Question ID 330225

[Beareke]

A quick question here:
The question:
(Refer to Annex 033-033 or Flight planning Manual SEP 1 Figure 2.4)
Given:
Aeroplane mass at start-up 3663 lbs
Aviation gasoline (density 6 lbs/gal)-fuel load 74 gal
Take-off altitude sea level
Headwind 40 kt
Cruising altitude 8000 ft
Power setting full throttle 2300 RPM 20

[JJ Jones]

Your question was cut short (cut and paste does this sometimes). If your question was that the formula in the explanation for NGM should read NGM = NAM x (GS/TAS) then you are correct. I have corrected it in the databank and the changed version will appear after the next update cycle.
All the best.