@A340

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 204312D50883

This page transmits Revision No.02 of Service Bulletin No.A340-25-4349

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 02 issued to:

- update the illustration to correct the bonding hole location

- add a note in illustration to indicate Typical Installation

- update steps in Job Set-up to remove the parts as necessary from the coat stowage

- add a note in concurrent requirement

- add a note in Procedure to adapt bonding lead length

- add step in Test procedure to test the operation and correct close of cockpit door

- update steps in Close-up to install the removed parts from the coat stowage.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS UPDATED R

REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE

UPDATED

R

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

CONCURRENT REQUIREMENTS CONCURRENT SB LIST UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED R

INDUSTRY SUPPORT INFORMATION INDUSTRY SUPPORT INFORMATION UPDATED R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Components

Component COMPD02 PART MATERIAL SET UPDATED

QUANTITY UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 254349- 831-848-001-Modification

Subtask 254349-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 254349-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 254349-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 254349-831-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

PART NUMBER UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

Subtask 254349-831-202-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

Subtask 254349-831-201-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

PART NUMBER UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

R

Subtask 254349-831-202-002 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 254349-831-201-004 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

PART NUMBER UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

R

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 254349-831-202-004 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 254349-760-201-001 SUBTASK SOLUTION UPDATED R

Subtask 254349-760-201-001 SUBTASK SOLUTION UPDATED R

Subtask 254349-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 254349-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 254349-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Fig. A-GBCAA

Fig. A-GBCAA Sheet 02 SHEET UPDATED R

Fig. A-GBCAA Sheet 03 SHEET UPDATED R

Fig. A-GBCAB

Fig. A-GBCAB Sheet 02 SHEET UPDATED R

Fig. A-GBCAB Sheet 03 SHEET UPDATED R

FILLING 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

Revision No. 01 issued to:

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

delete MSN 0048 and 0088 from the effectivity

update of Concurrent Requirement to add Service Bulletin No. A340-25-4217

update the kits and associated accomplishment instructions.

REVISION SEQUENCE

ORIGINAL: May 28/14

REVISION No. : 01 - Oct 27/14

REVISION No. : 02 - Sep 04/15

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 4

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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 204312D50883

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 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

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 254349D01R06 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 254349D01R06 1 730.00 Screw, Washer, Nut, Rivet, Bracket,

Bonding-Lead, Tube, Placard

Component COMPD01 1 See SB Bonding Lead, Washer, Screw

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 254349D02R02 1 735.00 Screw, Washer, Nut, Rivet, Bracket,

Bonding-Lead, Tube, Placard

Component COMPD02 1 See SB Bonding Lead, Washer, Screw

EFFECTIVITY

**CONF ALL

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

06Y 15R 15T 22O 31V 56W 74W 83V 98W 98X ABD AFR AIB

ALD ALK ARG BOE CAL CCA CPA DGA DLH F2I FIN G8E GAF

HFM HFY IBE IRC IRM KAC LAN M3R MAU MDG O2X PAL PUE

QAF S3R SAA SAS SFB SLM SVW SWR TAP THT THY UAE VCV

XAX

CONCURRENT REQUIREMENTS

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

following Service Bulletin:

Service Bulletin No. A340-25-4217

NOTE: Service Bulletin No. A340-25-4217 (EQUIPMENT/FURNISHINGS - PAX

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT DOOR

PLATE COVER) which applies Modification No. 51911D44499.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 2

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SERVICE BULLETIN

SUMMARY

NOTE: Service Bulletin No. A340-25-4217 (EQUIPMENT/FURNISHINGS - PAX

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT DOOR

PLATE COVER) is valid for all aircraft in the effectivity of this Service Bulletin which

have not embodied Modification No. 52869D44765 or Modification No. 53292D44777.

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

ISI None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 254349-831-848-001: Modification

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

**CONF 002

Task 254349-831-848-001: Modification

TOTAL MANHOURS 8.75

ELAPSED TIME (HOURS) 8.75

**CONF 003

Task 254349-831-848-001: Modification

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

APPENDICES

**CONF ALL

None

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 001

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

F_SB_254349_6_SAAA_01_01

Figure A-GSAAA - Sheet 01

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 002

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

F_SB_254349_6_SAAB_01_01

Figure A-GSAAB - Sheet 01

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 003

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

F_SB_254349_6_SAAC_01_01

Figure A-GSAAC - Sheet 01

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 6

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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 204312D50883

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

340-211 340-212 340-213 340-311 340-312 340-313

(2) Effectivity by MSN

0002 0004 0006 0009 0014 0020 0022-0023 0025-0026 0029 0031-0034 0038 0041

0043-0044 0046-0047 0049 0051 0056-0058 0061 0063 0074-0076 0078-0081

0084-0085 0089-0091 0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128

0131 0134-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164

0166-0170 0173-0175 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199

0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0227-0228 0233 0236-0237

0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0273-0274 0278 0280

0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329 0331-0332

0335 0347 0352 0354-0355 0359 0363 0367 0373-0374 0377-0379 0381 0385 0387

0390 0395 0399 0402 0406 0411 0413 0415 0424 0429-0430 0433-0435 0438 0442

0446-0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546 0554 0556

0559 0561-0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800 0835 0844

0921 0938 0955

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

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

06Y 0139 0149

15R 0151

15T 0009

22O 0257

31V 0093

56W 0006

74W 0047 0051

83V 0216 0280 0292

98W 0014 0022

98X 0429

ABD 0210

AFR 0029 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377

0399

AIB 0131 0141 0161 0182 0192 0199

ALD 0156 0159 0178

ALK 0032 0033 0034 0367 0374 0381

ARG 0063 0074 0080 0085 0094 0123 0126 0128 0170 0193 0373

BOE 0554

CAL 0402 0406 0411 0415 0433 0541

CCA 0201 0242 0243 0264

CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228

DGA 0075 0081

DLH 0135 0158 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347

0352 0354 0379 0390 0434 0447

F2I 0038 0043 0114 0214

FIN 0058 0168 0174 0835 0844 0921 0938

G8E 0173 0187 0196

GAF 0274 0355

HFM 0117

HFY 0190 0202

IBE 0125 0134 0145 0146 0217 0221 0329 0483

IRC 0002

IRM 0020 0056 0164 0282

KAC 0089 0090 0101 0104

LAN 0359 0363 0442

M3R 0061

MAU 0076 0152 0194 0268 0793 0800

MDG 0319

O2X 0273

PAL 0302 0318 0332 0387 0459 0474

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

SERVICE BULLETIN

OPERATOR MSN

PUE 0212 0215

QAF 0026 0528

S3R 0004 0204

SAA 0197 0378 0544 0582 0590 0643 0646 0651

SAS 0167 0413 0424 0430 0435 0450 0467 0470

SFB 0046

SLM 0049

SVW 0955

SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561

0562 0585 0598

TAP 0041 0044 0079 0091

THT 0385 0395 0438 0446 0668

THY 0023 0025 0057 0115 0180 0270 0331

UAE 0163 0166 0185 0236

VCV 0031

XAX 0278

(4) Configuration by MSN

MSN CONFIGURATION

0002 0006 0009 0014 0020 0022 0023 0025 0026 0029 0031

0032 0033 0034 0038 0041 0043 0044 0047 0049 0051 0056

0057 0058 0063 0074 0075 0076 0078 0079 0080 0081 0084

0085 0089 0090 0091 0093 0094 0101 0104 0114 0115 0117

0123 0125 0126 0128 0131 0134 0135 0136 0137 0139 0141

0142 0145 0146 0147 0149 0150 0152 0154 0156 0157 0158

0159 0160 0161 0163 0164 0166 0167 0168 0169 0170 0173

0174 0175 0178 0179 0180 0182 0185 0186 0187 0190 0192

0193 0194 0196 0197 0199 0201 0202 0207 0208 0210 0212

0213 0214 0215 0216 0217 0218 0220 0221 0227 0228 0233

0236 0237 0242 0243 0245 0246 0252 0257 0260 0263 0264

0268 0270 0273 0274 0278 0280 0282 0292 0297 0302 0304

0307 0310 0318 0319 0321 0325 0327 0329 0331 0332 0335

0347 0352 0354 0355 0359 0363 0367 0373 0374 0377 0379

0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0415

0424 0429 0430 0433 0434 0435 0438 0442 0446 0447 0450

0459 0467 0470 0474 0483 0528 0538 0541 0544 0545 0546

0554 0556 0559 0561 0562 0582 0585 0590 0598 0643 0646

0651 0668 0955

001

0004 0046 0061 0151 0204 0378 001 003

0793 0800 0835 0844 0921 0938 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 A340-25-4187 or SB A340-25-4205.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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SERVICE BULLETIN

**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 and have

installed a reinforced partition structure via mod 50561S16638.

**CONF 003

Config. 003 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 not installed a

reinforced partition structure via mod 50561S16638 or SB A340-25-4187 or SB

A340-25-4205.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 254349D01R06 1

Component COMPD01 1 (1)

Consumable CMLD01 1

NOTE (1): Operators with Kit 254349D01R04 will require COMPD01

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 254349D01R06 1

Component COMPD01 1 (1)

Consumable CMLD01 1

NOTE (1): Operators with Kit 254349D01R04 will require COMPD01

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 254349D02R02 1

Component COMPD02 1 (1)

Consumable CMLD01 1

NOTE (1): Operators with Kit 254349D02R01 will require COMPD02

**CONF ALL

B. CONCURRENT REQUIREMENTS

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

the following Service Bulletin:

Service Bulletin No. A340-25-4217

NOTE: Service Bulletin No. A340-25-4217 (EQUIPMENT/FURNISHINGS - PAX

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 4

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@A340

SERVICE BULLETIN

NOTE: Service Bulletin No. A340-25-4217 (EQUIPMENT/FURNISHINGS - PAX

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT

DOOR PLATE COVER) is valid for all aircraft in the effectivity of this

Service Bulletin which have not embodied Modification No. 52869D44765 or

Modification No. 53292D44777.

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 254349-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

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

**CONF 002

Task 254349-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

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

**CONF 003

Task 254349-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

SERVICE BULLETIN

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(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 254349-831-848-001: 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 254349-831-848-001: Modification

Get Access 1.00

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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SERVICE BULLETIN

Task 254349-831-848-001: Modification

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

ELAPSED TIME (HOURS) 8.75

**CONF 003

Task 254349-831-848-001: 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 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 +0.13 KG (+0.2865 LB)

Effect on Balance +1.317 KGM (+9.525 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

52-51-11 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

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Illustrated Parts Catalog (IPC) 52-51-01

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) 52-51-01

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 003

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) 52-51-01

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 ALL

K. PUBLICATION AFFECTED

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

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

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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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 254349D01R06

Kit 254349D02R02

AIRBUS Material, Logistics and Suppliers

ATP II B,

Hein-Sass-Weg 24

21129 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

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

Telephone Hotlines:

A330/A340. A300/310: +49 40 743 51616

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

Component COMPD02

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

254349D01R04 COMPD01 254349D01R06

254349D02R01 COMPD02 254349D02R02

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from Operator‘s stock.

Kit 254349D01R06

Cost 730.00 USD

Availability 90 calendar days from receipt of order

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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.

Kit 254349D02R02

Cost 735.00 USD

Availability 90 calendar days from receipt of order

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 254349D01R06

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

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

NOTES

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 F2529200700200 6 PLACARD

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.

Kit 254349D02R02

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 0.7 (ME) TUBING

11 E0090-10-125NN 1 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

17 E0090-10-200NN 1 LEAD

18 F2529200700200 6 PLACARD

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.

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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 254349D01R04 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.

Component COMPD02

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 254349D02R01 will require COMPD02

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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

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This Page Intentionally Left Blank

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 254349-831-848-001 - 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.

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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 003

Zone

220

Manpower

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 254349-910-201-001 - 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

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References

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.

(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.

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(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 254349-839-201-001 - 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 254349-910-201-001 - 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).

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(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.

(2) Subtask 254349-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

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**CONF 003

(1) Subtask 254349-910-201-001 - 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.

(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.

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- 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 254349-839-201-001 - 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 ALL

B. PREPARATION

**CONF 001

(1) Subtask 254349-941-201-001 - 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

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SERVICE BULLETIN

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) Based on aircraft configuration, if installed, remove the upper panel from the coat

stowage, refer to AMM Task 25-13-46-000-801.

(e) Based on aircraft configuration, if installed, remove the parts as necessary from the

coat stowage to get access to the work area, refer to AMM Task 25-13-46-000-801.

**CONF 002

(1) Subtask 254349-941-201-001 - 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

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SERVICE BULLETIN

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) Based on aircraft configuration, if installed, remove the upper panel from the coat

stowage, refer to AMM Task 25-13-46-000-801.

(e) Based on aircraft configuration, if installed, remove the parts as necessary from the

coat stowage to get access to the work area, refer to AMM Task 25-13-46-000-801.

**CONF 003

(1) Subtask 254349-941-201-001 - 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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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SERVICE BULLETIN

- 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) Based on aircraft configuration, if installed, remove the upper panel from the coat

stowage, refer to AMM Task 25-13-46-000-801.

(e) Based on aircraft configuration, if installed, remove the parts as necessary from the

coat stowage to get access to the work area, refer to AMM Task 25-13-46-000-801.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 254349-831-201-001 - 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 254349D01R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-8 2 SCREW

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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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 F2529200700200 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 52-51-11-820-801

Task 52-51-15-000-801

Task 52-51-15-400-801

Illustrated Parts Catalog (IPC) 52-51-01

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.

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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 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

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 254349-831-202 001

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 F2529200700200 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.

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SERVICE BULLETIN

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

NOTE: Bonding can be performed on other door post location

than shown in Fig. A-GBCAA Sheet 02 if this lead to less

equipment removal. Bonding is to be performed at one

position with screw NAS1102-3-8 installed.

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

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 52-51-01.

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

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SERVICE BULLETIN

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 F2529200700200 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.

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

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SERVICE BULLETIN

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 F2529200700200 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.

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 F2529200700200 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.

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SERVICE BULLETIN

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

1 Placard F2529200700200 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 254349-831-202 001

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.

(2) Subtask 254349-831-202-001 - 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 254349D01R06

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

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

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 254349D01R04 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 52-51-11-820-801

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.

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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 on 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

NOTE: The bonding lead length may be adapted by using next longer

bonding lead length if necessary.

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

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

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SERVICE BULLETIN

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

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 on 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

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SERVICE BULLETIN

For operators with KITD01R04 get this item from COMPD01:

1 Bonding Lead E0090-18-200NN Item 22

NOTE: The bonding lead length may be adapted by using next longer

bonding lead length if necessary.

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 KITD01R04 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

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

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@A340

SERVICE BULLETIN

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.

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

Task 52-51-11-820-801.

**CONF 002

(1) Subtask 254349-831-201-002 - 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 254349D01R06

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 F2529200700200 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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 35

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@A340

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

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) 52-51-01

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.

(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.

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SERVICE BULLETIN

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 254349-831-202 002

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 F2529200700200 Item 18

(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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 37

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SERVICE BULLETIN

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

Varnish - Electrical

Bonding

04TMB2 As required

NOTE: Bonding can be performed on other door post location

than shown in Fig. A-GBCAB Sheet 02 if this lead to less

equipment removal. Bonding is to be performed at one

position with screw NAS1102-3-8 installed.

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 52-51-01.

e Remove as shown on Fig. A-GBCAB 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-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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 38

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@A340

SERVICE BULLETIN

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 F2529200700200 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.

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 39

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@A340

SERVICE BULLETIN

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 F2529200700200 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 F2529200700200 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.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 40

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@A340

SERVICE BULLETIN

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

1 Placard F2529200700200 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 254349-831-202 002

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 254349-831-202-002 - 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

Material necessary to do the job

Kit 254349D01R06

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 41

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

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 254349D01R04 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

(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.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 42

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SERVICE BULLETIN

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 on 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

NOTE: The bonding lead length may be adapted by using next longer

bonding lead length if necessary.

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

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 43

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@A340

SERVICE BULLETIN

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.

7 Install at the door post as shown on 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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 44

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@A340

SERVICE BULLETIN

For operators with KITD01R04 get this item from COMPD01:

1 Bonding Lead E0090-18-200NN Item 22

NOTE: The bonding lead length may be adapted by using next longer

bonding lead length if necessary.

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 KITD01R04 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

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 45

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@A340

SERVICE BULLETIN

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 wire harness to the wire protection as shown on Fig. A-GBDAB Sheet

06, View L.

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

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

Task 52-51-11-820-801.

**CONF 003

(1) Subtask 254349-831-201-004 - 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 254349D02R02

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 F2529200700200 6 PLACARD

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 46

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@A340

SERVICE BULLETIN

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) 52-51-01

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-GBEAC

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.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 47

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SERVICE BULLETIN

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

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 254349-831-202 004

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 F2529200700200 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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 48

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@A340

SERVICE BULLETIN

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

Varnish - Electrical

Bonding

04TMB2 As required

NOTE: Bonding can be performed on other door post location

than shown in Fig. A-GBCAA Sheet 02 if this lead to less

equipment removal. Bonding is to be performed at one

position with screw NAS1102-3-8 installed.

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

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 52-51-01.

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 49

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@A340

SERVICE BULLETIN

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 F2529200700200 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.

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 50

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@A340

SERVICE BULLETIN

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 F2529200700200 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-GBEAC 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-GBEAC Sheet 02, View D.

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

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

1 Placard F2529200700200 Item 18

2 Prepare the bonding points at the LH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAC 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-GBEAC Sheet 03, View F.

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 51

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@A340

SERVICE BULLETIN

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

1 Placard F2529200700200 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 254349-831-202 004

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.

(2) Subtask 254349-831-202-004 - 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 254349D02R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.7 TUBING

11 E0090-10-125NN 1 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 52

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 NAS1726C3P 4 NUT

16 E0090-10-100NN 1 LEAD

17 E0090-10-200NN 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 COMPD02

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 254349D02R01 will require COMPD02

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

Fig. A-GBDAC

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-GBDAC 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-GBDAC Sheet 03, View F.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 53

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SERVICE BULLETIN

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 one piece of tubing to a length of 0.11 m (4.33 in.) and one piece to a

length of 0.185 m (7.28 in.) from:

0.7 Tubing ABS0916B05 Item 10

5 Push the tubings, item 10 over the bonding-leads, item 11 and 17 and shrink

them.

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

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

1 Bonding-Lead E0090-10-200NN Item 17

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

NOTE: The bonding lead length may be adapted by using next longer

bonding lead length if necessary.

7 Attach the bonding-lead, item 11 to the wire protection as shown on Fig. AGBDAC 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

9 Attach the bonding-lead, item 17 to the web as shown on Fig. A-GBDAC

Sheet 05, View J with:

1 Screw NAS1802-3-7 Item 12

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 54

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SERVICE BULLETIN

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-GBDAC

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. AGBDAC 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-GBDAC 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-GBDAC 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:

0.7 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 on Fig. A-GBDAC 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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 55

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SERVICE BULLETIN

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

For operators with KITD02R01 get these items from COMPD02:

1 Bonding Lead E0090-18-200NN Item 22

NOTE: The bonding lead length may be adapted by using next longer

bonding lead length if necessary.

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

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 KITD02R01 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. AGBDAC 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

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

Sheet 05, View K with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 56

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SERVICE BULLETIN

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

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. AGBDAC Sheet 04, View H:

Varnish - Electrical

Bonding

04TMB2 As required

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

06, View L.

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

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 254349-760-201-001 - 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 254349-831-201 001 Modify the Cockpit Door Frame Structure :

- 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.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 57

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SERVICE BULLETIN

**CONF 002

(1) Subtask 254349-760-201-002 - 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 Tests which are

given in SUBTASK 254349-831-201 002 Modify the Cockpit Door Frame Structure

and SUBTASK 254349-831-202 002 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 003

(1) Subtask 254349-760-201-001 - 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 254349-831-201 004 Modify the Cockpit Door Frame Structure :

- 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.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 58

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SERVICE BULLETIN

(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 254349-942-201-001 - 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) Based on aircraft configuration, if removed, install the parts to the coat stowage,

refer to AMM Task 25-13-46-400-801.

(d) Based on aircraft configuration, if removed, install the upper panel to the coat

stowage, refer to AMM Task 25-13-46-400-801.

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

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

**CONF 002

(1) Subtask 254349-942-201-001 - 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) Based on aircraft configuration, if removed, install the parts to the coat stowage,

refer to AMM Task 25-13-46-400-801.

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 59

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SERVICE BULLETIN

(d) Based on aircraft configuration, if removed, install the upper panel to the coat

stowage, refer to AMM Task 25-13-46-400-801.

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

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

**CONF 003

(1) Subtask 254349-942-201-001 - 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) Based on aircraft configuration, if removed, install the parts to the coat stowage,

refer to AMM Task 25-13-46-400-801.

(d) Based on aircraft configuration, if removed, install the upper panel to the coat

stowage, refer to AMM Task 25-13-46-400-801.

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

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

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 60

6

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@A340

SERVICE BULLETIN

**CONF 001, 003

FR11

FR16A

B

A

C

B

A

Z220

F_SB_254349_6_BAAA_01_00

Figure A-GBAAA - Sheet 01

Prepare the bonding points at the wire protection

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 61

6

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@A340

SERVICE BULLETIN

**CONF 001, 003

C

01

01

01

01

NOTE:

01 LOOSEN ONLY THE NUTS TO REMOVE THE ELECTRICAL HARNESS

D

E

18 SB25−4349

F_SB_254349_6_BAAA_02_00

Figure A-GBAAA - Sheet 02

Prepare the bonding points at the wire protection

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 62

6

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SERVICE BULLETIN

**CONF 001, 003

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_254349_6_BAAA_03_00

Figure A-GBAAA - Sheet 03

Prepare the bonding points at the wire protection

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 63

6

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@A340

SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

C

B

A

Z220

F_SB_254349_6_BAAB_01_00

Figure A-GBAAB - Sheet 01

Prepare the bonding points at the wire protection

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 64

6

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@A340

SERVICE BULLETIN

**CONF 002

C

01

01

01

01

NOTE:

01 LOOSEN ONLY THE NUTS TO REMOVE THE ELECTRICAL HARNESS

D

E

18 SB25−4349

F_SB_254349_6_BAAB_02_00

Figure A-GBAAB - Sheet 02

Prepare the bonding points at the wire protection

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 65

6

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@A340

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_254349_6_BAAB_03_00

Figure A-GBAAB - Sheet 03

Prepare the bonding points at the wire protection

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 66

6

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@A340

SERVICE BULLETIN

**CONF 001, 003

FR11

FR16A

B

A

B

C

G

D

A

Z220

F_SB_254349_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

Prepare the bonding points at the door posts

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 67

6

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@A340

SERVICE BULLETIN

**CONF 001, 003

AFTER

1

02

03

F

(1)

BEFORE

NOTE:

02 REMOVE SURFACE PROTECTION TO A DIA APPROX.

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

03 APPLY VARNISH (MATERIAL NO.04TMB2).

RH SIDE LH SIDE

C D

E

E F

E F

18

SB25−4349

18

SB25−4349

05

05

05 TYPICAL INSTALLATION.

FWD FWD

F_SB_254349_6_BCAA_02_02

Figure A-GBCAA - Sheet 02

Prepare the bonding points at the door posts

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 68

6

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@A340

SERVICE BULLETIN

**CONF 001, 003

(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

DIA APPROX. 3.0 mm (0.12 in)

G

H

J

H J

05 TYPICAL INSTALLATION 05

F_SB_254349_6_BCAA_03_01

Figure A-GBCAA - Sheet 03

Prepare the bonding points at the door posts

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 69

6

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@A340

SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

B

C

G

D

A

Z220

F_SB_254349_6_BCAB_01_00

Figure A-GBCAB - Sheet 01

Prepare the bonding points at the door posts

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 70

6

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@A340

SERVICE BULLETIN

**CONF 002

AFTER

1

02

03

F

(1)

BEFORE

NOTE:

02 REMOVE SURFACE PROTECTION TO A DIA APPROX.

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

03 APPLY VARNISH (MATERIAL NO.04TMB2).

RH SIDE 05 TYPICAL INSTALLATION.

FWD C

LH SIDE

D

E

E F

E F

18

SB25−4349

18

SB25−4349

FWD

05

05

F_SB_254349_6_BCAB_02_02

Figure A-GBCAB - Sheet 02

Prepare the bonding points at the door posts

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 71

6

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@A340

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

DIA APPROX. 3.0 mm (0.12 in)

G

H

J

H J

05 TYPICAL INSTALLATION 05

F_SB_254349_6_BCAB_03_01

Figure A-GBCAB - Sheet 03

Prepare the bonding points at the door posts

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 72

6

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@A340

SERVICE BULLETIN

**CONF 001, 003

FR11

FR16A

B

A

C

B

A

Z220

F_SB_254349_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

Install the bracket at the pelmet

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 73

6

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@A340

SERVICE BULLETIN

**CONF 001, 003

C

D

7

18 SB25−4349

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_254349_6_BBAA_02_00

Figure A-GBBAA - Sheet 02

Install the bracket at the pelmet

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 74

6

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SERVICE BULLETIN

**CONF 001, 003

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_254349_6_BBAA_03_00

Figure A-GBBAA - Sheet 03

Install the bracket at the pelmet

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 75

6

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SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

C

B

A

Z220

F_SB_254349_6_BBAB_01_00

Figure A-GBBAB - Sheet 01

Install the bracket at the pelmet

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 76

6

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@A340

SERVICE BULLETIN

**CONF 002

C

D

7

18 SB25−4349

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_254349_6_BBAB_02_00

Figure A-GBBAB - Sheet 02

Install the bracket at the pelmet

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 77

6

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@A340

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_254349_6_BBAB_03_00

Figure A-GBBAB - Sheet 03

Install the bracket at the pelmet

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 78

6

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@A340

SERVICE BULLETIN

**CONF 001 thru 002

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

E

C

F_SB_254349_6_BEAA_01_01

Figure A-GBEAA - Sheet 01

Prepare the bonding points at the webs

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 79

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

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 SB25−4349

C

D

RH DOOR POST

F_SB_254349_6_BEAA_02_02

Figure A-GBEAA - Sheet 02

Prepare the bonding points at the webs

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 80

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 002

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 SB25−4349

F_SB_254349_6_BEAA_03_02

Figure A-GBEAA - Sheet 03

Prepare the bonding points at the webs

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 81

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

FR11

FR16A

B

A

B

FR11

FR11A

A E

Z220

C

F_SB_254349_6_BEAC_01_01

Figure A-GBEAC - Sheet 01

Prepare the bonding points at the webs

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 82

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

C

12.0 mm

(0.47 in)

FR11A

D FWD

FR11

5.1mm DIA

(0.20 in)

17.0 mm DIA

(0.70 in)

10.0 mm

(0.39 in)

18 SB25−4349

D

RH DOOR POST

F_SB_254349_6_BEAC_02_01

Figure A-GBEAC - Sheet 02

Prepare the bonding points at the webs

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 83

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

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 SB25−4349

F_SB_254349_6_BEAC_03_01

Figure A-GBEAC - Sheet 03

Prepare the bonding points at the webs

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 84

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

C L

J

K

F_SB_254349_6_BDAA_01_01

Figure A-GBDAA - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 85

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001

C

D

E F

D

G H

F_SB_254349_6_BDAA_02_00

Figure A-GBDAA - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 86

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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_254349_6_BDAA_03_00

Figure A-GBDAA - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 87

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001

AFTER

BEFORE

(1)

9

13

16

14

10

19

22

20

21

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. F_SB_254349_6_BDAA_04_01

Figure A-GBDAA - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 88

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001

13

12 01

11

J

15

16

13

12

LH DOOR POST

K

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

RH DOOR POST

01 15

F_SB_254349_6_BDAA_05_01

Figure A-GBDAA - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 89

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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_254349_6_BDAA_06_01

Figure A-GBDAA - Sheet 06

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 90

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

C L

J

K

F_SB_254349_6_BDAB_01_01

Figure A-GBDAB - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 91

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002

C

D

E F

D

G H

F_SB_254349_6_BDAB_02_00

Figure A-GBDAB - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 92

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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_254349_6_BDAB_03_00

Figure A-GBDAB - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 93

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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_254349_6_BDAB_04_01

Figure A-GBDAB - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 94

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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_254349_6_BDAB_05_01

Figure A-GBDAB - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 95

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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_254349_6_BDAB_06_01

Figure A-GBDAB - Sheet 06

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 96

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

FR11

FR16A

B

A

A

Z220

B

FR11

FR11A

C L

J

K

F_SB_254349_6_BDAC_01_01

Figure A-GBDAC - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 97

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

C

D

E F

D

G H

F_SB_254349_6_BDAC_02_00

Figure A-GBDAC - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 98

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

AFTER

9

13

17

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_254349_6_BDAC_03_00

Figure A-GBDAC - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 99

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

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_254349_6_BDAC_04_01

Figure A-GBDAC - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 100

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

15

16

13

12

LH DOOR POST

K

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

13

12 01

17

J

RH DOOR POST

01 15

F_SB_254349_6_BDAC_05_02

Figure A-GBDAC - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 101

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

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_254349_6_BDAC_06_00

Figure A-GBDAC - Sheet 06

Install the bonding-leads at the upper door frame

DATE: May 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 102

6

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@A340

SERVICE BULLETIN

REPORTING SHEET

TITLE: EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

MODIFICATION No.: 203228D50684 204312D50883

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 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 1

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@A340

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 28/14 SERVICE BULLETIN No.: A340-25-4349

REVISION No.: 02 - Sep 04/15 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.