TM 55-1510-220-10
Table 2-2. Fuel Quantity Data
TANKS
NUMBER
GALLONS
**POUNDS
LEFT ENGINE
Wing Tanks
Nacelle Tank
Auxiliary Tank
5
1
1
135
57
79
877.5
370.5
513.5
RIGHT ENGINE
Wing Tanks
Nacelle Tank
Auxiliary Tank
5
1
1
135
57
79
877.5
370.5
513.5
*TOTALS
14
542
3523.0
* Unusable fuel quantity and weight (4 gallons, 26 pounds not included in totals).
** Fuel weight is based on standard day conditions at 6.5 pounds per U.S. gallon.
BTO 1490
management panel to the OVERRIDE position. This will
energize the transfer control motive flow valve. The
transfer systems are protected by. 5ampere circuit
breakers placarded AUXILIARY TRANSFER No. 1 or No.
2, located on the overhead circuit breaker panel (fig. 2-
27).
NOTE
In turbulence or during maneuvers
the NO FUEL XFR annunciators
may momentarily illuminate after
the auxiliary fuel has completed
transfer.
d.
Fuel Gaging System. The total fuel quantity
in the left or right main system, or left or right auxiliary
system is measured by a capacitance type fuel gaging
system. Two fuel gages, one for the left and one for the
right fuel system, indicate the fuel quantity in pounds.
Refer to Section IX for fuel capacities and weights. A
maximum of 3% error may be encountered in each
system. However the system is compensated for fuel
density changes due to temperature excursions. In
addition to the fuel gages, yellow No. 1 NAC LOW or No.
2 NAC LOW annunciators on the caution/advisory
annunciator panel illuminate when there is approximately
20 minutes of fuel per engine remaining (on standard day,
lat sea level, maximum cruise power consumption rate).
The fuel gaging system is protected by individual 5-
ampere circuit breakers placarded QTY IND and QTY
WARN No. I or No. 2 located on the overhead circuit
breaker panel (fig. 2-27). A mechanical spiral float gage
is installed in each auxiliary fuel tank to provide an
indication of fuel level when servicing the tank. The gage
is installed on the auxiliary fuel tank cover, adjacent to the
filler neck (fig. 2-17). A small sight window in the upper
wing skin permits observation of the gage.
e.
Fuel Management Panel. The fuel management
panel is located on the cockpit overhead between the pilot
and copilot. It contains the fuel gages, standby fuel pump
switches, the crossfeed valve switch and a fuel gaging
system control switch and transfer control switches are
also installed.
(1)
Fuel gaging system control switch. A
switch on the fuel management panel (fig. 2-14)
placarded FUEL QUANTITY, MAIN AUXILIARY, controls
the fuel gaging system. When in the MAIN position the
fuel gages read the total fuel quantity in the left and right
wing fuel system. When in the AUXILIARY position the
fuel gages read the fuel quantity in the left and right
auxiliary tanks only.
(2)
Standby
fuel
pump
switches.
Two
switches, placarded STANDBY PUMP ON located on the
fuel management panel (fig. 2-14) control a submerged
fuel pump located in the corresponding nacelle tank.
During normal aircraft operation both switches are off so
long as the engine-driven boost pumps function and
during crossfeed operation. The loss of fuel
Change 2 2-29
