Mc-130h Engine Run Quiz

The ground observer should indicate the rotation of the propeller within 5 seconds of engaging the starter button. This indicates that the propeller is functioning properly and the engine has started successfully. Waiting any longer could indicate a problem with the engine or starter system.

The answer "External, APU, engine" correctly identifies the three sources of bleed air. Bleed air is extracted from the compressor stages of the aircraft's engines, the auxiliary power unit (APU), and from external sources such as ground power units or air conditioning units. These sources provide the necessary compressed air for various aircraft systems, including cabin pressurization, air conditioning, and engine starting.

The correct answer is 69-75.5%. This range represents the RPM (Rotations Per Minute) range of low speed ground idle (LSGI). LSGI is a mode in which the engine operates at a lower RPM while the aircraft is on the ground, typically during taxiing or when the aircraft is stationary. This range ensures that the engine runs at an appropriate speed for ground operations, providing sufficient power without causing excessive wear or fuel consumption.

If the start valve light does not illuminate within 5 seconds during starting, the correct action to be taken is to discontinue the start. This is because the start valve light indicates that the start valve is open and fuel is being introduced into the engine. If the light does not illuminate, it suggests a potential issue with the start valve or fuel flow, and continuing the start could lead to further complications or damage to the engine. Therefore, it is necessary to discontinue the start to prevent any potential risks or damages.

The normal engine starting temperature (TIT) is typically between 750-830C. This range ensures that the engine reaches a suitable temperature for efficient combustion and operation. Temperatures below 750C may not provide enough heat for proper ignition, while temperatures above 830C could potentially cause damage to the engine components. Therefore, the correct answer is 750-830C.

The normal reduction gear box oil pressure is between 150-250psi. This range is considered standard for the oil pressure in a reduction gear box. It is important for the oil pressure to be within this range to ensure proper lubrication and functioning of the gear box. Higher or lower oil pressure levels can indicate potential issues or damage to the gear box.

The #3 engine generator powers the Main AC electrical bus under normal operation.

The booster hydraulic system is operated by the #3 and #4 engine driven hydraulic pumps. These pumps are specifically designed to provide hydraulic power to the booster system, which assists in controlling various aircraft functions such as the landing gear, flaps, and brakes. The engine-driven pumps are directly connected to the engines and use the engine's power to generate hydraulic pressure, ensuring reliable and efficient operation of the booster system.

The correct answer is the #1 and #2 engine driven hydraulic pumps. These pumps are responsible for operating the utility hydraulic system in the aircraft. They are driven by the engines and provide the necessary hydraulic pressure to power various systems and components, such as landing gear, flaps, and brakes. The #3 and #4 engine driven hydraulic pumps may be responsible for operating other hydraulic systems in the aircraft, but not specifically the utility hydraulic system. The aircraft auxiliary pump and emergency pump are backup systems that are used in case of failure of the engine driven pumps.

The correct answer is 200C and 100C if using enrichment. This means that for engine restarting, the Turbine Inlet Temperature (TIT) must be below 200C. However, if enrichment is being used, the TIT must be below 100C. Enrichment refers to the process of adding additional fuel to the engine to increase its power output.

The four input conditions for the engine fuel control are Compressor Inlet Pressure (CIP), Throttle Lever Angle (TLA), Compressor Inlet Temperature (CIT), and Engine Revolutions Per Minute (RPM). This means that these four factors are used to control and regulate the fuel flow in the engine.

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It is important for personnel and equipment to be clear of the propellers before pressurizing the bleed air system to ensure safety. Pressurizing the system can cause the propellers to spin rapidly, posing a risk to anyone or anything in close proximity. Therefore, it is necessary to make sure that the area is clear before proceeding with pressurization.

To ensure the aircraft has been depressurized before opening the aircraft crew door, the pilots or co-pilots swing window should be opened. This step allows for equalization of the pressure inside and outside the aircraft, preventing any sudden release of pressure that could cause harm to the crew or damage to the aircraft. By opening the window, the pressure can be safely equalized before opening the crew door.

The spacing required for engine runs operated above ground idle is 200 ft to the front and 400 ft to the rear. This distance is necessary to ensure the safety of personnel and equipment in case of any unexpected events or accidents during the engine run. It allows for sufficient space for the engine exhaust and debris to disperse without causing harm to nearby individuals or property.

The #1 engine generator powers the Left AC bus under normal operation.

The correct answer is 200C and 100C if using enrichment. This means that for an engine restart, the turbine inlet temperature must be below 200C. However, if enrichment is being used, the temperature must be below 100C. Enrichment refers to the process of adding extra fuel to the engine to increase its power output. Therefore, if enrichment is being used, the temperature threshold for engine restart is lower.

The correct answer is 1500psi +or- 100psi. This means that the range for the normal brake accumulator pre-load is 1400psi to 1600psi.

The maximum turbine inlet temperature that should not be exceeded is 1083C.

The #4 engine generator powers the electrical AC bus on the right side under normal operation.

The engine should be on speed and stable within 60 seconds of engaging the starting sequence. This means that after starting the engine, it should reach its desired speed and maintain stability within a minute. This is important for the proper functioning and efficiency of the engine.

The maximum starting temperature with one re-start allowed is 850C. This means that if the temperature reaches 850C and needs to be restarted, it can be brought back to that same temperature. It cannot exceed 850C in any case.

If the starting temperature is between 831C and 850C, the correct action to be taken is to continue the start and document the 781A aircraft forms. This suggests that there is no immediate danger or issue with the starting temperature within this range, but it is still important to record the temperature for documentation purposes.

When the AC bus is tied, the APU generator will power the main AC electrical bus as well as the essential. This means that the APU generator will provide electrical power to both the main AC electrical bus and the essential systems when the AC bus is connected or tied.

The correct answer is 96-106%. This range represents the maximum reverse RPM limit. Reverse RPM refers to the speed at which an engine can rotate in the opposite direction. The range of 96-106% indicates that the engine can safely operate in reverse at speeds between 96% and 106% of its maximum RPM.

The minimum aircraft battery voltage is 21 volts. This means that the battery voltage should never drop below 21 volts in order to ensure proper functioning of the aircraft. A voltage lower than this can lead to various issues and can potentially compromise the safety and performance of the aircraft.

Pressure may be slightly lower than 35psi on certain days dependent on atmospheric and weather conditions

The takeoff RPM limitation refers to the range of RPM (rotations per minute) that is allowed during the takeoff phase of an aircraft. In this case, the correct answer is 98-102%, which means that the RPM should be between 98% and 102% during takeoff. This range ensures that the engine is operating within the specified limits for optimal performance and safety during the critical phase of takeoff.

Normal oil temperature for most vehicles typically ranges between 60-85 degrees Celsius. This temperature range ensures that the oil is warm enough to flow smoothly and lubricate the engine effectively, but not too hot to cause damage or breakdown. Maintaining the oil within this range helps to optimize engine performance and longevity.

When exceeding 8,000 in/lbs of torque, there is a minimum weight requirement of 95,000lbs for the aircraft. This means that the aircraft must weigh at least 95,000lbs in order to safely handle the torque.

When operating the APU with less than 2,000lbs of fuel in the #2 tank, it is necessary to turn on the #2 boost pump. This is because the fuel level in the surge box needs to be maintained, and the #2 boost pump is responsible for supplying fuel to the surge box. By turning on the #2 boost pump, the fuel level in the surge box can be maintained even with low fuel in the #2 tank.

If a propeller warning malfunction is known or suspected, it is important to shut the engine down by placing the engine condition lever in ground stop. This is especially important when shutting down an engine above 8,000 in/lb torque on slippery surfaces. In these cases, it is necessary to shut down the engines together or retard them symmetrically. Failing to do so can result in extreme yaw circumstances and potentially cause the aircraft to jump off the chocks. Therefore, the statement is true.

When one engine generator is operating without the APU generator, the Main and Essential electrical buses will be powered. This means that the essential systems and the main systems of the aircraft will receive power from the operating engine generator. The Left and Right electrical buses will not be powered in this scenario.

The maximum starting temperature with one re-start allowed is 850°C. This means that the temperature can reach up to 850°C initially, and if it needs to be restarted, it can be brought back to that temperature. However, it cannot exceed 850°C even with a re-start.

The utility and booster hydraulic system pre-loads are set at 1500psi with a tolerance of plus or minus 100psi. This means that the system is designed to operate at a pressure of 1500psi, but it can fluctuate within a range of 100psi higher or lower than that value. This allows for some flexibility in the system's performance while still maintaining a relatively consistent pressure level.

The APU generator will power only the essential electrical bus during normal operation. This means that it will provide power to the systems that are necessary for the safe operation of the aircraft, such as critical instruments, essential lighting, and communication systems. The left, right, and main electrical buses are not powered by the APU generator in this scenario.

The #2 engine generator powers the Essential AC electrical bus under normal operation.

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To set the aircraft parking brake, the correct procedure is to fully depress both of the pilots brake pedals simultaneously. Then, with both pedals fully depressed, pull out the parking t-handle and release the brake pedals while holding the t-handle extended. Finally, release the t-handle and ensure that both pedals stay down while the t-handle stays extended. This process is described as the correct way to set the parking brake, indicating that the answer "True" is correct.

In order to restart an engine without fuel enrichment, the turbine inlet temperature must be below 200°C. This means that the temperature of the air entering the turbine should not exceed 200°C for a successful restart without the need for additional fuel enrichment.

The correct answer is "essential and main". This means that both the essential and main electrical buses will be powered by a single engine generator operating.

The engine starter duty cycle refers to the pattern of time intervals for starting and resting the engine. The correct answer states that the engine should be started for 1 minute, then rested for either 1 minute, 5 minutes, or 30 minutes, depending on the specific situation. This cycle allows the engine to cool down and prevents overheating, ensuring optimal performance and longevity.

The utility hydraulic system is responsible for supplying normal brake pressure. This system is designed to provide the necessary hydraulic pressure to operate the brakes effectively. It ensures that the brakes are able to generate the required force to stop the vehicle efficiently. The utility hydraulic system is specifically designed for this purpose and is separate from other hydraulic systems such as the booster, auxiliary, and emergency systems.

When running engines with high torque on slippery surfaces, retarding only one engine can cause the aircraft to jump chocks. This means that if only one engine is slowed down or stopped while the other engines are still running at high torque, the aircraft can experience a sudden and forceful movement, causing it to jump over the chocks. This is because the uneven power distribution between the engines can create an imbalance in the aircraft's movement, leading to this potentially dangerous situation.

The normal engine generator frequency is 380-420cps/hz. This frequency range is commonly used in engine generators to ensure efficient and reliable operation of electrical equipment. It is important for the frequency to be within this range to prevent damage to the equipment and ensure proper functioning.

In fuel balancing, the total amount allowed between wings is 1500lbs. This means that the difference in fuel quantity between the left and right wings should not exceed 1500lbs. This ensures that the aircraft remains balanced and stable during flight.

The bleed air bleed down check limitations refer to the rate at which the pressure in the system decreases. The correct answer states that the pressure should go from 30psi to 15psi in no less than 16 seconds. This means that the pressure should not decrease faster than 30psi to 15psi in 16 seconds, indicating a specific time frame for the bleed down process.

The maximum allowable engine torque that should not be exceeded is 19,600 in/lbs. This means that the engine should not produce a torque greater than this value, as it may lead to mechanical failure or damage. Torque is a measure of rotational force, and in this case, it is measured in inch-pounds. Therefore, the correct answer indicates the maximum limit for the engine torque in inch-pounds.

During normal operation, the APU EGT (exhaust gas temperature) should not exceed 680C. This temperature threshold is likely determined based on the specifications and limitations of the APU system. Exceeding this temperature could indicate a potential issue or malfunction with the APU, which could lead to further damage or safety concerns. Therefore, monitoring and ensuring that the APU EGT stays below 680C is important for the safe and efficient operation of the aircraft.

The maximum allowable oil temperature is 100C for 30 minutes on the ground. This means that the oil temperature should not exceed 100C while the aircraft is on the ground, and this limit should be maintained for a maximum of 30 minutes. This is important to prevent overheating and potential damage to the engine and other components.