# @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: 53 

### TITLE: FUSELAGE - MAIN STRUCTURE - INSPECTION FOR MISSING FASTENERS AT FR24 BETWEEN STR17 & STR18 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On MSN 5255, at VIP cabin customization at manufacturers site, several fasteners and an angle PN D5323006520103 were found missing at right hand side on FR24 between STR17 and STR18 during inspections. An inspection is therefore needed on 70 Aircraft potentially impacted by this issue. This Service Bulletin recommends doing special detailed inspections for missing fasteners and missing splice. The special detailed inspections consists in rototest under insulation blankets in case of missing parts. Accomplishment of this Service Bulletin will clarify the build status at the identified location and restore it conform to the applicable design standard when needed. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (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 NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational disruptions.

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 1 5

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPA01 1 See SB Rivet, Bush. Component COMPA02 1 See SB Splice EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

54S AAR ABY AFL AXM AZA BER CCA CEB CES CRK CSC CSN DLH EZY GFA GOW HKE HVN IAW IGO JJP JST LAN MEA ONE QTR RJD SLK SVA TAI TAM TBA THA THY USA 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 531285-832-801-001: Inspection TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 APPENDICES None

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 2 5

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY
**CONF ALL

AREA TO BE INSPECTED 

### A Z232

**NOTE:** 

## A FR24 STGR18 

### B

N_SB_531285_5_SAAA_01_01 Figure A-FSAAA - Sheet 01
DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 3 5

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY
**CONF ALL



### C FR24 FR25 FR23

STGR17 STGR18

STGR17

STGR18 FR24 **FWD** 

## B

**C E** 

**D**

N_SB_531285_5_SAAA_02_01 Figure A-FSAAA - Sheet 02
DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 4 5

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY
**CONF ALL

STGR17

STGR18 FR24

VIEW LOOKING AFT 

## D

**NOTE:** MISSING FASTENERS STGR18 FR24

PART MISSING



## E
N_SB_531285_5_SAAA_03_01 Figure A-FSAAA - Sheet 03
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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: 53 

### TITLE: FUSELAGE - MAIN STRUCTURE - INSPECTION FOR MISSING FASTENERS AT FR24 BETWEEN STR17 & STR18 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 319-111 319-112 319-115 319-132 319-133 320-214 320-216 320-232 320-233 321-211 321-231 321-232 (2) Effectivity by MSN 5230-5294 5296-5300 (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 54S 5261 AAR 5287 ABY 5276 AFL 5271 AXM 5272 5283 DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 1 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
OPERATOR MSN AZA 5294 BER 5246 5252 CCA 5265 CEB 5250 CES 5242 5267 5273 CRK 5260 CSC 5233 5286 CSN 5237 5268 5279 5288 DLH 5239 5284 5293 EZY 5236 5249 5289 GFA 5257 GOW 5232 HKE 5264 5266 HVN 5241 5247 5251 5275 5297 IAW 5290 IGO 5230 5231 5259 5262 5291 5298 JJP 5245 5274 5281 JST 5270 LAN 5234 5263 MEA 5253 ONE 5278 5299 QTR 5255 RJD 5277 SLK 5296 SVA 5285 TAI 5238 5243 5280 TAM 5240 TBA 5256 THA 5248 5258 THY 5254 USA 5235 5244 5269 5282 5292 5300 (4) Configuration by MSN MSN CONFIGURATION 5230 5231 5232 5233 5234 5235 5236 5237 5238 5239 5240 5241 5242 5243 5244 5245 5246 5247 5248 5249 5250 5251 5252 5253 5254 5255 5256 5257 5258 5259 5260 5261 5262 5263 5264 5265 5266 5267 5268 5269 5270 5271 5272 5273 5274 5275 5276 5277 5278 5279 5280 5281 5282 5283 5284 5285 5286 5287 5288 5289 5290 5291 5292 5293 5294 5296 5297 5298 5299 5300 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. DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 2 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Component COMPA01 1 Component COMPA02 1 Consumable CMLA01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History On MSN 5255, at VIP cabin customization at manufacturers site, several fasteners and an angle PN D5323006520103 were found missing at right hand side on FR24 between STR17 and STR18 during inspections. An inspection is therefore needed on 70 Aircraft potentially impacted by this issue. (2) Objective/Action This Service Bulletin recommends doing special detailed inspections for missing fasteners and missing splice. The special detailed inspections consists in rototest under insulation blankets in case of missing parts. (3) Advantages Accomplishment of this Service Bulletin will clarify the build status at the identified location and restore it conform to the applicable design standard when needed. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 531285-832-801-001: Inspection (1) Do a General Visual Inspection of FR 24 between STGR 17 and 18 RH side. (2) Depending on Inspection Results: Remove the Fasteners of FR 24 between STGR 17 and 18 RH side. (3) Do a Rototest Inspection of the Fastener Holes at FR 24 between STGR 17 and 18 RH side. (4) Depending on Inspection Results: Reinstall Fasteners and Splice at FR 24 between STGR 17 and 18 RH side.
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# @A318/A319/A320/A321 SERVICE BULLETIN E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale This Service Bulletin has been classified Recommended. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to change this classification to Mandatory. It is anticipated that the AD will confirm the thresholds given below but reference should be made to the AD for confirmation of the mandated accomplishment timescale. Table 1, Config.001: Inspection of Frame 24 between stringer 17 and stringer 18 RH side Condition Action Compliance Time Repetitive Interval All Aircraft Do a General Visual Inspection of Frame 24 between stringer 17 and stringer 18 RH side, refer to TASK 531285-832-801 001 Inspection Within 5000 FC from entry into service None

No missing fasteners and/or splice No further action None None Remove fasteners of holes 1 to 44, refer to SUBTASK 531285-831-001 001 Depending on Inspection Results: Remove the Fasteners of FR 24 between STGR 17 and 18 RH side. and Before next flight None Missing fasteners and/or splice

Do the rototest inspection of all holes, refer to SUBTASK 531285-832-002 001 Do a Rototest Inspection of the Fastener Holes at FR 24 between STGR 17 and 18 RH side. Before next flight None

If crack is found Contact Airbus for further action Before next flight None

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 4 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Table 1, Config.001: Inspection of Frame 24 between stringer 17 and stringer 18 RH side Condition Action Compliance Time Repetitive Interval Reinstall fasteners and splice, refer to SUBTASK 531285-831-002 001 Depending on Inspection Results: Reinstall Fasteners and Splice at FR 24 between STGR 17 and 18 RH side. SUBTASK 531285-831-002-001 and Before next flight None If no crack is found

No further action None None 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. 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 531285-832-801-001: Inspection Get Access 4.00 On Aircraft Do a General Visual Inspection of FR 24 between STGR 17 and 18 RH side. 0.25 Depending on Inspection Results: Remove the Fasteners of FR 24 between STGR 17 and 18 RH side. 6.50 Do a Rototest Inspection of the Fastener Holes at FR 24 between STGR 17 and 18 RH side. 12.00 Depending on Inspection Results: Reinstall Fasteners and Splice at FR 24 between STGR 17 and 18 RH side. 12.00 Close-Up 4.25 TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 NOTE: The minimum manhours necessary to accomplish this Service Bulletin are DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 5 5

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# @A318/A319/A320/A321 SERVICE BULLETIN those for the Inspection. Depending on the inspection result, additional manhours can apply. H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24 20-21-11 25-21-41 25-23-43 25-23-44 25-80-00 52-10-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 53-21-00 Impact on scheduled maintenance: Refer to Maintenance Planning Document (MPD). L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 6 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to B/E Aerospace. The address is: Component COMPA01 B/E AEROSPACE INC. CONSUMABLES MANAGEMENT 10000 NW 15th Terrace Miami FL 33172 USA Tel EMEA: +49 (0) 822 285 31500 Tel US: +1 305 925 2600 Tel ASIA: +1 310 900 1300 Fax EMEA: +49 (0) 822 285 31010 Fax US: +1 305 507 7191 Fax ASIA: +1 310 819 1200 SITA: MIAMMCR E-mail: AOGdesk_CMG@beaerospace.com internet: http://www.beconsumables.com 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: Component COMPA02 AIRBUS Material, Logistics and suppliers IFD - In Flight Desk Weg Beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 4012 For ordering by E-mail: ifd.spares@airbus.com (2) Price and Availability No AIRBUS kit will be provided. Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be purchased by a spares purchase order. Operator supplied standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock.

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 7 5

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# @A318/A319/A320/A321 SERVICE BULLETIN B. INDUSTRY SUPPORT INFORMATION AIRBUS will credit the man hours indicated in this Service Bulletin for inspections that are performed on aircraft in warranty at the time of such inspection. Credit will be at the agreed inhouse warranty labour rate. Claims for labour allowance should be received not later than 90 days after completion of the last affected warranted aircraft. For those aircraft in warranty at the time of such inspection with findings further to inspection as per this Service Bulletin, AIRBUS will share the costs of accomplishment of this Service Bulletin by crediting the operator supplied AIRBUS parts for orders placed before Sep 30/17. Claims for this allowance should be received not later than 90 days after completion of the last affected aircraft of your fleet. For the accomplishment of this Service Bulletin before Sep 30/17, AIRBUS will share the costs by crediting the operator supplied standard hardware parts. Claims for this allowance should be received not later than 90 days after completion of the last affected aircraft of your fleet. Airbus will credit the man hours indicated in this Service Bulletin for corrections that are performed on aircraft in warranty at the time of such correction. Credit will be at the agreed inhouse warranty labour rate. Claims for labour allowance should be received not later than 90 days after completion of the last affected warranted aircraft. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint-- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-- External Structure 04JAA3 As required Polysulfide Sealant-General Purpose Fillet 06AAB1 As required (2) Components Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 2 ASNA2536-3 55 NUT 3 ASNA2657V3-5Y 6 BOLT 4 EN6114V3-5 6 BOLT 5 EN6114V3-4 6 BOLT DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 8 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 6 EN6114V3-3 8 BOLT 7 EN6114V3-6 10 BOLT 9 EN6115V3-8 16 BOLT 10 EN6114V3-7 3 BOLT 11 ASNA2050DXJ4020 10 RIVET 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. NOTE: The above list of components is not AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 D5323006520103 1 SPLICE NOTE: The above list of components is not AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 9 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

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# @A318/A319/A320/A321 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 531285-832-801-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEPELECTRICAL 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. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical 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: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition.

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# @A318/A319/A320/A321 SERVICE BULLETIN Task Associated Data Zone 232 Access Door 831 Manpower TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 A. GENERAL (1) Subtask 531285-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 (a) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) Remove and install fasteners in accordance with SRM 51-42-00. (d) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (f) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (g) Apply sealant in accordance with SRM 51-24-00. (h) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (2) Subtask 531285-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.
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# @A318/A319/A320/A321 SERVICE BULLETIN B. PREPARATION (1) Subtask 531285-941-002-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 232 Work location Frame 24 from Stringer 17 to Stringer 18 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-21-41-000-001 Task 25-23-43-000-001 Task 25-23-44-000-001 25-80-00, Page Block 201 Task 52-10-00-010-001 (a) The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - 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. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put an access platform(s) in position at door 831. (d) Open the passenger/crew door 831, refer to AMM Task 52-10-00-010-001. (e) If necessary, remove the passenger seats around Frame 24, refer to AMM Task 25-21-41-000-001.

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 13 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (f) Remove the sidewall panels 232DW, 232EW, 232GW and 232HW, refer to AMM Task 25-23-43-000-001 and AMM Task 25-23-44-000-001. (g) Move insulation blankets around the Frame 24, refer to AMM 25-80-00, Page Block 201. C. PROCEDURE (1) Subtask 531285-832-001-001 - Do a General Visual Inspection of FR 24 between STGR 17 and 18 RH side. Work Zones and Access Panels Zone Access/Work location 232 Access Door 831 Work location Frame 24 from Stringer 17 to Stringer 18 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAA Flow Chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Fig. A-FBAAA Area to be Inspected Sheet 01 Sheet 02 Sheet 03 (a) At the threshold given in the Planning Information paragraph E.(2): Do a General Visual Inspection of Frame 24 between stringer 17 and stringer 18 RH side. Refer to Fig. A-FBAAAand Fig. A-FFAAA
. 1 If there are no missing fasteners and/or splice: a No further action. 2 If there are missing fasteners and/or splice: a Do SUBTASK 531285-831-001 001 Depending on Inspection Results: Remove the Fasteners of FR 24 between STGR 17 and 18 RH side. and Do SUBTASK 531285-832-002 001 Do a Rototest Inspection of the Fastener Holes at FR 24 between STGR 17 and 18 RH side. DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 14 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (b) For the Inspection Report, refer to Fig. A-FRAAA
. (2) Subtask 531285-831-001-001 - Depending on Inspection Results: Remove the Fasteners of FR 24 between STGR 17 and 18 RH side. Work Zones and Access Panels Zone Access/Work location 232 Access Door 831 Work location Frame 24 from Stringer 17 to Stringer 18 Manpower Resources Manhours 6.50 Minimum number of person 1 Subtask elapsed time 6.50 Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-42-00 Fig. A-FBCAA Removal/Installation of Fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove fasteners of holes 1 to 44: Refer to Fig. A-FBCAA
. In accordance with SRM 51-42-00. 6 Bush Item (2) Discard 3 Rivet Item (3) Discard 6 Rivet Item (4) Discard 22 Bush Item (5) Discard 6 Rivet Item (6) Discard 8 Rivet Item (7) Discard 3 Rivet Item (8) Discard 2 Rivet Item (9) Discard 16 Rivet Item (10) Discard

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 15 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (3) Subtask 531285-832-002-001 - Do a Rototest Inspection of the Fastener Holes at FR 24 between STGR 17 and 18 RH side. Work Zones and Access Panels Zone Access/Work location 232 Access Door 831 Work location Frame 24 from Stringer 17 to Stringer 18 Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FBBAA Rototest Inspection of Fasteners Holes Sheet 01 Sheet 02 Sheet 03 Fig. A-FFAAA Flow Chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 (a) Do the rototest inspection of all holes: Refer to Fig. A-FBBAAand Fig. A-FFAAA
. Refer to NTM 51-10-01. 1 If crack is found: a Contact Airbus for further instruction. 2 If no crack is found: a Do SUBTASK 531285-831-002 001 Depending on Inspection Results: Reinstall Fasteners and Splice at FR 24 between STGR 17 and 18 RH side. (b) For the Inspection Report, refer to Fig. A-FRAAA
.

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 16 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (4) Subtask 531285-831-002-001 - Depending on Inspection Results: Reinstall Fasteners and Splice at FR 24 between STGR 17 and 18 RH side. Work Zones and Access Panels Zone Access/Work location 232 Access Door 831 Work location Frame 24 from Stringer 17 to Stringer 18 Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills NON SPECIFIC Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2536-3 55 NUT 3 ASNA2657V3-5Y 6 BOLT 4 EN6114V3-5 6 BOLT 5 EN6114V3-4 6 BOLT 6 EN6114V3-3 8 BOLT 7 EN6114V3-6 10 BOLT 9 EN6115V3-8 16 BOLT 10 EN6114V3-7 3 BOLT 11 ASNA2050DXJ4020 10 RIVET NOTE: The above list of components is not AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPA02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 D5323006520103 1 SPLICE NOTE: The above list of components is not AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint-- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-- External Structure 04JAA3 As required

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 17 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant-General Purpose Fillet 06AAB1 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 Fig. A-FBCAA Removal/Installation of Fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 (a) Install fasteners of holes 1 to 44: Refer to Fig. A-FBCAA
. In accordance with SRM 51-42-00 and SRM 51-43-00. Refer to AMM Task 20-21-11-911-001. 44 Nut ASNA2536-3 Item 2 6 Bolt ASNA2657V3-5Y Item 3 6 Bolt EN6114V3-5 Item 4 6 Bolt EN6114V3-4 Item 5 8 Bolt EN6114V3-3 Item 6 2 Bolt EN6114V3-6 Item 7 16 Bolt EN6115V3-8 Item 9 (b) Install the missing splice and fasteners: Refer to Fig. A-FBCAA
. In accordance with SRM 51-42-00, SRM 51-43-00 and SRM 51-44-00. Refer to AMM Task 20-21-11-911-001. 1 Temporarily, put the Splice Item 1 in position as shown on Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
.
DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 18 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Drill eleven holes on the structure to align with the holes of the splice Item 1 to the diameter given in Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
. 3 Drill ten holes on the splice Item 1 to align with the holes of the structure to the diameter given in Fig. A-FBCAA Sheet 04
. 4 Remove the splice Item 1 and deburr the holes. 5 Between the splice Item 1 and the structure apply:Polysulfide SealantGeneral Purpose Fillet 06AAB1 As required
Refer to SRM 51-24-00 6 Install: Refer to Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
. 1 Splice D5323006520103 Item 1 8 Bolt EN6114V3-6 Item 7 3 Bolt EN6114V3-7 Item 10 11 Nut ASNA2536-3 Item 2 10 Rivet ASNA2050DXJ4020 Item 11 7 Do a sealant bead around the splice Item 1 with:Polysulfide SealantGeneral Purpose Fillet 06AAB1 As required
8 On the splice apply: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required
Top Coat Polyurethane-- External Structure 04JAA3 As required
D. TEST (1) Subtask 531285-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 19 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 25-21-41, Page Block 401 NOTE: This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtasks. If necessary, do the test procedure as specified in the SEAT - PASSENGER - REMOVAL/INSTALLATION, refer to AMM 25-21-41, Page Block 401. E. CLOSE-UP (1) Subtask 531285-942-001-001 - Close-up Work Zones and Access Panels Zone Access/Work location 232 Access Door 831 Work location Frame 24 from Stringer 17 to Stringer 18 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 Task 25-23-43-400-001 Task 25-23-44-400-001 Task 25-80-00-400-001 Task 52-10-00-410-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install insulation blankets, refer to AMM Task 25-80-00-400-001. (c) Install the sidewall panels 232DW, 232EW, 232GW and 232HW, refer to AMM Task 25-23-43-400-001 and AMM Task 25-23-44-400-001. (d) If removed, install the passenger seats, refer to AMM Task 25-21-41-400-001. (e) Close passenger/crew door, refer to AMM Task 52-10-00-410-001. (f) Remove the access platform(s). (g) Restore the systems and the aircraft to normal operating condition.

DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 20 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

AREA TO BE INSPECTED 

### A Z232

**NOTE:** 

## A FR24 STGR18 

### B

N_SB_531285_5_BAAA_01_01 Figure A-FBAAA - Sheet 01 Area to be Inspected DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 21 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL



### C FR24 FR25 FR23

STGR17 STGR18

STGR17

STGR18 FR24 **FWD** 

## B

**C E** 
**D**

N_SB_531285_5_BAAA_02_01 Figure A-FBAAA - Sheet 02 Area to be Inspected DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 22 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

STGR17

STGR18 FR24

VIEW LOOKING AFT 

## D

**NOTE:** MISSING FASTENERS STGR18 FR24

PART MISSING



## E
N_SB_531285_5_BAAA_03_01 Figure A-FBAAA - Sheet 03 Area to be Inspected DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 23 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

AREA TO BE INSPECTED 

### A Z232

**NOTE:** 

## A FR24 STGR18 

### B

N_SB_531285_5_BBAA_01_01 Figure A-FBBAA - Sheet 01 Rototest Inspection of Fasteners Holes DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 24 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL



### C FR24 FR25 FR23

STGR17 STGR18

STGR17

STGR18 FR24 **FWD** 

## B

**C F** 

**E D** 

N_SB_531285_5_BBAA_02_01 Figure A-FBBAA - Sheet 02 Rototest Inspection of Fasteners Holes DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 25 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

STGR17

STGR18 FR24

VIEW LOOKING AFT STGR18 FR24



## E STGR18 FR24



## D

**NOTE:** HOLE WITH FASTENER TO BE INSPECTED HOLE WITHOUT FASTENER TO BE INSPECTED 

## F **G** FR24

**FWD** 

## G

N_SB_531285_5_BBAA_03_01 Figure A-FBBAA - Sheet 03 Rototest Inspection of Fasteners Holes DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 26 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

AREA TO BE INSPECTED 

### A Z232

**NOTE:** 

## A FR24 STGR18 

### B

N_SB_531285_5_BCAA_01_01 Figure A-FBCAA - Sheet 01 Removal/Installation of Fasteners DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 27 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL



### C FR24 FR25 FR23

STGR17 STGR18

STGR17

STGR18 FR24 **FWD** 

## B

**C F** 

**E D** 

N_SB_531285_5_BCAA_02_01 Figure A-FBCAA - Sheet 02 Removal/Installation of Fasteners DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 28 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

STGR18 FR24



## E STGR18 FR24



## D

**NOTE:**BETWEEN THE SPLICE AND THE 1 01

01 STRUCTURE APPLY MAT. No 06AAB1. H8 H16

H15 H14 H6 H7

H5 H4 H13 H12

H3 H2 H1 H11 H10 H9
H20 H19 H28 H27 H26

H25 H24
H23

H22

H21 H17 H18 20.33 mm

(0.8 in) 02 03

DO A SEALANT BEAD AROUND THE SPLICE WITH MAT. No 06AAB1. 02 ON THE SPLICE APPLY MAT. No 04EAC2 03 AND MAT. No 04JAA2. N_SB_531285_5_BCAA_03_01 Figure A-FBCAA - Sheet 03 Removal/Installation of Fasteners DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 29 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

STGR17

STGR18 FR24

VIEW LOOKING AFT **NOTE:** HOLE SYMBOLE OLD ITEM ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX

EN6114V3−5 ASNA2657V3−5Y

ASNA2536−3

ASNA2536−3 EN6114V3−4 ASNA2536−3 EN6114V3−3 ASNA2536−3 ASNA2657V3−5Y

ASNA2536−3 EN6114V3−6 ASNA2536−3 EN6115V3−8 EN6114V3−6 ASNA2536−3 EN6114V3−7 ASNA2536−3 ASNA2050DXJ4020 NUT BOLT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT

4.14 mm (0.163 in) 4.14 mm (0.163 in)
3.94 mm (0.155 in) 4.15 mm (0.164 in) 4.15 mm (0.164 in)

4 mm (0.157 in) 2 3 4 2 5 2 6 2 3 2 7 2 9 7 2 10 2 11 (2) (3) (4) (5) (6) (5) (7) (5) (8) (2) (9) (5) (10)H32 H31 H36 H40 H35 H39

H34H38 H37
H33 H30 H29

2 ASNA2536−3 NUT BOLT NUT BOLT NUT RIVET FR24

**FWD** H44

H43 H42
H41


## F **G G** 

N_SB_531285_5_BCAA_04_01 Figure A-FBCAA - Sheet 04 Removal/Installation of Fasteners DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 30 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

INFORMATION PARAGRAPH E.(2). REFER TO TASK 531285−832−801−001.

MISSING FASTENERS AND/OR NO YES

REMOVE FASTENERS FROM HOLES 1 TO 44

REFER TO SUBTASK 531285−831−001−001 & RH SIDE.

STGR18 AT THE THRESHOLD GIVEN IN THE PLANNING

REPORT RESULTS TO AIRBUS

CRACKS? NO YES

CONTACT AIRBUS FOR FURTHER INSTRUCTION DO A GENERAL VISUAL INSPECTION OF BETWEEN FR24 STGR17

SPLICE

DO A ROTOTEST INSPECTION OF ALL HOLES

REFER TO SUBTASK 531285−832−002−001

REINSTALL FASTENERS AND SPLICE REFER TO SUBTASK 531285−831−002−001

NO FURTHER ACTION NO FURTHER ACTION

REPORT RESULTS TO AIRBUS

QUESTION ACTION FINDING **NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN. N_SB_531285_5_FAAA_01_01 Figure A-FFAAA - Sheet 01 Flow Chart DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 31 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−53−1285

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES4 PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD : 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−mail: Structure.sbinspectionresult@airbus.com GENERAL VISUAL SPECIAL DETAILED INSPECTION INSPECTION

YES NO MISSING FASTENERS AND/OR SPLICE ? YES NO CRACK FOUND ON THE FASTENERS HOLES ?

HOLE NUMBER(S) FOUND WITH CRACK ? YES NO MISSING FASTENERS AND SPLICE INSTALLED ? CENTER WING BOX (SA/LA)
FAX +33 (0)5 61 93 36 14

N_SB_531285_5_RAAA_01_00 Figure A-FRAAA - Sheet 01 Inspection Report DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 32 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

STGR17

STGR18 FR24

VIEW LOOKING AFT STGR18 FR24



## E STGR18 FR24



## D

**NOTE:** HOLE WITH FASTENER TO BE INSPECTED HOLE WITHOUT FASTENER TO BE INSPECTED H8 H16

H15 H14 H6 H7

H5 H4 H13 H12

H3 H2 H1 H11 H10 H9 H20 H19 H28 H27 H26

H25 H24
H23

H22

H21 H17 H18

H32 H31 H36 H40 H35

H39

H34H38 H37
H33 H30 H29



## F **G** FR24

**FWD**H44

H43 H42
H41


## G

N_SB_531285_5_RAAA_02_01 Figure A-FRAAA - Sheet 02 Inspection Report DATE: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 33 5

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

### TITLE: FUSELAGE - MAIN STRUCTURE - INSPECTION FOR MISSING FASTENERS AT FR24 BETWEEN STR17 & STR18 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: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 1 5

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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 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: Jan 29/14 SERVICE BULLETIN No.: A320-53-1285 REVISION No.: 00 - Jan 29/14 Page: 1 5

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