# @A340-500/600 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 THE EXTERNAL RADIUS ON THE UPPER HORIZONTAL CRUCIFORM FITTING AT FRAME 47 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During the A340-600EF2 fatigue test, damages have occurred in external radius on upper horizontal cruciform in rear corner at Frame 47, on LH and RH sides. These damages were detected after tear down inspections using High Frequency Eddy Current (HFEC) method. This condition, if not corrected, could impair the structural integrity of the affected aeroplanes. This mandated Inspection Service Bulletin (ISB) request to perform a repetitive HFEC inspection of the external radius on upper horizontal cruciform fitting at Frame 47 on LH and RH sides. Accomplishment of this Service Bulletin will allow early detection of cracks on upper horizontal cruciform in rear corner at frame 47, ensuring the structural integrity of the area. Accomplishment of this Service Bulletin will avoid extensive repairs and related aircraft down time. 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: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 575029A01R00 1 175.00 Bolt, Nut **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 575029A02R00 1 900.00 Bolt, Nut EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

06U 62X 70U 72W 79W CES CHH DLH ETD HFY IBE QAF QTR SAA SIA SOR TAM THA UAE VIR 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

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 575029-832-801-001: Inspection TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 10.00 **CONF 002 Task 575029-832-801-001: Inspection TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 10.00 APPENDICES **CONF ALL Appendix 01 : Inspection Report Appendix 02 : Elapsed Time Assumption

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 3 5

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# @A340-500/600 SERVICE BULLETIN SUMMARY

**CONF ALL

FR40 FR47


### B



## A **B**

LH SIDE SHOWN RH SIDE SYMMETRICAL

AREA TO BE INSPECTED **NOTE:** 200 mm (7.874 in)



## B EXTERNAL RADIUS



### C

POSSIBLE CRACK 

## C

F_SB_575029_5_SAAA_01_01 UPPER HORIZONTAL CRUCIFORM FITTING FR47



### A

Figure A-FSAAA - Sheet 01

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 4 5

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# @A340-500/600 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF THE EXTERNAL RADIUS ON THE UPPER HORIZONTAL CRUCIFORM FITTING AT FRAME 47 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 340-541 340-542 340-642 (2) Effectivity by MSN 0371 0376 0383 0391 0394 0410 0416-0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761-0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079 1091 1102 1122

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 06U 1091 1102 62X 0779 70U 0902 72W 0917 79W 0924 CES 0468 0488 0514 0577 0586 CHH 0436 0453 0475 DLH 0482 0517 0523 0537 0540 0543 0566 0569 0580 0583 0762 0763 0767 0771 0790 0794 0812 0846 0848 0897 0972 0981 0987 1005 ETD 0748 0757 0761 0783 0829 0837 0870 0929 0933 1030 1040 HFY 0910 0912 IBE 0431 0440 0460 0601 0604 0606 0617 0619 0672 0702 0727 0744 0960 0993 1017 1079 1122 QAF 0495 QTR 0715 0740 0766 0798 SAA 0410 0417 0426 0531 0534 0547 0557 0626 0630 SIA 0478 0492 0499 0560 0563 SOR 0886 0894 TAM 0445 0464 THA 0624 0628 0677 0681 0689 0698 0710 0719 0775 0953 UAE 0394 0457 0471 0485 0520 0572 0608 0611 0685 0694 VIR 0371 0376 0383 0391 0416 0449 0575 0615 0622 0639 0706 0723 0736 0753 0764 0765 0768 0787 0804 (4) Configuration by MSN MSN CONFIGURATION 0371 0376 0383 0391 0394 0410 0416 0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761 0762 0763 0764 0765 0766 0767 0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 001

1079 1091 1102 1122 002

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN (5) Configuration definition **CONF 001 Config. 001 concerns aircraft on which Mod. No. 57691S19466 (FUSELAGE - CENTER FUSELAGE - MODIFY UPPER BELLY FAIRING - (PRODUCTION SOL)) is not embodied. **CONF 002 Config. 002 concerns aircraft on which Mod. No. 57691S19466 (FUSELAGE - CENTER FUSELAGE - MODIFY UPPER BELLY FAIRING - (PRODUCTION SOL)) is embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 575029A01R00 1 Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 575029A02R00 1 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History During the A340-600EF2 fatigue test, damages have occurred in external radius on upper horizontal cruciform in rear corner at Frame 47, on LH and RH sides. These damages were detected after tear down inspections using High Frequency Eddy Current (HFEC) method. This condition, if not corrected, could impair the structural integrity of the affected aeroplanes. (2) Objective/Action This mandated Inspection Service Bulletin (ISB) request to perform a repetitive HFEC inspection of the external radius on upper horizontal cruciform fitting at Frame 47 on LH and RH sides.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 3 5

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# @A340-500/600 SERVICE BULLETIN (3) Advantages Accomplishment of this Service Bulletin will allow early detection of cracks on upper horizontal cruciform in rear corner at frame 47, ensuring the structural integrity of the area. Accomplishment of this Service Bulletin will avoid extensive repairs and related aircraft down time. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 575029-832-801-001: Inspection (1) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side). (2) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side). **CONF 002 Task 575029-832-801-001: Inspection (1) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side). (2) Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side). **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA).

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 4 5

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# @A340-500/600 SERVICE BULLETIN

COMPLIANCE TIME REPETITIVE INTERVAL NOT TO EXCEED CONDITION ACTION
THRESHOLD GRACE PERIOD First accomplishment of SB 57-5029 Inspect in accordance with SUBTASK 575029-250-001 Refer to Table 2 for the threshold values of the aircraft to be inspected NO Not applicable

Crack found Contact AIRBUS for further instructions Before next flight NO Not applicable
No crack found Repeat the inspection in accordance with SUBTASK 575029-250-001 Not applicable NO Refer to Table 2 for the interval values of theaircraft to be reinspected Table 1. Inspection for Cracks of the Upper Horizontal Cruciform Fitting at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 5 5

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# @A340-500/600 SERVICE BULLETIN

THRESHOLD (whichever occurs first) REPETITIVE INTERVAL (whichever occurs first) CRITERIA AIRCRAFT CONCERNED
FC FH FC FH Pre Mod. No. 56558S19405 and pre Mod. No. 48487H14261 all A340-642 WV000 and WV001 aircraft 9,750 63,600 6,200 40,500

Pre Mod. No. 56558S19405 and post Mod. No. 48487H14261 all A340-642 WV000 and WV001 aircraft 7,050 46,100 4,550 29,700

all A340-642 WV000 and WV001 aircraft except for all the aircraft listed below for which a specific threshold is defined 6,350 41,500 3,650 24,000

0371 7,235 47,030 3,650 24,000 0376, 0410, 0417, 0426, 0431, 0440, 0449 and 0460 6,395 51,170 3,650 24,000
0383, 0391 and 0416 6,380 51,170 3,650 24,000 0436 7,050 47,030 3,650 24,000 Post Mod. No. 56558S19405 and pre Mod. No. 48487H14261

0453 6,350 51,170 3,650 24,000 all A340-642 WV000 and WV001 aircraft except for all the aircraft listed below for which a specific threshold is defined 4,600 30,000 2,700 17,500

0475, 0482, 0517, 0523, 0531, 0534, 0537, 0540, 0543, 0547, 0557, 0566, 0569, 0575, 0580, 0583, 0601, 0604, 0606, 0615, 0617, 0619, 0622, 0626, 0630, 0639, 0672, 0702, 0706, 0710 and 0744 4,615 36,950 2,700 17,500 A340-642 Weight Variant (WV)000 and WV001

Post Mod. No. 56558S19405 and post Mod. No. 48487H14261

0468, 0488, 0514, 0577, 0586, 0677, 0681, 0689 and 0719 5,220 33,950 2,700 17,500

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 6 5

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# @A340-500/600 SERVICE BULLETIN

THRESHOLD (whichever occurs first) REPETITIVE INTERVAL (whichever occurs first) CRITERIA AIRCRAFT CONCERNED
FC FH FC FH Pre Mod. No. 56558S19405 and pre Mod. No. 48487H14261 All A340-541 WV000, WV001, WV002, WV003 and WV004 aircraft 9,700 73,900 6,050 46,200

Pre Mod. No. 56558S19405 and post Mod. No. 48487H14261 All A340-541 WV000, WV001, WV002, WV003 and WV004 aircraft 7,100 54,200 4,500 34,400

all A340-541 WV000, WV001, WV002, WV003 and WV004 aircraft except for all the aircraft listed below for which a specific threshold is defined 6,350 48,400 3,550 27,400

0394 and 0457 7,235 55,170 3,550 27,400 0471 7,205 55,170 3,550 27,400 445 6,830 54,610 3,550 27,400 Post Mod. No. 56558S19405 and pre Mod. No. 48487H14261

464 6,965 54,640 3,550 27,400 all A340-541 WV000, WV001, WV002, WV003 and WV004 aircraft except for all the aircraft listed below for which a specific threshold is defined 4,650 35,500 2,650 20,500

0478 and 0492 5,205 40,320 2,650 20,500 0485, 0520, 0572, 0608, 0611, 0685 and 0694 5,285 40,320 2,650 20,500
0499 5,240 40,320 2,650 20,500 0560 5,145 40,300 2,650 20,500 0563 5,190 40,320 2,650 20,500 0624 5,170 40,320 2,650 20,500 0628 5,115 40,320 2,650 20,500 A340-541 Weight Variant (WV)000, WV001, WV002, WV003 and WV004

Post Mod. No. 56558S19405 and post Mod. No. 48487H14261

0698 5,080 40,320 2,650 20,500

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 7 5

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# @A340-500/600 SERVICE BULLETIN

THRESHOLD (whichever occurs first) REPETITIVE INTERVAL (whichever occurs first) CRITERIA AIRCRAFT CONCERNED
FC FH FC FH Pre Mod. No. (56558S19405 and 56026S19358 and 56026S19415 and 56633S19416) all A340-642 WV101, WV102 and WV103 and A340-643 WV101, WV102 and WV103 aircraft 8,400 58,000 5,350 37,000

all A340-642 WV101, WV102 and WV103 and A340-643 WV101, WV102 and WV103 aircraft except for all the aircraft listed below for which a specific threshold is defined 4,800 33,100 2,700 18,600 A340-642 Weight Variant (WV)101, WV102 and WV103 and A340-643 WV101, WV102 and WV103 Post Mod. No. (56558S19405 or 56026S19358 or 56026S19415 or 56633S19416)

0762, 0763, 0767 and 0771 5,420 38,880 2,700 18,600 Pre Mod. No. (56558S19405 and 56633S19416) all A340-541 WV101, WV102 and WV103 and A340-542 WV101, WV102 and WV103 aircraft 7,800 62,500 4,750 38,200 A340-541 Weight Variant (WV)101, WV102 and WV103 and A340-542 WV101, WV102 and WV103 Post Mod. No. (56558S19405 or 56633S19416) all A340-541 WV101, WV102 and WV103 and A340-542 WV101, WV102 and WV103 aircraft 4,450 35,600 2,350 19,000

Table 2. Threshold and repetitive interval.
NOTE: The thresholds for aircraft post Mod. No. 56558S19405 (Service Bulletin No. A340-57-5010 accomplished) must be counted from the aircraft first flight and not from Service Bulletin No. A340-57-5010 accomplishment. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 8 5

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# @A340-500/600 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 575029-832-801-001: Inspection Get Access 4.00 On Aircraft Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side). 5.00 Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side). 5.00 Close-Up 6.00 TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 10.00 NOTE: For the details concerning the elapsed time, refer to Appendix 02 : Elapsed Time Assumption . **CONF 002 Task 575029-832-801-001: Inspection Get Access 4.00 On Aircraft Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side). 5.00 Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side). 5.00 Close-Up 6.00 TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 10.00 NOTE: For the details concerning the elapsed time, refer to Appendix 02 : Elapsed Time Assumption . **CONF ALL H. WEIGHT AND BALANCE Not Changed DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 9 5

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# @A340-500/600 SERVICE BULLETIN
I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24 20-21-11 20-28-00 53-35-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00 Non Destructive Test Manual (NTM) 57-18-07 Service Bulletin (SB) A340-57-5010 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-44-00 **CONF 002 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24 20-21-11 20-28-00 53-35-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00 Non Destructive Test Manual (NTM) 57-18-07 Service Bulletin (SB) A340-57-5010 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-44-00 **CONF ALL K. PUBLICATION AFFECTED Impact on scheduled maintenance : Refer to Maintenance Planning Document (MPD). L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 10 5

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# @A340-500/600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 575029A01R00 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: Airbus Material, Logistics and Suppliers Weg beim Jeager 150 D-22335 Hamburg Germany For ordering by internet : http://spares.airbus.com For ordering modification kits by fax : +49 40 50 76 25 90 For ordering of single spares by fax : +49 40 50 76 40 13 Kit 575029A02R00 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: Airbus Material, Logistics and Suppliers Weg beim Jeager 150 D-22335 Hamburg Germany For ordering by internet : http://spares.airbus.com For ordering modification kits by fax : +49 40 50 76 25 90 For ordering of single spares by fax : +49 40 50 76 40 13 (2) Price and Availability

Kit 575029A01R00 Cost 175.00 USD Availability 15 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits 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 at the issue date of the Service Bulletin.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 11 5

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# @A340-500/600 SERVICE BULLETIN

Kit 575029A02R00 Cost 900.00 USD Availability 15 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits 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 at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION This Service Bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP policy. C. LIST OF COMPONENTS Kit 575029A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 3 ASNA2531-3 32 Nut 6 EN6115V3-3 20 Bolt 7 EN6115V3-4 12 Bolt 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 575029A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 2 EN6115V3X4 28 Bolt 3 ASNA2531-3 28 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. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Electrical Bonding Coating (blue Color) 07-001D As required

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 12 5

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# @A340-500/600 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Interfay Sealant 09-005A As required Sealant-Brush Consistency 09-013 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

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# @A340-500/600 SERVICE BULLETIN

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# @A340-500/600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 575029-832-801-001 - 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 **CONF 001 Zone 147 148 Manpower TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 10.00 **CONF 002 Zone 147 148 Manpower TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 10.00

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# @A340-500/600 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 575029-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Electrical Bonding Coating (blue Color) 07-001D As required Interfay Sealant 09-005A As required Sealant-Brush Consistency 09-013 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 Task 20-21-11-911-801 Task 20-28-00-912-801 Task 20-28-00-912-802 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-44-00 (a) Refer to Consumable Materials List (CML) for the specification of materials (Mat. No.) you must use in this Service Bulletin. (b) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of the Zones (Refer to AMM 06-20-00, Page Block 001). (d) Tag the parts that you must remove and retain to make the subsequent installation. (e) Put all the retained hardware in identified plastic bags to the related unit.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 16 5

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# @A340-500/600 SERVICE BULLETIN (f) Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number to part number relationship. (g) For the alternative and substitute fasteners (Refer to SRM 51-43-00). (h) Remove and install the fasteners (Refer to SRM 51-42-00). (i) Drill and deburr the holes (Refer to SRM 51-44-00). (j) To torque tighten the standard threaded fasteners (Refer to AMM Task 20-21-11-911-801). (k) Apply the sealant (Refer to SRM 51-24-00). (l) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (m) For the protection, refer to SRM 51-23-12. (n) Install the fasteners on the structure with : Sealant-Brush Consistency 09-013 As required

(wet assembly) (o) Install the karman webs with interposition of : Interfay Sealant 09-005A As required (p) Renew the sealant bead around the supports with : Corrosion Inhibiting fillet Consistency 09-016 As required (q) Do the electrical bonding (Refer to ESPM 20-51-20, AMM Task 20-28-00-912-801 and AMM Task 20-28-00-912-802) and protect with : Electrical Bonding Coating (blue Color) 07-001D As required (2) Subtask 575029-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 17 5

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# @A340-500/600 SERVICE BULLETIN
**CONF 002 (1) Subtask 575029-910-001-002 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Electrical Bonding Coating (blue Color) 07-001D As required Interfay Sealant 09-005A As required Sealant-Brush Consistency 09-013 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 Task 20-21-11-911-801 Task 20-28-00-912-802 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-44-00 (a) Refer to Consumable Materials List (CML) for the specification of materials (Mat. No.) you must use in this Service Bulletin. (b) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of the Zones (Refer to AMM 06-20-00, Page Block 001). (d) Tag the parts that you must remove and retain to make the subsequent installation. (e) Put all the retained hardware in identified plastic bags to the related unit. (f) Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number to part number relationship.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 18 5

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# @A340-500/600 SERVICE BULLETIN (g) For the alternative and substitute fasteners (Refer to SRM 51-43-00). (h) Remove and install the fasteners (Refer to SRM 51-42-00). (i) Drill and deburr the holes (Refer to SRM 51-44-00). (j) To torque tighten the standard threaded fasteners (Refer to AMM Task 20-21-11-911-801). (k) Apply the sealant (Refer to SRM 51-24-00). (l) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (m) For the protection, refer to SRM 51-23-12. (n) Install the fasteners on the structure with : Sealant-Brush Consistency 09-013 As required

(wet assembly) (o) Install the karman webs with interposition of : Interfay Sealant 09-005A As required (p) Renew the sealant bead around the supports with : Corrosion Inhibiting fillet Consistency 09-016 As required (q) Do the electrical bonding (Refer to ESPM 20-51-20 and AMM Task 20-28-00-912-802) and protect with : Electrical Bonding Coating (blue Color) 07-001D As required (2) Subtask 575029-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 19 5

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# @A340-500/600 SERVICE BULLETIN
**CONF ALL B. PREPARATION **CONF 001 (1) Subtask 575029-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 53-35-11-000-801 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position. (2) Subtask 575029-010-004-001 - Remove the Karman Web and the Sealant at FR47 (LH side). Work Zones and Access Panels Zone Access/Work location 147 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBCAA Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02 (a) Remove the wing to fuselage fairing 147AT (Refer to AMM Task 53-35-11-000-801). (b) Remove : Refer to Fig. A-FBCAA 10 Blind Rivet Item (4) Discard 6 Blind Rivet Item (5) Discard 1 Web Item (1) Retain

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 20 5

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# @A340-500/600 SERVICE BULLETIN (c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet 01

. (3) Subtask 575029-010-002-001 - Remove the Karman Web and the Sealant at FR47 (RH side). Work Zones and Access Panels Zone Access/Work location 148 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801 Fig. A-FBCAA Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02 Fig. A-FBBAA Area to be Inspected Sheet 01 (a) Remove the wing to fuselage fairings 148AT (Refer to AMM Task 53-35-11-000-801). (b) Remove : Refer to Fig. A-FBCAA 10 Blind Rivet Item (4) Discard 6 Blind Rivet Item (5) Discard 1 Web Item (1) Retain (c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet 01

. **CONF 002 (1) Subtask 575029-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 53-35-11-000-801 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802).

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 21 5

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# @A340-500/600 SERVICE BULLETIN (b) Put the access platform(s) in position. (2) Subtask 575029-010-004-002 - Remove the Karman Web and the Sealant at FR47 (LH side). Work Zones and Access Panels Zone Access/Work location 147 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBCAB Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02 (a) Remove the wing to fuselage fairing 147AT (Refer to AMM Task 53-35-11-000-801). (b) Remove : Refer to Fig. A-FBCAB 14 Bolt Item (2) Discard 14 Nut Item (3) Discard 1 Web Item (1) Retain (c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet 01

. (3) Subtask 575029-010-002-002 - Remove the Karman Web and the Sealant at FR47 (RH side). Work Zones and Access Panels Zone Access/Work location 148 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 53-35-11-000-801 Fig. A-FBCAB Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02
DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 22 5

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# @A340-500/600 SERVICE BULLETIN

References Fig. A-FBBAA Area to be Inspected Sheet 01 (a) Remove the wing to fuselage fairings 148AT (Refer to AMM Task 53-35-11-000-801). (b) Remove : Refer to Fig. A-FBCAB 14 Bolt Item (2) Discard 14 Nut Item (3) Discard 1 Web Item (1) Retain (c) Remove the sealant from the area to be inspected, refer to Fig. A-FBBAA Sheet 01

. **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 575029-250-001-001 - Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side). Work Zones and Access Panels Zone Access/Work location 147 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-18-07 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBAAA Flow Chart Sheet 01 (a) For the inspection area, refer to Fig. A-FBBAA Sheet 01

.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 23 5

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# @A340-500/600 SERVICE BULLETIN (b) Do a special detailed inspection of the external radius on the upper horizontal cruciform fitting at Frame 47 (LH side) as per NTM 57-18-07. Refer to Fig. A-FBAAA Sheet 01 (c) For the inspection report, refer to Appendix 01 : Inspection Report . (2) Subtask 575029-250-002-001 - Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side). Work Zones and Access Panels Zone Access/Work location 148 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-18-07 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBAAA Flow Chart Sheet 01 (a) For the inspection area, refer to Fig. A-FBBAA Sheet 01

. (b) Do a special detailed inspection of the external radius on the upper horizontal cruciform fitting at Frame 47 (RH side) as per NTM 57-18-07. Refer to Fig. A-FBAAA Sheet 01 (c) For the inspection report, refer to Appendix 01 : Inspection Report . **CONF 002 (1) Subtask 575029-250-001-001 - Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (LH side). Work Zones and Access Panels Zone Access/Work location 147 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME
DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 24 5

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# @A340-500/600 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 57-18-07 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBAAA Flow Chart Sheet 01 (a) For the inspection area, refer to Fig. A-FBBAA Sheet 01

. (b) Do a special detailed inspection of the external radius on the upper horizontal cruciform fitting at Frame 47 (LH side) as per NTM 57-18-07. Refer to Fig. A-FBAAA Sheet 01 (c) For the inspection report, refer to Appendix 01 : Inspection Report . (2) Subtask 575029-250-002-001 - Do a Special Detailed Inspection of the External Radius on the Upper Horizontal Cruciform Fitting at FR 47 (RH side). Work Zones and Access Panels Zone Access/Work location 148 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-18-07 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBAAA Flow Chart Sheet 01 (a) For the inspection area, refer to Fig. A-FBBAA Sheet 01

. (b) Do a special detailed inspection of the external radius on the upper horizontal cruciform fitting at Frame 47 (RH side) as per NTM 57-18-07. Refer to Fig. A-FBAAA Sheet 01 (c) For the inspection report, refer to Appendix 01 : Inspection Report .

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 25 5

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# @A340-500/600 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 575029-410-001-001 - Install the Karman Web and apply the Sealant at FR47 (LH side). Work Zones and Access Panels Zone Access/Work location 147 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 575029A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 ASNA2531-3 16 Nut 6 EN6115V3-3 10 Bolt 7 EN6115V3-4 6 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required
References Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801 Fig. A-FBBAA Area to be Inspected Sheet 01

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 26 5

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# @A340-500/600 SERVICE BULLETIN

References Fig. A-FBCAA Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02 (a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) : Corrosion Inhibiting fillet Consistency 09-016 As required (b) Put in position : Refer to Fig. A-FBCAA 1 Web Item (1) Retained at removal (c) Oversize the 16 holes to a diameter comprised between 4.78 mm (0.188 in.) and 4.82 mm (0.190 in.) as shown on Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02

. (d) Remove the web Item(1) and clean before final installation. (e) Install : Refer to Fig. A-FBCAA 1 Web Item (1) Retained at removal 10 Bolt EN6115V3-3 Item 6 6 Bolt EN6115V3-4 Item 7 16 Nut ASNA2531-3 Item 3 Apply the protection on the fasteners before installation, refer to SUBTASK 575029-910-001 001 Standard Practices . (f) Install the wing to fuselage fairing 147AT (Refer to AMM Task 53-35-11-400-801). (2) Subtask 575029-410-002-001 - Install the Karman Web and apply the Sealant at FR47 (RH side). Work Zones and Access Panels Zone Access/Work location 148 Manpower Resources Skills AIRFRAME

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 27 5

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# @A340-500/600 SERVICE BULLETIN
Material necessary to do the job Kit 575029A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 ASNA2531-3 16 Nut 6 EN6115V3-3 10 Bolt 7 EN6115V3-4 6 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required
References Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBCAA Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02 (a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) : Corrosion Inhibiting fillet Consistency 09-016 As required (b) Put in position : Refer to Fig. A-FBCAA 1 Web Item (1) Retained at removal (c) Oversize the 16 holes to a diameter comprised between 4.78 mm (0.188 in.) and 4.82 mm (0.190 in.) as shown on Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02

. (d) Remove the web Item(1) and clean before final installation. (e) Install : Refer to Fig. A-FBCAA 1 Web Item (1) Retained at removal 10 Bolt EN6115V3-3 Item 6 6 Bolt EN6115V3-4 Item 7
DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 28 5

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# @A340-500/600 SERVICE BULLETIN

16 Nut ASNA2531-3 Item 3 Apply the protection on the fasteners before installation, refer to SUBTASK 575029-910-001 001 Standard Practices . (f) Install the wing to fuselage fairing 148AT (Refer to AMM Task 53-35-11-400-801). (3) Subtask 575029-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Restore the systems and the aircraft to normal operating condition. (c) Remove the access platform(s). **CONF 002 (1) Subtask 575029-410-001-002 - Install the Karman Web and apply the Sealant at FR47 (LH side). Work Zones and Access Panels Zone Access/Work location 147 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 575029A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 EN6115V3X4 14 Bolt 3 ASNA2531-3 14 Nut Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required
References Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801
DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 29 5

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# @A340-500/600 SERVICE BULLETIN

References Fig. A-FBCAB Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02 Fig. A-FBBAA Area to be Inspected Sheet 01 (a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) : Corrosion Inhibiting fillet Consistency 09-016 As required (b) Put in position : Refer to Fig. A-FBCAB 1 Web Item (1) Retained at removal (c) Oversize the 14 holes to a diameter comprised between 5.11 in. (0.201 in.) and 5.15 (0.203 in.) as shown on Fig. A-FBCAB Sheet 01 and Fig. A-FBCAB Sheet 02

. (d) Remove the web Item(1) and clean before final installation. (e) Install : Refer to Fig. A-FBCAB 1 Web Item (1) Retained at removal 14 Bolt EN6115V3X4 Item 2 14 Nut ASNA2531-3 Item 3 Apply the protection on the fasteners before installation, refer to SUBTASK 575029-910-001 002 Standard Practices . (f) Install the wing to fuselage fairing 147AT (Refer to AMM Task 53-35-11-400-801). (2) Subtask 575029-410-002-002 - Install the Karman Web and apply the Sealant at FR47 (RH side). Work Zones and Access Panels Zone Access/Work location 148 Manpower Resources Skills AIRFRAME

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 30 5

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# @A340-500/600 SERVICE BULLETIN
Material necessary to do the job Kit 575029A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 EN6115V3X4 14 Bolt 3 ASNA2531-3 14 Nut Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required
References Aircraft Maintenance Manual (AMM) Task 53-35-11-400-801 Fig. A-FBBAA Area to be Inspected Sheet 01 Fig. A-FBCAB Removal/Installation of the Karman Webs at FR47. Sheet 01 Sheet 02 (a) Apply the sealant on the inspected area (Refer to Fig. A-FBBAA Sheet 01) : Corrosion Inhibiting fillet Consistency 09-016 As required (b) Put in position : Refer to Fig. A-FBCAB 1 Web Item (1) Retained at removal (c) Oversize the 14 holes to a diameter comprised between 5.11 in. (0.201 in.) and 5.15 (0.203 in.) as shown on Fig. A-FBCAB Sheet 01 and Fig. A-FBCAB Sheet 02

. (d) Remove the web Item(1) and clean before final installation. (e) Install : Refer to Fig. A-FBCAB 1 Web Item (1) Retained at removal 14 Bolt EN6115V3X4 Item 2 14 Nut ASNA2531-3 Item 3 Apply the protection on the fasteners before installation, refer to SUBTASK 575029-910-001 002 Standard Practices . DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 31 5

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# @A340-500/600 SERVICE BULLETIN (f) Install the wing to fuselage fairing 148AT (Refer to AMM Task 53-35-11-400-801). (3) Subtask 575029-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Restore the systems and the aircraft to normal operating condition. (c) Remove the access platform(s).

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 32 5

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# @A340-500/600 SERVICE BULLETIN

**CONF 001

FR40 FR47

### B

STGR28

(1)

VIEW LOOKING FWD LH SIDE SHOWN RH SIDE SYMMETRICAL 

## B **A B** 

F_SB_575029_5_BCAA_01_01 UPPER HORIZONTAL CRUCIFORM FITTING FR47



### A

Figure A-FBCAA - Sheet 01 Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 33 5

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# @A340-500/600 SERVICE BULLETIN

**CONF 001

HOLE SYMBOL ITEM PN DESCRIPTION REMARKS HOLE DIAMETER MIN MAX

4.78 mm (0.188 in) 4.82 mm (0.190 in) TRANSITION OLD ITEM NEW

FIT (4) (5) 6

7 N
N APPLY MAT. No. 09−013 ON THE FASTENERS (WET ASSEMBLY). 01 INSTALL THE WEB ITEM WITH INTERFAYING SEALANT MAT No. 09−005A. 02 RENEW SEALANT BEAD WITH MAT No. 09−016. 03 **NOTE:**

HEAD ON THE VISIBLE SIDE N

01
01 02 03 03

(1)

4.78 mm (0.188 in) 4.82 mm (0.190 in) TYPICAL VIEW

EN6115V3−3 BOLT ASNA2531−3 NUT EN6115V3−4 BOLT ASNA2531−3 NUT 3
3 TRANSITION FIT F_SB_575029_5_BCAA_02_04 Figure A-FBCAA - Sheet 02 Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 34 5

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# @A340-500/600 SERVICE BULLETIN

**CONF 002

FR40 FR47

### B



## A **B**

(1)

VIEW LOOKING FWD LH SIDE SHOWN RH SIDE SYMMETRICAL 

## B F_SB_575029_5_BCAB_01_01 UPPER HORIZONTAL CRUCIFORM FITTING FR47



### A

Figure A-FBCAB - Sheet 01 Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 35 5

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# @A340-500/600 SERVICE BULLETIN

**CONF 002

HOLE SYMBOL ITEM PN DESCRIPTION REMARKS HOLE DIAMETER MIN MAX 5.15 mm (0.203 in) TRANSITION EN6115V3X4 BOLT OLD ITEM NEW

FIT (2) 2 F APPLY MAT. No. 09−013 ON THE FASTENERS (WET ASSEMBLY). 01 INSTALL THE WEB ITEM WITH INTERFAYING SEALANT MAT No. 09−005A. 02 RENEW SEALANT BEAD WITH MAT No. 09−016. 03 **NOTE:**

HEAD ON HIDDEN SIDE F

01 02 03 03

ASNA2531−3 NUT (3) 3 (1) TYPICAL VIEW

5.11 mm (0.201 in) F_SB_575029_5_BCAB_02_04 Figure A-FBCAB - Sheet 02 Removal/Installation of the Karman Webs at FR47.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 36 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

FR40 FR47


### B FR47



### A



## A **B**

LH SIDE SHOWN RH SIDE SYMMETRICAL
SEALANT TO REMOVE FOR THE INSPECTION PROCEDURE 01 AREA TO BE INSPECTED **NOTE:** 200 mm (7.874 in)



## B EXTERNAL RADIUS

UPPER HORIZONTAL 

### C

POSSIBLE CRACK 01



## C CRUCIFORM FITTING

F_SB_575029_5_BBAA_01_01 Figure A-FBBAA - Sheet 01 Area to be Inspected

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 37 5

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# @A340-500/600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING CRACK YES NO

DO THE INSPECTION AGAIN FITTING AT FR47 AT THE THRESHOLDS AND INTERVALS GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2). DO A SPECIAL DETAILED INSPECTION AS PER NTM 57−18−07 OF THE EXTERNAL RADIUS ON THE UPPER HORIZONTAL CRUCIFORM

AND FOLLOW THEIR

CONTACT AIRBUS

NO FURTHER ACTION

SEND TO AIRBUS THE INSPECTION REPORT WITHIN 90 DAYS CORRECTIVE ACTION BEFORE NEXT FLIGHT

F_SB_575029_5_BAAA_01_04 REFER TO APPENDIX 01 SEND TO AIRBUS THE INSPECTION REPORT WITHIN 90 DAYS REFER TO APPENDIX 01

Figure A-FBAAA - Sheet 01 Flow Chart

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 38 5

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# @A340-500/600 SERVICE BULLETIN Appendix 01 : Inspection Report **CONF ALL The results of the inspection, including no findings, replacement or action to be done, must be forwarded to Airbus department SEES1, on the attached inspection report sheet.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF ALL
**INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A340−57−5029

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

INSPECTION METHOD : − CENTER WING BOX (WB/LR)
SPECIAL DETAILED INSPECTION 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 3614

PLEASE RECORD OTHER FINDINGS : LH SIDE YES NO
CRACK RH SIDE NO YES

F_SB_575029_5_AAAA_01_00 Figure A-FAAAA - Sheet 01 Inspection Report

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN Appendix 02 : Elapsed Time Assumption **CONF ALL This chart is only a proposal. Operators may determine that another way to do the work is more suitable for them.

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN Appendix 02 : Elapsed Time Assumption

**CONF ALL

**ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A340−57−5029**

GET ACCESS (LH SIDE) MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 20.0 10.0 STEPS

2.00 2.00

10 0 5.00 5.00

CLOSE−UP (LH SIDE) 3.00 3.00

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. MANHOURS GIVEN IN VENDOR SERVICE BULLETINS ARE NOT REFLECTED IN THIS GANTT CHART. 01
02 **NOTES:** PER

1

1

1

: : SB ELAPSED TIME (HOURS) 2 4 6 8 RADIUS ON THE UPPER INSPECTION OF THE EXTERNAL HORIZONTAL CRUCIFORM FITTING AT FR47 (LH SIDE) GET ACCESS (RH SIDE) 2.00 2.00

5.00 5.00

CLOSE−UP (RH SIDE) 3.00 3.00 1

1

1 RADIUS ON THE UPPER INSPECTION OF THE EXTERNAL HORIZONTAL CRUCIFORM FITTING AT FR47 (RH SIDE)

F_SB_575029_5_ABAA_01_04 Figure A-FABAA - Sheet 01 Elapsed Time Assumption

DATE: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 2 5

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# @A340-500/600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF THE EXTERNAL RADIUS ON THE UPPER HORIZONTAL CRUCIFORM FITTING AT FRAME 47 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: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 1 5

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# @A340-500/600 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - 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: Feb 25/11 SERVICE BULLETIN No.: A340-57-5029 REVISION No.: 00 - Feb 25/11 Page: 1 5

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