@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

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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

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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

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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

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

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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

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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

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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

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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

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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

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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

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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

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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 262RW

Manpower

TOTAL MANHOURS 760.00

ELAPSED TIME (HOURS) 400.0

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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.

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(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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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

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

(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

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

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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

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

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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

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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

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@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

D E B C

H J F G

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

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@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

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@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

FR28 FR28A

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

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@A300-600

SERVICE BULLETIN

**CONF ALL

FR30

FR30A FR31

D_SB_536170_6_BAAA_05_00

STGR26

STGR27

STGR25

BEFORE

FWD

(110)

(111)

(112) (121) (123)

(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

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@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)

(123) (127) (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

1 mm AFTER

(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 P/N DESCRIPTION

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 P/N DESCRIPTION

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

LH SHOWN FWD

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 FR73

FR73A

FR74 FR75

FR75A

FR76 FR77

FR72 FR73A

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

FR72 FR73A

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

03 CUT LINE OF NOTE 07

02 CUT LINE OF NOTE 08

01 CUT LINE OF NOTE 09

B

B

16 mm

(0.630 in)

0.5 mm

(0.118 in)

NOTE:

03 02 06

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 05 06

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

03 CUTLINE OF NOTE 07

02 CUTLINE OF NOTE 08

01 CUTLINE OF NOTE 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

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

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

11 30

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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

HOLE

SYMBOL ITEM P/N DESCRIPTION

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

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

FR28A FR30A

FWD

BEFORE AFTER

C

01

100

101

A A B B

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

(108) LH

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

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

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

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