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11. Maximum Tire Speed:
Airplane
Serial Number
Configuration Nose Tires Main Tires Overall Limit
1000 - 1213 Without ASC
190 / ASC 266
182 KTS / 210
MPH
182 KTS / 210
MPH
182 KTS / 210
MPH
1000 - 1213 With ASC 266 182 KTS / 210
MPH
195 KTS / 220
MPH
182 KTS / 210
MPH
1000 - 1213 With ASC 190 195 KTS / 220
MPH
195 KTS / 220
MPH
195 KTS / 220
MPH
1214 & Subs Production 195 KTS / 220
MPH
195 KTS / 220
MPH
195 KTS / 220
MPH
OPERATING MANUAL
EXPANDED LIMITATIONS 01-03-00
Page 5
May 30/02
Revision 7
Altitude / Mach Flight Envelope — SN 1000 And Subs Without ASC 61
Figure 2
OPERATING MANUAL
01-03-00 EXPANDED LIMITATIONS
Page 6
May 30/02
Revision 7
Altitude / Mach Flight Envelope — SN 1000 - 1214 With ASC 61
Figure 3
OPERATING MANUAL
EXPANDED LIMITATIONS 01-03-00
Page 7
May 30/02
Revision 7
01-03-70: Flight Load Acceleration Limits
1. Flaps UP:
-1.0 to 2.5 G for all weights up to maximum takeoff weight.
2. Flaps DOWN:
0 to 2.0 G for all weights up to maximum landing weight.
01-03-80: Weight Limitations
Airplane
Serial
Number:
Maximum
Zero Fuel
Weight:
Maximum
Ramp
Weight:
Maximum
Takeoff
Weight (1):
Maximum
Landing
Weight (2):
1000 - 1213
Without ASC
190 / ASC 61
46,500 lb
(21,092 kg)
73,600 lb
(33,385 kg)
73,200 lb
(33,204 kg)
58,500 lb
(26,536 kg)
1000 - 1213
With ASC 61
49,000 lb
(22,226 kg)
73,600 lb
(33,385 kg)
73,200 lb
(33,204 kg)
58,500 lb
(26,536 kg)
1000 - 1213
With ASC 190
49,000 lb
(22,226 kg)
75,000 lb
(34,020 kg)
74,600 lb
(33,838 kg)
66,000 lb
(29,937 kg)
1214 And Subs 49,000 lb
(22,226 kg)
75,000 lb
(34,020 kg)
74,600 lb
(33,838 kg)
66,000 lb
(29,937 kg)
NOTE(S):
(1) Maximum takeoff weight, unless restricted by climb performance, brake energy, or tire
speed for approved altitudes and ambient temperature or by field length. Refer to GIV
Airplane Flight Manual Performance Section for weight limitations.
(2) Maximum landing weight, unless restricted by climb requirements. Refer to GIV
Airplane Flight Manual Performance Section for weight limitations.
01-03-90: Center of Gravity Envelope
The allowable Center Of Gravity (CG) range is a function of gross weight as shown in the
charts that follow. Zero fuel gross weight CG must be within the allowable Zero Fuel
Gross Weight CG Envelope. The fueled aircraft CG will then be within limits for all fuel
loads.
OPERATING MANUAL
01-03-00 EXPANDED LIMITATIONS
Page 8
May 30/02
Revision 7
Zero Fuel Gross Weight Center Of Gravity Envelope (For Airplanes SN 1000 - 1213
Without ASC 61 / ASC 190)
Figure 4
OPERATING MANUAL
EXPANDED LIMITATIONS 01-03-00
Page 9
May 30/02
Revision 7
Zero Fuel Gross Weight Center Of Gravity Envelope (For Airplanes SN 1000 - 1213
With ASC 61)
Figure 5
OPERATING MANUAL
01-03-00 EXPANDED LIMITATIONS
Page 10
May 30/02
Revision 7
Zero Fuel Gross Weight Center Of Gravity Envelope (For Airplanes SN 1214 And
Subs, And SN 1000 - 1213 With ASC 190)
Figure 6
OPERATING MANUAL
EXPANDED LIMITATIONS 01-03-00
Page 11
May 30/02
Revision 7
OPERATING MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK.
01-03-00 EXPANDED LIMITATIONS
Page 12
May 30/02
AIRPLANE SERVICING
01-12-10: Hydraulic Fluids
The following fire-resistant Type 4 hydraulic fluids are approved for use:
• HyJet IV
• HyJet IV-A
• Skydrol LD-4
• Skydrol 500B-4
01-12-20: APU Fuel Grades and Fuel Temperatures
APU operation requires fuel at a viscosity of not more than 12 centistokes. The
corresponding fuel temperatures are as follows:
Fuel Grade: Minimum Fuel Temperature:
ASTM D1655, Jet A -30°C
MIL-T-5624, Grade JP-5 -30°C
MIL-T-83133, JP-8 -30°C
DEF STAN 91-86 -30°C
DEF STAN 91-87 -30°C
CAN 3-GP-24 -30°C
ASTM D1655, Jet A-1 -40°C
ASTM D1655, Jet B -40°C
CAN 2.3.23 -40°C
MIL-T-5624, Grade JP-4 -50°C
DEF STAN 91-88 -50°C
DEF STAN 91-91 -50°C
CAN 2.3.22 -50°C
01-12-30: Engine Fuel Grades
1. Kerosene Type:
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湾流4操作手册 Gulfstream IV Operating Manual 1(12)
