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climb gradient of 3.9% exceeds the required average enroute climb gradient of
0.6%. Hence, the enroute obstacle clearance requirement is conservatively
satisfied (note that the net enroute climb gradient available is the gross gradient
reduced by 1.1% in accordance with FAR 25).
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-16 FAA APPROVED
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.6-17
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.6-18 FAA APPROVED
30 May 2002
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GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.7-1
30 May 2002
SECTION 5.7 ENROUTE CLIMB
Charts are presented for choosing the enroute climb speed (VSE) and for determining the enroute
climb gradient. The enroute climb speed shown is the speed for best gradient. The gradient data
shown have been reduced by a gradient of 1.1% as specified by FAR 25. The gradient of climb
read from chart should be used directly.
Conditions:
(1) Landing gear retracted
(2) Flaps 0°
(3) One engine inoperative
(4) Operating engine at Maximum Continuous Thrust
EXAMPLE: Find the enroute climb speed and the resulting gradient
Given: Ambient Temperature .......................................................................................-9° C
Pressure Altitude ...........................................................................................8000 ft.
Gross Weight.................................................................. 63,000 pounds (28,580 kg)
Headwind ....................................................................................................10 knots
Cowl and Wing Anti-icing .................................................................................. ON
Solution:
A. Enter the ENROUTE CLIMB SPEED chart with Pressure Altitude = 8000 ft.
Proceed right to 63,000 pounds (28,580 kg), then read down to Climb Speed =
170.8 KCAS.
B. Enter the ENROUTE CLIMB GRADIENT chart with temperature -9° C. Proceed
right to 8000 ft., up to 63,000 pounds (28,580 kg), then read left to Net Gradient =
3.9%.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.7-2 FAA APPROVED
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.7-3
30 May 2002
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.7-4 FAA APPROVED
31 May 2001
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GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.8-1
31 May 2001
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 (•M = 0.90 - 0.48)
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
5.8-2 FAA APPROVED
31 May 2001
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 5
PERFORMANCE
FAA APPROVED 5.9-1
31 May 2001
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
　
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