@A340-500/600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

MODIFICATION No.: 203228D50684

This page transmits Revision No.01 of Service Bulletin No.A340-25-5212

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to:

- update the reason paragraph to remove reference to the In-Flight Entertainment (IFE) wiring

- update of Concurrent Requirement to add Service Bulletin No. A340-25-5046.

- update the kits and associated accomplishment instructions.

CHANGES

SUMMARY

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

REASON UPDATED R

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS ADDED N

CONCURRENT REQUIREMENTS DELETED FOR

APPLICABLE MSN

D

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 002 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS UPDATED R

CONCURRENT SB LIST ADDED N

REASON

History HISTORY UPDATED R

WEIGHT AND BALANCE Minor editorial or document structure change R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL AVAILABILITY UPDATED

MATERIAL PRICE UPDATED

MATERIAL SET UPDATED

R

INDUSTRY SUPPORT INFORMATION INDUSTRY SUPPORT INFORMATION UPDATED R

LIST OF COMPONENTS

Kit 255212D01R04 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Components COMPONENTS UPDATED R

Component COMPD01 PART MATERIAL SET ADDED N

ACCOMPLISHMENT INSTRUCTIONS

TASK 255212- 831-848-001-Modification TASK SOLUTION UPDATED

CAUTION UPDATED

NOTE UPDATED

R

Subtask 255212-910-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 255212-910-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 255212-941-201-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 255212-941-201-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 255212-831-201-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 255212-831-202-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 255212-831-201-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 255212-831-202-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 255212-942-201-001 SUBTASK SOLUTION UPDATED R

Subtask 255212-942-201-001 SUBTASK SOLUTION UPDATED R

Fig. A-GBDAA

Fig. A-GBDAA Sheet 04 SHEET UPDATED R

Fig. A-GBDAB

Fig. A-GBDAB Sheet 04 SHEET UPDATED R

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: May 27/14

REVISION No. : 01 - Oct 27/14

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 4

6

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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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 203228D50684

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

Airbus has identified a potential risk of electrical shocks in case of chafing at the cockpit door. The

electrical bonding of the cockpit door has to be improved in order to mitigate this potential risk.

This Service Bulletin details the work necessary to improve the electrical bonding.

Accomplishment of this Service Bulletin improves the effectiveness of the electrical bonding thus will

contribute to prevent the risk of an electrical shock.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 1

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 255212D01R04 1 730.00 Screw, Washer, Nut, Rivet, Bracket,

Bonding-Lead, Tube, Placard

Component COMPD01 1 See SB Bonding Lead, Washer, Screw

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 255212D01R04 1 730.00 Screw, Washer, Nut, Rivet, Bracket,

Bonding-Lead, Tube, Placard

Component COMPD01 1 See SB Bonding Lead, Washer, Screw

EFFECTIVITY

**CONF ALL

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

06U 25R 32P 36V 70U 72W 81Q AHY AIB CES CHH DLH ETD

HFY I2L IBE QAF QTR SAA TAM THA UAE VIR

CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the

following Service Bulletins:

Service Bulletin No. A340-25-5046

NOTE: Service Bulletin No. A340-25-5046 (EQUIPMENT/FURNISHINGS - PAX

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT DOOR

PLATE COVER) which applies Modification No. 51911D44499.

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 2

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SERVICE BULLETIN

SUMMARY

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 255212-831-848-001: Modification

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

**CONF 002

Task 255212-831-848-001: Modification

TOTAL MANHOURS 8.75

ELAPSED TIME (HOURS) 8.75

APPENDICES

**CONF ALL

None

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 3

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SERVICE BULLETIN

SUMMARY

**CONF 001

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

F_SB_255212_6_SAAA_01_01

Figure A-GSAAA - Sheet 01

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 4

6

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@A340-500/600

SERVICE BULLETIN

SUMMARY

**CONF 002

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

F_SB_255212_6_SAAB_01_01

Figure A-GSAAB - Sheet 01

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 5

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 6

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

MODIFICATION No.: 203228D50684

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

This modification is applicable by Service Bulletin only.

(1) Models

340-541 340-542 340-642

(2) Effectivity by MSN

0371 0376 0383 0391 0394 0410 0416-0417 0426 0431 0436 0440 0445 0449 0453

0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517

0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575

0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626

0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719

0723 0727 0736 0740 0744 0748 0753 0757 0761-0768 0771 0775 0779 0783 0787

0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910

0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040

1079 1091 1102 1122

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 1

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SERVICE BULLETIN

(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

06U 1091 1102

25R 0924

32P 0560

36V 0391 0416

70U 0902

72W 0917

81Q 0563

AHY 0779 0886 0894

AIB 0371 0376 0478 0492 0499

CES 0468 0488 0514 0577 0586

CHH 0475

DLH 0482 0517 0523 0537 0540 0543 0566 0569 0580 0583 0762 0763

0767 0771 0790 0794 0812 0846 0848 0897 0972 0981 0987 1005

ETD 0748 0757 0761 0783 0829 0837 0870 0929 0933 1030 1040

HFY 0383 0910 0912

I2L 0436 0453

IBE 0431 0440 0460 0601 0604 0606 0617 0619 0672 0702 0727 0744

0960 0993 1017 1079 1122

QAF 0495

QTR 0715 0740 0766 0798

SAA 0410 0417 0426 0531 0534 0547 0557 0626 0630

TAM 0445 0464

THA 0624 0628 0677 0681 0689 0698 0710 0719 0775 0953

UAE 0394 0457 0471 0485 0520 0572 0608 0611 0685 0694

VIR 0449 0575 0615 0622 0639 0706 0723 0736 0753 0764 0765 0768

0787 0804

(4) Configuration by MSN

MSN CONFIGURATION

0371 0376 0383 0391 0394 0410 0416 0417 0426 0431 0436

0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0482

0485 0488 0495 0514 0517 0520 0523 0531 0534 0537 0540

0543 0547 0557 0566 0569 0572 0575 0577 0580 0583 0586

0601 0604 0606 0608 0611 0617 0619 0624 0626 0628 0630

0672 0677 0681 0685 0689 0694 0698 0702 0710 0715 0719

0727 0740 0744 0748 0757 0761 0762 0763 0766 0767 0771

0775 0779 0783 0790 0794 0798 0812 0829 0837 0846 0848

0870 0886 0894 0897 0902 0910 0912 0917 0924 0929 0933

0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079

1091 1102 1122

001

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 2

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SERVICE BULLETIN

MSN CONFIGURATION

0478 0492 0499 0560 0563 0615 0622 0639 0706 0723 0736

0753 0764 0765 0768 0787 0804

002

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin which

have installed the cockpit door via mod 50014D44099 and have installed a reinforced

partition structure via mod 50561S16638 or SB A340-25-5003.

**CONF 002

Config. 002 is valid for all the aircraft given in the effectivity of this Service Bulletin

which have installed a damping device to the cockpit door via mod 51720D44340 or

Service Bulletin A340-25-5132 and have installed a reinforced partition structure via mod

50561S16638 or SB A340-25-5003.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 255212D01R04 1

Component COMPD01 1 (1)

Consumable CMLD01 1

NOTE (1): Operators with Kit 255212D01R03 will require COMPD01.

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 255212D01R04 1

Component COMPD01 1 (1)

Consumable CMLD01 1

NOTE (1): Operators with Kit 255212D01R03 will require COMPD01.

**CONF ALL

B. CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of

the following Service Bulletins:

Service Bulletin No. A340-25-5046

NOTE: Service Bulletin No. A340-25-5046 (EQUIPMENT/FURNISHINGS - PAX

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT

DOOR PLATE COVER) which applies Modification No. 51911D44499.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 3

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C. REASON

(1) History

Airbus has identified a potential risk of electrical shocks in case of chafing at the cockpit

door. The electrical bonding of the cockpit door has to be improved in order to mitigate

this potential risk.

(2) Objective/Action

This Service Bulletin details the work necessary to improve the electrical bonding.

(3) Advantages

Accomplishment of this Service Bulletin improves the effectiveness of the electrical

bonding thus will contribute to prevent the risk of an electrical shock.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 255212-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

(2) Install Bonding-Leads to the Upper Cockpit Door Frame

**CONF 002

Task 255212-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

(2) Install Bonding-Leads to the Upper Cockpit Door Frame

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 4

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SERVICE BULLETIN

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. The accomplishment timescale, which has not yet been

defined, will be given in the AD.

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 255212-831-848-001: Modification

Get Access 1.00

On Aircraft

Modify the Cockpit Door Frame Structure 3.50

Install Bonding-Leads to the Upper Cockpit Door

Frame

1.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

**CONF 002

Task 255212-831-848-001: Modification

Get Access 1.00

On Aircraft

Modify the Cockpit Door Frame Structure 3.75

Install Bonding-Leads to the Upper Cockpit Door

Frame

2.50

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 8.75

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 5

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Task 255212-831-848-001: Modification

ELAPSED TIME (HOURS) 8.75

**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’s items. For the definition of

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

Manufacturers Empty Weight +0.387 KG (+0.8531 LB)

Effect on Balance +3.97 KGM (+28.715 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

11-00-00 12-34-24 20-21-11

20-21-15 20-28-00 25-13-44

25-13-46 25-23-42 52-51-00

52-51-15

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20 20-33-00 20-33-30

20-51-20 20-55-00

Illustrated Parts Catalog (IPC) 52-51-10

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

11-00-00 12-34-24 20-21-11

20-21-15 20-28-00 25-13-44

25-13-46 25-23-42 52-51-00

52-51-11 52-51-15

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20 20-33-00 20-33-30

20-51-20 20-55-00

Illustrated Parts Catalog (IPC) 52-51-10

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

Weight and Balance Manual (WBM) Chapter 1-00-07

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 6

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SERVICE BULLETIN

**CONF ALL

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 52-51-00 52-51-11

Illustrated Parts Catalog (IPC) 25-81-01 52-51-10

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 7

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This Page Intentionally Left Blank

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 8

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

Kit 255212D01R04 AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

For ordering by E-mail: airbus.kit@airbus.com

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

Component COMPD01 AIRBUS Material, Logistics and Suppliers

IFD - In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 4012

For ordering by E-mail:

ifd.spares@airbus.com

(2) Price and Availability

This table shows the component kits COMP needed to update the kits already held in

your stock to the latest status.

KIT HELD BY OPERATOR COMP KIT REQUIRED LATEST STATUS OF KIT

255212D01R03 COMPD01 255212D01R04

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from Operator‘s stock.

Kit 255212D01R04

Cost 730.00 USD

Availability 90 calendar days from receipt of order

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 9

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SERVICE BULLETIN

The availability given above is the standard lead time from the date of your purchase

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

B. INDUSTRY SUPPORT INFORMATION

For aircraft under warranty at Jan 01/12, AIRBUS will credit the manhours indicated in this

Service Bulletin at the agreed in-house warranty labor rate for claims received not later than

90 days after completion of the last affected aircraft of your fleet and AIRBUS will provide the

kits and COMPD01 listed in paragraph 2.D at no charge for orders placed before Nov 30/16.

For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit

management department.

AIRBUS CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

France

Tel : (33) 5 67 19 06 22

E-mail : monitored.retrofit@airbus.com

Fax : (33) 5 61 93 27 45

C. LIST OF COMPONENTS

Kit 255212D01R04

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

NOTES

1 NAS1102-3-8 2 SCREW

2 NAS1102-08-10 6 SCREW

5 NAS1096-3-12 1 SCREW

6 NSA5320-10 1 WASHER

7 ABS1577D54 1 BRACKET

8 ABS0547D503 2 RIVET

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 (ME) TUBING

11 E0090-10-125NN 2 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

15 NAS1726C3P 4 NUT

16 E0090-10-100NN 1 LEAD

18 F2529200700400 6 PLACARD

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

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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 CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Mineral Oil Base Grease 03FAB1 As required

Varnish - Electrical Bonding 04TMB2 As required

Polysulfide Sealant 06AAB1 As required

Non Aqueous Cleaner-General 08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

(2) Components

Component COMPD01

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

NOTES

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

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.

NOTE: Operators with Kit 255212D01R03 will require COMPD01.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

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This Page Intentionally Left Blank

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 255212-831-848-001 - 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.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

"refer to" are used and the operator has a procedure accepted by the local

authority he belongs to, the accepted alternative procedure can be used. When the

words "in accordance with" are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

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SERVICE BULLETIN

Task Associated Data

**CONF 001

Zone

220

Manpower

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

**CONF 002

Zone

220

Manpower

TOTAL MANHOURS 8.75

ELAPSED TIME (HOURS) 8.75

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 255212-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-11-911-801

Task 20-21-15-912-801

20-28-00, Page Block 201

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20

20-33-00

20-33-30

20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

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(c) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(d) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(e) For the specification of materials (Mat. No.) given in this Service Bulletin refer to

Consumable Materials List (CML).

(f) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(g) To torque tighten the electrical component fasteners, refer to AMM Task

20-21-15-912-801.

(h) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-00, Page Block

201.

(i) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

- Deburr the holes after you have drilled them.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

(k) Remove and install fasteners in accordance with SRM 51-42-00.

(l) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(m) Apply sealant in accordance with SRM 51-24-00.

(n) Renew the protective finish in accordance with SRM 51-75-12.

(o) For the identification of wire and wire harnesses, refer to ESPM 20-32-20.

(p) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

(q) For the installation of the protective electrical conduits, refer to ESPM 20-33-30.

(r) For the installation of placards, refer to AMM 11-00-00, Page Block 201.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

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SERVICE BULLETIN

(2) Subtask 255212-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 002

(1) Subtask 255212-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-11-911-801

Task 20-21-15-912-801

20-28-00, Page Block 201

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20

20-33-00

20-33-30

20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(d) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(e) For the specification of materials (Mat. No.) given in this Service Bulletin refer to

Consumable Materials List (CML).

(f) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(g) To torque tighten the electrical component fasteners, refer to AMM Task

20-21-15-912-801.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

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(h) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-00, Page Block

201.

(i) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

- Deburr the holes after you have drilled them.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

(k) Remove and install fasteners in accordance with SRM 51-42-00.

(l) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(m) Apply sealant in accordance with SRM 51-24-00.

(n) Renew the protective finish in accordance with SRM 51-75-12.

(o) For the identification of wire and wire harnesses, refer to ESPM 20-32-20.

(p) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

(q) For the installation of the protective electrical conduits, refer to ESPM 20-33-30.

(r) For the installation of placards, refer to AMM 11-00-00, Page Block 201.

(2) Subtask 255212-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 17

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**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 255212-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-13-44-000-801

Task 25-13-46-000-801

Task 25-23-42-000-801

NOTE: The following items shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(b) Remove the ceiling panel 221AC, refer to AMM Task 25-23-42-000-801.

(c) Remove the ceiling panel 211LC and 211MC, refer to AMM Task

25-13-44-000-801.

(d) Remove the upper panel from the coat stowage, refer to AMM Task

25-13-46-000-801.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 18

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SERVICE BULLETIN

**CONF 002

(1) Subtask 255212-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-13-44-000-801

Task 25-13-46-000-801

Task 25-23-42-000-801

NOTE: The following items shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(b) Remove the ceiling panel 221AC, refer to AMM Task 25-23-42-000-801.

(c) Remove the ceiling panel 211LC and 211MC, refer to AMM Task

25-13-44-000-801.

(d) Remove the upper panel from the coat stowage, refer to AMM Task

25-13-46-000-801.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 19

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**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 255212-831-201-001 - Modify the Cockpit Door Frame Structure

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 3.50

Minimum number of person 1

Subtask elapsed time 3.50

Skills AIRFRAME

Material necessary to do the job

Kit 255212D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-8 2 SCREW

2 NAS1102-08-10 6 SCREW

5 NAS1096-3-12 1 SCREW

6 NSA5320-10 1 WASHER

7 ABS1577D54 1 BRACKET

8 ABS0547D503 2 RIVET

18 F2529200700400 6 PLACARD

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Mineral Oil Base Grease 03FAB1 As required

Varnish - Electrical Bonding 04TMB2 As required

Polysulfide Sealant 06AAB1 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 52-51-00-710-803

Task 52-51-15-000-801

Task 52-51-15-400-801

Illustrated Parts Catalog (IPC) 52-51-10

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References

Fig. A-GBAAA

Prepare the bonding points at the wire

protection

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBBAA

Install the bracket at the pelmet

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBCAA

Prepare the bonding points at the door

posts

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBEAA

Prepare the bonding points at the webs

Sheet 01

Sheet 02

Sheet 03

(a) Remove the keypad from the gap cover, refer to AMM Task 52-51-15-000-801.

(b) Loosen the nuts and carefully remove the wire harness from the wire protection as

shown on Fig. A-GBAAA Sheet 02, View C.

(c) Modify the wire protection as follows:

1 Prepare the bonding point at the front side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAA Sheet

03, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAA Sheet 03, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAA Sheet 03, View D.

2 Prepare the bonding point at the upper side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAA Sheet

03, View E.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAA Sheet 03, View E.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAA Sheet 03, View E.

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

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Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 255212-831-202 001

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

5 Install as shown on Fig. A-GBAAA Sheet 02, View C:

1 Placard F2529200700400 Item 18

(d) Modify the door posts as follows:

1 Prepare the bonding point at the LH door post:

a Remove as shown on Fig. A-GBCAA Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAA Sheet 02, View F.

c Install as shown on Fig. A-GBCAA Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

d Apply to the screw, item 1 as shown on Fig. A-GBCAA Sheet 02, View F:

Varnish - Electrical

Bonding

04TMB2 As required

2 Prepare the bonding points at the RH door post:

a Remove as shown on Fig. A-GBCAA Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAA Sheet 02, View F.

c Install as shown on Fig. A-GBCAA Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

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d Remove as shown on Fig. A-GBCAA Sheet 03, View G:

6 Screw Item (2) Discard

1 Gap Cover Item (3) Retain

1 Door Frame Panel Item (4) Retain

NOTE: For the PN of the gap cover, item (3) and the door frame

panel, item (4), refer to IPC 52-51-10.

e Remove as shown on Fig. A-GBCAA Sheet 03, View H:

1 Screw Item (5) Discard

1 Washer Item (6) Discard

f Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the screw head diameter as

shown on Fig. A-GBCAA Sheet 03, View J.

g Install as shown on Fig. A-GBCAA Sheet 03, View J:

1 Screw NAS1096-3-12 Item 5

1 Washer NSA5320-10 Item 6

h Apply to the screws, item 1 and 5 as shown on Fig. A-GBCAA Sheet 02,

View F and Fig. A-GBCAA Sheet 03, View J:

Varnish - Electrical

Bonding

04TMB2 As required

i Install as shown on Fig. A-GBCAA Sheet 03, View G:

1 Gap Cover Item (3) Retained at

removal

1 Door Frame Panel Item (4) Retained at

removal

6 Screw NAS1102-08-10 Item 2

3 Install as shown on Fig. A-GBCAA Sheet 02, View C and D:

2 Placard F2529200700400 Item 18

(e) Install the bracket as follows:

1 Remove the surface protection from the contact area of the bracket, item 7 to

the pelmet as shown on Fig. A-GBBAA Sheet 02, View D.

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2 Use the bracket, item 7 as template and mark the position of the holes as

shown on Fig. A-GBBAA Sheet 03, View E.

3

CAUTION: MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN

A DEPTH OF 21 MM (0.83 IN.) TO AVOID DAMAGE TO

THE S_GLASS ON THE CABIN SIDE.

Drill pilot holes to a diameter of 2.5 mm (0.098 in.) and a depth of 21 mm-1

mm (0.83 in.-0.039 in.).

4 Drill the pilot holes to the final diameter of 4.1 mm (0.16 in.) and a depth of 21

mm-1 mm (0.83 in.-0.039 in.) as shown on Fig. A-GBBAA Sheet 03, Section

A-A.

5 Deburr the holes.

6 Remove the surface protection around the rivet holes to a diameter

approximately 3 mm (0.12 in.) larger than the rivet head diameter as shown on

Fig. A-GBBAA Sheet 02, View D.

7 Clean the modification area with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

8 Install as shown on Fig. A-GBBAA Sheet 02, View D:

1 Bracket ABS1577D54 Item 7

2 Rivet ABS0547D503 Item 8

9 Apply to the rivets, item 8 and to the edges of the bracket, item 7 as shown on

Fig. A-GBBAA Sheet 03, Section A-A:

Polysulfide Sealant 06AAB1 As required

Varnish - Electrical

Bonding

04TMB2 As required

10 Install as shown on Fig. A-GBBAA Sheet 02, View C:

1 Placard F2529200700400 Item 18

(f) Modify the webs as follows:

1 Prepare the bonding points at the RH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

02, View D.

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b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 02, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 02, View D.

e Install as shown on Fig. A-GBEAA Sheet 02, View D:

1 Placard F2529200700400 Item 18

2 Prepare the bonding points at the LH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

03, View F.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 03, View F.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 03, View F.

e Install as shown on Fig. A-GBEAA Sheet 03, View F:

1 Placard F2529200700400 Item 18

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 255212-831-202 001

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

(g) Install the keypad to the gap cover, refer to AMM Task 52-51-15-400-801.

(h) Do the operational test of the cockpit door emergency access, refer to AMM Task

52-51-00-710-803.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 25

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

(2) Subtask 255212-831-202-001 - Install Bonding-Leads to the Upper Cockpit Door

Frame

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 255212D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 TUBING

11 E0090-10-125NN 2 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

15 NAS1726C3P 4 NUT

16 E0090-10-100NN 1 LEAD

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

NOTE: Operators with Kit 255212D01R03 will require COMPD01.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Varnish - Electrical Bonding 04TMB2 As required

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 26

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Fig. A-GBDAA

Install the bonding-leads at the upper

door frame

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the bonding-leads at the RH door post as follows:

1 Remove as shown on Fig. A-GBDAA Sheet 03, View E:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAA Sheet 03, View F.

3 Clean the bonding points at the wire protection and the door post with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Cut two pieces of tubing to a length of 0.11 m (4.33 in.) from:

0.6 Tubing ABS0916B05 Item 10

5 Push the tubings, item 10 over the bonding-leads, item 11 and shrink them.

6 Install at the door post as shown Fig. A-GBDAA Sheet 03, View F:

2 Bonding-Lead E0090-10-125NN Item 11

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

7 Attach the bonding-lead, item 11 to the wire protection as shown on Fig. AGBDAA Sheet 03, View F with:

1 Screw NAS1802-3-7 Item 12

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 27

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

8 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

9 Attach the bonding-lead, item 11 to the web as shown on Fig. A-GBDAA

Sheet 05, View J with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

10 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAA

Sheet 05, View J:

Varnish - Electrical

Bonding

04TMB2 As required

11 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAA Sheet 03, View F:

Varnish - Electrical

Bonding

04TMB2 As required

(b) Install the bonding-leads at the LH door post as follows:

1 Remove as shown on Fig. A-GBDAA Sheet 04, View G:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAA Sheet 04, View H.

3 Make sure that there is no surface protection at the bonding point from the

bracket.

4 Clean the bonding points at the wire protection, the bracket and the door post

with:

Non Aqueous

Cleaner-General

08BAA9 As required

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 28

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

Textile-Lint Free

Cotton

14SBA1 As required

5 Cut two pieces of tubing to a length of 0.085 m (3.35 in.) and one piece to a

length of 0.185 m (7.28 in.) from:

0.6 Tubing ABS0916B05 Item 10

6 Push the tubings, item 10 over the bonding-leads, item 16, 21 and 22 and

shrink them.

7 Install at the door post as shown Fig. A-GBDAA Sheet 04, View H:

1 Bonding-Lead E0090-10-100NN Item 16

1 Bonding Lead E0090-18-200NN Item 22

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

for operators with KITD01R03, get this item from COMPD01:

1 Bonding Lead E0090-18-200NN Item 22

8 Attach the bonding-lead, item 22, to the bracket as shown on Fig. A-GBDAA

Sheet 04, View H with:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

for operators with KITD01R03, get these items from COMPD01:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

9 Attach the bonding-lead, item 21, to the wire protection as shown on Fig. AGBDAA Sheet 04, View H with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 29

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

10 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

11 Attach the bonding-lead, item 16 to the web as shown on Fig. A-GBDAA

Sheet 05, View K with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

12 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAA

Sheet 05, View K:

Varnish - Electrical

Bonding

04TMB2 As required

13 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAA Sheet 04, View H:

Varnish - Electrical

Bonding

04TMB2 As required

(c) Install the wire harness to the wire protection as shown on Fig. A-GBDAA Sheet

06, View L.

**CONF 002

(1) Subtask 255212-831-201-002 - Modify the Cockpit Door Frame Structure

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 3.75

Minimum number of person 1

Subtask elapsed time 3.75

Skills AIRFRAME

Material necessary to do the job

Kit 255212D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-8 2 SCREW

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 30

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 NAS1102-08-10 6 SCREW

5 NAS1096-3-12 1 SCREW

6 NSA5320-10 1 WASHER

7 ABS1577D54 1 BRACKET

8 ABS0547D503 2 RIVET

18 F2529200700400 6 PLACARD

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Mineral Oil Base Grease 03FAB1 As required

Varnish - Electrical Bonding 04TMB2 As required

Polysulfide Sealant 06AAB1 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 52-51-00-710-803

Task 52-51-11-000-802

Task 52-51-15-000-801

Task 52-51-15-400-801

Illustrated Parts Catalog (IPC) 52-51-10

Fig. A-GBAAB

Prepare the bonding points at the wire

protection

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBBAB

Install the bracket at the pelmet

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBCAB

Prepare the bonding points at the door

posts

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBEAA

Prepare the bonding points at the webs

Sheet 01

Sheet 02

Sheet 03

(a) Remove the damper unit from the pelmet, refer to AMM Task 52-51-11-000-802.

(b) Remove the keypad from the gap cover, refer to AMM Task 52-51-15-000-801.

(c) Loosen the nuts and carefully remove the wire harness from the wire protection as

shown on Fig. A-GBAAB Sheet 02, View C.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 31

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

(d) Modify the wire protection as follows:

1 Prepare the bonding point at the front side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAB Sheet

03, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAB Sheet 03, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAB Sheet 03, View D.

2 Prepare the bonding point at the upper side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAB Sheet

03, View E.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAB Sheet 03, View E.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAB Sheet 03, View E.

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 255212-831-202 002

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

5 Install as shown on Fig. A-GBAAB Sheet 02, View C:

1 Placard F2529200700400 Item 18

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 32

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

(e) Modify the door posts as follows:

1 Prepare the bonding point at the LH door post:

a Remove as shown on Fig. A-GBCAB Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAB Sheet 02, View F.

c Install as shown on Fig. A-GBCAB Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

d Apply to the screw, item 1 as shown on Fig. A-GBCAB Sheet 02, View F:

Varnish - Electrical

Bonding

04TMB2 As required

2 Prepare the bonding points at the RH door post:

a Remove as shown on Fig. A-GBCAB Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAB Sheet 02, View F.

c Install as shown on Fig. A-GBCAB Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

d Remove as shown on Fig. A-GBCAB Sheet 03, View G:

6 Screw Item (2) Discard

1 Gap Cover Item (3) Retain

1 Door Frame Panel Item (4) Retain

NOTE: For the PN of the gap cover, item (3) and the door frame

panel, item (4), refer to IPC 52-51-10.

e Remove as shown on Fig. A-GBCAB Sheet 03, View H:

1 Screw Item (5) Discard

1 Washer Item (6) Discard

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 33

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

f Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the screw head diameter as

shown on Fig. A-GBCAB Sheet 03, View J.

g Install as shown on Fig. A-GBCAB Sheet 03, View J:

1 Screw NAS1096-3-12 Item 5

1 Washer NSA5320-10 Item 6

h Apply to the screws, item 1 and 5 as shown on Fig. A-GBCAB Sheet 02,

View F and Fig. A-GBCAB Sheet 03, View J:

Varnish - Electrical

Bonding

04TMB2 As required

i Install as shown on Fig. A-GBCAB Sheet 03, View G:

1 Gap Cover Item (3) Retained at

removal

1 Door Frame Panel Item (4) Retained at

removal

6 Screw NAS1102-08-10 Item 2

3 Install as shown on Fig. A-GBCAB Sheet 02, View C and D:

2 Placard F2529200700400 Item 18

(f) Install the bracket as follows:

1 Remove the surface protection from the contact area of the bracket, item 7 to

the pelmet as shown on Fig. A-GBBAB Sheet 02, View D.

2 Use the bracket, item 7 as template and mark the position of the holes as

shown on Fig. A-GBBAB Sheet 03, View E.

3

CAUTION: MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN

A DEPTH OF 21 MM (0.83 IN.) TO AVOID DAMAGE TO

THE S_GLASS ON THE CABIN SIDE.

Drill pilot holes to a diameter of 2.5 mm (0.098 in.) and a depth of 21 mm-1

mm (0.83 in.-0.039 in.).

4 Drill the pilot holes to the final diameter of 4.1 mm (0.16 in.) and a depth of 21

mm-1 mm (0.83 in.-0.039 in.) as shown on Fig. A-GBBAB Sheet 03, Section

A-A.

5 Deburr the holes.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 34

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

6 Remove the surface protection around the rivet holes to a diameter

approximately 3 mm (0.12 in.) larger than the rivet head diameter as shown on

Fig. A-GBBAB Sheet 02, View D.

7 Clean the modification areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

8 Install as shown on Fig. A-GBBAB Sheet 02, View D:

1 Bracket ABS1577D54 Item 7

2 Rivet ABS0547D503 Item 8

9 Apply to the rivets, item 8 and to the edges of the bracket, item 7 as shown on

Fig. A-GBBAB Sheet 03, Section A-A:

Polysulfide Sealant 06AAB1 As required

Varnish - Electrical

Bonding

04TMB2 As required

10 Install as shown on Fig. A-GBBAB Sheet 02, View C:

1 Placard F2529200700400 Item 18

(g) Modify the webs as follows:

1 Prepare the bonding points at the RH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

02, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 02, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 02, View D.

e Install as shown on Fig. A-GBEAA Sheet 02, View D:

1 Placard F2529200700400 Item 18

2 Prepare the bonding points at the LH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

03, View F.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 35

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 03, View F.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 03, View F.

e Install as shown on Fig. A-GBEAA Sheet 03, View F:

1 Placard F2529200700400 Item 18

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 255212-831-202 002

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

(h) Install the keypad to the gap cover, refer to AMM Task 52-51-15-400-801.

(i) Do the operational test of the cockpit door emergency access, refer to AMM Task

52-51-00-710-803.

(2) Subtask 255212-831-202-002 - Install Bonding-Leads to the Upper Cockpit Door

Frame

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 36

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

Material necessary to do the job

Kit 255212D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 TUBING

11 E0090-10-125NN 2 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

15 NAS1726C3P 4 NUT

16 E0090-10-100NN 1 LEAD

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

NOTE: Operators with Kit 255212D01R03 will require COMPD01.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Varnish - Electrical Bonding 04TMB2 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 52-51-11-400-802

Task 52-51-11-820-801

Fig. A-GBDAB

Install the bonding-leads at the upper

door frame

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 37

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

(a) Install the bonding-leads at the RH door post as follows:

1 Remove as shown on Fig. A-GBDAB Sheet 03, View E:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAB Sheet 03, View F.

3 Clean the bonding points at the wire protection and the door post with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Cut two pieces of tubing to a length of 0.11 m (4.33 in.) from:

0.6 Tubing ABS0916B05 Item 10

5 Push the tubings, item 10 over the bonding-leads, item 11 and shrink them.

6 Install at the door post as shown Fig. A-GBDAB Sheet 03, View F:

2 Bonding-Lead E0090-10-125NN Item 11

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

7 Attach the bonding-lead, item 11 to the wire protection as shown on Fig. AGBDAB Sheet 03, View F with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

8 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 38

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

9 Attach the bonding-lead, item 11 to the web as shown on Fig. A-GBDAB

Sheet 05, View J with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

10 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAB

Sheet 05, View J:

Varnish - Electrical

Bonding

04TMB2 As required

11 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAB Sheet 03, View F:

Varnish - Electrical

Bonding

04TMB2 As required

(b) Install the bonding-leads at the LH door post as follows:

1 Remove as shown on Fig. A-GBDAB Sheet 04, View G:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAB Sheet 04, View H.

3 Make sure that there is no surface protection at the bonding point from the

bracket.

4 Clean the bonding points at the wire protection, the bracket and the door post

with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

5 Cut two pieces of tubing to a length of 0.085 m (3.35 in.) and one piece to a

length of 0.185 m (7.28 in.) from:

0.6 Tubing ABS0916B05 Item 10

6 Push the tubings, item 10 over the bonding-leads, item 16, 21 and 22 and

shrink them.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 39

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

7 Install at the door post as shown Fig. A-GBDAB Sheet 04, View H:

1 Bonding-Lead E0090-10-100NN Item 16

1 Bonding Lead E0090-18-200NN Item 22

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

For operators with KITD01R03, get this item from COMPD01:

1 Bonding Lead E0090-18-200NN Item 22

8 Attach the bonding-lead, item 22, to the bracket as shown on Fig. A-GBDAB

Sheet 04, View H with:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

For operators with KITD01R03, get these items from COMPD01:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

9 Attach the bonding-lead, item 21, to the wire protection as shown on Fig. AGBDAB Sheet 04, View H with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

10 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 40

6

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SERVICE BULLETIN

11 Attach the bonding-lead, item 16 to the web as shown on Fig. A-GBDAB

Sheet 05, View K with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

12 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAB

Sheet 05, View K:

Varnish - Electrical

Bonding

04TMB2 As required

13 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAB Sheet 04, View H:

Varnish - Electrical

Bonding

04TMB2 As required

(c) Install the wire harness to the wire protection as shown on Fig. A-GBDAB Sheet

06, View L.

(d) Install the damper unit to the pelmet, refer to AMM Task 52-51-11-400-802.

(e) Make sure that cockpit door operates easily and closes correctly, refer to AMM

Task 52-51-11-820-801.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 255212-760-201-001 - Bonding Test

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

(a) This Service Bulletin requires the accomplishment of the following Test which is

given in SUBTASK 255212-831-201 001 Modify the Cockpit Door Frame Structure :

- operational test of the cockpit door emergency access

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 41

6

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SERVICE BULLETIN

The manhours for the tests are included in the referenced Service Bulletin

subtasks.

(b) Do a check of the electrical bonding, refer to AMM Task 20-28-00-720-805.

**CONF 002

(1) Subtask 255212-760-201-002 - Bonding Test

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

(a) This Service Bulletin requires the accomplishment of the following Test which is

given in SUBTASK 255212-831-201 002 Modify the Cockpit Door Frame Structure

and SUBTASK 255212-831-202 002 Install Bonding-Leads to the Upper Cockpit

Door Frame :

- operational test of the cockpit door emergency access

- test of easy operation and correct close of the cockpit door

The manhours for the tests are included in the referenced Service Bulletin

subtasks.

(b) Do a check of the electrical bonding, refer to AMM Task 20-28-00-720-805.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 255212-942-201-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-13-44-400-801

Task 25-13-46-400-801

Task 25-23-42-400-801

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 42

6

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@A340-500/600

SERVICE BULLETIN

(b) Install the ceiling panel 211MC and 211LC, refer to AMM Task 25-13-44-400-801.

(c) Install the upper panel to the coat stowage, refer to AMM Task 25-13-46-400-801.

(d) Install the ceiling panel 221AC, refer to AMM Task 25-23-42-400-801.

(e) Put the aircraft back to its initial configuration.

**CONF 002

(1) Subtask 255212-942-201-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-13-44-400-801

Task 25-13-46-400-801

Task 25-23-42-400-801

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the ceiling panel 211MC and 211LC, refer to AMM Task 25-13-44-400-801.

(c) Install the upper panel to the coat stowage, refer to AMM Task 25-13-46-400-801.

(d) Install the ceiling panel 221AC, refer to AMM Task 25-23-42-400-801.

(e) Put the aircraft back to its initial configuration.

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 43

6

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@A340-500/600

SERVICE BULLETIN

**CONF 001

FR11

FR16A

B

A

C

B

A

Z220

F_SB_255212_6_BAAA_01_00

Figure A-GBAAA - Sheet 01

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 44

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

C

01

01

01

01

NOTE:

01 LOOSEN ONLY THE NUTS TO REMOVE THE ELECTRICAL HARNESS

D

E

18 SB25−5212

F_SB_255212_6_BAAA_02_00

Figure A-GBAAA - Sheet 02

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 45

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

12.24 mm

(0.48 in)

12.0 mm

(0.47 in)

5.1 mm DIA

(0.20 in)

D

46.8 mm

(1.84 in)

17.7 mm

(0.70 in)

5.1 mm DIA

(0.20 in)

E

12.5 mm DIA

(0.49 in)

12.5 mm DIA

(0.49 in)

F_SB_255212_6_BAAA_03_00

Figure A-GBAAA - Sheet 03

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 46

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

C

B

A

Z220

F_SB_255212_6_BAAB_01_00

Figure A-GBAAB - Sheet 01

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 47

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

C

01

01

01

01

NOTE:

01 LOOSEN ONLY THE NUTS TO REMOVE THE ELECTRICAL HARNESS

D

E

18 SB25−5212

F_SB_255212_6_BAAB_02_00

Figure A-GBAAB - Sheet 02

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 48

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

12.24 mm

(0.48 in)

12.0 mm

(0.47 in)

5.1 mm DIA

(0.20 in)

D

46.8 mm

(1.84 in)

17.7 mm

(0.70 in)

5.1 mm DIA

(0.20 in)

E

12.5 mm DIA

(0.49 in)

12.5 mm DIA

(0.49 in)

F_SB_255212_6_BAAB_03_00

Figure A-GBAAB - Sheet 03

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 49

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

FR11

FR16A

B

A

B

C

G

D

A

Z220

F_SB_255212_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 50

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

(1)

FWD FWD

BEFORE

AFTER

1

NOTE:

02 REMOVE SURFACE PROTECTION TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE COUNTERSINK DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

02

03

RH SIDE LH SIDE

C D

E

F

E F

E F

18

SB25−5212

18

SB25−5212

F_SB_255212_6_BCAA_02_01

Figure A-GBCAA - Sheet 02

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 51

6

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@A340-500/600

SERVICE BULLETIN

**CONF 001

(2)

2 6X

(3)

(4)

BEFORE

AFTER

(5)

(6)

5

6

NOTE:

04 REMOVE SURFACE PROTECTION TO A

LARGER THAN THE SCREW HEAD DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

04

03

G DIA APPROX. 3.0 mm (0.12 in)

H

J

H J

F_SB_255212_6_BCAA_03_00

Figure A-GBCAA - Sheet 03

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 52

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

B

C

G

D

A

Z220

F_SB_255212_6_BCAB_01_00

Figure A-GBCAB - Sheet 01

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 53

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

(1)

FWD FWD

BEFORE

AFTER

1

NOTE:

02 REMOVE SURFACE PROTECTION TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE COUNTERSINK DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

02

03

RH SIDE LH SIDE

C D

E

F

E F

E F

18

SB25−5212

18

SB25−5212

F_SB_255212_6_BCAB_02_01

Figure A-GBCAB - Sheet 02

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 54

6

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@A340-500/600

SERVICE BULLETIN

**CONF 002

(2)

2 6X

(3)

(4)

BEFORE

AFTER

(5)

(6)

5

6

NOTE:

04 REMOVE SURFACE PROTECTION TO A

LARGER THAN THE SCREW HEAD DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

04

03

G DIA APPROX. 3.0 mm (0.12 in)

H

J

H J

F_SB_255212_6_BCAB_03_00

Figure A-GBCAB - Sheet 03

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 55

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

FR11

FR16A

B

A

C

B

A

Z220

F_SB_255212_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 56

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

C

D

7

18 SB25−5212

8

D

NOTE:

01 REMOVE SURFACE PROTECTION TO A DIA 

APPROX. 3.0 mm (0.12 in) LARGER THAN THE 

E

DIA OF THE RIVET HEAD.

02 REMOVE SURFACE PROTECTION FROM

THE CONTACT AREA.

02

01

F_SB_255212_6_BBAA_02_00

Figure A-GBBAA - Sheet 02

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 57

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

4.0 mm

(0.16 in)

7

E

A A

NOTE:

03 MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN A DEPTH

VIEW FROM COCKPIT SIDE

OF 21.0 mm (0.83 in) TO AVOID DAMAGE TO THE S−GLASS ON THE CABIN SIDE.

FLUSH WITH CHANNEL EDGE

A

A

A

A

21.0 mm −1.0 mm

(0.83 in −0.039 in)

4.1 mm DIA

(0.16 in)

S−GLASS

03

7

8

04

04

04

04 APPLY VARNISH (MAT.NO.04TMB2) AND SEALANT (MAT.NO.06AAB1).

F_SB_255212_6_BBAA_03_00

Figure A-GBBAA - Sheet 03

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 58

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

C

B

A

Z220

F_SB_255212_6_BBAB_01_00

Figure A-GBBAB - Sheet 01

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 59

6

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@A340-500/600

SERVICE BULLETIN

**CONF 002

C

D

7

18 SB25−5212

8

D

NOTE:

01 REMOVE SURFACE PROTECTION TO A DIA 

APPROX. 3.0 mm (0.12 in) LARGER THAN THE 

E

DIA OF THE RIVET HEAD.

02 REMOVE SURFACE PROTECTION FROM

THE CONTACT AREA.

02

01

F_SB_255212_6_BBAB_02_00

Figure A-GBBAB - Sheet 02

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 60

6

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@A340-500/600

SERVICE BULLETIN

**CONF 002

4.0 mm

(0.16 in)

7

E

A A

NOTE:

03 MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN A DEPTH

VIEW FROM COCKPIT SIDE

OF 21.0 mm (0.83 in) TO AVOID DAMAGE TO THE S−GLASS ON THE CABIN SIDE.

FLUSH WITH CHANNEL EDGE

A

A

A

A

21.0 mm −1.0 mm

(0.83 in −0.039 in)

4.1 mm DIA

(0.16 in)

S−GLASS

03

7

8

04

04

04

04 APPLY VARNISH (MAT.NO.04TMB2) AND SEALANT (MAT.NO.06AAB1).

F_SB_255212_6_BBAB_03_00

Figure A-GBBAB - Sheet 03

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 61

6

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@A340-500/600

SERVICE BULLETIN

**CONF ALL

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

E

C

F_SB_255212_6_BEAA_01_01

Figure A-GBEAA - Sheet 01

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 62

6

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@A340-500/600

SERVICE BULLETIN

**CONF ALL

21.5 mm

(0.85 in)

18.0 mm

(0.71 in)

FR11A

FWD

5.1mm DIA

(0.20 in)

17.0 mm DIA

(0.70 in)

D

FR11

18 SB25−5212

C

D

RH DOOR POST

F_SB_255212_6_BEAA_02_02

Figure A-GBEAA - Sheet 02

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 63

6

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@A340-500/600

SERVICE BULLETIN

**CONF ALL

LH DOOR POST

E

F

FR11A

FR11

5.1mm DIA

(0.20 in)

17.0 mm DIA

(0.70 in)

19.0 mm

(0.75 in)

17.5 mm

(0.69 in)

F FWD

18 SB25−5212

F_SB_255212_6_BEAA_03_02

Figure A-GBEAA - Sheet 03

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 64

6

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@A340-500/600

SERVICE BULLETIN

**CONF 001

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

C L

J

K

F_SB_255212_6_BDAA_01_01

Figure A-GBDAA - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 65

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 001

C

D

E F

D

G H

F_SB_255212_6_BDAA_02_00

Figure A-GBDAA - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 66

6

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@A340-500/600

SERVICE BULLETIN

**CONF 001

AFTER

9

13

11

14

10

11

10

12

13

15

BEFORE

(1)

E

F

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

01

02 REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14.

02

F_SB_255212_6_BDAA_03_00

Figure A-GBDAA - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 67

6

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@A340-500/600

SERVICE BULLETIN

**CONF 001

AFTER

BEFORE

(1)

9

13

16

14

10

12

13

15

10

10

G

H

01

01

01

01

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

02

02

REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14.

19

22

20

21

F_SB_255212_6_BDAA_04_01

Figure A-GBDAA - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 68

6

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@A340-500/600

SERVICE BULLETIN

**CONF 001

15

16

13

12

LH DOOR POST

K

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

13

12 01

11

J

RH DOOR POST

01 15

F_SB_255212_6_BDAA_05_01

Figure A-GBDAA - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 69

6

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@A340-500/600

SERVICE BULLETIN

**CONF 001

04 MAKE SURE THAT THERE IS NO CHAFING

BETWEEN THE WIRE HARNESS AND THE BONDING LEAD

L

03

03

03

03

04

NOTE:

03 TIGHTEN THE NUTS TO FIX THE ELECTRICAL HARNESS

TO THE WIRE PROTECTOR

F_SB_255212_6_BDAA_06_01

Figure A-GBDAA - Sheet 06

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 70

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

C L

J

K

F_SB_255212_6_BDAB_01_01

Figure A-GBDAB - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 71

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340-500/600

SERVICE BULLETIN

**CONF 002

C

D

E F

D

G H

F_SB_255212_6_BDAB_02_00

Figure A-GBDAB - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 72

6

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@A340-500/600

SERVICE BULLETIN

**CONF 002

AFTER

9

13

11

14

10

11

10

12

13

15

BEFORE

(1)

E

F

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

01

02

02

REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14. F_SB_255212_6_BDAB_03_00

Figure A-GBDAB - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 73

6

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@A340-500/600

SERVICE BULLETIN

**CONF 002

AFTER

BEFORE

(1)

9

13

16

14

10

12

13

15

10

10

G

H

01

01

01

01

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

02

02

REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14.

19

22

20

21

F_SB_255212_6_BDAB_04_01

Figure A-GBDAB - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 74

6

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@A340-500/600

SERVICE BULLETIN

**CONF 002

15

16

13

12

LH DOOR POST

K

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

13

12 01

11

J

RH DOOR POST

01 15

F_SB_255212_6_BDAB_05_01

Figure A-GBDAB - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 75

6

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@A340-500/600

SERVICE BULLETIN

**CONF 002

04 MAKE SURE THAT THERE IS NO CHAFING

BETWEEN THE WIRE HARNESS AND THE BONDING LEAD

L

03

03

03

03

04

NOTE:

03 TIGHTEN THE NUTS TO FIX THE ELECTRICAL HARNESS

TO THE WIRE PROTECTOR

F_SB_255212_6_BDAB_06_01

Figure A-GBDAB - Sheet 06

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 76

6

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@A340-500/600

SERVICE BULLETIN

REPORTING SHEET

TITLE: EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

MODIFICATION No.: 203228D50684

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: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 1

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@A340-500/600

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: May 27/14 SERVICE BULLETIN No.: A340-25-5212

REVISION No.: 01 - Oct 27/14 Page: 1

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