# @A318/A319/A320/A321 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. ATA SYSTEM: 57 

### TITLE: WINGS - OUTER WING - REFUEL APERTURE - INSPECTION OF ELECTRICAL BONDING **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Cases of corrosion findings have been experienced on the overwing refuelling aperture (used for gravity filling the fuel tank) on the wing top skin. The reported corrosion was on the mating surface of the aperture flange, underneath the refuel adaptor. Corrosion findings have been repaired on a case by case basis. On the aircraft in the effectivity of this Service Bulletin, Repair Instruction R572 58539 Iss A incorrectly gave requirements to apply primer coating on the mating surface. This primer coating can prevent proper electrical bonding provision between the overwing refuel cap adaptor and the wing skin. Electrical bonding is performed to prevent the accumulation of electrostatic charges and provide a path for conveying lightning strike. In this case, electrical bonding should be achieved between the bare metal surfaces of the refuel adaptor and the top skin panel. NOTE: To ensure conservative coverage at aircraft level, this inspection is to be accomplished on both wings, regardless of whether repairs were only performed on one wing. This Service Bulletin details instructions to carry out an electrical bonding check to verify the bond between the refuel adaptor and the top skin panel. If the bonding check fails, the refuel adaptor is removed and the surface treatment on the aperture flange is removed. If corrosion is apparent, a repair instruction is referenced. A conversion coating and a thin layer of sealant is applied (electrical bonding is achievable through these mediums) and the refuel adaptor is re-installed. A further electrical bonding check is then carried out. Accomplishment of this Service Bulletin will make sure that there is electrical bonding between the overwing refuel adaptor and the top skin panel. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 1 7

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY EVALUATION TABLE POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational disruptions. MATERIAL PRICE INFORMATION No Material EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

AAF ACA AFR AIJ AUA BAW BEL BGH BMA CCA CYP DAL DLH FHY GWY ISS IWD JET KKK LBT SSV SVR SWR TAM TCX TRK UAL USA VLK CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 571152-832-895-001: Inspection TOTAL MANHOURS 12.50 ELAPSED TIME (HOURS) 7.0 APPENDICES None
DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 2 7

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY

**CONF ALL

RIB19 RIB20

540PB (640PB) 

### A

CAP LANYARD

O−RING
AFFECTED AREA ADAPTOR

WING SKIN PANEL No. 2 

## A 44QM (45QM)
42QM (43QM)

N_SB_571152_7_SUAA_01_01 Figure A-USUAA - Sheet 01

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 3 7

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY

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# @A318/A319/A320/A321 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 ATA SYSTEM: 57 

### TITLE: WINGS - OUTER WING - REFUEL APERTURE - INSPECTION OF ELECTRICAL BONDING MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models 319-111 319-112 319-132 320-111 320-211 320-212 320-214 320-232 321-111 321-211 321-212 321-231 (2) Effectivity by MSN 0005 0007 0016 0039 0078 0109 0118 0120 0153 0174 0187 0203 0215 0218 0226-0228 0236-0237 0269-0270 0278 0285-0288 0294 0301 0337 0377 0462-0465 0520 0523 0528 0544 0876 0888 0921 0935 0974 1014 1102 1130 1160 1162 1177 1215 1250 1287 1336 1388 1404 1444 1449 1476 1505 1524 1564 1605 1616 1622 1640 1645 1658 1677 1691 1729 1905 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN AAF 0888 ACA 0174 DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 1 7

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# @A318/A319/A320/A321 SERVICE BULLETIN

OPERATOR MSN AFR 0005 0007 0016 0187 0226 0227 0228 0236 0237 0270 0278 0285 0286 0287 0337 0377 0544 1404 1444 1449 1476 1505 1524 1616 1622 1640 1645 1658 1677 1691 AIJ 1162 AUA 0935 BAW 0039 0109 0120 BEL 1160 1336 1388 BGH 0294 BMA 1014 1177 CCA 0876 0921 CYP 1729 DAL 0118 0153 DLH 0078 0218 0269 FHY 0288 GWY 1564 ISS 1102 IWD 1130 JET 0215 KKK 0974 LBT 0301 SSV 1605 SVR 0203 SWR 0520 TAM 1215 TCX 1250 TRK 1905 UAL 0462 0463 0464 0465 0523 USA 1287 VLK 0528 (4) Configuration by MSN MSN CONFIGURATION 0005 0007 0016 0039 0078 0109 0118 0120 0153 0174 0187 0203 0215 0218 0226 0227 0228 0236 0237 0269 0270 0278 0285 0286 0287 0288 0294 0301 0337 0377 0462 0463 0464 0465 0520 0523 0528 0544 0876 0888 0921 0935 0974 1014 1102 1130 1160 1162 1177 1215 1250 1287 1336 1388 1404 1444 1449 1476 1505 1524 1564 1605 1616 1622 1640 1645 1658 1677 1691 1729 1905 001

(5) Configuration definition **CONF 001 Config. 01 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration.

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 2 7

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# @A318/A319/A320/A321 SERVICE BULLETIN (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLB01 As required B. CONCURRENT REQUIREMENTS None C. REASON (1) History Cases of corrosion findings have been experienced on the overwing refuelling aperture (used for gravity filling the fuel tank) on the wing top skin. The reported corrosion was on the mating surface of the aperture flange, underneath the refuel adaptor. Corrosion findings have been repaired on a case by case basis. On the aircraft in the effectivity of this Service Bulletin, Repair Instruction R572 58539 Iss A incorrectly gave requirements to apply primer coating on the mating surface. This primer coating can prevent proper electrical bonding provision between the overwing refuel cap adaptor and the wing skin. Electrical bonding is performed to prevent the accumulation of electrostatic charges and provide a path for conveying lightning strike. In this case, electrical bonding should be achieved between the bare metal surfaces of the refuel adaptor and the top skin panel. NOTE: To ensure conservative coverage at aircraft level, this inspection is to be accomplished on both wings, regardless of whether repairs were only performed on one wing. (2) Objective/Action This Service Bulletin details instructions to carry out an electrical bonding check to verify the bond between the refuel adaptor and the top skin panel. If the bonding check fails, the refuel adaptor is removed and the surface treatment on the aperture flange is removed. If corrosion is apparent, a repair instruction is referenced. A conversion coating and a thin layer of sealant is applied (electrical bonding is achievable through these mediums) and the refuel adaptor is re-installed. A further electrical bonding check is then carried out. (3) Advantages Accomplishment of this Service Bulletin will make sure that there is electrical bonding between the overwing refuel adaptor and the top skin panel. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to :
DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 3 7

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# @A318/A319/A320/A321 SERVICE BULLETIN Task 571152-832-895-001: Inspection (1) Inspection - Bonding Test (2) Removal of Primer - Inspection for Corrosion (3) Repair E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale Accomplishment is requested at or before 24 months from the issue date of this Service Bulletin. Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. 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 571152-832-895-001: Inspection Get Access 0.5 On Aircraft Inspection - Bonding Test 0.5 Removal of Primer - Inspection for Corrosion 5.0 Repair 6.0 Tests 0.0 Close-Up 0.5
DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 4 7

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# @A318/A319/A320/A321 SERVICE BULLETIN
Task 571152-832-895-001: Inspection TOTAL MANHOURS 12.50 ELAPSED TIME (HOURS) 7.0 NOTE: If the initial bonding test is satisfactory, the manhours for removal, inspection and repair can be deducted from the Total Manhours and the Elapsed Time can be reduced accordingly. H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 20-21-11 20-28-00 28-11-43 Elec. Std. Practices Manual (ESPM) 20-55-00 Structural Repair Manual (SRM) 51-21-11 51-74-00 51-75-11 51-76-12 57-21-11 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 5 7

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# @A318/A319/A320/A321 SERVICE BULLETIN

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# @A318/A319/A320/A321 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION For those aircraft with findings further to inspection as per this Service Bulletin, AIRBUS will credit the manhours for the correction at the operator’s agreed in-house warranty labor rate for claims received not later than 90 days after completion of the last affected aircraft of your fleet. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials NOTE: To accomplish this Service Bulletin it is necessary to use the consumable materials listed in the AMM 28-11-43 Page Block 401. Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Lint-Free Cotton Cloth 19-003 As required (2) Components NOTE: To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the AMM 28-11-43 Page Block 401. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None
DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 7 7

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# @A318/A319/A320/A321 SERVICE BULLETIN
F. TOOLING (1) Tooling - Price and Availability None (2) Tools NOTE: To accomplish this Service Bulletin it is necessary to use the standard tools listed in the AMM 28-11-43 Page Block 401. (3) Special Tools None

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 8 7

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# @A318/A319/A320/A321 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 571152-832-895-001 - Inspection NOTE: The instructions that follow are applicable to the LH and the RH wings. Task Associated Data Zone 540 640 Modified FIN 42QM 43QM Manpower TOTAL MANHOURS 12.50 ELAPSED TIME (HOURS) 7.0 A. GENERAL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00, CLEANING. (1) Subtask 571152-910-401-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201 20-28-00, Page Block 201 20-28-00, Page Block 501 Structural Repair Manual (SRM) 51-21-11 51-74-00 51-75-11 51-76-12 DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 9 7

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# @A318/A319/A320/A321 SERVICE BULLETIN

References (a) Tightening Torques for Standard Threaded Fasteners (Refer to AMM 20-21-11, Page Block 201). (b) Electrical Bonding - Maintenance Practice (Refer to AMM 20-28-00, Page Block 201). (c) Electrical Bonding - Testing (Refer to AMM 20-28-00, Page Block 501). (d) Application of Protective Treatment to Metal Parts (Refer to SRM 51-21-11). (e) Repair of Corroded Areas (Refer to SRM 51-74-00). (f) Paint Stripping/Removal (Refer to SRM 51-75-11). (g) Repair of Fuel Tank Sealing (Refer to SRM 51-76-12). (2) Subtask 571152-839-401-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 571152-941-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 540 Work location from Rib 19 to Rib 20 640 Work location from Rib 19 to Rib 20 Manpower Resources Skills NON SPECIFIC (a) Put access platforms in position at Zone 540 and Zone 640 between Rib 19 and Rib 20. C. PROCEDURE (1) Subtask 571152-832-402-001 - Inspection - Bonding Test Work Zones and Access Panels Zone Access/Work location 540 Work location FIN 44-QM 640 Work location FIN 45-QM

DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 10 7

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# @A318/A319/A320/A321 SERVICE BULLETIN
Manpower Resources Manhours 0.5 Minimum number of person 2 Subtask elapsed time 0.5 Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) Task 20-28-00-720-006 Fig. A-UAAAA Inspection Flow Chart Sheet 01 Refer to Fig. A-UAAAA Sheet 01 (a) Do a bonding test from the adaptor FIN 42QM and FIN 43QM to the wing skin panels (Refer to AMM Task 20-28-00-720-006). (b) If the resistance value is 10 milliOhms or less at the LH wing and the RH wing, no more work is necessary. Go to SUBTASK 571152-942-401 001 Close-up . (c) If the resistance value is greater than 10 milliOhms at the LH wing and/or the RH wing, do the worksteps that follow. (2) Subtask 571152-832-401-001 - Removal of Primer - Inspection for Corrosion Work Zones and Access Panels Zone Access/Work location 540 Work location FIN 42-QM 640 Work location FIN 43-QM Manpower Resources Manhours 5.0 Minimum number of person 2 Subtask elapsed time 2.5 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Lint-Free Cotton Cloth 19-003 As required References Aircraft Maintenance Manual (AMM) 28-11-43, Page Block 401 Fig. A-UAAAA Inspection Flow Chart Sheet 01

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# @A318/A319/A320/A321 SERVICE BULLETIN

References Fig. A-UACAA Inspection for Corrosion after Removal of Primer Sheet 01

Refer to Fig. A-UAAAA Sheet 01 and to Fig. A-UACAA Sheet 01 (a) Remove the applicable gravity fill cap/adaptor FIN 42QM and/or FIN 43QM (Refer to AMM 28-11-43, Page Block 401). NOTE: The above AMM reference gives instructions to defuel and vent the wing fuel tanks and to remove the applicable manhole covers. (b) Remove the paint/primer from the rim of the aperture for the gravity fill adaptor in the top skin panel with abrasive paper grade 320, Fig. A-UACAA Sheet 01 Section A-A. (c) Clean the mating surfaces back to bare metal, use: Lint-Free Cotton Cloth 19-003 As required

made moist with: Solvent General Purpose 11-026 As required (d) Do an inspection of the component interface and/or adjacent area. (e) If the inspection shows defects on the aperture flange, before completing the steps that follow, go to SUBTASK 571152-833-401 001 Repair . (f) If there are no defects, apply: Chemical Conversion Coating Yellow Aluminum 13-002 As required

to the area shown. (g) Install the applicable gravity fill cap/adaptor FIN 42QM and/or FIN 43QM (Refer to AMM 28-11-43, Page Block 401). NOTE: It will not be necessary to remove paint from the component interface or apply Mat. No 13-002 as detailed in the AMM 28-11-43, Page Block 401 reference under Preparation for Installation, as these worksteps are included in para. (b) and (f) above. NOTE: The AMM 28-11-43, Page Block 401 reference for installation of the gravity fill cap/adaptor includes a bonding check, if the bonding resistance is greater than 10 milliOhms, repeat SB accomplishment instructions or contact AIRBUS for instructions. NOTE: The above AMM reference gives instructions to install the applicable
DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 12 7

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# @A318/A319/A320/A321 SERVICE BULLETIN manhole covers and refuel the wing fuel tanks as necessary. (3) Subtask 571152-833-401-001 - Repair Manpower Resources Manhours 6.0 Minimum number of person 2 Subtask elapsed time 3.0 Skills AIRFRAME References Structural Repair Manual (SRM) 51-74-00 57-21-11 Page Block 101 57-21-11 Fig. A-UACAA Inspection for Corrosion after Removal of Primer Sheet 01
(a) Remove any signs of corrosion (Refer to SRM 51-74-00). (b) Refer to SRM 57-21-11 for allowable damage and repair instructions. NOTE: SRM 57-21-11 is in the process of revision to include allowable damage and repair instructions for this area. AIRBUS should be contacted for Repair Instruction and RAS prior to the SRM revision. (c) If no SRM allowable damage and repair instructions are available, contact AIRBUS before next flight to get an approved repair. D. TEST None E. CLOSE-UP (1) Subtask 571152-942-401-001 - Close-up Work Zones and Access Panels Zone Access/Work location 540 Work location from Rib 19 to Rib 20 640 Work location from Rib 19 to Rib 20 Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Move the access platforms clear of the aircraft.

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

NO FURTHER ACTION RESISTANCE VALUE 10 milliOhms OR LESS? AT OR BEFORE 24 MONTHS FROM THE ISSUE DATE OF THIS SERVICE BULLETIN, DO AN ELECTRICAL BONDING

YES NO

INSPECTION SHOW DEFECTS ON

THE APERTURE FLANGE? CHECK OF THE GRAVITY FILL ADAPTOR

REMOVE THE GRAVITY FILL ADAPTOR REF AMM

NO

SEAL AND REINSTALL

THE GRAVITY FILL ADAPTOR REF AMM RE−PROTECT SURFACES,

BONDING CHECK OF THE GRAVITY FILL ADAPTOR REF AMM DO AN ELECTRICAL YES

IS SRM ALLOWABLE DAMAGE AND REPAIRS AVAILABLE?

YES NO

BEFORE NEXT FLIGHT FOR APPROVED REPAIR CONTACT AIRBUS

BEFORE NEXT FLIGHT PERFORM SRM REPAIR AND REINSTALL

GRAVITY FILL

ADAPTOR REF AMM

**NOTE:** TO ENSURE CONSERVATIVE COVERAGE AT AIRCRAFT LEVEL, THE ABOVE INSPECTION PROCEDURE SHOULD BE PERFORMED ON BOTH WINGS OF THE IDENTIFIED AIRCRAFT. N_SB_571152_7_AAAA_01_11 CLEAN OFF MATING SURFACES BACK TO BARE METAL. REF: FIGURE A−UACAA SHEET 01 SECTION A−A AND AMM

DO AN INSPECTION OF THE COMPONENT INTERFACE REF AMM

DID THE

Figure A-UAAAA - Sheet 01 Inspection Flow Chart
DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 14 7

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RIB19 RIB20

540PB (640PB) 

### A CAP

LANYARD

O−RING ADAPTOR ADAPTOR

WING SKIN PANEL No. 2 FLANGE 

### B

3 TO 5 mm (0.118 TO 0.196 in) PAINT/PRIMER REMOVED.

CAP

ADAPTOR WING SKIN

O−RINGS (REF. ONLY) FRONT SPAR LINE OF FLIGHT

GRAVITY FILL CAP/ADAPTOR APERTURE



### A **A** RIB19 44QM (45QM)

42QM (43QM)



## A

**B**

N_SB_571152_7_ACAA_01_01 

## A **A** Figure A-UACAA - Sheet 01 Inspection for Corrosion after Removal of Primer
DATE: Jun 14/10 SERVICE BULLETIN No.: A320-57-1152 REVISION No.: 00 - Jun 14/10 Page: 15 7

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# @A318/A319/A320/A321 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - OUTER WING - REFUEL APERTURE - INSPECTION OF ELECTRICAL BONDING 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.

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# @A318/A319/A320/A321 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

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

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