# @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: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame 40 (FR40), initiating at the first hole aft of FR40 datum. The structural analysis led to the issue of the Mandatory Inspection Service Bulletin No. A340-57-4089 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)) and the issue of the Recommended modification Service Bulletin No. A340-57-4106, Modification No. 56467S18944 (WINGS - CENTER WING BOX-MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR40). Accomplishment of the Service Bulletin No. A340-57-4106 cancels the inspection requirements of the Service Bulletin No. A340-57-4089. The accomplishment Instructions in Service Bulletin No. A340-57-4106 must be completed for all aircraft belonging to configuration 002 listed in the effectivity of this Service Bulletin Rev. 01 and Rev. 02. A missing instruction has been detected in the following cases: - Either with a crack indication at hole 5 at time of Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment (Case 1), - or with a bush installed before Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment at hole 5 and without a crack indication at hole 5 at time of Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment (Case 2). CASE 1:

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 1 5

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# @A340 SERVICE BULLETIN SUMMARY In case of crack indication during rototest inspection of fastener hole 5 as per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. CASE 2: In case of bush installation before Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment at hole 5 and no crack indication at hole 5 reported by rototest per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. Doing a rototest inspection before the cold working is considered a standard practice. Nevertheless, two Service Bulletin Information Transmission (SBIT) Ref. 11-0041 and 12-0032 have been issued to inform operators about this occurrence. Operators Information Transmission (OIT) Ref. 999.0082/12 can also be consulted about this occurrence. Eventually this Service Bulletin is issued to settle this matter. This Service Bulletin requests a one time ultrasonic inspection of fastener hole 6 in the junction keel beam fitting at FR40 LH/RH side to ensure that no crack was left unrepaired at time of fastener hole cold working. In case of no finding, affected aircraft are inspected as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63 based on interval value. In case of finding, AIRBUS repair department will have to be contacted for further repair instructions. For aircraft which have not accomplished Service Bulletin No. A340-57-4106 at Rev. 01 or Rev. 02, perform repetitive inspection as per Inspection Service Bulletin No. A340-57-4089 or apply Service Bulletin No. A340-57-4106 at Rev. 03 or next when recommended threshold is reached. Accomplishment of this Service Bulletin will avoid extensive repair in the junction keel beam fitting at FR40. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 2 5

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# @A340 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPA01 1 See SB Nut EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

83V ABQ AFR AIB ALK ARG CAL CCA CES CPA DLH GAF GFA IBE LAN MAU MDG MSR PAL S3R SAA SAS SWR 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 Operator Information Telex (OIT) No.999.0082/12 and OIT No. 999.0086/11 OTHER SBIT 11-0041 and SBIT 12-0032 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 574126-832-801-001: Inspection TOTAL MANHOURS 22.75 ELAPSED TIME (HOURS) 22.75 APPENDICES Appendix 01: Inspection Report

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 3 5

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# @A340 SERVICE BULLETIN SUMMARY

**CONF ALL

FR40 FR47



### B **B**



## A **A**

− Z141 Z142

HOLE 6 TO BE INSPECTED LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 VIEW INSIDE CENTER TANK AT FR40 Y−1959 DATUM Y1959 FR40 DATUM FR40

STGR1 STGR1

**F W**  **D** 

## B **C C** 

F_SB_574126_5_SAAA_01_02 Figure A-FSAAA - Sheet 01

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 4 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: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40 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 340-212 340-213 340-312 340-313 (2) Effectivity by MSN 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 0235-0237 0239 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 (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.
DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 1 5

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# @A340 SERVICE BULLETIN

OPERATOR MSN 83V 0235 0239 0280 0292 ABQ 0216 0257 AFR 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399 AIB 0332 ALK 0367 0374 0381 ARG 0373 CAL 0402 0406 0411 0415 0433 CCA 0192 0199 0201 0242 0243 0264 CES 0182 CPA 0208 0218 0220 0227 0228 DLH 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447 GAF 0274 0355 GFA 0212 0215 0282 IBE 0193 0217 0221 0318 0329 0387 0414 0459 0474 0483 LAN 0359 0363 0429 0442 MAU 0194 0268 MDG 0210 0319 MSR 0178 PAL 0176 0187 0196 S3R 0204 SAA 0197 0378 SAS 0413 0424 0430 0435 0450 0467 0470 SWR 0179 0263 THT 0385 0395 0438 0446 THY 0180 0270 0331 UAE 0185 0190 0202 0236 VCV 0302 VIR 0214 0225 XAX 0273 0278 (4) Configuration by MSN MSN CONFIGURATION 0176 0178 0179 0180 0182 0185 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 0235 0236 0237 0239 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 001

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 2 5

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# @A340 SERVICE BULLETIN
(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Component COMPA01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame 40 (FR40), initiating at the first hole aft of FR40 datum. The structural analysis led to the issue of the Mandatory Inspection Service Bulletin No. A340-57-4089 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)) and the issue of the Recommended modification Service Bulletin No. A340-57-4106, Modification No. 56467S18944 (WINGS - CENTER WING BOX-MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR40). Accomplishment of the Service Bulletin No. A340-57-4106 cancels the inspection requirements of the Service Bulletin No. A340-57-4089. The accomplishment Instructions in Service Bulletin No. A340-57-4106 must be completed for all aircraft belonging to configuration 002 listed in the effectivity of this Service Bulletin Rev. 01 and Rev. 02. A missing instruction has been detected in the following cases: - Either with a crack indication at hole 5 at time of Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment (Case 1), - or with a bush installed before Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment at hole 5 and without a crack indication at hole 5 at time of Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment (Case 2). CASE 1: In case of crack indication during rototest inspection of fastener hole 5 as per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. CASE 2:

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 3 5

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# @A340 SERVICE BULLETIN

In case of bush installation before Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment at hole 5 and no crack indication at hole 5 reported by rototest per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. Doing a rototest inspection before the cold working is considered a standard practice. Nevertheless, two Service Bulletin Information Transmission (SBIT) Ref. 11-0041 and 12-0032 have been issued to inform operators about this occurrence. Operators Information Transmission (OIT) Ref. 999.0082/12 can also be consulted about this occurrence. Eventually this Service Bulletin is issued to settle this matter. (2) Objective/Action This Service Bulletin requests a one time ultrasonic inspection of fastener hole 6 in the junction keel beam fitting at FR40 LH/RH side to ensure that no crack was left unrepaired at time of fastener hole cold working. In case of no finding, affected aircraft are inspected as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63 based on interval value. In case of finding, AIRBUS repair department will have to be contacted for further repair instructions. For aircraft which have not accomplished Service Bulletin No. A340-57-4106 at Rev. 01 or Rev. 02, perform repetitive inspection as per Inspection Service Bulletin No. A340-57-4089 or apply Service Bulletin No. A340-57-4106 at Rev. 03 or next when recommended threshold is reached. (3) Advantages Accomplishment of this Service Bulletin will avoid extensive repair in the junction keel beam fitting at FR40. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 574126-832-801-001: Inspection (1) On the LH and RH sides, remove (if necessary) the ducts between FR39.1 and FR40, for access. (2) Inspect one keel beam fastener hole between FR40 and STGR1. (3) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 4 5

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# @A340 SERVICE BULLETIN

E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

Perform repetitive inspection as per SB A340-57-4089 A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) Refer to A340-57-4089

OR SB A340-57-4106 at Rev. 01 or Rev. 02 not accomplished.

Apply SB A340-57-4106 at Rev. 03 or next. A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) Refer to A340-57-4106

SB A340-57-4106 at Rev. 01 or Rev. 02 accomplished, hole 5 bushed and rototest at hole 6 made before cold working during SB A340-57-4106 accomplishment No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) At the threshold given in ALI Task ref. 57-11-63 None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 5 5

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# @A340 SERVICE BULLETIN
Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

SB A340-57-4106 at Rev. 01 or Rev. 02 accomplished, hole 5 bushed and rototest at hole 6 not made before cold working during SB A340-57-4106 accomplishment Do the preparation procedure (Refer to SUBTASK 574126-941-001 001 Job Set-up ) and do the one time ultrasonic inspection at hole 6 (Refer to SUBTASK 574126-832-002 001 Inspect one keel beam fastener hole between FR40 and STGR1. ) A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) - FC optimized set: 4,700FC / 17,700FH or - FH optimized set: 4,250FC / 27,900FH - 24 months from SB issuance date or - 1,300FC from SB issuance date None

Crack found on hole 6 Contact AIRBUS A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) Before next flight None None

No crack found on hole 6 No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) At the interval given in ALI Task ref. 57-11-63 None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 6 5

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# @A340 SERVICE BULLETIN
Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

SB A340-57-4106 at Rev. 01 or Rev. 02 accomplished, hole 5 not bushed and no crack found on hole 5 during SB A340-57-4106 accomplishment No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) At the threshold given in ALI Task ref. 57-11-63 None None

SB A340-57-4106 at Rev. 01 or Rev. 02 accomplished, hole 5 not bushed, crack found on hole 5 and rototest made to hole 6 before cold working during SB A340-57-4106 accomplishment No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) At the threshold given in ALI Task ref. 57-11-63 None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 7 5

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# @A340 SERVICE BULLETIN
Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

SB A340-57-4106 at Rev. 01 or Rev. 02 accomplished, hole 5 not bushed, crack found on hole 5 and rototest not made to hole 6 before cold working during SB A340-57-4106 accomplishment Do the preparation procedure (Refer to SUBTASK 574126-941-001 001 Job Set-up ) and do the one time ultrasonic inspection at hole 6 (Refer to SUBTASK 574126-832-002 001 Inspect one keel beam fastener hole between FR40 and STGR1. ) A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) - FC optimized set: 4,700FC / 17,700FH or - FH optimized set: 4,250FC / 27,900FH - 24 months from SB issuance date or - 1,300FC from SB issuance date None

Crack found on hole 6 Contact AIRBUS A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) Before next flight None None

No crack found on hole 6 No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A340-200 (WV002) and A340-200 (WV021) and A340-300 (WV020 serie) At the interval given in ALI Task ref. 57-11-63 None None

NOTE: Threshold to be counted from Service Bulletin No. A340-57-4106 accomplishment. NOTE: For FH and FC optimization on A340 aircraft, operators shall select the set that better suits aircraft operation and utilization, refer to OIT No. 999.086/11.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 8 5

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# @A340 SERVICE BULLETIN

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. 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. Task 574126-832-801-001: Inspection Get Access 10.00 On Aircraft On the LH and RH sides, remove (if necessary) the ducts between FR39.1 and FR40, for access. 1.00 Inspect one keel beam fastener hole between FR40 and STGR1. 0.50 On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. 1.00 Tests 0.25 Close-Up 10.00 TOTAL MANHOURS 22.75 ELAPSED TIME (HOURS) 22.75 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI) 57-11-63 Aircraft Maintenance Manual (AMM) 06-31-53 12-34-24 20-21-11 21-20-00 21-53-18 36-12-41 53-35-13 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-11-63 Service Bulletin (SB) A340-57-4089 A340-57-4106
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# @A340 SERVICE BULLETIN
Standards Manual (SM) Structural Repair Manual (SRM) 51-42-00 51-43-00 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A340 SERVICE BULLETIN

2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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 COMPA01 B/E AEROSPACE INC. CONSUMABLES MANAGEMENT 10000 NW 15th Terrace Miami FL 33172 USA 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 standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock. 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 None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 11 5

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# @A340 SERVICE BULLETIN
(2) Components Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 10 MS21071-3 1 NUT 15 NSA5050-4 2 NUT 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: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 12 5

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# @A340 SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS Task 574126-832-801-001 - 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. Task Associated Data Manpower TOTAL MANHOURS 22.75 ELAPSED TIME (HOURS) 22.75 A. GENERAL 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. (1) Subtask 574126-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 13 5

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# @A340 SERVICE BULLETIN
(c) Remove and install fasteners in accordance with SRM 51-42-00. (d) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (2) Subtask 574126-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 574126-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 21-20-00-010-801 Task 21-53-18-000-801 Task 36-12-41-000-801 Task 53-35-13-000-802 NOTE: Access to aircraft is only necessary to allow the ultrasonic inspection at hole 6. Before this step you have to check your Service Bulletin reports to see if this ultrasonic inspection is necessary. (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put access platform(s) in position. (c) Do the Job Set-up as specified in the Removal of the air-conditioning distribution ducts, refer to AMM Task 21-20-00-010-801. (d) Do the Job Set-up procedure as specified in the Removal of the pack discharge temperature-sensor (542HH), refer to AMM Task 21-53-18-000-801. (e) Do the Job Set-up procedure as specified in the Removal of the APU bleed-air ducts, refer to AMM Task 36-12-41-000-801. (f) Remove the Belly Fairing Access-Panels 191FB for the LH side and 192GB for the RH side, refer to AMM Task 53-35-13-000-802. (g) Get access to the work area.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 14 5

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# @A340 SERVICE BULLETIN

C. PROCEDURE (1) Subtask 574126-832-001-001 - On the LH and RH sides, remove (if necessary) the ducts between FR39.1 and FR40, for access. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-53-18-000-801 Task 36-12-41-000-801 Structural Repair Manual (SRM) 51-42-00 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access Sheet 01

Fig. A-FBBAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40 for access Sheet 01

(a) On RH side, remove the air conditioning duct. Refer to Fig. A-FBAAA Sheet 01 Refer to SRM 51-42-00 1 Remove : 1 Duct Item (8) Retain 1 Insulation Item (9) Retain 1 Nut Item (10) Discard 1 Bolt Item (11) Retain 1 Washer Item (12) Retain 2 Screw Item (13) Retain 2 Washer Item (14) Retain 2 Nut Item (15) Discard 1 Clamp Item (16) Retain

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 15 5

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# @A340 SERVICE BULLETIN
1 Clamp Item (17) Retain NOTE (01): Disconnect and move the rod Items (18) and (19) without removal. NOTE (02): Remove the Insulation Item (9) with associated clamp Item (17) from the duct Item (8) only if necessary. NOTE (03): For the removal of the sensor 542HH, refer to AMM Task 21-53-18-000-801. (b) On RH side, remove the air ventilation duct. Refer to Fig. A-FBBAA Sheet 01 Refer to SRM 51-42-00 1 Remove : 1 Duct Item (20) Retain 4 Clamp Item (21) Retain 8 Clamp Item (22) Retain 1 Sleeve Item (23) Retain 2 Sleeve Item (24) Retain (c) On LH side, remove the necessary APU bleed air system ducts between FR39.1 and FR40, refer to AMM Task 36-12-41-000-801. (d) Put the blanking plugs on the disconnected line ends. (2) Subtask 574126-832-002-001 - Inspect one keel beam fastener hole between FR40 and STGR1. Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI) 57-11-63 Non Destructive Test Manual (NTM) 57-11-63 Service Bulletin (SB) A340-57-4089 A340-57-4106

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 16 5

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# @A340 SERVICE BULLETIN

References Fig. A-FBCAA Inspection of Hole 6 in the junction keel beam Sheet 01 Sheet 02 (a) At the threshold given in the PLANNING INFORMATION paragraph 1.E.(2): Do a special detailed inspection of hole 6 in the junction keel beam fitting at FR40. 1 If Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 is not accomplished:
a Perform repetitive inspection as per Inspection Service Bulletin No. A340-57-4089
or Apply Service Bulletin No. A340-57-4106 at Rev. 03 or next when recommended threshold is reached. 2 If Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 is accomplished:
a Do the inspection of the Hole 6. Refer to Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02 <1> Hole 5 has been already bushed before Service Bulletin No. A340-57-4106 accomplishment: <a> If Rototest at Hole 6 was made before cold working during Service Bulletin No. A340-57-4106 accomplishment: [1] No further action for Hole 6 in accordance with this Service Bulletin (Hole 6 is covered by Airworthiness Limitation Items (ALI) Task ref. 57-11-63). [2] Inspect Hole 6 at the threshold of the Airworthiness Limitation Items (ALI) Task ref. 57-11-63. <b> If Rototest at Hole 6 was not made before cold working during Service Bulletin No. A340-57-4106 accomplishment: [1] Do the preparation procedure, refer to SUBTASK 574126-941-001 001 Job Set-up . [2] Do the one time ultrasonic inspection of the Hole 6, refer to NTM 57-11-63. [3] If crack found on Hole 6: [a] Contact AIRBUS before next flight.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 17 5

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# @A340 SERVICE BULLETIN
[4] If crack not found on Hole 6: [a] Send inspection report to AIRBUS, refer to Appendix 01: Inspection Report . [b] No further action on Hole 6 in accordance with this Service Bulletin. [c] Re-inspect the Hole 6 as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63, at the task interval, refer to NTM 57-11-63. <2> Hole 5 has not been already bushed before Service Bulletin No. A340-57-4106 accomplishment: <a> Crack not found on Hole 5 during Service Bulletin No. A340-57-4106 accomplishment: [1] No further action on Hole 6 in accordance with this Service Bulletin (Hole 6 is covered by Airworthiness Limitation Items (ALI) Task ref. 57-11-63). [2] Inspect Hole 6 at the threshold of the Airworthiness Limitation Items (ALI) Task ref. 57-11-63. <b> Crack found on Hole 5 during Service Bulletin No. A340-57-4106 accomplishment: [1] If Rototest at Hole 6 was made before cold working during Service Bulletin No. A340-57-4106 accomplishment: [a] No further action on Hole 6 in accordance with this Service Bulletin (Hole 6 is covered by Airworthiness Limitation Items (ALI) Task ref. 57-11-63). [b] Inspect Hole 6 at the threshold of the Airworthiness Limitation Items (ALI) Task ref. 57-11-63. [2] If Rototest at Hole 6 was not made before cold working during Service Bulletin No. A340-57-4106 accomplishment: [a] Do the preparation procedure, refer to SUBTASK 574126-941-001 001 Job Set-up . [b] Do the one time ultrasonic inspection of the Hole 6, refer to NTM 57-11-63. [c] If crack found on Hole 6: - Contact AIRBUS before next flight.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 18 5

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# @A340 SERVICE BULLETIN
[d] If crack not found on Hole 6: - Send inspection report to AIRBUS, refer to Appendix 01: Inspection Report . - No further action on Hole 6 in accordance with this Service Bulletin. - Re-inspect the Hole 6 as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63, at the task interval, refer to NTM 57-11-63. (b) Send inspection report to AIRBUS, refer to Appendix 01: Inspection Report . (3) Subtask 574126-832-003-001 - On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 10 MS21071-3 1 NUT 15 NSA5050-4 2 NUT NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Task 21-53-18-400-801 Task 36-12-41-400-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access Sheet 01

Fig. A-FBBAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40 for access Sheet 01

(a) Remove the blanking plugs on the disconnected line ends.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 19 5

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# @A340 SERVICE BULLETIN
(b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1 and FR40, refer to AMM Task 36-12-41-400-801. (c) On RH side, install (if removed) the air ventilation duct. Refer to Fig. A-FBAAA Sheet 01 Refer to AMM Task 20-21-11-911-801 Refer to SRM 51-42-00 and SRM 51-43-00 1 Install: 1 Duct Item (20) Retained at removal 4 Clamp Item (21) Retained at removal 8 Clamp Item (22) Retained at removal 1 Sleeve Item (23) Retained at removal 2 Sleeve Item (24) Retained at removal (d) On RH side, install (if removed) the air conditioning duct. Refer to Fig. A-FBBAA Sheet 01 Refer to AMM Task 20-21-11-911-801 Refer to SRM 51-42-00 and SRM 51-43-00 1 Install: 1 Duct Item (8) Retained at removal 1 Insulation Item (9) Retained at removal 1 Nut MS21071-3 Item 10 1 Bolt Item (11) Retained at removal 1 Washer Item (12) Retained at removal

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 20 5

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# @A340 SERVICE BULLETIN
2 Screw Item (13) Retained at removal 2 Washer Item (14) Retained at removal 2 Nut NSA5050-4 Item 15 1 Clamp Item (16) Retained at removal 1 Clamp Item (17) Retained at removal NOTE (01): Reconnect the rod Items (18) and (19). NOTE (02): For the installation of the sensor 542HH, refer to AMM Task 21-53-18-400-801. D. TEST (1) Subtask 574126-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 53-35-13-400-802 (a) Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as specified in the Installation of the Belly Fairing Access-Panels, refer to AMM Task 53-35-13-400-802. E. CLOSE-UP (1) Subtask 574126-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-53-18-400-801 Task 36-12-41-400-801 Task 53-35-13-400-802 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the Belly Fairing Access-Panels 191FB for the LH side and 192GB for the RH side, refer to AMM Task 53-35-13-400-802.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 21 5

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# @A340 SERVICE BULLETIN
(c) Do the Close-up procedure as specified after the Installation of the Belly Fairing Access-Panels, refer to AMM Task 53-35-13-400-802. (d) Do the Close-up procedure as specified after the Installation of the APU bleed-air ducts, refer to AMM Task 36-12-41-400-801. (e) Do the Close-up procedure as specified after the Installation of the pack discharge temperature-sensor (542HH), refer to AMM Task 21-53-18-400-801. (f) Do the Close-up procedure as specified after the Installation of the air-conditioning distribution ducts, refer to AMM Task 21-20-00-410-801. (g) Remove access platform(s). (h) Restore the systems and the aircraft to normal operating condition.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 22 5

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# @A340 SERVICE BULLETIN

**CONF ALL



## A FR40.2
FR39.2



## B (9) (18)

(15) (17)

(8) (16)

(10) (11) (12) (13) (14) (19) (15) (13) (14)

542HH 

### A **B** Z190

15

15

10

F_SB_574126_5_BAAA_01_01 Figure A-FBAAA - Sheet 01 Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 23 5

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# @A340 SERVICE BULLETIN

**CONF ALL



## A **B**



## C **D C**  **D**

**D** 

## B FR40 FR47

(20) (21) (22) (23) (24) (21) (22) 

### C **D C**  **D C**  **D A**  Z190

F_SB_574126_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Removal/Installation of the Ventilation ducts between FR39.1 and FR40 for access
DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 24 5

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# @A340 SERVICE BULLETIN

**CONF ALL

LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 DATUM
Y1959 FR40 FR47



### B



## A **B**



## B **C** FR40

STGR1 

### A

− Z141 Z142

F_SB_574126_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Inspection of Hole 6 in the junction keel beam
DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 25 5

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# @A340 SERVICE BULLETIN

**CONF ALL
Y1959

VIEW SIDE CENTRE TANK AT FR 40

FASTENER NOT AFFECTED HOLE 6

CENTER WING BOX

LOWER PANEL

HOLE TO BE INSPECTED AREA TO BE INSPECTED FR40DATUM

STGR1

**F W**  **D** 

## C

**D D**  KEEL BEAM FITTING STGR1 FR40 

### D

**D**

TYPICAL F_SB_574126_5_BCAA_02_03 Figure A-FBCAA - Sheet 02 Inspection of Hole 6 in the junction keel beam
DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 26 5

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# @A340 SERVICE BULLETIN

**CONF ALL

QUESTION
ACTION
FINDING RE−INSPECT THE HOLE 6 AT THE INTERVAL OF THE ALI 57.11.63 CRACK FOUND ON HOLE 6 DO THE ONE TIME ULTRASONIC INSPECTION AT HOLE 6, AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2).

REFER TO SUBTASK 574126−832−002−001 INSPECT THE HOLE 6 AT THE THRESHOLD OF THE ALI 57.11.63 CRACK FOUND ON HOLE 5 DURING SB 57−4106 ACCOMPLISHMENT HOLE 5 ALREADY BUSHED BEFORE SB 57−4106 ACCOMPLISHMENT SB 57−4106 REV. 01 OR REV. 02 EMBODIED
PERFORM REPETITIVE INSPECTION AS REV.03 OR NEXT WHEN RECOMMENDED THRESHOLD IS REACHED DO A SPECIAL DETAILED INSPECTION OF ONE FASTERNER HOLE IN THE

JUNCTION KEEL BEAM FITTING AT FR40 AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2). REFER TO SUBTASK 574126−832−002−001

YES CHECK YOUR SERVICE BULLETIN REPORTS AND IF NECESSARY

YES NO NO

PER ISB 57−4089 OR APPLY SB 57−4106 AT

YES NO

NO YES ROTOTEST AT HOLE 6 MADE PRIOR TO COLD WORKING DURING SB 57−4106 ACCOMPLISHMENT

NO FURTHER ACTION HOLE 6 REFER TO SUBTASK 574126−941−001−001 DO THE PREPARATION PROCEDURE

YES NO

CONTACT AIRBUS BEFORE NEXT FLIGHT

NO FURTHER ACTION HOLE 6 F_SB_574126_5_FAAA_01_02 Figure A-FFAAA - Sheet 01 Flow Chart

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 27 5

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# @A340 SERVICE BULLETIN

This Page Intentionally Left Blank

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# @A340 SERVICE BULLETIN Appendix 01: Inspection Report **CONF ALL (1) The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department SEES1, on the attached inspection report sheet.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 1 5

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# @A340 SERVICE BULLETIN Appendix 01: Inspection Report

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A340−57−4126

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−mail: structure.sbinspectionresult@airbus.com FAX +33 (0)5 61 93 36 14

YES NO YES NO YES NO YES NO SIDE
HOLE 6 HOLE 6 LH RH ULTRASONIC CRACK FOUND ? INSPECTION ?

F_SB_574126_5_RAAA_01_02 Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 2 5

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# @A340 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40 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: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 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: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126 REVISION No.: 00 - Jan 25/13 Page: 1 5

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