Weight and Balance Report

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WEIGHT AND BALANCE

CESSNA 152 REPORT

PROJECT: G -11

TITLE : PERFOM AIRCRAFT WEIGHING

NAME : MUHD LUQMAN BIN MHD REJAB

ID : 53133208283

CLASS : 1 MANUFACTURING

INSTRUCTOR : TUAN HAJI RASHID BIN HAJI MAHMOOD


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CONTENtSINTRODUCTIONPURPOSETOOLS AND EQUIPMENTS USEAIRCRAFT WEIGHTING PROCEDURE:-

PREPARATION

CALIBRATE THE WEINGHTING SCALE

JACK THE AIRCRAFT

LEVEL THE AIRCRAFT

READING WEIGHING SCALE

MEASURE THE DATUM

HOUSE KEEPING/TIDY UP CALCULATION AND DATA ENTRY

WEIGHING FORMMAKE A TYPICAL LOGBOOK ENTRYAppendixConclusion


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INTRODUCTION:

a) WHY WEIGHT AND BALANCE IMPORTANT?

Weight and balance is one of the most important factors affecting safety of flight. A

overweight aircraft, or one whose centre of gravity is outside the allowable limits, is inefficieand dangerous to fly. The responsibility for proper weight and balance control begins with th

engineers and designers and extends to the pilots who operates and Aviation MaintenanTechnician (AMT) who maintain the aircraft.

The designers of an aircraft have determined the maximum weight, based on the amount of li

the wings or rotors can provide under the operating condition for which the aircraft is designe

The structural strength of the aircraft also limits the maximum weight the aircraft can safeticarry. The designer very carefully determined the ideal location of the centre of gravity (CG

and the maximum deviation allowed from this specific location has been calculation.

The manufacturer provides the aircraft operator with the empty weight of the aircraft and th

location of its empty-weight center of gravity (EWCG) at the time the aircraft left the factor

The AMT who maintains the aircraft and performs the maintenance inspections keeps thweight and balance records current, recording any changes that have been made because repair or alterations.

Maximum weight: The maximumauthorized weight of the aircraft and all of

its equipment as specified in the Type

Certificate Data Sheets (TCDS) for the

aircraft.

Centre of gravity: the point atwhich an airplane would balance if

suspended. Its distance from thereference datum is found by

dividing the total moment by the

total weight of the airplane.

Empty weight: The weight of the

airframe, engines, and all items ofoperating equipment that have fixed

locations and arepermanentlyinstalled in the aircraft

Empty weight center of gravity

(EWCG): The center of gravity of anaircraft, when the aircraft contains onlythe items specified in the aircraft emptyweight


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b) CESSNA 152 INFORMATION AND SPECIFICATION

General characteristics

Crew: 1 pilot

Capacity: 1 passenger

Length: 24 ft 1 in (7.3 m)

Wingspan: 33 ft 9 in (10.3 m)

Height: 8 ft 6 in (2.6 m) Wing area: 160 ft (14.9 m)

Empty weight: 1,100 lb (500 kg)

Max takeoff weight: 1,670 lb (757 kg)

Powerplant: 1 Lycoming O-235-L2Cflat-4 engine, 110 hp (82 kW) driving a 69 in (175

cm), two-blade, fixed-pitch propeller

Performance

Maximum speed: 126 mph (109 knots, 203 km/h)

Stall speed: 49 mph (43 knots, 79 km/h) unpowered, flaps down

Range: 477 mi (414 nm, 768 km) Extended range 795 mi (690 nm, 1,280 km) with long-range tanks

Service ceiling 14,700 ft (4,480 m)

Takeoff roll: 725 ft (221 m)

Rate of climb: 715 ft/min (3.6 m/s)

Max wing loading: 10.44 lb/ft (51 kg/m)

Minimum power/mass: .066 hp/lb (108 W/kg)
http://en.wikipedia.org/wiki/Wingspanhttp://en.wikipedia.org/wiki/Maximum_Takeoff_Weighthttp://en.wikipedia.org/wiki/Lycoming_O-235http://en.wikipedia.org/wiki/Flat-4http://en.wikipedia.org/wiki/Flat-4http://en.wikipedia.org/wiki/V_speeds#Vnohttp://en.wikipedia.org/wiki/Stall_speedhttp://en.wikipedia.org/wiki/Range_(aircraft)http://en.wikipedia.org/wiki/Ceiling_(aeronautics)http://en.wikipedia.org/wiki/Rate_of_climbhttp://en.wikipedia.org/wiki/Wing_loadinghttp://en.wikipedia.org/wiki/Power-to-weight_ratiohttp://www.flugzeuginfo.net/acimages/reims-cessna_f152_kp.jpghttp://en.wikipedia.org/wiki/Maximum_Takeoff_Weighthttp://en.wikipedia.org/wiki/Lycoming_O-235http://en.wikipedia.org/wiki/Flat-4http://en.wikipedia.org/wiki/V_speeds#Vnohttp://en.wikipedia.org/wiki/Stall_speedhttp://en.wikipedia.org/wiki/Range_(aircraft)http://en.wikipedia.org/wiki/Ceiling_(aeronautics)http://en.wikipedia.org/wiki/Rate_of_climbhttp://en.wikipedia.org/wiki/Wing_loadinghttp://en.wikipedia.org/wiki/Power-to-weight_ratiohttp://en.wikipedia.org/wiki/Wingspan


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PURPOSE:

Safety To achieve the utmost efficiency during flight

Improper loading reduces the efficiency during flight from th

standpoint of ceiling, maneuverability, rate of climb, fuel consumption

TOOLS AND EQUIPMENT USE FOR AIRCRAFT

WEIGHT

AND BALANCE:


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NO ITEM QUANTITY


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1 Light fixed-wing aircraft 01

2 Aircraft jack As required

3 Bottle jack As required

4 Jack adapter 03

5 Weighting scale 1 set

6 Chocks 06

7 Plum bob 02

8 Measuring tape 019 Spirit level 02

10 L engineering square 01

11 Chalky line 01

12 Chalk 4 pieces

13 Tire inflator and gauge 01

14 Nitrogen gas bottle + chuck key 01

15 Electrical wire cable / connector 01

AIRCRAFT DEFUELING1 Empty container (cleaned) As required

2 Filter + funnel 1 each

3 Step 02

4 Ground bonding 02

5 Rags As required

6 Fire extinguisher 01

7 Hand tools As required

AIRCRAFT WASHING1 Soap cleaner As required

2 Water spray gun 1 set

3 Rags and sponge As required

4 Masking tape 2 rolls

5 Cleaning solvent As required

Light fixed-wing

aircraft

Aircraft jack Bottle jackL engineeringsquare


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AIRCRAFT WEIGHT PROCEDURE:

PREPARATION

1-Obtain all required data with regard to weighing TCDS etc.

Jack adapter and weighing scale

Plum bobMeasuring tape

Spirit level

Chalky line

Tire inflator and

gauae step Fire extinguisher Nitrogen gas botle


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2- a)Check aircraft fuel. If it is not empty, drain the fuel / top up to the require

specification.

b)If any fuel is left in the tanks, the aircraft will weigh more, and all lat

calculations for useful load and balance will be affected

3- a)Only trapped or unusable fuel (residual fuel) is considered part of the aircra

empty weight

b)Fuel tank caps should be on the tanks or placed as close as possible to their corre

locations, so that the weight distribution will be correct.

4-a)Clean the aircraft / washing

b)Clean your plane and get as much dirt and debris out and off of it a

possible.

Safety precautions:-Cover all static port and pitot tube before cleaning

-Use approved detergent / soap

-Use brushes and rags that are clean from dirt / sand or FOD

5-Make sure aircraft is in the closed hangar on level ground.

6-Check equipment list or ballast-refer TCDS

7-Inflate all tyres to the recommended operating pressure- refer maintenance manual

PRESSURE GAUGEREADING (psi )

CESSNA 152STANDARD TYRES

PRESSURE (psi )

NOSE WHEEL 20 30

MAIN RIGHT

WHEEL

20 21

MAIN LEFT 25 21


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WHEEL

8-Place front seat in most forward position with seat back in most nearly vertic

position .

9-Check the aircraft date of registration-refer TCDS prior to first march 1978:drain o

& operatin fluid

10-The position of such items as spoilers, slats, flaps, and helicopter rotor systems is a

important factor when weighing an aircraft

11-Always refer to the manufacturer's instructions for the proper position of these item

CALIBRATE THE WEGHING SCALE

Zero out the reading on the scale refer to the manual

After completing the weighing operation, remove all load from the cells an

check to see if the cell reading is still zero

Weigh the chocks and record reading / tare weight(Any deviation from zero

referred to as the "zero scale shift" and constitutes the tare when using electron

weighing scales)

*note: get instructor approval

The direction of shift is the factor that determines whether the tare is added to o

subtracted from the scale reading


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Always follow the instructions of the manufacture whose scales you are using

JACK THE AIRCRAFT

Read aircraft manufacturer instruction prior to jacking

*rope of the jacking area / nobody should be in the aircraft

Jack the aircraft up ~ get instructor

Safety

-use approved and appropriate jacks-check the load capacity

-make sure there is no obstruction

-proper adapter or stress plate has been installed

-jack the aircraft up simultaneous and very slowly

-place on the nose or place support on the tail to prevent tipping

Place the weighing scale under the nose and main gears


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Safety

-chock the aircraft

-make sure the brakes are release

Jack the aircraft down

Safety

-make sure there is no obstruction & place the gears centre of the scale

-jack the aircraft down simultaneously and very slowly

LEVEL THE AICRAFT

1-Read manufacturer instruction and TCDS

2-Level the aircraft laterally using spirit level and adjusting the level condition o the

Aircraft by deflating or inflating the struts/tyres of the main landing gears using

Nitrogen -

3-Level at thejig located nut plate and screws at Station +94.63 and +132.94 on left

side of the tailcone.~get instructor

SAFETY:-

Avoid any contact with the aircraft

Slowly adjusting the regulator during charging the strut and release the strut slowly

3-Level the aircraft horizontally/longitudinally using the spirit level condition of the

aircraft by deflating or inflating the oleo struts of the nose gear using nitrogen gas


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~get instructor

SAFETY:-

Avoid any contact with the aircraft

Slowly adjusting the regulator during charging the strut and release the strut slowly

#GET INSTRUCTOR APPROVAL

READING WEIGHING SCALE

1-Read the weight shown on the scale for each gear ~ Get Instructor.

2-make sure colour of the wire cable are correct.

-nose wheel=yellow

-right main wheel=green

-left main wheel=red

SAFETY:-

Make sure the scale has been calibrated/zero

Make sure the unit use or shown on the scale is correct (lbs/kgs) and get a least

minimum of three readings to get the average.

Avoid contact with the aircraft.

3-deduct any tare weight, if applicable from each reading.


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4-Record the value in the weight and balance form.

5-the reading is :-nose wheel tire=220

- Right main wheel tire=530

-left main wheel tire=550

#GET INTRUCTOR APPROVAL

MEASURING THE DATUM

1-Read TCDS the position of datum

2-Using plum bob, chalk and measuring tape, mark the datum and weighing point,

using chalky line or

chalky string ~ Get Instructor.

3-Measure the distance in inches of the nose gear and both the main landing gears from

the datum.

4-Record the measurements.

NOSE WHEEL=-14 INCHES

MAIN WHEEL=+44 INCHES


HOUSE KEEPING / TIDY UP

1-removed the weighing scale from the aircraft ~ get instructor

2-fill up the fuel / replenish the oil as per TCDS, inflate tyres ~ get instructor

SAFETY:-

Use approved and correct type for fuel and oil

Install bonding strip / cable to prevent electrical- static build up

3-clean the area

4-return all tools and equipments to the tools store ~ get instructor


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CALCULATION AND DATA ENTRY

1.Calculate the empty weight of the aircraft(EW) and empty weight centre

gravity(EWCG) and record it in the weight and balance form.

#THE EMPTY WEIGHT (EW)=

WEIGHING SCALE

POINT

SCALE READING

(lbs)

TARE WEIGHT

(lbs)

NET WEIGHT

(lbs)

NOSE WHEEL 220 -3 217

RIGHT MAIN WHEEL 530 -3 527

LEFT MAIN WHEEL 550 -3 547TOTAL NET

WEIGHT

1291

The empty weight is 1291.00 lbs

#THE EMPTY WEIGHT OF THE GRAVITY (EWCG)=

WEIGHING POINT NET WEIGHT (lbs) ARM (inch) MOMENT(lb/inch)

NOSE WHEEL 217 -14 -3038

RIGHT MAIN WHEEL 527 +44 +23188

LEFT MAIN WHEEL 547 +44 +24068

TOTAL MOMENT 1291 44218

Total moment 44218

CG = -------------------- = ----------- = 34.25 inches

Total weight 1291


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2.Find the maximum gross weight of the aircraft and calculate the useful load for th

aircraft.Record it in weighing form G-11.

3.Sign the weighing form

4.Record the latest weight and balance data in the aircraft log book and sample o

aircraft log sheet for project G-11.

5.Sign the aircraft log book and aircraft log sheet G-11.

6.Make a report of your result finding or conclusion.


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IX - Model 152, 2 PCLM (Utility Category), Approved March 16, 1977

Engine S/N 15279406 through 15285594

Lycoming O-235-L2C

S/N 15285595 and on aircraft reworked per SK152-15 or SK152-16

Lycoming O-235-N2C

*Fuel 100LL/100 min. grade aviation gasoline

*Engine limits S/N 15279406 through 15285594

For all operations, 2550 r.p.m. (110 hp.)

S/N 15285595 and onFor all operations 2550 r.p.m. (108 hp.)

Propeller and 1. (a) McCauley 1A103/TCM 23.2 lb. (-36.5)

propeller limits Diameter: not over 69 in., not under 67.5 in.

Static rpm at full throttle (carburetor heat off and mixture

leaned to maximum r.p.m.) is 2280 to 2380 r.p.m. For

allowable variations in static r.p.m. at non-standard

temperatures, refer to the Service Manual.

(b) Spinner: Dwg. 0450073

*Airspeed Limits (IAS) Never exceed 149 knots

(See NOTE 4 on Use Maximum structural cruising 111 knots

of IAS) Maneuvering 104 knots

Flaps extended 85 knots

C.G. range (+32.65) to (+36.5) at 1670 lb.

(+31.0) to (+36.5) at 1350 lb. or less

Straight line variation between points given

Empty weight C.G. range None

Leveling means Jig located nut plates and screws at Stations +94.63 an

+132.94 on left side of tailcone

*Maximum weight 1670 lb.

1675 lb. ramp weight (S/N 15282032 and on)


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No. of seats 2 at (+39); (for child's optional jump seat, refer to

Equipment List)

Maximum baggage 120 lb. (Reference weight and balance data)

Name Date

WEIGHING FORM

MAKE MODEL SERIAL N

DATUM LOCATION:

WEIGHING CONDITION:

Main weighing point is located (- forward) (+ aft) of datum

Tail or nose weighing point is located (- forward) (+ aft) of datum

WEIGHING

POINT

SCALE

READING

- TARE = NET

WEIGHT

X ARM = MOME

LEFT MAIN

RIGHT MAIN

NOSE OR

TAIL

TOTAL AS

WEIGHED

Space for listing of items when aircraft is not Weighed Empty

ITEM NET WEIGHT ARM MOMENT

Aircraft AsWight

Fuel Gal.F #gal

Aircraft Empty Weight & CG

Maximum allowable gross weight Computed by:

Useful load A & P Number:

Date:


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APPENDIX

Tools and equipment. Instal the cable wire

Weighing Scale Washing the aircraft


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Measure the datum. Datum line

CONCLUSIONWhen the calculating a weight and balance report, certain procedures

must be followed in order to make the report. These procedures include mor

than just weighing ,we also understanding weight and balance term,nowing

how to prepare the aircraft for weighing.We also lern more about FAA

regulation that apply to the general aviation as compare to commercial

aviation that must be adhered.

In the other side, the pilot command of the aircraft has the responsibility on

every flight to know the maximum allowable gross weight of the aircraft an

CG limits. This allow the pilot to determine on the preflight inspection that

the aircraft is loaded in such a way that the CG is within the allowable limit

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Weight and Balance Report

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