Section 6
Weight & Balance /
Model GA8-TC 320
Equipment List
Page 6-8
5 Feb 2009
C01-01-08
6.3
LOADING SYSTEM
The loading charts on the following pages will assist the pilot in ensuring that the aircraft is operated
within the prescribed weight and centre of gravity limitations. Two formats of charts are provided.
The first is the Loading Trim Sheet, which uses graphical evaluation for the centre of gravity and
the second is a Loading Envelope Chart that allows direct computation of the centre of gravity. Both
formats of charts are supplied in combined passenger/freight and freighter configurations. These
are given in metric and imperial units. It is at the pilot’s discretion as to which is the more appropriate
loading chart to use for any particular flight.
The cabin is divided into 6 areas for weight and balance purposes. The aft luggage bin net (P/N
GA8-255011-9) must be in place whenever any articles are carried in the aft luggage bin or on the
cabin baggage shelf. Ensure the local limitations of each area and restraint requirements stipulated
in Section 6.4 of this manual are followed during loading.
6.3.1 Procedure for Loading Trim Sheet
Rows of the Loading Trim Sheet for the carriage of crew and passengers are divided into two scales.
The first scale is 77 kg per division (170 lb per division for imperial trim sheet) corresponding to the
standard person weight. The second scale is 50 kg per division (100 lb per division for imperial trim
sheet), which can also be used when a passenger and freight occupy the same row. See example
loading on the PAX/Freighter Loading Trim Sheet. A scale of 50 litres or 72 kg per division (20 US
gallons or 100 lb per division for imperial trim sheet) is provided for fuel calculations.
1. Write weights of aircraft, pilot, passengers, cargo and fuel in each of the appropriate boxes
down the right hand side of the sheet.
2. Add the aircraft basic weight, pilot, passengers and cargo to obtain a Zero Fuel Weight
subtotal.
(The current aircraft basic weight and basic index can be found on the Aircraft Load
Data Sheet contained in this manual)
3. Add the fuel weight to this subtotal to obtain the Aircraft Take-off Weight. Ensure the Take-off
Weight does not exceed the Aircraft Maximum Take-off Weight.
4. Subtract the fuel weight to destination to obtain the Landing Weight. Ensure the Landing
Weight does not exceed the Aircraft Maximum Landing Weight
5. On the Centre of Gravity Moment Chart draw two horizontal lines equating to the Take-off
Weight and Zero Fuel Weight.
6. Mark the Aircraft Basic Index Unit at the top of the sheet and drop a line down to the Row 1
scales.
7. Count across, to the right, the number of divisions equivalent to the weight listed for Row
1. From this point, drop a line down to the next row scale and count across, to the right, the
number of divisions equivalent to the weight listed for that row.
8.
Repeat
Step 7
for all appropriate rows remembering that either or both divisions can be used
for any one row.
9. From the final item drop a line down on to the Centre of Gravity Moment Chart to meet the
Zero Fuel Weight.
10. In the fuel section, count across to the right the number of divisions equivalent to the quantity
or weight of fuel and drop a line down on to the Centre of Gravity Moment Chart to meet the
Take-off Weight.
11. If both of these two intersections are within the unhatched area of the graph, the aircraft will
remain inside the Weight and Centre of Gravity envelope for all fuel states.
01 Aug 2011
Summary of Contents for GIPPSAERO GA8-TC 320
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Page 35: ...C01 01 08 5 Feb 2009 Page 2 13 Section 2 Model GA8 TC 320 Limitations...
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