Aircraft Run Test For The T-38c Aircraft

In order for the instruments to work when the left engine is started before the right engine, external electrical power is required. This means that the aircraft needs to be connected to an external power source to provide the necessary electrical energy for the instruments to function properly. The other options mentioned in the question, such as the MDP being in the ON position, the MDP screen switch being in the Day or Night position, and the EGI selector switch being in the ON position, are not directly related to the instruments working and therefore not the correct answer. The fully charged aircraft battery is also not sufficient on its own to power the instruments in this scenario.

Before advancing the throttles above idle, it is important to ensure that the hand is always on the throttle and the brakes are pumped up and held. This is necessary to maintain control and prevent the aircraft from moving forward unexpectedly. The other options listed, such as pushing the start button, having the MDP switch in the ON position, and turning on the rotating beacon switch, are not directly related to the action of advancing the throttles and maintaining control of the aircraft.

Before starting the engine, it is important to ensure that the work area is free of foreign objects. This is necessary to prevent any potential damage to the engine or aircraft systems. Foreign objects such as tools, debris, or loose parts can pose a safety risk and may interfere with the proper functioning of the engine. Therefore, it is crucial to inspect and remove any foreign objects before starting the engine.

Before entering the cockpit, the first item that should be checked is the egress status safety pins installed. This is important because the safety pins ensure that the aircraft's egress systems, such as the canopy or doors, are secured and will not accidentally open during flight or on the ground. Checking the egress status safety pins is a crucial step in ensuring the safety of the aircraft and its occupants.

The correct answer is 5 minutes. This is the maximum continuous operating time for a J-85 engine being run in Afterburner (MAX) Power. Afterburner is a mode in which additional fuel is injected into the exhaust stream of a jet engine to provide extra thrust. However, running the engine in this mode for too long can cause excessive heat buildup and potential damage to the engine components. Therefore, the maximum continuous operating time in Afterburner power is limited to 5 minutes to ensure the engine's safety and longevity.

Personnel should be briefed on the importance of foreign objects in the workplace to ensure safety and prevent accidents. Foreign objects can pose a risk by causing equipment malfunctions, interfering with processes, or creating hazards. By being aware of the presence and potential dangers of foreign objects, employees can take necessary precautions to maintain a clean and organized work environment, reducing the likelihood of incidents and injuries.

When external power is applied to the T-38C aircraft and the cockpit Battery Switch is in the On position, there is a possibility of the charging voltage exceeding the maximum allowed. This can lead to potential damage to the aircraft's battery and electrical systems. It is important to ensure that the charging voltage remains within the specified limits to prevent any adverse effects on the battery and the overall functioning of the aircraft.

All signals pertaining to ground engine operation of the T-38C aircraft must originate from the cockpit. This means that any commands or actions related to the engine operation, such as starting or stopping the engines, must be initiated from the cockpit. The cockpit is where the pilot sits and controls the aircraft, so it is the central location for all operations and communications related to the aircraft's functioning.

The maximum continuous operating time for a J-85 engine being run at Military Power is 5 minutes. This means that the engine can operate continuously at its maximum power output for a duration of 5 minutes without any adverse effects. It is important to adhere to this time limit to prevent overheating or damage to the engine.

After the engine is shut down, it is recommended to check the engine oil level within 15 minutes. This is because during operation, the engine oil circulates throughout the engine and various components, ensuring proper lubrication and cooling. After the engine is turned off, the oil begins to settle, and checking the level within 15 minutes allows for an accurate measurement before the oil fully settles. Waiting longer than 15 minutes may result in an inaccurate reading as the oil may have already settled in the oil pan.

When running aircraft engines at night, it is important to have the Position and Beacon lights on. The Position lights, also known as navigation lights, are used to indicate the position and direction of the aircraft to other pilots and ground personnel. These lights are typically located on the wings and tail of the aircraft. The Beacon light, on the other hand, is a rotating or flashing light located on the top or bottom of the aircraft. It is used to increase visibility and alert others of the aircraft's presence. Having both the Position and Beacon lights on ensures maximum visibility and safety during night operations.

When engines are being operated, it is recommended to stay at least 12 feet away from the engine inlet. This distance is necessary to ensure personal safety and prevent any potential hazards that may arise from the engine's operation. Being too close to the engine inlet can expose individuals to high temperatures, strong winds, and flying debris, which can be dangerous. By maintaining a safe distance of 12 feet, the risk of injury or accidents can be minimized.

The engine anti-ice valve is responsible for preventing ice from forming on the engine during flight. Monitoring the Exhaust Gas Temperature (EGT) is crucial for testing the valve because it indicates the temperature of the gas leaving the engine. If the EGT is too low, it could mean that the anti-ice valve is not functioning properly and may need to be inspected or repaired. Therefore, monitoring the EGT helps ensure the effectiveness of the engine anti-ice system.

During an engine compressor stall, there is an interruption in the flow of air through the compressor. This can lead to a decrease in engine speed as the compressor is not able to maintain the required airflow. Additionally, the interruption in airflow can cause an increase in exhaust gas temperature (EGT) as the fuel-air mixture is not being properly compressed and burned. Therefore, the correct answer is engine speed reduction and an increase in EGT.

If an aircraft engine is running and there is a generator failure, it is dangerous to attempt to reset the generator more than one time. This is because there is a risk of the generator burning.

If there is an indication of smoke, fumes, or odor in the cockpit during T-38C engine operation, the most correct sequence of events is to first set the throttles to idle to reduce engine power. Then, activate the cabin pressure switch to perform a RAM dump, which helps to clear any smoke or fumes from the cockpit. Next, open the canopy to allow fresh air to enter the cockpit. Afterward, turn the throttles off to shut down the engines and finally, turn off the battery to cut off all electrical power. This sequence ensures the safety of the pilot and minimizes the risk of any further damage or danger.

The engine start time is measured from the initial fuel flow, which is the moment fuel starts flowing into the engine, to the peak Idle EGT (Exhaust Gas Temperature), which is the highest temperature reached during idle. This measurement helps determine the efficiency and performance of the engine during startup.

The correct answer is the #2 engine throttle lever. This lever is located in the front cockpit of the T-38C aircraft and serves as the radio transmit key. When the pilot presses or activates the throttle lever, it also functions as the transmit key for the aircraft's radio communication system.

The correct idle RPM for the J-85 engine used in the T-38C is 47-49%. This means that when the engine is at idle, it should be running at a speed between 47% and 49% of its maximum RPM. This range ensures that the engine is operating at a stable and efficient idle speed, allowing for smooth and reliable operation of the aircraft.

Before starting the engine, it is important to ensure that all accessories and attachments on the aircraft are properly secured. This is crucial for the safety and proper functioning of the aircraft during the flight. If any accessories or attachments are loose or not properly secured, it can lead to malfunctions or accidents during the flight. Therefore, prior to engine start, it is necessary to check and ensure that all accessories and attachments are securely in place.

A sudden change of 10 PSIG or greater in oil pressure indicates a significant and potentially dangerous fluctuation. Such a change could indicate a malfunction or failure in the system, which could lead to further damage or even catastrophic failure if not addressed immediately. Therefore, any sudden change of this magnitude requires an immediate shutdown and investigation to identify and rectify the issue before it worsens.

The correct Military Power RPM for the J-85 engine used in the T-38C is 99-100%.

The Fire Warning lights in the cockpit of the T-38C aircraft are located on the Main Instrument Panel in both cockpits.

The correct Afterburner (MAX) RPM for the J-85 engine used in the T-38C is 99-100%.

The T-38C Static Inverter converts electricity from the DC Bus to 115 VAC voltage.

After completing the engine run in the T38C aircraft, it is recommended to operate the engines for 2 minutes at 70% RPM before shutting them down. This allows the engines to cool down gradually and prevents any potential damage that could occur from sudden shutdown.

The normal fuel flow limits for the J-85 engine operating at Idle are 400-600 PPH.

After making rapid throttle movements, the nozzle position needs to stabilize within a certain range. The question asks how many seconds it should take for the nozzle position to stabilize. The correct answer is 10, indicating that it should take 10 seconds for the nozzle position to stabilize within the permissible flux range.

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If the engine oil pressure of the J-85 exceeds 55 PSIG during cold weather engine operation and does not drop within 6 minutes, the engine should be shut down.

If you experience a No Start when trying to start the J-85 engine, you should wait for 2 minutes before attempting to restart. This waiting period allows time for any potential issues to resolve themselves and for the engine to cool down if overheating was the cause of the initial problem. Restarting too quickly could potentially worsen the issue or cause further damage to the engine.

When shutting down engines, it is important to monitor the Exhaust Gas Temperature (EGT) to prevent post shutdown fires. The correct answer is 350°C because exceeding this temperature could indicate a potential fire hazard. By keeping the EGT below 350°C, the risk of a fire occurring during the shutdown process is minimized.

The maximum acceleration time from Idle to Military Power on the J-85 engine is 10 seconds. This means that it takes a maximum of 10 seconds for the engine to go from idle to its highest power setting.

The maximum allowable oil consumption of the J-85 engine is 6 ounces per hour.

The Variable Exhaust Nozzle (VEN) position at Idle on the J-85 engine is 77-92%. This means that the VEN is adjusted to be within this range when the engine is at idle. The VEN helps to control the exhaust flow and optimize engine performance at different operating conditions.

The correct answer is 3000 +/-150 PSIG. This means that the hydraulic pressure limits on the T-38C aircraft can range from 2850 to 3150 PSIG. This range allows for some flexibility in the hydraulic system while still maintaining a safe operating pressure.

When trimming the J-85 engine in the T-38C aircraft, the correct switch position is "Cabin Pressure in Ram Dump." This means that the cabin pressure should be set to the ram dump mode. Ram dump is a mode in which the cabin pressure is automatically adjusted to maintain a safe and comfortable environment for the occupants of the aircraft. This switch position ensures that the cabin pressure is properly regulated during the engine trimming process.

The correct answer is "As required position." When engines are running in the T-38C aircraft, the Cabin Pressure switch should be in the "As required position" to maintain the desired cabin pressure. The position of the switch may vary depending on the specific requirements of the flight and conditions, so it needs to be adjusted accordingly to ensure proper cabin pressurization.

During the engine start of the J-85 engine, once starting air has been applied, the engine speed must reach a maximum of 14% RPM within 12 seconds before advancing the throttles to Idle.

When retarding throttles from military to Idle power, a momentary flicker of the generator light is acceptable, providing the generator comes back online within 1 second. This means that a temporary interruption in the generator's operation is allowed, as long as it quickly resumes functioning.

The correct answer is the option that allows for the maximum duty cycle for the left and right ignition system. This means that the system can perform the most consecutive starts without overheating or causing damage. The option that states "4 consecutive 30 second starts, then 3 minutes off, then 4 more 30 second starts then 23 minutes off" provides the longest duration of starts (8 starts in total) with sufficient time for cooling off periods in between. This ensures that the ignition system can operate effectively and safely without exceeding its maximum duty cycle.

The maximum allowable transient RPM on the J-85 engine is 107%. This means that the engine can operate at a maximum of 107% of its normal operating RPM for a short period of time during transient conditions. This allows for a temporary increase in power output when needed, such as during takeoff or maneuvering. Operating the engine at higher RPMs for extended periods of time can cause damage and reduce its lifespan, so the maximum allowable transient RPM is set to ensure safe and reliable operation.

The J-85 engine ignition system is energized for approximately 30 seconds, with a possible variation of plus or minus 3 seconds. This occurs when either the start button is pressed or the throttle is placed in the Afterburner (MAX) position.

A sudden change of 10 PSIG in oil pressure while operating the J-85 engine in the T-38C aircraft at any stabilized engine RPM is cause for engine shutdown and investigation. This indicates that a significant and abrupt fluctuation in oil pressure could potentially indicate a malfunction or failure in the engine system, which requires immediate attention and investigation to ensure the safety and functionality of the aircraft.

The maximum RPM allowed on the flight line for installed engine run-up is 75%. This means that during the engine run-up procedure, the RPM should not exceed 75% of the engine's maximum RPM capability. This limit is set to ensure the safety of the aircraft and prevent any potential damage to the engine or other components. By adhering to this limit, the aircraft can undergo necessary maintenance and testing while minimizing the risk of accidents or malfunctions.

If the engine Exhaust Gas Temperature (EGT) does not begin to rise within 12 seconds after the first indication of fuel flow, it is recommended to abort the start by placing the throttles in the OFF position. This is important because a delayed rise in EGT could indicate a potential issue with the engine start-up process, and it is safer to stop the start-up procedure to prevent any further damage or hazards.

If the Fuel Shutoff Switch is closed while the engine speed is above a certain RPM and the throttle is not in the off position, the engine driven fuel pump may be damaged. This suggests that the engine driven fuel pump is sensitive to the fuel shutoff switch being closed under these conditions.

The normal Exhaust Gas Temperature (EGT) limit for the J-85 engine operating in Afterburner (MAX) is between 630°C and 650°C.

The normal fuel flow limits for the J-85 engine operating at Military Power are 2100-2700 PPH.