Page 579 - POH-SUPER KING AIR B200/B200C

text_perf_sect.fm Page 12 Thursday, April 19, 2007 10:49 AM
Section 5
HFG Performance Super King Air B200/B200C
13. (Step 8 procedures): Use the weights of Step 8 and Step 12 to obtain a new
assumed weight.
a. Flaps 0%:
10,800 - 10,150 = 650
650 ÷ 2 = 325
325 + 10,150 = 10,475 pounds
b. Flaps 40%:
10,550 - 10,190 = 360
360 ÷ 2 = 180
180 + 10,190 = 10,370 pounds
Use these assumed weights for second iteration.
14. After several additional iterations, the exact weights which will satisfy all the
given conditions are:
a. Flaps 0% = 10,310 pounds with a 4.5% Net Gradient of Climb.
b. Flaps 40% = 10,360 pounds with a 3.3% Net Gradient of Climb.
The fuel quantity required for start and taxi can be added to these weights.

TAKE-OFF DISTANCE
Enter the TAKE-OFF DISTANCE graphs at 28°C, 5433 feet pressure altitude,
12,500 pounds and 9.5 knots headwind component and obtain the following
results:
FLAPS 0% FLAPS 40%

Ground Roll. . . . . . . . . . . . . . . . . . . . . . . . . . . 2870 feet 2700 feet
Total Distance Over 50-foot Obstacle . . . . . . 4900 feet 3750 feet
Take-off Speed
At VR. . . . . . . . . . . . . . . . . . . . . . . . . . . 96 knots 94 knots
At V2. . . . . . . . . . . . . . . . . . . . . . . . . . . . 121 knots 106 knots

FLIGHT PLANNING
The following calculations provide information for flight planning at various
parameters of weight, power, altitude and temperature. Graphs and tables are
included for: TIME, FUEL, AND DISTANCE TO CLIMB; TIME, FUEL, AND
DISTANCE TO DESCEND; NORMAL CRUISE POWER AT 1700 RPM;
MAXIMUM CRUISE POWER AT 1700 RPM; NORMAL CRUISE POWER AT
1800 RPM; MAXIMUM CRUISE POWER AT 1800 RPM; MAXIMUM RANGE
POWER AT 1700 RPM; and HOLDING TIME.

HIGH FLOTATION GEAR Revised: April, 2007
5-12 P/N 101-590010-279