# Airbus Service Bulletin A300-57-6010

Copy: Revision 05 ("FAA-2015-6550_SB A300-57-6010_Rev5"), 19 pages: PDF https://openairdocs.org/files/sha256/08/80/08807f175d227de46e51130ea4a80a56b8c86f0f18a7c85705ae58cb9d5f9d0b; text https://openairdocs.org/service-documents/airbus/a300-57-6010/file/08807f175d22.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-6550; AD 2016-18-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A300-57-6010
- Latest revision known: A300-57-6010, Revision 05, dated February 21, 2011 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-57-6010

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2016-18-08](https://openairdocs.org/ad/2016-18-08.md), effective Oct 20, 2016: Revisions 1, 02, 03, 04 and 05

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a300-57-6010/proposed.md).

## Text (19 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-6550; AD 2016-18-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1 (OCR)

A300 - 600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
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 : 57
TITLE : WINGS - INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET
MODIFICATION No. : None
This page transmits revision No. 05 of Service Bulletin A300-57-6010.
ADDITIONAL WORK
No additional work is required by this revision for aircraft inspected by any
previous revision.
REASON
This Service Bulletin has been issued to inform Operators that Flight Hours (FH)
conversion figures have been added to the Accomplishment Timescale. In addition a
maximum crack length has been included.
CHANGES
SUMMARY :
. AIRBUS address has been amended.
. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
. Text has been amended.
- EFFECTIVITY
. Effectivity has been updated.
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. : 05 Feb 21/11  PAGE : 1
Printed in France

### Page 2 (OCR)

• A300 - 600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
SERVICE BULLETIN:
- AIRBUS address has been amended.
. Copyright statement has been moved below TITLE and Airbus Industrie has
been changed to AIRBUS.
- PLANNING INFORMATION
- EFFECTIVITY
. Para. (2) (a) Effectivity has been updated.
. Para. (2) (b) Effectivity has been updated.
. Para. (2) (c) Effectivity by MSN and
kit/configuration has been added.
- REASON
. Para. 8. (5) Text has been amended.
- APPROVAL
. Approval statement has been amended
. MATERIAL-COST AND AVAILABILITY
. AIRBUS address has been amended.
- ACCOMPLISHMENT INSTRUCTIONS
- INSPECTION
. Para. (4) (a) and (b) FH conversion figures have been added.
. Para. (4) (b) and (c) Allowable critical crack length limit has been added.
. AI/SE-A has been changed to AIRBUS.
- CLOSE UP
- Para. (6) Airbus Industrie and AI/SE-A have been changed to AIRBUS.
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. : 05 Feb 21/11  PAGE : 2
Printed in France

### Page 3 (OCR)

» A300 - 600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
ACCEPTANCE/REJECTION SHEET:
. AIRBUS address has been amended.
FILING INSTRUCTIONS
1. Remove and destroy pages 1, 2 and 3 of the Summary and pages 1, 2, 3, 4, 5, 6,
7, 8 and 9 of the Service Bulletin and page 1 of the Acceptance/Rejection sheet.
2. Insert pages 1, 2,  3 and 4 of the Summary and pages 1, 2, 3, 4, 5, 6, 7, 8, 8A,
8B and 9/10 of the Service Bulletin and page 1 of the Acceptance/Rejection
sheet.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
This is only applicable for Revision 05 and subsequent. If information is required
for revisions issued previous to this, please check your copies of Revision
Transmittal Sheet or contact AIRBUS.
REVISION SEQUENCE
ORIGINAL : Dec 17/86
REVISION No. : 01 - Dec 14/90
REVISION No.  : 02 - Mar 30/98
REVISION No. : 03 - Sep 16/98
REVISION No. : 04 - Feb 22/99
REVISION No. : 05 - Feb 21/11
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. : 05 Feb 21/11  PAGE : 3/4
Printed in France

### Page 4 (OCR)

4300 - 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 : 57
TITLE: WINGS - INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET
MODIFICATION No. : NONE
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
An ALL Operator Telex (AOT) 57/86/01 has been issued to all A300 Operators requesting
inspection of the aft hinge brackets of the outer shroud box. This inspection revealed
that approximately half of all the brackets inspected were cracked.
This Inspection Service Bulletin introduces a visual inspection of the forward and aft
outer shroud box hinge brackets for cracks or complete fracture of the bracket.
Accomplishment of this Service Bulletin will lead to the early detection of the cracks in
the shroud box hinge brackets and will prevent the fracture of the brackets.  Fracture of
a bracket would allow vertical movement of the inner shroud box structure in the
immediate area which could result in damage to the top skin of the inboard flap.
Additionally, the loads carried through the brackets will be transferred to the remaining
supports which may also crack and cause extensive structural damage.
A detailed visual inspection is necessary of the shroud box hinge brackets.
The inspection thresholds and repeat intervals are given in this Service Bulletin. In
addition a maximum crack length is included.
The inspection of the forward and aft brackets is only applicable to aircraft which are
pre production Mod. No. 06661H1033.
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 Feb 21/11  PAGE : 1
Printed in France

### Page 5 (OCR)

A300 - 600
SERVICE BULLETIN
SUMMARY
NOTE:  The original issue of this Service Bulletin did not specify an inspection of
the forward hinge brackets. If the inspection of the forward hinge brackets,
in accordance with this Service Bulletin at Revision 01 or any later approved
revision, was not done before accomplishment of Service Bulletin A300-57-6011
(Mod. 06661) you must do an inspection of the forward hinge brackets within
Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an
Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The
AD must be used as the reference document for the mandatory accomplishment timescale.
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. : 05 Feb 21/11  PAGE : 2
Printed in France

### Page 6 (OCR)

A300-600
SERVICE BULLETIN
SUMMARY
EFFECTIVITY
This Service Bulletin is applicable to these customers :
AAL, AAW, DLH, F2I, FDX, IRM, KAC, THA
SERVICE BULLETIN TO BE ACCOMPLISHED
PREVIOUSLY OR  SIMULTANEQUSLY
None
REFERENCES/REPERCUSSIONS
TFU  : 572200001
OEB  : None
AOT  : 57/86/01
SIL  : None
LIFE  LIMIT  : None
LINE MAINTENANCE AFFECTED  : None
OTHER  : None
NATURE OF THE WORK
AIRCRAFT  Yes
EQUIPMENT  No
HARD  No
SOFT  No
OBRM  No
COMPLIANCE
Mandatory
MANPOWER
Aircraft
TOTAL MANHOURS  8.0
ELAPSED TIME (HOURS)  4.0
MATERIAL INFORMATION
AIRCRAFT DATA
None
EQUIPMENT DATA
None
APPENDICES
None
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 3
Printed in France

### Page 7 (OCR)

5, 4300-600  SUMMARY
INNER SHROUD BOX
OUTER SHROUD BOX
FLAP TRACK
/ BEAM No 2
INNER SHROUD BOX
RIB 9
FORWARD
OUTBOARD  FORWARD HINGE
BRACKET
OUTER SHROUD BOX
REAR HINGE BRACKET
JOINT LINE
USUAL STARTING POINT
OF CRACKS
CRACK IN VERTICAL
WEB RADIUS
CRACK IN VERTICAL FLANGE
UNDER BEARING ASSY. NUT
EXAMPLE 'A'
EXAMPLE 'B'
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 4
Printed in France

### Page 8 (OCR)

• 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 : 57
TITLE :  WINGS - INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET
MODIFICATION No. : NONE
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain
the property of AIRBUS; no intellectual property right or license 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
A.  EFFECTIVITY
(7)  Models
B4-601, B4-603, B4-605R, B4-620, B4-622, C4-620
(2)  Aircraft
(a)  Effectivity by MSN
The Service Bulletin is applicable to aircraft MSN:
0284  0294 0301 0307 0312 0317 0321 0336 0344 0348
0351  0354 0358 0361 0365 0368 0380 0398 0401 0405
0408  0411 0414 0423
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 Feb 21/11  PAGE : 1
Printed in France

### Page 9 (OCR)

© A300 - 600
SERVICE BULLETIN
NOTE: This Service Bulletin is only applicable to aircraft which
are pre production Modification No. 0661H1033.  Modification
No. 06661H1033 has been embodied on aircraft MSN 388, 417,
420, 459 and subsequent.
(b)  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 further 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
AAL  0423
AAW  0354
DLH  0380 0401 0405
F2I  0284 0294 0301  0307 0312 0317
0321 0336 0348 0351 0408
FDX  0358 0361 0365
IRM  0411 0414
KAC  0344
THA  0368 0398
(c) Effectivity by MSN and Kit/Configuration
None
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. : 05 Feb 21/11  PAGE : 2
Printed in France

### Page 10 (OCR)

SERVICE BULLETIN  A300-600
(3) Spares
None
B. REASON
(1) History
An All Operator Telex (A0T) 57/86/01 has been issued to all A300
Operators requesting inspection of the aft hinge brackets of the
outer shroud box. This inspection revealed that approximately half
of all the brackets inspected were cracked or completely fractured.
Fracture of the bracket would allow vertical movement of the inner
shroud box structure in the immediate area  which could result in
damage to the top skin of the inboard flap. Additionally, the loads
carried through the brackets will be transferred to the remaining
supports which may also crack and cause extensive structural
damage.
There is also some evidence of un-reported fractures of the forward
hinge bracket of the outer shroud box.
Pre production  and retro Modification No. 06661H1033 (Service
Bulletin A300-57-6011) have been introduced which replace the
aluminium alloy aft bracket with a steel bracket.
(2)  Objective/Action
A mandatory detailed visual inspection is required of the LH and RH
outer shroud box hinge brackets to detect any cracks or complete
fracture of the brackets on aircraft pre production
Mod. No. 06661H1033.
NOTE :  The original issue of this Service Bulletin did not specify
an inspection of the forward hinge brackets. If the
inspection of the forward hinge brackets, in accordance
with this Service Bulletin at Revision 01 or any later
approved revision, was not done before accomplishment of
Service Bulletin A300-57-6011 (Mod. 06661) you must do an
inspection of the forward hinge brackets within 18 months
from accomplishment of the modification.
(3) Advantages
Accomplishment of this Service Bulletin will lead to the early
detection of the cracks in the shroud box hinge brackets and will
prevent the fracture of the brackets.
(4)  Operational/Maintenance Consequences
None.
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/1  PAGE : 3

### Page 11 (OCR)

• A300 - 600
SERVICE BULLETIN
(5)  Accomplishment Timescale
Accomplishment of this Service Bulletin has been rendered mandatory by
the issue of an Airworthiness Directive (AD) published by the European
Aviation Safety Agency (EASA). The AD must be used as the reference
document for the mandatory accomplishment timescale.
For those aircraft that are pre Modification No. 06661H1033 a
detailed visual inspection is to be done on the forward and aft
hinge brackets of the outer shroud box not Later than 5,000 FC or
10,400 FH. For aircraft already within the inspection program, the
inspection must be completed within the next interval period. However,
where the FH limit only has been exceeded the inspection may be extended
to the previously planned FC inspections.
The repeat visual inspection intervals are as follows:
- If no cracks are found on either the forward or aft hinge
brackets, do the repeat inspection every 1,000 FC or 2,000 FH
until the Service Bulletin A300-57-6011 (Mod. 06661H1033) is
embodied.
- If a crack not more than 8 mm in length is found in one half bracket,
do the repeat inspection every 50 FC or 100 FH until replacement of the
damaged hinge bracket.
- If the crack length is more than 8 mm or both half brackets are cracked
or a hinge bracket has fractured, replace the bracket before the next
flight.
The inspection thresholds and repeat inspection intervals are the same
for aircraft subject to normal range or short range operation.
NOTE :  Each hinge bracket (forward and aft) is manufactured from two
half brackets joined at the vertical face of the flange which
supports its bearing assembly.
C. DESCRIPTION
To accomplish this Service Bulletin it is necessary to:
(1)  Get access to both the LH and RH inner and outer shroud boxes, forward
and aft hinge brackets.
(2)  Do a detailed visual inspection of the hinge brackets.
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 Feb 21/11  PAGE : 4
Printed  in France

### Page 12 (OCR)

» A300 - 600
SERVICE BULLETIN
(3)  Repair by replacement, as necessary.
(4)  If a bracket is cracked do additional visual inspections for secondary
damage of the support structure, attachment brackets and the top skin of
the inboard flap in the area of the inner and outer shroud boxes.
(5)  Close-up after the work is accomplished.
D. APPROVAL
Approved under EASA Design Organisation Approval No. EASA. 21J.031.
If an aircraft listed in the effectivity has a modification or repair that is not
of AIRBUS origin, and which effects 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.
E -  MANPOWER
This Inspection Service Bulletin is written for an aircraft in a maintenance
condition. The manhours/elapsed time does not include time to prepare for the
inspection, non-productive elapsed time, repair or administration.
On aircraft
Get access  2.0
Inspection  4.0
Close-up  2.0
TOTAL MANHOURS  8.0
ELAPSED TIME (HOURS)  4.0
F.  MATERIAL - COST AND AVAILABILITY
If replacement brackets are required send a Spares Purchase Order, quoting this
Service Bulletin number, to:
AIRBUS
MATERIAL SUPPORT CENTER
P.O. BOX 630262
22312 HAMBURG
GERMANY
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 Feb 21/11  PAGE : 5
Printed in France

### Page 13 (OCR)

© A300 - 600
SERVICE BULLETIN
G. TOOLING - PRICE AND AVAILABILITY
None
H. WEIGHT AND BALANCE
Not changed
I. REFERENCES
Aircraft Maintenance Manual (AMM)  : 06-41-57, 24-00-00, 27-50-00,
27-61-54
Service Bulletin (SB)  A300 - 57-6011
J. PUBLICATIONS AFFECTED
None
DATE: Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. : 05 Feb 21/11  PAGE : 6
Printed in France

### Page 14 (OCR)

A300-600
SERVICE BULLETIN
2. ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL
WARNING :  MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE
CAUTIONS IN THE REFERENCED PROCEDURES.
WARNING :  PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION
BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND RELATED DOORS
- COMPONENTS THAT MOVE.
WARNING :  MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL
SURFACES ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A
HYDRAULIC SYSTEM.
WARNING :  MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED
BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.
(1) Preparation
(a) Make sure that the aircraft is electrically grounded (Refer to
AMM: 24-00-00, P. Block 301).
(b) Put warning notices in the flight compartment to tell persons
not to operate the flight controls.
(c) Put the safety barriers in position.
(d) Extend the flaps (Refer to AMM: 27-50-00, P. Block 301).
(e) Extend the spoilers 1 and 2 (Refer to AMM: 27-61-54, P. Block
401>.
(f) Remove  and retain the access panels 577CT, 577DT (LH) and
677CT, 677DT (RH), (Refer to AMM: 06-41-57, P. Block 1).
(g) Get access to the Inner Shroud Box forward attachments through
the Main Landing Gear Bays.
(2) Standard Practices
None
B. INSPECTION
The procedure that follows is applicable to the (LH) and (RH) wings.
Refer to Figure 1
(1) Cleaning:
Clean the area to be inspected with Cleaning Agent (Mat. No. 11-026).
(2)  Get access  from the top surface of the wing through the gap between
the inner and outer shroud boxes. Move the seal between the shroud
boxes, as necessary, to visually inspect the top of the outer
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 7
Printed in France

### Page 15 (OCR)

A300-600
SERVICE BULLETIN
shroud-box hinge brackets.
(3) Do a detailed inspection of the outer shroud-box forward and aft
hinge bracket assemblies, as follows:
(a)  Inspect the small radius between the top flange and the
vertical flange, as shown in example 'A' and example 'B' of
Figure 1, for signs of cracks on the hinge bracket.
(b)  Get access from the lower surface of the wing and with the use
of an inspection mirror, visually inspect both halves of the
hinge brackets for signs of cracks or fracture of the bracket.
NOTE 1 : Each hinge bracket (forward and aft) is manufactured
from two half brackets joined at the vertical  face of
the flange which supports its bearing assembly.
NOTE 2 : The cracks can start in either of the two half brackets
and run down the vertical web radius (example 'A' of
Figure 1), or run through the vertical flange under
the bearing assembly attachment nut (example  'B' of
Figure 1).
(4) Use the results of the inspection to do one or more of the worksteps
that follow:
If no cracks are found on either the forward or aft hinge brackets, do the
repeat inspection every 1,000 FC or 2,000 FH or until Service Bulletin
A300-57-6011 (Modification 06661H1033) is embodied.
If a crack not more than 8 mm in length is found in one half bracket, do
the repeat inspection every 50 FC or 100 FH (whichever comes first) until
a repair is done, as detailed in Para. C. REPAIR.
(c) If the crack length is more than 8 mm or both half brackets are cracked or
a hinge bracket has fractured, do a repair as detailed in Para. C. REPAIR.
(d) If a crack is found in one half bracket or both half brackets,
do a visual inspection for secondary damage in the areas that
follow:
1 The inner shroud-box forward attachments and the attachment
brackets at the inboard end.
2  The inner and outer shroud-box structure, adjacent to the
fractured bracket.
3 The top skin of the inboard flap.
NOTE :  If any damage is found contact AIRBUS for an
applicable repair procedure.
(5)  If Service Bulletin A300-57-6011 (Modification 06661H1033) has been
embodied after the fracture of the aft hinge bracket, then visually
inspect the forward hinge bracket for cracks immediately after the
embodiment of the modification.
If this modification was embodied before the receipt of Revision 01
of this Service Bulletin, you must do a once only inspection of
the forward hinge brackets within 18 months from the embodiment
of the modification.
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 8
Printed in France

### Page 16 (OCR)

A300-600
SERVICE BULLETIN
C. REPAIR
(1) If a crack is found in one half bracket, less than 8mm the bracket
should be:
- replaced as soon as a replacement part is available, or
- Service Bulletin A300-57-6011 (Modification 06661H1033) should
be embodied.
(2) If both half brackets are cracked or the hinge bracket has fractured
or cracks are greater than 8mm in one half bracket:
- replace the damaged hinge bracket before the next flight or
- embody Service Bulletin A300-57-6011 (Modification No. 06661H1033)
before the next flight.
D. TEST
None
E. CLOSE-UP
(1) Make sure that the work area is clean and clear of tools and other
items of equipment.
Install the access panels 577CT, 577DT (LH) and 677CT, 677DT (RH),
(Refer to AMM: 06-41-57, P. Block 1).
(3)  Retract the spoilers 1 and 2 (Refer to AMM: 27-61-54, P. Block 401).
(4)  Retract the flaps (Refer to AMM: 27-50-00, P. Block 301).
(5)  Remove the safety barriers and the warning notices.
(6)  Results of the inspections, including NIL findings, should be sent
immediately to AIRBUS.
NOTE: AIRBUS requests the return of the fractured hinge brackets
for investigation.
F. DOCUMENTATION
Write in the applicable aircraft records that you have done all the work
given in this Service Bulletin.
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 8A
Printed in France

### Page 17 (OCR)

G A300-600
SERVICE BULLETIN
INNER SHROUD BOX
OUTER SHROUD BOX
FLAP TRACK
/ BEAM No 2
INNER SHROUD BOX
RIB 9
FORWARD
OUTBOARD  FORWARD HINGE
BRACKET
OUTER SHROUD BOX
REAR HINGE BRACKET
JOINT LINE  USUAL STARTING POINT
OF CRACKS
CRACK IN VERTICAL
WEB RADIUS
CRACK IN VERTICAL FLANGE
UNDER BEARING ASSY. NUT
EXAMPLE 'A'
EXAMPLE 'B'
Outer Shroud Box Hinge Brackets - Inspection area
Figure 1 Sheet 1
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 8B
Printed in France

### Page 18 (OCR)

A300-600
SERVICE BULLETIN
3. MATERIAL INFORMATION
A. LIST OF COMPONENTS
None
B.  SPECIAL TOOLS
None
C. LIST OF MATERIAL - OPERATOR SUPPLIED
DESCRIPTION  REFERENCE TO CML  QTY PER A/C
Cleaning agent  (Mat. No. 11-026)  As required
D. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 9/10
Printed in France

### Page 19 (OCR)

A300-600
SERVICE BULLETIN
ACCEPTANCE/REJECTION SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice BELLONTE
31707 BLAGNAC CEDEX FRANCE
Tel: (33) 5 61-93-33-33
Telex: AIRBU 530526 F
TITLE : WINGS - INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET
MODIFICATION No. :  NONE  ATA SYSTEM : 57
IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW
Please fill :  ... REJECTED
...WILL BE EMBODIED
...EFFECTIVITY
This SB can only be incorporated in your "customized"
documentation within the agreed time schedule in so far as this
sheet  returned to us  on purchase date  and signed by a duly
authorized  and empowered officer or  representative.
FROM :  Please return to :
AIRLINE :  AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
NAME :  31707 BLAGNAC CEDEX FRANCE
Attn : AI/SE-D32 Technical Data
DATE :  and Documentation Services
FAX : (+33) 5 61 93 28 06
7 DATE : Dec 17/86  SERVICE BULLETIN No. : A300-57-6010
REVISION No. :  05 - Feb 21/11  PAGE : 1 of 1
Printed in France

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