@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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - AFT SECTION - INSPECT DOOR FRAME HOLES AT

FR56A, FR57A & FR73A

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During the aircraft preparation phase for conversion of an A300-600 aircraft from PAX to Freighter, a

crack was detected in Door Frame(FR) 73A, between STGR24 and STGR25, LH/RH. The crack

initiation was found on the seal retainer run out rivet hole, near the frame web of door stops No.8.

Because the emergency exit and AFT passenger/crew doors have the same structural door frame

design, Airbus has decided to do a special detailed inspection of door frame FR56A, FR57A and

FR73A.

This Service Bulletin requires the operator to introduce a High Frequency Eddy Current (HFEC)

inspection of the seal retainer run out rivet hole at FR56A, FR57A and FR73A.

Accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible

crack propagation and will contribute to ensure the structural integrity of the door frame FR56A, FR57A

and FR73A.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

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

36V 67Q ABR BCS CES F2I FDX GBG I2L IRA IRM KAC MGC

MNB MON MRJ MSR MXU SUD TAR THA URS UZB

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 536175-832-848-001: Inspection

TOTAL MANHOURS 10.75

ELAPSED TIME (HOURS) 4.50

APPENDICES

Appendix 01 - Elapsed Time Assumption

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF ALL

Z250

Z260

OF DOOR 

FRAME HOLES

A

INSPECTION

FR76

FR58

LH SHOWN A RH SYMMETRICAL

FR73A

FR57A

FR56A

D_SB_536175_6_SAAA_01_00

Figure A-GSAAA - Sheet 01

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 4

6

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - AFT SECTION - INSPECT DOOR FRAME HOLES AT

FR56A, FR57A & FR73A

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

B4-603 B4-605R B4-622R

(2) Effectivity by MSN

0505 0521 0525 0529-0530 0532 0536 0543 0546 0553 0555 0557-0559 0561 0563

0572 0575 0577 0579 0581 0584 0602-0605 0607-0608 0611 0613 0617-0618 0621

0623 0625-0626 0629-0630 0632-0633 0637 0641 0643 0657 0659 0664 0666 0668

0670 0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709

0711 0713 0715 0717 0719 0721-0725 0727 0729-0730 0732-0734 0737 0739-0741

0743-0744 0746 0749-0750 0753-0754 0756 0762-0764 0767 0770 0773 0775

0782-0788 0797 0836-0838

(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.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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@A300-600

SERVICE BULLETIN

OPERATOR MSN

36V 0605

67Q 0584 0603 0744 0749 0764

ABR 0683 0770

BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730

0737 0740 0753 0783 0797 0836 0837

CES 0707 0725 0732 0741 0746 0754 0763

F2I 0529 0557

FDX 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625

0630 0633 0657 0659 0664 0668 0688 0709 0713 0715

GBG 0626 0643

I2L 0677

IRA 0632 0696 0723 0727

IRM 0546 0553 0608 0618 0623 0701 0773 0838

KAC 0673 0694 0699 0719 0721

MGC 0743

MNB 0521 0525 0532 0734 0739 0756

MON 0604

MRJ 0750 0762

MSR 0561 0607

MXU 0767 0788

SUD 0666 0775

TAR 0505 0558 0563

THA 0577 0629 0681 0705 0782 0784 0785 0786 0787

URS 0733

UZB 0717 0722

(4) Configuration by MSN

MSN CONFIGURATION

0505 0521 0525 0529 0530 0532 0536 0543 0546 0553 0555

0557 0558 0559 0561 0563 0572 0575 0577 0579 0581 0584

0602 0603 0604 0605 0607 0608 0611 0613 0617 0618 0621

0623 0625 0626 0629 0630 0632 0633 0637 0641 0643 0657

0659 0664 0666 0668 0670 0673 0677 0679 0681 0683 0688

0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715

0717 0719 0721 0722 0723 0724 0725 0727 0729 0730 0732

0733 0734 0737 0739 0740 0741 0743 0744 0746 0749 0750

0753 0754 0756 0762 0763 0764 0767 0770 0773 0775 0782

0783 0784 0785 0786 0787 0788 0797 0836 0837 0838

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

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@A300-600

SERVICE BULLETIN

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During the aircraft preparation phase for conversion of an A300-600 aircraft from PAX

to Freighter, a crack was detected in Door Frame(FR) 73A, between STGR24 and

STGR25, LH/RH. The crack initiation was found on the seal retainer run out rivet

hole, near the frame web of door stops No.8. Because the emergency exit and AFT

passenger/crew doors have the same structural door frame design, Airbus has decided

to do a special detailed inspection of door frame FR56A, FR57A and FR73A.

(2) Objective/Action

This Service Bulletin requires the operator to introduce a High Frequency Eddy Current

(HFEC) inspection of the seal retainer run out rivet hole at FR56A, FR57A and FR73A.

(3) Advantages

Accomplishment of this Service Bulletin will allow early detection of cracks in order to

avoid possible crack propagation and will contribute to ensure the structural integrity of

the door frame FR56A, FR57A and FR73A.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 536175-832-848-001: Inspection

(1) Do a HFEC inspection for cracks at FR56A LH

(2) Do a HFEC Inspection for cracks at FR56A RH

(3) Do a HFEC Inspection for cracks at FR57A LH

(4) Do a HFEC Inspection for cracks at FR57A RH

(5) Do a HFEC Inspection for cracks at FR73A LH

(6) Do a HFEC Inspection for cracks at FR73A RH

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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@A300-600

SERVICE BULLETIN

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given below but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

Table 01: Config 001 - Inspection of seal retainer run out rivet hole at frame 56A, 57A and 73A

Compliance Time

Whichever occurs later

Condition Action

Threshold: Grace Period:

Repetitive interval

Aircraft not

covered by Special

Detailed Inspection

(SDI)

TD_K4_S1_43707

_2013 at frame

56A, 57A and 73A

Do a HFEC

inspection of the

seal retainer run

out rivet hole at

frame 56A, 57A

and 73A

32000 FC from

aircraft first flight

Whichever occurs

first between a)

and b)

a) 36000 FC from

aircraft first flight

or

b) 36 months after

the Service Bulletin

issue date

7500 FC

Aircraft covered by

Special Detailed

Inspection (SDI)

TD_K4_S1_43707

_2013 at frame

56A, 57A and 73A

Do a HFEC

inspection of the

seal retainer run

out rivet hole at

frame 56A, 57A

and 73A

7500 FC from TD’s

embodiment

none 7500 FC

Contact AIRBUS

Repair Support

Before the next

flight

Crack findings none none

Report inspection

result to AIRBUS

Within 10 days none none

Report inspection

result to AIRBUS

No crack findings Within 1 month none none

Next HFEC

inspection of the

seal retainer run

out rivet hole

none none 7500FC

NOTE: TD_K4_S1_43707_2013 is applicable for MSN 0553 only

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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@A300-600

SERVICE BULLETIN

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 536175-832-848-001: Inspection

Get Access 3.00

On Aircraft

Do a HFEC inspection for cracks at FR56A LH 0.50

Do a HFEC Inspection for cracks at FR56A RH 0.50

Do a HFEC Inspection for cracks at FR57A LH 0.50

Do a HFEC Inspection for cracks at FR57A RH 0.50

Do a HFEC Inspection for cracks at FR73A LH 0.50

Do a HFEC Inspection for cracks at FR73A RH 0.50

Tests 4.50

Close-Up 0.25

TOTAL MANHOURS 10.75

ELAPSED TIME (HOURS) 4.50

NOTE: For a breakdown of the manhours and elapsed time, refer to the Gantt Chart

Fig. A-GAAAA as given in Appendix 01

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

20-21-12 24-00-00 24-41-00

25-00-00 25-12-11 25-22-11

25-23-41

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-52-10 20-55-00

Non Destructive Test Manual (NTM) 51-10-08

Structural Repair Manual (SRM) 51-24-00 51-40-20

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SERVICE BULLETIN

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 531618-01-1

531814-01-1

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

No Material Set

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner-General - - 08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use the tools listed in NTM

51-10-08, Page Block 601.

(3) Special Tools

None

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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This Page Intentionally Left Blank

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 536175-832-848-001 - Inspection

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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@A300-600

SERVICE BULLETIN

Task Associated Data

Zone

250 260

Manpower

TOTAL MANHOURS 10.75

ELAPSED TIME (HOURS) 4.50

A. GENERAL

(1) Subtask 536175-910-201-001 - Standard Practices

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-52-10

Structural Repair Manual (SRM) 51-24-00

51-40-20

(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 zones, refer to AMM 06-21-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(e) Do a check of the electrical connectors before you connect them, refer to ESPM

20-52-10.

(f) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(g) Remove and install fasteners in accordance with SRM 51-40-20.

(h) Use a non-metallic spatula to remove the sealant and clean the surface.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 536175-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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@A300-600

SERVICE BULLETIN

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

B. PREPARATION

(1) Subtask 536175-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 73A LH/RH

250 Work location Frame 57A LH/RH

Frame 56A LH/RH

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-41-00, Page Block 301

25-00-00, Page Block 801

25-22-11, Page Block 401

25-23-41, Page Block 401

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page

Block 301.

(c) Energize the ground service network, refer to AMM 24-41-00, Page Block 301.

(d) Put an access platform in position of the MID and AFT doors 834, 844, 833 and

843.

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(e) Open, safety/lock and tag the applicable circuit breakers as specified in the removal

of door frame linings, refer to AMM 25-23-41, Page Block 401.

(f) At Frame 56A, Frame 57A and Frame 73A LH/RH , remove the door frame linings

for access, refer to AMM 25-23-41, Page Block 401.

(g) Put blanking caps on the disconnected electrical connectors.

(h) Between Frame 56 and Frame 56A, Frame 57 and Frame 57A and between Frame

73 and Frame 73A, remove the heat and sound insulation blankets for access, refer

to AMM 25-22-11, Page Block 401.

(i) If necessary for repair of insulation blankets, refer to AMM 25-00-00, Page Block

801.

C. PROCEDURE

(1) Subtask 536175-250-202-001 - Do a HFEC inspection for cracks at FR56A LH

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 56A LH

from Stringer 24 to Stringer 25

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

Fig. A-GBBAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

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SERVICE BULLETIN

(a) At Frame 56A, LH, between STGR 25 and STGR 25A as shown on Fig. A-GBBAA

Sheet 01, View A and Fig. A-GBBAA Sheet 02, View B, clean the inspection

surface area with:

Textile-Lint Free

Cotton -

14SBA1 As required

Non Aqueous

Cleaner-General -

08BAA9 As required

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of seal retainer run out hole at Frame 56A LH, refer to NTM 51-10-08, Page

Block 601, Fig. A-GBBAA Sheet 01, View A, Fig. A-GBBAA Sheet 02, View B and

as shown on flow chart Fig. A-GFAAA Sheet 01, at the threshold given in Para

1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBBAA Sheet

02, View B.

2 If there are no cracks:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

(2) Subtask 536175-250-201-001 - Do a HFEC Inspection for cracks at FR56A RH

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 56A RH

from Stringer 24 to Stringer 25

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

Fig. A-GBBAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

(a) At Frame 56A RH, between STGR 25 and STGR 25A as shown on Fig. A-GBBAA

Sheet 01, View A and Fig. A-GBBAA Sheet 02, View B, clean the inspection

surface area with:

Textile-Lint Free

Cotton -

14SBA1 As required

Non Aqueous

Cleaner-General -

08BAA9 As required

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of seal retainer run out hole at Frame 56A RH, refer to NTM 51-10-08, Page

Block 601, Fig. A-GBBAA Sheet 01, View A, Fig. A-GBBAA Sheet 02, View B and

as shown on flow chart Fig. A-GFAAA Sheet 01, at the threshold given in Para

1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBBAA Sheet

02, View B.

2 If there are no crack:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 14

6

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@A300-600

SERVICE BULLETIN

(3) Subtask 536175-250-203-001 - Do a HFEC Inspection for cracks at FR57A LH

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 57A LH

from Stringer 24 to Stringer 25

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

Fig. A-GBAAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

(a) At Frame 57A LH, between STGR 25 and STGR 25A as shown on Fig. A-GBAAA

Sheet 01, View A and Fig. A-GBAAA Sheet 02, View B, clean the inspection

surface area with:

Textile-Lint Free

Cotton -

14SBA1 As required

Non Aqueous

Cleaner-General -

08BAA9 As required

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 15

6

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

SERVICE BULLETIN

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of seal retainer run out hole atFrame 57A LH, refer to NTM 51-10-08, Page

Block 601, Fig. A-GBAAA Sheet 01, View A, Fig. A-GBAAA Sheet 02, View B and

as shown on flow chart Fig. A-GFAAA Sheet 01, at the threshold given in Para

1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet

02, View B.

2 If there are no crack:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

(4) Subtask 536175-250-204-001 - Do a HFEC Inspection for cracks at FR57A RH

Work Zones and Access Panels

Zone Access/Work location

250 Work location Frame 57A RH

from Stringer 24 to Stringer 25

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 16

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

SERVICE BULLETIN

References

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

Fig. A-GBAAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

(a) At Frame 57A, RH, between STGR 25 and STGR 25A as shown on Fig. A-GBAAA

Sheet 01, View A and Fig. A-GBAAA Sheet 02, View B, clean the inspection

surface area with:

Textile-Lint Free

Cotton -

14SBA1 As required

Non Aqueous

Cleaner-General -

08BAA9 As required

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of seal retainer run out hole, at Frame 57A RH, refer to NTM 51-10-08, Page

Block 601, Fig. A-GBAAA Sheet 01, View A, Fig. A-GBAAA Sheet 02, View B and

as shown on flow chart Fig. A-GFAAA Sheet 01, at the threshold given in Para

1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet

02, View B.

2 If there are no cracks:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

(5) Subtask 536175-250-205-001 - Do a HFEC Inspection for cracks at FR73A LH

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 73A LH

from Stringer 24 to Stringer 25

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 17

6

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

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

Fig. A-GBCAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

(a) At Frame 73A, LH, between STGR 24 and STGR 25 as shown on Fig. A-GBCAA

Sheet 01, View A and Fig. A-GBCAA Sheet 02, View B, clean the inspection

surface area with:

Textile-Lint Free

Cotton -

14SBA1 As required

Non Aqueous

Cleaner-General -

08BAA9 As required

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of seal retainer run out hole, at Frame 73A LH, refer to NTM 51-10-08, Page

Block 601, Fig. A-GBCAA Sheet 01, View A, Fig. A-GBCAA Sheet 02, View B and

as shown on flow chart Fig. A-GFAAA Sheet 01, at the threshold given in Para

1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBCAA Sheet

02, View B.

2 If there are no cracks:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 18

6

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@A300-600

SERVICE BULLETIN

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

(6) Subtask 536175-250-206-001 - Do a HFEC Inspection for cracks at FR73A RH

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 53A RH

from Stringer 24 to Stringer 25

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

Fig. A-GBCAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

(a) At Frame 73A, RH, between STGR 24 and STGR 25 as shown on Fig. A-GBCAA

Sheet 01, View A and Fig. A-GBCAA Sheet 02, View B, clean the inspection

surface area with:

Textile-Lint Free

Cotton -

14SBA1 As required

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 19

6

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

SERVICE BULLETIN

Non Aqueous

Cleaner-General -

08BAA9 As required

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of seal retainer run out hole, at Frame 73A RH, refer to NTM 51-10-08, Page

Block 601, Fig. A-GBCAA Sheet 01, View A, Fig. A-GBCAA Sheet 02, View B and

as shown on flow chart Fig. A-GFAAA Sheet 01, at the threshold given in Para

1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBCAA Sheet

02, View B.

2 If there are no cracks:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

D. TEST

(1) Subtask 536175-720-201-001 - Functional Test

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 73A LH/RH

250

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401

25-23-41, Page Block 401

(a) BetweenFrame 56 and Frame 56A, Frame 57 and Frame 57A and between, Frame

73 and Frame 73A LH/RH, install the heat and insulation blankets, refer to AMM

25-12-11, Page Block 401.

(b) Remove the blanking caps from the disconnected electrical connectors.

(c) At Frame 56A, Frame 57A and Frame 73A, install the door frame linings , refer to

AMM 25-23-41, Page Block 401.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 20

6

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@A300-600

SERVICE BULLETIN

(d) Remove the safety clips and/or the tags and close/unlock the applicable circuit

breakers as specified after installation of door frame linings, refer to AMM 25-23-41,

Page Block 401.

(e) Do the applicable tests of exit lights as specified after installation of door frame

linings, refer to AMM 25-23-41, Page Block 401.

E. CLOSE-UP

(1) Subtask 536175-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

260

Manpower Resources

Skills NON SPECIFIC

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

equipment.

(b) Close the passenger MID and AFT passenger/crew doors 834, 844, 833 and 843.

(c) Remove the access platforms.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 21

6

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

SERVICE BULLETIN

**CONF ALL

STGR26

STGR27

STGR25A

STGR30

STGR29

STGR25

FR56A

FR57A

FR58

FR57.3

FR57.2

FR57.1

FR57

FR56

STGR28

Z250

A LH SHOWN

RH SYMMETRICAL

SEAL

RETAINER

A

B

D_SB_536175_6_BAAA_01_03

Figure A-GBAAA - Sheet 01

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 22

6

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

SERVICE BULLETIN

**CONF ALL

STGR25

STGR25A

STGR26

FR57A

DOOR

STOP 8

10.0 mm

(0.39 in)

AREA TO BE INSPECTED.

MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD.

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

SEALANT

RETAINER

STGR24

B

D_SB_536175_6_BAAA_02_02

Figure A-GBAAA - Sheet 02

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 23

6

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

SERVICE BULLETIN

**CONF ALL

STGR26

STGR27

STGR25A

STGR30

STGR29

STGR25

FR56A

FR57A

FR58

FR57.3

FR57.2

FR57.1

FR57

FR56

STGR28

A LH SHOWN

RH SYMMETRICAL

SEAL

RETAINER

B

Z250

A

D_SB_536175_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 24

6

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@A300-600

SERVICE BULLETIN

**CONF ALL

AREA TO BE INSPECTED.

MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD.

DOOR

STGR23A

STGR24

STGR25

STGR25A

STOP 8

10.0 mm

(0.39 in)

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT

SEAL 

RETAINER FR56A

B

D_SB_536175_6_BBAA_02_00

Figure A-GBBAA - Sheet 02

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 25

6

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

SERVICE BULLETIN

**CONF ALL

STGR18

STGR22X

STGR22A

STGR23

STGR24

STGR25

STGR26

STGR27

STGR28

STGR29

FR73

FR73A

FR74

FR75

FR75A

FR76

LH SHOWN

RH SYMMETRICAL

SEAL

REATAINER

Z260

A

A

B

D_SB_536175_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 26

6

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@A300-600

SERVICE BULLETIN

**CONF ALL

STGR22A

STGR23

STGR24

STGR25

FR73A

AREA TO BE INSPECTED.

MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD.

DOOR STOP 8

10.0 mm

(0.39 in)

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT

SEAL RETAINER

B

D_SB_536175_6_BCAA_02_00

Figure A-GBCAA - Sheet 02

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 27

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

SERVICE BULLETIN

**CONF ALL

CRACKS FOUND NO

CONTACT AIRBUS REPAIR SUPPORT

BEFORE NEXT FLIGHT

REPORT INSPECTION RESULT WITHIN

10 DAYS TO AIRBUS

1 MONTH TO AIRBUS

REPORT INSPECTION RESULT WITHIN

AT INTERVAL

DO A REPETITIVE INSPECTION

DO A SPECIAL DETAILED INSPECTION OF THE HOLES

AT THRESHOLD

DETAILED IN PARA. 1.E.(2)

YES

DETAILED IN PARA. 1.E.(2)

FOR THE CRACKED FRAME(S)

ON NON−REPAIRED FRAME(S)

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN

PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE

D_SB_536175_6_FAAA_01_02

Figure A-GFAAA - Sheet 01

HFEC Inspection Flow Chart

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 28

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@A300-600

SERVICE BULLETIN

**CONF ALL

YES NO

RESULT OF INSPECTION

CRACK ON

FRAME No

LEFT SIDE RIGHT SIDE

73A

YES NO

57A

56A

INSPECTION REPORT

DISCRIPTION OF FINDINGS

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A300−53−6175

DATE OF INSPECTION :

INSPECTION METHOD :

GENERAL

INSPECTION

DETAILED

INSPECTION DETAILED

INSPECTION

VISUAL

x SPECIAL

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE 

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Structure.sbinspectionresult@airbus.com

FAX +33 (0)5 61 93 36 14

E−mail:

CENTER WING BOX (WB/LR)

D_SB_536175_6_RAAA_01_02

Figure A-GRAAA - Sheet 01

HFEC inspection Reporting Sheet

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 29

6

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

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 30

6

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

SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A300−53−6175

ON DOOR 843

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

10.75

4.50

STEPS

0.50 0.50

0 10

INSPECTION DOOR 833 0.50 0.50

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

PER

1

1

:

:

SB ELAPSED TIME

(HOURS)

2 4 6 8 12

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

REMOVE FRAME LININGS 

ON DOOR 834 2

REMOVE FRAME LININGS 

INSPECTION DOOR 843

ON DOOR 844 2 0.50

INSPECTION DOOR 834 1.00 1.00 1

1.00 0.50

0.50 0.50 1

1.00

REMOVE FRAME LININGS 

ON DOOR 833 0.75 1 0.375

INSTALL FRAME LININGS 

INSPECTION DOOR 844 1.00 1.00 1

ON DOOR 843 0.75 1 0.375

INSTALL FRAME LININGS 

ON DOOR 833 0.50 0.50 1

REMOVE FRAME LININGS 

ON DOOR 844 1.50 0.75 2

INSTALL FRAME LININGS 

ON DOOR 834 1.50 0.75 2

INSTALL FRAME LININGS 

CLOSE UP 0.25 0.25 1

D_SB_536175_6_AAAA_01_02

Figure A-GAAAA - Sheet 01

Gantt chart

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 1

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@A300-600

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - AFT SECTION - INSPECT DOOR FRAME HOLES AT

FR56A, FR57A & FR73A

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 1

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@A300-600

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175

REVISION No.: 00 - May 28/14 Page: 1

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