曝光台 注意防骗
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table in Figure 4-25 (Flaps UP, Anti-Ice OFF), Figure 4-27 (Flaps UP, Anti-Ice ON), Figure 4-
29 (Flaps 15°, Anti-Ice OFF), or Figure 4-31 (Flaps 15°, Anti-Ice ON).
7. If the available runway length is less than the required field length, the airplane weight must
be reduced until this requirement can be met.
8. Determine level off altitude. Level off altitude is airport barometric altitude plus takeoff climb
increment (Figure 4-35, 4-36, 4-39, or 4-40) required for obstacle clearance.
9. If the obstacle clearance is a factor, the single-engine takeoff flight path charts (Figures
4-33, 4-35, or 4-36, and 4-37, 4-39 or 4-40) must be used to determine if the net takeoff
flight path provides the required obstacle clearance. If the required obstacle clearance is not
achieved, the gross weight must be adjusted until the net takeoff flight path assures the
required obstacle clearance.
NOTE
If the takeoff flight path has not been completed within ten (10) minutes, reduce power
to maximum continuous single engine thrust and continue with the takeoff flight path.
10. The second segment (Figure 4-45, 4-46, 4-47 or 4-48) and enroute (Figure 4-49 or 4-50)
turning climb, up to and including a 15° bank angle, if the takeoff weight is 8352 pounds or
less, multiply the takeoff weight by 1.035 to obtain an adjusted weight. Enter the appropriate
second segment or enroute climb table at the adjusted weight to find the actual climb
performance of the airplane in the bank. If the takeoff weight is greater than 8352 pounds,
reduce the net climb gradient by 0.9.
11. The first segment takeoff net climb tables are presented in Figures 4-41, 4-42, 4-43 and
4-44.
4-40 AA 510FM-07
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-21*
510FM-05 AA 4-41
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-22*
4-42 AA 510FM-05
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-23*
510FM-05 AA 4-43
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-24*
4-44 AA 510FM-05
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
TAKEOFF FIELD LENGTH - FEET, FLAPS UP
(DRY RUNWAY OVER A 35 FOOT SCREEN HEIGHT)
(ANTI-ICE OFF)
Determine takeoff field length, V1, VR, V2 and VENR from Figure 4-26. If the runway has a gradient,
adjust V1 and takeoff field length using figure 4-25.
If the required distance is greater than the available distance, the airplane weight must be reduced
until distance required is less than or equal to distance available.
Figure 4-25*
510FM-06 AH 4-45
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-26 (Sheet 1 of 15)*
4-46 AH 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-26 (Sheet 2)*
510FM-06 AH 4-47
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-26 (Sheet 3)*
4-48 AH 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-26 (Sheet 4)*
510FM-06 AH 4-49
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-26 (Sheet 5)*
4-50 AH 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-26 (Sheet 6)*
510FM-06 AH 4-51
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-26 (Sheet 7)*
4-52 AH 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-26 (Sheet 8)*
510FM-06 AH 4-53
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-26 (Sheet 9)*
4-54 AH 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-26 (Sheet 10)*
510FM-06 AH 4-55
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-26 (Sheet 11)*
4-56 AH 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-26 (Sheet 12)*
510FM-06 AH 4-57
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-26 (Sheet 13)*
4-58 AH 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
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Citation Mustang airplane flight manual 2(3)
