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attitude and presents the corrected information of individual tank quantities, and total
fuel quantity displayed on EICAS. The FMQGC can display quantity in either pounds
(standard) or kilograms (optional). The primary EICAS page displays fuel quantity in
all fuel tanks, and total fuel in the airplane.
GX_appx_011
YD OFF
GLD MANU
PARK/EME
<– FUEL
TOTAL FUEL (LBS) 362OO
1.54
15O5O 61OO 15O5O
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
575O
115
81
SPD
EPR
I
G
N
START START
I
G
N
ND
STAB
1.54
73.3
T/O
N1
SYNC
73.3
789
ITT
SYNC
789 DN D
G
–TR
NL
LWD
7.2
NU
93.4
575O
115
81
Fuel Flow Readout
Indicates fuel flow in pounds per
hour (PPH) to the respective
engine.
Fuel Quantity Readout
(Wing Tank)
Green
Amber
Indicates fuel quantity in the
respective wing tank, in
pounds (lbs).
• – Left and right tanks
are balanced.
• – A fuel quantity
imbalance exists.
Total Fuel Readout
Green
Amber
Indicates total fuel quantity in
pounds (lbs), of all the tanks.
• – Total fuel quantity is
valid and in normal range.
• – A fuel low quantity or
discrepancy exists.
Fuel Quantity Readout
(Center Fuselage Tank)
Green
Amber
Indicates fuel quantity in the
cente tank, in pounds (lbs).
• – Quantity is valid.
• – A fuel quantity
discrepancy exists.
r
EICAS PRIMARY DISPLAY
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-28 For Training Purposes Only
Sept 04
FLIGHT MANAGEMENT DISPLAY
When both engines are started, the Flight Management System (FMS) fuel quantity
switches from Fuel Quantity Gauge System (FMQGC) to FMS computed fuel
quantity, based on fuel flow data from the engines and APU.
Fuel quantity information to the FMS is used for monitoring and sensing, to assist in
determining a fuel leak. When a fuel leak is detected, a crew alert (“MSG” on the
Primary Flight Display) will be displayed and a message will appear on the scratchpad
of the FMS CDU.
COMPARE FUEL QUANTITY
0DEPARTURE
0PERFORMANCE INIT–LB 5/5
0BOW
51000
PASS/@ LB0
5/170
0FUEL (GAUGE) PASS WT00
25000 (23900) 8500
0CARGO GROSS WT00
200 770500
CONFIRM INIT0
GX_appx_012
COMPARE FUEL QUANTITY
0DEPARTURE T.O.INIT0
000ACTIVE FLT PLAN 1/4
0BOW PASS/@ LB0
0/170
0055°00154NM
15820 (00+21
0K0P0H0X0001152Z
SJN
0059°00121NM
15820 (00+15 .75M/10000A
CLS
ABQ
0ORIGIN
.75M/10000A
CLS
COMPARE FUEL
QUANTITY
Displays when
the gauge fuel
weight and the
FMS fuel weight
differ by more
than 2% of the
Basic Operating
Weight (BOW).
For Training Purposes Only
Sept 04
Appx-29
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
ENGINE FEED SYSTEM
Fuel is provided to each engine from the two AC boost pumps. In normal operation,
both boost pumps are continuously on, and provide all engine fuel flow once the
engine is started. The AC pumps are located in the inboard section of each wing (feed
tank), and each AC pump is powered by a separate bus.
Loss of pressure at any AC boost pump causes the DC pump to come on, to provide a
back up of the remaining boost pump. The DC pumps also come on automatically for
takeoff, based on flaps/slats position and weight on wheels logic.
The engine fuel burn schedule is automatically controlled by the FMQGC to ensure
correct distribution for all airplane configurations.
The engine fuel burn sequence is as follows:
• Fuel from the wing tank will burn first
• When the wing tanks get below 93%, fuel transfers from the center tank to the
wing tank until it is at or above 97%
• When the center tank empties, fuel from the wing tanks continue to burn
P I LOT T R A I N I N G GU I D E
GLOBAL 5000 DIFFERENCES
APPENDIX 1
Appx-30 For Training Purposes Only
Sept 04
Engine Feed System Indication
The left FUEL synoptic page below represents the normal engine start mode of
operation. The right engine is started using the Auxiliary Power Unit (APU) as the
source of electrical power and left engine is off. The right Fuel synoptic display
　
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