Embraer 170 - 175 Limitations

The maximum altitude that an airplane can fly is 41000ft. This means that the airplane is capable of reaching a height of 41000ft above sea level. At this altitude, the airplane is able to operate efficiently and safely within the limits of its design and capabilities.

The correct answer is 50 ft. This means that the autopilot (AP) can be disengaged when the aircraft reaches an altitude of 50 ft or lower. This altitude is likely chosen to ensure that the aircraft is close to the ground and in a stable position before the pilot takes full control of the aircraft. It is important for the pilot to have control at this low altitude to ensure a safe landing or maneuvering.

The minimum engagement height for AP use is 400 ft. This means that the aircraft must be at least 400 ft above ground level in order to engage the AP (Autopilot) system. This height requirement ensures that the aircraft is at a safe altitude before the autopilot takes control of the aircraft's navigation and flight controls.

The VLO (Velocity Limitation for Extension) refers to the maximum airspeed at which an aircraft's landing gear can be extended. The correct answer of 250 Kts indicates that the aircraft should not exceed this speed when extending the landing gear to ensure safe operation and prevent any potential damage to the landing gear system.

The Max Tailwind component refers to the maximum amount of tailwind that an aircraft can safely operate in. In this case, the correct answer is 10 Kts, indicating that the aircraft can handle a maximum tailwind of 10 knots.

The maximum runway (RWY) slope deviation is between -2% and +2%. This means that the runway slope can vary within this range without exceeding the acceptable limits. A slope of -2% indicates a downward gradient, while +2% indicates an upward gradient. It is crucial to maintain the runway within these limits to ensure safe takeoffs and landings for aircraft.

The VLE refers to the Maximum Landing Gear Extended Speed, which is the maximum speed at which an aircraft can safely operate with the landing gear extended. In the case of the ERJ170, the VLE is 250 Kts, meaning that the aircraft should not exceed this speed when the landing gear is extended to ensure safe operations.

The maximum imbalance that can be had is 360 kg. This means that the difference in weight between the two sides can be up to 360 kg.

The VLO (Velocity Limitation for Operation) for retraction refers to the maximum airspeed at which an aircraft can retract its landing gear. In this case, the correct answer is 250 Kts, indicating that the aircraft should not exceed this speed while retracting its landing gear. This limitation is crucial to ensure the safe operation and functionality of the landing gear system.

The correct answer is 195 Kts. This suggests that the maximum tire speed is 195 knots.

The VRA (Turbulent Air Penetration) at or above 10000 ft is 270 Kts. This means that when flying at or above 10000 ft, the recommended airspeed to penetrate turbulent air is 270 knots. This speed is determined based on various factors such as aircraft performance and safety considerations to ensure a smooth and stable flight in turbulent conditions.

The APU (Auxiliary Power Unit) is a device that provides power to the aircraft when the main engines are not running. In addition to power, the APU also supplies bleed air, which is used for various purposes including air conditioning and pressurization. The maximum altitude at which the APU can provide bleed air for air conditioning is 15,000 ft. This means that above this altitude, the APU will not be able to supply bleed air and other sources of air conditioning and pressurization must be used.

The maximum altitude to start the APU is 30000 ft. This means that the APU (Auxiliary Power Unit) should be started before the aircraft reaches an altitude of 30000 ft. Starting the APU at higher altitudes may not be possible or may cause issues due to the reduced air density and lower oxygen levels at higher altitudes. Therefore, it is important to start the APU at a lower altitude to ensure its proper functioning during the flight.

The APU (Auxiliary Power Unit) is a device in an aircraft that provides electrical power when the main engines are not running. The question is asking about the maximum altitude at which the APU can provide electrical power. The correct answer is 33000 ft. This means that the APU can supply electrical power up to an altitude of 33000 ft.

During ground start, the maximum ITT (Interstage Turbine Temperature) is 815°C. Ground start refers to the process of starting an aircraft's engine while it is on the ground. The ITT is a critical parameter that measures the temperature of the gases in the turbine section of the engine. It is important to monitor and control the ITT during engine start to ensure safe and efficient operation. In this case, the correct answer indicates that the maximum allowable ITT during ground start is 815°C.

The correct answer is the third option. Flaps 1 has a speed of 230 Kts, Flaps 2 has a speed of 215 Kts, Flaps 3 has a speed of 200 Kts, Flaps 4 has a speed of 180 Kts, Flaps 5 has a speed of 180 Kts, and Flaps Full has a speed of 165 Kts. This is the only option where all the given flap speeds match the correct speeds.

The VRA (Turbulent Air Penetration) below 10000 ft is 250 kts. This means that when flying below 10000 ft, the maximum recommended airspeed to penetrate turbulent air is 250 knots. This speed is determined to ensure the safety and stability of the aircraft in turbulent conditions at lower altitudes.

The Max. Ramp Weight (MRW) refers to the maximum weight at which an aircraft can be safely parked or moved on the ground. It includes the weight of the aircraft itself, fuel, passengers, cargo, and any other items on board. In this case, the correct answer is 36150 KG, indicating that this particular aircraft can safely be parked or moved on the ground at a maximum weight of 36150 KG.

The maximum altitude for flap extension is 20000ft. Flaps are aerodynamic devices on the wings of an aircraft that help increase lift and drag during takeoff and landing. They are typically used at lower speeds and altitudes to improve the aircraft's performance. However, at higher altitudes, the air density decreases, which affects the effectiveness of the flaps. Therefore, it is not recommended to extend flaps beyond 20000ft as they may not provide the desired lift and could potentially compromise the safety and stability of the aircraft.

The correct answer is Min 25 PSI / Max 95 PSI. This means that the minimum oil pressure for engines should be at least 25 pounds per square inch (PSI), while the maximum oil pressure should not exceed 95 PSI. Maintaining oil pressure within this range ensures proper lubrication and functioning of the engine.

The Max Landing Weight (MLW) refers to the maximum weight at which an aircraft can safely land. It is a crucial parameter that determines the structural integrity and performance capabilities during landing. In this case, the correct answer is 32800 KG, indicating that the aircraft can safely land at this weight without exceeding its structural limitations.

The APU (Auxiliary Power Unit) is a small engine located at the rear of an aircraft that provides power to start the main engines and operate various systems. It also supplies bleed air, which is used to start the engines. However, the APU's ability to provide bleed air is limited at higher altitudes due to reduced air density. The correct answer, 21000 ft, indicates that the APU can provide bleed air for engine start up to this altitude.

The VRA (Turbulent Air Penetration) at or above 10000 ft in MACH is 0.76 M.

During the "Start / Cont" phase for the APU, the maximum exhaust gas temperature (EGT) is 1032°C, while the maximum continuous EGT is 717°C.

The correct answer is 253 kts. This is the maximum speed for windshield wipers.

The maximum negative pressure is -0.5 PSI. Negative pressure refers to a pressure that is lower than the surrounding atmospheric pressure. In this case, the maximum negative pressure is 0.5 PSI below atmospheric pressure. This means that the pressure inside the system or container is 0.5 PSI lower than the pressure outside.

The Max Zero Fuel Weight (MZFW) refers to the maximum weight of an aircraft without any fuel. In this case, the correct answer is 30140 KG, which means that the aircraft can carry a maximum weight of 30140 KG including passengers, cargo, and other items, but without any fuel onboard.

The correct answer is 7,8 PSI. At altitudes above 37000 ft, the air pressure decreases significantly. The maximum difference in pressure between the outside environment and the inside of an aircraft is measured in PSI (pounds per square inch). Therefore, the maximum difference in pressure below 37000 ft would be 7,8 PSI.

The correct answer is 4714 Kg. This is the maximum usable fuel per wing.

The correct answer is 155°C. This is the maximum oil temperature for engines. It is important to monitor and control the oil temperature to ensure proper lubrication and prevent overheating, which can lead to engine damage.

The correct answer is 34 kg. This means that each wing of the aircraft contains 34 kg of unusable fuel. Unusable fuel refers to the fuel that cannot be used for the normal operation of the aircraft, such as fuel that remains in the tanks due to technical limitations or safety regulations. This amount of unusable fuel is important to consider for fuel planning and determining the range and endurance of the aircraft.

When flying with both engines on at V2+10kt, the maximum bank angle is 25°. Bank angle refers to the angle at which an aircraft is tilted to the side, and it is important to maintain a safe bank angle to prevent stalling or losing control of the aircraft. In this scenario, the maximum bank angle is determined based on the aircraft's speed (V2+10kt). By selecting a bank angle of 25°, the pilot ensures that the aircraft remains within safe operating parameters while maintaining a steady flight.

The maximum fuel capacity is 9496 kg. This means that the vehicle or object in question can hold up to 9496 kg of fuel.

The MAX N1 rating in % for the CF34-8E5 engine is 99,5%.

The correct answer is 960°C. This is the maximum continuous ITT (interstage turbine temperature) that can be sustained without causing damage to the engine components. Operating the engine at temperatures higher than this limit can lead to overheating, degradation of turbine blades, and potential engine failure. Therefore, it is crucial to monitor and control the ITT within the specified range to ensure safe and efficient engine operation.

The correct answer is -54°C / ISA +35°C. This means that the minimum temperature to start the APU is -54°C, while the maximum temperature is ISA +35°C. ISA refers to the International Standard Atmosphere, which is a standard set of atmospheric conditions used for aircraft performance calculations. This answer suggests that the APU can be started in temperatures as low as -54°C and as high as ISA +35°C.

During takeoff and go-around, the maximum allowable Interstage Turbine Temperature (ITT) is 990°C. This temperature limit ensures that the turbine is not subjected to excessive heat, which could lead to damage or failure. By setting a maximum ITT limit, aircraft manufacturers and operators can ensure the safe and efficient operation of the engine during critical phases of flight.

The Max Takeoff Weight (MTOW) refers to the maximum weight at which an aircraft is allowed to take off. In this case, the correct answer is 35990 KG, which means that the aircraft can safely take off with a maximum weight of 35990 KG.

When the aircraft is in AUTO MODE during Takeoff/Go-Around (TO/GA) and there is an engine failure (N-1) or a windshear condition, the maximum allowable ITT (Interstage Turbine Temperature) after 2 minutes is 990°C. This temperature limit is set to ensure the engine's safety and prevent any damage or failure.

When the fluid temperature reaches 125°C, the shutoff valve (SOV) will automatically actuate, isolating the EDP from the respective hydraulic flow line. This is likely a safety measure to prevent damage or overheating of the system.

During takeoff and landing, the aircraft experiences changes in air pressure. The question asks for the maximum negative pressure, which refers to the lowest pressure experienced by the aircraft during these phases. Among the given options, 0.2 PSI is the lowest value, indicating the maximum negative pressure during takeoff and landing.

The maximum gust wind for door operation is 40 kts. This means that the door can safely be operated in winds up to 40 knots. Wind gusts refer to sudden increases in wind speed, so it is important to have a maximum limit to ensure the door does not get damaged or pose a safety risk when opening or closing.

The MIN/N2 rating refers to the minimum and maximum rotational speed of the N2 compressor section of the CF34-8E5 engine. The correct answer is 58,5% / 99,4%, indicating that the N2 compressor can operate at a minimum rotational speed of 58.5% and a maximum rotational speed of 99.4%. This range ensures optimal performance and efficiency of the engine during different operating conditions.

During inflight start, the maximum allowable ITT (Interstage Turbine Temperature) is 815°C. This temperature limit is set to ensure the safety and optimal performance of the aircraft's engine. Exceeding this temperature could lead to engine damage or failure. Therefore, it is crucial for pilots to closely monitor the ITT during inflight start procedures to ensure it stays within the specified limit.

In the event of hydraulic system overheat, the HYD 1 OVERHEAT EICAS warning message will be displayed. The correct answer is 145°C. When the fluid temperature exceeds this temperature, the warning message will be triggered. To address the issue, the SOV (Shut-Off Valve) can be manually commanded through a guarded pushbutton on the hydraulic system control panel.

When flying at V2+10kt, the maximum bank angle is 25°. Bank angle refers to the angle at which an aircraft is tilted or banked while turning. It is important to maintain a proper bank angle during turns to ensure stability and prevent excessive strain on the aircraft. In this scenario, the maximum bank angle of 25° is necessary to maintain control and stability while flying at V2+10kt.

During AUTO MODE, when TO/GA (Takeoff/Go-around) is engaged and there is an N-1 (engine failure) or a Windshear condition, the maximum ITT (Interstage Turbine Temperature) in the first 2 minutes is 1006°C.

The correct answer is 8.6 PSI. The question is asking for the maximum over pressure, which refers to the highest pressure above atmospheric pressure. Out of the given options, 8.6 PSI is the highest value, indicating the maximum over pressure.

When the hydraulic fluid temperature increases to 100°C, the HYD 1 HI TEMP EICAS caution message will be displayed.

When flying at V2, which is the takeoff safety speed, the maximum bank angle is typically limited to 15°. This is because at this speed, the aircraft is still close to the ground and any excessive bank angle could increase the risk of stalling or losing control. Therefore, to ensure safety during takeoff, pilots are advised to maintain a maximum bank angle of 15°.