12.110. Centre of Gravity (C of G)

12.110.4(b) . aft limit. 

If the CG is behind the aft limit the aircraft would be very tail heavy very hard to control and would tend to stall and / or spin more easily – might be difficult / impossible to recover from this

12.110.4. State the effect on the stability and control of an aircraft if flown with the C of Gat the: 

12.110.2. State the reasons for operating an aircraft within the C of G limits.

12.108. Weight and Loading

12.108.2(c) . use index units. 

When calculating the weight and balance of an aircraft the moments are often large numbers
The size of the number is reduced by dividing by 10,000
An index unit is 10,000kg-mm

12.108.2(b) . use a typical loading graph to determine C of G position; 

Determine the take-off weight and moment for the loaded aircraft
To find the moments for each station, enter with the weight on the vertical axis.
Read horizontally across to the sloping line marked “Fuel AVGAS” then move vertically up to read off the moment
Repeat the process for each station listed in the loading details sheet
When complete add up the two columns to find the take-off weight and moment
Check to ensure that the weight and CG are within limits
Enter the CG Moment Envelope graph from the R and from the top..
The CG is where the two lines intersect

12.108.2(a) . calculate the C of G position; 

1. List all weights and their arms
2. Multiply the weights by their arms to obtain individual moments
3. Add all the weights to obtain the gross
4. Add the moments to obtain total moment
5. Divide the total momenjt by total gross weight to obtain the CG position

12.108.2. Given a basic aircraft load sheet/data, demonstrate the ability to:

12.106. Definitions, Terminology and AbbreviationsSub Topic Syllabus Item