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release point. Therefore, obstacle is located 26,900 feet (8199 m) (32,500-5600)
from reference zero.
D. Determine obstacle height above reference zero - reference zero is 56 ft. (17 m)
above brake release point, therefore, obstacle height above reference zero is 1274
feet (1330 - 56).
E. Locate obstacle on Flaps 20° DISTANT OBSTACLE CLEARANCE chart with:
Horizontal Distance from Reference Zero = 26,900 feet (8199 m) and Height
Above Reference Zero = 1274 ft. (388 m). Determine the required 400 foot net
gradient to be 5.0% .
F. Enter the Flaps 20° AVAILABLE NET GRADIENT, TAKEOFF SECOND
SEGMENT CLIMB chart with -5°C and proceed right to Airport Pressure
Altitude = 6000 feet. Proceed up to Takeoff Gross Weight = 63,000 pounds
(28,580 kg). Proceed left through corrections and determine the available 400
foot net gradient to be 5.0%.
G. The available net gradient of 5.0% at 400 ft. is equal to the required net gradient
of 5.0% at 400 ft. The assumed takeoff weight of 63,000 pounds (28,580 kg.) is
not limited by obstacle.
NOTE: If available gradient had been less than that required, obstacle would
be limiting. Reduced allowable takeoff gross weight for obstacle
clearance must be determined.
H. To determine reduced takeoff gross weight, enter the Flaps 20° AVAILABLE
NET GRADIENT, TAKEOFF SECOND SEGMENT CLIMB chart with Net
Gradient Required at 400 ft. (determined from Step E). Work backward through
corrections, while also entering with airport ambient temperature and airport
pressure altitude and proceed up. The resulting intersection at weight correction
grid is takeoff gross weight limited by the obstacle clearance.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-4 FAA APPROVED
31 May 2001
I. The takeoff gross weight from Step H may be optimized by iteration since new
weight will result in new reference zero.
Repeat Steps A through H as desired or until the allowable takeoff gross weight is
maximized. If the takeoff weight with flaps 20° is limited by obstacle clearance,
takeoff with flaps 10° could allow the higher weight.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.6-5
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-6 FAA APPROVED
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.6-7
31 May 2001
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-8 FAA APPROVED
31 May 2001
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.6-9
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-10 FAA APPROVED
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.6-11
31 May 2001
FINAL TAKEOFF CLIMB
Charts are presented for choosing final takeoff climb speed (VFS) and for determining final
takeoff climb gradient. The steady gross gradient of climb may not be less than 1.2%.
Conditions:
(1) Landing gear retracted
(2) Flaps 0°
(3) One engine inoperative
(4) Operating engine at Maximum Continuous Thrust
EXAMPLE: Find final climb speed and resulting gradient
Given: Airport Ambient Temperature............................................................................-5°C
Airport Pressure Altitude ..............................................................................6000 ft.
Takeoff Gross Weight .................................................... 63,000 pounds (28,580 kg)
Cowl and Wing Anti-icing .................................................................................. ON
Solution:
A. Enter FINAL TAKEOFF CLIMB SPEED chart with Airport Pressure Altitude =
6000 ft. Proceed right to 63,000 pounds (28,580 kg), then read down to Climb
Speed = 162.5 KCAS.
B. Enter FINAL TAKEOFF CLIMB GRADIENT chart with -5°C. Proceed right to
6000 ft., up to 63,000 pounds (28,580 kg), then read left to 1500 Foot Gross
Gradient = 5.0%.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-12 FAA APPROVED
31 May 2001
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.6-13
31 May 2001
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-14 FAA APPROVED
30 May 2002
DISTANCE TO ACCELERATE FROM V2 TO VSE AT 1500 FEET AGL
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湾4飞机飞行手册AFM Gulfstream IV AIRPLANE FLIGHT MANUAL 2(94)
