ATR 72 – Powerplant - SmartCockpit - Airline training guides, Aviation, Operations, Safety

There are two sensing torque probes on the reduction gear box. One of them sends a signal to the AFU which controls the torque analogic pointer. The other one sends a signal to the EEC which controls the torque digital counter.

False.

True.

Correct! Wrong!

The propeller control system uses the condition lever, the PWR MGT selector, and the power lever to activate the pitch change mechanism through the governors and associated equipment. The system is protected against:

Low pitch angle in flight, overspeed and hydraulic pressure loss.

Low and high pitch angle, overspeed and hydraulic pressure loss.

Low and high pitch angle, overspeed, overpressure and hydraulic pressure loss.

Correct! Wrong!

At takeoff, as soon as both landing gear absorbers are released, a gate prevents PL angle reduction below FI. At landing _____ , this gate is automatically retracted and the PL can travel down to GI and reverse (below GI).

As soon as one landing gear absorber is compressed

As soon as the two main landing gear absorbers are compressed

Below 10 ft RA or as soon as one landing gear absorber is compressed

Correct! Wrong!

When NH is less than _____, exciters A + B are automatically activated.

50 %

60 %

45 %

Correct! Wrong!

The EEC’s auto ignition logic stops commanding ignition above 65% NH.

When EEC is deselected or lost, exciters A + B can manually be activated, using the MAN IGN pb.

False.

True.

Correct! Wrong!

The HOTEL mode, available on the RH engine only, is only used on the ground to provide aircraft autonomy in terms of air conditioning and DC power supply with the gas generator operating and the propeller locked by a pneumatic brake.

True.

False.

Correct! Wrong!

The propeller is locked by a hydraulic brake.

After a propeller braking or releasing sequence, READY light can remain ON for about _____

30 seconds.

15 seconds.

45 seconds.

Correct! Wrong!

The START label indicates the status of the engine during engine start. What is the meaning of an amber display?

An engine start fault is detected and the engine start sequence is interrupted for at least 30 seconds.

An engine start fault is detected.

Discrepancy between engine start indication and light test, or an engine start fault is detected.

Correct! Wrong!

Each engine is equipped with a high energy ignition system: two engine mounted ignition exciters (A and B) powered by the _____ and two spark igniters, one for each ignition exciter.

DC ESS BUS

DC EMER BUS

Batteries

Correct! Wrong!

If the ATPCS pb is pressed in during flight, uptrim and autofeather function are armed.

True.

False.

Correct! Wrong!

If pressed in in flight, only the autofeather function is armed.

Engine Start Panel - If a start sequence is selected, ignition is selected when fuel shutoff valve is open (controlled by CL). Starter and ignition are automatically deactivated when NH reaches _____.

40 %

54 %

45 %

Correct! Wrong!

The Transition mode is the intermediate mode between Blade Angle Governing mode, and Fuel Governing mode.

It only applies on ground, or in flight at low power and low speed.

It only applies on ground.

It only applies in flight at low power

Correct! Wrong!

The propulsion unit includes an Automatic Takeoff Power Control System (ATPCS). In the case of an engine failure during takeoff, the ATPCS feathers the failed engine, and provides the remaining engine with the uptrimmed takeoff power. This system enables to reduce the power normally used for takeoff by an amount of about _____ below the power certified by the engine manufacturer.

10 %

20 %

15 %

Correct! Wrong!

This is favorable to engine/propeller life without affecting the takeoff performance in case of an engine failure. Full ATPCS (i.e. uptrim and autofeather) is only available for takeoff.

The Power Levers (PLs) are mechanically connected to the Hydro Mechanical Unit (HMU) and to the Propeller Valve Module (PVM) through cables and rods. They control the power plant thrust from MAX rated TQ to MAX reverse.

False.

True.

Correct! Wrong!

In the case of engine failure, the PLs remain active controlling the pitch angle, and therefore associated propeller drag as long as propeller is not feathered.

Engine Start Panel - The START 1 or 2 pb initiates the starting (or cranking) sequence of the related engine provided the ENG START selector is in one of the START positions (or CRANK). The FAULT light comes on amber and the FWS is activated if:

Starter or GCU fails to engage, on RH engine when the propeller brake is ON with the gust lock engaged.

Starter or GCU fails to engage on ground.

Starter remains engaged after 45 %, GCU fails during starting, on RH engine when the propeller brake is ON but the gust lock is not engaged.

Correct! Wrong!

Propeller Speed Governing - This is the normal in-flight governing mode. The Propeller Valve Module (PVM) adjusts the propeller pitch based on the power setting in order to maintain a constant propeller speed NP. This governing is available regardless of EEC is ON or OFF.

False.

True.

Correct! Wrong!

The Fuel Governing control mode is canceled when:

EEC is OFF

EEC is OFF and CL is set to AUTO position.

EEC is OFF or when the propeller is in FEATHER position.

Correct! Wrong!

Propeller regulation is _____ controlled.

Hydraulically

Pneumatically

Electronically

Correct! Wrong!

The Propeller Valve Module (PVM) provides a fuel flow which generates the NH compressor rotation speed.

True.

False.

Correct! Wrong!

An EEC provides control of fuel flow in the Hydro Mechanical Unit (HMU), through a stepper motor in such a way as to control the torque in accordance with outside conditions and positions of the power lever (PLA), the power management selector (PWR MGT selector) and the bleed valves. The HMU provides a fuel flow which generates the NH compressor rotation speed.

The propeller brake is installed on a countershaft on the RH engine reduction gearbox in order to stop the propeller (and the power turbine). When the engine is running in Hotel mode:

The LP and HP spool drive the DC generator. Bleed pressure is available downstream the HP compressor and supplies a single pack during normal operations.

The HP spool drives the DC generator. Bleed pressure is available downstream the HP compressor and supplies a single pack when outside temperature is less than 25 deg.C (77 deg. F).

The HP spool drives the DC generator. Bleed pressure is available downstream the HP compressor and supplies both packs.

Correct! Wrong!

The engine accessories are mounted on two accessory gear boxes, one driven by the HP spool, and one by the propeller reduction gear box.

True.

False.

Correct! Wrong!

MAN IGN guarded pb - Manual ignition is selected by pressing the guarded pushbutton. Exciters are continuously energized on both engines. ON light comes on blue. The manual ignition should only be used following an EEC(s) loss(es) under certain flight conditions (Atmospheric or ground icing conditions, engine(s) flame out, emergency descent, severe turbulence, heavy rain).

False.

True.

Correct! Wrong!

The propulsion unit includes an Automatic Takeoff Power Control System (ATPCS). In the case of an engine failure during takeoff, the ATPCS feathers the failed engine, and provides the remaining engine with the uptrimmed takeoff power. Once the mode triggers, its cancellation can only result from either:

PWR MGT selector other than TO, or ATPCS pb set to OFF, or one PL retarted below 20%

PWR MGT selector other than TO, or ATPCS pb set to OFF

PWR MGT selector other than TO, or ATPCS pb set to OFF, or both PL retarded.

Correct! Wrong!

The EEC pb controls the EEC of the associated engine. If selected OFF, the OFF light turns on white and:

The HMU controls only NH as a function of PL angle.

The EEC adjusts the HMU action, and the fuel flow is frozen to maintain the power.

The EEC adjusts the HMU action, by controlling the stepper motor which reduces the fuel flow ordered by HMU.

Correct! Wrong!

ATR 72 – Powerplant