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

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

AFDX cable on ADCN network by AFDX sw’s.

22 option for 23

A-G 7

1-4. PADS, EBAS, OHDS, SCS

1-4. AGS, AVS, CPCS, TCS, VCS

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

1+3. 1 has ATC. 3 has ACR

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

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

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

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

Only same type and software loaded

Yes. Fully interchangeable

For redundancy

AFDX end sys, part of CPU board.

IOMs (429, discrete, LRUs)

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

- CPIOM E – CBMS, ELMS, ESB.

- 28vdc

- 28vdc

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

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

1 to 9 (no number 8)

11 to 19 (no number 10, 18)

It’s the MP-FAP or the cabin laptop

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

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

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

2 and 6 failed is allowed with B repair interval

2 and 6 with B interval

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

CKPT effect (AVIONICS NETWORK MULTIPLE SWITCH FAULT (REDUNDANCY DEGRADED)a/c effect no- no go class 1 level 1

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

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

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

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

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

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

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

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

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

Only of same type and may need reprogramming

Avionics computers freeze their config

FIN - Functional Identification Number

apps are done by ATA chapter

no STS will relate to fuel

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

CPIOM or IOM

HMI’S - MPFAP and cabin laptop

Ethernet

Avionics, Flight Ops, Communication and Cabin

2 ANSU-OPS, 2 ANSU-ARUs, 1 SIRU, 2 SCIs

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

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

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

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

OWD

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

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

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

Validates ACARS and connects PMATs and FAPs to Avionics Domain

Bidirectional gateway between Avionics World and Avionics domain

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

OITs, TPUs, OMT, PMAT, MP FAP

Data transfer function.

select sw to (NSS AV) .

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

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

ANSU OPS 2, ARU OPS 2 and ARU-AFMER.

no.1

- no.2

the upper avionics.(2900VU)

main avionics.

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.

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

Press the OIT XFR button on ACD

Move the OIT brightness knob to OFF

(NSS master switch p/bsw)

REMOTE C/B CTL p/bsw

, battery is not charging

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

static data and dynamic data.

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

Replication

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.

After a fault in the replication process or an ANSU change

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

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

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)

Access to Avionics Domain from outside cockpit.

Tests with caution

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

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

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.

An advisory has occurred and the appropriate page has been selected

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

Avionics and Flt Ops

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

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

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

Passive and active

Exchange data between avionics world, NSS and HMI

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

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

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

AVIONICS Domain

FLIGHT OPS Domain

Avionics Domain in ANSU-OPS(PDCS, CMS, DLCS, ACMS, E-LOGBOOK, MEL, CDL)

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

System stops until P/Ns are the same

OMT PMT OIT

Class 1

ANSU-OPS

Airman on ground

FAP

SCI (Secure Communication Interfaces)

Ground only

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

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

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

AVIONIC WORLD

ANSU-OPS

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

Using Real Time Monitoring Function

OMT

Apps are done by ATA chapter

FIN - Functional Identification Number

Core, config, app

No

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

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

System bite, FWS

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.

Class 2

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.

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

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

In the ANSU-OPSs

OITs OMT OMAT and Printer 1

Only possible in Flight Phase 1. Uploaded to SCIs


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

ACDN normally. ADIRU and FWS direct for backup

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

CAPTS (DC BUS 1 as backup)

DC BUS 1 and DC BUS 2

Hard PP activates the screen positions pre installed application software

Non-critical systems

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

L1 and R1

EWD, SD, and PFD Lower zone.

PFD and ND

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

Use arrows on keyboard

GPS1 only from MMR1

24hrs

ADIRUS

C2 STS has priority on the EWD

PFD, EWD

ACDN and Arinc 429 backup

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

ABN PROC button on ECP

C1 and C2

IOMs 7 and 8

Class 4

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

Flt ph 1 and 12

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)

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

AFDX and Canbus/discrete for backup control

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

ECAM-EWD and LAND ANSA on EFIS-PFD

Fibre optics

EWD

CDAM

Aft RHS of upper deck

Aft cargo fwd end

Analogue Arinc 717 havard bi-phase

115V ESS

25hrs.

CDAM

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

GND test or Pre Flt check

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

From the RCDR P/B on overhead panel

DSFDR EVENT P/B on centre Pedastal

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

1,2,5 and 6

7 and 8

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

CAN 02B @ 125Kb/s

Cabin

Flight Limitation Zone

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

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

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

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

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

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

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.

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

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

8 cruise

500/1000 hrs

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

1

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

OANS, CDSS, ETACS

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

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

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

Onboard Airport Navigation Computer. Transmits by fibre optics

Using Fibre optics.

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)

Segregated CAN Bus

Self monitored and monitored in a loop by another DU


AC ESS BUS

115v 150KVA 370-770Hz

115v 120KVA 400Hz (constant speed APU)

115v 70KVA 370-800Hz

90KVA 115V 400Hz

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

Yes

No

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

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)

VFG1/EXT1/APU GEN A

ELEC DC PAGE

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

AC ESS via TR ESS

DC 1 and 2 in PEPDC and DC ESS in EEPDC

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

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

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

AC Bus 2 and DC Bus 1

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

NBPT and HOT BAT BUS

AC EMERGENCY BUS only

Static inverter

EXT 1

DR M1L

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

1,2,3,4,ESS and EMER

Physical check,

AC BUS1 with AC BUS4 as a backup

All busbars and loads supplied

All busbars supplied some loads shed

Only on side busbars

BTC 1-6 and SIC (System Isolation Contactor)

The EGLC

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

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

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

AC BUS 4 and RAT

No needs to be replaced

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

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

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

Use the c/b control switch

Voltage regulation , protection, BITE

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

Onside TRU powered from HOT BATT BUS

Closes IBLC

2

Static inv powers it until RAT deploys

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.

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

Through CPIOM-E1 CBM app

RAT - GCU, ENG GGPCU 1-4, APU GGPCU 5-6

SRPS -Safe Redundant Power Supply (4 cards)

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

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

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

RAT continues to operate the bus.

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

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

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

The GCU once POR says all is correct

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

Using overhead reset GCU C/B

DC1

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

For fault and whilst deploying

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

2314

BAT ESS and BAT LC ESS

IBLC1I

AC BUS 3

STATIC INV or the emergency generator via the AC ESS BUS

Main Avionics

2 - side 1 and side 2

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.

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

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

Through the PEDMU

28VDC ESS or VFG PMG (rectified in GGPCU)

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

PCDM

The master lever

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

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

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

CPIOM E

Fan air

GGPCU

GGPCU and PCDM

BTC and SIC

5 and 6

Via ESB (electrical system bite)

It talks to FADEC

ELM function in CPIOM-E

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

IBLC1 and IBLC2

Via CMS

SEPDB and SPDB

Through OIT/ OMT / PMAT

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