WEIGHT BALANCE/EQUIP LIST TABLE OF …i?eechcmft Super King Air B200 WEIGHING INSTRUCTIONS Section VI Weight & Balance/Equip List Periodic weighing of the airplane may be required

i?eechcmftSuper King Air B200

SECTION VIWEIGHT & BALANCE/EQUIP LIST

TABLE OF CONTENTS8200

SLIBJECT

Weighing Instructions .

Basic Empty Weight and Balance Form .

Dimensional and Loading Data .Standard Seating .Cargo Configuration .

Cabin Arrangement Diagram .

Useful Load Weights and Moments .Occupants .

g:~?n~econienis··:::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::Usable Fuel .: .

Density Variation of Aviation Fuel .

Loading Instructions .

Cargo Loading .

Computing Procedure .

Weight and Balance Loading Form .

Weight and Balance Diagram .

Moment Limits Versus Weight Graph .

Moment Limits Versus Weight Table .Center of Gravity Limits (Landing Gear Down) .

Equipment Item Number Location Diagram .

Weight and Balance (B200C) .

PAGE

6-3

6-4

6-56-56-6

6-7

6-86-86-96-9

6-10

6-12

6-13

6-13

6-13

6-14

6-15

6-16

6-176-17

6-18

6-19

Equipment List Prepared on an Individual Airplane Basis

December, 1994 6-1

Section VIWeight & BalancelEquip List

6·2

THIS PAGE INTENTIONALLY LEFT BLANK

<DeechcmftSuper King Air 8200

December, 1994

'i?eechcmftSuper King Air B200

WEIGHING INSTRUCTIONS

Section VIWeight & Balance/Equip List

Periodic weighing of the airplane may be required to keep the Basic Empty Weight current. Frequency ofweighing is to be determined by the operator. All changes to the airplane affecting weight and/or balance arethe responsibility of the airplane operator.

1. Airplane may be weighed on wheels or jacks points. Three jack points are provided: one on the nosesection of the fuselage at station 83.5, and one on each wing center section rear spar at station 225.5.Wheel reaction locations should be measured as described in paragraph 6 below.

2. Fuel should be drained preparatory to weighing. Tanks are drained from the regular drain ports with theairplane in static ground attitude. When tanks are drained, 10.5 pounds of unusable fuel remains in theairplane at an arm of 188.0 inches. The remainder of the unusable fuel to .be added to a drained system is 33.5 pounds at station 164.0.

3. Engine oil must be at the full level in each tank. Total engine oil aboard when both tanks are full is 62pounds at an arm of 131.0 inches.

4. To determine airplane configuration at time of weighing, installed equipment is checked against the airplane equipment list or superseding forms. All equipment must be in its proper place during weighing.

5. The airplane is placed on the scales in a level attitude. Leveling screws are located on the fuselageentrance door frame. Leveling is accomplished with a plumb bob. Jack pad leveling may require thenose gear shock to be secured in the static position to prevent its extension. Wheel weighings can beleveled by varying the amount of air in the shocks and tires.

6. Measurement of the reaction arms for a wheel weighing is made using the nose jacking point for a reference. Using a steel measuring tape, measurements are taken with the airplane level on the scalesfrom a reference (a plumb bob hung from the center of the nose jacking point) to the axle center line ofthe nose gear and then from the nose gear axle center line to the main wheel axle center line. The mainwheel axles center line is best located by stretching a string across from one main wheel to the other.All measurements are to be taken with the tape level with the hangar floor and parallel to the fuselagecenter line. The locations of the wheel reactions will be approximately at an arm of 209 inches for mainwheels and 30 inches for the nose wheel.

7. The:Basic Empty Weight and Moment are determined from the scale readings. Items weighed which arenot part of the empty airplane are subtracted, i.e., usable fuel. Unusable fuel and engine oil are addedif not already in the airplane.

8. Weighing should always be made in a enclosed area which is free from air currents. The scales usedshould be properly calibrated and certified in accordance with the Bureau of Standards.

NOTEThe certificated maximum weight (this is 12,590 Ibs ramp weight for a normal category airplane) may not be exceeded with:

a. Full fuel and minimum crew (one pilot, 170 Ibs.) and/or

b. Each seat occupied and enough fuel for one-half hour operation at maximum continuouspower.

December, 1994 6-3


BASIC EMPTY WEIGHT AND BALANCE

Ci?eedtcmftSuper King Air B200

DATE: _

STRUT POSITION - NOSEEXTENDED 29.4COMPRESSED 30.8

MAIN208.5210.5

PREPARED BY:

JACK POINT LOCATIONFORWARD 83.5AFT 225.5

REACTION SCALEWHEEL - JACK POINTS READING

LEFT MAIN

TARE NET WEIGHT

STATIONOR

ARM MOMENT

RIGHT MAIN

SUB TOTAL

NOSE

TOTAL (AS WEIGHED)

'/"/"/ ./

'/ ,//./h "/ '-';/ '/ 'l"/ "/ '// '/

'//////////////h

SPACE BELOW PROVIDED FOR ADDITIONS AND SUBTRACTIONS TO AS WEIGHED CONDITfoN

EMPTY WEIGHT

ENGINE OIL 62 131 8122UNUSABLE FUEL 44 170 7480

BASIC EMPTY WEIGHT-

6-4 December, 1994

~ftSuper King Air B200

SectIon VIWeight & BalanceJEqulp Ust

179.5"

LEVELING POINTSF.S. 309.25

REAR JACK POINTS·MOLD LINE REAR'SPAR F .S. 225.5

DIMENSIONAL AND LOADING D\TA

FRONT JACKPOINT F. S. 83.5 ---.;::I~-_--_--------------_...a-

...---- J79.5"---~

......------------ 525.0"---------------....

171.23 n 70.41 n

........-- LEMAC ---.......... MAC

MOLD LINE ----+-.....cMAIN SPARF.S. 190.0

REFERENCE-- DATUM

F.S. 0.0

IROW II

I ROW

OCCIFANTCREWROW IROW IIROW IIILI

F.S.30

D

J:~ s .152

C WROW

CABIN

[]

I[]

FOYERI I

[]

f

[]

I ~~F.S.279 .

LI F.S. F.S.1.11 305 348CENIRQI)

F.S. 129F .5. J 76F.S. 215F.S. 259F.S. 293

CONFIGURATION

SIDE PASSENGERSEAT AND TOILET

BAGGAGE COMPARTMENT• FOYER - 'Ef?WR"<4d

AFT CABIN -~

BAGGAGE CAPACITY150

••

CENTROIDF.S. 293F.S. 325 I

NOTE: FOYER IS NOT EOUIPPED FOR LOOSE BAGGAGE; CLOTHING ON HANGERS MAY BE HUNGFROM THE ROD PROVIDED.

_LOADING DATA FOR STANDARD CONFIGURATIONS ONLY .

• -410 LBS FOR SERIALS PRIOR TO B6-1091. EXCEPT 88-1052 NOT EOUIPPED WITH BEECHKIT PIN 101-5068; 550 LBS FOR SERIALS B8-1052. B8-1091 AND AFTER. AND PRIORAIRPLANES EQUIPPED WITH BEECH KIT PIN 101-5068.

April, 1996 6-5

Super King Air B200 II ~beo Ai ftSection VI - Weight & Balance/Equip Ust a.. n rcra

LOADING DATACARGO CONFIGURATION

7. 410 LBS FOR SERIALS PRIOR TO B8-1091.EXCEPT BB-1052. NOT EQUIPPED WITH BEECHKIT PIN 101-5068; 550 LBS FORSERIALS B8-1052, 8B-1091 AND AFTERAND PRIOR AIRPLANES EQUIPPED WITHBEECH KIT PIN 101-5068.

BB06C960418 C

SECllON IIADaAI CENTRQI) ARM

A 880 LB. F.S. 171B 860 LB. F.S. 210C 830 LB. F.S. 2500 550 LB. F .. S. 288E SEE NOTE 7 F.S. 325

----F.S. 84.0

-----F.S.30.0

-0

EQUIPCOMPT

----F.S. 129.0

._•••'----F.S. 152.0

t-------~}SECTION A

1-------1---- F . S. 190.0

}

(MOLD LINE MAIN SPAR)t--------I SECTION B1--------1

J-------I----F.S. 230.0

I-------I} SECTION C

1--------:---- F · S. 270.0

t--------f} SECTION 0

\-- -1---- F . S. 305.0

} SECTION E

••••~----F.S. 348.0

I. ALL CARGO IN SECTIONS A. B.C ~ 0 MUST BE SUPPORTED ONAND SECURED TO THE SEAT TRACKSBY AN FAA APPROVED SYSTEM.

CARGO TIEDOWN PROVISIONSARE NOT PROVIDED.

5. CONCENTRATED FLOOR LOADINGS OFCARGO OR BAGGAGE IN SECTION EMUST NOT EXCEED 100 LBS. PERSQUARE FOOT.

4. FOOTMAN LOOPS IN SECTION E ARETO BE USED TO SECURE CARGO BAGGAGE IN THAT AREA ONLY.

6. ANY EXCEPTIONS TO THE ABOVEPROCEDURES WILL REQUIRE APPROVALBY A LOCAL FAA OFFICE.

2. CONCENTRATED CARGO LOADS INSECTIONS A. B. C & D MUST NOTEXCEED 200 LBS. PER SQUAREFOOT & MUST BE SUPPORTED ONTHE SEAT RAILS.

3. CARGO IN SECTION E IS TO BESECURED BY BEECH FURNISHEDBAGGAGE NET, WEBBING, ORSTRAPS.

NOTES:

LOADING DATA (CARGO CONFIGURATION)

6-6 April, 1997

CiJeechcmftSuper King Air B200


CABIN' ARRANGEMENT DIAGRAM

o o

o

o FRONT FACING TOILETo SIDE FACING TOILETWITH VANITY

o AFT FOLD UP S~ATS

_-------------------NOTES:-------------------..·0 SIDE FACING TOILET

IIIIIIIIII

1

The cabin seating may be arranged in different combinations. The diagrams marked~ above represent the seating arrangement established for this airplane prior todelivery. The passenger locations shown on the designated diagram are averages.Additional data for modified arrangements are noted. No diagrams are included forHi-density versions.

200-603-29

December, 1994 6-7


USEFUL LOAD WEIGHTS AND MOMENTS

OCCUPANTS

OeechcmftSuper King Air B200

USE CREW CABIN CHAIRS LAVATORY SEATCOLUMNSMARKED F.S.129 F.S. 171 F.S.176 F.S.215 F.S.259 F.S.293 F.S.335

XtWEIGHT MOMENT/100

80 103 137 141 172 207 234 26890 116 154 158 194 233 264 302

100 129 171 176 215 259 293 335110 142 188 194 237 285 322 369120 155 205 211 258 311 352 402130 168 222 - -- 229 280 337 381 436140 181 239 246 301 363 410 469150 194 257 264 323 389 440 503160 _206. 274 282 344 414 469 536170 219 291 299 366 440 498 570180 232 308 317 387 466 527 603190 245 325 334 409 492 557 637200 258 342 352 430 518 586 670210 271 359 370 452 544 615 704220 284 376 387 473 570 645 737230 297 393 405 495 596 674 771240 310 410 422 516 622 703 804

OCCUPANTS

USE TWO PLACE COUCH FOUR PLACE COUCH AFT FOLDCOLUMNS FORWARD POSITION AFT POSITION UP SEATSMARKED F.S.163 F.S.183 F.S. 208 F.S.228 F.S.247 F.S.266 F.S.330

XtWEIGHT MOMENT/100

80 130 146 166 182 198 213 26490 147 165 187 205 222 239 297

100 163 183 208 228 247 266 330110 179 201 229 251 272 293 363120 196 220 250 274 296 319 396130 212 238 270 296 321 346 429140 228 256 291 319 346 372 462150 245 275 312 342 371 399 495160 261 293 333 365 395 426 528170 277 311 354 388 420 452 561180 293 329 374 410 445 479 594190 310 348 395 433 469 505 627200 326 366 416 456 494 532 660210 342 384 437 479 519 559 693220 359 403 458 502 543 585 726230 375 421 478 524 568 612 759240 391 439 499 547 593 638 792250 408 458 520 570 618 665 825-

6-8 December, 1994

'ikechcraftSuper King Air 8200


BAGGAGE


(Clothing on Hangers)WEIGHT FOYER AFT CABIN

F.S.292 F.S.325MOMENT/100

10 29 3320 58 6530 88 9840 117 13050 146 16360 175 19570 204 22880 234 26090 263 293

100 292 325200 650300 975370 1203400 1300500 1625510 1658550 1788

*SEE CABIN ARRANGEMENT DIAGRAM

CABINET CONTENTS

USE CHART FORWARD MIDDLE AFT COUCH

COLUMNS CASES CABINET CABINET CABINET DRAWERS

MARKED F.S.l48 F.S.158 F.S.l96 F.S.272 F.S.173X.WEI~HT MOMENT/100

10 15 16 20 27 1720 30 32 39 54 3530 44 47 59 82 5240 59 63 78 10950 74 7960 9570 11180 12690 142

100 158

NOTE: Weight and Moment/100 of Cabinet Contents must be included in all loadingcomputations.

December, 1994 6-9



CARGO

Ci2eecbcraftSuper King Air 8200

COMPARTMENT *A B C 0 E

F.S. 152-190 FS. 190-230 FS.230-270 F.S. 270-305 FS.305-348WEIGHT CENTROID

F.S. 171 FS.210 F.S.250 F.S.288 F.S.325MOMENT/100

10 17 21 25 29 3320 34 42 50 58 ·,6530 51 63 75 86 9840 68 84 100 115 13050 86 105 125 144 16360 103 126 150 173 19570 120 147 175 202 22880 137 168 200 230 26090 154 189 225 259 293

100 171 210 250 288 325200 342 420 500 576 650300 513 630 750 864 975400 684 840 1000 1152 1300500 855 1050 1250 1440 1625510 872 1071 1276 1469 1658550 940 1155 1375 1584 1788600 1026 1260 1500700 1197 1470 1750800 1368 1680 2000 NOTE: All cargo must be830 1419 1743 2075 supported by the seat tracks860 1471 1806 in a uniform distribution and880 1505 tied down to the tracks by an

FAA approved method.

*Refer to LOADING DATA CARGO CONFIGURATION.

6·10 December, 1994


USEFUL LOAO- WEIGHTS AND MOMENTS

USABLE FUEL


6.4 LB/GAL 6.5 LB/GAL 6.6 LB/GAL 6.7 LB/GALGALLONS WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT

100 100 100 100

10 64 99 65 100 66 102 67 10320 128 197 130 200 132 203 134 20630 192 305 195 310 198 314 201 31940 256 423 260 430 264 436 268 44350 320 542 325 550 330 559 335 56760 384 662 390 672 396 683 402 69370 448 782 455 794 462 807 469 81980 512 904 520 918 528 932 536 94690 576 1023 585 1039 594 1055 603 1071

100 640 1142 650 1160 660 1178 670 1196110 704 1260 715 1280 726 1300 737 1319120 768 1379 780 1400 792 1422 804 1443130 832 1496 845 1519 858 1543 871 1566140 896 1615 . 910 1640 924 1665 938 1690150 960 1734 975 1761 990 1788 1005 1815160 1024 1852 1040 1881 1056 1910 1072 1939170 1088 1971 1105 2002 1122 2033 1139 2064180 1152 2090 1170 2122 1188 2155 1206 2188190 1216 2209 1235 2244 1254 2279 1273 2313200 1280 2328 1300 2365 1320 2401 1340 2437210 1344 2447 1365 2486 1386 2524 1407 2562220 1408 2567 1430 2607 1452 2647 1474 2687230 1472 2686 1495 2728 1518 2770 1541 2812240 1536 2806 1560 2850 1584 2894 1608 2938250 1600 2926 1625 2971 1650 3017 1675 3063260 1664 3045 1690 3093 1716 3140 1742 3188270 1728 3164 1755 3213 1782 3263 1809 3312280 1792 3283 1820 3334 1848 3386 1876 3437290 1856 3402 1885 3455 1914 3508 1943 3562300 1920 3521 1950 3576 1980 3631 2010 3686310 1984 3641 2015 3698 2046 3754 2077 3811320 2048 3760 2080 3819 2112 3878 2144 3936330 2112 3880 2145 3940 2178 4001 2211 4062340 2176 3999 2210 4062 2244 4124 2278 4187350 2240 4119 2275 4184 2310 4248 2345 4312360 2304 4244 2340 4310 2376 4377 2412 4443370 2368 4365 2405 4434 2442 4502 2479 4570380 2432 4489 2470 4560 2508 4630 2546 4700386 2470 4562 2509 4634 2548 4706 2586 4776400 2560 4741 2600 4815 2640 4889 2680 4963410 2624 4869 2665 4945 2706 5021 2747 5097420 2688 4997 2730 5075 2n2 5153 2814 5231430 2752 5126 2795 5206 2838 5286 2881 5366440 2816 5255 2860 5337 2904 5419 2948 5501450 2880 5386 2925 5470 2970 5554 3015 5638460 2944 5514 2990 5600 3036 5686 3082 5773470 3008 5645 3055 5733 3102 5821 3149 5909480 3072 5775 3120 5866 3168 5956 3216 6046490 3136 5907 3185 5999 3234 6091 3283 6184

500 3200 6040 3250 6134 3300 6229 3350 6323510 3264 6172 3315 6269 3366 6365 3417 6462520 3328 6307 3380 6405 3432 6504 3484 6602530 3392 6441 3445 6542 3498 6643 3551 6743540 3456 6573 3510 6676 3564 6779 3618 6881544 3482 6626 3536 6729 3590 6832 3645 6936

December, 1994 6-11

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Ci?eechcmftSuper King Air B200

LOADING INSTRUCTIONS


It is the responsibility of the airplane operator to ensure that the airplane is properly loaded. At the time ofdelivery, Beech Aircraft Corporation provides the necessary weight and balance data to compute individualloadings. All subsequent changes in airplane weight and balance are the responsibility of the airplane ownerand/or operator.

The basic empty weight and moment of the airplane at the time of delivery are shown on the Basic EmptyWeight and Balance form. Useful load items which may be loaded into the airplane are shown on the Useful Load Weight and Moment tables. The minimum and maximum moments approved by the FAA are shownon the Moment Umits vs. Weight graph or table. These moments correspond to the forward and aft centerof gravity flight limits (landing gear down) for a particular weight. All moments are divided by 100 to simplifycomputations.

CARGO LOADING

The method of loading cargo, its placement in the airplane and the method of restraint should each be determined before starting the actual loading.

For loads that are evenly distributed in a given section, the useful Load Table under the heading of CargoCompartment should be used. For any load that cannot be located at the centroid of a section or that extendsover more than one .seetlon, it will be necessary to determine its own CG and its location in the airplane.Determine the CG arm (Fuselage Station) by measuring in inches, from a known location in the cabin to theCG of the load. Determine the "moment' for the load by multiplying the weight by the CG arm (FuselageStation). This resultant should be divided by 100 to be compatible with other loading data

COMPUTING PROCEDURE

1. Record the basic empty weight and moment from the Basic Empty Weight and Balance form (or fromthe latest superseding forms). The moment must be divided by 100 to correspond to Useful LoadMoments.

2. Record the weight and corresponding moment of each item to be carried. These values are found onthe Useful Load Weight and Moment tables.

3. Total the weight column and moment column. The total weight without usable fuel must not exceed theMaximum Zero Fuel Weight limitation of 11,000 pounds. All weight in excess of this limitation must befuel. The aUXiliary tanks may be used only when the main tanks are completely filled. The total take-offweight must not exceed the maximum allowable take-off weight and the total moment must be withinthe minimum and maximum moments shown on the Moment Limits Vs. Weight table or graph.

4. Using the page titled Useful Load Weights and Moments - Usable Fuel, determine the weight and corresponding moment of fuel to be used by subtracting the amount on board on landing from the amounton board at takeoff.

5. For landing configuration weight and balance, subtract the weight and moment of fuel to be used fromthe take-off weight and moment. The landing moment must be within the minimum and maximummoments shown on Weight and Moment Limits table for that weight. If the total moment is less than theminimum moment allowed, useful load items must be shifted aft, or forward load items reduced. If thetotal moment is greater than the maximum moment allowed, useful load items must be shifted forward,or aft load items reduced. If the quantity or location of load items is changed, the calculations must berevised and the moments rechecked.

6. Loadings may be made on the Weight and Balance Loading Form.

December, 1994 6-13


GJeechcraft SUPER KING AIR B200/B200C


WEIGHT AND BALANCE LOADING FORM

ISERIAL REGISTRATION NO:

PASSENGERS OR CARGOREF

ITEM

DATE:

WEIGHT MOM/100

ITEMWEIGHT MOM/100

LOCATION (ROW, F.S.,ETC)

1 BASIC EMPTY CONDo

2. PILOT

3. PASSENGERSOR CARGO

4. BAGGAGE

5. CABINETCONTENTS

········)i;~;.~.·!;;ii··.

~IB!~·l:7. FUEL LOADING

.:'::): ':" ...", ,>::..':: •... ,.:.<.'.'.i:":.:"<' :..:::.: .:

·:.:c:.,,::,:.,: .,::,.:. ;,::.(:-.::: :.:".'

:.: .

. -.'.'. :.' ....

9. *LESS FUEL FOR START,TAXI, AND TAKE OFF

.. : ".

I·" "

1:0. .SUB.·TOTAL·TAKE.OFF:CONDITION

",':

11 LESS FUEL TODESTINATION

.'..::.:, .... .' '. . ,.',:

TOTAL PASSENGERSOR CARGO 12j L.A.NDlNG·:CONDITION

..;..•. , .:,.·c· ..... ,;.'.." ,..••••....:.,:..,.,.:, :::"..''::': ..::

i ..... ,x':iI:: ..·, ...... .....

*Fuel for start, taxi and take-off is normally 90 Ibs at an average moment/100 of 177.

6-14 December, 1994

~ftSuper King Air 8200

Section VIWeight & BalancelEquip Ust

WEIGHT AND BALANCE DIAGRAM

180 182 184 186 188 190 192 194 196

CENTER OF GRAVITY -INCHES AFT OF DATUM

\ \ 1 I Max Take-OffILanding Weight

- \ \ } 1 1\ \ 1 I I\ \ , I ,\ \ I J

00 \ \ 'I , I I\ \ V I I

1800 \ \ I I I\ \

"

1 I I11600· \ \ V \ I I

\ \ J I 111400 \ I I

\ , ,1

11200 \ I I\ I

11000 \ MAX ZERO

\ --, FUEL WEIGHT

10800 \ l I,\ I

10600\, ,

I\ I

10400 \ /\ I

10200 \l ,

rooeo \ I

\ \

9800\~

9600 \\

9400 \, I I

\ ,1 I

J9200\

9000\ 1

8800?

l8600

,,8400 \,

8200 I \ I, 18000 \ I , I

\ I,. •7800 ~1

§7600 I I ~\ \ II~ I I CD

1 I 1 1

120

12200

12400

12600

December, 1994 6-15

SectionVIWeight & Balance/Equip List

MOMENT LIMITS vs WEIGHT


10600 ~.:.:.:.:.~.:.:.:.:.:."":':':':~~':':':':':':':",:,:":.::.~.:.~.:.~.~.~.~.:.~.'...'.'.::~.'.~.'.'.:.'.:.~.~:~t..:::~ i l'--J.~ "I'--..~~ ""'-.... m:$t~¥fHMi.~~ <, 11 ti\~ iW:ii§

•$::::::::·· ·:·:~;~?::l ~ '~ ''-.... litlt.tWmt

10000 ~.:.':.'.~.:.::'.:.:.:.:.:.:.:.:.:.:.:.:~:.:.:.:.: ~~: ~:.:~:.~~::.:.,~~·:·:.O.·.·:::;':::~~ "I'--.. "'-~:l: ' <, ~~ JtW£\It.ml~

6-16 December, 1994


Section VIWeight & Balance/Equip Ust

MOMENT LIMITS VS. WEIGHT

MINIMUM MAXIMUM MINIMUM MAXIMUMWEIGHT MOMENT/100 MOMENT/100 WEIGHT MOMENT/100 MOMENT/100

7200 13032 14141 9900 17919 194447250 13122 14239 9950 18010 195427300 13213 14337 10000 18100 196407350 13304 14435 10050 18190 197387400 13394 14534 10100 18281 198367450 13484 14632 10150 18372 199357500 13575 14730 10200 18462 200337550 13666 14828 10250 18552 201317600 13756 14926 10300 18643 202297650 13846 15025 10350 18734 20327noo 13937 15123 10400 18824 20426n50 14028 15221 10450 18914 205247800 14118 15319 10500 19005 206227850 14208 15417 10550 19096 207207900 14299 15516 10600 19186 208187950 14390 15614 10650 19276 209178000 14480 15712 10700 19367 210158050 14570 15810 10750 19458 211138100 14661 15908 10800 19548 212118150 14752 16007 10850 19638 213098200 14842 16105

MAX 10900 19729 214088250 14932 16203 10950 19820 215068300 15023 16301 ZERO 11000 19910 21604-8350 15114 16399 FUEL 11050 20000 217028400 15204 16498 WEIGHT 11100 20091 218008450 15294 16596 11150 20182 218998500 15385 16694 11200 20272 219978550 15476 16792 11250 20362 220958600 15566 16890 11300 20461 221938650 15656 16989 11350 20570 222918700 15747 17087 11400 20679 223908750 15838 17185 11450 20789 224888800 15928 17283 11500 20898 225868850 16018 17381 11550 21008 226848900 16109 17480 11600 21118 227828950 16200 17578 11650 21228 228819000 16290 17676 11700 21338 229799050 16380 ln74 11750 21449 230n9100 16471 17872 11800 21559 231759150 16562 17971 11850 21670 232739200 16652 18069 11900 21781 233729250 16742 18167 11950 21892 234709300 16833 18265 12000 22003 235689350 16924 18363 12050 22115 236669400 17014 18462 12100 22226 237649450 17104 18560 12150 22338 238639500 17195 18658 12200 22450 239619550 17286 18756 12250 22562 240599600 17376 18854 12300 22674 241579650 17466 18953 12350 22787 242559700 17557 19051 12400 22899 243549750 17648 19149 12450 23012 244529800 ln38 19247 12500 23125 245509850 17828 19345

CENTER OF GRAVITY LIMITS (LANDING GEAR DOWN)

WEIGHT CONDITION FORWARD CG LIMIT AFT CG LIMIT

12,500 LBS (MAX. TAKE-OFF OR LANDING) 185.0 196.411,279 LBS OR LESS 181.0 196.4

December, 1994 6-17



FOYER ANDAFT CABIN AFT FUS.

,EQUIPMENT LIST

EQUIPMENT ITEM NUMBERLOCATION DIAGRAM

17-0I.8-0

THIS LIST ITEMIZES THE EQUIPMENT IN THE- BASICEMPTY CONDITION SPECIFIED TO BE INSTALLED WHENTHE AIRPLANE IS DELIVERED.LOCATIONS SHOWN FOR AVIONIC ITEMS INSTALLED INTHE NOSE. AND AFT BAYS ARE APPROXIMATELY THECENTER OF THE BAY. WHEN REPLACING ORRELOCATING EQUIPMENT ACTUAL LOCATIONDIMENSIONS SHOULD BE USED.

5-06-0

3·04-0

COCKPIT

FS8414.2

NOSE

FS 190.0MOLD LINEMAIN SPAR

8200-603-52

6-18 December, 1994


SECTION VIWEIGHT & BALANCE/EQUIP LIST

TABLE OF CONTENTSB200C

SUBJECT PAGE

Weighing Instructions 6-21

Baisc Empty Weight and Balance Form 6-22

Change from Passenger to Cargo Configuration -............... 6-23

Dimensional and Loading Data 6-24Standard Seating 6-24Cargo Configuration· 6-25

Cabin Arrangement Diagrams ., ~................................. 6-26

Useful Load Weights and Moments ~ !..................................................................................................... 6-27Occupants 6-27Baggage 6-28Cabinet Contents 6-28

S~~~eC~u~r~.~~.~~.~.::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: ~=~gDensity Variation of Aviation Fuel................................................................................................................................. 6-31

Loading Instructions........................................................................................................................................................ 6-32

Cargo Loading 6-32

Computing Procedure 6-32

Weight and Balance .Loading Form 6-33

Weight and Balance Diagram 6-34

Moment Limits Versus Weight Graph ~ ~.............................. 6-35

Moment Limits Versus Weight Table 6-36Center of Gravity Limits (Landing Gear Down) 6-36

Equipment Item Number Location Diagram 6-37

Equipment List Prepared on an Individual Airplane Basis

December, 1994 6-19


6-20


Ci?eechcmftSuper King Air 8200

December, 1994

CileechcmftSuper King Air B200

WEIGHING INSTRUCTIONS


Periodic weighing of the airplane may be required to keep the Basic Empty Weight current. Frequency ofweighing is to be determined by the operator. All changes to the airplane affecting weight and/or balance arethe responsibility of the airplane operator.

1. Airplane may be weighed on wheels or jacks points. Three jack points are provided: one on the nosesection of the fuselage at station 83.5, and one on each wing center section rear spar at station 225.5.Wheel reaction locations should be measured as described in paragraph 6 below.

2. Fuel should be drained preparatory to weighing. Tanks are drained from the regular drain ports with theairplane in static ground attitude. When tanks are drained, 10.5 pounds of unusable fuel remains in theairplane at an arm of 188.0 inches. The remainder of the unusable fuel to be added to a drained system is 33.5 pounds at station 164.0.

3. Engine oil must be at the full level in each tank. Total engine oil aboard when both tanks are full is 62 .pounds at an arm of 131.0 inches.

4. To determine airplane configuration at time of weighing, installed equipment is checked against the airplane equipment list or superseding forms. All equipment must be in its proper place during weighing.

5. The airplane is placed on the scales in a level attitude. Leveling screws are located on the fuselageentrance door frame. Leveling is accomplished with a plumb bob. Jack pad leveling may require thenose gear shcck.to be secured in the static position to prevent its extension. Wheel weighings can beleveled by varying the amount of air in the shocks and tires.

6. Measurement of the reaction arms for a wheel weighing is made using the nose jacking point for a reference. Using a steel measuring tape, measurements are taken with the airplane level on the scalesfrom a reference (a plumb bob hung from the center of the nose jacking point) to the axle center line ofthe nose gear and then from the nose gear axle center line to the main wheel axle center line. The mainwheel axles center line is best located by stretching a string across from one main wheel to the other.All measurements are to be taken with the tape level with the hangar floor and parallel to the fuselagecenter line. The locations of the wheel reactions will be approximately at an arm of 209 inches for mainwheels and 30 inches for the nose wheel.

7. The Basic EmptyWeight and Moment are determined from the scale readings. Items weighed which arenot part of the empty airplane are subtracted, i.e., usable fuel. Unusable fuel and engine oil are addedif not already in the airplane.

8. Weighing should alWays be made in a enclosed area which is free from air currents. The scales usedshould be properly calibrated and certified in accordance with the Bureau of Standards.

NOTEThe certificated maximum weight (this is 12,590 Ibs ramp weight for a normal category airplane) may not be exceeded with:

a. Full fuel and minimum crew (one pilot, 170 Ibs.) and/or

b, Each seat occupied and enough fuel for one-half hour operation at maximum continuouspower.

December, 1994 6-21



BASIC EMPTY WEIGHT AND BALANCE

DATE: _

STRUT POSITION - NOSEEXTENDED 29.4COMPRESSED 30.8

MAIN208.5210.5

SERIAL NO: _

REGISTRATION NO: _

PREPARED BY: _

JACK POINT LOCATIONFORWARD 83.5AFT 225.5

REACTION SCALEWHEEL - JACK POINTS READING TARE NET WEIGHT

STATIONOR

ARM MOMENT

LEFT MAIN

RIGHT MAIN

SUB TOTAL

NOSE

TOTAL (AS WEIGHED)

SPACE BELOW PROVIDED FOR ADDITIONS AND SUBTRACTIONS TO AS WEIGHED CONDITION

II

II

III

I

I

I I I

II

I;

\;

EMPTY WEIGHT

ENGINE OIL1

62 131 8122

UNUSABLE FUEL I44 170 I 7480

I

BASIC EMPTY WEIGHT Ii i

o<.0Co~

6-22 December, 1994

~Super King Air B200

Change from Passenger to Cargo Configuration

.._-------

Section VIWeight .& BalanceJEquip Ust

Date Ser. No. ---- Reg. No. _

Item Weight Arm Moment

Basic Empty Wt - Pass Config. (Pg 25)

~

Basic Empty Wt - cargo Config.

Basic Empty Wt - Pass Config.

Basic Empty Wt - Cargo Config.

December, 1994 6-23


iDeed1CI3ftSuper KIng Air B200

REAR ~ACK POINTSMOLD LINE REARSPAR F.S. 225.5

DIMENSIONAL AND LOADING IMTA

FRONT JACKPOINT F. S. 83. 5 ----~-----------------------

..---- 179.5"-----

171.23 U 70.41"....-- LEMAC---........- MAC

MOLD LINE -----t--...MAIN SPAR

F .5. 190.0

REFERENCEr--- DATUM

F.S. 0.0

IF.S.305

LAVATORY

CEN1RCJI)

F.S.129F .5. 171F.S. 222F.S. 258F.S. 335

CABIN

OJ

IROW II

ROW III

OCCIIMNT'

CREWROW IROW IIROW IIILAV PASS

[]

[] OJ OJ

II

F.S.152

C W ROW

AFTI CABIN

-----~---------

I

CONFIGURATION

AFT PASSENGER SEATAND TOILET

BAGGAGE COMPARTMENT

AFT CREW - ~

BAGGAGE CAPACITY

•CENTROID

F.S. 325

NOTE·MAXIMUM STRUCTURAL CAPACITY OF AFT CABIN IS 410 LBS FOR SERIALS PRIOR TO BL-58NOT EQUIPPED WITH BEECH KIT P/N 101-5068; 550 LBS FOR SERIALS BL-58 AND AFTER.AND PRIOR AIRPLANES EQUIPPED WITH BEECH KIT PIN 101-5068. BAGGAGE CAPACITY ISAMOUNT REMAINING AFTER SUBTRACTING WEIGHT OF THE TOILET AND OTHER EQUIPMENTINSTALLED (SEE EQUIPMENT LIST) AND LAVATORY PASSENGER WHEN CARRIED.

C9!5BB06C 1382 C

6-24 April, 1996

lIaytbeen Aircraft Super King Air B200Section VI • Weight & Balance/Equip List

LOADING DATACARGO CONFIGURATION

F.S. 30~---

F.S. 84--

F .S. 129--+-1

IT-D COCKPIT

SECTlON

III

I IIIV

MAXNUMS1RUCTURAL

CAPACITY

800 LBS1300 LBS1370 LBS

SEE NOTE 7

CENTROIDARM

F .S. 170F.S. 218F.S. 276F.S. 325

F.S. 152--

SECTIONI

F.S. 188~

SECTIONMOLDLINECMAIN SPAR II

F.S. 190 ABIN

F.S. 248--

SECTIONIII

F . S. 305--1~====1---,

AFTCABIN

F . S. 348---1'------'.--l

NOTES:I. ALL CARGO IN SECTIONS I, I I, & J I I

MUST BE SUPPORTED ON AND SECUREDTO THE SEAT TRACKS BY AN FAA APPROVEDSYSTEM.

2. CONCENTRATED CARGO LOADS IN SECTIONSI. I I ~ I I I MUST NOT EXCEED 200 LBS.PER SQUARE FOOT ~ MUST BE SUPPORTEDON THE SEAT RAILS.

3. CARGO IN SECTION IV IS TO BE SECUREDBY BEECH FURNISHED BAGGAGE NET,WEBBING, OR STRAPS.

4. FOOTMAN LOOPS IN SECTION IV ARE TO BEUSED TO SECURE CARGO/BAGGAGE IN THATAREA ONLY.

5. CONCENTRATED FLOOR LOADINGS OF CARGOOR BAGGAGE IN SECTION IV MUST NOTEXCEED 100 LBS. PER SQUARE FOOR.

6. ANY EXCEPTIONS TO THE ABOVE PROCEDURESWILL REQUIRE APPROVAL BY A LOCAL FAAOFFICE.

7.410 LBS FOR SERIALS PRIOR TO.BL-58NOT EQUIPPED WITH BEECH KITPIN 101-5068; 550 LBS FOR SERIALSBL-58 AND AFTER, AND PRIOR AIRPLANESEQUIPPED WITH BEECH KIT PIN 101-5068.

BB06C960419 C

April, 1997

LOADING DATA (CARGO CONFIGURATION)

6·25


o

o

tl SIDE FACING TOILET

CABIN ARRANGEMENT DIAGRAM

o

o AFT FOLD UP SEATS

'DeechcraftSuper King Air B200

o FRONT FACING TOILET

6-26

---------------NOTES:-------------.....

The cabin seating may be arranged in different combinations. The diagrams marked [jC

above represent the seating arrangement established for this airplane prior to delivery.The passenger locations shown on the designated diagram are averages. Additionaldata for modified arrangements is noted. No diagrams are included for Hi-densityversions. 8200-603-48

December, 1994

OeechcraftSuper King Air B200


OCCUPANTS


USE CREW CABIN CHAIRS LAVATORYCOLUMNS F.S.129 F.S. 171 F.S.176 F.S.206 F.S.222 F.S.251 F.S.258 F.S.335

MARKED X.WEIGHT MOMENT/100

80 103 137 141 165 178 201 206 26890 116 154 158 185 200 226 232 302

100 129 171 176 206 222 251 258 335110 142 188 194 227 244 276 284 369120 155 205 211 247 266 301 310 . 402130 168 222 229 268 289 326 335 436140 181 239 246 288 311 351 361 469150 194 257 264 309 333 377 387 503160 ,206 274 282 330 355 402 413 536170 219 291 299 350 377 427 439 570180 232 308 317 371 400 452 464 603190 245 325 334 391 422 4n 490 637200 258 342 352 412 444 502 516 670210 271 359 370 433 466 527 542 704220 284 376 387 453 488 552 568 737230 297 393 405 474 511 577 593 771240 310 410 422 494 533 602 619 804

OCCUPANTS

USE TWO PLACE COUCH FOUR PLACE COUCH AFT FOLDCOLUMNS FORWARD POSITION AFT POSITION UP SEATSMARKED F.S. 163 F.S.183 F.S.208 F.S.228 F.S.247 F.S. 266 F.S.330x.WEIGHT MOMENT/100 '

80 130 146 166 182 198 213 26490 147 165 187 205 222 239 297

100 163 183 208 228 247 266 330110 179 201 229 251 272 293 363120 196 220 250 274 296 319 396130 212 238 270 296 321 346 429140 228 256 291 319 346 372 462150 245 275 312 342 371 399 495160 261 293 333 365 395 426 528170 277 311 354 388 420 452 561180 293 329 374 410 445 479 594190 310 348 395 433 469 505 627200 326 366 416 456 494 532 660210 342 384 '437 479 519 559 693220 359 403 458 502 543 585 726230 375 421 478 524 568 612 759240 391 439 499 547 593 638 792250 408 458 520 570 618 665 825

December, 1994 6-27



BAGGAGE

AFT CABIN F.S.325

WEIGHT MOMENT/100

10 ( 3320 6530 9840 13050 16360 19570 22880 26090 293

100 325200 650300 975400 1300500 1625

. 510 1658550 1788

·SEE CABIN ARRANGEMENT DIAGRAM

CABINET CONTENTS

USE CHART FORWARD MIDDLE AFT COUCH

COLUMNS CASES CABINET CABINET. CABINET DRAWERS

MARKED F.S.148 F.S. 158 F.S. 196 F.S.272 F.S. 173

X-.+WEIGHT MOMENT/100

10 15 16 20 27 1720 30 32 39 54 3530 44 47 59 82 5240 59 63 78 10950 74 79

-,60 9570 11180 12690 142

100 158

CileechcmftSuper King Air B200

NOTE: Weight and Moment/100 of Cabinet Contents must be included in all loading computations.

December, 1994



CARGO COMPARTMENT


CABINAFT

CABINSection I Section II Section III Section IV

WEIGHT FS. 152-188 FS. 188-248 F.S. 248-305 F.S. 305-348CENTI tOlD

F.S. 170 F.S. 218 FS.276 FS.325MOMENT/l00

10 17 22 28 3320 34 44 55 6530 51 65 83 9840 68 87 110 13050 85 109 138 16360 102 131 166 19570 119 153 193 22880 136 174 221 26090 153 196 248 293

100 170 218 276 325200 340 436 552 650300 510 654 828 975400 680 872 1104 1300500 850 1090 1380 1625510 867 1112 1408 1658550 935 1199 1518 1788600 1020 1308 1656700 1190 1526 1932800 1360 1744 2208900 1962 2484

1000 2180 27601100 2398 30361200 2616 33121300 2834 35881370 3781

*Refer to LOADING DATA CARGO CONFIGURATION

December, 1994

NOTE: All cargo in Sections t." & III must be supported bythe seat tracks in auniform distribution and tieddown to the tracks by an FAAapproved method.

6-29



USABLE FUEL


6.4 LB/GAL 6.5 lB/GAL 6.6 L:l/GAL 6.7 LB/GALGALLONS WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT WEIGHT MOMENT

100 100 100 10010 64 99 65 100 66 102 67 10320 128 197 130 200 132 203 134 20630 192 305 195 310 198 314 201 31940 256 423 260 430 264 436 268 44350 320 542 325 550 330 559 335 56760 384 662 390 672 396 683 402 69370 448 782 455 794 462 807 469 81980 512 904 520 918 528 932 536 94690 576 1023 585 1039 594 1055 603 1071

100 640 1142 650 1160 660 1178 670 1196110 704 1260 715 1280 726 1300 737 1319120 768 1379 780 1400 792 1422 804 1443130 832 1496 845 1519 858 1543 871 1566140 896 1615 910 1640 924 1665 938 1690150 960 1734 975 1761 990 1788 1005 1815160 1024 1852 1040 1881 1056 1910 1072 1939170 1088 1971 1105 2002 1122 2033 1139 2064180 1152 2090 1170 2122 1188 2155 1206 2188190 1216 2209 1235 2244 1254 2279 1273 2313200 1280 2328 1300 2365 1320 2401 1340 2437210 1344 2447 1365 2486 1386 2524 1407 2562220 1408 2567 1430 2607 1452 2647 1474 2687230 1472 2686 1495 2728 1518 2no 1541 2812240 1536 2806 1560 2850 1584 2894 1608 2938250 1600 2926 1625 2971 1650 3017 1675 3063260 1664 3045 1690 3093 1716 3140 1742 3188270 1728 3164 1755 3213 1782 3263 1809 3312280 1792 3283 1820 3334 1848 3386 1876 3437290 1856 3402 1885 3455 1914 3508 1943 3562300 1920 3521 1950 3576 1980 3631 2010 3686310 1984 3641 2015 3698 2046 3754 20n 3811320 2048 3760 2080 3819 2112 3878 2144 3936330 2112 3880 2145 3940 2178 4001 2211 4062340 2176 3999 2210 4062 2244 4124 2278 4187350 2240 4119 2275 4184 2310 4248 2345 4312360 2304 4244 2340 4310 2376 43n 2412 4443370 2368 4365 2405 4434 2442 4502 2479 4570380 2432 4489 2470 4560 2508 4630 2546 4700386 2470 4562 2509 4634 2548 4706 2586 4n6400 2560 4741 2600 4815 2640 4889 2680 4963410 2624 4869 2665 4945 2706 5021 2747 5097420 2688 4997 2730 5075 2n2 5153 2814 5231430 2752 5126 2795 5206 2838 5286 2881 5366440 2816 5255 2860 5337 2904 5419 2948 5501450 2880 5386 2925 5470 2970 5554 3015 5638460 2944 5514 2990 . 5600 3036 5686 3082 sn3470 3008 5645 3055 5733 3102 5821 3149 5909480 3072 5n5 3120 5866 3168 5956 3216 6046490 3136 5907 3185 5999 3234 6091 3283 6184500 3200 6040 3250 6134 3300 6229 3350 6323510 3264 6172 3315 6269 3366 6365 3417 6462520 3328 6307 3380 6405 3432 6504 3484 6602530 3392 6441 3445 6542 3498 6643 3551 6743540 3456 6573 3510 6676 3564 6n9 3618 6881544 3482 6626 3536 6729 3590 6832 3645 6936

6-30 December, 1994

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LOADING INSTRUCTIONS


6-32

It is the responsibility of the airplane operator to ensure that the airplane is properly loaded. At the time ofdelivery, Beech Aircraft Corporation provides the necessary weight and balance data to compute individualloadings. All subsequent changes in airplane weight and balance are the responsibility of the airplane ownerand/or operator. .

The basic empty weight and moment of the airplane at the time of delivery are shown on the Basic EmptyWeight and Balance form. Useful load items which may be loaded into the airplane are shown on the Useful Load Weight and Moment tables. The minimum and maximum moments approved by the FAA are shownon the Moment Limits vs. Weight graph or table. These moments correspond to the forward and aft centerof gravity flight limits (landing gear down) for a particular weight. All moments are divided by 100 to simplifycomputations.

CARGO LOADING

The method of loading cargo, its placement in the airplane and the method of restraint should each be determined before starting the actual loading.

For loads that are evenly distributed in a given section, the useful Load Table under the heading of CargoCompartment should be used. For any load that cannot be located at the centroid of a section or that extendsover more than one section, it will be necessary to determine its own CGand· its -location in the airplane.Determine the CG arm (Fuselage Station) by measuring in inches, from a known location in the cabin to theCG of the load. Determine the "moment" for the load by mUltiplying the weight by the CG arm (FuselageStation). This resultant should be divided by 100 to be compatible with other loading data.

COMPUTING PROCEDURE

1. Record the basic empty weight and moment from the Basic Empty Weight and Balance form (or fromthe latest superseding forms). The moment must be divided by 100 to correspond to Useful LoadMoments.

2. Record the weight and corresponding moment of each item to be carried. These values are found onthe Useful Load Weight and Moment tables.

3. Total the weight column and moment column. The total weight without usable fuel must not exceed theMaximum Zero Fuel Weight limitation of 11,000 pounds. All weight in excess of this llrmtatlon must befuel. The auxiliary tanks may be used only when the main tanks are completely filled. The total take-offweight must not exceed the maximum allowable take-off weight and the total moment must be withinthe minimum and maximum moments shown on the Moment Umits Vs. Weight table or graph.

4. Using the page titled Useful Load Weights and Moments - Usable Fuel, determine the weight and corresponding moment of fuel to be used by subtracting the amount on board on landing from the amounton board at takeoff.

5. For landing configuration weight and balance, subtract the weight and moment of fuel to be used fromthe take-off weight and moment. The landing moment must be within the minimum and maximummoments shown on Weight and Moment Limits table for that weight. If the total moment is less than theminimum moment allowed, useful load items must be shifted aft, or forward load items reduced. If thetotal moment is greater than the maximum moment allowed, useful load items must be shifted forward,or aft load items reduced. If the quantity or location of load items is changed, the calculations must berevised and the moments rechecked.

6. Loadings may be made on the Weight and Balance Loading Form.

December, 1994



Cl]eechcraft SUPER KING AIR B200/B200c

WEIGHT AND BALANCE LOADING FORM

ISERIAL REGISTRATION NO: DATE:

PASSENGERS OR CARGOREF

ITEM WEIGHT MOM/100

ITEMWEIGHT MOM/1oo

LOCATION (ROW, F.S.,ETC)

1 BASIC EMPTY CONDo

2. PILOT

3. PASSENGERSOR CARGO

4. BAGGAGE

5. CABINETCONTENTS

7. FUEL LOADING

'.:.:....:::"::.:".:

9. *LESS FUEL FOR START,TAXI, AND TAKE OFF

.... . ...

:: .. / :.:.:..

..........:..: : .•... >

.,.::

...:.>....:.. ':::)'" ....:::

:< :>':-:,.::: :.:.

• •••

.,', .·i .... : .;.... ..::/: ....::

:..•.,.: <. i".":: .:.•.....:. :........

!: ::::: :.:,' :>:" :::":: ......: :.::·.'i:::·:

> !' :".:. ·:.i· ::'?i .:'::.'.:.'::::':'::. ",:::::

<:':: <.:::::. ..:::../:.

11 LESS FUEL TODESTINATION

TOTAL PASSENGERSOR CARGO

[:--<:::> :.::. .:>.

~:o,1·~ •.:.....>f·: .• i :> .. ,,>.:(i

*Fuel for start, taxi and take-off is normally 90 Ibs at an average moment/100 of 177.

December, 1994

B2()(H)()1-219

6·33



WEIGHT AND BALANCE DIAGRAM

, \ I ,Max Take-OffILanding Weight

- \ \ II I\ \ I I\ \ ,\ \ III: I

00 \ \ \/ I\ \ V I

1800 \ \ I I\ \ I I

11600 \ \ V I\ \ 1\ I

11400 \ \ I I\ \

,/

11200 \ \ I\ \ /

11000 1 \ l MAX ZERO

\ \ --FUEL WEIGHT

10800 \ \ I\ I

10600 \1

\10400 \ \

,\

10200 \ ,roooo \ l

\9800 \

\,

9600I

9400 II

9200 1 I,I

9000 I

8800\ I

8600 I1 I I

8400 l , ' I II

1 \ I8200\ 1 I

8000 \\ I J

I I\

~

7800 ~, I I 0\ I I

c:o

7600 6

I HI I I0

\ C\ImI I I I I

120

12200

12400

12600

180 182 184 186 188 190 192 194 196

CENTER OF GRAVITY --INCHES AFT OF DATUM

6-34 December, 1994


Section VIWeight & BalancelEquip Ust

MOMENT LIMITS vs WEIGHT

1220

12400

12600 %it1l1~1HW~\WWttllWl%&%llJt~ (ttl ~m$:lr{%l~~t%{JtttJJ§*{t%W fill &Wtt~l\\twtvi;~"'f~'k;~~~ffT'randing Weight

"'~

120

rJ)

o5 '1oc..

8600~.·.~.·.~.:.~.~~·.~:~.~..~·.~...:~~...:.~~~...S.....·.....:..:~.~~~~·.·.~:~~:a~:...~••:.:.:.~.~.~.:.~.~.~.l~. . I N,r-.... '" --. I'--r-.... ; tfi iff l~f~~f ~:1:' ~l"-t "'. ~ "~il\~ w: gJ

~~~ ~~ ",~ lMm~8oo°llti1rn "I'--~

7800'11 \t' ~r-.... ~~ ":1=,:~:~",:.~.::..;·.I~..:~:.:.:.·..:.:..·~.~.:::.s.:..:::·.:.~;::.:.:.:::.:.:.!:;.:.1..:~:~...:.:...~.~.~~;.~.;.:::::.;.:.:.·.:..·:.:.t.~::..::·:.;.::;.r-.:..·:.,:.·.~.:.~:.:.::.:·.~.::.:.:.:.fm~ol.76oo:\\~~ t'i--J '"~ ..... ~" n :"'E>~ ..

:::::ll%~ll:::~~~ 'N '"'" "" ~~~l' t'~: it~

::~.i.:.i.::....~.:.;:.,..;;....·.:.~.:.s:·.r.a.:.:.;.;.;.:..:;.:.:..~~..~:.....::...:'..:'.~..':.:.:.'.:..':.:.~.:.:.'...:.~..'..~.~..~.~.::~~ ~~~r-....~~"~~~ ::::~~:\~ 1 \ 'r-, " "' ~:tWi\lMJ

180 182 184 186 188 190 192 194 196

CENTER OF GRAVITY -- INCHES AFT OF DATUM

December, 1994 6-35


MOMENT LIMITS VS. WEIGHT


MINIMUM MAXIMUM MINIMUM MAXIMUMWEIGHT MOMENT/100 MOMENT/100 WEIGHT MOMENT/100 MOMENT/100

7200 13032 14141 9900 17919 194447250 13122 14239 9950 18010 195427300 13213 14337 ioooo 18100 196407350 13304 14435 iooso 18190 197387400 13394 14534 10100 18281 198367450 13484 14632 10150 18372 199357500 13575 14730 10200 18462 200337550 13666 14828 10250 18552 201317600 13756 14926 10300 18643 202297650 13846 15025 10350 18734 20327noo 13937 15123 10400 18824 204267750 14028 15221 10450 18914 205247800 14118 15319 10500 19005 206227850 14208 15417 10550 19096 207207900 14299 15516 10600 19186 208187950 14390 15614 10650 19276 209178000 14480 15712 10700 19367 210158050 14570 15810 10750 19458 211138100 14661 15908 10800 19548 212118150 14752 16007 108SO 19638 213098200 14842 16105

MAX 10900 19729 214088250 14932 16203

ZERO10950 19820 21506

8300 15023 16301FUEL 11000 19910 21604-

8350 15114 16399WEIGHT 11050 20000 21702

8400 15204 16498 11100 20091 218008450 15294 16596 11150 20182 218998500 15385 16694 11200 20272 219978550 15476 16792 11250 20362 220958600 15566 16890 11300 20461 221938650 15656 16989 11350 20570 222918700 15747 17087 11400 20679 223908750 15838 17185 11450 20789 224888800 15928 17283 11500 20898 225868850 16018 17381 11550 21008 226848900 16109 17480 11600 21118 227828950 16200 17578 11650 21228 228819000 16290 17676 11700 21338 229799050 16380 17774 11750 21449 230779100 16471 17872 11800 21559 231759150 16562 17971 11850 21670 232739200 16652 18069 11900 21781 233729250 16742 18167 11950 21892 234709300 16833 18265 12000 22003 235689350 16924 18363 12050 22115 236669400 17014 18462 12100 22226 237649450 17104 18560 12150 22338 238639500 17195 18658 12200 22450 239619550 17286 18756 12250 22562 240599600 17376 18854 12300 22674 241579650 17466 18953 12350 22787 242559700 17557 19051 12400 22899 243549750 17648 19149 12450 23012 244529800 17738 19247 12500 23125 245509850 17828 19345

CENTER OF GRAVITY LIMITS (LANDING GEAR DOWN)

WEIGHT CONDITION FORWARD CG LIMIT AFT CG LIMIT

12,500 LBS (MAX. TAKE-OFF OR LANDING) 185.0 196.411,279 LBS OR LESS 181.0 196.4

6-36 December, 1994

·Oeechcraft'Super King Air 8200

Section VIWeight & BalancelEqulp List

EQUIPMENT LIST

EQUIPMENT ITEM NUMBERLOCAnON DIAGRAM

FS305

AFTCABIN AFT FUS.

I7-0 I

8-0 '----===::1

THIS LIST ITEMIZES THE EQUIPMENT IN THE BASICEMPTY CONDITION SPECIFIED TO BE INSTALLED WHENTHE AIRPLANE IS DELIVERED.LOCATIONS SHOWN FOR AVIONIC ITEMS INSTALLED INTHE NOSE AND AFT BAYS ARE APPROXIMATELY THECENTER OF THE BAY. WHEN REPLACING ORRELOCATING EQUIPMENT ACTUAL LOCATIONDIMENSIONS SHOULD BE USED.

5-06-0

11-012-0

15-016-0

II

INACELLE

FS152

3-04-0

COCKPIT

FS84

NOSE

IFS 190.0

MOLD LINEMAIN SPAR

8200-603-51

December, 1994 6-37


6·38



December, 1994

Documents

WEIGHT BALANCE/EQUIP LIST TABLE OF …i?eechcmft Super King Air B200 WEIGHING INSTRUCTIONS Section VI Weight & Balance/Equip List Periodic weighing of the airplane may be required