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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 pages 2-12 and 2-13. The FAA considers addition
or removal of equipment included in this list 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 aircraft mechanic or repairman.
The only documentation required 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]
Major Alteration and Repair
Within the following text, information concerning major
repairs or major alterations does not apply to any aircraft
within the light-sport category. This category of aircraft is
not eligible for major repairs or alterations.
Any major alteration or repair requires the work to be done
by an appropriately-rated aircraft mechanic or facility. The
work must be checked for conformity to FAA-approved
data and signed off by an aircraft mechanic holding an
Inspection Authorization, or by an authorized agent of
an appropriately rated FAA-approved repair station. A
repair station record or 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.
Figure 5-1. A typical Part 23 weight and balance record.
5–
Figure 5-2. A typical CAR 3 airplane weight and balance revision record.
5–
Weight and Balance Revision Record
Aircraft manufacturers use different formats for their
weight and balance data, but Figure 5-2 is typical of a
weight and balance revision record. All weight and balance
records should be kept with the other aircraft records.
Each revision record should be identified by the date, the
aircraft make, model, and serial number. The pages should
be signed by the person making the revision and his or her
certificate type and number must be included.
The computations for a weight and balance revision are
included on a weight and balance revision form. The
date those computations were made is shown in the
upper right-hand corner of Figure 5-2. When this work is
superseded, a notation must be made on the new weight
and balance revision form, including a statement that these
computations supersede the computations dated “XX/XX/
XX.”
Appropriate fore-and-aft extreme loading conditions
should be investigated and the computations shown.
The weight and balance revision sheet should clearly
show the revised empty weight, empty weight arm and/or
moment index, and the new useful load.
Weight Changes Caused by a Repair or
Alteration
A typical alteration might consist of removing two pieces
of radio equipment from the instrument panel, and a power
supply that was located in the baggage compartment
behind the rear seat. In this example, these two pieces are
replaced with a single lightweight, self-contained radio.
At the same time, an old emergency locator transmitter
(ELT) is removed from its mount near the tail, and a lighter
weight unit is installed. A passenger seat is installed in the
baggage compartment.
Computations Using Weight, Arm, and Moment
The first step in the weight and balance computation is to
make a chart like the one in Figure 5-3, listing all of the
items that are involved.
The new CG of 36.4 inches aft of the datum is determined
by dividing the new moment by the new weight.
Figure 5-3. Weight, arm, and moment changes caused by typical alteration.
5–
Computations Using Weight and Moment Indexes
If the weight and balance data uses moment indexes
rather than arms and moments, this same alteration can be
computed using a chart like the one shown on Figure 5-4.
Subtract the weight and moment indexes of all the
removed equipment from the empty weight and moment
index of the airplane. Add the weight and moment indexes
of all equipment installed and determine the total weight
and the total moment index. To determine the position of
the new CG in inches aft of the datum, multiply the total
moment index by 100 to get the moment, and divide this
by the total weight to get the new CG.
Empty-Weight CG Range
The fuel tanks, seats, and baggage compartments of
some aircraft are so located that changes in the fuel or
　
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