# @A330 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 FASTENER HOLES AT FRAME 40 VERTICAL WEB BELOW INTRADOS **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During ALI 57.11.04 inspections tasks on the rear fitting of the Frame 40 between stringer 38 & 39 LH/RH side, cracks have been found on the fasteners next to the one to be inspected. After reaming at second oversize of the subjected hole, the crack is still present. This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web between stringer 38 & 39 - below Intrados, left and right sides for all A330 aircraft pre-modification 44360 embodiment.The aim of this Inspection Service Bulletin is to implement the corrective inspection necessary to the inservice aircraft. For aircraft on which FR40 web is already repaired on one side or on both sides as per Repair Instruction R57115092, Inspection task of this ISB is not necessary for the repaired side(s); dedicated Repair Design Approval Sheet (RDAS) instructions have to be followed. For aircraft previously inspected as per Technical Disposition Ref. LR57D11029171 or LR57D11030741, next inspection is due based on interval value given in this ISB. Accomplishment of this ISB will permit early detection of cracks on the Frame 40 Vertical Web between stringer 38 & 39 - below Intrados, left and right sides and will ensure that the structural integrity of the area is maintained. The Task ALI 57.11.04 applicable to aircraft pre-mod 44360 will be superseded by accomplishment of ISB 57-3114.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 1 5

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# @A330 SERVICE BULLETIN SUMMARY 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 ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573114A01R04 2 17,560.00 Screws, Nuts EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

BEL BER CPA GIA HDA HFY KAL MAS OHY RSY SAI THA TSC XAX This Service Bulletin is only applicable to aircraft on which Mod. No. 44360S13013 and 44360S13482 are not embodied. CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.11.00.007 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER OIT Ref. 999.0082/12 OTHER OIT Ref. 999.0086/11 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 2 5

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# @A330 SERVICE BULLETIN SUMMARY MANPOWER Task 573114-832-801-001: Inspection TOTAL MANHOURS 37.25 ELAPSED TIME (HOURS) 37.25 Task 573114-833-801-001: Repair TOTAL MANHOURS 49.25 ELAPSED TIME (HOURS) 49.25 APPENDICES Appendix 01 : Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 3 5

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# @A330 SERVICE BULLETIN SUMMARY

**CONF ALL

FR40 LH SIDE SHOWN RH SIDE SYMMETRICAL **NOTE:** HOLES OF AREA A TO BE INSPECTED HOLE OF AREA B TO BE INSPECTED VIEW LOOKING AFT FR47

FR40



### A − Z141 Z142 

## A

**B** STGR38

STGR39

STGR40 

### B **B**

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_SAAA_01_02 Figure A-FSAAA - Sheet 01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 4 5

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# @A330 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 FASTENER HOLES AT FRAME 40 VERTICAL WEB BELOW INTRADOS 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 NOTE: This Service Bulletin is only applicable to aircraft on which Mod. No. 44360S13013 and 44360S13482 are not embodied. (1) Models 330-301 330-321 330-322 330-341 330-342 (2) Effectivity by MSN 0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0067 0069-0073 0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0113 0116 0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 1 5

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# @A330 SERVICE BULLETIN

OPERATOR MSN BEL 0030 0037 0045 0082 0095 BER 0127 CPA 0012 0017 0102 0113 0118 0121 0155 GIA 0138 0140 0144 0148 0153 0165 HDA 0071 0083 0099 0106 0109 HFY 0096 KAL 0162 0172 MAS 0067 0069 0073 0077 0100 0107 0110 0116 0119 OHY 0072 0087 0098 0143 RSY 0120 0171 SAI 0055 0070 0086 THA 0050 0060 0062 0064 0065 0066 0112 0122 TSC 0111 0132 XAX 0054 (4) Configuration by MSN MSN CONFIGURATION 0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064 0065 0066 0067 0069 0070 0071 0072 0073 0077 0082 0083 0086 0087 0095 0096 0098 0099 0100 0102 0106 0107 0109 0110 0111 0112 0113 0116 0118 0119 0120 0121 0122 0127 0132 0138 0140 0143 0144 0148 0153 0155 0162 0165 0171 0172 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Kit 573114A01R04 2 Consumable CMLA01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History During ALI 57.11.04 inspections tasks on the rear fitting of the Frame 40 between stringer 38 & 39 LH/RH side, cracks have been found on the fasteners next to the one to be inspected. After reaming at second oversize of the subjected hole, the crack is still present.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 2 5

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# @A330 SERVICE BULLETIN (2) Objective/Action This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web between stringer 38 & 39 - below Intrados, left and right sides for all A330 aircraft pre-modification 44360 embodiment. The aim of this Inspection Service Bulletin is to implement the corrective inspection necessary to the in-service aircraft. For aircraft on which FR40 web is already repaired on one side or on both sides as per Repair Instruction R57115092, Inspection task of this ISB is not necessary for the repaired side(s); dedicated Repair Design Approval Sheet (RDAS) instructions have to be followed. For aircraft previously inspected as per Technical Disposition Ref. LR57D11029171 or LR57D11030741, next inspection is due based on interval value given in this ISB. (3) Advantages Accomplishment of this ISB will permit early detection of cracks on the Frame 40 Vertical Web between stringer 38 & 39 - below Intrados, left and right sides and will ensure that the structural integrity of the area is maintained. (4) Operational/Maintenance Consequences The Task ALI 57.11.04 applicable to aircraft pre-mod 44360 will be superseded by accomplishment of ISB 57-3114. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 573114-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, LH side (2) Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, RH side (3) Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, LH side (4) Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, RH side (5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side (6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side (7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 3 5

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# @A330 SERVICE BULLETIN (8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side (9) Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side (10) Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side Task 573114-833-801-001: Repair (1) Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side (2) Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side (3) Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, LH side (4) Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, RH side (5) Install new same fastener of the Area B in transition fit, LH side (6) Install new same fastener of the Area B in transition fit, RH side (7) Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, LH side (8) Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, RH side (9) Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, LH side (10) Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, RH side (11) Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, LH side (12) Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, RH side (13) Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side (14) Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side (15) Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side (16) Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 4 5

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# @A330 SERVICE BULLETIN (17) Install new fastener of the Area B in transition fit, LH side (18) Install new fastener of the Area B in transition fit, RH side E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Table 1: Special Detailed Inspection of the Fasteners Holes of the Area A of the frame 40, LH and RH sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

ALI 57-11-04 accomplished Do a Rototest Inspection Pre SB No.A330-57-3083 on LH and RH Sides, refer to SUBTASK 573114-832-003 001 for LH Side and to SUBTASK 573114-832-008 001 for RH Side Refer to table 3

OR Apply Service Bulletin No. A330-57-3083 and Before next flight ALI 57-11-04 not accomplished Pre Service Bulletin No. A330-57-3083

Do a Rototest Inspection Post SB No.A330-57-3083 on LH and RH Sides, refer to SUBTASK 573114-832-004 001 for LH Side and to SUBTASK 573114-832-009 001 for RH Side Refer to table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 5 5

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# @A330 SERVICE BULLETIN
Table 1: Special Detailed Inspection of the Fasteners Holes of the Area A of the frame 40, LH and RH sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

ALI 57-11-04 accomplished ALI 57-11-04 not accomplished Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No.A330-57-3083 on LH and RH Sides, refer to SUBTASK 573114-832-004 001 for LH Side and to SUBTASK 573114-832-009 001 for RH Side Refer to table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

Table 2: Special Detailed Inspection of the Fastener Hole of the Area B of the frame 40, LH and RH sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval Config. 001 Do a Rototest Inspection on LH and RH Sides, refer to SUBTASK 573114-832-005 001 for LH Side and to SUBTASK 573114-832-010 001 for RH Side Refer to table 5

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 6 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners Holes of the Area A of the frame 40, LH and RH sides Compliance Time Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

ALI 57-11-04 accomplished None None FC optimized set: 7,400 FC /24,300 FH from ALI embodiment or FH optimized set: 5,950 FC /40,400 FH from ALI embodiment See NOTE (*) Pre Service Bulletin No. A330-57-3083

ALI 57-11-04 not accomplished Do a Rototest Inspection Pre SB No.A330-57-3083 on LH and RH Sides, refer to SUBTASK 573114-832-003 001 for LH Side and to SUBTASK 573114-832-008 001 for RH Side

FC optimized set: 17,400 FC /57,000 FH or FH optimized set: 13,500 FC /91,500 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 7 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners Holes of the Area A of the frame 40, LH and RH sides Compliance Time Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New same fasteners in transition fit Pre SB No.A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-833-001 001 for LH Side and/or to SUBTASK 573114-833-012 001 for RH Side and Before next flight None None

Repeat the Rototest Inspection of the holes Pre SB No. A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-832-003 001 for LH Side and/or to SUBTASK 573114-832-008 001 for RH Side None None FC optimized set: 7,400 FC /24,300 FH or FH optimized set: 5,950 FC /40,400 FH See NOTE (*) No Crack found

OR Apply Service Bulletin No. A330-57-3083 and Before next flight None None No Crack found Do a Rototest Inspection Post SB No.A330-57-3083 on LH and RH Sides, refer to SUBTASK 573114-832-004 001 for LH Side and to SUBTASK 573114-832-009 001 for RH Side Refer to table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 8 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners Holes of the Area A of the frame 40, LH and RH sides Compliance Time Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the holes to first oversize in comparison with the current hole diameter Pre SB No.A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-833-003 001 for LH Side and/or to SUBTASK 573114-833-015 001 for RH Side and Do a Rototest Inspection Before next flight None None

Crack found after Rototest Inspection Contact Airbus Before next flight None None Install new fasteners in transition fit Pre SB No.A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-833-005 001 for LH Side and/or to SUBTASK 573114-833-018 001 for RH Side and Before next flight None None No Crack found after Rototest Inspection

Repeat the Rototest Inspection of the holes Pre SB No. A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-832-003 001 for LH Side and/or to SUBTASK 573114-832-008 001 for RH Side None None FC optimized set: 7,400 FC /24,300 FH or FH optimized set: 5,950 FC /40,400 FH See NOTE (*)
NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 9 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners holes of the Area A of the frame 40, LH and RH Sides Compliance Time Condition Action Threshold from SB 57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Post Service Bulletin No. A330-57-3083 ALI 57-11-04 accomplished or not Do a Rototest Inspection Post SB No.A330-57-3083 on LH and RH Sides, refer to SUBTASK 573114-832-004 001 for LH Side and to SUBTASK 573114-832-009 001 for RH Side FC optimized set: 30,900 FC/100,900 FH or FH optimized set: 23,900 FC /162,000 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install new same fasteners in transition fit Post SB No.A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-833-007 001 for LH Side and/or to SUBTASK 573114-833-013 001 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection of the holes Post SB No. A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-832-004 001 for LH Side and/or to SUBTASK 573114-832-009 001 for RH Side None None FC optimized set: 7,400 FC /24,300 FH or FH optimized set: 5,950 FC /40,400 FH See NOTE (*)

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 10 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners holes of the Area A of the frame 40, LH and RH Sides Compliance Time Condition Action Threshold from SB 57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the holes to first oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573114-833-011 001 for LH Side and/or to SUBTASK 573114-833-016 001 for RH Side and Do a Rototest Inspection Before next flight None None

Crack found after Rototest Inspection Contact Airbus Before next flight None None Install new fasteners in transition fit Post SB No.A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-833-009 001 for LH Side and/or to SUBTASK 573114-833-019 001 for RH Side and Before next flight None None No Crack found after Rototest Inspection

Repeat the Rototest Inspection of the holes Post SB No. A330-57-3083 on LH and/or RH Sides, refer to SUBTASK 573114-832-004 001 for LH Side and/or to SUBTASK 573114-832-009 001 for RH Side None None FC optimized set: 7,400 FC /24,300 FH or FH optimized set: 5,950 FC /40,400 FH See NOTE (*)
NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 11 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the fastener hole of the Area B of the frame 40, LH and RH Sides Compliance Time Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval Config. 001 Do a Rototest Inspection on LH and RH Sides, refer to SUBTASK 573114-832-005 001 for LH Side and to SUBTASK 573114-832-010 001 for RH Side FC optimized set: 17,400 FC /57,000 FH or FH optimized set: 13,500 FC /91,500 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install new same fastener in transition fit on LH and/or RH Sides, refer to SUBTASK 573114-833-002 001 for LH Side and/or to SUBTASK 573114-833-014 001 for RH Side and Before next flight None None No Crack found

Repeat the Rototest Inspection on LH and/or RH Sides, refer to SUBTASK 573114-832-005 001 for LH Side and/or to SUBTASK 573114-832-010 001 for RH Side None None FC optimized set: 7,400 FC /24,300 FH or FH optimized set: 5,950 FC /40,400 FH See NOTE (*) Crack found Oversize the hole to first oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573114-833-010 001 for LH Side and/or to SUBTASK 573114-833-017 001 for RH Side and Do a Rototest Inspection Before next flight None None

Crack found after Rototest Inspection Contact Airbus Before next flight None None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 12 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the fastener hole of the Area B of the frame 40, LH and RH Sides Compliance Time Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Install new fastener in transition fit on LH and/or RH Sides, refer to SUBTASK 573114-833-006 001 for LH Side and/or to SUBTASK 573114-833-020 001 for RH Side and Before next flight None None No Crack found after Rototest Inspection

Repeat the Rototest Inspection of the holes on LH and/or RH Sides, refer to SUBTASK 573114-832-005 001 for LH Side and/or to SUBTASK 573114-832-010 001 for RH Side None None FC optimized set: 7,400 FC /24,300 FH or FH optimized set: 5,950 FC /40,400 FH See NOTE (*) NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better suits aircraft operation and utilization (Refer to OIT 999.0086/11). This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds and intervals given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 13 5

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# @A330 SERVICE BULLETIN
G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 573114-832-801-001: Inspection Get Access 13.00 On Aircraft Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, LH side 0.25 Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, RH side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, LH side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, RH side 0.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side 2.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side 2.25 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side 2.25 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side 2.25 Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side 0.25 Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side 0.25 Tests 0.75 Close-Up 13.00 TOTAL MANHOURS 37.25 ELAPSED TIME (HOURS) 37.25 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 14 5

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# @A330 SERVICE BULLETIN
Task 573114-833-801-001: Repair Get Access 13.00 On Aircraft Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side 1.75 Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side 1.75 Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, LH side 1.75 Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, RH side 1.75 Install new same fastener of the Area B in transition fit, LH side 0.25 Install new same fastener of the Area B in transition fit, RH side 0.25 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, LH side 1.75 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, RH side 1.75 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, LH side 1.75 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, RH side 1.75 Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, LH side 0.25 Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, RH side 0.25 Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side 1.75 Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side 1.75 Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side 1.75 Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side 1.75 Install new fastener of the Area B in transition fit, LH side 0.25 Install new fastener of the Area B in transition fit, RH side 0.25 Tests 0.75 Close-Up 13.00 TOTAL MANHOURS 49.25 ELAPSED TIME (HOURS) 49.25

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 15 5

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# @A330 SERVICE BULLETIN
NOTE: For Area A, if SB No.A330-57-3083 is accomplished, only the manhours stating post SB No.A330-57-3083 apply. For Area A, if SB No.A330-57-3083 is not accomplished, only the manhours stating pre SB No.A330-57-3083 apply. H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

ALI 57.11.04 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 25-52-00 25-80-00 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Standards Manual (SM) Structural Repair Manual (SRM) 51-11-00 51-22-00 51-24-00 51-42-00 51-43-00 51-44-00 K. PUBLICATION AFFECTED Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) PART 2. Maintenance Planning Document (MPD) Impact on Scheduled Maintenance: Refer to MPD L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 16 5

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# @A330 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: Kit 573114A01R04 AIRBUS Material Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 2590 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability

Kit 573114A01R04 Cost 8,780.00 USD Availability 90 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION This Service Bulletin is subject to a specific support provided by AIRBUS. For more details regarding the applicable commercial policy, please contact your Customer Support Director. C. LIST OF COMPONENTS Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 EN6115V5-12 1 SCREW 2 ASNA2529-5 7 NUT 3 EN6115T7-18 1 SCREW 4 ASNA2531-7 1 NUT 5 EN6115V4-6 4 SCREW
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 17 5

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 6 EN6115V4-10 2 SCREW 7 ASNA2529-4 6 NUT 10 EN6115V5X12 1 SCREW 11 EN6115T7X18 1 SCREW 12 EN6115V4X6 4 SCREW 13 EN6115V4X10 2 SCREW 16 EN6115V6-12 1 SCREW 17 ASNA2529-6 1 NUT 18 EN6115V5-6 4 SCREW 19 EN6115V5-10 2 SCREW 21 EN6115V6X12 1 BOLT 22 EN6115V5X6 4 SCREW 23 EN6115V5X10 2 SCREW 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 NOTE: To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the AMM Task 21-52-41-000-801 mentioned in paragraph job set-up and in the AMM Task 21-52-41-400-801 mentioned in paragraph close-up. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Polysulphide Fuel Tank Sealant 09-046 As required Trichloroethane (Methyl Chloroform) 11-004 As required Lint-Free Cotton Cloth 19-003 As required (2) Components None (3) Equipment None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 18 5

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# @A330 SERVICE BULLETIN
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools NOTE: To accomplish this Service Bulletin it is necessary to use the tools listed in the AMM Task 21-52-41-000-801 mentioned in paragraph job set-upand in the AMM Task 21-52-41-400-801 mentioned in paragraph closeup. (3) Special Tools None

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 19 5

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# @A330 SERVICE BULLETIN

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 573114-832-801-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. 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 Zone 137 138 Manpower TOTAL MANHOURS 37.25 ELAPSED TIME (HOURS) 37.25

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 21 5

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# @A330 SERVICE BULLETIN
A. GENERAL CAUTION: To accomplish this Service Bulletin it is not necessary to put the aircraft under zero stress jacking. No zero stress jacking is required also in case of concurrent accomplishment of maintenance tasks or SBs in frame 40 area. However this is applicable only for the accomplishment of these tasks/SBs without deviation. Indeed, in case of heavy repair, a temporary re-installation of fasteners and/or zero stress jacking procedure could be anticipated. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. NOTE: The purpose of flow charts are for information only to show the various Inspection/Repair phases described in this Service Bulletin. (1) Subtask 573114-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 Consumable Material List (CML) Structural Repair Manual (SRM) 51-42-00 (a) For the Frame (FR) identification (Refer to AMM 06-31-53). (b) For the identification of Access Panels (Refer to AMM 06-41-53). (c) For the specification of the material numbers (Mat. No.) refer to Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00 (f) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (g) Remove and install the fasteners (Refer to SRM 51-42-00). (2) Subtask 573114-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 22 5

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# @A330 SERVICE BULLETIN Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 573114-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 21-20-00-010-801 Task 25-52-00-000-802 Task 53-35-13-000-802 (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 at door 821. (2) Subtask 573114-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbotton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source. (3) Subtask 573114-010-001-001 - Remove/Open for Access in the Belly Fairing Area RH side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 36-22-19-000-801 Task 53-35-13-000-802 Fig. A-FBAAA Remove/Install the Heat Shield Sheet 01 Sheet 02

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 23 5

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# @A330 SERVICE BULLETIN

References Fig. A-FDBAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FDCAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

(a) Remove the Belly Fairing Access-Panels 193DB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FDBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FDCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) Remove, if necessary, the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task 36-22-19-000-801). (e) Remove the Heat Shield of the RH Conditioning Pack (Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02): 1 Heat Shield Item (8) Retain 12 Screw Item (9) Retain

(4) Subtask 573114-010-002-001 - Remove/Open for Access in the Belly Fairing Area LH side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 53-35-13-000-802 (a) Remove the Belly Fairing Access-Panels 192PB (Refer to AMM Task 53-35-13-000-802).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 24 5

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# @A330 SERVICE BULLETIN(5) Subtask 573114-941-006-001 - Remove/Open for Access in the FWD CargoCompartment Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FDAAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FDAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain 2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573114-110-001-001 - Cleaning of the structure Manpower Resources Skills NON SPECIFIC

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 25 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Trichloroethane (Methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection area with: Trichloroethane (Methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (7) Subtask 573114-210-001-001 - Preparation of the inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00 51-22-00 DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 26 5

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# @A330 SERVICE BULLETIN (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damages or discontinuities. (d) Make sure that there is no: 1 Corrosion damage: - If you find corrosion damage, refer to the Structural Repair Manual for Types, inspection, removal and corrosion protection (Refer to SRM 51-22-00). 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...): - If you find this type of damage, refer to the Structural Repair Manual for damage classification and corrective action (Refer to SRM 51-11-00). C. PROCEDURE (1) Subtask 573114-832-001-001 - Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON DESTRUCTIVE TESTING AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Sheet 04 Refer to Fig. A-FFAAA

. (a) If Service Bulletin No.A330-57-3083 is accomplished: 1 Do SUBTASK 573114-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 27 5

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# @A330 SERVICE BULLETIN (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573114-832-003 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight. And do the SUBTASK 573114-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (2) Subtask 573114-832-006-001 - Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON DESTRUCTIVE TESTING AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Sheet 04 Refer to Fig. A-FFAAA

. (a) If Service Bulletin No.A330-57-3083 is accomplished: 1 Do SUBTASK 573114-832-009 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the threshold given in the table 4 of the Planning Information Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 28 5

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# @A330 SERVICE BULLETIN (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573114-832-008 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight. And do the SUBTASK 573114-832-009 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (3) Subtask 573114-832-002-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Sheet 04 Refer to Fig. A-FFAAA

. (a) Do SUBTASK 573114-832-005 001 Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (4) Subtask 573114-832-007-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 29 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Sheet 04 Refer to Fig. A-FFAAA

. (a) Do SUBTASK 573114-832-010 001 Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (5) Subtask 573114-832-003-001 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.25 Minimum number of person 1 Subtask elapsed time 2.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Fig. A-FCBAA Inspection Area Sheet 01 Sheet 02 At the Threshold/Interval given in the Planning Information Paragraph E.(2): NOTE: If ALI 57-11-04 is accomplished, the Interval is to be applied. If ALI 57-11-04 is not accomplished, the Threshold is to be applied. (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the area A of the frame 40, LH side. - Remove the fasteners from holes H41, H42, H44, and H46, LH side: DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 30 5

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# @A330 SERVICE BULLETIN
Refer to Fig. A-FCAAA

. 4 Screw Item (5) Discard 4 Nut Item (7) Discard - Remove the fasteners from holes H45 and H259, LH side: Refer to Fig. A-FCAAA

. 2 Screw Item (6) Discard 2 Nut Item (7) Discard - Remove the fastener from hole H25, LH side: Refer to Fig. A-FCAAA

. 1 Screw Item (1) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and H259, LH side. Refer to Fig. A-FCBAA Refer to NTM 51-10-01 1 If no crack is found:
a Do SUBTASK 573114-833-001 001 Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-003 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight. And do the SUBTASK 573114-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the threshold given in the table 4 of the Planning Information Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 31 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Do SUBTASK 573114-833-003 001 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, LH side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Do SUBTASK 573114-833-005 001 Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-003 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (6) Subtask 573114-832-008-001 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.25 Minimum number of person 1 Subtask elapsed time 2.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Fig. A-FCBAA Inspection Area Sheet 01 Sheet 02 At the Threshold/Interval given in the Planning Information Paragraph E.(2): NOTE: If ALI 57-11-04 is accomplished, the Interval is to be applied.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 32 5

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# @A330 SERVICE BULLETIN If ALI 57-11-04 is not accomplished, the Threshold is to be applied. (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the area A of the frame 40, RH side. - Remove the fasteners from holes H41, H42, H44, and H46, RH side: Refer to Fig. A-FCAAA

. 4 Screw Item (5) Discard 4 Nut Item (7) Discard - Remove the fasteners from holes H45 and H259, RH side: Refer to Fig. A-FCAAA

. 2 Screw Item (6) Discard 2 Nut Item (7) Discard - Remove the fastener from hole H25, RH side: Refer to Fig. A-FCAAA

. 1 Screw Item (1) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and H259, RH side. Refer to Fig. A-FCBAA Refer to NTM 51-10-01 1 If no crack is found:
a Do SUBTASK 573114-833-012 001 Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-008 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight. And do the SUBTASK 573114-832-009 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the threshold given in the table 4 of the Planning Information Paragraph E.(2).
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 33 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Do SUBTASK 573114-833-015 001 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, RH side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Do SUBTASK 573114-833-018 001 Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-008 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (7) Subtask 573114-832-004-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.25 Minimum number of person 1 Subtask elapsed time 2.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Inspection Area Sheet 01 Sheet 02 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02 At the threshold given in the Planning Information Paragraph E.(2):

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 34 5

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# @A330 SERVICE BULLETIN
NOTE: As Service Bulletin No. A330-57-3083 is applied even if ALI 57-11-04 is accomplished or not, the Threshold is to be applied. (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the area A of the frame 40, LH side. - In the area A, remove the fasteners from holes H41, H42, H44, and H46, LH side: Refer to Fig. A-FCCAA

. 4 Bolt Item (18) Discard 4 Nut Item (2) Discard - In the area A, remove the fasteners from holes H45 and H259, LH side: Refer to Fig. A-FCCAA

. 2 Bolt Item (19) Discard 2 Nut Item (2) Discard - In the area A, remove the fastener from hole H25, LH side: Refer to Fig. A-FCCAA

. 1 Bolt Item (16) Discard 1 Nut Item (17) Discard - Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and H259, LH side. Refer to Fig. A-FCBAA Refer to NTM 51-10-01 1 If no crack is found:
a Do SUBTASK 573114-833-007 001 Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, LH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 35 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Do SUBTASK 573114-833-011 001 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, LH side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Do SUBTASK 573114-833-009 001 Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the interval given in the table 4 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (8) Subtask 573114-832-009-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.25 Minimum number of person 1 Subtask elapsed time 2.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Inspection Area Sheet 01 Sheet 02 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02 At the threshold given in the Planning Information Paragraph E.(2):

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 36 5

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# @A330 SERVICE BULLETIN
NOTE: As Service Bulletin No. A330-57-3083 is applied even if ALI 57-11-04 is accomplished or not, the Threshold is to be applied. (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the area A of the frame 40, RH side. - In the area A, remove the fasteners from holes H41, H42, H44, and H46, RH side: Refer to Fig. A-FCCAA

. 4 Bolt Item (18) Discard 4 Nut Item (2) Discard - In the area A, remove the fasteners from holes H45 and H259, RH side: Refer to Fig. A-FCCAA

. 2 Bolt Item (19) Discard 2 Nut Item (2) Discard - In the area A, remove the fastener from hole H25, RH side: Refer to Fig. A-FCCAA

. 1 Bolt Item (16) Discard 1 Nut Item (17) Discard - Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and H259, RH side. Refer to Fig. A-FCBAA Refer to NTM 51-10-01 1 If no crack is found:
a Do SUBTASK 573114-833-013 001 Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, RH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-009 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 37 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Do SUBTASK 573114-833-016 001 Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, RH side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Do SUBTASK 573114-833-019 001 Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-009 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the interval given in the table 4 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (9) Subtask 573114-832-005-001 - Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Fig. A-FCBAA Inspection Area Sheet 01 Sheet 02 Refer to Fig. A-FCAAA

. At the threshold given in the Planning Information Paragraph E.(2):

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 38 5

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# @A330 SERVICE BULLETIN (a) Do a rototest inspection of the area B of the frame 40, LH side. - Remove fastener from hole H39, LH side, refer to Fig. A-FCAAA Sheet 02: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard - Do a rototest inspection at hole H39, LH side. Refer to Fig. A-FCBAA Refer to NTM 51-10-01 1 If no crack is found:
a Do SUBTASK 573114-833-002 001 Install new same fastener of the Area B in transition fit, LH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-005 001 Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Do SUBTASK 573114-833-010 001 Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, LH side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Do SUBTASK 573114-833-006 001 Install new fastener of the Area B in transition fit, LH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-005 001 Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side at the interval given in the table 5 of the Planning Information Paragraph E.(2).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 39 5

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# @A330 SERVICE BULLETIN (10) Subtask 573114-832-010-001 - Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Fig. A-FCBAA Inspection Area Sheet 01 Sheet 02 Refer to Fig. A-FCAAA

. At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the area B of the frame 40, RH side. - Remove fastener at hole H39, RH side, refer to Fig. A-FCAAA Sheet 02: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard - Do a rototest inspection at hole H39, RH side. Refer to Fig. A-FCBAA Refer to NTM 51-10-01 1 If no crack is found:
a Do SUBTASK 573114-833-014 001 Install new same fastener of the Area B in transition fit, RH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-010 001 Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 40 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Do SUBTASK 573114-833-017 001 Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, RH side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Do SUBTASK 573114-833-020 001 Install new fastener of the Area B in transition fit, RH side before next flight and Repeat the rototest inspection as described in SUBTASK 573114-832-010 001 Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side at the interval given in the table 5 of the Planning Information Paragraph E.(2). D. TEST (1) Subtask 573114-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access refer to SUBTASK 573114-410-001 001 Install/Close Items Removed/Opened for access in the Belly Fairing Area RH side , SUBTASK 573114-410-002 001 Install/Close Items Removed/Opened for access in the Belly Fairing Area LH side , SUBTASK 573114-942-006 001 Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment and SUBTASK 573114-942-001 001 Close-up . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802).

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# @A330 SERVICE BULLETIN

2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). E. CLOSE-UP (1) Subtask 573114-410-001-001 - Install/Close Items Removed/Opened for access in the Belly Fairing Area RH side 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 Adhesion Promoter For Polysulfide Sealant 09-028 As required Polysulphide Fuel Tank Sealant 09-046 As required
References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-80-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 42 5

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# @A330 SERVICE BULLETIN

References Fig. A-FBAAA Remove/Install the Heat Shield Sheet 01 Sheet 02 Fig. A-FDBAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FDCAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573114-700-003 001 Testing . (a) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). Install the Heat Shield of the RH Conditioning Pack, refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02: 1 Heat shield Item (8) Retained at removal 12 Screw Item (9) Retained at removal - Install screws Item (9) with: Adhesion Promoter For Polysulfide Sealant 09-028 As required
Polysulphide Fuel Tank Sealant 09-046 As required

on and around the screws. (b) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDCAA Sheet 01

. 1 Install: 1 Duct Item (41) Retained at removal
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 43 5

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# @A330 SERVICE BULLETIN (c) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (d) Install the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). (e) Install the Belly Fairing Access-Panels 193DB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573114-410-002-001 - Install/Close Items Removed/Opened for access in the Belly Fairing Area LH side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 53-35-13-400-802 NOTE: The parts removed for the access must be installed before the SUBTASK 573114-700-003 001 Testing . (a) Install the Belly Fairing Access-Panels 192PB (Refer to AMM Task 53-35-13-400-802). (3) Subtask 573114-942-006-001 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FDAAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573114-700-003 001 Testing .

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 44 5

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# @A330 SERVICE BULLETIN (a) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retain (b) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (c) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801). (d) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (4) Subtask 573114-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 45 5

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# @A330 SERVICE BULLETIN

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# @A330 SERVICE BULLETIN Task 573114-833-801-001 - Repair WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. 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 Zone 137 138 Manpower TOTAL MANHOURS 49.25 ELAPSED TIME (HOURS) 49.25

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# @A330 SERVICE BULLETIN
A. GENERAL (1) Subtask 573114-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 20-21-11, Page Block 201 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of Access Panels (Refer to AMM 06-41-53, Page Block 001). (c) For the specification of the material numbers (Mat. No.) refer to Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant. (e) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (f) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00 (g) Remove and install the fasteners (Refer to SRM 51-42-00). (h) Drill and deburr the holes (Refer to SRM 51-44-00). (i) Torque the standard threaded fasteners (Refer to AMM Task 20-21-11-911-801). (j) Apply the sealant (Refer to SRM 51-24-00). (k) For alternative and substitute fasteners (Refer to SRM 51-43-00). (2) Subtask 573114-839-002-001 - 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: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 48 5

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# @A330 SERVICE BULLETIN
B. PREPARATION NOTE: This PREPARATION procedure is already done in the INSPECTION task. (1) Subtask 573114-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 (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 at door 821. (2) Subtask 573114-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbotton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source. (3) Subtask 573114-010-003-001 - Remove/Open for Accesss in the Belly Fairing Area RH side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 36-22-19-000-801 Task 53-35-13-000-802 Fig. A-FBAAA Remove/Install the Heat Shield Sheet 01 Sheet 02 Fig. A-FDBAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 49 5

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# @A330 SERVICE BULLETIN

References Fig. A-FDCAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

(a) Remove the Belly Fairing Access-Panels 193DB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FDBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FDCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) Remove, if necessary, the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task 36-22-19-000-801). (e) Remove the Heat Shield of the RH Conditioning Pack (Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02): 1 Heat Shield Item (8) Retain 12 Screw Item (9) Retain

(4) Subtask 573114-010-004-001 - Remove/Open for Access in the Belly Fairing Area LH side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 53-35-13-000-802 (a) Remove of the Belly Fairing Access-Panels 192PB (Refer to AMM Task 53-35-13-000-802).(5) Subtask 573114-941-005-001 - Remove/Open for Access in the FWD CargoCompartment Manpower Resources Skills NON SPECIFIC

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 50 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FDAAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove, if necessary, the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. AFDAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain 2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573114-110-002-001 - Cleaning of the structure 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 Trichloroethane (Methyl Chloroform) 11-004 As required Lint-Free Cotton Cloth 19-003 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 51 5

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# @A330 SERVICE BULLETIN
WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. Clean the inspection area with: Trichloroethane (Methyl Chloroform) 11-004 As required and (if necessary) Lint-Free Cotton Cloth 19-003 As required (7) Subtask 573114-210-002-001 - Preparation of the repair Areas Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00 51-22-00 (a) Use a FLASHLIGHT to do this repair if necessary. (b) Make sure that the surface of the repair area is clean and smooth. (c) Do a visual check of the repair area for damages or discontinuities.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 52 5

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# @A330 SERVICE BULLETIN (d) Make sure that there is no: 1 Corrosion damage: - If you find corrosion damage, refer to the Structural Repair Manual for Types, inspection, removal and corrosion protection (Refer to SRM 51-22-00). 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...): - If you find this type of damage, refer to the Structural Repair Manual for damage classification and corrective action (Refer to SRM 51-11-00). C. PROCEDURE (1) Subtask 573114-833-001-001 - Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V5-12 1 SCREW 2 ASNA2529-5 1 NUT 5 EN6115V4-6 4 SCREW 6 EN6115V4-10 2 SCREW 7 ASNA2529-4 6 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 53 5

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# @A330 SERVICE BULLETIN
Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

. Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 (a) Depending on inspection results of the Area A, if no crack is found, install the fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V4-6 Item 5 4 Nut ASNA2529-4 Item 7 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Screw EN6115V5-12 Item 1 1 Nut ASNA2529-5 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V4-10 Item 6 2 Nut ASNA2529-4 Item 7 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573114-833-012-001 - Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 54 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V5-12 1 SCREW 2 ASNA2529-5 1 NUT 5 EN6115V4-6 4 SCREW 6 EN6115V4-10 2 SCREW 7 ASNA2529-4 6 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

. Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 (a) Depending on inspection results of the Area A, if no crack is found, install the fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V4-6 Item 5 4 Nut ASNA2529-4 Item 7 Wet install the fasteners with:

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 55 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Screw EN6115V5-12 Item 1 1 Nut ASNA2529-5 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V4-10 Item 6 2 Nut ASNA2529-4 Item 7 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573114-833-007-001 - Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2529-5 6 NUT 16 EN6115V6-12 1 SCREW 17 ASNA2529-6 1 NUT 18 EN6115V5-6 4 SCREW 19 EN6115V5-10 2 SCREW

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 56 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02
Refer to Fig. A-FCCAA Sheet 01and Fig. A-FCCAA Sheet 02

. In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 Refer to AMM Task 20-21-11-911-801 (a) Depending on inspection results of the Area A, if no crack is found, install the fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V5-6 Item 18 4 Nut ASNA2529-5 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Screw EN6115V6-12 Item 16 1 Nut ASNA2529-6 Item 17 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V5-10 Item 19 2 Nut ASNA2529-5 Item 2 DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 57 5

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# @A330 SERVICE BULLETIN
Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573114-833-013-001 - Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in transition fit, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2529-5 6 NUT 16 EN6115V6-12 1 SCREW 17 ASNA2529-6 1 NUT 18 EN6115V5-6 4 SCREW 19 EN6115V5-10 2 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02
Refer to Fig. A-FCCAA Sheet 01 and Fig. A-FCCAA Sheet 02

. In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 Refer to AMM Task 20-21-11-911-801

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 58 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the Area A, if no crack is found, install the fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V5-6 Item 18 4 Nut ASNA2529-5 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Screw EN6115V6-12 Item 16 1 Nut ASNA2529-6 Item 17
Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V5-10 Item 19 2 Nut ASNA2529-5 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required (5) Subtask 573114-833-002-001 - Install new same fastener of the Area B in transition fit, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 59 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 EN6115T7-18 1 SCREW 4 ASNA2531-7 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 (a) Depending on inspection results of the Area B, if no crack is found, install the fastener. 1 In the Area B:
a Install the fastener at hole H39: 1 Screw EN6115T7-18 Item 3 1 Nut ASNA2531-7 Item 4 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (6) Subtask 573114-833-014-001 - Install new same fastener of the Area B in transition fit, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 60 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 EN6115T7-18 1 SCREW 4 ASNA2531-7 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 (a) Depending on inspection results of the Area B, if no crack is found, install the fastener. 1 In the Area B:
a Install the fastener at hole H39: 1 Screw EN6115T7-18 Item 3 1 Nut ASNA2531-7 Item 4 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 61 5

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# @A330 SERVICE BULLETIN (7) Subtask 573114-833-003-001 - Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02

. In accordance with SRM 51-44-00 (a) Depending on inspection results of the Area A, if crack is found, oversize the holes. 1 In the area A:
a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45, H46 and H259 to the dimension given in Fig. A-FCAAA Sheet 02

. b Do a rototest inspection on the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573114-833-015-001 - Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A pre Service Bulletin No. A330-57-3083, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 62 5

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# @A330 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02

. In accordance with SRM 51-44-00 (a) Depending on inspection results of the Area A, if crack is found, oversize the holes. 1 In the area A:
a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45, H46 and H259 to the dimension given in Fig. A-FCAAA Sheet 02

. b Do a rototest inspection on the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (9) Subtask 573114-833-011-001 - Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02
Refer to Fig. A-FCCAA Sheet 02

. In accordance with SRM 51-44-00

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 63 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the Area A, if crack is found, oversize the holes. 1 In the area A:
a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45, H46 and H259 to the dimension given in Fig. A-FCCAA Sheet 02

. b Do a rototest inspection on the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (10) Subtask 573114-833-016-001 - Oversize the holes to the first Oversize in comparison with the current hole diameter of the Area A post Service Bulletin No. A330-57-3083, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02
Refer to Fig. A-FCCAA Sheet 02

. In accordance with SRM 51-44-00 (a) Depending on inspection results of the Area A, if crack is found, oversize the holes. 1 In the area A:
a Drill to the first oversize diameter the holes H25, H41, H42, H44, H45, H46 and H259 to the dimension given in Fig. A-FCCAA Sheet 02

. b Do a rototest inspection on the drilled holes to check if the crack is still present. Refer to NTM 51-10-01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 64 5

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# @A330 SERVICE BULLETIN (11) Subtask 573114-833-010-001 - Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02

. In accordance with SRM 51-44-00 (a) Depending on inspection results of the Area B, if crack is found, oversize the hole. 1 In the Area B:
a Drill to the first oversize diameter the hole H39 to the dimension given in Fig. A-FCAAA Sheet 02

. b Do a rototest inspection on the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (12) Subtask 573114-833-017-001 - Oversize the hole to the first Oversize in comparison with the current hole diameter of the Area B, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 65 5

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# @A330 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02

. In accordance with SRM 51-44-00 (a) Depending on inspection results of the Area B, if crack is found, oversize the hole. 1 In the Area B:
a Drill to the first oversize diameter the hole H39 to the dimension given in Fig. A-FCAAA Sheet 02

. b Do a rototest inspection on the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (13) Subtask 573114-833-005-001 - Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2529-5 1 NUT 7 ASNA2529-4 6 NUT 10 EN6115V5X12 1 SCREW 12 EN6115V4X6 4 SCREW 13 EN6115V4X10 2 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 66 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02 In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 Refer to AMM Task 20-21-11-911-801 (a) Depending on inspection results of the Area A, if no crack is found, install the new fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V4X6 Item 12 4 Nut ASNA2529-4 Item 7 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Screw EN6115V5X12 Item 10 1 Nut ASNA2529-5 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V4X10 Item 13 2 Nut ASNA2529-4 Item 7 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 67 5

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# @A330 SERVICE BULLETIN (14) Subtask 573114-833-018-001 - Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2529-5 1 NUT 7 ASNA2529-4 6 NUT 10 EN6115V5X12 1 SCREW 12 EN6115V4X6 4 SCREW 13 EN6115V4X10 2 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02 In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 Refer to AMM Task 20-21-11-911-801

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 68 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the Area A, if no crack is found, install the new fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V4X6 Item 12 4 Nut ASNA2529-4 Item 7 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Screw EN6115V5X12 Item 10 1 Nut ASNA2529-5 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V4X10 Item 13 2 Nut ASNA2529-4 Item 7 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required (15) Subtask 573114-833-009-001 - Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 69 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2529-5 6 NUT 17 ASNA2529-6 1 NUT 21 EN6115V6X12 1 BOLT 22 EN6115V5X6 4 SCREW 23 EN6115V5X10 2 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02
Refer to Fig. A-FCCAA Sheet 02

. In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 Refer to AMM Task 20-21-11-911-801 (a) Depending on inspection results of the area A, if no crack is found, install the new fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V5X6 Item 22 4 Nut ASNA2529-5 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Bolt EN6115V6X12 Item 21
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 70 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA2529-6 Item 17 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V5X10 Item 23 2 Nut ASNA2529-5 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required (16) Subtask 573114-833-019-001 - Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2529-5 6 NUT 17 ASNA2529-6 1 NUT 21 EN6115V6X12 1 BOLT 22 EN6115V5X6 4 SCREW 23 EN6115V5X10 2 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 71 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Remove/Install the fasteners post Service Bulletin No. A330-57-3083 Sheet 01 Sheet 02
Refer to Fig. A-FCCAA Sheet 02

. In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 Refer to AMM Task 20-21-11-911-801 (a) Depending on inspection results of the area A, if no crack is found, install the new fasteners. 1 In the area A:
a Install the fasteners at holes H41, H42, H44 and H46: 4 Screw EN6115V5X6 Item 22 4 Nut ASNA2529-5 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required
b Install the fastener at hole H25: 1 Bolt EN6115V6X12 Item 21 1 Nut ASNA2529-6 Item 17 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

c Install the fasteners at holes H45 and H259: 2 Screw EN6115V5X10 Item 23 2 Nut ASNA2529-5 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 72 5

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# @A330 SERVICE BULLETIN (17) Subtask 573114-833-006-001 - Install new fastener of the Area B in transition fit, LH side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2531-7 1 NUT 11 EN6115T7X18 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02

. In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 Refer to AMM Task 20-21-11-911-801 (a) Depending on inspection results of the area B, if no crack is found, install the new fastener. 1 In the Area B:
a Install the fastener at hole H39: 1 Screw EN6115T7X18 Item 11 1 Nut ASNA2531-7 Item 4 DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 73 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN
Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (18) Subtask 573114-833-020-001 - Install new fastener of the Area B in transition fit, RH side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573114A01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2531-7 1 NUT 11 EN6115T7X18 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Remove/Install the fasteners Sheet 01 Sheet 02 Refer to Fig. A-FCAAA Sheet 02

. In accordance with SRM 51-43-00 In accordance with SRM 51-42-00 Refer to AMM Task 20-21-11-911-801

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 74 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area B, if no crack is found, install the new fastener. 1 In the Area B:
a Install the fastener at hole H39: 1 Screw EN6115T7X18 Item 11 1 Nut ASNA2531-7 Item 4 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
D. TEST (1) Subtask 573114-700-002-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access refer to SUBTASK 573114-942-002 001 Install/Close Items Removed/Opened for access in the Belly Fairing Area RH side , SUBTASK 573114-942-003 001 Install/Close Item Removed/Opened for access in the Belly Fairing Area LH side , SUBTASK 573114-942-004 001 Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment and SUBTASK 573114-942-005 001 Close-up . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801).

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 75 5

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# @A330 SERVICE BULLETIN

4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). E. CLOSE-UP (1) Subtask 573114-942-002-001 - Install/Close Items Removed/Opened for access in the Belly Fairing Area RH side 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 Adhesion Promoter For Polysulfide Sealant 09-028 As required Polysulphide Fuel Tank Sealant 09-046 As required
References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-80-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 Structural Repair Manual (SRM) 51-24-00 Fig. A-FBAAA Remove/Install the Heat Shield Sheet 01 Sheet 02 Fig. A-FDCAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 76 5

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# @A330 SERVICE BULLETIN

References Fig. A-FDBAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573114-700-002 001 Testing . (a) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (b) Install the Heat Shield of the RH Conditioning Pack refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02: 1 Heat shield Item (8) Retained at removal 12 Screw Item (9) Retained at removal - Install screws Item (9) with: Adhesion Promoter For Polysulfide Sealant 09-028 As required

Apply the sealant, refer to SRM 51-24-00. Polysulphide Fuel Tank Sealant 09-046 As required

on and around the screws. (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDCAA Sheet 01

. 1 Install: 1 Duct Item (41) Retained at removal

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 77 5

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# @A330 SERVICE BULLETIN (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). (f) Install the Belly Fairing Access-Panels 193DB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573114-942-003-001 - Install/Close Item Removed/Opened for access in the Belly Fairing Area LH side Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 53-35-13-400-802 NOTE: The parts removed for the access must be installed before the SUBTASK 573114-700-002 001 Testing . (a) Install the Belly Fairing Access-Panels 192PB (Refer to AMM Task 53-35-13-400-802). (3) Subtask 573114-942-004-001 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FDAAA Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573114-700-002 001 Testing .

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 78 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN (a) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retain (b) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (c) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801). (d) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (4) Subtask 573114-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 79 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

FR47

FR40



## A

**C** (8) FR40.3 FR41

FR40.2



## B − Z192 Z196 

### B **A**

(9) (12 POS)
G_SB_573114_5_BAAA_01_02 Figure A-FBAAA - Sheet 01 Remove/Install the Heat Shield
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 80 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

**NOTES:** 01 INSTALL SCREW ITEM (9) WITH MAT. No 09−046 (WET ASSEMBLY). APPLY A TORQUE VALUE OF 1.65 N.m ± 0.15 (14.60 lbf.in). 02 APPLY MAT. No 09−028 and 09−046 ON AND AROUND THE SCREW. **FWD** 

## C FR41


### A **A**



## A **A** (9) 01

02 RECEPTACLE HEAT SHIELD (8)

TYPICAL SECTION

G_SB_573114_5_BAAA_02_02 Figure A-FBAAA - Sheet 02 Remove/Install the Heat Shield
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 81 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL



### A − Z141 Z142

FR47

FR40



## A

**B**

**B**

G_SB_573114_5_CAAA_01_03 Figure A-FCAAA - Sheet 01 Remove/Install the fasteners
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 82 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

FR40 LH SIDE SHOWN RH SIDE SYMMETRICAL STGR38

STGR39

STGR40 H25 H39

H44 H41 H42

H46 H45 H259 HOLE SYMBOL PN DESCRIPTION REMARKS FINAL HOLE DIAMETER MIN MAX

6.706 mm (0.264 in) 6.747 mm (0.266 in) EN6115V4−6 SCREW ASNA2529−4 NUT EN6115V4X6 SCREW NUT **NOTE:**

INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) 02 DEPENDING ON INSPECTION RESULT 01

N ASNA2529−4 5 7 12 7 01 02 N HEAD ON THE VISIBLE SIDE

EXISTING HOLE DIAMETER MIN MAX

6.227 mm (0.245 in) 6.262 mm (0.246 in) FIRST OVERSIZE 01 02

11.476 mm (0.452 in) 11.515 mm (0.453 in) 10.972 mm (0.432 in) 11.007 mm (0.433 in) 6.310 mm (0.248 in) 6.350 mm (0.250 in)

EN6115V4−10 SCREW ASNA2529−4 NUT EN6115V4X10 SCREW NUT F ASNA2529−4 6 7 13 7 01 02 01 02 EN6115T7−18 SCREW ASNA2531−7 NUT EN6115T7X18 SCREW NUT N ASNA2531−7 3 4 11 4 01 02 01 02

8.296 mm (0.327 in) 8.835 mm (0.328 in) EN6115V5−12 SCREW ASNA2529−5 NUT EN6115V5X12 SCREW NUT N ASNA2529−5 1 2 10 2 01 02 7.815 mm (0.308 in) 7.849 mm (0.309 in) 01 02 11.080 mm (0.436 in) 11.120 mm (0.438 in)

7.900 mm (0.311 in) 7.940 mm (0.312 in) F HEAD ON THE HIDDEN SIDE

VIEW LOOKING AFT FASTENER (5) (7) (5) (7) (6) (7) (6) (7) (3) (4) (3) (4) (1) (2) (1) (2)

ITEM

6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.227 mm (0.245 in) 6.262 mm (0.246 in) STANDARD FASTENER IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE FASTENER STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE FASTENER STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE FASTENER STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT 6.310 mm (0.248 in) 6.350 mm (0.250 in)



## B AREA HOLE NUMBER
39 25, 41, 42, 44, 45, 46, 259 B A CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_CAAA_02_05 Figure A-FCAAA - Sheet 02 Remove/Install the fasteners
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 83 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL



### A − Z141 Z142

FR47

FR40



## A

**B**

**B**

G_SB_573114_5_CBAA_01_02 Figure A-FCBAA - Sheet 01 Inspection Area
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 84 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

FR40 LH SIDE SHOWN RH SIDE SYMMETRICAL 

## B
VIEW LOOKING AFT STGR38

STGR39

STGR40 H25 H39

H44 H41 H42

H46 H45 H259

**NOTE:**

AREA HOLE NUMBER
39 25, 41, 42, 44, 45, 46, 259 B A CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_CBAA_02_02 Figure A-FCBAA - Sheet 02 Inspection Area
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 85 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL



### A − Z141 Z142

FR47

FR40



## A

**B**

**B**

G_SB_573114_5_CCAA_01_03 Figure A-FCCAA - Sheet 01 Remove/Install the fasteners post Service Bulletin No. A330-57-3083
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 86 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

STGR38

STGR39

STGR40 H25

H44 H41 H42

H46 H45 H259 HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX EN6115V5−6 SCREW ASNA2529−5 NUT EN6115V5X6 SCREW NUT N ASNA2529−5 18 2 22 2 EXISTING HOLE DIAMETER MIN MAX

EN6115V5−10 SCREW ASNA2529−5 NUT EN6115V5X10 SCREW NUT F ASNA2529−5 19 2 23 2 EN6115V6−12 SCREW ASNA2529−6 NUT EN6115V6X12 SCREW NUT N ASNA2529−6 16 17 21 17 7.815 mm (0.308 in) 7.849 mm (0.309 in) 8.296 mm (0.327 in) 8.335 mm (0.328 in) 7.900 mm (0.311 in) 7.940 mm (0.312 in)

9.387 mm (0.370 in) 9.427 mm (0.371 in) 9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.490 mm (0.373 in) 9.530 mm (0.375 in) INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) 02 DEPENDING ON INSPECTION RESULT 01

FR40 LH SIDE SHOWN RH SIDE SYMMETRICAL

VIEW LOOKING AFT (18) (2) (18) (2) (19) (2) (19) (2) (16) (17) (16) (17) ITEM

7.815 mm (0.308 in) 7.849 mm (0.309 in) 8.296 mm (0.327 in) 8.335 mm (0.328 in) 7.900 mm (0.311 in) 7.940 mm (0.312 in) REMARKS
01 02 FIRST OVERSIZE 01 02 01 02 01 02 01 02 01 02 FASTENER STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE FASTENER STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE FASTENER STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT 

## B **NOTE:** N HEAD ON THE VISIBLE SIDE F HEAD ON THE HIDDEN SIDE

AREA HOLE NUMBER 25, 41, 42, 44, 45, 46, 259 A CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_CCAA_02_05 Figure A-FCCAA - Sheet 02 Remove/Install the fasteners post Service Bulletin No. A330-57-3083
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 87 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

RH SIDE SHOWN LH SIDE SYMMETRICAL Z130 FR39.1 FR40

(11) (12)

(14) (13)



## B **B**
**B A** 



## A

G_SB_573114_5_DAAA_01_00 Figure A-FDAAA - Sheet 01 Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment)
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 88 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL



### A **B** FR39.2FR40.2



## A

**B** (26) Z192

G_SB_573114_5_DBAA_01_00 Figure A-FDBAA - Sheet 01 Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 89 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

FR39.2FR40.2



### B

(41) 

## A

**B A**  Z192

G_SB_573114_5_DCAA_01_00 Figure A-FDCAA - Sheet 01 Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 90 5

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# @A330 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDINGAT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2 OF THE PLANNING INFORMATION PARAGRAPH E.(2). (REFER TO SUBTASK 573114−832−001 AND 573114−832−002) AND RH SIDE (REFER TO SUBTASK 573114−832−006 AND 573114−832−007)

CRACKS YES NO

INSTALL NEW SAME FASTENER OF THE AREA B

(REFER TO SUBTASK 573114−832−005) AND DO A ROTOTEST INSPECTION OF THE FASTENER HOLE OF THE AREA B OF THE FRAME 40, LH AND RH SIDES

FOUND

(REFER TO SUBTASK 573114−832−005) OF THE FASTENER HOLE OF THE AREA B OF THE FRAME 40, SEE FIG. A−FFAAA SHEET 04 SEE FIG. A−FFAAA SHEET 04

AREA B IN TRANSITION FIT, LH AND (REFER TO SUBTASK 573114−833−002) AND DO A SPECIAL DETAILED INSPECTION OF THE FASTENER HOLES OF THE AREAS A AND B OF THE FRAME 40, LH SIDE

REPEAT THE ROTOTEST INSPECTION AREA A

ALI 57−11−04 YES NO ACCOMPLISHED

SEE FIG. A−FFAAA SHEET 03 SEE FIG. A−FFAAA SHEET 02 LH AND RH SIDES (REFER TO SUBTASK 573114−833−014) RH SIDES, BEFORE NEXT FLIGHT

AND AT THE INTERVAL GIVEN IN THE (REFER TO SUBTASK 573114−832−010) (REFER TO SUBTASK 573114−832−010) AT THE THRESHOLD GIVEN IN THE TABLE 5 OF THE PLANNING INFORMATION PARAGRAPH E.(2). HOLE 39 HOLES 25, 41, 42, 44, 45, 46 AND 259

TABLE 5 OF THE PLANNING INFORMATION PARAGRAPH E.(2).
G_SB_573114_5_FAAA_01_03 Figure A-FFAAA - Sheet 01 Flow Chart
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 91 5

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# @A330 SERVICE BULLETIN

**CONF ALL

**NOTE:** THRESHOLD TO BE COUNTED FROM MSB 57−3083 EMBODIMENT 01 QUESTION ACTION FINDING CRACKS OR

(REFER TO SUBTASK 573114−832−003) AND SB No A330−57−3083 OF THE FASTENER HOLES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

FOUND A330−57−3083 NO YES ACCOMPLISHED SEE FIG. A−FFAAA SHEET 01

SB No

CRACKS YES NO (REFER TO SUBTASK 573114−832−004) AND

FOUND

SEE FIG. A−FFAAA SHEET 04 SEE FIG. A−FFAAA SHEET 04

OR

(REFER TO SUBTASK 573114−832−003) AND SB No A330−57−3083 OF THE FASTENER HOLES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES APPLY SB No A330−57−3083

NO YES

SEE FIG. A−FFAAA SHEET 04 (SB No A330−57−3083 ACCOMPLISHED) SEE FIG. A−FFAAA SHEET 04 (SB No A330−57−3083 NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENERS PRE SB No A330−57−3083

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES, THE AREA A OF THE FRAME 40, LH AND RH SIDES DO A ROTOTEST INSPECTION PRE SB No A330−57−3083 OF THE FASTENER HOLES OF DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573114−832−004) AND SB No A330−57−3083 OF THE FASTENER HOLES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES INSTALL NEW SAME FASTENERS POST SB No A330−57−3083 (REFER TO SUBTASK 573114−833−007) AND

REPEAT THE ROTOTEST INSPECTION POST 01 BEFORE NEXT FLIGHT (REFER TO SUBTASK 573114−832−008) AT THE THRESHOLD GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). (REFER TO SUBTASK 573114−832−009) AT THE THRESHOLD GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−008) AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). (REFER TO SUBTASK 573114−833−013)

(REFER TO SUBTASK 573114−832−009) AT THE INTERVAL GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2). BEFORE NEXT FLIGHT (REFER TO SUBTASK 573114−833−001) AND (REFER TO SUBTASK 573114−833−012) OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES, BEFORE NEXT FLIGHT

G_SB_573114_5_FAAA_02_04 Figure A-FFAAA - Sheet 02 Flow Chart
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 92 5

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# @A330 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING **NOTE:** THRESHOLD TO BE COUNTED FROM MSB 57−3083 EMBODIMENT INITIAL INTERVAL TO BE COUNTED FROM ALI 57−11−04 EMBODIMENT 01 02 CRACKS OR

(REFER TO SUBTASK 573114−832−003) AND SB No A330−57−3083 OF THE FASTENER HOLES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

FOUND A330−57−3083 NO YES ACCOMPLISHED SEE FIG. A−FFAAA SHEET 01

SB No

CRACKS YES NO (REFER TO SUBTASK 573114−832−004) AND

FOUND

SEE FIG. A−FFAAA SHEET 04 SEE FIG. A−FFAAA SHEET 04

OR

(REFER TO SUBTASK 573114−832−003) AND SB No A330−57−3083 OF THE FASTENER HOLES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES APPLY SB No A330−57−3083

NO YES

SEE FIG. A−FFAAA SHEET 04 (SB No A330−57−3083 ACCOMPLISHED) SEE FIG. A−FFAAA SHEET 04 (SB No A330−57−3083 NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENERS PRE SB No A330−57−3083 (REFER TO SUBTASK 573114−833−001) AND THE AREA A OF THE FRAME 40, LH AND RH SIDES DO A ROTOTEST INSPECTION PRE SB No A330−57−3083 OF THE FASTENER HOLES OF DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573114−832−004) AND SB No A330−57−3083 OF THE FASTENER HOLES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES INSTALL NEW SAME FASTENERS POST SB No A330−57−3083 (REFER TO SUBTASK 573114−833−007) AND

REPEAT THE ROTOTEST INSPECTION POST 01 02 BEFORE NEXT FLIGHT (REFER TO SUBTASK 573114−832−008) AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−833−012)

(REFER TO SUBTASK 573114−832−008) AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). (REFER TO SUBTASK 573114−832−009) AT THE THRESHOLD GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−833−013)

(REFER TO SUBTASK 573114−832−009) AT THE INTERVAL GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2). OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES, BEFORE NEXT FLIGHT OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES, BEFORE NEXT FLIGHT

G_SB_573114_5_FAAA_03_04 Figure A-FFAAA - Sheet 03 Flow Chart
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 93 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING CRACKS YES NO FOUND

NO YES SEE FIG. A−FFAAA SHEET 01, SHEET 02 AND SHEET 03

INSTALL NEW FASTENER PRE OR POST THE CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION, OVERSIZE THE HOLES OF THE AREA A PRE OR POST SB No A330−57−3083 TO FIRST OVERSIZE IN COMPARISON WITH (REFER TO SUBTASK 573114−833−003 AND 573114−833−015) OR

SEE FIG. A−FFAAA SHEET 02 AND 03 (SB No A330−57−3083 NOT ACCOMPLISHED) SEE FIG. A−FFAAA SHEET 02 AND 03 (SB No A330−57−3083

ACCOMPLISHED) SEE FIG. A−FFAAA SHEET 01 A330−57−3083 ACCOMPLISHED SB No SB No A330−57−3083 OF THE AREA A (REFER TO SUBTASK 573114−833−011 AND 573114−833−016)

(REFER TO SUBTASK 573114−832−003) AND SB No A330−57−3083 OF THE FASTENER HOLES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES, REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573114−832−004) AND SB No A330−57−3083 OF THE FASTENER HOLES OF REPEAT THE ROTOTEST INSPECTION POST IN TRANSITION FIT, LH AND RH SIDES, BEFORE NEXT FLIGHT CRACKS YES NO FOUND

INSTALL NEW FASTENER OF THE HOLE DIAMETER AND DO A ROTOTEST INSPECTION, OVERSIZE THE HOLE OF THE AREA B TO FIRST OVERSIZE IN COMPARISON WITH THE CURRENT (REFER TO SUBTASK 573114−833−010) AND

CONTACT AIRBUS AREA B IN TRANSITION FIT, LH AND RH SIDES, (REFER TO SUBTASK 573114−833−006) AND

(REFER TO SUBTASK 573114−832−005) AND

OF THE FASTENER HOLE OF THE AREA B

OF THE FRAME 40, LH AND RH SIDES REPEAT THE ROTOTEST INSPECTION

THE AREA A OF THE FRAME 40, LH AND RH SIDES, LH AND RH SIDES, BEFORE NEXT FLIGHT LH AND RH SIDES, BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT CONTACT AIRBUS BEFORE NEXT FLIGHT (REFER TO SUBTASK 573114−833−005 AND 573114−833−018) OR (REFER TO SUBTASK 573114−833−009 AND 573114−833−019) (REFER TO SUBTASK 573114−833−020) BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573114−832−010) AT THE INTERVAL GIVEN IN THE TABLE 5 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573114−832−008) AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). (REFER TO SUBTASK 573114−832−009) AT THE INTERVAL GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2). (REFER TO SUBTASK 573114−833−017) AREA B AREA A HOLE 39 HOLES 25, 41, 42, 44, 45, 46 AND 259

G_SB_573114_5_FAAA_04_05 Figure A-FFAAA - Sheet 04 Flow Chart
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 94 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report **CONF ALL The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department SEES1, on the attached inspection report sheet.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 1 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3114

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

INSPECTION METHOD :

LH SIDE ROTOTEST

CRACKS
YES INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

CRACKS AFTER OVERSIZE NO H25 CRACKS CRACKS AFTER OVERSIZE YES NO YES NO YES NO RH SIDE

YES NO H39 YES NO YES NO YES NO YES NO H41 YES NO YES NO YES NO YES NO H42 YES NO YES NO YES NO YES NO H44 YES NO YES NO YES NO YES NO H45 YES NO YES NO YES NO YES NO H46 YES NO YES NO YES NO YES NO H259 YES NO YES NO YES NO E−mail: Structure.sbinspectionresult@airbus.com

G_SB_573114_5_RAAA_01_01 Figure A-FRAAA - Sheet 01 Appendix 01 : Inspection Report
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 2 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3114

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

INSPECTION METHOD :

LH SIDE ROTOTEST

mm INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

FINAL DIAMETER in H25 RH SIDE E−mail: Structure.sbinspectionresult@airbus.com

INITIAL DIAMETER FINAL DIAMETER INITIAL DIAMETER

mm in mm in mm in

mm in H39 mm in mm in mm in

mm in H41 mm in mm in mm in

mm in H42 mm in mm in mm in

mm in H44 mm in mm in mm in

mm in H45 mm in mm in mm in

mm in H46 mm in mm in mm in

mm in H259 mm in mm in mm in

G_SB_573114_5_RAAA_02_01 Figure A-FRAAA - Sheet 02 Appendix 01 : Inspection Report
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 3 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF ALL

FR40 VIEW LOOKING AFT STGR38

STGR39

STGR40 H25 H39

H44 H41 H42

H46 H45 H259

LH SIDE SHOWN RH SIDE SYMMETRICAL CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573114_5_RAAA_03_00 Figure A-FRAAA - Sheet 03 Appendix 01 : Inspection Report
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 4 5

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF ALL

FR40 FRONT FITTING (8.5 mm) (0.335 in) FR40 REAR FITTING (9.2 mm) (0.362 in) 

### HOLE 25

**FWD**

**NOTE:** THESE THICKNESSES ARE THEORETICAL 

### HOLE 39

HOLE 45, 259 HOLE 41, 42, 44, 46 FR40 POST Y1959 (6 mm) (0.236 in) FITTING Y1959 (12 mm) (0.472 in) FR40 SPAR WEB (4 mm) (0.157 in)

FR40 REAR

FITTING (5 mm) (0.197 in) **FWD**

**FWD FWD**  FR40 SPAR WEB (4 mm) (0.157 in) FR40 REAR

FITTING (5 mm) (0.197 in)

FR40 ORBITAL TEE (6 mm) (0.236 in) FR40 SPAR WEB (4 mm) (0.157 in) FR40 REAR

FITTING (5 mm) (0.197 in) AFT LOWER

G_SB_573114_5_RAAA_04_01 Figure A-FRAAA - Sheet 04 Appendix 01 : Inspection Report
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 5 5

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT FRAME 40 VERTICAL WEB BELOW INTRADOS 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: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 1 5

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# @A330 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114 REVISION No.: 00 - Mar 12/13 Page: 1 5

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