# @A300-600 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: A300-600 - GENERAL - INSTALL REINFORCEMENTS AT DOOR FRAME SHELL OF DOOR 2 AND 4 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13578D23280 MINOR None NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The aircraft structure life is 42500 Flight Cycles (FC)/89000 Flight Hours (FH) and to extend the structure life to 51000 FC/89000 FH the passenger door frames at door No. 2 and 4 have to be reinforced. This Service Bulletin proposes to modify the door frame with additional reinforcement and filler plates at the No. 2 and 4 doors. Accomplishment of this Service Bulletin will extend the structure life from 42500 FC/89000 FH to 51000 FC/89000 FH for the door frames of the passenger doors 2 and 4. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE OPTIONAL (1) CANCELS INSPECTION SB NO POTENTIAL AD NO 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 for convenience or option.

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 1 6

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# @A300-600 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 536170D01R05 1 See SB Doublers, Filler, Key, Hi-Lok and Collars Kit 536170D02R02 1 See SB Doublers, Filler, Key, Hi-Lok and Collars Kit 536170D03R00 1 See SB Doubler, Hi-Lok and Collars EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

KAL NOTE: This Service Bulletin is written for the operators listed above. The modification in this Service Bulletin can be done by other operators. If other operators want to do this modification, use the RFC/RMO procedure and write to : AIRBUS CUSTOMER SERVICES DIRECTORATE SC Department 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE 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 536170-831-848-001: Modification TOTAL MANHOURS 760.00 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 2 6

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# @A300-600 SERVICE BULLETIN SUMMARY Task 536170-831-848-001: Modification ELAPSED TIME (HOURS) 400.0 APPENDICES None

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 3 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF ALL Z261 (Z262)

Z171 (Z172)

FR76 FR73

FR28

FR76 FR73

FR28

AREAS TO BE MODIFIED. **NOTE:** D_SB_536170_6_SAAA_01_00 Z131 (Z132) Z231 (Z232) 

### D **C B** 

**A**



## A **B**

**C**

**D** FR31

FR31

Figure A-GSAAA - Sheet 01
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 4 6

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# @A300-600 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: A300-600 - GENERAL - INSTALL REINFORCEMENTS AT DOOR FRAME SHELL OF DOOR 2 AND 4 MODIFICATION No.: 13578D23280 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 B4-622R (2) Effectivity by MSN 0627 0662 (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 KAL 0627 0662 (4) Configuration by MSN MSN CONFIGURATION 0627 0662 001
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 1 6

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# @A300-600 SERVICE BULLETIN (5) Configuration definition **CONF 001 Config. 001 is valid for the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Kit 536170D01R05 1 Kit 536170D02R02 1 Kit 536170D03R00 1 Consumable CMLD01 As required B. CONCURRENT REQUIREMENTS None C. REASON (1) History The aircraft structure life is 42500 Flight Cycles (FC)/89000 Flight Hours (FH) and to extend the structure life to 51000 FC/89000 FH the passenger door frames at door No. 2 and 4 have to be reinforced. (2) Objective/Action This Service Bulletin proposes to modify the door frame with additional reinforcement and filler plates at the No. 2 and 4 doors. (3) Advantages Accomplishment of this Service Bulletin will extend the structure life from 42500 FC/89000 FH to 51000 FC/89000 FH for the door frames of the passenger doors 2 and 4. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 536170-831-848-001: Modification (1) Remove the fasteners at the LH/RH Mid Passenger/Crew Door Frame Corners (2) Remove the fasteners at the LH/RH AFT Passenger/Crew Door Frame Corners (3) Install an additional doubler between the strip and the door structure at the MID passenger/crew doors DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 2 6

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# @A300-600 SERVICE BULLETIN (4) Install an additional doubler between the strip and the door structure at the AFT passenger/crew doors (5) Install the reinforcement at the LH MID Passenger/Crew Door Frame (6) Install the reinforcement at the RH MID Passenger/Crew Door Frame (7) Install the reinforcement at the LH AFT Passenger/Crew Door Frame (8) Install the reinforcement at the RH AFT Passenger/Crew Door Frame E. COMPLIANCE (1) Classification OPTIONAL: Service Bulletin for convenience or option. (2) Accomplishment Timescale This Service Bulletin must be accomplished before 42500 Flight Cycles (FC). 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 536170-831-848-001: Modification Get Access 10.0 On Aircraft Remove the fasteners at the LH/RH Mid Passenger/Crew Door Frame Corners 4.00 Remove the fasteners at the LH/RH AFT Passenger/Crew Door Frame Corners 4.00 Install an additional doubler between the strip and the door structure at the MID passenger/crew doors 16.00 Install an additional doubler between the strip and the door structure at the AFT passenger/crew doors 16.00

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 3 6

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# @A300-600 SERVICE BULLETIN
Task 536170-831-848-001: Modification Install the reinforcement at the LH MID Passenger/Crew Door Frame 180.0 Install the reinforcement at the RH MID Passenger/Crew Door Frame 180.0 Install the reinforcement at the LH AFT Passenger/Crew Door Frame 160.0 Install the reinforcement at the RH AFT Passenger/Crew Door Frame 160.0 Close-Up 30.0 TOTAL MANHOURS 760.00 ELAPSED TIME (HOURS) 400.0 H. WEIGHT AND BALANCE The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator items. For the definition of MEW and operator items refer to Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight +70.361 KG (+155.1178 LB) Effect on Balance +2170.764 KGM (+15701.136 LB.FT ) I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-53 12-34-24 20-21-12 25-23-41 25-28-12 52-10-00 53-10-25 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-21 51-40-30 51-40-40 51-40-44 51-71-15 51-75-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 K. PUBLICATION AFFECTED

Structural Repair Manual (SRM) 53-14-12 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 4 6

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 536170D01R05 Kit 536170D02R02 Kit 536170D03R00 The Airbus material is included in the commercial offer of the Letter Agreement, and as such will be supplied by AIRBUS Upgrade Services. To facilitate the material reception, Airline Customers are requested to send a Customer Purchase Order to: AIRBUS Upgrade Services Attn: FCO manager (2) Price and Availability Sales terms must be agreed between the Customer and AIRBUS in accordance with the RFC (or RFC/RMO) procedure. B. INDUSTRY SUPPORT INFORMATION Refer to the paragraph: ’Price and Availability’. C. LIST OF COMPONENTS Kit 536170D01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 B5377037620000 1 DOUBLER 2 B5377037620100 1 DOUBLER 3 B5377037620200 1 DOUBLER 4 B5377037620300 1 DOUBLER 5 B5377037621200 2 DOUBLER 6 B5377039820400 2 KEY 7 B5377037620400 1 DOUBLER 8 B5377037620500 1 DOUBLER 9 B5377037620600 1 DOUBLER 10 B5377037620700 1 DOUBLER 11 B5377037621400 2 DOUBLER 12 B5377039820600 2 KEY 13 B5377037720000 2 LEDGE 14 B5377039820000 1 DOUBLER 15 B5377039820100 1 DOUBLER 16 B5377037620800 1 DOUBLER 17 B5377037620900 1 DOUBLER 18 B5377039820200 1 DOUBLER 19 B5377039820300 1 DOUBLER DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 5 6

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 20 B5377037621000 1 DOUBLER 21 B5377037621100 1 DOUBLER 31 DAN6-6-7X 12 PIN 32 DAN6-6-5X 116 PIN 33 DAN6-6-6X 82 PIN 34 DAN6-6-8X 154 PIN 35 DAN6-6-9X 122 PIN 36 DAN6-6-10X 168 PIN 37 DAN6-6-11X 74 PIN 38 DAN6-6-12X 100 PIN 39 DAN6-6-13X 102 PIN 40 DAN6-6-14X 60 PIN 41 DAN6-6-16X 24 PIN 42 DAN6-6-5Y 12 PIN 43 DAN6-6-6Y 6 PIN 44 DAN6-6-8Y 10 PIN 45 DAN6-6-9Y 2 PIN 46 DAN6-6-11Y 2 PIN 47 DAN6-6-12Y 54 PIN 48 DAN6-6-13Y 14 PIN 49 DAN6-6-14Y 118 PIN 50 DAN6-6-15Y 8 PIN 51 DAN6-6-16Y 24 PIN 52 DAN6-6-4 12 PIN 53 DAN6-6-5 26 PIN 54 DAN6-6-6 196 PIN 55 DAN6-6-7 126 PIN 56 DAN6-6-8 218 PIN 57 DAN6-6-9 296 PIN 58 DAN6-6-10 570 PIN 59 DAN6-6-11 330 PIN 60 DAN6-6-12 64 PIN 61 DAN6-6-14 26 PIN 62 DAN6-8-9 6 PIN 63 DAN6-8-10 8 PIN 64 DAN6-8-11 8 PIN 65 DAN6-8-12 6 PIN 66 DAN6-8-14 4 PIN 67 DAN6-8-15 10 PIN 68 DAN6-8-16 2 PIN 69 NSA5075-6 1864 COLLAR 70 NSA5075-8 44 COLLAR 71 DAN11-6X 1014 COLLAR 72 DAN11-6Y 250 COLLAR 73 B5377039820800 2 DOUBLER DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 6 6

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# @A300-600 SERVICE BULLETIN
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. Kit 536170D02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 22 A5398104020000 1 DOUBLER 23 A5398104020100 1 DOUBLER 24 A5398104020200 1 DOUBLER 25 A5398104020300 1 DOUBLER 26 A5398104020400 1 DOUBLER 27 A5398104020500 1 DOUBLER 28 A5398104020600 1 DOUBLER 29 A5398104020700 1 DOUBLER 30 A5398104020800 2 DOUBLER 31 DAN6-6-7X 50 PIN 33 DAN6-6-6X 8 PIN 34 DAN6-6-8X 376 PIN 35 DAN6-6-9X 722 PIN 36 DAN6-6-10X 16 PIN 37 DAN6-6-11X 158 PIN 38 DAN6-6-12X 250 PIN 39 DAN6-6-13X 114 PIN 53 DAN6-6-5 48 PIN 55 DAN6-6-7 312 PIN 58 DAN6-6-10 24 PIN 69 NSA5075-6 384 COLLAR 71 DAN11-6X 1678 COLLAR 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. Kit 536170D03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 100 A5217508820000 1 SHIM 101 A5217508620000 2 SHIM 102 NAS1102E3-18 70 SCREW 103 NAS1726C3 70 NUT 104 DIN65399-4018CF 580 RIVET 106 A5217508620100 1 SHIM

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 7 6

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# @A300-600 SERVICE BULLETIN
NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Top coat grey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required Lint-Free Cotton Cloth 19-003 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 8 6

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 536170-831-848-001 - Modification 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 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 ELECTRICAL 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. Task Associated Data Zone From 131 to 231 From 132 to 232 From 171 to 261 From 172 to 262 From 231 to 232 From 261 to 262 From 832 to 842 From 833 to 843 Access Panel 231LW 231MW 231NW 231PW 231QW 231RW 231SW 231TW 231UW 231VW 231WW 231XW 231YW 232LW 232MW 232NW 232PW 232QW 232RW 232SW 232TW 232UW 232VW 232WW 232XW 232YW 261AW 261AZ 261BW 261CW 261DW 261EW 261FW 261GW 261NW 261PW 261QW 261RW 262AW 262AZ 262BW 262CW 262DW 262EW 262FW 262GW 262NW 262PW 262QW 262RWManpower TOTAL MANHOURS 760.00 ELAPSED TIME (HOURS) 400.0

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 9 6

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# @A300-600 SERVICE BULLETIN
A. GENERAL (1) Subtask 536170-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Top coat grey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required Lint-Free Cotton Cloth 19-003 As required References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-21 51-40-30 51-40-40 51-40-44 51-71-15 51-75-10 (a) For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to Consumable Material List (CML)). (b) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of aircraft zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001). (e) Tag the parts that you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related units. DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 10 6

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# @A300-600 SERVICE BULLETIN (g) Remove old sealant with a non-metallic scraper and a stiff brush. (h) To torque tighten standard threaded fasteners (Refer to AMM 20-21-12, Page Block 001). (i) For fastener installation and removal (Refer to SRM 51-40-21). (j) For alternative and substitute fasteners (Refer to SRM 51-40-30). (k) For hole and drill data (Refer to SRM 51-40-40). (l) For the installation of transition fit Hi-Lok fasteners (Refer to SRM 51-40-44). (m) Existing countersink (Refer to SRM 51-71-15). (n) After drilling and cutting, apply (Refer to SRM 51-75-10): Wash Primer 16-020 As required Anti-Corrosion Primer (polyurethane) 16-001 As required
Polyurethane Top coat grey (for Internal Applic.) 16-002 As required
(o) If necessary, clean the work area(s) with: Lint-Free Cotton Cloth 19-003 As required

made moist with Solvent General Purpose 11-026 As required (p) Seal the reworked surfaces, rivets and fasteners with (Refer to SRM 51-24-00): Corrosion Inhibiting Brush Consistency 09-013 As required (q) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 536170-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 11 6

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# @A300-600 SERVICE BULLETIN Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 536170-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location From 833 To 843 From 832 To 842 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 52-10-00, Page Block 201 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page Block 201). (b) Put access platform(s) in position below the MID passenger/crew doors 832 and 842 and the AFT passenger/crew doors 833 and 843. (c) Open the MID passenger/crew doors 832 and 842 (Refer to AMM Task 52-10-00, Page Block 201). (d) Open the AFT passenger/crew doors 833 and 843 (Refer to AMM Task 52-10-00, Page Block 201). (2) Subtask 536170-010-201-001 - Remove/Open for Access Work Zones and Access Panels Zone Access/Work location From 231 Access Panel 231LW, Panel 231MW, Panel 231NW, Panel 231PW, Panel 231QW, Panel 231RW, Panel 231SW, Panel 231TW, Panel 231UW, Panel 231VW, Panel 231WW, Panel 231XW, Panel 231YW To 232 Access Panel 232LW, Panel 232MW, Panel 231NW, Panel 232PW, Panel 232QW, Panel 232RW, Panel 232SW, Panel 232TW, Panel 232UW, Panel 232VW, Panel 232WW, Panel 232XW, Panel 232YW From 261 Access Panel 261AW, Panel 261BW, Panel 261CW, Panel 261DW, Panel 261EW, Panel 261FW, Panel 261GW, Panel 261NW, Panel 261PW, Panel 261QW, Panel 261RW, Panel 261AZ DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 12 6

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# @A300-600 SERVICE BULLETIN
To 262 Access Panel 262AW, Panel 262BW, Panel 262CW, Panel 262DW, Panel 262EW, Panel 262FW, Panel 262GW, Panel 262NW, Panel 262PW, Panel 262QW, Panel 262RW, Panel 262AZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 25-23-41, Page Block 401 25-28-12, Page Block 401 53-10-25, Page Block 401 (a) Remove and retain the MID passenger/crew side wall panels LH 231LW, 231MW, 231NW, 231PW, 231QW, 231RW, 231SW, 231TW, 231UW, 231VW, 231XW, 231YW and 231WW (Refer to AMM 25-23-41, Page Block 401). (b) Remove and retain the MID passenger/crew side wall panels RH 232LW, 232MW, 232NW, 232PW, 232QW, 232RW, 232SW, 232TW, 232UW, 232VW, 232XW, 232YW and 232WW (Refer to AMM 25-23-41, Page Block 401). (c) Remove and retain the AFT passenger/crew side wall panels LH 261AW, 261BW, 261CW, 261DW, 261EW, 261FG, 261GW, 261NW, 261PW, 261RW, 261QW and 261AZ (Refer to AMM 25-23-41, Page Block 401). (d) Remove and retain the AFT passenger/crew side wall panels RH 262AW, 262BW, 262CW, 262DW, 262EW, 262FG, 262GW, 262NW, 262PW, 262RW, 262QW and 262AZ (Refer to AMM 25-23-41, Page Block 401). (e) Remove and retain the floor covering to get access to floor panels 231TF, 231SF, 232TF, 232SF, 261QF, 261PF, 262QF and 262PF (Refer to AMM 25-28-12, Page Block 401). (f) Remove and retain the floor panels at the MID passenger/crew LH/RH position 231TF, 231SF, 232TF and 232SF (Refer to AMM 53-10-25, Page Block 401). (g) Remove and retain the floor panels at the AFT passenger/crew LH/RH position 261QF, 261PF, 262QF and 262PF (Refer to AMM 53-10-25, Page Block 401). C. PROCEDURE (1) Subtask 536170-831-201-001 - Remove the fasteners at the LH/RH Mid Passenger/Crew Door Frame Corners Work Zones and Access Panels Zone Access/Work location From 132 Work location from Frame 28 to Frame 31 To 232 Work location from Frame 28 to Frame 31 From 131 Work location from Frame 28 to Frame 31 To 231 Work location from Frame 28 to Frame 31
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 13 6

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBAAA Installation of doublers and reinforcement at the MID passenger/crew door frame Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 (a) Remove the fasteners between Frame 30 thru Frame 32 and stringer 12 thru stringer 15 at the LH/RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Remove the fasteners as shown in Fig. A-GBAAA, Views A and B. 2 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (b) Remove the fasteners between Frame 27 thru Frame 29 and stringer 12 thru stringer 15 at the LH/RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Remove the fasteners as shown in Fig. A-GBAAA, Views A and D. 2 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 14 6

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# @A300-600 SERVICE BULLETIN (c) Remove the fasteners between Frame 30 thru Frame 31 and stringer 25 thru stringer 28 at the LH/RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Remove the fasteners as shown in Fig. A-GBAAA, Views A and F. 2 Remove and discard: 2 Plate-Retainer A5377698200000 Item (110) Discard 2 Plate-Retainer A5377698601400 Item (111) Discard 2 Plate-Retainer A5377699900300 Item (112) Discard 2 Plate-Retainer A5377698500200 Item (113) Discard 2 Plate-Retainer A5377698601200 Item (114) Discard 2 Plate-Retainer A5377698600400 Item (115) Discard 2 Plate-Cover A5377696700000 Item (116) Discard 4 Plate-Retainer A5377698600200 Item (117) Discard 2 Plate-Retainer A5377698900000 Item (118) Discard 119 Plate-Retainer A5377698900400 Item (2) Discard 2 Plate-Retainer A5377699200800 Item (120) Discard 2 Plate-Retainer A5377699201000 Item (121) Discard 2 Plate-Retainer A5377699400100 Item (122) Discard 2 Plate Assy A5377698800000 Item (123) Discard 3 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (d) Remove the fasteners between Frame 27 thru Frame 29 and stringer 25 thru stringer 27 at the LH/RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Remove the fasteners as shown in Fig. A-GBAAA, Views A and H.

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 15 6

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# @A300-600 SERVICE BULLETIN
2 Remove and discard: 2 Plate-Retainer A5377698600200 Item (117) Discard 2 Plate-Retainer A5377698900000 Item (118) Discard 2 Plate Assy A5377698800000 Item (123) Discard 2 Plate Assy A5377699800000 Item (124) Discard 2 Plate-Retainer A5377699700000 Item (125) Discard 2 Plate-Retainer A5377698900200 Item (126) Discard 2 Plate-Retainer A5377699200600 Item (127) Discard 2 Plate-Retainer A5377698601000 Item (128) Discard 2 Plate-Retainer A5377699500200 Item (129) Discard 2 Bracket Assy A5377699600000 Item (130) Discard 2 Plate-Retainer A5377698600800 Item (131) Discard 2 Plate-Retainer A5377699200200 Item (132) Discard 2 Plate-Retainer A5377698400200 Item (133) Discard 3 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (e) Remove the fasteners between Frame 28 thru Frame 30 and stringer 12 thru stringer 13 at the LH/RH Mid Passenger/Crew Door Frame. Refer to Fig. A-GBAAA 1 Remove the fasteners as shown in Fig. A-GBAAA, Views A and K. 2 Remove and retain LH: 1 Deflector-Rainwater A5377517320600 Item (90) Retain 12 Screw NAS1102E3-14 Item (91) Retain 12 Nut MS21043-3 Item (92) Retain 5 Spacer A5377517420200 Item (93) Retain DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 16 6

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# @A300-600 SERVICE BULLETIN 7 Spacer A5377517420300 Item (94) Retain 3 Remove and retain RH: 1 Deflector-Rainwater A5377517320700 Item (95) Retain 12 Screw NAS1102E3-14 Item (91) Retain 12 Nut MS21043-3 Item (92) Retain 5 Spacer A5377517420200 Item (93) Retain 7 Spacer A5377517420300 Item (94) Retain 4 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (2) Subtask 536170-831-205-001 - Remove the fasteners at the LH/RH AFT Passenger/Crew Door Frame Corners Work Zones and Access Panels Zone Access/Work location From 172 Work location from Frame 73 to Frame 76 To 262 Work location from Frame 73 to Frame 76 From 171 Work location from Frame 73 to Frame 76 To 261 Work location from Frame 73 to Frame 76 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 17 6

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# @A300-600 SERVICE BULLETIN
References Fig. A-GBBAA Installation of doublers and reinforcement at the AFT passenger/crew door frame Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 (a) Remove the fasteners between Frame 72 thru Frame 74 and stringer 24 thru stringer 27 at the LH/RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Remove the fasteners as shown in Fig. A-GBBAA, Views A and B. 2 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (b) Remove the fasteners between Frame 75 thru Frame 76 and stringer 23 thru stringer 27 at the LH/RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Remove the fasteners as shown in Fig. A-GBBAA, Views A and D. 2 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (c) Remove the fasteners between Frame 73 thru Frame 74 and stringer 10 thru stringer 13 at the LH/RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Remove the fasteners as shown in Fig. A-GBBAA, Views A and F. 2 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required

. (d) Remove the fasteners between Frame 74 thru Frame 75 at stringer 11 at the LH/RH AFT Passenger/Crew Door Frame. Refer to Fig. A-GBBAA DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 18 6

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# @A300-600 SERVICE BULLETIN
1 Remove the fasteners as shown in Fig. A-GBBAA, Views A, F and H. NOTE: To install the doubler remove every third fastener. 2 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (e) Remove the fasteners between Frame 75 thru Frame 76 and stringer 10 thru stringer 13 at the LH/RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Remove the fasteners as shown in Fig. A-GBBAA, Views A and H. 2 Clean the fastener holes and adjacent area with: Solvent General Purpose 11-026 As required (3) Subtask 536170-831-206-001 - Install an additional doubler between the strip and the door structure at the MID passenger/crew doors Work Zones and Access Panels Zone Access/Work location From 832 To 842 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536170D03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 100 A5217508820000 1 SHIM 101 A5217508620000 1 SHIM 102 NAS1102E3-18 34 SCREW 103 NAS1726C3 34 NUT 104 DIN65399-4018CF 340 RIVET

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 19 6

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# @A300-600 SERVICE BULLETIN
Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBCAA Installation of a doubler at the MID and AFT passenger/crew doors Sheet 01 Sheet 02 Sheet 03 (a) Install an additional doubler, Item 100 between the strip, Item (110) and the door structure at the MID passenger/crew door LH. Refer to Fig. A-GBCAA, Views A and C. 1 Remove: 1 Strip-Cover A5217016601200 Item (110) Retain 1 Retainer-Door Seal A5217015820200 Item (112) Retain 1 Retainer-Door Seal A5217015920200 Item (113) Retain 1 Retainer-Door Seal A5217015920300 Item (114) Retain 17 Screw NSA5022-3-11 Item (102) Discard 17 Nut NAS1726C3S Item (103) Discard 2 Remove the old sealant from the door structure with: Solvent General Purpose 11-026 As required
3 Put in position at the door structure. Refer to Fig. A-GBCAA, Views A and C. 1 Shim A5217508820000 Item 100 NOTE: Make sure that the edges of the shim are flush with the door structure. 4 Temporarily attach the shim, Item 100 with the strip, Item (110) to the door structure and transfer drill the fastener holes. 5 Countersink the fastener holes of the strip, Item (110).
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 20 6

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# @A300-600 SERVICE BULLETIN
6 Wet install the shim, Item 100 and the strip, Item (110) with: 170 Rivet DIN65399-4018CF Item 104 7 Install: 1 Retainer-Door Seal A5217015820200 Item (112) Retained at removal 1 Retainer-Door Seal A5217015920200 Item (113) Retained at removal 1 Retainer-Door Seal A5217015920300 Item (114) Retained at removal with: 17 Screw NAS1102E3-18 Item 102 17 Nut NAS1726C3 Item 103 8 Apply: Corrosion Inhibiting fillet Consistency 09-016 As required to the edges of the shim, Item 100 and the strip, Item (110). (b) Install an additional doubler, Item 101 between the strip, Item (110) and the door structure at the MID passenger/crew door RH. Refer to Fig. A-GBCAA, Views A and C. 1 Remove: 1 Strip-Cover A5217016601200 Item (110) Retain 1 Retainer-Door Seal A5217015820200 Item (112) Retain 1 Retainer-Door Seal A5217015920200 Item (113) Retain 1 Retainer-Door Seal A5217015920300 Item (114) Retain 17 Screw NSA5022-3-11 Item (102) Discard 17 Nut NAS1726C3S Item (103) Discard 2 Remove the old sealant from the door structure with: Solvent General Purpose 11-026 As required

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 21 6

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# @A300-600 SERVICE BULLETIN
3 Put in position at the door structure. Refer to Fig. A-GBCAA, Views A and C. 1 Shim A5217508620000 Item 101 NOTE: Make sure that the edges of the shim are flush with the door structure. 4 Temporarily attach the shim, Item 101 with the strip, Item (110) to the door structure and transfer drill the fastener holes. 5 Countersink the fastener holes of the strip, Item (110). 6 Wet install the shim, Item 101 and the strip, Item (110) with: 170 Rivet DIN65399-4018CF Item 104 7 Install: 1 Retainer-Door Seal A5217015820200 Item (112) Retained at removal 1 Retainer-Door Seal A5217015920200 Item (113) Retained at removal 1 Retainer-Door Seal A5217015920300 Item (114) Retained at removal with: 17 Screw NAS1102E3-18 Item 102 17 Nut NAS1726C3 Item 103 8 Apply: Corrosion Inhibiting fillet Consistency 09-016 As required to the edges of the shim, Item 101 and the strip, Item (110). (4) Subtask 536170-831-207-001 - Install an additional doubler between the strip and the door structure at the AFT passenger/crew doors Work Zones and Access Panels Zone Access/Work location From 833 To 843

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 22 6

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 536170D03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 101 A5217508620000 1 SHIM 102 NAS1102E3-18 36 SCREW 103 NAS1726C3 36 NUT 104 DIN65399-4018CF 240 RIVET 106 A5217508620100 1 SHIM Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBCAA Installation of a doubler at the MID and AFT passenger/crew doors Sheet 01 Sheet 02 Sheet 03 (a) Install an additional doubler, Item 101 between the strip, Item (108) and the door structure at the AFT passenger/crew door LH. Refer to Fig. A-GBCAA, Views B and D. 1 Remove: 1 Cover Assy A5217533300800 Item (108) Retain 2 Retainer-Door Seal A5217528820400 Item (115) Retain or 2 Retainer-Door Seal A5217528820800 Item (115) Retain 1 Retainer-Door Seal A5217528620800 Item (116) Retain 18 Screw NSA5022-3-11 Item (102) Discard
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 23 6

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# @A300-600 SERVICE BULLETIN 18 Nut NAS1726C3S Item (103) Discard 2 Remove the old sealant from the door structure with: Solvent General Purpose 11-026 As required
3 Put in position at the door structure. Refer to Fig. A-GBCAA, Views B and D. 1 Shim A5217508620000 Item 101 NOTE: Make sure that the edges of the shim are flush with the door structure. 4 Temporarily attach the shim, Item 101 with the cover assy, Item (108) to the door structure and transfer drill the fastener holes. 5 Countersink the fastener holes of the cover assy, Item (108). 6 Wet install the shim, Item 101 and the cover assy, Item (108) with: 120 Rivet DIN65399-4018CF Item 104 7 Install: 1 Cover Assy A5217533300800 Item (108) Retained at removal 2 Retainer-Door Seal A5217528820400 Item (115) Retained at removal or 2 Retainer-Door Seal A5217528820800 Item (115) Retained at removal 1 Retainer-Door Seal A5217528620800 Item (116) Retained at removal with: 18 Screw NAS1102E3-18 Item 102 18 Nut NAS1726C3 Item 103 8 Apply: Corrosion Inhibiting fillet Consistency 09-016 As required to the edges of the shim, Item 101 and the cover assy, Item (108).
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 24 6

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# @A300-600 SERVICE BULLETIN (b) Install an additional doubler, Item 106 between the strip, Item (109) and the door structure at the AFT passenger/crew door RH. Refer to Fig. A-GBCAA, Views B and D. 1 Remove: 1 Cover Assy A5217533300900 Item (109) Retain 2 Retainer-Door Seal A5217528820400 Item (115) Retain or 2 Retainer-Door Seal A5217528820800 Item (115) Retain 1 Retainer-Door Seal A5217528620900 Item (117) Retain 18 Screw NSA5022-3-11 Item (102) Discard 18 Nut NAS1726C3S Item (103) Discard 2 Remove the old sealant from the door structure with: Solvent General Purpose 11-026 As required
3 Put in position at the door structure. Refer to Fig. A-GBCAA, Views B and D. 1 Shim A5217508620100 Item 106 NOTE: Make sure that the edges of the shim are flush with the door structure. 4 Temporarily attach the shim, Item 106 with the cover assy, Item (109) to the door structure and transfer drill the fastener holes. 5 Countersink the fastener holes of the cover assy, Item (109). 6 Wet install the shim, Item 106 and the cover assy, Item (109) with: 120 Rivet DIN65399-4018CF Item 104 7 Install: 1 Cover Assy A5217533300900 Item (109) Retained at removal 2 Retainer-Door Seal A5217528820400 Item (115) Retained at removal or DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 25 6

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# @A300-600 SERVICE BULLETIN 2 Retainer-Door Seal A5217528820800 Item (115) Retained at removal 1 Retainer-Door Seal A5217528620900 Item (117) Retained at removal with: 18 Screw NAS1102E3-18 Item 102 18 Nut NAS1726C3 Item 103 8 Apply: Corrosion Inhibiting fillet Consistency 09-016 As required to the edges of the shim, Item 106 and the cover assy, Item (109). (5) Subtask 536170-831-202-001 - Install the reinforcement at the LH MID Passenger/Crew Door Frame Work Zones and Access Panels Zone Access/Work location From 131 Work location from Frame 28 to Frame 31 To 231 Work location from Frame 28 to Frame 31 Manpower Resources Manhours 180.0 Minimum number of person 2 Subtask elapsed time 90.00 Skills AIRFRAME Material necessary to do the job Kit 536170D01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 B5377037620000 1 DOUBLER 3 B5377037620200 1 DOUBLER 5 B5377037621200 1 DOUBLER 6 B5377039820400 1 KEY 7 B5377037620400 1 DOUBLER 9 B5377037620600 1 DOUBLER 11 B5377037621400 1 DOUBLER 12 B5377039820600 1 KEY 13 B5377037720000 1 LEDGE 14 B5377039820000 1 DOUBLER 16 B5377037620800 1 DOUBLER 18 B5377039820200 1 DOUBLER DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 26 6

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 20 B5377037621000 1 DOUBLER 31 DAN6-6-7X 6 PIN 32 DAN6-6-5X 58 PIN 33 DAN6-6-6X 41 PIN 34 DAN6-6-8X 77 PIN 35 DAN6-6-9X 61 PIN 36 DAN6-6-10X 84 PIN 37 DAN6-6-11X 37 PIN 38 DAN6-6-12X 50 PIN 39 DAN6-6-13X 51 PIN 40 DAN6-6-14X 30 PIN 41 DAN6-6-16X 12 PIN 42 DAN6-6-5Y 6 PIN 43 DAN6-6-6Y 3 PIN 44 DAN6-6-8Y 5 PIN 45 DAN6-6-9Y 1 PIN 46 DAN6-6-11Y 1 PIN 47 DAN6-6-12Y 27 PIN 48 DAN6-6-13Y 7 PIN 49 DAN6-6-14Y 59 PIN 50 DAN6-6-15Y 4 PIN 51 DAN6-6-16Y 12 PIN 52 DAN6-6-4 6 PIN 53 DAN6-6-5 13 PIN 54 DAN6-6-6 98 PIN 55 DAN6-6-7 63 PIN 56 DAN6-6-8 109 PIN 57 DAN6-6-9 148 PIN 58 DAN6-6-10 285 PIN 59 DAN6-6-11 165 PIN 60 DAN6-6-12 32 PIN 61 DAN6-6-14 14 PIN 62 DAN6-8-9 3 PIN 63 DAN6-8-10 4 PIN 64 DAN6-8-11 4 PIN 65 DAN6-8-12 3 PIN 66 DAN6-8-14 2 PIN 67 DAN6-8-15 5 PIN 68 DAN6-8-16 1 PIN 69 NSA5075-6 932 COLLAR 70 NSA5075-8 22 COLLAR 71 DAN11-6X 507 COLLAR 72 DAN11-6Y 125 COLLAR 73 B5377039820800 1 DOUBLER
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 27 6

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# @A300-600 SERVICE BULLETIN
References Fig. A-GBAAA Installation of doublers and reinforcement at the MID passenger/crew door frame Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 (a) Install the reinforcement between Frame 29 thru Frame 32 and stringer 12 thru stringer 15 at the LH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 29 thru Frame 32 and stringer 12 thru stringer 15. Refer to Fig. A-GBAAA, Views A and C. 1 Doubler B5377037620000 Item 1 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 1 is flush with the contour of the outer skin. 2 Transfer drill outer profile holes in the doubler, Item 1 and install temporary fasteners to hold in position. NOTE: Transfer drill at 3 positions for the doubler, Item 1 without the doubler, Item 3. 3 Put in position: 1 Doubler B5377037620200 Item 3 1 Key B5377039820400 Item 6 1 Doubler B5377037621200 Item 5 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers and key Items 1, 3, 5 and 6. 6 Wet install the doubler, Item 1 at 3 positions with: 3 Pin DAN6-6-7 Item 55 and wet install the doublers and key Items 1, 3, 5 and 6 with:
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 28 6

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# @A300-600 SERVICE BULLETIN
4 Pin DAN6-6-7X Item 31 22 Pin DAN6-6-5X Item 32 6 Pin DAN6-6-6X Item 33 9 Pin DAN6-6-8X Item 34 10 Pin DAN6-6-9X Item 35 29 Pin DAN6-6-10X Item 36 4 Pin DAN6-6-11X Item 37 37 Pin DAN6-6-12X Item 38 2 Pin DAN6-6-13X Item 39 1 Pin DAN6-6-8Y Item 44 20 Pin DAN6-6-12Y Item 47 3 Pin DAN6-6-4 Item 52 13 Pin DAN6-6-5 Item 53 36 Pin DAN6-6-6 Item 54 29 Pin DAN6-6-7 Item 55 43 Pin DAN6-6-8 Item 56 13 Pin DAN6-6-9 Item 57 136 Pin DAN6-6-10 Item 58 8 Pin DAN6-6-11 Item 59 1 Pin DAN6-6-12 Item 60 284 Collar NSA5075-6 Item 69 123 Collar DAN11-6X Item 71 21 Collar DAN11-6Y Item 72 (b) Install the reinforcement between Frame 27 thru Frame 29 and stringer 12 thru stringer 15 at the LH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 29 6

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# @A300-600 SERVICE BULLETIN
1 Put in position at the outer skin between Frame 27 thru Frame 29 and stringer 12 thru stringer 15. Refer to Fig. A-GBAAA, Views A and E. 1 Doubler B5377037620400 Item 7 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 7 is flush with the contour of the outer skin. 2 Transfer drill outer profile holes in the doubler, Item 7 and install temporary fasteners to hold in position. 3 Put in position: 1 Doubler B5377037620600 Item 9 1 Doubler B5377037621400 Item 11 1 Key B5377039820600 Item 12 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers and key Items 7, 9, 11 and 12. 6 Wet install the doublers and key Items 7, 9, 11 and 12 with: 2 Pin DAN6-6-7X Item 31 9 Pin DAN6-6-5X Item 32 19 Pin DAN6-6-6X Item 33 15 Pin DAN6-6-8X Item 34 4 Pin DAN6-6-9X Item 35 5 Pin DAN6-6-10X Item 36 2 Pin DAN6-6-11X Item 37 23 Pin DAN6-6-13X Item 39 19 Pin DAN6-6-14X Item 40 2 Pin DAN6-6-6Y Item 43 4 Pin DAN6-6-13Y Item 48 36 Pin DAN6-6-14Y Item 49 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 30 6

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# @A300-600 SERVICE BULLETIN
3 Pin DAN6-6-4 Item 52 18 Pin DAN6-6-6 Item 54 17 Pin DAN6-6-7 Item 55 39 Pin DAN6-6-9 Item 57 37 Pin DAN6-6-10 Item 58 55 Pin DAN6-6-11 Item 59 24 Pin DAN6-6-12 Item 60 4 Pin DAN6-6-14 Item 61 197 Collar NSA5075-6 Item 69 98 Collar DAN11-6X Item 71 42 Collar DAN11-6Y Item 72 (c) Install the reinforcement between Frame 28 thru Frame 30 at stringer 13 at the LH Mid Passenger/Crew Door Frame. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 28 thru Frame 30 at stringer 13. Refer to Fig. A-GBAAA, Views A and K. 1 Doubler B5377039820800 Item 73 and attach it temporarily. 2 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. NOTE: Drill and ream clearance hole in the doubler, Item 73. 3 Remove and clean the doubler, Item 73. 4 Wet install the doubler, Item 73 with: 29 Pin DAN6-6-9X Item 35 47 Pin DAN6-6-10X Item 36 8 Pin DAN6-6-11X Item 37 84 Collar DAN11-6X Item 71
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 31 6

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# @A300-600 SERVICE BULLETIN (d) Install the rain deflector, Item (90) and Filler, Item 13 between Frame 28 thru Frame 30 and stringer 12 at the LH Mid Passenger/Crew Door. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 28 thru Frame 30 at stringer 12. Refer to Fig. A-GBAAA, Views A, C, E and K. 1 Filler B5377037720000 Item 13 and attach it temporarily. 2 Transfer drill for fasteners and deburr the fastener holes. 3 Remove and clean the filler, Item 13. 4 Trim the deflector, Item 90, refer to Fig. A-GBAAA, Views C and E. 1 Deflector-Rainwater A5377517320600 Item (90) Retained at removal and deburr. 5 Wet install filler, Item 13 and deflector, Item 90 with: 12 Screw NAS1102E3-14 Item (91) Retained at removal 12 Nut MS21043-3 Item (92) Retained at removal 5 Spacer A5377517420200 Item (93) Retained at removal 7 Spacer A5377517420300 Item (94) Retained at removal (e) Install the reinforcement between Frame 29 thru Frame 32 and stringer 24 thru stringer 28 at the LH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 29 thru Frame 32 and stringer 24 thru stringer 32. Refer to Fig. A-GBAAA, Views A and G. 1 Doubler B5377039820000 Item 14 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 14 is flush with DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 32 6

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# @A300-600 SERVICE BULLETIN
the contour of the outer skin. 2 Transfer drill outer profile holes in the doubler, Item 14 and install temporary fasteners to hold in position. 3 Put in position: 1 Doubler B5377037620800 Item 16 and attach it temporarily. 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers, Items 14 and 16. 6 Wet install the doublers, Items 14 and 16 with: 14 Pin DAN6-6-5X Item 32 16 Pin DAN6-6-6X Item 33 23 Pin DAN6-6-8X Item 34 7 Pin DAN6-6-9X Item 35 5 Pin DAN6-6-11X Item 37 19 Pin DAN6-6-13X Item 39 8 Pin DAN6-6-14X Item 40 4 Pin DAN6-6-16X Item 41 3 Pin DAN6-6-5Y Item 42 1 Pin DAN6-6-6Y Item 43 2 Pin DAN6-6-8Y Item 44 1 Pin DAN6-6-9Y Item 45 21 Pin DAN6-6-14Y Item 49 4 Pin DAN6-6-15Y Item 50 8 Pin DAN6-6-16Y Item 51 27 Pin DAN6-6-6 Item 54 5 Pin DAN6-6-7 Item 55 41 Pin DAN6-6-8 Item 56 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 33 6

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# @A300-600 SERVICE BULLETIN
54 Pin DAN6-6-9 Item 57 48 Pin DAN6-6-10 Item 58 85 Pin DAN6-6-11 Item 59 5 Pin DAN6-6-12 Item 60 4 Pin DAN6-6-14 Item 61 3 Pin DAN6-8-10 Item 63 1 Pin DAN6-8-11 Item 64 3 Pin DAN6-8-12 Item 65 4 Pin DAN6-8-15 Item 67 1 Pin DAN6-8-16 Item 68 269 Collar NSA5075-6 Item 69 12 Collar NSA5075-8 Item 70 96 Collar DAN11-6X Item 71 40 Collar DAN11-6Y Item 72 (f) Install the reinforcement between Frame 27 thru Frame 29 and stringer 24 thru stringer 28 at the LH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 27 thru Frame 29 and stringer 24 thru stringer 32. Refer to Fig. A-GBAAA, Views A and J. 1 Doubler B5377039820200 Item 18 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 18 is flush with the contour of the outer skin. 2 Transfer drill outer profile holes in the doubler, Item 18 and install temporary fasteners to hold in position. 3 Put in position: 1 Doubler B5377037621000 Item 20
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 34 6

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# @A300-600 SERVICE BULLETIN and attach it temporarily. 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers, Items 18 and 20. 6 Wet install the doublers, Items 18 and 20 with: 13 Pin DAN6-6-5X Item 32 30 Pin DAN6-6-8X Item 34 11 Pin DAN6-6-9X Item 35 3 Pin DAN6-6-10X Item 36 18 Pin DAN6-6-11X Item 37 13 Pin DAN6-6-12X Item 38 7 Pin DAN6-6-13X Item 39 3 Pin DAN6-6-14X Item 40 8 Pin DAN6-6-16X Item 41 3 Pin DAN6-6-5Y Item 42 2 Pin DAN6-6-8Y Item 44 1 Pin DAN6-6-11Y Item 46 7 Pin DAN6-6-12Y Item 47 3 Pin DAN6-6-13Y Item 48 2 Pin DAN6-6-14Y Item 49 4 Pin DAN6-6-16Y Item 51 17 Pin DAN6-6-6 Item 54 9 Pin DAN6-6-7 Item 55 25 Pin DAN6-6-8 Item 56 42 Pin DAN6-6-9 Item 57 64 Pin DAN6-6-10 Item 58 17 Pin DAN6-6-11 Item 59 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 35 6

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# @A300-600 SERVICE BULLETIN
2 Pin DAN6-6-12 Item 60 6 Pin DAN6-6-14 Item 61 3 Pin DAN6-8-9 Item 62 1 Pin DAN6-8-10 Item 63 3 Pin DAN6-8-11 Item 64 2 Pin DAN6-8-14 Item 66 1 Pin DAN6-8-15 Item 67 182 Collar NSA5075-6 Item 69 10 Collar NSA5075-8 Item 70 106 Collar DAN11-6X Item 71 22 Collar DAN11-6Y Item 72

(6) Subtask 536170-831-208-001 - Install the reinforcement at the RH MID Passenger/Crew Door Frame Work Zones and Access Panels Zone Access/Work location From 132 Work location from Frame 28 to Frame 31 To 232 Work location from Frame 28 to Frame 31 Manpower Resources Manhours 180.0 Minimum number of person 2 Subtask elapsed time 90.0 Skills AIRFRAME Material necessary to do the job Kit 536170D01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 B5377037620100 1 DOUBLER 4 B5377037620300 1 DOUBLER 5 B5377037621200 1 DOUBLER 6 B5377039820400 1 KEY 8 B5377037620500 1 DOUBLER 10 B5377037620700 1 DOUBLER 11 B5377037621400 1 DOUBLER 12 B5377039820600 1 KEY DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 36 6

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 13 B5377037720000 1 LEDGE 15 B5377039820100 1 DOUBLER 17 B5377037620900 1 DOUBLER 19 B5377039820300 1 DOUBLER 21 B5377037621100 1 DOUBLER 31 DAN6-6-7X 6 PIN 32 DAN6-6-5X 58 PIN 33 DAN6-6-6X 41 PIN 34 DAN6-6-8X 77 PIN 35 DAN6-6-9X 61 PIN 36 DAN6-6-10X 84 PIN 37 DAN6-6-11X 37 PIN 38 DAN6-6-12X 50 PIN 39 DAN6-6-13X 51 PIN 40 DAN6-6-14X 30 PIN 41 DAN6-6-16X 12 PIN 42 DAN6-6-5Y 6 PIN 43 DAN6-6-6Y 3 PIN 44 DAN6-6-8Y 5 PIN 45 DAN6-6-9Y 1 PIN 46 DAN6-6-11Y 1 PIN 47 DAN6-6-12Y 27 PIN 48 DAN6-6-13Y 7 PIN 49 DAN6-6-14Y 59 PIN 50 DAN6-6-15Y 4 PIN 51 DAN6-6-16Y 12 PIN 52 DAN6-6-4 6 PIN 53 DAN6-6-5 13 PIN 54 DAN6-6-6 98 PIN 55 DAN6-6-7 63 PIN 56 DAN6-6-8 109 PIN 57 DAN6-6-9 148 PIN 58 DAN6-6-10 285 PIN 59 DAN6-6-11 165 PIN 60 DAN6-6-12 32 PIN 61 DAN6-6-14 12 PIN 62 DAN6-8-9 3 PIN 63 DAN6-8-10 4 PIN 64 DAN6-8-11 4 PIN 65 DAN6-8-12 3 PIN 66 DAN6-8-14 2 PIN 67 DAN6-8-15 5 PIN 68 DAN6-8-16 1 PIN 69 NSA5075-6 932 COLLAR 70 NSA5075-8 22 COLLAR 71 DAN11-6X 507 COLLAR DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 37 6

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 72 DAN11-6Y 125 COLLAR 73 B5377039820800 1 DOUBLER References Fig. A-GBAAA Installation of doublers and reinforcement at the MID passenger/crew door frame Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 (a) Install the reinforcement between Frame 29 thru Frame 32 and stringer 12 thru stringer 15 at the RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 29 thru Frame 32 and stringer 12 thru stringer 15. Refer to Fig. A-GBAAA, Views A and C. 1 Doubler B5377037620100 Item 2 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 2 is flush with the contour of the outer skin. 2 Transfer drill some outer profile holes in Item 2 and install temporary fasteners to hold in position. NOTE: Transfer drill at 3 positions for Item 2 without Item 4. 3 Put in position: 1 Doubler B5377037620300 Item 4 1 Key B5377039820400 Item 6 1 Doubler B5377037621200 Item 5 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers and key Items 2, 4, 5 and 6.

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 38 6

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# @A300-600 SERVICE BULLETIN
6 Wet install the doubler, Item 2 at 3 positions with: 3 Pin DAN6-6-7 Item 55 and wet install the doublers and key Items 2, 4, 5 and 6 with 4 Pin DAN6-6-7X Item 31 22 Pin DAN6-6-5X Item 32 6 Pin DAN6-6-6X Item 33 9 Pin DAN6-6-8X Item 34 10 Pin DAN6-6-9X Item 35 29 Pin DAN6-6-10X Item 36 4 Pin DAN6-6-11X Item 37 37 Pin DAN6-6-12X Item 38 2 Pin DAN6-6-13X Item 39 1 Pin DAN6-6-8Y Item 44 20 Pin DAN6-6-12Y Item 47 3 Pin DAN6-6-4 Item 52 13 Pin DAN6-6-5 Item 53 36 Pin DAN6-6-6 Item 54 29 Pin DAN6-6-7 Item 55 43 Pin DAN6-6-8 Item 56 13 Pin DAN6-6-9 Item 57 136 Pin DAN6-6-10 Item 58 8 Pin DAN6-6-11 Item 59 1 Pin DAN6-6-12 Item 60 284 Collar NSA5075-6 Item 69 123 Collar DAN11-6X Item 71 21 Collar DAN11-6Y Item 72 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 39 6

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# @A300-600 SERVICE BULLETIN (b) Install the reinforcement between Frame 27 thru Frame 29 and stringer 12 thru stringer 15 at the RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 27 thru Frame 29 and stringer 12 thru stringer 15. Refer to Fig. A-GBAAA, Views A and E. 1 Doubler B5377037620500 Item 8 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 8 is flush with the contour of the outer skin. 2 Transfer drill some outer profile holes in Item 8 and install temporary fasteners to hold in position. 3 Put in position: 1 Doubler B5377037620700 Item 10 1 Doubler B5377037621400 Item 11 1 Key B5377039820600 Item 12 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers and key Items 8, 10, 11 and 12. 6 Wet install the doublers and key Items 8, 10, 11 and 12 with: 2 Pin DAN6-6-7X Item 31 9 Pin DAN6-6-5X Item 32 19 Pin DAN6-6-6X Item 33 15 Pin DAN6-6-8X Item 34 4 Pin DAN6-6-9X Item 35 5 Pin DAN6-6-10X Item 36 2 Pin DAN6-6-11X Item 37 23 Pin DAN6-6-13X Item 39 19 Pin DAN6-6-14X Item 40 2 Pin DAN6-6-6Y Item 43 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 40 6

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# @A300-600 SERVICE BULLETIN
4 Pin DAN6-6-13Y Item 48 36 Pin DAN6-6-14Y Item 49 3 Pin DAN6-6-4 Item 52 18 Pin DAN6-6-6 Item 54 17 Pin DAN6-6-7 Item 55 39 Pin DAN6-6-9 Item 57 37 Pin DAN6-6-10 Item 58 55 Pin DAN6-6-11 Item 59 24 Pin DAN6-6-12 Item 60 2 Pin DAN6-6-14 Item 61 197 Collar NSA5075-6 Item 69 98 Collar DAN11-6X Item 71 42 Collar DAN11-6Y Item 72 (c) Install the reinforcement between Frame 28 thru Frame 30 at stringer 13 at the RH Mid Passenger/Crew Door Frame. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 28 thru Frame 30 at stringer 13. Refer to Fig. A-GBAAA, Views A, C, E and K. 1 Doubler B5377039820800 Item 73 and attach it temporarily. 2 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. NOTE: Drill and ream clearance holes in the doubler, Item 73. 3 Remove and clean the doubler, Item 73. 4 Wet install the doubler, Item 73 with: 29 Pin DAN6-6-9X Item 35 47 Pin DAN6-6-10X Item 36
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 41 6

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# @A300-600 SERVICE BULLETIN
8 Pin DAN6-6-11X Item 37 84 Collar DAN11-6X Item 71 (d) Install the rain deflector, Item (91) and Filler, Item 13 between Frame 28 thru Frame 30 and stringer 12 at the RH Mid Passenger/Crew Door. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 28 thru Frame 30 at stringer 12. Refer to Fig. A-GBAAA, Views A, C, E and K. 1 Filler B5377037720000 Item 13 and attach it temporarily. 2 Transfer drill for fasteners and deburr the fastener holes. 3 Remove and clean the filler, Items 13. 4 Trim the deflector, Item 90, refer to Fig. A-GBAAA, Views C and E. 1 Deflector-Rainwater A5377517320700 Item (95) Retained at removal and deburr. 5 Wet install filler, Item 13 and deflector, Item 95 with: 12 Screw NAS1102E3-14 Item (91) Retained at removal 12 Nut MS21043-3 Item (92) Retained at removal 5 Spacer A5377517420200 Item (93) Retained at removal 7 Spacer A5377517420300 Item (94) Retained at removal (e) Install the reinforcement between Frame 29 thru Frame 32 and stringer 24 thru stringer 28 at the RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 29 thru Frame 32 and stringer 24 thru stringer 32. Refer to Fig. A-GBAAA, Views A and G.
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 42 6

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# @A300-600 SERVICE BULLETIN
1 Doubler B5377039820100 Item 15 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 15 is flush with the contour of the outer skin. 2 Transfer drill outer profile holes in the doubler, Item 15 and install temporary fasteners to hold in position. 3 Put in position: 1 Doubler B5377037620900 Item 17 and attach it temporarily. 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers, Items 15 and 17. 6 Wet install the doublers Items 15 and 17 with: 14 Pin DAN6-6-5X Item 32 16 Pin DAN6-6-6X Item 33 23 Pin DAN6-6-8X Item 34 7 Pin DAN6-6-9X Item 35 5 Pin DAN6-6-11X Item 37 19 Pin DAN6-6-13X Item 39 8 Pin DAN6-6-14X Item 40 4 Pin DAN6-6-16X Item 41 3 Pin DAN6-6-5Y Item 42 1 Pin DAN6-6-6Y Item 43 2 Pin DAN6-6-8Y Item 44 1 Pin DAN6-6-9Y Item 45 21 Pin DAN6-6-14Y Item 49 4 Pin DAN6-6-15Y Item 50 8 Pin DAN6-6-16Y Item 51
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 43 6

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# @A300-600 SERVICE BULLETIN
27 Pin DAN6-6-6 Item 54 5 Pin DAN6-6-7 Item 55 41 Pin DAN6-6-8 Item 56 54 Pin DAN6-6-9 Item 57 48 Pin DAN6-6-10 Item 58 85 Pin DAN6-6-11 Item 59 5 Pin DAN6-6-12 Item 60 4 Pin DAN6-6-14 Item 61 3 Pin DAN6-8-10 Item 63 1 Pin DAN6-8-11 Item 64 3 Pin DAN6-8-12 Item 65 4 Pin DAN6-8-15 Item 67 1 Pin DAN6-8-16 Item 68 269 Collar NSA5075-6 Item 69 12 Collar NSA5075-8 Item 70 96 Collar DAN11-6X Item 71 40 Collar DAN11-6Y Item 72 (f) Install the reinforcement between Frame 27 thru Frame 29 and stringer 24 thru stringer 28 at the RH Mid Passenger/Crew Door Frame Corner. Refer to Fig. A-GBAAA 1 Put in position at the outer skin between Frame 27 thru Frame 29 and stringer 24 thru stringer 32. Refer to Fig. A-GBAAA, Views A and J. 1 Doubler B5377039820300 Item 19 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 19 is flush with the contour of the outer skin.
DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 44 6

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# @A300-600 SERVICE BULLETIN
2 Transfer drill outer profile holes in the doubler, Item 19 and install temporary fasteners to hold in position. 3 Put in position: 1 Doubler B5377037621100 Item 21 and attach it temporarily. 4 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 5 Remove and clean the doublers, Items 19 and 21. 6 Wet install the doublers, Items 19 and 21 with: 13 Pin DAN6-6-5X Item 32 30 Pin DAN6-6-8X Item 34 11 Pin DAN6-6-9X Item 35 3 Pin DAN6-6-10X Item 36 18 Pin DAN6-6-11X Item 37 13 Pin DAN6-6-12X Item 38 7 Pin DAN6-6-13X Item 39 3 Pin DAN6-6-14X Item 40 8 Pin DAN6-6-16X Item 41 3 Pin DAN6-6-5Y Item 42 2 Pin DAN6-6-8Y Item 44 1 Pin DAN6-6-11Y Item 46 7 Pin DAN6-6-12Y Item 47 3 Pin DAN6-6-13Y Item 48 2 Pin DAN6-6-14Y Item 49 4 Pin DAN6-6-16Y Item 51 17 Pin DAN6-6-6 Item 54 9 Pin DAN6-6-7 Item 55 25 Pin DAN6-6-8 Item 56 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 45 6

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# @A300-600 SERVICE BULLETIN
42 Pin DAN6-6-9 Item 57 64 Pin DAN6-6-10 Item 58 17 Pin DAN6-6-11 Item 59 2 Pin DAN6-6-12 Item 60 6 Pin DAN6-6-14 Item 61 3 Pin DAN6-8-9 Item 62 1 Pin DAN6-8-10 Item 63 3 Pin DAN6-8-11 Item 64 2 Pin DAN6-8-14 Item 66 1 Pin DAN6-8-15 Item 67 182 Collar NSA5075-6 Item 69 10 Collar NSA5075-8 Item 70 106 Collar DAN11-6X Item 71 22 Collar DAN11-6Y Item 72

(7) Subtask 536170-831-203-001 - Install the reinforcement at the LH AFT Passenger/Crew Door Frame Work Zones and Access Panels Zone Access/Work location From 171 Work location from Frame 73 to Frame 76 To 261 Work location from Frame 73 to Frame 76 Manpower Resources Manhours 160.0 Minimum number of person 2 Subtask elapsed time 80.00 Skills AIRFRAME Material necessary to do the job Kit 536170D02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 22 A5398104020000 1 DOUBLER 24 A5398104020200 1 DOUBLER 26 A5398104020400 1 DOUBLER DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 46 6

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 28 A5398104020600 1 DOUBLER 30 A5398104020800 1 DOUBLER 31 DAN6-6-7X 25 PIN 33 DAN6-6-6X 4 PIN 34 DAN6-6-8X 188 PIN 35 DAN6-6-9X 361 PIN 36 DAN6-6-10X 8 PIN 37 DAN6-6-11X 79 PIN 38 DAN6-6-12X 125 PIN 39 DAN6-6-13X 57 PIN 53 DAN6-6-5 24 PIN 55 DAN6-6-7 156 PIN 58 DAN6-6-10 12 PIN 69 NSA5075-6 192 COLLAR 71 DAN11-6X 839 COLLAR References Fig. A-GBBAA Installation of doublers and reinforcement at the AFT passenger/crew door frame Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 (a) Install the reinforcement between Frame 73 thru Frame 74 and stringer 24 thru stringer 27 at the LH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 73 thru Frame 74 and stringer 24 thru stringer 27. Refer to Fig. A-GBBAA, Views A and C. 1 Doubler A5398104020000 Item 22 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 22 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 4 Remove and clean the doubler, Item 22. DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 47 6

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# @A300-600 SERVICE BULLETIN
5 Wet install the doubler, Item 22 with: 4 Pin DAN6-6-6X Item 33 51 Pin DAN6-6-8X Item 34 82 Pin DAN6-6-9X Item 35 27 Pin DAN6-6-11X Item 37 26 Pin DAN6-6-12X Item 38 28 Pin DAN6-6-13X Item 39 24 Pin DAN6-6-5 Item 53 32 Pin DAN6-6-7 Item 55 6 Pin DAN6-6-10 Item 58 62 Collar NSA5075-6 Item 69 214 Collar DAN11-6X Item 71 (b) Install the reinforcement between Frame 75 thru Frame 76 and stringer 23 thru stringer 27 at the LH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 75 thru Frame 76 and stringer 23 thru stringer 27. Refer to Fig. A-GBBAA, Views A and E. 1 Doubler A5398104020200 Item 24 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 24 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 4 Remove and clean the doubler, Item 24. 5 Wet install the doubler, Item 24 with: 4 Pin DAN6-6-7X Item 31 52 Pin DAN6-6-8X Item 34 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 48 6

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# @A300-600 SERVICE BULLETIN
63 Pin DAN6-6-9X Item 35 8 Pin DAN6-6-10X Item 36 18 Pin DAN6-6-11X Item 37 25 Pin DAN6-6-12X Item 38 21 Pin DAN6-6-13X Item 39 43 Pin DAN6-6-7 Item 55 43 Collar NSA5075-6 Item 69 187 Collar DAN11-6X Item 71 (c) Install the reinforcement between Frame 73 thru Frame 74 and stringer 10 thru stringer 13 at the LH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 73 thru Frame 74 and stringer 10 thru stringer 13. Refer to Fig. A-GBBAA, Views A and G. 1 Doubler A5398104020400 Item 26 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 26 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 4 Remove and clean the doubler, Item 26. 5 Wet install the doubler, Item 26 with: 8 Pin DAN6-6-7X Item 31 36 Pin DAN6-6-8X Item 34 90 Pin DAN6-6-9X Item 35 15 Pin DAN6-6-11X Item 37 36 Pin DAN6-6-12X Item 38 4 Pin DAN6-6-13X Item 39 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 49 6

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# @A300-600 SERVICE BULLETIN
40 Pin DAN6-6-7 Item 55 40 Collar NSA5075-6 Item 69 189 Collar DAN11-6X Item 71 (d) Install the reinforcement between Frame 75 thru Frame 76 and stringer 10 thru stringer 13 at the LH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 75 thru Frame 76 and stringer 10 thru stringer 13. Refer to Fig. A-GBBAA, Views A and J. 1 Doubler A5398104020600 Item 28 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 28 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 4 Remove and clean the doubler, Item 28. 5 Wet install the doubler, Item 28 with: 6 Pin DAN6-6-7X Item 31 45 Pin DAN6-6-8X Item 34 106 Pin DAN6-6-9X Item 35 19 Pin DAN6-6-11X Item 37 36 Pin DAN6-6-12X Item 38 4 Pin DAN6-6-13X Item 39 41 Pin DAN6-6-7 Item 55 6 Pin DAN6-6-10 Item 58 47 Collar NSA5075-6 Item 69 216 Collar DAN11-6X Item 71

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 50 6

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# @A300-600 SERVICE BULLETIN (e) Install the doubler, Item 30 between Frame 73 thru Frame 75 at stringer 11 at the LH AFT Passenger/Crew Door Frame. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 73 thru Frame 75 and stringer 11. Refer to Fig. A-GBBAA, Views G and J. 1 Doubler A5398104020800 Item 30 and attach it temporarily. 2 Transfer drill for HI-Lok transition fit fasteners every third fastener position and deburr the fastener holes. 3 Remove and clean the doubler, Item 30. 4 Wet install the doubler, Item 30 with: 7 Pin DAN6-6-7X Item 31 4 Pin DAN6-6-8X Item 34 20 Pin DAN6-6-9X Item 35 2 Pin DAN6-6-12X Item 38 33 Collar DAN11-6X Item 71

(8) Subtask 536170-831-204-001 - Install the reinforcement at the RH AFT Passenger/Crew Door Frame Work Zones and Access Panels Zone Access/Work location From 172 Work location from Frame 73 to Frame 76 To 262 Work location from Frame 73 to Frame 76 Manpower Resources Manhours 160.0 Minimum number of person 2 Subtask elapsed time 80.00 Skills AIRFRAME Material necessary to do the job Kit 536170D02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 23 A5398104020100 1 DOUBLER DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 51 6

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# @A300-600 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 25 A5398104020300 1 DOUBLER 27 A5398104020500 1 DOUBLER 29 A5398104020700 1 DOUBLER 30 A5398104020800 1 DOUBLER 31 DAN6-6-7X 25 PIN 33 DAN6-6-6X 4 PIN 34 DAN6-6-8X 188 PIN 35 DAN6-6-9X 361 PIN 36 DAN6-6-10X 8 PIN 37 DAN6-6-11X 79 PIN 38 DAN6-6-12X 125 PIN 39 DAN6-6-13X 57 PIN 53 DAN6-6-5 24 PIN 55 DAN6-6-7 156 PIN 58 DAN6-6-10 12 PIN 69 NSA5075-6 192 COLLAR 71 DAN11-6X 839 COLLAR References Fig. A-GBBAA Installation of doublers and reinforcement at the AFT passenger/crew door frame Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 (a) Install the reinforcement between Frame 73 thru Frame 74 and stringer 24 thru stringer 27 at the RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 73 thru Frame 74 and stringer 24 thru stringer 27. Refer to Fig. A-GBBAA, Views A and C. 1 Doubler A5398104020100 Item 23 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 23 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 52 6

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# @A300-600 SERVICE BULLETIN
4 Remove and clean the doubler, Items 23. 5 Wet install the doubler, Items 23 with: 4 Pin DAN6-6-6X Item 33 51 Pin DAN6-6-8X Item 34 82 Pin DAN6-6-9X Item 35 27 Pin DAN6-6-11X Item 37 26 Pin DAN6-6-12X Item 38 28 Pin DAN6-6-13X Item 39 24 Pin DAN6-6-5 Item 53 32 Pin DAN6-6-7 Item 55 6 Pin DAN6-6-10 Item 58 62 Collar NSA5075-6 Item 69 214 Collar DAN11-6X Item 71 (b) Install the reinforcement between Frame 75 thru Frame 76 and stringer 23 thru stringer 27 at the RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 75 thru Frame 76 and stringer 23 thru stringer 27. Refer to Fig. A-GBBAA, Views A and E. 1 Doubler A5398104020300 Item 25 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 25 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 4 Remove and clean the doubler, Item 25. 5 Wet install the doubler, Item 25 with: 4 Pin DAN6-6-7X Item 31 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 53 6

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# @A300-600 SERVICE BULLETIN
52 Pin DAN6-6-8X Item 34 63 Pin DAN6-6-9X Item 35 8 Pin DAN6-6-10X Item 36 18 Pin DAN6-6-11X Item 37 25 Pin DAN6-6-12X Item 38 21 Pin DAN6-6-13X Item 39 43 Pin DAN6-6-7 Item 55 43 Collar NSA5075-6 Item 69 187 Collar DAN11-6X Item 71 (c) Install the reinforcement between Frame 73 thru Frame 74 and stringer 10 thru stringer 13 at the RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 73 thru Frame 74 and stringer 10 thru stringer 13. Refer to Fig. A-GBBAA, Views A and G. 1 Doubler A5398104020500 Item 27 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 27 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 4 Remove and clean the doubler, Item 27. 5 Wet install the doubler, Item 27 with: 8 Pin DAN6-6-7X Item 31 36 Pin DAN6-6-8X Item 34 90 Pin DAN6-6-9X Item 35 15 Pin DAN6-6-11X Item 37 36 Pin DAN6-6-12X Item 38 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 54 6

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# @A300-600 SERVICE BULLETIN
4 Pin DAN6-6-13X Item 39 40 Pin DAN6-6-7 Item 55 40 Collar NSA5075-6 Item 69 189 Collar DAN11-6X Item 71 (d) Install the reinforcement between Frame 75 thru Frame 76 and stringer 10 thru stringer 13 at the RH AFT Passenger/Crew Door Frame Corner. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 75 thru Frame 76 and stringer 10 thru stringer 13. Refer to Fig. A-GBBAA, Views A and J. 1 Doubler A5398104020700 Item 29 and attach it temporarily. NOTE: Make sure that the radius of the doubler, Item 29 is flush with the contour of the outer skin. 2 Mark positions of new fastener holes. 3 Transfer drill for HI-Lok transition fit fasteners and deburr the fastener holes. 4 Remove and clean the doubler, Item 29. 5 Wet install the doubler, Item 29 with: 6 Pin DAN6-6-7X Item 31 45 Pin DAN6-6-8X Item 34 106 Pin DAN6-6-9X Item 35 19 Pin DAN6-6-11X Item 37 36 Pin DAN6-6-12X Item 38 4 Pin DAN6-6-13X Item 39 41 Pin DAN6-6-7 Item 55 6 Pin DAN6-6-10 Item 58 47 Collar NSA5075-6 Item 69 216 Collar DAN11-6X Item 71 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 55 6

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

# @A300-600 SERVICE BULLETIN (e) Install the doubler, Item 30 between Frame 73 thru Frame 75 at stringer 11 at the LH AFT Passenger/Crew Door Frame. Refer to Fig. A-GBBAA 1 Put in position at the outer skin between Frame 73 thru Frame 75 and stringer 11. Refer to Fig. A-GBBAA, Views G and J. 1 Doubler A5398104020800 Item 30 and attach it temporarily. 2 Transfer drill for HI-Lok transition fit fasteners every third fastener position and deburr the fastener holes. 3 Remove and clean the doubler, Item 30. 4 Wet install the doubler, Item 30 with: 7 Pin DAN6-6-7X Item 31 4 Pin DAN6-6-8X Item 34 20 Pin DAN6-6-9X Item 35 2 Pin DAN6-6-12X Item 38 33 Collar DAN11-6X Item 71 D. TEST None E. CLOSE-UP (1) Subtask 536170-410-201-001 - Install/Close Items Removed/Opened for access Work Zones and Access Panels Zone Access/Work location From 231 Access Panel 231LW, Panel 231MW, Panel 231NW, Panel 231PW, Panel 231QW, Panel 231RW, Panel 231SW, Panel 231TW, Panel 231UW, Panel 231VW, Panel 231XW, Panel 231YW, Panel 231WW To 232 Access Panel 232LW, Panel 232MW, Panel 232NW, Panel 232PW, Panel 232QW, Panel 232RW, Panel 232SW, Panel 232TW, Panel 232UW, Panel 232VW, Panel 232XW, Panel 232YW, Panel 232WW

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 56 6

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# @A300-600 SERVICE BULLETIN
From 261 Access Panel 261AW, Panel 261BW, Panel 261CW, Panel 261DW, Panel 261EW, Panel 261FW, Panel 261GW, Panel 261NW, Panel 261PW, Panel 261RW, Panel 261QW, Panel 261AZ To 262 Access Panel 262AW, Panel 262BW, Panel 262CW, Panel 262DW, Panel 262EW, Panel 262FW, Panel 262GW, Panel 262NW, Panel 262PW, Panel 262RW, Panel 262QW, Panel 262AZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 25-23-41, Page Block 401 25-28-12, Page Block 401 53-10-25, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the retained floor panels at the FWD passenger/crew LH/RH position 231TF, 231SF, 232TF and 232SF (Refer to AMM 53-10-25, Page Block 401). (c) Install the retained floor panels at the AFT passenger/crew LH/RH position 261QF, 261PF, 262QF and 262PF (Refer to AMM 53-10-25, Page Block 401). (d) Install the retained floor covering at the floor panels 231TF, 231SF, 232TF, 232SF, 261QF, 261PF, 262QF and 262PF (Refer to AMM 25-28-12, Page Block 401). (e) Install the retained mid passenger/crew side wall panels LH 231LW, 231MW, 231NW, 231PW, 231QW, 231RW, 231SW, 231TW, 231UW, 231VW, 231XW, 231YW and 231WW (Refer to AMM 25-23-41, Page Block 401). (f) Install the retained mid passenger/crew side wall panels RH 232LW, 232MW, 232NW, 232PW, 232QW, 232RW, 232SW, 232TW, 232UW, 232VW, 232XW, 232YW and 232WW (Refer to AMM 25-23-41, Page Block 401). (g) Install the retained AFT passenger/crew side wall panels LH 261AW, 261BW, 261CW, 261DW, 261EW, 261FG, 261GW, 261NW, 261PW, 261RW, 261QW and 261AZ (Refer to AMM 25-23-41, Page Block 401). (h) Install the retained AFT passenger/crew side wall panels RH 262AW, 262BW, 262CW, 262DW, 262EW, 262FG, 262GW, 262NW, 262PW, 262RW, 262QW and 262AZ (Refer to AMM 25-23-41, Page Block 401). (2) Subtask 536170-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location From 833 To 843 From 832 DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 57 6

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# @A300-600 SERVICE BULLETIN
To 842 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 52-10-00, Page Block 201 (a) Close the AFT passenger/crew doors 833 and 843 (Refer to AMM Task 52-10-00, Page Block 201). (b) Close the MID passenger/crew doors 832 and 842 (Refer to AMM Task 52-10-00, Page Block 201). (c) Remove the access platform(s).

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 58 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR12 FR30 FR30A FR31 

## BEFORE

STGR13

STGR14

STGR15

**FWD** FR27 FR28A FR29 FR28 FR32 FR31 STGR9 STGR10 STGR11 STGR12 STGR13 STGR14 STGR15 STGR16 STGR17 STGR18 STGR19 STGR20 STGR21 STGR22 STGR23 STGR24 STGR25 STGR26 STGR27 STGR28 STGR29 FR30 FR30A

LH SHOWN RH SYMMETRICAL **FWD** 

### B **C D**  **E**

**F G**  **H J**  **K**

D_SB_536170_6_BAAA_01_00 Z131 (Z132) Z231 (Z232)


### A



## A **A**

REMARKS
REMOVE FASTENERS HOLE SYMBOL



## B

Figure A-GBAAA - Sheet 01 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 59 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR12

STGR13

STGR14

STGR15 FR30 FR30A FR31 

## AFTER

**FWD** FR31 EXTERNAL LOFT LINE

LH RH LH RH 3 4 1 2 5 6 LH RH

LH RH 

### A **A** 10 mm (0.394 in)

2 mm (0.078 in) 135.0 = 5 x 27 mm (5.315 = 5 x 1.063 in) 22 mm (0.866 in) CUT RAIN DEFLECTOR 12 mm (0.472 in) ITEMS 3 AND 4

60 = 3 x 20 mm (2.362 = 3 x 0.787 in) RIVETING WITHOUT
10 mm (0.394 in)



## A **A C** 

**NOTE:** FOR FASTENER SYMBOLS, REFER TO SHEET 10. D_SB_536170_6_BAAA_02_00 6

5 1 2

3 4

Figure A-GBAAA - Sheet 02 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 60 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR12

STGR13

STGR14

STGR15 FR28 FR28A 

## BEFORE

**FWD**
D_SB_536170_6_BAAA_03_00 REMARKS
REMOVE FASTENERS HOLE SYMBOL

NOT AFFECTED FASTENERS 

## D

Figure A-GBAAA - Sheet 03 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 61 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_536170_6_BAAA_04_00 FR28

LH RH LH RH 7 8 9 10 11 12 STGR12

STGR13

STGR14

STGR15 FR28A FR28

11 LH RH

LH RH

**FWD** 

## AFTER

12

2 mm (0.078 in) CUT RAIN DEFLECTOR 60 mm (2.362 in)

10 mm (0.394 in) 81.0 = 3 x 27mm (3.189 = 3 x 1.063 in) 125.0 = 5 x 25 mm (4.921 = 5 x 0.984 in) 27 mm (1.063 in)



## B **B B**  **B**

**NOTE:** FOR FASTENER SYMBOLS, REFER TO SHEET 10. 

## E 7 8

9 10

Figure A-GBAAA - Sheet 04 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 62 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

FR30 FR30A FR31

D_SB_536170_6_BAAA_05_00 STGR26

STGR27 STGR25 

## BEFORE

**FWD** (110)
(111) (112) (123) (121)

(122)

(120)

(119)
(117)

(118) (117) (116) (114) (115) (113) REMARKS
REMOVE FASTENERS HOLE SYMBOL



## F

Figure A-GBAAA - Sheet 05 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 63 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

FR30 FR31 FR30A

STGR25

STGR26

STGR27

**NOTE:** FOR FASTENER SYMBOLS, REFER TO SHEET 10. **FWD** 

## AFTER

LH RH

LH RH 16 17

14 15 SCUFF PLATE CONTOUR OF

D_SB_536170_6_BAAA_06_00 SCUFF PLATE CUT LINE OF

SCUFF PLATE CUT LINE OF 3 mm (0.118 in) 3 mm (0.118 in)



## C **C D**  **D** 1 mm (0.039 in)



### C **C D**  **D**



## G

Figure A-GBAAA - Sheet 06 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 64 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR26

STGR27 STGR25 FR28 FR28A 

## BEFORE

**FWD** (129) (130)

(124) (125) (117) (118) (126) (132) (127) (123) (133) (131) (128) REMARKS
REMOVE FASTENERS HOLE SYMBOL



## H

D_SB_536170_6_BAAA_07_01 Figure A-GBAAA - Sheet 07 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 65 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_536170_6_BAAA_08_00 STGR26

STGR27 STGR25 FR28 FR28A

SCUFF PLATE CONTOUR OF

**FWD** 

## AFTER 1 mm (0.039 in)

SCUFF PLATE CUT LINE OF

SCUFF PLATE CUT LINE OF 3 mm (0.118 in) 3 mm (0.118 in)

**NOTE:** FOR FASTENER SYMBOLS, REFER TO SHEET 10. LH RH

LH RH 18 19

20 21 

## E **E F**  **F**

**E E**  **F F** 



## J

Figure A-GBAAA - Sheet 08 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 66 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

13 FR29 FR30 ONLY IN ITEM 73 MAKE CLEARANCE HOLE 5.5 mm (0.216 in)

73 (90) (91) (92) (93) (94) (95)

STGR12

STGR13

**FWD** 

## AFTER

**NOTE:** FOR FASTENER SYMBOLS, REFER TO SHEET 10. 

## K

D_SB_536170_6_BAAA_09_00 LH

RH

Figure A-GBAAA - Sheet 09 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 67 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

HOLE SYMBOL ITEM DESCRIPTION P/N
DAN11−6Y PIN COLLAR DAN6−6−15Y

NSA5075−5 PIN COLLAR DAN6−6−5

DAN11−6X PIN COLLAR DAN6−6−7X

DAN11−6X PIN COLLAR DAN6−6−6X

NSA5075−6 PIN COLLAR DAN6−6−4

DAN11−6Y PIN COLLAR DAN6−6−9Y

NSA5075−8 PIN COLLAR DAN6−8−14

NSA5075−8 PIN COLLAR DAN6−8−9

DAN11−6Y PIN COLLAR DAN6−6−16Y

DAN11−6Y PIN COLLAR DAN6−6−14Y

DAN11−6X PIN COLLAR DAN6−6−14X

NSA5075−8 PIN COLLAR DAN6−8−10

NSA5075−8 PIN COLLAR DAN6−8−11

NSA5075−8 PIN COLLAR DAN6−8−15

NSA5075−6 PIN COLLAR DAN6−6−14

NSA5075−6 PIN COLLAR DAN6−6−6

NSA5075−6 PIN COLLAR DAN6−6−7

NSA5075−6 PIN COLLAR DAN6−6−8

NSA5075−6 PIN COLLAR DAN6−6−9 HOLE SYMBOL ITEM DESCRIPTION P/N
NSA5075−6 PIN COLLAR DAN6−6−10

NSA5075−6 PIN COLLAR DAN6−6−11

NSA5075−6 PIN COLLAR DAN6−6−12

DAN11−6X PIN COLLAR DAN6−6−5X

DAN11−6X PIN COLLAR DAN6−6−8X

DAN11−6X PIN COLLAR DAN6−6−9X

DAN11−6X PIN COLLAR DAN6−6−10X

DAN11−6X PIN COLLAR DAN6−6−11X

DAN11−6X PIN COLLAR DAN6−6−12X

DAN11−6X PIN COLLAR DAN6−6−13X

DAN11−6Y PIN COLLAR DAN6−6−8Y

DAN11−6Y PIN COLLAR DAN6−6−12Y

DAN11−6X PIN COLLAR DAN6−6−16X

DAN11−6Y PIN COLLAR DAN6−6−5Y

DAN11−6Y PIN COLLAR DAN6−6−13Y

DAN11−6Y PIN COLLAR DAN6−6−11Y

NSA5075−8 PIN COLLAR DAN6−8−12

NSA5075−8 PIN COLLAR DAN6−8−16

DAN11−6Y PIN COLLAR DAN6−6−6Y 50 72 53 69 31 71 33 71 52 69 45 72 66 70 62 70 51 72 49 72 40 71 63 70 64 70 67 70 61 69 54 69 55 69 56 69 57 69 58 69 59 69 60 69 32 71 34 71 35 71 36 71 37 71 38 71 39 71 44 72 47 72 41 71 42 72 48 72 46 72 65 70 68 70 43 72 01 02 **NOTE:** USE NEXT NOMINAL IF REQUIRED. USE OVERSIZE IF REQUIRED. 01

01 01 01 01

01 01

01

01 02

02 02 02 02 02 02 02

02

02 02 02 02 02

D_SB_536170_6_BAAA_10_00 Figure A-GBAAA - Sheet 10 Installation of doublers and reinforcement at the MID passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 68 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL 

## BEFORE

**FWD** LH SHOWN RH SYMMETRICAL **FWD**

D_SB_536170_6_BBAA_01_00 STGR9 STGR10 STGR11 STGR12 STGR13 STGR14 STGR15 STGR16 STGR17 STGR18 STGR19 STGR20 STGR21 STGR22 STGR23 STGR24 STGR25 STGR26 STGR27 STGR28 FR72 FR73FR73A FR74 FR75 FR75A FR76 FR77 FR73A FR72

FR74 STGR25

STGR26

STGR27 

### D **E F**  **G H**  **J**

**B C** 



## A REMARKS
REMOVE FASTENERS HOLE SYMBOL

NOT AFFECTED FASTENERS Z261 (Z262)

Z171 (Z172) 

### A **A**



## B

Figure A-GBBAA - Sheet 01 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 69 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL 

## AFTER

**FWD** D_SB_536170_6_BBAA_02_00 FR73A FR72

FR74 STGR25

STGR26

STGR27

SCUFF PLATE 09

CLAMPING STRIP CORNER PLATE CONNECTING PLATE REMOVE, CUT IN ACORDANCE WITH DOUBLERS, TO AVIOD STRESSING. THE DOUBLER HAS TO BE PRE−SHAPED TO MATCH THE FUSELAGE CONTOUR TO AVOID STRESSING.

A539−80439−202 (LH) / −203 (RH) A539−80437−204 (LH) / −205 (RH) A539−80426−202 (LH) / −203 (RH) A539−80425−202 (LH) / −203 (RH) 07 06 05 04 08

CUT LINE OF NOTE 03 07 CUT LINE OF NOTE 02 08 CUT LINE OF NOTE 01 09 

### B
**B**

16 mm (0.630 in) 0.5 mm (0.118 in)

**NOTE:** 06 02 03 05 07 04 22 23

05 01 08 09 R 16 mm (0.630 in) R 16 mm (0.630 in) R 25 mm (0.984 in) 8 mm (0.315 in)

8 mm (0.315 in)

3 x 26 = 78 mm (3 x 1.024 = 3.070 in) 3 x 22 = 78 mm (3 x 1.024 = 3.070 in) R 25 mm (0.984 in) 7 x 26 = 182 mm (7 x 1.024 = 7.165 in) 24 mm (0.945 in)

5 mm (0.197 in) R 25 mm (0.984 in)
23 mm (0.905 in) 20 mm (0.787 in)

3 x 23 = 69 mm (3 x 0.906 = 2.716 in) 25 mm (0.984 in) 35 mm (1.378 in)

=
= 

### A **A** 25 mm (0.984 in)

28 mm (1.102 in) 8 mm (0.118 in)

4 mm (0.118 in) 1 mm (0.039 in)

R 1 mm (0.039 in) 1 mm (0.039 in) 1 mm (0.039 in)

1 mm (0.039 in) 8 mm (0.118 in) R 1 mm (0.039 in)



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

**C** FOR FASTENER SYMBOLS, REFER TO SHEET 9.
Figure A-GBBAA - Sheet 02 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 70 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL 

## BEFORE

**FWD** FR75A FR76

FR75

D_SB_536170_6_BBAA_03_00 STGR24

STGR25

STGR26

STGR27

STGR28 REMARKS
REMOVE FASTENERS HOLE SYMBOL

NOT AFFECTED FASTENERS 

## D

Figure A-GBBAA - Sheet 03 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 71 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL 

## AFTER

**FWD** FR75A FR76

FR75

D_SB_536170_6_BBAA_04_00 R 16 mm (0.630 in) R 16 mm (0.630 in)

16 mm (0.630 in) **NOTE:** R 16 mm (0.630 in) 7 x 23 = 161 mm (7 x 0.906 = 6.339 in)

8 mm (0.315 in) 32 mm (1.260 in)

16 mm (0.630 in)

2 x 24 = 48 mm (2 x 0.945 = 1.890 in) 41 mm (1.614 in)

40 mm (1.575 in) R 16 mm (0.630 in)

R 16 mm (0.630 in) 22 mm (0.866 in) 5 x 23 = 115 mm (5 x 0.906 = 4.528 in) 2 x 20= 40 mm (2 x 0.787 = 1.575 in)

24 25

01 08 06 05 01 07 04

10 AS IN SKIN SAME HOLE

09 =
= STGR28 STGR27 STGR26 STGR24

STGR25



## E SCUFF PLATE CLAMPING STRIP CORNER PLATE CONNECTING PLATE REMOVE, CUT IN ACORDANCE WITH DOUBLERS, TO AVIOD STRESSING. THE DOUBLER HAS TO BE PRE−SHAPED TO MATCH THE FUSELAGE CONTOUR TO AVOID STRESSING.

A539−80439−202 (LH) / −203 (RH) A539−80437−204 (LH) / −205 (RH) A539−80426−202 (LH) / −203 (RH) A539−80425−202 (LH) / −203 (RH) 07 06 05 04 CUTLINE OF NOTE 03 07 CUTLINE OF NOTE 02 08 CUTLINE OF NOTE 01 09

08 09 TRANSFER EXISTING HOLE FOR HOIST FITTING. INSTALL BLANKING PLUG AFTER REPAIR. 10 FOR FASTENER SYMBOLS, REFER TO SHEET 9.

Figure A-GBBAA - Sheet 04 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 72 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL FR73 FR73A FR74

**FWD** STGR10

STGR11

STGR12

STGR13 

## BEFORE



## F

D_SB_536170_6_BBAA_05_00 REMARKS
REMOVE FASTENERS HOLE SYMBOL

NOT AFFECTED FASTENERS
Figure A-GBBAA - Sheet 05 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 73 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL
FR73 FR73A FR74

**FWD** STGR10

STGR11

STGR12

STGR13 

## AFTER

D_SB_536170_6_BBAA_06_00 8 mm (0.315 in) 2.5 mm (0.098 in) 0.5 mm (0.020 in)

16 mm (0.630 in) 3 x 26 = 78mm (3 x 1.024 = 3.071 in) 16 mm (0.630 in) R 16 mm (0.630 in) 30 27 26 2 x 30 = 60mm (2 x 1.181 = 2.362 in)

R 16 mm (0.630 in)

THE DOUBLER HAS TO BE PRE−SHAPED TO MATCH THE FUSELAGE CONTOUR TO AVOID STRESSING. 12 FOR INSTALLATION OF DOUBLER (ITEM 30) USE ONLY EVERY THIRD RIVET. 11 1 mm (0.039 in) 12 11



## G **NOTE:** 

## C **C C**  **C**

FOR FASTENER SYMBOLS, REFER TO SHEET 9. Figure A-GBBAA - Sheet 06 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 74 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

**FWD** STGR10

STGR11

STGR12

STGR13 

## BEFORE FR75 FR75A FR76

D_SB_536170_6_BBAA_07_00 REMARKS
REMOVE FASTENERS HOLE SYMBOL

NOT AFFECTED FASTENERS 

## H

Figure A-GBBAA - Sheet 07 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 75 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

**FWD** STGR10

STGR11

STGR12

STGR13 

## AFTER FR75 FR75A FR76

D_SB_536170_6_BBAA_08_00 THE DOUBLER HAS TO BE PRE−SHAPED TO MATCH THE FUSELAGE CONTOUR TO AVOID STRESSING. 12 FOR INSTALLATION OF DOUBLER (ITEM 30) USE ONLY EVERY THIRD RIVET. 11 **NOTE:**

FOR FASTENER SYMBOLS, REFER TO SHEET 9. R 10 mm (0.394 in) R 10 mm (0.394 in)

R 10 mm (0.394 in) 2 x 21 = 42 mm (2 x 0.827 = 1.654 in)

1 mm (0.039 in) 10 mm (0.394 in) 1 mm (0.039 in)

8 mm (0.315 in)

16 mm (0.630 in) 30 mm (1.181 in) LH RH 28 29



### A
**A** 30 11

12



## J

Figure A-GBBAA - Sheet 08 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 76 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

HOLE SYMBOL ITEM DESCRIPTION P/N
NSA5075−5 PIN COLLAR DAN6−6−5

DAN11−6X PIN COLLAR DAN6−6−7X

DAN11−6X PIN COLLAR DAN6−6−6X

NSA5075−6 PIN COLLAR DAN6−6−7

NSA5075−6 PIN COLLAR DAN6−6−10

DAN11−6X PIN COLLAR DAN6−6−5X

DAN11−6X PIN COLLAR DAN6−6−8X

DAN11−6X PIN COLLAR DAN6−6−9X

DAN11−6X PIN COLLAR DAN6−6−10X

DAN11−6X PIN COLLAR DAN6−6−11X

DAN11−6X PIN COLLAR DAN6−6−12X

DAN11−6X PIN COLLAR DAN6−6−13X

DAN11−6Y PIN COLLAR DAN6−6−8Y 53 69 31 71 33 71 55 69 58 69 32 71 34 71 35 71 36 71 37 71 38 71 39 71 44 72 01

01 01 01 01 01 01 01 01 01

01 **NOTE:** USE OVERSIZE IF REQUIRED. D_SB_536170_6_BBAA_09_00 ITEMS 33−39 AND 55−58. Figure A-GBBAA - Sheet 09 Installation of doublers and reinforcement at the AFT passenger/crew door frame DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 77 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_536170_6_BCAA_01_00 Z832 Z842 Z843

Z833



### A **B**

LH SHOWN RH SYMMETRICAL LH SHOWN RH SYMMETRICAL FR30A FR28A

FR73A

FR75A 

### C

**D**



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

Figure A-GBCAA - Sheet 01 Installation of a doubler at the MID and AFT passenger/crew doors DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 78 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

EDGE BEAM

(102) (103) 102 103 LH RH (110)

(112) (113) (114) (112) (113) (114) (110) CENTER OF DOOR

EDGE BEAM (107)

SEAL EDGES **NOTE:** 01 01 104

EDGE BEAM UPPER 

### A

**A B** 

**B** FR30A FR28A

**FWD** 

## BEFORE **AFTER** 

## C

01 100 101



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

D_SB_536170_6_BCAA_02_00 (17 POSITIONS) (170 POSITIONS)

Figure A-GBCAA - Sheet 02 Installation of a doubler at the MID and AFT passenger/crew doors DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 79 6

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

# @A300-600 SERVICE BULLETIN

**CONF ALL

EDGE BEAM

(102) (103) 102 103 LH RH LH RH
LH RH 105 106 LH RH LH RH EDGE BEAM

SEAL EDGES **NOTE:** 01 01 EDGE BEAM UPPER FR73A FR75A CENTER OF DOOR 

### C

**C D** 

**D** (109)RH LH (108) 104

(108) (109) (108) (109)

(115) (116) (117) (117) (116) (115) 

## BEFORE **AFTER**

01 **FWD** 

## D

**C C**  **D D** 

D_SB_536170_6_BCAA_03_00 (18 POSITIONS) (170 POSITIONS)

Figure A-GBCAA - Sheet 03 Installation of a doubler at the MID and AFT passenger/crew doors DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 80 6

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: A300-600 - GENERAL - INSTALL REINFORCEMENTS AT DOOR FRAME SHELL OF DOOR 2 AND 4 MODIFICATION No.: 13578D23280 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: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 1 6

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# @A300-600 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.

DATE: May 16/11 SERVICE BULLETIN No.: A300-53-6170 REVISION No.: 00 - May 16/11 Page: 1 6

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