曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
B. Obstacle Horizontal Distance from Reference Zero = 4500 FEET
510FM-05 AA 4-143
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-37*
4-144 AA 510FM-05
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
SINGLE-ENGINE TAKEOFF FLIGHT PATH DISTANCES
FLAPS 15°
The data presented in Figure 4-39 (Anti-ice OFF) and 4-40 (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 4-38*
*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 + 1710 = 5635 FEET.
SINGLE-ENGINE FLIGHT PATH CONDITIONS:
FIRST SEGMENT SECOND SEGMENT THIRD SEGMENT
LANDING GEAR DOWN TRANSITION TO
UP
UP UP
WING FLAP DEGREES 15 15 15 TRANSITIONING TO 0
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 = 15°
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 4-39
Reference Zero to End of First Segment = 2501 FEET
Reference Zero to End of Second Segment = 26,859 FEET
Reference Zero to End of Third Segment = 31,369 FEET
Takeoff Climb Increment (TCI) = 1710 FEET
510FM-05 AA 4-145
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 1 of 15)*
4-146 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-39 (Sheet 2)*
510FM-06 AA 4-147
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 3)*
4-148 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-39 (Sheet 4)*
510FM-06 AA 4-149
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 5)*
4-150 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-39 (Sheet 6)*
510FM-06 AA 4-151
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 7)*
4-152 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-39 (Sheet 8)*
510FM-06 AA 4-153
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 9)*
4-154 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-39 (Sheet 10)*
510FM-06 AA 4-155
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 11)*
4-156 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-39 (Sheet 12)*
510FM-06 AA 4-157
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 13)*
4-158 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-39 (Sheet 14)*
510FM-06 AA 4-159
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-39 (Sheet 15)*
4-160 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-40 (Sheet 1 of 15)*
510FM-06 AA 4-161
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-40 (Sheet 2)*
4-162 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
Figure 4-40 (Sheet 3)*
510FM-06 AA 4-163
SECTION IV - PERFORMANCE MODEL 510
TAKEOFF
FAA APPROVED
U.S. Configuration
Figure 4-40 (Sheet 4)*
4-164 AA 510FM-06
MODEL 510 SECTION IV - PERFORMANCE
TAKEOFF
FAA APPROVED
Configuration U.S.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
Citation Mustang airplane flight manual 2(9)
