STEMME S6-RT, Руководство по эксплуатации самолета

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! " #$ % &
, - # % %ward in flight C.G. for the aircraft is reached for
loading configuration ”Fuel Tank empty“. So the critical case
to be checked is with landing gear retracted (most rearward
C.G. limit).
If the most forward in flight C.G. limit is exceeded for this
case the aircraft loading has to be adjusted clearly rearward.
Otherwise there is no fuel load possible.
7. Finally the fuel load must be determined precisely. Calculate the
corresponding mass moment by using the same methods as in point 2.
Place these values in the corresponding columns of row 7 of the table. The
lever of the fuel mass changes with changes in the amout of fuel. Due to
this, ONLY use diagram 6.4.1 for this.
8. Now calculate the total mass and total moment from row 4 and row 7 of the
table. Place these values in row 8. This represents the aircraft in its T/O
configuration with fuel.
The constant mass moment from row 5 (as result of retraction of landing
gear) must NOT be considered here.
, - Due to displacement of C.G. forward with maximum fuel load
the critical case to be checked is with landing gear extended
(most forward in flight CG limit) for this loading configuration.
9. Divide the results from row 8 to determine the lever of the CG in the T/O
configuration. These values must be within the allowed limits. If this is not
the case, useful load and fuel must be adjusted.
All mentioned and used levers give the distance from the corresponding CG to
the reference plane (RP)!
- The CG must always stay within the allowed limits. If this is
not the case, unstable aircraft behavior might result!