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Clearway..................................................................................................... 500 ft. (152 m)
Headwind ..............................................................................................................10 knots
Anti-Skid ......................................................................................................OPERATIVE
Cowl and Wing Anti-Ice .............................................................................................. ON
Solution:
A. From Example 1, Section 5.2, The takeoff decision speed ratio V1 / VR can range in
value from 0.87 to 1.00.
NOTE: V1 / VR of 0.87 is used in this example because there is no height obstacle.
This will reduce brake wear (See Example 1, Section 5.2).
B. Enter the Flaps 20° TAKEOFF SPEEDS Chart at -5°C, read right to 6000 ft. Proceed
up to Takeoff Gross Weight = 63,000 pounds (28,580 kg). Move right to read
Rotation Speed = 135 KCAS.
C. Proceed left to the V1 / VR reference line. Follow guide lines to V1 / VR = 0.87.
Read V1 = 117 KCAS.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.5-2 FAA APPROVED
31 May 2001
D. Enter the Flaps 20° V2 Chart with Airport Pressure Altitude = 6000 ft.
Proceed right to 63,000 pounds (28,580 kg). Read down to Takeoff Safety Speed =
140 KCAS.
E. Enter the Flaps 20° MINIMUM V1 FOR CONTROL ON GROUND, V1MCG Chart
at -5° C to check V1MCG.
Proceed right to 6000 ft. then down, following weight guide lines to 63,000 pounds
(28,580 kg).
Read V1MCG = 116.0 KCAS. Since V1 determined in Step C (117 KCAS) is greater
than the minimum V1 for control on the ground (116.0 KCAS), V1 can range from
117 KCAS to VR (135 KCAS).
NOTE: If V1 determined in Step C is less than V1MCG, higher V1 / VR must be
selected from the range in Step A. A higher V1 / VR may result in lower
effective runway length which in turn will result in a corresponding
decrease in the field length limited takeoff gross weight. The field length
limited takeoff gross weight should be checked if the effective runway
length is reduced. See Example 2.
F. Enter the Flaps 20° MAXIMUM V1 FOR BRAKE ENERGY LIMITS, VMBE Chart
at -5° C to check VMBE.
Proceed right to 6000 ft. then up to 63,000 pounds (28,580 kg). Proceed left following
wind correction guidelines to 10 knots headwind, and slope correction guidelines to
+1%. Read VMBE = 169 KCAS.
Since V1 range determined in Step E (117 to 136 KCAS) is less than VMBE (169
KCAS), brake energy is not limiting.
NOTE: If highest V1 in range determined in Step E is greater than VMBE, V1
range must be restricted to values less than VMBE. If lowest V1 in range
determined in Step E is also greater than VMBE, takeoff weight must be
reduced.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.5-3
31 May 2001
EXAMPLE 2: Determine maximum allowable takeoff gross weight limited by VMCG.
Given: Airport Ambient Temperature....................................................................................30°C
Airport Pressure Altitude ......................................................................................2,000 ft.
Flaps ..............................................................................................................................20°
Runway Length ......................................................................................................6500 ft.
Runway Slope ...............................................................................................................0%
Stopway....................................................................................................................500 ft.
Clearway.......................................................................................................................0 ft.
Headwind ..............................................................................................................10 knots
Ground Spoilers............................................................................................OPERATIVE
Anti-Skid ..................................................................................................INOPERATIVE
Anti-Ice........................................................................................................................OFF
Solution:
A. Enter the Flaps 20° REFERENCE ACCELERATE - STOP DISTANCE Chart with:
Accelerate-Stop Distance available = 7000 ft. (6500 + 500)
Determine:
Reference Accelerate-Stop Distance = 3900 ft.
B. Enter the Flaps 20° REFERENCE ACCELERATE-GO DISTANCE Chart with:
Actual runway length = 6500 ft.
　
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