examen modulo 1

01. The Start Power Unit (SPU): Changes 115Vac or 28Vdc electrical power to 270Vdc power. Converts mechanical rotation from the accessory gearbox directly into regulated alternating current. Changes 28Vdc to 115Vac. Steps down high-voltage alternating current to power low-voltage emergency lighting buses.

02. - On the GND with ENG's OFF, when you push the SYS sw on a DSP the dafault page is: FUEL. FLT CTLs. ECS / PNEU. STATUS.

03. - The common core system (CCS) provides: Mechanical backup flight control linkages to the primary actuators during total loss of electrical power. Improved reliability, decreased cost and weight. Direct hydraulic pressure regulation and mechanical pitch control trim limits. Dedicated independent analog displays for each individual flight instrument.

04. - Where is the electrical fligth bag (EFB) software and data stored?. In GPM 7. In a hard drive inside the EFB display unit. In the core network file server module (FSM). In a hard drive inside the EFB electronic unit (EU).

05. - How many display show data if one graphics generator fails?. Six displays show data (five HDD and one HUD). Only the specific display units driven directly by that graphics generator go blank, requiring manual reversionary switching. All displays on the affected pilot's side completely shut down with no automatic reconfiguration. Exactly two displays lose data permanently while the central display enters a degraded reversionary mode.

06. - How many graphics generator (GG) does the primary display system (PDS) have?. Four Graphics Generator. Six Graphics Generator. Eight Graphics Generator. Six Graphics Generator.

07. - If one power conditioning module (PCM) fails. The affected Common Computing Resource cabinet automatically switches to an independent pneumatic backup generator. All primary flight control surfaces immediately transition into direct mechanical cable-reversionary mode. The other PCM continues to supply to all CCR cabinet module. The auxiliary power unit (APU) shuts down automatically to prevent cascading overvoltage on the main AC buses.

08. - What component change 235Vac or 115Vac to +/- 270?. Variable Frequency Starter Generator (VFSG). Main Battery Charger Unit (MBCU). Bus Power Control Unit (BPCU). ATRUs.

09. - What are the components of the CDN?. ACSs, the FOXs, the ARSs and associated fiber optic cables and coppper wire interface. Hydraulic Power Transfer Units, Motor Driven Pumps, and Ram Air Turbines. Flight Control Electronic Modules, Actuator Control Electronics, and Primary Flight Computers. Main Battery Chargers, Variable Frequency Starter Generators, and Bus Power Control Units.

10. - How many displays does the primary displays system (PDS) have?. Four (4) independent 12-inch cathode-ray tube displays, dedicated exclusively to displaying Primary Flight Display (PFD) and Navigation Display (ND) data for the Captain and First Officer. Six (6) high-definition liquid crystal display units, configured as a redundant array with dual dedicated standby flight displays mounted on the center console. Five head down displays (HDD) and two head up displays (HUD). Eight (8) integrated multi-function display units, divided into four primary forward screens for flight instruments and four lower pedestal screens for engine and system status.

11. Each comen computing resource (CCR) contains: Two ACSs, two FOXs, eight GPMs, two PCMs. Four high-voltage Power Conditioning Units, six dedicated Flight Control Computers (FCCs), four ARINC 429 bus interface cards, and three independent cockpit display drivers. Six General Processor Modules (GPMs), four Primary Flight Computers (PFCs), two cabin pressurization controllers, and three dedicated fuel management processor units. One Central Maintenance Computer, twelve Remote Data Concentrators (RDCs), two high-capacity hard drives for navigation databases, and four dual-channel analog-to-digital converters.

12. - In primary displays system, HUD projector is cooled by: Dedicated forced-air bleed air drawn directly from the environmental control system (ECS) mixing manifold. Direct liquid cooling loops connected to the aircraft hydraulic system return lines to dissipate heat through heat exchangers. Internal Fan. Natural convection and ambient flight deck radiation without any active thermal management or electronic airflow monitoring.

13. - What is the onboard data load function (ODLF) purpose?. Continuously monitors structural fatigue cycles and records maximum load limits on primary wing spars during high-G maneuvers. Automatically purges and recalibrates the environmental control system duct pressures during emergency cabin decompression events. Converts raw analog sensor data from the engine exhaust gas temperature probes into digital bus-compatible ARINC 429 streams. It loads loadable software airplane parts (LSAPs) from the file server module (FSM) to airplane.

14. - At initial power-up, where is the EICAS displayed?. On the inboard side of the captain's inboard HDD. On the outboard Primary Flight Display (PFD) screen on the Captain's side, overriding the airspeed and altitude indicators until system initialization is complete. On both the Captain's and First Officer's inboard screens simultaneously as a dual-redundant primary display configuration. On the lower pedestal MFD unit, defaulting to engine primary parameters while system diagnostic checks are run in the background.

15. - Who controls the LOAD MANAGEMENT function?. The Integrated Drive Generator Control Units (IDGCUs) via automated bus-tie contactor cycling based on continuous engine rotational speed inputs. The Central Maintenance Computer (CMC) in conjunction with the Remote Data Concentrators (RDCs) through scheduled priority shedding logic. The Bus Power Control Units (BPCUs). The Primary Flight Computers (PFCs) via real-time aerodynamic load sensing and adaptive flap/slat position feedback loops.

16. - How is the Variable Frequency Starter Generator (VFSG) cooled down?. By an Air/Oil Heat Exchanger (AOHE). By the Power Electronics Cooling System (PECS) using a dedicated polyalphaolefin (PAO) liquid coolant loop routed directly through the generator housing. By ram air directed through external NACA ducts on the engine nacelle cowlings via high-speed centrifugal cooling fans. By fuel-cooled oil heat exchangers that continuously circulate heated engine fuel through an internal generator stator jacket before combustion.

17. - The CCS has: Four CCRs, Four ARSs, and Sixteen RDCs. One CCR, Eight ARSs, and Twenty-Four RDCs. Three CCRs, Five ARSs, and Eighteen RDCs. Two CCRs, Six ARSs and Twety-One RDC.

18. - What is the purpose of the FOX modules?. Changes light signals to electrical signals and visa versa. Converts hydraulic pressure into digital avionics data. Modulates high-frequency radio signals for satellite communication. Regulates voltage output across primary alternating current buses.

19. The GATU transform: 115Vac to 28Vdc. 235Vac to 115 Vac. 28Vdc to 115Vac. 235Vac to +/- 270Vdc.

20. - In which common core system (CCS) components are the hosted software applications for airplanes systems stored?. Remote Data Concentrators (RDCs). Fiber Optic Translator Modules (FOX). General Processor Modules (GPM). ARINC 664 Network Cabinet Switches (ACS).

21. - Electronic Flight Bag is used to: Directly actuate flight control surfaces during automated landing sequences. Process real-time engine vibration monitoring and core temperature telemetry. Replaced some paper material (MEL, QRH, etc). Automatically modulate electrical bus-tie contactors during generator failure.

22. The E-BPSU changes: 28Vdc to +/- 130Vdc. 115Vac to 28Vdc. +/- 270Vdc to 115Vac. 28Vdc to 235Vac.

23. - What component control related generator output voltaje?. Bus Power Control Unit (BPCU). The GCUs. The ELCU. The VFSG.

24. - How does the CCS send and receive airplane data?. Through a common data network (CDN). Using legacy ARINC 429 point-to-point copper data buses managed by centralized relay panels. Using high-frequency radio frequency (RF) telemetry wireless links routed through external blade antennas. Through centralized MIL-STD-1553 multiplex buses.

25. - What is the function of the recorder independent power supply (RIPS)?. To supply uninterrupted 28 VDC power to the flight deck common core system (CCS) cabinets for up to 30 minutes following total generator failure. To provide emergency battery backup power exclusively to the captain's primary flight display during dual engine flameout. To give power to the forward flight recorder for 10min. when aircraft power is not available. To regulate and step down primary alternating current bus voltage to supply continuous power to the electronic flight bag (EFB) units.

26. - The Graphics Generator (GG) has: Six outputs buses, but only two buses can be active at a time. Four output buses, but only two buses can be active at a time. Eight output buses, but only four buses can be active at a time. Two output buses, but both buses must remain active simultaneously.

27. - What components does the Head Up Displays (HUD) have?. Projector and Combiner. Display Unit and Symbol Generator. Transceiver and Indicator Panel. Optical Glass and Sensor Unit.

28. - To perfom maintenance task and tests in the airplane, the system that is used is: CMCF (Central Maintenance Computing Function). Common Data Network (CDN). Common Core System (CCS). Common Computing Resource (CCR) cabinets for executing partitioned application software.

29. - What is the function of CBIC?. To automatically shed non-essential electrical loads based on predetermined priority schedules during dual-generator failure. To multiplex digital avionics data between the remote data concentrators and the common data network. Monitor and control electronic circuit breakers. Convert high-voltage alternating current into regulated direct current for the flight deck common core system cabinets.

30. - How many copies of DCAF software are there on the B787?. Two copies, one hosted in each Common Computing Resource (CCR) cabinet. Six copies, distributed across all active General Processor Modules (GPM). Eight copies, with redundant pairs assigned to every Remote Data Concentrator (RDC). There are 4 copies of the DCAF software.

31. - Current Return Network (CRN) provides: Return path for normal and fault AC and DC current. Dedicated optical path for high-speed avionics data streams. Primary low-voltage power distribution bus for flight deck displays. Isolated grounding network for lightning protection of composite structures.

32. - How is APU Battery Chargeg?. Charged directly from the 28 VDC essential bus via a dedicated battery charger unit (BCU). By a Battery Charger supplid from the F/O INSTR BUS. Charged continuously from the main variable-frequency engine-driven generators through the Common Data Network. Charged automatically by the Variable Frequency Starter Generator Control Unit (VGCU) during APU operation.

33. What is the Remote Data Concentrator main purpose?. To convert incoming ARINC 664 Ethernet datagrams into legacy ARINC 429 and discrete signals for flight deck indicators. To regulate and distribute primary 235 Vac electrical power across the centralized equipment center bus bars. To host the partitioned application software modules within the Common Core System computing cabinets. The RDC main purpose is to change airplane system data from ANALOG, DISCRETE, ARINC 429, CAN BUS DATA to ARINC 664 format.

34. - What is the function of the ENG switch on the EFIS/DSP?. To manually command the Electronic Engine Control (EEC) from normal mode into hard alternate scheduling. To transfer primary engine instrumentation data feeds directly between the left and right Common Core System cabinets. To show or remove secondary engine data from EICAS. To override and isolate the fuel metering unit during an uncontained engine vibration event.

35. - How can you connect the maintenance laptop (ML) to the airplane?. Wire Ethernet connection or Wireless network. Through legacy ARINC 429 serial data links routed through the Central Maintenance Computer (CMC). Through MIL-STD-1553 multiplex bus connections located in the forward electrical equipment bay. Through direct analog discrete wiring harnesses connected to the Primary Display System (PDS).

36. What is the purpose of the 2 nose gear pressure transducers informations?. The DCAF uses the data to verify the calculated stabilizer green band position. To measure hydraulic fluid pressure within the nose gear extension and retraction actuator lines. To monitor nose wheel rotational speed and provide anti-skid deceleration data to the brake system. To regulate emergency pneumatic pressure during alternate landing gear deployment.

37. - What is the Core Network Function that allows you to find and delete loadable software airplane part (LSAP) from the crew informations system - maintenance system (CIS/MS) file server module (FSM)?. Common Core System (CCS) central maintenance function. Electronic Flight Bag (EFB) data management utility. Variable Frequency Starter Generator Control Unit (VGCU) software loader. The Onboard Storage Management Function (OSMF).

38. - Which components is used to control the LH Aft External Power Contactor to open or close?. The L2 GCU. The L1 GCU. The Bus Power Control Unit. The APU Generator Control Unit.

39. - The Power Conditioning Module (PCM) changes 28Vdc to: +28 Vdc for the Common Core System General Processor Modules and +115 Vac for internal equipment cooling fans. +21,5Vdc used by all modules in CCR and +28Vdc to cooling fan and control valve motor. ±15 Vdc for analog discrete interface cards and +5 Vdc for internal Common Data Network switch logic. +270 Vdc for heavy motor control units and +12 Vdc for maintenance laptop data ports.

40. - How can the Airplane be in the virtual GROUND HANDLING MODE?. If forward external power is connected but not selected ON, and no other electrical power is supplied. Automatically initiated by the Bus Power Control Unit (BPCU) whenever the left main landing gear air/ground sensor indicates weight-on-wheels. When the APU generator is selected ON and the main battery switch is placed to the STANDBY position while parked at the gate. Automatically triggered when both forward and aft external power sources are connected and synchronized by the Generator Control Units.