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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 4-35 or 4-36, determine the available climb gradient from Figure 4-45 or 4-46. Using this
climb gradient, the required horizontal distance can be determined from Figure 4-33. 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 4-35, the takeoff climb increment (TCI) above the runway surface is 1710 FEET. The
pressure altitude at the airport plus the takeoff climb increment (TCI) is 4710 FEET.
From Figure 4-45, the available climb gradient at a pressure altitude of 4710 feet under the specific
conditions is 8.0 percent.
From Figure 4-33, for 8.0 percent gradient, the required horizontal distance to clear the obstacle is
3080 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 (3080 feet).
EXAMPLE:
Flaps = UP
Anti-Ice = OFF
Pressure Altitude at Airport = 3000 FEET
Gross Weight at Brake Release = 7,000 POUNDS
Ambient Temperature at Airport = 0°C
Wind = -10 KNOTS (Tailwind)
A. Obstacle Height = 200 feet above runway surface
B. Obstacle Horizontal Distance from Reference Zero = 4500 FEET
510FM-05 AA 4-109
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-33*
4-110 AA 510FM-05
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
SINGLE-ENGINE TAKEOFF FLIGHT PATH DISTANCES
FLAPS UP
The data presented in Figure 4-35 (Anti-ice OFF) and 4-36 (Anti-ice ON) is for the purpose of
determining the takeoff climb increment (TCI) and the horizontal distances along the net takeoff flight
path. The net takeoff flight path is used to plan obstacle clearance.
Figure 4-34*
*TAKEOFF THRUST IS LIMITED TO TEN MINUTES MAXIMUM AND THEREAFTER TO
MAXIMUM CONTINUOUS THRUST.
Calculate the level off altitude by adding the takeoff climb increment to the airport barometric altitude.
3925 + 1680 = 5605 FEET.
SINGLE-ENGINE FLIGHT PATH CONDITIONS:
FIRST SEGMENT SECOND SEGMENT THIRD SEGMENT
LANDING GEAR DOWN TRANSITION TO
UP
UP UP
WING FLAP UP UP UP
SPEED BRAKES RETRACT RETRACT RETRACT
INOPERATIVE ENGINE WINDMILLING WINDMILLING WINDMILLING
OPERATIVE ENGINE TO THRUST TO THRUST TO THRUST
AIRSPEED V2 V2 V2 TRANSITION TO VENR
EXAMPLE:
Flaps = UP
Anti-Ice = OFF
Pressure Altitude at Airport = 3000 FEET
Gross Weight at Brake Release = 8000 POUNDS
Ambient Temperature at Airport = 10°C
Wind = 0 KNOT WIND
Airport Barometric Altitude = 3925 FEET MSL
Horizontal Distance and Takeoff Climb Increment from Figure 4-35
Reference Zero to End of First Segment = 2893 FEET
Reference Zero to End of Second Segment = 23,255 FEET
Reference Zero to End of Third Segment = 25,011 FEET
Takeoff Climb Increment (TCI) = 1680 FEET
510FM-05 AA 4-111
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 1 of 15)*
4-112 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-35 (Sheet 2)*
510FM-06 AA 4-113
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 3)*
4-114 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-35 (Sheet 4)*
510FM-06 AA 4-115
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 5)*
4-116 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-35 (Sheet 6)*
510FM-06 AA 4-117
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 7)*
4-118 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-35 (Sheet 8)*
510FM-06 AA 4-119
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-35 (Sheet 9)*
4-120 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
　
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