Page 575 - POH-SUPER KING AIR B200/B200C

text_perf_sect.fm Page 8 Thursday, April 19, 2007 10:49 AM
Section 5
HFG Performance Super King Air B200/B200C
The performance graphs associated with the above conditions are:

TAKE-OFF WEIGHT - TO MEET 14 CFR PART 25 TAKE-OFF CLIMB
REQUIREMENTS graphs
ACCELERATE-STOP graphs
ACCELERATE-GO graphs
NET GRADIENT OF CLIMB graphs
TAKE-OFF FLIGHT PATH graph
(Reference 14 CFR Part 25.109, 25.111, 25.115 and 25.121)
The performance presented using this criteria is predicated on the autofeather
system being armed and operable. The Ground Minimum Control Speed (VMCG)
has been determined to be 84 knots. At this speed, control within 25 feet of the
runway center line is possible.
The following example illustrates the procedures required to obtain a take-off
weight value using the CONDITIONS specified below, and illustrated by the
TAKE-OFF FLIGHT PATH diagram.
CONDITIONS (These conditions do not pertain to any particular airport location.):
Outside Air Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28°C
Field Elevation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5330 feet
Altimeter Setting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .29.82 in. Hg
Surface Wind . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 140° at 11 knots
Runway 17 Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6486 feet
Pressure Altitude (29.92 - 29.82 = 0.10 in. Hg) 5330 + 100. . . . . . . 5430 feet
Headwind Component (From WIND COMPONENTS graph) . . . . . 9.5 knots
Obstacles (Height above runway):
• 20-foot-high wires 300 feet beyond end of runway
• 175-foot-high ridge 3000 feet beyond end of runway

TAKE-OFF FLIGHT PATH
1. From the TAKE-OFF WEIGHT - TO MEET 14 CFR PART 25 TAKE-OFF
CLIMB REQUIREMENTS graphs, determine that the maximum take-off
weights to meet 14 CFR Part 25 climb requirements are 12,500 pounds with
flaps at 0% and 12,000 pounds with flaps at 40%.
2. From the ACCELERATE-STOP graphs, using 12,500 pounds with flaps at
0%, and 12,000 with flaps at 40%, determine that the resulting distances are
less than the runway length. Therefore, accelerate-stop is not a limiting
factor.
3. From the ACCELERATE-GO graphs, using 12,500 pounds with flaps at 0%,
and 12,000 with flaps at 40%, determine that the resulting distances are
greater than the available accelerate-go distance of 6786 feet. (Refer to the
TAKE-OFF FLIGHT PATH diagram.)
HIGH FLOTATION GEAR Revised: April, 2007
5-8 P/N 101-590010-279