Avionics 2a352g Volume 1

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| By Robdduarte1
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Robdduarte1
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Quizzes Created: 2 | Total Attempts: 873
Questions: 24 | Attempts: 147

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Avionics Quizzes & Trivia

Questions and Answers
  • 1. 

    ON THE F-16 AIRCRAFT, FUSELAGE STATION ZERO IS LOCATED

    • A.

      AT THE AFT END OF THE NOSE RADOME

    • B.

      AT THE FORWARD END OG THE NOSE RADOME

    • C.

      5.0 INCHES AFT OF THE FORWARD END OF THE NOSE RADOME

    • D.

      5.0 INCHES FORWARD OF THE FORWARD END OF THE NOSE RADOME

    Correct Answer
    C. 5.0 INCHES AFT OF THE FORWARD END OF THE NOSE RADOME
  • 2. 

    ON THE F-16, WATERLINE 65.0 IS LOCATED 65.0 INCHES IN WHICH DIRECTION FROM WATERLINE 0.0?

    • A.

      AFT

    • B.

      ABOVE

    • C.

      BELOW

    • D.

      FORWARD

    Correct Answer
    B. ABOVE
    Explanation
    Waterline 65.0 is located 65.0 inches above waterline 0.0 on the F-16. This means that it is positioned higher in relation to the reference point of waterline 0.0.

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  • 3. 

    WHEN SHOULD WORN DOOR/PANEL FASTENERS BE REPLACED?

    • A.

      IMMEDIATELY

    • B.

      BEFORE THE AIRCRAFT TAXIS

    • C.

      WHEN SHEET METAL SHOP SEES FIT

    • D.

      THE NEXT TIME YOU PERFORM MAINTENANCE UNDER THAT DOOR/PANEL

    Correct Answer
    A. IMMEDIATELY
    Explanation
    Worn door/panel fasteners should be replaced immediately to ensure the safety and integrity of the aircraft. These fasteners play a crucial role in holding the doors or panels securely in place, and any wear or damage can compromise their effectiveness. Waiting until the next maintenance or when the sheet metal shop sees fit may lead to further deterioration or potential incidents during operation. Therefore, immediate replacement is necessary to maintain the aircraft's structural integrity and prevent any potential hazards.

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  • 4. 

    WHICH OF THE FOLLOWING STRUCTURES IS NOT A PART OF THE EMPENNAGE GROUP?

    • A.

      WINGS

    • B.

      RUDDER

    • C.

      VENTRAL FINS

    • D.

      HORIZONTAL STABS

    Correct Answer
    A. WINGS
    Explanation
    The wings are not a part of the empennage group. The empennage group typically consists of the rudder, ventral fins, and horizontal stabs, which are located at the tail of an aircraft. The wings, on the other hand, are located on the main body of the aircraft and are responsible for generating lift.

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  • 5. 

    THE LEADING EDGE FLAPS FOR THE F-16 ARE LOCATED ON THE

    • A.

      WING ASSEMBLY

    • B.

      EMPENNAGE GROUP

    • C.

      FUSELAGE ASSEMBLY

    • D.

      HORIZONTAL STABS

    Correct Answer
    A. WING ASSEMBLY
    Explanation
    The correct answer is "WING ASSEMBLY". The leading edge flaps for the F-16 are located on the wing assembly. This means that these flaps are positioned on the front edge of the wings of the aircraft. They are used to modify the shape and angle of the wing during flight, allowing for improved control and maneuverability. By adjusting the position of the leading edge flaps, the pilot can optimize the aircraft's performance in different flight conditions.

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  • 6. 

    ON THE F-16 INSTALLIG THE EMERGENCY POWER UNIT SAFETY PIN WILL

    • A.

      NOT PREVENT THE FIRING OF THE EPU IN FLIGHT

    • B.

      PREVENT THE ACCIDENTAL FIRING OF THE EPU ONLY IN FLIGHT

    • C.

      NOT PREVENT THE FIRING OF THE EPU IF THE EXTERNAL SOURCE SHUTS DOWN

    • D.

      PREVENT THE ACCIDENTAL FIRING OF THE EPU DURING GROUND MAINTENANCE

    Correct Answer
    D. PREVENT THE ACCIDENTAL FIRING OF THE EPU DURING GROUND MAINTENANCE
    Explanation
    The correct answer is "PREVENT THE ACCIDENTAL FIRING OF THE EPU DURING GROUND MAINTENANCE." Installing the emergency power unit (EPU) safety pin on the F-16 will prevent any accidental firing of the EPU while performing maintenance on the ground. This safety measure ensures that the EPU does not activate unexpectedly, which could cause harm to personnel or damage to the aircraft during maintenance operations. However, it does not prevent the firing of the EPU in flight or if the external power source shuts down.

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  • 7. 

    TO OPERATE THE AIRCRAFT PRIMARY FLIGHT CONTROLS, THE F-16 HYDRAULIC SYSTEMS PROVIDE HYDRAULIC PRESSURE AT APPROXIMATELY WHAT PSI

    • A.

      1100

    • B.

      2100

    • C.

      3100

    • D.

      4100

    Correct Answer
    C. 3100
    Explanation
    The F-16 hydraulic systems provide hydraulic pressure at approximately 3100 PSI to operate the aircraft's primary flight controls. This high pressure is necessary to ensure efficient and precise control of the aircraft during flight.

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  • 8. 

    AT AIRCRAFT ALTITUDES BETWEEN 800 AND 2300 FEET, THE F-16 CABIN PRESSURE IS REGULATED TO

    • A.

      8000 FOOT AIR PRESSURE

    • B.

      THE 23000 FOOT AIR PRESSURE

    • C.

      AMBIENT AIR PRESSURE

    • D.

      5 PSI ABOVE AMBIENT AIR PRESSURE

    Correct Answer
    A. 8000 FOOT AIR PRESSURE
    Explanation
    At aircraft altitudes between 800 and 2300 feet, the F-16 cabin pressure is regulated to 8000 foot air pressure.

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  • 9. 

    THE DIGITAL FLIGHT CONTROL SYSTEM USES WHAT MEANS TO TRANSFER INPUTS TO THE CONTROL SURFACES?

    • A.

      CONTROL CABLES

    • B.

      FULL FLY BY WIRE

    • C.

      MECHANICAL LINKAGE

    • D.

      A COMBINATION OF CONTROL CABLES AND ELECTRICAL WIRE

    Correct Answer
    B. FULL FLY BY WIRE
    Explanation
    The correct answer is "FULL FLY BY WIRE." In a digital flight control system, the inputs from the pilot are transferred to the control surfaces using a full fly by wire system. This means that instead of using control cables or mechanical linkages, the inputs are transmitted electronically through wires. This allows for more precise and efficient control of the aircraft's movements.

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  • 10. 

    ARTIFICIAL FEEL IN THE DIGITAL FLIGHT CONTROL SYSTEM IS PROVIDED BY BEAMS AND COIL SPRINGS

    • A.

      INTERNAL TO THE HANDGRIP ASSEMBLY

    • B.

      INTERNAL TO THE TRANSDUCER ASSEMBLY

    • C.

      EXTERNAL TO THE HANDGRIP ASSEMBLY

    • D.

      EXTERNAL TO THE TRANSDUCER ASSEMBLY

    Correct Answer
    B. INTERNAL TO THE TRANSDUCER ASSEMBLY
    Explanation
    The correct answer is "INTERNAL TO THE TRANSDUCER ASSEMBLY". This means that the artificial feel in the digital flight control system is provided by beams and coil springs that are located within the transducer assembly.

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  • 11. 

    IN ADDITION TO RUDDER CONTROL, THE RUDDER PEDALS ARE ALSO USED TO GENERATE

    • A.

      BRAKE COMMAND SIGNALS ONLY

    • B.

      NOSEWHEEL STEERING SIGNALS ONLY

    • C.

      BRAKE COMMAND AND NOSEWHEEL STEERING SIGNALS

    • D.

      ANTI-SKID COMMAND AND NOSEWHEEL STEERING SIGNALS

    Correct Answer
    C. BRAKE COMMAND AND NOSEWHEEL STEERING SIGNALS
    Explanation
    The rudder pedals are not only used for controlling the rudder, but they are also used to generate brake command and nosewheel steering signals. This means that when the pilot presses on the rudder pedals, in addition to controlling the rudder, they can also activate the brakes and steer the nosewheel of the aircraft. This allows for precise control during taxiing, takeoff, and landing.

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  • 12. 

    YAW TRIM ON THE F-16 IS ACCOMPLISHED BY USING THE

    • A.

      YAW TRIM CONTROL ON THE MANUAL TRIM PANEL

    • B.

      YAW TRIM CONTROL ON THE SIDE STICH CONTROLLER

    • C.

      RUDER TRIM CONTROL ONTHE MANUAL TRIM PANEL

    • D.

      RUDDER TRIM CONTROL ON THE SIDE STICK CONTROLLER

    Correct Answer
    A. YAW TRIM CONTROL ON THE MANUAL TRIM PANEL
    Explanation
    The correct answer is the YAW TRIM CONTROL ON THE MANUAL TRIM PANEL. This means that the F-16 aircraft's yaw trim, which is used to adjust the aircraft's yaw or side-to-side movement, is controlled through the manual trim panel. This panel allows the pilot to make small adjustments to the aircraft's trim settings to ensure stable flight. The other options mentioned, such as the yaw trim control on the side stick controller or rudder trim control, are incorrect as they do not specifically refer to the manual trim panel.

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  • 13. 

    WHAT HAPPENS IF THE FLIGHT DATA RECORDER MEMORY CAPACITY IS EXCEEDED?

    • A.

      WRITE OVERWILL WILL OCCUR

    • B.

      CAUTION-CAUTION IS HEARD IN THE HEADSETS

    • C.

      THE FLIGHT DATA RECORDER AUTOMATICALLY SHUTS OFF

    • D.

      THE FLIGHT DATA RECORDER CAUTION LIGHT ILLUMINATES

    Correct Answer
    A. WRITE OVERWILL WILL OCCUR
    Explanation
    If the flight data recorder memory capacity is exceeded, a "write overwill" will occur. This means that the recorder will start overwriting the oldest data with new data, in order to make space for the new information. This can result in the loss of important flight data if not managed properly.

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  • 14. 

    WHICH OF THE FOLLOWING FUNCTIONS DOES THE STORES MANAGEMENT SET PERFORM?

    • A.

      QUICK REACTION FINGERTIP CONTROL OF NAVIGATION DISPLAYS

    • B.

      PROBVIDES TARGET DATA TO THE FIRE CONTROL AVIONICS SUBSYSTEM

    • C.

      SWITCHING VIDEO AND POWER CONTROLS AT THE WEAPONS STATIONS

    • D.

      GENERATES SYMBOLS FOR ESSENTIAL AIRCRAFT PERFORMANCE DATA INCLDING ALTITUDE, AIRSPEED, ATTITUDE, AND HEADING

    Correct Answer
    C. SWITCHING VIDEO AND POWER CONTROLS AT THE WEAPONS STATIONS
    Explanation
    The correct answer is "SWITCHING VIDEO AND POWER CONTROLS AT THE WEAPONS STATIONS". This function is responsible for controlling the video and power systems at the weapons stations in the store management set. It involves managing the switching of video signals and power controls to ensure proper functioning of the weapons systems.

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  • 15. 

    ON THE F-16, 10JG PROCEDURES MUST BE AVVOMPLISHED PRIOR TOHYDRAULIC POWER APPLICATION: INSURE THE AIRCRAFT EXTERIOR IS SAFE, THE AIRCRAFT COCKPIT IS SAFE FOR ENTRY, AND THE AIRCAFT IS SAFE FOR

    • A.

      COOLING AIR

    • B.

      AVIONICS SYSTEMS POWER APPLICATION

    • C.

      ELECTRICAL AND HYDRAULIC POWER APPLICATION

    • D.

      COOLING AIR AND AVIONIC SYSTEMS POWER APPLICATION

    Correct Answer
    C. ELECTRICAL AND HYDRAULIC POWER APPLICATION
    Explanation
    The given correct answer is "ELECTRICAL AND HYDRAULIC POWER APPLICATION". This means that before applying electrical and hydraulic power to the F-16, certain procedures need to be accomplished. These procedures include ensuring the safety of the aircraft exterior, the safety of the aircraft cockpit for entry, and ensuring that the aircraft is safe for cooling air. Therefore, before applying electrical and hydraulic power, these safety measures must be taken.

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  • 16. 

    WHAT ARE YOU VERIFYING WHEN YOU INSURE THE AIRCRAFT EXTERIOR IS SAFE FOR MAINTENANCE?

    • A.

      THAT THE CREW CHIEF DID THEIR JOB

    • B.

      THAT ITS OK TO APPLY ELECTRICAL POWER

    • C.

      THAT AVIONIC SYSTEMS ARE SAFE FOR MAINTENANCE

    • D.

      BASICALLY THAT ALL APPLICABLE SAFETY/LOCKPINS ARE INSTALLED

    Correct Answer
    D. BASICALLY THAT ALL APPLICABLE SAFETY/LOCKPINS ARE INSTALLED
    Explanation
    When insuring the aircraft exterior is safe for maintenance, you are verifying that all applicable safety/lockpins are installed. These pins are crucial in securing various components of the aircraft, such as control surfaces and access panels, during maintenance procedures. Ensuring that these safety measures are in place helps prevent accidental movement or detachment of parts, reducing the risk of injuries or damage to the aircraft and personnel.

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  • 17. 

    YOU PERFORM THE SAFE FOR COCKPIT ENTRY PROCEDURE

    • A.

      STANDING ON THE GROUND

    • B.

      SITTING IN THE PILOTS SEAT

    • C.

      DURING AIRCRAFT WALKAROUND

    • D.

      STANDING ON THE CREW LADDER

    Correct Answer
    D. STANDING ON THE CREW LADDER
    Explanation
    The correct answer is "STANDING ON THE CREW LADDER" because the crew ladder is specifically designed to provide safe access to the cockpit. By standing on the crew ladder, you can ensure that you have a stable platform to perform the cockpit entry procedure without any risk of falling or injuring yourself. Standing on the ground, sitting in the pilot's seat, or performing the procedure during aircraft walkaround may not provide the necessary stability and safety required for cockpit entry.

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  • 18. 

    AFTER ENGINE ENGINE SHUTDOWN THE ENGINE EXHAUST NOZZLE SHOULD E AVOIDED FOR AT LEAST

    • A.

      2 MIN

    • B.

      5 MIN

    • C.

      15 MIN

    • D.

      45 MIN

    Correct Answer
    C. 15 MIN
    Explanation
    After the engine shuts down, it is necessary to avoid the engine exhaust nozzle for at least 15 minutes. This is because the exhaust nozzle remains extremely hot even after the engine is turned off. Approaching or touching the exhaust nozzle before it has cooled down can result in severe burns or injuries. Therefore, it is important to wait for a sufficient amount of time to ensure the exhaust nozzle has cooled down before approaching it.

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  • 19. 

    WHAT HAZARDS DOES THE JFS POSE?

    • A.

      JFS ELECTRIC STARTER SEPARATION OR DISINTEGRATION

    • B.

      JFS ELECTRIC STARTER SEPARATION AND DISINTEGRATION

    • C.

      HIGH TEMP HIGH VELOCITY EXHAUST AND NOISE ONLY

    • D.

      INTAKE SUCTION, HIGH TEMP HIGH VELOCITY EXHAUST AND NOISE

    Correct Answer
    D. INTAKE SUCTION, HIGH TEMP HIGH VELOCITY EXHAUST AND NOISE
    Explanation
    The JFS (Jet Fuel Starter) poses hazards related to intake suction, high temperature, high velocity exhaust, and noise. These hazards can arise due to the operation of the JFS. The intake suction can cause objects or debris to be drawn into the engine, potentially causing damage. The high temperature and high velocity exhaust can pose a risk of burns or fire. Additionally, the noise generated by the JFS can be a hazard to personnel working in the vicinity, potentially causing hearing damage.

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  • 20. 

    WHO IS RESPONSIBLE FOR FOD PREVENTION?

    • A.

      EVERYONE

    • B.

      EXPEDITERS

    • C.

      CREW CHIEFS

    • D.

      INDIVDUALS WHO CREATED FOD

    Correct Answer
    A. EVERYONE
    Explanation
    FOD (Foreign Object Debris) prevention is a collective responsibility that falls on everyone involved in any task or operation. It includes individuals at all levels, including expediters, crew chiefs, and even the individuals who may have unintentionally created the FOD. This answer emphasizes the importance of a proactive approach to FOD prevention, highlighting that it is not the sole responsibility of a specific group or individual, but rather a shared obligation to maintain a safe and clean working environment.

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  • 21. 

    THE MOST COMMON INJURY ASSOCIATED WITH MOVING FLIGHT CONTROL SURFACES IS

    • A.

      A BLOW TO THE HEAD

    • B.

      A DEEP THIGH BRUISE

    • C.

      A SEVERED FINGER

    • D.

      A LACERATION USUALLY BELOW THE HEAD

    Correct Answer
    A. A BLOW TO THE HEAD
    Explanation
    Moving flight control surfaces can pose a risk of injury, and the most common injury associated with this activity is a blow to the head. This could occur if a person is not careful and accidentally hits their head on a control surface or another object while moving it. This type of injury can be serious and may result in concussions or other head trauma. It is important to exercise caution and use proper lifting techniques to prevent such injuries.

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  • 22. 

    IN THE FIRST FEW MINUTES AFTER AN AIRCRAFT WITH HOT BRAKES COMES TO A STOP, THE DANGER OF A TIRE BLOWOUT

    • A.

      DECREASES

    • B.

      INCREASES

    • C.

      IS ELIMINATED

    • D.

      STAYS THE SAME

    Correct Answer
    B. INCREASES
    Explanation
    In the first few minutes after an aircraft with hot brakes comes to a stop, the danger of a tire blowout increases. This is because when the brakes of an aircraft become overheated, it can cause the tires to also become excessively hot. As the aircraft comes to a stop, the heat generated from the brakes can transfer to the tires, causing them to expand and potentially leading to a blowout. Therefore, the longer the aircraft remains stationary after landing with hot brakes, the greater the risk of a tire blowout.

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  • 23. 

    IN AIRCRAFT MAINTENANCE A NO STEP AREA IS AN AREA

    • A.

      WHERE WALKING IS PROHIBITED

    • B.

      THAT IS RESTRICTED AROUND AIRCRAFT MUNITIONS

    • C.

      WHERE NO MAINTENANCE STANDS ARE PERMITTED

    • D.

      IN FRONT OF, OR BEHIND AN AIRCRAFT WERE VARIOUS AIRCRAFT HAZARDS EXISTS

    Correct Answer
    A. WHERE WALKING IS PROHIBITED
    Explanation
    The correct answer is "WHERE WALKING IS PROHIBITED." This means that a no step area in aircraft maintenance is an area where walking is not allowed. This could be due to safety reasons or to prevent damage to the aircraft or its components. It is important to follow these restrictions to ensure the safety of personnel and the integrity of the aircraft.

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  • 24. 

    WHAT IS THE PROPER WAY TO REMOVE EXCESSIVE SOLDER FROM A SOLDERING IRON OR GUN?

    • A.

      SWING OR SHAKE IT

    • B.

      USE A SOLDER SUCKER

    • C.

      DIP THE HOT TIP IN WATER

    • D.

      WIPE THE HOT TIP ACROSS A DAMP RAG OR SPONGE

    Correct Answer
    D. WIPE THE HOT TIP ACROSS A DAMP RAG OR SPONGE
    Explanation
    The proper way to remove excessive solder from a soldering iron or gun is to wipe the hot tip across a damp rag or sponge. This method allows the excess solder to be easily removed from the tip, ensuring that it is clean and ready for further use. It is important to use a damp rag or sponge to avoid damaging the tip or causing any safety hazards.

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Quiz Review Timeline +

Our quizzes are rigorously reviewed, monitored and continuously updated by our expert board to maintain accuracy, relevance, and timeliness.

  • Current Version
  • Mar 18, 2023
    Quiz Edited by
    ProProfs Editorial Team
  • Oct 05, 2011
    Quiz Created by
    Robdduarte1
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