ATR 72-600

The ATR fire protection system provides detection and warning for: Each engine, nacelle and cabin. Engine #2 only, nacelle and cabin. Cockpit, Each engine and cabin.

Where are the smoke detector located?. Inner wing, landing gear and cargo compartment. Cargo compartmens, lavatory and electrical panels in the cockpit. cabin, lavatory, avionic bay, and flight compartment.

What is the maining of "loop" in amber on the EWD. Indicates a fire detection "loop" failure on the corresponding engine. Indicates an imminent fire attempt on the corresponding fire. indicates a malfuntion of the corresponding computer.

What is the name of the device which connects every detection element?. FDCU (fire detection control unit). FACU (fire alerting control unit). MCDU (multi detection control unit).

If a breaking on a sensing element loop a/ lopp b. NO. Yes, is the affected loop is selected to "off" position. Only one loop can sense fire detection.

A "DISCH" warning light will illuminate the fire extinguishing bottle drops below: 522 psi. 252 psi. 225 psi.

After one extinguishing bottle is discharged in case of engine fire, how mucho time do you have to wait in order to discharge the second bottle?. Never wait. 60 seconds. 30 seconds.

what is the name of the device which controls the smoke detection fans?. MCDU Multi-propouse control and display unit. MFC Multifuntion Computer. SDFCU Smoke detection fan control unit.

What happen when the fire handle is pulled (engine 1 or 2) for the agent (1 or 2) on the overhead panel. The agent is discharged. The "SQUIB" light illuminates white and armed. The "DISCH" LIGHT illuminates and the agent is discharged.

What happens when the "test" selector switch is selected to up position (fire test) on the corresponding panel?. The CCAS is activated / the engine fire handle is activated / the associated fire flag on the EWD is displayed /the "fuel shut off valve warning light on the associated condition lever is illuminated. The CCAS is activated / the engine fire label is displayed on PFD/ the associated fire flag on the EWD is displayed / the "fuel shut off valve warning light on the associated lever is illuminated. the CCAS is activated / the engine fire handle is activated / the associated fire flag on the EWD is displayed / the "fuel shut off valve warning light on the associated condition lever disappears.

What happens when the SQUIB TEST push button is pressed on the corresponding fire panel?. The "SQUIB" light illuminates amber. The "SQUIB" light illuminates white. The fire handle activates.

A "NAC OVHT" flag is displayed on the MFD (SD display) when: The thermal switch detects a temp above 170º C inside the R/H engine. The engine fire loop detects a temp above 170ºC inside the R/H engine. the thermal switch detects a temp below 170ºC inside the R/H engine.

The following is NOT true regarding to the extract fan. When "AFT COMPT SMK" & "LAV SMK" are detected the extracts fan keep on running. When "AFT COMPT SMK" is detected the extract fan is stopped. When "LAV SMK" is detected the extract fan is stopped.

Hp bleed valve opens at low power engine ranges and regulates air pressure at: 52 psi in flight or 38 psi on ground. 25 psi in flight or 28 psi on ground. 25 psi in flight or 38 psi on ground.

A flow limiting Venturi is installed inside the HP bleed duct immediately after the compressor outlets, for protection aganist: Excess bleed overflow, into the engine nacelle in case of downstream duct failure. Excess bleed overflow, into the engine compressor in case of downstream duct failure. Excess bleed overflow, into the engine LP compressor in case of downstream duct failure.

A LP ckeck valve is installed in the LP bleed Duct to prevent: Reverse flow towards the LP Compressor when the HP Bleed Valve is open. Reverse flow towards the HP Compressor when the HP Bleed Valve is open. Reverse flow towards the LP Compressor when the LP Bleed Valve is open.

This installed only on the LH side: A bleed Air Check Valve (avoids airflow toward left Engine Compressor in Hotel Mode). A LP Check Valve (prevents Reverse flow towards the LP Compressor when the HP Bleed Valve is open). A handling Bleed Valve (which provides adequate surge margin and good steady state engine power characteristics).

The Crossfeed Valve installed in the pressurized area opens: Only in flight. Only on ground. During take-off only.

A bleed air duct over temperature is exceeds at: 764ºC. 243ºC. 274ºC.

What is the purpose of the Bleed Air Check Valve?. Prevents air flow into the engine LP compressor when the HP bleed air valve is open in low engine power conditions. Prevents air flow into the engine HP compressor when the LP bleed air valve is open in low engine power conditions. Prevents air flow into the engine air intake when the HP bleed air valve is open in low engine power conditions.

The Bleed Air Shut Off Valve is: Pneumatically actuated and electrically controlled. Electronically actuated and Pneumatically controlled. Fuel muscle actuated and Pneumatically controlled.

How many Bleed Air Overtemperature Switches are found in the aircraft?. 6. 4. 2.

The Bleed Air Pressure Switch detects air overpressure above: 45 psi. 48 psi. 80 psi.

when an overpressure is detected by the Bleed air Pressure Switch the air shut off valve will: close. open. Goes to neutral position.

The air leak Detection System protects LH and RH: Engine nacelle fairings. Bleed air ducts. Bleed Air Shut-Off Valves and Cross feed Valve ducts.

The Air Leak pushbuttom test is used to: Test the engine bleed air ducts. Test the bleed air shut off valves. Test the continuity of the loops, the controller and the associated warnings.

The control Unit for the air leak detection system is installed. Shelf 80VU. Shelf 92VU. Shelf 72VU.

One of the safety precautions seen on the training course is: Test the PTT pneumatic system before set battery on. Check the bleed shut off valve before the operation. Check that Pneumatic system is depressurized.

The Pack Valve is: electrically operated and pneumatically activated. pneumatically operated and electrically controlled. Hydraulically operated and ram air actuated.

The air conditioning system is divided in. Air condition, air cooling, air temperature and air distribution. Air condition, air cooling, air supply and air distribution. Air condition, pressurization air, air temperature and air distribution.

According to the training course the word "conditioning" means. Improvement of the of the ambient ram air. Cooled, dried and compressed air. Smooth air delivered to the cabin and flight compartment.

Mark if the following sentence is false or true: "The cross feed opens only on ground with one engine bleed valve open ( the other one closed)'". False. True. None of above.

In case of pack overheat (204°C) will: Opens automatically. Must be close manually. Closes automatically.

A cooling turbo-fan provides cooling air. Only on ground. On ground and flight with aircraft speed is above 150kts and landing gear up. On ground and flight with aircraft speed is lower 150kts and the landing gear up.

The air supplied to the passenger compartment and flight compartment is delivered from: R/H engine: passenger compartment and L/H engine: flight compartmen and 32% of the flight compartment. L/H engine: passenger compartment and R/H engine: flight compartment and 32 % of the flight compartment. R/H engine: passenger compartment and L/H engine: flight compartment.

Depending on the aircraft configuration, cooling of the heat exchangers is provided by: The T.I.C valve. Ram air only. Ram air inlet or by the ground cooling turbo-fan.

What is the purpose of the water extractor?. Extract water from the compressor duct and spray it on the turbine. The water extractor extracts water from the air then, the water is sprayed the cooling air stream and contributes to the efficiency of heat exchangers. The water extractor extracts water from the air then; the water is sprayed in the compressor outlet.

The air cycle machine consist of: A mixing section and a turbine section. A condenser section and a compressor section. A compressor section and turbine section.

Turbo fan Shut-off valve is energized by: The MFC when the pack valve push button is selected ON with the aircraft on ground. The CAC's when the pack valve push button is selected OFF with the aircraft on ground. The MPC when the pack valve push button is selected ON with the aircraft is in flight.

The electronic temperature controller is located on: On the forward landing gear fairing compartment. On the 93VU and the 94VU racks. On the nose wheel avionics compartment.

In manual mode, each temperature control valve is controlled directly by: The overhead air conditions panel zone temperature demand selector. A electronic temperature controller. A temperature trimming resistor.

In automatic mode, the temperature selector allows a cabin termperature of: between 16º C and 32º C. in automatic mode no selection is allowed. 15ºC and 23ºC.

The hot bypass start to open when the temperature control valve opens at about: 25%. 42%. 50%.

The hot bypass valve is: Slave and controlled by the Temp Ctl. Valve in automatic and manual mode. Master and controlled by the pack Valve in automatic mode only. Master and controlled by the Temp Ctl. Valve in automatic mode only.

OVHT light illuminates when the duct temperature is greater than: 62ºC. 92ºF. 92ºC.

On ground, the conditioning of the cabin can be accomplished by: Only by engine 2 in hotel mode only. The ground cart only. Either engine or the ground cart.

The recírculation fan thermal switch closes when the floor temperature falls below: 21ºC. 81ºC. 18ºC.

In which case the recirculation fan pushbuttom FAULT light illuminates " AIR RECIRC FAN" on EWD flashes, MASTER CAUTION flashes and single chime is heard?. When a recirculation fan underspeed or overheat is detected. When a recirculation fan overspeed or overheat is detected. When a recirculation fan underspeed or short circuit is detected.

On ground when the engine 1 is not running, air is evacuated through: The overboard ventilation valve. The underfloor ventilation valve. Anti-smoke valve.

In flight or on ground with engine 1 running the overboard ventilation valve is: closed. open. in transition.

As engine one starts, the extraction fan is inhibited from running from________and exhaust mode FAULT light illuminates. 112 seconds. 120 seconds. 102 seconds.

n flight, in case of air extraction fan overheat or underspeed, which light comes ON?. No light. The OVBD valve Fault light and the Exhaust mode Fault light. The Exhaust mode FAULT light.

What is the purpose of the Overboard Ventilation Valve?. It is used to discharge avionics ventilation air out of the aircraft. It is used to discharge overpressure out of the aircraft. It is used to ventilate the flight compartment.

The gaseous fumes produce by both batteries are evacuated: Directly outside by the extraction fan. Directly outside by the ventilation fan. Directly outside from the overboard valve.

The lavatory ventilation is ensured by: Air from cabin area distribution and discharged directly. Air from the individual distribution and discharged directly. Air from the bled air from a dedicated compressor and overboard overboard discharged directly overboard.

If a Manual Override needs to be accomplished by selecting FULL OPEN during an emergency procedure or for a Test, You need to check that: The Differential Pressure is less than 1psi. The Outboard Valve is in a transition Mode. The extract Fan is not operating.

What is purpose of the ELV SET switch in the Automatic Pressurization Control Panel?. Selects the elevation of the planned destination airport shown by the landing elevation display. Selects the pressurization target. Selects the rate of discharge in case of a Go Around.

What happen when the DUMP guarded pushbuttom in the Automatic Pressurization Control Panel is selected in the On position? (only in AUTO mode). The Outboard valve fully opens. he Pneumatic Outflow Valve Opens Only. Both Outflow valves are commanded fully Open.

What is shown when you make a test on the Automatic Pressurization Panel?. It displays alternative 18,800 and 8000 as long as the push buttom is pressed and a FAULT legend appears in MAN pushbuttom on the Manual Pressurization Control panel. It displays alternative 800 and 8000 as long as the push buttom is pressed and a FAULT legend appears in MAN pushbuttom on the Manual Pressurization Control panel. Nothing Happens.

As a Safety precaution, before undertaking work on the Air conditioning System, be sure that: both the Pneumatic system and the Air conditioning system are Depressurized. Do not use tools with Grease. Follow the Supervisor instructions.

Opening a pressure sealed door when the aircraft is fully or partially pressurized will cause: An explosive Decompression. Death or Injury to the personnel and damage to the aircraft could occur. Damage to the ADC1 and ADC2. Nothing Happens.

The Ice protection Levels are: 1. Permanent Protection, 2. Anti-Icing Protection, 3. De-icing Protection. 1. Pneumatic Protection, 2. Anti-Icing Protection, 3. De-icing Protection. 1. Permanent Protection, 2. Melting-lcing Protection, 3. De- icing Protection.

The purpose of the AMP function ( Aircraft Performance Monitoring) is: To reinforce the knowledge and awareness of the Crew with regard to severe icing conditions during flights. Display the isolation valves malfunction. Monitor the engine bled air flow.

Anti- Icing allows level 2 Ice protection control which consist of: Leading Edges, Rudder and Horns. Propeller, Horns and Side window heating control. Windshields, Propeller, and engine intakes heating Control.

The pneumatic de-icing system is supplied by air, bled from: The electrical power compressor. The engine high pressure compressor. External Air Directly.

The Ice detection probe has an axial frequency of. 40 KHz. 34 KHz. 14KHz.

The ICING Angle of Aftack green light goes out when: Horns anti-icing pushbuttons are selected OFIF. It is turn off automatically by the MFC's. Horns anti-icing pushbuttons are selected OFF and the push- button on the Ice Detector panel is manually depressed by the flight Crew.

The propeller is driven through: A reduction gear box (RGB) by free or power turbine. A reduction gear box (RGB) by the LP turbine. An accessory reduction gear box (RGB) by free or power turbine.

The propeller brake is fitted on: The reduction gear box on the right engine. The propeller hub disc on the right engine. accessory gear box on the left engine.

Propeller oil supply and controls comprise following components: An internal oil cavity, A HP pump, An accessory Gear box and a Hydraumechanical unit HMU. An internal oil cavity, A HP pump, An electrical feathering pump and a Propeller valve module. An internal oil cavity, A HP pump, A Hydraulic feathering pump and a Propeller valve module.

How is controlled the propeller blade angle in normal condition?. Mechanically with the condition levers acting on the hydraulic valves. Electrically with PEC modulating hydraulic pressure through the EHV. Mechanically with the power levers acting on the hydraulic valves.

Complete the sentence: Feathering Pump electrical motor is heat sensitive. Allow____minutes cooling time if the pump is activated more than_____ seconds. 30-40. 10-15. 10-30.

The Synchrophaser control can be de-activated if the selected governing RPM of the slave propeller differs more than: 16 RPM. 4 RPM. 6 RPM.

The single coil pulse generator is installed on: The engine 2. The engine 1. Both Engines.

Which component allows momentary propeller overspeed to reach fully reverse operation?. The EHV. The overspeed governor. The Electrical Feathering Pump.

During ground governing mode, at low power, the EEC automatically increases the fuel flow to maintain at: 82%. 100%. 70.8%.

When the pulse generator signal is lost the Np counter on the EWD displays: XXXX. NULL. ------- (DASHES).

The propeller brake system is supplied by: The yellow system. Blue system. Electrical feathering pump.

Is it possible to use the blue hydraulic pump to engage the propeller brake?. Yes , because NP is over 66 %. No, because the ACW generator is lost. Yes , because NP is below 66 %.

Which are the conditions necessary to lock or unlock the propeller brake?. Hyd. Press Available, A/C on Ground, Right fire handle not pulled, Gust lock ON, CL to FTR or Fuel s/o. Hyd. Press Available, A/C on Ground, Left fire handle not pulled, Gust lock ON, CL to FTR or Fuel S/O. Hyd. Press Available, A/C on Ground, Right fire handle not pulled, Gust lock ON, PL to FTR or Fuel S/O.

One of the following indication is not true regarding to the statements. LO PITCH (green)-pitch below 8 (PL less than FI). LO PITCH (amber)-pitch below 8 (PL less than Fl). LO PITCH ( green) pitch below 8 (PL on T/O notch).