EXAMEN ATA 70 ENGINE

How many Pivoting blokers doors has the Thrust reverser system in each engine?. 3. 4. 5.

The Thrust reverser system Indication is show in ECAM in the middle of which indication?. N1. N2. EGT.

Where is located the N1 TACHOMETER- for CFM56?. AGB. N1 (Fan case lh side). N1 (Fan case Rh side).

The Fuel return Valve Principle is BASED On the?. OIL TEMP / FUEL TEMP. Hyd Pressure. Thrust Reverse Position and Oil Temp.

The PMA supplies electrical power to each ECU channel when: Rotational engine speed N2 <10% rpm. Rotational engine speed N2> 55% rpm. Rotational engine speed N2> 15% rpm.

The FMV (Fuel Metering Valve) inside the HMU is controlled by: ECU. EIU. TLA.

How many degrees open the FAN COWLS in the CFM56-5B Engine?. Minimun 30° Maximum 60°. Minimun 40° Maximum 53.5°. Minimun 40° Maximum 55°.

When the engine master sw is set to off?. HPSOV Valve (High Pressure Fuel Shut off Valve) is energized and the valve close. HPSOV is De- energized and the valve closes. HPSOV solenoid is energized and the valve closes.

Servo fuel is sent from the HMU to: VBV, VSV, HPTACC, FMV, TBV. VSV, VBV, LPTACC, FMV and Start Valve. HPTACC, LPTACC, VBV, VSV, FMV, TBV.

How many valves closes When the master SW is set to off during the shut down procedure?. 3 Valves: HPSOV and Fuel Return Valve. 2 Valves: LPV and Fuel Return Valve. 2 Valves: LPV and HPSOV.

Which Chapter is ENGINE Instruments or Indication?. ATA 80. ATA 77. ATA 78.

Which Chapter is Engine Oil?. ATA 79. ATA 80. ATA 77.

During a Manual start Which ignition system works?. A. B. Both.

The air system call the VBV uses: 12 Valves. 4 Unison Ring to move stators. 1 Valve.

At which speed opens the pressure valve, which is part of the manifold in the Drain Collector Assembly when the A/C is in flight?. Aircraft speed reaches 300 KTS. Aircraft speed reaches 100 KTS. Aircraft speed reaches 200 KTS.

The LPT (Low Pressure Turbine) consists of?. 3 stages. 4 stages. 5 stages.

The Accessory Gear Box receive movements from the?. LPT Low Pressure Turbine. HPC High Pressure Compressor. LPC Low Pressure Compressor.

During and Automatic Start who controls the Ignition: Automatically control by the ECU. Automatically control by the ECU when the n1 Reached 16%. Automatically control by the ECU When n1 reached 22%.

What is the Output Voltages of the Ignition Boxes: 10 Volts. 20 Volts. 20 Joules.

How many fuel Nozzle has the engine?. 22 Nozzles. 18 Nozzles. 20 Nozzles.

In the Engine Fuel system which cooler FIRST heats the FUEL from the TANKS?. IDG OIL COOLER. Main OIL/FUEL heat exchanger. Servo Fuel Heater.

In which Fuel tank enters the Fuel returning from the Engine via FUEL RETURN VALVE?. Wing Tank. Central Tank.

The Cowlings of the CFM56-5B Engine are?. Fan cowls, thrust reverser and CNA. Fan cowls, thrust reverser C Duct, Centerbody and primary nozzle. Fan cowls, thrust reverser C Duct, Exhaust sleeve and plug.

The Acronyms FADEC means?. Full authority digital electronic control. Full authority data engine control. Full authority digital engine control.

The main ENGINE CFM56-5B FADEC component used to control the Fuel is the: FCU. HMU. FMU.

Where are located the FADEC ground power switches to energized FADEC on ground?. 40 VU. 45 VU. 50 VU.

Where are located the MANUAL START PUSH BOTTONS to manually start the Engines?. Overhead panel. Main Instrument Panel. Center pedestal.

the transient bleed valve bleed air from. 7th stage. 5th stage. 9th stage.

the LPTCC valve uses air in the cfm56-5b from. 4th and 9th stages. 5th and 9 th stages. fan.

the vsv system in the cfm56-5b controls or move. IGV 1st and 2nd and 3nd stators of the LPC stage. IGV 1st and 2nd and 3nd stators of the HPC stage.

IN THE TURBINE SECTION. The High Pressure Turbine (HPT) module consists of 2-stage nozzle and rotor and the Low Pressure Turbine (LPT) consists on 4-stage nozzle and rotor. The HPT module consists of 4-stage nozzle and rotor and the LPT consists on 1-stage nozzle and rotor. The HPT module consists of 1-stage nozzle and rotor and the LPT consists on 4-stage nozzle and rotor.

IN CASE OF METAL PARTICLES DETECTION, THE MASTER CHIP DETECTOR WILL: Send a signal to the Electronic Control Unit (ECU). Send a warning to the ECAM system. Operate a visual indicator for ground inspection.

(Both engines) A NACELLE TEMPERATURE SENSOR MONITORS THE: Accessory gearbox area temperature only. Pylon area temperature only. Core compartment temperature.

THE PURPOSE OF THE LOW PRESSURE AND HIGH PRESSURE TURBINE CLEARANCE CONTROL SYSTEMS IS TO: Prevent overheating of the turbine case. Reduce wear of the turbine blades. Optimize engine performance.

CFM - THE FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) SYSTEM IS SELF-POWERED BY A PERMANENT MAGNET ALTERNATOR WHEN: N2 > 5%. N2 > 58%. N1 > 15%.

THE ENG FADEC GND PWR PUSHBUTTON IS USED TO: Start the engine automatically. Supply the FADEC for maintenance purposes when the engine is not running. Start the engine manually.

BOTH - THE FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) CONSISTS OF: Electronic Control Unit (ECU/EEC) and Engine Interface Unit (EIU). EIU and the engine controls. ECU/EEC, the peripheral sensors and control components on the engine.

The 28 VDC electrical supply from aircraft for each ECU channel is: Directly from the bus bars. Through the EIU. There is not 28 VDC supply from the A/C.

The Master SW (Master Lever) controls: FRV. LP fuel Valve and HP fuel valve. FRV and HP Valve.

During automatic starting the Ignition system is energized at: 10% N2. 16% N2. 25% N2.

During automatic Starting, fuel is sent to the fuel nozzles. Between 20 and 22% N2. Between 15 and 18% N2. Between 45 and 50% N2.

If you need to Reset the FADEC system in an engine, you must: Move the Mode selector sw to Crank or Ign/Start position. Move the FADEC Ground Power sw in panel 50VU to on position. Move the respective Master sw to On then Off position.

After engine shutdown, the FADEC system will be energized for: 50 seconds. 5 minutes. Goes to Standby immediately.

The engine primary parameters are shown in the ECAM EWD: Passing first by the EIU. Directly from the sensors. Directly from the ECU.

The engine reference parameter for perform power calculations is: EPR. N2. N1.

The drain mast has a pressure valve which: Closes when A/C speed is above 200 Kts. Opens when A/C speed is above 200 Kts. Opens when A/C speed is below 100 Kts.

To control de Fuel Return Valve (FRV), the ECU continuously monitors: The engine fuel temperature. The engine oil temperature. The engine fuel pressure.

The FADEC system basically consist of: ECU with 2 channels only. ECU with 2 channels, control and monitoring peripherals. ECU with 4 channels and monitoring peripherals.

The 28 VDC electrical supply from aircraft for each ECU channels is: Directly from the bus bars. Through the EIU. There is not 28 VDC supply from A/C.

The master SW (Master Lever) controls. FRV. LP fuel valve and HP fuel valve (HPSOV). FRV and HP valve.

During automatic starting the ignition system is energized at: 10%N2. 16%N2. 25%N2.

During automatic starting, fuel is sent to the fuel nozzles: Between 20 to 22% N2. Between 15 to 18% N2. Between 45 to 50% N2.

If you need to reset the FADEC system in an engine, you must: Move the mode selector SW to crank or Ign/Star position. Move the FADEC ground power SW in panel 50VU to on position. Move the respective master SW to On then Off position.

To initiate a dry cranking sequence, the correct selection of the following controls should be: Mode selector to IGN START and MAN START push button selected ON. Mode selector to CRANK and MAN START push button selected ON. Mode selector to CRANK, master switch ON and MAN START push button selected ON.

The engine primary parameters are shown in the ECAM EWD: Passing first by the EIU. Directly from the sensors. Directly from the ECU.

the inhibition relay of the reverse system is controlled by. ECU. EIU. HCI.

the FMV ( fuel metering valve) in the HMU is controlled by. ECU. EIU. TLA.

where are located the FADEC ground power switches to energized FADEC on ground. 40vu. 50vu. 45vu.

the fuel return valve principle is BASED on the. oil temp and fuel temp. fuel temp and ambient temp. hyd pressure and hyd qty.