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Each main landing gear consists of two wheels with high speed tires. An anti-skid
system provides maximum braking efficiency on all runway surfaces an surface
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conditions.
7. Subsections:
The Dimensions, Areas and Major Component Locations section is divided into
the following subsections:
• 2A-06-20: Principal Dimensions
• 2A-06-30: Entrances, Exits and External Access Doors
• 2A-06-40: Flight Crew Station Components
2A-06-20: Principal Dimensions
1. Dimensions, Areas and Distances:
See Figure 2 through Figure 5 for principal dimensions, areas and distances.
2. General Weight Data:
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 Section 5, Performance.
(2) Maximum landing weight, unless restricted by climb requirements. Refer to
GIV Airplane Flight Manual Section 5, Performance.
3. General Powerplant Data:
A. Manufacturer: Rolls Royce
B. Model: Tay Mark 611-8
C. Number Installed: 2
D. Static Takeoff Thrust (Sea Level): 13,850 lb (6282.4 kg)
E. Maximum Continuous Thrust: 12,420 lb (5633.7 kg)
F. Engine Bypass Ratio: 3.10:1
G. Engine Pressure Ratio: 16.0:1
4. External Component Locations:
A. Antenna Locations:
Antenna locations are shown in Figure 1. For a description of the aircraft
antennas, see Section 2A-23-00, Communications.
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B. Light Locations:
Light locations are shown in Figure 6. For a description of the external
lights, see Section 2A-33-00, Lighting.
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External Antennas
Figure 1
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Exterior Dimensions
Figure 2
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Fuselage Dimensions
Figure 3
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Turning Dimensions and Distances
Figure 4
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Danger and Caution Areas
Figure 5
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2A-06-30: Entrances, Exits and External Doors
1. Main Entrance Door:
The main entrance door, located on the left side of the forward fuselage, is the
primary means of access for the passengers and flight crew. It consists of a door
structure with a folding stairway and handrails.
The main entrance door is hinged at its bottom to the aircraft fuselage. It can be
opened from either inside or outside the aircraft. Neither electrical nor hydraulic
power is required; the door free falls to the extended position under its own
weight.
See Section 2A-52-20, Main Entrance Door, for a description of the main entrance
External Lights
Figure 6
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door.
2. Cargo Door:
If Aircraft Service Change (ASC) 213 is incorporated, an upward opening,
hydraulically operated cargo door is installed on the right side of the fuselage
forward of the wing leading edge. Measuring 80.5” high and 81” wide, the cargo
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