Chapter 5 - Operation of Systems
What procedure should be followed concerning a partial loss of power in flight? (AFM)
* Answer refers to Cessna 152 Reference your aircraft's POH If a partial loss of power occurs, the first priority is to establish and maintain a suitable airspeed (best glide airspeed if necessary) Then, select an emergency landing area and remain within gliding distance As time allows, attempt to determine the cause and correct it Complete the following checklist: 1. Check carburetor heat 2. Check the amount of fuel in each tank and switch fuel tanks if necessary 3. Check the fuel selector valve's current position 4. Check the mixture control 5. Check that the primer control is all the way in and locked 6. Check the operation of the magnetos in all three positions; both, left, or right
What type of fuel system does your aircraft have? (AFM)
* Answer refers to Cessna 152 Reference your aircraft's POH The fuel system is a "gravity feed" system Using gravity, the fuel flows from two wing fuel tanks to a fuel shutoff valve which, in the "on" position, allows fuel to flow through a strainer and then to the carburetor From there, the fuel is mixed with air and then flows into the cylinders through the intake manifold tubes
What type of ignition system does your airplane have? (AFM)
*Answer refers to Cessna 152, 172, etc. Reference your aircraft's POH Engine ignition is provided by two engine-driven magnetos, and two spark plugs per cylinder The ignition system is completely independent of the aircraft electrical system The magnetos are engine-driven self-contained units supplying electrical current without using an external source of current However, before they can produce current, the magnetos must be actuated, as the engine crankshaft is rotated by some other means To accomplish this, the aircraft furnished electrical power to operate a starter which, through a series of gears, rotates the engine crankshaft This in turn actuates the armature of the magneto to produce the sparks for ignition of the fuel in each cylinder After the engine starts, the starter system is disengaged, and the battery no longer contributes to the actual operation of the engine
What instruments operate off of the pitot static system? (FAA-H-8083-15)
1. Altimeter 2. Vertical Speed Indicator 3. Airspeed Indicator
Interpret the following ammeter indications (Right & Left deflection, After Starting & During Flight)
1. Ammeter indicates a right deflection (positive) - After Starting - Power from the battery used for starting is being replenished by the alternator; or, if a full-scale charge is indicated for more than 1 minute, the starter is still engaged and a shutdown is indicated - During Flight - A faulty voltage regulator is causing the alternator to overcharge the battery. Reset the system and if the condition continues, terminate the flight as soon as possible 2. Ammeter indicates a left deflection (negative) - After Starting - It is normal during start. At other times this indicates the alternator is not functioning or an overload condition exists in the system. The battery is not receiving a charge - During Flight - The alternator is not functioning or an overload exists in the system. The battery is not receiving a charge. Possible causes: the master switch was accidentally shut off, or the alternator circuit breaker tripped
What are the two main advantages of a dual ignition system? (FAA-H-8083-25)
1. Increased Safety: In case one system fails the engine may be operated on the other until a landing is safely made 2. More complete and even combustion of the mixture, and consequently, improved engine performance; i.e., the fuel/air mixture will be ignited on each side of the combustion chamber and burn toward the center
Explain the limitations pilots should be aware of when using TIS-B for situational awareness. (AIM 4-5-8, AC 90-114)
1. TIS-B is not intended to be used as a collision avoidance system and does not relieve the pilot's responsibility to "See and Avoid" other aircraft, in accordance with 91.113b 2. A pilot may receive an intermittent TIS-B target of themselves, typically when maneuvering (e.g., climbing turns) due to the radar not tracking the aircraft as quickly as ADS-B 3.The ADS-B-to-radar association process within the ground system may at times have difficulty correlating an ADS-B report with corresponding radar returns from the same aircraft. When this happens the pilot may see duplicate traffic symbols (i.e., "TIS-B shadows") on the cockpit display 4. Updates of TIS-B traffic reports will occur less often than ADS-B traffic updates. TIS-B position updates will occur approximately once every 3 to 13 seconds depending on the type of radar system in use within the coverage area. In comparison, the update rate for ADS-B is normally once per second 5. The TIS-B only uplinks data pertaining to transponder-equipped aircraft. Aircraft without a transponder will not be displayed as TIS-B traffic Exam Tip: Be prepared to answer questions about any and all equipment installed in the aircraft. For example, if your aircraft has an autopilot, have an in-depth knowledge of its operation, even if you rarely use it
What instruments contain gyroscopes? (FAA-H-8083-25)
1. Turn Coordinator 2. Heading Indicator (Directional Gyro) 3. Attitude Indicator (Artificial Horizon)
What are some of the most common operational causes of detonation? (FAA-H-8083-25)
1. Using a lower fuel grade than that specified by the aircraft manufacturer 2. Operating with extremely high manifold pressures in conjunction with low RPM 3. Operating the engine at high power settings with an excessively lean mixture 4. Extended ground operations or steep climbs where cylinder cooling is reduced
What color of dye is added to the following fuel grades: 80, 100, 100LL, Turbine? (FAA-H-8083-25, FAA-P-8740-35)
80 (Obsolete): Red 100 (Obsolete): Green 100LL: Blue Jet A: Colorless or Straw
What is the function of a magnetometer? (FAA-H-8083-6)
A magnetometer is a device that measures the strength of the earth's magnetic field to determine aircraft heading; it provides this information digitally to the AHRS, which then sends it to the PFD
How does the carburetor heat system work? (AFM)
A carburetor heat valve, controlled by the pilot, allows unfiltered, heated air from a shroud located around an exhaust riser or muffler to be directed to the induction air manifold prior to the carburetor Carburetor heat should be used anytime suspected or known carburetor icing conditions exist
During a cross-country flight you notice that the oil pressure is low, but the oil temperature is normal. What is the problem and what action should be taken?
A low oil pressure in flight could be the result of any one of several problems, the most common being that of insufficient oil If the oil temperature continues to remain normal, a clogged oil pressure relief valve or an oil pressure gauge malfunction could be the culprit In any case, a landing at the nearest airport is advisable to check for the cause of trouble
How does an altimeter work? (FAA-H-8083-15)
A sensitive altimeter is an aneroid barometer that measures the absolute pressure of the ambient air and displays it in terms of feet above a selected pressure level The sensitive element in a sensitive altimeter is a stack of evacuated, corrugated bronze aneroid capsules The air pressure acting on these aneroids tries to compress them against their natural springiness, which tries to expand them The result is that their thickness changes as the air pressure changes Stacking several aneroids increases the dimension change as the pressure varies over the usable range of the instrument
Describe the function of the following avionics equipment acronyms: AHRS, ADC, PFD, MFD, FD, FMS, INS. (FAA-H-8083-6, DAT)
AHRS - Attitude and Heading Reference System Composed of three-axis sensors that provide heading, attitude, and yaw information for aircraft. AHRS are designed to replace traditional mechanical gyroscopic flight instruments and provide superior reliability and accuracy ADC - Air Data Computer An aircraft computer that receives and process pitot pressure, static pressure, and temperature to calculate precise altitude, indicated airspeed, true airspeed, vertical speed, and air temperature PFD - Primary Flight Display A display that provides increased situational awareness to the pilot by replacing the traditional six instruments with an easy-to-scan display that shows the horizon, airspeed, altitude, vertical speed, trend, trim, rate of turn, and more MFD - Multi-Function Display A cockpit display capable of presenting information (navigation data, moving maps, terrain awareness, etc.) to the pilot in configurable ways; often used in concert with PFD FD - Flight Director An electronic flight computer that analyzes the navigation selections, signals, and aircraft parameters. It presents steering instructions on the flight display as command bars or cross bars for the pilot to position the nose of the aircraft over or follow FMS - Flight Management System A computer system containing a database for programming of routes, approaches, and departures that can supply navigation data to the flight director/autopilot from various sources, and can calculate flight data such as fuel consumption, time remaining, possible range, and other values INS - Inertial Navigation System A computer-based navigation system that tracks the movement of an aircraft via signals produced by onboard accelerometers. The initial location of the aircraft is entered into the computer and all subsequent movement is then sensed and used to keep the aircraft's position updated
Define and state how you would determine the following altitudes: absolute, indicated, pressure, true, and density. (FAA-H-8083-25)
Absolute Altitude - The vertical distance of an aircraft above the terrain Indicated Altitude - The altitude read directly from the altimeter (uncorrected) after it is set to the current altimeter setting Pressure Altitude - The altitude when the altimeter setting window is adjusted to 29.92. Pressure altitude is used for computer solutions to determine density altitude, true altitude, true airspeed, etc. True Altitude - The true vertical distance of the aircraft above sea level. Airport, terrain, and obstacle elevations found on aeronautical charts are true altitudes Density Altitude - Pressure altitude corrected for nonstandard temperature variations. Directly related to an aircraft's takeoff, climb, and landing performance
Can other types of fuel be used if the specified grade is not available? (FAA-H-8083-25)
Airplane engines are designed to operate using a specific grade if fuel as recommended by the manufacturer If the proper grade of fuel is not available, it is possible, but not desirable, to us the next higher grade as a substitute Always reference the aircraft's AFM or POH Auto gas should never be used in aircraft engines unless the aircraft has been modified with an FAA-issued Supplemental Type Certificate (STC)
How does a vacuum system operate? (FAA-H-8083-25)
An engine-driven vacuum pump provides suction which pulls air from the instrument case Normal pressure entering the case is directed against rotor vanes to turn the rotor (gyro) at high speed, much like a water wheel or turbine operates Air is drawn into the instrument through a fiulter from the cockpit and eventually vented outside Vacuum values vary between manufacturers (usually between 4.5 and 5.5" Hg.), but provide rotor speeds from 8,000 to 18,000 RPM
What display information will be lost when an AHRS failure occurs? (FAA-H-8083-6)
An inoperative attitude indicator, shown with red Xs on the PFD, indicates failure of the AHRS
What purpose do fuel tank vents have? (AFM)
As the fuel level in an aircraft fuel tank decreases, a vacuum would be created within the tank which would eventually result in a decreasing fuel flow and finally engine stoppage Fuel system venting provides a way of replacing fuel with outside air, preventing formation of a vacuum
Define the terms anti-icing equipment and deicing equipment and state several examples of each. (FAA-H-8083-3, FAA-H-8083-25)
Anti-Icing Equipment - Prevents ice from forming on certain protected surfaces Examples: heated pitot tubes and static ports, carburetor heat, heated fuel vents, propeller blades with electro-thermal boots, and heated windshields It is normally actuated prior to flight into suspected icing conditions. Reference your AFM/POH Deicing Equipment - Removes ice that has already formed on protected surfaces Generally limited to pneumatic boots on the wing and tail leading edges
What are the errors of the attitude indicator? (FAA-H-8083-15)
Attitude indicators are free from most errors, but depending upon the speed with which the erection system functions, there may be a slight nose-up indication during a rapid acceleration There is also a possibility of a small bank angle and pitch error after a 180° turn These inherent errors are small and correct themselves within a minute or so after returning to straight-and-level flight
What are the two types of ADS-B equipment? (AC 90-114)
Automatic Dependent Surveillance - Broadcast Out (ADS-B OUT) - Automatically broadcasts aircraft's GPS position, altitude, velocity, and other information out to ATC ground-based surveillance stations as well as directly to other aircraft. It is required in all airspace where transponders are required Automatic Dependent Surveillance - Broadcast In (ADS-B IN) - The receipt, processing, and display of ADS-B transmissions. ADS-B In capability is necessary to receive ADS-B traffic and broadcast services (e.g., FIS-B and TIS-B)
What error is the heading indicator subject to? (FAA-H-8083-25)
Because of precession, caused chiefly by friction, the heading indicator will creep or drift from a heading to which it is set Among other factors, the amount of drift depends largely upon the conditions of the instrument The heading indicator may indicate as much as 15° error per every hour of operation
What does the carburetor do? (FAA-H-8083-25)
Carburetion may be defined as the process of mixing fuel and air in the correct proportions so as to form a combustible mixture The carburetor vaporizes liquid fuel into small particles and then mixes it with air. It measures the airflow and meters fuel accordingly.
What conditions are favorable for carburetor icing? (FAA-H-8083-25)
Carburetor ice is most likely to occur when temperatures are below 70°F (21°C) and the relative humidity is above 80% However, due to the sudden cooling that takes place in the carburetor, icing can occur even with temperatures as high as 100°F (38°C) and humidity as low as 50% This temperature drop can be as much as 60° to 70°F
What action should be taken if preignition is suspected? (FAA-H-8083-25)
Corrective actions for preignition include any type of engine operation which would promote cooling such as: 1. Reduce power 2. Reduce the climb rate for better cooling 3. Enrich the fuel/air mixture 4. Open cowl flaps if available
Name several important airspeed limitations not marked on the face of the airspeed indicator. (FAA-H-8083-25)
Design Maneuvering Speed (Vᴬ) - The maximum speed at which the structural design's limit load can be imposed (either by gusts or full deflection of the control surfaces) without causing structural damage Note: Operating at or below Vᴬ does not provide structural protection against multiple full control inputs in one axis or full control inputs in more than one axis at the same time Landing Gear Operating Speed (Vᴸᴼ) - The maximum speed for extending or retracting the landing gear if using aircraft equipped with retractable landing gear Best Angle-of-Climb (Vᵡ) - Important when a short-field takeoff to clear an obstacle is required Best Rate-of-Climb (Vᵞ) - The airspeed that will give the pilot the most altitude in a given period of time
What is detonation? (FAA-H-8083-25)
Detonation is an uncontrolled, explosive ignition of the fuel/air mixture within the cylinder's combustion chamber It causes excessive temperature and pressure which , if not corrected, can quickly lead to failure of the piston, cylinder, or valves In less severe cases, detonation causes engine overheating, roughness, or loss of power Detonation is characterized by high cylinder head temperatures, and is most likely to occur when operating at high power settings
What action should be taken if detonation is suspected? (FAA-H-8083-25)
Detonation may be avoided by following these basic guidelines during the various phases of ground and flight operations: 1. Ensure that the proper grade of fuel is used 2. Keep the cowl flaps (if available) in the full-open position while on the ground to provide the maximum airflow through the cowling 3. Use an enriched fuel mixture, as well as a shallow climb angle, to increase cylinder cooling during takeoff and initial climb 4. Avoid extended, high power, steep climbs 5. Develop the habit of monitoring the engine instruments to verify proper operation according to procedures established by the manufacturer
What are the four main control surfaces and what are their functions? (FAA-H-8083-25)
Elevators - The elevators control the movement of the airplane about its lateral axis (Pitch) Ailerons - The ailerons control the airplane's movement about its longitudinal axis (Roll) Rudder - The rudder controls movement of the airplane about its vertical axis (Yaw) Trim Tabs - Trim tabs are small, adjustable hinged-surfaces on the aileron, rudder, or elevator control surfaces. They are labor saving devices that enable the pilot to release manual pressure on the primary control
If an airplane has anti-icing and/or deicing equipment installed, can it be flown into icing conditions? (FAA-H-8083-3)
Even though it may appear elaborate and complete, the presence of anti-icing and deicing equipment does not necessarily mean that an airplane is approved for flight in icing conditions The AFM/POH, placards, and even the manufacturer should be consulted for specific determination of approvals and limitations
Which standby flight instruments are normally provided in an advanced avionics aircraft? (FAA-H-8083-6)
Every aircraft equipped with electronic flight instruments must also contain a minimal set of backup/standby instruments Usually conventional "round dial instruments", they typically include an attitude indicator, an airspeed indicator, and an altimeter
How does the aircraft cabin heat work? (AFM)
Fresh air, heated by an exhaust shroud, is directed to the cabin through a series of ducts
How will loss of a magnetometer affect the AHRS operation? (FAA-H-8083-6)
Heading information will be lost
What action should be taken if the ammeter indicates a continuous charge while in flight (more than two needle widths)?
If a continuous rate of charge were allowed for any extended period of time, the battery would overheat and evaporate the electrolyte at an excessive rate A possible explosion of the battery could result Also, electronic components in the electrical system would be adversely affected by higher than normal voltage Protection is provided by an overvoltage sensor which will shut the alternator down if an excessive voltage is detected If this should occur, the following should be done: 1. The alternator should be turned off; pull the circuit breaker (the field circuit will continue to draw power from the battery) 2. All electrical equipment not essential to flight should be turned off (the battery is now the only source of electrical power) 3. The flight should be terminated and a landing made as soon as possible *Exam Tip: Expect the examiner to test your knowledge of the aircraft's electrical system by asking several "what of" type of questions such as: What if your alternator failed in flight? What systems, instruments and equipment would be operative/inoperative? After an alternator failure, what systems and equipment will the battery supply power to? How long will the battery supply power? When the battery finally dies, will the engine continue to operate? You get the idea; know you aircraft's electrical system well
What are the various power sources that may be used to power the gyroscopic instruments in an airplane? (FAA-H-8083-25)
In some airplanes, all the gyros are vacuum, pressure, or electrically operated; in others, vacuum or pressure systems provide the power for the heading and attitude indicators, while the electrical system provides the power for the turn coordinator Most airplanes have at least two sources of power to ensure at least one source of bank information if one power source fails
When a display failure occurs, what other system components will be affected? (AFM/POH)
In some systems, failure of a display will also result in partial loss of navigation, communication, and GPS capability Reference your specific AFM/POH
If one display fails (PFD or MFD), what information will be presented on the remaining display? (FAA-H-8083-6)
In the event of a display failure, some systems offer a reversion capability to display the primary flight instruments and engine instruments on the remaining operative display
What are the different types of aircraft speeds? (FAA-H-8083-25)
Indicated Airspeed (IAS) - The speed of the airplane as observed on the airspeed indicator. It is the airspeed without correction for indicator, position (or installation), or compressibility errors Calibrated Airspeed (CAS) - The airspeed indicator reading corrected for position (or installation), and instrument errors. CAS is equal to TAS at sea level in standard atmosphere. The color-coding for various design speeds marked on airspeed indicators may be IAS or CAS Equivalent Airspeed (EAS) - The airspeed indicator reading corrected for position (or installation), or instrument error, and for adiabatic compressible flow for the particular altitude. EAS is equal to CAS at sea level in standard atmosphere True Airspeed (TAS) - CAS corrected for altitude and nonstandard temperature; the speed of the airplane in relation to the air mass in which it is flying
What display information will be affected when an ADC failure occurs? (FAA-H-8083-6)
Inoperative airspeed, altitude, and vertical speed indicators, shown with red Xs on the PFD, indicate the failure of the air data computer
What does the mixture control do? (FAA-H-8083-25)
It regulates the fuel-to-air ratio All airplane engines incorporate a device called a mixture control, by which the fuel/air ratio can be controlled by the pilot during flight The purpose of a mixture control is to prevent the mixture from becoming too rich at high altitudes, due to decreasing air density It is also used to lean the mixture during cross-country flights to conserve fuel and provide optimum power
How is steering accomplished on the ground? (AFM)
Light airplanes are generally provided with nose-wheel steering capabilities through a simple system of mechanical linkage connected to the rudder pedals When a rudder pedal is depressed, a spring-loaded bungee (push-pull rod) connected to the pivotal portion of a nosewheel strut will turn the nosewheel
What are the five basic functions of aircraft engine oil? (FAA-H-8083-25)
Lubricates - the engine's moving parts Cools - the engine by reducing friction Removes - heat from the cylinders Seals - provides a seal between the cylinder walls and pistons Cleans - by carrying off metal and carbon particles and other oil contaminants
How does the magnetic compass work? (FAA-H-8083-25)
Magnetized needles fastened to a float assembly, around which is mounted a compass card, align themselves parallel to the earth's lines of magnetic force The float assembly is housed in a bowl filled with acid-free white kerosene
What are the limitations of a pressure altimeter? (FAA-H-8083-15)
Nonstandard pressure and temperature; temperature variations expand or contract the atmosphere and raise or lower pressure levels that the altimeter senses On a warm day - The pressure level is higher than on a standard day. The altimeter indicates lower than actual altitude On a cold day - The pressure level is lower than on a standard day. The altimeter indicates higher than actual altitude Changes in surface pressure also affect pressure levels at altitude Higher than standard pressure - The pressure level is higher than on a standard day. The altimeter indicates lower than actual altitude Lower than standard pressure - The pressure level is lower than on a standard day. The altimeter indicates higher than actual altitude Remember: High to low or hot to cold, look out below!
What changes occur to the fuel/air mixture when applying carburetor heat? (FAA-H-8083-25)
Normally, the introduction of heated air into the carburetor will result in a richer mixture Warm air is less dense, resulting in less air for the same amount of fuel Use of carburetor heat can cause a decrease in engine power of up to 15%
What are the various compass errors? (FAA-H-8083-15)
Oscillation Error - Erratic movement of the compass card caused by turbulence or rough control technique Deviation Error - Due to electrical and magnetic disturbances in the aircraft Variation Error - Angular difference between true and magnetic north; reference isogonic lines of variation Dip Errors: Acceleration Error - On east or west headings, while accelerating, the magnetic compass shows a turn to the north, and when decelerating, it shows a turn to the south Remember: ANDS Accelerate North Decelerate South Northerly Turning Error - The compass leads in the south half of a turn, and lags in the north half of a turn Remember: UNOS Undershoot North Overshoot South
What are the errors of the airspeed indicator?
Position Error - Caused by the static ports sensing erroneous static pressure; slipstream flow causes disturbances at the static port preventing actual atmospheric pressure measurement. It varies with airspeed, altitude, and configuration, and may be a plus or minus value Density Error - Changes in altitude and temperature are not compensated for by the instrument Compressibility Error - Caused by the packing of air into the pitot tube at high airspeeds, resulting in higher than normal indications. It is usually not a factor at slower speeds
What is preignition? (FAA-H-8083-25)
Preignition occurs when the fuel/air mixture ignites prior to the engine's normal ignition event resulting in reduced engine power and high operating temperatures Premature burning is usually caused by a residual hotspot in the combustion chamber, often created by a small carbon deposit on a spark plug, a cracked spark plug insulator, or other damage in the cylinder that causes a part to heat sufficiently to ignite the fuel/air charge As with detonation, preignition may also cause severe engine damage, because the expanding gases exert excessive pressure on the piston while still on its compression stroke
What type of hydraulic fluid does your aircraft use and what color is it? (FAA-H-8083-25, FAA-H-8083-31)
Refer to your AFM/POH A mineral-based hydraulic fluid (MIL-H-5606) is the most widely used type for small aircraft It has an odor similar to penetrating oil and is dyed RED A newer, fire-resistant fluid (MIL-H-83282) is also used in small aircraft and is dyed red
Does an aircraft have to remain stationary during AHRS system initialization? (FAA-H-8083-6)
Some AHRSs must be initialized on the ground prior to departure The initialization procedure allows the system to establish a reference attitude used as a benchmark for all future attitude changes Other systems are capable of initialization while taxiing as well as in flight
What procedures should be followed if an engine fire develops on the ground during starting? (AFM)
Reference your aircraft's POH Continue to attempt an engine start as a start will cause flames and excess fuel to be sucked back through the carburetor 1. If the engine starts: - Increase the power to a higher RPM for a few moments; and - Shut down the engine and inspect it 2. If the engine does not start: - Set the throttle to the "Full" position - Set the mixture control to "Idle cutoff" - Continue to try an engine start in an attempt to put out the fire by vacuum 3. If the fire continues: - Turn the ignition switch to "Off" - Turn the master switch to "Off" - Set the fuel selector to "Off" In all cases, evacuate the aircraft and obtain a fire extinguisher and/or assistance
Describe the electrical system on your aircraft. (AFM)
Reference your aircraft's POH Electrical energy is provided by a 28-volt, direct-current system powered by an engine-driven 60-amp alternator and a 24-volt battery
What procedure should be followed if an engine fire develops in flight? (AFM)
Reference your aircraft's POH In the event of an engine fire in flight, the following procedures should be used: 1. Set the mixture control to "Idle Cutoff" 2. Set the fuel selector valve to "Off" 3. Turn the master switch to "Off" 4. Set the cabin heat and air vents to "Off"; leave the overhead vents "On" 5. Establish an airspeed of 100 KIAS and increase the descent, if necessary, to find an airspeed that will provide for an incombustible mixture 6. Execute a forced landing and procedures checklist
How are the circuits for the various electrical accessories within the aircraft protected? (AFM)
Reference your aircraft's POH Most of the electrical circuits in an airplane are protected from an overload condition by either circuit breakers or fuses or both Circuit breakers perform the same function as fuses except that when an overload occurs, a circuit breaker can be reset
The electrical system provides power for what equipment in an airplane? (AFM)
Reference your aircraft's POH Normally the following: 1. Radio Equipment 2. Turn Coordinator 3. Fuel Gauges 4. Pitot Heat 5. Landing Light 6. Taxi Light 7. Strobe Lights 8. Interior Lights 9. Instrument Lights 10. Position Lights 11. Flaps (Maybe) 12. Stall Warning System (Maybe) 13. Oil Temperature Gauge 14. Electric Fuel Pump (Maybe)
What type fuel does your aircraft require (minimum octane rating and color)? (AFM)
Reference your aircraft's POH The approved fuel grade used is 100LL and the color is blue
What are the two fundamental properties of a gyroscope? (FAA-H-8083-25)
Rigidity in Space - A gyroscope remains in a fixed position in the plane in which it is spinning Precession - The tilting or turning of a gyro in response to a deflective force. The reaction to this force does not occur at the point where it was applied; rather, it occurs at a point that is 90° later in the direction of rotation. The rate at which the gyro precesses is inversely proportional to the speed of the rotor and proportional to the deflective force
Does your aircraft use a fuel pump? (AFM)
SFS Cessna 172S G1000: Yes * Answer refers to Cessna 152 Reference your aircraft's POH No, the fuel is transferred from the wing tanks to the carburetor by the "gravity-feed" system The gravity system does not require a fuel pump because the fuel is always under positive pressure to the carburetor For some aircraft where for some reason it is not possible to place the wings above the carburetor, or for which a greater pressure is required than what gravity feed can supply, it is necessary to utilize engine-driven fuel pumps and auxiliary fuel pumps as backups
What will the turn indicator indicate when the aircraft is in a "skidding" or a "slipping" turn? (FAA-H-8083-25)
Slip - The ball in the tube will be on the inside of the turn; not enough rate of turn for the amount of bank Skid - The ball in the tube will be to the outside of the turn; too much rate of turn for the amount of bank
Briefly describe Traffic Information Services-Broadcast (TIS-B). (AIM 4-5-6, 4-5-8, AC 90-114)
TIS-B is the broadcast of ATC derived traffic information to ADS-B equipped (1090ES or UAT) aircraft from ground radio stations The source of this traffic information is derived from ground-based air traffic surveillance sensors TIS-B service is available throughout the NAS where there is both adequate surveillance coverage from ground sensors and adequate broadcast coverage from ADS-B ground radio stations Note: TIS-B is not related to Traffic Information Service (TIS). TIS is only available at specific terminal mode S radar sites. Though similar in some ways, TIS is not related to TIS-B. See AIM 4-5-6
How does the pilot control temperature in the cabin? (AFM)
Temperature is controlled by mixing outside air (cabin air control) with heated air (cabin heat control) in a manifold near the cabin firewall This air is then ducted to vents located on the cabin floor
What are the limitations of the vertical speed indicator(VSI)? (FAA-H-8083-25)
The VSI is not accurate until the aircraft is stabilized Because of the restriction in airflow to the static line, a 6 to 9 second lag is required to equalize or stabilize the pressures Sudden or abrupt changes in aircraft attitude will cause erroneous instrument readings as airflow fluctuates over the static port Both rough control technique and turbulent air result in unreliable needle indications
How does the airspeed indicator operate? (FAA-H-8083-25)
The airspeed indicator is a sensitive, differential pressure gauge which measures the difference between impact pressure from the pitot head and undisturbed atmospheric pressure from the static source The difference is registered by the airspeed pointer on the face of the instrument
What is the limitation of the airspeed indicator? (FAA-H-8083-15)
The airspeed indicator is subject to proper flow of air in the pitot/static system
What actions should be taken if the ammeter indicates a continuous discharge while in flight?
The alternator has quit producing a charge, so the alternator circuit breaker should be checked and reset if necessary If this does not correct the problem, the following should be accomplished: 1. The alternator should be turned off; pull the circuit breaker (the field circuit will continue to draw power from the battery) 2. All electrical equipment not essential to flight should be turned off (the battery is now the only source of electrical power) 3. The flight should be terminated and a landing made as soon as possible
What does the ammeter indicate? (AFM)
The ammeter indicates the flow of current, in amperes, from the alternator to the battery or from the battery to the electrical system With the engine running and master switch on, the ammeter will indicate the charging rate to the battery If the alternator has gone off-line and is no longer functioning, or the electrical load exceeds the output of the alternator, the ammeter indicates the discharge rate of the battery
What are the limitations of the heading indicator? (FAA-H-8083-25)
The bank and pitch limits of the heading indicator vary with the particular design and make of instrument On some heading indicators found in light airplanes, the limits are approximately 55° of pitch and 55° of bank When either of these attitude limits is exceeded, the instrument "tumbles" or "spills" and no longer gives the correct indication until reset After spilling, it may be reset with the caging knob Many of the modern instruments used are designed in such a manner that they will not tumble
Why is the generator/alternator voltage output slightly higher than the battery voltage? (FAA-H-8083-25)
The difference in voltage keeps the battery charged For example, a 12-volt battery would be supplied with 14 volts
When powering up an aircraft with an FMS/RNAV unit installed, how will you verify the effective dates of the navigation database? (FAA-H-8083-6)
The effective dates for the navigation database are typically shown on a start-up screen that is displayed as the system cycles through its start-up self-test
How are the various flight controls operated? (AFM)
The flight control surfaces are manually actuated through use of either a rod or cable system A control wheel actuates the ailerons and elevator, and rudder/brake pedals actuate the rudder
Describe the braking system on this aircraft. (AFM)
The following answer is for the Cessna 152 Hydraulically actuated disc-type brakes are utilized on each main gear wheel A hydraulic line connects each brake to a master cylinder located on each pilot's rudder pedals By applying pressure to the top of either the pilot's or copilot's set of rudder pedals, the brakes may be applied
Describe the landing gear system on this airplane. (AFM)
The following answer is for the Cessna 152 The landing gear consists of a tricycle-type system utilizing two main wheels and a steerable nosewheel Tubular spring steel main gear struts provide main gear shock absorption, while nose gear shock absorption is provided by a combination air/oil shock strut
What type of engine does your aircraft have? (AFM)
The following answer is for the Cessna 172S Textron Lycoming IO-360-L2A LHAND L - Lycoming H - Horizontally Opposed A - Air Cooled N - Normally Aspirated D - Direct Drive - Fuel Injected - 360 Cubic Inch - 180 HP @ 2700 RPM - 2x Magnetos - 4x Cylinders - 8x Spark Plugs Propeller: McCauley Propeller Systems Number of Blades: 2 Propeller Diameter: 76 Inches Propeller Type: Fixed Pitch
What four strokes must occur in each cylinder of a typical four stroke engine in order for it to produce full power? (FAA-H-8083-25)
The four strokes are: Intake - Begins as the piston starts its downward travel causing the intake valve to open and the fuel-air mixture to be drawn into the cylinder Compression - Begins when the intake valve closes, and the piston starts moving back to the top of the cylinder. This phase of the cycle is used to obtain a much greater power output from the fuel Power/Ignition - Begins when the fuel-air mixture is ignited which causes a tremendous pressure increase in the cylinder and forces the piston downward away from the cylinder head, creating the power that turns the crankshaft Exhaust - Is used to purge the cylinder of burned gases and begins when the exhaust valve opens, and the piston starts to move toward the cylinder head once again *Remember: Suck, Squeeze, Bang, Blow
Describe a fuel injection system installed in some aircraft. (FAA-H-8083-25)
The fuel injection system injects fuel directly into the cylinders, or just ahead of the intake valve It incorporates six basic components: 1. Engine-Driven Fuel Pump - Provides fuel under pressure from the fuel tank to the fuel/air control unit 2. Fuel/Air Control Unit - Meters fuel based on the mixture control setting and sends it to the fuel manifold valve at a rate controlled by the throttle 3. Fuel Manifold Valve - Distributes fuel to the individual fuel discharge nozzles 4. Discharge Nozzles - Located in each cylinder head, these inject the fuel/air mixture at the precise time for each cylinder directly into each cylinder intake port 5. Auxiliary Fuel Pump - Provides fuel under pressure to fuel/air control unit for engine starting and/or emergency use 6. Fuel Pressure/Flow Indicators - Measures metered fuel pressure/flow
How does the attitude indicator work? (FAA-H-8083-25)
The gyro in the attitude indicator is mounted on a horizontal plane and depends upon rigidity in space for its operation The horizon bar represents the true horizon. This bar is fixed to the gyro and remains in a horizontal plane as the airplane is pitched or banked about its lateral or longitudinal axis, indicating the attitude of the airplane relative to the true horizon
What limitations does the magnetic compass have? (FAA-H-8083-15)
The jewel-and-pivot type mounting allows the float freedom to rotate and tilt up to approximately 18° angle of bank At steeper bank angles, the compass indications are erratic and unpredictable
During the before-takeoff run-up, you switch the magnetos from the "BOTH" position to the "RIGHT" position and notice there is no RPM drop. What condition does this indicate?
The left P-lead is not grounding, or the engine has been running only on the right magneto because the left magneto has totally failed
What is the function of the manual primer, and how does it operate? (AFM)
The manual primer's main function is to provide assistance in starting the engine The primer draws fuel from the fuel strainer and injects it directly into the cylinder intake ports This usually results in a quicker, more efficient engine start
How does the heading indicator operate? (FAA-H-8083-25)
The operation of the heading indicator uses the principle of rigidity in space The rotor turns in a vertical plane, and the compass card is fixed to the rotor. Since the rotor remains rigid in space, the points on the card hold the same position in space relative to the vertical plane As the instrument case and the airplane revolve around the vertical axis, the card provides clear and accurate heading information
What are the limitations of an attitude indicator? (FAA-H-8083-25)
The pitch and bank limits depend upon the make and model of the instrument Limits in the banking plane are usually from 100°-110°, and the pitch limits are usually from 60° to 70° If either limit is exceeded, the instrument will tumble or spill and will give incorrect indications until reset A number of modern attitude indicators will not tumble
For aircraft with electronic flight instrumentation, what is the function of the standby battery? (FAA-H-8083-15)
The standby battery is held in reserve and kept charged in case of a failure of the charging system and a subsequent exhaustion of the main battery The standby battery is brought online when the main battery voltage is depleted to a specific value, approximately 19 volts Generally, the standby battery switch must be in the ARM position for this to occur but pilots should refer to the aircraft flight manual (AFM) for specifics on an aircraft's electrical system
What does the throttle do? (FAA-H-8083-25)
The throttle allows the pilot to manually control the amount of fuel/air charge entering the cylinders This in turn regulates the engine speed and power
What information does the turn coordinator provide?(FAA-H-8083-25)
The turn coordinator shows the yaw and roll of the aircraft around the vertical and longitudinal axes The miniature airplane will indicate direction of the turn as well as rate of turn When aligned with the turn index, it represents a standard rate of turn of 3° per second The inclinometer of the turn coordinator indicates the coordination of aileron and rudder The ball indicates whether the airplane is in coordinated flight or is in a slip or skid
How does the turn coordinator operate? (FAA-H-8083-15)
The turn part of the instrument uses precession to indicate direction and approximate rate of turn A gyro reacts by trying to move in reaction to the force applied thus moving the needle or miniature aircraft in proportion to the rate of turn The slip/skid indicator is a liquid-filled tube with a ball that reacts to centrifugal force and gravity
What causes carburetor icing, and what are the first indications of its presence? (AFM)
The vaporization of fuel, combined with the expansion of air as it passes through the carburetor, causes a sudden cooling of the mixture The temperature of the air passing through the carburetor may drop as much as 60°F within a fraction of a second Water vapor is squeezed out by this cooling, and if the temperature in the carburetor reaches 32°F or below, the moisture will be deposited as frost or ice inside the carburetor For airplanes with a fixed-pitch propellor, the first indication of carburetor icing is loss of RPM For airplanes with controllable-pitch (constant-speed) propellers, the first indication is usually a drop in manifold pressure
How does the vertical speed indicator work? (FAA-H-8083-15)
The vertical speed indicator is a pressure differential instrument Inside the instrument case is an aneroid very much like the one in an airspeed indicator Both the inside of this aneroid and the inside of the instrument case are vented to the static system, but the case is vented through a calibrated orifice that causes the pressure inside the case to change more slowly than the pressure inside the aneroid As the aircraft ascends, the static pressure becomes lower and the pressure inside the case compresses the aneroid, moving the pointer upward, showing a climb and indicating the number of feet per minute the aircraft is ascending
What function does the voltage regulator have?
The voltage regulator is a device which monitors system voltage, detects changes, and makes the required adjustments in the output of the alternator to maintain a constant regulated system voltage It must do this at low RPM, such as during taxi, as well as at high RPM in flight In a 28-volt system, it will maintain 28 volts +/- 0.5 volts
What are flaps and what is their function? (FAA-H-8083-25)
The wing flaps are moveable panels on the inboard trailing edges of the wings They are hinged so that they may be extended downward into the flow of air beneath the wings to increase both lift and drag Their purpose is to permit a slower airspeed and a steeper angle of descent during a landing approach In some cases they may also be used to shorten the takeoff distance
Describe how an aircraft deicing system works. (FAA-H-8083-3)
Upon pilot actuation, boots attached to the wing leading edge inflate with air from a pneumatic pump(s) to break off accumulated ice After a few seconds of inflation, they are deflated back to their normal position with vacuum assistance The pilot monitors the buildup of ice and cycles the boots as directed in the AFM/POH
What method is used to determine that carburetor ice has been eliminated? (FAA-H-8083-25)
When heat is first applied, there will be a drop in RPM in airplanes equipped with a fixed-pitch propeller; there will be a drop in manifold pressure in the airplanes equipped with a controllable-pitch propeller If ice is present there will be a rise in RPM or manifold pressure after the initial drop (often accompanied by intermittent engine roughness); and then, when the carburetor heat is turned "off", the RPM or manifold pressure will rise to a setting greater that that before application of heat The engine should run more smoothly after the ice has been removed
What airspeed limitations apply to the color-coded marking system of the airspeed indicator? (FAA-H-8083-25)
White Arc - Flap Operating Range Lower A/S Limit White Arc - (Vs₀) Stall speed in landing configuration Upper A/S Limit White Arc - (Vꜰᴇ) Maximum flap extension speed Green Arc - Normal Operating Range Lower A/S Limit Green Arc - (Vs₁) Stall speed clean or specified configuration Upper A/S Limit Green Arc - (Vɴᴏ) Normal operations speed or maximum structural cruise speed Yellow Arc - Caution Range (Operations in smooth air only) Red Line - (Vɴᴇ) Never Exceed Speed; above this speed, structural failure may occur
If a non-turbine piston engine powered airplane is accidentally fueled with JET-A fuel, will it start? (FAA-H-8083-25, FAA-P-8740-35)
Yes Reciprocating engines may run briefly on jet fuel, but detonation and overheating will soon cause power failure When an aircraft that requires Avgas is inadvertently fueled with JET-A, there is usually a small amount of Avgas remaining in the aircraft's fuel system (tanks, fuel lines, carburetor, etc.) This remaining fuel can enable an aircraft to taxi, perform an engine run-up, and possibly even take off before experiencing a catastrophic engine failure Note: Other than the kerosene smell and the oily feel when rubbed between the fingers, it can be very difficult to visually identify an accidental mixture of 100LL Avgas 9blue) and JET-A (straw color)
