# Airbus Service Bulletin 55-2051

Copy: Revision 1 ("FAA-2014-1045 SB 55-2051-R1"), 119 pages: PDF https://openairdocs.org/files/sha256/35/d9/35d90094361b4951b84c35cf9e3438871ea5f5aff5c2a4bd7b17af8836c2f33a; text https://openairdocs.org/service-documents/airbus/sb-55-2051/file/35d90094361b.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-1045, the docket of AD 2016-01-13. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: 55-2051
- Latest revision known: 55-2051, Revision 1 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/sb-55-2051

## Text (119 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-1045, the docket of AD 2016-01-13. Not covered by OpenAirDocs’ CC0 dedication. Some pages are 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

@A310
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
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 - RUDDER S IDE SHELL SANDWICH REPAIR
INSPECTION
MODIFICATION No.: None
This page transmits Revision No.01 of Service Bulletin No.A310-55-2051
ADDITIONAL WORK
**CONF ALL
No additional work is required by this revision for aircraft modified by any previous issue.
REASON
Revision No. 01 issued to embody the local sanding procedure.
CHANGES
NOTE
: Revision bars against references not identified in the CHANGES paragraph appear due
to format changes introduced by new authorities’ rules.
SUMMARY
REASON/DESCRIPTION/OPERATIONAL
CONSEQUENCES
REASON UPDATED
 R
EFFECTIVITY
 OPERATOR LIST UPDATED
 R
REFERENCES / REPERCUSSIONS
 REFERENCES/REPERCUSSIONS TABLE
UPDATED
R
PLANNING INFORMATION
EFFECTIVITY
 EFFECTIVITY RELATED INFORMATION
UPDATED
R
Configuration definition
CONF 001
 CONFIGURATION DEFINITION UPDATED
 R
REASON
History
 HISTORY UPDATED
 R
COMPLIANCE
Accomplishment Timescale
 ACCOMPLISHMENT TIMESCALE UPDATED
 R
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A310
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
MANPOWER
 MANPOWER UPDATED
 R
REFERENCES
 REFERENCED DOCUMENTATION UPDATED
 R
MATERIAL INFORMATION
LIST OF MATERIALS - OPERATOR
SUPPLIED
Consumable Materials
Consumable CMLD01
 CONSUMABLE MATERIAL SET UPDATED
CONSUMABLE UPDATED
R
TOOLING
Tools
 TOOLS UPDATED
 R
ACCOMPLISHMENT INSTRUCTIONS
TASK 552051- 832-848-001-Inspection
 TASK SOLUTION UPDATED
NOTE UPDATED
R
Subtask 552051-910-201-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
MATERIAL LIST UPDATED
REFERENCED DOCUMENTATION UPDATED
R
Subtask 552051-941-201-001
 SUBTASK SOLUTION UPDATED
NOTE UPDATED
R
Subtask 552051-832-201-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
R
Subtask 552051-832-202-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
MATERIAL LIST UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
R
Subtask 552051-832-203-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
MATERIAL LIST UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
R
Subtask 552051-832-204-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
CONFIGURATION UPDATED
MATERIAL LIST UPDATED
R
Subtask 552051-832-205-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
MATERIAL LIST UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
REFERENCES UPDATED
R
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A310
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 552051-832-206-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
R
Subtask 552051-832-207-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
MATERIAL LIST UPDATED
REFERENCED DOCUMENTATION UPDATED
NOTE UPDATED
REFERENCES UPDATED
R
Subtask 552051-833-201-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
REFERENCED DOCUMENTATION UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 552051-832-208-001
 SUBTASK SOLUTION ADDED
 N
Subtask 552051-942-201-001
 SUBTASK SOLUTION UPDATED
 R
Fig. A-GBCAA
Fig. A-GBCAA Sheet 02
 SHEET UPDATED
 R
Fig. A-GBFAA
Fig. A-GBFAA Sheet 02
 SHEET UPDATED
 R
Fig. A-GBHAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-GBHAA Sheet 01
 SHEET UPDATED
 R
Fig. A-GBHAA Sheet 02
 SHEET UPDATED
 R
Fig. A-GBHAA Sheet 03
 SHEET UPDATED
 R
Fig. A-GBHAA Sheet 04
 SHEET UPDATED
 R
Fig. A-GBHAA Sheet 05
 SHEET UPDATED
 R
Fig. A-GBHAA Sheet 06
 SHEET ADDED
 N
Fig. A-GFAAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-GFAAA Sheet 01
 SHEET UPDATED
 R
Fig. A-GFAAA Sheet 02
 SHEET UPDATED
 R
Fig. A-GFAAA Sheet 03
 SHEET UPDATED
 R
Fig. A-GFAAA Sheet 04
 SHEET UPDATED
 R
Fig. A-GFAAA Sheet 05
 SHEET UPDATED
 R
Fig. A-GFAAA Sheet 06
 SHEET ADDED
 N
Fig. A-GAAAA
Fig. A-GAAAA Sheet 01
 SHEET UPDATED
 R
Fig. A-GABAA
Fig. A-GABAA Sheet 04
 SHEET UPDATED
 R
Fig. A-GABAA Sheet 08
 SHEET UPDATED
 R
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A310
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
FILLING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
No previous revision
REVISION SEQUENCE
ORIGINAL: Sep 11/12
REVISION No. : 01 - Aug 20/14
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A310
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 - RUDDER S IDE SHELL SANDWICH REPAIR
INSPECTION
**CONF ALL
MODIFICATIONS
None
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
On AIRBUS Single Aisle, Long Range and Wide Body family aircraft, the rudder side shell is a
sandwich structure made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic
(GFRP) with a honeycomb core. A case of skin damage was reported on a composite side panel of a
rudder installed on an A310 aircraft. Investigations have shown that the damage started from a skin
panel area previously repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig.
204 procedure. The new damage has been identified as a damage between the core and the skin in
the repaired area. This new damage has developed during normal operations due to the variation of
pressure during ground-air-ground cycles.
Following the above mentioned damage scenario, it has been identified that SRM procedures need to
be improved to ensure an adequate repair quality. An improper bonding between skin and core during a
repair may lead to a damage initiation and propagation, which may not be detectable visually. A large
rudder damage, resulting from an undetected damage growth, could affect the handling quality of the
aircraft.
This Service Bulletin details the inspection procedure to inspect affected rudders fitted on A310 aircraft
for potential damage.
Different inspection procedures are necessary:
- Pulse thermography inspection
- Elasticity Laminate Checker (ELCH) inspection
- Ultrasonic Testing (UT) inspection.
- Tap test inspection.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A310
SERVICE BULLETIN
SUMMARY
The accomplishment of this Service Bulletin will contribute to detect potential damage on rudders
made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a
honeycomb core.
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.
MATERIAL PRICE INFORMATION
No Material
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
18T 19U 40T
 58X 82Z 85Z 98W
 99Y AFG AIC BBC C9L CFC
DGA F2I
 FDX GAF HFY IRA IRM IYE K1P KAC KZU MGL PCA
PIA QAF R1T RJA ROT RZO SGX SUD
 THY TSC UBD UZB WHT
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 None
SIL
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 OIT 999.0017/10 OIT 999.0070/10 OIT 999.0130/06 OIT
999.0067/12 AD 2014-0026
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A310
SERVICE BULLETIN
SUMMARY
MANPOWER
Task 552051-832-848-001: Inspection
TOTAL MANHOURS
 38.00
APPENDICES
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A310
SERVICE BULLETIN
SUMMARY
**CONF ALL
Z326
AA
RUDDER SHELL
TO BE INSPECTED
B
AB
LH SHOWNRH SHOWN
B_SB_552051_6_SAAA_01_00
Figure A-GSAAA - Sheet 01
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A310
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 - RUDDER S IDE SHELL SANDWICH REPAIR
INSPECTION
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 applicable to all rudders with the Serial Number (SN)
from HF-1005 to HF-1323, HF-1325, HF-1327, HF-1329, HF-1331, HF-1332,
HF-1340, TS-1324, TS-1326, TS-1328, TS-1330, TS-1333 to TS-1339,
TS-1341 to TS-1420 or TS-2001 to TS-2197.
NOTE
: Repairs of rudder side shells which have been accomplished in accordance
with a SRM procedure older than SRM December 2009 revision, must be
inspected in accordance with this Service Bulletin.
NOTE
: In the case of a rudder originally fitted on one aircraft (refer to AIR delivery
document) that has been removed and installed on another aircraft, it is the
responsibility of the operator to apply the required instructions contained in
this Service Bulletin to the new aircraft.
NOTE
: In case of doubt, contact AIRBUS.
(1) Models
310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 1
6
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### Page 10

@A310
SERVICE BULLETIN
(2) Effectivity by MSN
0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356
 0362 0364 0369
0378
 0394 0399
 0407
 0413 0418-0419 0421-0422 0425 0431 0434 0436-0437 0439
0441 0444-0447
 0449
 0452 0454 0456-0458 0467 0472-0473 0478 0480
 0482-0484
0488-0492 0494-0500 0503
 0519-0520 0522-0524 0526-0527 0537
 0539
 0545
 0547
0549-0552 0562 0564-0565 0567-0568 0571 0574
 0576 0585-0588 0590-0595 0597
0599-0600 0620 0622 0624 0636 0644 0646-0649
 0651-0653
 0656 0658 0660-0661
0663 0667 0671-0672 0674 0676 0678 0682 0687
 0689 0691 0700 0702 0704 0706
(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
18T
 0473
19U
 0399
40T
 0413
58X
 0431
82Z
 0550 0551
85Z
 0527
98W
 0495
99Y
 0489
AFG
 0496 0497
AIC
 0407
BBC
 0594 0700
C9L
 0652
CFC
 0425 0441 0444 0446 0482
DGA
 0418 0421 0422
F2I
 0520
FDX
 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356
0362 0364 0369 0378 0394 0439 0449 0452 0454 0456 0457 0458
0467 0492 0500 0539 0549 0552 0593
GAF
 0434 0484 0498 0503 0522 0523
HFY
 0565
IRA
 0436 0671
IRM
 0488 0499
 0524 0537 0547
 0564 0567 0586 0595 0620
IYE
 0568 0702 0704
K1P
 0648
KAC
 0647 0649 0663
KZU
 0592 0622 0646
MGL
 0526
PCA
 0419
PIA
 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691
QAF
 0667
R1T
 0591
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A310
SERVICE BULLETIN
OPERATOR
 MSN
RJA
 0445 0490 0491
ROT
 0636 0644
RZO
 0571 0624 0651 0661
SGX
 0519
 0562
SUD
 0437
THY
 0478 0480
TSC
 0447 0472 0483 0545 0588 0597 0599 0600 0658
UBD
 0672 0674
UZB
 0574 0576 0706
WHT
 0494
(4) Configuration by MSN
MSN
 CONFIGURATION
0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331
0356 0362 0364 0369 0378 0394 0399 0407 0413 0418 0419
0421 0422 0425 0431 0434 0436 0437 0439 0441 0444 0445
0446 0447 0449 0452 0454 0456 0457 0458 0467 0472 0473
0478 0480 0482 0483 0484 0488 0489 0490 0491 0492 0494
0495 0496 0497 0498 0499 0500 0503 0519 0520 0522 0523
0524 0526 0527 0537 0539 0545 0547 0549 0550 0551 0552
0562 0564 0565 0567 0568 0571 0574 0576 0585 0586 0587
0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620
0622 0624 0636 0644 0646 0647 0648 0649 0651 0652 0653
0656 0658 0660 0661 0663 0667 0671 0672 0674 0676 0678
0682 0687 0689 0691 0700 0702 0704 0706
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
MATERIAL
 QTY PER A/C
 SEE NOTES
Consumable CMLD01
 1
B. CONCURRENT REQUIREMENTS
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 3
6
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### Page 12

@A310
SERVICE BULLETIN
C. REASON
(1) History
On AIRBUS Single Aisle, Long Range and Wide Body family aircraft, the rudder side
shell is a sandwich structure made of Carbon Fiber Reinforced Plastic (CFRP) and
Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core. A case of skin damage
was reported on a composite side panel of a rudder installed on an A310 aircraft.
Investigations have shown that the damage started from a skin panel area previously
repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig. 204
procedure. The new damage has been identified as a damage between the core and the
skin in the repaired area. This new damage has developed during normal operations due
to the variation of pressure during ground-air-ground cycles.
Following the above mentioned damage scenario, it has been identified that SRM
procedures need to be improved to ensure an adequate repair quality. An improper
bonding between skin and core during a repair may lead to a damage initiation and
propagation, which may not be detectable visually. A large rudder damage, resulting
from an undetected damage growth, could affect the handling quality of the aircraft.
(2) Objective/Action
This Service Bulletin details the inspection procedure to inspect affected rudders fitted
on A310 aircraft for potential damage.
Different inspection procedures are necessary:
- Pulse thermography inspection
- Elasticity Laminate Checker (ELCH) inspection
- Ultrasonic Testing (UT) inspection.
- Tap test inspection.
(3) Advantages
The accomplishment of this Service Bulletin will contribute to detect potential damage on
rudders made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced
Plastic (GFRP) with a honeycomb core.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
NOTE
: The listed subtasks are not in sequence with the work steps.
To accomplish this Service Bulletin it is necessary to :
Task 552051-832-848-001: Inspection
(1) Check the rudder repair records
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 4
6
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@A310
SERVICE BULLETIN
(2) Identify the type, location and size of repairs on the rudder side shell CFRP areas in
case of complete repair records since rudder EIS are available
(3) Do a pulse thermography inspection on the complete rudder side shell CFRP areas
to identify possible rudder in-service repairs in case of repair records are not complete or
not available
(4) Do the corrective actions in case of fluid ingress detected
(5) Do the ELCH and/or UT inspection around identified repairs/fluid ingress
(6) Do terminating actions in case of no damage detected
(7) Inspect the rudder side shell upper GFRP areas
(8) Close the holes in case of drilling thru the outer skin during paint thickness
measurement
(9) Identify the repair size by local sanding
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
This Service Bulletin has been classified Mandatory by the issue of an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA). The AD must
be used as the reference document for the mandated accomplishment timescale.
Table 1, Config. 001 - Rudder special detailed inspection for repair detection
Condition
 Action
 Compliance time
 Repetitive interval
All aircraft
 Identify the Serial
Number of the installed
rudder in accordance
with the accomplishment
instructions Subtask
552051-832-201-001
Within 4 months from
original Service Bulletin
issue date
None
All aircraft
 Check the completeness
of the rudder repair
records
Within 4 months from
original Service Bulletin
issue date
None
All aircraft
 Report information
about the repair records
to AIRBUS
Within 4 months from
original Service Bulletin
issue date
None
Repair records are not
complete or not
available
Continue with the
actions given in table 2A
for CFRP areas
Refer to table 2A
 Refer to table 2A
Repair records are not
complete or not
available
Continue with the
actions given in table 2B
for GFRP areas
Refer to table 2B
 Refer to table 2B
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
Table 1, Config. 001 - Rudder special detailed inspection for repair detection
Condition
 Action
 Compliance time
 Repetitive interval
Complete repair records
since rudder EIS are
available
Continue with the
actions given in table
2C for CFRP areas
Refer to table 2C
 Refer to table 2C
Complete repair records
since rudder EIS are
available
Continue with the
actions given in table
2D for GFRP areas
Refer to table 2D
 Refer to table 2D
Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Repair records are not
complete or not
available
Report undocumented
rudder Serial Number
list to AIRBUS to get
related rudder
manufacturing rework
data
3 months in advance
before pulse
thermography inspection
is scheduled
None
Repair records are not
complete or not
available
Make sure that the paint
thickness in all areas to
be inspected does not
exceed the limits given
in the accomplishment
instructions Subtask
552051-832-203-001
Within 24 months from
original Service Bulletin
issue date, before the
pulse thermography
inspection
None
Repair records are not
complete or not
available
Do a pulse
thermography inspection
on the complete side
shells (LH/RH) to
identify repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-203-001
Within 24 months from
original Service Bulletin
issue date
None
No repair detected
 Report to AIRBUS
No further action
necessary in accordance
with this Service Bulletin
Within 1 month from the
pulse thermography
inspection
None
Repairs in the booster
area =< 55000 mm 2
(85.25 sq.in) detected
Report to AIRBUS
 Within 1 month from the
pulse thermography
inspection
None
Repairs in the booster
area > 55000 mm 2
(85.25 sq.in) or not in
the booster area
detected during pulse
thermography
inspection
Do an ELCH and/or UT
inspection around the
identified repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Within 24 months from
original Service Bulletin
issue date
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 6
6
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SERVICE BULLETIN
Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Fluid ingress detected
during pulse
thermography//UT
inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
Damage detected
during ELCH and/or UT
inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions.
Before next flight
 None
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
Table 2B, Config. 001 - Repair records are not complete or not available (GFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Repair records are not
complete or not
available
Make sure that the paint
thickness in all areas to
be inspected does not
exceed the limits given
in the accomplishment
instructions Subtask
552051-832-207-001
Within 24 months from
original Service Bulletin
issue date, before the
pulse thermography
inspection
None
Repair records are not
complete or not
available
Do a pulse
thermography inspection
on the complete GFRP
area in accordance with
the accomplishment
instructions Subtask
552051-832-207-001
Within 24 months from
original Service Bulletin
issue date
None
Repair records are not
complete or not
available
In case of findings, mark
the repairs which are
not manufacturing
reworks
Within 24 months from
original Service Bulletin
issue date
None
Repair records are not
complete or not
available
Do a Tap test inspection
on the complete GFRP
area to identify skin to
core disbonding in
accordance with the
accomplishment
instructions Subtask
552051-832-207-001
Within 24 months from
original Service Bulletin
issue date
None
N os k i nt oc o r e
disbonding but repairs
identified
Do an ELCH and/or UT
inspection on the
complete GFRP area in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Within 24 months from
original Service Bulletin
issue date
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 7
6
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### Page 16

@A310
SERVICE BULLETIN
Table 2B, Config. 001 - Repair records are not complete or not available (GFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Fluid ingress detected
during pulse
thermography/UT
inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
Damage detected during
Tap test/ELCH and/or
UT inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions.
Before next flight
 None
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
No repair performed or
repair not to be
inspected in
accordance with this
Service Bulletin
Report to AIRBUS
No further action
necessary in accordance
with this Service Bulletin
Within 24 months from
original Service Bulletin
issue date
None
Repair is performed
since rudder EIS
Identify the repair type in
accordance with the
accomplishment
instructions Subtask
552051-832-202-001
Within 24 months from
original Service Bulletin
issue date
None
Repair identified as a
type to be inspected
Make sure that the paint
thickness in all areas to
be inspected does not
exceed the limits given
in the accomplishment
instructions Subtask
552051-832-202-001
Within 24 months from
original Service Bulletin
issue date, before the
pulse thermography
inspection
None
Repair identified as a
type to be inspected
Do a pulse
thermography inspection
on repair location in
accordance with the
accomplishment
instructions Subtask
552051-832-202-001
or
Identify the repair size
by local sanding, refer to
Subtask
552051-832-208-001
Within 24 months from
original Service Bulletin
issue date
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 8
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 17

@A310
SERVICE BULLETIN
Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Repairs in the booster
area =< 55000 mm 2
(85.25 sq.in) detected
during pulse
thermography
inspection or local
sanding
Report to AIRBUS
 Within 1 month from the
pulse thermography
inspection
None
Repairs in the booster
area > 55000 mm 2
(85.25 sq.in) or not in
the booster area
detected during pulse
thermography
inspection or local
sanding
Do an ELCH and/or UT
inspection around the
identified repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Within 24 months from
original Service Bulletin
issue date
None
Fluid ingress detected
during pulse
thermography/UT
inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
Damage detected
during ELCH and/or UT
inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions
Before next flight
 None
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
No repair performed or
repair not to be
inspected in accordance
with this Service Bulletin
Report to AIRBUS
No further action
necessary in
accordance with this
Service Bulletin
Within 24 months from
original Service Bulletin
issue date
None
Repair performed and
identified as type to be
inspected
Make sure that the paint
thickness in all areas to
be inspected does not
exceed the limits given
in the accomplishment
instructions Subtask
552051-832-207-001
Within 24 months from
original Service Bulletin
issue date, before the
pulse thermography
inspection
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 9
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 18

@A310
SERVICE BULLETIN
Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Repair identified as type
to be inspected
Do a pulse
thermography inspection
on repair location in
accordance with the
accomplishment
instructions Subtask
552051-832-207-001
or
Identify the repair size
by local sanding, refer
to Subtask
552051-832-208-001
Within 24 months from
original Service Bulletin
issue date
None
Repair type A-A
identified
Do a Tap test inspection
on the repair in
accordance with the
accomplishment
instructions Subtask
552051-832-207-001
Within 24 months from
original Service Bulletin
issue date
None
All other repairs
 Do an ELCH and/or UT
inspection around the
identified repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Within 24 months from
original Service Bulletin
issue date
None
Fluid ingress detected
during pulse
thermography/UT
inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
Damage detected during
Tap test/ELCH and/or
UT inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions
Before next flight
 None
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
Table 3, Config. 001 - Fluid ingress detected
Condition
 Action
 Compliance time
 Repetitive interval
Fluid ingress detected
 Do an ELCH and/or UT
inspection around the
identified fluid ingress in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Before next flight
 None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 10
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 19

@A310
SERVICE BULLETIN
Table 3, Config. 001 - Fluid ingress detected
Condition
 Action
 Compliance time
 Repetitive interval
Damage detected
around the identified
fluid ingress
Report to AIRBUS and
follow their instructions.
Before next flight
 None
Local single spot fluid
ingress =< 1500 mm 2
(2.33 sq.in) (no damage
detected around the
identified fluid ingress)
Report to AIRBUS.
 Within 1 month from
pulse thermography
inspection
None
Maximum of 5 local
single spots fluid ingress
per side shell > 1500
mm2 (2.33 sq.in) and =<
5000 mm2 (7.75 sq.in)
detected (no damage
detected around the
identified fluid ingress)
Drain by core ventilation
in accordance with the
accomplishment
instructions Subtask
552051-832-204-001
Before next flight
 None
Core ventilation done
 Option 1:
Close the holes with
adhesive tape
Before next flight
 None
Holes closed with tape
 Option 1:
Do repetitive detailed
inspections of the
restored area for loose
or lost tape
Within 500 FH or 4
months after closing
holes
At intervals not
exceeding 500 FH or 4
months, whichever
occurs later
Loose or lost tape found
 Option 1:
Close the holes again
with adhesive tape or
refer to Option 2
Before next flight
 None
Core ventilation done
 Option 2:
Close the holes with
GFRP plies
Before next flight
 None
Maximum of 5 local
single spots fluid ingress
per side shell > 1500
mm2 (2.33 sq.in) and =<
5000 mm2 (7.75 sq.in)
detected (no damage
detected around the
identified fluid ingress)
Option 1 and 2:
Repetitive thermography
inspections in
accordance with the
accomplishment
instructions Subtask
552051-832-204-001
Within 1000 FC after
closing holes
Within intervals of 1000
Flight Cycles (FC) until
repair
Maximum of 5 local
single spots fluid ingress
per side shell > 1500
mm2 (2.33 sq.in) and =<
5000 mm2 (7.75 sq.in)
detected (no damage
detected around the
identified fluid ingress)
Do the repair
 Within 4500 FC but not
exceeding 24 months
from the first inspection
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 11
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 20

@A310
SERVICE BULLETIN
Table 3, Config. 001 - Fluid ingress detected
Condition
 Action
 Compliance time
 Repetitive interval
Maximum of 5 local
single spots fluid ingress
per side shell > 1500
mm2 (2.33 sq.in) and =<
5000 mm2 (7.75 sq.in)
detected (no damage
detected around the
identified fluid ingress)
Report to AIRBUS
 Within 1 month from the
repair
None
More than 5 local single
spots fluid ingress per
side shell > 1500 mm 2
(2.33 sq.in.) and =<
5000 mm2 (7.75 sq.in.)
detected (no damage
detected around the
identified fluid ingress)
Report to AIRBUS and
follow their instructions
Before next flight
 None
Local single spot fluid
ingress > 5000 mm 2
(7.75 sq.in) detected (no
damage detected
around the identified
fluid ingress)
Report to AIRBUS and
follow their instructions
Before next flight
 None
Tables 4.A thru 4.D, Config. 001: No damage detected during ELCH/UT inspection:
For an identified repair size of a maximum of 10000 mm 2 (15.50 sq.in.), continue with
table 4.A.
For an identified repair size larger than 10000 mm 2 (15.50 sq.in.) up to 20000 mm 2
(31.00 sq.in.), continue with table 4.B.
For an identified repair size larger than 20000 mm 2 (31.00 sq.in.) up to 80000 mm 2 (124
sq.in.), continue with table 4.C.
For an identified repair size larger than 80000 mm 2 (124 sq.in.), continue with table 4.D.
Table 4.A, Config. 001 - Identified repair size of a maximum of 10000 mm
2
(15.50 sq.in.)
Condition
 Action
 Compliance time
 Repetitive interval
Repair size =< 10000
mm
2
(15.50 sq.in)
Provide detailed
information about the
identified repair and
report to AIRBUS
Within 1 month from
ELCH/UT inspection
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 12
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 21

@A310
SERVICE BULLETIN
Table 4.B, Config. 001 - Identified repair size larger than 10000 mm
2
(15.50 sq.in.) and up to 20000
mm
2
(31.00 sq.in.)
Condition
 Action
 Compliance time
 Repetitive interval
Repair size > 10000
mm
2
(15.50 sq.in.) and
=< 20000 mm
2
(31.00
sq.in.)
Option 1:
Do the core ventilation
thru the inner skin in
accordance with the
accomplishment
instructions Subtask
552051-832-206-001
Before next flight
 None
Core ventilation done
 Option 1:
Hole closing option 1:
Close the holes with
adhesive tape
Before next flight
 None
Holes closed with tape
 Option 1:
Hole closing option 1:
Do repetitive detailed
inspections of the
restored area for loose
or lost tape
Within 500 FH or 4
months after closing the
holes
At intervals not
exceeding 500 FH or 4
months, whichever
occurs later
Loose or lost tape found
 Option 1:
Hole closing option 1:
Close the holes again
with adhesive tape or
refer to hole closing
option 2
Before next flight
 None
Core ventilation done
 Option 1:
Hole closing option 2:
Close the holes with
GFRP plies
Before next flight
 None
Core ventilation done
 Option 1:
Report detailed
information about the
identified repair and the
planned terminating
action to AIRBUS
Within 1 month from first
ELCH/UT inspection
None
Core ventilation done
 Option 1:
Do the repair in
accordance with the
SRM at the identified
repair location
Within 4500 FC, not
exceeding 24 months,
from the first inspection
date
None
Repair size > 10000
mm
2
(15.50 sq.in.) and
=< 20000 mm
2
(31.00
sq.in.)
Option 2:
Do repetitive ELCH/UT
inspections around the
identified repair area in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Within 750 FC from first
ELCH/UT inspection
Every 750 FC from first
ELCH/UT inspection
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 13
6
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### Page 22

@A310
SERVICE BULLETIN
Table 4.B, Config. 001 - Identified repair size larger than 10000 mm
2
(15.50 sq.in.) and up to 20000
mm
2
(31.00 sq.in.)
Condition
 Action
 Compliance time
 Repetitive interval
Findings during
repetitive ELCH/UT
inspections
Option 2:
Report to AIRBUS and
follow their instructions.
Before next flight
 None
No findings during
repetitive ELCH/UT
inspections
Option 2:
Report detailed
information about the
identified repair and the
planned terminating
action to AIRBUS
Within 1 month from first
ELCH/UT inspection
None
No findings during
repetitive ELCH/UT
inspections
Option 2:
Do the repair in
accordance with the
SRM at the identified
repair location
Within 4500 FC, not
exceeding 24 months,
from the first inspection
date
None
Table 4.C, Config. 001 - Identified repair size larger than 20000 mm
2
(31.00 sq.in.) and up to 80000
mm
2
(124 sq.in.)
Condition
 Action
 Compliance time
 Repetitive interval
Repair size > 20000
mm
2
(31.00 sq.in.) and
=< 80000 mm
2
(124
sq.in.)
Do the core ventilation
thru inner skin in
accordance with the
accomplishment
instructions Subtask
552051-832-206-001
Before next flight
 None
Core ventilation done
 Option 1:
Close the holes with
adhesive tape
Before next flight
 None
Holes closed with tape
 Option 1:
Do repetitive detailed
inspections of the
restored area for loose
or lost tape
Within 500 FH or 4
months after closing the
holes
At intervals not
exceeding 500 FH or 4
months, whichever
occurs later
Loose or lost tape found
 Option 1:
Close the holes again
with adhesive tape or
refer to Option 2
Before next flight
 None
Core ventilation done
 Option 2:
Close the holes with
GFRP plies
Before next flight
 None
Repair size > 20000
mm2 (31.00 sq.in.) and
=< 80000 mm2 (124
sq.in.)
Report detailed
information about the
identified repair and the
planned terminating
action to AIRBUS
Within 1 month from first
ELCH/UT inspection
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 14
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 23

@A310
SERVICE BULLETIN
Table 4.C, Config. 001 - Identified repair size larger than 20000 mm
2
(31.00 sq.in.) and up to 80000
mm
2
(124 sq.in.)
Condition
 Action
 Compliance time
 Repetitive interval
Core ventilation done
and repair size =<
30000 mm
2
(46.50
sq.in.)
Do the repair in
accordance with the
SRM at the identified
repair location
Within 4500 FC, not
exceeding 24 months,
from the first inspection
date
None
Core ventilation done
and repair size > 30000
mm2 (46.50 sq.in.) =<
80000 mm2 (124 sq.in.)
Do the repair in
accordance with the
SRM and additional
instructions from
AIRBUS
Within 4500 FC, not
exceeding 24 months,
from the first inspection
date
None
Table 4.D, Config. 001 - Identified repair size larger than 80000 mm 2 (124 sq.in.)
Condition
 Action
 Compliance time
 Repetitive interval
Repair size > 80000
mm2 (124 sq.in.)
Do the core ventilation
thru inner skin in
accordance with the
accomplishment
instructions Subtask
552051-832-206-001
Before next flight
 None
Core ventilation done
 Option 1:
Close the holes with
adhesive tape
Before next flight
 None
Holes closed with tape
 Option 1:
Do repetitive detailed
inspections of the
restored area for loose
or lost tape
Within 500 FH or 4
months after closing the
holes
At intervals not
exceeding 500 FH 4
months, whichever
occurs later
Loose or lost tape found
 Option 1:
Close the holes again
with adhesive tape or
refer to Option 2
Before next flight
 None
Core ventilation done
 Option 2:
Close the holes with
GFRP plies
Before next flight
 None
Repair size > 80000
mm2 (124 sq.in.)
Report detailed
information about the
identified repair and the
planned terminating
action to AIRBUS
Within 1 month from first
ELCH/UT inspection
None
Repair size > 80000
mm
2
(124 sq.in.)
Replace the affected
rudder shell
OR
Replace the rudder
No further action
necessary in
accordance with this
Service Bulletin
Within 4500 FC, not
exceeding 24 months,
from the first inspection
date
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 15
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 24

@A310
SERVICE BULLETIN
Table 5, Config. 001 - Hole closing in case of damaged outer skin during paint measurement
Condition
 Action
 Compliance time
 Repetitive interval
Sandwich structure
damaged
Option 1:
Close the holes with
resin and adhesive tape
Before next flight
 None
Holes closed
 Option 1:
Restore the surface
protection
Within 4500 FC from the
pulse thermography
inspection
None
Sandwich structure
damaged
Option 2:
Do the permanent
restoration procedure
Before next flight
 None
Table 6.A, Config. 001 - Identify the repair size by local sanding
Condition
 Action
 Compliance time
 Repetitive interval
Repair performed and
identified as type to be
inspected
Identify paint thickness
and primer
Within 24 months from
original Service Bulletin
issue date
None
Repair performed and
identified as type to be
inspected
Do local sanding on top
and around the repair
up to the initial basic
primer
Within 24 months from
original Service Bulletin
issue date
None
Largest repair ply is not
visible
Continue with the
actions given in table
6.B
Before next flight
 None
Largest repair ply is
visible
Remove the dust and
dry the area
Before next flight
 None
Largest repair ply is
visible
Inspect the sanded area
for damage
Before next flight
 None
Damage found
 Do the damage
assessment
Before next flight
 None
No damage found
 Mark the repair on the
rudder surface
Before next flight
 None
Repairs in the booster
area =< 55000 mm 2
(85.25 sq.in.) detected
Restore the surface
protection
Before next flight
 None
Repairs in the booster
area =< 55000 mm
2
(85.25 sq.in.) detected
Report to AIRBUS
 Within 1 month
 None
Repairs in the booster
area > 55000 mm 2
(85.25 sq.in.) or not in
the booster area
detected
Do an ELCH and/or UT
inspection around the
identified repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Before next flight
 None
Fluid ingress detected
during UT inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 16
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 25

@A310
SERVICE BULLETIN
Table 6.A, Config. 001 - Identify the repair size by local sanding
Condition
 Action
 Compliance time
 Repetitive interval
Damage detected during
ELCH and/or UT
inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions
Before next flight
 None
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible
Condition
 Action
 Compliance time
 Repetitive interval
Largest repair ply is not
visible
Continue local sanding
up to the pore
filler/adhesive
Before next flight
 None
Largest repair ply is
visible now
Remove the dust and
dry the area
Before next flight
 None
Largest repair ply is still
not visible
Continue with the
actions given in table
6.C for CFRP areas and
table 6.D for GFRP
areas
Before next flight
 None
Largest repair ply is
visible now
Inspect the sanded area
for damage
Before next flight
 None
Damage found
 Do the damage
assessment
Before next flight
 None
No damage found
 Mark the repair on the
rudder surface
Before next flight
 None
Repairs in the booster
area =< 55000 mm
2
(85.25 sq.in.) detected
Restore the surface
protection
Before next flight
 None
Repairs in the booster
area =< 55000 mm 2
(85.25 sq.in.) detected
Report to AIRBUS
 Within 1 month
 None
Repairs in the booster
area > 55000 mm
2
(85.25 sq.in.) or not in
the booster area
detected
Do an ELCH and/or UT
inspection around the
identified repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Before next flight
 None
Fluid ingress detected
during UT inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
Damage detected during
ELCH and/or UT
inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions
Before next flight
 None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 17
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 26

@A310
SERVICE BULLETIN
Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible
Condition
 Action
 Compliance time
 Repetitive interval
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
Table 6.C, Config. 001 - Do the pulse thermography inspection (CFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Largest repair ply is still
not visible
Do a pulse
thermography inspection
on repair location in
accordance with the
accomplishment
instructions Subtask
552051-832-202-001
Before next flight
 None
Repairs in the booster
area =< 55000 mm
2
(85.25 sq.in.) detected
during pulse
thermography inspection
Restore the surface
protection
Before next flight
 None
Repairs in the booster
area =< 55000 mm 2
(85.25 sq.in.) detected
during pulse
thermography inspection
Report to AIRBUS
 Within 1 month
 None
Repairs in the booster
area > 55000 mm
2
(85.25 sq.in.) or not in
the booster area
detected during pulse
thermography inspection
Do an ELCH and/or UT
inspection around the
identified repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Before next flight
 None
Fluid ingress detected
during pulse
thermography/UT
inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
Damage detected during
ELCH and/or UT
inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions
Before next flight
 None
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
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Table 6.D, Config. 001 - Do the pulse thermography inspection (GFRP areas)
Condition
 Action
 Compliance time
 Repetitive interval
Repair identified as type
to be inspected
Do a pulse
thermography inspection
on repair location in
accordance with the
accomplishment
instructions Subtask
552051-832-207-001
Before next flight
 None
Repair type A-A
identified
Do a Tap test inspection
on the identified repair
in accordance with the
accomplishment
instructions Subtask
552051-832-207-001
Before next flight
 None
All other repairs
 Do an ELCH and/or UT
inspection around the
identified repairs in
accordance with the
accomplishment
instructions Subtask
552051-832-205-001
Before next flight
 None
Fluid ingress detected
during pulse
thermography/UT
inspection
Continue with the
actions given in table 3
Refer to table 3
 Refer to table 3
Damage detected during
Tap test/ELCH and/or
UT inspection
Provide a detailed
damage report, report to
AIRBUS and follow their
instructions
Before next flight
 None
No damage detected
during ELCH and/or UT
inspection
Continue with the
actions given in table 4
Refer to table 4
 Refer to table 4
F. APPROVAL
The technical content of this document is approved under authority of Design Organization
Approval No. EASA.21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
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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 552051-832-848-001: Inspection
Get Access
 1.00
On Aircraft
Check the rudder repair records
 4.00
Identify the type, location and size of repairs on the
rudder side shell CFRP areas in case of complete
repair records since rudder EIS are available
0
Do a pulse thermography inspection on the complete
rudder side shell CFRP areas to identify possible
rudder in-service repairs in case of repair records are
not complete or not available
32.00
Do the corrective actions in case of fluid ingress
detected
0
Do the ELCH and/or UT inspection around identified
repairs/fluid ingress
0
Do terminating actions in case of no damage detected
 0
Inspect the rudder side shell upper GFRP areas
 0
Close the holes in case of drilling thru the outer skin
during paint thickness measurement
0
Identify the repair size by local sanding
 0
Close-Up
 1.00
TOTAL MANHOURS
 38.00
NOTE
: Manhours and elapsed time depend on the size of the area to be inspected.
Find below a table with the information for the manhours, elapsed time
and number of persons per 1 m 2 (1550 sq.in.) for the different inspection
procedures:
Steps
 Manhours
 Elapsed time
 Number of
persons
Get access
 1.00
 0.75
 2
Rudder SN
identification
0.25
 0.25
 1
Pulse
thermography
inspection
1.00
 0.50
 2
UT inspection
 1.25
 1.25
 1
ELCH inspection
 1.50
 0.75
 1
Tap test inspection
 0.25
 0.25
 1
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Steps
 Manhours
 Elapsed time
 Number of
persons
Local sanding
 1.00
 1.00
 1
Close-up
 1.00
 0.75
 2
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 06-41-55 20-16-00 24-00-00
55-40-00 55-42-11
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 51-10-03 51-10-19 51-10-24
51-10-25 51-10-26 55-40-09
55-40-50
Structural Repair Manual (SRM)
 51-10-00
 51-10-14
 51-23-10
51-75-10 51-75-20 51-77-00
51-77-10 51-77-11
K. PUBLICATION AFFECTED
None
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
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This Page Intentionally Left Blank
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2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
None
This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.
(2) Price and Availability
None
B. INDUSTRY SUPPORT INFORMATION
For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
France
E-mail : monitored.retrofit@airbus.com
T e l:( 3 3 )56 71 90 62 2
F a x:( 3 3 )56 19 32 74 5
AIRBUS will provide specific industry support for inspection Service Bulletin completion. For
detailed information, please contact your AIRBUS Customer Support Director.
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
Adhesive Film Tape- Aluminium Foil
 05RAB9
 As required
Pressure Sensitive Tape
 05RFB1
 As required
Self-Adhes. Disks
 05TNB1
 As required
Non Aqueous Cleaner-General
 08BAA9
 As required
Methyl-Ethyl-Ketone
 08BBF1
 As required
Trichloroethane Legacy
 08BBU9
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
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ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Laminating Resin-Epoxy Srm Type
2
13EBC1
 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
Not Applicable
(2) Tools
To find the correct tool-PN for the different inspection tools, refer to the subsequent
table:
Inspection
 tool
 PN
UT inspection
 UT-equipment
 Refer to NTM 51-10-24
Tap test inspection
 Tap test inspection tool
 Refer to NTM 51-10-03
Tap test inspection (with
Woodpecker)
Function test block
and
Woodpecker
Refer to NTM 51-10-19
ELCH inspection
 Elasticity Laminate Checker Kit
 Refer to NTM 51-10-26
Pulse thermography inspection
 Pulse thermography kit
 99A55407324000
Thermography inspection
 Thermography kit
 Refer to NTM 51-10-25
Paint thickness measurement
 TNO Paint Borer Kit
 Model 518 or 518S or 518MC
with drill measuring range 10 to
1000 and 20 to 2000 microns
To order the pulse thermography kit and the paint borer kit, contact:
For tools on loan:
AIRBUS Material, Logistics and Suppliers
Lease Tool Service
Weg beim Jaeger 150
D-22335 HAMBURG
Germany
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
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For ordering by internet : http.//spares.airbus.com
For ordering by E-mail: tool.lease@airbus.com
For ordering by fax: +49 40 5076 3225
For tools to buy:
AIRBUS Material, Logistics and Suppliers
IFD- In Flight Desk
Weg beim Jaeger 150
D-22335 HAMBURG
Germany
For ordering by internet : http.//spares.airbus.com
For ordering by E-mail: ifd.spares@airbus.com
For ordering by fax: +49 40 5076 4012
(3) Special Tools
None
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 552051-832-848-001 - Inspection
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
WARNING
: OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE CLEANING
AGENTS, ADHESIVES, SEALANTS AND PAINTS. THESE MATERIALS ARE
DANGEROUS.
WARNING
: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS
WHEN YOU USE CLEANING AGENTS, A DHESIVES, SEALANTS AND PAINTS.
THESE MATERIALS ARE DANGEROUS.
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
: 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.
NOTE
: This Service Bulletin is classified mandatory or expected to be classified mandatory
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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.
Task Associated Data
Manpower
TOTAL MANHOURS
 38.00
A. GENERAL
(1) Subtask 552051-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-55, Page Block 001
20-16-00, Page Block 201
Consumable Material List (CML)
(a) For location of the access panels, refer to
 AMM 06-41-55, Page Block 001.
(b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to
Consumable Materials List (CML).
(c) For circuit breaker safety practices, refer to
 AMM 20-16-00, Page Block 201.
(d) The purpose of flow charts are for information only to show the various
Inspection/Repair phases described in this Service Bulletin.
(2) Subtask 552051-839-201-001 - 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 552051-941-201-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
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References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
55-40-00, Page Block 601
55-42-11, Page Block 401
NOTE
: The items given in this note 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.
(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page
Block 301.
(b) In the cockpit, put warning notices in position to tell persons not to operate the flight
controls.
(c) Do the rudder inspection/check Job Set-up procedure, refer to AMM 55-40-00,
Page Block 601, Para 1.B.(1)(a) thru (d).
(d) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic
systems.
(e) Put access platforms in position at the rudder.
(f) To remove the access panel 326AL from rudders which have not embodied Mod.
8827, refer to
 AMM 55-42-11, Page Block 401.
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C. PROCEDURE
(1) Subtask 552051-832-201- 001 - Check the rudder repair records
Manpower Resources
Manhours
 4.00
Minimum number of person
 1
Subtask elapsed time
 4.00
Skills
 NON DESTRUCTIVE
TESTING
References
Fig. A-GBAAA
Rudder SN identification
Sheet 01
Sheet 02
Fig. A-GBCAA
Repair type identification
Sheet 01 - SRM list
Sheet 02 - RAS list
Fig. A-GBHAA
Report sheet and sketches
Sheet 01 -
 Pulse thermography report sheet
Sheet 02 -
 Repair records report sheet
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Fig. A-GBJAA
GFRP area location
Sheet 01
Sheet 02
Sheet 03
(a) Identify the Serial Number (SN) and the Part Number (PN) of the installed rudder.
1
 Check the Aircraft Inspection Report and the maintenance records to verify the
rudder identification and a potential rudder swap since EIS.
2
 In case of doubts, check the rudder identification plate on the aircraft, as
shown on Fig. A-GBAAA Sheet 01
 for rudder before Modification No. 8827, or
as shown on Fig. A-GBAAA Sheet 02
 for rudder after Modification No. 8827.
3
 If you do not find a SN/PN placard on the rudder, contact AIRBUS for further
instructions.
(b) Check the completeness of the rudder records and report the result to AIRBUS.
Use the report sheet Fig. A-GBHAA Sheet 02
 .
NOTE
: This action is not necessary, if the information has been already
sent to AIRBUS in accordance with the OIT 999.0070/10 and the
situation did not change since then.
(c) Check the rudder records if repairs are recorded since rudder EIS.
1
 Repairs not affected by this Service Bulletin are those which:
- have been covered by AIRBUS Repair Design Approval Sheet (RDAS)
after December 2009,
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- have been done in accordance with the SRM revision December 2009 or
later,
- have been accomplished in accordance with the SRM procedures as
listed in Fig. A-GBCAA Sheet 01
 ,
- are indicated in the AIRBUS Repair Approval Sheet (RAS) list
 Fig. A-
GBCAA Sheet 02
 with "ISB inspection required: NO".
NOTE
: If you find a RAS which is not listed in the RAS list, contact
AIRBUS and follow their instructions.
2
 Report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
 .
NOTE
: This action is not necessary, if the information has been
already sent to AIRBUS in accordance with the OIT
999.0070/10 and the situation did not change since then.
3
 If repairs are recorded and the repair records are complete, refer to:
- Subtask 552051-832-202-001 of this Service Bulletin for the rudder side
shell areas made of CFRP.
- Subtask 552051-832-207-001 of this Service Bulletin for the upper rudder
side shell areas made of GFRP.
NOTE
: The outer skin ply of the upper area of the rudders is made
of GFRP. GFRP areas require different pulse thermography
inspection parameter than CFRP areas and additionally Tap
test inspection have to be performed. For the identification of
the GFRP areas, refer to the subsequent table:
Rudder PN
 Refer to Figure
A55471710
A55471730
Fig. A-GBJAA Sheet 02
A55471500
 Fig. A-GBJAA Sheet 03
4
 If no repairs have been duly recorded, report the result to AIRBUS. Use the
report sheet Fig. A-GBHAA Sheet 02
 .
No further action is necessary in accordance with this Service Bulletin.
5
 In case of any doubts about the accomplishment of repairs, refer to:
- Subtask 552051-832-203-001 of this Service Bulletin for the rudder side
shell areas made of CFRP.
- Subtask 552051-832-207-001 of this Service Bulletin for the upper rudder
side shell areas made of GFRP.
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6
 If the repair records are not complete or not available, refer to:
- Subtask 552051-832-203-001 of this Service Bulletin for the rudder side
shell areas made of CFRP.
- Subtask 552051-832-207-001 of this Service Bulletin for the upper rudder
side shell areas made of GFRP.
NOTE
: The outer skin ply of the upper area of the rudders is made
of GFRP. GFRP areas require different pulse thermography
inspection parameter than CFRP areas and additionally Tap
test inspection have to be performed. For the identification of
the GFRP areas, refer to the subsequent table:
Rudder PN
 Refer to Figure
A55471710
A55471730
Fig. A-GBJAA Sheet 02
A55471500
 Fig. A-GBJAA Sheet 03
(2) Subtask 552051-832-202-001 - Identify the type, location and size of repairs on the
rudder side shell CFRP areas in case of comp lete repair records since rudder EIS
are available
Manpower Resources
Manhours
 0
Minimum number of person
 1
Subtask elapsed time
 0
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 Cleaner-
General
08BAA9
Textile-Lint Free Cotton
 14SBA1
 As required
References
Non Destructive Test Manual (NTM)
 55-40-50 Page Block 1001
Structural Repair Manual (SRM)
 51-75-10
51-75-20
Fig. A-GBBAA
Repair type identification
Sheet 01
Sheet 02
Fig. A-GBDAA
Booster area definition
Sheet 01
Sheet 02
Sheet 03
Sheet 04
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References
Fig. A-GBEAA
Typical pulse thermography and
ELCH/UT inspection
Sheet 01
Sheet 02 - Repair size assessment
Sheet 03 - Repair size assessment
Sheet 04 - Boundary and grid of ELCH/UT
inspection
Sheet 05 - ELCH inspection grid
Fig. A-GBHAA
Report sheet and sketches
Sheet 01 -
 Pulse thermography report sheet
Sheet 02 -
 Repair records report sheet
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Fig. A-GFAAA
Flow Chart
Sheet 01 - Flow Chart 1
Sheet 02 - Flow Chart 2
Sheet 03 - Flow Chart 3
Sheet 04 - Flow Chart 4
Sheet 05 - Flow Chart 5
Sheet 06
Fig. A-GABAA
Paint borer instructions
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Sheet 08
(a) If no repair has been done or the recorded repair is not to be inspected in
accordance with this Service Bulletin, report to AIRBUS. Use the report sheet Fig.
A-GBHAA Sheet 02
.
NOTE
: This action is not necessary, if the information has been already
sent to AIRBUS in accordance with the OIT 999.0070/10 and the
situation did not change since then.
No further action is necessary in accordance with this Service Bulletin.
(b) If a repair must be inspected in accordance with this Service Bulletin, do the
subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 01
 :
1
 Identify the repair type, refer to Fig. A-GBBAA Sheet 01
 and Fig. A-GBBAA
Sheet 02
.
2
 Make sure that the paint thickness in the areas to be inspected does not
exceed:
- 800 microns.
- 400 microns below the decal foil if a decal foil is installed.
NOTE
: It is the responsibility of the operator to ensure that the paint
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thickness in all areas to be inspected is below or equal to the
limits given above.
a
 If the paint coating and/or logo application is too thick, abrade the paint in
accordance with the
 SRM 51-75-20 to a thickness below or equal to the
limits given above.
NOTE
: Chemical paint stripping is not allowed.
b
 In case of doubts about the paint thickness, measure the thickness using
a Paint Borer Kit, refer to the Figure
 Fig. A-GABAA Sheet 01
 thru Fig. A-
GABAA Sheet 08
.
<1>
CAUTION
: DO NOT DRILL DEEPLY INTO THE BASE
MATERIAL (CFRP OR GFRP). DRILLING TOO
DEEP LEADS TO DAMAGE IN THE OUTER SKIN
If you damage the outer skin with the paint borer, refer to the
Subtask 552051-833-201-001 for repair instructions.
3
 Clean the areas to be inspected with:
Non Aqueous
Cleaner-General
08BAA9
 As required
and
Textile-Lint Free
Cotton
14SBA1
 As required
4
 Do a pulse thermography inspection to get the precise location and the size of
the repair, refer to NTM 55-40-50 Page Block 1001.
NOTE
: As an alternative for the pulse thermography inspection, you
can identify the repair size by local sanding, refer to Subtask
552051-832-208-001.
NOTE
: The pulse thermography inspection indicates the outer skin
repair ply geometry. The largest repair ply defines the
boundary of the repair area.
NOTE
: In case of any findings (repair, damage, fluid ingress) during
the pulse thermography inspection, save the images and send
it together with the report sheet to AIRBUS.
5
 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02
 and
Fig. A-GBEAA Sheet 03
 .
6
 If fluid ingress has been detected during the pulse thermography inspection,
refer to Subtask 552051-832-204-001 of this Service Bulletin.
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7
 Identify the booster areas in accordance with the subsequent table:
Rudder PN
 Refer to Figure
A55471710
A55471730
Fig. A-GBDAA Sheet 02
 and Fig. A-GBDAA Sheet 03
A55471500
 Fig. A-GBDAA Sheet 04
8
 If repairs in the booster areas up to 55000 mm 2 (85.25 sq.in.) have been
detected, report the findings to AIRBUS. Use the report sheet
 Fig. A-GBHAA
Sheet 01
 and the rudder related sketches, refer to the subsequent table:
Rudder PN
 Refer to Figure (sketch)
A55471710
A55471730
Fig. A-GBHAA Sheet 03
 and Fig. A-GBHAA Sheet 04
A55471500
 Fig. A-GBHAA Sheet 05
 and Fig. A-GBHAA Sheet 06
No further actions on these repairs in accordance with this Service Bulletin.
9
 If repairs in the booster areas larger than 55000 mm
2
(85.25 sq.in.) have been
detected, do the UT inspection around the repair in accordance with Subtask
552051-832-205-001 of this Service Bulletin.
10
 If repairs not in the booster area have been detected, do the ELCH and/or UT
inspection in accordance with Subtask 552051-832-205-001 of this Service
Bulletin.
11
 After the inspection, restore the paint coating in accordance with the
 SRM
51-75-10.
NOTE
: Refer to OIT 999.0130/06 ’pai nt system - best practices’.
(3) Subtask 552051-832-203-001 - Do a pulse thermography inspection on the
complete rudder side shell CFRP areas to identify possible rudder in-service
repairs in case of repair records are not complete or not available
Manpower Resources
Manhours
 32.00
Minimum number of person
 2
Subtask elapsed time
 32.00
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 Cleaner-
General
08BAA9
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 35
6
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### Page 44

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SERVICE BULLETIN
References
Non Destructive Test Manual (NTM)
 55-40-50 , Page Block 1001
Structural Repair Manual (SRM)
 51-75-10
51-75-20
Fig. A-GFAAA
Flow Chart
Sheet 01 - Flow Chart 1
Sheet 02 - Flow Chart 2
Sheet 03 - Flow Chart 3
Sheet 04 - Flow Chart 4
Sheet 05 - Flow Chart 5
Sheet 06
Fig. A-GBDAA
Booster area definition
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Fig. A-GBHAA
Report sheet and sketches
Sheet 01 -
 Pulse thermography report sheet
Sheet 02 -
 Repair records report sheet
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Fig. A-GABAA
Paint borer instructions
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Sheet 08
(a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA
Sheet 01
:
1
 Report undocumented rudder S/N list to AIRBUS.
a
 To get related manufacturing rework data, provide AIRBUS with the
rudder P/N, S/N and aircraft MSN in accordance with the accomplishment
timescale instructions, refer to Para 1.E table 2A of this Service Bulletin.
The manufacturing rework data will be provided through drawings
covered by Mod. 13659.
2
 Make sure that the paint thickness in the areas to be inspected does not
exceed:
- 800 microns.
- 400 microns below the decal foil if a decal foil is installed.
NOTE
: It is the responsibility of the operator to ensure that the paint
thickness in all areas to be inspected is below or equal to the
limits given above.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 36
6
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### Page 45

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SERVICE BULLETIN
a
 If the paint coating and/or logo application is too thick, abrade the paint in
acccordance with the
 SRM 51-75-20 to a thickness below or equal to the
limits given above.
NOTE
: Chemical paint stripping is not allowed.
b
 In case of doubts about the paint thickness, measure the thickness using
a Paint Borer Kit, refer to the Figure
 Fig. A-GABAA Sheet 01
 thru Fig. A-
GABAA Sheet 08
.
<1>
CAUTION
: DO NOT DRILL DEEPLY INTO THE BASE
MATERIAL (CFRP OR GFRP). DRILLING TOO
DEEP LEADS TO DAMAGE IN THE OUTER SKIN
If you damage the outer skin with the paint borer, refer to the
Subtask 552051-833-201-001 for repair instructions.
3
 Clean the areas to be inspected with:
Non Aqueous
Cleaner-General
08BAA9
 As required
and
Textile-Lint Free
Cotton
14SBA1
 As required
4
 Do a pulse thermography inspection on the complete side shell CFRP areas
(LH/RH) to identify repairs, refer to NTM 55-40-50 , Page Block 1001.
NOTE
: The pulse thermography inspection indicates the outer skin
repair ply geometry. The largest repair ply defines the
boundary of the repair area.
NOTE
: In case of any findings (repair, damage, fluid ingress) during
the pulse thermography inspection, save the images and send
it together with the report sheet to AIRBUS.
5
 If no repair has been detected during the pulse thermography inspection,
report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 01
 .
No further action is necessary in accordance with this Service Bulletin.
6
 If fluid ingress has been detected during the thermograhy inspection, refer to
Subtask 552051-832-204-001 of this Service Bulletin.
7
 Identify the booster areas in accordance with the subsequent table:
Rudder PN
 Refer to Figure
A55471710
A55471730
Fig. A-GBDAA Sheet 02
 and Fig. A-GBDAA Sheet 03
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 37
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### Page 46

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SERVICE BULLETIN
Rudder PN
 Refer to Figure
A55471500
 Fig. A-GBDAA Sheet 04
8
 If repairs in the booster areas up to 55000 mm 2 (85.25 sq.in.) have been
detected which are not manufacturing rework, report the findings to AIRBUS.
Use the report sheet
 Fig. A-GBHAA Sheet 01
 and the rudder related sketches,
refer to the subsequent table:
Rudder PN
 Refer to Figure (sketch)
A55471710
A55471730
Fig. A-GBHAA Sheet 03
 and Fig. A-GBHAA Sheet 04
A55471500
 Fig. A-GBHAA Sheet 05
 and Fig. A-GBHAA Sheet 06
No further actions on these repairs in accordance with this Service Bulletin.
9
 If repairs in the booster areas larger than 55000 mm 2 (85.25 sq.in.) have been
detected which are not manufacturing rework, do the UT inspection around the
repairs in accordance with the Subtask 552051-832-205-001 of this Service
Bulletin.
10
 If repairs have been detected during the pulse thermography inspection which
are not manufacturing rework and not in the booster areas, do the ELCH
and/or UT inspection around the repairs in accordance with the Subtask
552051-832-205-001 of this Service Bulletin.
11
 After the inspection, restore the paint coating in accordance with the
 SRM
51-75-10.
NOTE
: Refer to OIT 999.0130/06 ’pai nt system - best practices’.
(4) Subtask 552051-832-204-001 - Do the corrective actions in case of fluid ingress
detected
Manpower Resources
Manhours
 0
Minimum number of person
 1
Subtask elapsed time
 0
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
Adhesive Film Tape-
Aluminium Foil
05RAB9
 As required
Pressure Sensitive Tape
 05RFB1
 As required
Self-Adhes. Disks
 05TNB1
 As required
Methyl-Ethyl-Ketone
 08BBF1
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 38
6
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### Page 47

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SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Trichloroethane Legacy
 08BBU9
 As required
Laminating Resin-Epoxy
Srm Type 2
13EBC1
 As required
References
Non Destructive Test Manual (NTM)
 51-10-25
55-40-50 , Page Block 1001
Fig. A-GFAAA
Flow Chart
Sheet 01 - Flow Chart 1
Sheet 02 - Flow Chart 2
Sheet 03 - Flow Chart 3
Sheet 04 - Flow Chart 4
Sheet 05 - Flow Chart 5
Sheet 06
Fig. A-GBHAA
Report sheet and sketches
Sheet 01 -
 Pulse thermography report sheet
Sheet 02 -
 Repair records report sheet
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Fig. A-GBFAA
Core ventilation procedure
Sheet 01
Sheet 02
Sheet 03
Fig. A-GAAAA
Closing of ventilation holes
Sheet 01
Sheet 02
(a) If fluid ingress has been detected, continue with the subsequent work steps in
accordance with the Flow Chart Fig. A-GFAAA Sheet 03
 :
1
 Around the identified fluid ingress, do the ELCH and/or UT inspection in
accordance with the Subtask 552051-832-205-001 of this Service Bulletin.
2
 If a damage has been detected during the ELCH and/or UT inspection, contact
AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA
Sheet 01
.
3
 If local single spots up to 1500 mm
2
(2.33 sq.in.) with fluid ingress have been
detected, report the findings to AIRBUS. Use the report sheet
 Fig. A-GBHAA
Sheet 01
 and the rudder related sketches, refer to the subsequent table:
Rudder PN
 Refer to Figure (sketch)
A55471710
A55471730
Fig. A-GBHAA Sheet 03
 and Fig. A-GBHAA Sheet 04
A55471500
 Fig. A-GBHAA Sheet 05
 and Fig. A-GBHAA Sheet 06
No further actions on these local single spots of fluid ingress in accordance
with this Service Bulletin.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 39
6
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### Page 48

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SERVICE BULLETIN
4
 If a maximum of 5 local single spots per side shell larger than 1500 mm
2
(2.33
sq.in.) and up to 5000 mm
2
(7.75 sq.in.) have been detected, do the ventilation
of the rudder core:
a
CAUTION
: TO DRILL THE HOLES APPLY MODERATE
PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT
THE END OF THE DRILLING OPERATION. DO NOT
DRILL THE OPPOSITE SHELL.
Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner
skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet
02
 and Fig. A-GBFAA Sheet 03
 .
NOTE
: Spots of fluid ingress behind the trailing edge screw line
must not be vented.
b
 Temporary restoration of the drain holes option 1:
<1> Close the drain holes with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
<2> Do repetitive detailed inspections of the restored area for loose or
lost adhesive disks or tape until the repair of the affected area has
been done.
<3> In case of loose or lost tape or disks, close the holes again with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
c
 Temporary restoration of the drain holes option 2:
<1> Close the drain holes in accordance with the instructions given in
the Figure Fig. A-GAAAA Sheet 01
 and Fig. A-GAAAA Sheet 02
 .
<a> Consumable material needed to close the drain holes:
Pressure Sensitive
Tape
05RFB1
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 40
6
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### Page 49

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SERVICE BULLETIN
Laminating Resin-
Epoxy Srm Type 2
13EBC1
 As required
Methyl-Ethyl-Ketone 08BBF1
 As required
Trichloroethane
Legacy
08BBU9
 As required
5
 Do repetitive thermography inspections until the repair of the affected area has
been done, refer to
 NTM 51-10-25 (preferred)) or refer to
 NTM 55-40-50 ,
Page Block 1001.
NOTE
: In case of any findings during the pulse thermography
inspection, save the images and send it together with the
report sheet to AIRBUS.
6
 Do the repair in accordance with the SRM.
Due to the pending availability of the SRM improved repair, contact AIRBUS
for detailed repair instructions.
7
 Report the repair to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02
 .
8
 If more than 5 local single spots per side shell larger than 1500 mm 2 (2.33
sq.in.) and up to 5000 mm 2 (7.75 sq.in.) have been detected, report to
AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA
Sheet 01
.
9
 If local single spots larger than 5000 mm 2 (7.75 sq.in.) with fluid ingress have
been detected, report the findings to AIRBUS and follow their instructions. Use
the report sheet
 Fig. A-GBHAA Sheet 01
 .
(5) Subtask 552051-832-205-001 - Do the ELCH and/ or UT inspection around identified
repairs/fluid ingress
Manpower Resources
Manhours
 0
Minimum number of person
 1
Subtask elapsed time
 0
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 Cleaner-
General
08BAA9
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 41
6
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### Page 50

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SERVICE BULLETIN
References
Non Destructive Test Manual (NTM)
 51-10-24, Page Block 401
51-10-26, Page Block 701
55-40-09 , Page Block 1001 Para 7
Fig. A-GBEAA
Typical pulse thermography and
ELCH/UT inspection
Sheet 01
Sheet 02 - Repair size assessment
Sheet 03 - Repair size assessment
Sheet 04 - Boundary and grid of ELCH/UT
inspection
Sheet 05 - ELCH inspection grid
Fig. A-GBHAA
Report sheet and sketches
Sheet 01 -
 Pulse thermography report sheet
Sheet 02 -
 Repair records report sheet
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Fig. A-GBGAA
Rudder skin thickness identification
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
(a) If necessary, clean the areas to be inspected with:
Non Aqueous
Cleaner-General
08BAA9
 As required
and
Textile-Lint Free
Cotton
14SBA1
 As required
(b) Identify the skin thickness of the areas to be inspected, refer to the subsequent
table:
Rudder PN
 Refer to Figure
A55471710
A55471730
Fig. A-GBGAA Sheet 02
 and Fig. A-GBGAA Sheet 03
A55471500
 Fig. A-GBGAA Sheet 04
 and Fig. A-GBGAA Sheet 05
(c) If the skin thickness of the affected areas does not exceed 1.5 mm (0.06 in.), do an
ELCH inspection around the marked repair areas, refer to
 NTM 51-10-26, Page
Block 701.
1
 For the ELCH inspection, use a grid of 75 mm x 75 mm from the boundary of
the largest repair ply up to 200 mm around the largest repair ply, refer to Fig.
A-GBEAA Sheet 04
.
a
 For the adjustment of the ELCH, refer to NTM 51-10-26, Page Block 701.
b
 For the assessment criteria (yellow and red values) for the ELCH
inspection, refer to NTM 55-40-09 , Page Block 1001 Para 7.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 42
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SERVICE BULLETIN
(d) If the skin of the affected areas is thicker than 1.5 mm (0.06 in.), do an UT
inspection around the marked repair areas, refer to NTM 51-10-24, Page Block
401.
1
 Do the UT inspection in an area between the boundary of the largest repair
ply up to 75 mm around the largest repair ply, refer to Fig. A-GBEAA Sheet
04
.
(e) If a damage has been detected during the ELCH/UT inspection, provide detailed
information of the identified repair, report to AIRBUS and follow their instructions.
Use the report sheet Fig. A-GBHAA Sheet 02
 and the rudder related sketches,
refer to the subsequent table:
Rudder PN
 Refer to Figure (sketch)
A55471710
A55471730
Fig. A-GBHAA Sheet 03
 and Fig. A-GBHAA Sheet 04
A55471500
 Fig. A-GBHAA Sheet 05
 and Fig. A-GBHAA Sheet 06
(f) If no damage has been detected during the ELCH/UT inspection, continue with the
steps given in the Subtask 552051-832-206-001 of this Service Bulletin.
(6) Subtask 552051-832-206-001 - Do terminating actions in case of no damage
detected
Manpower Resources
Manhours
 0
Minimum number of person
 1
Subtask elapsed time
 0
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
Adhesive Film Tape-
Aluminium Foil
05RAB9
 As required
Pressure Sensitive Tape
 05RFB1
 As required
Self-Adhes. Disks
 05TNB1
 As required
Methyl-Ethyl-Ketone
 08BBF1
 As required
Trichloroethane Legacy
 08BBU9
 As required
Laminating Resin-Epoxy
Srm Type 2
13EBC1
 As required
References
Fig. A-GBFAA
Core ventilation procedure
Sheet 01
Sheet 02
Sheet 03
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 43
6
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### Page 52

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SERVICE BULLETIN
References
Fig. A-GBHAA
Report sheet and sketches
Sheet 01 -
 Pulse thermography report sheet
Sheet 02 -
 Repair records report sheet
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Fig. A-GFAAA
Flow Chart
Sheet 01 - Flow Chart 1
Sheet 02 - Flow Chart 2
Sheet 03 - Flow Chart 3
Sheet 04 - Flow Chart 4
Sheet 05 - Flow Chart 5
Sheet 06
Fig. A-GAAAA
Closing of ventilation holes
Sheet 01
Sheet 02
(a) If no damage has been detected, continue with the subsequent work steps in
accordance with the Flow Chart Fig. A-GFAAA Sheet 02
 :
1
 If a repair up to 10000 mm 2 (15.50 sq.in.) has been detected, provide detailed
information about the repair and report to AIRBUS. Use the report sheet Fig.
A-GBHAA Sheet 02
 and the rudder related sketches, refer to the subsequent
table:
Rudder PN
 Refer to Figure (sketch)
A55471710
A55471730
Fig. A-GBHAA Sheet 03
 and Fig. A-GBHAA Sheet 04
A55471500
 Fig. A-GBHAA Sheet 05
 and Fig. A-GBHAA Sheet 06
2
 If a repair larger than 10000 mm 2 (15.50 sq.in.) and up to 20000 mm 2 (31.00
sq.in.) has been detected, do the ventilation of the core:
NOTE
: Instead of the core ventilation procedure, you can do repetitive
ELCH and/or UT inspections around the repair areas until the
repair has been done, refer to Subtask 552051-832-205-001.
a
CAUTION
: TO DRILL THE HOLES APPLY MODERATE
PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT
THE END OF THE DRILLING OPERATION. DO NOT
DRILL THE OPPOSITE SHELL.
Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner
skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet
02
 and Fig. A-GBFAA Sheet 03
 .
NOTE
: Spots of fluid ingress behind the trailing edge screw line
must not be vented.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 44
6
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### Page 53

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SERVICE BULLETIN
b
 Temporary restoration of the drain holes option 1:
<1> Close the drain holes with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
<2> Do repetitive detailed inspections of the restored area for loose or
lost adhesive disks or tape until the repair of the affected area has
been done.
<3> In case of loose or lost tape or disks, close the holes again with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
c
 Temporary restoration of the drain holes option 2:
<1> Close the drain holes in accordance with the instructions given in
the Figure Fig. A-GAAAA Sheet 01
 and Fig. A-GAAAA Sheet 02
 .
<a> Consumable material needed to close the drain holes:
Pressure Sensitive
Tape
05RFB1
 As required
Laminating Resin-
Epoxy Srm Type 2
13EBC1
 As required
Methyl-Ethyl-Ketone 08BBF1
 As required
Trichloroethane
Legacy
08BBU9
 As required
d
 Report the results and the planned terminating action to AIRBUS. Use
the report sheet Fig. A-GBHAA Sheet 02
 .
e
 Do the terminating action in accordance with the SRM.
Due to the pending availability of the SRM improved repair, contact
AIRBUS for detailed repair instructions.
NOTE
: The new repair cutout is equal to the largest outer skin
repair ply.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 45
6
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### Page 54

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SERVICE BULLETIN
3
 If a repair larger than 20000 mm
2
(31.00 sq.in.) and up to 80000 mm
2
(124
sq.in.) has been detected, do the ventilation of the core:
a
CAUTION
: TO DRILL THE HOLES APPLY MODERATE
PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT
THE END OF THE DRILLING OPERATION. DO NOT
DRILL THE OPPOSITE SHELL.
Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner
skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet
02
 and Fig. A-GBFAA Sheet 03
 .
b
 Temporary restoration of the drain holes option 1:
<1> Close the drain holes with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
<2> Do repetitive detailed inspections of the restored area for loose or
lost adhesive disks or tape until the repair of the affected area has
been done.
<3> In case of loose or lost tape or disks, close the holes again with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
c
 Temporary restoration of the drain holes option 2:
<1> Close the drain holes in accordance with the instructions given in
the Figure Fig. A-GAAAA Sheet 01
 and Fig. A-GAAAA Sheet 02
 .
<a> Consumable material needed to close the drain holes:
Pressure Sensitive
Tape
05RFB1
 As required
Laminating Resin-
Epoxy Srm Type 2
13EBC1
 As required
Methyl-Ethyl-Ketone 08BBF1
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 46
6
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SERVICE BULLETIN
Trichloroethane
Legacy
08BBU9
 As required
d
 Report the results and the planned terminating action to AIRBUS. Use
the report sheet Fig. A-GBHAA Sheet 02
 .
e
 Do the terminating action in accordance with the SRM.
NOTE
: The new repair cutout is equal to the largest outer skin
repair ply.
NOTE
: If the repair is larger than 30000 mm 2 (46.50 sq.in.),
contact AIRBUS for additional instructions.
4
 If a repair larger than 80000 mm
2
(124 sq.in.) has been detected, do the
ventilation of the core:
a
CAUTION
: TO DRILL THE HOLES APPLY MODERATE
PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT
THE END OF THE DRILLING OPERATION. DO NOT
DRILL THE OPPOSITE SHELL.
Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner
skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet
02
 and Fig. A-GBFAA Sheet 03
 .
b
 Temporary restoration of the drain holes option 1:
<1> Close the drain holes with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
<2> Do repetitive detailed inspections of the restored area for loose or
lost adhesive disks or tape until the repair of the affected area has
been done.
<3> In case of loose or lost tape or disks, close the holes again with:
Adhesive Film
Tape- Aluminium
Foil
05RAB9
 As required
or
Self-Adhes. Disks 05TNB1
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 47
6
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SERVICE BULLETIN
c
 Temporary restoration of the drain holes option 2:
<1> Close the drain holes in accordance with the instructions given in
the Figure Fig. A-GAAAA Sheet 01
 and Fig. A-GAAAA Sheet 02
 .
<a> Consumable material needed to close the drain holes:
Pressure Sensitive
Tape
05RFB1
 As required
Laminating Resin-
Epoxy Srm Type 2
13EBC1
 As required
Methyl-Ethyl-Ketone 08BBF1
 As required
Trichloroethane
Legacy
08BBU9
 As required
d
 Report the results and the planned terminating action to AIRBUS. Use
the report sheet Fig. A-GBHAA Sheet 02
 .
e
 Do the terminating action:
Replace the rudder in accordance with the grace period given in the
accomplishment timescale table
or
replace the affected rudder shell.
NOTE
: The rudder shell replacement can be done only at
the AIRBUS Stade facility. Before sending the rudder,
contact:
AIRBUS
Department SBO5 Monitored Retrofit Campaign Account
MONITORED.RETROFIT@airbus.com
to validate the feasibility of the rudder shell replacement.
No further action is necessary in accordance with this Service Bulletin.
(7) Subtask 552051-832-207- 001 - Inspect the rudder side shell upper GFRP areas
Manpower Resources
Manhours
 0
Minimum number of person
 1
Subtask elapsed time
 0
Skills
 NON DESTRUCTIVE
TESTING
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 48
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 57

@A310
SERVICE BULLETIN
Material necessary to do the job
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
References
Non Destructive Test Manual (NTM)
 51-10-03, Page Block 501
51-10-19, Page Block 501
55-40-50 , Page Block 1001
Structural Repair Manual (SRM)
 51-75-10
51-75-20
Fig. A-GBBAA
Repair type identification
Sheet 01
Sheet 02
Fig. A-GBEAA
Typical pulse thermography and
ELCH/UT inspection
Sheet 01
Sheet 02 - Repair size assessment
Sheet 03 - Repair size assessment
Sheet 04 - Boundary and grid of ELCH/UT
inspection
Sheet 05 - ELCH inspection grid
Fig. A-GFAAA
Flow Chart
Sheet 01 - Flow Chart 1
Sheet 02 - Flow Chart 2
Sheet 03 - Flow Chart 3
Sheet 04 - Flow Chart 4
Sheet 05 - Flow Chart 5
Sheet 06
Fig. A-GABAA
Paint borer instructions
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Sheet 08
(a) If repairs in the rudder side shell upper GFRP area are recorded, do the
subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA Sheet 04
 :
1
 Make sure that the paint thickness in the areas to be inspected does not
exceed:
- 400 microns.
- 400 microns below the decal foil if a decal foil is installed.
NOTE
: It is the responsibility of the operator to ensure that the paint
thickness in all areas to be inspected is below or equal to the
limit of 400 microns.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 49
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 58

@A310
SERVICE BULLETIN
a
 If the paint coating and/or logo application is too thick, abrade the paint in
accordance with the
 SRM 51-75-20 below or equal to the limit of 400
microns.
NOTE
: Chemical paint stripping is not allowed.
b
 In case of doubts about the paint thickness, measure the thickness using
a Paint Borer Kit, refer to the Figure
 Fig. A-GABAA Sheet 01
 thru Fig. A-
GABAA Sheet 08
.
<1>
CAUTION
: DO NOT DRILL DEEPLY INTO THE BASE
MATERIAL (CFRP OR GFRP). DRILLING TOO
DEEP LEADS TO DAMAGE IN THE OUTER SKIN
If you damage the outer skin with the paint borer, refer to the
Subtask 552051-833-201-001 for repair instructions.
2
 Clean the areas to be inspected with:
Non Aqueous
Cleaner-General
08BAA9
 As required
and
Textile-Lint Free
Cotton
14SBA1
 As required
3
 Do a pulse thermography inspection to get the precise location and size of the
repair, refer to NTM 55-40-50 , Page Block 1001.
NOTE
: As an alternative for the pulse thermography inspection, you
can identify the repair size by local sanding, refer to Subtask
553043-832-208-001.
NOTE
: The pulse thermography inspection indicates the outer skin
repair ply geometry. The largest repair ply defines the
boundary of the repair area.
NOTE
: Make sure that you use the pulse thermography inspection
parameters for GFRP, refer to
 NTM 55-40-50 , Page Block
1001.
4
 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02
 and
Fig. A-GBEAA Sheet 03
 .
5
 If a repair type A-A, refer to
 Fig. A-GBBAA Sheet 02
 , has been identified, do a
Tap test inspection on the repair, refer to NTM 51-10-03, Page Block 501
 or
NTM 51-10-19, Page Block 501 to identify a skin to core disbonding.
6
 For all other repair types, do the ELCH and/or UT inspection around the
repair, refer to the Subtask 552051-832-205-001 of this Service Bulletin.
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 50
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 59

@A310
SERVICE BULLETIN
7
 If fluid ingress has been detected, refer to Subtask 552051-832-204-001 of
this Service Bulletin.
8
 For further actions continue with the instructions given in the Subtask
552051-832-206-001 and the actions in the Flow Chart Fig. A-GFAAA Sheet
02
 of this Service Bulletin.
9
 After the inspection, restore the paint coating in accordance with the
 SRM
51-75-10.
NOTE
: Refer to OIT 999.0130/06 ’pai nt system - best practices’.
(b) If there is no information about repairs in the rudder side shell upper GFRP area,
do the subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA
Sheet 04
:
1
 Make sure that the paint thickness in the areas to be inspected does not
exceed:
- 400 microns.
- 400 microns below the decal foil if a decal foil is installed.
NOTE
: It is the responsibility of the operator to ensure that the paint
thickness in all areas to be inspected is below or equal to the
limit of 400 microns.
a
 If the paint coating and/or logo application is too thick, abrade the paint in
accordance with the
 SRM 51-75-20 below or equal to the limit of 400
microns.
NOTE
: Chemical paint stripping is not allowed.
b
 In case of doubts about the paint thickness, measure the thickness using
a Paint Borer Kit, refer to the Figure
 Fig. A-GABAA Sheet 01
 thru Fig. A-
GABAA Sheet 08
.
<1>
CAUTION
: DO NOT DRILL DEEPLY INTO THE BASE
MATERIAL (CFRP OR GFRP). DRILLING TOO
DEEP LEADS TO DAMAGE IN THE OUTER SKIN
If you damage the outer skin with the paint borer, refer to the
Subtask 552051-833-201-001 for repair instructions.
2
Non Aqueous
Cleaner-General
08BAA9
 As required
Textile-Lint Free
Cotton
14SBA1
 As required
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 51
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 60

@A310
SERVICE BULLETIN
3
 Do a pulse thermography inspection on the complete GFRP area to identify
repairs, refer to NTM 55-40-50 , Page Block 1001.
NOTE
: The pulse thermography inspection indicates the outer skin
repair ply geometry. The largest repair ply defines the
boundary of the repair area.
NOTE
: Make sure that you use the pulse thermography inspection
parameters for GFRP, refer to
 NTM 55-40-50 , Page Block
1001.
4
 If repairs which are not manufacturing rework have been identified, mark the
boundary of the repair area, refer to Fig. A-GBEAA Sheet 02
 and Fig. A-
GBEAA Sheet 03
.
5
 Do a Tap test inspection, refer to NTM 51-10-03, Page Block 501
 or NTM
51-10-19, Page Block 501, on the complete GFRP area to identify a skin to
core disbonding.
6
 Do the ELCH and/or UT inspection around the repair, refer to the Subtask
552051-832-205-001 of this Service Bulletin.
7
 If fluid ingress has been detected, refer to Subtask 552051-832-204-001 of
this Service Bulletin.
8
 For further actions continue with the instructions given in the Subtask
552051-832-206-001 and the actions in the Flow Chart Fig. A-GFAAA Sheet
02
 of this Service Bulletin.
9
 After the inspection, restore the paint coating in accordance with the
 SRM
51-75-10.
NOTE
: Refer to OIT 999.0130/06 ’pai nt system - best practices’.
(8) Subtask 552051-833-201-001 - Close the holes in case of drilling thru the outer
skin during paint thickness measurement
Manpower Resources
Manhours
 0
Minimum number of person
 1
Subtask elapsed time
 0
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Adhesive Film Tape-
Aluminium Foil
05RAB9
 As required
Self-Adhes. Disks
 05TNB1
DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051
REVISION No.: 01 - Aug 20/14 Page: 52
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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