Take-Off Distance - Beechcraft Baron G58 Pilot Operating Handbook

Model G58
Enter the Take-Off Weight graph at 5653 ft pressure altitude
and 15°C, to determine the maximum take-off weight to
achieve a positive one-engine-inoperative rate-of-climb at lift-
off.
Take-off Weight = 4870 lbs

TAKE-OFF DISTANCE

Enter the Take-Off Distance graph at 15°C, 5653 ft pressure
altitude, 5500 lbs, and 10 knots headwind component:
Ground Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2200 ft
Total Distance over 50-ft Obstacle . . . . . . . . . . . . . . 3775 ft
Enter the Accelerate-Stop graph at 15°C, 5653 ft pressure alti-
tude, 5500 lbs, and 10 knots headwind component:
Accelerate-Stop Distance . . . . . . . . . . . . . . . . . . . . . 3960 ft
Since 3960 ft is less than the available field
length of 10,004 ft, the accelerate-stop pro-
cedure can be performed at any weight.
Take-off at 5500 lbs can be accomplished. However, if an
engine failure occurs before becoming airborne, the acceler-
ate-stop procedure must be performed.
The following example assumes the airplane is loaded so that
the take-off weight is 4700 lbs.
Although not required by regulations, information has been
presented to determine the take-off weight, field requirements
and take-off flight path assuming an engine failure occurs dur-
ing the take-off procedure. The following illustrates the use of
these graphs.
July, 2014
NOTE
Section 5
Performance
5-9