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@A340
SERVICE BULLETIN
SUMMARY AIRBUS
CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 This summary is for information only and is not approved for modification of the aircraft.
ATA SYSTEM: 57 TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER HOLES NO 25,38,39 and 43 AT FRAME 40 VERTICAL WEB BELOW
CENTER WING BOX LOWER PANEL **CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION MAJOR 206048S33788 MINOR None NOTE : As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The area at Frame (FR) 40 is subjected to a specific maintenance program. A new campaign of modifications has been launched to improve the maintenance program, decrease the number of maintenance actions and to improve the structural potential of the aircraft to meet the Extended Service Goal (ESG)/Design Service Goal (DSG).
This Service Bulletin recommends the application of Cold Working on holes 25, 38, 39 and 43 at FR40 to improve the fatigue behaviour.
Depending on the configuration, this reinforcement consists in doing a first or second cold expansion of fastener holes 25, 38, 39 and 43 and installing oversized fastener with high interference.
Accomplishment of this Service Bulletin will contribute to prevent cracks and will increase the fatigue life in the area of FR40.
Depending on configuration, accomplishment of this Service Bulletin cancels the requirements of Inspection Service Bulletin No. A340-57-4125 for holes 25, 38, 39 and 43, if accomplished after the lower bound described in Inspection Service Bulletin No. A340-57-4125. For hole 25, for Aircraft in Conf 004 and 005, this modification Service Bulletin is not terminative and must be monitored by Inspection Service Bulletin No. A340-57-4125.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
SUMMARY
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE RECOMMENDED (1)
CANCELS INSPECTION SB NO
POTENTIAL AD NO
A/C OPERATION AFFECTED NO
RELIABILITY AFFECTED NO
PAX COMFORT AFFECTED NO
COST SAVING NO
LROPS AFFECTED NO
STRUCTURAL LIFE EXTN NO
VENDOR SB INVOLVED NO NOTE
(1) : Service Bulletin recommended to be accomplished to prevent significant operational disruptions.
MATERIAL PRICE INFORMATION **CONF 001
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
QTY PER A/C
PRICE PER
A/C (USD)
MAIN PARTS Kit 574139A01R01 1
120.00 Bolts, Nuts Kit 574139A02R00 1
50.00 Bolts, Nuts TOTAL
170.00 Standard tool TOOLA01 1 See SB Durable Tool Kit Standard tool TOOLA02 1 See SB Expendable Tool Kit **CONF 002
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
QTY PER A/C
PRICE PER
A/C (USD)
MAIN PARTS Kit 574139A01R01 1
120.00 Bolts, Nuts Standard tool TOOLA01 1 See SB Durable Tool Kit Standard tool TOOLA02 1 See SB Expendable Tool Kit **CONF 003
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
QTY PER A/C
PRICE PER
A/C (USD)
MAIN PARTS Kit 574139A01R01 1
120.00 Bolts, Nuts Kit 574139A02R00 1
50.00 Bolts, Nuts TOTAL
170.00 Standard tool TOOLA01 1 See SB Durable Tool Kit Standard tool TOOLA02 1 See SB Expendable Tool Kit DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
SUMMARY **CONF 004
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
QTY PER A/C
PRICE PER
A/C (USD)
MAIN PARTS Kit 574139A01R01 1
120.00 Bolts, Nuts Kit 574139A02R00 1
50.00 Bolts, Nuts TOTAL
170.00 Standard tool TOOLA01 1 See SB Durable Tool Kit Standard tool TOOLA02 1 See SB Expendable Tool Kit
EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :
09M 83V ABD ACA AFR AIB ALD ARG AXY BEK BOE CAL CPA DLH EDW F2I FIN GAF HFM HFY IBE IRM LAN MAU MDG MRJ O2X PAL PUE QAF ROI S3R SAA SAS SLM SVW SWR THT THY UAE
CONCURRENT REQUIREMENTS None
REFERENCES / REPERCUSSIONS TFU
57.11.00.007 OEB None AOT None SIL None ISI None
LINE MAINTENANCE AFFECTED No
LIFE LIMIT None OTHER None
NATURE OF THE WORK
AIRCRAFT YES
EQUIPMENT NO HARD NO SOFT NO OBRM NO
MANPOWER **CONF 001 Task 574139-831-801-001: Modification
TOTAL MANHOURS
29.00 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
SUMMARY Task 574139-831-801-001: Modification
ELAPSED TIME (HOURS)
14.75 **CONF 002 Task 574139-831-801-001: Modification
TOTAL MANHOURS
26.50
ELAPSED TIME (HOURS)
13.50 **CONF 003 Task 574139-831-801-001: Modification
TOTAL MANHOURS
29.00
ELAPSED TIME (HOURS)
14.75 **CONF 004 Task 574139-831-801-001: Modification
TOTAL MANHOURS
29.00
ELAPSED TIME (HOURS)
14.75
APPENDICES **CONF ALL Appendix 01 - Manpower Gantt Chart Appendix 02 - Configuration Definition table DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
SUMMARY **CONF 001, 003 thru 004
VIEW LOOKING AFT
RH SHOWN
LH SYMMETRICAL BU P INBD
CENTER WING BOX
LOWER PANEL REFERENCE
COLD WORKING OF 4 FASTENER HOLES Z140 A FR40 STGR39RH STGR38RH H25 H38 H39 H43 A FR47 FR40 B F_SB_574139_5_SAAA_01_03 Figure A-FSAAA - Sheet 01 Cold Working of the Fasteners Holes 25, 38, 39 and 43 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
SUMMARY **CONF 002
VIEW LOOKING AFT
RH SHOWN
LH SYMMETRICAL BU P INBD
CENTER WING BOX
LOWER PANEL REFERENCE
COLD WORKING OF 3 FASTENER HOLES Z140 A FR40 STGR39RH STGR38RH H38 H39 H43 A FR47 FR40 B F_SB_574139_5_SAAB_01_03 Figure A-FSAAB - Sheet 01 Cold Working of the Fasteners Holes 38, 39 and 43 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN AIRBUS
CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 ATA SYSTEM: 57 TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER HOLES NO 25,38,39 and 43 AT FRAME 40 VERTICAL WEB BELOW
CENTER WING BOX LOWER PANEL MODIFICATION No.: 206048S33788 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent.
1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE : This modification is applicable by Service Bulletin only.
NOTE : This Service Bulletin is only applicable to aircraft on which MOD No.
44360S13013 or MOD No. 44360S13482 is embodied.
(1) Models 340-212 340-213 340-312 340-313
(2) Effectivity by MSN 0178-0180 0185-0186 0190 0192-0194 0197 0199 0201-0202 0204 0207-0208 0210 0212-0215 0217-0218 0220-0221 0227-0228 0233 0236-0237 0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0273-0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329 0331-0332 0335 0347 0352 0354-0355 0363 0367 0373-0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0415 0424 0430 0433-0435 0438 0446-0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546 0554 0556 0559 0561-0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800 0835 0844 0921 0938 0955 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
(3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.
OPERATOR MSN 09M 0483 83V 0280 0292 ABD 0210 ACA 0278 AFR 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399 AIB 0192 0243 0264 ALD 0178 ARG 0193 0373 AXY 0374 BEK 0381 BOE 0554 CAL 0402 0406 0411 0415 0433 0541 CPA 0208 0218 0220 0227 0228 DLH 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447 EDW 0562 F2I 0214 FIN 0835 0844 0921 0938 GAF 0274 0355 HFM 0367 HFY 0190 0202 IBE 0217 0221 0329 IRM 0282 LAN 0363 MAU 0194 0268 0793 0800 MDG 0319 MRJ 0257 O2X 0273 PAL 0302 0318 0332 0387 0459 0474 PUE 0212 0215 QAF 0528 ROI 0199 0201 S3R 0204 SAA 0197 0378 0544 0582 0590 0643 0646 0651 SAS 0413 0424 0430 0435 0450 0467 0470 SLM 0242 SVW 0955 SWR 0179 0263 0538 0545 0546 0556 0559 0561 0585 0598 THT 0385 0395 0438 0446 0668 THY 0180 0270 0331 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
OPERATOR MSN UAE 0185 0236
(4) Configuration by MSN MSN
CONFIGURATION 0178 0180 0185 0190 0192 0199 0201 0202 0204 0212 0214 0215 0236 0242 0243 0257 0264 0270 0273 0278 0280 0282 0292 0318 0319 0331 0363 0373 0378 0385 0395 0413 0424 0430 0435 0438 0446 0450 0467 0470 001 002 0179 0186 0193 0194 0197 0207 0208 0210 0213 0217 0218 0220 0221 0227 0228 0233 0237 0245 0246 0252 0260 0263 0268 0274 0297 0302 0304 0307 0310 0321 0325 0327 0329 0332 0335 0347 0352 0354 0355 0367 0374 0377 0379 0381 0387 0390 0399 0402 0406 0411 0415 0433 0434 0447 0459 0474 0483 0538 002 0528 0541 002 003 0544 0545 0546 0554 0556 0559 0561 0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800 003 0835 0844 0921 0938 0955 004
(5) Configuration definition The following table gives further information of the Configuration Definition.
**CONF 001 Config 001 is valid for aircraft on which:
- MOD No. 49202S16307 is not embodied
- Service Bulletin No. A330-57-4090 is not accomplished.
**CONF 002 Config 002 is valid for aircraft on which:
- MOD No. 49202S16307 is not embodied
- Service Bulletin No. A330-57-4090 is accomplished.
**CONF 003 Config 003 is valid for aircraft on which:
- MOD No. 49202S16307 is embodied
- MOD No. 55306S18660 is not embodied.
**CONF 004 Config 004 is valid for aircraft on which:
- MOD No. 49202S16307 is embodied
- MOD No. 55306S18660 is embodied.
For further information concerning the Configuration Definition, refer to Appendix 02 - Configuration Definition table .
(6) Material Effectivity NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN **CONF 001, 003 thru 004
MATERIAL
QTY PER A/C
SEE NOTES Kit 574139A01R01 1 Kit 574139A02R00 1 Consumable CMLA01 1 Standard tool TOOLA01 1 Standard tool TOOLA02 1 **CONF 002
MATERIAL
QTY PER A/C
SEE NOTES Kit 574139A01R01 1 Consumable CMLA01 1 Standard tool TOOLA01 1 Standard tool TOOLA02 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON
(1) History The area at Frame (FR) 40 is subjected to a specific maintenance program. A new campaign of modifications has been launched to improve the maintenance program, decrease the number of maintenance actions and to improve the structural potential of the aircraft to meet the Extended Service Goal (ESG)/Design Service Goal (DSG).
(2) Objective/Action This Service Bulletin recommends the application of Cold Working on holes 25, 38, 39 and 43 at FR40 to improve the fatigue behaviour.
Depending on the configuration, this reinforcement consists in doing a first or second cold expansion of fastener holes 25, 38, 39 and 43 and installing oversized fastener with high interference.
(3) Advantages Accomplishment of this Service Bulletin will contribute to prevent cracks and will increase the fatigue life in the area of FR40.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
(4) Operational/Maintenance Consequences Depending on configuration, accomplishment of this Service Bulletin cancels the requirements of Inspection Service Bulletin No. A340-57-4125 for holes 25, 38, 39 and 43, if accomplished after the lower bound described in Inspection Service Bulletin No.
A340-57-4125. For hole 25, for Aircraft in Conf 004 and 005, this modification Service Bulletin is not terminative and must be monitored by Inspection Service Bulletin No.
A340-57-4125.
D. DESCRIPTION To accomplish this Service Bulletin it is necessary to :
**CONF 001 Task 574139-831-801-001: Modification
(1) Remove the Fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(2) Do an Inspection of the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(3) Do a Cold Working of the fastener Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(4) Install the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(5) Remove the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(6) Do an Inspection of the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(7) Do a Cold Working of the fastener Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(8) Install the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side **CONF 002 Task 574139-831-801-001: Modification
(1) Remove the Fastener at the Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(2) Do an Inspection of the Fastener at the Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(3) Do a Cold Working of the fastener Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340
SERVICE BULLETIN
(4) Install the fastener at the Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(5) Remove the fastener at the Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(6) Do an Inspection of the fastener at the Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(7) Do a Cold Working of the fastener Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(8) Install the fastener at the Holes 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side **CONF 003 Task 574139-831-801-001: Modification
(1) Remove the Fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(2) Do an Inspection of the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(3) Do a Cold Working of the fastener Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(4) Install the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(5) Remove the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(6) Do an Inspection of the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(7) Do a Cold Working of the fastener Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side
(8) Install the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the RH side **CONF 004 Task 574139-831-801-001: Modification
(1) Remove the Fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(2) Do an Inspection of the fastener at the Holes 25, 38, 39 and 43 between STGR38 and STGR40 at FR40 on the LH side
(3) Do a Cold Working of the fastener Holes 25, 38, 39 and 43 between STGR38 and DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4139 REVISION No.: 00 - Nov 23/16 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.