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OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-28-00
Page 23
October 11/01
Revision 5
See Section 01-12-30, Engine Fuel Grades.
CAUTION
THE ENGINE WILL RUN ON SUCTION FUEL FEED
ONLY AT OR BELOW 20,000 FEET. ABOVE 20,000
FEET, THE ENGINE WILL RUN ERRATICALLY AND
FLAME OUT IF THE CROSSFLOW VALVE IS NOT
OPEN WITH AT LEAST ONE BOOST PUMP ON.
B. Other Limitations:
Normal operation of the fuel system is from tank to respective engine. For
takeoff and landing, all operable boost pumps are selected on.
OPERATING MANUAL
2A-28-00 PRODUCTION AIRCRAFT SYSTEMS
Page 24
October 11/01
Revision 5
Refueling Adapter and Precheck Controls
Figure 4
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-28-00
Page 25
October 11/01
Revision 5
Fuel Boost Pump
Figure 5
OPERATING MANUAL
2A-28-00 PRODUCTION AIRCRAFT SYSTEMS
Page 26
October 11/01
Revision 5
Fuel Ejector
Figure 6
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-28-00
Page 27
October 11/01
Revision 5
2A-28-40: Fuel Indication System
1. General Description:
The fuel indication system provides the flight crew with continuous indication of
fuel quantity and warns of a low fuel level. Continuous indication of fuel tank
temperature is also provided. The fuel indication system is composed of the
following subsystems, units and components:
• Fuel Quantity Indication System
• Fuel Low Level Warning System
• Fuel Temperature Indication System
Fuel flow and engine fuel temperature indications are described in Section 2A-73-
Permissible Fuel Unbalance For All Flight Operations
Figure 7
OPERATING MANUAL
2A-28-00 PRODUCTION AIRCRAFT SYSTEMS
Page 28
October 11/01
Revision 5
10, Engine Fuel System.
2. Description of Subsystems, Units and Components:
A. Fuel Quantity Indication System:
(See Figure 8 through Figure 10.)
(1) General:
A set of 21 parallel-wired, capacitence-type fuel probes extend into
various parts of each wing tank to provide an accurate
measurement of tank fuel quantity. The two sets of probes are
identical and independent. Each set connects to a signal conditioner
through a signal junction box. The signal conditioner, powered by
the Essential DC bus, uses the composite readings to drive the
standby fuel quantity indicator and to provide driving signals to Data
Acquisition Units (DAUs) No. 1 (left side) and No. 2 (right side) for
display on the Engine Instrument and Crew Alerting System
(EICAS).
(2) EICAS Fuel Displays:
Fuel quantity appears in the lower right corner of the EICAS engine
instruments display as FUEL QTY. The Left (L) and Right (R)
displays show fuel quantity in the respective wing in 50 lb
increments, ranging from 0 lb to 15,000 lb. The Total (T) display
shows the combined fuel quantity of both wings in 50 lb increments,
ranging from 0 lb to 30,000 lb. The FUEL system page on CAS
displays the identical information. Under normal conditions, EICAS
fuel quantity data is displayed white in color. If a low fuel condition in
one wing is detected, the respective quantity display digits change
to amber. If a low fuel condition in both wings is detected, the entire
FUEL QTY display changes to amber. If a DAU fails, the associated
side’s display digits are replaced with amber dashes.
(3) Standby Fuel Quantity Indicator:
Located on the copilot’s flight panel, the standby fuel quantity
indicator contains three 4 digit displays: LEFT, RIGHT and TOTAL.
Values shown on each display are in pounds to be multiplied by ten
(LBS × 10). Above the LEFT and RIGHT displays are associated
amber LOW FUEL warning lights which illuminate when
approximately 650 pounds (295 kg) of usable fuel remains in the
respective hopper.
To the right of the TOTAL display is a three-position, momentaryaction
TEST switch, used to test both the standby fuel quantity
indication system and / or the EICAS fuel quantity indication system.
Switch positions are “D” (for standby fuel quantity indicator display
testing only), off (the spring-loaded center position) and “T” (for
testing the entire fuel quantity indication system). Holding the TEST
switch in “D” results in the standby fuel quantity indicator’s three
displays showing all eights (8888); EICAS is not tested in this mode.
Holding the TEST switch in “T” results in the standby fuel quantity
indicator and EICAS FUEL QTY display showing 7000 pounds in
each wing and 14,000 pounds total. (If the No. 21 probe
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湾流4操作手册 Gulfstream IV Operating Manual 2(38)
