Full examen 5

The fuel pump of the APU: It is a mechanical pump, driven by an accessory gearbox. It is located in the LH wing tank (aircraft). It is an electrical two stages pump, controlled by the APUC.

Fuel quantity management system (FQMS): Gives data to the common core system (CCS). Controls fuel pump and valve operation. Supplies power to the override jettison pumps.

The fuel scavenge pump and fuel scavenge isolation valve work together to: Remove fuel from main tanks. Remove all fuel from center tank. Drain fuel from surge tank, during overfill operation.

If the APU fire extinguishing bottle has overpressure: The safety relief disc will break and the agent release into APU fire zone. APU fire extinguishing bottle does not have overpressure relief valve. The safety relief disc will break and the agent release into stabilizer compartment.

The type of compressor that the APU has is: Centrifugal and axial, dual stage. Axial, dual stage. Centrifugal, single stage.

HP shaft is supported by: Front two ball bearing and rear one roller bearing. Front one ball bearing, and rear one roller bearing. Front one roller bearing and rear one ball bearing.

The oil debris signal conditioner is used to: Read data from engine oil level sensor. Compare the oil debris sensor (ODS) data to predetermined levels. Trigger a status messages if the oil supply filter is clog.

To pressurize and control the fuel for starting and normal operation, the system uses: A fuel module. A fuel control unit. A mechanical fuel pump and control unit.

The cargo compartment fire extinguishing flow valves are used to: Filter extinguishing agent from low rate discharge (LRD) bottles. Send the extinguishing agent to forward or aft/bulk cargo compartments. Send the fire cargo alarm to cargo fire protection system (CFPS) function.

Water scavenge jet pumps are used to: Prevent water build-up in the main tanks only. Prevent water build-up in all tanks. Move fuel from the center tank to the main.

With AC Power ( External Power ) and NO fuel pumps selected on P5 panel, wich fuel pump comes on to send fuel to the APU?. The Left FWD Boost Pump. The Left AFT Boost Pump. The DC APU Pump.

What functions can you do from the Refuel Control Panel (RCP)?. Refueling, Defueling and Transfer. Refueling only. Balancing and Refueling only.

If the fuel control switch is in cutoff position, the engine fire switch (fire handle) is: Locked, because there is no engine fire. In the last position. Unlocked.

During Battery power refueling procedure: Only Left main tank can be refueled. All fuel tanks can be refueled. Only Center tank can be refueled.

When airborne, and if the airplane does not have any variable frequency starter generator (VFSG) on-line, the auto start function occurs: After 60 second delay. After 120 second delay. Immediately, with no delay.

How does the EEC detect if a Low Pressure shaft (N1) breakage has occurred?. Detecting an un-commanded N1 deceleration. Detecting a difference between low turbine speed and low compressor speed. Detecting a difference between high compressor speed and low compressor speed.

Where is the APU controller located?. E12 Rack, forward of the bulk cargo door. Forward E&E compartment. Aft E&E compartment.

How many bleed valves are there?. Five, 3 IP and 2 HP bleed valves. Five, 2 IP and 3 HP bleed valves. Four, 2 IP and 2 HP bleed valves.

When the fuel density sensor (FDS) measures the fuel density?. During flight only. Is used in all airplane operations. During ground operation only.

In the nitrogen generation system (NGS), the flow control valve is used to: Control the nitrogen enriched air (NEA) flow to the fuel tanks. Control the oxygen enriched air (OEA) flow overboard. Control the nitrogen enriched air (NEA) temperature to main fuel tanks.

How many channels does the squib monitor control unit (SMCU) have?. Two channels. One channel. Three channels.

How many fuel pumps are there in the fuel system?. Four pumps; one in each main tank, two in the center tank. Six pumps; two in each main tank, two in the center tank. Three pumps; one in each main tank, one in the center tank.

How could you open the T/R cowis for maintenance if the power door opening system (PDOS) is inoperative?. You need use a manual hand pump method. You can use the right hydraulic system. You can not open the T/R cowls if the PDOS is inoperative.

How many igniters are used by the EEC for in flight engine start?. One igniter during first attempt and both two igniters for others attempts. Both two igniters,. One igniter only.

The main parameter of the Trent 1000 engine is: TPR. EPR. N1.

The jettison system remove fuel from: All three fuel tanks. Main tank only. Center tank only.

Where are the thrust reverser feedback units located?. Next to the upper actuators. Aft zone of translating sleeves. Inside of the lower actuators.

For supplying fuel to the combustion chamber, the fuel system has: 12 duplex nozzles. 6 simplex and 6 duplex nozzles. 12 simplex nozzles.

The APU controller sends a close signal to APU air inlet door if: The APU selector switch is in off position only. APU RPM is less than 15%. The remote shutdown switch in the P40 is pushed.

For starting purpose, the APU uses: Pneumaic Starter. Both ASG, allways. One ASG.

How many low pressure turbine speed probes are there?. There are not turbine speed probes. Four. Two.

The air separation module has: Five membrane separators connected in parallel. One active and two backup membrane separators. Three membrane separators connected in serial.

Which air is used by the engine section stator (ESS) system to prevent ice in the intermediate inlet compressor?. 2,5 station. 1P8. HP6.

If both channels of squib monitor control unit (SMCU) are inoperative, then: The cargo fire extinguishing will work normally. The cargo fire extinguishing is operative in aft cargo only. The cargo fire extinguishing is inoperative.

The drains collector tank receives fuel drained from: VSV and TCC servo actuators. Fuel manifold after an engine shutdown on ground only. Fuel manifold after an engine shutdown on ground or flight.

If the secondary air system (SAS) valve is open, Wich air is used to seal and pressurize the HP / IP turbine bearing chamber. HP 6. HP 3. IP 8.

For boroscope purposes How can be turned manually the IP Drum?. With a turning tool that attaches to the breather housing. Using an special tool to conect in either VFSG. Moving the fan disk faster than normal.

When is the amber REV indication shown on the EICAS?. When the translating sleeve are fully deployed. When a thrust reverser trouble has occurred. When the translating sleeves have been move more than 10% and less than 90% of deploy.

The Rolls Royce Trent 1000 has shaft breakage detections in: N1 only. N1 and N2 only. All three shafts.

The Fuel quantity data concentrator (FQDC): Controls fuel valves and pumps operation. Converts Analog / Digital signals and send data to the COS. Is a function hosted in the CCS.