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KC-10 Aircrew Training System 

Principles of Weight and Balance 

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Principles of Weight and Balance 

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TABLE OF CONTENTS 

1.0 INTRODUCTION .................................................................................................. 1-1 

2.0 OBJECTIVE .......................................................................................................... 2-1 

3.0 AERODYNAMICS AND PERFORMANCE ........................................................... 3-1 

4.0 SOURCE DOCUMENTS ...................................................................................... 4-1 

5.0 DEFINITIONS AND FORMULAS ......................................................................... 5-1 

6.0 CHARTS AND TABLES........................................................................................ 6-1 

7.0 LESSON EXERCISE ........................................................................................... 7-1 
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1.0 INTRODUCTION

One of your most important tasks is to accurately compute weight and balance 

information. To a great extent, aircraft safety and efficient performance depend on your 

attention to all the factors involved with this process. 

This workbook will provide you the knowledge necessary to utilize weight and balance 

formulas and procedures. It includes an explanation of basic aerodynamics, which 

shows the relation of weight and balance to aircraft performance. Next is a compilation 

of terms, from weight and balance publications, for your convenience as a ready 

reference. 

Questions will give you the opportunity to test your knowledge of the subject. If you 

miss a question, review the applicable information. If you have any questions, please 

check with your instructor. 
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2.0 OBJECTIVE

1. Compute KC-10 Weight and Balance. 
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3.0 AERODYNAMICS AND PERFORMANCE

3.1 General

The relation of weight and balance to aircraft performance begins with an explanation of 

how aircraft move through the air. All aircraft rotate around three axis, or lines of force. 

As shown in Figure 3-1, these are the vertical, lateral, and longitudinal axis. Of course, 

the movements are not done separately. Flight controls are designed to operate in a 

coordinated manner. Flight control systems are explained in your flight manual. 

Notice, the three axis intersect at the center of gravity. This is because aircraft must 

operate in compliance with a basic law of physics, which is: An object will move, or 

rotate, about its center of gravity. 

Figure 3-1. Aircraft Rotational Axis. 

LATERAL AXIS

PITCH

LONGITUDINAL AXIS

ROLL

VERTICAL AXIS

YAW

CENTER OF GRAVITY (CG)

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3.2 The Wing

Since the design of an aircraft’s wing plays a large part in defining the performance 

envelope and flying characteristics, it is important to understand the relationship of 

aircraft weight and balance to the wing. 

The overall shape and size of a wing or a horizontal stabilizer is defined as a wing 

planform. The primary impact of the planform on flight characteristics is in the realm of 

high speed and low speed flight. The KC-10 wing has been designed to maximize the 

aerodynamic advantages of the planform and minimize the disadvantages. 

3.3 Wing Loading

The most important factor involved in aircraft performance is weight, and how it is 

distributed within the wing and fuselage. This distribution affects wing loading and the 

wing’s ability to produce lift. When an airplane is in a static condition, the only loads 

imposed upon the structural components are the results of weight. In steady level flight, 

the structure is not only acted upon by weight but also by local air conditions, thrust, lift, 

and drag. An additional load is imposed when the airplane is subjected to acceleration, 

whether induced by the pilot or by rough air. When the wing encounters rough air and 

is subjected to gusts, the additional loads imposed are caused by abrupt changes in 

angle-of-attack. The structural wing loads are affected by the wing fuel load distribution, 

sequence of fuel usage, air load, wing and engine nacelle weight, and the weight of the 

fuselage and payload (cargo and passengers.) 

3.4 Inflight Wing and Fuselage Loads

When in level flight, the total supporting upload (total lifting force) on the wings equals 

the total airplane gross weight. Opposing downloads are fuselage, fuel, wing, and 

nacelle weights, as shown in figure 3-2. In order to lift the fuselage, the wing lifting 

capability must be greater than the total wing down loads. As a result, an upward 

bending moment is produced at the wing roots. To illustrate, think of the wing as a 

floating bridge. Place a heavy weight at the center, and the bridge will bend at this point. 

Since the weight is lowering the middle of the bridge, the ends will come up. If the 

weight is increased enough, the bridge will break. Going back to the wing, it is obvious 

what the results will be if there is too much weight in the fuselage, and not enough in the 

outboard wing tanks. 

Now, if the weight can be spread across the span of the wing, the angle, or bending 

moment, will be reduced. When the aircraft fuselage is heavy with cargo and/or body 

tank fuel, the wing tanks must be kept full and fuel burned from the body tanks. This 

action will reduce metal fatigue and increase the safety margin of the wing. Fuel 

loading also has a marked effect on the center of gravity (CG) location. 
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Figure 3-2. Inflight Wing & Fuselage Loads.

3.5 Center of Gravity and Aircraft Performance

The efficiency of the wing is dependent upon the location of the center of gravity (CG). 

The crew’s control of the CG begins before takeoff, and continues throughout the flight. 

To understand the role the CG plays in aircraft performance, it is necessary to discuss 

the relationship of CG to the Aerodynamic Center (AC) of the wing. The aerodynamic 

center of the KC-10 wing is located one quarter of the way back from the leading edge 

of the Mean Aerodynamic Chord (MAC). In other words, the AC is at 25% MAC. The AC 

does move about a bit during low and high speeds, but for practical purposes it is 

considered to be at 25% MAC. 

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The sum of wing uploads per side 

equals half the gross weight 

The sum of wing downloads 

per side equals wing, engine 

nacelle, and fuel weight TOTAL FUSELAGE WEIGHT

BENDING MOMENT 
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Figure 3-3. AC Position Within the MAC. 

The allowable CG range varies with weight, but for the purpose of this explanation, the 

limits are considered to be 8 percent forward and 29 percent aft. The resultant of any 

change in lift on the wing takes place at the AC. 

Figure 3-4. Wing Aerodynamic Center.

AC MAC

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ALLOWABLE

CG RANGE

8% - 29%

MAC

AERODYNAMIC CENTER

25% MAC

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The CG is the rotational axis of the aircraft. It is apparent then that a change in lift acting 

on the AC will create a pitching moment about the CG. For any given change in lift, the 

magnitude of the pitching moment depends on the distance of the CG from the AC. The 

closer the CG is to the AC, the less abrupt pitch changes will be. The advantages of this 

are: 

 (1) Mechanical forces on the flight controls and flight guidance 

system are less strenuous. 

 (2) The adverse effects of turbulence and other gust loads on 

the airframe are diminished. 

 (3) Aircraft performance is enhanced during marginal situations, 

such as a maximum gross weight takeoff on a very hot day. 

Figure 3-5. Effect of CG Location on Wing Rotation Forces.

The location of the CG in relation to the AC causes nose up or nose down forces on the 

wing. These forces work against control inputs and increase pilot workload. The flight 

controls at the aft end of the aircraft, known as the empennage, are used to trim out or 

neutralize them. The horizontal stabilizer is hinged at the aft spar. Its movement is 

controlled through pilot operated trim switches, or the autopilot. The stabilizer is 

adjusted as necessary to balance the force required (tail up or tail down) to counteract 

imbalances caused by CG movement, airspeed changes, or changes in control 

configurations. 

If the horizontal stabilizer were fixed, the balancing forces would have to be provided by 

the elevators alone. An increased drag penalty would be imposed on aircraft 

performance. Excess drag results in greater engine power requirements and fuel burn. 

In some extreme cases such as the CG at the forward or aft limit, full elevator deflection 

AERODYNAMIC CENTER

AERODYNAMIC CENTER

CENTER OF GRAVITY

CENTER OF GRAVITY

CHANGE IN LIFT

CHANGE IN LIFT

PITCH UP

PITCH DOWN

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may be required to offset the pitching moment. There would be a decided lack of 

additional elevator authority in the desired direction. In other words, the pilot would run 

out of controls. 

With a moveable stabilizer, required fore and aft control forces are trimmed to zero by 

moving the stabilizer, allowing the elevators full range of operation. 

Figure 3-6. Balancing Contribution of the Movable Stabilizer. 

DOWNWARD

BALANCING

FORCE

UPWARD

BALANCING

FORCE

WEIGHT

AFT C.G.

WEIGHT

FORWARD C.G.

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Figure 3-7. Balancing Contribution of the Elevators.

3.6 Summary

Section Three has presented an explanation of aerodynamic principles, which show the 

relationship of an aircraft’s center of gravity to the wing’s aerodynamic center. For 

safety and structural integrity, it is mandatory that the aircraft operate within flight 

manual specifications. The most important factor in this requirement is the accurate 

knowledge of the current gross weight and CG. 

The Flight Engineer uses the gross weight and CG to compute takeoff speeds, the 

stabilizer trim setting, and fuel use (fuel burn). When operating in situations such as a 

heavy fuel load and a cargo load that must meet zone load limitations, a lot will depend 

on your accuracy in computing weight and balance. 

DOWNWARD

BALANCING

FORCE

UPWARD

BALANCING

FORCE

WEIGHT

AFT C.G.

WEIGHT

FORWARD C.G.

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4.0 SOURCE DOCUMENTS

All aircraft are required to have a weight and balance history. This is maintained to 

ensure there are no unknown factors, such as equipment changes or major airframe 

modifications, which could affect safety or performance. These two volumes make up 

the weight and balance record. 

4.1 TO 1-1B-50 - Weight and Balance

Each Air Force aircraft is assigned a TO 1-1B-50, which provides the means to control 

weight and balance for the specified aircraft. This manual is to remain with the aircraft in 

accordance with instructions as outlined in the technical order. 

CHART A DD Form 365-1 

The Chart A, Basic Weight Checklist, is a list of equipment that is or may be installed in 

the aircraft. The manufacturer, prior to delivery, initiates it. 

Whenever equipment is added or removed from the aircraft, it is noted by a checkmark 

(9) in the applicable column. 

When checkmarks are entered in the “In Aircraft” column, these entries serve as the 

inventory of items included in the basic weight. Weight and balance personnel make 

periodic inventories. An inventory is required when: 

1. The pilot reports unsatisfactory flight characteristics. 

2. The aircraft undergoes a major periodic inspection, or has maintenance that 

alters the configuration. 

3. The aircraft is received at a new base. 

4. The aircraft is weighed. 

CHART B DD Form 365-2 

The Chart B, Aircraft Weighing Record, is the history of the actual weighing of the 

aircraft. 

CHART C DD Form 365-3 

The Chart C, Basic Weight and Balance Record, is a continuous history of the basic 

weight and moment resulting from structural and equipment changes. 

The weights and moments of items listed on the Chart A are entered in the Chart C, and 

a running total is kept. This is the aircraft’s basic weight and moment. 

At all times, the latest weight and moment entries are used for loading calculations. 
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4.2 TO 1C-10(K)A-5 – Basic Weight Checklist and Loading Data 

Each aircraft has a weight and balance handbook, containing aircraft specific data, to be 

used in conjunction with TO 1-1B-50. It contains a sample Chart A, Basic Weight 

Checklist and a Chart E, Loading Data. 

CHART E LOADING DATA 

The Chart E serves two functions. 

1. It has instructions for weighing the aircraft, which is a periodic requirement. 

2. It has instructions and the necessary information for completing DD Form 

365-4. 

DD FORM 365-4 (FORM F). 

The Form F is the official documentation of aircraft loading for the current flight. 

Instructions for use of the completed form are in the Flight Information Publication 

(FLIP) General Planning Document, Chapter 4. The following is presented for your 

information. 

DD Form 175, Item 19. WEIGHT AND BALANCE - When filing a flight plan, the pilot 

shall either file a DD Form 365-4 with the flight plan or certify on the flight plan that the 

loading for the proposed flight does not exceed the loading limits. When making this 

certification, he may cite a previously filed DD Form 365-4 for the particular aircraft. 

Enter one of the following: 

1. N/A - When the aircraft flight manual does not require completion of 

DD Form 365-4 for each mission. 

2. ATTACHED - If the DD Form 365-4 is attached. Note: Electronic 

computer data sheets may be used when information therein is 

identical to that required on the DD Form 365-4. 

3. (Filed at) / (date) , when citing a previously filed 

DD Form 365-4 for a normal loading. 

4. When required, a new DD Form 365-4 will be filed with the military 

Base Operations office, when flights originate from bases having 

such offices, or with the Airport Manager (or other suitable person) 

when flights originate from established flying areas without a Base 

Operations office. 

5. (Filed with) / when impracticable to file a DD Form 365-4 

with the flight plan. (This is the normal operation for the KC-10 to 

file the DD Form 365-4). 
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5.0 DEFINITIONS AND FORMULAS 

Several definitions and formulas are used in computing aircraft weight and balance. 

Since these are used regularly, they are presented here as a convenient reference. 

Source: 

TO 1C-10(K)A-5 Basic Weight Checklist and Loading Data 

5.1 Weight and Balance Definitions 

REFERENCE DATUM LINE 

A reference datum is a zero reference position from which distances are measured. 

Aircraft have three zero reference datum from which aircraft locations are measured in 

the longitudinal (using fuselage station), lateral (using buttlines), and vertical (using 

waterlines) directions. 

For transport type aircraft the RDL is placed in front of the nose, so that all 

measurements will be positive numbers. The KC-10 RDL is 239 inches ahead of the 

nose. 

Reference datum lines are also used in conjunction with lateral and vertical axis, but this 

lesson will be concerned with the one primarily used in computing weight and balance. 

LONGITUDINAL AXIS 

The longitudinal axis extends on a horizontal plane from the RDL through the fuselage 

to the tail. All lengthwise measurements, given in inches, are taken on the longitudinal 

axis, beginning at the RDL. 

ARM (A) 

Arm is the distance of a weight from a reference datum. 

AVERAGE ARM (AA) 

An average arm is calculated by adding the weights of several items, adding their 

moments, and dividing the total moments by the total weight. 

STATION NUMBER 

The location of fuselage identifiers, such as equipment items, crew locations, cargo 

compartments, etc. are labeled with station numbers, which are nothing more than the 

item’s arm, or distance in inches from the RDL. 
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COMPARTMENT 

Compartments are areas in the fuselage used for designated functions, such as cargo 

compartments, the avionics bay, and wheel wells. They are defined by their forward and 

aft fuselage stations, measured in inches from the RDL. For example, the ARO 

compartment is from Station 1761 to Station 2007. Cargo compartments are also 

labeled with alphabetical identifiers, such as Compartment A, DD, etc. 

 

CENTROID 

Centroid is commonly used as the average arm or geometric center of a compartment. 

ILLUSTRATIONS 

These illustrations show how the definitions are used. 

Figure 5-1 shows fuselage compartments. Their contents are listed in the Chart A. 

Figure 5-2 shows cargo compartments. 

Figure 5-3 shows another way a cargo centroid (CG) can be identified by Air Freight, 

rather than using the centroid symbol. The gross weight is written on a piece of tape, 

with an arrow pointing to the CG. Also, front and rear axle weights are written on tape 

placed over the front and rear wheels. 
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Figure 5-1. Fuselage Compartments. 

275

239 275 464 595 859 1100 1154 1360 1521 1761 2007

396 2007

B C

RDL D

STATION

ZERO

EF G J H KL M P
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Figure 5-2. Cargo Compartments 
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Figure 5-3. How a CG is identified on a vehicle. 
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MOMENT (MOM) 

Moment is the leverage, or force, affecting balance. Alternately, moment is the weight of 

an item, multiplied by its arm (distance from the RDL) in inches. Moments are 

expressed in inch pounds. 

SIMPLIFIED MOMENT 

As noted above moments are computed in inches, which can result in large, hard to use 

numbers. For convenience of use, moments are reduced by dividing the number by a 

constant factor. This size of this factor is decided upon by the aircraft designers. 

The KC-10 simplified moment constant is 10,000. The symbol is MOM/10,000. 

MEAN AERODYNAMIC CHORD (MAC) 

MAC is the average chord, or width, of the wing. To find the mean aerodynamic chord 

the manufacturer measures the wing chord, or width, at several points along the wing. 

Then, this total is divided by the number of measurements. The KC-10 MAC is 295.8 

inches. 

LEADING EDGE OF THE MEAN AERODYNAMIC CHORD (LEMAC) 

LEMAC is the distance from the RDL to the front edge of MAC. For the KC-10, it is 

1,312.0 inches from the RDL to LEMAC. 

CENTER OF GRAVITY (CG) 

The center of gravity (CG) is the point at which an aircraft would balance if it were 

suspended. CG is an arm measured in inches from the RDL. You may also see it 

labeled Center of Gravity Arm (CGA). 

CG LIMITS 

The CG limits, forward and aft, define the CG envelope. This is the distance the CG 

may move within the mean aerodynamic chord. CG limits are the result of aircraft 

design and testing, and must be strictly adhered to. 

PERCENT OF THE MEAN AERODYNAMIC CHORD (% MAC) 

% MAC is the CG expressed as a percent of MAC. This is attained by multiplying the 

decimal answer of less than one by 100, when working the CG formula. For example, 

0.225 is 22.5%. 

AERODYNAMIC CENTER (AC) 

The aerodynamic center is the theoretical point at which the total lift of the airfoil is 

concentrated. The relationship between the AC and the CG determines the flight control 
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response characteristics of the aircraft. For the KC-10, the AC is considered to be at 

25% of MAC. Alternately, the AC may be termed the Center of Lift (CL).

BASIC WEIGHT 

The basic weight is an aircraft’s weight as it is equipped to fly, before crew, fuel and 

other items of variable load are added. The basic weight record is kept on the Chart C 

(DD Form 365-3). 

BASIC MOMENT 

The basic moment is the sum of the moments of all items making up the aircraft basic 

weight. 

OPERATING WEIGHT 

The operating weight includes basic weight, crew, water, aircraft storage, extra 

equipment, emergency equipment and any configuration change. This is the weight of 

the aircraft before fuel cargo and passengers are added. 

ZERO FUEL WEIGHT (ZFW) 

The weight of a loaded aircraft without fuel. Included in the zero fuel weight is the weight 

of cargo, passengers, and crew. 

MAXIMUM ZERO FUEL WEIGHT (MZFW) 

The maximum zero fuel weight is the weight at which the aircraft can fly with zero 

usable fuel in the No. 1, 2, and 3 main wing tanks. For planning purposes, the weight of 

body tank fuel is considered to be cargo. This requirement is necessary to meet zoneloading limitations for the upper and lower fuselage compartments. 

5.2 WEIGHT AND BALANCE FORMULAS 

ROUNDING 

Rounding numbers is a standard process for simplifying an answer. The basic 

arithmetical rule is: Calculations must be carried out to at least one number greater than 

the value desired. Example: 26.4527 = 26.5 23.1416 = 23.1 

FORMULAS 

Simplified Moment = Moment 

 10,000 
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Weight = Moment Arm = Moment Moment = Weight X Arm 

 Arm Weight 

Aircraft CG (Arm) = Total (Gross) Moment 

 Total (Gross) Weight 

Aircraft %MAC = Arm - LEMAC X 100 

 MAC 

EXAMPLE 

 1392 - 1312 X 100 80 X 100 MAC = 27%

 295.8 295.8 

% MAC to Arm = % MAC X MAC + LEMAC 100 

EXAMPLE 

 25 X 295.8 + 1312 = 1386

 100 

WEIGHT - ARM - MOMENT (WAM) TRIANGLE 

The WAM triangle is a convenient tool for working weight and balance formulas. To 

solve for an unknown, simply multiply or divide the known numbers. 

Moment is above, so Moment divided by Weight (Arm) gives the dividend Arm (Weight). 

Weight (Arm) times Arm (Weight) gives the product Moment. 
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6.0 CHARTS AND TABLES

Since weight and balance calculations involve the repetitive use of standard data, the 

information is presented in Chart E as tabulated data. The first part of the chart, which is 

very informative, contains instructions for weighing the aircraft. 

6.1 Loading Data for Operational Items

Operational items consist of the crew, water for drinking and waste disposal, and storage 

provisions. 

6.1.1 Crew Positions

Crew weight is a constant of 215 pounds. The arm is the distance from the RDL to the crew 

position. The cumulative weight and moment gives you the total for the number of crew 

selected. These are what you enter in Ref. 3 of DD Form 365-4, the Form F. 

COCKPIT CREW 

POSITION WEIGHT 

(POUNDS) 

ARM MOMENT 

10,000 

CUMULATIVE 

WEIGHT 

CUMULATIVE 

MOMENT 

PILOT 

COPILOT 

FLIGHT ENGINEER 

BOOM OPERATOR 

OBSERVER 

215 

215 

215 

215 

215 

325 

325 

362 

360 

385 

7 

7 

8 

8 

8 

 215 

 430 

 645 

 860 

1075 

 7 

14 

22 

30 

38 

ARO COMPARTMENT (Not occupied during Takeoff and Landing) 

BOOM OPERATOR 

INSTRUCTOR 

OBSERVER/TRAINEE 

215 

215 

215 

1794 

1794 

1794 

39 

39 

39 

215 

430 

645 

 39 

 77 

116

Figure 6-1. Crew Positions.
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6.1.2 Stowage Provisions

There are three fuselage positions designated for stowing professional equipment and crew 

baggage. The left column reflects a storage unit at the aft end of the cargo compartment. 

The center column is a compartment just to the left of the galley. The right column is a unit, 

which is part of the Increased Accommodation Unit. The totals from the selected column 

are entered in Ref. 4, Crew=s Baggage. Any other baggage and equipment stowed in the 

cargo compartment is entered in Ref. 13. 

STORAGE 

CONTAINER 

AIRCRAFT 

STORAGE 

ACCOM. KIT - 

STORAGE 

CENTROID 1970 400.2 603.7 

WEIGHT MOMENT/10000 

10 

20 

30 

40 

50 

60 

70 

80 

90 

100 

200 

300 

400 

440 

500 

600 

686 

700 

800 

900 

1000 

1100 

1200 

1300 

1400 

1421 

2 

4 

6 

8 

10 

12 

14 

16 

18 

20 

39 

59 

79 

87 

99 

118 

135 

138 

158 

177 

197 

217 

236 

256 

276 

280 

0 

1 

1 

2 

2 

2 

3 

3 

4 

4 

8 

12 

16 

18 

20 

24 

27 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

1 

1 

2 

2 

3 

4 

4 

5 

5 

6 

12 

18 

24 

27 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

-- 

--

Figure 6-2. Stowage Provisions.
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6.1.3 Water Systems

Potable is the chemical designation for “drinkable.” Drinking and wastewater are listed in 

Ref. 5, Steward=s Equipment. Notice that water is converted from gallons to a percentage 

of volume. The most common entry is 550 pounds (100% of potable plus 25 lbs. for waste 

water) and 37 MOM. *

POTABLE WATER 

63 GALLONS MAXIMUM 

VOLUME 

(PERCENT OF MAX) 

WEIGHT 

(POUNDS) 

ARM 

(INCHES) 

MOMENT 

10,000 

10 

20 

30 

40 

50 

60 

70 

80 

90 

*100 

 53 

105 

158 

210 

263 

315 

368 

420 

473 

525 

676.3 

676.3 

 4 

 7 

11 

14 

18 

21 

25 

28 

32 

36 

WASTE WATER 

3 GALLONS MAXIMUM IN EACH TOILET 

*100 25 412.0 1 

100 25 589.0 1

Figure 6-3. Water Systems.
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6.2 Configuration Alternatives

There are 10 passenger seating configurations, A through J. This table shows the weight 

and MOM change to be entered in Ref. 8 should the Chart C entry differ from the actual 

configuration. For example: Seating has been changed from A to D, which is the IAU. Read 

from A across to D and find you must add 5,022 lbs and 368.5 MOM. The Ref. 8 Item entry 

will be: D75 14 þ 75 +. The middle figure is the arm, which is included for the convenience 

of weight and balance personnel. 

Figure 6-4. Weight and Moment Change, With H-Arms, Between Chart A 

Interior Configuration Alternatives. 

WEIGHT AND MOMENTS CHANGES, WITH H-ARMS, FOR 

CONFIGURATION ALTERNATIVES 

Figure 3-29 provides weight and moment changes, with H-arms, between 

the following Chart A interior configuration alternatives: 

 Code Configuration 

 A 14-personnel 

 B 16-personnel 

 C 20-personnel (23 pallets) 

 D 75-personnel (expanded) 

 E 25- or 27- pallet (all cargo) 

 F 6-additional crew 

 G 20-personnel, 17-pallet positions, cargo barrier net at 

station 948 (position 3), environmental curtain and bunk at 

station 576 (position 2) 

Code Configuration 

 H 53-personnel seats, one patient support pallet (6 

litters) in position 2 right, and one blank pallet in 

position 3 right. 

 I 53-personnel seats and 2 patient support pallets (9 

litters) in positions 2 right and 3 right. 

 J 31 useable seats, no cargo, no passengers 

Descriptions and arrangement illustrations for each configuration are 

included in the Cargo Loading Manual, TO 1C-10(K)A-9. 

A list of equipment included in each configuration is provided in the 

Equipment Inventory List, TO 1C-10(K)-21. 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-5 01 DEC 12 

6.3 Fuel Loading Data

Maintenance personnel to refuel the aircraft use these fuel load tables. Moments were 

computed on JP-8 fuel, which has a density of 6.7 pounds per gallon. Tables for other 

densities are in TO 1C-10(K)A-2-12, Servicing. 

Moments may be rounded to the nearest whole number i.e. 1782.4 to 1782.0, 3293.6 to 

3294.0. Weights may be rounded to the nearest 500 lb. increment i.e. 15,100 to 15,000; 

27400 to 27,500. Interpolation of weights and moments between the 500 lb increments is 

not required. 

These fuel tables are the basis for standard operational loads. Instructions for mission fuel 

management are in Sections III and IV of the flight manual. Boom Operator/Flight Engineer 

coordination during fuel configuration is important to ensure that all limitations are complied 

with. 

6.3.1 No. 1 and 3 Wing Tanks

FUEL 

(POUNDS) 

MOMENT 

10,000 

 FUEL 

(POUNDS) 

MOMENT 

10,000 

 FUEL 

(POUNDS) 

MOMENT 

10,000 

 500 

 1,000 

 1,500 

 2,000 

 2,500 

 3,000 

 3,500 

 4,000 

 4,500 

 5,000 

 5,500 

 6,000 

 6,500 

 7,000 

 7,500 

 8,000 

 8,500 

 9,000 

 9,500 

10,000 

10,500 

11,000 

11,500 

12,000 

12,500 

13,000 

13,500 

14,000 

14,500 

 70.0 

 139.9 

 209.6 

 279.3 

 348.8 

 418.2 

 487.5 

 556.6 

 625.7 

 703.2 

 782.9 

 864.2 

 946.9 

1,030.7 

1,115.6 

1,201.1 

1,287.2 

1,373.4 

1,459.4 

1,544.8 

1,629.3 

1,705.7 

1,782.4 

1,856.5 

1,928.5 

1,998.8 

2,068.0 

2,137.0 

2,206.4 

 15,000 

15,500 

16,000 

16,500 

17,000 

17,500 

18,000 

18,500 

19,000 

19,500 

20,000 

20,500 

21,000 

21,500 

22,000 

22,500 

23,000 

23,500 

24,000 

24,500 

25,000 

25,500 

26,000 

26,500 

27,000 

27,500 

28,000 

28,500 

29,000 

2,277.2 

2,351.4 

2,423.8 

2,496.1 

2,568.4 

2,640.6 

2,712.9 

2,785.2 

2,857.6 

2,930.0 

3,002.5 

3,075.1 

3,147.8 

3,220.6 

3,293.6 

3,366.7 

3,440.0 

3,511.5 

3,584.7 

3,658.0 

3,731.1 

3,804.2 

3,877.3 

3,950.2 

4,023.2 

4,096.0 

4,168.8 

4,238.5 

4,313.9 

 29,500 

30,000 

30,500 

31,000 

31,500 

32,000 

32,500 

33,000 

33,500 

34,000 

34,500 

35,000 

35,500 

36,000 

36,500 

37,000 

37,500 

38,000 

38,500 

39,000 

39,500 

40,000 

40,500 

40,704* 

41,000 

41,500 

42,000 

42,500 

43,000 

4,388.9 

4,463.6 

4,538.0 

4,612.3 

4,686.4 

4,760.4 

4,834.3 

4,908.3 

4,982.3 

5,056.4 

5,130.6 

5,205.1 

5,279.7 

5,354.6 

5,429.9 

5,505.4 

5,581.3 

5,657.5 

5,734.2 

5,811.2 

5,888.7 

5,966.6 

6,044.9 

6,076.9 

6,123.6 

6,202.6 

6,282.1 

6,361.8 

6,441.9 

Figure 6-5. No. 1 and 3 Wing Tanks.
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-6 01 DEC 12 

6.3.2 No. 2 Wing Tank

FUEL 

(POUNDS) 

MOMENT 

10,000 

FUEL 

(POUNDS) 

MOMENT 

10,000 

 FUEL 

(POUNDS) 

MOMENT 

10,000 

FUEL 

(POUNDS) 

MOMENT 

10,000 

 500 

 1,000 

 1,500 

 2,000 

 2,500 

 3,000 

 3,500 

 4,000 

 4,500 

 5,000 

 5,500 

 6,000 

 6,500 

 7,000 

 7,500 

 8,000 

 8,500 

 9,000 

 9,500 

10,000 

10,500 

11,000 

11,500 

12,000 

12,500 

13,000 

13,500 

14,000 

14,500 

15,000 

15,500 

16,000 

16,500 

17,000 

17,500 

66.4 

132.6 

198.8 

264.7 

330.6 

396.3 

461.9 

527.3 

592.7 

657.8 

722.9 

787.8 

852.6 

917.2 

981.7 

1,046.1 

1,111.7 

1,177.1 

1,242.4 

1,307.7 

1,373.1 

1,438.4 

1,503.7 

1,569.0 

1,634.3 

1,699.6 

1,764.8 

1,830.1 

1,895.4 

1,960.6 

2,025.9 

2,091.1 

2,156.3 

2,221.6 

2,286.8 

18,000 

18,500 

19,000 

19,500 

20,000 

20,500 

21,000 

21,500 

22,000 

22,500 

23,000 

23,500 

24,000 

24,500 

25,000 

25,500 

26,000 

26,500 

27,000 

27,500 

28,000 

28,500 

29,000 

29,500 

30,000 

30,500 

31,000 

31,500 

32,000 

32,500 

33,000 

33,500 

34,000 

34,500 

35,000 

2,352.0 

2,417.2 

2,482.4 

2,547.6 

2,612.7 

2,677.9 

2,743.1 

2,808.2 

2,873.3 

2,938.5 

3,003.6 

3,068.7 

3,133.8 

3,198.9 

3,264.0 

3,329.1 

3,394.1 

3,459.2 

3,524.2 

3,589.3 

3,654.3 

3,719.3 

3,784.3 

3,849.3 

3,914.3 

3,979.3 

4,044.2 

4,109.2 

4,174.1 

4,239.1 

4,304.0 

4,368.9 

4,433.8 

4,498.7 

4,563.6 

 35,500 

36,000 

36,500 

37,000 

37,500 

38,000 

38,500 

39,000 

39,500 

40,000 

40,500 

41,000 

41,500 

42,000 

42,500 

43,000 

43,500 

44,000 

44,500 

45,000 

45,500 

46,000 

46,500 

47,000 

47,500 

48,000 

48,500 

49,000 

49,500 

50,000 

50,500 

51,000 

51,500 

52,000 

52,500 

4,628.4 

4,693.3 

4,758.1 

4,823.0 

4,887.8 

4,952.6 

5,017.4 

5,082.2 

5,147.0 

5,211.8 

5,276.5 

5,341.3 

5,406.0 

5,470.7 

5.535.4 

5,600.1 

5,664.8 

5,729.4 

5,794.1 

5,858.7 

5,923.4 

5,988.0 

6,052.6 

6,117.2 

6,181.8 

6,246.3 

6,310.9 

6,375.4 

6,439.9 

6,504.5 

6,569.0 

6,633.4 

6,697.9 

6,762.4 

6,826.8 

53,000 

53,500 

54,000 

54,500 

55,000 

55,500 

56,000 

56,500 

57,000 

57,500 

58,000 

58,500 

59,000 

59,500 

60,000 

60,500 

61,000 

61,500 

62,000 

62,500 

63,000 

63,500 

64,000 

64,500 

65,000 

65,438* 

65,500 

66,000 

66,500 

67,000 

67,500 

68,000 

68,500 

69,000 

69,500 

6,891.2 

6,955.7 

7,020.1 

7,084.4 

7,148.8 

7,213.2 

7,277.5 

7,341.8 

7,406.2 

7,470.5 

7,534.7 

7,599.0 

7,663.3 

7,727.5 

7,791.7 

7,855.9 

7,920.1 

7,984.3 

8,048.5 

8,112.6 

8,176.8 

8,240.9 

8,305.0 

8,369.1 

8,433.1 

8,489.3 

8,497.2 

8,561.2 

8,625.2 

8,689.2 

8,753.2 

8,817.2 

8,881.1 

8,945.1 

9,009.0 

Figure 6-6. No. 2 Wing Tank.
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-7 01 DEC 12 

6.3.3 Forward Body Tank

FUEL 

(POUNDS) 

MOMENT 

10,000 

FUEL 

(POUNDS) 

MOMENT 

10,000 

 FUEL 

(POUNDS) 

MOMENT 

10,000 

FUEL 

(POUNDS) 

MOMENT 

10,000 

 500 

 1,000 

 1,500 

 2,000 

 2,500 

 3,000 

 3,500 

 4,000 

 4,500 

 5,000 

 5,500 

 6,000 

 6,500 

 7,000 

 7,500 

 8,000 

 8,500 

 9,000 

 9,500 

10,000 

10,500 

11,000 

11,500 

12,000 

12,500 

13,000 

13,500 

14,000 

14,500 

15,000 

 47.9 

 95.9 

143.8 

191.8 

239.7 

287.7 

335.6 

383.6 

431.5 

479.5 

527.4 

575.4 

623.3 

671.3 

719.2 

767.2 

815.1 

863.1 

911.0 

959.0 

1,006.9 

1,054.9 

1,102.8 

1,150.8 

1,198.7 

1,246.7 

1,294.6 

1,342.6 

1,390.5 

1,438.5 

15,500 

16,000 

16,500 

17,000 

17,500 

18,000 

18,500 

19,000 

19,500 

20,000 

20,500 

21,000 

21,500 

22,000 

22,500 

23,000 

23,500 

24,000 

24,500 

25,000 

25,500 

26,000 

26,500 

27,000 

27,500 

28,000 

28,500 

29,000 

29,500 

30,000 

1,486.4 

1,534.4 

1,582.3 

1,630.3 

1,678.2 

1,726.2 

1,774.1 

1,822.1 

1,870.0 

1,918.0 

1,965.9 

2,013.9 

2,061.8 

2,109.8 

2,157.7 

2,205.7 

2,253.6 

2,301.6 

2,349.5 

2,397.5 

2,445.4 

2,493.4 

2,541.3 

2,589.3 

2,637.2 

2,685.2 

2,733.1 

2,781.1 

2,829.0 

2,877.0 

 30,500 

31,000 

31,500 

32,000 

32,500 

33,000 

33,500 

34,000 

34,500 

35,000 

35,500 

36,000 

36,500 

37,000 

37,500 

38,000 

38,500 

39,000 

39,500 

40,000 

40,500 

41,000 

41,500 

42,000 

42,500 

43,000 

43,500 

44,000 

44,500 

45,000 

2,924.9 

2,972.9 

3,020.8 

3,068.8 

3,116.7 

3,164.7 

3,212.6 

3,260.6 

3,308.5 

3,356.5 

3,404.4 

3,452.4 

3,500.3 

3,548.3 

3,596.2 

3,644.2 

3,692.1 

3,740.1 

3,788.0 

3,836.0 

3,883.9 

3,931.9 

3,979.8 

4,027.8 

4,075.7 

4,123.7 

4,171.6 

4,219.6 

4,267.5 

4,315.5 

45,500 

46,000 

46,500 

47,000 

47,500 

48,000 

48,500 

49,000 

49,500 

50,000 

50,500 

51,000 

51,500 

52,000 

52,500 

53,000 

53,500 

54,000 

54,500 

55,000 

55,306* 

55,500 

56,000 

56,500 

57,000 

57,500 

58,000 

58,500 

59,000 

59,500 

4,363.4 

4,411.4 

4,459.3 

4,507.3 

4,555.2 

4,603.2 

4,651.1 

4,699.1 

4,747.0 

4,795.0 

4,842.9 

4,890.9 

4,938.8 

4,986.8 

5,034.7 

5,082.7 

5,130.6 

5,178.6 

5,226.5 

5,274.5 

5,303.8 

5,322.4 

5,370.4 

5,418.3 

5,466.3 

5,514.2 

5,562.2 

5,610.1 

5,658.1 

5,706.0 

Figure 6-7. Forward Body Tank. 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-8 01 DEC 12 

6.3.4 Center Wing Tank

Because of its large size, the center wing tank has 2 pages of fuel loads. Only the first page 

is shown. 

FUEL 

(POUNDS) 

MOMENT 

10,000 

 FUEL 

(POUNDS) 

MOMENT 

10,000 

 FUEL 

(POUNDS) 

MOMENT 

10,000 

 500 

 1,000 

 1,500 

 2,000 

 2,500 

 3,000 

 3,500 

 4,000 

 4,500 

 5,000 

 5,500 

 6,000 

 6,500 

 7,000 

 7,500 

 8,000 

 8,500 

 9,000 

 9,500 

10,000 

10,500 

11,000 

11,500 

12,000 

12,500 

13,000 

13,500 

14,000 

14,500 

15,000 

15,500 

16,000 

16,500 

17,000 

17,500 

67.4 

133.8 

199.5 

264.6 

329.5 

394.1 

458.7 

523.2 

587.7 

652.3 

716.9 

781.5 

846.1 

910.6 

975.0 

1,039.3 

1,103.5 

1,167.6 

1,231.5 

1,295.4 

1,359.3 

1,423.3 

1,487.9 

1,552.1 

1,616.3 

1,680.3 

1,744.4 

1,808.4 

1,872.4 

1,936.4 

2,000.3 

2,064.1 

2,128.0 

2,191.8 

2,255.6 

 18,000 

18,500 

19,000 

19,500 

20,000 

20,500 

21,000 

21,500 

22,000 

22,500 

23,000 

23,500 

24,000 

24,500 

25,000 

25,500 

26,000 

26,500 

27,000 

27,500 

28,000 

28,500 

29,000 

29,500 

30,000 

30,500 

31,000 

31,500 

32,000 

32,500 

33,000 

33,500 

34,000 

34,500 

35,000 

2,319.3 

2,383.0 

2,446.7 

2,510.3 

2,574.0 

2,637.5 

2,701.1 

2,764.6 

2,828.1 

2,891.6 

2,955.1 

3,018.5 

3,081.9 

3,145.2 

3,208.6 

3,271.9 

3,335.2 

3,398.5 

3,461.7 

3,524.9 

3,588.1 

3,651.3 

3,714.5 

3,777.6 

3,840.8 

3,903.9 

3,967.0 

4,030.0 

4,093.1 

4,156.1 

4,219.1 

4,282.1 

4,345.1 

4,408.1 

4,471.1 

 35,500 

36,000 

36,500 

37,000 

37,500 

38,000 

38,500 

39,000 

39,500 

40,000 

40,500 

41,000 

41,500 

42,000 

42,500 

43,000 

43,500 

44,000 

44,500 

45,000 

45,500 

46,000 

46,500 

47,000 

47,500 

48.000 

48,500 

49,000 

49,500 

50,000 

50,500 

51,000 

51,500 

52,000 

52,500 

4,534.0 

4,597.0 

4,659.9 

4,722.8 

4,785.7 

4,848.5 

4,911.5 

4,974.3 

5,037.2 

5,100.1 

5,162.9 

5,225.7 

5,288.6 

5,351.4 

5,414.2 

5,477.0 

5,539.9 

5,602.7 

5,665.5 

5,728.3 

5,791.1 

5,853.9 

5,916.7 

5,979.5 

6,042.3 

6,105.1 

6,167.9 

6,230.7 

6,293.5 

6,356.3 

6,419.1 

6,491.5 

6,556.5 

6,621.4 

6,686.2 

Figure 6-8. Center Wing Tank.
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-9 01 DEC 12 

6.3.5 Aft Body Tank

FUEL 

(POUNDS) 

MOMENT 

10,000 

FUEL 

(POUNDS) 

MOMENT 

10,000 

 FUEL 

(POUNDS) 

MOMENT 

10,000 

FUEL 

(POUNDS) 

MOMENT 

10,000 

 500 

 1,000 

 1,500 

 2,000 

 2,500 

 3,000 

 3,500 

 4,000 

 4,500 

 5,000 

 5,500 

 6,000 

 6,500 

 7,000 

 7,500 

 8,000 

 8,500 

 9,000 

 9,500 

10,000 

10,500 

11,000 

11,500 

12,000 

12,500 

13,000 

13,500 

14,000 

14,500 

15,000 

15,500 

16,000 

16,500 

17,000 

17,500 

18,000 

82.0 

164.1 

246.1 

328.2 

410.2 

492.3 

574.3 

656.4 

738.4 

820.5 

902.5 

984.6 

1,066.6 

1,148.7 

1,230.7 

1,312.8 

1,394.8 

1,476.9 

1,558.9 

1,641.0 

1,723.0 

1,805.1 

1,887.1 

1,969.2 

2,051.2 

2,133.3 

2,215.3 

2,297.4 

2,379.4 

2,461.5 

2,543.5 

2,625.6 

2,707.6 

2,789.7 

2,871.7 

2,953.8 

18,500 

19,000 

19,500 

20,000 

20,500 

21,000 

21,500 

22,000 

22,500 

23,000 

23,500 

24,000 

24,500 

25,000 

25,500 

26,000 

26,500 

27,000 

27,500 

28,000 

28,500 

29,000 

29,500 

30,000 

30,500 

31,000 

31,500 

32,000 

32,500 

33,000 

33,500 

34,000 

34,500 

35,000 

35,500 

36,000 

3,035.8 

3,117.9 

3,199.9 

3,282.0 

3,364.0 

3,446.1 

3,528.1 

3,610.2 

3,692.2 

3,774.3 

3,856.3 

3,938.4 

4,020.4 

4,102.5 

4,184.5 

4,266.6 

4,348.6 

4,430.7 

4,512.7 

4,594.8 

4,676.8 

4,758.9 

4,840.9 

4,923.0 

5,005.0 

5,087.1 

5,169.1 

5,251.2 

5,333.2 

5,415.3 

5,497.3 

5,579.4 

5,661.4 

5,743.5 

5,825.5 

5,907.6 

 36,500 

37,000 

37,500 

38,000 

38,500 

39,000 

39,500 

40,000 

40,500 

41,000 

41,500 

42,000 

42,500 

43,000 

43,500 

44,000 

44,500 

45,000 

45,500 

46,000 

46,500 

47,000 

47,500 

48,000 

48,500 

49,000 

49,500 

50,000 

50,500 

51,000 

51,500 

52,000 

52,500 

53,000 

53,500 

54,000 

5,989.6 

6,071.7 

6,153.7 

6,235.8 

6,317.8 

6,399.9 

6,481.9 

6,564.0 

6,646.0 

6,728.1 

6,810.1 

6,892.2 

6,974.2 

7,056.3 

7,138.3 

7,220.4 

7,302.4 

7,384.5 

7,466.5 

7,548.6 

7,630.6 

7,712.7 

7,794.7 

7,876.8 

7,958.8 

8,040.9 

8,122.9 

8,205.0 

8,287.0 

8,369.1 

8,451.1 

8,533.2 

8,615.2 

8,697.3 

8,779.3 

8,861.4 

54,500 

55,000 

55,500 

56,000 

56,500 

57,000 

57,500 

58,000 

58,500 

59,000 

59,500 

60,000 

60,500 

61,000 

61,500 

62.000 

62,500 

63,000 

63,500 

64,000 

64,500 

65,000 

65,500 

66,000 

66,149* 

66,500 

67,000 

67,500 

68,000 

68,500 

69,000 

69,500 

70,000 

70,500 

71,000 

71,500 

8,943.4 

9,025.5 

9,107.5 

9,189.6 

9,271.6 

9,353.7 

9,435.7 

9,517.8 

9,599.8 

9,681.9 

9,763.9 

9,846.0 

9,928.0 

10,010.1 

10,092.1 

10,174.2 

10,256.2 

10,338.3 

10,420.3 

10,502.4 

10,584.4 

10,666.5 

10,748.5 

10,830.6 

10,855.0 

10,912.6 

10,994.7 

11,076.7 

11,158.8 

11,240.8 

11,322.9 

11,404.9 

11,487.0 

11,569.0 

11,651.1 

11,733.1 

Figure 6-9. Aft Body Tank.
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-10 01 DEC 12 

6.4 Passenger Loading Data

The * and ** in the seat location column, Figure 6-10, show the preferred positions for 

additional crew and support personnel. When planning for combined passenger and cargo 

loads, refer to T.O. 1C-10(K)A-9 for instructions and limitations. 

Figure 6-10. Passenger Seating. 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-11 01 DEC 12 

6.5 Cargo Loading Data

Figure 6-11 shows the 25-pallet compartment arrangement. This is the basic configuration, 

which is modified for various passenger/cargo loads. Compartment load capacities are 

shown. Notice how the station numbers (distance from the RDL) identify compartment 

boundaries. 

Figure 6-11. Cargo Compartment Configuration.
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-12 01 DEC 12 

6.6 Cargo Load Computations

The top lines on Figure 6-12 show compartment limits and centroid (CG). The weight limits 

in the left column are for two pallets in each compartment. This information can be used for 

reference during load planning. For example, you have 5,870 lb. to go in 7L. Read right to 

intersect each of the moments, and add. 

 WEIGHT MOM 

 5000 614.8 

 800 98.4 

 70 8.6 

 5870 721.8 (Round to 722.0) 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-13 01 DEC 12 

Figure 6-12. Cargo Load Computations. 

COMPT (LOC) A (1) B (2) C (3) D(4) E(5) F(6) G (7) H (8) J (9) K (10) L (11) M (12) N (13) 

FWD LIMIT 521.0 630.0 739.0 848.0 957.0 1,066.0 1,175.0 1,284.0 1,393.0 1,502.0 1,611.0 1,720.0 1,829.0 

AFT LIMIT 630.0 739.0 848.0 957.0 1,066.0 1,175.0 1,284.0 1,393.0 1,502.0 1,611.0 1,720.0 1,829.0 1,937.0 

CENTROID 575.5 684.5 793.5 902.5 1,011.5 1,120.5 1,229.5 1,338.5 1,447.5 1,556.5 1,665.5 1,774.5 1,883.0 

WEIGHT 

(LB/PALLET) 

MOMENT/10,000 AT CENTROID LISTED ABOVE (MOMENTS ARE LISTED FOR EACH PALLET UP TO MAXIMUM CAPACITY, INCLUDING 

WEIGHT OF PALLET. THERE ARE PROVISIONS FOR TWO PALLETS AT EACH LOCATION EXCEPT PALLET LOCATION 13.) 

10 0.5 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4 1.6 1.7 1.8 1.9

20 1.1 1.4 1.6 1.8 2.0 2.2 2.5 2.7 2.9 3.1 3.3 3.5 3.8

30 1.7 2.1 2.4 2.7 3.0 3.4 3.7 4.0 4.3 4.7 5.0 5.3 5.7

40 2.3 2.7 3.2 3.6 4.0 4.5 4.9 5.4 5.8 6.2 6.7 7.1 7.5

50 2.9 3.4 4.0 4.5 5.1 5.6 6.1 6.7 7.2 7.8 8.3 8.9 9.4

60 3.5 4.1 4.8 5.4 6.1 6.7 7.4 8.0 8.7 9.3 10.0 10.6 11.3

70 4.0 4.8 5.6 6.3 7.1 7.8 8.6 9.4 10.1 10.9 11.7 12.4 13.2

80 4.6 5.5 6.3 7.2 8.1 9.0 9.8 10.7 11.6 12.5 13.3 14.2 15.1

90 5.2 6.2 7.1 8.1 9.1 10.1 11.1 12.0 13.0 14.0 15.0 16.0 17.0

100 5.8 6.8 7.9 9.0 10.1 11.2 12.3 13.4 14.5 15.6 16.7 17.8 18.8

200 11.5 13.7 15.9 18.1 20.2 22.4 24.6 26.8 29.0 31.1 33.3 35.5 37.7

300 17.3 20.5 23.8 27.1 30.3 33.6 36.9 40.2 43.4 46.7 50.0 53.2 56.5

400 23.0 27.4 31.7 36.1 40.5 44.8 49.2 53.5 57.9 62.3 66.6 71.0 75.3

500 28.8 34.2 39.7 45.1 50.6 56.0 61.5 66.9 72.4 77.8 83.3 88.7 94.2

600 34.5 41.1 47.6 54.2 60.7 67.2 73.8 80.3 86.9 93.4 99.9 106.5 113.0

700 40.3 47.9 55.5 63.2 70.8 78.4 86.1 93.7 101.3 109.0 116.6 124.2 131.8

800 46.0 54.8 63.5 72.2 80.9 89.6 98.4 107.1 115.8 124.5 133.2 142.0 150.6

900 51.8 61.6 71.4 81.2 91.0 100.8 110.7 120.5 130.3 140.1 149.9 159.7 169.5

1,000 57.5 68.5 79.4 90.3 101.2 112.1 123.0 133.9 144.8 155.7 166.6 177.5 188.3

2,000 115.1 136.9 158.7 180.5 202.3 224.1 245.9 267.7 289.5 311.3 333.1 354.9 376.6

3,000 172.7 205.4 238.1 270.8 303.5 336.2 368.9 401.6 434.3 467.0 499.7 532.4 564.9

4,000 230.2 273.8 317.4 361.0 404.6 448.2 491.8 535.4 579.0 622.6 666.2 709.8 753.2

5,000 287.8 342.3 396.8 451.3 505.8 560.3 614.8 669.3 723.8 778.3 832.8 887.3 941.5

6,000 345.3 410.7 476.1 541.5 606.9 672.3 737.7 803.1 868.5 933.9 999.3 1,064.7 1,129.8

6,500 374.1 444.9 515.8 586.6 657.5 728.3 799.2 870.0 940.9 1,011.7 1,082.6 1,153.4 1,224.0

7,000 402.9 479.2 555.5 631.8 708.1 784.4 860.7 937.0 1,013.3 1,089.6 1.165.9 1.242.2 -- 

8,000 460.4 547.6 634.8 722.0 809.2 896.4 983.6 1,070.8 1,158.0 1,245.2 1,332.4 1,419.6 -- 

9,000 518.0 616.1 714.2 812.3 910.4 1,008.5 1,106.6 1,204.7 1,307.8 1,400.9 1,499.0 1,597.1 -- 

10,000 575.5 684.5 793.5 902.5 1,011.5 1,120.5 1,229.5 1,338.5 1,447.5 1,556.5 1,665.5 1,774.5 -- 

11,000 633.1 753.0 872.9 992.8 1,112.7 1,232.6 1,352.5 1,472.4 1,592.3 1,712.2 1,832.1 1,952.0 -- 

12,000 690.6 821.4 952.2 1,083.0 1,213.8 1,344.6 1,475.4 1,606.2 1,737.0 1,867.8 1,998.6 2,129.4 -- 

13,000 748.2 889.9 1,031.6 1,173.3 1,315.0 1,456.7 1,598.4 1,740.1 1,881.8 2,023.5 2,165.2 2,306.9 -- 

14,000 -- -- -- -- -- -- 1,721.3 1,873.9 2,026.5 2,179.1 2,331.7 -- -- 

15,000 -- -- -- -- -- -- 1,844.3 2,007.8 2,171.3 2,334.8 2,498.3 -- -- 

16,000 -- -- -- -- -- -- 1,967.2 2,141.6 2,316.0 2,490.4 2,664.8 -- -- 

17,000 -- -- -- -- -- -- 2,090.2 2,275.5 2,460.8 2,646.1 2,831.4 -- -- 

18,000 -- -- -- -- -- -- 2,213.1 2,409.3 2,605.6 2,801.7 2,997.9 -- -- 

19,000 -- -- -- -- -- -- 2,336.1 2,543.2 2,750.3 2,957.4 3,164.5 -- -- 

20,000 -- -- -- -- -- -- 2,459.0 2,677.0 2,895.0 3,113.0 3,331.0 -- -- 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-14 01 DEC 12 

6.7 Center of Gravity Graph

The CG design limits graph, Figure 6-13, can be used as a quick reference to determine 

forward and aft % MAC limits for a known gross weight. 

Enter on left with gross weight; read to the right to the forward limit, and read down to the % 

MAC. 

For the aft limit, read right from the gross weight to the aft limit line, then down to the aft 

% MAC. 

In addition to the -5, this graph is in TO 1C-10(K)A-1, Section III, Limitations. 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-15 01 DEC 12 

Figure 6-13. CG Limits Table. 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-16 01 DEC 12 

6.8 % MAC Tables

There are 11 of these tables, Figure 6-14, which show % MAC as a function of gross 

weight and moment. Weight is given in 500-pound increments. Enter with gross weight, 

read right to the gross weight arm (MOM). Read up to read the % MAC. 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-17 01 DEC 12 

Figure 6-14. CG Load Computations. 

GROSS 

WEIGHT 

(LB) 

8 % 

MAC 

(1335.62) 

8.4 

% 

MAC 

(1336.81) 

9 

 % 

MAC 

(1338.58) 

10 

 % 

MAC 

(1341.54)

10.3 

% 

MAC 

(1342.43)

11 

 % 

MAC 

(1344.5)

11.4 

 % 

MAC 

(1345.68)

12 

% 

MAC 

(1347.45) 

13 

 % 

MAC 

(1350.41) 

14 

 % 

MAC 

(1353.37)

240000 

240500 

241000 

241500 

242000 

242500 

243000 

243500 

32074 

32141 

32287 

32274 

32341 

32408 

32474 

32541 

32083 

32150 

32217 

32283 

32350 

32417 

32484 

32551 

32125 

32192 

32259 

32326 

32393 

32460 

32527 

32594 

32196 

32264 

32331 

32398 

32465 

32532 

32599 

32666 

32218 

32285 

32352 

32419 

32486 

32553 

32620 

32688 

32267 

32335 

32402 

32469 

32536 

32604 

32671 

32738 

32296 

32363 

32430 

32498 

32565 

32632 

32700 

32767 

32338 

32406 

32473 

32541 

32608 

32675 

32743 

32810 

32409 

32477 

32544 

32612 

32679 

32747 

32815 

32882 

32480 

32548 

32616 

32683 

32751 

32819 

32886 

32954 

244000 

244500 

245000 

245500 

246000 

246500 

247000 

247500 

32608 

32675 

32742 

32808 

32875 

32942 

33009 

33076 

32618 

32684 

32751 

32818 

32885 

32952 

33019 

33085 

32661 

32728 

32795 

32862 

32929 

32996 

33062 

33129 

32733 

32800 

32867 

32934 

33001 

33068 

33136 

33203 

32755 

32822 

32889 

32956 

33023 

33090 

33157 

33225 

32805 

32872 

32940 

33007 

33074 

33141 

33209 

33276 

32834 

32901 

32969 

33036 

33103 

33171 

33238 

33305 

32877 

32945 

33012 

33080 

33147 

33214 

33282 

33349 

32950 

33017 

33085 

33152 

33220 

33287 

33355 

33422 

33022 

33089 

33157 

33225 

33292 

33360 

33428 

33495 

248000 

248500 

249000 

249500 

250000 

250500 

251000 

251500 

33142 

33209 

33276 

33343 

33409 

33476 

33543 

33610 

33152 

33219 

33286 

33353 

33420 

33487 

33553 

33620 

33196 

33263 

33330 

33397 

33464 

33531 

33598 

33665 

33270 

33337 

33404 

33471 

33538 

33605 

33672 

33739 

33292 

33359 

33426 

33493 

33560 

33627 

33694 

33762 

33343 

33410 

33477 

33545 

33612 

33679 

33746 

33814 

33372 

33440 

33507 

33574 

33642 

33709 

33776 

33843 

33416 

33484 

33551 

33619 

33686 

33753 

33821 

33888 

33490 

33557 

33625 

33692 

33760 

33827 

33895 

33962 

33563 

33631 

33698 

33766 

33834 

33901 

33969 

34037 

252000 

252500 

253000 

253500 

254000 

254500 

255000 

255500 

33677 

33743 

33810 

33877 

33944 

34010 

34077 

34144 

33687 

33754 

33821 

33888 

33954 

34021 

34088 

34155 

33732 

33799 

33866 

33933 

33999 

34066 

34133 

34200 

33806 

33873 

33940 

34008 

34075 

34142 

34209 

34276 

33829 

33896 

33963 

34030 

34097 

34164 

34231 

34299 

33881 

33948 

34015 

34083 

34150 

34217 

34284 

34351 

33911 

33978 

34045 

34113 

34180 

34247 

34314 

34382 

33955 

34023 

34090 

34157 

34225 

34292 

34360 

34427 

34030 

34097 

34165 

34232 

34300 

34368 

34435 

34503 

34104 

34172 

34240 

34307 

34375 

34443 

34510 

34578 

256000 

256500 

257000 

257500 

258000 

258500 

259000 

259500 

34211 

34278 

34344 

34411 

34478 

34545 

34611 

34678 

34222 

34289 

34355 

34422 

34489 

34556 

34623 

34690 

34267 

34334 

34401 

34468 

34535 

34602 

34669 

34736 

34343 

34410 

34477 

34544 

34611 

34678 

34745 

34812 

34366 

34433 

34500 

34567 

34634 

34701 

34768 

34835 

34419 

34486 

34553 

34620 

34688 

34755 

34822 

34889 

34449 

34516 

34583 

34651 

34718 

34785 

34853 

34920 

34494 

34562 

34629 

34696 

34764 

34831 

34899 

34966 

34570 

34638 

34705 

34773 

34840 

34908 

34975 

35043 

34646 

34713 

34781 

34849 

34916 

34984 

35052 

35119 

260000 

260500 

261000 

261500 

262000 

262500 

263000 

263500 

34745 

34812 

34879 

34945 

35012 

35079 

35146 

35213 

34756 

34823 

34890 

34957 

35024 

35091 

35158 

35224 

34803 

34870 

34936 

35003 

35070 

35137 

35204 

35271 

34880 

34947 

35014 

35081 

35148 

35215 

35282 

35349 

34903 

34970 

35037 

35104 

35171 

35238 

35305 

35372 

34956 

35024 

35091 

35158 

35225 

35293 

35360 

35427 

34987 

35054 

35122 

35189 

35256 

35324 

35391 

35458 

35033 

35101 

35168 

35235 

35303 

35370 

35438 

35505 

35110 

35178 

35245 

35313 

35380 

35448 

35515 

35583 

35187 

35255 

35322 

35390 

35458 

35525 

35593 

35661 

264000 

264500 

265000 

265500 

266000 

266500 

267000 

267500 

35279 

35346 

35413 

35480 

35546 

35613 

35680 

35747 

35291 

35358 

35425 

35492 

35559 

35625 

35692 

35759 

35338 

35405 

35472 

35539 

35606 

35673 

35740 

35807 

35416 

35483 

35550 

35617 

35684 

35752 

35819 

35886 

35440 

35507 

35574 

35641 

35708 

35775 

35842 

35909 

35494 

35561 

35629 

35696 

35763 

35830 

35898 

35965 

35525 

35593 

35660 

35727 

35795 

35862 

35929 

35996 

35572 

35640 

35707 

35774 

35842 

35909 

35977 

36044 

35650 

35718 

35785 

35853 

35920 

35988 

36056 

36123 

35728 

35796 

35864 

35931 

35999 

36067 

36135 

36202 

268000 

268500 

269000 

269500 

270000 

270500 

271000 

271500 

35814 

35880 

35947 

36014 

36081 

36147 

36214 

36281 

35826 

35893 

35960 

36026 

36093 

36160 

36227 

36294 

35873 

35940 

36007 

36074 

36141 

36208 

36278 

36342 

35953 

36020 

36087 

36154 

36221 

36288 

36355 

36422 

35977 

36044 

36111 

36178 

36245 

36312 

36379 

36446 

36032 

36099 

36166 

36234 

36301 

36368 

36435 

36503 

36064 

36131 

36198 

36266 

36333 

36400 

36467 

36535 

36111 

36179 

36246 

36313 

36381 

36448 

36516 

36583 

36191 

36258 

36326 

36393 

36461 

36528 

36596 

36663 

36270 

36338 

36405 

36473 

36541 

36608 

36676 

36744 
KC-10 Aircrew Training System 

Principles of Weight and Balance

CH 4 

W010-06 6-18 01 DEC 12 

THIS PAGE INTENTIONALLY LEFT BLANK 
KC-10 Aircrew Training System 

Principles of Weight and Balance 

CH 3 

W010-07 7-1 01 JUL 11

7.0 LESSON EXERCISE 

References for the following are in Chapters 3, 4, 5, and 6. The answer for each 

question is on the reverse of its page. If you miss a question, review the applicable 

information. Should you need clarification on any point, please confer with your 

instructor. 

1. The Reference Datum Line is located in front of the aircraft 

nose. 

2. All lengthwise fuselage measurements are taken on the . 

3. identify the boundaries of fuselage 

compartments, equipment items, and crew stations. 

4. The Mean Aerodynamic Chord (MAC) is defined as the. 

5. LEMAC is from the RDL. 

6. Aircraft Center of Gravity (CG) is defined as the point at which. 

7. The Aerodynamic Center (AC) of the KC-10 wing is at approximately 

 MAC. 

8. An aircraft’s Basic Weight is defined as the weight at which it is equipped 

to fly before . 

9. The Aircraft Operating Weight includes . 

10. The formula for Weight is . 

11. The formula for Arm is . 

12. The formula for Moment is . 

13. An aircraft’s weight and balance history is maintained in which Technical Order? 

 . 

14. The latest entry in the is considered to be the 

aircraft’s current weight and balance status. 
KC-10 Aircrew Training System 

Principles of Weight and Balance 

CH 3 

W010-07 7-2 01 JUL 11

7.1 Page One Exercise Answers 

1. 239 inches 

2. Longitudinal axis 

3. Station numbers 

4. the average chord, or width, of the wing 

5. 1,312 inches 

6. an aircraft would balance if it were suspended 

7. 25% MAC 

8. the crew, fuel, and other items of variable load are added 

9. basic weight, crew, water, aircraft storage, extra equipment, emergency 

equipment and configuration change 

10. moment divided by arm 

11. moment divided by weight 

 

12. weight times arm 

13. TO 1-1B-50 Weight and Balance 

14. DD Form 365-3, Chart C 
KC-10 Aircrew Training System 

Principles of Weight and Balance 

CH 3 

W010-07 7-3 01 JUL 11

15. Use the WAM triangle to complete the following problems. 

NOTE: All Moments are depicted simplified

15a. Weight: 5,000 Arm: 1160 Moment: . 

15b. Arm: 865 Moment: 5622 Weight: . 

15c. Moment: 1229 Weight: 9550 Arm: . 

 . 

16. Aircraft Gross Weight: 508,000 Total Moment: 69502 

 What is the Takeoff CG Arm? . 

17. Aircraft Gross Weight: 556,500 Total Moments: 76631 

 What is the Takeoff CG in %MAC? . 

18. You will have 5 crewmembers for a flight. What weight and moment will 

you enter in the Form F? . 

19. When you compared your planned Form F with the Chart C, the 

passenger seating had been changed from B to D. What information will 

you enter in Ref. 8? . (Figure 6-5) 

20. What is the MOM entry for 59,000 lbs in No. 2 Wing Tank? . 
KC-10 Aircrew Training System 

Principles of Weight and Balance 

CH 3 

W010-07 7-4 01 JUL 11

7.2 Page Three Exercise Answers 

15a. 5000 X 1160 = 5,800,000 ÷ 10,000 = 580 

15b. 5622 X10,000 = 56,220,000 ÷ 865 = 64,994 

15c. 1229 ÷ 9550 = 1286.9 

 1229 X 10,000 = 12,290,000 ÷ 9550 = 1286.9 

16. 69502 ÷ 508000 = .1368 .1368 X 10000 = 1368 

17. a. Arm: 76631 ÷ 556500 = .1377 .1377 X 10000 = 1377 

 b. 1377 - 1312 X 100 65 X 100 = .21974 X 100 = 22.0%

 295.8 295.8 

18. 1075 lbs and 38 MOM. 

19. D75 16  75 + 4959 + 366 

20. 7663