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GIV-SP 31 May 2000
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GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
SPECIAL
PERFORMANCE
FAA APPROVED 5.8-1
31 May 2000 GIV-SP
SECTION 5.8 BUFFET BOUNDARY
A buffet boundary chart is presented.
EXAMPLE 1: A self-explanatory example for the following condition is presented on chart.
Mach No. 0.65
Gross weight 60,000 pounds (27,216 kg)
Altitude 43,000 ft.
Under the above conditions, buffet can be expected at 1.24g load factor or at bank angle of 36°.
Margin between the high speed and low speed buffet boundaries can be obtained from this curve
by entering the chart from the bottom.
EXAMPLE 2: (Not shown on chart)
Altitude 40,000 ft.
Load factor l g
Gross weight 50,000 pounds (22,680 kg)
Speed margin 0.42 M (¨0 
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
SPECIAL
PERFORMANCE
5.8-2 FAA APPROVED
GIV-SP 31 May 2000
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
SPECIAL
PERFORMANCE
FAA APPROVED 5.9-1
31 May 2000 GIV-SP
SECTION 5.9 APPROACH CLIMB
Charts are presented for choosing the approach climb speed and for determining the approach
climb gradient. The approach climb speed shown is VREF+10 knots where VREF is the
approach speed for landing distance with flaps 39°. The steady gradient of climb may not be less
than 2.1%.
Conditions:
(1) Landing gear retracted
(2) Flaps 20°
(3) One engine inoperative
(4) Operating engine at Go-Around Thrust
EXAMPLE: Find the approach climb speed and resulting gradient
Given: Airport Ambient Temperature...........................................................................-5° C
Airport Pressure Altitude ..............................................................................6000 ft.
Gross Weight.................................................................. 55,000 pounds (24,948 kg)
Cowl and Wing Anti-icing .................................................................................. ON
Solution:
A. Enter the APPROACH CLIMB SPEED chart with Airport Pressure Altitude =
6000 ft. Proceed right to 55,000 pounds (24,948 kg), then read down to Approach
Climb Speed = 147 KCAS.
B. Enter the APPROACH CLIMB GRADIENT chart with temperature -5° C.
Proceed right to 6000 ft, up to 55,000 pounds (24,948 kg), then proceed left to
Cowl and Wing Anti-icing reference line and follow guidelines to read Climb
Gradient = 8.0%.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
SPECIAL
PERFORMANCE
5.9-2 FAA APPROVED
GIV-SP 31 May 2000
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
SPECIAL
PERFORMANCE
FAA APPROVED 5.9-3
31 May 2000 GIV-SP
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
SPECIAL
PERFORMANCE
5.9-4 FAA APPROVED
GIV-SP 31 May 2000
THIS PAGE INTENTIONALLY LEFT BLANK.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
SPECIAL
PERFORMANCE
FAA APPROVED 5.10-1
31 May 2000 GIV-SP
SECTION 5.10 ALL ENGINE LANDING CLIMB
Charts are presented for choosing all engine landing climb speed and for determining the all
engine landing climb gradient. The all engine landing climb speed shown is speed for best
gradient. The gradient may not be less than 3.2% and is based upon the thrust available eight (8)
seconds after movement of the power levers from high idle to go-around position.
NOTE: As controlled by the dual-datum idle system, engines will automatically advance to
high idle H.P. RPM when landing configuration (flaps 39°, gear down) is achieved.
CONDITIONS:
(1) Landing gear extended
(2) Flaps 39°
(3) All engines operating at Go-around Thrust (Overfueling Enabled, if Airstart Ignition -
ON, then Cowl Anti-ice - ON must be selected)
EXAMPLE: Find the all engine landing climb speed and resulting gradient.
Given: Airport Ambient Temperature...........................................................................-5° C
Airport Pressure Altitude ..............................................................................6000 ft.
Gross Weight.................................................................. 55,000 pounds (24,948 kg)
Cowl and Wing Anti-icing .................................................................................. ON
Solution:
A. Enter the ALL ENGINE LANDING CLIMB SPEED chart with Airport Pressure
Altitude = 6000 ft. Proceed right to 55,000 pounds (24,948 kg), then read down
to Landing Climb Speed = 136.5 KCAS.
　
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