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airplane’s actual takeoff flight paths diminished by gradient of climb equal to 0.8%.
5. At all points along takeoff path below 400 feet above takeoff surface, available gross
gradient of climb shall not be less than 2.4% with zero wind (FAR minimum
requirement).
6. At all points along takeoff path starting at 400 feet above the takeoff surface, the
available gross gradient of climb shall not be less than 1.2% with zero wind. (FAR
requirement for final takeoff climb).
Based on above requirements, obstacle clearance charts presenting required net takeoff flight
paths have been constructed. A chart which presents available second segment net climb
gradient for takeoff flight path is also shown. The available gradient chart is based on
assumption of one engine failure at critical engine failure speed (VEF) and inoperative thereafter.
All charts are conservatively based on no weight reduction due to fuel consumption during the
takeoff run and climb. Hence, weight to be used in charts should be that assumed at brake
release. Similarly, airport altitudes and temperatures are quoted throughout.
The charts provided may be used in the following manner:
A. Determine the required net gradient to clear obstacle: Enter the Required Net Takeoff
Flight Path charts with Height and Horizontal Distance equal to computed values of
obstacle height and distance relative to reference zero.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-2 FAA APPROVED
30 May 2002
B. Determine the available net gradient for an assumed takeoff weight: This is shown as
the 400 foot net gradient in Available Second Segment Climb Gradient chart. If this
available gradient is greater than the required gradient from (A), then takeoff at the
assumed takeoff weight can be made. If this requirement is not satisfied, the takeoff
gross weight must be reduced. (If this requirement is not met with flaps 20°, takeoff
with flaps 10° should be considered since this provides better climb capability.)
←
←
Available Net
Gradient
Required Net Takeoff Flight Path
Reference Zero
Horizontal Distance
Obstacle Height
↓
Conditions:
(1) Takeoff flap setting
(2) One engine inoperative
(3) Operating engine at Takeoff Thrust
(4) V2 climb speed
EXAMPLE: Find maximum allowable takeoff gross weight:
Given: Airport Ambient Temperature...........................................................................-5° C
Airport Pressure Altitude ..............................................................................6000 ft.
Flaps .....................................................................................................................20°
Obstacle: 32,500 ft. (9906 m) from brake release point
1330 ft. (405 m) above brake release point
Takeoff gross weight...................................................... 63,000 pounds (28,580 kg)
Runway Slope .......................................................................................+1% (uphill)
Headwind .....................................................................................................10 knots
Runway Length ............................................................................. 7000 ft. (2134 m)
Stopway .............................................................................................. 200 ft. (61 m)
Clearway............................................................................................ 500 ft. (152 m)
Anti-Skid .............................................................................................OPERATIVE
Cowl and Wing Anti-Ice ..................................................................................... ON
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.6-3
30 May 2002
Solution:
A. Determine Accelerate-go distance using highest possible V1 / VR. Higher values
of V1 / VR are used to reduce accelerate-go distance which determines reference
zero. Moving reference zero point closer to brake release provides greater
horizontal distance in which to clear the obstacle. From Example 3, Section 5.2,
accelerate-go distance is 5600 ft. (1707 m).
B. Determine Reference Zero - Distance from brake release point to reference zero is
same as the accelerate-go distance (5600 ft. (1707 m)) for takeoff gross weight.
Since runway slopes uphill (+1%), reference zero is 56 feet above brake release
point (0.01 x 5600).
C. Determine obstacle distance from reference zero - Obstacle is located 32,500 ft.
(9906 m) from brake release point, reference zero is 5600 ft. (1707 m) from brake
　
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