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AVMT-1105
| Question | Answer |
|---|---|
| What is the purpose of a fuel tank vent | To maintain atmospheric pressure |
| An aircrafts integral fuel tank is | A part of the aircraft structure |
| What method is used on turbine powered aircraft to determine when the condition of the fuel is approaching the danger of ice crystals | Fuel temperature indicator |
| Some turbine powered aircraft have a fuel temperature indicator located in the cockpit to | monitor the fuel temp during high altitude flight |
| normal fuel cross feed system operation in multiengine aircraft | Provides a means to maintain a balanced fuel load condition |
| when an aircraft is fueled from a truck or fuel farm that has not been contaminated, daily draining | of strainers and sumps is combined with periodic filter changes and inspection to ensure fuel is contaminate free |
| 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 | the tank airspace must be interconnected |
| Which of the following would be the most useful source to locate and trouble shoot an internal leak in an aircraft fuel system | Maintenance manual diagrams and descriptions |
| when defueling an aircraft which of the following must be accomplished | Always defuel outside the hanger |
| As a general rule which statement is true regarding fuel leaks | stains, seeps, and heavy seeps (in addition to running leaks) are considered flight hazards when located in unvented area of the aircraft |
| why are jet fuels more susceptible to water contamination than aviation Gasoline | Jet fuel has a higher viscosity the gasoline |
| Aircraft pressure fueling systems instructional procedures are normally place carded on the | Fuel control panel access door |
| why is the main fuel strainer located at the lowest point in the fuel system | It trap any small amount of water that may be present in the fuel system |
| A fuel system must be designed to prevent fuel vapor ignition cause by | Lightning |
| The primary purpose of an aircrafts fuel jettisoning system is to quickly achieve a | lower landing weight |
| Integral fuel tanks on transport aircraft are | supported by the aircraft structure |
| Fuel jettisoning past the limits prescribed by FAR is usually prevented by | Dump limit valves or a low level circuit |
| What is one disadvantage of using aromatic aviation fuels | Deteriorates rubber parts |
| What is the minimum distance allowed between a fuel tank and the fire wall separating the engine | One half inch |
| 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 | A fuel pressure warning signal system |
| which of the following precautions is most important during refueling operations | fuel to be used must be appropriately identified |
| system you should check all valves located downstream of the boost pump with the pumps | operating |
| a fuel pressure warning switch contacts close and warning light is turned on when | The fuel pressure drops below specified limits |
| fuel system components must be bonded and grounded in order to | drain off static charges |
| the function of a fuel heater is to | protect the engine fuel system from ice formation |
| what is used in many aircraft to prevent bubbles from forming in the fuel after it leaves the tank when atmospheric pressure is lower than fuel vapor pressure | Boost pumps |
| on a large pressure refueling system a pressure refueling receptacle and control panel will permit one person to | Fuel and defuel any of the tanks on an aircraft |
| 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 | interference with the fuel flow interference with the fuel quantity indicators and electrolytic corrosive action in a metal tank |
| what is the purpose of a float operated transmitter installed in a fuel tank | its sends an electric signal to the fuel quantity indicator |
| where is fuel pressure taken for the pressure warning signal on most aircraft engines | fuel pressure line of the carburetor |
| A fuel pressure relief valve is required on an aircraft | positive displacement fuel pump |
| which of the following is employed to maintain lateral stability when jettisoning fuel | two separate independent systems |
| what is the primary purpose of the cross feed system | it allows any tank fuel to any engine |
| what are the four general types of fuel quantity gauges | sight glass, mechanical, electrical ,and electronic |
| How may the antiknock characteristics of a fuel be improved | by adding a knock inhibitor |
| fuel boost pumps are operated | to provide a positive flow of fuel to the engine |
| what can be done to eliminate or minimize the microbial growth in an aircraft jet fuel tank | use anti-icing and antibacterial additives |
| the presence of fuel stains around a fuel nozzle would indicate | clogged fuel nozzle |
| what markings must be placarded on or near each appropriate fuel filler cover on standard category aircraft | The word "AVGAS" and the minimum fuel grade |
| fuel jettisoning is usually accomplished | through a common manifold and outlet in each wing |
| which of the following is necessary to effectively troubleshoot a fuel pressure warning system | the manufactures maintenance manual |
| fuel is moved overboard in most fuel jettison systems by | Boost pumps |
| the primary purpose of a fuel tank sumo is to provide a | place for contaminants and water to settle, with a drain valve to remove the impurities |
| the fuel jettison valve must be designed to allow flight personnel | to close the valve at any time and the fuel must discharge clear of the aircraft |
| why are integral fuel tanks used in many large aircraft | to reduce weight |
| to prevent vapor lock in fuel lines high altitude some aircraft are equipped with | booster pumps |
| select one means of controlling the fuel temperature on turbine powered aircraft | Engine bleed air to a heat exchanger |
| why are centrifugal type boost pumps used in fuel systems of aircraft at high altitude | to supply fuel under pressure to engine driven pumps |
| how many engine driven pumps per engine are required for engines requiring fuel pumps | one fuel pump for each engine |
| what flight safety related advantages does a pressure fueling system provide | reduces the time required for fueling |
Created by:
Hfrancis883