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tubes on the forward side of the rack and 6 on the aft side of the rack, 2 tubes per shelf.
These piccolos are connected via 2 lines to the underfloor avionics fan. The forward
exhaust line is tapped into the cockpit display exhaust line and the aft exhaust line (AV
FAN) is run separately back to the AV FAN manifold.
The rack and avionics bay fans can run at two speeds and are controlled the ACSC.
Refer to page 13-33 for control and operations.
The avionics fans ON/OFF switching logic is based on aircraft altitude. The fans are
on at an altitude of less than 30,000 feet with a default to always ON in the event of
loss of altitude data from the DAUs.
(Global 5000)
MAIN
DOOR
UNDER FLOOR
AVIONICS EQUIPMENT
Forward Outflow
Valve
Avionics
Exhaust Fan
Display Units
GX_appx_033
AIR
FROM
UNDER
FLOOR
AV Rack
Fan &
Filter
Above Floor
Avionics Rack
For Training Purposes Only
Sept 04
Appx-11
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
FMS AIRCRAFT TYPE
The aircraft type can be found on the PERF INIT page. For the Global 5000, it should
read: G5000-L1.
(Global 5000)
GX_appx_034
TAIL #0
000PERFORMANCE INIT 1/5
––––––O
0PERF MODE
G050000000–0L011152Z
0ACFT TYPE
FULL PERF ORO
Note:
GEX005V2 = 96,000 lb Global
GEX006V2 = 98,000 lb Global
G5000-L1 = G5000
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-12 For Training Purposes Only
Sept 04
GLOBAL 5000 FUEL SECTION
This section describes the fuel system for the Global 5000 aircraft.
Chapter 11 of the Pilot Training Guide describes the fuel system for the Global
Express. If you operate a Global Express, do not read this section, proceed directly to
Chapter 11.
SUMMARY OF GLOBAL 5000 FUEL SYSTEM CHANGES
The Global 5000 fuel system is a modified version of the Global Express fuel system.
In order to accommodate the reduced range requirements for Global 5000, the aircraft
total fuel capacity is reduced to maximum 5361 U.S. gallons (36,200 lb @ 6.75 lb/U.S.
gal). The fuel system changes are as follows:
AFT FUEL TANK REMOVAL
The entire aft fuel tank and its distribution equipment located in the aft equipment bay
is removed. Also, all the aft tank functions and their associated EICAS and synoptic
indications are deleted. As a result, the Cockpit Fuel Control Panel and Refuel/Defuel
Panel is modified to reflect this change. Also, the routing of engine feed and recirc
lines in the aft equipment bay are modified to accommodate The removal of the aft
tank structure.
CENTER TANK FUEL QUANTITY LIMITATION
The maximum fuel quantity in the center tank, achieved by pressure refueling, is
limited to 903 gallons, compared with 1655 gallons in the Global Express. The
existing high level shutoff methods used to stop refueling of the center tank is retained
for the Global 5000 aircraft, but the shutoff threshold is reduced by means of a
FMQGC software change. The change in aircraft pressure refuel quantity is reflected
in the placard located near the single point pressure refueling station and in the AFM
Limitations section.
Also, the maximum fuel quantity in the center tank achieved by gravity refueling is
limited to 830 gallons, vs. 1650 gallons in the Global Express. A dedicated Gravity
Fill Valve installed inside the center tank shuts off the gravity refueling when the
maximum capacity is reached. Also, the change in aircraft gravity refuel quantity is
reflected in the placard located near the center tank gravity port and in the AFM
Limitations section.
AUTOMATIC CONTROL OF FUEL RECIRCULATION SYSTEM
The fuel recirculation system is automatically controlled by the fuel computer
(-9 FMQGC), in order to provide the ability to maintain fuel tanks temperature within
the approved limits for prolonged flight at cold ambient temperatures.
For Training Purposes Only
Sept 04
Appx-13
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
GLOBAL 5000 FUEL SYSTEM – DETAILS
Fuel is contained in a wet wing box structure, which is sealed to form the three main
separate wing tanks. The tanks are vented to atmosphere and slightly pressurized by an
air scoop located on the lower surface of each wing. A scavenge pump purges fuel
from the vent lines and a climb vent, located in each main wing tank, provides
ventilation when the airplane is in a nose up attitude.
Each engine is supplied with fuel from its respective feed tank which contains two
　
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