Technical data

13773-001
8-20
Page 2 30 Nov 2000
surements. Subtract this measurement from dimension ‘A’ to obtain the nose wheel
weighting point arm (dimension ‘B’).
(c) Determine and record the moment for each of the main nose gear weighting points using
the following formula:
Moment = Net Weight x Arm
(d) Calculate and record the as-weighed C.G. weight and moment by totaling the appropriate
columns.
(e) Determine and record the as-weighed C.G. in inches aft of datum using the following for-
mula:
C.G. = Total Moment/Total Weight
(f) Add or subtract any items not included in the as-weighted condition to determine the
empty condition. Application of the above C.G. formula will determine the C.G. for this
condition.
(g) Add the correction for engine oil (15.0 lb at FS 79.3) if the airplane was weighed with oil
drained. Add the correction for unusable fuel (18.0 lb at FS 154.9) to determine the Basic
Empty Weight and Moment. Calculate and record the Basic Empty Weight C.G. by apply-
ing the above C.G. formula.
(h) Record the new weight and C.G. values on the Weight and Balance Record located in the
airplanes’ Pilot’s Operating Handbook.