tiranosaurio rex

1- (navegation) The coaxial supressor cable installed between the DME,ATC and TCAS is used....... A- To prevent simultaneous transmission of those units. B- To intercepte the ATC reply when the DME is in stanby. C- To allow the DME, ATC and TCAS simultaneous operation.

2- (navegacion) How the DME interrogator is tuned ?. A- Selecting a DME frequency on the RMP in bacup mode. B- Selecting a DME frequency whith the MCDU. C- Via Auto/Manual tuning from FMGC or Backup tuning from RMP.

3- (navegation) Each VOR equipment includes the Marker Beacon. Which on uses the maker function. A- VOR/MKR receiver #1. B- VOR/MKR reciver #2. C- VOR/MKR #1 and #2.

4- Navegation) Wich Radio altimeter activates the modes at the ground proximity Warning system ?. A- The stanby altimeter. B- The radio Altimeter #1. C- The radio altimeter #2.

5- ( navegation) The ATC/S frecuency is tuned from.. A- The Capt. Or F/O EFIS control panel. B The frequency is not tuned because is only on for transmission and anothe for reception. C- The RMP in stanby NAV, when the FMGC is failed.

6- (navegation) In normal operation which unit controls the navegation system tuning. A- FMGC1. B- FMGC 2. c- RPM1.

7- (Navegation) During approach. how does the RAs work ?. A- The RA 1 is command and the RA 2 is in STANBY. B- Both are working independently all the times. C- They are not.

8- (navegation) Where is the VOR information shown ?. A- In both NDs and in the DDRMI. B- In the captain ND and in the DDRMI. C- In the F/O ND and in the MCDU.

9- (navegation ) Where is the DME system information shown ?. A- Only in the PFDs. B- In the PFDs, NDs and DDRMI. C- In the Ecam displays only.

10- (navegation ) Who is the main user of the GPIR signal ?. A- The DMCs. B- The FMGCs. C- The VOR and ILS system.

11- (navegation) How is a resolution Advisory, of the TCAS system, in the PFD shown ?. A- By means of a change in the V/S indication. B- By means of a change in the air speed indication. C- In the overhead panel there is a flashing light.

12- (navegation) When you test the ILS1, where is the information displayed ?. A- On the upper ECAM. B- On the capt.PFD and F/O ND. C- On both PFDs and NDs simultaneously.

13- (navegation) WR / PWS. when does the predictive windshear function operate automatically. A- Below 2300 ft. at least one engine running and ATC / TCAS in AUTO or ON position. B- Whenever a windshear event is encountered. C- Above 2300ft. both engines running and ATC /TCAS in AUTO or ON position.

14- (navegation) When does the lateral deviation scale flash on PFD ?. A- When the deviation is excessive. B- When the aircraft is out of range. C- When the signal is NCD (no computed data).

15- (navegation) Which component controls the weather radar antenna stabilization. A- ADIRU. B- Transceiver. C- Antenna.

16- (navegation) LRRA 1 has failed whith a radio altitude below 2500ft, which statement is right ?. A- No radio altitude is displayed in capts. PFD. B- A flag is shown on capts PFD. C- LRRA 2 is used in case of LRRA 1 failure to supply capts. PFD whith radio Alt.

17- (navegation) The ATC-mode S transponder... A- It has only one Antenna. B- Automatically switches to ADIRU 3 if no altitude information is available from the normal ADIRUs. C- Recives the mode S Address via PIN-Programing.

18- (navegation) The MMR comprises the following functions : A- ILS only. B- ILS and GPS. C- GPS only.

19- (navegacion) What are the analog inputs to the ADIRUs Air Data part ?. A- TAT and AOA. B- Heading indication. C- The data base included in the ADIRUs.

20- (navegation) Where is the barometric correction performed ?. A- In the EFIS control panel in the glareshield. B- In the ECAM switching panel. C- In the air data modules.

21-(navegation) Where are the TAT and SAT indicated ?. A- In the PFD. B- in the ND. C- in the ECAM SD.

22- (navegation) When is the ON BAT indicator set to ON ?. A- When the ADIRUs are battery supplied or for 5 sec. during power up test. B- Is set to ON if you press the BAT, BAT2 o the APU BAT switch. C- This indicator doesn´t exist.

23- (navegation) Which DMC8s get information from the ADIRU 3 ?. A- All the DMCs. B- Only DMC 1. C- Only DMCs 1 and 3.

24- (navegation) How are the radio navegation frequencies normally tuned ?. A- Automatically by the FMGEC. B- Automatically by the MCDU. C- Manually from the RMPs.

25- (navegation) In the pitot/ static system, which pressure line (s) need (s) to be drained ?. A- Only the standby static line. B- Only the pitot lines. C- All the pitot and static lines.

26- (navegation) What must be done in case of ADR1 failure?. A- Set air data switch to F/O ON 3 position. B- Set ATT HDG switch to CAPT ON 3 position. C- Set Air Data switch to CAPT ON 3 position.

27- (navegation) Where does heading discrepancy detected ?. A- DMCs. B- ADIRs. C- FWCs.

28- (navegation) How do pitot and static probes supply the ADIRUs ?. A- Pitot and static lines are connected directly. B- Through ADMs which converts input pressure into digital format. C- Through thr SDACs.

29- (navegation) The DDRMI is supplied with heading information from... A- ADIRU 1 or by manual switching ADIRU3. B- ADIRU 2. C- The DDRMI itself.

30- (navegation) The normal present position entry is performed via... A- ADIRs mode selector unit. B- Automatically at electrical power up. C- The MCDU.

31- (auto flight) Which LRU computer the landing capability in the AFS ?. A- The FAC according to the availability of the others computers. B- The FMGC according to the availability of varius sensors and functions. C- The ELAC according to the availability of the sensors.

32- (auto flight) If engine starts on ground : A- you can engage the autopilot system. B- The autopilot will be disengaged, if was engaged before. C- The autopilot will be engaged automatically.

33- Were are the landing capabilities displayed ?. A- In the left ND. B- In the upper part of the E/W display. C- In both PFD/ FMA sections.

34-(auto flight) If both FMGCs fail, can you tune the navegation frequency ?. A- Yes, by the ACP. b- yes, from the RMPs. C- Yes, from either MCDU.

35- (auto flight) The BARO selections are normally controlled by... A- The FCU processor 2 which controls both the F/O an capt.baro selection. B- The FCU processor 1 which controls capt.and f/o baro selection. C- The FCU processor 1 controls the capt. baro selection and ACU processor.

36- ( auto flight) The fault isolation detection system is part of. A- The FAC #1. B- The FAC#2. C- the AIDS.

37- (auto flight) In TOGA mode : A- The A/THR must be engaged manually. B- The A/THR is engaged automatically. C- The A/THR is disconnected.

38- (auto flight) The A/P can be engaged. A- On ground whith bolt engines running. B- Only in cruse phase. C-5 seconds after the lift off.

39- (auto flight) The auto pilot is engaged and the pilot wants to control flight parameters manu...FCU, he must do the following : A- Rotate and pull the associated selector knob. B- Push and rotate the selector knob. C- Disconnect the auto pilot.

40- (auto flight) If one channel in the FCU is inoperative. A- The other channel will be in active and all FCU function operative. B- The A/thr and A/P will be inoperative. C-The F/D #1 and #2 will be inoperative.

41- (auto flight) Can the A/THR be automatically engaged ?. A- Yes, when the thrust levers are moved to the TOGA. B- Yes, when the vertical speed is selcted. C- No, it is never engaged automatically.

42- (auto flight)The FCU SPD /Mach window display dashes lines and the white indicator light... A- The pilot is managing the speed by FCU. B- The FM part of the FMGC is managing the aircraft speed. C- The A/THR is managing the speed by means of throttle lever.

43- (auto flight) The auto flight system calculates orders to control automatically. A- The flight control only. B- The flight control and the engines. C- The engines only.

44- (auto flight) If the alpha floor signal is triggered by the FAC. A- The pilots have to set the T/O thrust. B- The thrust lever are moved to the TOGA position. C- The A/THR function is atomatically active in TOGA thrust.

45- The flight guidence functions are : A- Autopilot modes only. B- Autopilot, flight director and autothrust. C- Guidance along a flight plan.

46- (auto flight) What does the green message "TOGA LK" with an amber flashing box on the FMA means. A- The A/THR is active whith alphafloor protection active and the alphafloor is detected in th....... B- An order to manually set the thrust levers at TOGA detent. C- The A/THR is active whith the alphafloor protection active but with the alphafloor dect..longer present in the FACs.

47- (auto flight) Do the side sticks move during AFS operation ?. A- Yes, they move. B- No, they don´t move. C- Yes, in APP only.

48- (auto flight) The functions of the FMGC are : A- Yaw damper and rudder trim. B- Calculation of the characteristic speed and flight envelope monitor. C- Autopilot, flight director, Autothrust control and flight management.

49- (CAT 2/3) What is DH ?. A- It is the safe altitude of flight. B- It is the minimum height where the pilot can abort the landing. C- It is height for engine shut down.

50- (CAT2/3) What is RVR ?. A- It is the height of a rejected T/O. B- It is the distance where the pilit can see the runway and visual indicat.... C- It is the parameter defined by the aeronautic regulation different in ea....

Which TAT probe provides outside temperature to ADR 3?**. Stby TAT probe. F/O TAT probe. Captain TAT probe.

In case of emergency electrical configuration, what happens with the ADIRU 3?. ADR function is lost immediately , IR function is available. Both ADR & IR parts are de- energized. ADR function is lost immediately, IR function is lost after 5 minutes.

Which is the component used for the display of the ATC exchanged messages?**. The DCDU. The ATSU. The MMR.

What are the ATIMS components?**. ATSU, DCDUs and ATC MSG pushbuttons. SDU, VHF 3 and AMU. FMS, CMS and ATC MSG pushbutton.

What is the purpose of HF Antena Coupler?**. To switch between AM and SSB transmission modes. To math the impedance between the transceiver and antenna. To amplify the RF signal send it the antenna.

CIDS- When is the Emergency Mode activated?**. When ESS BUS and SERVICE BUS are available. When ESS BUS is lost and SERVICE BUS is available. When the SERVICE BUS is lost and ESS BUS is available.

Which unit provides ATTENDAT and MECHANIC call decoding?**. VHF 3. FWC. Selcall Call card on AMU.

In case of RMP 1 failure, VHF 1 is lost.**. TRUE. FALSE.

SATCOM - Which unit provides electronic steering command to point the antenna beam toward the desired satellite?**. D/LNA ( Diplexer/ Low Noise Amplifier). BSU (Beam Steering Unit). RFU ( RADIO frequency Unit).

When the Solid State Cockpit Voice Recorder is recording?**. Aircraft on ground and parking brake set. Five minutes after de- energize the electrical network. At any engine start.

What is the meaning of The " VHF-X-EMITTING" message in the ECAM?**. The HF system is transmitting for more than 60 sec. The VHF system is transmitting for more than 60 sec. The PTT switch has been pressed during less than 60 sec.

In the cockpit, how do you know when a selcal call is coming ?**. By means of the buzzer sound. An ECAM message appears automatically. By mean of a call illuminated amber in the ACP and Buzzer sound.

If capt or F/O audio control panel fail. How can you recover the audio signals?**. Changing the position of the FMGEC switch. There is no back up. Changing the position of the AUDIO switch, to the Cap. on 3 or F/O on 3.

CIDS- who has the priority for the PA announcements? **. The Cabin crew. The pre- recorded announcements. The Flight crew.

CIDS - when is the audio level increased automatically?**. All the time there is noise in the ambient. At engine start or rapid cabin decompression. only when airplane is in flight.

CIDS- how are the DEU's A connected to the Director?**. By means of 2 Arinc 429 buses. By means of 6 high Speed Top Data Bus Lines. They are hardwire on by one.

CIDS- In what case the CIDS CAUTION light goes on?**. When there is a failure associated with any system related with the CIDS. When the Flight crew is calling to the cabin crew. When a pax is calling to the attendant.

CIDS - which are the units directly related with the pax service?**. The Decoder Enconder Units B. The Directors. The Decoder Encoder Units A.

CIDS - How is the CIDS normally powered?**. By means of the Essential bat only. By means of the 28 Vdc Service bus (601pp). By means of both. Essential and Service Bus (CREO).

CIDS - Which are the main computers of the CIDS?**. the CMC's. the Director 1 and the Director 2. the DMU's.

CIDS- Why the EIVMUs are connected to the Directors?**. To increase the PA level in case of rapid cabin decompression. To increase the PA level, when the cockpit door is open. To increase the PA level when at least one engine is running.