Embraer 190 - Ice And Rain Protection

The correct answer is four smart and two TAT probes. This means that there are a total of six probes installed on the nose fuselage section of the airplane. Four of these probes are smart probes, which are used for measuring various parameters, and two of them are TAT (Total Air Temperature) probes, which measure the temperature of the air entering the aircraft. Each probe also has a dedicated heater, which helps to maintain accurate measurements in different weather conditions.

If one bleed air fails, the anti-ice system automatically opens. This means that if one of the bleed air sources fails, the anti-ice system will automatically activate and open to allow the opposite bleed air source to be used for both wings' anti-ice. This ensures that both wings are still protected from ice buildup, even if one bleed air source is not functioning properly.

During ground operation, when an aircraft is moving at low speeds and there is visible moisture in the air, ice can accumulate on the engine cowls. However, this ice may not be detected by the ice detectors on the aircraft. Therefore, the statement is true.

If one ice detector fails, it means that there is no longer a backup system in place. Therefore, if the remaining sensor detects an icing condition, the system needs to automatically activate the engine and wing anti-ice systems to prevent ice buildup and ensure safe operation.

When wing anti-ice is required for takeoff, the MCDU DATASET "ALL" commands the wing anti-ice valves to open when the wheel speed is above 40 kt.

The APU is not capable of supplying bleed air for the anti-ice operation. This means that the APU does not have the ability or capacity to provide the necessary air for the anti-ice system to function.

When the SAT temperature for take off is lower than 5°C, it means that the temperature is cold. In such conditions, it is necessary to set the A/I system on the MCDU (Takeoff Dataset Menu) to ALL. This means that both the engine and wing anti-ice systems should be turned on to prevent ice buildup on the engine and wings, ensuring safe takeoff and flight.

In case of a dual ice detector failure, the anti-ice operation is only possible in the manual mode. This means that the automatic activation of the anti-ice system will not occur if both ice detectors fail. Instead, the pilot will need to manually activate the anti-ice system to prevent ice buildup on the aircraft.

The correct answer is ALL. When the MCDU setting is set to ALL, the engine anti-ice valves are commanded open after the completion of engine start and the wing anti-ice valves are commanded open when the wheel speed exceeds 40 kt. This selection is confirmed by the EICAS status message ENG TDS REF A-I ALL.

The MCDU setting operates the anti-ice system and inhibits the ice detectors activation logic during takeoff until 1700 ft AGL or 2 min after liftoff, whichever occurs first. This means that once the aircraft reaches an altitude of 1700 ft AGL or 2 minutes after liftoff, the ice detectors will be activated and the anti-ice system will be operational. This setting ensures that the anti-ice system is not activated prematurely during takeoff, but is activated at a safe altitude or time after liftoff to prevent ice buildup on the aircraft.

In case of a single AC electrical source in-flight, the left windshield heating is powered. However, if the left windshield heating system fails, the right windshield heating becomes available as a backup option. Therefore, in this situation, there is still windshield heating available through the right windshield heating system.

The windshield anti-ice system, pitot and static ports, and water lines all use electrical power as a heat source. The windshield anti-ice system uses electrical power to heat the windshield and prevent ice formation. The pitot and static ports use electrical power to heat the probes and prevent ice buildup, which could affect the accuracy of airspeed and altitude measurements. Water lines also use electrical power to heat the water and prevent freezing.

The correct answer is ENG. This means that only the engine anti-ice valve will be kept open after engine start. The wing anti-ice valves will remain inhibited closed. This selection is confirmed by the display of the EICAS status message ENG TDS REF A-I ENG.

When the SAT temperature for take off is higher than 5°C and lower than 10°C, the A/I (anti-ice) system on the MCDU (Takeoff Dataset Menu) must be set to ENGINE ONLY. This means that only the engine anti-ice system should be activated during takeoff, while other anti-ice systems such as wing or tail anti-ice should remain off.

The correct answer is "activated if icing conditions exist." This means that after landing, the Ice Protection System should be turned on if there are icing conditions present. This is important because the system is designed to prevent ice from forming on the aircraft, which can be dangerous and affect its performance. By activating the system in icing conditions, the aircraft can safely continue its operations.

The wing anti-ice system tests itself during flight (SAI IBIT) 10 minutes after takeoff or at 10000 ft AGL, whichever occurs first. At this time the Slat Anti-Ice Valves will be opened (EICAS messages A-I WING VLV OPEN and A-I Synoptic page will indicate that valves have opened).

The engines cowls and wing slats use bleed air from the engines as a heat source. Bleed air is a portion of compressed air taken from the engine's compressor section. It is used for various purposes, including anti-icing systems. In the case of engines cowls, the bleed air is used to prevent ice formation on the cowl surfaces. Wing slats also utilize bleed air to prevent ice formation and ensure proper functioning.

The correct answer is "low stage bleed valve." The engines cowls are heated with air from the low stage bleed valve, which is extracted from the respective engine. This indicates that the low stage bleed valve is responsible for providing the necessary air to heat the engine cowls and prevent ice formation. Additionally, it is mentioned that each engine anti-ice system is independent, further reinforcing the importance of the low stage bleed valve in providing the necessary air for anti-icing purposes.

The engine bleed valve is fail safe if either the electrical or pressure signal are not present. This means that if there is a failure in either the electrical system or the pressure system, the valve will automatically open to prevent any potential damage or malfunction. This ensures that the engine continues to operate safely even in the absence of these signals.

When an icing condition is detected during flight, the ice detectors activate the wing and engine anti-ice valves to prevent ice accumulation. These valves remain open and activated for a certain period of time after the icing condition is no longer detected. In this case, the correct answer is 5 minutes, which means that the anti-ice valves will continue to remain open and activated for 5 minutes after the icing condition has cleared.

The anti-ice valves will rely on ice detection above 1700 ft AGL or 2 min after liftoff in ENG or ALL modes. This means that in both engine-only (ENG) mode and all modes (ALL), the anti-ice valves will activate and rely on ice detection after reaching a certain altitude or time after liftoff.

When the batteries are the only electrical source to the airplane, only the ADSP 3 will be heated. This implies that the ADSP 3 is the only component that requires heating when the airplane is solely relying on batteries for its electrical power.

The SAI IBIT duration is 60 seconds (maximum) because the test can be finished earlier if all slat temperature sensors have an increase of 10°F. This means that if the temperature sensors reach the required increase before the 60-second mark, the test can be completed earlier.

During the takeoff phase, the anti-ice valves are inhibited closed until a certain altitude or time has passed. This means that the valves will remain closed and the anti-ice system will be turned off. After reaching the specified altitude or time, if ice is detected, the engine and wing anti-ice valves will open to activate the anti-ice system. Therefore, the correct setting on the MCDU for this phase is "OFF" to keep the valves closed until the specified conditions are met.

The windshield heating controller performs its standard power-up BIT routine for 120 seconds when a single AC power is available. This suggests that it takes this amount of time for the controller to fully heat the windshield and complete its routine.

When the TO DATASET MENU is set to OFF or ENG and the MODE SELECTOR KNOB is in the "ON" position, the WING ANTI-ICE ACTIVATION will occur at the moment of liftoff. This means that the wing anti-ice system will be activated as soon as the aircraft leaves the ground during takeoff.