Aircraft Fuel System Questions

1. (8698) Fuel jettisoning is usually accomplished
~ Fuel jettisoning is usually accomplished by a fuel dump manifold, which connects the dumpable fuel tanks to the dump valves and to a fixed or extendable dump chute in each wing.
@ Fuel jettisoning is usually accomplished by a fuel dump manifold, which connects the dumpable fuel tanks to the dump valves and to a fixed or extendable dump chute in each wing.
*a. through a common manifold and outlet in each wing.
b. by gravity flow into the outboard wing tanks and overboard through a common outlet in each wing.
c. through individual outlets for each tank.

2. (8699) The primary purpose of an aircraft's fuel jettison system is to quickly achieve a
~ Some aircraft are allowed to have a higher takeoff weight than is allowed for landing. These aircraft must have a fuel jettison system that allows the pilot or flight engineer to safely dump, or jettison, enough fuel to reduce the aircraft weight to its allowable landing weight.
@ Some aircraft are allowed to have a higher takeoff weight than is allowed for landing. These aircraft must have a fuel jettison system that allows the pilot or flight engineer to safely dump, or jettison, enough fuel to reduce the aircraft weight to its allowable landing weight.
*a. lower landing weight.
b. balanced fuel load.
c. reduced fire hazard.

3. (8700) (1) The fuel jettison valve must be designed to allow flight personnel to close the valve during any part of the jettisoning operation.
(2) During the fuel jettisoning operation, the fuel must discharge clear of any part of the airplane.
Regarding the above statements,
~ Statement (1) is true. The fuel-jettisoning valve must be designed to allow flight personnel to close the valve during any part of the jettisoning operation. Statement (2) is also true. During the fuel-jettisoning operation, the fuel must discharge clear of any part of the airplane.
@ Statement (1) is true. The fuel-jettisoning valve must be designed to allow flight personnel to close the valve during any part of the jettisoning operation. Statement (2) is also true. During the fuel-jettisoning operation, the fuel must discharge clear of any part of the airplane.
*a. both No. 1 and No. 2 are true.
b. only No. 2 is true.
c. neither No. 1 nor No. 2 is true.

4. (8701) Which of the following is employed to maintain lateral stability when jettisoning fuel?
~ Lateral stability during fuel jettisoning is maintained by having two separate and independent jettisoning systems. There is one system for each side of the aircraft.
@ Lateral stability during fuel jettisoning is maintained by having two separate and independent jettisoning systems. There is one system for each side of the aircraft.
*a. Two separate independent systems.
b. Crossfeed system.
c. Two interconnected systems.

5. (8702) A fuel jettison system is required under certain conditions if the maximum takeoff weight exceeds the maximum landing weight. What regulations cover the requirements of fuel jettisoning?
~ The regulations governing fuel jettisoning systems are covered in Federal Aviation Regulations Parts 23 and 25, and in the Civil Air Regulations Part 04 for aircraft that were certificated by the Civil Aeronautics Administration before the formation of the FAA.
@ The regulations governing fuel jettisoning systems are covered in Federal Aviation Regulations Parts 23 and 25, and in the Civil Air Regulations Part 04 for aircraft that were certificated by the Civil Aeronautics Administration before the formation of the FAA.
a. Federal Aviation Regulation Part 43 and 91.
*b. Federal Aviation Regulation Part 23, 25 and CAM 4b.
c. Federal Aviation Regulation Part 21, 43 and CAM 8.

6. (8703) Fuel is moved overboard in most fuel jettison systems by
~ Fuel is moved overboard in a jettison system by boost pumps located in the fuel tanks.
@ Fuel is moved overboard in a jettison system by boost pumps located in the fuel tanks.
*a. boost pumps.
b. gravity.
c. gravity and engine-driven fuel pumps.

7. (8704) Fuel jettisoning past the limits prescribed by Federal Aviation Regulations is usually prevented by
~ Fuel tanks whose fuel can be jettisoned are equipped with a dump limit switch that will shut off the flow to the dump chute if the pressure drops below that needed to supply the engine with adequate fuel, or when the tank level reaches a preset dump shutoff level.
@ Fuel tanks whose fuel can be jettisoned are equipped with a dump limit switch that will shut off the flow to the dump chute if the pressure drops below that needed to supply the engine with adequate fuel, or when the tank level reaches a preset dump shutoff level.
a. closely monitoring the fuel quantity and turning off the fuel dump switch(es).
*b. dump limit valves or a low-level circuit.
c. standpipes in the fuel tanks.

8. (8705) Which procedure must be followed when defueling aircraft with sweptback wings?
~ Unless the service manual specifies otherwise, the outboard fuel tanks on an aircraft with swept back wings should be defueled first. This procedure minimizes the twisting effect on the wing caused by the fuel being located behind the wing attachment points on the fuselage.
@ Unless the service manual specifies otherwise, the outboard fuel tanks on an aircraft with swept back wings should be defueled first. This procedure minimizes the twisting effect on the wing caused by the fuel being located behind the wing attachment points on the fuselage.
a. Defuel all the tanks at one time.
b. Defuel the inboard wing tanks first.
*c. Defuel the outboard wing tanks first.

9. (8706) (Refer to Figure 17.) What is the purpose of the pump crossfeed valve?
~ The pump cross-feed valve shown here allows both engines to operate from either of the two tanks.
@ The pump cross-feed valve shown here allows both engines to operate from either of the two tanks.
a. Balance the fuel in the tanks.
*b. Allow operation of engines from one tank.
c. Allow operation of the left engine when the right fuel-boost pump is inoperative.

10. (8707.1) Normal fuel crossfeed system operation in multiengine aircraft
~ Multiengine aircraft normally have fuel tanks located in widely separated parts of the aircraft. A crossfeed fuel system allows fuel to be used from any tank by any of the engines. This allows a balanced fuel load to be maintained.
@ Multiengine aircraft normally have fuel tanks located in widely separated parts of the aircraft. A crossfeed fuel system allows fuel to be used from any tank by any of the engines. This allows a balanced fuel load to be maintained.
a. calls for jettisoning of fuel overboard to correct lateral instability.
b. reduces contamination and/or fire hazards during fueling or defueling operations.
*c. provides a means to maintain a balanced fuel load condition.

11. (8708) What is the primary purpose of the crossfeed system?
~ A cross-feed system allows any engine on a multiengine aircraft to be fed from any tank. This can be used to maintain a balanced fuel load.
@ A cross-feed system allows any engine on a multiengine aircraft to be fed from any tank. This can be used to maintain a balanced fuel load.
*a. To allow the feeding of any engine from any tank.
b. To allow the feeding of fuel from one tank for defueling.
c. To provide automatic refueling of a tank to any desired level.

12. (8709.1) Fuel system components must be bonded and grounded in order to
~ Aircraft fuel-system components must be bonded to the aircraft structure and must be grounded in order to prevent a buildup of static electricity. Static electricity could cause a spark and a fire.
@ Aircraft fuel-system components must be bonded to the aircraft structure and must be grounded in order to prevent a buildup of static electricity. Static electricity could cause a spark and a fire.
*a. drain off static charges.
b. prevent stray currents.
c. retard galvanic corrosion.

13. (8710.1) A typical large transport aircraft fuel manifold system allows how many of the following?
1. All tanks can be serviced through a single connection.
2. Any engine can be fed from any tank.
3. All engines can be fed from all tanks simultaneously.
4. A damaged tank can be isolated from the rest of the fuel system.
~ In a large aircraft manifold fuel system, all tanks can be serviced through a single connection, any engine can be fed from any tank, all engines can be fed from all tanks simultaneously, and a damaged tank can be isolated from the rest of the fuel system.
@ In a large aircraft manifold fuel system, all tanks can be serviced through a single connection, any engine can be fed from any tank, all engines can be fed from all tanks simultaneously, and a damaged tank can be isolated from the rest of the fuel system.
a. 1 and 2.
b. 1, 2, and 3.
*c. 1, 2, 3, and 4.

14. (8711) The use of turbine fuels in aircraft has resulted in some problems not normally associated with aviation gasolines. One of these problems is
~ Microbial contamination is a fuel system problem that is associated with the higher viscosity fuel used in turbine engine aircraft. Turbine engine fuel holds water more readily than gasoline. Microorganisms live in this water and form a scum which clogs the fuel filters, lines, and fuel controls. The scum holds water against the fuel tank structure and causes tank corrosion.
@ Microbial contamination is a fuel system problem that is associated with the higher viscosity fuel used in turbine engine aircraft. Turbine engine fuel holds water more readily than gasoline. Microorganisms live in this water and form a scum which clogs the fuel filters, lines, and fuel controls. The scum holds water against the fuel tank structure and causes tank corrosion.
a. increasing viscosity of fuel as fuel temperature lowers at altitude.
b. higher vapor pressure.
*c. microbial contaminants.

15. (8712) What is used in many aircraft to prevent bubbles in the fuel after it leaves the tank when atmospheric pressure is lower than fuel vapor pressure?
~ Boost pumps installed in many aircraft fuel tanks have an agitator on their shaft along with the impeller. The agitator causes bubbles in the fuel to be released into the tank before the fuel is forced into the fuel lines. The boost pumps hold a pressure on the fuel in the lines to prevent additional vapors from forming.
@ Boost pumps installed in many aircraft fuel tanks have an agitator on their shaft along with the impeller. The agitator causes bubbles in the fuel to be released into the tank before the fuel is forced into the fuel lines. The boost pumps hold a pressure on the fuel in the lines to prevent additional vapors from forming.
a. Air-fuel separators.
b. Anti-foaming additives.
*c. Boost pumps.

16. (8713) Which of the following precautions is most important during refueling operations?
~ It is extremely important when fueling an aircraft that the fuel be properly identified. The use of fuel with a lower than allowed octane or performance rating can cause detonation which can destroy an engine. A number of airplanes have been destroyed by the inadvertent fueling of a reciprocating engine aircraft with turbine-engine fuel. Turbine-engine fuel will cause severe detonation when a reciprocating engine is operated at takeoff power.
@ It is extremely important when fueling an aircraft that the fuel be properly identified. The use of fuel with a lower than allowed octane or performance rating can cause detonation which can destroy an engine. A number of airplanes have been destroyed by the inadvertent fueling of a reciprocating engine aircraft with turbine-engine fuel. Turbine-engine fuel will cause severe detonation when a reciprocating engine is operated at takeoff power.
a. All outside electrical sources must be disconnected from the aircraft.
*b. Fuel to be used must be appropriately identified.
c. All electrical switches must be in OFF position.

17. (8714) Before fueling an aircraft by using the pressure fueling method, what important precaution should be observed?
~ Before fueling an aircraft, it is important that the fuel-truck pump pressure be correct for the refueling system. Some systems, such as that used on the Boeing 727, require a maximum fuel delivery pressure of 50 psi. The delivery pressure varies with the different aircraft.
@ Before fueling an aircraft, it is important that the fuel-truck pump pressure be correct for the refueling system. Some systems, such as that used on the Boeing 727, require a maximum fuel delivery pressure of 50 psi. The delivery pressure varies with the different aircraft.
*a. The truck pump pressure must be correct for that refueling system.
b. The truck pump pressure must be adjusted for minimum filter pressure.
c. The aircraft's electrical system must be on to indicate quantity gauge readings.

18. (8715) What flight safety-related advantage does a pressure fueling system provide?
~ Pressure fueling of an aircraft reduces the chances of fuel contamination, as well as reducing the danger of static electricity igniting fuel vapors.
@ Pressure fueling of an aircraft reduces the chances of fuel contamination, as well as reducing the danger of static electricity igniting fuel vapors.
a. Keeps the aircraft within weight and balance limitations.
*b. Reduces the chances for fuel contamination.
c. Reduces the time required for fueling.

19. (8716) Aircraft pressure fueling systems instructional procedures are normally placarded on the
~ Pressure-fueling instructional procedures are normally placarded on the fuel control panel access door. No one should fuel an aircraft with a fuel pressure fueling system unless he or she has been thoroughly checked out on the procedure.
@ Pressure-fueling instructional procedures are normally placarded on the fuel control panel access door. No one should fuel an aircraft with a fuel pressure fueling system unless he or she has been thoroughly checked out on the procedure.
*a. fuel control panel access door.
b. lower wing surface adjacent to the access door.
c. aircraft ground connection point.

20. (8717) Pressure fueling of aircraft is usually accomplished through
~ A manifold fuel system allows an aircraft to be fueled by the pressure fueling method. All of the tanks can be fueled at the same time through a single manifold connection. This reduces the fueling time, minimizes the chance of contamination, and minimizes the buildup of static electrical charges.
@ A manifold fuel system allows an aircraft to be fueled by the pressure fueling method. All of the tanks can be fueled at the same time through a single manifold connection. This reduces the fueling time, minimizes the chance of contamination, and minimizes the buildup of static electrical charges.
a. pressure connections on individual fuel tanks.
*b. at least one single point connection.
c. individual fuel tank overwing and/or fuselage access points.

21. (8718) Which of the following may be used for the repair of fuel leaks on most integral fuel tanks?
~ Since an integral fuel tank is a part of the aircraft structure, it is repaired by riveting, and resealing the repaired area.
@ Since an integral fuel tank is a part of the aircraft structure, it is repaired by riveting, and resealing the repaired area.
a. Welding and resealing.
b. Brazing and resealing.
*c. Riveting and resealing.

22. (8719) How is the outlet fuel pressure regulated on a submerged, single-speed, centrifugal-type fuel pump?
~ The outlet fuel pressure produced by a submerged, single-speed, centrifugal-type fuel pump is determined by the pump's design and its internal clearances and characteristics.
@ The outlet fuel pressure produced by a submerged, single-speed, centrifugal-type fuel pump is determined by the pump's design and its internal clearances and characteristics.
a. By the engine-driven pump's design and internal clearance.
b. By the first check valve downstream from the pump.
*c. By the pump's design and internal clearances.

23. (8720) What is one purpose of a fuel tank vent?
~ A fuel-tank vent maintains atmospheric pressure on top of the fuel in the tank to provide for proper fuel flow from the tank to the engine.
@ A fuel-tank vent maintains atmospheric pressure on top of the fuel in the tank to provide for proper fuel flow from the tank to the engine.
*a. To maintain atmospheric pressure.
b. To decrease fuel vapor pressure.
c. To decrease tank internal air pressure.

24. (8721) When inspecting a removable rigid fuel tank for leaks, what procedure should be followed?
~ After a removable rigid fuel tank has been repaired, it should be pressurized with no more than 1/2-psi air pressure, and all seams and the repaired area should be inspected by brushing on liquid soap or a soap bubble solution to check for any indication of leaks.
@ After a removable rigid fuel tank has been repaired, it should be pressurized with no more than 1/2-psi air pressure, and all seams and the repaired area should be inspected by brushing on liquid soap or a soap bubble solution to check for any indication of leaks.
*a. pressurize the tank with air and brush with soapy water.
b. fill the tank with water and pressurize with air and brush with soapy water.
c. pressurize the tank with air and submerge in water to locate leaks.

25. (8722) If it is necessary to enter an aircraft's fuel tank, which procedure should be avoided?
~ You are asked which procedure should be avoided. All defueling and purging must be done outside, not in any building, air-conditioned or otherwise.
@ You are asked which procedure should be avoided. All defueling and purging must be done outside, not in any building, air-conditioned or otherwise.
a. Continue purging the tank during the entire work period.
b. Station an assistant outside the fuel tank access to perform rescue operations if required.
*c. Conduct the defueling and tank purging operation in an air-conditioned building.

26. (8723) What is the recommended practice for cleaning a fuel tank before welding?
~ Before a gasoline tank is welded, it should be washed out with hot water and a detergent. Then, live steam should be passed through the tank for about a half hour. This treatment vaporizes and removes any residual fuel that may be left in the tank.
@ Before a gasoline tank is welded, it should be washed out with hot water and a detergent. Then, live steam should be passed through the tank for about a half hour. This treatment vaporizes and removes any residual fuel that may be left in the tank.
a. Purge the tank with air.
b. Flush the inside of the tank with clean water.
*c. Steam clean the tank interior.

27. (8724) An aircraft's integral fuel tank is
~ An aircraft integral fuel tank is actually a portion of the aircraft structure that is sealed off and is used as a fuel tank.
@ An aircraft integral fuel tank is actually a portion of the aircraft structure that is sealed off and is used as a fuel tank.
a. usually located in the bottom of the fuselage.
*b. a part of the aircraft structure.
c. a self-sealing tank.

28. (8725) Which gas is used for purging an aircraft fuel tank?
~ Carbon dioxide can be used to purge an aircraft fuel tank of fuel vapors.
@ Carbon dioxide can be used to purge an aircraft fuel tank of fuel vapors.
a. Helium or argon.
*b. Carbon dioxide.
c. Carbon monoxide.

29. (8726) Why is the main fuel strainer located at the lowest point in the fuel system?
~ One reason for having the main fuel strainer of an aircraft located at the lowest point in the fuel system is so it will trap and hold any small amount of water that is in the fuel system.
@ One reason for having the main fuel strainer of an aircraft located at the lowest point in the fuel system is so it will trap and hold any small amount of water that is in the fuel system.
*a. It traps any small amount of water that may be present in the fuel system.
b. It provides a drain for residual fuel.
c. It filters and traps all micro-organisms that may be present in the fuel system.

30. (8727) The purpose of a diaphragm in a vane-type fuel pump is to
~ The diaphragm in a compensated vane-type fuel pump is used to compensate the fuel pressure for altitude changes. It maintains the fuel pressure a constant amount above the pressure of the ambient air.
@ The diaphragm in a compensated vane-type fuel pump is used to compensate the fuel pressure for altitude changes. It maintains the fuel pressure a constant amount above the pressure of the ambient air.
a. equalize fuel pressure at all speeds.
b. vary fuel pressure according to throttle setting.
*c. compensate fuel pressures to altitude changes.

31. (8728) When moving the mixture control on a normally operating engine into the idle cutoff position, engine RPM should
~ An engine normally uses an idling fuel-air mixture richer than that which produces the most efficient burning. When the mixture control is moved into the IDLE CUTOFF position, the mixture passes through the ratio that produces the best burning. The RPM picks up a few RPMs before it drops off completely.
@ An engine normally uses an idling fuel-air mixture richer than that which produces the most efficient burning. When the mixture control is moved into the IDLE CUTOFF position, the mixture passes through the ratio that produces the best burning. The RPM picks up a few RPMs before it drops off completely.
*a. slightly increase before the engine starts to die.
b. slightly decrease and then drop rapidly.
c. remain the same until the cutoff is effected, then drop rapidly.

32. (8729) Entrained water in aviation turbine fuel is a hazard because of its susceptibility to freezing as it passes through the filters. What are common methods of preventing this hazard?
~ Turbine engine fuel may have moisture entrained in it that will condense out and freeze on the fuel filters. This ice will shut off the flow of fuel to the engines. To eliminate this danger, anti-icing additives may be put in the turbine fuel to lower the freezing temperature of the water and prevent its freezing on the filters. Most jet transport aircraft have fuel heaters, or heat exchangers, that use engine compressor bleed air or engine oil to raise the temperature of the fuel enough that it will not freeze on the filters.
@ Turbine engine fuel may have moisture entrained in it that will condense out and freeze on the fuel filters. This ice will shut off the flow of fuel to the engines. To eliminate this danger, anti-icing additives may be put in the turbine fuel to lower the freezing temperature of the water and prevent its freezing on the filters. Most jet transport aircraft have fuel heaters, or heat exchangers, that use engine compressor bleed air or engine oil to raise the temperature of the fuel enough that it will not freeze on the filters.
a. Micromesh fuel strainers and fuel heater.
b. High-velocity fuel pumps and fuel heater.
*c. Anti-icing fuel additives and fuel heater.

33. (8730) As a general rule, which statement is true regarding fuel leaks?
~ Any fuel leaking from an aircraft fuel tank can constitute a safety of flight situation under certain conditions. A stain, seep, or even a heavy seep is not considered to be a flight hazard unless it is in an unvented area where the fumes can collect and cause a fire hazard. Any type of leak that allows fuel vapors to accumulate must be repaired before the aircraft can be released for flight.
@ Any fuel leaking from an aircraft fuel tank can constitute a safety of flight situation under certain conditions. A stain, seep, or even a heavy seep is not considered to be a flight hazard unless it is in an unvented area where the fumes can collect and cause a fire hazard. Any type of leak that allows fuel vapors to accumulate must be repaired before the aircraft can be released for flight.
a. Stains, seeps, and heavy seeps are not flight hazards.
b. All fuel leaks regardless of location or severity are considered a hazard to flight.
*c. Stains, seeps, and heavy seeps, (in addition to running leaks) are considered flight hazards when located in unvented areas of the aircraft.

34. (8731) The presence of fuel stains around a fuel nozzle would indicate
~ A clogged fuel-injection nozzle will allow the fuel to escape through the air bleed holes in the side of the nozzle. There will be fuel stains on the cylinder head around the clogged nozzle.
@ A clogged fuel-injection nozzle will allow the fuel to escape through the air bleed holes in the side of the nozzle. There will be fuel stains on the cylinder head around the clogged nozzle.
a. too much fuel pressure.
b. excessive airflow across the venturi.
*c. clogged fuel nozzle.

35. (8732) What should be used to inert an integral fuel tank before attempting repairs?
~ Before working inside an integral fuel tank, you should inert it (replace the gasoline fumes with an inert gas). Integral fuel tanks can be inerted by filling them with carbon dioxide (CO(2)).
@ Before working inside an integral fuel tank, you should inert it (replace the gasoline fumes with an inert gas). Integral fuel tanks can be inerted by filling them with carbon dioxide (CO(2)).
*a. CO(2).
b. Water.
c. Steam.

36. (8733) What should be used to remove flux from an aluminum tank after welded repairs?
~ Promptly, upon completion of welding, wash the inside and outside of the tank with liberal quantities of hot water and then drain. Next, immerse the tank in either a 5% nitric-acid or 5% sulfuric-acid solution.
@ Promptly, upon completion of welding, wash the inside and outside of the tank with liberal quantities of hot water and then drain. Next, immerse the tank in either a 5% nitric-acid or 5% sulfuric-acid solution.
a. Soft brush and warm water.
*b. 5 percent solution of nitric or sulfuric acid.
c. Mild solution of soap and warm water.

37. (8734) What method would be used to check for internal leakage of a fuel valve without removing the valve from the aircraft?
~ Internal leakage in a fuel valve can be checked by placing the valve in the OFF position and then draining the fuel strainer bowl. Turn the fuel-tank boost pump on. If fuel flows into the empty strainer bowl, the valve has an internal leak.
@ Internal leakage in a fuel valve can be checked by placing the valve in the OFF position and then draining the fuel strainer bowl. Turn the fuel-tank boost pump on. If fuel flows into the empty strainer bowl, the valve has an internal leak.
*a. Place the valve in the OFF position, drain the strainer bowl, and with boost pump on, watch to see if fuel flows to the strainer bowl.
b. Remove fuel cap(s), turn boost pump(s) on, and watch for bubbling in the tanks.
c. Apply regulated air pressure on the downstream side of the fuel pump and listen for air passing through the valve.

38. (8735) Why are jet fuels more susceptible to water contamination than aviation gasoline?
~ Jet fuels have a higher viscosity than aviation gasoline. Because of this higher viscosity, contaminants such as water remain suspended in the fuel and do not settle out into the fuel tank sumps.
@ Jet fuels have a higher viscosity than aviation gasoline. Because of this higher viscosity, contaminants such as water remain suspended in the fuel and do not settle out into the fuel tank sumps.
*a. Jet fuel has a higher viscosity than gasoline.
b. Jet fuel is lighter than gasoline; therefore, water is more easily suspended.
c. Condensation is greater because of the higher volatility of jet fuels.

39. (8736) When installing a rigid fuel line, 1/2 inch in diameter, at what intervals should the line be supported?
~ Rigid fuel lines installed in an aircraft should be supported by clamps or brackets at the distances specified in AC 43.13-1B. For a 1/2-inch line, the supports should be installed every 16 inches along the run of the line.
@ Rigid fuel lines installed in an aircraft should be supported by clamps or brackets at the distances specified in AC 43.13-1B. For a 1/2-inch line, the supports should be installed every 16 inches along the run of the line.
a. 24 inches.
b. 12 inches.
*c. 16 inches.

40. (8737) The probe of a capacitance-type fuel level gauge is essentially a
~ A capacitance-type, fuel-quantity-indicating system uses a capacitor (condenser) as a tank probe. Fuel and air are the dielectric between the plates of the probe.
@ A capacitance-type, fuel-quantity-indicating system uses a capacitor (condenser) as a tank probe. Fuel and air are the dielectric between the plates of the probe.
a. float-actuated variable capacitor.
b. capacitor with fuel and air acting as one plate.
*c. capacitor with fuel and air acting as a dielectric.

41. (8738) Which statement concerning an electronic capacitance-type fuel quantity indicating system is true?
~ The capacitance-type, fuel-quantity-indicating system uses probes with no moving parts inside the tank. These probes are made of two concentric tubes that serve as the plates of a capacitor. Fuel and air act as the dielectric.
@ The capacitance-type, fuel-quantity-indicating system uses probes with no moving parts inside the tank. These probes are made of two concentric tubes that serve as the plates of a capacitor. Fuel and air act as the dielectric.
*a. It has no moving parts in the tank.
b. It has two tubes separated by an electronic field in the tank.
c. It utilizes a variable capacitor to indicate the fuel tank capacity.

42. (8739) What type of remote-reading fuel quantity indicating system has several probes installed in each fuel tank?
~ The electronic (capacitance-type), remote-reading, fuel-quantity-indicating system has several probes installed in each fuel tank. The total capacity of the probes accurately relates to the amount of fuel in the tank.
@ The electronic (capacitance-type), remote-reading, fuel-quantity-indicating system has several probes installed in each fuel tank. The total capacity of the probes accurately relates to the amount of fuel in the tank.
a. Electromechanical.
*b. Electronic.
c. Direct reading.

43. (8740) Which aircraft fuel quantity indicating system incorporates a signal amplifier?
~ An electronic (capacitance-type) fuel-quantity-indicating system incorporates a signal amplifier.
@ An electronic (capacitance-type) fuel-quantity-indicating system incorporates a signal amplifier.
*a. Electronic.
b. Sight glass.
c. Electrical.

44. (8741) A drip gauge may be used to measure
~ A drip gauge is used to measure the quantity of fuel in a fuel tank when the aircraft is on the ground. The drip gauge is pulled down from the bottom of the tank until fuel begins to drip from its end. The quantity of fuel in the tank is indicated on the gauge by the amount the gauge is pulled from the tank before it begins to drip.
@ A drip gauge is used to measure the quantity of fuel in a fuel tank when the aircraft is on the ground. The drip gauge is pulled down from the bottom of the tank until fuel begins to drip from its end. The quantity of fuel in the tank is indicated on the gauge by the amount the gauge is pulled from the tank before it begins to drip.
*a. the amount of fuel in the tank.
b. system leakage with the system shut down.
c. fuel pump diaphragm leakage.

45. (8742) The electronic-type fuel quantity indicating system consists of a bridge circuit,
~ An electronic (capacitance-type), fuel-quantity-indicating system contains the following parts: Capacitor probes, mounted in the tanks. A bridge circuit to measure the capacity of the probes. An amplifier to increase the amplitude of the signal from the bridge circuit to a value high enough to drive the indicator. An indicator mounted in the instrument panel to show the amount of fuel in the tanks.
@ An electronic (capacitance-type), fuel-quantity-indicating system contains the following parts: Capacitor probes, mounted in the tanks. A bridge circuit to measure the capacity of the probes. An amplifier to increase the amplitude of the signal from the bridge circuit to a value high enough to drive the indicator. An indicator mounted in the instrument panel to show the amount of fuel in the tanks.
*a. an amplifier, an indicator, and a tank unit.
b. a tank, an amplifier, and an indicator.
c. a tank unit, a tank, and an amplifier.

46. (8743) A probe or a series of probes is used in what kind of fuel quantity indicating system?
~ Probes, which are capacitors, are used as the fuel-quantity-sensing elements in a capacitor-type, fuel-quantity-indicating system.
@ Probes, which are capacitors, are used as the fuel-quantity-sensing elements in a capacitor-type, fuel-quantity-indicating system.
a. Selsyn.
*b. Capacitor.
c. Synchro.

47. (8744) Why is the capacitance fluid quantity indicating system more accurate in measuring fuel level than a mechanical type?
~ The electronic (capacitor-type), fuel-quantity-indicating system is more accurate than other types of systems used for measuring fuel quantity. These systems use several capacitor-type probes extending across each tank from top to bottom. When the attitude of the aircraft changes, fuel rises in some probes and lowers in others. The total capacitance of all probes remains constant as the aircraft attitude changes. This causes the fuel-level indication to remain constant as attitude changes. The dielectric constant of the fuel changes with its density. Therefore, the system is able to determine the mass (weight) of the fuel rather than its volume.
@ The electronic (capacitor-type), fuel-quantity-indicating system is more accurate than other types of systems used for measuring fuel quantity. These systems use several capacitor-type probes extending across each tank from top to bottom. When the attitude of the aircraft changes, fuel rises in some probes and lowers in others. The total capacitance of all probes remains constant as the aircraft attitude changes. This causes the fuel-level indication to remain constant as attitude changes. The dielectric constant of the fuel changes with its density. Therefore, the system is able to determine the mass (weight) of the fuel rather than its volume.
a. Only one probe and one indicator are necessary for multiple tank configurations.
b. It measures in gallons and converts to pounds.
*c. It measures by weight instead of volume.

48. (8745) One advantage of electrical and electronic fuel quantity indicating systems is that
~ Two important advantages of the electronic and electrical fuel-quantity-indicating systems are that the indicator can be located any distance from the tanks and the fuel levels of several tanks can be read on one indicator.
@ Two important advantages of the electronic and electrical fuel-quantity-indicating systems are that the indicator can be located any distance from the tanks and the fuel levels of several tanks can be read on one indicator.
a. the indicators are calibrated in gallons; therefore, no conversion is necessary.
b. only one transmitter and one indicator are needed regardless of the number of tanks.
*c. several fuel tank levels can be read on one indicator.

49. (8746.1) A fuel totalizer is a component which indicates the
~ A fuel totalizer is a single instrument that gives an indication of the total quantity of the fuel remaining on board the aircraft. The totalizer adds the quantities of the fuel in all of the tanks.
@ A fuel totalizer is a single instrument that gives an indication of the total quantity of the fuel remaining on board the aircraft. The totalizer adds the quantities of the fuel in all of the tanks.
a. total amount of fuel being consumed by all engines.
b. amount of fuel in any given tank.
*c. amount of fuel in all tanks.

50. (8747) What is the dielectric (nonconducting material) in a capacitance-type fuel quantity indicating system?
~ The dielectric used in the tank probes of a capacitor-type, fuel-quantity-indicating system is the fuel and the air in the tank above the fuel. Fuel has a dielectric constant of approximately two. Air has a dielectric constant of one.
@ The dielectric used in the tank probes of a capacitor-type, fuel-quantity-indicating system is the fuel and the air in the tank above the fuel. Fuel has a dielectric constant of approximately two. Air has a dielectric constant of one.
a. Outer shell of the capacitor.
b. Fuel in the tank.
*c. Fuel and air in the tank.

51. (8748) A capacitance-type fuel quantity indicating system measures fuel in
~ A capacitance-type, fuel-quantity-indicating system measures the density of the fuel (the dielectric constant of the fuel changes with its density). It indicates the quantity of fuel in pounds rather than in gallons.
@ A capacitance-type, fuel-quantity-indicating system measures the density of the fuel (the dielectric constant of the fuel changes with its density). It indicates the quantity of fuel in pounds rather than in gallons.
*a. pounds.
b. pounds per hour.
c. gallons.

52. (8749) What are the four general types of fuel quantity gauges?
1. Sight glass.
2. Mechanical.
3. Electrical.
4. Electronic.
5. Bourdon tube.
6. Vane-type transmitter.
7. Litmus indicator.
8. Direct-reading static pressure type.
~ The types of fuel-quantity-indicating systems used in aircraft are sight glasses, mechanical systems, electrical systems, and electronic systems.
@ The types of fuel-quantity-indicating systems used in aircraft are sight glasses, mechanical systems, electrical systems, and electronic systems.
*a. 1, 2, 3, 4.
b. 1, 3, 6, 8.
c. 2, 3, 5, 7.

53. (8750) How does temperature affect fuel weight?
~ The density of aircraft fuel varies with its temperature. The colder the fuel, the more pounds of fuel there are in a gallon. Aircraft engines use fuel on the basis of its weight rather than its volume.
@ The density of aircraft fuel varies with its temperature. The colder the fuel, the more pounds of fuel there are in a gallon. Aircraft engines use fuel on the basis of its weight rather than its volume.
*a. Cold fuel is heavier per gallon.
b. Warm fuel is heavier per gallon.
c. Temperature has no effect.

54. (8751) One advantage of electrical and electronic fuel quantity indicating systems is that the indicator
~ Most modern aircraft use electrical or electronic fuel-quantity-indicating systems because of the ease with which the indicator can be located a distance from the fuel tanks.
@ Most modern aircraft use electrical or electronic fuel-quantity-indicating systems because of the ease with which the indicator can be located a distance from the fuel tanks.
*a. can be located any distance from the tank(s).
b. has no movable devices.
c. always measures volume instead of mass.

55. (8752) When fuel quantity is measured in pounds instead of gallons, the measurement will be more accurate because fuel volume
~ An indication of the weight of the fuel in an aircraft fuel tank is more important than a measure of its volume. The engine uses the fuel on the basis of its weight, and the volume of the fuel in the tanks changes as the temperature of the fuel changes.
@ An indication of the weight of the fuel in an aircraft fuel tank is more important than a measure of its volume. The engine uses the fuel on the basis of its weight, and the volume of the fuel in the tanks changes as the temperature of the fuel changes.
*a. varies with temperature change.
b. increases when temperature decreases.
c. varies with changes in atmospheric pressure.

56. (8753) An electrical-type fuel quantity indicating system consists of an indicator in the cockpit and a
~ An electrical fuel-quantity-indicating system uses a float-operated transmitter in the fuel tank to furnish information to the indicator on the instrument panel. The transmitter is normally a float-operated variable resistor.
@ An electrical fuel-quantity-indicating system uses a float-operated transmitter in the fuel tank to furnish information to the indicator on the instrument panel. The transmitter is normally a float-operated variable resistor.
*a. float-operated transmitter installed in the tank.
b. float resting on the surface of the tank.
c. float-operated receiver installed in the tank.

57. (8754) What is the purpose of a float-operated transmitter installed in a fuel tank?
~ A float-operated, fuel-quantity transmitter is normally a variable resistor whose resistance changes with the fuel level in the tank. Information on the fuel level is sent as an electrical signal to the fuel-quantity indicator on the instrument panel.
@ A float-operated, fuel-quantity transmitter is normally a variable resistor whose resistance changes with the fuel level in the tank. Information on the fuel level is sent as an electrical signal to the fuel-quantity indicator on the instrument panel.
*a. It sends an electric signal to the fuel quantity indicator.
b. It senses the total amount of fuel density.
c. It senses the dielectric qualities of fuel and air in the tank.

58. (8755) In an electronic-type fuel quantity indicating system, the tank sensing unit is a
~ The fuel-tank transmitters in an electronic-type fuel quantity indicating system are capacitors. A tank probe (transmitter) is made of two concentric metal tubes that act as the plates of a capacitor. The fuel in the tank and the air above the fuel act as the dielectric. The capacitance of the probe is determined by the relative amount of fuel and air between the plates.
@ The fuel-tank transmitters in an electronic-type fuel quantity indicating system are capacitors. A tank probe (transmitter) is made of two concentric metal tubes that act as the plates of a capacitor. The fuel in the tank and the air above the fuel act as the dielectric. The capacitance of the probe is determined by the relative amount of fuel and air between the plates.
*a. capacitor.
b. variable resistor.
c. variable inductor.

59. (8756) What must each fuel quantity indicator be calibrated to read during level flight when the quantity of fuel remaining is equal to the unusable fuel supply?
~ Each fuel quantity indicator must be calibrated to read 'zero' during level flight when the quantity of the fuel remaining in the tank is equal to the unusable fuel supply.
@ Each fuel quantity indicator must be calibrated to read 'zero' during level flight when the quantity of the fuel remaining in the tank is equal to the unusable fuel supply.
a. The total unusable fuel quantity.
b. Both the total unusable fuel quantity and the unusable fuel quantity in each tank.
*c. Zero.

60. (8757) What unit would be adjusted to change the fuel pressure warning limits?
~ The contacts on the pressure-sensitive mechanism would be adjusted to change the pressure at which the fuel-pressure-warning unit actuates.
@ The contacts on the pressure-sensitive mechanism would be adjusted to change the pressure at which the fuel-pressure-warning unit actuates.
a. Fuel flowmeter bypass valve.
*b. Pressure-sensitive mechanism.
c. Fuel pressure relief valve.

61. (8758) Select one means of controlling the fuel temperature on turbine-powered aircraft.
~ Ice is prevented from clogging the filter of a turbine-powered aircraft fuel system by routing warm compressor bleed air through an air-to-fuel heat exchanger. All of the fuel that flows to the engine must pass through this heat exchanger.
@ Ice is prevented from clogging the filter of a turbine-powered aircraft fuel system by routing warm compressor bleed air through an air-to-fuel heat exchanger. All of the fuel that flows to the engine must pass through this heat exchanger.
a. Engine bleed air to the fuel filter.
b. Engine bleed air to the fuel tank.
*c. Engine bleed air to a heat exchanger.

62. (8759) What is the purpose of flapper-type check valves in integral fuel tanks?
~ Some integral fuel tanks have flapper-type check valves that allow fuel to flow to the booster pump, but prevent rough air or abrupt flight maneuvers from causing the fuel to flow away from the booster pump. Some aircraft also have a pump-removal, flapper-type check valve that allows a booster pump to be removed from the tank without having to first drain the tank.
@ Some integral fuel tanks have flapper-type check valves that allow fuel to flow to the booster pump, but prevent rough air or abrupt flight maneuvers from causing the fuel to flow away from the booster pump. Some aircraft also have a pump-removal, flapper-type check valve that allows a booster pump to be removed from the tank without having to first drain the tank.
a. To allow defueling of the tanks by suction.
*b. To prevent fuel from flowing away from the boost pumps.
c. To allow the engine-driven pumps to draw fuel directly from the tank if the boost pump fails.

63. (8760) What unit is generally used to actuate the fuel pressure warning system?
~ A pressure-sensitive mechanism (generally a bellows) is used to actuate the fuel-pressure-warning system.
@ A pressure-sensitive mechanism (generally a bellows) is used to actuate the fuel-pressure-warning system.
a. Fuel flowmeter.
*b. Pressure-sensitive mechanism.
c. Fuel pressure gauge.

64. (8761) What method is used on turbine-powered aircraft to determine when the condition of the fuel is approaching the danger of forming ice crystals?
~ Fuel-temperature-indicating systems are required in turbine aircraft to warn when there is danger of ice crystals forming in the fuel. A fuel-strainer differential pressure gauge gives an indication that ice crystals have already formed and are restricting the fuel filter. Ice crystals on the filter element cause an excessive pressure drop across the filter.
@ Fuel-temperature-indicating systems are required in turbine aircraft to warn when there is danger of ice crystals forming in the fuel. A fuel-strainer differential pressure gauge gives an indication that ice crystals have already formed and are restricting the fuel filter. Ice crystals on the filter element cause an excessive pressure drop across the filter.
a. Fuel pressure warning.
b. Fuel pressure gauge.
*c. Fuel temperature indicator.

65. (8762) Which of the following would give the first positive indication that a change-over from one fuel tank to another is needed?
~ The fuel-pressure-warning system should give the first indication, by a loss of pressure, that a fuel tank is empty. This drop in pressure warns the pilot to switch to a full tank.
@ The fuel-pressure-warning system should give the first indication, by a loss of pressure, that a fuel tank is empty. This drop in pressure warns the pilot to switch to a full tank.
*a. Fuel pressure warning.
b. Fuel pressure gauge.
c. Fuel quantity indicator.

66. (8763) A fuel pressure warning switch contacts close and warning light is turned on when
~ The fuel-pressure-warning-switch contacts close and a warning light turns on when the fuel pressure drops below a specified limit.
@ The fuel-pressure-warning-switch contacts close and a warning light turns on when the fuel pressure drops below a specified limit.
a. a measured quantity of fuel has passed through it.
b. the fuel flow stops.
*c. the fuel pressure drops below specified limits.

67. (8764) A transmitter in a fuel pressure warning system serves what function?
~ The transmitter in a fuel-pressure-warning system converts the pressure of the fuel into an electrical signal that turns on a warning light or flashes a warning on an annunciator panel.
@ The transmitter in a fuel-pressure-warning system converts the pressure of the fuel into an electrical signal that turns on a warning light or flashes a warning on an annunciator panel.
a. Transmits an electrical signal to fluid pressure.
*b. Converts fluid pressure to an electrical signal.
c. Transmits fluid pressure directly to the indicator.

68. (8765) Where is fuel pressure taken for the pressure warning signal on most aircraft engines?
~ The fuel-pressure-warning signal used with most aircraft engines is taken from the fuel-pressure line that goes to the fuel inlet of the carburetor.
@ The fuel-pressure-warning signal used with most aircraft engines is taken from the fuel-pressure line that goes to the fuel inlet of the carburetor.
a. Outlet side of the boost pump.
*b. Fuel pressure line of the carburetor.
c. Between the fuel pump and the strainer.

69. (8766) Which of the following is necessary to effectively troubleshoot a fuel pressure warning system?
~ The manufacturer's maintenance manuals give all the information needed to effectively troubleshoot a fuel-pressure-warning system.
@ The manufacturer's maintenance manuals give all the information needed to effectively troubleshoot a fuel-pressure-warning system.
*a. The manufacturer's maintenance manuals.
b. AC 43.13-1B, Acceptable Methods, Techniques, and Practices -- Aircraft Inspection and Repair.
c. A set of Federal Aviation Regulations.

70. (8767) Which of the following would be most useful to locate and troubleshoot an internal fuel leak in an aircraft fuel system?
~ A schematic diagram of the fuel system furnishes the most useful information to help in locating and troubleshooting an internal fuel leak in an aircraft fuel system.
@ A schematic diagram of the fuel system furnishes the most useful information to help in locating and troubleshooting an internal fuel leak in an aircraft fuel system.
a. Aircraft structure repair manual.
b. Illustrated parts manual.
*c. A fuel system schematic.

71. (8768) In some aircraft with several fuel tanks, the possible danger of allowing the fuel supply in one tank to become exhausted before the selector valve is switched to another tank is prevented by the installation of
~ Fuel-pressure-warning-signal systems are installed in many large aircraft to warn the pilot or flight engineer that a tank has been emptied and a full tank should be selected.
@ Fuel-pressure-warning-signal systems are installed in many large aircraft to warn the pilot or flight engineer that a tank has been emptied and a full tank should be selected.
*a. a fuel pressure warning signal system.
b. a fuel pressure relief valve.
c. an engine fuel pump bypass valve.

72. (8769) (1) The function of a fuel heater is to protect the engine fuel system from ice formation.
(2) An aircraft fuel heater cannot be used to thaw ice in the fuel screen.
Regarding the above statements,
~ Statement (1) is true. The function of a fuel heater is to protect the engine-fuel system from ice formation. Statement (2) is not true. A fuel heater can be used to thaw ice that has formed on the fuel screen.
@ Statement (1) is true. The function of a fuel heater is to protect the engine-fuel system from ice formation. Statement (2) is not true. A fuel heater can be used to thaw ice that has formed on the fuel screen.
*a. only No. 1 is true.
b. only No. 2 is true.
c. both No. 1 and No. 2 are true.

73. (8770) (1) Gas-turbine-engine fuel systems are very susceptible to the formation of ice in the fuel filters.
(2) A fuel heater operates as a heat exchanger to warm the fuel.
Regarding the above statements,
~ Statement (1) is true. Gas-turbine-engine fuel systems are very susceptible to the formation of ice on the fuel filters. Statement (2) is also true. The fuel heater operates as a heat exchanger to warm the fuel. These heat exchangers may use engine compressor bleed air or warm engine oil to furnish the heat.
@ Statement (1) is true. Gas-turbine-engine fuel systems are very susceptible to the formation of ice on the fuel filters. Statement (2) is also true. The fuel heater operates as a heat exchanger to warm the fuel. These heat exchangers may use engine compressor bleed air or warm engine oil to furnish the heat.
a. only No. 1 is true.
b. only No. 2 is true.
*c. both No. 1 and No. 2 are true.

74. (8771) (1) A fuel heater can use engine bleed air as a source of heat.
(2) A fuel heater can use engine lubricating oil as a source of heat.
Regarding the above statements,
~ Statement (1) is true. A fuel heater can use engine bleed air as a source of heat. Statement (2) is also true. A fuel heater can use engine lubricating oil as a source of heat.
@ Statement (1) is true. A fuel heater can use engine bleed air as a source of heat. Statement (2) is also true. A fuel heater can use engine lubricating oil as a source of heat.
a. only No. 1 is true.
*b. both No. 1 and No. 2 are true.
c. neither No. 1 nor No. 2 is true.

75. (8772) (1) A fuel pressure gauge is a differential pressure indicator.
(2) A fuel pressure gauge indicates the pressure of the fuel entering the carburetor.
Regarding the above statements,
~ Statement (1) is true. Most fuel-pressure gauges are differential pressure gauges. They measure the difference in the pressure of the fuel and the pressure of some reference air. When a pressure carburetor is used, this reference air pressure is the carburetor upper-deck air pressure. Statement (2) is also true. The pressure shown on the gauge is the pressure of the fuel as it enters the carburetor.
@ Statement (1) is true. Most fuel-pressure gauges are differential pressure gauges. They measure the difference in the pressure of the fuel and the pressure of some reference air. When a pressure carburetor is used, this reference air pressure is the carburetor upper-deck air pressure. Statement (2) is also true. The pressure shown on the gauge is the pressure of the fuel as it enters the carburetor.
a. only No. 2 is true.
*b. both No. 1 and No. 2 are true.
c. neither No. 1 nor No. 2 is true.

76. (8773) (1) A fuel pressure relief valve is required on an aircraft positive-displacement fuel pump.
(2) A fuel pressure relief valve is required on an aircraft centrifugal fuel boost pump.
Regarding the above statements,
~ Statement (1) is true. A pressure-relief valve is required for a positive-displacement aircraft fuel pump. Statement (2) is not true. A pressure-relief valve is not needed with a centrifugal fuel boost pump.
@ Statement (1) is true. A pressure-relief valve is required for a positive-displacement aircraft fuel pump. Statement (2) is not true. A pressure-relief valve is not needed with a centrifugal fuel boost pump.
*a. only No. 1 is true.
b. only No. 2 is true.
c. both No. 1 and No. 2 are true.

77. (8774) The primary purpose of a fuel tank sump is to provide a
~ Fuel tanks are equipped with sumps (low points in the tank) in which water and dirt will accumulate to be collected and drained.
@ Fuel tanks are equipped with sumps (low points in the tank) in which water and dirt will accumulate to be collected and drained.
a. positive system of maintaining the design minimum fuel supply for safe operation.
*b. place where water and dirt accumulations in the tank can collect and be drained.
c. reserve supply of fuel to enable the aircraft to land safely in the event of fuel exhaustion.

78. (8775) Why are integral fuel tanks used in many large aircraft?
~ Integral fuel tanks are used in large aircraft to reduce weight and to utilize as much of the space as possible for carrying fuel.
@ Integral fuel tanks are used in large aircraft to reduce weight and to utilize as much of the space as possible for carrying fuel.
a. To reduce fire hazards.
b. To facilitate servicing.
*c. To reduce weight.

79. (8776) If an aircraft is fueled from a truck or storage tank which is known to be uncontaminated with dirt or water, periodic checks of the aircraft's fuel tank sumps and system strainers
~ Even though an aircraft is fueled from an uncontaminated source, the fuel tank sumps and strainers must be periodically checked, as there is always the possibility of contamination from other sources.
@ Even though an aircraft is fueled from an uncontaminated source, the fuel tank sumps and strainers must be periodically checked, as there is always the possibility of contamination from other sources.
a. can be eliminated except for the strainer check before the first flight of the day and the fuel tank sump check during 100-hour or annual inspections.
*b. are still necessary due to the possibility of contamination from other sources.
c. can be sharply reduced since contamination from other sources is relatively unlikely and of little consequence in modern aircraft fuel systems.

80. (8777) Aircraft defueling should be accomplished
~ Both fueling and defueling operations should be conducted in the open air where there is good ventilation.
@ Both fueling and defueling operations should be conducted in the open air where there is good ventilation.
a. with the aircraft's communication equipment on and in contact with the tower in case of fire.
b. in a hangar where activities can be controlled.
*c. in the open air for good ventilation.

81. (8778) Integral fuel tanks on transport aircraft are
~ Integral fuel tanks are actually a part of the aircraft structure in which all of the seams and riveted joints are sealed with an appropriate sealant. The fuel is carried in the sealed-off aircraft structure.
@ Integral fuel tanks are actually a part of the aircraft structure in which all of the seams and riveted joints are sealed with an appropriate sealant. The fuel is carried in the sealed-off aircraft structure.
a. usually constructed of nonmetallic material.
b. readily removed from the aircraft.
*c. formed by the aircraft structure.

82. (8779) What precautions must be observed if a gravity-feed fuel system is permitted to supply fuel to an engine from more than one tank at a time?
~ If a gravity-feed fuel system is permitted to supply fuel to an engine from more than one tank at a time, the air space above the fuel in the tanks must be interconnected.
@ If a gravity-feed fuel system is permitted to supply fuel to an engine from more than one tank at a time, the air space above the fuel in the tanks must be interconnected.
*a. The tank airspaces must be interconnected.
b. The fuel outlet ports of each tank must have the same cross-sectional area.
c. Each tank must have a valve in its outlet that automatically shuts off the line when the tank is empty.

83. (8780) The purpose of the baffle plate in a fuel tank is to
~ Baffle plates in a fuel tank resist (prevent) the fuel from surging in the tank.
@ Baffle plates in a fuel tank resist (prevent) the fuel from surging in the tank.
a. provide an expansion space for the fuel.
*b. resist fuel surging within the fuel tank.
c. provide internal structural integrity.

84. (8781) What minimum required markings must be placed on or near each appropriate fuel filler cover on utility category aircraft?
~ 14 CFR 23.1557 states that the fuel filler openings on a reciprocating-engine-powered airplane must be marked at or near the filler cover with the word 'Avgas' and the minimum fuel grade. If the airplane is turbine-engine-powered, the markings must include the words 'Jet Fuel' and the permissible fuel designations or reference to the Airplane Flight Manual (AFM) for permissible fuel designations.
@ 14 CFR 23.1557 states that the fuel filler openings on a reciprocating-engine-powered airplane must be marked at or near the filler cover with the word 'Avgas' and the minimum fuel grade. If the airplane is turbine-engine-powered, the markings must include the words 'Jet Fuel' and the permissible fuel designations or reference to the Airplane Flight Manual (AFM) for permissible fuel designations.
a. The word 'Avgas' and the minimum fuel grade, and the total fuel tank capacity.
b. The word 'Avgas' and the minimum fuel grade or designation for the engines, and the usable fuel tank capacity.
*c. The word 'Avgas' and the minimum fuel grade.

85. (8782) What is one disadvantage of using aromatic aviation fuels?
~ Aromatic additives in aviation gasoline increase its antidetonation characteristics, but they also cause deterioration of rubber parts. Any hose, seal, or diaphragm used with a fuel that contains aromatic additives must be specifically formulated to withstand these additives.
@ Aromatic additives in aviation gasoline increase its antidetonation characteristics, but they also cause deterioration of rubber parts. Any hose, seal, or diaphragm used with a fuel that contains aromatic additives must be specifically formulated to withstand these additives.
a. A fuel intercooler is required.
*b. Deteriorates rubber parts.
c. Results in low fuel volatility.

86. (8783) Fuel-boost pumps are operated
~ Fuel boost pumps are used to provide a positive flow of fuel from the tank to the engine. Boost pumps are used for engine starting, as a backup for takeoff and landing, and in many cases, to transfer fuel from one tank to another.
@ Fuel boost pumps are used to provide a positive flow of fuel from the tank to the engine. Boost pumps are used for engine starting, as a backup for takeoff and landing, and in many cases, to transfer fuel from one tank to another.
*a. to provide a positive flow of fuel to the engine.
b. primarily for fuel transfer.
c. automatically from fuel pressure.

87. (8784) Flapper valves are used in fuel tanks to
~ Flapper valves are used in fuel tanks to serve as check valves. Flapper valves allow fuel to flow to the booster pump but prevent its flowing away from the pump during certain flight maneuvers.
@ Flapper valves are used in fuel tanks to serve as check valves. Flapper valves allow fuel to flow to the booster pump but prevent its flowing away from the pump during certain flight maneuvers.
a. reduce pressure.
b. prevent a negative pressure.
*c. act as check valves.

88. (8785) Why are centrifugal-type boost pumps used in fuel systems of aircraft operating at high altitude?
~ Centrifugal boost pumps are used in the fuel tanks of aircraft that operate at high altitude. Boost pumps supply fuel under positive pressure to the inlet of the engine-driven fuel pumps under conditions where the ambient pressure is too low to ensure a positive supply.
@ Centrifugal boost pumps are used in the fuel tanks of aircraft that operate at high altitude. Boost pumps supply fuel under positive pressure to the inlet of the engine-driven fuel pumps under conditions where the ambient pressure is too low to ensure a positive supply.
a. Because they are positive displacement pumps.
*b. To supply fuel under pressure to engine-driven pumps.
c. To permit cooling air to circulate around the motor.

89. (8786) Why is it necessary to vent all aircraft fuel tanks?
~ According to 14 CFR 23.975, fuel tanks must be vented with the vents having sufficient capacity to allow the rapid relief of excessive pressure between the interior and the exterior of the tank.
@ According to 14 CFR 23.975, fuel tanks must be vented with the vents having sufficient capacity to allow the rapid relief of excessive pressure between the interior and the exterior of the tank.
a. To ensure a positive head pressure for a submerged boost pump.
b. To exhaust fuel vapors.
*c. To limit pressure differential between the tank and atmosphere.

90. (8787) According to Part 23, what minimum required markings must be placed at or near each appropriate fuel filler cover for reciprocating engine-powered airplanes?
~ According to 14 CFR 23.1557, fuel filler openings for reciprocating engine-powered airplanes must be marked at or near the filler cover with the word 'Avgas,' and the minimum fuel grade.
@ According to 14 CFR 23.1557, fuel filler openings for reciprocating engine-powered airplanes must be marked at or near the filler cover with the word 'Avgas,' and the minimum fuel grade.
*a. The word 'Avgas' and the minimum fuel grade.
b. The word 'Fuel' and usable fuel capacity.
c. The word 'Avgas' and the total fuel capacity.

91. (8788) The location of leaks and defects within the internal portions of the fuel system can usually be determined by
~ It is possible, by watching the fuel-pressure gauge and operating the selector valves, to isolate a portion of a large-aircraft fuel system that has an internal leak.
@ It is possible, by watching the fuel-pressure gauge and operating the selector valves, to isolate a portion of a large-aircraft fuel system that has an internal leak.
a. visual inspection for evidence of wet spots and stains, and feeling for unusually warm components.
b. performing a fuel flow check.
*c. observing the pressure gauge and operating the selector valves.

92. (8789) What type of fuel-booster pump requires a pressure relief valve?
~ A sliding-vane fuel pump requires a pressure-relief valve because it is a constant-displacement pump.
@ A sliding-vane fuel pump requires a pressure-relief valve because it is a constant-displacement pump.
a. Concentric.
*b. Sliding vane.
c. Centrifugal.

93. (8790) To prevent vapor lock in fuel lines at high altitude, some aircraft are equipped with
~ Booster pumps are installed in the fuel tanks of some aircraft to prevent vapor lock in the fuel lines at high altitudes. The booster pump holds a positive pressure on the fuel in the lines, between the tank and the engine-driven fuel pump.
@ Booster pumps are installed in the fuel tanks of some aircraft to prevent vapor lock in the fuel lines at high altitudes. The booster pump holds a positive pressure on the fuel in the lines, between the tank and the engine-driven fuel pump.
a. vapor separators.
b. direct-injection-type carburetors.
*c. booster pumps.

94. (8791) A fuel temperature indicator is located in the fuel tanks on some turbine-powered airplanes to tell when the fuel may be
~ Fuel-temperature sensors (fuel-temperature indicators) are installed in the fuel tanks of some jet-powered aircraft to show the flight engineer the temperature of the fuel. By knowing the temperature of the fuel in the tanks, the flight engineer can know when there is danger of ice crystals forming in the fuel and blocking the fuel strainers.
@ Fuel-temperature sensors (fuel-temperature indicators) are installed in the fuel tanks of some jet-powered aircraft to show the flight engineer the temperature of the fuel. By knowing the temperature of the fuel in the tanks, the flight engineer can know when there is danger of ice crystals forming in the fuel and blocking the fuel strainers.
a. getting cold enough to form hard ice.
*b. in danger of forming ice crystals.
c. about to form rime ice.

95. (8792) When inspecting a fuel system, you should check all valves located downstream of boost pumps with the pumps
~ In order to inspect a fuel system for leaks, you should inspect all of the valves located downstream of the booster pump, with the pumps operating and producing maximum pressure.
@ In order to inspect a fuel system for leaks, you should inspect all of the valves located downstream of the booster pump, with the pumps operating and producing maximum pressure.
a. at idle.
b. dormant.
*c. operating.

96. (8793) The type of fuel-boost pump that separates air and vapor from the fuel before it enters the line to the carburetor is the
~ Centrifugal boost pumps normally have a small agitator (a small propeller) that spins when the pump impeller is turning to separate the vapor from the fuel before the fuel enters the lines to the carburetor.
@ Centrifugal boost pumps normally have a small agitator (a small propeller) that spins when the pump impeller is turning to separate the vapor from the fuel before the fuel enters the lines to the carburetor.
a. gear-type pump.
*b. centrifugal-type pump.
c. sliding vane-type pump.

97. (8794) (1) On a large aircraft pressure refueling system, a pressure refueling receptacle and control panel will permit one person to fuel or defuel any or all fuel tanks of an aircraft.
(2) Because of the fuel tank area, there are more advantages to a pressure fueling system in light aircraft.
Regarding the above statements,
~ Statement (1) is true. Large aircraft pressure-fueling systems consist of a refueling receptacle and a panel of controls and gauges that permit one person to fuel or defuel any or all fuel tanks of an aircraft. Statement (2) is not true. Because of the limited fuel tank area, there are fewer advantages of a pressure-fueling system in light aircraft.
@ Statement (1) is true. Large aircraft pressure-fueling systems consist of a refueling receptacle and a panel of controls and gauges that permit one person to fuel or defuel any or all fuel tanks of an aircraft. Statement (2) is not true. Because of the limited fuel tank area, there are fewer advantages of a pressure-fueling system in light aircraft.
*a. only No. 1 is true.
b. only No. 2 is true.
c. both No. 1 and No. 2 are true.

98. (8795) When routing a fuel line between two rigidly mounted fittings the line should
~ Never install a straight length of tubing between two rigidly mounted fittings. Always incorporate at least one bend between such fittings to absorb strain caused by vibration and temperature changes.
@ Never install a straight length of tubing between two rigidly mounted fittings. Always incorporate at least one bend between such fittings to absorb strain caused by vibration and temperature changes.
*a. have at least one bend between such fittings.
b. be a straight length of tubing and clamped to the aircraft structure.
c. have a flexible line added between two metal lines to allow for ease of installation.

99. (8796) (1) If aviation gasoline vaporizes too readily, fuel lines may become filled with vapor and cause increased fuel flow.
(2) A measure of a gasoline's tendency to vapor lock is obtained from the Reid vapor pressure test.
Regarding the above statements,
~ Statement (1) is not true. If the gasoline vaporizes too readily, fuel lines may become filled with vapor and cause decreased, not increased, fuel flow. Statement (2) is true. The Reid vapor pressure of a fuel is a measure of the fuel's tendency to vapor lock.
@ Statement (1) is not true. If the gasoline vaporizes too readily, fuel lines may become filled with vapor and cause decreased, not increased, fuel flow. Statement (2) is true. The Reid vapor pressure of a fuel is a measure of the fuel's tendency to vapor lock.
*a. only No. 2 is true.
b. both No. 1 and No. 2 are true.
c. neither No. 1 nor No. 2 is true.

100. (8797) Microbial growth is produced by various forms of microorganisms that live and multiply in the water interfaces of jet fuels. Which of the following could result if microbial growth exists in a jet fuel tank and is not corrected?
1. Interference with fuel flow.
2. Interference with fuel quantity indicators.
3. Engine seizure.
4. Electrolytic corrosive action in a metal tank.
5. Lower grade rating of the fuel.
6. Electrolytic corrosive action in a rubber tank.
~ The buildup of micro-organisms in the fuel tank of a jet aircraft can not only interfere with fuel flow and with the fuel quantity indicators, but more importantly, can start electrolytic corrosion in metal fuel tanks.
@ The buildup of micro-organisms in the fuel tank of a jet aircraft can not only interfere with fuel flow and with the fuel quantity indicators, but more importantly, can start electrolytic corrosion in metal fuel tanks.
*a. 1, 2, 4.
b. 2, 3, 5.
c. 1, 5, 6.

101. (8798) The vapor pressure of aviation gasoline is
~ The vapor pressure of aviation gasoline is limited to a maximum of 7 psi, which is lower than the vapor pressure of many grades of automobile gasoline.
@ The vapor pressure of aviation gasoline is limited to a maximum of 7 psi, which is lower than the vapor pressure of many grades of automobile gasoline.
*a. lower than the vapor pressure of automotive gasoline.
b. higher than the vapor pressure of automotive gasoline.
c. approximately 20 PSI at 100°F.

102. (8799) What can be done to eliminate or minimize the microbial growth problem in an aircraft jet fuel tank?
~ An anti-icing and antibacterial additive is often used in jet aircraft fuel tanks to minimize the problems caused by microbial growth inside the fuel tanks.
@ An anti-icing and antibacterial additive is often used in jet aircraft fuel tanks to minimize the problems caused by microbial growth inside the fuel tanks.
*a. Use anti-icing and antibacterial additives.
b. Add CO(2) as a purgative.
c. Keep the fuel tank topped off.

103. (8800) What is the maximum vapor pressure allowable for an aircraft fuel?
~ A Reid vapor pressure of 7 psi at 100°F is the maximum allowed for aviation gasoline.
@ A Reid vapor pressure of 7 psi at 100°F is the maximum allowed for aviation gasoline.
*a. 7 PSI.
b. 5 PSI.
c. 3 PSI.

104. (8801) If a bladder-type fuel tank is to be left empty for an extended period of time, the inside of the tank should be coated with a film of
~ If a rubberized fabric bladder tank is to remain empty for an extended period of time, it should be cleaned out thoroughly and its interior covered with a film of clean engine oil.
@ If a rubberized fabric bladder tank is to remain empty for an extended period of time, it should be cleaned out thoroughly and its interior covered with a film of clean engine oil.
*a. engine oil.
b. linseed oil.
c. ethylene glycol.

105. (8802) How may the antiknock characteristics of a fuel be improved?
~ The antiknock characteristics of a fuel may be improved by adding a knock inhibitor such as tetraethyl lead to the fuel.
@ The antiknock characteristics of a fuel may be improved by adding a knock inhibitor such as tetraethyl lead to the fuel.
*a. By adding a knock inhibitor.
b. By adding a knock enhancer.
c. By adding a fungicide agent.

106. (8746.2) A digital fuel totalizer automatically indicates the amount of fuel used, fuel remaining, current rate of consumption, and fuel
~ A fuel totalizer is a fuel quantity indicator that gives the total amount of fuel remaining on board the aircraft on one instrument. The totalizer adds the quantites of fuel in all of the tanks and gives the pilot an indication of the total number of pounds of fuel remaining.
@ A fuel totalizer is a fuel quantity indicator that gives the total amount of fuel remaining on board the aircraft on one instrument. The totalizer adds the quantites of fuel in all of the tanks and gives the pilot an indication of the total number of pounds of fuel remaining.
*a. weight, aboard at takeoff.
b. remaining at the 45-minute IFR fuel reserve.
c. remaining, flight time at the current power setting.

107. (8707.2) How many vents, arranged so that they are not likely to become plugged at the same time, must be used in multiengine fuel systems?
~ According to 14 CFR 23.953(b)(2), if a single fuel tank (or series of fuel tanks interconnected to function as a single tank) is used on a multi-engine airplane, the tank must have at least two vents arranged to minimize the probability of both vents becoming obstructed simultaneously.
@ According to 14 CFR 23.953(b)(2), if a single fuel tank (or series of fuel tanks interconnected to function as a single tank) is used on a multi-engine airplane, the tank must have at least two vents arranged to minimize the probability of both vents becoming obstructed simultaneously.
*a. Two.
b. Four.
c. Six.

108. (8709.2) How many engine driven fuel pumps per engine are required for engines requiring fuel pumps?
~ According to 14 CFR 23.991(a)(1)(i), for reciprocating engine installations having fuel pumps to supply fuel to the engine, at least one pump for each engine must be directly driven by the engine and must meet 14 CFR 23.955. This pump is the main pump. There must be at least one main fuel pump for each turbine engine.
@ According to 14 CFR 23.991(a)(1)(i), for reciprocating engine installations having fuel pumps to supply fuel to the engine, at least one pump for each engine must be directly driven by the engine and must meet 14 CFR 23.955. This pump is the main pump. There must be at least one main fuel pump for each turbine engine.
a. Two engines can share one fuel pump.
*b. One fuel pump for each engine.
c. Two fuel pumps for each engine.

109. (8710.2) A fuel system must be designed to prevent fuel-vapor ignition caused by
~ A fuel system must be designed to prevent fuel-vapor ignition caused by lightning.
@ A fuel system must be designed to prevent fuel-vapor ignition caused by lightning.
a. over-heating.
b. back-fire.
*c. lightning.

110. (8710.3) What is the minimum distance allowed between a fuel tank and the fire wall separating the engine?
~ There must be at least one-half inch of clearance between the fuel tank and the firewall.
@ There must be at least one-half inch of clearance between the fuel tank and the firewall.
*a. One-half inch.
b. One inch.
c. Two inches.

111. (8710.4) Fuel baffles are installed in tanks to prevent ______________________ caused by changes in the altitude of the aircraft.
~ Baffles are installed in aircraft fuel tanks to prevent the fuel sloshing or surging in the tank caused by changes in attitude of the aircraft.
@ Baffles are installed in aircraft fuel tanks to prevent the fuel sloshing or surging in the tank caused by changes in attitude of the aircraft.
a. vapors
*b. surging
c. starvation

112. (8710.5) Many fuel tanks incorporate _________________ valves to prevent fuel from flowing away from the boost pump or tank outlet when the aircraft is in a high 'G' maneuver.
~ Many fuel tanks incorporate flapper valves that prevent fuel in the tank from flowing away from the boost pump or tank outlet any time the aircraft is in a high "G" maneuver. These valves are normally open, but if some maneuver causes the fuel to flow away from the pump or outlet, they flap shut until the force moving the fuel no longer exists, then they automatically open.
@ Many fuel tanks incorporate flapper valves that prevent fuel in the tank from flowing away from the boost pump or tank outlet any time the aircraft is in a high "G" maneuver. These valves are normally open, but if some maneuver causes the fuel to flow away from the pump or outlet, they flap shut until the force moving the fuel no longer exists, then they automatically open.
*a. flapper
b. check
c. dump

113. (8710.6) Fuel heaters are used with fuel systems for turbine engines to prevent ____________ in the fuel from clogging system filters.
~ Turbine powered aircraft incorporate fuel heaters to prevent ice crystals from forming in the fuel and clogging the fuel system filters.
@ Turbine powered aircraft incorporate fuel heaters to prevent ice crystals from forming in the fuel and clogging the fuel system filters.
a. moisture
*b. ice crystals
c. contamination

114. (8710.7) A transducer in a fuel pressure system serves what function?
~ A transducer is a device that changes energy from one form into another. A fuel pressure transducer converts fuel pressure into an electrical signal that is proportional to the fuel pressure. This signal is transmitted to the fuel pressure indicator.
@ A transducer is a device that changes energy from one form into another. A fuel pressure transducer converts fuel pressure into an electrical signal that is proportional to the fuel pressure. This signal is transmitted to the fuel pressure indicator.
a. Transmits an electrical signal to the transmitter for fluid pressure.
b. Transmits electrical signal proportional to the fluid pressure.
*c. Converts fluid pressure directly through a transmitter to the indicator.