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Must be disengaged by 50 ft. (AGL) on approach.
1-22-30: Autopilot:
Do not engage below 200 ft. (AGL) on takeoff.
Must be disengaged on approach by 50 ft. (AGL).
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 1
LIMITATIONS
FAA APPROVED 1-25
31 May 2000
1-24-00: ELECTRICAL POWER
1-24-10: Standby Electrical System:
When standby electrical system is in operation, the following limitations apply:
• Minimum HP RPM is 67 percent.
• Speed Brakes may be used, however, operation should be slow (approximately five (5)
seconds for full range movement).
• Landing is approved provided auto ground spoilers and thrust reversers are not used for
landing. See Appendix C for appropriate checklist.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 1
LIMITATIONS
1-26 FAA APPROVED
13 September 2000
1-27-00: FLIGHT CONTROLS
1-27-10: Angle Of Attack System (AOA):
Angle-of-Attack (AOA) may be used as reference, but does not replace airspeed as the primary
reference.
AOA indication must be within white band once forward airspeed is attained during takeoff roll.
AOA indication shall not be used as a speed reference for takeoff rotation.
1-27-20: Stall Warning/Stall Barrier System:
Both Stall Warning/Stall Barrier Systems must be operative for takeoff. Stall Barrier Systems
must be ON during all flight operations except as noted in Section 4-15-40: Stall Barrier
Malfunction. See GIV Operating Manual, STALL WARNING/STALL BARRIER CHECKOUT
PROCEDURE.
1-27-30: Yaw Damper:
If Yaw Damper fails prior to takeoff:
1. Maximum fuel quantity permitted for takeoff is 9,000 lb (4082 kg).
If Yaw Damper fails in-flight:
2. Above 18,000 ft. maintain airspeed at or above 220 KCAS.
3. Below 18,000 ft. maintain airspeed, as function of fuel quantity, at or above that shown
below until ready to configure for approach and landing.
Fuel Quantity - 1000 lb 8 10 12 14 16 18 20 22 24 26 28 30
Minimum Airspeed - KCAS 96 107 117 126 135 143 151 158 165 172 178 184
When Yaw Damper failure is coupled with failure of Mach Trim Compensation, observe speed
limitations for both failures and limit altitude to 41,000 ft.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 1
LIMITATIONS
FAA APPROVED 1-27
31 May 2000
1-27-40: Speed Brakes:
Speed brakes are not approved for extension with flaps at 39° or with landing gear extended.
Do NOT pull FLIGHT POWER SHUTOFF handle with speed brakes extended.
1-27-50: Ground Spoilers:
Takeoff is permitted with Ground Spoilers inoperative, provided Anti-Skid is operative and 20°
flaps are used for takeoff.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 1
LIMITATIONS
1-28 FAA APPROVED
31 May 2000
1-28-00: FUEL
1-28-10: Usable Fuel Capacities:
For maximum unbalanced fuel, see Figure 1-7: PERMISSIBLE FUEL UNBALANCE. Before
the imbalance exceeds that shown, proceed with Fuel Balancing.
The usable fuel capacities are:
Right Tank 14,750 pounds ( 6,690 kg) 2,185 gallons ( 8,271 liters)
Left Tank 14,750 pounds ( 6,690 kg) 2,185 gallons ( 8,271 liters)
Total 29,500 pounds (13,380 kg) 4,370 gallons (16,542 liters)
NOTE: It is possible to upload fuel in excess of 29,500 pounds. This is permitted as long as the
maximum ramp weight and/or the maximum takeoff weight is not exceeded, and the
loaded airplane center of gravity is within limits.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 1
LIMITATIONS
FAA APPROVED 1-29
31 May 2000
Figure 1-7: Permissible Fuel Unbalance For All Flight Operations
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 1
LIMITATIONS
1-30 FAA APPROVED
11 October 2001
1-28-20: Boost Pumps:
During cruise, one (1) boost pump per side may be selected OFF provided:
1. The fuel contains an Anti-Icing additive, or
2. Fuel tank temperature is above 0°C.
See ENGINE FUEL GRADES, this Section.
CAUTION: THE ENGINE WILL ONLY RUN ON SUCTION FUEL FEED AT OR BELOW
20,000 FT. ABOVE 20,000 FT, THE ENGINE WILL RUN ERRATICALLY
AND FLAME OUT IF THE CROSSFLOW IS NOT OPEN WITH AT LEAST
ONE BOOST PUMP ON.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 1
LIMITATIONS
FAA APPROVED 1-31
31 May 2000
1-30-00: ICE AND RAIN PROTECTION
1-30-10: Wing Anti-Icing:
Operation of Wing Anti-Icing System is required if icing conditions are imminent, or
immediately upon detection of ice formation on wings, winglets, or windshield edges.
1-30-20: Cowl Anti-Icing:
Operation of Cowl Anti-Icing System is required for taxi and takeoff when static air temperature
　
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