home/td d570 pro data tmp/N000001203304-ENG …A320-53-1298) and for the cargo compartment (SB A320-53-1299) have also been issued. ... Inspection of Inboard and Outboard Flap Parts

@A318/A319/A320/A321SERVICE BULLETIN

SUMMARY

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEXFRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORYATA SYSTEM: 57

TITLE: WINGS - FLAPS - INSPECTION OF FLAP PARTS FOLLOWINGMATERIAL NON CONFORMITY

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

AIRBUS quality control have identified that items manufactured with wrong aluminium alloy or incorrectheat treatment condition may have entered the supply chain. Detailed assessment of the impact onaircraft structure of suspected and/or actual non conformance to design definition has been performed.For the Single Aisle program this is 13 Part Numbers (PNs) for 2392 aircraft that are potentiallyaffected.

The Inspection detailed in this Service Bulletin is focussed on potentially affected structural partslocated on the flaps.

This Service Bulletin introduces a one time inspection of 2 PN’s on 176 aircraft. Refer to OIT999.0053/14.

NOTE: Service Bulletins (SB) for the inspection of parts in the cabin (SB A320-53-1298) and forthe cargo compartment (SB A320-53-1299) have also been issued.

Accomplishment of this Service Bulletin will allow detection of the affected parts.

GENERAL EVALUATION

EVALUATION TABLECOMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NORELIABILITY AFFECTED NO PAX COMFORT AFFECTED NOCOST SAVING NO ETOPS AFFECTED NOSTRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

DATE: Jan 24/17 SERVICE BULLETIN No.: A320-57-1198

REVISION No.: 00 - Jan 24/17 Page: 1

6

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


SUMMARY

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

AAR AFL AFR AMU ASV BEC BER CCA CES CSC CSN DLH EVAGFA HVN KHV KZR MON RJA SNG SVA SWR TAM THY USA VJC

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU NoneOEB NoneAOT NoneSIL NoneISI NoneLINE MAINTENANCE AFFECTED NoLIFE LIMIT NoneOTHER OIT 999.0053/14

NATURE OF THE WORK

AIRCRAFT YESEQUIPMENT NO

HARD NOSOFT NOOBRM NO

MANPOWER

Task 571198-832-848-001: Inspection

TOTAL MANHOURS 3.00ELAPSED TIME (HOURS) 3.00

APPENDICES

Appendix 01 - Assessment for Wrong Material using Eddy Current Conductivity Measurement (COT) onAluminum Alloys

Appendix 02 - Assessment for Wrong Material using Eddy Current Conductivity Measurement (COT) onLower Outboard Doubler at Outboard Flap, Tab Rib 5, LH/RH

Appendix 03 - Effectivity by MSN/SN/PN

Appendix 04 - Reporting Sheet



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SUMMARY

**CONF ALL

A

RIB5TAB

RIB4TAB

RIB3TAB

RIB2TAB

RIB1TAB

REARSPAR

FRONTSPAR

RIB1

RIB19

A

LH SHOWNRH SIMILAR

AREA FOR INSPECTION.

N_SB_571198_6_SAAA_01_01

Figure A-GSAAA - Sheet 01



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SUMMARY

This Page Intentionally Left Blank



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AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEXFRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORYATA SYSTEM: 57


MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain theproperty of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection withany information contained in it. It is delivered on the express condition that said document and theinformation contained in it shall be treated as confidential, shall not be used for any purpose other thanthat for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shallnot be duplicated in any manner (except for the purposes of performing the tasks described hereunderand provided that any recipient of such document shall comply with the conditions herein), withoutAIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

321-211 321-212 321-213 321-231 321-232

(2) Effectivity by MSN

4585 4643 4648 4654 4662 4669 4672 4682 4698 4703 4706 4710 4719 4728 47314737 4746 4753 4761 4771 4779 4783 4788 4792 4811 4819 4824 4826 4830 48344838 4843 4847 4850 4856 4863 4873 4881 4885 4893 4898 4901 4916 4923 49254932 4935 4940 4945 4949 4957 4960 4962 4966 4971 4976 4994 5009 5025 50285035 5038 5044 5049 5054 5059 5065 5074 5077 5083 5087 5099 5118 5124 51265133 5154 5160 5164 5169 5173 5177 5180 5186 5192 5197 5199 5205 5210 52275233 5235 5237 5241 5244 5247 5251 5254 5257 5265 5269 5271 5275 5279 52825285 5287 5292 5295 5297 5300 5303 5306 5309 5314 5317 5321 5328 5332 53365340 5343 5346 5350 5354 5357 5368 5374 5377 5382 5385 5388 5392 5402 54045409 5413 5418 5422 5427 5432 5435 5438 5444 5447 5450 5456 5459 5462 54655469-5470 5475 5481 5485 5490 5495 5500 5504 5509 5513 5519 5523 5528 55345538 5543 5546 5549 5555 5558 5567 5573 5575 5582 5584 5588



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(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the timeof issue in accordance with the information available to AIRBUS. Any future changesresulting from transfer of an aircraft from one operator to another will not be reflected inthis list unless the Service Bulletin is revised for another reason.

OPERATOR MSNAAR 5169 5173 5287 5350 5382 5462 5500AFL 5044 5059 5271AFR 4901AMU 5459 5523ASV 5035BEC 5538BER 4728 5038 5126 5133CCA 4719 4771 4834 4873 4949 5054 5124 5199 5265 5346 5432 5435

5573CES 4746 5192 5210 5227 5309 5402 5481 5519 5558 5575CSC 4731 4824 4830 4856 4923 5160 5197 5233 5303 5470 5543CSN 5237 5279 5534DLH 4585 4672 4710 4753 4792 4819 4881 4916 4976 4994 5028 5049

5087 5186 5413EVA 5328 5354 5377 5485GFA 5025 5074 5180 5257 5321 5336HVN 4669 4703 4737 4783 4826 4863 4945 4971 5164 5241 5247 5251

5275 5297 5306 5340 5385 5392 5418 5427 5438 5456 5469 54955555

KHV 5343KZR 5357 5404MON 5582RJA 5099 5177SNG 4648SVA 4811 4838 4925 4962 5009 5065 5285 5314 5447 5509 5549SWR 5567TAM 4662 5528THY 4643 4654 4682 4698 4706 4761 4779 4788 5077 5083 5118 5154

5205 5254 5388 5450 5465 5490 5546 5584USA 4843 4847 4850 4885 4893 4898 4932 4935 4940 4957 4960 4966

5235 5244 5269 5282 5292 5300 5317 5332 5368 5374 5409 54225444 5475 5504 5513 5588

VJC 5295



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(4) Configuration by MSN

MSN CONFIGURATION4585 4643 4648 4654 4662 4669 4672 4682 4698 4703 47064710 4719 4728 4731 4737 4746 4753 4761 4771 4779 47834788 4792 4811 4819 4824 4826 4830 4834 4838 4843 48474850 4856 4863 4873 4881 4885 4893 4898 4901 4916 49234925 4932 4935 4940 4945 4949 4957 4960 4962 4966 49714976 4994 5009 5025 5028 5035 5038 5044 5049 5054 50595065 5074 5077 5083 5087 5099 5118 5124 5126 5133 51545160 5164 5169 5173 5177 5180 5186 5192 5197 5199 52055210 5227 5233 5235 5237 5241 5244 5247 5251 5254 52575265 5269 5271 5275 5279 5282 5285 5287 5292 5295 52975300 5303 5306 5309 5314 5317 5321 5328 5332 5336 53405343 5346 5350 5354 5357 5368 5374 5377 5382 5385 53885392 5402 5404 5409 5413 5418 5422 5427 5432 5435 54385444 5447 5450 5456 5459 5462 5465 5469 5470 5475 54815485 5490 5495 5500 5504 5509 5513 5519 5523 5528 55345538 5543 5546 5549 5555 5558 5567 5573 5575 5582 55845588

001

(5) Configuration definition

**CONF 001Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as astandard configuration.

(6) Material Effectivity

No Material Set

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

AIRBUS quality control have identified that items manufactured with wrong aluminiumalloy or incorrect heat treatment condition may have entered the supply chain. Detailedassessment of the impact on aircraft structure of suspected and/or actual nonconformance to design definition has been performed. For the Single Aisle program thisis 13 Part Numbers (PNs) for 2392 aircraft that are potentially affected.

(2) Objective/Action

The Inspection detailed in this Service Bulletin is focussed on potentially affectedstructural parts located on the flaps.

This Service Bulletin introduces a one time inspection of 2 PN’s on 176 aircraft. Refer toOIT 999.0053/14.



6



NOTE: Service Bulletins (SB) for the inspection of parts in the cabin (SBA320-53-1298) and for the cargo compartment (SB A320-53-1299) havealso been issued.

(3) Advantages

Accomplishment of this Service Bulletin will allow detection of the affected parts.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :


(1) Eddy Current Conductivity Measurement of the Flap

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory. It is expected that an AirworthinessDirective (AD) published by the European Aviation Safety Agency (EASA) will be issuedto confirm this classification. It is anticipated that the AD will confirm the thresholdsgiven but reference should be made to the AD for confirmation of the mandatedaccomplishment timescale.

To avoid an unnecessary long layover period it is recommended to accomplish thisInspection Service Bulletin at the next major scheduled check.

Table 1. Inspection of Inboard and Outboard Flap Parts following Material Non Conformity

Condition Action Compliance time Repetitive interval

All Aircraft Inspect for material NonConformity

6 years from the date ofaircraft manufacture

None

F. APPROVAL

The technical content of this document is approved under the authority of DesignOrganisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not ofAIRBUS origin, and which affects the content of this Service Bulletin, the operator isresponsible for obtaining approval by its airworthiness authority for any adaptation necessarybefore incorporation of the Service Bulletin.



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G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost todo 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 notinclude the time to prepare, plan or inspect the work. Manufacture and procurement of partsand tools, drying times for paints, sealants, etc., and general administration work are also notincluded.


Get Access 1.00On Aircraft

Eddy Current Conductivity Measurement of the Flap 1.00

Close-Up 1.00


NOTE: The given Manhours (Total and Elapsed) are for the Inspection only.Manhours to Get Access and Close-Up are not considered as they are part ofthe aircraft 6 year scheduled maintenance check.

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 12-34-24 27-50-00Elec. Std. Practices Manual (ESPM) 20-55-00

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None



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This Page Intentionally Left Blank



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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 apurchase order to AIRBUS. Parts will only be delivered upon findings. The address is:

AIRBUS Material, Logistics and SuppliersIFD - In Flight DeskWeg beim Jaeger 150D-22335 HAMBURGGERMANYFor ordering by internet: http://spares.airbus.comFor ordering by fax: +49 40 50 76 40 12For ordering by E-mail: [email protected]

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to bepurchased by a spares purchase order.

Operator supplied standard hardware parts required to accomplish this Service Bulletinare to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will credit the manhours indicated in this Service Bulletin at the agreed in-housewarranty labor rate for claims received not later than 90 days after completion of the lastaffected aircraft of your fleet.

For aircraft with findings further to inspection as per this Service Bulletin, Airbus will providethe parts at no charge.

AIRBUS will credit the manhours for parts replacement at the agreed in-house warranty laborrate for claims received not later than 90 days after completion of the last affected aircraft ofyour fleet.

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofitmanagement department.

AIRBUS CUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEXFranceE-mail: [email protected]



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C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use the tools listed in Appendix 01- Assessment for Wrong Material using Eddy Current Conductivity Measurement (COT)on Aluminum Alloys and Appendix 02 - Assessment for Wrong Material using EddyCurrent Conductivity Measurement (COT) on Lower Outboard Doubler at Outboard Flap,Tab Rib 5, LH/RH .

(3) Special Tools

None



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3. ACCOMPLISHMENT INSTRUCTIONS

Task 571198-832-848-001 - Inspection

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONSINCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEPELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLYAND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCEWORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DOTHIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. ASNECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL ANDOTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATIONAND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin include procedures givenin other documents or in other sections of the Service Bulletin. When the words’refer to’ are used and the operator has a procedure accepted by the local authorityhe belongs to, the accepted alternative procedure can be used. When the words ’inaccordance with’ are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in thisService Bulletin do not constitute or affect the technical intent of the ServiceBulletin. Operators can therefore, as deemed necessary, omit or add access and/orclose-up steps to add flexibility to their maintenance operations as long as thetechnical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatoryby an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in theseaccomplishment instructions are Required for Compliance (RC) and must be doneto comply with the AD. Other paragraphs are recommended and may be deviatedfrom, done as part of other actions or done with accepted methods different fromthose given in the Service Bulletin, as long as the RC paragraphs can be done andthe aircraft can be put back into a serviceable condition.

NOTE: The purpose of flowcharts is to supplement the information given in the Procedureand Compliance paragraphs and not to serve as the primary source for tasks orcompliance times given in this Service Bulletin.

NOTE: Discarded parts must be managed at the operator’s discretion.



6



NOTE: This Service Bulletin contains the instructions for the on-aircraft maintenancenecessary to ensure the continued airworthiness of the aircraft.

For any deviations to the instructions contained herein, contact AIRBUS for furtherinstructions and approval.

Task Associated Data

Zone580 680

Manpower


A. GENERAL

(1) Subtask 571198-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

ReferencesAircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(2) Subtask 571198-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in thisService Bulletin.

B. PREPARATION

(1) Subtask 571198-941-201-001 - Job Set-up

Manpower Resources

Skills AIRFRAME

ReferencesAircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 27-50-00-866-008

NOTE: The items given in this note shall be considered as the basic Aircraftconfiguration before you start a maintenance task:

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration



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- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task12-34-24-869-002

(b) Make sure that the flaps are fully extended or in the zero position, refer to AMMTask 27-50-00-866-008.

(c) Put the warning notices in position on the flap levers to tell persons not to operatethe flap/slat controls.

(d) Put access platforms in position below the outboard flaps LH and RH.

C. PROCEDURE

(1) Subtask 571198-832-201-001 - Eddy Current Conductivity Measurement of the Flap

Work Zones and Access PanelsZone Access/Work location

580 Work location from Rib 4 to Rib 5680 Work location from Rib 4 to Rib 5

Manpower Resources

Manhours 1.00Minimum number of person 1

Subtask elapsed time 1.00

Skills NON DESTRUCTIVETESTING

ReferencesFig. A-GBAAAEddy Current Conductivity Measurementof the Flap

Sheet 01

Fig. A-GFAAAInspection Flowchart

Sheet 01Sheet 02

NOTE: These instructions are applicable to both the Left Hand (LH) and RightHand (RH) wings.

(a) If installed, remove and retain the Blanking Caps from the inspection holes, refer toFig. A-GBAAA Sheet 01.



6



(b) Do the Eddy Current Conductivity Measurement of the installed structural parts inthe involved areas, refer to Fig. A-GFAAA Sheet 01, Fig. A-GFAAA Sheet 02,Fig. A-GBAAA Sheet 01, Appendix 01 - Assessment for Wrong Material usingEddy Current Conductivity Measurement (COT) on Aluminum Alloys , Appendix 02- Assessment for Wrong Material using Eddy Current Conductivity Measurement(COT) on Lower Outboard Doubler at Outboard Flap, Tab Rib 5, LH/RH , Appendix03 - Effectivity by MSN/SN/PN and Appendix 04 - Reporting Sheet .

NOTE: The inspection requires direct access to a flat area of the part witha probe.

1 If you have no findings:

a Complete and send the Report Sheet to AIRBUS within 30 days, refer toAppendix 04 - Reporting Sheet .

b No further action.

2 If you have findings:

a Contact AIRBUS for further instructions.

b Complete and send the Report Sheet to AIRBUS within 30 days, refer toAppendix 04 - Reporting Sheet .

c No further action.

D. TEST

None

E. CLOSE-UP

(1) Subtask 571198-942-201-001 - Close-up

Manpower Resources

Skills AIRFRAME

ReferencesAircraft Maintenance Manual (AMM) Task 27-50-00-866-009

Fig. A-GBAAAEddy Current Conductivity Measurementof the Flap

Sheet 01

(a) Make sure that the work areas are clean and clear of tools and other items ofequipment.

(b) If removed, re-install the Blanking Caps on the inspection holes, refer to Fig. A-GBAAA Sheet 01.

(c) Remove the access platforms.

(d) Remove the warning notices.



6



(e) Fully retract the flaps or make sure they are in the zero position, refer to AMM Task27-50-00-866-009.

(f) Put the aircraft back to its initial configuration.



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**CONF ALL

NOIS

THE MATERIALCORRECT?

CLOSE UP AREA

NO FURTHER ACTIONIN ACCORDANCE WITH

THIS SERVICE BULLETIN

NOTE:SEE SHEET 2 FOR INSPECTION METHOD AND DETAILS

THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATIONGIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TOSERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES

CONTACT AIRBUS FORFURTHER INSTRUCTIONSYES

GAIN ACCESS AND INSPECTTHE APPLICABLE PART NUMBERS FOR THE FLAP SN

AS PER APPENDIX 02

TO IDENTIFY THE PART NUMBERS TO BE INSPECTED ON A SPECIFICFLAP SN, REFER TO APPENDIX 03: ’EFFECTIVITY BY MSN/SN/PN’

COMPLETE REPORT SHEETAND REPORT TO AIRBUS

WITHIN 30 DAYS

N_SB_571198_6_FAAA_01_07

Figure A-GFAAA - Sheet 01Inspection Flowchart



6



**CONF ALL

YES

NO

DO THE CONDUCTIVITY ( ) MEASUREMENT WITH 60kHz

> 20,0 MS/m

=CALCULATE DIFFERENCE

− =

< 1MS/m

> 26 MS/m

YES

NO

YES

NO

=(REFER TO APPENDIX 01 AND 02)

DO THE CONDUCTIVITY ( ) MEASUREMENT WITH 480kHz

MATERIALNOT CORRECT

MS/m OR % IACS=(REFER TO APPENDIX 01 AND 02)

MATERIALCORRECT

MS/m OR % IACS

MS/m OR % IACS

(34.4% IACS)

(1.7% IACS)

(44.8% IACS)

IS

NOTE:NEGATIVE VALUES ARE POSSIBLE01

01

USE MS/m OR IACS DEPENDING ON AVAILABLE MEASURING TOOL02

02

N_SB_571198_6_FAAA_02_09

Figure A-GFAAA - Sheet 02Inspection Flowchart



6



**CONF ALL

A

RIB5TAB

RIB4TAB

RIB3TAB

RIB2TAB

RIB1TAB

REARSPAR

FRONTSPAR

RIB5TAB

RIB4TAB

RIB1

RIB19

A

B

LH SHOWNRH SIMILAR

LHRH

2425

CTYPICAL

BLANKINGCAP

CB

C

N_SB_571198_6_BAAA_01_02

Figure A-GBAAA - Sheet 01Eddy Current Conductivity Measurement of the Flap



6




**CONF ALL

N_SB_571198_6_ACAA_01_03

Figure A-GACAA - Sheet 01Assessment for Wrong Material using Eddy Current Conductivity Measurement (COT) on Aluminum

Alloys



6




**CONF ALL

N_SB_571198_6_ACAA_02_03


Alloys



6




**CONF ALL

N_SB_571198_6_ACAA_03_03


Alloys



6




**CONF ALL

N_SB_571198_6_ACAA_04_03


Alloys



6




**CONF ALL

N_SB_571198_6_ACAA_05_03


Alloys



6




**CONF ALL

N_SB_571198_6_ACAA_06_03


Alloys



6




**CONF ALL

N_SB_571198_6_ABAA_01_02

Figure A-GABAA - Sheet 01Assessment for Wrong Material using Eddy Current Conductivity Measurement (COT) on Lower

Outboard Doubler at Outboard Flap, Tab Rib 5, LH/RH



6




**CONF ALL

N_SB_571198_6_ABAA_02_02





6




**CONF ALL

N_SB_571198_6_ABAA_03_03





6




**CONF ALL

N_SB_571198_6_ABAA_04_04





6




**CONF ALL

N_SB_571198_6_ABAA_05_02





6




**CONF ALL

N_SB_571198_6_ABAA_06_04





6




**CONF ALL

N_SB_571198_6_ABAA_07_01





6




**CONF ALL

N_SB_571198_6_ABAA_08_01





6




**CONF ALL

N_SB_571198_6_ABAA_09_03





6




**CONF ALL

N_SB_571198_6_ABAA_10_00





6




**CONF ALL

MSN

4585

4643

4648

4654

4662

4669

4672

4682

4698

4703

4706

4710

4719

4728

4731

4737

4746

4753

4761

4771

4779

4783

4788

4792

4811

4819

4824

4826

4830

483448384843

4847

4850

4856

4863

48734881

4885

4893

4898

4901

4916

4923

4925

4932

4935

4940

4945

4949

4957

4960

4962

4966

4971

4976

4994

5009

5025

5028

5035

5038

5044

5049

5054

5059

5065

5074

5077

5083

5087

5099

5118

5124

5126

5133

5154

5160

5164

5169

5173

5177

5180

5186

5192

5197

5199

5205

5210

5227

5233

5235

5237

5241

5244

5247

TB 14607

TB 14643

TB 14648

TB 14654

TB 14662

TB 14669

TB 14672

TB 14682

TB 14698

TB 14703

TB 14706

TB 14710

TB 14719

TB 14728

TB 14731

TB 14737

TB 14834

TB 14753

TB 14761

TB 14771

TB 14779

TB 14788

TB 14783

TB 14792

TB 14811

TB 14863

TB 14824

TB 14826

TB 14830

TB 14746TB 14838TB 14843

TB 14940

TB 14850

TB 14856

TB 14881

TB 14873TB 14819

TB 14885

TB 14893

TB 14898

TB 14901

TB 14916

TB 14923

TB 14925

TB 14932

TB 14935

TB 14949

TB 14945

TB 14957

TB 14960

TB 14962

TB 14966

TB 14971

TB 15009

TB 14976

TB 14994

TB 15025

TB 15035

TB 15028

TB 15038

TB 15044

TB 14847

TB 15049

TB 15054

TB 15059

TB 15065

TB 15074

TB 15077

TB 15083

TB 15087

TB 15099

TB 15118

TB 15124

TB 15126

TB 15133

TB 15154

TB 15192

TB 15164

TB 15169

TB 15180

TB 15160

TB 15177

TB 15186

TB 15205

TB 15227

TB 15199

TB 15210

TB 15233

TB 15197

TB 15237

TB 15241

TB 15247

TB 15251

TB 15244

TB 15257

TB 14626

TB 14643

TB 14648

TB 14654

TB 14662

TB 14669

TB 14585

TB 14682

TB 14698

TB 14703

TB 14706

TB 14710

TB 14719

TB 14728

TB 14731

TB 14737

TB 14746

TB 14753

TB 14761

TB 14771

TB 14779

TB 14788

TB 14783

TB 14792

TB 14811

TB 14819

TB 14824

TB 14826

TB 14830

TB 14834TB 14838TB 14843

TB 14940

TB 14850

TB 14856

TB 14863

TB 14873TB 14881

TB 14885

TB 14893

TB 14898

TB 14901

TB 14916

TB 14923

TB 14925

TB 14932

TB 14935

TB 14949

TB 14945

TB 14957

TB 14960

TB 14962

TB 14966

TB 14971

TB 15009

TB 14976

TB 14994

TB 15025

TB 15035

TB 15028

TB 15038

TB 15044

TB 14847

TB 15049

TB 15054

TB 15059

TB 15065

TB 15074

TB 15077

TB 15083

TB 15087

TB 15099

TB 15124

TB 15118

TB 15126

TB 15133

TB 15154

TB 15192

TB 15164

TB 15169

TB 15180

TB 15235

TB 15177

TB 15186

TB 15205

TB 15173

TB 15199

TB 15210

TB 15233

TB 15227

TB 15237

TB 15241

TB 15247

TB 15251

TB 15244

TB 15257

LH OUTER FLAP SN RH OUTER FLAP SN

CONTINUED ON SHEET 2.NOTE:

D57

5862

4421

700

D57

5862

4421

600

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X XX XX X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X XX XX X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X XX XX X

MSN

D57

5862

4421

700

D57

5862

4421

600

MSN

D57

5862

4421

700

D57

5862

4421

600

LH OUTER FLAP SN RH OUTER FLAP SN LH OUTER FLAP SN RH OUTER FLAP SN

N_SB_571198_6_AAAA_01_02

Figure A-GAAAA - Sheet 01Effectivity by MSN/SN/PN



6




**CONF ALL

5251

5254

5257

5265

5269

5271

5275

5279

5282

5285

5287

5292

5297

5300

TB 15235

TB 15254

TB 15265

TB 15271

TB 15269

TB 15275

TB 15282

TB 15279

TB 15285

TB 15287

TB 15292

TB 15297

TB 15303

TB 15300

TB 15160

TB 15254

TB 15265

TB 15271

TB 15269

TB 15275

TB 15282

TB 15279

TB 15285

TB 15287

TB 15292

TB 15297

TB 15303

TB 153005303

5306

5309

5314

5317

5321

5328

5332

5336

5340

5343

5346

5350

5354

5357

5368

5374

5377

5382

5385

5388

5392

5402

5404

5409

5413

5418

5422

5427

5432

5435

5438

5444

5447

5450

5456

5459

5462

5465

5469

5470

5475

5481

5485

5490

5495

5500

5504

5509

5513

5519

5523

5528

5534

5538

5543

5546

5549

5555

5558

5567

5573

5575

5582

5584

5588

TB 15173

TB 15309

TB 15306

TB 15314

TB 15317

TB 15321

TB 15328

TB 15332

TB 15336

TB 15340

TB 15343

TB 15346

TB 15350

TB 15354

TB 15357

TB 15368

TB 15374

TB 15377

TB 15382

TB 15385

TB 15388

TB 15392

TB 15404

TB 15402

TB 15413

TB 15418

TB 15422

TB 15427

TB 15432

TB 15435

TB 15409

TB 15438

TB 15444

TB 15450

TB 15456

TB 15447

TB 15462

TB 15534

TB 15470

TB 15469

TB 15475

TB 15481

TB 15459

TB 15490

TB 15485

TB 15495

TB 15500

TB 15509

TB 15504

TB 15513

TB 15519

TB 15523

TB 15528

TB 15549

TB 15543

TB 15546

TB 15465

TB 15555

TB 15558

TB 15573

TB 15567

TB 15575

TB 15582

TB 15584

TB 15588

TB 15594

TB 15197

TB 15309

TB 15306

TB 15314

TB 15317

TB 15321

TB 15328

TB 15332

TB 15336

TB 15340

TB 15343

TB 15346

TB 15350

TB 15354

TB 15357

TB 15368

TB 15374

TB 15377

TB 15382

TB 15385

TB 15388

TB 15392

TB 15404

TB 15402

TB 15413

TB 15418

TB 15422

TB 15427

TB 15432

TB 15435

TB 15409

TB 15438

TB 15444

TB 15447

TB 15450

TB 15485

TB 15462

TB 15456

TB 15465

TB 15469

TB 15470

TB 15475

TB 15490

TB 15481

TB 15459

TB 15495

TB 15500

TB 15504

TB 15509

TB 15513

TB 15519

TB 15523

TB 15528

TB 15534

TB 15543

TB 15546

TB 15549

TB 15555

TB 15558

TB 15538

TB 15573

TB 15575

TB 15582

TB 15584

TB 15588

TB 15594

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X XX XX X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X XX XX X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

X X

MSN LH OUTER FLAP SN RH OUTER FLAP SN

D57

5862

4421

700

D57

5862

4421

600


D57

5862

4421

700

D57

5862

4421

600


D57

5862

4421

700

D57

5862

4421

600

N_SB_571198_6_AAAA_02_02

Figure A-GAAAA - Sheet 02Effectivity by MSN/SN/PN



6




**CONF ALL

24 LH OUTBOARD FLAP TAB RIB5 / REAR SPAR (REFER TO FIG A−GBAAA)D5758624421600

25 RH OUTBOARD FLAP TAB RIB5 / REAR SPAR (REFER TO FIG A−GBAAA)D5758624421700

ITEM

YESFINDINGS:

FLIGHT HOURS:

NO

SERVICE BULLETIN No: A320−57−1198

A/C MSN:

INSPECTION REPORT

FLIGHT CYCLES:

PART NUMBER ZONE/LOCATION

COT WITH 60 kHz DIFFERENCE= 480 − 60 MATERIAL

CORRECT NOT

REFER TO INSPECTION FLOWCHART

CALCULATE

PLACE OF INSPECTION:

INSPECTOR:

AMBIENT TEMPERATURE:

DATE OF INSPECTION:

MS/m % IACS MS/m % IACS MS/m % IACS

COT WITH 480 kHz480=...[MS/m], IF 60 >20 MS/m

OR 34.5% IACS60

FLAP SN (LH AND RH):

MATERIAL

CORRECT

NOTE: USE MS/m OR IACS DEPENDING ON TOOL.

UPLOAD THIS INSPECTION REPORTIN ACCORDANCE WITH ISI 00.00.00179

USING THE ONLINE REPORTINGAPPLICATION IN AIRBUSWORLD

N_SB_571198_6_AEAA_01_00

Figure A-GAEAA - Sheet 01Reporting Sheet



6




**CONF ALL

YESFINDINGS:

FLIGHT HOURS:

NO

SERVICE BULLETIN No: A320−57−1198

A/C MSN:

EXAMPLE OF A COMPLETED INSPECTION REPORT

FLIGHT CYCLES:

5020

5326

620

X

R00

25.5 X

19.5 X

26.0 26.0−25.5=0.524 LH OUTBOARD FLAP TAB RIB5 / REAR SPAR (REFER TO FIG A−GBAAA)D5758624421600

25 RH OUTBOARD FLAP TAB RIB5 / REAR SPAR (REFER TO FIG A−GBAAA)D5758624421700

PLACE OF INSPECTION:

INSPECTOR:

AMBIENT TEMPERATURE:

DATE OF INSPECTION:

BREMEN

JOHN TEST

22°C

11−11−2014

COT WITH 60 kHz60

DIFFERENCE= 480 − 60

REFER TO INSPECTION FLOWCHART

CALCULATE

MS/m % IACS MS/m % IACS MS/m % IACSITEM PART NUMBER ZONE/LOCATION

44.0

33.6

44.8 44.8−44.0=0.8

COT WITH 480 kHz480=...[MS/m], IF 60 >20 MS/m

OR 34.5% IACS MATERIALCORRECT NOT

MATERIAL

CORRECT

FLAP SN (LH AND RH): TB XXXXX

NOTE: USE MS/m OR IACS DEPENDING ON TOOL.

UPLOAD THIS INSPECTION REPORTIN ACCORDANCE WITH ISI 00.00.00179

USING THE ONLINE REPORTINGAPPLICATION IN AIRBUSWORLD

N_SB_571198_6_AEAA_02_00

Figure A-GAEAA - Sheet 02Reporting Sheet



6



Service Bulletin REPORTING


MODIFICATION No.: None

SB Reporting status

This Service Bulletin will only be incorporated into affected customized Maintenance and FlightOperations Products if it is duly reported to Airbus.

General information

The SB Reporting policy is published in ISI 00.00.00135. This document provides information regarding:the SB Reporting means and benefits, the update of customized Maintenance Products and customizedFlight Operations Products.

If this Service Bulletin has an operational impact, refer to paragraph "Flight Operations Products" forfurther information on the update of affected Flight Operations Products.

SB Reporting procedure

Standard practice to report SB is to use the online reporting application on AirbusWorld.

Refer to ISI 00.00.00179:- For complete information on reporting means to Airbus. Question 2 "What are the standard

practices for SB reporting?"- If this SB requires previous or simultaneous accomplishment of other SBs, Question 3 "What about

the reporting of prerequisite Service Bulletin?"

NOTE: ISI 00.00.00179 covers all the frequently asked questions about SB Reporting. It is revised on aregular basis.



6



QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported datathat you provide us will be used to analyse areas of difficulties and to take corrective action to furtherimprove 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 ashort 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:

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins ManagementFAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.



6


Documents

home/td d570 pro data tmp/N000001203304-ENG …A320-53-1298) and for the cargo compartment (SB A320-53-1299) have also been issued. ... Inspection of Inboard and Outboard Flap Parts