Transicion rac 65

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Transicion rac 65

sistema de combustible

eunice contreras
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Fuel jettisoning is usually accomplished Trough a common manifold and outlet in each wing By gravity flow into the outboard wing tanks and overboars trhough a common outlet in each wing Trough individual outlets for each tank.
The primary purpose of an aircraft`s fuel jettison system is to quickly achieve a Lower landing weight Balanced fuel load Reduced fire hazard.
(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, Both N°.1 and N° 2 are true Only N°2 is true Neither N° 1 nor N°. 2 is true.
Which of the following is employed to maintain lateral stability when jettisoning fuel? To separate independent systems. Crossfeed system. Two interconnected systems.
Which procedure must be followed when defueling aircraft whith sweptback wings? Defuel all the tanks at one time. Defuel the inboard wing tanks first. Defuel the outboard wing tanks first.
Normal fuel crossfeed system operation in multiengine aircraft Calls for jettisoning of fuel overboard to correct lateral instavility. Reduces contamination and/or fire hazards during fueling or defueling operations. Provides a means to maintain a balanced fuel load condition.
Fuel heaters are used with fuel systems for turbine engines to prevent__________in the fuel from cloggin system filters . Moisture Ice crystals Contamination.
What is the primary purpose of the crossfeed system? To allow the feeding of any engine from any tank To allow the feeding of fuel from one tank for defueling To provide automatic refueling of a tank to any desired level.
Fuel system components must be bonded and grounded in order to Drain off static charges Prevent stray currents Retard galvanic corrosion.
What is one purpose of a fuel tank vent? To maintain atmospheric pressure To decrease fuel vapor pressure To decrease tank internal air pressure .
A typical large transport aircraft fuel manifold systen allows how many of the following? 1. All tanks can be serviced througha 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. 1 and 2 1, 2 and 3 1,2,3, and 4.
The use of turbine fuels in aircraft has resulted in some problems not normally associated with aviation gasolines. Ones of these problems is Increasing viscosity of fuel as fuel temperature lowers at altitude Higher vapor pressure. Microbial contaminants.
Which of the following precautions is most important during refueling operations? All outside electrical sources must be disconnected from the aircraft. Fuel to be used must be appropriately identfied. All electrical switches must be in OFF position.
Before fueling an aircraft by using the pressure fueling method, what important precaution should be observed The truck pump pressure must be correct for that refueling systems The truck pump pressure must be adjusted for minimumfilter pressure The aircraft's electrical systems must be on to indicate quanty gauge readings.
What flight safety-related advantage does a pressure fueling system provide Keeps the aircraft wirhin weight and balance limitations Reduces the chances for fuel contamination Reduces the time required for fueling .
Aircraft pressure fueling systems instructonional procedures are normally pkacarded on the Fuel control panel access door Lower wing surface adjacent to the access door Aircraft groundo connection point.
Pressure fueling of aircraft is usually accomplished trough Pressure connections on individual fuel 5anks At least one singlr point connection Individual fuel tank overwing and/or fuselage access points .
Whic of the following may be used for the repair of fuel leaks on most integral fuel tanks Welding and resealing Brazing and resealing Riveting and resealing.
How is the outlet fuel pressure regulated on a submerged, single-speed, centrifugal-type fuel pump? By the engine-driven pump's design and internal clearance By the first chek valve downstream from the pump By the pump's desing and internal clearances .
When inspecting a removable rigid fuel tank for leaks, what procedure shoul be followed? Pressurize the tank with air brush with soapy water Fill the tank with water and pressurize with air and brush with soapy water Pressurize the tank with air an sumerge in water to llocate leaks.
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' maneuvèr Flapper Check Dump.
If is becessary to enter an aircraft's fuel tank, which procedure should be avoided? Continue purging the tank during the entire work period Station an assistant outside the fuel tank access to perform rescue operations if required Conduct the defueling and tank purging operation in an air- conditioned building.
What is the recomended practice for cleaning a fuel tank before welding Purge the tank with air Flush the inside of the tank with clean water Steam clean the tank interior.
(Refervto figure ) what is the purpose of the pump crossfeed valve? Balance the fuel in the tanks Allow operation of engines from one tank Allow operation of the left engine when the right fuel-boost pum is inoperative.
An aicraft's integral fuel tank is Usually located in the bottom of the fuselage A part of the aircraft strcture A selft-sealing tank.
Which gas is used for purging an aircraft fuel tank? Helium or argon Carbon dioxide Carbon monoxide .
Why is the main fuel strainer located at the lowest point in the fuel system? It traps any small amountcof water that may be present in the fuel systems It provides a drain for residual fuel It filters and traps all micro-organisms that may be present in the fuel system.
28. (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? Micromesh fuel strainers and fuel heater. High-velocity fuel pumps and fuel heater. Anti-icing fuel additives and fuel heater.
29. (8730) As a general rule, which statement is true regarding fuel leaks? Stains, seeps, and heavy seeps are not flight hazards. All fuel leaks regardless of location or severity are considered a hazard to flight. Stains, seeps, and heavy seeps, (in addition to running leaks) are considered flight hazards when located in unvented areas of the aircraft.
30. (8732) What should be used to inert an integral fuel tank before attempting repairs? CO(2). Water. Steam.
31. (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, only No. 1 is true. only No. 2 is true. both No. 1 and No. 2 are true.
32. (8735) Why are jet fuels more susceptible to water contamination than aviation gasoline? Jet fuel has a higher viscosity than gasoline. Jet fuel is lighter than gasoline; therefore, water is more easily suspended. Condensation is greater because of the higher volatility of jet fuels.
33. (8736) When installing a rigid fuel line, 1/2 inch in diameter, at what intervals should the line be supported? 24 inches. 12 inches. 16 inches.
34. (8737) The probe of a capacitance-type fuel level gauge is essentially a float-actuated variable capacitor. capacitor with fuel and air acting as one plate. capacitor with fuel and air acting as a dielectric.
35. (8745) One advantage of electrical and electronic fuel quantity indicating systems is that the indicators are calibrated in gallons; therefore, no conversion is necessary. only one transmitter and one indicator are needed regardless of the number of tanks. several fuel tank levels can be read on one indicator.
36.(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. 1, 2, 3, 4. 1, 3, 6, 8. 2, 3, 5, 7.
37. (8742) The electronic-type fuel quantity indicating system consists of a bridge circuit, an amplifier, an indicator, and a tank unit. a tank, an amplifier, and an indicator. a tank unit, a tank, and an amplifier.
38. (8744) Why is the capacitance fluid quantity indicating system more accurate in measuring fuel level than a mechanical type? Only one probe and one indicator are necessary for multiple tank configurations. It measures in gallons and converts to pounds. It measures by weight instead of volume.
39. (8746.1) A fuel totalizer is a component which indicates the total amount of fuel being consumed by all engines. amount of fuel in any given tank. amount of fuel in all tanks.
40. (8747) What is the dielectric (nonconducting material) in a capacitance-type fuel quantity indicating system? Outer shell of the capacitor. Fuel in the tank. Fuel and air in the tank.
41. (8748) A capacitance-type fuel quantity indicating system measures fuel in pounds. pounds per hour. gallons.
42. (8750) How does temperature affect fuel weight? Cold fuel is heavier per gallon Warm fuel is heavier per gallon. Temperature has no effect.
43. (8752) When fuel quantity is measured in pounds instead of gallons, the measurement will be more accurate because fuel volume varies with temperature change. increases when temperature decreases. varies with changes in atmospheric pressure.
44. (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, only No. 1 is true. only No. 2 is true. both No. 1 and No. 2 are true.
45.(8753) An electrical-type fuel quantity indicating system consists of an indicator in the cockpit and a float-operated transmitter installed in the tank. float resting on the surface of the tank. float-operated receiver installed in the tank.
46. (8754) What is the purpose of a float-operated transmitter installed in a fuel tank? It sends an electric signal to the fuel quantity indicator. It senses the total amount of fuel density. It senses the dielectric qualities of fuel and air in the tank.
47. (8755) In an electronic-type fuel quantity indicating system, the tank sensing unit is a capacitor. variable resistor. variable inductor.
48.(8758) Select one means of controlling the fuel temperature on turbine-powered aircraft. Engine bleed air to the fuel filter. Engine bleed air to the fuel tank. Engine bleed air to a heat exchanger.
49. (8764) A transmitter in a fuel pressure warning system serves what function? Transmits an electrical signal to fluid pressure. Converts fluid pressure to an electrical signal. Transmits fluid pressure directly to the indicator.
50. (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, only No. 1 is true. only No. 2 is true. both No. 1 and No. 2 are true.
51.(8766) Which of the following is necessary to effectively troubleshoot a fuel pressure warning system? The manufacturer's maintenance manuals. AC 43.13-1B, Acceptable Methods, Techniques, and Practices -- Aircraft Inspection and Repair. A set of Federal Aviation Regulations.
52. (8767) Which of the following would be most useful to locate and troubleshoot an internal fuel leak in an aircraft fuel system? Aircraft structure repair manual. Illustrated parts manual. A fuel system schematic.
53. (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, only No. 1 is true. both No. 1 and No. 2 are true. neither No. 1 nor No. 2 is true.
54. (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, only No. 1 is true. only No. 2 is true. both No. 1 and No. 2 are true.
55. (8777) Aircraft defueling should be accomplished with the aircraft's communication equipment on and in contact with the tower in case of fire. in a hangar where activities can be controlled. in the open air for good ventilation.
56. (8778) Integral fuel tanks on transport aircraft are usually constructed of nonmetallic material. readily removed from the aircraft. formed by the aircraft structure.
57.(8780) The purpose of the baffle plate in a fuel tank is to provide an expansion space for the fuel. resist fuel surging within the fuel tank. provide internal structural integrity.
58.(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 gear-type pump. centrifugal-type pump. sliding vane-type pump.
59. (8799) What can be done to eliminate or minimize the microbial growth problem in an aircraft jet fuel tank? Use anti-icing and antibacterial additives. Add CO(2) as a purgative. Keep the fuel tank topped off.
60. (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, only No. 2 is true. both No. 1 and No. 2 are true. neither No. 1 nor No. 2 is true.
61. (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. 1, 2, 4. 2, 3, 5. 1, 5, 6.
62. (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, only No. 2 is true. both No. 1 and No. 2 are true. neither No. 1 nor No. 2 is true.
63. (8731) The presence of fuel stains around a fuel nozzle would indicate too much fuel pressure. excessive airflow across the venturi. clogged fuel nozzle.
64. (8774) The primary purpose of a fuel tank sump is to provide a positive system of maintaining the design minimum fuel supply for safe operation. place where water and dirt accumulations in the tank can collect and be drained. reserve supply of fuel to enable the aircraft to land safely in the event of fuel exhaustion.
65. (8733) What should be used to remove flux from an aluminum tank after welded repairs? Soft brush and warm water. 5 percent solution of nitric or sulfuric acid. Mild solution of soap and warm water.
66. (8738) Which statement concerning an electronic capacitance-type fuel quantity indicating system is true? It has no moving parts in the tank. It has two tubes separated by an electronic field in the tank. It utilizes a variable capacitor to indicate the fuel tank capacity.
67. (8740) Which aircraft fuel quantity indicating system incorporates a signal amplifier? Electronic. Sight glass. Electrical.
68. (8751) One advantage of electrical and electronic fuel quantity indicating systems is that the indicator can be located any distance from the tank(s). has no movable devices. always measures volume instead of mass.
69. (8760) What unit is generally used to actuate the fuel pressure warning system? Fuel flowmeter. Pressure-sensitive mechanism. Fuel pressure gauge.
70. (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 pressure warning. Fuel pressure gauge. Fuel temperature indicator.
71. (8765) Where is fuel pressure taken for the pressure warning signal on most aircraft engines? Outlet side of the boost pump. Fuel pressure line of the carburetor. Between the fuel pump and the strainer.
72-. (8775) Why are integral fuel tanks used in many large aircraft? To reduce fire hazards. To facilitate servicing. To reduce weight.
73. (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 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. are still necessary due to the possibility of contamination from other sources. can be sharply reduced since contamination from other sources is relatively unlikely and of little consequence in modern aircraft fuel systems.
74. (8781) What minimum required markings must be placed on or near each appropriate fuel filler cover on utility category aircraft? The word 'Avgas' and the minimum fuel grade, and the total fuel tank capacity. The word 'Avgas' and the minimum fuel grade or designation for the engines, and the usable fuel tank capacity. The word 'Avgas' and the minimum fuel grade.
75. 8802) How may the antiknock characteristics of a fuel be improved? By adding a knock inhibitor. By adding a knock enhancer. By adding a fungicide agent.
76. (8710.4) Fuel baffles are installed in tanks to prevent ______________________ caused by changes in the altitude of the aircraft. vapors surging starvation.
77. (8746.2) A digital fuel totalizer automatically indicates the amount of fuel used, fuel remaining, current rate of consumption, and fuel weight, aboard at takeoff. remaining at the 45-minute IFR fuel reserve. remaining, flight time at the current power setting.
78.(8786) Why is it necessary to vent all aircraft fuel tanks? To ensure a positive head pressure for a submerged boost pump. To exhaust fuel vapors. To limit pressure differential between the tank and atmosphere.
79. (8709.2) How many engine driven fuel pumps per engine are required for engines requiring fuel pumps? Two engines can share one fuel pump. One fuel pump for each engine. Two fuel pumps for each engine.
80. (8710.3) What is the minimum distance allowed between a fuel tank and the fire wall separating the engine? One-half inch. One inch. Two inches.
81. (8791) A fuel temperature indicator is located in the fuel tanks on some turbine-powered airplanes to tell when the fuel may be getting cold enough to form hard ice. in danger of forming ice crystals. about to form rime ice.
82. (8710.7) A transducer in a fuel pressure system serves what function? Transmits an electrical signal to the transmitter for fluid pressure. Transmits electrical signal proportional to the fluid pressure. Converts fluid pressure directly through a transmitter to the indicator.
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