SECTION 6 WEIGHT AND BALANCE/EQUIPMENT LIST TABLE …beechcraft.com/customer_support/technical_publications... · 2013-08-13 · Model G58 6-2 December, 2009 Section 6 THIS PAGE INTENTIONALLY

Model G58

SECTION 6WEIGHT AND BALANCE/EQUIPMENT LIST

TABLE OF CONTENTS

SUBJECT PAGE

sec06toc.fm Page 1 Monday, December 14, 2009 3:46 PM

Basic Empty Weight and Balance - Actual . . . . . . . . . . . 6-3

Sample Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-5

Weighing Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-6Dimensional Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-6

Basic Empty Weight and Balance Form . . . . . . . . . . . . . 6-9

Weight and Balance Record . . . . . . . . . . . . . . . . . . . . . . 6-10

Payload Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-12

Weight and Balance Diagram . . . . . . . . . . . . . . . . . . . . . 6-13

Moment Limits vs Weight Table . . . . . . . . . . . . . . . . . . . 6-14

Loading Computing Procedure . . . . . . . . . . . . . . . . . . . 6-15

Weight and Balance Loading Form . . . . . . . . . . . . . . . . 6-17

Useful Load - Payload, Weights and Moments Table. . 6-19Occupants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-19Baggage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-20

Useful Load Weight and Moments Table. . . . . . . . . . . . 6-21Usable Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21

Equipment List . . . . .Prepared on an individual airplane basis

6-1December, 2009

Model G58

Section 6

Wt and Bal/Equip List

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Section 6

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Wt and Bal/Equip ListModel G58

BASIC EMPTY WEIGHT AND BALANCE -ACTUAL

(THIS PAGE TO BE REPLACED UPONAIRCRAFT DELIVERY)

6-3December, 2009

Section 6


Wt and Bal/Equip List Model G58

SAMPLE LOADING(THIS PAGE TO BE REPLACED UPON

AIRCRAFT DELIVERY)

6-4 December, 2009

Section 6



INTRODUCTION

Every new Model G58 is delivered with the following formswhich are unique to each serial-numbered airplane:

• Basic Empty Weight and Balance (Actual)• Sample Loading• Equipment List

It is the Owner’s responsibility to ensure that changes in equip-ment and weight and balance are kept up to date. It is recom-mended that the Weight and Balance Record in this POH/AFMSection, or similar form, be used. The current Equipment Listand Basic Empty Weight and Balance data must stay with theairplane when it changes ownership. Hawker Beechcraft Cor-poration cannot maintain the current airplane configuration sta-tus.

The airplane Pilot-in-Command is responsible for the airplaneto be properly loaded for each flight. All pertinent weight andbalance loading data is presented in this POH/AFM Section.The airplane weight and center of gravity limits are shown onthe Weight and Balance Diagram page, with the moment limitsshown in the Moment Limits vs. Weight Table. A blank Weightand Balance Loading Form, along with Computing Procedureinstructions on how to complete it, are provided for the Pilot’suse, or to use as an example for creating a separate loadingform. Payload and fuel weights, center of gravities, moments/100 and applicable limits are shown on the Useful LoadWeights and Moments pages.

All Weights are in pounds (lb) and all Arms are in horizontalinches (in.) from the Fuselage Datum, which may also beexpressed as Fuselage Stations (FS). Moments/100 are inpound-inches (lb-in.).

6-5December, 2009

Section 6



WEIGHING INSTRUCTIONS

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6-6 December, 2009

Section 6



Periodic weighing of the airplane may be required to keep theBasic Empty Weight current. All changes to the airplane affect-ing weight and balance are the responsibility of the airplane’sowner and/or operator.

1. Three jack points are provided for weighing: two on thewing front spar at Fuselage Station 83.1 and one on theaft fuselage at Fuselage Station 271.0.

2. Fuel should be drained prior to weighing. Tanks aredrained from the regular drain ports with the airplane instatic ground attitude. When tanks are drained, 5.7pounds of trapped fuel remain in the airplane at Fuse-lage Station 81.6. The remainder of the unusable fuel tobe added to a drained system is 30.3 pounds at Fuse-lage Station 78.5.

3. Engine oil must be at the full level or completely drained.Total engine oil when full is 45 pounds at Fuselage Sta-tion 43.

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

5. The airplane must be longitudinally and laterally levelwith the landing gear fully extended at the time of weigh-ing. Leveling screws are located on the left side of thefuselage at Fuselage Station 152.25 (approximately).Longitudinally level attitude is determined with a plumbbob. Laterally level attitude is obtained when the verticaldistance from each wing tip to the floor is equal.

6-7December, 2009

Section 6



6. Measurement of the reaction arms for a wheel weighingis made using a steel measuring tape. Measurementsare taken with the airplane level on the scales, from thereference (a plumb bob dropped from the center of eithermain jack point) to the axle center line of the main gearand then to the nose wheel axle center line. The mainwheel axle center line is best located by stretching astring across from one main wheel to the other. All mea-surements are to be taken with the tape level with thehangar floor and parallel to the fuselage center line. Thelocations of the wheel reactions will be approximately atFuselage Station 96.7 for main wheels and FuselageStation -10.3 for the nose wheel.

7. Jack point weighings are accomplished by placingscales at the jack points specified in step 1 above. Sincethe center of gravity of the airplane is forward of Fuse-lage Station 83.1, the tail reaction of the airplane will bein an up direction. This can be measured on regularscales by placing ballast of approximately 200 poundson the scales to which the aft weighing point is attachedby cable of adjustable length. The up reaction will thenbe total ballast weight minus the scale reading and isentered in the weighing form as a negative quantity.

8. Weighing should always be made in an enclosed areawhich is free from air currents. The scales used shouldbe properly calibrated and certified.

6-8 December, 2009

Section 6



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6-9December, 2009

Section 6



6-10 December, 2009

Section 6



6-11December, 2009

Section 6



TH06C 053923AA.AI

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(3RD SEAT

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(4TH SEAT

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(PILOT)(FRONT

SEAT PASS.)

CREW FS 75.0 TO FS 82.0

PASS. FS 152.0

AFT FACING PASS FS 111.0 TO FS 115.0

FWD FACING PASS FS 115.0 TO FS 120.0

BAGGAGE FS 108.0

BAGGAGE FS 150.0

BAGGAGE FS 180.0

FS -10.0

Maximum Baggage Weight is 300 pounds.Maximum Baggage Weight is 200 pounds between Front and Rear Spars with aft facing or removed 3rd and 4th seats. This location is not approved for baggage when the 3rd and 4th seats are facing forward.Maximum Baggage Weight is 400 pounds aft of the Rear Spar, with 5th and 6th seats removed, or 200 pounds with only the 5th or 6th seat removed.

Notes1. The floor structure load limit is 50 pounds per square foot

between the front and rear spars, and 100 pounds per square foot aft of the rear spar.

2. Any combination of the 3rd, 4th, 5th and 6th seats may be removed by the Owner/Operator or Pilot-in-Command, with the appropriate Log Book approved entry and Weight and Balance Record change. Refer to the Equipment List for seat weights and arms.

3. All Maximum Baggage Weights include baggage, cargo and installed equipment, if applicable. All baggage and cargo must be secured with an approved retention system.

Maximum Baggage Weight is 120 pounds.

FS 39.0BAGGAGE FS 15.0

NOTES:

6-12 December, 2009

Section 6



TH06C 053924AA.AI

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72 74 76 78 80 82 84 86 88

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6-13December, 2009

Section 6



MOMENT LIMITS vs. WEIGHT TABLE

WEIGHT(lb)

MOMENT/100 (lb-in. )

FWD LIMIT AFT LIMIT

38003850390039504000405041004150420042504300435044004450450045504600465047004750480048504900495050005050510051505200525053005350540054505500

28122849288629232960299730343071310831523196324132853330337534203465351035563601364736933740378638323879392639734020406741154163421042584307

32683311335433973440348335263569361236553698374137843827387039133956399940424085412841714214425743004343438644294472451545584601464446874730

6-14 December, 2009

Section 6



LOADING COMPUTING PROCEDURE

NOTELoadings may be prepared accumulatingweights and moments/100 only and usingthe Moment Limits vs. Weight Table forStep 10. compliance. Or, by also includingthe calculated arms as indicated and usingthe Weight and Balance Diagram for Step10. compliance. For each step that indi-cates the Arm to be calculated, divide thetotal moment/100 by the total weight andmultiply the result by 100.

1. Record the most current Basic Empty Weight, Arm(optional) and Moment on line 1. The moment must bedivided by 100 to correspond to the Useful Load Weightsand Moments Tables.

2. Record the weight, arm (optional) and correspondingmoment/100 from the appropriate Useful Load - Pay-load, Weights and Moments Table, for each payloaditem on lines 2. through 9.

3. Total the weight column and moment/100 column todetermine the Zero Fuel Weight on line 10. Calculatethe arm.

4. Record the weight and corresponding moment/100 forthe total fuel loaded on line 11. Add the fuel weight andmoment/100 to the Zero Fuel Weight values to deter-mine the Ramp Weight on Line 12. Calculate the arm.

5. Record the weight and corresponding moment/100 forthe fuel to be used for start, taxi and take-off on Line 13.Subtract the fuel weight and moment/100 from the RampWeight values to determine the Take-off Weight on Line14. Calculate the arm.

6-15December, 2009

Section 6



6. Copy the fuel load weight only from Line 11. to Line 15.7. Off to the side, add the calculated fuel to destination to

the Start, Taxi and Run-Up fuel. Record the total weightonly on line 16.

8. Subtract the Line 16. weight from the Line 15 weight andrecord the results on Line 17. Obtain the correspondingmoment/100 from the Usable Fuel Table. Interpolationmay be necessary.

9. Copy the Zero Fuel Weight from Line 10. to Line 18.and the fuel remaining from Line 17. to Line 19. Add theLine 19. weight and moment/100 to the Line 18. valuesto determine the Landing Weight on Line 20. Calculatethe arm.

10. Refer to the Moment Limits vs. Weight Table or theWeight and Balance Diagram and ensure that the ZeroFuel Weight, Take-Off Weight and Landing Weightare all within the Weight and Center of Gravity orMoment/100 Limits. If not, rearrange or remove UsefulLoad Item(s) to stay within the limits.

6-16 December, 2009

Section 6



WEIGHT AND BALANCE LOADING FORM

Serial No.: ______________ Date: ___________

LINE ITEMWEIGHT

(lb)ARM(in.)

MOMENT100

(lb-in.)

1. BASIC EMPTY WEIGHT

2. Pilot and Front Seat Passenger

3. 3rd and/or 4th Seat Passengers

4. 5th and/or 6th Seat Passengers 152.0

5. Baggage - Nose Compartment 15.0

6. Baggage - Between Spars 108.0

7. Baggage - Aft of Rear Spar 150.0

8. Baggage - Aft Compartment 180.0

9. Other -

10. ZERO FUEL WEIGHT

11. Fuel Load

12. RAMP WEIGHT(DO NOT EXCEED 5524 LB)

13. *Less Fuel for Start, Taxi and Run-Up

14. TAKE-OFF WEIGHT(DO NOT EXCEED 5500 LB)

15. Fuel Load from Line 11.

16. Less Fuel to Destination including Start,Taxi and Run-up from Line 13.

17. Fuel Remaining - Moment/100 fromUsable Fuel Table

18. Zero Fuel Weight from Line 10.

19. Add Fuel Remaining from Line 17.

20. LANDING WEIGHT(DO NOT EXCEED 5400 LB)

* Fuel for start, taxi and run-up is typically 24 lb with a Moment/100 of 20 lb-in., which may operationally vary.

6-17December, 2009

Wt and Bal/Equip List Model G58Section 6

6-18

WEIGHT AND BALANCE LOADING FORM

Serial No.: ______________ Date: ___________

LINE ITEMWEIGHT

(lb)ARM(in.)

MOMENT100

(lb-in.)

1. BASIC EMPTY WEIGHT

2. Pilot and Front Seat Passenger

3. 3rd and/or 4th Seat Passengers

4. 5th and/or 6th Seat Passengers 152.0

5. Baggage - Nose Compartment 15.0

6. Baggage - Between Spars 108.0

7. Baggage - Aft of Rear Spar 150.0

8. Baggage - Aft Compartment 180.0

9. Other -

10. ZERO FUEL WEIGHT

11. Fuel Load

12. RAMP WEIGHT(DO NOT EXCEED 5524 LB)

13. *Less Fuel for Start, Taxi and Run-Up

14. TAKE-OFF WEIGHT(DO NOT EXCEED 5500 LB)

15. Fuel Load from Line 11.

16. Less Fuel to Destination including Start,Taxi and Run-up from Line 13.

17. Fuel Remaining - Moment/100 fromUsable Fuel Table

18. Zero Fuel Weight from Line 10.

19. Add Fuel Remaining from Line 17.

20. LANDING WEIGHT(DO NOT EXCEED 5400 LB)

* Fuel for start, taxi and run-up is typically 24 lb with a Moment/100 of 20 lb-in., which may operationally vary.

December, 2009


Wt and Bal/Equip ListSection 6

Model G58

USEFUL LOAD - PAYLOAD, WEIGHTS AND MOMENTS TABLE

OCCUPANTS

Weight (lb)

Pilot & 2nd Seats3rd & 4th Seats

5th & 6th SeatsAft Facing (Club Arr.) Forward Facing

Fwd. Pos.A

Aft Pos. Fwd. Pos Aft Pos.n.)

Fwd. Pos.Arm 115 (in.)

Aft Pos.Arm 120 (in.)

Arm 152 (in.)

b-in.)

100110120130140150160170180190200

115127138150161173184196207219230

120132144156168180192204216228240

152167182198213228243258274289304

Note: Occupan reme positions. Intermediate positions (0.75 in. increments forthe front seats a tion of the Moment/100 values.

6-19December, 200

sec06fo.fm Page 1 Monday, December 14, 2009 3:59 PM

rm 75 (in.) Arm 82 (in.) Arm 111 (in.) Arm 115 (i

Moment/100 (l

75839098

105113120128135143150

829098

107115123131139148156164

111122133144155167178189200211222

115127138150161173184196207219230

t Arms and Moments/100 for adjustable seats are shown at their extnd 1.00 in. increments for the 3rd & 4th seats) will require interpola

9


6-20

USEFUL LOAD WEIGHTS AND MOMENTS TABLE

BAGGAGE

Weight(lb)

Nose Compart

ment

Arm 15 (in.)

Between Spars

(Aft Facing orRemoved 3rd

and4th Seats)

Arm 108 (in.)

Aft of Rear Spar

(5th or 6th Seat

Removed)

Arm 150 (in.)

Aft of Rear Spar

(5th and 6th Seats

Removed)

Arm 150 (in.)

Aft Compart

ment

Arm 180(in.)

Moment/100 (lb-in.)

102030405060708090

100110120130140150160170180190200210220240260280300320340360380400

235689

1112141517182021232426272930323336394245

112232435465768697

108119130140151162173184194205216

153045607590105120135150165180195210225240255270285300

153045607590105120135150165180195210225240255270285300330360390420450480510540570600

1836547290

108126144162180198216

NOTE: All baggage must be secured with an approved retention system.

December, 2009


Wt and Bal/Equip ListSection 6

Model G58

6-21

USEFUL LOAD WEIGHTS AND MOMENTS TABLE

USABLE FUEL

Variable Arm

GallonsWeight

(lb)166 Gal. 194 Gal.

Moment/100 (lb-in.)

10 60 46 46

20 120 92 92

30 180 140 140

40 240 189 189

50 300 238 238

60 360 288 288

70 420 338 338

80 480 388 388

90 540 439 439

100 600 489 489

110 660 539 539

120 720 590 590

130 780 641 641

140 840 692 692

150 900 743 743

160 960 793 793

166 996 824 824

170 1020 845

180 1080 899

190 1140 953

194 1164 974

December, 2009



6-22

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December, 2009


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SECTION 6 WEIGHT AND BALANCE/EQUIPMENT LIST TABLE …beechcraft.com/customer_support/technical_publications... · 2013-08-13 · Model G58 6-2 December, 2009 Section 6 THIS PAGE INTENTIONALLY