SU2: Airplane Instruments, Engines, and Systems Flashcards
Altimeter setting is the value to which the barometric pressure scale of the altimeter is set so the altimeter indicates
A. calibrated altitude at field elevation.
B. absolute altitude at field elevation.
C. true altitude at field elevation.
C. true altitude at field elevation.
Answer (C) is correct. (FAA-H-8083-25B Chap 8) ( ? )
Altimeter setting is the value to which the scale of the pressure altimeter is set so that the altimeter indicates true altitude at field elevation.
If a pilot changes the altimeter setting from 30.11 to 29.96, what is the approximate change in indication?
30.11-29.96 = 0.15
150 feet (.15 × 1,000 feet) lower.
(FAA-H-8083-25B Chap 8) ( ? )
Atmospheric pressure decreases approximately 1” of Hg (mercury) for every 1,000 feet of altitude gained. As an altimeter setting is changed, the change in altitude indication changes the same way (i.e., approximately 1,000 feet for every 1” change in altimeter setting) and in the same direction (i.e., lowering the altimeter setting lowers the altitude reading). Thus, changing from 30.11 to 29.96 is a decrease of .15 in., or 150 feet (.15 × 1,000 feet) lower.
During the run-up at a high-elevation airport, a pilot notes a slight engine roughness that is not affected by the magneto check but grows worse during the carburetor heat check. Under these circumstances, what would be the most logical initial action?
Check the results obtained with a leaner setting of the mixture.
(FAA-H-8083-25B Chap 7) ( ? )
If, during a run-up at a high-elevation airport, you notice a slight roughness that is not affected by a magneto check but grows worse during the carburetor heat check, you should check the results obtained with a leaner setting of the mixture control. At a high-elevation field, the air is less dense and the application of carburetor heat increases the already too rich fuel-to-air mixture. By leaning the mixture during the run-up, the condition should improve.
If the grade of fuel used in an aircraft engine is lower than specified for the engine, it will most likely cause
detonation
(FAA-H-8083-25B Chap 7) ( ? )
If the grade of fuel used in an airplane engine is lower than specified for the engine, it will probably cause detonation. Lower grades of fuel ignite at lower temperatures. A higher temperature engine (which should use a higher grade of fuel) may cause lower grade fuel to explode (detonate) rather than burn evenly
An aircraft which is equipped with an Electronic Flight Display (EFD) can
offer new capabilities and simplify the basic flying task.
(FAA-H-8083-25B Chap 2) ( ? )
EFDs offer new capabilities, such as enhanced situational awareness, and simplify basic flying tasks, such as traditional cross-country flight planning and fuel management.
In the Northern Hemisphere, a magnetic compass will normally indicate initially a turn toward the east if
a left turn is entered from a north heading.
(FAA-H-8083-25B Chap 8) ( ? )
In the Northern Hemisphere, a magnetic compass normally initially indicates a turn toward the east if a left (west) turn is entered from a north heading.
If the ignition switch ground wire becomes disconnected, the magneto
may continue to fire.
(FAA-H-8083-25B Chap 7) ( ? )
Loose or broken wires in the ignition system can cause problems. For example, if the ignition switch is OFF, the magneto may continue to fire if the ignition switch ground wire is disconnected. If this occurs, the only way to stop the engine is to move the mixture lever to the idle cut-off position, then have the system checked by a qualified aviation maintenance technician.
The presence of carburetor ice in an aircraft equipped with a fixed-pitch propeller can be verified by applying carburetor heat and noting
a decrease in RPM and then a gradual increase in RPM.
(FAA-H-8083-25B Chap 7) ( ? )
The presence of carburetor ice in an airplane equipped with a fixed-pitch propeller can be verified by applying carburetor heat and noting a decrease in RPM and then a gradual increase. The decrease in RPM as heat is applied is caused by less dense hot air entering the engine and reducing power output. Also, if ice is present, melting water entering the engine may also cause a loss in performance. As the carburetor ice melts, however, the RPM gradually increases until it stabilizes when the ice is completely removed.
Under which condition will pressure altitude be equal to true altitude?
When standard atmospheric conditions exist.
Pressure altitude equals true altitude when standard atmospheric conditions (29.92” Hg AND 15°C at sea level) exist.
If a pilot suspects that the engine (with a fixed-pitch propeller) is detonating during climb-out after takeoff, the initial corrective action to take would be to
lower the nose slightly to increase airspeed.
(FAA-H-8083-25B Chap 7) ( ? )
If you suspect engine detonation during climb-out after takeoff, you would normally decrease the pitch to increase airspeed (more cooling) and decrease the load on the engine. Detonation is usually caused by a poor grade of fuel or an excessive engine temperature.
Which condition would cause the altimeter to indicate a lower altitude than true altitude?
ir temperature warmer than standard.
(FAA-H-8083-25B Chap 8) ( ? )
In air that is warmer than standard temperature, the airplane will be higher than the altimeter indicates. Said another way, the altimeter will indicate a lower altitude than actually flown.
To properly purge water from the fuel system of an aircraft equipped with fuel tank sumps and a fuel strainer quick drain, it is necessary to drain fuel from the
fuel strainer drain and the fuel tank sumps.
(FAA-H-8083-25B Chap 7) ( ? )
One should purge water from both the fuel strainer drain and all the fuel tank sumps on an airplane. This is the purpose of such drains. They are placed at low areas of the fuel system and should be drained prior to each flight.
One purpose of the dual ignition system on an aircraft engine is to provide for
improved engine performance.
(FAA-H-8083-25B Chap 7) ( ? )
Most airplane engines are equipped with dual ignition systems, which have two magnetos to supply the electrical current to two spark plugs for each combustion chamber. The main advantages of the dual system are increased safety and improved burning and combustion of the mixture, which results in improved performance.
The uncontrolled firing of the fuel/air charge in advance of normal spark ignition is known as
A. detonation.
B. pre-ignition.
C. combustion.
pre-ignition.
Answer (B) is correct. (FAA-H-8083-25B Chap 7) ( ? )
Pre-ignition is the ignition of the fuel prior to normal ignition or ignition before the electrical arcing occurs at the spark plug. Pre-ignition may be caused by excessively hot exhaust valves, carbon particles, or spark plugs and electrodes heated to an incandescent, or glowing, state. These hot spots are usually caused by high temperatures encountered during detonation. A significant difference between pre-ignition and detonation is that, if the conditions for detonation exist in one cylinder, they usually exist in all cylinders, but pre-ignition often takes place in only one or two cylinders.
A precaution for the operation of an engine equipped with a constant-speed propeller is to
A. always use a rich mixture with high RPM settings.
B. avoid high manifold pressure settings with low RPM.
C. avoid high RPM settings with high manifold pressure.
B. avoid high manifold pressure settings with low RPM.
Answer (B) is correct. (FAA-H-8083-25B Chap 7) ( ? )
For any given RPM, there is a manifold pressure that should not be exceeded. Manifold pressure is excessive for a given RPM when the cylinder design pressure is exceeded, placing undue stress on them. If repeated or extended, the stress would weaken the cylinder components and eventually cause engine failure.
