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FAA APPROVED
Configuration U.S.
Figure 4-35 (Sheet 10)*
510FM-06 AA 4-121
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 11)*
4-122 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-35 (Sheet 12)*
510FM-06 AA 4-123
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 13)*
4-124 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-35 (Sheet 14)*
510FM-06 AA 4-125
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 15)*
4-126 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 1 of 15)*
510FM-06 AA 4-127
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-36 (Sheet 2)*
4-128 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 3)*
510FM-06 AA 4-129
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-36 (Sheet 4)*
4-130 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 5)*
510FM-06 AA 4-131
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-36 (Sheet 6)*
4-132 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 7)*
510FM-06 AA 4-133
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-36 (Sheet 8)*
4-134 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 9)*
510FM-06 AA 4-135
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-36 (Sheet 10)*
4-136 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 11)*
510FM-06 AA 4-137
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-36 (Sheet 12)*
4-138 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 13)*
510FM-06 AA 4-139
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-36 (Sheet 14)*
4-140 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-36 (Sheet 15)*
510FM-06 AA 4-141/4-142

MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
SINGLE-ENGINE TAKEOFF FLIGHT PATH - FLAPS 15°
FIRST AND SECOND SEGMENTS
Knowing weight, altitude, temperature, wind, obstacle height above runway surface and the obstacle
distance from "reference zero", at the airport pressure altitude plus the takeoff climb increment (TCI)
from Figure 4-39 or 4-40, determine the available climb gradient from Figure 4-47 or 4-48. Using this
climb gradient, the required horizontal distance can be determined from Figure 4-37. If this required
horizontal distance is less than the horizontal distance to the obstacle, the takeoff weight determined
by other limitations is satisfactory; otherwise, the weight must be reduced to correspond with the
required horizontal distance.
From Figure 4-40, the takeoff climb increment (TCI) above the runway surface is 1850 FEET. The
pressure altitude at the airport plus the takeoff climb increment (TCI) is 2850 FEET.
From Figure 4-48, the available climb gradient at a pressure altitude of 2850 feet under the specific
conditions is 6.0 percent.
From Figure 4-37, for 6.0 percent gradient, the required horizontal distance to clear the obstacle is
3840 feet.
The obstacle can be cleared since the horizontal distance to the obstacle (4500 feet) is greater than
the required horizontal distance to clear the obstacle (3840 feet).
EXAMPLE:
Flaps = 15°
Anti-Ice = ON
Pressure Altitude at Airport = 1000 FEET
Gross Weight at Brake Release = 8000 POUNDS
Ambient Temperature at Airport = -10°C
Wind = 10 KNOTS (Headwind)
A. Obstacle Height = 200 feet above runway surface
　
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