@A310

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

ATA SYSTEM: 22

TITLE: AUTO FLIGHT - GENERAL - INSTALL SYSTEM PROVISION FOR

RUDDER REVERSAL WARNING FUNCTION

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 13592S22847

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

This Service Bulletin is issued further to an operator’s request.

Following report of events of excessive rapid alternating and large rudder pedal inputs that resulted

in high vertical stabilizer loads, the Stop Rudder Input Warning device (SRIW) provides increased

protection by improvement of the cockpit crew awareness in case of excessive rudder reversal control

input.

The activation of the SRIW device is achieved by the Service Bulletin A310-22-2064.

First, the installation of the system provision is required.

This service bulletin installs all the electrical and mechanical provisions for rudder reversal warning.

The modification consists in:

- Modifying the panel 13VU in the glareshield in front of captain and F/O before installation of both

warning light 510VU.

- Installing a wiring provision between FCCs and FWCs in the avionic bay and cockpit 13VU.

- Modifying wiring on circuit breaker panel 49VU.

In addition of the above and in order to prepare future activation of two new TCAS messages,

electrical wiring is added between TCAS and FWC1 and FWC2.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

SUMMARY

Accomplishment of this Service Bulletin will satisfy the operator’s request.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational

disruptions.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 222063A02R00 1 See SB Bundle, Modules

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 222063A01R01 1 See SB Bundle, Modules

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 222063A02R00 1 See SB Bundle, Modules

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 222063A01R01 1 See SB Bundle, Modules

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

99Y FDX

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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@A310

SERVICE BULLETIN

SUMMARY

NOTE: This Service Bulletin is written for the operators listed above. The modification in this

Service Bulletin can be done by other operators. If other operators want to do this

modification, use the RFC/RMO procedure and write to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

SC Department

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT YES

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 222063-831-801-001: Modification

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF 002

Task 222063-831-801-001: Modification

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF 003

Task 222063-831-801-001: Modification

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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@A310

SERVICE BULLETIN

SUMMARY

**CONF 004

Task 222063-831-801-001: Modification

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

APPENDICES

**CONF ALL

Appendix 01: Gantt Chart

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

MODIFICATION OF 13VU

MODIFICATION OF THE EQUIPEMENT 

AND THE WIRING IN 90VU

MODIFICATION OF THE EQUIPEMENT 

AND THE WIRING IN 500VU

MODIFICATION OF THE 

WIRING IN 490VU

FR1

FR20

MODIFICATION OF THE EQUIPEMENT

190VT AND THE WIRING IN 80VU

B_SB_222063_5_SAAA_01_01

Figure A-FSAAA - Sheet 01

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 6

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 22

TITLE: AUTO FLIGHT - GENERAL - INSTALL SYSTEM PROVISION FOR

RUDDER REVERSAL WARNING FUNCTION

MODIFICATION No.: 13592S22847

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

310-203 310-221 310-222 310-304 310-308 310-324

(2) Effectivity by MSN

0162 0201 0217 0230 0233 0237 0241 0245 0248 0251 0254 0264 0267 0278 0281

0283 0288 0297 0313 0316 0318 0326 0331 0333 0335 0339 0343 0345-0346 0353

0355-0356 0359 0362 0364 0369 0378 0394 0439 0449 0452 0454 0456-0458 0467

0489 0492 0500 0534 0539 0542 0549 0552 0593 0638

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

99Y 0489

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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@A310

SERVICE BULLETIN

OPERATOR MSN

FDX 0162 0201 0217 0230 0233 0237 0241 0245 0248 0251 0254 0264

0267 0278 0281 0283 0288 0297 0313 0316 0318 0326 0331 0333

0335 0339 0343 0345 0346 0353 0355 0356 0359 0362 0364 0369

0378 0394 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500

0534 0539 0542 0549 0552 0593 0638

(4) Configuration by MSN

MSN CONFIGURATION

0162 0201 0217 0230 0233 0237 0241 0245 0248 0251 0254

0264 0281 0283 0297 0313 0316 0326 0335 0353 0355 0356

0359 0362 0364 0369 0378 0394 0454 0500 0534 0549 0593

002

0267 0278 0288 0318 0331 0333 0339 0343 0345 0346 0439

0449 0456 0457 0458 0467 0492 0539 0542 0552 0638

001

0452 003

0489 004

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which:

- Service Bulletin No. A310-34-2050 is embodied

- Service Bulletin No. A310-23-2048 is not embodied

**CONF 002

Config. 002 is valid for aircraft on which:

- Service Bulletin No. A310-34-2050 is not embodied

- Service Bulletin No. A310-23-2048 is not embodied

**CONF 003

Config. 003 is valid for aircraft on which:

- Service Bulletin No. A310-34-2050 is embodied

- Service Bulletin No. A310-23-2048 is embodied

**CONF 004

Config. 004 is a dedicated configuration.

(6) Material Effectivity

**CONF 002, 004

MATERIAL QTY PER A/C SEE NOTES

Kit 222063A01R01 1

Consumable CMLA01 1

Reidentified part set REIDA01 1

**CONF 001, 003

MATERIAL QTY PER A/C SEE NOTES

Kit 222063A02R00 1

Consumable CMLA01 1

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES

Reidentified part set REIDA01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

This Service Bulletin is issued further to an operator’s request.

(2) Objective/Action

Following report of events of excessive rapid alternating and large rudder pedal inputs

that resulted in high vertical stabilizer loads, the Stop Rudder Input Warning device

(SRIW) provides increased protection by improvement of the cockpit crew awareness in

case of excessive rudder reversal control input.

The activation of the SRIW device is achieved by the Service Bulletin A310-22-2064.

First, the installation of the system provision is required.

This service bulletin installs all the electrical and mechanical provisions for rudder

reversal warning.

The modification consists in:

- Modifying the panel 13VU in the glareshield in front of captain and F/O before

installation of both warning light 510VU.

- Installing a wiring provision between FCCs and FWCs in the avionic bay and cockpit

13VU.

- Modifying wiring on circuit breaker panel 49VU.

In addition of the above and in order to prepare future activation of two new TCAS

messages, electrical wiring is added between TCAS and FWC1 and FWC2.

(3) Advantages

Accomplishment of this Service Bulletin will satisfy the operator’s request.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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@A310

SERVICE BULLETIN

**CONF 001

Task 222063-831-801-001: Modification

(1) Modify the Wiring in the Left Electronics Rack 80VU.

(2) Modify the Wiring in the Right Electronics Rack 90VU.

(3) Modify the Wiring and the Equipment in the Electronics Rack 500VU.

(4) Modify the Wiring and the Equipment in the Avionics Compartment.

(5) Modify the Wiring in the Maintenance Panel 490VU.

(6) Modify the Wiring between the Cockpit and the Avionics Compartment.

(7) Remove the Instrument Panels.

(8) Modify the Wiring and the Equipment in the Cockpit.

(9) Modify the Routing in the Glareshield Panel 13VU.

(10) Modify the Instrument Panels.

(11) Install the Instrument Panels.

(12) Install the Items removed for access.

**CONF 002

Task 222063-831-801-001: Modification

(1) Modify the Wiring in the Left Electronics Rack 80VU.

(2) Modify the Wiring in the Right Electronics Rack 90VU.

(3) Modify the Wiring and the Equipment in the Electronics Rack 500VU.

(4) Modify the Wiring and the Equipment in the Avionics Compartment.

(5) Modify the Wiring in the Maintenance Panel 490VU.

(6) Modify the Wiring between the Cockpit and the Avionics Compartment.

(7) Remove the Instrument Panels.

(8) Modify the Wiring and the Equipment in the Cockpit.

(9) Modify the Routing in the Glareshield Panel 13VU.

(10) Modify the Instrument Panels.

(11) Install the Instrument Panels.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(12) Install the Items removed for access.

**CONF 003

Task 222063-831-801-001: Modification

(1) Modify the Wiring in the Left Electronics Rack 80VU.

(2) Modify the Wiring in the Right Electronics Rack 90VU.

(3) Modify the Wiring and the Equipment in the Electronics Rack 500VU.

(4) Modify the Wiring and the Equipment in the Avionics Compartment.

(5) Modify the Wiring in the Maintenance Panel 490VU.

(6) Modify the Wiring between the Cockpit and the Avionics Compartment.

(7) Remove the Instrument Panels.

(8) Modify the Wiring and the Equipment in the Cockpit.

(9) Modify the Routing in the Glareshield Panel 13VU.

(10) Modify the Instrument Panels.

(11) Install the Instrument Panels.

(12) Install the Items removed for access.

**CONF 004

Task 222063-831-801-001: Modification

(1) Modify the Wiring in the Left Electronics Rack 80VU.

(2) Modify the Wiring in the Right Electronics Rack 90VU.

(3) Modify the Wiring and the Equipment in the Electronics Rack 500VU.

(4) Modify the Wiring and the Equipment in the Avionics Compartment.

(5) Modify the Wiring in the Maintenance Panel 490VU.

(6) Modify the Wiring between the Cockpit and the Avionics Compartment.

(7) Remove the Instrument Panels.

(8) Modify the Wiring and the Equipment in the Cockpit.

(9) Modify the Routing in the Glareshield Panel 13VU.

(10) Modify the Instrument Panels.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(11) Install the Instrument Panels.

(12) Install the Items removed for access.

**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 222063-831-801-001: Modification

Get Access 0.50

On Aircraft

Modify the Wiring in the Left Electronics Rack 80VU. 7.00

Modify the Wiring in the Right Electronics Rack 90VU. 9.00

Modify the Wiring and the Equipment in the Electronics

Rack 500VU.

6.50

Modify the Wiring and the Equipment in the Avionics

Compartment.

4.00

Modify the Wiring between the Cockpit and the

Avionics Compartment.

17.00

Remove the Instrument Panels. 0.50

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

Task 222063-831-801-001: Modification

Modify the Wiring and the Equipment in the Cockpit. 10.00

Modify the Routing in the Glareshield Panel 13VU. 2.00

Install the Instrument Panels. 1.00

Install the Items removed for access. 2.00

On Bench

Modify the Wiring in the Maintenance Panel 490VU. 1.50

Modify the Instrument Panels. 3.00

Tests 4.50

Close-Up 0.50

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

NOTE: For detailed concerning the elapsed time assumptions, refer to Appendix 01:

Gantt Chart .

**CONF 002

Task 222063-831-801-001: Modification

Get Access 0.50

On Aircraft

Modify the Wiring in the Left Electronics Rack 80VU. 7.00

Modify the Wiring in the Right Electronics Rack 90VU. 9.00

Modify the Wiring and the Equipment in the Electronics

Rack 500VU.

6.50

Modify the Wiring and the Equipment in the Avionics

Compartment.

4.00

Modify the Wiring between the Cockpit and the

Avionics Compartment.

17.00

Remove the Instrument Panels. 0.50

Modify the Wiring and the Equipment in the Cockpit. 10.00

Modify the Routing in the Glareshield Panel 13VU. 2.00

Install the Instrument Panels. 1.00

Install the Items removed for access. 2.00

On Bench

Modify the Wiring in the Maintenance Panel 490VU. 1.50

Modify the Instrument Panels. 3.00

Tests 4.50

Close-Up 0.50

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF 003

Task 222063-831-801-001: Modification

Get Access 0.50

On Aircraft

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

Task 222063-831-801-001: Modification

Modify the Wiring in the Left Electronics Rack 80VU. 7.00

Modify the Wiring in the Right Electronics Rack 90VU. 9.00

Modify the Wiring and the Equipment in the Electronics

Rack 500VU.

6.50

Modify the Wiring and the Equipment in the Avionics

Compartment.

4.00

Modify the Wiring between the Cockpit and the

Avionics Compartment.

17.00

Remove the Instrument Panels. 0.50

Modify the Wiring and the Equipment in the Cockpit. 10.00

Modify the Routing in the Glareshield Panel 13VU. 2.00

Install the Instrument Panels. 1.00

Install the Items removed for access. 2.00

On Bench

Modify the Wiring in the Maintenance Panel 490VU. 1.50

Modify the Instrument Panels. 3.00

Tests 4.50

Close-Up 0.50

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF 004

Task 222063-831-801-001: Modification

Get Access 0.50

On Aircraft

Modify the Wiring in the Left Electronics Rack 80VU. 7.00

Modify the Wiring in the Right Electronics Rack 90VU. 9.00

Modify the Wiring and the Equipment in the Electronics

Rack 500VU.

6.50

Modify the Wiring and the Equipment in the Avionics

Compartment.

4.00

Modify the Wiring between the Cockpit and the

Avionics Compartment.

17.00

Remove the Instrument Panels. 0.50

Modify the Wiring and the Equipment in the Cockpit. 10.00

Modify the Routing in the Glareshield Panel 13VU. 2.00

Install the Instrument Panels. 1.00

Install the Items removed for access. 2.00

On Bench

Modify the Wiring in the Maintenance Panel 490VU. 1.50

Modify the Instrument Panels. 3.00

Tests 4.50

Close-Up 0.50

TOTAL MANHOURS 69.00

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

Task 222063-831-801-001: Modification

ELAPSED TIME (HOURS) 32.50

**CONF ALL

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.790 KG (+1.7416 LB)

Effect on Balance +10.973 KGM (+79.367 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

06-41-52 06-41-53 11-00-00

20-21-12 21-21-00 21-31-00

22-10-00 22-15-12 22-18-34

22-27-00 22-40-00 24-00-00

24-31-11 28-21-00 31-10-00

31-31-15 31-51-00 31-53-34

33-12-00 33-13-00 33-14-00

34-44-34 34-48-00 34-52-00

34-73-11 52-10-00 52-30-00

52-52-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-33

20-33-44 20-52-10 20-52-21

20-55-00

Service Bulletin (SB) A310-22-2064

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00 51-40-20 51-40-40

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

**CONF 002

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

06-41-52 06-41-53 11-00-00

20-21-12 21-21-00 21-31-00

22-10-00 22-15-12 22-18-34

22-27-00 22-40-00 24-00-00

24-31-11 28-21-00 31-10-00

31-31-15 31-51-00 31-53-34

33-12-00 33-13-00 33-14-00

34-44-34 34-48-00 34-52-00

34-73-11 52-10-00 52-30-00

52-52-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-33

20-33-44 20-52-10 20-52-21

20-55-00

Service Bulletin (SB) A310-22-2064

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00 51-40-20 51-40-40

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 003

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

06-41-52 06-41-53 11-00-00

20-21-12 21-21-00 21-31-00

22-10-00 22-15-12 22-18-34

22-27-00 22-40-00 24-00-00

24-31-11 28-21-00 31-10-00

31-31-15 31-51-00 31-53-34

33-12-00 33-13-00 33-14-00

34-44-34 34-48-00 34-52-00

34-73-11 52-10-00 52-30-00

52-52-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-33

20-33-44 20-52-10 20-52-21

20-55-00

Service Bulletin (SB) A310-22-2064

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00 51-40-20 51-40-40

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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**CONF 004

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

06-41-52 06-41-53 11-00-00

20-21-12 21-21-00 21-31-00

22-10-00 22-15-12 22-18-34

22-27-00 22-40-00 24-00-00

24-31-11 28-21-00 31-10-00

31-31-15 31-51-00 31-53-34

33-12-00 33-13-00 33-14-00

34-44-34 34-48-00 34-52-00

34-73-11 52-10-00 52-30-00

52-52-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-33

20-33-44 20-52-10 20-52-21

20-55-00

Service Bulletin (SB) A310-22-2064

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00 51-40-20 51-40-40

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Aircraft Schematic Manual (ASM) 22-12-00 31-32-00 31-53-00

33-13-00 33-14-00 34-44-00

Aircraft Wiring List (AWL)

Aircraft Wiring Manual (AWM) 22-12-01 22-12-02 22-12-03

22-12-04 22-12-05 22-12-06

31-32-12 31-53-01 33-13-15

33-14-05 34-44-03

Illustrated Parts Catalog (IPC) 31-11-01

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 222063A01R01

Kit 222063A02R00

The AIRBUS material is included in the

commercial offer of the Letter Agreement,

and as such will be supplied by AIRBUS

Upgrade Services. To facilitate the material

reception, Airline Customers are requested to

send a Customer Purchase Order to:

AIRBUS Upgrade Services

Attn Key Account Manager (KAM)

(2) Price and Availability

Sales terms must be agreed between the Customer and AIRBUS in accordance with the

RFC (or RFC/RMO) procedure.

B. INDUSTRY SUPPORT INFORMATION

Refer to paragraph 2.A.(2): ’Price and Availability’.

C. LIST OF COMPONENTS

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 NSA937901MA2002 2 MODULE

2 NSA937901MA2204 1 MODULE

8 ASNA2327-3-4 2 BRACKET

9 NSA935513-07 4 MOUNT

10 NSA935504-01 4 BRACKET

11 NSA5527-03-06 2 SPACER

12 NSA5527-03-08 2 SPACER

13 NAS1801-3-28 2 SCREW

14 NAS1149F0332P 2 WASHER

15 ASNA2051DCJ3215 4 RIVET

16 ASNA2051DCJ2412 16 RIVET

17 A9251134000000 2 PLATE

18 MS21071-08 4 NUT

20 EN3646A61210BN 1 CONNECTR

21 ABS0638A12 4 BACKSHLL

22 NAS1149FN832P 4 WASHER

23 NAS1101-08-8 4 SCREW

24 NSA935401-05 1662 TIE

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ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

25 EN6049-007-08-5 10 (M) SLEEVE

28 NSA5527-03-14 4 SPACER

29 EN3646A61210BW 1 CONNECTR

30 EN3646A61210BX 1 CONNECTR

31 EN3646A61210BY 1 CONNECTR

A9000095401695 1 BUNDLE

A9100095401496 1 PLACARD

NSA935401-03 1050 TIE

NSA935401-08 1000 TIE

NSA937901E3 2 LABEL

NSA937901E4 1 LABEL

NSA937901E5 1 LABEL

NSA937901E9 1 LABEL

NSA937901S 4 CLAMP

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 NSA937901MA2002 2 MODULE

8 ASNA2327-3-4 2 BRACKET

9 NSA935513-07 4 MOUNT

10 NSA935504-01 4 BRACKET

11 NSA5527-03-06 2 SPACER

12 NSA5527-03-08 2 SPACER

13 NAS1801-3-28 2 SCREW

14 NAS1149F0332P 2 WASHER

15 ASNA2051DCJ3215 4 RIVET

16 ASNA2051DCJ2412 16 RIVET

17 A9251134000000 2 PLATE

18 MS21071-08 4 NUT

20 EN3646A61210BN 1 CONNECTR

21 ABS0638A12 4 BACKSHLL

22 NAS1149FN832P 4 WASHER

23 NAS1101-08-8 4 SCREW

24 NSA935401-05 1662 TIE

25 EN6049-007-08-5 10 (M) SLEEVE

28 NSA5527-03-14 4 SPACER

29 EN3646A61210BW 1 CONNECTR

30 EN3646A61210BX 1 CONNECTR

31 EN3646A61210BY 1 CONNECTR

A9000095401695 1 BUNDLE

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ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

NSA935401-03 1050 TIE

NSA935401-08 1000 TIE

NSA937901E3 2 LABEL

NSA937901E4 1 LABEL

NSA937901E5 1 LABEL

NSA937901S 2 CLAMP

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL (3) A9252407020200

6 A9251134300100 PANEL (4) A9252407020300

F. TOOLING

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 222063-831-801-001 - Modification

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

**CONF 001

Zone

120 210

From 120 to 210

Modified FIN

511VC1A 511VC1A1 511VC2A 511VC2A1 512VC1A 512VC1A1 512VC2A 512VC2A1

190VT 190VT34 190VT35

Access

Door 131AZ 132AZ 811 831 841

Manpower

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF 002

Zone

120 210

From 120 to 210

Modified FIN

511VC1A 511VC1A1 511VC2A 511VC2A1 512VC1A 512VC1A1 512VC2A 512VC2A1

190VT 190VT34 190VT35 1487VT 1487VT9

Access

Door 131AZ 132AZ 811 831 841

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Manpower

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF 003

Zone

120 210

From 120 to 210

Modified FIN

511VC1A 511VC1A1 511VC2A 511VC2A1 512VC1A 512VC1A1 512VC2A 512VC2A1

190VT 190VT34 190VT35

Access

Door 131AZ 132AZ 811 831 841

Manpower

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF 004

Zone

120 210

Modified FIN

511VC1A 511VC1A1 511VC2A 511VC2A1 512VC1A 512VC1A1 512VC2A 512VC2A1

190VT 190VT34 190VT35 1487VT 1487VT9

Access

Door 131AZ 132AZ 811 831 841

Manpower

TOTAL MANHOURS 69.00

ELAPSED TIME (HOURS) 32.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 222063-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

(2) Subtask 222063-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

11-00-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-33

20-33-44

20-52-21

Structural Repair Manual (SRM) 51-23-00

51-40-20

51-40-40

(a) For the specification of the materials (Mat. No.) given in this Service Bulletin (Refer

to Consumable Material List (CML)).

(b) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001).

(d) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001).

(e) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(f) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(g) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page

Block 001).

(h) To torque tighten the standard threaded fasteners (Refer to AMM 20-21-12, Page

Block 001).

(i) For the removal and installation of fasteners (Refer to SRM 51-40-20).

(j) Renew the protective finish (Refer to SRM 51-23-00).

(k) For fastener hole diameters and drill and deburr data (Refer to SRM 51-40-40).

(l) Cut the rivets to the necessary length.

(m) Obey the instructions for the general installation of electrical wire harnesses (Refer

to ESPM 20-33-00).

(n) Put blanking caps on the disconnected electrical connectors.

(o) To install new wires, cut them to the necessary length, crimp the terminals and

connect them.

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(p) Route the new wires with the wires that are in the aircraft.

(q) Use existing spare conduits to route wires in locations with difficult access.

(r) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(s) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM

20-25-51).

(t) When you install protective electrical conduit (Refer to ESPM 20-33-44 and ESPM

20-33-33):

- Beburr the ends after you have cut it to the correct size.

- At the lowest part of a cable loop make two cut-outs in the conduit to give

drainage.

- Cut the conduit before installation to make sure you do not damage the

electrical cables.

- When necessary, install cable ties from between 13 mm and 15 mm (0.51 and

0.59 in.) from the cut ends of the conduit, to give support.

- Where necessary, attach the conduit to the aircraft structure or the existing

cable harnesses, with the cable ties supplied.

(u) For the general installation of placards (Refer to AMM 11-00-00, Page Block 001).

**CONF 002

(1) Subtask 222063-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

(2) Subtask 222063-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

11-00-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

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References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-33

20-33-44

20-52-21

Structural Repair Manual (SRM) 51-23-00

51-40-20

51-40-40

(a) For the specification of the materials (Mat. No.) given in this Service Bulletin (Refer

to Consumable Material List (CML)).

(b) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001).

(d) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001).

(e) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(f) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(g) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page

Block 001).

(h) To torque tighten the standard threaded fasteners (Refer to AMM 20-21-12, Page

Block 001).

(i) For the removal and installation of fasteners (Refer to SRM 51-40-20).

(j) Renew the protective finish (Refer to SRM 51-23-00).

(k) For fastener hole diameters and drill and deburr data (Refer to SRM 51-40-40).

(l) Cut the rivets to the necessary length.

(m) Obey the instructions for the general installation of electrical wire harnesses (Refer

to ESPM 20-33-00).

(n) Put blanking caps on the disconnected electrical connectors.

(o) To install new wires, cut them to the necessary length, crimp the terminals and

connect them.

(p) Route the new wires with the wires that are in the aircraft.

(q) Use existing spare conduits to route wires in locations with difficult access.

(r) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

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(s) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM

20-25-51).

(t) When you install protective electrical conduit (Refer to ESPM 20-33-44 and ESPM

20-33-33):

- Beburr the ends after you have cut it to the correct size.

- At the lowest part of a cable loop make two cut-outs in the conduit to give

drainage.

- Cut the conduit before installation to make sure you do not damage the

electrical cables.

- When necessary, install cable ties from between 13 mm and 15 mm (0.51 and

0.59 in.) from the cut ends of the conduit, to give support.

- Where necessary, attach the conduit to the aircraft structure or the existing

cable harnesses, with the cable ties supplied.

(u) For the general installation of placards (Refer to AMM 11-00-00, Page Block 001).

**CONF 003

(1) Subtask 222063-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

(2) Subtask 222063-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

11-00-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-33

20-33-44

20-52-21

Structural Repair Manual (SRM) 51-23-00

51-40-20

51-40-40

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(a) For the specification of the materials (Mat. No.) given in this Service Bulletin (Refer

to Consumable Material List (CML)).

(b) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001).

(d) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001).

(e) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(f) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(g) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page

Block 001).

(h) To torque tighten the standard threaded fasteners (Refer to AMM 20-21-12, Page

Block 001).

(i) For the removal and installation of fasteners (Refer to SRM 51-40-20).

(j) Renew the protective finish (Refer to SRM 51-23-00).

(k) For fastener hole diameters and drill and deburr data (Refer to SRM 51-40-40).

(l) Cut the rivets to the necessary length.

(m) Obey the instructions for the general installation of electrical wire harnesses (Refer

to ESPM 20-33-00).

(n) Put blanking caps on the disconnected electrical connectors.

(o) To install new wires, cut them to the necessary length, crimp the terminals and

connect them.

(p) Route the new wires with the wires that are in the aircraft.

(q) Use existing spare conduits to route wires in locations with difficult access.

(r) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(s) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM

20-25-51).

(t) When you install protective electrical conduit (Refer to ESPM 20-33-44 and ESPM

20-33-33):

- Beburr the ends after you have cut it to the correct size.

- At the lowest part of a cable loop make two cut-outs in the conduit to give

drainage.

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- Cut the conduit before installation to make sure you do not damage the

electrical cables.

- When necessary, install cable ties from between 13 mm and 15 mm (0.51 and

0.59 in.) from the cut ends of the conduit, to give support.

- Where necessary, attach the conduit to the aircraft structure or the existing

cable harnesses, with the cable ties supplied.

(u) For the general installation of placards (Refer to AMM 11-00-00, Page Block 001).

**CONF 004

(1) Subtask 222063-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

(2) Subtask 222063-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

11-00-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-33

20-33-44

20-52-21

Structural Repair Manual (SRM) 51-23-00

51-40-20

51-40-40

(a) For the specification of the materials (Mat. No.) given in this Service Bulletin (Refer

to Consumable Material List (CML)).

(b) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001).

(d) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001).

(e) Tag the parts that you must remove and retain to make the subsequent installation

easier.

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(f) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(g) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page

Block 001).

(h) To torque tighten the standard threaded fasteners (Refer to AMM 20-21-12, Page

Block 001).

(i) For the removal and installation of fasteners (Refer to SRM 51-40-20).

(j) Renew the protective finish (Refer to SRM 51-23-00).

(k) For fastener hole diameters and drill and deburr data (Refer to SRM 51-40-40).

(l) Cut the rivets to the necessary length.

(m) Obey the instructions for the general installation of electrical wire harnesses (Refer

to ESPM 20-33-00).

(n) Put blanking caps on the disconnected electrical connectors.

(o) To install new wires, cut them to the necessary length, crimp the terminals and

connect them.

(p) Route the new wires with the wires that are in the aircraft.

(q) Use existing spare conduits to route wires in locations with difficult access.

(r) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(s) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM

20-25-51).

(t) When you install protective electrical conduit (Refer to ESPM 20-33-44 and ESPM

20-33-33):

- Beburr the ends after you have cut it to the correct size.

- At the lowest part of a cable loop make two cut-outs in the conduit to give

drainage.

- Cut the conduit before installation to make sure you do not damage the

electrical cables.

- When necessary, install cable ties from between 13 mm and 15 mm (0.51 and

0.59 in.) from the cut ends of the conduit, to give support.

- Where necessary, attach the conduit to the aircraft structure or the existing

cable harnesses, with the cable ties supplied.

(u) For the general installation of placards (Refer to AMM 11-00-00, Page Block 001).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 222063-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put the access platforms in position at the level of doors 831 or 841 and 811.

(c) Open the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(d) Open the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(e) Open the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001 and

AMM 06-41-53, Page Block 001).

(f) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(g) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(h) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(i) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(j) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(k) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(l) Put a warning notice in the cockpit to tell persons not to start the APU.

(m) Put a warning notice in the cockpit to tell persons not to start the ENG1,2

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(n) Battery disconnection:

1 For Job Set-up, refer to the removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

2 Turn the knurled nut a quarter turn

3 Disconnect the connectors

4 Connect the connector on the battery

5 Turn the knurled nut a quarter turn

**CONF 002

(1) Subtask 222063-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put the access platforms in position at the level of doors 831 or 841 and 811.

(c) Open the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(d) Open the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(e) Open the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001 and

AMM 06-41-53, Page Block 001).

(f) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(g) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(h) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(i) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(j) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(k) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(l) Put a warning notice in the cockpit to tell persons not to start the APU.

(m) Put a warning notice in the cockpit to tell persons not to start the ENG1,2

(n) Battery disconnection:

1 For Job Set-up, refer to the removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

2 Turn the knurled nut a quarter turn

3 Disconnect the connectors

4 Connect the connector on the battery

5 Turn the knurled nut a quarter turn

**CONF 003

(1) Subtask 222063-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put the access platforms in position at the level of doors 831 or 841 and 811.

(c) Open the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(d) Open the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(e) Open the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001 and

AMM 06-41-53, Page Block 001).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(f) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(g) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(h) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(i) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(j) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(k) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(l) Put a warning notice in the cockpit to tell persons not to start the APU.

(m) Put a warning notice in the cockpit to tell persons not to start the ENG1,2

(n) Battery disconnection:

1 For Job Set-up, refer to the removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

2 Turn the knurled nut a quarter turn

3 Disconnect the connectors

4 Connect the connector on the battery

5 Turn the knurled nut a quarter turn

**CONF 004

(1) Subtask 222063-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put the access platforms in position at the level of doors 831 or 841 and 811.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(c) Open the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(d) Open the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(e) Open the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001 and

AMM 06-41-53, Page Block 001).

(f) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(g) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(h) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(i) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(j) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(k) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(l) Put a warning notice in the cockpit to tell persons not to start the APU.

(m) Put a warning notice in the cockpit to tell persons not to start the ENG1,2

(n) Battery disconnection:

1 For Job Set-up, refer to the removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

2 Turn the knurled nut a quarter turn

3 Disconnect the connectors

4 Connect the connector on the battery

5 Turn the knurled nut a quarter turn

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 30

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**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 222063-831-001-002 - Modify the Wiring in the Left Electronics Rack 80VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 80VU

Manpower Resources

Manhours 7.00

Minimum number of person 1

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 200 TIE

A9000095401695 BUNDLE

NSA935401-03 200 TIE

NSA935401-08 150 TIE

References

Aircraft Maintenance Manual (AMM) 22-18-34, Page Block 401

Fig. A-FWAAA

Modification of the Wiring in the Left

Electronic Rack 80VU.

Sheet 01

Fig. A-FHAAA

Hook-up Chart of the Modification of the

Wiring in the Left Electronic Rack 80VU.

Sheet 01

(a) Remove the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(b) Install the wires as shown in the wiring diagram Fig. A-FWAAA Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 14 (Refer to Fig. A-FHAAA Sheet 01), supplied in:

Bundle A9000095401695

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SERVICE BULLETIN

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

150 Tie-Cable NSA935401-08

(d) Install the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(2) Subtask 222063-831-002-003 - Modify the Wiring in the Right Electronics Rack

90VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 90VU

Manpower Resources

Manhours 9.00

Minimum number of person 1

Subtask elapsed time 9.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

NSA935401-03 300 TIE

NSA935401-08 300 TIE

References

Aircraft Maintenance Manual (AMM) 31-31-15, Page Block 401

31-53-34, Page Block 401

Fig. A-FHBAB

Hook-up Chart of the Modification of the

Wiring in the Right Electronic Rack

90VU.

Sheet 01

Sheet 02

Fig. A-FWBAB

Modification of the Wiring in the Right

Electronic Rack 90VU.

Sheet 01

Sheet 02

(a) Remove the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(b) Remove the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

(c) Modify the wires as shown in the wiring diagrams Fig. A-FWBAB Sheet 01and Fig.

A-FWBAB Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHBAB Sheet 01).

(d) If necessary, use the contacts supplied in:

Bundle A9000095401695

(e) Install the wires as shown in the wiring diagram Fig. A-FWBAB Sheet 02, and as

given in the hook-up chart lines:

- 12 thru 23 (Refer to Fig. A-FHBAB Sheet 01) and

- 1 thru 7 (Refer to Fig. A-FHBAB Sheet 02), supplied in:

Bundle A9000095401695

(f) Attach the wires with:

300 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

300 Tie-Cable NSA935401-08

(g) Install the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

(h) Install the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

(3) Subtask 222063-831-004-002 - Modify the Wiring and the Equipment in the

Electronics Rack 500VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 500VU

Manpower Resources

Manhours 6.50

Minimum number of person 1

Subtask elapsed time 6.50

Skills ELECTRICAL

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 33

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Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

References

Aircraft Maintenance Manual (AMM) 34-44-34, Page Block 401

Fig. A-FHDAA

Hook-up Chart of the Modification of the

Wiring in the Electronic Rack 500VU.

Sheet 01

Fig. A-FWDAA

Modification of the Wiring in the

Electronic Rack 500VU.

Sheet 01

Sheet 02

(a) Remove the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

(b) Modify the wiring in the Electronic Rack 500VU:

1 Modify the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 01 and

Fig. A-FWDAA Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHDAA Sheet 01).

2 If necessary, use contacts supplied in:

Bundle A9000095401695

3 Install the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 02, and

as given in the hook-up chart lines:

- 12 thru 21 (Refer to Fig. A-FHDAA Sheet 01), supplied in:

Bundle A9000095401695

4 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(c) Install the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 34

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SERVICE BULLETIN

(4) Subtask 222063-831-005-002 - Modify the Wiring and the Equipment in the

Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

References

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

Fig. A-FWFAA

Modification of the Wiring in the Avionics

Compartment.

Sheet 01

Fig. A-FHFAA

Hook-up Chart of the Modification of the

Wiring in the Avionics Compartment.

Sheet 01

(a) Modify the wiring in the avionics compartment:

1 Install the wires as shown in the wiring diagram Fig. A-FWFAA Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHFAA Sheet 01), supplied in:

Bundle A9000095401695

2 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 35

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SERVICE BULLETIN

(5) Subtask 222063-831-003-005 - Modify the Wiring in the Maintenance Panel 490VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 490VU

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 50 TIE

A9000095401695 BUNDLE

NSA935401-03 50 TIE

NSA935401-08 50 TIE

References

Aircraft Maintenance Manual (AMM) 33-13-00, Page Block 001

Fig. A-FHCAA

Hook-up Chart of the Modification of the

Wiring in the Maintenance Panel 490VU.

Sheet 01

Fig. A-FWCAA

Modification of the Wiring in the

Maintenance Panel 490VU.

Sheet 01

(a) Remove the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

(b) Install the wires as shown in the wiring diagram Fig. A-FWCAA Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHCAA Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

50 Tie-Cable NSA935401-03

50 Tie-Cable NSA935401-05 Item 24

50 Tie-Cable NSA935401-08

(d) Install the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 36

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SERVICE BULLETIN

(6) Subtask 222063-831-006-003 - Modify the Wiring between the Cockpit and the

Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

From 120 Access Door 811, Door 131AZ, Door 132AZ

To 210 Access Door 831, Door 841

Manpower Resources

Manhours 17.00

Minimum number of person 2

Subtask elapsed time 8.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA937901MA2002 2 MODULE

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

NSA935401-03 200 TIE

NSA935401-08 200 TIE

NSA937901E3 2 LABEL

NSA937901E4 1 LABEL

NSA937901E5 1 LABEL

NSA937901S 2 CLAMP

References

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

Fig. A-FHEAB

Hook-up Chart of the Modification of the

Wiring between the Avionics

Compartment and the Cockpit.

Sheet 01

Fig. A-FWEAB

Modification of the Wiring between the

Avionics Compartment and the Cockpit.

Sheet 01

Sheet 02

(a) Modify the terminal block 190VT:

1 At the positions 34 and 35, install (Refer to Fig. A-FBAAA Sheet 01):

FIN 190VT34

1 Module NSA937901MA2002 Item 1

with:

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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1 Label Identification NSA937901E3

1 Label Identification NSA937901E4

FIN 190VT35

1 Module NSA937901MA2002 Item 1

with:

1 Label Identification NSA937901E3

1 Label Identification NSA937901E5

2 If necessary, use:

2 Clamp-End NSA937901S

(b) Install the wires as shown in the wiring diagrams Fig. A-FWEAB Sheet 01 and Fig.

A-FWEAB Sheet 02, and as shown in the hook-up chart lines:

- 1 thru 18 (Refer to Fig. A-FHEAB Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

200 Tie-Cable NSA935401-08

(7) Subtask 222063-020-001-001 - Remove the Instrument Panels.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

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References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Remove the instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3) Retain

1 Instrument Panel A9252407020300 Item (4) Retain

NOTE: Remove and retain the attachment hardware.

(b) Remove and disconnect the EFIS control panels 42FN1 and 42FN2 (panels 412VU

and 413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet

01) for access.

(c) Remove and disconnect the Flight Control Unit 303CA (Refer to AMM 22-15-12,

Page Block 401 and Fig. A-FBCAA Sheet 01) for access.

(8) Subtask 222063-831-007-003 - Modify the Wiring and the Equipment in the Cockpit.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9100095401496 PLACARD

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 ASNA2327-3-4 2 BRACKET

9 NSA935513-07 4 MOUNT

10 NSA935504-01 4 BRACKET

11 NSA5527-03-06 2 SPACER

12 NSA5527-03-08 2 SPACER

13 NAS1801-3-28 2 SCREW

14 NAS1149F0332P 2 WASHER

15 ASNA2051DCJ3215 4 RIVET

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 39

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 ASNA2051DCJ2412 8 RIVET

20 EN3646A61210BN 1 CONNECTR

21 ABS0638A12 4 BACKSHLL

24 NSA935401-05 200 TIE

29 EN3646A61210BW 1 CONNECTR

30 EN3646A61210BX 1 CONNECTR

31 EN3646A61210BY 1 CONNECTR

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

References

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

Fig. A-FHGAB

Hook-up Chart of the Modification of the

Wiring in the Cockpit.

Sheet 01

Fig. A-FWGAB

Modification of the Wiring in the Cockpit.

Sheet 01

Fig. A-FBEAA

Modification of the Equipment in the

Cockpit.

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Modify the equipment in the cockpit (Refer to Fig. A-FBEAA):

1 On the LH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800000 Item (7) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

1 Spacer NSA5527-03-06 Item 11

1 Spacer NSA5527-03-08 Item 12

Attach with:

1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

2 On the RH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800100 Item (19) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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Decorative Paint 16-047 As required

c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

1 Spacer NSA5527-03-06 Item 11

1 Spacer NSA5527-03-08 Item 12

Attach with:

1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

(b) Modify the wiring in the cockpit:

1 Install the wires as shown in the wiring diagram Fig. A-FWGAB Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 10 (Refer to Fig. A-FHGAB Sheet 01), supplied in:

Bundle A9000095401695

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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2 Attach the wires with:

100 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(c) With the wires, install the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A

(Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02):

FIN 511VC1A

1 Connector-Plug EN3646A61210BN Item 20

FIN 511VC1A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 511VC2A

1 Connector-Plug EN3646A61210BW Item 29

FIN 511VC2A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 512VC1A

1 Connector-Plug EN3646A61210BX Item 30

FIN 512VC1A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 512VC2A

1 Connector-Plug EN3646A61210BY Item 31

FIN 512VC2A1

1 Backshell-Connector ABS0638A12 Item 21

(d) Together with the wires, install the identification plates 511VC1A, 511VC2A,

512VC1A and 512VC2A, supplied in:

Placard set A9100095401496

(9) Subtask 222063-831-009-002 - Modify the Routing in the Glareshield Panel 13VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 13VU

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 43

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SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9100095401496 PLACARD

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 12 TIE

25 EN6049-007-08-5 10 (M) SLEEVE

28 NSA5527-03-14 4 SPACER

References

Fig. A-FBHAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

Fig. A-FBIAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

(a) Install (Refer to Fig. A-FBHAA):

10 (M) Sleeve-Protective EN6049-007-08-5 Item 25

8 Tie-Cable NSA935401-05 Item 24

Near the rest plates, bond the placards identified 510VU1 and 510VU2 as shown in

Fig. A-FBHAA and supplied in:

Placard set A9100095401496

(b) Install (Refer to Fig. A-FBIAA):

4 Spacer NSA5527-03-14 Item 28

4 Tie-Cable NSA935401-05 Item 24

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 44

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SERVICE BULLETIN

(10) Subtask 222063-831-008-002 - Modify the Instrument Panels.

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 ASNA2051DCJ2412 8 RIVET

18 MS21071-08 4 NUT

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL (3) A9252407020200

6 A9251134300100 PANEL (4) A9252407020300

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Cut the LH and RH instrument panel at the dimensions given in Fig. A-FBDAA

Sheet 02):

(b) On the LH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(c) Temporary put in position the nut-plates Item 18.

(d) Drill four holes on the LH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

(e) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(f) On the RH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(g) Temporary put in position the nut-plates Item 18.

(h) Drill four holes on the RH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

(i) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(j) Re-identify the modified instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3)

becomes:

1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9252407020300 Item (4)

becomes:

1 Instrument Panel A9251134300100 Item 6

(11) Subtask 222063-420-001-002 - Install the Instrument Panels.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

17 A9251134000000 2 PLATE

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 46

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

22 NAS1149FN832P 4 WASHER

23 NAS1101-08-8 4 SCREW

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL

6 A9251134300100 PANEL

References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

Fig. A-FBFAA

Installation of the Rest Plates on the

Instrument Panels.

Sheet 01

(a) Install (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9251134300100 Item 6

NOTE: Use the retained attachment hardware.

(b) Connect the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A to the rest

plates Item 17 (Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02).

(c) Install (Refer to Fig. A-FBFAA Sheet 01):

2 Rest Plate A9251134000000 Item 17

4 Washer NAS1149FN832P Item 22

4 Screw NAS1101-08-8 Item 23

(12) Subtask 222063-410-001-001 - Install the Items removed for access.

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 47

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@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

(a) Connect and install the EFIS control panels 42FN1 and 42FN2 (panels 412VU and

413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet 01)

removed for access.

(b) Connect and install the Flight Control Unit 303CA (Refer to AMM 22-15-12, Page

Block 401 and Fig. A-FBCAA Sheet 01) removed for access.

**CONF 002

(1) Subtask 222063-831-001-001 - Modify the Wiring in the Left Electronics Rack 80VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 80VU

Manpower Resources

Manhours 7.00

Minimum number of person 1

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 200 TIE

A9000095401695 BUNDLE

NSA935401-03 200 TIE

NSA935401-08 150 TIE

References

Aircraft Maintenance Manual (AMM) 22-18-34, Page Block 401

Fig. A-FWAAA

Modification of the Wiring in the Left

Electronic Rack 80VU.

Sheet 01

Fig. A-FHAAA

Hook-up Chart of the Modification of the

Wiring in the Left Electronic Rack 80VU.

Sheet 01

(a) Remove the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 48

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SERVICE BULLETIN

(b) Install the wires as shown in the wiring diagram Fig. A-FWAAA Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 14 (Refer to Fig. A-FHAAA Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

150 Tie-Cable NSA935401-08

(d) Install the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(2) Subtask 222063-831-002-002 - Modify the Wiring in the Right Electronics Rack

90VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 90VU

Manpower Resources

Manhours 9.00

Minimum number of person 1

Subtask elapsed time 9.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

NSA935401-03 300 TIE

NSA935401-08 300 TIE

References

Aircraft Maintenance Manual (AMM) 31-31-15, Page Block 401

31-53-34, Page Block 401

Fig. A-FHBAB

Hook-up Chart of the Modification of the

Wiring in the Right Electronic Rack

90VU.

Sheet 01

Sheet 02

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 49

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SERVICE BULLETIN

References

Fig. A-FWBAB

Modification of the Wiring in the Right

Electronic Rack 90VU.

Sheet 01

Sheet 02

(a) Remove the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

(b) Remove the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

(c) Modify the wires as shown in the wiring diagrams Fig. A-FWBAB Sheet 01and Fig.

A-FWBAB Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHBAB Sheet 01).

(d) If necessary, use the contacts supplied in:

Bundle A9000095401695

(e) Install the wires as shown in the wiring diagram Fig. A-FWBAB Sheet 02, and as

given in the hook-up chart lines:

- 12 thru 23 (Refer to Fig. A-FHBAB Sheet 01) and

- 1 thru 7 (Refer to Fig. A-FHBAB Sheet 02), supplied in:

Bundle A9000095401695

(f) Attach the wires with:

300 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

300 Tie-Cable NSA935401-08

(g) Install the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

(h) Install the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

(3) Subtask 222063-831-004-001 - Modify the Wiring and the Equipment in the

Electronics Rack 500VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 500VU

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 50

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@A310

SERVICE BULLETIN

Manpower Resources

Manhours 6.50

Minimum number of person 1

Subtask elapsed time 6.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 NSA937901MA2204 1 MODULE

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

NSA937901E9 1 LABEL

NSA937901S 2 CLAMP

References

Aircraft Maintenance Manual (AMM) 34-44-34, Page Block 401

Fig. A-FBBAA

Modification of the Equipment in the

Electronic Rack 500VU.

Sheet 01

Fig. A-FWDAA

Modification of the Wiring in the

Electronic Rack 500VU.

Sheet 01

Sheet 02

Fig. A-FHDAA

Hook-up Chart of the Modification of the

Wiring in the Electronic Rack 500VU.

Sheet 01

(a) Remove the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

(b) Modify the terminal block 1487VT:

1 At the position 9, install (Refer to Fig. A-FBBAA Sheet 01):

FIN 1487VT9

1 Module NSA937901MA2204 Item 2

1 Label Identification NSA937901E9

2 If necessary, use:

2 Clamp-End NSA937901S

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(c) Modify the wiring in the Electronic Rack 500VU:

1 Modify the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 01 and

Fig. A-FWDAA Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHDAA Sheet 01).

2 If necessary, use contacts supplied in:

Bundle A9000095401695

3 Install the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 02, and

as given in the hook-up chart lines:

- 12 thru 21 (Refer to Fig. A-FHDAA Sheet 01), supplied in:

Bundle A9000095401695

4 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(d) Install the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

(4) Subtask 222063-831-005-001 - Modify the Wiring and the Equipment in the

Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 52

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@A310

SERVICE BULLETIN

References

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

Fig. A-FWFAA

Modification of the Wiring in the Avionics

Compartment.

Sheet 01

Fig. A-FHFAA

Hook-up Chart of the Modification of the

Wiring in the Avionics Compartment.

Sheet 01

(a) Modify the wiring in the avionics compartment:

1 Install the wires as shown in the wiring diagram Fig. A-FWFAA Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHFAA Sheet 01), supplied in:

Bundle A9000095401695

2 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(5) Subtask 222063-831-003-002 - Modify the Wiring in the Maintenance Panel 490VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 490VU

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 50 TIE

A9000095401695 BUNDLE

NSA935401-03 50 TIE

NSA935401-08 50 TIE

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 53

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@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 33-13-00, Page Block 001

Fig. A-FWCAA

Modification of the Wiring in the

Maintenance Panel 490VU.

Sheet 01

Fig. A-FHCAA

Hook-up Chart of the Modification of the

Wiring in the Maintenance Panel 490VU.

Sheet 01

(a) Remove the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

(b) Install the wires as shown in the wiring diagram Fig. A-FWCAA Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHCAA Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

50 Tie-Cable NSA935401-03

50 Tie-Cable NSA935401-05 Item 24

50 Tie-Cable NSA935401-08

(d) Install the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

(6) Subtask 222063-831-006-002 - Modify the Wiring between the Cockpit and the

Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

From 120 Access Door 811, Door 131AZ, Door 132AZ

To 210 Access Door 831, Door 841

Manpower Resources

Manhours 17.00

Minimum number of person 2

Subtask elapsed time 8.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA937901MA2002 2 MODULE

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 54

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@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA935401-03 200 TIE

NSA935401-08 200 TIE

NSA937901E3 2 LABEL

NSA937901E4 1 LABEL

NSA937901E5 1 LABEL

NSA937901S 2 CLAMP

References

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

Fig. A-FHEAB

Hook-up Chart of the Modification of the

Wiring between the Avionics

Compartment and the Cockpit.

Sheet 01

Fig. A-FWEAB

Modification of the Wiring between the

Avionics Compartment and the Cockpit.

Sheet 01

Sheet 02

(a) Modify the terminal block 190VT:

1 At the positions 34 and 35, install (Refer to Fig. A-FBAAA Sheet 01):

FIN 190VT34

1 Module NSA937901MA2002 Item 1

with:

1 Label Identification NSA937901E3

1 Label Identification NSA937901E4

FIN 190VT35

1 Module NSA937901MA2002 Item 1

with:

1 Label Identification NSA937901E3

1 Label Identification NSA937901E5

2 If necessary, use:

2 Clamp-End NSA937901S

(b) Install the wires as shown in the wiring diagrams Fig. A-FWEAB Sheet 01 and Fig.

A-FWEAB Sheet 02, and as shown in the hook-up chart lines:

- 1 thru 18 (Refer to Fig. A-FHEAB Sheet 01), supplied in:

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 55

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Bundle A9000095401695

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

200 Tie-Cable NSA935401-08

(7) Subtask 222063-020-001-001 - Remove the Instrument Panels.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Remove the instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3) Retain

1 Instrument Panel A9252407020300 Item (4) Retain

NOTE: Remove and retain the attachment hardware.

(b) Remove and disconnect the EFIS control panels 42FN1 and 42FN2 (panels 412VU

and 413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet

01) for access.

(c) Remove and disconnect the Flight Control Unit 303CA (Refer to AMM 22-15-12,

Page Block 401 and Fig. A-FBCAA Sheet 01) for access.

(8) Subtask 222063-831-007-002 - Modify the Wiring and the Equipment in the Cockpit.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 56

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SERVICE BULLETIN

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

AIRFRAME

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 ASNA2327-3-4 2 BRACKET

9 NSA935513-07 4 MOUNT

10 NSA935504-01 4 BRACKET

11 NSA5527-03-06 2 SPACER

12 NSA5527-03-08 2 SPACER

13 NAS1801-3-28 2 SCREW

14 NAS1149F0332P 2 WASHER

15 ASNA2051DCJ3215 4 RIVET

16 ASNA2051DCJ2412 8 RIVET

20 EN3646A61210BN 1 CONNECTR

21 ABS0638A12 4 BACKSHLL

24 NSA935401-05 200 TIE

29 EN3646A61210BW 1 CONNECTR

30 EN3646A61210BX 1 CONNECTR

31 EN3646A61210BY 1 CONNECTR

A9000095401695 BUNDLE

A9100095401496 PLACARD

NSA935401-03 100 TIE

NSA935401-08 100 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

References

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

Fig. A-FHGAB

Hook-up Chart of the Modification of the

Wiring in the Cockpit.

Sheet 01

Fig. A-FWGAB

Modification of the Wiring in the Cockpit.

Sheet 01

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 57

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SERVICE BULLETIN

References

Fig. A-FBEAA

Modification of the Equipment in the

Cockpit.

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Modify the equipment in the cockpit (Refer to Fig. A-FBEAA):

1 On the LH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800000 Item (7) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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1 Spacer NSA5527-03-06 Item 11

1 Spacer NSA5527-03-08 Item 12

Attach with:

1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

2 On the RH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800100 Item (19) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 59

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SERVICE BULLETIN

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

1 Spacer NSA5527-03-06 Item 11

1 Spacer NSA5527-03-08 Item 12

Attach with:

1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

(b) Modify the wiring in the cockpit:

1 Install the wires as shown in the wiring diagram Fig. A-FWGAB Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 10 (Refer to Fig. A-FHGAB Sheet 01), supplied in:

Bundle A9000095401695

2 Attach the wires with:

100 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(c) With the wires, install the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A

(Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02):

FIN 511VC1A

1 Connector-Plug EN3646A61210BN Item 20

FIN 511VC1A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 511VC2A

1 Connector-Plug EN3646A61210BW Item 29

FIN 511VC2A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 512VC1A

1 Connector-Plug EN3646A61210BX Item 30

FIN 512VC1A1

1 Backshell-Connector ABS0638A12 Item 21

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

FIN 512VC2A

1 Connector-Plug EN3646A61210BY Item 31

FIN 512VC2A1

1 Backshell-Connector ABS0638A12 Item 21

(d) Together with the wires, install the identification plates 511VC1A, 511VC2A,

512VC1A and 512VC2A, supplied in:

Placard set A9100095401496

(9) Subtask 222063-831-009-001 - Modify the Routing in the Glareshield Panel 13VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 13VU

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 12 TIE

25 EN6049-007-08-5 10 (M) SLEEVE

28 NSA5527-03-14 4 SPACER

A9100095401496 PLACARD

References

Fig. A-FBHAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

Fig. A-FBIAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

(a) Install (Refer to Fig. A-FBHAA):

10 (M) Sleeve-Protective EN6049-007-08-5 Item 25

8 Tie-Cable NSA935401-05 Item 24

Near the rest plates, bond the placards identified 510VU1 and 510VU2 as shown in

Fig. A-FBHAA and supplied in:

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

Placard set A9100095401496

(b) Install (Refer to Fig. A-FBIAA):

4 Spacer NSA5527-03-14 Item 28

4 Tie-Cable NSA935401-05 Item 24

(10) Subtask 222063-831-008-001 - Modify the Instrument Panels.

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 ASNA2051DCJ2412 8 RIVET

18 MS21071-08 4 NUT

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL (3) A9252407020200

6 A9251134300100 PANEL (4) A9252407020300

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Cut the LH and RH instrument panel at the dimensions given in Fig. A-FBDAA

Sheet 02):

(b) On the LH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(c) Temporary put in position the nut-plates Item 18.

(d) Drill four holes on the LH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(e) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(f) On the RH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(g) Temporary put in position the nut-plates Item 18.

(h) Drill four holes on the RH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

(i) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(j) Re-identify the modified instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3)

becomes:

1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9252407020300 Item (4)

becomes:

1 Instrument Panel A9251134300100 Item 6

(11) Subtask 222063-420-001-001 - Install the Instrument Panels.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 63

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SERVICE BULLETIN

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

17 A9251134000000 2 PLATE

22 NAS1149FN832P 4 WASHER

23 NAS1101-08-8 4 SCREW

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL

6 A9251134300100 PANEL

References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

Fig. A-FBFAA

Installation of the Rest Plates on the

Instrument Panels.

Sheet 01

(a) Install (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9251134300100 Item 6

NOTE: Use the retained attachment hardware.

(b) Connect the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A to the rest

plates Item 17 (Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02).

(c) Install (Refer to Fig. A-FBFAA Sheet 01):

2 Rest Plate A9251134000000 Item 17

4 Washer NAS1149FN832P Item 22

4 Screw NAS1101-08-8 Item 23

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(12) Subtask 222063-410-001-001 - Install the Items removed for access.

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

(a) Connect and install the EFIS control panels 42FN1 and 42FN2 (panels 412VU and

413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet 01)

removed for access.

(b) Connect and install the Flight Control Unit 303CA (Refer to AMM 22-15-12, Page

Block 401 and Fig. A-FBCAA Sheet 01) removed for access.

**CONF 003

(1) Subtask 222063-831-001-002 - Modify the Wiring in the Left Electronics Rack 80VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 80VU

Manpower Resources

Manhours 7.00

Minimum number of person 1

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 200 TIE

A9000095401695 BUNDLE

NSA935401-03 200 TIE

NSA935401-08 150 TIE

References

Aircraft Maintenance Manual (AMM) 22-18-34, Page Block 401

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 65

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SERVICE BULLETIN

References

Fig. A-FWAAA

Modification of the Wiring in the Left

Electronic Rack 80VU.

Sheet 01

Fig. A-FHAAA

Hook-up Chart of the Modification of the

Wiring in the Left Electronic Rack 80VU.

Sheet 01

(a) Remove the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(b) Install the wires as shown in the wiring diagram Fig. A-FWAAA Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 14 (Refer to Fig. A-FHAAA Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

150 Tie-Cable NSA935401-08

(d) Install the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(2) Subtask 222063-831-002-003 - Modify the Wiring in the Right Electronics Rack

90VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 90VU

Manpower Resources

Manhours 9.00

Minimum number of person 1

Subtask elapsed time 9.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

NSA935401-03 300 TIE

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 66

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA935401-08 300 TIE

References

Aircraft Maintenance Manual (AMM) 31-31-15, Page Block 401

31-53-34, Page Block 401

Fig. A-FHBAB

Hook-up Chart of the Modification of the

Wiring in the Right Electronic Rack

90VU.

Sheet 01

Sheet 02

Fig. A-FWBAB

Modification of the Wiring in the Right

Electronic Rack 90VU.

Sheet 01

Sheet 02

(a) Remove the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

(b) Remove the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

(c) Modify the wires as shown in the wiring diagrams Fig. A-FWBAB Sheet 01and Fig.

A-FWBAB Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHBAB Sheet 01).

(d) If necessary, use the contacts supplied in:

Bundle A9000095401695

(e) Install the wires as shown in the wiring diagram Fig. A-FWBAB Sheet 02, and as

given in the hook-up chart lines:

- 12 thru 23 (Refer to Fig. A-FHBAB Sheet 01) and

- 1 thru 7 (Refer to Fig. A-FHBAB Sheet 02), supplied in:

Bundle A9000095401695

(f) Attach the wires with:

300 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

300 Tie-Cable NSA935401-08

(g) Install the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

(h) Install the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 67

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SERVICE BULLETIN

(3) Subtask 222063-831-004-002 - Modify the Wiring and the Equipment in the

Electronics Rack 500VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 500VU

Manpower Resources

Manhours 6.50

Minimum number of person 1

Subtask elapsed time 6.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

References

Aircraft Maintenance Manual (AMM) 34-44-34, Page Block 401

Fig. A-FHDAA

Hook-up Chart of the Modification of the

Wiring in the Electronic Rack 500VU.

Sheet 01

Fig. A-FWDAA

Modification of the Wiring in the

Electronic Rack 500VU.

Sheet 01

Sheet 02

(a) Remove the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

(b) Modify the wiring in the Electronic Rack 500VU:

1 Modify the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 01 and

Fig. A-FWDAA Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHDAA Sheet 01).

2 If necessary, use contacts supplied in:

Bundle A9000095401695

3 Install the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 02, and

as given in the hook-up chart lines:

- 12 thru 21 (Refer to Fig. A-FHDAA Sheet 01), supplied in:

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

Bundle A9000095401695

4 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(c) Install the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

(4) Subtask 222063-831-005-002 - Modify the Wiring and the Equipment in the

Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

References

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

Fig. A-FWFAA

Modification of the Wiring in the Avionics

Compartment.

Sheet 01

Fig. A-FHFAA

Hook-up Chart of the Modification of the

Wiring in the Avionics Compartment.

Sheet 01

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(a) Modify the wiring in the avionics compartment:

1 Install the wires as shown in the wiring diagram Fig. A-FWFAA Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHFAA Sheet 01), supplied in:

Bundle A9000095401695

2 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(5) Subtask 222063-831-003-003 - Modify the Wiring in the Maintenance Panel 490VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 50 TIE

A9000095401695 BUNDLE

NSA935401-03 50 TIE

NSA935401-08 50 TIE

References

Aircraft Maintenance Manual (AMM) 33-13-00, Page Block 001

Fig. A-FHCAB

Hook-up Chart of the Modification of the

Wiring in the Maintenance Panel 490VU.

Sheet 01

Fig. A-FWCAB

Modification of the Wiring in the

Maintenance Panel 490VU.

Sheet 01

(a) Remove the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 70

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SERVICE BULLETIN

(b) Install the wires as shown in the wiring diagram Fig. A-FWCAB Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHCAB Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

50 Tie-Cable NSA935401-03

50 Tie-Cable NSA935401-05 Item 24

50 Tie-Cable NSA935401-08

(d) Install the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

(6) Subtask 222063-831-006-003 - Modify the Wiring between the Cockpit and the

Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

From 120 Access Door 811, Door 131AZ, Door 132AZ

To 210 Access Door 831, Door 841

Manpower Resources

Manhours 17.00

Minimum number of person 2

Subtask elapsed time 8.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA937901MA2002 2 MODULE

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

NSA935401-03 200 TIE

NSA935401-08 200 TIE

NSA937901E3 2 LABEL

NSA937901E4 1 LABEL

NSA937901E5 1 LABEL

NSA937901S 2 CLAMP

References

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 71

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SERVICE BULLETIN

References

Fig. A-FHEAB

Hook-up Chart of the Modification of the

Wiring between the Avionics

Compartment and the Cockpit.

Sheet 01

Fig. A-FWEAB

Modification of the Wiring between the

Avionics Compartment and the Cockpit.

Sheet 01

Sheet 02

(a) Modify the terminal block 190VT:

1 At the positions 34 and 35, install (Refer to Fig. A-FBAAA Sheet 01):

FIN 190VT34

1 Module NSA937901MA2002 Item 1

with:

1 Label Identification NSA937901E3

1 Label Identification NSA937901E4

FIN 190VT35

1 Module NSA937901MA2002 Item 1

with:

1 Label Identification NSA937901E3

1 Label Identification NSA937901E5

2 If necessary, use:

2 Clamp-End NSA937901S

(b) Install the wires as shown in the wiring diagrams Fig. A-FWEAB Sheet 01 and Fig.

A-FWEAB Sheet 02, and as shown in the hook-up chart lines:

- 1 thru 18 (Refer to Fig. A-FHEAB Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

200 Tie-Cable NSA935401-08

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 72

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SERVICE BULLETIN

(7) Subtask 222063-020-001-001 - Remove the Instrument Panels.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Remove the instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3) Retain

1 Instrument Panel A9252407020300 Item (4) Retain

NOTE: Remove and retain the attachment hardware.

(b) Remove and disconnect the EFIS control panels 42FN1 and 42FN2 (panels 412VU

and 413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet

01) for access.

(c) Remove and disconnect the Flight Control Unit 303CA (Refer to AMM 22-15-12,

Page Block 401 and Fig. A-FBCAA Sheet 01) for access.

(8) Subtask 222063-831-007-003 - Modify the Wiring and the Equipment in the Cockpit.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 73

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SERVICE BULLETIN

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9100095401496 PLACARD

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 ASNA2327-3-4 2 BRACKET

9 NSA935513-07 4 MOUNT

10 NSA935504-01 4 BRACKET

11 NSA5527-03-06 2 SPACER

12 NSA5527-03-08 2 SPACER

13 NAS1801-3-28 2 SCREW

14 NAS1149F0332P 2 WASHER

15 ASNA2051DCJ3215 4 RIVET

16 ASNA2051DCJ2412 8 RIVET

20 EN3646A61210BN 1 CONNECTR

21 ABS0638A12 4 BACKSHLL

24 NSA935401-05 200 TIE

29 EN3646A61210BW 1 CONNECTR

30 EN3646A61210BX 1 CONNECTR

31 EN3646A61210BY 1 CONNECTR

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

References

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

Fig. A-FHGAB

Hook-up Chart of the Modification of the

Wiring in the Cockpit.

Sheet 01

Fig. A-FWGAB

Modification of the Wiring in the Cockpit.

Sheet 01

Fig. A-FBEAA

Modification of the Equipment in the

Cockpit.

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(a) Modify the equipment in the cockpit (Refer to Fig. A-FBEAA):

1 On the LH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800000 Item (7) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

1 Spacer NSA5527-03-06 Item 11

1 Spacer NSA5527-03-08 Item 12

Attach with:

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

2 On the RH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800100 Item (19) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

1 Spacer NSA5527-03-06 Item 11

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

1 Spacer NSA5527-03-08 Item 12

Attach with:

1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

(b) Modify the wiring in the cockpit:

1 Install the wires as shown in the wiring diagram Fig. A-FWGAB Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 10 (Refer to Fig. A-FHGAB Sheet 01), supplied in:

Bundle A9000095401695

2 Attach the wires with:

100 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(c) With the wires, install the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A

(Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02):

FIN 511VC1A

1 Connector-Plug EN3646A61210BN Item 20

FIN 511VC1A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 511VC2A

1 Connector-Plug EN3646A61210BW Item 29

FIN 511VC2A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 512VC1A

1 Connector-Plug EN3646A61210BX Item 30

FIN 512VC1A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 512VC2A

1 Connector-Plug EN3646A61210BY Item 31

FIN 512VC2A1

1 Backshell-Connector ABS0638A12 Item 21

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(d) Together with the wires, install the identification plates 511VC1A, 511VC2A,

512VC1A and 512VC2A, supplied in:

Placard set A9100095401496

(9) Subtask 222063-831-009-002 - Modify the Routing in the Glareshield Panel 13VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 13VU

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9100095401496 PLACARD

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 12 TIE

25 EN6049-007-08-5 10 (M) SLEEVE

28 NSA5527-03-14 4 SPACER

References

Fig. A-FBHAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

Fig. A-FBIAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

(a) Install (Refer to Fig. A-FBHAA):

10 (M) Sleeve-Protective EN6049-007-08-5 Item 25

8 Tie-Cable NSA935401-05 Item 24

Near the rest plates, bond the placards identified 510VU1 and 510VU2 as shown in

Fig. A-FBHAA and supplied in:

Placard set A9100095401496

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(b) Install (Refer to Fig. A-FBIAA):

4 Spacer NSA5527-03-14 Item 28

4 Tie-Cable NSA935401-05 Item 24

(10) Subtask 222063-831-008-002 - Modify the Instrument Panels.

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 ASNA2051DCJ2412 8 RIVET

18 MS21071-08 4 NUT

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL (3) A9252407020200

6 A9251134300100 PANEL (4) A9252407020300

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Cut the LH and RH instrument panel at the dimensions given in Fig. A-FBDAA

Sheet 02):

(b) On the LH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(c) Temporary put in position the nut-plates Item 18.

(d) Drill four holes on the LH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(e) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(f) On the RH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(g) Temporary put in position the nut-plates Item 18.

(h) Drill four holes on the RH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

(i) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(j) Re-identify the modified instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3)

becomes:

1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9252407020300 Item (4)

becomes:

1 Instrument Panel A9251134300100 Item 6

(11) Subtask 222063-420-001-002 - Install the Instrument Panels.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 80

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SERVICE BULLETIN

Material necessary to do the job

Kit 222063A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

17 A9251134000000 2 PLATE

22 NAS1149FN832P 4 WASHER

23 NAS1101-08-8 4 SCREW

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL

6 A9251134300100 PANEL

References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

Fig. A-FBFAA

Installation of the Rest Plates on the

Instrument Panels.

Sheet 01

(a) Install (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9251134300100 Item 6

NOTE: Use the retained attachment hardware.

(b) Connect the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A to the rest

plates Item 17 (Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02).

(c) Install (Refer to Fig. A-FBFAA Sheet 01):

2 Rest Plate A9251134000000 Item 17

4 Washer NAS1149FN832P Item 22

4 Screw NAS1101-08-8 Item 23

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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SERVICE BULLETIN

(12) Subtask 222063-410-001-001 - Install the Items removed for access.

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

(a) Connect and install the EFIS control panels 42FN1 and 42FN2 (panels 412VU and

413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet 01)

removed for access.

(b) Connect and install the Flight Control Unit 303CA (Refer to AMM 22-15-12, Page

Block 401 and Fig. A-FBCAA Sheet 01) removed for access.

**CONF 004

(1) Subtask 222063-831-001-001 - Modify the Wiring in the Left Electronics Rack 80VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 80VU

Manpower Resources

Manhours 7.00

Minimum number of person 1

Subtask elapsed time 7.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 200 TIE

A9000095401695 BUNDLE

NSA935401-03 200 TIE

NSA935401-08 150 TIE

References

Aircraft Maintenance Manual (AMM) 22-18-34, Page Block 401

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 82

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References

Fig. A-FWAAA

Modification of the Wiring in the Left

Electronic Rack 80VU.

Sheet 01

Fig. A-FHAAA

Hook-up Chart of the Modification of the

Wiring in the Left Electronic Rack 80VU.

Sheet 01

(a) Remove the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(b) Install the wires as shown in the wiring diagram Fig. A-FWAAA Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 14 (Refer to Fig. A-FHAAA Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

150 Tie-Cable NSA935401-08

(d) Install the Flight Control Computers (FCCs) 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(2) Subtask 222063-831-002-001 - Modify the Wiring in the Right Electronics Rack

90VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 90VU

Manpower Resources

Manhours 9.00

Minimum number of person 1

Subtask elapsed time 9.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

NSA935401-03 300 TIE

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 83

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA935401-08 300 TIE

References

Aircraft Maintenance Manual (AMM) 31-31-15, Page Block 401

31-53-34, Page Block 401

Fig. A-FWBAA

Modification of the Wiring in the Right

Electronic Rack 90VU.

Sheet 01

Sheet 02

Fig. A-FHBAA

Hook-up Chart of the Modification of the

Wiring in the Right Electronic Rack

90VU.

Sheet 01

Sheet 02

(a) Remove the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

(b) Remove the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

(c) Modify the wires as shown in the wiring diagrams Fig. A-FWBAA Sheet 01 and Fig.

A-FWBAA Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHBAA Sheet 01).

(d) If necessary, use the contacts supplied in:

Bundle A9000095401695

(e) Install the wires as shown in the wiring diagram Fig. A-FWBAA Sheet 02, and as

given in the hook-up chart lines:

- 12 thru 23 (Refer to Fig. A-FHBAA Sheet 01) and

- 1 thru 7 (Refer to Fig. A-FHBAA Sheet 02), supplied in:

Bundle A9000095401695

(f) Attach the wires with:

300 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

300 Tie-Cable NSA935401-08

(g) Install the Digital Flight Data Acquisition Unit (DFDAU) 2TU (Refer to AMM

31-31-15, Page Block 401).

(h) Install the Flight Warning Computers (FWCs) 1WW1 and 1WW2 (Refer to AMM

31-53-34, Page Block 401).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(3) Subtask 222063-831-004-001 - Modify the Wiring and the Equipment in the

Electronics Rack 500VU.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Work location Electrical panel 500VU

Manpower Resources

Manhours 6.50

Minimum number of person 1

Subtask elapsed time 6.50

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 NSA937901MA2204 1 MODULE

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

NSA935401-03 100 TIE

NSA935401-08 100 TIE

NSA937901E9 1 LABEL

NSA937901S 2 CLAMP

References

Aircraft Maintenance Manual (AMM) 34-44-34, Page Block 401

Fig. A-FBBAA

Modification of the Equipment in the

Electronic Rack 500VU.

Sheet 01

Fig. A-FWDAA

Modification of the Wiring in the

Electronic Rack 500VU.

Sheet 01

Sheet 02

Fig. A-FHDAA

Hook-up Chart of the Modification of the

Wiring in the Electronic Rack 500VU.

Sheet 01

(a) Remove the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

(b) Modify the terminal block 1487VT:

1 At the position 9, install (Refer to Fig. A-FBBAA Sheet 01):

FIN 1487VT9

1 Module NSA937901MA2204 Item 2

1 Label Identification NSA937901E9

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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2 If necessary, use:

2 Clamp-End NSA937901S

(c) Modify the wiring in the Electronic Rack 500VU:

1 Modify the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 01 and

Fig. A-FWDAA Sheet 02, and as given in the hook-up chart lines:

- 1 thru 8 (Refer to Fig. A-FHDAA Sheet 01).

2 If necessary, use contacts supplied in:

Bundle A9000095401695

3 Install the wires as shown in the wiring diagram Fig. A-FWDAA Sheet 02, and

as given in the hook-up chart lines:

- 12 thru 21 (Refer to Fig. A-FHDAA Sheet 01), supplied in:

Bundle A9000095401695

4 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(d) Install the TCAS Computer 1SG (Refer to AMM 34-44-34, Page Block 401).

(4) Subtask 222063-831-005-001 - Modify the Wiring and the Equipment in the

Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811, Door 131AZ, Door 132AZ

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 100 TIE

A9000095401695 BUNDLE

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 86

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@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA935401-03 100 TIE

NSA935401-08 100 TIE

References

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

Fig. A-FWFAA

Modification of the Wiring in the Avionics

Compartment.

Sheet 01

Fig. A-FHFAA

Hook-up Chart of the Modification of the

Wiring in the Avionics Compartment.

Sheet 01

(a) Modify the wiring in the avionics compartment:

1 Install the wires as shown in the wiring diagram Fig. A-FWFAA Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHFAA Sheet 01), supplied in:

Bundle A9000095401695

2 Attach the wires with:

100 Tie-Cable NSA935401-03

100 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(5) Subtask 222063-831-003-002 - Modify the Wiring in the Maintenance Panel 490VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 490VU

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills ELECTRICAL

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 87

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@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 50 TIE

A9000095401695 BUNDLE

NSA935401-03 50 TIE

NSA935401-08 50 TIE

References

Aircraft Maintenance Manual (AMM) 33-13-00, Page Block 001

Fig. A-FWCAA

Modification of the Wiring in the

Maintenance Panel 490VU.

Sheet 01

Fig. A-FHCAA

Hook-up Chart of the Modification of the

Wiring in the Maintenance Panel 490VU.

Sheet 01

(a) Remove the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

(b) Install the wires as shown in the wiring diagram Fig. A-FWCAA Sheet 01, and as

given in the hook-up chart lines:

- 1 thru 5 (Refer to Fig. A-FHCAA Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

50 Tie-Cable NSA935401-03

50 Tie-Cable NSA935401-05 Item 24

50 Tie-Cable NSA935401-08

(d) Install the maintenance panel 490VU (Refer to AMM 33-13-00, Page Block 001).

(6) Subtask 222063-831-006-004 - Modify the Wiring between the Cockpit and the

Avionics Compartment.

Manpower Resources

Manhours 17.00

Minimum number of person 1

Subtask elapsed time 17.00

Skills ELECTRICAL

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Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA937901MA2002 2 MODULE

24 NSA935401-05 500 TIE

A9000095401695 BUNDLE

NSA935401-03 200 TIE

NSA935401-08 200 TIE

NSA937901E3 2 LABEL

NSA937901E4 1 LABEL

NSA937901E5 1 LABEL

NSA937901S 2 CLAMP

References

Fig. A-FHEAA

Hook-up Chart of the Modification of the

Wiring between the Avionics

Compartment and the Cockpit.

Sheet 01

Fig. A-FWEAA

Modification of the Wiring between the

Avionics Compartment and the Cockpit.

Sheet 01

Sheet 02

Fig. A-FBAAA

Modification of the Equipment in the

Avionics Compartment.

Sheet 01

(a) Modify the terminal block 190VT:

1 At the positions 34 and 35, install (Refer to Fig. A-FBAAA Sheet 01):

FIN 190VT34

1 Module NSA937901MA2002 Item 1

with:

1 Label Identification NSA937901E3

1 Label Identification NSA937901E4

FIN 190VT35

1 Module NSA937901MA2002 Item 1

with:

1 Label Identification NSA937901E3

1 Label Identification NSA937901E5

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2 If necessary, use:

2 Clamp-End NSA937901S

(b) Install the wires as shown in the wiring diagrams Fig. A-FWEAA Sheet 01 and Fig.

A-FWEAA Sheet 02, and as shown in the hook-up chart lines:

- 1 thru 18 (Refer to Fig. A-FHEAA Sheet 01), supplied in:

Bundle A9000095401695

(c) Attach the wires with:

200 Tie-Cable NSA935401-03

500 Tie-Cable NSA935401-05 Item 24

200 Tie-Cable NSA935401-08

(7) Subtask 222063-020-001-001 - Remove the Instrument Panels.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Remove the instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3) Retain

1 Instrument Panel A9252407020300 Item (4) Retain

NOTE: Remove and retain the attachment hardware.

(b) Remove and disconnect the EFIS control panels 42FN1 and 42FN2 (panels 412VU

and 413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet

01) for access.

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(c) Remove and disconnect the Flight Control Unit 303CA (Refer to AMM 22-15-12,

Page Block 401 and Fig. A-FBCAA Sheet 01) for access.

(8) Subtask 222063-831-007-001 - Modify the Wiring and the Equipment in the Cockpit.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

AIRFRAME

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 ASNA2327-3-4 2 BRACKET

9 NSA935513-07 4 MOUNT

10 NSA935504-01 4 BRACKET

11 NSA5527-03-06 2 SPACER

12 NSA5527-03-08 2 SPACER

13 NAS1801-3-28 2 SCREW

14 NAS1149F0332P 2 WASHER

15 ASNA2051DCJ3215 4 RIVET

16 ASNA2051DCJ2412 8 RIVET

20 EN3646A61210BN 1 CONNECTR

21 ABS0638A12 4 BACKSHLL

24 NSA935401-05 200 TIE

29 EN3646A61210BW 1 CONNECTR

30 EN3646A61210BX 1 CONNECTR

31 EN3646A61210BY 1 CONNECTR

A9000095401695 BUNDLE

A9100095401496 PLACARD

NSA935401-03 100 TIE

NSA935401-08 100 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

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References

Fig. A-FBEAA

Modification of the Equipment in the

Cockpit.

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FWGAA

Modification of the Wiring in the Cockpit.

Sheet 01

Fig. A-FHGAA

Hook-up Chart of the Modification of the

Wiring in the Cockpit.

Sheet 01

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

(a) Modify the equipment in the cockpit (Refer to Fig. A-FBEAA):

1 On the LH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800000 Item (7) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

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g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

1 Spacer NSA5527-03-06 Item 11

1 Spacer NSA5527-03-08 Item 12

Attach with:

1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

2 On the RH side:

a Remove (Refer to Fig. A-FBEAA Sheet 02):

1 Bracket A9252426800100 Item (19) Discard

4 Rivet ASNA2051DCJ2412 Item (16) Discard

b Install (Refer to Fig. A-FBEAA Sheet 03):

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

c Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) as shown on Fig. A-FBEAA Sheet 03.

d Temporary put in position the bracket Item 8.

e Drill one hole to a diameter comprised between 3.25 mm (0.128 in.) and

3.35 mm (0.132 in.) to match the hole of the bracket Item 8.

f Install (Refer to Fig. A-FBEAA Sheet 04):

1 Bracket ASNA2327-3-4 Item 8

Attach with:

2 Rivet ASNA2051DCJ3215 Item 15

NOTE: On the head of the rivets, apply:

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Decorative Paint 16-047 As required

g Drill two holes to a diameter comprised between 5 mm (0.197 in.) and

5.2 mm (0.201 in.) as shown on Fig. A-FBEAA Sheet 04.

h Install (Refer to Fig. A-FBEAA Sheet 04):

2 Mount NSA935513-07 Item 9

i On the bracket Item 8, install (Refer to Fig. A-FBEAA Sheet 04):

2 Bracket NSA935504-01 Item 10

1 Spacer NSA5527-03-06 Item 11

1 Spacer NSA5527-03-08 Item 12

Attach with:

1 Washer NAS1149F0332P Item 14

1 Screw NAS1801-3-28 Item 13

(b) Modify the wiring in the cockpit:

1 Install the wires as shown in the wiring diagram Fig. A-FWGAA Sheet 01, and

as given in the hook-up chart lines:

- 1 thru 10 (Refer to Fig. A-FHGAA Sheet 01), supplied in:

Bundle A9000095401695

2 Attach the wires with:

100 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-05 Item 24

100 Tie-Cable NSA935401-08

(c) With the wires, install the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A

(Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02):

FIN 511VC1A

1 Connector-Plug EN3646A61210BN Item 20

FIN 511VC1A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 511VC2A

1 Connector-Plug EN3646A61210BW Item 29

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FIN 511VC2A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 512VC1A

1 Connector-Plug EN3646A61210BX Item 30

FIN 512VC1A1

1 Backshell-Connector ABS0638A12 Item 21

FIN 512VC2A

1 Connector-Plug EN3646A61210BY Item 31

FIN 512VC2A1

1 Backshell-Connector ABS0638A12 Item 21

(d) Together with the wires, install the identification plates 511VC1A, 511VC2A,

512VC1A and 512VC2A, supplied in:

Placard set A9100095401496

(9) Subtask 222063-831-009-001 - Modify the Routing in the Glareshield Panel 13VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 13VU

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

24 NSA935401-05 12 TIE

25 EN6049-007-08-5 10 (M) SLEEVE

28 NSA5527-03-14 4 SPACER

A9100095401496 PLACARD

References

Fig. A-FBHAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

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References

Fig. A-FBIAA

Modification of the Routing in the

Glareshield Panel.

Sheet 01

Sheet 02

(a) Install (Refer to Fig. A-FBHAA):

10 (M) Sleeve-Protective EN6049-007-08-5 Item 25

8 Tie-Cable NSA935401-05 Item 24

Near the rest plates, bond the placards identified 510VU1 and 510VU2 as shown in

Fig. A-FBHAA and supplied in:

Placard set A9100095401496

(b) Install (Refer to Fig. A-FBIAA):

4 Spacer NSA5527-03-14 Item 28

4 Tie-Cable NSA935401-05 Item 24

(10) Subtask 222063-831-008-001 - Modify the Instrument Panels.

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 ASNA2051DCJ2412 8 RIVET

18 MS21071-08 4 NUT

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL (3) A9252407020200

6 A9251134300100 PANEL (4) A9252407020300

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Decorative Paint 16-047 As required

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

(a) Cut the LH and RH instrument panel at the dimensions given in Fig. A-FBDAA

Sheet 02):

(b) On the LH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(c) Temporary put in position the nut-plates Item 18.

(d) Drill four holes on the LH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

(e) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(f) On the RH instrument panel, drill two holes to a diameter comprised between 4.3

mm (0.169 in.) and 4.4 mm (0.173 in.) as shown on Fig. A-FBDAA Sheet 02.

(g) Temporary put in position the nut-plates Item 18.

(h) Drill four holes on the RH instrument panel to a diameter comprised between 2.46

mm (0.097 in.) and 2.57 mm (0.101 in.) to match the holes of the nut-plates Item

18.

(i) Install (Refer to Fig. A-FBDAA Sheet 02):

2 Nut-Plate MS21071-08 Item 18

Attach with:

4 Rivet ASNA2051DCJ2412 Item 16

NOTE: On the head of the rivets, apply:

Decorative Paint 16-047 As required

(j) Re-identify the modified instrument panels (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9252407020200 Item (3)

becomes:

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1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9252407020300 Item (4)

becomes:

1 Instrument Panel A9251134300100 Item 6

(11) Subtask 222063-420-001-001 - Install the Instrument Panels.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 222063A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

17 A9251134000000 2 PLATE

22 NAS1149FN832P 4 WASHER

23 NAS1101-08-8 4 SCREW

Reidentified part set REIDA01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

5 A9251134300001 PANEL

6 A9251134300100 PANEL

References

Fig. A-FBDAA

Cutting of the Instrument Panels.

Sheet 01

Sheet 02

Fig. A-FBGAA

Installation of the connectors 511VC1A,

511VC2A, 512VC1A and 512VC2A.

Sheet 01

Sheet 02

Fig. A-FBFAA

Installation of the Rest Plates on the

Instrument Panels.

Sheet 01

(a) Install (Refer to Fig. A-FBDAA Sheet 01):

1 Instrument Panel A9251134300001 Item 5

1 Instrument Panel A9251134300100 Item 6

NOTE: Use the retained attachment hardware.

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(b) Connect the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A to the rest

plates Item 17 (Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02).

(c) Install (Refer to Fig. A-FBFAA Sheet 01):

2 Rest Plate A9251134000000 Item 17

4 Washer NAS1149FN832P Item 22

4 Screw NAS1101-08-8 Item 23

(12) Subtask 222063-410-001-001 - Install the Items removed for access.

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 22-15-12, Page Block 401

34-73-11, Page Block 401

Fig. A-FBCAA

Location of the Equipment on the

Glareshield Panel removed for access.

Sheet 01

(a) Connect and install the EFIS control panels 42FN1 and 42FN2 (panels 412VU and

413VU) (Refer to AMM 34-73-11, Page Block 401 and Fig. A-FBCAA Sheet 01)

removed for access.

(b) Connect and install the Flight Control Unit 303CA (Refer to AMM 22-15-12, Page

Block 401 and Fig. A-FBCAA Sheet 01) removed for access.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 222063-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

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References

Aircraft Maintenance Manual (AMM) 21-21-00, Page Block 501

21-31-00, Page Block 501

22-10-00, Page Block 501

22-15-12, Page Block 401

22-27-00, Page Block 501

22-40-00, Page Block 501

22-40-00, Page Block 501

24-31-11, Page Block 401

28-21-00, Page Block 501

31-10-00, Page Block 201

31-31-15, Page Block 401

31-51-00, Page Block 501

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

34-44-34, Page Block 401

34-48-00, Page Block 501

34-52-00, Page Block 501

34-73-11, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Job Set-Up:

1 Battery re-connection:

a For Job Set-up, refer to the installation of the Batteries (Refer to AMM

24-31-11, Page Block 401).

b Remove the blanking cap from the electrical connectors

c Make sure that the electrical connectors are clean and in correct

condition

d Connect the connector on the battery

e Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Restore the systems and the aircraft to normal operating condition.

(b) Procedure

1 Preliminary Tests:

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501).

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a On each connector which was disconnected:

<1> Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested

by this ESPM procedure is given hereafter.

b Do the operational test of the Annunciator Light Test (Refer to AMM

33-14-00, Page Block 501).

c Do the operational test of the General Illumination (Refer to AMM

33-12-00, Page Block 501).

d Do the operational test of the Instrument and Panel Integral Lighting

(Refer to AMM 33-13-00, Page Block 501).

e Make sure that the ventilation system operates correctly (Refer to AMM

21-21-00, Page Block 501).

f Do the Automatic Flight System (AFS) Test (Refer to AMM 22-40-00,

Page Block 501 (para 1.A)).

g Do the operational test of Electronic Centralized Aircraft Monitoring

(ECAM)/ Electronic Flight Instrument System (EFIS) Display Test (Refer

to AMM 31-51-00, Page Block 501).

h Do the operational test of the Flight Warning Computer (FWC)1 and

FWC2 (Refer to AMM 31-51-00, Page Block 501).

2 Tests of the equipment:

a For 301CA1 and 301CA2:

<1> Do the detailed visual inspection of the autotrim function (Refer to

AMM 22-27-00, Page Block 501 (para 1.H)).

<2> Do the autopilot operational test (Refer to AMM 22-10-00, Page

Block 501 (para 1.D Check of Pitch Trim Autotrim circuits)).

b For 1WW1 and 1WW2:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501 (para 1.A. Flight Warning Computer Test)) and an

INPUTS test (AMM 31-51-00, Page Block 501 (para 1.H)).

c For 42FN1 and 42FN2:

<1> Do the test procedure as specified after the installation of the EFIS

control panels (42FN1, 42FN2), (Refer to AMM 34-73-11, Page

Block 401).

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d For 303CA:

<1> Do the test procedure as specified after the installation of the flight

control unit (303CA), (Refer to AMM 22-15-12, Page Block 401).

e For panels 412VU and 413VU:

<1> Do the test program after removal/installation of the Panels 412VU

and 413VU (Refer to AMM 31-10-00, Page Block 201).

f For 2TU:

<1> Do the test procedure as specified after the installation of the

DIGITAL FLIGHT DATA ACQUISITION UNIT 2TU (Refer to AMM

31-31-15, Page Block 401).

g For 1SG:

<1> Do the test procedure as specified after the installation of the TCAS

COMPUTER 1SG (Refer to AMM 34-44-34, Page Block 401).

3 Tests of the connectors:

a For 1653VC:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501, para. 1. C, loudspeaker/WARNING SYS NORM

CANCEL test).

b For 1654VC:

<1> Do the operational test of cabin pressure control and monitoring

(test OK) (Refer to AMM 21-31-00, Page Block 501).

c For 2224VC:

<1> Do the operational test of ATC transponder (Refer to AMM

34-52-00, Page Block 501).

d For 2283VC:

<1> Do the functional test of the fuel pump autofeed system (Refer to

AMM 28-21-00, Page Block 501).

e For 2321VC:

<1> Do the operational test of ground proximity warning computer (Refer

to AMM 34-48-00, Page Block 501).

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**CONF 002

(1) Subtask 222063-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-21-00, Page Block 501

21-31-00, Page Block 501

22-10-00, Page Block 501

22-15-12, Page Block 401

22-27-00, Page Block 501

22-40-00, Page Block 501

22-40-00, Page Block 501

24-31-11, Page Block 401

28-21-00, Page Block 501

31-10-00, Page Block 201

31-31-15, Page Block 401

31-51-00, Page Block 501

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

34-44-34, Page Block 401

34-48-00, Page Block 501

34-52-00, Page Block 501

34-73-11, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Job Set-Up:

1 Battery re-connection:

a For Job Set-up, refer to the installation of the Batteries (Refer to AMM

24-31-11, Page Block 401).

b Remove the blanking cap from the electrical connectors

c Make sure that the electrical connectors are clean and in correct

condition

d Connect the connector on the battery

e Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Restore the systems and the aircraft to normal operating condition.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

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(b) Procedure

1 Preliminary Tests:

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501).

a On each connector which was disconnected:

<1> Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested

by this ESPM procedure is given hereafter.

b Do the operational test of the Annunciator Light Test (Refer to AMM

33-14-00, Page Block 501).

c Do the operational test of the General Illumination (Refer to AMM

33-12-00, Page Block 501).

d Do the operational test of the Instrument and Panel Integral Lighting

(Refer to AMM 33-13-00, Page Block 501).

e Make sure that the ventilation system operates correctly (Refer to AMM

21-21-00, Page Block 501).

f Do the Automatic Flight System (AFS) Test (Refer to AMM 22-40-00,

Page Block 501 (para 1.A)).

g Do the operational test of Electronic Centralized Aircraft Monitoring

(ECAM)/ Electronic Flight Instrument System (EFIS) Display Test (Refer

to AMM 31-51-00, Page Block 501).

h Do the operational test of the Flight Warning Computer (FWC)1 and

FWC2 (Refer to AMM 31-51-00, Page Block 501).

2 Tests of the equipment:

a For 301CA1 and 301CA2:

<1> Do the detailed visual inspection of the autotrim function (Refer to

AMM 22-27-00, Page Block 501 (para 1.H)).

<2> Do the autopilot operational test (Refer to AMM 22-10-00, Page

Block 501 (para 1.D Check of Pitch Trim Autotrim circuits)).

b For 1WW1 and 1WW2:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501 (para 1.A. Flight Warning Computer Test)) and an

INPUTS test (AMM 31-51-00, Page Block 501 (para 1.H)).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 104

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SERVICE BULLETIN

c For 42FN1 and 42FN2:

<1> Do the test procedure as specified after the installation of the EFIS

control panels (42FN1, 42FN2), (Refer to AMM 34-73-11, Page

Block 401).

d For 303CA:

<1> Do the test procedure as specified after the installation of the flight

control unit (303CA), (Refer to AMM 22-15-12, Page Block 401).

e For panels 412VU and 413VU:

<1> Do the test program after removal/installation of the Panels 412VU

and 413VU (Refer to AMM 31-10-00, Page Block 201).

f For 2TU:

<1> Do the test procedure as specified after the installation of the

DIGITAL FLIGHT DATA ACQUISITION UNIT 2TU (Refer to AMM

31-31-15, Page Block 401).

g For 1SG:

<1> Do the test procedure as specified after the installation of the TCAS

COMPUTER 1SG (Refer to AMM 34-44-34, Page Block 401).

3 Tests of the connectors:

a For 1653VC:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501, para. 1. C, loudspeaker/WARNING SYS NORM

CANCEL test).

b For 1654VC:

<1> Do the operational test of cabin pressure control and monitoring

(test OK) (Refer to AMM 21-31-00, Page Block 501).

c For 2224VC:

<1> Do the operational test of ATC transponder (Refer to AMM

34-52-00, Page Block 501).

d For 2283VC:

<1> Do the functional test of the fuel pump autofeed system (Refer to

AMM 28-21-00, Page Block 501).

e For 2321VC:

<1> Do the operational test of ground proximity warning computer (Refer

to AMM 34-48-00, Page Block 501).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 105

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SERVICE BULLETIN

**CONF 003

(1) Subtask 222063-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-21-00, Page Block 501

21-31-00, Page Block 501

22-10-00, Page Block 501

22-15-12, Page Block 401

22-27-00, Page Block 501

22-40-00, Page Block 501

22-40-00, Page Block 501

24-31-11, Page Block 401

28-21-00, Page Block 501

31-10-00, Page Block 201

31-31-15, Page Block 401

31-51-00, Page Block 501

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

34-44-34, Page Block 401

34-48-00, Page Block 501

34-52-00, Page Block 501

34-73-11, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Job Set-Up:

1 Battery re-connection:

a For Job Set-up, refer to the installation of the Batteries (Refer to AMM

24-31-11, Page Block 401).

b Remove the blanking cap from the electrical connectors

c Make sure that the electrical connectors are clean and in correct

condition

d Connect the connector on the battery

e Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Restore the systems and the aircraft to normal operating condition.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 106

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SERVICE BULLETIN

(b) Procedure

1 Preliminary Tests:

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501).

a On each connector which was disconnected:

<1> Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested

by this ESPM procedure is given hereafter.

b Do the operational test of the Annunciator Light Test (Refer to AMM

33-14-00, Page Block 501).

c Do the operational test of the General Illumination (Refer to AMM

33-12-00, Page Block 501).

d Do the operational test of the Instrument and Panel Integral Lighting

(Refer to AMM 33-13-00, Page Block 501).

e Make sure that the ventilation system operates correctly (Refer to AMM

21-21-00, Page Block 501).

f Do the Automatic Flight System (AFS) Test (Refer to AMM 22-40-00,

Page Block 501 (para 1.A)).

g Do the operational test of Electronic Centralized Aircraft Monitoring

(ECAM)/ Electronic Flight Instrument System (EFIS) Display Test (Refer

to AMM 31-51-00, Page Block 501).

h Do the operational test of the Flight Warning Computer (FWC)1 and

FWC2 (Refer to AMM 31-51-00, Page Block 501).

2 Tests of the equipment:

a For 301CA1 and 301CA2:

<1> Do the detailed visual inspection of the autotrim function (Refer to

AMM 22-27-00, Page Block 501 (para 1.H)).

<2> Do the autopilot operational test (Refer to AMM 22-10-00, Page

Block 501 (para 1.D Check of Pitch Trim Autotrim circuits)).

b For 1WW1 and 1WW2:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501 (para 1.A. Flight Warning Computer Test)) and an

INPUTS test (AMM 31-51-00, Page Block 501 (para 1.H)).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 107

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c For 42FN1 and 42FN2:

<1> Do the test procedure as specified after the installation of the EFIS

control panels (42FN1, 42FN2), (Refer to AMM 34-73-11, Page

Block 401).

d For 303CA:

<1> Do the test procedure as specified after the installation of the flight

control unit (303CA), (Refer to AMM 22-15-12, Page Block 401).

e For panels 412VU and 413VU:

<1> Do the test program after removal/installation of the Panels 412VU

and 413VU (Refer to AMM 31-10-00, Page Block 201).

f For 2TU:

<1> Do the test procedure as specified after the installation of the

DIGITAL FLIGHT DATA ACQUISITION UNIT 2TU (Refer to AMM

31-31-15, Page Block 401).

g For 1SG:

<1> Do the test procedure as specified after the installation of the TCAS

COMPUTER 1SG (Refer to AMM 34-44-34, Page Block 401).

3 Tests of the connectors:

a For 1653VC:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501, para. 1. C, loudspeaker/WARNING SYS NORM

CANCEL test).

b For 1654VC:

<1> Do the operational test of cabin pressure control and monitoring

(test OK) (Refer to AMM 21-31-00, Page Block 501).

c For 2224VC:

<1> Do the operational test of ATC transponder (Refer to AMM

34-52-00, Page Block 501).

d For 2283VC:

<1> Do the functional test of the fuel pump autofeed system (Refer to

AMM 28-21-00, Page Block 501).

e For 2321VC:

<1> Do the operational test of ground proximity warning computer (Refer

to AMM 34-48-00, Page Block 501).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 108

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SERVICE BULLETIN

**CONF 004

(1) Subtask 222063-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-21-00, Page Block 501

21-31-00, Page Block 501

22-10-00, Page Block 501

22-15-12, Page Block 401

22-27-00, Page Block 501

22-40-00, Page Block 501

22-40-00, Page Block 501

24-31-11, Page Block 401

28-21-00, Page Block 501

31-10-00, Page Block 201

31-31-15, Page Block 401

31-51-00, Page Block 501

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

34-44-34, Page Block 401

34-48-00, Page Block 501

34-52-00, Page Block 501

34-73-11, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Job Set-Up:

1 Battery re-connection:

a For Job Set-up, refer to the installation of the Batteries (Refer to AMM

24-31-11, Page Block 401).

b Remove the blanking cap from the electrical connectors

c Make sure that the electrical connectors are clean and in correct

condition

d Connect the connector on the battery

e Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Restore the systems and the aircraft to normal operating condition.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 109

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SERVICE BULLETIN

(b) Procedure

1 Preliminary Tests:

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501).

a On each connector which was disconnected:

<1> Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested

by this ESPM procedure is given hereafter.

b Do the operational test of the Annunciator Light Test (Refer to AMM

33-14-00, Page Block 501).

c Do the operational test of the General Illumination (Refer to AMM

33-12-00, Page Block 501).

d Do the operational test of the Instrument and Panel Integral Lighting

(Refer to AMM 33-13-00, Page Block 501).

e Make sure that the ventilation system operates correctly (Refer to AMM

21-21-00, Page Block 501).

f Do the Automatic Flight System (AFS) Test (Refer to AMM 22-40-00,

Page Block 501 (para 1.A)).

g Do the operational test of Electronic Centralized Aircraft Monitoring

(ECAM)/ Electronic Flight Instrument System (EFIS) Display Test (Refer

to AMM 31-51-00, Page Block 501).

h Do the operational test of the Flight Warning Computer (FWC)1 and

FWC2 (Refer to AMM 31-51-00, Page Block 501).

2 Tests of the equipment:

a For 301CA1 and 301CA2:

<1> Do the detailed visual inspection of the autotrim function (Refer to

AMM 22-27-00, Page Block 501 (para 1.H)).

<2> Do the autopilot operational test (Refer to AMM 22-10-00, Page

Block 501 (para 1.D Check of Pitch Trim Autotrim circuits)).

b For 1WW1 and 1WW2:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501 (para 1.A. Flight Warning Computer Test)) and an

INPUTS test (AMM 31-51-00, Page Block 501 (para 1.H)).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 110

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c For 42FN1 and 42FN2:

<1> Do the test procedure as specified after the installation of the EFIS

control panels (42FN1, 42FN2), (Refer to AMM 34-73-11, Page

Block 401).

d For 303CA:

<1> Do the test procedure as specified after the installation of the flight

control unit (303CA), (Refer to AMM 22-15-12, Page Block 401).

e For panels 412VU and 413VU:

<1> Do the test program after removal/installation of the Panels 412VU

and 413VU (Refer to AMM 31-10-00, Page Block 201).

f For 2TU:

<1> Do the test procedure as specified after the installation of the

DIGITAL FLIGHT DATA ACQUISITION UNIT 2TU (Refer to AMM

31-31-15, Page Block 401).

g For 1SG:

<1> Do the test procedure as specified after the installation of the TCAS

COMPUTER 1SG (Refer to AMM 34-44-34, Page Block 401).

3 Tests of the connectors:

a For 1653VC:

<1> Do the operational test of ECAM system (Refer to AMM 31-51-00,

Page Block 501, para. 1. C, loudspeaker/WARNING SYS NORM

CANCEL test).

b For 1654VC:

<1> Do the operational test of cabin pressure control and monitoring

(test OK) (Refer to AMM 21-31-00, Page Block 501).

c For 2224VC:

<1> Do the operational test of ATC transponder (Refer to AMM

34-52-00, Page Block 501).

d For 2283VC:

<1> Do the functional test of the fuel pump autofeed system (Refer to

AMM 28-21-00, Page Block 501).

e For 2321VC:

<1> Do the operational test of ground proximity warning computer (Refer

to AMM 34-48-00, Page Block 501).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 111

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SERVICE BULLETIN

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 222063-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001).

(c) Close the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(d) Close the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(e) Remove the access platforms.

(f) Restore the system and the aircraft to the normal operating condition.

**CONF 002

(1) Subtask 222063-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001).

(c) Close the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 112

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SERVICE BULLETIN

(d) Close the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(e) Remove the access platforms.

(f) Restore the system and the aircraft to the normal operating condition.

**CONF 003

(1) Subtask 222063-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001).

(c) Close the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(d) Close the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(e) Remove the access platforms.

(f) Restore the system and the aircraft to the normal operating condition.

**CONF 004

(1) Subtask 222063-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

52-10-00, Page Block 001

52-30-00, Page Block 001

52-52-00, Page Block 001

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the door 131AZ or 132AZ (Refer to AMM 52-52-00, Page Block 001).

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 113

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SERVICE BULLETIN

(c) Close the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(d) Close the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(e) Remove the access platforms.

(f) Restore the system and the aircraft to the normal operating condition.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 114

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@A310

SERVICE BULLETIN

**CONF ALL

B_SB_222063_5_BAAA_01_00

FR1

FR20

B C

A

1

C

B

190VT

190VT34 190VT35

A

Figure A-FBAAA - Sheet 01

Modification of the Equipment in the Avionics Compartment.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 115

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@A310

SERVICE BULLETIN

**CONF 002, 004

1487VT

1487VT9

B

FR19

FR18

FR15A

FR20

2

C

Z120

A

B

A

C

B_SB_222063_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Modification of the Equipment in the Electronic Rack 500VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 116

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SERVICE BULLETIN

**CONF ALL

B_SB_222063_5_BCAA_01_00

A

413VU 13VU

303CA

412VU

510VU

A

Figure A-FBCAA - Sheet 01

Location of the Equipment on the Glareshield Panel removed for access.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 117

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@A310

SERVICE BULLETIN

**CONF ALL

B_SB_222063_5_BDAA_01_00

A

B

B

13VU

A

6

(4)

5

(3)

Figure A-FBDAA - Sheet 01

Cutting of the Instrument Panels.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 118

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@A310

SERVICE BULLETIN

**CONF ALL

96 mm (3.785 in)

89 mm (3.509 in)

5.5 mm (0.217 in)

57°

12.3 mm (0.485 in)

9 mm (0.355 in) 78 mm (3.075 in)

36 mm (1.419 in)

10 mm (0.394 in)8 mm (0.315 in)

28 mm (1.104 in)

LH SIDE SHOWN

RH SIDE SYMETRICAL

01

N HEAD ON VISIBLE SIDE

FASTENERS NOT AFFECTED

APPLY MAT. NO 16−047

B

NOTE:

R4 (x2)

R2.1 (x6)

18

18

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

16 RIVET 2.46 mm

(0.097 in)

2.57 mm

(0.101 in)

4.4 mm

(0.173 in)

4.3 mm

(0.169 in)

N

ASNA2051DCJ2412 01

B_SB_222063_5_BDAA_02_01

Figure A-FBDAA - Sheet 02

Cutting of the Instrument Panels.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 119

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SERVICE BULLETIN

**CONF ALL

B_SB_222063_5_BEAA_01_00

A

13VU

A

B C

Figure A-FBEAA - Sheet 01

Modification of the Equipment in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 120

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SERVICE BULLETIN

**CONF ALL

LH SIDE SHOWN

RH SIDE SYMETRICAL

Y 390

(7)

B

BEFORE

B_SB_222063_5_BEAA_02_01

(19)

LH

RH

Figure A-FBEAA - Sheet 02

Modification of the Equipment in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 121

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@A310

SERVICE BULLETIN

**CONF ALL

B_SB_222063_5_BEAA_03_00

105.4 mm (4.149 in)

169.4 mm (6.669 in)

LH SIDE SHOWN

RH SIDE SYMETRICAL

Y 390

30°

8

B B

C

A

A

9

AFTER

Figure A-FBEAA - Sheet 03

Modification of the Equipment in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 122

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SERVICE BULLETIN

**CONF ALL 69 mm (2.716 in)

15 mm (0.591 in)

9

N HEAD ON VISIBLE SIDE

LH SIDE SHOWN

RH SIDE SYMETRICAL

01 APPLY MAT. NO 16−047

NOTE: 

8

16 mm (0.629 in) 15 mm (0.591 in)

13

14

11

12

10

A A

B B

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

RIVET 2.46 mm

(0.097 in)

2.57 mm

(0.101 in)

3.35 mm

(0.132 in)

3.25 mm

(0.128 in)

N

ASNA2051DCJ2412 01

01

N

5 mm

(0.197 in)

5.2 mm

(0.201 in)

ASNA2051DCJ3215 RIVET

ITEM

15

(16) 16

OLD NEW

B_SB_222063_5_BEAA_04_02

Figure A-FBEAA - Sheet 04

Modification of the Equipment in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 123

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SERVICE BULLETIN

**CONF ALL

A

13VU

A

B_SB_222063_5_BHAA_01_00

B

Figure A-FBHAA - Sheet 01

Modification of the Routing in the Glareshield Panel.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 124

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SERVICE BULLETIN

**CONF ALL

24

LH SIDE SHOWN

RH SIDE SYMMETRICAL

24

25

NOTE:

01 PROTECT THE TWO HARNESSES USING SLEEVE ITEM

FROM THE BACK OF THE CONNECTORS UNTIL 20 mm (0.787 in)

AFTER THE FIRST ATTACHMENT POINT ON THE EXISTING RAMP

01

C

B

C

1M

2M

(510VU2)

510VU1

25

B_SB_222063_5_BHAA_02_01

Figure A-FBHAA - Sheet 02

Modification of the Routing in the Glareshield Panel.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 125

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SERVICE BULLETIN

**CONF ALL

A

13VU

A

B_SB_222063_5_BIAA_01_00

B

Figure A-FBIAA - Sheet 01

Modification of the Routing in the Glareshield Panel.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 126

5

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@A310

SERVICE BULLETIN

**CONF ALL

B_SB_222063_5_BIAA_02_00

FR3

FR2

FR3

LH SIDE SHOWN

RH SIDE SYMMETRICAL

LH SIDE SHOWN

RH SIDE SYMMETRICAL

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

B

B

24

28

24

28

1M

2M

B

A A

B B

Figure A-FBIAA - Sheet 02

Modification of the Routing in the Glareshield Panel.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 127

5

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@A310

SERVICE BULLETIN

**CONF ALL

A

13VU

A

B_SB_222063_5_BGAA_01_00

B

B

Figure A-FBGAA - Sheet 01

Installation of the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 128

5

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@A310

SERVICE BULLETIN

**CONF ALL

17

29

21

20

21

B

512VC1A

511VC1A (LH)

(RH)

511VC2A (LH)

512VC2A (RH)

30

31

B_SB_222063_5_BGAA_02_02

Figure A-FBGAA - Sheet 02

Installation of the connectors 511VC1A, 511VC2A, 512VC1A and 512VC2A.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 129

5

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@A310

SERVICE BULLETIN

**CONF ALL

AFTER

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A A

17

A

22

23 (2 POS)

NOTE:

01 APPLY MAT No. 16−047

01

B_SB_222063_5_BFAA_01_02

Figure A-FBFAA - Sheet 01

Installation of the Rest Plates on the Instrument Panels.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 130

5

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@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FWAAA - Sheet 01

Modification of the Wiring in the Left Electronic Rack 80VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 131

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 121 123VT 73B EN3155−016M2018 2212−0350 W1M CF18 2900 116 121 2297VC W.S. NSA936604CA0931 (a) A

 2 121 123VT W.S. NSA936604CA0931 2212−0351 W1M CF18 1500 60 121 301CA1−AC W.S. NSA936604CA0931 (a) A

 3 121 123VT 73G EN3155−016M2018 2212−0352 W1M CF24 3500 140 121 2321VC E EN3155−018M2018 (a) A

 4 121 123VT 52B EN3155−016M2222 2212−0353 W1A CF24 4500 180 121 2293VC C EN3155−018M2018 (a) A

 5 121 123VT 52A EN3155−016M2222 2212−0355 W1A CF24 1500 60 121 301CA1−AB 12J E0170FA2200 (a) A

 6 121 123VT 52F EN3155−016M2222 2212−0356 W1A CF24 1500 60 121 301CA1−AB 12K E0170FA2200 (a) A

 7 121 124VT 22B EN3155−016M2018 2212−0365 X2M CF18 4000 160 121 2616VC W.S. NSA936604CA0931 (a) A

 8 121 124VT W.S. NSA936604CA0931 2212−0366 X2M CF18 2000 80 121 301CA2−AC W.S. NSA936604CA0931 (a) A

 9 121 124VT 22G EN3155−016M2018 2212−0367 X2M CF24 2600 104 121 2283VC <C EN3155−018M2018 (a) A

10 121 124VT 23D EN3155−016M2018 2212−0368 X2A CF24 4000 160 121 2306VC G EN3155−018M2018 (a) A

11 121 124VT 23C EN3155−016M2018 2212−0370 X2A CF24 2000 80 121 301CA2−AB 12J E0170FA2200 (a) A

12 121 124VT 23E EN3155−016M2018 2212−0371 X2A CF24 2000 80 121 301CA2−AB 12K E0170FA2200 (a) A

13 121 301CA1−AB 11A E0170FA2200 2212−0354 W1A CF24 2500 100 121 2293VC D EN3155−018M2018 (a) A

14 121 301CA2−AB 11A E0170FA2200 2212−0369 X2A CF24 2700 108 121 2306VC H EN3155−018M2018 (a) A

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695

 A = ADDED WIRE

 W.S. = WIRE STOWED

Figure A-FHAAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Left Electronic Rack 80VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 132

5

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@A310

SERVICE BULLETIN

**CONF 004

Figure A-FWBAA - Sheet 01

Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 133

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 004

Figure A-FWBAA - Sheet 02

Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 134

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003

Figure A-FWBAB - Sheet 01

Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 135

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003

Figure A-FWBAB - Sheet 02

Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 136

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 004

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 2430VC SH 3132G7714 W1R TK24 122 2TU−AD SH M1O

 2 122 2430VC K 3132−1066 B W1R TK24 122 2TU−AD 10G M1O

 3 122 2430VC J 3132−1067 R W1R TK24 122 2TU−AD 10H M1O

 4 122 1411VT SH E0718−02−30 3132G7714 W1R TK24 122 2TU−AD SH E0718−02−30 M1N

 5 122 1411VT 7K EN3155−016M2222 3132−1066 B W1R TK24 122 2TU−AD 10G M1N

 6 122 1411VT 7L EN3155−016M2222 3132−1067 R W1R TK24 122 2TU−AD 10H M1N

 7 122 2430VC L 3132−1068 W1R CF24 122 3132G7714 W.F. M1O

 8 122 1411VT 7P EN3155−016M2222 3132−1068 W1R CF24 122 3132G7714 W.F. M1N

 9

10

11

12 92VU 1WW1−AA W.S. NSA936604CA0931 3153−3189 W1M CF24 3200 128 122 81VT 52C EN3155−016M2018 (a) A

13 93VU 1WW2−AA W.S. NSA936604CA0931 3153−3190 W1M CF24 3500 140 122 82VT 29B EN3155−018M2018 (a) A

14 122 1410VT 17B EN3155−016M2222 2212−0349 W1M CF24 4000 160 122 2366VC C EN3155−018M2018 (a) A

15 122 1410VT 17A EN3155−016M2222 2212−0364 W2M CF24 3500 140 122 2389VC 4 EN3155−008M2222 (a) A

16 122 1410VT 17C EN3155−016M2222 3153−3184 W1M CF24 4000 160 122 1WW2−AA 12F E0170FA2200 (a) A

17 122 1410VT 17E EN3155−016M2222 3153−3185 W1M CF24 4000 160 122 1WW1−AA 12F E0170FA2200 (a) A

18 122 1WW1−AA SH E0718−02−30 3153G7664 W1R TK24 7000 280 122 1411VT SH E0718−02−30 (a) A

19 122 1WW1−AA 2G E0170FA2200 3153−3186 B W1R TK24 7000 280 122 1411VT 7C EN3155−016M2222 (a) A

20 122 1WW1−AA 2H E0170FA2200 3153−3187 R W1R TK24 7000 280 122 1411VT 7D EN3155−016M2222 (a) A

21 122 1WW2−AA SH E0718−02−30 3153G7665 W2R TK24 6300 252 122 2436VC SH E0718−02−30 (a) A

22 122 1WW2−AA 2G E0170FA2200 3153−3191 B W2R TK24 6300 252 122 2436VC A EN3155−018M2018 (a) A

23 122 1WW2−AA 2H E0170FA2200 3153−3192 R W2R TK24 6300 252 122 2436VC B EN3155−018M2018 (a) A

24

25

 (a) = BUNDLE A9000095401695 M1N = NEW HOOK−UP ON END 1 W.S. = WIRE STOWED

 A = ADDED WIRE SH = SHIELD

 M1O = OLD HOOK−UP ON END 1 W.F. = WIRE FERRULE

Figure A-FHBAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 137

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 004

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 1411VT SH E0718−02−30 3132G7990 W1R TK24 3100 124 122 2430VC SH E0718−02−30 (a) A

 2 122 1411VT 7T EN3155−016M2222 3132−1619 B W1R TK24 3100 124 122 2430VC K EN3155−018M2018 (a) A

 3 122 1411VT 7U EN3155−016M2222 3132−1620 R W1R TK24 3100 124 122 2430VC J EN3155−018M2018 (a) A

 4 122 3132G7990 W.F. E0160−1−0H 3132−1621 W1R CF24 500 20 122 1411VT 7Y EN3155−016M2222 (a) A

 5 122 3132G7990 W.F. E0160−1−0H 3132−1622 W1R CF24 500 20 122 2430VC L EN3155−018M2018 (a) A

 6 122 3153G7664 W.F. E0160−1−0H 3153−3188 W1R CF24 500 20 122 1411VT 7G EN3155−016M2222 (a) A

 7 122 3153G7665 W.F. E0160−1−0H 3153−3193 W2R CF24 500 20 122 2436VC C EN3155−018M2018 (a) A

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695 W.F. = WIRE FERRULE

 A = ADDED WIRE

 SH = SHIELD

Figure A-FHBAA - Sheet 02

Hook-up Chart of the Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 138

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 2430VC SH 3132G7714 W1R TK24 122 2TU−AD SH M1O

 2 122 2430VC K 3132−1066 B W1R TK24 122 2TU−AD 10G M1O

 3 122 2430VC J 3132−1067 R W1R TK24 122 2TU−AD 10H M1O

 4 122 1411VT SH E0718−02−30 3132G7714 W1R TK24 122 2TU−AD SH E0718−02−30 M1N

 5 122 1411VT 7K EN3155−016M2222 3132−1066 B W1R TK24 122 2TU−AD 10G M1N

 6 122 1411VT 7L EN3155−016M2222 3132−1067 R W1R TK24 122 2TU−AD 10H M1N

 7 122 2430VC L 3132−1068 W1R CF24 122 3132G7714 W.F. M1O

 8 122 1411VT 7P EN3155−016M2222 3132−1068 W1R CF24 122 3132G7714 W.F. M1N

 9

10

11

12 92VU 1WW1−AA W.S. NSA936604CA0931 3153−3189 W1M CF24 3200 128 122 81VT 52C EN3155−016M2018 (a) A

13 93VU 1WW2−AA W.S. NSA936604CA0931 3153−3190 W1M CF24 3500 140 122 82VT 29B EN3155−018M2018 (a) A

14 122 1410VT 17B EN3155−016M2222 2212−0349 W1M CF24 4500 180 122 2366VC B EN3155−018M2018 (a) A

15 122 1410VT 17A EN3155−016M2222 2212−0364 W2M CF24 3500 140 122 2389VC 4 EN3155−008M2222 (a) A

16 122 1410VT 17C EN3155−016M2222 3153−3184 W1M CF24 4000 160 122 1WW2−AA 12F E0170FA2200 (a) A

17 122 1410VT 17E EN3155−016M2222 3153−3185 W1M CF24 4000 160 122 1WW1−AA 12F E0170FA2200 (a) A

18 122 1WW1−AA SH E0718−02−30 3153G7664 W1R TK24 7000 280 122 1411VT SH E0718−02−30 (a) A

19 122 1WW1−AA 2G E0170FA2200 3153−3186 B W1R TK24 7000 280 122 1411VT 7C EN3155−016M2222 (a) A

20 122 1WW1−AA 2H E0170FA2200 3153−3187 R W1R TK24 7000 280 122 1411VT 7D EN3155−016M2222 (a) A

21 122 1WW2−AA SH E0718−02−30 3153G7665 W2R TK24 6300 252 122 2436VC SH E0718−02−30 (a) A

22 122 1WW2−AA 2G E0170FA2200 3153−3191 B W2R TK24 6300 252 122 2436VC A EN3155−018M2018 (a) A

23 122 1WW2−AA 2H E0170FA2200 3153−3192 R W2R TK24 6300 252 122 2436VC B EN3155−018M2018 (a) A

24

25

 (a) = BUNDLE A9000095401695 M1N = NEW HOOK−UP ON END 1 W.S. = WIRE STOWED

 A = ADDED WIRE SH = SHIELD

 M1O = OLD HOOK−UP ON END 1 W.F. = WIRE FERRULE

Figure A-FHBAB - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 139

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 1411VT SH E0718−02−30 3132G7990 W1R TK24 3100 124 122 2430VC SH E0718−02−30 (a) A

 2 122 1411VT 7T EN3155−016M2222 3132−1619 B W1R TK24 3100 124 122 2430VC K EN3155−018M2018 (a) A

 3 122 1411VT 7U EN3155−016M2222 3132−1620 R W1R TK24 3100 124 122 2430VC J EN3155−018M2018 (a) A

 4 122 3132G7990 W.F. E0160−1−0H 3132−1621 W1R CF24 500 20 122 1411VT 7Y EN3155−016M2222 (a) A

 5 122 3132G7990 W.F. E0160−1−0H 3132−1622 W1R CF24 500 20 122 2430VC L EN3155−018M2018 (a) A

 6 122 3153G7664 W.F. E0160−1−0H 3153−3188 W1R CF24 500 20 122 1411VT 7G EN3155−016M2222 (a) A

 7 122 3153G7665 W.F. E0160−1−0H 3153−3193 W2R CF24 500 20 122 2436VC C EN3155−018M2018 (a) A

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695 W.F. = WIRE FERRULE

 A = ADDED WIRE

 SH = SHIELD

Figure A-FHBAB - Sheet 02

Hook-up Chart of the Modification of the Wiring in the Right Electronic Rack 90VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 140

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 002, 004

Figure A-FWCAA - Sheet 01

Modification of the Wiring in the Maintenance Panel 490VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 141

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 003

Figure A-FWCAB - Sheet 01

Modification of the Wiring in the Maintenance Panel 490VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 142

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 002, 004

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 212 86VD−A 2 EN3155−003F2222 3314−3894 1M CF24 1800 72 212 1348VT 15B EN3155−016M2018 (a) A

 2 212 86VD−A 5 EN3155−003F2222 3314−3895 1M CF24 1800 72 212 1348VT 15F EN3155−016M2018 (a) A

 3 212 86VD−A 17 EN3155−003F2222 3314−3897 1M CF24 1500 60 212 1653VC 21 EN3155−008M2222 (a) A

 4 212 86VD−A 20 EN3155−003F2222 3314−3898 1M CF24 1600 64 212 1654VC J EN3155−008M2222 (a) A

 5 212 1348VT 15G EN3155−016M2018 3314−3896 1M CF24 600 24 212 1348VT 16K EN3155−016M2018 (a) A

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695

 A = ADDED WIRE

Figure A-FHCAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Maintenance Panel 490VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 143

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 003

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 212 86VD−A 2 EN3155−003F2222 3314−3894 1M CF24 1800 72 212 1348VT 15B EN3155−016M2018 (a) A

 2 212 86VD−A 5 EN3155−003F2222 3314−3895 1M CF24 1800 72 212 1348VT 15F EN3155−016M2018 (a) A

 3 212 86VD−A 17 EN3155−003F2222 3314−3897 1M CF24 1500 60 212 1653VC 21 EN3155−008M2222 (a) A

 4 212 86VD−A 20 EN3155−003F2222 3314−3898 1M CF24 1600 64 212 1654VC J EN3155−008M2222 (a) A

 5 212 1348VT 15G EN3155−016M2018 3314−3896 1M CF24 1500 60 212 1348VT 16F EN3155−016M2018 (a) A

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695

 A = ADDED WIRE

Figure A-FHCAB - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Maintenance Panel 490VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 144

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FWDAA - Sheet 01

Modification of the Wiring in the Electronic Rack 500VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 145

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FWDAA - Sheet 02

Modification of the Wiring in the Electronic Rack 500VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 146

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 2224VC SH 3444G7519 2R TK24 122 1SG−AE SH M1O

 2 122 2224VC E 3444−0042 B 2R TK24 122 1SG−AE 7G M1O

 3 122 2224VC F 3444−0043 R 2R TK24 122 1SG−AE 7H M1O

 4 122 1487VT SH E0718−02−30 3444G7519 2R TK24 122 1SG−AE SH E0718−02−30 M1N

 5 122 1487VT 9B EN3155−016M2222 3444−0042 B 2R TK24 122 1SG−AE 7G M1N

 6 122 1487VT 9J EN3155−016M2222 3444−0043 R 2R TK24 122 1SG−AE 7H M1N

 7 122 2224VC G 3444−0026 2R CF24 122 3444G7519 W.F. M1O

 8 122 1487VT 9F EN3155−016M2222 3444−0026 2R CF24 122 3444G7519 W.F. M1N

 9

10

11

12 122 1487VT SH E0718−02−30 3153G7667 2R TK24 2700 108 122 2224VC SH E0718−02−30 (a) A

13 122 1487VT 9K EN3155−016M2222 3153−3200 R 2R TK24 2700 108 122 2224VC <F EN3155−018M2018 (a) A

14 122 1487VT 9C EN3155−016M2222 3153−3201 B 2R TK24 2700 108 122 2224VC <E EN3155−018M2018 (a) A

15 122 1487VT SH E0718−02−30 3444G7538 2R TK24 2700 108 122 2224VC SH E0718−02−30 (a) A

16 122 2224VC E EN3155−018M2018 3444−0237 B 2R TK24 2700 108 122 1487VT 9A EN3155−016M2222 (a) A

17 122 1487VT 9H EN3155−016M2222 3444−0238 R 2R TK24 2700 108 122 2224VC F EN3155−018M2018 (a) A

18 122 3153G7667 W.F. E0160−1−0H 3153−3198 2R CF24 500 20 122 2224VC <D EN3155−018M2018 (a) A

19 122 3153G7667 W.F. E0160−1−0H 3153−3199 2R CF24 500 20 122 1487VT 9M EN3155−016M2222 (a) A

20 122 3444G7538 W.F. E0160−1−0H 3444−0239 2R CF24 500 20 122 1487VT 9N EN3155−016M2222 (a) A

21 122 3444G7538 W.F. E0160−1−0H 3444−0240 2R CF24 500 20 122 2224VC G EN3155−018M2018 (a) A

22

23

24

25

 (a) = BUNDLE A9000095401695 M1N = NEW HOOK−UP ON END 1

 A = ADDED WIRE SH = SHIELD

 M1O = OLD HOOK−UP ON END 1 W.F. = WIRE FERRULE

Figure A-FHDAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Electronic Rack 500VU.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 147

5

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@A310

SERVICE BULLETIN

**CONF 004

Figure A-FWEAA - Sheet 01

Modification of the Wiring between the Avionics Compartment and the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 148

5

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@A310

SERVICE BULLETIN

**CONF 004

Figure A-FWEAA - Sheet 02

Modification of the Wiring between the Avionics Compartment and the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 149

5

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@A310

SERVICE BULLETIN

**CONF 001 thru 003

Figure A-FWEAB - Sheet 01

Modification of the Wiring between the Avionics Compartment and the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 150

5

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@A310

SERVICE BULLETIN

**CONF 001 thru 003

Figure A-FWEAB - Sheet 02

Modification of the Wiring between the Avionics Compartment and the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 151

5

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@A310

SERVICE BULLETIN

**CONF 004

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 190VT 34K EN3155−016M2018 3313−1660 2M CF18 1000 40 122 190VT W.S. NSA936604CA0931 (a) A

 2 122 190VT 35K EN3155−016M2018 3313−1661 2M CF18 1000 40 122 190VT W.S. NSA936604CA0931 (a) A

 3 122 190VT 34A EN3155−003F2222 3313−1662 R 1M PF22 8700 348 212 512VC1−A F EN3155−019F2018 (a) A

 4 122 190VT 35A EN3155−003F2222 3313−1663 B 1M PF22 8700 348 212 512VC1−A J EN3155−019F2018 (a) A

 5 122 190VT 34B EN3155−016M2018 3313−1664 R 2M PF22 8700 348 211 511VC2−A F EN3155−019F2018 (a) A

 6 122 190VT 35B EN3155−016M2018 3313−1665 B 2M PF22 8700 348 211 511VC2−A J EN3155−019F2018 (a) A

 7 122 472VC B EN3155−018M2018 3314−3902 2M CF24 11000 440 212 512VC2−A E EN3155−019F2018 (a) A

 8 122 472VC−A B EN3155−019F2018 3314−3900 2M CF24 7600 304 120 1654VC−A J EN3155−019F2018 (a) A

 9 122 473VC L EN3155−018M2018 3314−3901 1M CF24 10600 424 211 511VC1−A D EN3155−019F2018 (a) A

10 122 473VC−A L EN3155−019F2018 3314−3899 1M CF24 7100 284 212 1653VC−A 21 EN3155−003F2222 (a) A

11 122 2366VC−A C EN3155−019F2018 2212−0345 1M CF24 6000 240 211 511VC1−A F EN3155−019F2018 (a) A

12 122 2389VC−A 4 EN3155−003F2222 2212−0360 1M CF24 6000 240 212 512VC2−A F EN3155−019F2018 (a) A

13 121 2293VC−A C EN3155−019F2018 2212−0343 1A CF24 6000 240 211 511VC1−A K EN3155−019F2018 (a) A

14 121 2293VC−A D EN3155−019F2018 2212−0344 1A CF24 6000 240 211 511VC1−A J EN3155−019F2018 (a) A

15 121 2306VC−A G EN3155−019F2018 2212−0358 2A CF24 6000 240 212 512VC2−A K EN3155−019F2018 (a) A

16 121 2306VC−A H EN3155−019F2018 2212−0359 2A CF24 6000 240 212 512VC2−A J EN3155−019F2018 (a) A

17 121 2283VC−A <C EN3155−019F2018 2212−0357 2M CF24 6000 240 212 512VC2−A A EN3155−019F2018 (a) A

18 121 2321VC−A E EN3155−019F2018 2212−0342 1M CF24 6000 240 211 511VC1−A A EN3155−019F2018 (a) A

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695

 A = ADDED WIRE

 W.S. = WIRE STOWED

Figure A-FHEAA - Sheet 01

Hook-up Chart of the Modification of the Wiring between the Avionics Compartment and the

Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 152

5

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@A310

SERVICE BULLETIN

**CONF 001 thru 003

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 190VT 34K EN3155−016M2018 3313−1660 2M CF18 1000 40 122 190VT W.S. NSA936604CA0931 (a) A

 2 122 190VT 35K EN3155−016M2018 3313−1661 2M CF18 1000 40 122 190VT W.S. NSA936604CA0931 (a) A

 3 122 190VT 34A EN3155−003F2222 3313−1662 R 1M PF22 8700 348 212 512VC1−A F EN3155−019F2018 (a) A

 4 122 190VT 35A EN3155−003F2222 3313−1663 B 1M PF22 8700 348 212 512VC1−A J EN3155−019F2018 (a) A

 5 122 190VT 34B EN3155−016M2018 3313−1664 R 2M PF22 8700 348 211 511VC2−A F EN3155−019F2018 (a) A

 6 122 190VT 35B EN3155−016M2018 3313−1665 B 2M PF22 8700 348 211 511VC2−A J EN3155−019F2018 (a) A

 7 122 472VC A EN3155−018M2018 3314−3902 2M CF24 11000 440 212 512VC2−A E EN3155−019F2018 (a) A

 8 122 472VC−A A EN3155−019F2018 3314−3900 2M CF24 7600 304 120 1654VC−A J EN3155−019F2018 (a) A

 9 122 473VC L EN3155−018M2018 3314−3901 1M CF24 10600 424 211 511VC1−A D EN3155−019F2018 (a) A

10 122 473VC−A L EN3155−019F2018 3314−3899 1M CF24 7100 284 212 1653VC−A 21 EN3155−003F2222 (a) A

11 122 2366VC−A B EN3155−019F2018 2212−0345 1M CF24 6500 260 211 511VC1−A F EN3155−019F2018 (a) A

12 122 2389VC−A 4 EN3155−003F2222 2212−0360 1M CF24 6000 240 212 512VC2−A F EN3155−019F2018 (a) A

13 121 2293VC−A C EN3155−019F2018 2212−0343 1A CF24 6000 240 211 511VC1−A K EN3155−019F2018 (a) A

14 121 2293VC−A D EN3155−019F2018 2212−0344 1A CF24 6000 240 211 511VC1−A J EN3155−019F2018 (a) A

15 121 2306VC−A G EN3155−019F2018 2212−0358 2A CF24 6000 240 212 512VC2−A K EN3155−019F2018 (a) A

16 121 2306VC−A H EN3155−019F2018 2212−0359 2A CF24 6000 240 212 512VC2−A J EN3155−019F2018 (a) A

17 121 2283VC−A <C EN3155−019F2018 2212−0357 2M CF24 6000 240 212 512VC2−A A EN3155−019F2018 (a) A

18 121 2321VC−A E EN3155−019F2018 2212−0342 1M CF24 6000 240 211 511VC1−A A EN3155−019F2018 (a) A

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695

 A = ADDED WIRE

 W.S. = WIRE STOWED

Figure A-FHEAB - Sheet 01

Hook-up Chart of the Modification of the Wiring between the Avionics Compartment and the

Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 153

5

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@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FWFAA - Sheet 01

Modification of the Wiring in the Avionics Compartment.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 154

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 2224VC−A SH E0718−02−30 3153G7666 2R TK24 11000 440 122 2436VC−A SH E0718−02−30 (a) A

 2 122 2224VC−A <E EN3155−019F2018 3153−3195 B 2R TK24 11000 440 122 2436VC−A A EN3155−019F2018 (a) A

 3 122 2224VC−A <F EN3155−019F2018 3153−3196 R 2R TK24 11000 440 122 2436VC−A B EN3155−019F2018 (a) A

 4 122 3153G7666 W.F. E0160−1−0H 3153−3194 2R CF24 500 20 122 2436VC−A C EN3155−019F2018 (a) A

 5 122 3153G7666 W.F. E0160−1−0H 3153−9197 2R CF24 500 20 122 2224VC−A <D EN3155−019F2018 (a) A

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695 W.F. = WIRE FERRULE

 A = ADDED WIRE

 SH = SHIELD

Figure A-FHFAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Avionics Compartment.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 155

5

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@A310

SERVICE BULLETIN

**CONF 004

Figure A-FWGAA - Sheet 01

Modification of the Wiring in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 156

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003

Figure A-FWGAB - Sheet 01

Modification of the Wiring in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 157

5

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@A310

SERVICE BULLETIN

**CONF 004

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 211 511VC2−A B EN3155−019F2018 2212−0361 2M CF24 7500 300 212 512VC2−A B EN3155−019F2018 (a) A

 2 211 511VC2−A D EN3155−019F2018 2212−0362 2M CF24 7500 300 212 512VC2−A D EN3155−019F2018 (a) A

 3 211 511VC2−A H EN3155−019F2018 2491−2138 2M CF18 5000 200 210 221VT 6D EN3155−016M2018 (a) A

 4 211 511VC2−A G EN3155−019F2018 2491−2139 2M CF18 5000 200 210 221VT 6F EN3155−016M2018 (a) A

 5 211 511VC1−A B EN3155−019F2018 2212−0346 1M CF24 7500 300 212 512VC1−A B EN3155−019F2018 (a) A

 6 211 511VC1−A E EN3155−019F2018 2212−0347 1M CF24 7500 300 212 512VC1−A D EN3155−019F2018 (a) A

 7 211 511VC1−A G EN3155−019F2018 2212−0348 1M CF24 5000 200 210 1VT 16F EN3155−016M2018 (a) A

 8 210 221VT 24T EN3155−016M2222 2212−0363 2M CF24 5000 200 212 512VC2−A G EN3155−019F2018 (a) A

 9 210 221VT 12D EN3155−016M2018 2491−2136 1M CF18 5000 200 212 512VC1−A H EN3155−019F2018 (a) A

10 210 221VT 12F EN3155−016M2018 2491−2137 1M CF18 5000 200 212 512VC1−A G EN3155−019F2018 (a) A

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695

 A = ADDED WIRE

Figure A-FHGAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 158

5

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@A310

SERVICE BULLETIN

**CONF 001 thru 003

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 211 511VC2−A B EN3155−019F2018 2212−0361 2M CF24 7500 300 212 512VC2−A B EN3155−019F2018 (a) A

 2 211 511VC2−A D EN3155−019F2018 2212−0362 2M CF24 7500 300 212 512VC2−A D EN3155−019F2018 (a) A

 3 211 511VC2−A H EN3155−019F2018 2491−2138 2M CF18 5000 200 210 221VT 6D EN3155−016M2018 (a) A

 4 211 511VC2−A G EN3155−019F2018 2491−2139 2M CF18 5000 200 210 221VT 6F EN3155−016M2018 (a) A

 5 211 511VC1−A B EN3155−019F2018 2212−0346 1M CF24 7500 300 212 512VC1−A B EN3155−019F2018 (a) A

 6 211 511VC1−A E EN3155−019F2018 2212−0347 1M CF24 7500 300 212 512VC1−A D EN3155−019F2018 (a) A

 7 211 511VC1−A G EN3155−019F2018 2212−0348 1M CF24 5000 200 210 1VT 16F EN3155−016M2018 (a) A

 8 210 221VT 24T EN3155−016M2222 2212−0363 2M CF24 5000 200 212 512VC2−A G EN3155−019F2018 (a) A

 9 210 221VT 12G EN3155−016M2018 2491−2136 1M CF18 5500 220 212 512VC1−A H EN3155−019F2018 (a) A

10 210 221VT 12F EN3155−016M2018 2491−2137 1M CF18 5000 200 212 512VC1−A G EN3155−019F2018 (a) A

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095401695

 A = ADDED WIRE

Figure A-FHGAB - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Cockpit.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 159

5

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@A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 160

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@A310

SERVICE BULLETIN

Appendix 01: Gantt Chart

**CONF ALL

For detail concerning the elapsed time assumptions, refer to the Gantt chart shown below:

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 1

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@A310

SERVICE BULLETIN

Appendix 01: Gantt Chart

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−22−2063

SB ELAPSED TIME

(HOURS)

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

69.00

32.50

STEPS

0.50 0.50

0 5 10 15 20 25

MODIFY WIRING IN 80VU 6.50 6.50

17.00 8.50

1.50 1.50

TEST 4.50 4.50

CLOSE−UP 0.50 0.50

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MANHOURS GIVEN IN VENDOR SERVICE BULLETINS

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

1

1

2

1

1

1

1.00 1.50 1.00

:

:

MODIFY WIRING BETWEEN AVIONICS COMPARTMENT AND COCKPIT

MODIFY WIRING IN 90VU 9.00 9.00 1

MODIFY WIRING AND EQUIPMENT IN AVIONICS COMPARTMENT 4.50 4.50 1

MODIFY WIRING AND EQUIPMENT IN 500VU 6.50 6.50 1

REMOVE THE INSTRUMENT PANELS 0.50 0.50 1

MODIFY WIRING IN 490VU

MODIFY WIRING AND EQUIPMENT IN COCKPIT 10.00 10.00 1

INSTALL ITEMS REMOVED FOR ACCESS 2.00 2.00 1

MODIFY THE ROUTING IN 13VU 2.00 2.00 1

MODIFY THE INSTRUMENT PANELS 3.00 1.50 2

INSTALL THE INSTRUMENT PANELS

30 35

B_SB_222063_5_AAAA_01_00

Figure A-FAAAA - Sheet 01

Elapsed Time Assumption

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 2

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@A310

SERVICE BULLETIN

REPORTING SHEET

TITLE: AUTO FLIGHT - GENERAL - INSTALL SYSTEM PROVISION FOR

RUDDER REVERSAL WARNING FUNCTION

MODIFICATION No.: 13592S22847

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jun 20/12 SERVICE BULLETIN No.: A310-22-2063

REVISION No.: 00 - Jun 20/12 Page: 1

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