Boeing 787 - Anti Ice and Rain - SmartCockpit - Airline training guides, Aviation, Operations, Safety

The forward windows are equipped with independently controlled:

Four-speed wiper

Three-speed wiper

Five-speed wiper

Correct! Wrong!

When the WIPER selector in OFF, the respective wiper is off and stowed. Windshield scratching may occur if wipers are used on a dry windshield surface.

The automatic ice detection system senses the existence of icing conditions and provides signals to control the engine, wing, and pack inlet anti-ice. The system has one icing condition detector that measure liquid water content, using TAT and other air data information and temperature sources to determine if icing conditions exist.

False.

True

Correct! Wrong!

The system has two icing condition detectors that are heated electrically after engine start.

Pack Inlet Anti-Ice System - The pack inlet anti-ice system provides ice protection for both ram air inlets for the cabin air compressors. An electric heater on the leading edge of each inlet prevents ice formation and reduces ice formation in the duct during icing conditions. Pack inlet anti-ice functions automatically with signals from the automatic ice detection system. Operation is inhibited:

On the ground and when TAT is above 10 deg.C.

On the ground.

when OAT (on ground) or TAT (flight) is above 10 deg.C.

Correct! Wrong!

All flight deck windows are electrically heated. All windows have exterior surface anti-icing, and interior surface antifogging protection.

True.

False.

Correct! Wrong!

The side windows have interior surface antifogging protection only.

Wing anti-ice may be momentarily shed (60 seconds maximum) during high electrical loads, such as during flap retraction.

False.

True.

Correct! Wrong!

Wing anti-ice may be momentarily shed (30 seconds maximum) during high electrical loads, such as during flap retraction.

Wing anti-ice is powered:

Electrically by 4 separate mats on 3 midwing leading edge slats on each wing.

Electrically by 3 separate mats on 4 midwing leading edge slats on each wing.

Pneumatically by bleed air from each respective engine.

Correct! Wrong!

Wing Anti-Ice System Manual Operation - In flight with the WING ANTI-ICE selector ON, the system is powered any time:

OAT is below 15 deg.C and TAT is below 25 deg.C.

TAT is below 25 deg.C.

OAT is below 15 deg.C.

Correct! Wrong!

When a bleed air leak is detected:

The engine anti-ice valves must be manually closed by selecting OFF the engine anti-ice selectors.

The respective engine anti-ice valves close automatically.

Both engine anti-ice valves close.

Correct! Wrong!

Each engine has an anti-ice system duct leak detection system. If an anti-ice duct leak is detected, the respective engine anti-ice valves close.

The left and right engines have identical, independent anti-ice systems. This allows the remaining system to operate if one engine is shutdown.

True.

False.

Correct! Wrong!

The total air temperature probe is electrically heated for anti-ice protection:

When temperature is below 10 deg.C

In flight.

On ground and in flight.

Correct! Wrong!

The Captains and First Officers windshields are equipped with a windshield washer system. Windshield washer switches command:

A 5 sec application of washer fluid while held for at least 2 seconds.

A 10 sec application of washer fluid while held for at least 5 seconds.

A continuous application of washer fluid while held ON.

Correct! Wrong!

Three pitot probes and two angle of attack probes are electrically heated for anti-ice protection when:

AC power is available.

Either engine is operating.

Both engines are operating.

Correct! Wrong!

With the BACKUP L FWD and R FWD switches in the ON position, a backup antifogging system for the forward windows operates automatically if the primary window heat system fails.

True.

False.

Correct! Wrong!

Engine or wing anti-ice use modifies stick shaker logic, increasing the stick shaker speed and minimum maneuvering speed.

This happens in all conditions.

This happens with with landing flaps.

This happens with flaps out of up.

Correct! Wrong!

With flaps up, the use of engine or wing anti-ice has no effect on stick shaker speed and minimum maneuvering speed.

To maintain aerodynamic stability, system logic controls symmetrical operation of left and right wing anti-ice. If one wing anti-ice thermal mat fails, the wing anti-ice system automatically de-powers the opposite thermal mat to prevent asymmetrical wing icing.

True.

False.

Correct! Wrong!

Automatic ice detection is inhibited on the ground:

Below 60 knots.

Below 65 knots.

Below 75 knots.

Correct! Wrong!

Boeing 787 – Anti Ice and Rain

The forward windows are equipped with independently controlled:

All flight deck windows are electrically heated. All windows have exterior surface anti-icing, and interior surface antifogging protection.

Wing anti-ice may be momentarily shed (60 seconds maximum) during high electrical loads, such as during flap retraction.

Wing anti-ice is powered:

Wing Anti-Ice System Manual Operation - In flight with the WING ANTI-ICE selector ON, the system is powered any time:

When a bleed air leak is detected:

The left and right engines have identical, independent anti-ice systems. This allows the remaining system to operate if one engine is shutdown.

The total air temperature probe is electrically heated for anti-ice protection:

The Captains and First Officers windshields are equipped with a windshield washer system. Windshield washer switches command:

Three pitot probes and two angle of attack probes are electrically heated for anti-ice protection when:

With the BACKUP L FWD and R FWD switches in the ON position, a backup antifogging system for the forward windows operates automatically if the primary window heat system fails.

Engine or wing anti-ice use modifies stick shaker logic, increasing the stick shaker speed and minimum maneuvering speed.

To maintain aerodynamic stability, system logic controls symmetrical operation of left and right wing anti-ice. If one wing anti-ice thermal mat fails, the wing anti-ice system automatically de-powers the opposite thermal mat to prevent asymmetrical wing icing.

Automatic ice detection is inhibited on the ground: