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56 Cards in this Set
- Front
- Back
Which elements of the military standard 1553 data bus coordinates the flow of information |
Bus controller |
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When the bus controller detects a transmission error while communicating with a remote terminal on the military standard 1553B data bus the bus controller |
Transmits the command multiple times and then tries the back up data bus |
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Which elements of the military standard 1553B data bus is capable of being used as a back up bus controller |
Remote terminal |
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Which type of data bus stub is used for stubs less than 1 foot in length on the military standard 1553B databus |
Direct coupled stub |
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Each type of word used on the military standard 1553 B Data bus is |
20 bits long with a 3 bit command sync character, 16 information bits, and one parity bit |
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In a military standard 1553B databus command word, the field that refers to a function or area within the remote terminal to which the command is being directed is the |
Sub address/mode field |
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Military standard 1553B data bus status words are only transmitted in response to a command from the |
Bus controller |
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Which word on the military standard 1553B data bus contains the actual information to be transferred between remote terminals and the bus controller |
Data word |
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Data that must be sent between two processors in the ethernet local area network must flow through the |
Digital switching module |
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What type of data bus allows for faster transmission of data than traditional data buses |
Ethernet |
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The video symbology display system displays a visual representation of navigational Data airspeed altitude attitude and |
Various cautions |
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What's data plus provides the video symbology display system symbol generator unit with inertial navigation data |
Military standard 1553B data bus |
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What do mission computers manage |
Overall control of the aircraft systems and displays |
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What is the main software that controls the activities of the mission computer for pre-flight and taxi |
Operational flight program |
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Failure of either mission computer central processor will result in complete loss of |
Military standard 1553B databus related functions |
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Where do fuel savings advisory system computations take place in order to provide continuous in-flight advisories for minimized fuel consumption |
Fuel management advisory computer |
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How is fuel savings advisory data transmitted from your management advisory computer to the central display units |
Over the fuel savings advisory system data bus |
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When does the integrated diagnostic system illuminate lights on the instrument panel |
When the fault is classified as a caution or warning |
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Where are integrated diagnostic system fault codes recorded |
On the dual slotted the Data transfer system |
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As you increase in altitude static pressure |
Decreases |
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The standard datum plane is a theoretical plane where the atmospheric pressure is |
29.92 inches of mercury/HG and the temperature is +15°C |
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The pressure of the alternate static source is lower than |
Atmospheric pressure |
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Static pressure is |
Greater at lower altitudes and less at higher altitudes |
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What air data computer module converts pedal pressure input into a usable electrical signal |
Total transducer assembly |
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When the failure annunciator on the front of the air data computer is reset it shows |
A solid black |
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Why does the air data computer provide impact pressure to the stability augmentation system |
For roll and yaw stability functions |
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The TTU – 205 test set is capable of controlling and measuring |
Altitude and airspeed |
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When can the TTU 205 test set be disconnected from aircraft systems and instruments |
At ambient pressure |
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What color code does the TTU – 205 test set static hose assembly use |
red |
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When must the TTU – 205 test set auto exercise be performed |
When power has been off for more than one hour |
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What type of measurement is used for the altimeter barometric scale |
Inches of mercury |
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In which mode must be altimeter be in to receive data from the corresponding air data computer to drive the display |
Normal |
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The difference in pressure between the inside and outside of the vertical velocity indicators diaphragm is representative of the rate of change of |
Altitude |
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The ratio of speed of the aircraft to the speed of sound is known as |
Mach number |
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The maximum allowable airspeed of an aircraft is lower |
At higher altitudes |
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What type of pressure enters the airspeed indicator diaphragm |
Pitot |
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The altitude aneroid ensures accurate airspeed indicator operation regardless of |
Mach |
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What type of error is caused by the location and manner in which a pitot tube is installed |
Installation error |
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Which errors must be corrected for an airspeed indicator to display true airspeed |
Temperature and altitude |
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The sensing elements in the true airspeed indicator are surrounded by |
Static pressure |
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What condition causes and uncorrected airspeed indicator to read higher than it should |
Decreased temperature |
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What input does an air data computer need to compute true airspeed |
Total air temperature |
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Indicators displaying total air temperature are calibrated in |
Two–degree increments from -70°C to +80°C |
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Each total air temperature probe contains |
Two variable resistance type sensing elements |
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If a fault condition exists, the fault indicators on the front of the flight data acquisition unit are solid |
White |
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How is the underwater locator beacon of the flight data recorder activated |
Water immersion |
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Which caution/advisory warning lights indicate actuation and normal operation of aircraft equipment |
Green |
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What is the purpose of the caution advisory panel test switch |
To check for proper light bulb operation |
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What extinguishes caution advisory panel annunciations |
Reset by associated system |
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At what altitudes is the ground proximity warning system active |
15–2450 feet |
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What is the highest priority warning given by the ground proximity warning system |
"Whoop-whoop, pull up." |
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Which ground proximity warning system mode sounds the alert "don't sink" |
Mode three descent after takeoff |
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Which ground proximity warning system mode becomes active when an instrument landing system frequency has been selected and the aircraft is below 1000 feet |
Mode five descent below glideslope |
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The column shakers are prevented from operating continuously in phase with each other by |
Having the copilots Shaker run slower than the pilots shaker |
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Stall warning computer produces a shaker signal if the aircraft angle of attack and the permissible AOA are |
Equal |
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The stall warning computer produces a pusher signal if the aircraft angle of attack equals the permissible aoa for at least |
Five seconds |