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Total required fuel = 47 gallons
The pilot completes a chart like the one in Figure 4-13 using
moment indexes from the tables in Figures 4-14 through 4-16.
4–8
Figure 4-13. Typical weight and balance loading form.
Takeoff — 3,781 lbs and 4,310 moment/100
Landing — 3,571 lbs and 4,064 moment/100
Locate the moment/100 diagonal line for 4,310 and follow it
down until it crosses the horizontal line for 3,781 pounds.
These lines cross inside the envelope at the vertical line for a
CG location of 114 inches aft of the datum.
The maximum allowable takeoff weight is 3,900 pounds, and
this airplane weighs 3,781 pounds. The CG limits for 3,781
pounds are 109.8 to 117.5. The CG of 114 inches falls within
these allowable limits.
The moments/100 in the index column are found in the
charts in Figures 4-14 through 4-16. If the exact weight is
not in the chart, interpolate between the weights that are
included. When a weight is greater than any of those shown
in the charts, add the moment indexes for a combination of
weights to get that which is desired. For example, to get the
moments/100 for the 320 pounds in the front seat, add the
moment indexes for 100 pounds (105) to that for 220 pounds
(231). This gives the moment index of 336 for 320 pounds
in the front seat.
Use the moment limits vs. weight envelope in Figure 4-17
on Page 4-10 to determine if the weight and balance conditions
will be within allowable limits for both takeoff and
landing at the destination.
Interpolate: To determine a value in
a series between two known values.
Moment limits vs. weight envelope:
An enclosed area on a graph of three
parameters. The diagonal line
representing the moment/100 crosses
the horizontal line representing the
weight at the vertical line representing
the CG location in inches aft
of the datum. When the lines cross
inside the envelope, the aircraft
is loaded within its weight and
CG limits.
4– 9
Interpolation
Determine the weight and moment index of 55 gallons of fuel
55 is 50% of the way between 50 and 60. The weight and moment
index of 55 gallons is 50% of the difference between the weights and
moment indexes for 50 gallons and 60 gallons.
Weight Moment index
360 – 300 = 60. 421 – 351 = 70.
50% of 60 = 30. 50% of 70 = 35.
300 + 30 = 330. 351 + 35 = 386.
Figure 4-16. Weight and moment index for fuel.
Figure 4-14. Weight and moment index for occupants.
Figure 4-15. Weight and moment index for baggage.
4–10
Figure 4-17. Moment limits vs. weight envelope.
5– 1
Chapter 5
Center of Gravity Change
After Repair or Alteration
The largest weight changes that occur during the lifetime of
an aircraft are those caused by alterations and repairs. It is
the responsibility of the AMT doing the work to accurately
document the weight change and record it in both the
maintenance records and the POH/AFM.
Equipment List
A typical comprehensive equipment list is shown in Figure
2-22 on Page 2-13. Addition or removal of equipment
included in this list is considered by the FAA to be a minor
alteration. The weights and arms are included with the items
in the equipment list, and these minor alterations can be done
and the aircraft approved for return to service by an
appropriately rated AMT. The only documentation required
Minor alteration: An alteration
other than a major alteration. This
includes alterations that are listed in
the aircraft, aircraft engine, or
propeller specifications.
is an entry in the aircraft maintenance records and the
appropriate change to the weight and balance record in the
POH/AFM. [Figure 5-1]
Any major alteration or repair requires the work to be done
by an appropriately rated AMT or facility. The work must be
checked for conformity to FAA-approved data and signed off
by an AMT holding an Inspection Authorization, or by an
authorized agent of an appropriately rated FAA-approved
repair station. A repair station record or an FAA Form 337,
Major Repair and Alteration, must be completed which
describes the work. A dated and signed revision to
the weight and balance record is made and kept with the
maintenance records, and the airplane’s new empty weight
and empty weight arm or moment index are entered in
the POH/AFM.
Major alteration: An alteration not
listed in the aircraft, aircraft engine,
or propeller specifications —
(1) That might appreciably affect
weight, balance, structural strength,
performance, powerplant operation,
　
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