cuestionario

the airflow station 5 represent: Low pressure turbine discharge. HP compressor discharge. inter stage discharge.

the low pressure and the high pressure rotors are similar to: N1 and N2. N3 and N4. N1 and ERP.

the exhaust gas temperature (EGT) indicating system monitors the exhaust gas temperature: at the second stage low pressure turbine nozzles. at the second stage low pressure turbine rotor. at the first stage high pressure turbine nozzles.

the purpose of the thermocouple T5 (sensor) is: to be used just for trend monitoring,optional sensor. to control the operation of the HPTCC system. to show on ECAM the EGT of the engine.

the cross in the N2 indication on ECAM means : the N2 value is exceded. thrust reference value is reached. reference signal to put the during engine start.

the FMV is : a hydraulically operated and electrically controlled unit. a hydraulically operated and controlled unit. a hydraulically operated control unit.

the optimum position the VBVs to any given speed is calculated by: ECU using N11-N2-VSV-TRA signals. FMGEC using thrust reference. EIU using throttle lever angle (TLA).

the REV green indication changes to REV amber indication.It will happens when: At least 1 pivoting door is at les than 95% of its travel. at least 2 pivoting doors are between 95% to 99% of the deploy sequence. at least all pivoting door are between 95% to 99%of its travel.

what indication is used to represent low pressure compresor speed: N1. N2. P 2,5.

The scavenge oil to servo fuel heater is monitored by: an electrical master chip detector and must be monitored localy. An electrical master chip detector that sends its signal to ECAM. A clogging indicator.

.related to the fuel nozzles, the Flow divider that separates the fuel flow into primary and secondary flow,is located: in the fuel nozzle itself. in the fuel manifold. in the HMU.

in the reverse system: open command to open the HCU shut-off valve is provided by the ECU. the HCU pressure Sw provide feedback to ECU (hyd press OK). Only the FCPC´s serve as interlock to open the HCU shut off valve.

the rear sump in the engine is accomodation of: bearings Nr 4 to Nr 5. bearings Nr1 ,Nr2 and Nr3. bearings Nr 1 and Nr2 only.

the HP fuel valve is commanded by: the engine master Sw. the ECU. EIVMU.

The ECU receives several sensors signals.The signal of the T3 sensor is used for: controlling. indicating. monitoring.

-.the ECU is normally powered by: in flight from dedicated ECU alternator. in flight from aircraft electrical buses. on ground from a battery bus.

the majority of take-off thrust is provided by: the fan air,secondary stream. the N2 rotor system. the fan air,secondary stream.

the power supply for the ignition system is : 115 VAC from the aircraft network through the EIU, then to ECU to the ignition box. Fail safe us ignition ON (EIU failure). 115 VAC from the aircraft network through the EIU,then to ignition box,fail safe is ignition ON (EIU failure). 115 VAC from the aircraft network through the EIU,then to ignition box,fail safe is ignition OFF(EIU failure).

the structural strength for the FAN frame is obtained from: 12 struts. (Outlet guide vanes)OGV. two bearings.

the modulated idle operation depends of: eng oil temp and A/C flight / ground condition. the high fuel temperature in the main tanks. if it is detected a high fuel quantity in the tanks.

the spinner rear cone is made of: aluminum alloy. composite. titanium.

recirculation of fuel to the tank is inhibited and the FRV closed,when : high tank fuel temperature and high fuel tank level,among other reasons. high oil temp or engine fuel temp. during taxi in,slats extended.

the fuel return valve is controlled by the ECU,in accordance with: The engine oil temperature. the N2 engine speed. the engine fuel temperature and the core speed.

engine thrust is transfered by: Fwd engine mounts only. FWD and AFT engine mounts. aft engine mount only.

the engine urbalance data is obtained from: the engine vibration monitoring unit,via MCDU. the post flight report. directly form the EEC.

If N2 has exceded 105%,a red cross adjacent to the N2 indication appears: remaining the resto of the flight (aditional warning are triggered). and the overspeed governor (OSG) limits the engine speed to minimum idle. and immediately after, ECU initiales a protective shutdown.

the low pressure compressor needs proper operation in all speeds. What component of the following provide the function: VBVs (12). the low pressure turbine ACC system. the VSVs and IGV.

.structural strenght for the fan frame is obtained from: 12 struts. FWD sump. TRF.

what is the basic desing of the dan Blades: titanium alloy; mid- span shrouded. titanum alloy;shroudless. inconel alloy;shroudless.

the location of the starter valve Access door is : fan cowl,right side. fan cowl,left side. thrust reverser,right side.

the LPC and LPT are fixed to: an inner shaft called N1. an outer shaft called N1. an inner shaft called N2.

The CFM56-5B engine can obtain the maximum thrust up to: 30C. 25C. 35C.

how is the thrust reverse system isolated from the hydraulic system: the reverse system is isolated by a HCU. The reverse system is isolated by a shut-off valve. the reverse system is isolated by a inibition relay.

How is the IDG lubricating oil cooled : a fuel/oil heat exchanger. by means of heat exchanger oil/air. from air taken from the bypass duct (fan air).

what does anti-siphon devide avoid: oil from tank draining by gravity to the oil pump. oil from aft sump draining by press to oil pump. oil from system gallery draining by gravity to the tank.

during manual start mode : both ignition system A and B are simultaneously selected. only ignition system B is selected. ignition system A is selected first,and after a time delay ignition system B.

to abort a engine start sequence (automatic or manual) : The master sw must be selected in OFF position. the rotary selector Sw must be set in crank position. a N1 speed of 90% must be reached before to accomplished any corrective action.

which speed signals are supplied to the EVMU: N1 and N2. N2 only. N1 only.

the main purpose of the EIU is: to separate and isolate the engine from the other aircraft systems and compuerts,transfering certain data/parameters. to acquire all engine data and parameters and send them to the ECAM system. to send the different commands and signals from the ECU to the engine.

the low oil pressure condition is activated at: 13 PSI decreasing pressure. 15 PSI increasing pressure. 90PSI.