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weight and V1 / VR ratio.
Given: Airport Ambient Temperature............................................................................-5°C
Airport Pressure Altitude ..............................................................................6000 ft.
Flaps ....................................................................................................................20°
Takeoff Gross Weight .................................................... 63,000 pounds (28,580 kg)
Runway Length .......................................................................... 7000 feet (2134 m)
Runway Slope .......................................................................................+1% (uphill)
Stopway .............................................................................................. 200 ft. (61 m)
Clearway........................................................................................... 500 ft. (152 m)
Headwind .....................................................................................................10 knots
Anti-Skid and Ground Spoilers ..........................................................OPERATIVE
Cowl and Wing Anti-Ice .................................................................................... ON
V1 / VR ................................................................................................................ 1.0
Solution:
A. From example 1, effective runway length was found to be 5300 ft. (1615 m).
B. Enter the Flaps 20° RUNWAY LENGTH AND V1 ADJUSTMENTS chart with
effective runway length = 5300 ft. (1615 m) and V1 / VR = 1.00. Determine
reference accelerate-go distance to be 4900 ft. (1494 m) and reference acceleratestop
distance to be 5700 ft. (1737 m).
C. Enter the top of Flaps 20° REFERENCE ACCELERATE-GO DISTANCE chart
with 4900 ft. (1493 m) from Step B. Proceed down, making corrections as
necessary. DO NOT MAKE CLEARWAY CORRECTIONS. This result is
accelerate-go distance of 5600 ft. (1707 m). This distance is used for obstacle
clearance in Section 5.6.
D. Enter the top of Flaps 20° REFERENCE ACCELERATE-STOP DISTANCE chart
with 5700 ft. (1737 m) from Step B. Proceed down, making corrections as
necessary. Determine the accelerate-stop distance to be 5600 ft. (1707 m).
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.2-6 FAA APPROVED
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FAA APPROVED 5.2-9
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FAA APPROVED 5.2-11
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FAA APPROVED 5.2-13
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GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.3-1
30 May 2002
SECTION 5.3 CLIMB LIMITED PERFORMANCE
Takeoff gross weight is limited when available climb gradient is less than the minimum
allowable climb gradient. The FAR takeoff climb performance is limited by the most restrictive
of the following 3 engine-out climb requirements:
(1) A 2.4% climb gradient at 400 feet above takeoff surface with Takeoff Thrust and
takeoff flaps (10° or 20°).
(2) A 1.2% climb gradient at 1500 feet above takeoff surface with Maximum Continuous
Thrust and clean configuration.
(3) A 2.1% climb gradient at 0 feet above takeoff surface with Go-Around Thrust and
flaps 20°. (This last item is needed because the GIV does not have a fuel jettisoning
system.)
Conditions:
(1) Landing gear retracted
(2) Flaps 10° or 20°
(3) One engine inoperative
(4) Operating engine at Takeoff Thrust
(5) V2 speed
EXAMPLE: Find maximum allowable takeoff gross weight:
Given: Airport Ambient Temperature.................................................................................25°C
Airport Pressure Altitude ....................................................................................8000 ft.
　
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