ATR 72 – Ice and Rain Protection - SmartCockpit - Airline training guides, Aviation, Operations, Safety

For electrical heating, the power is supplied primarily by DC current.

False.

True.

Correct! Wrong!

For electrical heating, the power is supplied primarily by AC wild current.

Freezing rain is a precipitation composed of large super cooled water droplets which may be transformed into clear ice when impacting the skin of the aircraft in negative temperature condition. Nevertheless, if the SAT is slightly negative, these large droplets may not freeze immediately when impacting: clear ice builds up behind the leading edge. The ice detector may become inefficient.

True.

False.

Correct! Wrong!

Aircraft Performance Monitoring (APM) triggering thresholds - Depending on the flight phase, if drag and speed degradation exceed predefined threshold values, messages and/or alerts are triggered. They are organized on three levels of alerting depending on aircraft performance degradation. DEGRADED PERF alert indicates a significant performance degradation (in the order of 22 % or 28 % of drag increase). In climb, the alert is triggered by an increase of drag that generates a drastic reduction of:

Vertical speed.

Speed and vertical speed.

Speed.

Correct! Wrong!

MODE SEL AUTO pb pressed in - Two modes are available. First mode is 'NORMAL' and it is to be used when SAT is between -10 deg.C (14 deg.F) and 0 deg.C (32 deg.F). Second mode is 'ON' and it is to be used when SAT is between:

-20 deg.C (-4 deg.F) and -10 deg.C (14 deg.F)

-30 deg.C (-22 deg.F) and -10 deg.C (14 deg.F)

-20 deg.C (-4 deg.F) and -10 deg.C (14 deg.F)

Correct! Wrong!

Below -30 deg.C (-22 deg.F) icing problems should not be present (no supercooled water).

When DE ICING OVRD mode is selected, boots inflate:

All together without respecting a specific sequence and MFC is partially bypassed.

According to a separate timer and MFC is totally bypassed.

All together without respecting a specific sequence.

Correct! Wrong!

The emergency deicing activation is selected (timing cycle = 60 seconds), the light comes on white and all deicing lights turn off. This position is used when the associated FAULT light comes on.

The ice detector system is self-tested when the aircraft is in flight, and any failure generates a FAULT light with single chime.

True.

False.

Correct! Wrong!

The system is self-tested constantly, and any failure generates a FAULT light with single chime.

Aircraft ice protection is provided by electrical heating of:

Propeller blades, windshields, probes and flight control horns.

Propeller blades, windshields, and probes.

Propeller blades, windshields, probes, flight control horns, and center wing leading edges.

Correct! Wrong!

Rain removal from front windshields is provided by two wipers: Each wiper is driven by a two-speed electric motor. They are controlled by two WIPER selectors on the overhead panel: one for the captain, and one for the F/O. Maximum speed to operate the wipers is _____.

150 kt

160 kt

155 kt

Correct! Wrong!

Horns heating is inhibited on ground.

True.

False.

Correct! Wrong!

The ice detector is mounted _____, alerts the flight crew as soon as and as long as ice accretion is sensed by the probe.

Left of the front fuselage.

Under the left wing.

Under the right wing.

Correct! Wrong!

MODE SEL AUTO pb pressed in - MODE SEL is operative and available depending on the temperature. When selected on, the propeller anti-ice system starts to heat the blades only when NP is sensed above _____.

63 %

13%

52%

Correct! Wrong!

The push to test pushbutton is used to check the ice detector correct operation. Press and hold test button for _____

3 seconds

A minimum of 5 seconds.

5 seconds

Correct! Wrong!

ICING amber label is displayed flashing on FMA (with associated warning) if system works correctly. A ICING DETECT alert is displayed with associated procedure on EWD. Master caution light and single chime are activated.

The ice detector indicates that ice accretion is building up on the aircraft. Therefore, the amber icing light turning off must be regarded as an end of ice accretion and not as an absence of ice on the aircraft. Consequently a visual check must be performed to assure aircraft is cleared of ice after having encountered ice accretion conditions.

True.

False.

Correct! Wrong!

When the ice detector detects ice accretion:

Alert is generated by the amber ICING message on FMA and Vmin OPS is automatically increased.

Alert is generated by the amber ICING message on FMA, ICING AOA (green) light on central panel and Vmin OPS must be increased.

Alert is generated by the amber ICING message on FMA, ICING AOA (green) light on central panel and Vmin OPS is automatically increased.

Correct! Wrong!

The side windows are protected by an electrically heated system consisting of small wires embedded between two plies of glass. It is supplied with 28 V DC and keeps the inner temperature over:

5 deg.C (41 deg.F).

2 deg.C (35 deg.F).

21 deg.C (70 deg.F).

Correct! Wrong!

For the pneumatic system, the engines supply bleed air through the LH and RH deice valves (also called Pressure Regulator and Shutoff Valves, PRSOV) regardless of the engine bleed valves position.

False.

True.

Correct! Wrong!

Aircraft Performance Monitoring (APM) triggering thresholds - Depending on the flight phase, if drag and speed degradation exceed predefined threshold values, messages and/or alerts are triggered. They are organized on three levels of alerting depending on aircraft performance degradation. CRUISE SPEED LOW message indicates a limited performance degradation (in the order of 10 % of drag increase compared to theoretical drag in the same conditions) with a speed decay at least _____ below the expected cruise speed.

20 kt

15 kt

10 kt

Correct! Wrong!

With boots that equip the ATR 72-600, there is no need to wait for ice accretion on airframe before selecting it ON. This system MUST be selected ON as soon as and as long as ice accretion develops on airframe.

False.

True.

Correct! Wrong!

Aircraft Performance Monitoring (APM) triggering thresholds - Depending on the flight phase, if drag and speed degradation exceed predefined threshold values, messages and/or alerts are triggered. They are organized on three levels of alerting depending on aircraft performance degradation. All messages or alerts (cautions and/or warnings) are triggered after a confirmation time of _____.

60 seconds

30 seconds

40 seconds

Correct! Wrong!

ICING AOA light is supplied by the:

ACW BUS 1

DC EMER BUS

DC ESS BUS

Correct! Wrong!

Aircraft ice protection is provided by a pneumatic system operating on areas of the airframe:

Outer, center, and inner wing leading edges, horizontal tailplane leading edges and engine air intakes and gas paths.

Outer, center, and inner wing leading edges, horizontal tailplane leading edges, engine air intakes and flight control horns.

Outer, center, and inner wing leading edges, horizontal tailplane leading edges and engine air intakes.

Correct! Wrong!

WINDSHIELD HTG L or R pb – The FAULT light comes on amber and the FWS is activated when:

The heating system cannot deliver at least 70% of the expected protection or when the heating system is faulty.

The heating system cannot deliver at least 60% of the expected protection.

There is a power loss.

Correct! Wrong!

The light also comes on during MFC test.

As soon as at least one of the ANTI ICING HORNS pb is selected ON, stall alert threshold is:

Increased (in flight only).

Reduced.

Increased.

Correct! Wrong!

The Aircraft Performance Monitoring (APM) system monitors aircraft in-flight performance in order to enhance flight crew awareness about any degradation of performance and especially in icing conditions. Aircraft performance monitoring starts after _____

Landing gear and flap retraction and continues during the flight in clean configuration (flaps 0 and landing gear up) and as long as both engines are operating.

Landing gear or flap retraction and continues during the flight in clean configuration (flaps 0 and landing gear up) and as long as one engine is operating.

Flap retraction and continues during the flight in clean configuration (flaps 0 and landing gear up) and as long as both engines are operating.

Correct! Wrong!

STAT lights - Come on amber and the FWS is activated when the respective probe is _____

Not heated. Static ports are monitored by FWS as soon as one engine is running.

Not delivering enough power. Static ports are monitored by FWS and supplied by the DC EMER BUS as soon as one engine is running.

Not heated. In flight, static ports are not monitored by FWS.

Correct! Wrong!

Propeller anti-ice is performed by resistors installed near the surface of the inboard sections of the blade leading edges. On each propeller, the heating elements are electrically connected in three blades (every other blade). Propeller 1 ANTI ICING PWR and Propeller 2 ANTI ICING PWR are supplied:

Respectively by ACW BUS 1 and ACW BUS 2.

By the DC EMER BUS.

By the DC ESS BUS (or by the DC EMER BUS).

Correct! Wrong!

PROP ANTI ICING CTL and IND is the only one being supplied by the DC EMER BUS.

ATR 72 – Ice and Rain Protection