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Book 2 Review


Modules talk to ADCN, modules contain APPS. LRU’s talk to IOMs to get on to ACDN

1. Difference between LRU and LRM

VM is a smart panel talks digitally to ACDN and is dual channel.

2. Difference between VU and VM

AFDX cable on ADCN network by AFDX sw’s.

3. LRM data transfer by

22 option for 23

4. Number of CPIOMs in the system

A-G 7

5. How many types of CPIOM


6. Whats in and how many of CPIOM-A


7. Whats in and how many of CPIOM-B

1-2. FCU backup, WBBC (weight balance backup), FWS

8. Whats in and how many of CPIOM-C

1+3. 1 has ATC. 3 has ACR

9. Whats in and how many of CPIOM-D

1-2. CBMS, ELMS, ESB (electrical system bite)

10. Whats in and how many of CPIOM-E

1+2 COM. 3+ 4 MON. 1+2 have fuel CG COM , fuel measurement COM, fuel management COM. 3+4 have Fuel BITE MON, CG measurement MON, Fuel integrity MON, fuel monitor MON

11. Whats in and how many of CPIOM-F

1-4. 1+2 have BSC COM, WSCS MON, LGERS LO, WSCS BITE. 3+4 have BCS MON, WSCS COM, LGERS HI, Landing Gear monitoring (and separate BITE), LGERS BITE

12. Whats in and how many of CPIOM-G

8 (type A) spilt into side 1 (odd) and side 2 (even)

13. Number of IOMs in the system

Only same type and software loaded

14. Can CPIOMs be interchanged

Yes. Fully interchangeable

15. Can IOMs be interchanged

For redundancy

16. Why are the IOMs mirrored

AFDX end sys, part of CPU board.

17. AFDX connects to what in the CPIOM

IOMs (429, discrete, LRUs)

18. LRMs connect to outside of AFDX via

3- 4( at a 36 EBAS, OHDS, PADS) and( ATA 21 SCS option)

19. CPIOM ‘A’ has what apps/sub apps and how many


20. What CPIOM controls the energy apps

- 28vdc

21. What power to the IOMs

- 28vdc

22. What power to the CPIOMs

ADCN has 16 AFDX switches A and B networks 8 switches each 8,10,18 don’t exist

23. What does the ADCN comprise of

28VDC power supply board, Switching board for routing according to FLS config table, I/P O/P board.

24. What makes up an AFDX switch

1 to 9 (no number 8)

25. AFDX switch numbering on network A

11 to 19 (no number 10, 18)

26. AFDX switch numbering on network B

It’s the MP-FAP or the cabin laptop

27. What are the HMIs for accessing the COMM/cabin domain

Data discarded and MM generated. crc last 4-byte data is checked

28. Cyclic Redundancy check fails you get

both A and B networks operating. Normal ops is virtual link to both networks

29. A normal virtual link is

CKPT effect MAINTENANCE TIME LIMITED ITEM class 4 MEL item a/c effect no - after1000fh goes to class 1 – level 1

30. AFDX single sw loss

2 and 6 failed is allowed with B repair interval

31. Double AFDX switch fault REDUNDANCY DEGRADED on ECAM is sw’s

2 and 6 with B interval

32. Which AFDX switches are allowed to fail together

4 side 2 IOM loss- class1 level 1 -ECAM (AVIONICS NETWORK DOUBLE IOM FAULT)

33. Which IOMs are allowed to fail together


34. MULTI AFDX sw fault on one network. What happens

multiple sw fail on both networks) CLASS1 ( level 2 fault, single chime, master caution) no go

35. Multiple AFDX sw fault-NETWORK DEGRADED is

class 1 level 2 no go ( back up in air is ARINC 429 !) (ECAM AVIONICS NETWORK ALL SWITCHES FAULT)

36. All AFDX sw’s lost

class 4 fault, no a/c effect after 1000fh class1 level1 maintenance time limted item – mel c

37. Single AFDX cable loss is a

It is a class 1 level 1- a/c effect -(no go) (ECAM AVIONICS NETWORK MULTIPLE CABLE FAULT)

38. Multi cable fault. What happens

redundancy they share the same data. mirrored a1<->a2 a3<->a4 etc (side1<->side2)

39. IOM’S are mirrored 1 side and 2 side for

none class 4 fault – 1000fh it goes class 1 level 1

40. CKPT effect for single IOM fail

yes (avionics network multiple IOM fault(REDUNDANCY DEGRADED))no go- no a/c effect- class 1 level 1 fault

41. CKPT effect for multi IOM (non mirrored) fail

yes (avionic network multiple IOM fault (NETWORK DEGRADED)no go- sys effect-class 1 level 2 fault- master caution and chime

42. CKPT effect for multiple mirrored IOM loss

2 and 4 side 2 IOM loss- class1 level 1 -ECAM (AVIONICS NETWORK DOUBLE IOM FAULT)

43. THE two IOM’S that can be inop (special case) non-mirrored are

Only of same type and may need reprogramming

44. Are CPIOM fully interchangeable

Avionics computers freeze their config

45. How does ENG start affect SPP

FIN - Functional Identification Number

46. How are software apps identified in the AMM

apps are done by ATA chapter

47. Where do you find the software for an IOM

no STS will relate to fuel

48. If a CPIOM F fails will the pilot see a CPIOM F message

an IOM converts non-AFDX data, coming from conventional LRUS, into AFDX data used within the ADCN and vice versa.

49. What is the purpose of an IOM


50. How do non subscribers connect to system


HMI’S - MPFAP and cabin laptop

1. Access to cabin domain via


2. What is the main standard of comms for Open World

Avionics, Flight Ops, Communication and Cabin

3. What are the NSS domains


4. Describe Avionic Domain

3 laptops (CAPT, F/O, Backup) where flight ops app are hosted. 1 ANSU-AFMR, 1 ARU-AFMR

5. Describe Flt Ops Domain

1 HESU, 4 CWLUs, 4 leaky line antennas connected to SATCOM, a CVMS, IFE, MP FAPS, Cabin Maint laptops.

6. Describe Comms and Cabin domain

Avionics World with A/C systems and Open World with the 3 NSS domains

7. Describe the Worlds

bidirectional gateway/security function between AV. world and AV. domain.

8. Avionic domain the SCI does what


9. Avionic domain data to FLT-OPS domain and cabin domain is via

2 SCIs connect Avionics World to Avionics domain in the Open world. OWD connects Avionics Domain to the Flight Ops Domain and hence to on Comms and Cabin Domain via the ARU-AFMR

10. Describe how and where SCI and OWD are used

2 redundant servers supplying computing and memory resources to the OIS apps, docs, and db

11. Describe ANSU-OPS

2 redundant routers exchange data with Avionic world, NSS and HMIs

12. Describe ARU-OPS

Validates ACARS and connects PMATs and FAPs to Avionics Domain

13. Describe the SIRU

Bidirectional gateway between Avionics World and Avionics domain

14. Describe SCI

Passive or Active. Only one at a time is active. Change at Flight Phase 12 if operating over 6 hours.

15. How does the SCI operate and when does it change


16. How is Avionics Domain accessed

Data transfer function.

17. What is the ANSU-ARFM mostly used for

select sw to (NSS AV) .

18. To connect to avionic domain from the OIT

One Way Diode. An electrical device that gives a single way of communication from its left to its right. Stops malicious data entering Avionics World

19. OWD is

(MAINT GND connection) SW on o/h MAINT panel must be selected.

20. To use PMAT the


21. What units have back up fans


22. Avionic domain printer is

- no.2

23. FLT/OPS printer is

the upper avionics.(2900VU)

24. Location of most of the NSS equipment /boxes is in

main avionics.

25. TPU’S of the NSS system are in the

supplies DVI info to OIT from laptops data info from FLIGHT OPS domain.They make the physical segregation between the Avionics domain and the Flight Ops domain.

26. TPU what does it do

It is in ARU-OPS because TPU has no hard drive.

27. Where is the TPU ops and why

Press the OIT XFR button on ACD

28. How can 1 pilot see the other pilots screen

Move the OIT brightness knob to OFF

29. How can you reset OIT, Keyboard, ACD and TPU

(NSS master switch p/bsw)

30. Hard shut down of NSS is via the


31. F/O OIT access with batt power and on ground via

, battery is not charging

32. Laptop led blinks red means

Local Maint Function, Weight Balance App, Flt OPs Consultation tool(FOCT) containing AFM, MMEL, FCOM etc, A DLCM, A DB which is a backup for the NSS Flt Ops Domain (main repository is in ANSU-AFMR

33. What is on the Laptop-AFMR

static data and dynamic data.

34. ANSU OPS- the type of data on the hard disk is

On Ground with A/C power up though it does have an on/off switch

35. When does OMT power up


36. What is process for data storage backup in NSS called

It uses Replication. It is automatic if the difference between the ANSU-OPS is < 2GB. Not used by eLog as it talks to both sides anyway.

37. Describe Database Copying

After a fault in the replication process or an ANSU change

38. When is manual synchronising done

For Avionics Domain it is OMT to repository on ANSU-OPS

39. Describe Software Loading

Within 30s of OMT start up select F1. Install only possible from OMT drive

40. How do you perform a total reinstallation of NSS

To use the PMAT you have to select the MAINT GND CONNECTION switch on the maintenance panel (only 1 PMAT connection at a time and no tests with CAUTION)

41. How do you use PMAT

Access to Avionics Domain from outside cockpit.

42. What is the PMAT used for

Tests with caution

43. What can not be done on PMAT

It is a ground tool and not part of the A/C definition. All plugs are inhibited in flight

44. What is the definition of the PMAT and what state are the PMAT plugs usually in

Isolates NSS/avionics world from the aircraft systems incase of system failure or it is compromised. It’s a hard shutdown

45. What does NSS MASTER Switch do

DC from HOT BATT BUS, DC BUS and DC ESS BUS used if AC power lost. After 5 seconds a shutdown begins (up to 120s) F/O OIT, OIT-TPU and ARU-AFMR use HOT BAT BUS up to 120s to preserve data.

46. How do we ensure an orderly shutdown of NSS

An advisory has occurred and the appropriate page has been selected

47. On ECP, steady light on p/b indicates what

An advisory has occurred and the appropriate page needs to be selected

48. On ECP, flashing light on p/b indicates what

Avionics and Flt Ops

49. What domains can be displayed on OIT

Secure Interface Router Unit to connect PMATS AND FAPS and ACARS and the avionic domain

50. SIRU

Servers to supply computing and memory resources to Onboard Information System OIS

51. ANSU ops

Secure Communication Interfaces are gateways(firewall) between the avionics world LRU/LRM and OIS apps and the open world

52. SCI

Passive and active

53. What modes does SCI operate in

Exchange data between avionics world, NSS and HMI

54. ARU ops

supplies aircraft parameters and avionics data from the AVIONICS WORLD to the NSS for recording and for ACMS application needs

55. CDAM

Additional Control Device can be used as a backup of the keyboard for limited functions.

56. ACD

Portable Maintenance Access Terminal is used for access to the Avionics Domain from outside the cockpit

57. PMAT


58. Which domains do the OMT and OIT connect to


59. Which domain does the PILOT's Laptops connect to



1. CMS application is in which Domain and which server

ANSU-OPS 2, has ability to run in battery only mode, backup fan

2. Which is master ANSU-OPS

System stops until P/Ns are the same

3. What happens if ANSU 1 and 2 have different APP p/n’s


4. Access to the CMS can be from

Class 1

5. Failure Classification causing a FD Effect


6. ELOG Book DB lives where

Airman on ground

7. Legal repository for the e-log


8. How to make ELOG entry from Cabin

SCI (Secure Communication Interfaces)

9. To perform Data Loading ANSU-OPS data goes to A/C systems via?

Ground only

10. In what A/C condition is Interactive Mode Available

4 Digit random verification code to be entered in a limited time period

11. Test with caution, what comes up on OMT

Sync is done manually after failure, replacement, Replication is done normally and the master copies to the slave

12. Auto synchronisation of ANSU-OPS database

Is an APP that collect data for moving MAP and other NSS apps etc

13. What is the function of the ABDC (Avionics Broadcast Data Collector) in ACMS


14. CDAM (Centralised Data Acquisition Module) Data Acquisition function is in which world


15. Where is the OMS ACMS DLCS and Main software repository stored

Normal (on ground and in flight) and interactive(GND only)

16. What are the 2 OMS mode

Using Real Time Monitoring Function

17. How can the ACMS be used to aid real time fault diagnosis


18. Which LRU is used to load Avionic software

Apps are done by ATA chapter

19. Where do you find the software for a IOM

FIN - Functional Identification Number

20. How is the software identified

Core, config, app

21. What order do you load CPIOM software


22. Can PMAT be used in air

Last CMS data recording stopped for > 120s, >3 eng running for >180s, CAS> 80 kts or a new flight number entered.

23. When is CMS data recording (PFR) launched

Less than 3 engines running and CAS < 80Kts for > 150s

24. When does CMS data recording stop

System bite, FWS

25. where does the CMF get its fault info from

Class 1 = FDE. Class 3 = CE but not safety related. Class 4 = No FDE or CE but has a time limit. Class 5 = No FDE or CE, No safety, no time limit but potential delay with further failures. Class 6 = No FDE or CE or safety or time limit but effects economical performance.

26. List Failure Classification

Class 2

27. Which failure is no longer used

Standard A BITE and Standard B BITE. Standard A (mainly ATA 23 and 34) faults are in plain English to CMS and is only A429 subscribers. Standard B BITES are transmitted to CMS using fault codes and the status is continuously monitored. It is for A429 and AFDX.

28. What are the BITE standards

First 4 ATA Ch and sub Ch. Middle letter is event type. Last 3 are event number.

29. How is a BITE B fault code made up

Data loading Management, Config monitoring, Repository Management, Software Pin Programming

30. What are the sub sections of DLCS

In the ANSU-OPSs

31. Where is the DLCS hosted

OITs OMT OMAT and Printer 1

32. Which HMI can be used for DLCS

Only possible in Flight Phase 1. Uploaded to SCIs

33. When is SPP possible and where is it uploaded to

Indicating and Recording

2 PFDS, 2 NDS, 1 EWD, 1 SD, 2 MFDs

1. Describe the CDS make up

ACDN normally. ADIRU and FWS direct for backup

2. What is normal data trans and what is backup

CAN BUS (for the KCCU) and AFDX ARINC 429 also (incase AFDX fails) fibre for video

3. What are the types of data bus on CDS

CAPTS (DC BUS 1 as backup)

4. Which display systems are powered by the DC ESS BUS in FD

DC BUS 1 and DC BUS 2

5. Which bus is for F/O display system

Hard PP activates the screen positions pre installed application software

6. How do you know the position of the Display Units in flight deck? Hard Pin Programme or Software Pin Programme

Non-critical systems

7. What is SPP for

On the CDS reconfiguration control panels (1313VU/1314VU)

8. Where do you perform manual ND/PFD switching

L1 and R1

9. Where is EWD not available

EWD, SD, and PFD Lower zone.

10. Where does ECAM show

PFD and ND

11. Where does EFIS show

3 A/C sys or STS, Permanent data, ATC mail box

12. SD Page has how many boxes

Use arrows on keyboard

13. How do you control cursor after track ball failure

GPS1 only from MMR1

14. Where is the normal clock time signal from


15. In degraded mode how long is accuracy considered to be maintained


16. Backup time data is from

C2 STS has priority on the EWD

17. Location of STS page is on which DU

18. MORE in a square box. What does it mean how is it accessed? More info to see for STS. The CLR button on the ECP (or the MORE button??)?????????????


19. Where do aircraft limitations display

ACDN and Arinc 429 backup

20. FWS to CDS/DU, what kind of connection

CPIOM-C1/2(FWS) sends discrete to lights Sounds from FMS to AMU then to speakers

21. What lights the ATTN getters

ABN PROC button on ECP

22. How does pilot select abnormal procedures

C1 and C2

23. Which CPIOM for FWS

IOMs 7 and 8

24. Which IOM’s for FWS

Class 4

25. What class of alert accumulates a time limit

Any detected failure with neither Flight Deck Effect nor Cabin Effect but to be fixed within a time period. 500/1000hrs cat c becomes class 1 if not fixed

26. Definition of Class 4 fault

Flt ph 1 and 12

27. when does flt ph class 4 become class 1

Level 1- crew monitoring (no sound, advisory msg, master caution), level 2 - immediate crew awareness (single chime, advisory, master caution), level 3 - immediate crew reaction (continuous chime, repetitive noise or specific noise, master warning)

28. Airbus Emergency Levels

Designed to allow monitoring of minor faults or allow airlines to manage repair of faults

29. Time Limited Philosophy

AFDX and Canbus/discrete for backup control

30. ECP to FWS connection and backup

All except 7,8,11. Can only be triggered in 5,6,9 and 10. All others are a fault

31. Which flight phase is the tail strike warning inhibited


32. Where does Tail Strike ind appear

Fibre optics

33. How is data transferred from CMV to CDS


34. Video will display on all except


35. FD Acquisition data transfers to FDR via

Aft RHS of upper deck

36. Where is the FDR

Aft cargo fwd end

37. where is 3 axis gyro for FDR located

Analogue Arinc 717 havard bi-phase

38. what is the output of the FDR 3 axis gyro

115V ESS

39. What is FDR power supply


40. How long does the FDR record for


41. what hosts the FDIAF

PRIM MMR ADIRS ISIS and LRMs with ADCN and the 3 axis gyro.

42. Where does FDIAF receive data

GND test or Pre Flt check

43. What does the RCDR GND CTRL P/B do

5mins after power up, 1 eng running, in the air, 5 mins after eng off

44. Automatic FDR recording mode

From the RCDR P/B on overhead panel

45. How does pilot set the recording mode

DSFDR EVENT P/B on centre Pedastal

46. How does the pilot record an event marker

4 total. 2 sides of 2. CAN 1.1, 1.2, 2.1, 2.2

47. How many CAN busses on an overhead ICP and how arranged

1,2,5 and 6

48. What IOMs for the ICP CAN busses

7 and 8

49. What are the IOMs for ECP

2 CH CAN ECP1 and ECP2 (side 1 and 2)

50. What is the CAN bus for the ECP

CAN 02B @ 125Kb/s

51. What is the CAN bus standard used and what is its data rate


52. Who has the most limited access to the eLog

Flight Limitation Zone

53. Where is the flap/slat information displayed

CAPT MFD (P/B can switch to SD) and EWD

54. Which CDS displays are powered on battery

The clock backup and to ADCN if clock in SET or U/S

55. What is the time function of the ADIRU for

The failure causes loss of other systems (eg Hyd failure causes others sys fail)

56. What is primary failure

The failure caused by the primary system (eg the flaps)

57. What is a secondary failure

A failure that doesn’t affect other systems (eg Fuel Pump)

58. What is an independent failure

Emergency config. Immediate action required. Continuous Chime. Red Master Warning. Flashing. Red warning msg on EWD. SD sys (if there is one)

59. What are the indications and audio for level 3 messages

Abnormal config. Immediate awareness but not action. Single Chime. Amber Master Caution. Message on EWD if there is one and SD sys if there is one.

60. What are the indications and audio for level 2 messages

Monitor config. Amber msg on EWD. SD sys page if exists

61. What are the indications and audio for level 1 messages

Via discrete ARINC429 and AFDX to the switches and CDS.Data comes from FWS (CPIOM C1,2 IOM 7,8)

62. How are they transmitted

8 cruise

63. What is the default flight phase

500/1000 hrs

64. What timers are associated with class 4 messages

Concentrates Video signals from multiple sources (Concentrator and Multiplexer for Video)

65. What does the CMV do


66. How many video I/Ps does a DU have

PFDs, NDs, SD. MFDs if reconfigured. (NEVER EWD!!!)

67. Which DUs can show video


68. What systems are connected to CMV

External Taxi Aid Camera. CMV use A429 for crew selection (from EFIS to CIU) and transmits to DU via fibre optic.

69. Describe ETACS

Cockpit Door Surveillance System. Crew selection to CDSS controller via ACDN

70. Describe CDSS

Dats Acquisition Unit. Transits video by fibre as requested. DAU can make a priority request if an important situation arises.

71. Describe DAU

Onboard Airport Navigation Computer. Transmits by fibre optics

72. Describe OANS

Using Fibre optics.

73. What and how are pictures displayed on the CDS for CMV

2 probes, 2 loops in series. done by flt phase as to fault or strike Level 2 for strike with LAND ANSA (Ph 6,7,11)

74. what is in the tail strike system

Segregated CAN Bus

75. what backup signal output from KCCU

Self monitored and monitored in a loop by another DU

76. how are DU’s monitored for failure

Electrical power


1. What AC BUS is normally powered

115v 150KVA 370-770Hz


115v 120KVA 400Hz (constant speed APU)


115v 70KVA 370-800Hz


90KVA 115V 400Hz

5. EXT Power V KVA F

4 90KVA or 2 180KVA. Less will load shed

6. How many EXT for whole Network to be powered


7. APU and ENG GGPCU interchangeable


8. APU and ENG GEN interchangeable

EXT 1-4/ENG 1-4 = GGPCU 1-4. GEN A = 5. GEN B= 6

9. Which GGPCU manage which GENs

GEN A Bus 1 and 2 (along with AC ESS, AC EMER, TR ESS, DC ESS, DC1, TR1) , GEN B bus 3 and 4 (along with AC EHA, TR2, DC2 APU TR, APU STARTING DC)

10. What do APU GENs supply


11. AC BUS 1 priority supply


12. Where do you see battery condition

AC BUS 2 (TR1) and AC BUS 3 (TR2)

13. DC1 and DC2 normally powered by


14. DC ESS normally powered by

DC 1 and 2 in PEPDC and DC ESS in EEPDC

15. Where are DC1 and DC2 and DC ESS

On GND or emergency config when only Batteries are available. In Flight until RAT deployed.

16. When does Static Inverter Apply AC

BAT 1 and BAT ESS in parallel. 2.5 KVA 115V single phase 400hz

17. How is Static Inverter supplied and what is it’s O/P

Static Inverter supplies AC EMER BUS not the AC ESS BUS. BAT 1 also now supplies DC ESS BUS

18. If No AC power and BAT 1 and BAT ESS selected what is powered

AC Bus 2 and DC Bus 1

19. TR1A Power supply

Rectifies AC-DC up to 300A, Controls the Battery Line Contactor

20. TR does what


21. A primary function of Batteries


22. Lost 4 Engines and RAT is deploying. Which BUS is powered

Static inverter

23. What powers the AC EMER BUS


24. GND SRVC from which GND PWR


25. Where is GND SRVC sw

SPDBs (1-6 cabin, 7-8 cargo)

26. What manages the commercial loads

1,2,3,4,ESS and EMER

27. What are the main AC busses

Physical check,

28. What 3 ways can the state of some thermal cbs be determined

AC BUS1 with AC BUS4 as a backup

29. Which main Bus normally supplies the AC essential Bus

All busbars and loads supplied

30. What happens with only 3 VFGs

All busbars supplied some loads shed

31. What happens with only 2 VFGs

Only on side busbars

32. What happens with only 1 VFGs

BTC 1-6 and SIC (System Isolation Contactor)

33. What are the Transfer Circuit Contactors


34. What connects the RAT

EXT2 powers AC1 and 2, TR1A and DC1 and (via IBLC2) DC2 and DC EHA. (Bat 2 is not connected) BAT1 and ESS (via BLC) connect to their buses to do NBPT. AC1 connect to AC ESS, AC EMER and TR ESS and DC ESS BUS to ESS BAT for NBPT

35. With only EXT2 what is the config

Entire network powered. AC4 powered by AC3. AC3 supplies AC EHA and TR2A for DC2

36. WIth EXT 3 added to EXT 2

Main busbars and transfer circuits is in PEPDC, ESS is in EEPDC

37. Where are the main and busbars and transfer circuits and the AC ESS busbars

AC BUS 4 and RAT

38. What alternative sources does the AC ESS BUS have

39. What indications are there of VFG bite messages

No needs to be replaced

40. Can a VFG be reconnected after being mechanically disconnected

DRIVE P/B for mechanical (red guarded cover) . GEN P/B for electrical disconnect/reconnect

41. Which button mechanically and which electrically disconnects

42. How is each battery connected in a batteries only condition on the ground

Till it dribbles out of over flow and shows on sight glass

43. What is the procedure for filling the VFG with oil

1 PEPDC for loads > 15A, 2 SEPDC for technical loads (with 8 SPDB for commercial loads ) < 15A, 1 Emergency distribution by EPC

44. What are the names of the power distribution centres/boxes

Use the c/b control switch

45. If you are trying to change the state of electronic cb's and it is not working what might you have forgotten to do

Voltage regulation , protection, BITE

46. What are the functions of the GGPCU

Contain 11 AC SSPC and up to 4 DC SSPC. Side 1 has SDPB 1,3,5,7 and side 2 has 2,4,6,8. 1-6 are cabin and 7-8 are cargo

47. Describe SPDBs

48. How will SPDBs be affected if the ADCN network to them fails

Onside TRU powered from HOT BATT BUS

49. what controls and protects battery

Closes IBLC

50. what happens if TRU fails


51. how many buses can a single ext source or generator supply

Static inv powers it until RAT deploys

52. what happens if theres no power to AC ESS bus

Power Distribution Maintenance Interface. Allows monitoring of PEPDC, SEPDC and 8 SPDBs and the EPC. Allows control of RCCBs in PEPDC and SSPCs in SEPDCs and SPDBs. Can view all classic RCCBs too.

53. What is a PDMI

By 2 PDMCs and 2 PDCS apps(only accessible on GND via HMIs).

54. How are PDMI functions achieved

Through CPIOM-E1 CBM app

55. How do you monitor the EPC


56. what looks after power of RAT and main generator

SRPS -Safe Redundant Power Supply (4 cards)

57. what supplies power to cards in PEPDC

DC ESS and static inv to get AC EMERG (DC BUS 1 and DC BUS2 NOT supplied)

58. what do you get if BATT 1 and ESS BATT selected

ELEC DC page (the OMT; F/O OIT is also powered on BAT only)

59. what indications do you get on batt power only on power up

AC and DC EHA buses for TEFO only (because HYD pwr is lost!)

60. whats difference for TEFO and LMES

RAT continues to operate the bus.

61. Following a TEFO with RAT supplying AC ESS BUS. If all power is recovered what will then feed the AC ESS BUS

Using RAT pilot exciter and A/C power to excite main field.

62. How does RAT GCU regulate power

By GCU control and protect function using CTA in the Gen and the POR (point of regulation) in EEPC

63. How is RAT controlled and protected

A/C speed. 70KVA above 175kts. 58KVA 140 to 175kts

64. What affects EEPDC POR and what is the result

The GCU once POR says all is correct

65. What sends the Power Ready signal to EEPC

Only on GND tests. In air in emergency it must just work through the usual over/under V, over Freq, diff or feeder faults.

66. When do RAT GCU protective functions work

Using overhead reset GCU C/B

67. How are RAT GCU faults reset


68. What powers RAT retract

It gets to 12degs, re-extends and RAT NOT ALIGNED light comes on.

69. What happens if RAT is not aligned for stowing

For fault and whilst deploying

70. When does the EMER GEN fault light come on

select Bat 2, and if ADIRU is on ground with the remote ctrl c/b switch PDMC2 and OMT powered to check/isolate SEPDC and RCCBMS

71. To use control and monitoring devices on bat only


72. Normal GND power connection sequence


73. DC BUS ESS normal config for Bat and LC


74. How does DC BUS 1 connect to DC ESS BUS


75. In normal config how does TRA2 connects to which AC BUS

STATIC INV or the emergency generator via the AC ESS BUS

76. In EMERGENCY config how does AC EMER BUS powered

Main Avionics

77. Where is the location of the PEPDC

2 - side 1 and side 2

78. How many sides does PEPDC have

VFG/EXT1-4, APU 1-2, Galley 1-4, AC&DC CBS panel 1-2 DC contractors 1-2 AC RCCBS panel CH 1-2.

79. How many channels does PEPDC have

4 PEDMU cards, 8 RCCDM cards, 4 PCDM (Primary Contactor Driver Module)cards, 4 SRPS( Safe Redundant Power Supply) cards

80. What are the PEPDC LRUs

PEDMU (4 cards 1.1, 1.2, 2.1, 2.2)

81. In the PEPDC which LRU provides interfaces to the electronic units that interface with (LRM/LRU/PCDM/RCCBs)

Through the PEDMU

82. How does PEPDC command data loading from the open world

28VDC ESS or VFG PMG (rectified in GGPCU)

83. What is the GGPCU power supply

3 stages. 1 = pilot exciter with PMG to excite generator . It is regulated and excites Main Exciter. It is now rectified AC thanks to rotating diodes. Main alternator now produces 115VAC

84. How is the voltage regulation done by GGPCU


85. What closes the GLC

The master lever

86. What is GGPCU connected to so it knows if its a fault or an ENG shutdown

Point of regulation in PEPDC. It monitors and measures delivered voltage 115V =+/- 5V

87. What and where is the POR and what margins

2. 1 in VFG the other in PEPDC check fro over Current and phase imbalance

88. Where are the Current Transformers

Memorisation of the CB condition connected to the RCCB (It is not connected to PEDMU OR RCCB only to RCCBM)¯\_(ツ)_/¯ I got lost on this one! Can’t even make out his words on the recording

89. What is the function of the STRM


90. Which CPIOM controls electrical network

Fan air

91. How is VFG oil cooled


92. Signal of the POR for the gen to be connected is controlled and monitored by


93. Which LRUs in Electrical sys manage and control the LCs


94. Another function of the PCDM (Primary Contactor Driver Modules) to control the transfer circuit. What is being controlled

5 and 6

95. The GGPCU for GEN A and B is

Via ESB (electrical system bite)

96. How does GGPCU talk to CMS

It talks to FADEC

97. How does GGPCU know engine speed

ELM function in CPIOM-E

98. What controls how the loads are managed

ELC1 (to connect BAT 1 to DC ESS BUS) and IBLC1 to connect DC BUS 1 to DC BUS ESS

99. In the Emergency Power Center which contactors for emergency power supply


100. For transfer circuit of DC contactor in control is


101. How do you reset a TR


102. Which LRUs are responsible for the control and power supply of loads below 15A

Through OIT/ OMT / PMAT

103. How do you access the reset of RCCDs or SSCB

Capts l1 l2 l3 EWD (SD) on F/O side OIT etc.

104. On capts side and f/o side what is powered when on BATT power only