h. Divide total moment by total net weight to obtain
as weighed cg location in inches from reference datum.
Enter this distance in Total block under ARM column.
Transfer total (as weighed) weight, arm, and
moment to the reverse side of form.
Make no entries in OIL IN AIRPLANE line.
k. Subtract total weight and moment of items
entered in COLUMN I.
l. Add total weight and moment of items listed in
COLUMN II to obtain basic aircraft weight and moment
m. Divide basic moment by basic weight to obtain
basic arm. Transfer basic weight and moment to DD
n. Fill in reactions and type of scales used.
Include under REMARKS information as to attitude of
aircraft when weighed, method of support, etc.
Change 6 4-5