ATR 42: Trivia Questions On Aircraft Maintenance! Quiz

The master warning system is typically associated with an emergency situation. This system is designed to alert the pilot or operator of an aircraft or machinery about a critical or potentially dangerous condition that requires immediate attention. It serves as a vital tool to ensure the safety and prompt response in emergency situations, allowing the operator to take necessary actions to mitigate risks and prevent further damage or harm.

The cross-feed bleed valve opens automatically on the ground when bleed air is supplied from a single engine. This means that when only one engine is running and providing bleed air, the valve will automatically open to allow the bleed air to be distributed to the necessary systems. This is important for maintaining proper airflow and pressure in the aircraft's systems while on the ground.

If a pack valve is closed or inoperative, the other pack will supply both compartments (cockpit, cabin) through the mixing chamber. This means that the air from the functioning pack will be distributed to both compartments, ensuring that both the cockpit and cabin receive the necessary supply of air. Additionally, hot air is still available from the functioning pack via the temp control valve, further contributing to the air supply in both compartments.

Smoke detectors are provided in the avionics compartment, as well as in the forward and after cargo compartments. This is important for early detection of smoke or fire, allowing the crew to take necessary actions to prevent further damage or potential hazards. It is crucial to have smoke detectors in these areas to ensure the safety of the aircraft and its occupants.

The correct answer is "Both PL above 56` and both torque above 53%". This means that the Power Levers (PL) of both engines should be positioned above 56 degrees and the torque of both engines should be above 53%. This condition indicates that the engines are generating sufficient power and are ready for takeoff.

The emergency battery functions to provide positive power to protect critical items from power transients. It is not used to power the starters.

The "COMPT TEMP" indicator displays both the compartment and duct temperature of the selected side. This means that it provides information about the temperature in both the compartment and the duct on the selected side.

The correct answer is "Makes use of the MAIN BAT until 10% NH, THEN USES main bat AND OPPOSITE DC GEN (on ground only)". This means that during the start sequence, the cross start system initially relies on the main battery (MAIN BAT) until the engine reaches 10% NH (N1 high). After reaching this threshold, the system switches to using both the main battery and the opposite DC generator (OPPOSITE DC GEN) for starting the engine. However, this method of starting the engine using both the main battery and the opposite DC generator is only applicable when the aircraft is on the ground.

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The ATPCS (Automatic Thrust Power Control System) detects a failed engine when one torquemeter drops below 21%. This indicates that the engine is not producing the required amount of power.

The two amber bugs on the torque gauges indicate the reserve take off power setting (up trim value) when the PWR MGT is set to the intake off position. This setting is determined and set by the FDAU (flight data acquisition unit).

When the aircraft is on the ground and the engines are shut off, the fire test will only operate if the engine fire light is on the CAP (Control Annunciator Panel) and in the fire handle. In this scenario, the MASTER WARNINGS and CRC (Crew Rest Compartment) will be activated and heard in the CM1 (Crew Member 1) loudspeaker.

When the first leg of the landing gear unlocks before retraction, the T.O. INHI function is automatically cancelled. This means that the function is no longer active and any restrictions or limitations it imposed are lifted.

The LP valve at the outlet of each tank is controlled electrically by the related fire handle. The motor 1 is controlled by DC BUS 1 or 2, while the motor 2 is controlled by DC EMER BUS.

The correct answer is "Only one." This means that one electric pump can only supply power to one engine during takeoff. It implies that jet pump supply is not necessary for takeoff and only one engine requires the electric pump for power.

The correct answer is "Agent 1 DISCH on left engine + agent 2 DISCH on right engine." This means that after discharging agent 1 on the left engine, you should also discharge agent 2 on the right engine. This action is necessary to ensure that both engines are properly treated and any potential fire is extinguished.

When the main battery overheat with the main battery charge fault light on, the HOT MAIN BAT BUS is lost. In this situation, the DC ESS BAT BUS is powered by DC BUS 1.

The explanation for the given answer is that even though the RH engine is being started and the RH CL is at maximum RPM, the ACW BUS 1 and ACW BUS 2 are still being supplied by ACW WXT PWR. This means that the power source for these buses is still coming from the ACW WXT PWR instead of the RH ACW GEN or ACW EXT PWR.

The system is protected against exceeding the maximum cabin differential pressure by incorporating a manometric capsule (aneroid) in both outflow valves. This capsule is designed to hold the valve open sufficiently to prevent overpressure.

During cold weather starts, the oil in the engine may become thicker and more viscous, leading to increased oil pressure. This can cause surges and potentially damage the engine. To prevent this, a cold relief valve is used. This valve bypasses the oil back to the tank, reducing the pressure and ensuring that the oil flows smoothly through the engine. Therefore, option B is correct.