# @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. ATA SYSTEM: 25 

### TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - REINFORCE INSTRUMENT PANEL BRACKET 6 (SB ONLY). **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 203405S32617 MINOR None NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During flight tests carried out with an A340-600, high stress level was measured on the bracket No.6 (PN F25110128200 Pre Mod No.55128S18242 or PN F25113734200 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 runways and introduced through the Nose Landing Gear (NGL), and the cockpit panel. Resulting from accelerations introduced at pilot seat location, the bracket No.6 cannot sustain the fatigue loads of the Long Range Design Service Goal (DSG). This Service Bulletin recommends replacing the bracket No.6 PN F25110128200 Pre Mod No.55128S18242 or PN F25113734200 Post Mod No.55128S18242 of the Cockpit Instrument Panel by a reinforced titanium undrilled bracket PN F25114708200. Accomplishment of this Service Bulletin cancels the requirements of the Inspection Service Bulletin No. A330-25-4351. Accomplishment of this Service Bulletin will contribute to prevent the risk of having the bracket No.6 fully broken and, consequently, limit further damage on the surrounding structure.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 1 5

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# @A340 SERVICE BULLETIN SUMMARY GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES POTENTIAL AD NO A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational disruptions. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 254354A01R01 1 1,630.00 Bracket, Bolt, Nut, Rivet **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 254354A02R01 1 1,770.00 Bracket, Bolt, Nut, Rivet, Washer, Pin **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 254354A03R01 1 1,770.00 Bracket, Bolt, Nut, Rivet, Washer, Pin **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 254354A04R01 1 1,770.00 Bracket, Bolt, Nut, Rivet, Washer, Pin EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 2 5

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# @A340 SERVICE BULLETIN SUMMARY 15R 15T 56W 58X 83V ABD ABQ AFR AIB ALK ARG CAL CCA CPA DGA DLH FIN GAF GFA HFY I2L 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 254354-831-801-001: Modification TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF 002 Task 254354-831-801-001: Modification TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF 003 Task 254354-831-801-001: Modification TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF 004 Task 254354-831-801-001: Modification TOTAL MANHOURS 9.00 DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 3 5

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# @A340 SERVICE BULLETIN SUMMARY Task 254354-831-801-001: Modification ELAPSED TIME (HOURS) 9.00 APPENDICES **CONF ALL None

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 4 5

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# @A340 SERVICE BULLETIN SUMMARY

**CONF ALL



### A



## A BRACKET No 6

F_SB_254354_5_SAAA_01_00 Figure A-FSAAA - Sheet 01

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 5 5

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# @A340 SERVICE BULLETIN SUMMARY

This Page Intentionally Left Blank

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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 ATA SYSTEM: 25 

### TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - REINFORCE INSTRUMENT PANEL BRACKET 6 (SB ONLY). MODIFICATION No.: 203405S32617 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 NOTE: This modification is applicable by Service Bulletin only. (1) Models 340-211 340-212 340-213 340-311 340-312 340-313 (2) Effectivity by MSN 0002 0004-0006 0009 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

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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 I2L 0005 IBE 0088 0125 0134 0145 0146 0217 0221 0329 0387 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 QAF 0026 0528 RJA 0014 0022 0038 0043 S3R 0204
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# @A340 SERVICE BULLETIN
OPERATOR MSN SAA 0006 0197 0378 0544 0582 0590 0643 0646 0651 SAS 0167 0413 0424 0430 0435 0450 0467 0470 SFB 0046 SLM 0049 SVW 0955 SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561 0562 0585 0598 TAP 0041 0044 0079 0091 THT 0385 0395 0438 0446 0668 THY 0023 0025 0057 0115 0180 0270 0331 UAE 0139 0149 0163 0166 0185 0236 VCV 0031 VIR 0114 0164 0214 0225 XAX 0273 0278 (4) Configuration by MSN MSN CONFIGURATION 0002 0004 0005 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.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 3 5

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# @A340 SERVICE BULLETIN
**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. **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 Consumable CMLA01 1 Kit 254354A01R01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 Kit 254354A02R01 1 **CONF 003 MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 Kit 254354A03R01 1 **CONF 004 MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 Kit 254354A04R01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History During flight tests carried out with an A340-600, high stress level was measured on the bracket No.6 (PN F25110128200 Pre Mod No.55128S18242 or PN F25113734200 Post Mod No.55128S18242), which is one of the 8 parts used to attach the cockpit instrument panel to the aircraft structure. DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 4 5

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# @A340 SERVICE BULLETIN This is linked to a coupling between the vibration levels due to the bumps of runways and introduced through the Nose Landing Gear (NGL), and the cockpit panel. Resulting from accelerations introduced at pilot seat location, the bracket No.6 cannot sustain the fatigue loads of the Long Range Design Service Goal (DSG). (2) Objective/Action This Service Bulletin recommends replacing the bracket No.6 PN F25110128200 Pre Mod No.55128S18242 or PN F25113734200 Post Mod No.55128S18242 of the Cockpit Instrument Panel by a reinforced titanium undrilled bracket PN F25114708200. (3) Advantages Accomplishment of this Service Bulletin cancels the requirements of the Inspection Service Bulletin No. A330-25-4351. Accomplishment of this Service Bulletin will contribute to prevent the risk of having the bracket No.6 fully broken and, consequently, limit 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 254354-831-801-001: Modification (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access **CONF 002 Task 254354-831-801-001: Modification (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access **CONF 003 Task 254354-831-801-001: Modification (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 5 5

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# @A340 SERVICE BULLETIN
**CONF 004 Task 254354-831-801-001: Modification (1) Replace the Bracket No. 6. (2) Install/Close Items Removed/Opened for access **CONF ALL E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale Accomplishment of this Service Bulletin is recommended at the earliest opportunity where manpower and facilities are available. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 254354-831-801-001: Modification Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 1.50 Close-Up 2.50 TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 6 5

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# @A340 SERVICE BULLETIN
**CONF 002 Task 254354-831-801-001: Modification Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 1.50 Close-Up 2.50 TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF 003 Task 254354-831-801-001: Modification Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2 Install/Close Items Removed/Opened for access 0.50 Tests 1.50 Close-Up 2.50 TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF 004 Task 254354-831-801-001: Modification Get Access 2.50 On Aircraft Replace the Bracket No. 6. 2.00 Install/Close Items Removed/Opened for access 0.50 Tests 1.50 Close-Up 2.50 TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 7 5

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# @A340 SERVICE BULLETIN
J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24 20-21-11 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 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 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 20-21-11 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 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 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 20-21-11 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 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 8 5

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# @A340 SERVICE BULLETIN
**CONF 004 Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24 20-21-11 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 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00 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 L. INTERCHANGEABILITY/MIXABILITY **CONF 001 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Bracket F2511012820000 F2511470820095 03 Not Applicable Bracket F2511012820095 F2511470820095 03 Not Applicable NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. **CONF 002 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Bracket F2511012820000 F2511470820095 03 Not Applicable Bracket F2511012820095 F2511470820095 03 Not Applicable NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 9 5

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# @A340 SERVICE BULLETIN
**CONF 003 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Bracket F2511012820000 F2511470820095 03 Not Applicable Bracket F2511012820095 F2511470820095 03 Not Applicable NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. **CONF 004 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Bracket F2511373420000 F2511470820095 03 Not Applicable Bracket F2511373420095 F2511470820095 03 Not Applicable NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. **CONF ALL M. SPARES None

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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 : Kit 254354A01R01 Kit 254354A02R01 Kit 254354A03R01 Kit 254354A04R01 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet : http://spares.airbus.com For ordering by fax : +49 40 50 76 2590 For ordering by E-mail : airbus.kit@airbus.com (2) Price and Availability The Kit availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 254354A01R01 Cost 1,630.00 USD Availability 90 calendar days from receipt of order Kit 254354A02R01 Cost 1,770.00 USD Availability 90 calendar days from receipt of order Kit 254354A03R01 Cost 1,770.00 USD Availability 90 calendar days from receipt of order Kit 254354A04R01 Cost 1,770.00 USD Availability 90 calendar days from receipt of order B. INDUSTRY SUPPORT INFORMATION For aircraft under warranty at Jan 01/12, AIRBUS will share the costs of accomplishment of this Service Bulletin by providing the kits at no charge for orders placed before Jun 30/16. DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 11 5

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# @A340 SERVICE BULLETIN For aircraft under warranty at Jan 01/12 and for the accomplishment of this Service Bulletin before Jun 30/16, AIRBUS will credit the manhours indicated in this Service Bulletin at the agreed in-house warranty labor rate for claims received not later than 90 days after completion of the last affected aircraft of your fleet. C. LIST OF COMPONENTS Kit 254354A01R01 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 25 F2511470820095 1 BRACKET (16) F2511012820000 03 (16) F2511012820095 03 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 254354A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 11 ASNA2050DCJ3215 3 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 20 MS24665-134 1 PIN 25 F2511470820095 1 BRACKET (16) F2511012820000 03 (16) F2511012820095 03 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 12 5

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# @A340 SERVICE BULLETIN
Kit 254354A03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 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 25 F2511470820095 1 BRACKET (16) F2511012820000 03 (16) F2511012820095 03 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 254354A04R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 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 25 F2511470820095 1 BRACKET (6) F2511373420000 03 (6) F2511373420095 03 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 13 5

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# @A340 SERVICE BULLETIN
D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester base Grease 03HBD9 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 14 5

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# @A340 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 254354-831-801-001 - Modification WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. 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 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. Task Associated Data **CONF 001 Zone 212 Manpower TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 15 5

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# @A340 SERVICE BULLETIN
**CONF 002 Zone 212 Manpower TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF 003 Zone 212 Manpower TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF 004 Zone 212 Manpower TOTAL MANHOURS 9.00 ELAPSED TIME (HOURS) 9.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 254354-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to the Consumable Materials List (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. DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 16 5

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# @A340 SERVICE BULLETIN (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 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. (j) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (k) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 254354-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 254354-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to the Consumable Materials List (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.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 17 5

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# @A340 SERVICE BULLETIN (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 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. (j) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (k) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 254354-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 254354-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to the Consumable Materials List (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.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 18 5

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# @A340 SERVICE BULLETIN (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 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. (j) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (k) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 254354-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 254354-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-41-52, Page Block 001 Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to the Consumable Materials List (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.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 19 5

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# @A340 SERVICE BULLETIN (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 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. (j) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (k) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 254354-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 254354-941-001-001 - 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).

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 20 5

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# @A340 SERVICE BULLETIN - Engine shut down, thrust revers 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 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) (14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72S 742 702PP 10PB2 71S (j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to operate the pushbutton switches on the overhead panel : - 211VU (EMER ELEC PWR) - 235VU (ELEC) DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 21 5

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# @A340 SERVICE BULLETIN (k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to start the APU. (l) Make sure that the external connector(s) is (are) not connected to the aircraft receptacle(s) 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 connector(s). (2) Subtask 254354-010-001-001 - 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 (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 254354-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 22 5

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# @A340 SERVICE BULLETIN
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 revers 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 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) (14LE), refer to AMM Task 33-12-13-000-801.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 23 5

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# @A340 SERVICE BULLETIN (i) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72S 742 702PP 10PB2 71S (j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to operate the pushbutton switches on the overhead panel : - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to start the APU. (l) Make sure that the external connector(s) is (are) not connected to the aircraft receptacle(s) 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 connector(s). (2) Subtask 254354-010-001-001 - 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 (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

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 24 5

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# @A340 SERVICE BULLETIN (c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801. **CONF 003 (1) Subtask 254354-941-001-001 - 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 revers 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 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 25 5

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# @A340 SERVICE BULLETIN (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) (14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72S 742 702PP 10PB2 71S (j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to operate the pushbutton switches on the overhead panel : - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to start the APU. (l) Make sure that the external connector(s) is (are) not connected to the aircraft receptacle(s) 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 connector(s). (2) Subtask 254354-010-001-001 - 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 (a) Remove the protection plate. Refer to Fig. A-FBCAA Sheet 01

. 3 Stud Item (1) Retain 3 Washer Item (2) Retain DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 26 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 004 (1) Subtask 254354-941-001-001 - 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 revers 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 door 831 or 841.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 27 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) (14LE), refer to AMM Task 33-12-13-000-801. (i) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 742 701PP 10PB1 72S 742 702PP 10PB2 71S (j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to operate the pushbutton switches on the overhead panel : - 211VU (EMER ELEC PWR) - 235VU (ELEC) (k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to start the APU. (l) Make sure that the external connector(s) is (are) not connected to the aircraft receptacle(s) 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 connector(s). (2) Subtask 254354-010-001-001 - 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 28 5

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# @A340 SERVICE BULLETIN (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 254354-911-001-001 - 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 Kit 254354A01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NAS6604-10 1 BOLT 8 NAS1726-4E 1 NUT 11 ASNA2050DCJ3215 3 RIVET 25 F2511470820095 1 BRACKET 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 29 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 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 Sheet 01 and Fig. A-FBBAA Sheet 02

. 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 4.788 mm and 4.813 mm (0.188 in. and 0.189 in.). 2 Rivet Item (12) Discard 2 Rivet Item (14) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard or 1 Bracket F2511012820095 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBBAA Sheet 03 and Fig. A-FBBAA Sheet 04

. In accordance with SRM 51-42-00 and SRM 51-44-00.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 30 5

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# @A340 SERVICE BULLETIN
1 Temporarily put the bracket item 25 on the RH side on the upper bracket on the new bracket.
a If necessary, remove: 3 Rivet 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 25 with the bolt item 7. Install: 1 Bracket F2511470820095 Item 25 1 Bolt NAS6604-10 Item 7 NOTE: Install the bolt item 7 with: Synthetic Ester base Grease 03HBD9 As required

4 Measure the clearance between the new bracket item 25 and the upper bracket as shown in Fig. A-FBBAA Sheet 04

. a Check that the minimum clearance are 0.35 mm (0.014 in.) at LHS and 0.65 mm (0.026 in.) at RHS. 5 Match and drill the four holes of the cockpit main instrument panel on the new bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and 4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAA Sheet 03

. 6 Install: 4 Bolt ABS0114V3-5 Item 26 4 Nut NSA5050-3 Item 27 7 Install the nut item 8: 1 Nut NAS1726-4E Item 8 NOTE: Torque the nut item 8 to a value between 0.28 and 0.37 m.daN (24.782 and 32.748 lbf.in.).

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 31 5

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# @A340 SERVICE BULLETIN (2) Subtask 254354-410-001-001 - 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 **CONF 002 (1) Subtask 254354-911-001-002 - Replace the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 32 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 Kit 254354A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 11 ASNA2050DCJ3215 3 RIVET 17 NSA5042-04-160 1 BOLT 18 NSA5060-3 1 NUT 19 NSA5325-3 1 WASHER 20 MS24665-134 1 PIN 25 F2511470820095 1 BRACKET 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester base Grease 03HBD9
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 Sheet 01 and Fig. A-FBBAC Sheet 02

. In accordance with SRM 51-42-00. 1 Remove: 1 Bolt Item (17) Discard 1 Nut Item (18) Discard 1 Whasher Item (19) Discard 1 Pin Item (20) Discard
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 33 5

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# @A340 SERVICE BULLETIN
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 4.788 mm and 4.813 mm (0.188 in. and 0.189 in.). 2 Rivet Item (12) Discard 2 Rivet Item (14) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard or 1 Bracket F2511012820095 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBBAC Sheet 03 and Fig. A-FBBAC Sheet 04

. In accordance with SRM 51-42-00 and SRM 51-44-00. 1 Temporarily put the bracket item 25 on the RH side of the upper bracket.
a If necessary, remove: 3 Rivet 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 the position the new bracket item 25 with the bolt item 17. 1 Bracket F2511470820095 Item 25 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic Ester base Grease 03HBD9 As required

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 34 5

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# @A340 SERVICE BULLETIN
4 Measure the clearance between the new bracket item 25 and the upper bracket as show 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 Match and drill the four holes of the cockpit main instrument panel on the new bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and 4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAC Sheet 03

. 6 Install: 4 Bolt ABS0114V3-5 Item 26 4 Nut NSA5050-3 Item 27 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 value between 0.28 and 0.37 m.daN (24.782 and 32.748 lbf.in.). (2) Subtask 254354-410-001-002 - 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 DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 35 5

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# @A340 SERVICE BULLETIN (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 254354-911-001-003 - Replace the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212 Manpower Resources Manhours 2 Minimum number of person 1 Subtask elapsed time 2 Skills AIRFRAME Material necessary to do the job Kit 254354A03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 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 25 F2511470820095 1 BRACKET 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester base Grease 03HBD9 As required
References Structural Repair Manual (SRM) 51-42-00 51-44-00 DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 36 5

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# @A340 SERVICE BULLETIN
References 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 Sheet 01 and Fig. A-FBBAD Sheet 02

. In accordance with SRM 51-42-00. 1 Remove : 1 Bolt 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 4.788 mm and 4.813 mm (0.188 in. and 0.189 in.). 2 Rivet Item (12) Discard 2 Rivet Item (14) Discard 3 Remove the bracket: 1 Bracket F2511012820000 Item (16) Discard or 1 Bracket F2511012820095 Item (16) Discard (b) Install the new bracket. Refer to Fig. A-FBBAD Sheet 03 and Fig. A-FBBAD Sheet 04

. In accordance with SRM 51-42-00 and SRM 51-44-00. 1 Temporarily put the bracket item 25 on the RH side of the upper bracket.
a If necessary, remove: 3 Rivet Item (11) Discard DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 37 5

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# @A340 SERVICE BULLETIN
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 diameter comprised between 6.5 and 6.7 mm (0.256 and 0.264 in.). 3 Put in position the new bracket item 25 with the bolt item 17. Install: 1 Bracket F2511470820095 Item 25 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic Ester base Grease 03HBD9 As required

4 Measure the clearance between the new bracket item 25 and the upper bracket as show in Fig. A-FBBAD Sheet 04

. a Check that the minimum clearance are 0.35 mm (0.014 in.) at LHS and 0.65 mm (0.026 in.) at RHS. 5 Match and drill the four holes of the cockpit main instrument panel on the new bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and 4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAD Sheet 03

. 6 Install: 4 Bolt ABS0114V3-5 Item 26 4 Nut NSA5050-3 Item 27 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 value between 0.28 and 0.37 m.daN (24.782 and 32.748 lbf.in.).

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 38 5

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# @A340 SERVICE BULLETIN (2) Subtask 254354-410-001-003 - 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 **CONF 004 (1) Subtask 254354-911-001-004 - Replace the Bracket No. 6. Work Zones and Access Panels Zone Access/Work location 212

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 39 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 Kit 254354A04R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 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 25 F2511470820095 1 BRACKET 26 ABS0114V3-5 4 BOLT 27 NSA5050-3 4 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synthetic Ester base Grease 03HBD9 As required
References Structural Repair Manual (SRM) 51-42-00 51-44-00 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 Sheet 01 and Fig. A-FBBAB Sheet 02

. In accordance with SRM 51-42-00. 1 Remove: 1 Bolt Item (17) Discard 1 Nut Item (18) Discard 1 Washer Item (19) Discard 1 Pin Item (21) Discard
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 40 5

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# @A340 SERVICE BULLETIN
2 Remove the fasteners: 4 Bolt Item (9) Discard 4 Nut Item (10) Discard 3 Remove the bracket: 1 Bracket F2511373420000 Item (6) Discard or 1 Bracket F2511373420095 Item (6) Discard (b) Install the new bracket. Refer to Fig. A-FBBAB Sheet 03 and Fig. A-FBBAB Sheet 04

. In accordance with SRM 51-42-00 and SRM 51-44-00. 1 Temporarily put the bracket item 25 on the RH side of the upper bracket.
a If necessary, remove: 3 Rivet 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 comprise between 6.5 and 6.7 mm (0.256 and 0.264 in.). 3 Put the position the new bracket item 25 with the bolt item 17. 1 Bracket F2511470820095 Item 25 1 Bolt NSA5042-04-160 Item 17 NOTE: Install the bolt item 17 with: Synthetic Ester base Grease 03HBD9 As required

4 Measure the clearance between the new bracket item 25 and the upper bracket as show in Fig. A-FBBAB Sheet 04

. a Check that the minimum clearance are 0.35 mm (0.014 in.) at LHS and 0.65 mm (0.026 in.) at RHS.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 41 5

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# @A340 SERVICE BULLETIN
5 Match and drill the four holes of the cockpit main instrument panel on the new bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and 4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAB Sheet 03

. 6 Install: 4 Bolt ABS0114V3-5 Item 26 4 Nut NSA5050-3 Item 27 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 value between 0.28 and 0.37 m.daN (24.782 and 32.748 lbd.in.). (2) Subtask 254354-410-001-004 - 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

.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 42 5

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# @A340 SERVICE BULLETIN 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 254354-700-001-001 - 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 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 253548-410-002 001 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).

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 43 5

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# @A340 SERVICE BULLETIN (d) Remove the Safety clips and tags and close this (these) following circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 742VU 701PP 10PB1 72S 742VU 702PP 10PB2 71S (e) Preliminary Tests : 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 check as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test requested by this ESPM procedure is given hereafter. 2 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task 33-13-00-710-801). 3 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801) 4 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM Task 21-26-00-710-803). 5 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task 22-96-00-740-801). 6 Do the O/T of the ECAM Control Panel,(Refer to AMM Task 31-50-00-710-803) . 7 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801). 8 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802). (f) Procedure : 1 If removed, do the test procedure as specified after the Installation of the Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801). 2 If removed, do the test after the removal/installation of the Light Unit (LU) (14LE of the center main instrument panel, (Refer to AMM Task 33-12-13-400-801). **CONF 002 (1) Subtask 254354-700-001-001 - Test Manpower Resources Skills NON SPECIFIC
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 44 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 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 253548-410-002 001 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 tags and close this (these) following circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 742VU 701PP 10PB1 72S 742VU 702PP 10PB2 71S (e) Preliminary Tests : 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 check as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test requested by this ESPM procedure is given hereafter. 2 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task 33-13-00-710-801).

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 45 5

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# @A340 SERVICE BULLETIN
3 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801) 4 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM Task 21-26-00-710-803). 5 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task 22-96-00-740-801). 6 Do the O/T of the ECAM Control Panel,(Refer to AMM Task 31-50-00-710-803) . 7 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801). 8 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802). (f) Procedure : 1 If removed, do the test procedure as specified after the Installation of the Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801). 2 If removed, do the test after the removal/installation of the Light Unit (LU) (14LE of the center main instrument panel, (Refer to AMM Task 33-12-13-400-801). **CONF 003 (1) Subtask 254354-700-001-001 - 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 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 253548-410-002 001 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 46 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 tags and close this (these) following circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 742VU 701PP 10PB1 72S 742VU 702PP 10PB2 71S (e) Preliminary Tests : 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 check as defined by ESPM 20-52-20. NOTE: The functional test and/or operational test requested by this ESPM procedure is given hereafter. 2 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task 33-13-00-710-801). 3 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801) 4 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM Task 21-26-00-710-803). 5 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task 22-96-00-740-801). 6 Do the O/T of the ECAM Control Panel,(Refer to AMM Task 31-50-00-710-803) . 7 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801). 8 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802). (f) Procedure : 1 If removed, do the test procedure as specified after the Installation of the Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801). 2 If removed, do the test after the removal/installation of the Light Unit (LU) (14LE of the center main instrument panel, (Refer to AMM Task 33-12-13-400-801). DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 47 5

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# @A340 SERVICE BULLETIN
**CONF 004 (1) Subtask 254354-700-001-001 - 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 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 253548-410-002 001 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 tags and close this (these) following circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 742VU 701PP 10PB1 72S 742VU 702PP 10PB2 71S (e) Preliminary Tests : 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 check as defined by ESPM 20-52-20.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 48 5

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# @A340 SERVICE BULLETIN
NOTE: The functional test and/or operational test requested by this ESPM procedure is given hereafter. 2 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task 33-13-00-710-801). 3 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801) 4 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM Task 21-26-00-710-803). 5 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task 22-96-00-740-801). 6 Do the O/T of the ECAM Control Panel,(Refer to AMM Task 31-50-00-710-803) . 7 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801). 8 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802). (f) Procedure : 1 If removed, do the test procedure as specified after the Installation of the Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801). 2 If removed, do the test after the removal/installation of the Light Unit (LU) (14LE of the center main instrument panel, (Refer to AMM Task 33-12-13-400-801). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 254354-942-001-001 - 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 sur 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 253548-700-003 001 Test 1 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 49 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 31-63-22-400-801. (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 254354-942-001-001 - 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 sur 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 253548-700-003 001 Test 1 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801. 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 31-63-22-400-801. (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 254354-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 50 5

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# @A340 SERVICE BULLETIN
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 sur 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 253548-700-003 001 Test 1 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801. 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 31-63-22-400-801. (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 254354-942-001-001 - 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 sur 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 253548-700-003 001 Test 1 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801. 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 31-63-22-400-801. (d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 51 5

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

DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 52 5

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# @A340 SERVICE BULLETIN

**CONF 001

BRACKET No 6 

### A



## A **B C** 

F_SB_254354_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 53 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 (12) (14) (11) ASNA2051DEJ4020 ASNA2050DEJ4020

F_SB_254354_5_BBAA_02_00 Figure A-FBBAA - Sheet 02 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 54 5

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# @A340 SERVICE BULLETIN

**CONF 001

25

**FWD** 

## AFTER

**C** 01

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX BOLT

ASNA2050DCJ3215 RIVET 26

11 ABS0114V3−5

3.25 mm (0.128 in) 3.35 mm (0.132 in) 4.788 mm (0.189 in) 4.813 mm (0.190 in) **NOTE:**

DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in) 

### A

**A**

NUT 27 NSA5050−3 F
N F HEAD ON THE HIDDEN SIDE
N HEAD ON THE VISIBLE SIDE

F_SB_254354_5_BBAA_03_02 Figure A-FBBAA - Sheet 03 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 55 5

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# @A340 SERVICE BULLETIN

**CONF 001

APPLY MAT. No 03HBD9 ON THE BOLT ITEM 7 03 7

25 8



## A **A** 01 01

02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

**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 03

F_SB_254354_5_BBAA_04_00 Figure A-FBBAA - Sheet 04 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 56 5

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# @A340 SERVICE BULLETIN

**CONF 002

BRACKET No 6 

### A

**B C** 



## A

F_SB_254354_5_BBAC_01_00 Figure A-FBBAC - Sheet 01 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 57 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 (12) (14) (11) ASNA2051DEJ4020 ASNA2050DEJ4020

F_SB_254354_5_BBAC_02_00 Figure A-FBBAC - Sheet 02 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 58 5

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# @A340 SERVICE BULLETIN

**CONF 002

25

**FWD** 

## AFTER

**C** 01

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX BOLT

ASNA2050DCJ3215 RIVET 26

11 ABS0114V3−5

3.25 mm (0.128 in) 3.35 mm (0.132 in) 4.788 mm (0.189 in) 4.813 mm (0.190 in) **NOTE:**

DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in) 

### A

**A**

NUT 27 NSA5050−3 F
N F HEAD ON THE HIDDEN SIDE
N HEAD ON THE VISIBLE SIDE

F_SB_254354_5_BBAC_03_02 Figure A-FBBAC - Sheet 03 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 59 5

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# @A340 SERVICE BULLETIN

**CONF 002



## A **A** 01 01

25

17 19

18

20 02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

APPLY MAT. No 03HBD9 ON THE BOLT ITEM 17 03 **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 03

F_SB_254354_5_BBAC_04_00 Figure A-FBBAC - Sheet 04 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 60 5

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# @A340 SERVICE BULLETIN

**CONF 003

BRACKET No 6 

### A

**B C** 



## A

F_SB_254354_5_BBAD_01_00 Figure A-FBBAD - Sheet 01 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 61 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 (12) (14) (11) ASNA2051DEJ4020 ASNA2050DEJ4020

F_SB_254354_5_BBAD_02_00 Figure A-FBBAD - Sheet 02 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 62 5

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# @A340 SERVICE BULLETIN

**CONF 003

25

**FWD** 

## AFTER

**C**

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX BOLT

ASNA2050DCJ3215 RIVET 26

11 4.788 mm (0.189 in) 4.813 mm (0.190 in) ABS0114V3−5

3.25 mm (0.128 in) 3.35 mm (0.132 in) NUT NSA5050−3 27 

### A

**A** 01

**NOTE:**

DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in)

F
N F HEAD ON THE HIDDEN SIDE
N HEAD ON THE VISIBLE SIDE

F_SB_254354_5_BBAD_03_02 Figure A-FBBAD - Sheet 03 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 63 5

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# @A340 SERVICE BULLETIN

**CONF 003



## A **A** 01 01

25

17 19

18

21 02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

APPLY MAT. No 03HBD9 ON THE BOLT ITEM 17 03 **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 03

F_SB_254354_5_BBAD_04_00 Figure A-FBBAD - Sheet 04 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 64 5

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# @A340 SERVICE BULLETIN

**CONF 004

BRACKET No 6 

### A

**B C** 



## A

F_SB_254354_5_BBAB_01_00 Figure A-FBBAB - Sheet 01 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 65 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_254354_5_BBAB_02_00 Figure A-FBBAB - Sheet 02 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 66 5

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# @A340 SERVICE BULLETIN

**CONF 004

25

**FWD** 

## AFTER

**C**

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX BOLT

ASNA2050DCJ3215 RIVET 26

11 4.788 mm (0.189 in) 4.813 mm (0.190 in) ABS0114V3−5

3.25 mm (0.128 in) 3.35 mm (0.132 in) NUT NSA5050−3 27 

### A

**A** 01

**NOTE:**

DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in) 01 AND 6.7 mm (0.264 in)

F
N F HEAD ON THE HIDDEN SIDE
N HEAD ON THE VISIBLE SIDE

F_SB_254354_5_BBAB_03_02 Figure A-FBBAB - Sheet 03 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 67 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

25

17 19

18

21 02 MEASURE THE

CLEARANCE MEASURE THE CLEARANCE

APPLY MAT. No 03HBD9 ON THE BOLT ITEM 17 03 03

F_SB_254354_5_BBAB_04_00 Figure A-FBBAB - Sheet 04 Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 68 5

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# @A340 SERVICE BULLETIN

**CONF ALL

(3) (1) (2) 

## A**A B** 

F_SB_254354_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Removal/Installation of the protection plate and cover assembly panels
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 69 5

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# @A340 SERVICE BULLETIN

**CONF ALL

(4)

(5)

TYPICAL INSTALLATION 

### C **C**

**C**



## C **B**

F_SB_254354_5_BCAA_02_00 Figure A-FBCAA - Sheet 02 Removal/Installation of the protection plate and cover assembly panels
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 70 5

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# @A340 SERVICE BULLETIN REPORTING SHEET 

### TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - REINFORCE INSTRUMENT PANEL BRACKET 6 (SB ONLY). MODIFICATION No.: 203405S32617 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354 REVISION No.: 00 - Oct 31/13 Page: 1 5

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