# 2a354 CDC Set 1

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The American Air force is a major factor that gained the country its super power status for a long time. The 2a3554 CDC Set 1 quiz below is on the A-10 thunderbolt fighter jet. Learn more below.

• 1.

### Which of the following best describes the function of the A–10 EGI’s inertial cluster (ISA)?

• A.

Measures aircraft acceleration and attitude.

• B.

Provides the time mark and time-of day signals.

• C.

Provides the interface to the dual redundant 1553 serial digital data buses.

• D.

Produces the analog and synchro signals required by the flight instruments.

A. Measures aircraft acceleration and attitude.
Explanation
The A-10 EGI's inertial cluster (ISA) is responsible for measuring the aircraft's acceleration and attitude. This means that it detects and records changes in the aircraft's speed and direction, as well as its orientation in relation to the horizon. By accurately measuring these parameters, the ISA provides crucial information for navigation, control, and flight stability. It helps pilots to maintain proper aircraft performance and safety during flight.

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• 2.

### In the event the master bus controller (MBC) fails, which component will assume control of the A–10 digital data bus?

• A.

• B.

Control display unit.

• C.

Flight director computer.

• D.

Embedded GPS/INU unit.

D. Embedded GPS/INU unit.
Explanation
If the master bus controller (MBC) fails, the component that will assume control of the A-10 digital data bus is the Embedded GPS/INU unit. This unit is responsible for providing navigation and inertial guidance information, and in the event of a failure of the MBC, it will take over the control of the data bus to ensure that the necessary information is still being transmitted and received correctly.

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• 3.

### Which A–10 EGI system component provides the power-on discretes for the control display unit (CDU), embedded global positioning system/inertial navigation (EGI) and functional switching for the CDU?

• A.

EGI control panel.

• B.

NAV mode select panel.

• C.

Avionics auxiliary panel.

• D.

EGI/INS mode control panel.

C. Avionics auxiliary panel.
Explanation
The Avionics auxiliary panel provides the power-on discretes for the control display unit (CDU), embedded global positioning system/inertial navigation (EGI), and functional switching for the CDU. It is responsible for supplying power and control signals to these components, allowing them to function properly. The EGI control panel, NAV mode select panel, and EGI/INS mode control panel do not have this specific function, making them incorrect choices.

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• 4.

### Which A–10 embedded global positioning system/inertial navigation (EGI) system component’s purpose is to select the navigation information to be displayed on the horizontal situation indicator (HSI) and attitude director indicator (ADI)?

• A.

EGI control panel.

• B.

NAV mode select panel.

• C.

Avionics auxiliary panel.

• D.

EGI/INS mode control panel.

B. NAV mode select panel.
Explanation
The NAV mode select panel is the component responsible for selecting the navigation information to be displayed on the horizontal situation indicator (HSI) and attitude director indicator (ADI). This panel allows the pilot to choose the desired navigation mode, such as GPS or inertial navigation system (INS), and determines which information is shown on the HSI and ADI. The other options listed are not specifically designed for this purpose, making the NAV mode select panel the correct answer.

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• 5.

### If the A–10 embedded global positioning system/inertial navigation (EGI) magnetic heading is invalid, what indicator will be displayed on the horizontal situation indicator (HSI)?

• A.

• B.

Course deviation flag.

• C.

Bearing pointer No. 2.

• D.

Power OFF warning flag.

D. Power OFF warning flag.
Explanation
If the A-10 embedded global positioning system/inertial navigation (EGI) magnetic heading is invalid, the power OFF warning flag will be displayed on the horizontal situation indicator (HSI). This flag indicates that the power to the EGI system has been turned off, which would explain why the magnetic heading is invalid.

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• 6.

### What A–10 embedded global positioning system/inertial navigation (EGI) system components purpose is to convert navigation information received from the EGI to usable pitch and bank steering commands and flag warning signals for the attitude director indicator (ADI)?

• A.

• B.

Control Display Unit.

• C.

Flight Director Computer.

• D.

Embedded GPS/INU Unit.

C. Flight Director Computer.
Explanation
The Flight Director Computer is responsible for converting navigation information received from the EGI to usable pitch and bank steering commands and flag warning signals for the attitude director indicator (ADI). The other options, such as the GPS Receiver, Control Display Unit, and Embedded GPS/INU Unit, do not have this specific function.

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• 7.

### If an A–10 pilot designates the position of a landmark or object identified by the low altitude safety and targeting enhancement (LASTE) system, what type of mark point did the pilot designate?

• A.

Offset.

• B.

Position.

• C.

• D.

Designation.

A. Offset.
Explanation
The correct answer is "Offset." In this scenario, when an A-10 pilot designates the position of a landmark or object identified by the LASTE system, they are designating an offset mark point. This means that the pilot is indicating a specific location that is offset from the target or landmark, rather than directly over it or simply designating its position. The offset mark point allows for more precise targeting and navigation.

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• 8.

### If the A–10 embedded global positioning system/inertial navigation/global positioning system (EGI/GPS) is not loaded with a GPS almanac from the data transfer system (DTS), what will the EGI system have trouble completing?

• A.

Acquiring satellites.

• B.

Performing start-up BIT.

• C.

• D.

Completing NAV valid test.

A. Acquiring satellites.
Explanation
If the A-10 embedded global positioning system/inertial navigation/global positioning system (EGI/GPS) is not loaded with a GPS almanac from the data transfer system (DTS), the EGI system will have trouble acquiring satellites. The GPS almanac contains information about the location and status of all GPS satellites in orbit. Without this information, the EGI system will not be able to accurately determine the position of the aircraft by acquiring signals from the satellites. This can result in difficulties in navigation and determining the aircraft's location.

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• 9.

### When the A–10 embedded global positioning system/inertial navigation/global positioning (EGI) system begins satellite tracking and data is processed by the embedded global positioning system/inertial navigation/global positioning system (EGI/GPS) to provide an estimated satellite position to start GPS operation, which mode is the GPS operating in?

• A.

NAV.

• B.

INIT.

• C.

TEST.

• D.

STBY.

B. INIT.
Explanation
When the A-10 EGI system begins satellite tracking and processes the data to provide an estimated satellite position to start GPS operation, it is operating in the INIT mode. This mode is used for initializing the GPS system and determining the initial position and time. Once the initialization is complete, the system can switch to other modes like NAV for normal navigation, TEST for diagnostic testing, or STBY for standby mode.

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• 10.

### When EGI is selected as the present position keeping source and the HUD operating in the NAV mode, which A–10 HUD symbol consists of a 10-mil circle with three lines extending outward from the circle at the 12, 3, and 9 o’clock positions?

• A.

Destination index.

• B.

Steer point identifier.

• C.

Total velocity vector.

• D.

C. Total velocity vector.
Explanation
The correct answer is Total velocity vector. When the EGI is selected as the present position keeping source and the HUD is operating in the NAV mode, the A-10 HUD symbol that consists of a 10-mil circle with three lines extending outward from the circle at the 12, 3, and 9 o'clock positions represents the total velocity vector. This symbol provides information about the aircraft's current velocity, including speed and direction.

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• 11.

### When the new target elevation is flashing in the A–10 head up display (HUD), the pilot can store the hot elevation in the selected steer point by pressing the

• A.

DATA key.

• B.

ENTR key.

• C.

STEER key.

• D.

ACCEPT key.

B. ENTR key.
Explanation
When the new target elevation is flashing in the A-10 head up display (HUD), the pilot can store the hot elevation in the selected steer point by pressing the ENTR key.

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• 12.

### What will the A–10 1553 data bus transmitting remote terminal do if it detects a failure on its A-channel?

• A.

Switch to its B-channel.

• B.

Try the A-channel again.

• C.

Revert to built-in-test mode.

• D.

Stop data bus communication.

A. Switch to its B-channel.
Explanation
If the A–10 1553 data bus transmitting remote terminal detects a failure on its A-channel, it will switch to its B-channel. This means that it will start using the B-channel for data bus communication instead of the A-channel. This allows for uninterrupted communication even in the event of a failure on the A-channel.

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• 13.

### What A–10 1553 data bus word format contains the actual information to be transferred between the remote (RT) and bus controller (BC) or between RTs?

• A.

Data word format.

• B.

Status word format.

• C.

Control word format.

• D.

Command word format.

A. Data word format.
Explanation
The actual information to be transferred between the remote (RT) and bus controller (BC) or between RTs is contained in the Data word format. This format is used to transmit the data payload and is separate from the other formats such as Status word format, Control word format, and Command word format. The Data word format ensures that the correct information is transferred accurately and efficiently between the devices on the A-10 1553 data bus.

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• 14.

### Which A–10 1553 data bus component is the master bus controller (MBC) for the Avionics data bus No. 1?

• A.

Embedded global positioning system/inertial navigation (EGI).

• B.

Control display unit (CDU).

• C.

Central interface control unit (CICU).

• D.

Integrated flight and fire control computer (IFFCC).

B. Control display unit (CDU).
Explanation
The Control Display Unit (CDU) is the master bus controller (MBC) for the Avionics data bus No. 1. This means that it is responsible for controlling and coordinating the communication between various components on the data bus. It acts as the central hub for data transmission and ensures that data is properly routed and distributed to the appropriate devices. The CDU plays a crucial role in managing the flow of information on the data bus, making it the correct answer for this question.

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• 15.

### Which A–10 1553 data bus avionics data bus provides interfacing with the AN/ARC–210 system 1 VHF/UHF radio?

• A.

AVâ€“1.

• B.

AVâ€“2.

• C.

AVâ€“3.

• D.

AVâ€“4.

B. AVâ€“2.
Explanation
The AN/ARC-210 system 1 VHF/UHF radio is interfaced with the AV-2 A-10 1553 data bus avionics data bus.

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• 16.

### Which A–10 1553 data bus component is the bus controller for the Avionics data bus No. 3?

• A.

Control display unit (CDU).

• B.

Embedded global positioning system/inertial navigation (EGI).

• C.

Central interface control unit (CICU).

• D.

Integrated flight and fire control computer (IFFCC).

C. Central interface control unit (CICU).
Explanation
The central interface control unit (CICU) is the bus controller for the Avionics data bus No. 3. This means that it is responsible for managing and controlling the data transfer on the bus. The other options, such as the control display unit (CDU), embedded global positioning system/inertial navigation (EGI), and integrated flight and fire control computer (IFFCC), do not perform the role of a bus controller.

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• 17.

### Which A–10 support equipment provides the technician with software uploading capabilities for the AN/ALQ–184, AN/ALQ–131, AN/ALR–69, AN/ALQ–213, and AN/AAR–47?

• A.

Data Collection Unit (DCU).

• B.

Diagnostic Display Unit (DDU).

• C.

Portable Automated Test Station (PATS).

• D.

Common Aircraft Reprogrammable Equipment (CAPRE).

D. Common Aircraft Reprogrammable Equipment (CAPRE).
Explanation
The Common Aircraft Reprogrammable Equipment (CAPRE) provides the technician with software uploading capabilities for various A-10 support equipment such as the AN/ALQ-184, AN/ALQ-131, AN/ALR-69, AN/ALQ-213, and AN/AAR-47. This means that the CAPRE allows the technician to update or install software on these systems, ensuring they are up to date and functioning properly. The other options, Data Collection Unit (DCU), Diagnostic Display Unit (DDU), and Portable Automated Test Station (PATS), do not specifically mention software uploading capabilities for these specific systems.

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• 18.

### Which A–10 1553 data bus does the Data Transfer System use to communicate?

• A.

AVâ€“1.

• B.

AVâ€“2.

• C.

AVâ€“3.

• D.

AVâ€“4.

A. AVâ€“1.
Explanation
The Data Transfer System uses the AV-1 A-10 1553 data bus to communicate.

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• 19.

### When uploading an A–10 upgrade data transfer unit (UDTU) operational flight program (OFP), what will happen if you turn on the control display unit (CDU)?

• A.

Nothing at all, normal operation.

• B.

It will cause the CDU OFP to be lost.

• C.

It will corrupt the UDTU boot program.

• D.

It will restart the UDTU OFP upload process.

C. It will corrupt the UDTU boot program.
Explanation
When uploading an A-10 upgrade data transfer unit (UDTU) operational flight program (OFP), if you turn on the control display unit (CDU), it will corrupt the UDTU boot program. This means that the boot program, which is responsible for starting up the UDTU, will become damaged or unusable. This can lead to issues with the UDTU's functionality and may require further troubleshooting or repairs.

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• 20.

### When the pilot ejects from the A–10 aircraft, the

• A.

Control display unit (CDU) is erased and the identification friend or foe/global positioning system (IFF/GPS) key is zeroized.

• B.

CDU is erased and the embedded global positioning system/inertial navigation (EGI/GPS) key is zeroized.

• C.

DTC is erased and the IFF/GPS key is zeroized.

• D.

DTC is erased and the EGI/GPS key is zeroized.

D. DTC is erased and the EGI/GPS key is zeroized.
Explanation
When the pilot ejects from the A-10 aircraft, the DTC (Data Transfer Cartridge) is erased and the EGI/GPS (Embedded Global Positioning System/Inertial Navigation) key is zeroized. This ensures that sensitive information stored in the DTC is not compromised and that the EGI/GPS system cannot be accessed or used by unauthorized individuals.

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• 21.

### When the A–10 Data Transfer System (DTS) is turned-on and under normal operation, what built-in-test does the upgraded data transfer unit (UDTU) perform automatically?

• A.

Periodic built-in test (BIT).

• B.

Initiated BIT.

• C.

Continuous BIT.

• D.

Commanded BIT.

A. Periodic built-in test (BIT).
Explanation
When the A-10 Data Transfer System (DTS) is turned on and operating normally, the upgraded data transfer unit (UDTU) performs a periodic built-in test (BIT) automatically. This means that the UDTU regularly conducts self-tests to check its own functionality and ensure that it is working properly. This periodic BIT helps to detect any potential issues or malfunctions in the UDTU and allows for prompt maintenance or troubleshooting if necessary.

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• 22.

### How many multi-function color display (MFCDs) are there in the A–10C aircraft?

• A.

1.

• B.

2.

• C.

3.

• D.

4.

B. 2.
Explanation
The A-10C aircraft has two multi-function color displays (MFCDs). These displays provide pilots with essential information such as navigation data, weapon status, and communication systems. Having two MFCDs allows for better situational awareness and efficient management of the aircraft's systems during missions.

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• 23.

### Which programmable option select buttons are used to select the pages displayed on the A–10 multi-function color display (MFCD)?

• A.

4 through 7.

• B.

8 through 11.

• C.

12 through 15.

• D.

16 through 19.

C. 12 through 15.
Explanation
The correct answer is 12 through 15. This means that programmable option select buttons 12 through 15 are used to select the pages displayed on the A-10 multi-function color display (MFCD). These buttons allow the user to navigate through different pages and access various functions and information on the display.

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• 24.

### Which switch on the right throttle is used to toggle between the programmed displays on theA–10 multi-function color display (MFCD) using hands-on throttle stick (HOTAS)?

• A.

Sensor of interest (SOI) switch.

• B.

Target designation cue (TDC) switch.

• C.

Slew/Track switch.

• D.

CAGE/UNCAGE switch.

A. Sensor of interest (SOI) switch.
Explanation
The correct answer is the Sensor of interest (SOI) switch. This switch is used to toggle between the programmed displays on the A-10 multi-function color display (MFCD) using hands-on throttle stick (HOTAS). The SOI switch allows the pilot to select and focus on a specific sensor or target of interest, enabling them to quickly access the desired information on the display. This helps in efficiently managing and prioritizing information during flight operations.

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• 25.

### What A–10 LRU provides the primary interface for the MFCDs, HOTAS, and Targeting Pod?

• A.

Control display unit (CDU).

• B.

Heads up display unit ( HUD).

• C.

Central interface control unit (CICU).

• D.

Integrated flight and fire control computer (IFFCC).

C. Central interface control unit (CICU).
Explanation
The Central interface control unit (CICU) provides the primary interface for the MFCDs (Multi-Function Color Displays), HOTAS (Hands-On Throttle and Stick), and Targeting Pod. This means that the CICU is responsible for controlling and managing the communication between these different systems, allowing the pilot to interact with and control them effectively. The other options, CDU, HUD, and IFFCC, do not specifically fulfill this role of being the primary interface for all these systems.

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• 26.

### Which A–10 line replaceable unit (LRU) is primarily a weapons system processor?

• A.

• B.

Central interface control unit (CICU).

• C.

Integrated flight and fire control computer (IFFCC).

• D.

Armament/HUD control panel (AHCP).

B. Central interface control unit (CICU).
Explanation
The Central Interface Control Unit (CICU) is primarily a weapons system processor. It is responsible for controlling and coordinating the various weapon systems on an aircraft. The CICU interfaces with other avionics systems and sensors to gather and process data, and then uses that information to control the aircraft's weapons. It plays a crucial role in ensuring the accurate and effective deployment of weapons during combat operations.

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• 27.

### How many output video interfaces does the A–10 central interface control unit (CICU) provide to drive high resolution multi-function color display (MFCDs)?

• A.

1.

• B.

2.

• C.

3.

• D.

4.

D. 4.
Explanation
The A-10 central interface control unit (CICU) provides four output video interfaces to drive high resolution multi-function color displays (MFCDs).

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• 28.

### During the A–10 central interface control unit (CICU) start up sequence, what is performed after successful completion of any initialization and power-on fault detection sequences?

• A.

Power-on self test.

• B.

• C.

Initiated self test sequence.

• D.

Period/continuous self test sequence.

Explanation
After successful completion of any initialization and power-on fault detection sequences, the next step in the A-10 central interface control unit (CICU) start-up sequence is the boot-load sequence.

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• 29.

### What does the A–10 central interface control unit (CICU) provide to allow the Targeting Pod to operate properly?

• A.

Location and speed.

• B.

Altitude and airspeed.

• C.

Current date and time.

• D.

Azimuth and elevation signals.

C. Current date and time.
Explanation
The A-10 central interface control unit (CICU) provides the current date and time to allow the Targeting Pod to operate properly. This information is crucial for accurate targeting and tracking of objects. It helps in synchronizing the pod's data with other systems and ensures precise coordination during missions.

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• 30.

### Which A–10 low altitude safety and targeting enhancement (LASTE) components function is to turn on the radar altimeter, arm the enhanced altitude control (EAC) function, and control the low altitude autopilot?

• A.

Up Front controller.

• B.

LASTE control panel.

• C.

Stability augmentation system (SAS) control panel.

• D.

Armament heads up display (HUD) control panel.

B. LASTE control panel.
Explanation
The LASTE control panel is responsible for turning on the radar altimeter, arming the enhanced altitude control (EAC) function, and controlling the low altitude autopilot. The other options mentioned, such as the Up Front controller, Stability augmentation system (SAS) control panel, and Armament heads up display (HUD) control panel, do not have these specific functions related to low altitude safety and targeting enhancement (LASTE). Therefore, the correct answer is the LASTE control panel.

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• 31.

### What A–10 low altitude safety and targeting enhancement (LASTE) related component senses aircraft pitch, yaw, and roll rates?

• A.

Stability augmentation system (SAS) control panel.

• B.

LASTE control panel.

• C.

Avionics auxiliary panel.

• D.

Armament heads up display (HUD) control panel.

A. Stability augmentation system (SAS) control panel.
Explanation
The correct answer is the Stability augmentation system (SAS) control panel. This panel is responsible for sensing the aircraft's pitch, yaw, and roll rates, which are crucial for maintaining stability and enhancing safety during low altitude operations. The LASTE control panel, avionics auxiliary panel, and armament heads up display (HUD) control panel are not specifically designed for sensing these rates.

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• 32.

### What A–10 low altitude safety and targeting enhancement (LASTE) related component contains the integrated flight and fire control computer (IFFCC) ON/OFF switch?

• A.

Up Front controller.

• B.

LASTE control panel.

• C.

Stability augmentation system (SAS) control panel.

• D.

Armament heads up display (HUD) control panel.

D. Armament heads up display (HUD) control panel.
Explanation
The armament heads up display (HUD) control panel contains the integrated flight and fire control computer (IFFCC) ON/OFF switch. This switch allows the pilot to control the activation and deactivation of the IFFCC, which is an important component of the A-10 low altitude safety and targeting enhancement (LASTE) system. The HUD control panel is responsible for displaying critical information to the pilot, including weapon targeting and safety data, making it a logical location for the IFFCC switch.

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• 33.

### Which A–10 low altitude safety and targeting enhancement (LASTE) related component contains the weapons release button, nose wheel steering button, and master mode control button?

• A.

Stick grip.

• B.

Left Throttle grip.

• C.

Right Throttle grip.

• D.

Armament heads up display (HUD) control panel.

A. Stick grip.
Explanation
The stick grip is the correct answer because it contains the weapons release button, nose wheel steering button, and master mode control button. The stick grip is a component of the A-10 low altitude safety and targeting enhancement (LASTE) system, which is responsible for enhancing safety and targeting capabilities during low altitude operations. The stick grip allows the pilot to have easy access to important controls and buttons for weapon release, steering, and mode control.

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• 34.

### What navigation (NAV) operating mode does the A–10 heads up display (HUD) low altitude safety and targeting enhancement (LASTE) system default to as its backup?

• A.

Embedded global positioning system/inertial navigation (EGI).

• B.

• C.

Integrated flight and fire control computer (IFFCC).

• D.

Normal.

B. Heading attitude reference system (HARS).
Explanation
The A-10 HUD LASTE system defaults to the Heading Attitude Reference System (HARS) as its backup navigation operating mode. This means that if the primary navigation system fails, the HARS will take over and provide the necessary heading and attitude information for the aircraft. The HARS is a reliable backup system that ensures the aircraft can maintain its course and orientation in low altitude and targeting situations.

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• 35.

### Which of the below conditions must be met for the A–10 EAC to arm?

• A.

Low altitude auto pilot (LAAP) must be engaged with no failures.

• B.

Radar altitude must be on and operational.

• C.

Pitch and yaw stability augmentation system (SAS) must be engaged with no SAS failures.

• D.

Heading attitude reference system (HARS) must be selected on the NAV mode select panel and its data valid.

C. Pitch and yaw stability augmentation system (SAS) must be engaged with no SAS failures.
Explanation
The A-10 EAC will only arm if the pitch and yaw stability augmentation system (SAS) is engaged and there are no SAS failures. This means that the SAS must be functioning properly and there should be no errors or malfunctions in the system. The other conditions mentioned, such as the low altitude auto pilot (LAAP), radar altitude, and heading attitude reference system (HARS), are not relevant to arming the A-10 EAC.

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• 36.

### During the A–10 low altitude safety and targeting enhancements (LASTE) PAC–2 engagement, how long is LASTE able to stabilize the aircraft?

• A.

Up to 4 seconds.

• B.

Up to 5 seconds.

• C.

Up to 6 seconds.

• D.

Up to 7 seconds.

B. Up to 5 seconds.
Explanation
During the A-10 low altitude safety and targeting enhancements (LASTE) PAC-2 engagement, LASTE is able to stabilize the aircraft for up to 5 seconds.

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• 37.

### Which A–10 Ground Collision and Avoidance System (GCAS) voice and visual warnings are issued to notify the pilot that he needs to initiate an immediate maximum recovery maneuver to avoid ground impact?

• A.

90 Foot Warning.

• B.

Speedbrake Warning.

• C.

• D.

Ground collision Warning.

D. Ground collision Warning.
Explanation
The Ground Collision Warning is issued to notify the pilot that he needs to initiate an immediate maximum recovery maneuver to avoid ground impact. This warning is crucial in preventing accidents and ensuring the safety of the aircraft and its occupants. The other options, such as the 90 Foot Warning, Speedbrake Warning, and Altitude Alert Warning, may be important in different situations but do not specifically indicate the need for an immediate maximum recovery maneuver to avoid ground impact.

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• 38.

### Which A–10 component has optics that project the cathode ray tube (CRT) image onto a combining glass, providing the user with heads up display (HUD) low altitude safety and targeting enhancements (LASTE) system symbology?

• A.

Multi-function color display (MFCD).

• B.

Integrated flight and fire control computer (IFFCC).

• C.

Projection Unit.

• D.

LASTE control panel.

C. Projection Unit.
Explanation
The correct answer is Projection Unit. The question asks for the A-10 component that projects the CRT image onto a combining glass, providing the user with heads up display (HUD) low altitude safety and targeting enhancements (LASTE) system symbology. The Projection Unit is responsible for this function, allowing the pilot to see important information on the HUD while maintaining situational awareness. The other options, such as the Multi-function color display (MFCD) and Integrated flight and fire control computer (IFFCC), do not specifically mention this capability. The LASTE control panel is not responsible for projecting the image onto the combining glass.

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• 39.

### Which A–10 line replaceable unit (LRU) computes and generates weapon delivery symbology for display on the heads up display (HUD)?

• A.

Up-front controller (UFC).

• B.

Armament/HUD control panel (AHCP).

• C.

Integrated flight and fire control computer (IFFCC).

• D.

Projection Unit.

C. Integrated flight and fire control computer (IFFCC).
Explanation
The Integrated flight and fire control computer (IFFCC) is the correct answer because it is responsible for computing and generating weapon delivery symbology for display on the heads up display (HUD). This means that the IFFCC calculates the necessary information and symbols to guide the pilot in delivering weapons accurately. The other options, such as the Up-front controller (UFC), Armament/HUD control panel (AHCP), and Projection Unit, do not have the capability to perform this specific function.

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• 40.

### If you wanted to adjust the A–10 gun symbology positions with respect to the gun bore line (GBL) Cross position, what type of adjustment would you need to do?

• A.

• B.

• C.

• D.

Explanation
To adjust the A-10 gun symbology positions with respect to the gun bore line (GBL) Cross position, an offset adjustment would need to be done. This adjustment involves shifting the positions of the gun symbology in relation to the GBL Cross position. It allows for precise alignment and calibration of the gun's aiming point and ensures accurate targeting.

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• 41.

### If embedded global positioning system/inertial navigation (EGI) is selected on the navigation (NAV) mode select panel, but EGI attitudes are not valid, what mode will the A–10 heads up display (HUD) low altitude safety and targeting enhancement (LASTE) system default to?

• A.

NAV mode INS.

• B.

NAV mode EGI.

• C.

NAV mode HARS.

• D.

NAV mode Normal.

C. NAV mode HARS.
Explanation
If the EGI attitudes are not valid, the A-10 HUD LASTE system will default to NAV mode HARS.

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• 42.

### When in navigation (NAV) mode normal on the A–10 heads up display (HUD), what action is required to display the Depressible Pipper/Reticle?

• A.

Depressing target designation cue (TDC) switch.

• B.

Depressing the right throttle slew switch.

• C.

Depressing the up-front controller (UFC) MARK Key switch.

• D.

Depressing the armament/HUD control panel (AHCP) DEPR Reticle switch.

C. Depressing the up-front controller (UFC) MARK Key switch.
Explanation
Depressing the up-front controller (UFC) MARK Key switch is required to display the Depressible Pipper/Reticle in navigation mode on the A-10 heads up display (HUD).

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• 43.

### If the destination index symbol is within the A–10 heads up display (HUD) field of view (FOV), what symbol is it replaced by?

• A.

• B.

• C.

Target Designation Cue.

• D.

Target Designation Box.

D. Target Designation Box.
Explanation
When the destination index symbol is within the A-10 heads up display (HUD) field of view (FOV), it is replaced by the Target Designation Box.

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• 44.

### If the A–10 radar altimeter output data is valid, what is the radar altitude numeric range displayed on the heads up display (HUD)?

• A.

0 to 5,000 feet.

• B.

0 to 10,000 feet.

• C.

0 to 15,000 feet.

• D.

0 to 20,000 feet.

A. 0 to 5,000 feet.
Explanation
The A-10 radar altimeter output data is valid and it displays the radar altitude numeric range from 0 to 5,000 feet on the heads-up display (HUD).

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• 45.

### When in Guns mode on the A–10 aircraft, what is the primary (default) firing reference symbology?

• A.

CCIP Gun Cross.

• B.

CCIP Gun Reticle.

• C.

4000 Ft Gun Cross.

• D.

4/8/12 Gun Reticle.

B. CCIP Gun Reticle.
Explanation
In Guns mode on the A-10 aircraft, the primary (default) firing reference symbology is the CCIP Gun Reticle. This means that when the aircraft is in Guns mode, the reticle displayed on the HUD (Head-Up Display) is the CCIP Gun Reticle, which provides the pilot with the necessary information and aiming reference to accurately fire the aircraft's guns. The other options mentioned, such as CCIP Gun Cross and 4000 Ft Gun Cross, are not the primary firing reference symbology in Guns mode on the A-10 aircraft.

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• 46.

### When you want to deliver ordnances on targets outside the A–10 heads up display (HUD) field of view (FOV), which HUD mode would you use?

• A.

• B.

Continuously computed impact point (CCIP).

• C.

Continuously computed release point (CCRP).

• D.

GUNS.

C. Continuously computed release point (CCRP).
Explanation
When you want to deliver ordnances on targets outside the A-10 heads up display (HUD) field of view (FOV), you would use the Continuously computed release point (CCRP) HUD mode. This mode allows the pilot to compute the release point for the ordnance based on factors such as aircraft speed, altitude, and target location. It provides accurate aiming information for targets that are not visible in the HUD FOV, ensuring effective delivery of ordnances.

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• 47.

### What is the recording time of the A–10 removable mass memory device?

• A.

1.5 hours.

• B.

2.5 hours.

• C.

3.5 hours.

• D.

4.5 hours.

B. 2.5 hours.
Explanation
The correct answer is 2.5 hours. This means that the recording time of the A-10 removable mass memory device is 2.5 hours.

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• 48.

### The A–10 Cockpit Color Television Video Sensor (CCTVS) records a video recording of the

• A.

Control display unit (CDU).

• B.

TV monitor.

• C.

Right and left multi-function color display (MFCD).

• D.

View through the heads up display (HUD).

D. View through the heads up display (HUD).
Explanation
The A-10 Cockpit Color Television Video Sensor (CCTVS) records a video recording of the view through the heads up display (HUD). This means that the sensor captures the visual information displayed on the HUD, which provides important information to the pilot without them having to look away from their line of sight. This recording can be used for various purposes such as training, analysis, or documentation.

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• 49.

### Which A–10 Remote Control Panel switch position will cause the color cockpit television sensor/digital video airborne data recorder (CCTVS/DVADR) system to stop recording?

• A.

OFF.

• B.

REC.

• C.

STBY.

• D.

STOP.

A. OFF.
Explanation
The correct answer is OFF. When the A-10 Remote Control Panel switch is turned to the OFF position, it will cause the color cockpit television sensor/digital video airborne data recorder (CCTVS/DVADR) system to stop recording.

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• 50.

### Which ICS component is located on the A–10 aircraft’s left console and is placarded INTER?

• A.

Microphone switch.

• B.

• C.

Intercom control panel.

• D.

Antenna select control panel.

C. Intercom control panel.
Explanation
The correct answer is the intercom control panel. This component is located on the A-10 aircraft's left console and is placarded "INTER." The intercom control panel allows for communication between the pilot and other crew members on the aircraft. It is an essential component for effective communication during flight operations.

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