# Airbus Service Bulletin A300-55-6052

Copy: No revision named ("A300-55-6052"), 29 pages: PDF https://openairdocs.org/files/sha256/d4/73/d4737ce05caa2e9e638eb4723ba8dd1fefe71b77b84da535c9be9219e262a868; text https://openairdocs.org/service-documents/airbus/a300-55-6052/file/d4737ce05caa.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0192, the docket of AD 2019-14-14. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A300-55-6052
- Page: https://openairdocs.org/service-documents/airbus/a300-55-6052

## Text (29 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0192, the docket of AD 2019-14-14. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A300-600
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
This summary is for information only and is not approved for modification of the aircraft.
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 55
TITLE: STABILIZERS - VERTICAL STABILIZER - INSPECT THE VERTICAL
TAIL PLANE COMPOSITE ATTACHMENT FITTINGS
**CONF ALL
MODIFICATIONS
None
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
The AMM 55-36-11, Page Block 601 (VERTICAL STABILIZER ATTACH FITTINGS -
INSPECTION/CHECK) provides detailed information covering composite and meta llic vertical tail plane
attachment fitting visual inspections and damage limits. A discrepancy was found between inspection
requirements provided in AMM 55-36-11, Page Block 601 revision May 2017 and before and SRM
55-30-00, page block 101 (CFRP Vertical Stabilizer).
Previous inspections performed as per AMM 55-36-11, Page Block 601 revision May 2017 and before
may lead to incorrect damage assessment and if not repaired, might impair the structural integrity of the
vertical tail plane connection.
Refer to Operator Information Transmission (OIT) 999.0021/18.
A Detailed Inspection (DET) of the transverse load fittings and a DET plus Special Detailed Inspection
(SDI) of the main fittings for damage detection have to be performed.
The purpose of this inspection is to ensure that there is no damage on vertical tail plane attachment
fittings in composite (Post MOD No. 04886D3915).
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
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A300-600
SERVICE BULLETIN
SUMMARY
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
No Material
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
14S AAW ABR AHK BCS EFX FDX IRA IRM MNB MRJ MSR QSM
SOP SUD TAR THA TNO UPS URS UTP
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 None
SIL
 None
ISI
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
MANPOWER
Task 556052-832-848-001: Inspection
TOTAL MANHOURS
 21.00
ELAPSED TIME (HOURS)
 18.00
APPENDICES
Appendix 01 - Inspection Report
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 2
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@A300-600
SERVICE BULLETIN
SUMMARY
**CONF ALL
A B
REAR SPAR
FRONT SPAR
REAR SPAR
FRONT SPAR
INSPECTION OF THE MAIN
ATTACHMENT FITTINGS
INSPECTION OF THE TRANSVERSE
LOAD ATTACHMENT FITTINGS
INSPECTION OF THE TRANSVERSE
LOAD ATTACHMENT FITTINGS
INSPECTION OF THE MAIN
ATTACHMENT FITTINGS
INSPECTION OF THE MAIN
ATTACHMENT FITTINGS
Z311
Z312
LH
RH
Z320
A B
D_SB_556052_6_SAAA_01_02
Figure A-G SAAA - S heet 01
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 3
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@A300-600
SERVICE BULLETIN
SUMMARY
This Page Intentionally Left Blank
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 4
6
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### Page 5

@A300-600
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 55
TITLE: STABILIZERS - VERTICAL STABILIZER - INSPECT THE VERTICAL
TAIL PLANE COMPOSITE ATTACHMENT FITTINGS
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
NOTE
: This Service Bulletin is only applicable to aircraft on which MOD No.
04886D3915 (STABILIZERS - INTRODUCE VERTICAL STABILIZER BOX IN
CFRP) is embodied.
(1) Models
B4-603 B4-605R B4-622 B4-622R C4-605R/F F4-605R F4-622R
(2) Effectivity by MSN
0417 0477 0479 0505 0521 0525 0530 0532 0536 0543 0546 0553 0555 0557-0559
0561 0563 0572 0575 0579 0581 0584 0602-0603 0607-0608 0611 0613 0617-0618
0621 0623 0625-0626 0629-0630 0632-0633 0637 0641 0643 0657 0659 0664 0666
0668 0670 0677 0679 0683 0688 0694 0696 0699 0701 0703 0707 0709 0711 0713
0715 0717 0719 0721-0730 0732-0746 0748-0750 0752-0764 0766 0768-0775
0777-0794 0797 0799-0840 0845-0878
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 1
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@A300-600
SERVICE BULLETIN
(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
14S
 0694 0699 0719 0721 0782 0784 0785 0786 0787
AAW
 0788
ABR
 0557 0677 0717 0722
AHK
 0683 0770 0855 0856 0857 0858 0859 0860 0870 0871
BCS
 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730
0737 0740 0743 0753 0783 0797 0836 0837 0872
EFX
 0755
FDX
 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581
0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713
0715 0726 0728 0735 0736 0738 0742 0745 0748 0752 0757 0759
0760 0761 0766 0768 0769 0771 0772 0774 0777 0778 0779 0780
0781 0789 0790 0791 0792 0793 0794 0799 0800 0801 0802 0803
0804 0873 0874 0875 0876 0877 0878
IRA
 0632 0696 0723 0727
IRM
 0546 0553 0608 0618 0623 0701 0773 0838
MNB
 0521 0525 0734 0739 0756 0758
MRJ
 0750 0762
MSR
 0561 0607
QSM
 0584 0603 0744 0749 0764
SOP
 0532
SUD
 0666 0775
TAR
 0505 0558 0563
THA
 0629
TNO
 0626 0643
UPS
 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816
0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828
0829 0830 0831 0832 0833 0834 0835 0839 0840 0845 0846 0847
0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864 0865
0866 0867 0868 0869
URS
 0733
UTP
 0707 0725 0732 0741 0746 0754 0763
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 2
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@A300-600
SERVICE BULLETIN
(4) Configuration by MSN
MSN
 CONFIGURATION
0417 0477 0479 0505 0521 0525 0530 0532 0536 0543 0546
0553 0555 0557 0558 0559 0561 0563 0572 0575 0579 0581
0584 0602 0603 0607 0608 0611 0613 0617 0618 0621 0623
0625 0626 0629 0630 0632 0633 0637 0641 0643 0657 0659
0664 0666 0668 0670 0677 0679 0683 0688 0694 0696 0699
0701 0703 0707 0709 0711 0713 0715 0717 0719 0721 0722
0723 0724 0725 0726 0727 0728 0729 0730 0732 0733 0734
0735 0736 0737 0738 0739 0740 0741 0742 0743 0744 0745
0746 0748 0749 0750 0752 0753 0754 0755 0756 0757 0758
0759 0760 0761 0762 0763 0764 0766 0768 0769 0770 0771
0772 0773 0774 0775 0777 0778 0779 0780 0781 0782 0783
0784 0785 0786 0787 0788 0789 0790 0791 0792 0793 0794
0797 0799 0800 0801 0802 0803 0804 0805 0806 0807 0808
0809 0810 0811 0812 0813 0814 0815 0816 0817 0818 0819
0820 0821 0822 0823 0824 0825 0826 0827 0828 0829 0830
0831 0832 0833 0834 0835 0836 0837 0838 0839 0840 0845
0846 0847 0848 0849 0850 0851 0852 0853 0854 0855 0856
0857 0858 0859 0860 0861 0862 0863 0864 0865 0866 0867
0868 0869 0870 0871 0872 0873 0874 0875 0876 0877 0878
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.
(6) Material Effectivity
No Material Set
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
The AMM 55-36-11, Page Block 601 (VERTICAL STABILIZER ATTACH FITTINGS -
INSPECTION/CHECK) provides detailed information covering composite and meta llic
vertical tail plane attachment fitting visual inspections and damage limits. A discrepancy
was found between inspection requirements provided in AMM 55-36-11, Page Block 601
revision May 2017 and before and SRM 55-30-00, page block 101 (CFRP Vertical
Stabilizer).
Previous inspections performed as per AMM 55-36-11, Page Block 601 revision May
2017 and before may lead to incorrect damage assessment and if not repaired, might
impair the structural integrity of the vertical tail plane connection.
Refer to Operator Information Transmission (OIT) 999.0021/18.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 3
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@A300-600
SERVICE BULLETIN
(2) Objective/Action
A Detailed Inspection (DET) of the transverse load fittings and a DET plus Special
Detailed Inspection (SDI) of the main fittings for damage detection have to be performed.
(3) Advantages
The purpose of this inspection is to ensure that there is no damage on vertical tail plane
attachment fittings in composite (Post MOD No. 04886D3915).
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 556052-832-848-001: Inspection
(1) Do a DET of the Transverse Load Fittings at accessible area and the Main
Attachment Fittings
(2) SDI of the Main Attachment Fittings of the Vertical Stabilizer
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin must be done within 30 months from the
issuance of this Inspection Service Bulletin.
This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued
to confirm this classification. It is anticipated that the AD will confirm the 30 months
given but reference should be made to the AD for confirmation of the mandated
accomplishment timescale.
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approv al 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.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 4
6
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### Page 9

@A300-600
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 556052-832-848-001: Inspection
Get Access
 7.50
On Aircraft
Do a DET of the Transverse Load Fittings at
accessible area and the Main Attachment Fittings
2.00
SDI of the Main Attachment Fittings of the Vertical
Stabilizer
4.00
Close-Up
 7.50
TOTAL MANHOURS
 21.00
ELAPSED TIME (HOURS)
 18.00
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 05-51-11 05-51-44 06-21-00
06-41-00 24-00-00 53-10-67
53-10-69 55-00-00 55-30-00
55-30-11 55-33-13 55-36-11
Elec. Std. Practices Manual (ESPM)
 20-55-00
In Service Information (ISI)
 00.00.00179
Non Destructive Test Manual (NTM)
 55-30-01
Structural Repair Manual (SRM)
 55-30-00
K. PUBLICATION AFFECTED
None
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 5
6
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@A300-600
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
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@A300-600
SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
No Material Set
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will credit the man hours indicated in this Service Bulletin for inspections that are
performed on aircraft in warranty at the time of such inspection. Credit will be at the agreed
in-house warranty labor rate. Claims for labor allowance should be received no later than 90
days after completion of the last affected warranted aircraft.
For those aircraft in warranty at the time of such inspection with findings further to
inspection as per this Service Bulletin, AIRBUS will credit the man hours indicated in this
Service Bulletin for corrections that are performed on aircraft in warranty at the time of
such correction. Credit will be at the agreed in-house warranty labor rate. Claims for labor
allowance should be received no later than 90 days after completion of the last affected
warranted aircraft.
C. LIST OF COMPONENTS
No Kit
D. LIST OF MATERIALS - OPERATOR SUPPLIED
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
None
(2) Tools
To accomplish this Service Bulletin it is necessary to use the tools listed in the
subsequent refe renced tasks:
- AMM 53-10-67, Page Block 401
- AMM 55-30-00, Page Block 301
- AMM 55-00-00, Page Block 001
- NTM 55-30-01.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 7
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@A300-600
SERVICE BULLETIN
NOTE
: For this Service Bulletin only parts of the Area A and Area B of the NTM
55-30-01 needs to be inspected.
Therefore, only the following tools listed in NTM 55-30-01 are necessary:
USM25
 Standard tool
MK2S 2 Mhz
 Transducer
N22YK66438
 Delay shoe with 10 degree delay
wedge
99A55307306000
 Calibration block
For any further details, refer to NTM 55-30-01.
(3) Special Tools
NOTE
: Any equivalent ultrasonic equipment may be used that satisfies the
requirements of this Service Bulletin procedure and provides solution for
the first and second back-wall echo on each of the calibration blocks.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 8
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@A300-600
SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 556052-832-848-001 - 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.
IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.
NOTE
: The accomplishment instructions of this Service Bulletin include procedures given
in other documents or in other sections of the Service Bulletin. When the words
’refer to’ are used and the operator has a procedure accepted by the local authority
he belongs to, the accepted alternative procedure can be used. When the words ’in
accordance with’ are used then the given procedure must be followed.
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. To allow more flexibility, the rule "refer to" and "in
accordance with" will apply to these paragraphs 3.C. and 3.D. 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
: This Service Bulletin contains the instructions for the on-aircraft maintenance
necessary to ensure the continued airworthiness of the aircraft.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 9
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SERVICE BULLETIN
For any deviations to the instructions, including RC paragraph contained herein,
contact AIRBUS for further instructions and approval.
NOTE
: The purpose of flowcharts 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.
Task Associated Data
Zone
320
From 263 to 264
From 311 to 312
Access
Door
 311AZ 311BZ 312AR
Panel
 323AL 323AR 323BL 323BR 325AL 325AR
Manpower
TOTAL MANHOURS
 21.00
ELAPSED TIME (HOURS)
 18.00
A. GENERAL
(1) Subtask 556052-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-21-00, Page Block 001
06-41-00, Page Block 001
(a) For the identification of zones, refer to AMM 06-21-00, Page Block 001.
(b) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.
(2) Subtask 556052-839-201-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
B. PREPARATION
(1) Subtask 556052-210-202-001 - Do a Check of th e Aircraft Maintenance Records
Manpower Resources
Skills
 NON SPECIFIC
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 10
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SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 05-51-11, Page Block 001
05-51-44, Page Block 001
55-30-11, Page Block 401
55-36-11, Page Block 601
(a) Check for the availability of the maintenance records since aircraft Entry Into
Service (EIS) within the threshold g iven in PLANNING INFORMATION paragraph
E.(2).
1
 If maintenance records are available and completeness is done:
a
 Check the maintenance record for the accomplishment of AMM 55-36-11,
Page Block 601.
NOTE
: Check the maintenance records if one of the following
tasks are performed and if the AMM 55-36-11, Page
Block 601 was applied:
- AMM 55-30-11, Page Block 401
(VERTICAL STABILIZER SPAR BOX
(REMOVAL/INSTALLATION)
- AMM 05-51-11, Page Block 001 (INSPECTION
AFTER HARD OR OVERWEIGHT LANDING)
- AMM 05-51-44, Page Block 001 (AFTER FLIGHT
WITH HIGH LATERAL LOADS) : Do a detailed visual
inspection of fuselage external surface under fin to
fuselage.
<1> If AMM 55-36-11, Page Block 601 is accomplished or the
accomplishment status is unknown:
<a> Do the SUBTASK 556052-941-201 001 Job Set-up to
accomplish DET of main attachment fittings and transverse
load fittings at accessible area and SDI of the main attachment
fittings.
<1> If AMM 55-36-11, Page Block 601 is not accomplished:
<a> No further action required in accordance with this Service Bulletin.
2
 If maintenance records are not available:
a
 Do the SUBTASK 556052-941-201 001 Job Set-up to accomplish DET of
main attachment fittings and transverse load fittings at accessible area
and SDI of the main attachment fittings.
(2) Subtask 556052-941-201-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 11
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References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
53-10-67, Page Block 401
53-10-69, Page Block 401
55-30-00, Page Block 301
55-33-13, Page Block 401
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page
Block 301.
(b) Before entering composite vertical stabilizer, do the Job Set-up procedure as
specified in the vertical stabilizer access precautions, refer to AMM 55-30-00, Page
Block 301.
(c) Put an access platform in position to get access to the inspection area.
(d) Remove the access panels 323AL, 323BL, 323AR and 323BR for access as
specified in the vertical stabilizer side fairings - removal/installation, refer to AMM
53-10-69, Page Block 401.
(e) Remove the trailing edge access panels 325AL and 325AR for access, refer to
AMM 55-33-13, Page Block 401.
(f) Remove dorsal fin, refer to AMM 53-10-67, Page Block 401.
C. PROCEDURE
(1) Subtask 556052-210-203-001 - Do a DET of the Transverse Load Fittings at
accessible area and the Main Attachment Fittings
Work Zones and Access Panels
Zone
 Access/Work location
320
 Access
 Panel 323AL, Panel 323BL, Panel 323AR, Panel
323BR, Panel 325AL, Panel 325AR
Work location
 Rib 1
From
 263
To
 264
From
 311
 Access
 Door 311AZ, Door 311BZ
To
 312
 Access
 Door 312AR
Manpower Resources
Manhours
 2.00
Minimum number of person
 2
Subtask elapsed time
 1.00
Skills
 NON SPECIFIC
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 12
6
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### Page 17

@A300-600
SERVICE BULLETIN
References
In Service Information (ISI)
 00.00.00179
Structural Repair Manual (SRM)
 55-30-00
Fig. A-GBBAA
DET of the Transverse Load Fittings at
accessible area and Main Attachment
Fittings for the Vertical Stabilizer
Sheet 01
Fig. A-GFAAA
Flowchart
Sheet 01
(a) Do a DET of the transverse load fittings and the main attachment fittings at
accessible area without removal of any parts as shown on Fig. A-GBBAA
 and
Fig. A-GFAAA
 within the threshold given in PLANNING INFORMATION paragraph
E.(2).
(b) If damage/delamination found out of SRM 55-30-00 allowable damage limits:
1
 Contact AIRBUS before next flight with a detailed damage description and
follow their instructions.
(c) If no damage/delamination found:
1
 Upload the completed Inspection Report sheet given in Appendix 01 -
Inspection Report in accordance with ISI 00.00.00179.
NOTE
: Uploading the Inspection Report sheet is not Required for
Compliance.
(2) Subtask 556052-220-203-001 - SDI of the Main Attachment Fittings of the Vertical
Stabilizer
Work Zones and Access Panels
Zone
 Access/Work location
320
 Access
 Panel 323AL, Panel 323BL, Panel 323AR, Panel
323BR, Panel 325AL, Panel 325AR
Work location
 Rib 1
From
 263
To
 264
Manpower Resources
Manhours
 4.00
Minimum number of person
 2
Subtask elapsed time
 2.00
Skills
 NON DESTRUCTIVE
TESTING
References
In Service Information (ISI)
 00.00.00179
Non Destructive Test Manual (NTM)
 55-30-01
Structural Repair Manual (SRM)
 55-30-00
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 13
6
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### Page 18

@A300-600
SERVICE BULLETIN
References
Fig. A-GBAAA
SDI of the Main Attachment Fittings for
the Vertical Stabilizer
Sheet 01
Sheet 02
Fig. A-GFAAA
Flowchart
Sheet 01
(a) Do an ultrasonic inspection of the main attachment fittings for the vertical stabilizer
as shown on Fig. A-GBAAA
 and Fig. A-GFAAA
 in accordance with NTM 55-30-01
within the threshold given in PL ANNING INFORMATION paragraph E.(2).
(b) If damage/delamination found out of SRM 55-30-00 allowable damage limits:
1
 Contact AIRBUS before next flight with a detailed damage description and
follow their instructions.
(c) If no damage/delamination found:
1
 Upload the completed Inspection Report sheet given in Appendix 01 -
Inspection Report in accordance with ISI 00.00.00179.
NOTE
: Uploading the Inspection Report sheet is not Required for
Compliance.
D. TEST
None
E. CLOSE-UP
(1) Subtask 556052-942-201-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 53-10-67, Page Block 401
53-10-69, Page Block 401
55-30-00, Page Block 301
55-33-13, Page Block 401
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Do the Close-up procedure as specified in the vertical stabilizer access precautions,
refer to AMM 55-30-00, Page Block 301.
(c) Install dorsal fin, refer to AMM 53-10-67, Page Block 401.
(d) Install the trailing edge access panels 325AL and 325AR, refer to AMM 55-33-13,
Page Block 401.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 14
6
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### Page 19

@A300-600
SERVICE BULLETIN
(e) Install the access panels 323AL, 323BL, 323AR and 323BR as specified in the
vertical stabilizer side fairings - removal/installation, refer to AMM 53-10-69, Page
Block 401.
(f) Remove the access platform(s).
(g) Put the aircraft back to its initial configuration.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 15
6
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### Page 20

@A300-600
SERVICE BULLETIN
**CONF ALL
Z311
Z312
LH
RH
Z320
A B
REAR SPAR
FRONT SPAR
A B
REAR SPAR
FRONT SPAR
FUSELAGE
FUSELAGE
C C
D D
E E
D_SB_556052_6_BAAA_01_03
Figure A-G BAAA - S heet 01
SDI of the Main Attachment Fittings for the Vertical Stabilizer
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 16
6
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### Page 21

@A300-600
SERVICE BULLETIN
**CONF ALL
NOTE:
INSPECTION AREA
50 mm
(1.969 in)
50 mm
(1.969 in)
50 mm
(1.969 in)
50 mm
(1.969 in)
REAR SPAR
STGR2
STGR4
RIB1
STGR10STGR12
STGR14
RIB1
STGR24
RIB1
C
D
E
TYPICAL
TYPICAL
TYPICAL
50 mm
(1.969 in)
FRONT SPAR
FRONT MAIN ATTACHMENT
FITTING
CENTER MAIN ATTACHMENT
FITTING
REAR MAIN ATTACHMENT
FITTING
50 mm
(1.969 in)
D_SB_556052_6_BAAA_02_02
Figure A-G BAAA - S heet 02
SDI of the Main Attachment Fittings for the Vertical Stabilizer
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 17
6
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### Page 22

@A300-600
SERVICE BULLETIN
**CONF ALL
A B
REAR SPAR
FRONT SPAR
REAR SPAR
FRONT SPAR
NOTE:
INSPECTION AREA
MAIN ATTACHMENT
FITTINGS
TRANSVERSE LOAD
ATTACHMENT FITTINGS
MAIN ATTACHMENT
FITTINGS
Z311
Z312
LH
RH
Z320
A B
D_SB_556052_6_BBAA_01_03
Figure A-G BBAA - S heet 01
DET of the Transverse Load Fittings at accessible area and Main Attachment Fittings for the
Vertical Stabilizer
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 18
6
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### Page 23

@A300-600
SERVICE BULLETIN
**CONF ALL
THE PURPOSE OF FLOWCHARTS 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.
01
NOTE:
CHECK THE MAINTENANCE RECORDS FOR THE ACCOMPLISHMENT OF AMM 55−36−11 PB 601 
THROUGH ONE OF THE FOLLOWING AMM TASK(S) APPLICATION:
− AMM 55−30−11 PB 401 (VERTICAL STABILIZER SPAR BOX (REMOVAL/INSTALLATION))
− AMM 05−51−44 PB 001 (AFTER FLIGHT WITH HIGH LATERAL LOADS):
DO A DETAILED VISUAL INSPECTION OF FUSELAGE EXTERNAL SURFACE UNDER FIN TO FUSELAGE.
− AMM 05−51−11 PB 001 (INSPECTION AFTER HARD OR OVERWEIGHT LANDING)
YES
55−36−11 PB 601
ACCOMPLISHED?
IS AMM
01
NO
NO
YES/
UNKNOWN
DO A ONE−TIME INSPECTION OF VTP ATTACHMENT
FITTING WITHIN THE THRESHOLD GIVEN IN PLANNING
INFORMATION PARAGRAPH E.(2)
CHECK THE AIRCRAFT MAINTENANCE RECORDS FOR THE
ACCOMPLISHMENT OF AMM 55−36−11 PB 601 WITHIN THE
THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2)
REMOVE THE DORSAL FIN, SIDE FAIRING AND LOWER
PART OF THE TRAILING EDGE PANEL
DO A DET OF TRANSVERSE LOAD FITTINGS AND THE
MAIN ATTACHMENT FITTINGS AT ACCESSIBLE AREAS
DELAMINATION FOUND OUT OF
SRM 55−30−00 LIMITS?
IS DAMAGE OR
YES
CONTACT AIRBUS AND FOLLOW
THEIR INSTRUCTIONS
SEND INSPECTION
REPORT TO AIRBUS
NO FURTHER ACTION
NO
DO AN ULTRASONIC INSPECTION OF THE MAIN
ATTACHMENT FITTINGS OF THE VERTICAL STABILIZER INSTALL THE DORSAL FIN, SIDE FAIRING
AND LOWER PART OF THE TRAILING EDGE PANEL
MAINTENANCE RECORDS
AVAILABLE SINCE THE AIRCRAFT
ARE THE COMPLETE
ENTRY INTO SERVICE?
D_SB_556052_6_FAAA_01_05
Figure A-GFAAA - Sheet 01
Flowchart
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 19
6
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### Page 24

@A300-600
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 20
6
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### Page 25

@A300-600
SERVICE BULLETIN
Appendix 01 - Inspection Report
**CONF ALL
For an explanation of inspection report of the main attachment fittings and transverse load fittings at
accessible area for the vertical tail plane, refer to the next page(s).
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 1
6
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### Page 26

@A300-600
SERVICE BULLETIN
Appendix 01 - Inspection Report
**CONF ALL
INSPECTION REPORT
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES :
FLIGHT HOURS :
A300−600−55−6052
DATE OF INSPECTION :
INSPECTION METHOD : DETAILED
INSPECTION
UPLOAD THE COMPLETED INSPECTION REPORT
SHEET IN ACCORDANCE WITH ISI 00.00.00179
IF DAMAGE/DELAMINATION FOUND OUT OF SRM 55−30−00
REMARKS:
FRONT CENTER REAR
LOCATION
YES NO YES NO YES NOTRANSVERSE LOAD FITTING ATACCESSIBLE AREA
MAIN ATTACHMENT FITTING LH
MAIN ATTACHMENT FITTING RH
YES NO YES NO YES NO
YES NO YES NO YES NO
DETAILED INSPECTION OF THE TRANSVERSE LOAD AND THE MAIN ATTACHMENT FITTINGS
D_SB_556052_6_AAAA_01_02
Figure A-G AAAA - S heet 01
Inspection Report
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 2
6
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### Page 27

@A300-600
SERVICE BULLETIN
Appendix 01 - Inspection Report
**CONF ALL
INSPECTION REPORT
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES :
FLIGHT HOURS :
A300−600−55−6052
DATE OF INSPECTION :
INSPECTION METHOD : SPECIAL DETAILED
INSPECTION
UPLOAD THE COMPLETED INSPECTION REPORT
SHEET IN ACCORDANCE WITH ISI 00.00.00179
IF DAMAGE/DELAMINATION FOUND OUT OF SRM 55−30−00
REMARKS:
FRONT CENTER REAR
LOCATION
MAIN ATTACHMENT FITTING LH
MAIN ATTACHMENT FITTING RH
YES NO YES NO YES NO
YES NO YES NO YES NO
SPECIAL DETAILED INSPECTION OF THE MAIN ATTACHMENT FITTINGS OF THE VERTICAL STABILIZER
D_SB_556052_6_AAAA_02_02
Figure A-G AAAA - S heet 02
Inspection Report
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 3
6
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### Page 28

@A300-600
SERVICE BULLETIN
Service Bulletin REPORTING
TITLE: STABILIZERS - VERTICAL STABILIZER - INSPECT THE VERTICAL
TAIL PLANE COMPOSITE ATTACHMENT FITTINGS
MODIFICATION No.: None
SB Reporting status
This Service Bulletin will only be incorporated into affected customized Maintenance and Flight
Operations Products if it is duly reported to Airbus.
General information
The SB Reporting policy is published in ISI 00.00.00135. This document provides information regarding:
the SB Reporting means and benefits, the update of customized Maintenance Products and customized
Flight Operations Products.
If this Service Bulletin has an operational impact, refer to paragraph "Flight Operations Products" for
further information on the update of affected Flight Operations Products.
SB Reporting procedure
Standard practice to report SB is to use the online reporting application on AirbusWorld.
Refer to ISI 00.00.00179:
- For complete information on reporting means to Airbus. Question 2 "What are the standard
practices for SB reporting?"
- If this SB requires previous or simultaneous accomplishment of other SBs, Question 3 "What about
the reporting of prerequisite Service Bulletin?"
NOTE:
 ISI 00.00.00179 covers all the frequently asked questions about SB Reporting. It is revised on a
regular basis.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 1
6
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### Page 29

@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
F A X:( 3 3 )56 19 34 25 1
Or via your Resident Customer Support Office.
DATE: Aug 31/18 SERVICE BULLETIN No.: A300-55-6052
REVISION No.: 00 - Aug 31/18 Page: 1
6
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---
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