats, at zero weight.

(c) Draw a line up the slot to the 380 pound position ( 180 + 200) and puta dot.

(d) Continue moving the plastic and plotting points to account for weightin the rear seats (80 + 100), baggage compartment (45), and fueltanks (360).

(e) As can be seen from the illustration, the final dot shows the totalweight to be 3329 pounds with the CO. at 89.30. This is well withinthe envelope.

(f) There will be room for more fuel.

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As fuel is burned off, the weight and CO. will follow down the fuel lineand stay within the envelope for landing.

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REPORT: VB-16166-16


PA·44·180, SEMINOLESECTION 6

WEIGHT AND BALANCE

MAX. T.O. AND 89 90 91 92 933800 LANDING WEIGHT- A=--"""'T'-__,r---r-- .•..•

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8485 8687 8889 90 919293C.G. LOCATION (INCHES AFT DATUM)

SAMPLE PROBLEMFigure 6-17

ISSUED: JULY 12, 1995 REPORT: VB·16166·17

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SECTION 6WEIGHT AND BALANCE PA·44·180, SEMINOLE

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iREPORT: VB·16166·18


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