# @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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 25 

### TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT INSTRUMENT PANEL BRACKET 6. MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A340-25-4351 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 01 issued to: - add Service Bulletin No A340-25-4354 as terminating solution, - update the effectivity, - and minor changes. CHANGES SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED R

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 1 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
REASON Objective/Action OBJECTIVE/ACTION UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Procurement Addresses PROCUREMENT ADDRESSES UPDATED MATERIAL SET UPDATED R LIST OF MATERIALS - OPERATOR SUPPLIED Components COMPONENTS UPDATED R Component COMPA03 PART MATERIAL SET UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED KEYWORD UPDATED R

Component COMPA04 PART MATERIAL SET UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED KEYWORD UPDATED R

Component COMPA05 PART MATERIAL SET UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED KEYWORD UPDATED R

Component COMPA07 PART MATERIAL SET DELETED D ACCOMPLISHMENT INSTRUCTIONS TASK 254351- 832-801-001-Inspection. Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED REFERENCES UPDATED R

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 2 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED REFERENCES UPDATED R

Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED REFERENCES UPDATED R

Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED REFERENCES UPDATED R
TASK 254351- 833-801-001-Replace Bracket No. 6. Subtask 254351-833-001-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED KEYWORD UPDATED PART NUMBER DESCRIPTION UPDATED MATERIAL LIST UPDATED R

Subtask 254351-833-001-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED KEYWORD UPDATED PART NUMBER DESCRIPTION UPDATED MATERIAL LIST UPDATED R

Subtask 254351-833-001-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED KEYWORD UPDATED PART NUMBER DESCRIPTION UPDATED MATERIAL LIST UPDATED R

Subtask 254351-833-001-004 SUBTASK SOLUTION UPDATED R TASK 254351- 833-802-001-Replace Bracket No. 7. Subtask 254351-833-002-001 SUBTASK SOLUTION UPDATED ITEM NUMBER UPDATED R

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 3 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 254351-833-002-002 SUBTASK SOLUTION UPDATED ITEM NUMBER UPDATED R Subtask 254351-833-002-003 SUBTASK SOLUTION UPDATED ITEM NUMBER UPDATED R Subtask 254351-833-002-004 SUBTASK SOLUTION UPDATED ITEM NUMBER UPDATED MATERIAL LIST UPDATED R Fig. A-FBBAA Fig. A-FBBAA Sheet 02 SHEET UPDATED R Fig. A-FBBAA Sheet 03 SHEET UPDATED R Fig. A-FBBAC Fig. A-FBBAC Sheet 02 SHEET UPDATED R Fig. A-FBBAC Sheet 03 SHEET UPDATED R Fig. A-FBBAD Fig. A-FBBAD Sheet 02 SHEET UPDATED R Fig. A-FBBAD Sheet 03 SHEET UPDATED R Fig. A-FBDAA Fig. A-FBDAA Sheet 02 SHEET UPDATED R Fig. A-FBDAB Fig. A-FBDAB Sheet 02 SHEET UPDATED R Fig. A-FBDAC Fig. A-FBDAC Sheet 02 SHEET UPDATED R Fig. A-FFAAA Fig. A-FFAAA Sheet 01 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 No previous revision REVISION SEQUENCE ORIGINAL: Sep 10/13 REVISION No. : 01 - Jan 31/14

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 4 5

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# @A340 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. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 25 

### TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT INSTRUMENT PANEL BRACKET 6. **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During flight tests carried out with A340-600, high stress level were measured on the bracket No. 6 (PN F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000 Post Mod No. 55128S18242), which is one of the 8 parts used to attach the cockpit instrument panel to the aircraft structure. This is linked to a coupling between the vibration levels due to the bumps of the runways and introduced through the Nose Landing Gear (NLG), and the cockpit panel. Using accelerations introduced at pilot seat location, the bracket No. 6 cannot sustain any fatigue loads of the Long Range Design Service Goal (DSG). Accomplishment of this Inspection Service Bulletin is no longer necessary in the case of Service Bulletin A340-25-4354 has been embodied. This inspection Service Bulletin requires performing a detailed inspection before 17,200 Flight Cycles (FC) of the bracket No. 6 PN F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000 Post Mod No. 55128S18242 of the Cockpit Instrument Panel. Depending on the results of this inspection, this Service Bulletin is issued to give the relevant corrective action. Accomplishment of this Service Bulletin will prevent the risk of having the Bracket No. 6 fully broken and, consequently, further damage on the surrounding structure. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 1 5

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# @A340 SERVICE BULLETIN SUMMARY EVALUATION TABLE 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. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPA01 2 See SB Bracket Component COMPA03 1 See SB Fastening Component COMPA08 1 See SB Fastening **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPA01 2 See SB Bracket Component COMPA04 1 See SB Fastening Component COMPA09 1 See SB Fastening **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPA01 2 See SB Bracket Component COMPA05 1 See SB Fastening Component COMPA10 1 See SB Fastening **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPA01 1 See SB Bracket Component COMPA02 1 See SB Bracket Component COMPA06 1 See SB Fastening Component COMPA10 1 See SB Fastening

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 2 5

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# @A340 SERVICE BULLETIN SUMMARY EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

15R 15T 56W 58X 83V ABD ABQ AFR AIB ALK ARG CAL CCA CPA DGA DLH FIN GAF GFA HFY IBE IRC IRM KAC LAN M3R MAU MDG MSR NMB OAL PAL QAF RJA S3R SAA SAS SFB SLM SVW SWR TAP THT THY UAE VCV VIR XAX CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 254351-832-801-001: Inspection. TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 3 5

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# @A340 SERVICE BULLETIN SUMMARY **CONF 002 Task 254351-832-801-001: Inspection. TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 003 Task 254351-832-801-001: Inspection. TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 004 Task 254351-832-801-001: Inspection. TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 APPENDICES **CONF ALL None DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 4 5

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# @A340 SERVICE BULLETIN SUMMARY

**CONF ALL

TO BE INSPECTED 

### A



## A TO BE INSPECTED BRACKET No 6 BRACKET No 7

F_SB_254351_5_SAAA_01_01 Figure A-FSAAA - Sheet 01
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 5 5

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# @A340 SERVICE BULLETIN SUMMARY

This Page Intentionally Left Blank

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 6 5

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# @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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 25 

### TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT INSTRUMENT PANEL BRACKET 6. MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models 340-211 340-212 340-213 340-311 340-312 340-313 (2) Effectivity by MSN 0002 0004 0006 0009 0011 0013-0014 0018-0020 0022-0029 0031-0035 0038 0041 0043-0044 0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081 0084-0085 0088-0091 0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128 0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164 0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199 0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225 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: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 1 5

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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 15R 0151 15T 0009 56W 0011 0013 0018 0019 58X 0004 83V 0133 ABD 0210 ABQ 0216 0257 AFR 0029 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399 AIB 0131 0141 0161 0182 ALK 0032 0033 0034 0367 0374 0381 ARG 0048 0063 0074 0080 0085 0093 0094 0123 0126 0128 0170 0193 0373 CAL 0402 0406 0411 0415 0433 0541 CCA 0192 0199 0201 0242 0243 0264 CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228 DGA 0075 0081 DLH 0024 0027 0028 0035 0052 0053 0135 0158 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447 FIN 0058 0168 0174 0835 0844 0921 0938 GAF 0274 0355 GFA 0212 0215 0282 0554 HFY 0117 0190 0202 IBE 0088 0125 0134 0145 0146 0217 0221 0329 0414 0459 0474 0483 IRC 0002 IRM 0020 0056 KAC 0089 0090 0101 0104 LAN 0359 0363 0429 0442 M3R 0061 MAU 0076 0152 0194 0268 0793 0800 MDG 0319 MSR 0156 0159 0178 NMB 0047 0051 OAL 0280 0292 PAL 0173 0176 0187 0196 0302 0318 0332 0387 QAF 0026 0528 RJA 0014 0022 0038 0043 S3R 0204 SAA 0006 0197 0378 0544 0582 0590 0643 0646 0651 SAS 0167 0413 0424 0430 0435 0450 0467 0470 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 2 5

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# @A340 SERVICE BULLETIN

OPERATOR MSN 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 0139 0149 0163 0166 0185 0236 VCV 0031 VIR 0114 0164 0214 0225 XAX 0273 0278 (4) Configuration by MSN MSN CONFIGURATION 0002 0004 0006 0009 0011 0013 0014 0018 0019 0020 0022 0023 0024 0025 0026 0027 0028 0029 0031 0032 0033 0034 0035 0038 0041 0043 0044 0046 0047 0048 0049 0051 0052 0053 0056 0057 0058 0061 0063 0074 0075 0076 0078 0079 0080 0081 0084 0085 0088 0089 0090 0091 0093 0094 0101 0104 0114 0115 0117 0123 0125 0126 0128 0131 0133 0134 0135 0136 0137 0139 0141 0142 0145 0146 0147 0149 0150 0151 0152 0154 0156 0157 0158 0159 0160 0161 0163 0164 0166 0167 0168 0169 0170 0173 0174 0175 0176 0178 0179 0180 0182 0185 001

0186 0187 0190 0192 0193 0194 0196 0197 0199 0201 0202 0204 0207 0208 0210 0212 0213 0214 0215 0216 0217 0218 0220 0221 0225 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 0378 0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0414 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 002

0668 0793 0800 0835 0844 003 0921 0938 0955 004 (5) Configuration definition **CONF 001 Config. 001 is valid for aircraft on which Mod. No. 45411S13604 , Mod. No. 53446S18217 and Mod. No. 55128S18242 are not embodied. **CONF 002 Config. 002 is valid for aircraft on which Mod. No. 45411S13604 is embodied and Mod. No. 53446S18217 and Mod. No. 55128S18242 are not embodied.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 3 5

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# @A340 SERVICE BULLETIN
**CONF 003 Config. 003 is valid for aircraft on which Mod. No. 45411S13604 and Mod. No. 53446S18217 are embodied and Mod. No. 55128S18242 is not embodied. **CONF 004 Config. 004 is valid for aircraft on which Mod. No. 45411S13604 , Mod. No. 53446S18217 and Mod. No. 55128S18242 are embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Component COMPA01 2 Component COMPA03 1 Consumable CMLA01 1 Component COMPA08 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Component COMPA01 2 Component COMPA04 1 Consumable CMLA01 1 Component COMPA09 1 **CONF 003 MATERIAL QTY PER A/C SEE NOTES Component COMPA01 2 Component COMPA05 1 Consumable CMLA01 1 Component COMPA10 1 **CONF 004 MATERIAL QTY PER A/C SEE NOTES Component COMPA01 1 Component COMPA02 1 Component COMPA06 1 Consumable CMLA01 1 Component COMPA10 1 **CONF ALL B. CONCURRENT REQUIREMENTS None
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 4 5

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# @A340 SERVICE BULLETIN
C. REASON (1) History During flight tests carried out with A340-600, high stress level were measured on the bracket No. 6 (PN F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000 Post Mod No. 55128S18242), which is one of the 8 parts used to attach the cockpit instrument panel to the aircraft structure. This is linked to a coupling between the vibration levels due to the bumps of the runways and introduced through the Nose Landing Gear (NLG), and the cockpit panel. Using accelerations introduced at pilot seat location, the bracket No. 6 cannot sustain any fatigue loads of the Long Range Design Service Goal (DSG). (2) Objective/Action Accomplishment of this Inspection Service Bulletin is no longer necessary in the case of Service Bulletin A340-25-4354 has been embodied. This inspection Service Bulletin requires performing a detailed inspection before 17,200 Flight Cycles (FC) of the bracket No. 6 PN F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000 Post Mod No. 55128S18242 of the Cockpit Instrument Panel. Depending on the results of this inspection, this Service Bulletin is issued to give the relevant corrective action. (3) Advantages Accomplishment of this Service Bulletin will prevent the risk of having the Bracket No. 6 fully broken and, consequently, further damage on the surrounding structure. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 254351-832-801-001: Inspection. (1) Do a Detailed Inspection of the Bracket No. 6. (2) Do a Detailed Inspection of the Bracket No. 7. (3) Install/Close Items Removed/Opened for access. Task 254351-833-801-001: Replace Bracket No. 6. (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 5 5

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# @A340 SERVICE BULLETIN Task 254351-833-802-001: Replace Bracket No. 7. (1) Replace the Bracket No. 7 (2) Install/Close Items Removed/Opened for access **CONF 002 Task 254351-832-801-001: Inspection. (1) Do a Detailed Inspection of the Bracket No. 6. (2) Do a Detailed Inspection of the Bracket No. 7. (3) Install/Close Items Removed/Opened for access. Task 254351-833-801-001: Replace Bracket No. 6. (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access Task 254351-833-802-001: Replace Bracket No. 7. (1) Replace the Bracket No. 7 (2) Install/Close Items Removed/Opened for access **CONF 003 Task 254351-832-801-001: Inspection. (1) Do a Detailed Inspection of the Bracket No. 6. (2) Do a Detailed Inspection of the Bracket No. 7. (3) Install/Close Items Removed/Opened for access. Task 254351-833-801-001: Replace Bracket No. 6. (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access Task 254351-833-802-001: Replace Bracket No. 7. (1) Replace the Bracket No. 7 (2) Install/Close Items Removed/Opened for access

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 6 5

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# @A340 SERVICE BULLETIN
**CONF 004 Task 254351-832-801-001: Inspection. (1) Do a Detailed Inspection of the Bracket No. 6. (2) Do a Detailed Inspection of the Bracket No. 7. (3) Install/Close Items Removed/Opened for access. Task 254351-833-801-001: Replace Bracket No. 6. (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access Task 254351-833-802-001: Replace Bracket No. 7. (1) Replace the Bracket No. 7 (2) Install/Close Items Removed/Opened for access **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

All aircraft Do a detailed inspection of the bracket No. 6 (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC from aircraft first flight 500 FC See Note* None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 7 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) None None 2,600 FC

OR Implement Service Bulletin No. A340-25-4354 as terminative solution. 2600 FC None None
OR Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND No crack found

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Crack found and both bracket lugs are not fully broken

Implement Service Bulletin No. A340-25-4354 as terminative solution. 2,600 FC None None
Crack found and both bracket lugs fully broken Do a detailed inspection of the bracket No. 7 (Refer to SUBTASK 254351-700-004 001 Do a Detailed Inspection of the Bracket No. 7. ) Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 8 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) and replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND No crack found on bracket No. 7

Implement Service Bulletin No. A340-25-4354 as terminative solution. Before next flight None None
Crack found on bracket No. 7 Contact AIRBUS Before next flight None None Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500 FC from SB first issuance date Table 1 - Do a detailed inspection of the Bracket No. 6.
**CONF 002 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

All aircraft Do a detailed inspection of the bracket No. 6 (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC from aircraft first flight 500 FC See Note* None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 9 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) None None 2,600 FC

OR Implement Service Bulletin No. A340-25-4354 as terminative solution. 2600 FC None None
OR Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND No crack found

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Crack found and both bracket lugs are not fully broken

Implement Service Bulletin No. A340-25-4354 as terminative solution. 2,600 FC None None
Crack found and both bracket lugs fully broken Do a detailed inspection of the bracket No. 7 (Refer to SUBTASK 254351-700-004 001 Do a Detailed Inspection of the Bracket No. 7. ) Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 10 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) and replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND No crack found on bracket No. 7

Implement Service Bulletin No. A340-25-4354 as terminative solution. Before next flight None None
Crack found on bracket No. 7 Contact AIRBUS Before next flight None None Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500 FC from SB first issuance date Table 1 - Do a detailed inspection of the Bracket No. 6.
**CONF 003 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

All aircraft Do a detailed inspection of the bracket No. 6 (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC from aircraft first flight 500 FC See Note* None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 11 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) None None 2,600 FC

OR Implement Service Bulletin No. A340-25-4354 as terminative solution. 2600 FC None None
OR Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND No crack found

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Crack found and both bracket lugs are not fully broken

Implement Service Bulletin No. A340-25-4354 as terminative solution. 2,600 FC None None
Crack found and both bracket lugs fully broken Do a detailed inspection of the bracket No. 7 (Refer to SUBTASK 254351-700-004 001 Do a Detailed Inspection of the Bracket No. 7. ) Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 12 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) and replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND No crack found on bracket No. 7

Implement Service Bulletin No. A340-25-4354 as terminative solution. Before next flight None None
Crack found on bracket No. 7 Contact AIRBUS Before next flight None None Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500 FC from SB first issuance date Table 1 - Do a detailed inspection of the Bracket No. 6.
**CONF 004 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

All aircraft Do a detailed inspection of the bracket No. 6 (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC from aircraft first flight 500 FC See Note* None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 13 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) None None 2,600 FC

OR Implement Service Bulletin No. A340-25-4354 as terminative solution. 2600 FC None None
OR Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND No crack found

Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) Within 2,600 FC after inspection None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Crack found and both bracket lugs are not fully broken

Implement Service Bulletin No. A340-25-4354 as terminative solution. 2,600 FC None None
Crack found and both bracket lugs fully broken Do a detailed inspection of the bracket No. 7 (Refer to SUBTASK 254351-700-004 001 Do a Detailed Inspection of the Bracket No. 7. ) Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 14 5

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# @A340 SERVICE BULLETIN
Compliance (whichever occurs later) Condition Action Threshold Grace period from SB first issuance date Repetitive interval

Replace the bracket No. 6 (Refer to TASK 254351-833-801 001 Replace Bracket No. 6. ) and replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND Do a detailed inspection of the bracket No. 6 again (Refer to TASK 254351-832-801 001 Inspection. ) 17,200 FC None None

OR Replace the bracket No. 7 (Refer to TASK 254351-833-802 001 Replace Bracket No. 7. ) Before next flight None None

AND No crack found on bracket No. 7

Implement Service Bulletin No. A340-25-4354 as terminative solution. Before next flight None None
Crack found on bracket No. 7 Contact AIRBUS Before next flight None None Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500 FC from SB first issuance date Table 1 - Do a detailed inspection of the Bracket No. 6.
**CONF ALL F. APPROVAL The technical content of this document is approved under the authority of Design Organization 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.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 15 5

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# @A340 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 254351-832-801-001: Inspection. Get Access 2.50 On Aircraft Do a Detailed Inspection of the Bracket No. 6. 1.00 Do a Detailed Inspection of the Bracket No. 7. 1.00 Install/Close Items Removed/Opened for access. 0.50 Close-Up 2.50 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 Close-Up 2.50 TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. Get Access 2.50 On Aircraft Replace the Bracket No. 7 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 Close-Up 2.50 TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 002 Task 254351-832-801-001: Inspection. Get Access 2.50 On Aircraft Do a Detailed Inspection of the Bracket No. 6. 1.00 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 16 5

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# @A340 SERVICE BULLETIN
Task 254351-832-801-001: Inspection. Do a Detailed Inspection of the Bracket No. 7. 1.00 Install/Close Items Removed/Opened for access. 0.50 Close-Up 2.50 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 Close-Up 2.50 TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. Get Access 2.50 On Aircraft Replace the Bracket No. 7 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 Close-Up 2.50 TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 003 Task 254351-832-801-001: Inspection. Get Access 2.50 On Aircraft Do a Detailed Inspection of the Bracket No. 6. 1.00 Do a Detailed Inspection of the Bracket No. 7. 1.00 Install/Close Items Removed/Opened for access. 0.50 Close-Up 2.50 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 17 5

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# @A340 SERVICE BULLETIN
Task 254351-833-801-001: Replace Bracket No. 6. Close-Up 2.50 TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. Get Access 2.50 On Aircraft Replace the Bracket No. 7 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 Close-Up 2.50 TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 004 Task 254351-832-801-001: Inspection. Get Access 2.50 On Aircraft Do a Detailed Inspection of the Bracket No. 6. 1.00 Do a Detailed Inspection of the Bracket No. 7. 1.00 Install/Close Items Removed/Opened for access. 0.50 Close-Up 2.50 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 Task 254351-833-801-001: Replace Bracket No. 6. Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 Close-Up 2.50 TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 Task 254351-833-802-001: Replace Bracket No. 7. Get Access 2.50 On Aircraft Replace the Bracket No. 7 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 4.00 Close-Up 2.50 TOTAL MANHOURS 11.50 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 18 5

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# @A340 SERVICE BULLETIN
Task 254351-833-802-001: Replace Bracket No. 7. ELAPSED TIME (HOURS) 11.50 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24 21-26-00 22-96-00 22-97-00 24-41-00 25-11-51 31-50-00 31-60-00 31-63-22 33-12-13 33-13-00 33-14-00 52-10-00 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 Service Bulletin (SB) A340-25-4354 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 **CONF 002 Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24 21-26-00 22-96-00 22-97-00 24-41-00 25-11-51 31-50-00 31-60-00 31-63-22 33-12-13 33-13-00 33-14-00 52-10-00 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 Service Bulletin (SB) A340-25-4354 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 **CONF 003 Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24 21-26-00 22-96-00 22-97-00 24-41-00 25-11-51 31-50-00 31-60-00 31-63-22 33-12-13 33-13-00 33-14-00 52-10-00 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 Service Bulletin (SB) A340-25-4354 Standards Manual (SM)
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 19 5

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# @A340 SERVICE BULLETIN Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 **CONF 004 Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24 21-26-00 22-96-00 22-97-00 24-41-00 25-11-51 31-50-00 31-60-00 31-63-22 33-12-13 33-13-00 33-14-00 52-10-00 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 Service Bulletin (SB) A340-25-4354 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 **CONF ALL K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 25-14-01 Impact on Scheduled maintenance: Refer to MPD L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 20 5

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# @A340 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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 COMPA01 Component COMPA02 AIRBUS Material, Logistic and Supplier 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 AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive multiple suppliers ensure access to minimum prices AIRBUS recommends Customers with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to B/E Aerospace. The address is: Component COMPA03 Component COMPA04 Component COMPA05 Component COMPA06 Component COMPA08 Component COMPA09 Component COMPA10 B/E AEROSPACE INC. CONSUMABLES MANAGEMENT 10000 NW 15th Terrace Miami FL 33172 Tel EMEA: +49 (0) 40 822 285 31500 Tel US: +1 305 925 2600 Tel ASIA: +1 310 900 1300 Fax EMEA: +49 (0) 40 822 285 31010 Fax US: +1 305 507 7191 Fax ASIA: +1 310 819 1200 SITA: MIAMMCR E-Mail: AOGdesk_CMG@beaerospace.com internet: http://www.beconsumables.com or, alternatively any other source on the open market (2) Price and Availability No AIRBUS kit will be provided. Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be purchased by a spares purchase order. Operator supplied standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 21 5

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# @A340 SERVICE BULLETIN
B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESSynthetic Ester Base GreaseGeneral Purpose Low T 03HBD9 As required (2) Components Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 16 F2511012820095 1 BRACKET (16) F2511012820000 NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 6 F2511373420095 1 BRACKET (6) F2511373420000 NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 7 NAS6604-10 1 BOLT 8 NAS1726-4E 1 NUT 11 ASNA2050DCJ3215 3 RIVET 15 ASNA2050DEJ4020 4 RIVET 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.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 22 5

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# @A340 SERVICE BULLETIN
NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 11 ASNA2050DCJ3215 3 RIVET 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 20 MS24665-134 1 PIN 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: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 11 ASNA2050DCJ3215 3 RIVET 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 21 MS24665-71 1 PIN 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: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA06 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 EN6115V3-5 4 BOLT 10 ASNA2531-3 4 NUT 11 ASNA2050DCJ3215 3 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 23 5

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# @A340 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 21 MS24665-71 1 PIN 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: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA08 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 7 NAS6604-10 1 BOLT 8 NAS1726-4E 1 NUT 15 ASNA2050DEJ4020 4 RIVET 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: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA09 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 20 MS24665-134 1 PIN 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: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA10 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 2 BOLT DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 24 5

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# @A340 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 21 MS24665-71 1 PIN 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: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 25 5

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# @A340 SERVICE BULLETIN

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DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 26 5

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# @A340 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 254351-832-801-001 - Inspection. WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the AIRBUS document must be used. 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. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 27 5

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# @A340 SERVICE BULLETIN
Task Associated Data **CONF 001 Zone 212 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 **CONF 002 Zone 212 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 **CONF 003 Zone 212 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 **CONF 004 Zone 212 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 254351-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 (a) For the identification of zones, refer to AMM 06-20-00, Page Block 001. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 28 5

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# @A340 SERVICE BULLETIN (b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001. (2) Subtask 254351-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 254351-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 (a) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001. (2) Subtask 254351-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 254351-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 (a) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001. (2) Subtask 254351-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 29 5

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# @A340 SERVICE BULLETIN Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 254351-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 (a) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001. (2) Subtask 254351-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 254351-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 52-10-00-010-801 (a) 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.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 30 5

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# @A340 SERVICE BULLETIN - 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position at the door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (2) Subtask 254351-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain **CONF 002 (1) Subtask 254351-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 31 5

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# @A340 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 52-10-00-010-801 (a) 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position at the door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (2) Subtask 254351-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 32 5

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# @A340 SERVICE BULLETIN (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain **CONF 003 (1) Subtask 254351-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 52-10-00-010-801 (a) 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position at the door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (2) Subtask 254351-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 33 5

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# @A340 SERVICE BULLETIN

References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain **CONF 004 (1) Subtask 254351-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 52-10-00-010-801 (a) 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.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 34 5

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# @A340 SERVICE BULLETIN - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position at the door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (2) Subtask 254351-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 35 5

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# @A340 SERVICE BULLETIN
Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 6. Refer to Fig. A-FBAAA Refer to Fig. A-FFAAA 1 If no crack is found:
a Do a detailed inspection of the bracket No. 6 at the interval given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection.
or b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2).
or c Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 36 5

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# @A340 SERVICE BULLETIN

2 If a crack is found and both bracket lugs are not fully broken:
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 3 If a crack is found and both bracket lugs are fully broken:
a Do a detailed inspection of the bracket No. 7. Refer to SUBTASK 254351-700-004 001 (b) Send inspection report to Airbus, refer to Fig. A-FRAAA

. (2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 7. Refer to Fig. A-FBAAA Refer to Fig. A-FFAAA

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 37 5

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# @A340 SERVICE BULLETIN

1 If no crack is found on the bracket No. 7.
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 2 If a crack is found on the bracket No. 7.
a Contact AIRBUS before next flight. (b) Send inspection report, refer to Fig. A-FRAAA

. (3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access. Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 38 5

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# @A340 SERVICE BULLETIN (a) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (b) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal **CONF 002 (1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 6. Refer to Fig. A-FBAAA DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 39 5

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# @A340 SERVICE BULLETIN
Refer to Fig. A-FFAAA 1 If no crack is found:
a Do a detailed inspection of the bracket No. 6 at the interval given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection.
or b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2).
or c Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. 2 If a crack is found and both bracket lugs are not fully broken:
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 3 If a crack is found and both bracket lugs are fully broken:
a Do a detailed inspection of the bracket No. 7. Refer to SUBTASK 254351-700-004 001 (b) Send inspection report to Airbus, refer to Fig. A-FRAAA

.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 40 5

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# @A340 SERVICE BULLETIN (2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 7. Refer to Fig. A-FBAAA Refer to Fig. A-FFAAA 1 If no crack is found on the bracket No. 7.
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 41 5

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# @A340 SERVICE BULLETIN Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 2 If a crack is found on the bracket No. 7.
a Contact AIRBUS before next flight. (b) Send inspection report, refer to Fig. A-FRAAA

. (3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access. Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (b) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 42 5

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# @A340 SERVICE BULLETIN
**CONF 003 (1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 6. Refer to Fig. A-FBAAA Refer to Fig. A-FFAAA 1 If no crack is found:
a Do a detailed inspection of the bracket No. 6 at the interval given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection.
or b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2).
or c Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 43 5

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# @A340 SERVICE BULLETIN Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. 2 If a crack is found and both bracket lugs are not fully broken:
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 3 If a crack is found and both bracket lugs are fully broken:
a Do a detailed inspection of the bracket No. 7. Refer to SUBTASK 254351-700-004 001 (b) Send inspection report to Airbus, refer to Fig. A-FRAAA

. (2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 7. Refer to Fig. A-FBAAA DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 44 5

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# @A340 SERVICE BULLETIN
Refer to Fig. A-FFAAA 1 If no crack is found on the bracket No. 7.
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 2 If a crack is found on the bracket No. 7.
a Contact AIRBUS before next flight. (b) Send inspection report, refer to Fig. A-FRAAA

. (3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access. Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 45 5

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# @A340 SERVICE BULLETIN (a) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (b) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal **CONF 004 (1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 6. Refer to Fig. A-FBAAA DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 46 5

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# @A340 SERVICE BULLETIN
Refer to Fig. A-FFAAA 1 If no crack is found:
a Do a detailed inspection of the bracket No. 6 at the interval given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection.
or b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2).
or c Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. 2 If a crack is found and both bracket lugs are not fully broken:
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 3 If a crack is found and both bracket lugs are fully broken:
a Do a detailed inspection of the bracket No. 7. Refer to SUBTASK 254351-700-004 001 (b) Send inspection report to Airbus, refer to Fig. A-FRAAA

.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 47 5

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# @A340 SERVICE BULLETIN (2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC References Service Bulletin (SB) A340-25-4354 Fig. A-FBAAA Area to be inspected Sheet 01 Sheet 02 Fig. A-FFAAA Flow-chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 At the threshold given in the PLANNING INFORMATION paragraph E.(2): (a) Do a detailed inspection of the bracket No. 7. Refer to Fig. A-FBAAA Refer to Fig. A-FFAAA 1 If no crack is found on the bracket No. 7.
a Replace the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001 Replace Bracket No. 6. and Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and Do a detailed inspection of the bracket No. 6 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-832-801 001 Inspection. OR b Replace the bracket No. 7 at the threshold given in the PLANNING INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001 Replace Bracket No. 7. and
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 48 5

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# @A340 SERVICE BULLETIN Implement Service Bulletin No. A340-25-4354 as terminative solution at the threshold given in the PLANNING INFORMATION paragraph E.(2). 2 If a crack is found on the bracket No. 7.
a Contact AIRBUS before next flight. (b) Send inspection report, refer to Fig. A-FRAAA

. (3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access. Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (b) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 49 5

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# @A340 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 254351-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. (b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (c) Remove the access platform. (d) Restore the systems and the aircraft to normal operation conditions. **CONF 002 (1) Subtask 254351-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 50 5

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# @A340 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. (b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (c) Remove the access platform. (d) Restore the systems and the aircraft to normal operation conditions. **CONF 003 (1) Subtask 254351-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. (b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (c) Remove the access platform. (d) Restore the systems and the aircraft to normal operation conditions. **CONF 004 (1) Subtask 254351-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. (b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 51 5

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# @A340 SERVICE BULLETIN (c) Remove the access platform. (d) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 52 5

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# @A340 SERVICE BULLETIN Task 254351-833-801-001 - Replace Bracket No. 6. **CONF ALL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 53 5

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# @A340 SERVICE BULLETIN
Task Associated Data **CONF 001 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 002 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 003 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 004 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 254351-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 54 5

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# @A340 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 254351-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 254351-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 55 5

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# @A340 SERVICE BULLETIN (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 254351-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 254351-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 56 5

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# @A340 SERVICE BULLETIN (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 254351-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 254351-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 57 5

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# @A340 SERVICE BULLETIN (2) Subtask 254351-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 254351-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 (a) 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 58 5

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# @A340 SERVICE BULLETIN (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU) (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. (g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B). (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors. (2) Subtask 254351-010-002-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 59 5

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# @A340 SERVICE BULLETIN
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. **CONF 002 (1) Subtask 254351-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 (a) 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.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 60 5

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# @A340 SERVICE BULLETIN - 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU) (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. (g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B).

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 61 5

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# @A340 SERVICE BULLETIN (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors. (2) Subtask 254351-010-002-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. **CONF 003 (1) Subtask 254351-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 62 5

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# @A340 SERVICE BULLETIN (a) 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU) (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. (g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 63 5

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# @A340 SERVICE BULLETIN (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B). (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors. (2) Subtask 254351-010-002-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 64 5

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# @A340 SERVICE BULLETIN
**CONF 004 (1) Subtask 254351-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 (a) 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU) (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. (g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 65 5

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# @A340 SERVICE BULLETIN - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B). (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors. (2) Subtask 254351-010-002-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 66 5

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# @A340 SERVICE BULLETIN
1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 254351-833-001-001 - Replace the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 F2511012820095 1 BRACKET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NAS6604-10 1 BOLT 8 NAS1726-4E 1 NUT 11 ASNA2050DCJ3215 3 RIVET 15 ASNA2050DEJ4020 4 RIVET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 67 5

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# @A340 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBBAA Replacement of the bracket No. 6 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the bracket No. 6. Refer to Fig. A-FBBAA In accordance with SRM 51-42-00 1 Remove: 1 Screw Item (7) Discard 1 Nut Item (8) Discard 2 Remove the rivets: - Remove the head of the four rivets. - Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in). 2 Rivet Item (15) Discard 2 Rivet Item (14) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBBAA In accordance with SRM 51-42-00 and SRM 51-44-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 68 5

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# @A340 SERVICE BULLETIN

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a If necessary, remove: 3 Rivets Item (11) Discard b Mark the position of the hole of the upper bracket on the new bracket.
c If removed, install: 3 Rivet ASNA2050DCJ3215 Item 11 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in). 3 Put in position the new bracket item 16 with the bolt item 7. Install: 1 Bracket F2511012820095 Item 16 1 Bolt NAS6604-10 Item 7 NOTE: Install the bolt item 7 with: Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper bracket as shown in Fig. A-FBBAA Sheet 04
a Check that the minimum clearances are 0.35 mm (0.026 in) at LHS and 0.65 mm (0.014 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure. 6 Install: 4 Rivet ASNA2050DEJ4020 Item 15 7 Install the nut item 8: 1 Nut NAS1726-4E Item 8 NOTE: Torque the nut item 8 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in).

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 69 5

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# @A340 SERVICE BULLETIN (2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal **CONF 002 (1) Subtask 254351-833-001-002 - Replace the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 70 5

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# @A340 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 F2511012820095 1 BRACKET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 11 ASNA2050DCJ3215 3 RIVET 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 20 MS24665-134 1 PIN NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBBAC Replacement of the bracket No. 6 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the bracket No. 6. Refer to Fig. A-FBBAC In accordance with SRM 51-42-00
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 71 5

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# @A340 SERVICE BULLETIN

1 Remove: 1 Axis Item (17) Discard 1 Nut Item (18) Discard 1 Washer Item (19) Discard 1 Pin Item (20) Discard 2 Remove the rivets: - Remove the head of the four rivets. - Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in). 2 Rivet Item (15) Discard 2 Rivet Item (14) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBBAC In accordance with SRM 51-42-00 and SRM 51-44-00 1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a If necessary, remove: 3 Rivets Item (11) Discard b Mark the position of the hole of the upper bracket on the new bracket.
c If removed, install: 3 Rivet ASNA2050DCJ3215 Item 11 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in). 3 Put in position the new bracket item 16 with the bolt item 17. Install: 1 Bracket F2511012820095 Item 16
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 72 5

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# @A340 SERVICE BULLETIN

1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper bracket as shown in Fig. A-FBBAC Sheet 04
a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and 0.65 mm (0.026 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure. 6 Install: 4 Rivet ASNA2050DEJ4020 Item 15 7 Install the nut item 18: 1 Nut NSA5060-3 Item 18 1 Washer NSA5325-3 Item 19 1 Pin-Cotter MS24665-134 Item 20 NOTE: Torque the nut item 18 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in). (2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 73 5

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# @A340 SERVICE BULLETIN (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal **CONF 003 (1) Subtask 254351-833-001-003 - Replace the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 F2511012820095 1 BRACKET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 11 ASNA2050DCJ3215 3 RIVET DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 74 5

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# @A340 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 21 MS24665-71 1 PIN NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBBAD Replacement of the bracket No. 6 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the bracket No. 6. Refer to Fig. A-FBBAD In accordance with SRM 51-42-00 1 Remove: 1 Axis Item (17) Discard 1 Nut Item (18) Discard 1 Washer Item (19) Discard 1 Pin Item (21) Discard 2 Remove the rivets: - Remove the head of the four rivets. - Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in). 2 Rivet Item (15) Discard DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 75 5

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# @A340 SERVICE BULLETIN
2 Rivet Item (14) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBBAD In accordance with SRM 51-42-00 and SRM 51-44-00 1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a If necessary, remove: 3 Rivets Item (11) Discard b Mark the position of the hole of the upper bracket on the new bracket.
c If removed, install: 3 Rivet ASNA2050DCJ3215 Item 11 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in). 3 Put in position the new bracket item 16 with the bolt item 17. Install: 1 Bracket F2511012820095 Item 16 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper bracket as shown in Fig. A-FBBAD Sheet 04

. a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and 0.65 mm (0.026 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure. 6 Install: 4 Rivet ASNA2050DEJ4020 Item 15 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 76 5

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# @A340 SERVICE BULLETIN

7 Install the nut item 18: 1 Nut NSA5060-3 Item 18 1 Washer NSA5325-3 Item 19 1 Pin-Cotter MS24665-71 Item 21 NOTE: Torque the nut item 18 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in). (2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 77 5

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# @A340 SERVICE BULLETIN
**CONF 004 (1) Subtask 254351-833-001-004 - Replace the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 6 F2511373420095 1 BRACKET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA06 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 EN6115V3-5 4 BOLT 10 ASNA2531-3 4 NUT 11 ASNA2050DCJ3215 3 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 21 MS24665-71 1 PIN NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 78 5

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# @A340 SERVICE BULLETIN

References Fig. A-FBBAB Replacement of the bracket No. 6 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the bracket No. 6. Refer to Fig. A-FBBAB In accordance with SRM 51-42-00 1 Remove: 1 Axis Item (17) Discard 1 Nut Item (18) Discard 1 Washer Item (19) Discard 1 Pin Item (21) Discard 2 Remove the fasteners: 4 Bolt Item (9) Discard 4 Nut Item (10) Discard 3 Remove the bracket: 1 Bracket F2511373420000 Item (6) Discard (b) Install the new bracket. Refer to Fig. A-FBBAB In accordance with SRM 51-42-00 and SRM 51-44-00 1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a If necessary, remove: 3 Rivets Item (11) Discard b Mark the position of the hole of the upper bracket on the new bracket.
c If removed, install: 3 Rivet ASNA2050DCJ3215 Item 11 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in).
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 79 5

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# @A340 SERVICE BULLETIN
3 Put in position the new bracket item 6 with the bolt item 17. Install: 1 Bracket F2511373420095 Item 6 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 6 and the upper bracket as shown in Fig. A-FBBAB Sheet 04

. a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and 0.65 mm (0.026 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure. 6 Install: 4 Bolt EN6115V3-5 Item 9 4 Nut ASNA2531-3 Item 10 7 Install the nut item 18: 1 Nut NSA5060-3 Item 18 1 Washer NSA5325-3 Item 19 1 Pin-Cotter MS24665-71 Item 21 NOTE: Torque the nut item 18 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in). (2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 80 5

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# @A340 SERVICE BULLETIN

References Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal **CONF ALL D. TEST **CONF 001 (1) Subtask 254351-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 81 5

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# @A340 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801. 1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 82 5

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# @A340 SERVICE BULLETIN
3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. 8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801. **CONF 002 (1) Subtask 254351-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT, DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 83 5

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# @A340 SERVICE BULLETIN - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801. 1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. 3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. 8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 84 5

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# @A340 SERVICE BULLETIN
**CONF 003 (1) Subtask 254351-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 85 5

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# @A340 SERVICE BULLETIN

1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. 3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. 8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801. **CONF 004 (1) Subtask 254351-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 86 5

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# @A340 SERVICE BULLETIN

References Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801. 1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. 3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 87 5

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# @A340 SERVICE BULLETIN
8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801. **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 254351-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801. 2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 88 5

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# @A340 SERVICE BULLETIN
**CONF 002 (1) Subtask 254351-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801. 2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions. **CONF 003 (1) Subtask 254351-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 89 5

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# @A340 SERVICE BULLETIN (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801. 2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions. **CONF 004 (1) Subtask 254351-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish an associated Repair Task during the same layover period, the subsequent Close-up procedure is not necessary. (a) Make sure that the work areas are clean and clear of tools and other items. (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801. 2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 90 5

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# @A340 SERVICE BULLETIN Task 254351-833-802-001 - Replace Bracket No. 7. **CONF ALL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 91 5

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# @A340 SERVICE BULLETIN
Task Associated Data **CONF 001 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 002 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 003 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF 004 Zone 212 Manpower TOTAL MANHOURS 11.50 ELAPSED TIME (HOURS) 11.50 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 254351-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 92 5

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# @A340 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 254351-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 254351-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 93 5

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# @A340 SERVICE BULLETIN (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 254351-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 254351-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 94 5

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# @A340 SERVICE BULLETIN (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 254351-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 254351-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to Consumable Materials (CML). (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 06-41-52, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with SRM 51-44-00. (g) Cut the rivets to the necessary length. (h) Renew the protective finish in accordance with SRM 51-75-12. (i) Apply sealant in accordance with SRM 51-24-00.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 95 5

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# @A340 SERVICE BULLETIN (2) Subtask 254351-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 254351-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) 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.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 96 5

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# @A340 SERVICE BULLETIN (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. (g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B). (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors. (2) Subtask 254351-010-003-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 97 5

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# @A340 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. **CONF 002 (1) Subtask 254351-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 98 5

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# @A340 SERVICE BULLETIN (a) 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. (g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 99 5

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# @A340 SERVICE BULLETIN (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B). (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors. (2) Subtask 254351-010-003-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 100 5

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# @A340 SERVICE BULLETIN
**CONF 003 (1) Subtask 254351-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 101 5

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# @A340 SERVICE BULLETIN (g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B). (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors. (2) Subtask 254351-010-003-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 102 5

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# @A340 SERVICE BULLETIN
3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. **CONF 004 (1) Subtask 254351-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-11-51-000-801 Task 31-63-22-000-801 Task 33-12-13-000-801 Task 52-10-00-010-801 NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) 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.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 103 5

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# @A340 SERVICE BULLETIN - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put the access platform in position door 831 or 841. (d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801. (f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. (g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are released: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (j) Make sure that there are warning notices in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there are warning notices in the cockpit to tell persons not to start the APU. (l) Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B). (m) Make sure that there is a warning notice at the access door 121EL to tell persons not to connect the external power connectors.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 104 5

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# @A340 SERVICE BULLETIN (2) Subtask 254351-010-003-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02
NOTE: If you intend to accomplish this Repair Task during the same layover period as the associated Inspection, the subsequent Preparation procedure is not necessary. (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retain 3 Washer Item (2) Retain 1 Panel Item (3) Retain (b) Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retain 1 Panel Item (4) Retain (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 254351-833-002-001 - Replace the Bracket No. 7 Work Zones and Access Panels Zone Access/Work location 212

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 105 5

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# @A340 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 F2511012820095 1 BRACKET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NAS6604-10 1 BOLT 8 NAS1726-4E 1 NUT 15 ASNA2050DEJ4020 4 RIVET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBDAA Replacement of the bracket No. 7 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the bracket No. 7. Refer to Fig. A-FBDAA In accordance with SRM 51-42-00 1 Remove: 1 Screw Item (7) Discard DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 106 5

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# @A340 SERVICE BULLETIN
1 Nut Item (8) Discard 2 Remove the rivets: - Remove the head of the four rivets. - Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in). 4 Rivet Item (15) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBDAA In accordance with SRM 51-42-00 and SRM 51-44-00. 1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a Mark the position of the hole of the upper bracket on the new bracket. 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in). 3 Put in position the new bracket item 16 with the bolt item 7. Install: 1 Bracket F2511012820095 Item 16 1 Bolt NAS6604-10 Item 7 NOTE: Install the bolt item 7 with: Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper bracket as shown in Fig. A-FBDAA Sheet 04
a Check that the minimum clearances are 0.35 mm (0.026 in) at LHS and 0.65 mm (0.014 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 107 5

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# @A340 SERVICE BULLETIN
6 Install: 4 Rivet ASNA2050DEJ4020 Item 15 7 Install the nut item 8: 1 Nut NAS1726-4E Item 8 NOTE: Torque the nut item 8 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in). (2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 108 5

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# @A340 SERVICE BULLETIN
**CONF 002 (1) Subtask 254351-833-002-002 - Replace the Bracket No. 7 Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 F2511012820095 1 BRACKET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA09 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 20 MS24665-134 1 PIN NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBDAB Replacement of the bracket No. 7 Sheet 01 Sheet 02 Sheet 03 Sheet 04 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 109 5

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# @A340 SERVICE BULLETIN (a) Remove the bracket No. 7. Refer to Fig. A-FBDAB In accordance with SRM 51-42-00 1 Remove: 1 Axis Item (17) Discard 1 Nut Item (18) Discard 1 Washer Item (19) Discard 1 Pin Item (20) Discard 2 Remove the rivets: - Remove the head of the four rivets. - Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in). 4 Rivet Item (15) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBDAB In accordance with SRM 51-42-00 and SRM 51-44-00 1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a Mark the position of the hole of the upper bracket on the new bracket. 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in). 3 Put in position the new bracket item 16 with the bolt item 17. Install: 1 Bracket F2511012820095 Item 16 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with:
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 110 5

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# @A340 SERVICE BULLETIN
Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper bracket as shown in Fig. A-FBDAB Sheet 04
a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and 0.65 mm (0.026 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure. 6 Install: 4 Rivet ASNA2050DEJ4020 Item 15 7 Install the nut item 18: 1 Nut NSA5060-3 Item 18 1 Washer NSA5325-3 Item 19 1 Pin-Cotter MS24665-134 Item 20 NOTE: Torque the nut item 18 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in). (2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 111 5

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# @A340 SERVICE BULLETIN
1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal **CONF 003 (1) Subtask 254351-833-002-003 - Replace the Bracket No. 7 Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 F2511012820095 1 BRACKET NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA10 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 21 MS24665-71 1 PIN NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 112 5

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# @A340 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBDAC Replacement of the bracket No. 7 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the bracket No. 7. Refer to Fig. A-FBDAC In accordance with SRM 51-42-00 1 Remove: 1 Axis Item (17) Discard 1 Nut Item (18) Discard 1 Washer Item (19) Discard 1 Pin Item (21) Discard 2 Remove the rivets: - Remove the head of the four rivets. - Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in). 4 Rivet Item (15) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBDAC In accordance with SRM 51-42-00 and SRM 51-44-00

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 113 5

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# @A340 SERVICE BULLETIN

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a Mark the position of the hole of the upper bracket on the new bracket. 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in). 3 Put in position the new bracket item 16 with the bolt item 17. Install: 1 Bracket F2511012820095 Item 16 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper bracket as shown in Fig. A-FBDAC Sheet 04

. a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and 0.65 mm (0.026 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure. 6 Install: 4 Rivet ASNA2050DEJ4020 Item 15 7 Install the nut item 18: 1 Nut NSA5060-3 Item 18 1 Washer NSA5325-3 Item 19 1 Pin-Cotter MS24665-71 Item 21 NOTE: Torque the nut item 18 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in). (2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 114 5

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# @A340 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal **CONF 004 (1) Subtask 254351-833-002-004 - Replace the Bracket No. 7 Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 F2511012820095 1 BRACKET DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 115 5

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# @A340 SERVICE BULLETIN
NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA10 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 15 ASNA2050DEJ4020 4 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 21 MS24665-71 1 PIN NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required

References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBDAC Replacement of the bracket No. 7 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the bracket No. 7. Refer to Fig. A-FBDAC In accordance with SRM 51-42-00 1 Remove: 1 Axis Item (17) Discard 1 Nut Item (18) Discard 1 Washer Item (19) Discard 1 Pin Item (21) Discard 2 Remove the rivets: - Remove the head of the four rivets.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 116 5

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# @A340 SERVICE BULLETIN - Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in). 4 Rivet Item (15) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBDAC In accordance with SRM 51-42-00 and SRM 51-44-00 1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.
a Mark the position of the hole of the upper bracket on the new bracket. 2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in). 3 Put in position the new bracket item 16 with the bolt item 17. Install: 1 Bracket F2511012820095 Item 16 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic EsterBase GreaseGeneral Purpose Low T 03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper bracket as shown in Fig. A-FBDAC Sheet 04

. a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and 0.65 mm (0.026 in) at RHS. 5 Drill the four holes in the bracket item 16 to align with the holes of the structure. 6 Install: 4 Rivet ASNA2050DEJ4020 Item 15 7 Install the nut item 18: 1 Nut NSA5060-3 Item 18 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 117 5

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# @A340 SERVICE BULLETIN

1 Washer NSA5325-3 Item 19 1 Pin-Cotter MS24665-71 Item 21 NOTE: Torque the nut item 18 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in). (2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801 Fig. A-FBCAA Removal/Installation of the protection plate and cover assembly panels Sheet 01 Sheet 02 (a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b) Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02 3 Stud Item (5) Retained at removal 1 Panel Item (4) Retained at removal (c) Install the protection plate. Refer to Fig. A-FBCAA Sheet 01 3 Stud Item (1) Retained at removal 3 Washer Item (2) Retained at removal 1 Panel Item (3) Retained at removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 118 5

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# @A340 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 (1) Subtask 254351-700-005-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 119 5

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# @A340 SERVICE BULLETIN
22-97-00-740-801. 1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. 3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. 8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801. **CONF 002 (1) Subtask 254351-700-005-001 - Test Manpower Resources Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 120 5

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# @A340 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801. 1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 121 5

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# @A340 SERVICE BULLETIN
3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. 8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801. **CONF 003 (1) Subtask 254351-700-005-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT,
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 122 5

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# @A340 SERVICE BULLETIN - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801. 1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. 3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. 8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801.
DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 123 5

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# @A340 SERVICE BULLETIN
**CONF 004 (1) Subtask 254351-700-005-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803 Task 22-96-00-740-801 Task 22-97-00-740-801 Task 24-41-00-861-801 Task 25-11-51-400-801 Task 31-50-00-710-803 Task 31-50-00-740-801 Task 31-60-00-710-802 Task 31-63-22-200-802 Task 33-12-13-400-801 Task 33-13-00-710-801 Task 33-14-00-710-801 Elec. Std. Practices Manual (ESPM) 20-52-20 NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 254351-410-002 001 Install/Close Items Removed/Opened for access. (a) In the cockpit, on the panel 235VU, push these pushbutton switches: - BAT 1, BAT 2, APU BAT, - GEN 1, (2), APU GEN, - EXT A (B). (b) Remove the warning notices. (c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801. (d) Remove the safety clips and/or tags and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72 S 742 702PP 10PB2 71 S (e) Preliminary test: NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 124 5

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# @A340 SERVICE BULLETIN

1 On each connector which was disconnected: - Do the checks as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter. 2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801. 3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801. 4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task 21-26-00-710-803. 5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task 22-96-00-740-801. 6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803. 7 Do the test of the FWS, AMM Task 31-50-00-740-801. 8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802. (f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-200-802. (g) If removed, do the test procedure as specified after the installation of the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (h) If removed, do the test procedure as specified after the installation of the LU (FIN 14LE ), refer to AMM Task 33-12-13-400-801. **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 254351-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 (a) Make sure that the work areas are clean and clear of tools and other items.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 125 5

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# @A340 SERVICE BULLETIN (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801. 2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions. **CONF 002 (1) Subtask 254351-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 (a) Make sure that the work areas are clean and clear of tools and other items. (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801. 2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 126 5

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# @A340 SERVICE BULLETIN
**CONF 003 (1) Subtask 254351-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 (a) Make sure that the work areas are clean and clear of tools and other items. (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801. 2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions. **CONF 004 (1) Subtask 254351-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801 Task 31-63-22-400-801 Task 33-12-13-400-801 Task 52-10-00-010-801 (a) Make sure that the work areas are clean and clear of tools and other items. (b) Parts and/or equipment removed for access, to be installed before the SUBTASK 254351-700-003 001 Testing 1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 127 5

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# @A340 SERVICE BULLETIN

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801. (c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and 3WK2), refer to AMM Task 33-12-13-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801. (e) Remove the access platform. (f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 128 5

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# @A340 SERVICE BULLETIN

**CONF ALL

BRACKET No 6 

### A



## A BRACKET No 7



### C **B**

F_SB_254351_5_BAAA_01_01 Figure A-FBAAA - Sheet 01 Area to be inspected DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 129 5

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# @A340 SERVICE BULLETIN

**CONF ALL

TYPICAL CRACKS LOCATIONS

AREAS TO BE INSPECTED (BOTH SIDES OF THE TWO LUGS) 

## B **C**

TYPICAL CRACKS LOCATIONS 

### D



## D

F_SB_254351_5_BAAA_02_02 Figure A-FBAAA - Sheet 02 Area to be inspected DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 130 5

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# @A340 SERVICE BULLETIN

**CONF 001

BRACKET No 6 

### A



## A **B C** 

F_SB_254351_5_BBAA_01_01 Figure A-FBBAA - Sheet 01 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 131 5

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# @A340 SERVICE BULLETIN

**CONF 001

(16)

**FWD** 

## BEFORE

(7) (8)



## B

HOLE SYMBOL ITEM OLD PN DESCRIPTION
RIVET
RIVET
ASNA2050DCJ3215 RIVET (15) (14) (11) ASNA2051DEJ4020 ASNA2050DEJ4020

F_SB_254351_5_BBAA_02_03 Figure A-FBBAA - Sheet 02 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 132 5

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# @A340 SERVICE BULLETIN

**CONF 001

16

**FWD** 

## AFTER

**C** 01

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX RIVET
ASNA2050DCJ3215 RIVET 15

11 4.06 mm (0.160 in) 4.17 mm (0.164 in) ASNA2050DEJ4020
3.25 mm (0.128 in) 3.35 mm (0.132 in) **NOTE:** DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in) 

### A

**A**

F_SB_254351_5_BBAA_03_05 Figure A-FBBAA - Sheet 03 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 133 5

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# @A340 SERVICE BULLETIN

**CONF 001

**NOTE:** CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS AND 0.65 mm (0.026 in) AT RHS 01 TORQUE THE NUT ITEM 8 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in) AND 0.37 m.daN (32.748 lbf.in) 02 7

16 8



## A **A** 01 01

02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

F_SB_254351_5_BBAA_04_02 Figure A-FBBAA - Sheet 04 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 134 5

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# @A340 SERVICE BULLETIN

**CONF 002

BRACKET No 6 

### A

**B C** 



## A

F_SB_254351_5_BBAC_01_00 Figure A-FBBAC - Sheet 01 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 135 5

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# @A340 SERVICE BULLETIN

**CONF 002

(16)

**FWD** 

## BEFORE

(17) (18)



## B (19) (20)

HOLE SYMBOL ITEM OLD PN DESCRIPTION
RIVET
RIVET
ASNA2050DCJ3215 RIVET (15) (14) (11) ASNA2051DEJ4020 ASNA2050DEJ4020

F_SB_254351_5_BBAC_02_02 Figure A-FBBAC - Sheet 02 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 136 5

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# @A340 SERVICE BULLETIN

**CONF 002

16

**FWD** 

## AFTER

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX RIVET
ASNA2050DCJ3215 RIVET 15

11 4.07 mm (0.160 in) 4.16 mm (0.164 in) ASNA2050DEJ4020
3.25 mm (0.128 in) 3.35 mm (0.132 in) **NOTE:** DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in) 

### A

**A** 01



## C

F_SB_254351_5_BBAC_03_04 Figure A-FBBAC - Sheet 03 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 137 5

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# @A340 SERVICE BULLETIN

**CONF 002

**NOTE:** CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS AND 0.65 mm (0.026 in) AT RHS 01 TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in) AND 0.37 m.daN (32.748 lbf.in) 02 

## A **A** 01 01

16

17 19

18

20 02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

F_SB_254351_5_BBAC_04_01 Figure A-FBBAC - Sheet 04 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 138 5

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# @A340 SERVICE BULLETIN

**CONF 003

BRACKET No 6 

### A

**B C** 



## A

F_SB_254351_5_BBAD_01_00 Figure A-FBBAD - Sheet 01 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 139 5

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# @A340 SERVICE BULLETIN

**CONF 003

(16)

**FWD** 

## BEFORE

(17) (18)



## B (19) (21)

HOLE SYMBOL ITEM OLD PN DESCRIPTION
RIVET
RIVET
ASNA2050DCJ3215 RIVET (15) (14) (11) ASNA2051DEJ4020 ASNA2050DEJ4020

F_SB_254351_5_BBAD_02_02 Figure A-FBBAD - Sheet 02 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 140 5

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

# @A340 SERVICE BULLETIN

**CONF 003

16

**FWD** 

## AFTER

**C** 01

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX RIVET
ASNA2050DCJ3215 RIVET 15

11 4.07 mm (0.160 in) 4.16 mm (0.164 in) ASNA2050DEJ4020
3.25 mm (0.128 in) 3.35 mm (0.132 in) **NOTE:** DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in) 

### A

**A**

F_SB_254351_5_BBAD_03_03 Figure A-FBBAD - Sheet 03 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 141 5

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# @A340 SERVICE BULLETIN

**CONF 003

**NOTE:** CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS AND 0.65 mm (0.026 in) AT RHS 01 TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in) AND 0.37 m.daN (32.748 lbf.in) 02 

## A **A** 01 01

16

17 19

18

21 02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

F_SB_254351_5_BBAD_04_01 Figure A-FBBAD - Sheet 04 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 142 5

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# @A340 SERVICE BULLETIN

**CONF 004

BRACKET No 6 

### A

**B C** 



## A

F_SB_254351_5_BBAB_01_00 Figure A-FBBAB - Sheet 01 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 143 5

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# @A340 SERVICE BULLETIN

**CONF 004

(6)

**FWD** 

## BEFORE

(17) (18)



## B

HOLE SYMBOL ITEM OLD PN DESCRIPTION BOLT

ASNA2050DCJ3215 RIVET (9)
(11) EN6115V3−5 NUT ASNA2531−3 (10) (19) (21)

F_SB_254351_5_BBAB_02_04 Figure A-FBBAB - Sheet 02 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 144 5

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# @A340 SERVICE BULLETIN

**CONF 004

6

**FWD** 

## AFTER

**C**

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX BOLT

ASNA2050DCJ3215 RIVET 9

11 4.780 mm (0.189 in) 4.821 mm (0.190 in) EN6115V3−5

3.25 mm (0.128 in) 3.35 mm (0.132 in) NUT ASNA2531−3 10 **NOTE:** DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in) 

### A

**A** 01

F_SB_254351_5_BBAB_03_03 Figure A-FBBAB - Sheet 03 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 145 5

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# @A340 SERVICE BULLETIN

**CONF 004

**NOTE:** CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS AND 0.65 mm (0.026 in) AT RHS 01 TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in) AND 0.37 m.daN (32.748 lbf.in) 02 

## A **A** 01 01

6 17 19

18

21 02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

F_SB_254351_5_BBAB_04_02 Figure A-FBBAB - Sheet 04 Replacement of the bracket No. 6 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 146 5

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# @A340 SERVICE BULLETIN

**CONF 001



## A BRACKET No 7



### B **C A** 

F_SB_254351_5_BDAA_01_00 Figure A-FBDAA - Sheet 01 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 147 5

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# @A340 SERVICE BULLETIN

**CONF 001

**FWD** 

## BEFORE

**B**

HOLE SYMBOL ITEM OLD PN DESCRIPTION
RIVET (15) ASNA2050DEJ4020 (7) (8)
(16)

F_SB_254351_5_BDAA_02_01 Figure A-FBDAA - Sheet 02 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 148 5

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# @A340 SERVICE BULLETIN

**CONF 001



## AFTER

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX RIVET 15 4.07 mm (0.160 in) 4.16 mm (0.164 in) ASNA2050DEJ4020 DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in) AND 6.7 mm (0.264 in) 16

**FWD**

**NOTE:** 01 01 

### A

**A** 

## C

F_SB_254351_5_BDAA_03_01 Figure A-FBDAA - Sheet 03 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 149 5

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# @A340 SERVICE BULLETIN

**CONF 001

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS AND 0.65 mm (0.026 in) AT RHS TORQUE THE NUT ITEM TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in) AND 0.37 m.daN (32.748 lbf.in)7

16 8 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE



## A **A**

**NOTE:** 01 02 01

02 01

8 F_SB_254351_5_BDAA_04_00 Figure A-FBDAA - Sheet 04 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 150 5

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# @A340 SERVICE BULLETIN

**CONF 002



## A BRACKET No 7



### B **C A** 

F_SB_254351_5_BDAB_01_00 Figure A-FBDAB - Sheet 01 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 151 5

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# @A340 SERVICE BULLETIN

**CONF 002

**FWD** 

## BEFORE

**B**

HOLE SYMBOL ITEM OLD PN DESCRIPTION
RIVET (15) ASNA2050DEJ4020 (17) (18) (19) (20) (16)

F_SB_254351_5_BDAB_02_01 Figure A-FBDAB - Sheet 02 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 152 5

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# @A340 SERVICE BULLETIN

**CONF 002



## AFTER

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX RIVET 15 4.07 mm (0.160 in) 4.16 mm (0.164 in) ASNA2050DEJ4020 DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in) AND 6.7 mm (0.264 in) 16

**FWD**

**NOTE:** 01 01 

### A

**A** 

## C

F_SB_254351_5_BDAB_03_01 Figure A-FBDAB - Sheet 03 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 153 5

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# @A340 SERVICE BULLETIN

**CONF 002

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS AND 0.65 mm (0.026 in) AT RHS TORQUE THE NUT ITEM TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in) AND 0.37 m.daN (32.748 lbf.in) 17

16 18 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE



## A **A**

**NOTE:** 01 02 01

02 01

18 20 19

F_SB_254351_5_BDAB_04_00 Figure A-FBDAB - Sheet 04 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 154 5

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# @A340 SERVICE BULLETIN

**CONF 003 thru 004



## A BRACKET No 7



### B **C A** 

F_SB_254351_5_BDAC_01_00 Figure A-FBDAC - Sheet 01 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 155 5

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# @A340 SERVICE BULLETIN

**CONF 003 thru 004

**FWD** 

## BEFORE

**B**

HOLE SYMBOL ITEM OLD PN DESCRIPTION
RIVET (15) ASNA2050DEJ4020 (16) (17) (18) (19) (21)

F_SB_254351_5_BDAC_02_01 Figure A-FBDAC - Sheet 02 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 156 5

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# @A340 SERVICE BULLETIN

**CONF 003 thru 004



## AFTER

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX RIVET 15 4.07 mm (0.160 in) 4.16 mm (0.164 in) ASNA2050DEJ4020 DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in) AND 6.7 mm (0.264 in) 16

**FWD**

**NOTE:** 01 01 

### A

**A** 

## C

F_SB_254351_5_BDAC_03_01 Figure A-FBDAC - Sheet 03 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 157 5

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# @A340 SERVICE BULLETIN

**CONF 003 thru 004

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS AND 0.65 mm (0.026 in) AT RHS TORQUE THE NUT ITEM TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in) AND 0.37 m.daN (32.748 lbf.in) 17

16 18 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE



## A **A**

**NOTE:** 01 02 01

02 01

18 21 19

F_SB_254351_5_BDAC_04_00 Figure A-FBDAC - Sheet 04 Replacement of the bracket No. 7 DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 158 5

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# @A340 SERVICE BULLETIN

**CONF ALL

(3) (1) (2) 

## A**A B** 

F_SB_254351_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Removal/Installation of the protection plate and cover assembly panels DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 159 5

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# @A340 SERVICE BULLETIN

**CONF ALL

(4)

(5)

TYPICAL INSTALATION 

### C **C**

**C**



## C **B**

F_SB_254351_5_BCAA_02_00 Figure A-FBCAA - Sheet 02 Removal/Installation of the protection plate and cover assembly panels DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 160 5

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# @A340 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING YES CRACKS FOUND AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 254351−832−801−001

BRACKET LUGS ARE FULLY BROKEN YES

DO A DETAILED INSPECTION OF THE COCKPIT INSTRUMENT PANEL BRACKET No 7 OR

CRACKS FOUND? YES

CONTACT AIRBUS

BEFORE NEXT FLIGHT REPLACE BRACKET No 6 AND BRACKET No 7 REFER TO TASK 254351−833−801−001 REFER TO SUBTASK 254351−700−004−001 TWO

BEFORE NEXT FLIGHT NO REPLACE BRACKET No 6
REFER TO TASK 254351−833−801−001 AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) DO A DETAILED INSPECTION OF THE COCKPIT INSTRUMENT PANEL BRACKET No 6 REFER TO TASK 254351−832−801−001 AT THE INTERVAL GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) NO NO INSTRUMENT PANEL BRACKET No 6 DO A DETAILED INSPECTION OF THE COCKPIT

AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 254351−832−801−001 INSTRUMENT PANEL BRACKET No 6 DO A DETAILED INSPECTION OF THE COCKPIT

**NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN. AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

AND TASK 254351−833−802−001 REPLACE BRACKET No 7 REFER TO TASK 254351−833−802−001 BEFORE NEXT FLIGHT OR

OR

IMPLEMENT SB No 25−4354 AS TERMINATIVE SOLUTION IMPLEMENT SB No 25−4354 AS TERMINATIVE SOLUTION AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

F_SB_254351_5_FAAA_01_08 Figure A-FFAAA - Sheet 01 Flow-chart DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 161 5

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# @A340 SERVICE BULLETIN

**CONF ALL **INSPECTION REPORT** RETURN TO: AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−mail: Structure.sbinspectionresult@airbus.com FAX +33 (0)5 61 93 36 14 WING BOX (WB/LR) SERVICE BULLETIN NO.: A/C MSN: OPERATOR: FLIGHT HOURS (FH): FLIGHT CYCLES (FC): INSPECTION METHOD: DATE OF INSPECTION: A340−25−4351

DETAILED INSPECTION

CRACKS FOUND YES NO TWO LUGS FULLY BROKEN YES NO BRACKET REPLACED YES NO

CRACKS FOUND YES NO BRACKET NUMBER 6

BRACKET NUMBER 7 BRACKET REPLACED YES NO

F_SB_254351_5_RAAA_01_01 Figure A-FRAAA - Sheet 01 Inspection Report DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 162 5

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# @A340 SERVICE BULLETIN REPORTING SHEET 

### TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT INSTRUMENT PANEL BRACKET 6. MODIFICATION No.: None 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: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 1 5

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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: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351 REVISION No.: 01 - Jan 31/14 Page: 1 5

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