# @ A340 SERVICE BULLETIN SUMMARY

5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : 1 of 4 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft ATA SYSTEM : 57 TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40 MODIFICATION No. : 56467S18944 REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at FR40, initiating at the first fastener hole aft of FR40 datum. The test bench was in post Mod. No. 41652S12091 (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) production solution configuration. The intention of the production solution was also proposed by Service Bulletin A340-57-4036 for retrofit. The structural analysis has led to the issue of the Inspection Service Bulletin A340-57-4089 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)). The Inspection Service Bulletin requires a detailed inspection on A340 aircraft pre Mod. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) including mandatory and recommended thresholds and repetitive inspection intervals. This Service Bulletin recommends to modify the fasteners installation in the junction of the keel beam fitting at FR40. Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin A340-57-4089 for aircraft on which Mod. No. 44360S13013 (WING - CENTER WING - MODIFY FR40 and FRONT SPAR) in not embodied. This fix for the existing mandatory Inspection Service Bulletin at frame 40 keel beam.

EVALUATION TABLE

COMPLIANCE Recommended CANCELS INSPECTION SB Yes POTENTIAL AD No A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

# @ A340 SERVICE BULLETIN SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. EFFECTIVITY This Service Bulletin is applicable to these operators : AAW ACA AFR AUA CES CPA DLH ETD GFA IBE MAU MSR PAL SWR THY UAE VIR NOTE : This Service Bulletin is only applicable to aircraft on which modification No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340 COMMONALITY ITEMS) is embodied and modification No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) and modification No. 44360S13013 (WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) are not embodied. CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : 57.11.00.005 OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None NATURE OF THE WORK AIRCRAFT : YES EQUIPMENT : NO COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No KIT PRICE (USD) A01R00 180

MODIFICATION CLASSIFICATION MAJOR 56467S18944 MINOR None EVALUATION TABLE

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# @ A340 SERVICE BULLETIN SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved HARD : NO SOFT : NO OBRM : NO MANPOWER Config. 01

MATERIAL INFORMATION AIRCRAFT DATA Config. 01 Kit 574106A01R00 Bolts, nuts and washer APPENDICES Appendix 1 - REPORT TOTAL MANHOURS 53.0 ELAPSED TIME (HOURS) 38.0

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# @ A340 SERVICE BULLETIN SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 4

# @ A340 SERVICE BULLETIN

5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : 1 of 31 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 ATA SYSTEM : 57 TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40 MODIFICATION No. : 56467S18944 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 A. EFFECTIVITY (1) Models 340-212 340-213 340-311 340-312 340-313 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0114 0115 0117 0123 0125 0126 0128 0129 0131 0133-0137 0139 0141 0142 0145-0147 0149-0152 0154 0156-0161 0163 0164 0166-0170 0173-0175 NOTE : This Service Bulletin is only applicable to aircraft on which modification No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340 COMMONALITY ITEMS) is embodied and modification No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) and modification No. 44360S13013 (WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) are not embodied.

# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (b) 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.

(c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 0114-0115 0117 0123 0125-0126 0128-0129 0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164 0166-0170 0173-0175

NOTE : Config. 01 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. OPERATOR MSN AAW 0151 ACA 0154 0167 0170 0175 AFR 0168 0174 AUA 0169 CES 0129 0131 0141 0161 CPA 0123 0126 0128 0136 0137 0142 0147 0157 0160 DLH 0135 0158 ETD 0117 GFA 0133 IBE 0125 0134 0145 0146 MAU 0152 MSR 0156 0159 PAL 0173 SWR 0150 THY 0115 UAE 0139 0149 0163 0166 VIR 0114 0164

KIT No. QTY PER A/C CONFIGURATION 574106A01R00 2 01

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at FR40, initiating at the first fastener hole aft of FR40 datum. The test bench was in post Mod. No. 41652S12091 (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) production solution configuration. The intention of the production solution was also proposed by Service Bulletin A340-57-4036 for retrofit. The structural analysis has led to the issue of the Inspection Service Bulletin A340-57-4089 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)). The Inspection Service Bulletin requires a detailed inspection on A340 aircraft pre Mod. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) including mandatory and recommended thresholds and repetitive inspection intervals. (2) Objective/Action This Service Bulletin recommends to modify the fasteners installation in the junction of the keel beam fitting at FR40. (3) Advantages Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin A340-57-4089 for aircraft on which Mod. No. 44360S13013 (WING - CENTER WING - MODIFY FR40 and FRONT SPAR) in not embodied. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access.

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (b) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. (c) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners, for aircraft with bush installed on hole 5. (d) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. E. COMPLIANCE (1) Classification Recommended (2) Accomplishment Timescale Accomplishment of this Service Bulletin is recommended at the earliest opportunity where manpower and facilities are available. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 Get access 12.0 Removal of the ducts 6.0 Removal of fastener hole 5 1.0 Rotating probe inspection hole 5 1.0 Installation of the fastener hole 5 2.5 Removal of fastener holes 6 and 7 2.0

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA Not changed J. REFERENCES

PMS 01-05-05 Service Bulletin No. A340-57-4036 Service Bulletin No. A340-57-4089 Appendix 1 K. PUBLICATIONS AFFECTED Not changed L. INTERCHANGEABILITY/MIXABILITY Not applicable Rotating probe inspection holes 6 and 7 1.5 Cold expansion hole 6 1.5 Installation of fasteners holes 6 and 7 2.5 Installation of the ducts 6.0 Test 2.0 Close-up 15.0 TOTAL MANHOURS 53.0 ELAPSED TIME (HOURS) 38.0

Aircraft Maintenance Manual (AMM) : 06-41-53 12-34-24 20-21-11 21-20-00 21-53-18 27-84-45 28-25-00 32-12-00 36-12-41 53-35-13 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) : 20-55-00 Non destructive Testing Manual (NTM) : 51-10-01 51-10-18 Service Information Letter (SIL) : 51-012 Structural Repair Manual (SRM) : 51-42-11 51-43-00 51-44-11 51-48-00 51-76-12

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DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material 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 SPARES SUPPORT AND SERVICES Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 (2) Price and Availability Kit 574106A01R00 Cost : 180.00 US Dollars Availability : 120 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 the Kit(s) 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 574106A01R00 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 25 EN6115-6Y-20 1 Bolt 26 NSA5368-616D 1 Washer 27 ASNA2531-6 1 Nut 31 ASNA2531-5 1 Nut 32 EN6115-5-12 1 Bolt 33 ASNA2529-6 1 Nut 34 EN6115V6Y-16 1 Bolt

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : 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. D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials

(2) Components None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR None F. TOOLING — PRICE AND AVAILABILITY (1) To accomplish this Service Bulletin, it is necessary to use the following tools and equipment. (a) Equipment and materials for the check of the holes as per NTM 51-10-01 Part 6. (b) Equipment and materials for the check of the holes as per NTM 51-10-18 Part 6. (2) Fatigue Technology Incorporated (FTI) has allocated the following tool kit numbers for cold working : NOTE : For definition of capital, durable and expendable tools, refer to SIL 51-012. — Capital tooling : ref. FTI-A340-57-4106-1 This tool reference include all capital, durable and expendable tooling kits regardless of effectivity but capital tooling is 35 F5332433420000 1 Washer 42 NSA5368PD616D 1 Washer

DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP
Fuel Tank Sealant Polysulfide 09-002B As required Corrosion Inhibiting Brush Consistency 09-013B As required Solvent General Purpose 11-026 As required ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved normally already and previously bought by the operator as a long term investment or loaned from FTI. — Durable tooling : ref. DK-A340-57-4106-1 NOTE : In this durable tool, there is the minimum quantity necessary to accomplish this Service Bulletin on one aircraft. In case of accomplishment of this Service Bulletin on more than one aircraft, operator can define the quantity of durable tool to be ordered by reference to SIL 51-012. — Expendable tooling : ref. EK-A340-57-4106-1 NOTE : In this expendable tool, there is the minimum quantity necessary to accomplish this Service Bulletin on one aircraft. One expendable tool has to be ordered for each aircraft where this Service Bulletin is accomplished. Operators interested in obtaining the FTI tool kit should contact : Fatigue Technology Inc. 401 Andover Park West SEATTLE, WA 98188-7605 USA E.Mail : sales@fatiguetech.com E.Mail : aog@fatiguetech.com Phone : (1) 206 2462010 Fax : (1) 206 2449886 G. SPECIAL TOOLS None

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DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS : — PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. — REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. (1) Preparation (a) Config. 01 1 Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page block 201). 2 Put the access platform(s) in position. 3 Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page block 201). 4 Do the preparation procedure as specified in removal/installation of the air-conditioning distribution ducts (Refer to AMM 21-20-00 Page block 201). 5 Do the preparation procedure as specified in removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page block 401). 6 Do the preparation procedure as specified in removal/installation of the APU bleed-air ducts (Refer to AMM 36-12-41 Page block 401). 7 Remove the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page block 401 and AMM 06-41-53).

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 8 Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page block 401). 9 Defuel the center tank (Refer to AMM 28-25-00 Page block 301). 10 Remove the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45 Page block 401). 11 Get access to the work area. (2) Standard Practices (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with Solvent General Purpose (Mat No. 11-026) . (c) Use a non-metallic spatula to remove the sealant and clean the areas with Solvent General Purpose (Mat No. 11-026) . (d) Drill and deburr the holes (Refer to SRM 51-44-11). (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) on all the fasteners to be installed (wet assembly). (g) For the oversize and alternative fasteners (Refer to SRM 51-43-00). (h) Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page block 201). (i) Do the cold expansion of the holes (Refer to SRM 51-48-00). (j) Apply the sealant (Refer to SRM 51-76-12). (k) Install the plug with liquid nitrogen (Refer to PMS 01-05-05 ). B. MODIFICATION (1) Config. 01 (a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. Refer to Figures 1 and 2 1 On RH side, remove the air conditioning duct. Refer to Figure 1

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Remove :

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 21-53-18 Page block 401). 2 On RH side, remove the air ventilation duct. Refer to Figure 2 a Remove :

3 On LH side, remove the necessary APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page block 401). 4 Put the blanking plugs on the disconnected line ends. (b) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. Refer to Kit 574106A01R00 Refer to Figure 3 NOTE : Description below is given for one side of the aircraft, two Kit 574106A01R00 are necessary to modify one aircraft. 1 Inspect the hole 5.

1 Duct Item (8) Retain 1 Insulation Item (9) Retain 1 Nut Item (10) Retain 1 Bolt Item (11) Retain 1 Washer Item (12) Retain 2 Screw Item (13) Retain 2 Washer Item (14) Retain 2 Nut Item (15) Retain 1 Clamp Item (16) Retain 1 Clamp Item (17) Retain

1 Duct Item (20) Retain 8 Clamp Item (21) Retain 4 Clamp Item (22) Retain 2 Sleeve Item (23) Retain 1 Sleeve Item (24) Retain

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Refer to Figure 3 , Sheets 1 and 2 a Remove :

b Remove the sealant and clean the hole. c Do a rotating probe inspection (Refer to NTM 51-10-01) through all the layers. — If no crack is detected, do the operations given in paragraph (1)(b)2. — If crack is detected do the operations given in paragraph (1)(b)3. 2 No crack, oversize the hole 5 in the keel beam. Refer to Figure 3 , Sheets 1 , 3 and 4 a Ream the hole at the level of the keel beam only to a diameter comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). c Oversize the hole 5 through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). d Clean the drilled area. e Install :

NOTE (01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) (wet assembly). NOTE (02) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat No. 09-002B) . 3 Crack detected, oversize the hole 5 in the keel beam. Refer to Figure 3 , Sheets 1 , 3 and 4 1 Bolt Item (41) Discard 1 Nut Item (4) Discard

1 Bolt EN6115V6Y-16 Item 34 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616D Item 42

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Ream the hole 5 at the level of the keel beam only to a diameter comprised between 15mm (0.591in.) and 15.2mm (0.598in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 0.5mm (0.02in.) and 0.7mm (0.028in.). b Do a rotating probe inspection at the level of the keel beam only (Refer to NTM 51-10-18). — Crack finding, contact AIRBUS. — No crack finding, oversize the hole in the keel beam only to a diameter comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). — Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). — Oversize the hole 5 through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.) — Install :

NOTE (01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) (wet assembly). NOTE (02) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat No. 09-002B) . 4 Inspect holes 6 and 7 Refer to Figure 3 , Sheets 1 and 2 a Remove :

b Remove the sealant and clean the holes. c Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to NTM 51-10-01). — If a crack is detected, contact AIRBUS. 1 Bolt EN6115V6Y-16 Item 34 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616D Item 42

1 Nut Item (2) Discard 1 Nut Item (4) Discard 1 Bolt Item (1) Discard 1 Bolt Item (3) Discard

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — If no crack is detected, do the operations given in paragraphes (1)(b)5 and 6. 5 Do the cold working of the hole 6. Refer to Figure 3 , Sheets 1 , 3 and 4 a Ream the hole to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. b Clean the drilled area. c Do the cold working of the hole (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. d Ream the hole to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. e Clean the drilled area. f Install :

NOTE (01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) (wet assembly). NOTE (02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat No. 09-002B) . 6 Install the fastener in hole 7. Refer to Figure 3 , Sheets 1 , 3 and 4 a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install :

NOTE (01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) (wet assembly). 1 Bolt EN6115-6Y-20 Item 25 1 Nut ASNA2531-6 Item 27 1 Washer NSA5368-616D Item 26

1 Bolt EN6115-5-12 Item 32 1 Nut ASNA2531-5 Item 31

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE (02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat No. 09-002B) . NOTE (03) If necessary, contact AIRBUS for a specific washer solution. 7 For the report after modification, refer to Appendix 01 . (c) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners, for aircraft with bush installed on hole 5. Refer to Figure 4 NOTE (01) Description below is given for one side of the aircraft, two Kit 574106A01R00 are necessary to modify one aircraft. NOTE (02) If the diameter of the bush is >13mm (0.512in.) or if the bush is installed in other layers than keel beam fitting only, contact AIRBUS. 1 Inspect the hole 5. Refer to Figure 4 , Sheets 1 and 2 a Remove :

b Remove the sealant and clean the hole. c Do a rotating probe inspection (Refer to NTM 51-10-18) through all the layers. — If crack is detected, contact AIRBUS. — If no crack is detected, do the operations given in paragraph (1)(c)2. 2 No crack finding, oversize the hole in the keel beam. Refer to Figure 4 , Sheets 1 , 3 and 4 a Ream the hole at the level of the keel beam only to a diameter comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.) b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 1 Bush Item (5) Discard

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved c Oversize the hole through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.) d Install :

NOTE (01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) (wet assembly). NOTE (02) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat No. 09-002B) . 3 Inspect holes 6 and 7. Refer to Figure 4 , Sheets 1 and 2 a Remove :

b Remove the sealant and clean the holes. c Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to NTM 51-10-01). — If a crack is detected, contact AIRBUS. — If no crack is detected, do the operations given in the paragraphes (1)(c)4 and 5. 4 Do the cold working of the hole 6. Refer to Figure 4 , Sheets 1 , 3 and 4 a Ream the hole to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. Clean the drilled area. b Do the cold working of the hole (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 1 Bolt EN6115V6Y-16 Item 34 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616D Item 42

1 Nut Item (2) Discard 1 Nut Item (4) Discard 1 Bolt Item (1) Discard 1 Bolt Item (41) Discard

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved c Ream the hole to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. d Clean the drilled area. e Install :

NOTE (01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) (wet assembly). NOTE (02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat No. 09-002B) . 5 Install the fastener in hole 7. Refer to Figure 4 , Sheets 1 , 3 and 4 a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install :

NOTE (01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat No. 09-013B) (wet assembly). NOTE (02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat No. 09-002B) . NOTE (03) If necessary, contact AIRBUS for a specific washer solution. 6 For the report after modification, refer to Appendix 01 . (d) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Refer to Figures 1 and 2 1 Remove the blanking plugs on the disconnected line ends. 2 On LH side, install (if removed) the APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page block 401). 1 Bolt EN6115-6Y-20 Item 25 1 Nut ASNA2531-6 Item 27 1 Washer NSA5368-616D Item 26

1 Bolt EN6115-5-12 Item 32 1 Nut ASNA2531-5 Item 31

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 3 On RH side, install (if removed) the air ventilation duct. Refer to Figure 2 a Install :

NOTE : Items (20) thru (24) were retained at removal. 4 On RH side, install (if removed) the air conditioning duct. Refer to Figure 1 a Install :

NOTE (01) Reconnect the rod Items (18) and (19). NOTE (02) For the installation of the sensor 542HH (Refer to AMM 21-53-18 Page block 401). NOTE (03) Items (8) thru (17) were retained at removal. C. TEST (1) Config. 01 (a) Preparation 1 Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page block 401). 2 Refuel the center tank (Refer to AMM 28-25-00 Page block 301). 3 Install the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45 Page block 201). 1 Duct Item (20) 8 Clamp Item (21) 4 Clamp Item (22) 2 Sleeve Item (23) 1 Sleeve Item (24)

1 Duct Item (8) 1 Insulation Item (9) 1 Nut Item (10) 1 Bolt Item (11) 1 Washer Item (12) 2 Screw Item (13) 2 Washer Item (14) 2 Nut Item (15) 1 Clamp Item (16) 1 Clamp Item (17)

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 4 Install the removed air-conditioning distribution ducts (Refer to AMM 21-20-00 Page block 201). (b) Tests 1 Do the test after the removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page block 401). 2 Do the test after the removal/installation of the APU bleed air ducts (Refer to AMM 36-12-41 Page block 401). 3 Do the test after the removal/installation of the covers (147AZ and 148AZ) (Refer to AMM 57-17-11 Page block 401). 4 Do the test after the removal/installation of the torque shaft assy (5010CW and 5070CW)(Refer to AMM 27-84-45 Page block 401). 5 Do the test after the removal/installation of the air conditioning distribution ducts (Refer to AMM 21-20-00 Page block 201). D. CLOSE UP (1) Config. 01 (a) Do the close-up procedure as specified in removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page block 401). (b) Do the close-up procedure as specified in removal/installation of the APU bleed-air ducts (Refer to AMM 36-12-41 Page block 401). (c) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page block 401 and AMM 06-41-53). (d) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page block 201). (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Remove the access platform(s). (g) Restore the systems and the aircraft to normal operating condition. E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 1 Config. 01 : Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for Access.

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 2 Sheet 1 Config. 01 : Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for Access.

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 3 Sheet 1 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 3 Sheet 2 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 3 Sheet 3 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 3 Sheet 4 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 4 Sheet 1 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 4 Sheet 2 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 4 Sheet 3 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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# @ A340 SERVICE BULLETIN

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 4 Sheet 4 Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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# @ A340 SERVICE BULLETIN APPENDIX 01

5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : 1 of 2 Printed in FRANCE © AIRBUS, 2007 All rights reserved 1. REPORT The results of the accomplishment of this Service Bulletin, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department AI/SEE8, on the attached inspection report sheet.

# @ A340 SERVICE BULLETIN APPENDIX 01

DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 1 Inspection Report

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# @ A340 SERVICE BULLETIN REPORTING SHEET

5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : 1 of 1 Printed in FRANCE © AIRBUS, 2007 All rights reserved TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40 MODIFICATION No. : 56467S18944
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:..........................

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........................................ B - SB HAS BEEN embodied on aircraft:.....................

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........................................ Operator comments:..............................

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....................................... 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: 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.

# @ A340 SERVICE BULLETIN QUALITY PERCEPTION FORM

5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340—57—4106 REVISION No. : 00 — Page : 1 of 1 Printed in FRANCE © AIRBUS, 2007 All rights reserved 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 X Mod/Inspection X Manpower Operator Supplied 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 Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.