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an E6-B can also be solved with a dedicated flight computer
using the information in Figure 8-1.
Each flight computer handles the problems in slightly
different ways, but all are programmed with prompts that
solicit you to input the required data so you do not need to
memorize any formulas. Weights and arms are input as
called for, and a running total of the weight, moment, and
CG are displayed.
Figure 8-4. A typical electronic calculator is useful for solving
most types of weight and balance problems.
Determining CG in Inches From the Datum
This type of problem is solved by first determining the
location of the CG in inches from the main-wheel weighing
points, then measuring this location in inches from the datum.
There are four types of problems involving the location of
the CG relative to the datum.
8 –4
Nose Wheel Airplane with Datum
Ahead of the Main Wheels
The datum (D) is 128 inches ahead of the main-wheel
weighing points, the weight of the nose wheel (F) is 340
pounds, and the distance between main wheels and nose
wheel (L) is 78 inches. The total weight (W) of the airplane
is 2,006 pounds. Refer to Figure 3-5 on Page 3-5.
Use this formula:
Tail Wheel Airplane with Datum
Ahead of the Main Wheels
The datum (D) is 7.5 inches ahead of the main-wheel
weighing points, the weight of the tail wheel (R) is 67 pounds,
and the distance between main wheels and tail wheel (L) is
222 inches. The total weight (W) of the airplane is 1,218
pounds. Refer to Figure 3-7 on Page 3-6.
Use this formula:
1. Determine the CG in inches from the main wheels:
(340)(?)(78)(÷)(2006)(=) 13.2
2. Determine the CG in inches from the datum:
(128)(–)(13.2)(=) 114.8
The CG is 114.8 inches behind the datum.
Nose Wheel Airplane with Datum
Behind the Main Wheels
The datum (D) is 75 inches behind the main-wheel weighing
points, the weight of the nose wheel (F) is 340 pounds, and
the distance between main wheels and nose wheel (L) is 78
inches. The total weight (W) of the airplane is 2,006 pounds.
Refer to Figure 3-6 on Page 3-6.
Use this formula:
1. Determine the CG in inches from the main wheels:
(340)(?)(78)(÷)(2006)(=) 13.2
2. Determine the CG in inches from the datum:
(75)(+)(13.2)(=) 88.2
The minus sign before the parenthesis in the formula means
the answer is negative. The CG is 88.2 inches ahead of the
datum (–88.2).
1. Determine the CG in inches from the main wheels:
(67)(?)(222)(÷)(1218)(=) 12.2
2. Determine the CG in inches from the datum:
(7.5)(+)(12.2)(=) 19.7
The CG is 19.7 inches behind the datum.
Tail Wheel Airplane with Datum
Behind the Main Wheels
The datum (D) is 80 inches behind the main-wheel weighing
points, the weight of the tail wheel (R) is 67 pounds, and the
distance between main wheels and tail wheel (L) is 222
inches. The total weight (W) of the airplane is 1,218 pounds.
Refer to Figure 3-8 on Page 3-7.
Use this formula:
1. Determine the CG in inches from the main wheels:
(67)(?)(222)(÷)(1218)(=) 12.2
2. Determine the CG in inches from the datum:
(80)(+/–)(+)(12.2)(=) –67.8
The CG is 67.8 inches ahead of the datum.
8– 5
Determining CG, Given Weights and Arms
Some weight and balance problems involve weights and
arms to determine the moments. Divide the total moment
by the total weight to determine the CG. Figure 8-5 contains
the specifications for determining the CG using weights and
arms.
Determine the CG by using the data in Figure 8-5 and
following these steps:
1. Determine the total weight and record this number:
(830)(+)(836)(+)(340)(=) 2006
2. Determine the moment of each weighing point and record
them:
(830)(?)(128)(=) 106240
(836)(?)(128)(=) 107008
(340)(?)(50)(=) 17000
3. Determine the total moment and divide this by the
total weight:
(106240)(+)(107008)(+)(17000)(=)(÷)(2006)(=) 114.8
This airplane weighs 2,006 pounds and its CG is 114.8 inches
from the datum.
Determining CG, Given Weights
and Moment Indexes
Other weight and balance problems involve weights and
moment indexes, such as moment/100, or moment/1,000. To
determine the CG, add all the weights and all the moment
indexes. Then divide the total moment index by the total
weight and multiply the answer by the reduction factor. Figure
8-6 contains the specifications for determining the CG using
weights and moment indexes.
Determine the CG by using the data in Figure 8-6 and
following these steps:
　
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