The wing anti-ice and engine anti-ice systems are normally activated automatically based on signals from the ice detection system. They can also be manually activated by the flight crew based on recognition of icing conditions. _____and they provide a surface for the formation and detection of ice.
Two ice detector probes are mounted on each side of nose cone just below the pilot and copilot windows. The ice detector probes measure ice accumulation on the tip of each probe. Ice formation on the probes changes the resonant properties of the probe, proportional to the accumulation thickness.
The WAI system uses hot bleed air from the engines as the main source of energy to maintain the critical wing leading edge areas free of ice. Each engine provides bleed air for its respective wing and there is cross feed between the sides for operation during a single supply for both wings. The bleed air supply is extracted from the low-pressure _____ of the engine.
In normal climb and cruise cases, the 5th stage provides the bleed air for wing anti-icing operation and in cases where the 5th stage pressure is insufficient, such as during descent, bleed air is extracted from the 8th stage.
What is the true statement?
What do amber wing anti-ice lines indicate on ECS/PRESS synoptic page?
Holding in icing conditions is limited to 0 deg. (UP) flaps only. Additionally, a minimum speed of _____ must be maintained when holding in icing conditions.
Engine vibrations may increase when icing occurs. The fan should normally shed the ice, and vibrations will return to a normal level. To help shed the ice when high vibration occurs and operational circumstances permit, one engine at a time may be quickly retarded to idle, held there for _____. The power lever may then be returned to its original position.
A test pushbutton, labelled 'ICE DET' is located on the SYSTEM TEST panel on the cockpit overhead. Depressing the button will initiate an operational test of the ice detector control circuits of the ice protection system. The full system test requires placing the ANTI-ICE control switches in the ON position prior to testing the ice detection system.
The full system test requires placing the ANTI-ICE control switches in the OFF position prior to testing the ice detection system as a preventative measure. Failure to do so may cause the APU generator to drop off line due to the additional electrical load created from the rapid closing of the APU load control valve.
After the amber Ice Detected CAS message extinguishes, the cowl heat continues to receive heat for _____ and the wing heat continues for _____.
What do blue wing anti-ice lines indicate on ECS/PRESS synoptic page?
What kind of rain removal system does G650 have?
Rain removal is accomplished by a serviceable Surface Seal coating on the windshields. The coating is sensitive to abrasive cleaners which degrade the ability of the coating to provide a clear view through the windshields during rain encounters. The Surface Seal coating has been demonstrated to provide satisfactory forward visibility in all precipitation encounters.
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WAI operates regardless of altitude or ice detection.
The Wing anti-ice system consists of two independent control systems, pneumatically linked via the crossover duct. One system provides WAI for left wing and one provides WAI for right wing.
Operations in freezing fog below _____ is prohibited.
There is a temperature sensor located outside the wing leading edge and it monitors the leading edge bay (D-bay) exhaust air temperature and commands the WAI valve through a closed-loop control system in order to maintain the temperature at 130 plus or minus 10 deg.F (54 plus or minus 12 deg.C).
The temperature control system consists of a sensor located inside (not outside) the wing leading edge in the return air exhaust, which is at the inboard portion of the wing.
What is monitored within the duct leading to the engine cowl to ensure that an adequate supply of heated air is available for cowl anti-icing?
Pressure is monitored rather than temperature because the TAI bleed air is drawn off prior to the bleed air system precooler, and therefore the temperature of the air supplied to the cowl is not controllable. A pressure transducer is located within the ducting, downstream of the control valve to measure the bleed air pressure actually delivered to the engine cowl.
Automatic anti-icing is also not available above _____, since air temperatures and moisture content are extremely low and icing conditions unlikely. Engine bleed air can then be fully employed in meeting the demands of pressurization and cabin heating.
An auto anti-ice inhibit relay is installed to prevent automatic activation of Cowl and Wing Anti-Ice (WAI) above 35,000 feet AGL. However, if the automatic WAI function is operating, it will continue to operate.
Engine cowl and wing anti-ice may be manually selected ON at any altitude when ice protection is required.
Ice protection systems on the aircraft employ either warm engine bleed air or heat generated by electrical resistance to prevent the formation of ice on critical structures and installations.
There are two types of protection used on G650: electric and pneumatic.
The anti-iced portion of the engine cowl is represented by a colored band at the front of the graphic depicting each engine. The band is shown in white when the engine is not running. If the engine is running and cowl anti-ice is selected on and the bleed air pressure to the cowl is between 1.6 psi and 33 psi, the band is shown in green. If bleed air pressure is less than 1.6 psi or greater than 33 psi, the band is shown in amber. If the pressure transducer data is invalid, the band is displayed in _____.
The TAT sensing system consists of two identical TAT probes. When the aircraft is on the ground, the probes are aspirated by air from the bleed air manifold.
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Cowl anti-icing is required for taxi and takeoff when Static Air Temperature (SAT) is 10 deg.C (50 deg.F) or below and visible moisture, precipitation, or wet runway are present. When taxiing or holding on the ground at low power in temperatures less than 1 deg.C (34 deg.F), engine operation at _____ is recommended just prior to takeoff and at intervals of not more than 60 minutes under these temperature and moisture conditions.
Are TAT (Total Air Temperature) probes heated on ground?
TAT probes located on the left and right sides of the forward fuselage provide outside air temperature to the associated MFP. The MFP controls and monitors the TAT heater to reduce the power requirements based on temperature and aircraft state.
What happens to cowl anti-ice if both ENG BLEED AIR switches are selected to OFF?
Where is wing anti-ice exhausted overboard?
What happens to cowl anti-ice valve with loss of electrical power or loss of 8th stage air to hold it closed?
What happens to the spinner if ice accumulates during engine operation?
The 16 cabin windows are electrically heated with single phase of high-power alternating current (AC) when WOW is in flight mode.
The 16 cabin windows are electrically heated with single phase of low power alternating current (AC) when WOW is in flight mode and OFF caption is extinguished. When WOW is in ground mode, the 16 cabin windows are not electrically heated and OFF caption is illuminated unless this feature is overridden by activating WDO HT GND BYP switch controlled through MCDU SSPC menu.
What happens when cowl anti-ice is selected to ON?
Where is cowl anti-ice exhausted overboard?
What do green wing anti-ice lines indicate on ECS/PRESS synoptic page?
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The BR-725 engine has been designed such that if the outside ambient temperature is less than approximately ten degrees Celsius (10 deg.C / 50 deg.F), use of the anti-ice systems will not result in a decrease in takeoff thrust.
The FADEC maintains the takeoff Engine Pressure Ratio (EPR) even if automatic activation of the anti-ice system occurs during the takeoff and takeoff climb segments. Additionally, the FADEC incorporates an EPR logic that does not allow thrust degradation due to bleed system configuration changes during takeoff.