* Asterisk indicates page(s) revised or added by the current revision.
Sec. 12 LEP-2 MD-80 Rev. 12/01/00 #29 Continental Flight Manual
LIST OF EFFECTIVE PAGES PAGE
DATE PAGE DATE
PAGE DATE
* LEP-1 12/01/00
* LEP-2 12/01/00
* Asterisk indicates page(s) revised or added by the current revision.
FUEL
TABLE OF CONTENTS
FUEL ................................................................................................. 1
General ....................................................................................... 1
Fuel Tanks................................................................................... 1
Fuel Feed .................................................................................... 2
Fuel Tank Quantity Indicating ...................................................... 3
Fueling and Defueling.................................................................. 3
Continental
Rev. 12/01/00 #29 Flight Manual
INTENTIONALLY LEFT BLANK
FUEL
General
The airplane fuel system is designed to provide an uninterrupted fuel flow under all conditions and attitudes encountered in normal service, with minimum system management. The system is also designed to permit fuel servicing activities to be accomplished from a single point.
Fuel Tanks
The three integral fuel tanks, left main, center, and right main have a capacity of 5,840 U.S. gallons (22,104 liters) or 39,128 pounds (17,748 kilograms), based on a density of 6.7 pounds per gallon (0.803 kilograms per liter).
A sump drain is located at the lowest inboard point of each main tank and aft at the bottom of each auxiliary fuel tank (if installed). Two sump drains are located in the center tank. Four magnetic, dripless sticks (magna-sticks) are located in each main tank and one in the center tank. An inclinometer in the nosewheel well provides airplane ground attitude information for fuel gauging calibrations. Sump drains and magna-sticks can be operated with a screwdriver.
Some airplanes have two auxiliary fuselage tanks (not used at Continental), one in the mid-cargo compartment and one in the aft cargo compartment. Each auxiliary tank has a capacity of 565 gallons (2,139 liters) for a total of 1,130 U.S. gallons (4,278 liters) or 7,571 pounds (3,343 kilograms).
Tank Venting
The fuel tank vent system is designed to provide fuel tank ventilation, scavenging from the vent system, and overfill protection during fueling.
The vent system is composed of bellmouth openings, fuel line vent valves, and climb vent float valves housed within each tank, and vent boxes located in each wing tip.
Normally as fuel is consumed, air enters the tank through the vent lines.
If the tank is overfilled during refueling, the fuel will fill the vent lines and then move to the opposite wing vent box. If the vent box becomes overfilled, fuel will spill out onto the ramp. Therefore a fuel spill from a vent box indicates that the opposite wing is overfilled.
Note: The Center Tank vents to the right wing vent box along with the left wing main tank.
Continental
Rev. 12/01/00 #29 Flight Manual
Fuel Feed
Each main fuel tank has two AC boost pumps installed. These pumps are connected in parallel to provide approximately 15 psi with one or both pumps operating. Either boost pump in the main fuel tanks has adequate flow to supply both engines at takeoff power. An interconnect system and cable operated crossfeed valve between the fuel tank systems permits use of fuel from either main fuel tank to both engines.
The two center tank pumps are connected in series to provide pressure higher than that of the main tank pumps, and insure usage of the center tank fuel even with both main tank pumps operating. When fuel is loaded in the Center tank, both pumps are selected ON until the center tank is empty. One way poppet valves are installed in the center tank supply lines to prevent engine flameout caused by the engine pumps suction feeding air from an empty center tank.
Each AC boost pump is powered by a different electrical system so that one pump in each tank remains operational with a loss of either left or right AC power.
Note: With only one pump operating in each fuel tank, the center fuel will
not feed normally due to the operation of the poppet valves. A 28-volt DC start pump, operated by a switch on the overhead panel, is installed in the right main tank and is used for APU or engine starting when AC power is not available. The start pump is powered by the DC Transfer bus and has an output of approximately 10 psi maximum.
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