@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER SIDE 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

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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

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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

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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

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER SIDE 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

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@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

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@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

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@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

Z326

A

RUDDER SHELL

TO BE INSPECTED

B

B A

RH SHOWN LH 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.
@A310

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER SIDE 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

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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

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@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

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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

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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 Aviation Safety Agency (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

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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 mm2

(85.25 sq.in) detected

Report to AIRBUS Within 1 month from the

pulse thermography

inspection

None

Repairs in the booster

area > 55000 mm2

(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

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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

No skin to core

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

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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

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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 mm2

(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 mm2

(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

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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

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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 mm2

(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

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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 mm2

(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 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

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 mm2 (15.50 sq.in.), continue with

table 4.A.

For an identified repair size larger than 10000 mm2 (15.50 sq.in.) up to 20000 mm2

(31.00 sq.in.), continue with table 4.B.

For an identified repair size larger than 20000 mm2 (31.00 sq.in.) up to 80000 mm2 (124

sq.in.), continue with table 4.C.

For an identified repair size larger than 80000 mm2 (124 sq.in.), continue with table 4.D.

Table 4.A, Config. 001 - Identified repair size of a maximum of 10000 mm2 (15.50 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size =< 10000

mm2 (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

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SERVICE BULLETIN

Table 4.B, Config. 001 - Identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000

mm2 (31.00 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 10000

mm2 (15.50 sq.in.) and

=< 20000 mm2 (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

mm2 (15.50 sq.in.) and

=< 20000 mm2 (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

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SERVICE BULLETIN

Table 4.B, Config. 001 - Identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000

mm2 (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 mm2 (31.00 sq.in.) and up to 80000

mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 20000

mm2 (31.00 sq.in.) and

=< 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 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

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SERVICE BULLETIN

Table 4.C, Config. 001 - Identified repair size larger than 20000 mm2 (31.00 sq.in.) and up to 80000

mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Core ventilation done

and repair size =<

30000 mm2 (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 mm2 (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

mm2 (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

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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 mm2

(85.25 sq.in.) detected

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(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

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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 mm2

(85.25 sq.in.) detected

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(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

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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 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(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

REVISION No.: 01 - Aug 20/14 Page: 18

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SERVICE BULLETIN

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

REVISION No.: 01 - Aug 20/14 Page: 19

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SERVICE BULLETIN

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 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 m2 (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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 20

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SERVICE BULLETIN

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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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

Tel : (33) 5 67 19 06 22

Fax : (33) 5 61 93 27 45

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

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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

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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

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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, ADHESIVES, 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. AGBCAA 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 complete 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 CleanerGeneral08BAA9

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. AGABAA 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 mm2 (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 mm2 (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 ’paint 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 CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

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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.

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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. AGABAA 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

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Rudder PN Refer to Figure

A55471500 Fig. A-GBDAA Sheet 04

8 If repairs in the booster areas up to 55000 mm2 (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 mm2 (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 ’paint 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 TapeAluminium Foil05RAB9 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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

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 mm2 (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

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SERVICE BULLETIN

4 If a maximum of 5 local single spots per side shell larger than 1500 mm2 (2.33

sq.in.) and up to 5000 mm2 (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

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@A310

SERVICE BULLETIN

Laminating ResinEpoxy 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 mm2 (2.33

sq.in.) and up to 5000 mm2 (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 mm2 (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 CleanerGeneral08BAA9 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

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

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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@A310

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 TapeAluminium Foil05RAB9 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

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@A310

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 mm2 (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 mm2 (15.50 sq.in.) and up to 20000 mm2 (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

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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 ResinEpoxy Srm Type 213EBC1 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

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@A310

SERVICE BULLETIN

3 If a repair larger than 20000 mm2 (31.00 sq.in.) and up to 80000 mm2 (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 ResinEpoxy 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

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@A310

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 mm2 (46.50 sq.in.),

contact AIRBUS for additional instructions.

4 If a repair larger than 80000 mm2 (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

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@A310

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 ResinEpoxy Srm Type 213EBC1 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

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@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 CleanerGeneral08BAA9 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

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@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. AGABAA 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

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@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 ’paint 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. AGABAA 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

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@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. AGBEAA 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 ’paint 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 TapeAluminium Foil05RAB9 As required

Self-Adhes. Disks 05TNB1

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Laminating Resin-Epoxy

Srm Type 2

13EBC1 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Structural Repair Manual (SRM) 51-75-10

51-77-00 Page Block 101 Para 6

51-77-10 Para 2

51-77-10 Para 3.D

51-77-11 Para 4.A.(3)

51-77-11 Para 4.E

(a) Hole closing procedure option 1:

1

WARNING: OBEY THE MANUFACTURER’S 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,

ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS

ARE DANGEROUS.

Prepare and dry the restoration area in accordance with the SRM 51-77-10

Para 2.

2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):

Laminating ResinEpoxy Srm Type 213EBC1 As required

NOTE: The data sheets for each adhesive, resin or low density

compound states the maximum quantity that can be safely

mixed at one time without causing an exotherm reaction.

Always refer to the appropriate data sheet before mixing the

chosen material.

3 Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F).

4 Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.)

and inject the resin through the hole into the cells of the honeycomb core.

Start the injection at the cell bottom and finish when the resin is leaking out of

the hole.

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5 Close the filled holes with

Adhesive Film

Tape- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

6 Let the resin cure for a minimum of 6 hours at room temperature.

If the room temperature is below 18 ̊C (64F), extend the curing time and

perform a gelation test outside the restoration area. After resin gelation plus 2

h, the aircraft can be released to operations again.

OR

Cure the resin at 60 ̊C (140F) for 45 minutes. Install a heating blanket with a

vacuum bag on the rudder surface and control the temperature by means of

thermocouples in accordance with the SRM 51-77-10 Para 3.D.

7 Do the final surface restoration in accordance with the compliance time given

in Para 1.E.(2), table 5:

a Remove the self adhesive tape from the restoration areas.

b Inspect the restoration in accordance with the SRM 51-77-00 Page Block

101 Para 6.

c Remove any surplus resin from the border area of the restoration. Use

abrasive cloth. Start with 280 grade and finish with 400 grade.

d Clean the restoration areas in accordance with the SRM 51-77-11 Para

4.E with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

e Restore the surface protection in accordance with the SRM 51-75-10.

(b) Hole closing procedure option 2:

1

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN

YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS

AND PAINTS: THESE MATERIALS ARE DANGEROUS.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES

AND FILTER MASKS WHEN YOU USE CLEANING AGENTS,

ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS

ARE DANGEROUS.

Prepare and dry the restoration area in accordance with the SRM 51-77-10

Para 2.

2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):

Laminating ResinEpoxy Srm Type 213EBC1 As required

NOTE: The data sheets for each adhesive, resin or low density

compound states the maximum quantity that can be safely

mixed at one time without causing an exotherm reaction.

Always refer to the appropriate data sheet before mixing the

chosen material.

3 Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F).

4 Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.)

and inject the resin through the hole into the cells of the honeycomb core.

Start the injection at the cell bottom and finish when the resin is leaking out of

the hole.

5 Close the filled holes with

Adhesive Film

Tape- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

6 Let the resin cure for a minimum of 12 hours at room temperature.

If the room temperature is below 18 ̊C (64F), extend the curing time and

perform a gelation test outside the restoration area.

After resin gelation plus 4 h, continue with the subsequent steps:

a Remove the self adhesive tape from the restoration areas.

b Inspect the restoration in accordance with the SRM 51-77-00 Page Block

101 Para 6.

c Remove any surplus resin from the border area of the restoration. Use

abrasive cloth. Start with 280 grade and finish with 400 grade.

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d Clean the restoration areas in accordance with the SRM 51-77-11 Para

4.E, with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

e Restore the surface protection in accordance with the SRM 51-75-10.

(9) Subtask 552051-832-208-001 - Identify the repair size by local sanding

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 55-40-50

Structural Repair Manual (SRM) 51-10-00

51-10-14

51-23-10

51-75-10

51-77-10 Para 2.D.

51-77-10 Para 2.E

51-77-10 Para 2.G.

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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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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

CAUTION: IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT

STRUCTURAL SIDE SHELL OUTER SKIN PLY (CFRP OR GFRP) IN

ACCORDANCE WITH THE DESIGN DRAWING IS NOT DAMAGED

DURING THE LOCAL SANDING PROCESS.

REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER

SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY. IN

CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT

FLIGHT IS REQUIRED. AN AREA DAMAGED BY THE LOCAL

SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD

TO A NON-REPAIRABLE SIZE AND SUBSEQUENT SIDE SHELL

REPLACEMENT.

NOTE: The local sanding procedure is only valid for fully documented repairs.

(a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA

Sheet 01, beginning with the box ’LOCAL PAINT THICKNESS IDENTIFICATION’.

1 Identify the paint thickness and the initial basic primer on top of the repair and

beside the repair location.

NOTE: It is recommended to use a Paint Borer Kit Model 518, 518S

or 518MC.

2 Clean the previous repair area in accordance with the SRM 51-77-10 Para

2.E.

3 Do a local mechanical sanding on top and around the repair in accordance

with the SRM 51-77-10 Para 2.D. on a step-by-step basis up to the initial

basic primer layer.

NOTE: The allowed maximum repair size is 1m2 (10.76sq.ft.) per local

repair.

4 If the largest repair ply is visible:

a Remove the dust and dry the area in accordance with the SRM 51-77-10

Para 2.G.

b Use a magnifying lens to inspect the sanded area for damage.

<1> In case of findings, do the damage assessment in accordance with

the SRM 51-10-00 thru SRM 51-10-14.

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c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

d 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

e If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings 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

<1> Restore the surface protection in accordance with the SRM

51-75-10.

No further actions on these repairs in accordance with this Service

Bulletin.

f If repairs in the booster areas larger than 55000 mm2 (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.

g 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.

h If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 552051-832-204-001 of this Service Bulletin.

i After the inspection, restore the paint coating in accordance with the

SRM 51-75-10 and SRM 51-23-10.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

5 If the largest repair ply is not visible, continue the local mechanical sanding on

top and around the repair in accordance with the SRM 51-77-10 Para 2.D.

on a step-by-step basis up to the pore filler or adhesive with a radius of

approximately 50.0mm (1.97in.) beyond the initial detected repair patch.

6 If the largest repair ply is visible now:

a Remove the dust and dry the area in accordance with the SRM 51-77-10

Para 2.G..

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b Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

c Use a magnifying lens to inspect the sanded area for damage.

d In case of findings, do the damage assessment in accordance with the

SRM 51-10-00 thru SRM 51-10-14.

e 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

f If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings 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

<1> Restore the surface protection in accordance with the SRM

51-75-10.

No further actions on these repairs in accordance with this Service

Bulletin.

g If repairs in the booster areas larger than 55000 mm2 (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.

h 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.

i If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 552051-832-204-001 of this Service Bulletin.

j After the inspection, restore the paint coating in accordance with the

SRM 51-75-10 and SRM 51-23-10.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

7 If the largest repair ply is still not visible:

a Remove the dust and dry the area in accordance with the SRM 51-77-10

Para 2.G..

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b Do a pulse thermography inspection to get the precise location and the

size of the repair, refer to NTM 55-40-50.

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.

c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

d If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 552051-832-204-001 of this Service Bulletin.

e 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

f If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings to AIRBUS. Use the report sheet

Fig. A-GBHAA Sheet 02and 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

<1> Restore the surface protection in accordance with the SRM

51-75-10.

No further actions on these repairs in accordance with this Service

Bulletin.

g If repairs in the booster areas larger than 55000 mm2 (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.

h 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.

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i After the inspection, restore the paint coating in accordance with the

SRM 51-75-10 and SRM 51-23-10.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

D. TEST

None

E. CLOSE-UP

(1) Subtask 552051-942-201-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 55-40-00, Page Block 601

55-42-11, Page Block 401

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

equipment

(b) To install the access panel 326AL on rudders, which have not embodied Mod.

8827, refer to AMM 55-42-11, Page Block 401.

(c) Remove the access platforms.

(d) Do the rudder inspection/check Close-up procedure, refer to AMM 55-40-00, Page

Block 601.

(e) In the cockpit, remove all warning notices.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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**CONF ALL

NOTE:

REMOVE AND INSTALL ACCESS PANEL

AS PER AMM 55−42−11. 

POSITION OF

RUDDER S/N PLACARD

Z326

A

326AL

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

A55471XXXXXXX

TS(HF)−XXXX

01

01

B

B

A C

VALID FOR RUDDERS BEFORE

MODIFICATION NO.8827

B_SB_552051_6_BAAA_01_02

Figure A-GBAAA - Sheet 01

Rudder SN identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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**CONF ALL

POSITION OF

RUDDER S/N PLACARD

VALID FOR RUDDERS AFTER

MODIFICATION NO.8827

02

NOTE:

02 USE A MIRROR OR FLEXIBLE ENDOSCOPE IF NECESSARY

C

B

B

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

A55471XXXXXXX

TS(HF)−XXXX

B_SB_552051_6_BAAA_02_00

Figure A-GBAAA - Sheet 02

Rudder SN identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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**CONF ALL

Z326

A

B_SB_552051_6_BBAA_01_00

A LH SHOWN

RH SIMILAR

A

A

B

B

C

C

D

D

E

E

F

F

Figure A-GBBAA - Sheet 01

Repair type identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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**CONF ALL

OUTER SKIN WITH AND WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR

WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR

WITH CORE CLOSING

BOTH SKIN AND CORE REPAIR

DELAMINATION AND 

CORE DAMAGE WITH CORE CLOSING 

(SRM 55−41−12 PAGE BLOCK 201 FIG.203)

A A

B B

C C

(SRM 55−41−12 PAGE BLOCK 201 FIG.202)

(SRM 55−41−12 PAGE BLOCK 201 FIG.204/205)

(SRM 55−41−12 PAGE BLOCK 201 FIG.204/205)

(SRM 55−41−12 PAGE BLOCK 201 (SRM 55−41−12 PAGE BLOCK 201 

D D

E E

F F

FIG. 208A/208B/209 /211/212/213/213A/214/217) FIG. 208A/208B/209/211/212 /213/213A/214/217)

BOTH SKIN AND CORE REPAIR WITH AND

WITHOUT CORE CLOSING / REPAIR WITH

ACCESS FROM BOTH SIDE

WITH AND WITHOUT CORE CLOSING /

REPAIR WITH ACCESS FROM ONE SIDE ONLY

B_SB_552051_6_BBAA_02_04

Figure A-GBBAA - Sheet 02

Repair type identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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**CONF ALL

CHAPTER REPAIR PROCEDURE PARA. FIG.

A310 SRM ISSUE: 01. JUN 2009

55−41−12 REPAIR OF LIGHTNING PROTECTION PLATE 12. 207

55−41−12 REPAIR OF APEX STRIP FOR STATIC DISCHARGER 13. 208

55−41−12 REPAIR OF LOWER SHELL EDGE 20. 210

55−41−12 REPLACEMENT OF BLINDNUT 26. 215

55−41−12 REPAIR OF DELAMINATION OF GFRP FITTING CONNECTION 1 THRU 7 27. 216

55−41−12 INSTALLATION OF REINFORCING PLATES FOR HANDHOLES 29. 218

55−41−12 REPAIR OF SKIN DAMAGE AT SCREW LINE 31. 221, 222

AT GFRP FITTING CONNECTION 6 AND 7

(AROUND/NEAR SCREW POINTS)

55−41−12 REPAIR OF DAMAGE AT LOWER AFT HOIST POINT 32. 223

55−41−12 REPAIR OF DAMAGE AT LOWER FWD HOIST POINT 33. 224

55−41−12 REPAIR OF DAMAGE AT UPPER HOIST POINT 34. 225

55−41−12 REPAIR OF SKIN DAMAGE IN REPAIR ZONE A AND ZONE J 30. 219, 220

55−41−12 REPAIR OF SURFACE CRACK 6. 201

55−41−12 REPAIR OF ATTACHMENT EDGE 11. 206

55−41−12 REPAIR OF APEX STRIP 16. 208C

55−41−12 TEMPORARY REPAIR FOR LARGE DAMAGE 17. 208D

55−41−12 TEMPORARY REPAIR FOR DEBONDING WITHOUT CRACKS AND HOLES 18. 208E

B_SB_552051_6_BCAA_01_03

Figure A-GBCAA - Sheet 01

Repair type identification - SRM list

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**CONF ALLFAM A/C TYP MSN Airline Rudder S/N Damage report date RAS Reference ISB Inspection required

WB A300B4−600 354 PFD NOT REPORTED (HF−1078) 17. OCT. 1994 RAS/DAHAM/0216/94 YESWB A310 392 AIC HF−1137 3. DEC. 2007 RAS/DAHAM/4023488/2007 NOWB A310 397 FDX HF−1099 13. NOV.2008 RAS/DAHAM/4026439/2008 NOWB A310 446 CDN NOT REPORTED (NO DATA) 29. MAR. 1995 RAS/DAHAM/1028/95 YESWB A310 476 THY NOT REPORTED (HF−1171) 22. APR. 2002 RAS/DAHAM/4015292/2002 YESWB A310 483 TAP HF−1190 27. MAR. 2008 RAS/DAHAM/4024646/2008 NOWB A300B4−600 530 AIB HF−1236 23. JUN. 2005 RAS/DAHAM/4019647/2005 NOWB A300B4−600 533 GXY HF−1240 2. JAN. 2008 RAS/DAHAM/4024029/2008 NOWB A300B4−600 536 FDX HF−1244 8. NOV. 2007 RAS/DAHAM/4023298/2007 NOWB A310 537 THY NOT REPORTED (HF−1255) 10. JUN. 2002 RAS/DAHAM/4015486/2002 YESWB A300B4−600 540 MON HF−1242 4. MAR. 2008 RAS/DAHAM/4024490/2008 NOWB A310 541 TAP HF−1260 21. DEC. 2007 RAS/DAHAM/4024000/2007 NOWB A300B4−600 558 TAR NOT REPORTED (HF−1261) 12. JAN. 2004 RAS/DAHAM/4017787/2004 YESWB A310 565 TAP NOT REPORTED (HF−1289) 23. OCT. 2006 RAS/DAHAM/4021406/2006 YESWB A300B4−600 604 MON HF−1270 20. FEB. 2008 RAS/DAHAM/4024422/2008 NOWB A300B4−600 624 AUA TS−1343 28. JAN.1998 RAS/DAHAM/1019/98 YESWB A300B4−600 630 FDX TS−1351

21. JUN. 1999

RAS/DAHAM/4025917/2008 NO

WB A300B4−600 713 CES NOT REPORTED (TS−1418)

21. OCT. 2003

RAS/DAHAM/4011302/1999 YES

WB A300B4−600 782 THA NOT REPORTED (TS−2080)

31. JUL. 2002

RAS/DAHAM/4017547/2003 YES

WB A300B4−600 824 UPS NOT REPORTED (TS−2123) RAS/DAHAM/4015671/2002 YESWB A300F4−600 858 AHK TS−2150 8. AUG. 2006 RAS/DAHAM/4021168/2006 YESWB WB ALL SPARE UPS TS−2194 29. DEC. 2008 RAS/DAHAM/4026846/2008 NO

19. SEP. 2008

WB 434 HF−1136 RAS/DAHAM/4023199/2007 NOWB HF−1163 RAS/DAHAM/4025922/2008 NO

A310A310 447

GAF

TSC

17.OCT.2007

18.SEP.2008

B_SB_552051_6_BCAA_02_03

Figure A-GBCAA - Sheet 02

Repair type identification - RAS list

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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**CONF ALL

Z326

A

A

B D

B_SB_552051_6_BDAA_01_00

C D

Figure A-GBDAA - Sheet 01

Booster area definition

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

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**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

A55471730

A55471710

B LH SHOWN

1040.0 mm

(40.94 in)

1760.0 mm

(69.30 in)

2070.0 mm

(81.50 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

B_SB_552051_6_BDAA_02_00

Figure A-GBDAA - Sheet 02

Booster area definition

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 69

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

A55471730

A55471710

1035.0 mm

(40.75 in)

2000.0 mm

(78.74 in)

1950.0 mm

(76.77 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

C RH SHOWN

B_SB_552051_6_BDAA_03_00

Figure A-GBDAA - Sheet 03

Booster area definition

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 70

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

A55471500

LH SHOWN

RH SYMMETRICAL

675.0 mm

(26.57 in)

1060.0 mm

(41.73 in)

2950.0 mm

(116.14 in)

BR1

BR3

BR4

BR5

BR6

BR7

BR2

B_SB_552051_6_BDAA_04_00

D

Figure A-GBDAA - Sheet 04

Booster area definition

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 71

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Z326

A

A

B E

B E

B_SB_552051_6_BEAA_01_01

Figure A-GBEAA - Sheet 01

Typical pulse thermography and ELCH/UT inspection

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 72

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

TYPICAL 

PULSE THERMOGRAPHY

INSPECTION

LH SHOWN

RH SYMETRICAL

BR1

BR2

BR3

BR4

BR5

BR6

BR7

B

C

D

B_SB_552051_6_BEAA_02_02

Figure A-GBEAA - Sheet 02

Typical pulse thermography and ELCH/UT inspection - Repair size assessment

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 73

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

REPAIR SIZE = D2 x /4

100.0mm x 100.0mm

(3.93 in x 3.93 in)

(15.50 sq.in)

DAMAGE IN THE 

OUTER SKIN AND CORE

MAX. REPAIR PLY

REPAIR PLY

D

 (110.0mm)2 x /4

= (4.33 in2 x /4)

 ca. 10 000 mm2 =

DAMAGE IN THE 

OUTER SKIN AND CORE

MAX. REPAIR PLY

REPAIR PLIES

REPAIR SIZE = A x B

=

50.0mm x 200.0mm

(1.97 in x 7.87 in) =

OR

(15.50 sq.in)

10 000 mm2 =

B

A

EXAMPLE:

EXAMPLE:

D = 110.0mm DIA

C

D

02 THE NEW CUTOUT SIZE FOR THE REPAIR IS THE

SIZE OF THE FORMER OUTER SKIN REPAIR PLY.

02

02

B_SB_552051_6_BEAA_03_02

Figure A-GBEAA - Sheet 03

Typical pulse thermography and ELCH/UT inspection - Repair size assessment

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 74

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

TYPICAL 

ELCH/UT

INSPECTION

LH SHOWN

RH SYMETRICAL

BR1

BR2

BR3

BR4

BR5

BR6

BR7

MAX. REPAIR PLY

INSPECTION AREA

ELCH/UT

A

SKIN THICKNESS 1.5mm (0.23 in):

A=200.0mm (7.87 in) 

AROUND THE MAX. REPAIR PLY 

ELCH METHOD

GRID = 75.0mm x75.0mm (2.95 in x 2.95 in)

SKIN THICKNESS 1.5mm (0.23 in):

A=75.0mm (2.95 in) 

AROUND THE MAX. REPAIR PLY 

UT−METHOD

E

F

B_SB_552051_6_BEAA_04_01

Figure A-GBEAA - Sheet 04

Typical pulse thermography and ELCH/UT inspection - Boundary and grid of ELCH/UT inspection

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 75

6

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@A310

SERVICE BULLETIN

**CONF ALL

TYPICAL TRAILING EDGE

ELCH INSPECTION

NOTE:

DISTANCE FROM EDGE 

F

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

EXISTING SCREW

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

01

01

INSPECTION POINT

ELCH TOOL

TYPICAL TRAILING EDGE

ELCH INSPECTION

AROUND REPAIR AREA

75.0 mm

(2.95 in) 75.0 mm

(2.95 in)

MAX. REPAIR PLY

02

02

02 SCREWS AND ELCH TOOL ARE NOT DRAWN TO SCALE

B_SB_552051_6_BEAA_05_06

Figure A-GBEAA - Sheet 05

Typical pulse thermography and ELCH/UT inspection - ELCH inspection grid

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 76

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Z326

A

A

B

B

B_SB_552051_6_BFAA_01_00

Figure A-GBFAA - Sheet 01

Core ventilation procedure

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 77

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

MAX. RECTANGULAR REPAIR SIZE 100.0mm (3.94 in):

DRILL HOLES THRU INNER AND OUTER SKIN.

CAUTION: DO NOT DRILL THE OPPOSITE SHELL.

NOTE:

03

01

MIN. 90.0 mm

(3.54 in)

100.0 mm

(3.94 in)

02 REPAIR SIZE DETECTED BY THERMOGRAPHY

MAX. REPAIR PLY

02

APPLICABLE TO MAX. 6 HOLES

IN A ROW

TYPICAL 

CORE VENTING

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.),

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

MAX. 100.0 mm

(3.94 in)

03

C

DRILL 1 ROW IN THE MID OF THE REPAIR.

IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN

100.0mm (3.94 in), DRILL 2 ROWS 

AS SHOWN IN FIG. A−GBFAA, SHEET 03.

05 CONFIRM BY AN ADDITIONAL INSPECTION THAT THE DRILL

HOLE HAS PENETRATED THE INNER SKIN.

(E.G. BY INSERTING A SUITABLE PIN DEEPER THAN NOMINAL

PANEL THICKNESS, OR BY ILLUMINATION OF THE RUDDER

FROM INSIDE THROUGH A HOLE IN THE SPAR AND VISUAL

INSPECTION THROUGH THE DRILL HOLE.)

A A

01

3.0 mm DIA

(0.12 in)

01

OUTER SKIN

INNER SKIN

OPPOSITE SHELL

MAX. REPAIR PLY

02

C D

A 05

A

50.0 mm

(1.97 in)

TE−SCREW

B

B_SB_552051_6_BFAA_02_05

Figure A-GBFAA - Sheet 02

Core ventilation procedure

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 78

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN

100.0 mm

(3.94 in)

NOTE:

04

MIN. 90.0 mm

(3.54 in) MIN. 90.0 mm (3.54 in)

100.0 mm

(3.94 in)

02 REPAIR SIZE DETECTED BY THERMOGRAPHY

MAX. REPAIR PLY

02

04

D

APPLICABLE TO MAX. 6 HOLES

IN A SQUARE GRID

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.),

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

> 100.0 mm

(3.94 in)

100.0 mm (3.94 in), DRILL 2 ROWS.

B_SB_552051_6_BFAA_03_01

Figure A-GBFAA - Sheet 03

Core ventilation procedure

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 79

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Z326

A

A

C E

B D

B_SB_552051_6_BGAA_01_00

Figure A-GBGAA - Sheet 01

Rudder skin thickness identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 80

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER

A55471730

LH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

SKIN THICKNESS 

A55471710

> 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

B

B_SB_552051_6_BGAA_02_00

Figure A-GBGAA - Sheet 02

Rudder skin thickness identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 81

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

A55471730

RH SHOWN SKIN THICKNESS 

A55471710 > 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

C

B_SB_552051_6_BGAA_03_00

Figure A-GBGAA - Sheet 03

Rudder skin thickness identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 82

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

A55471500

LH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

33

38

10

SKIN THICKNESS 

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

NO INSPECTION

D

B_SB_552051_6_BGAA_04_00

Figure A-GBGAA - Sheet 04

Rudder skin thickness identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 83

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

A55471500

RH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

30

40

10

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

< 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

E

B_SB_552051_6_BGAA_05_00

Figure A-GBGAA - Sheet 05

Rudder skin thickness identification

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 84

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

REPAIR DETECTED WITH NIL DAMAGE

NO REPAIR DETECTED

PLEASE SEND REPORTING SHEET TO:

AIRBUS

CUSTOMER SERVICE STRUCTURE ENGINEERING

DEPARTMENT SEES2

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Structure.sbinspectionresult@airbus.com

REPAIR DETECTED WITH DAMAGE

PLEASE SEND REPORTING SHEET TO:

DEPARTMENT SEOE1/2/3

NOTE: ATTACH ALSO THE INITIAL PUSLE THERMOGRAPHY PHOTOS.

PREVIOUS REPORTS PER SB55−2051 REV00 FIGURE A−GBHAA − SHEET 01/02/03 ARE VALID

AIRCRAFT

MSN

RUDDER S/N

INSPECTION DATE

FLIGHT CYCLES FC

FLIGHT HOURS FH

DATA

PULSE THERMOGRAPHY

COMPLETE INSPECTION LH AND RH SIDE

YES/NO

INSPECTION RESULT

REPAIR DETECTED

LH

RH

LIQUID INGRESS DETECTION

DAMAGE CHECK UT − ELCH INDICATION

SUMMARY

RUDDER SIDE SHELLS SANDWICH REPAIR PULSE THERMOGRAPHY REPORT

B_SB_552051_6_BHAA_01_05

Figure A-GBHAA - Sheet 01

Report sheet and sketches - Pulse thermography report sheet

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 85

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

PLEASE SEND REPORTING SHEET TO:

AIRBUS

CUSTOMER SERVICE STRUCTURE ENGINEERING

DEPARTMENT SEES2

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Structure.sbinspectionresult@airbus.com

FIGURE A−GBHAA − SHEET 01 / REPORT SHEET AND SKETCHES − REPORT SHEET

PREVIOUS REPORTS PER SB55−2051 REV00 FIGURE A−GBHAA − SHEET 01 ARE VALID

AIRCRAFT

MSN

RUDDER S/N

RECORDS REVIEW DATE

DATA

RECORDS STATUS

REPAIR RECORDS COMPLETE SINCE ORIGINAL

YES/NO

REPAIR SCHEME

RUDDER FLIGHT CYCLES / FLIGHT HOURS

REPAIR DATE

LH OR RH SIDE SHELL

SRM FIGURE 2XX (SRM 55−41−00 AND/OR 55−41−13 PB201)

DAMAGE SIZE (CIRCULAR) DIAMETER IN mm

SUMMARY

RUDDER SIDE SHELLS SANDWICH REPAIR RECORDS

SRM (STRUCTURAL REPAIR MANUAL) REPAIR PERFORMED

REPAIR APPROVED BY LOCAL AIRWORTHINESS

DAMAGE SIZE (RECTANGULAR SHAPE) LENGTH AND WIDTH IN mm

DAMAGE SIZE (mm2)

REPAIR OUTER PLY SIZE (mm2) IF KNOWN FROM RECORDS

LOCATION AS PER SRM 55−41−00 PB101 FIGURE 103 ZONE CODE.

SERVICE BULLETIN NO.: A310−55−2051 REVXX

IN CASE OF MORE THAN 1 REPAIR, DUPLICATE THIS REPORTING SHEET

(0 FLIGHT CYCLES) EIS ENTRY INTO SERVICE

AUTHORITIES (NO AIRBUS APPROVAL)

B_SB_552051_6_BHAA_02_03

Figure A-GBHAA - Sheet 02

Report sheet and sketches - Repair records report sheet

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 86

6

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@A310

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

LH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

A55471730

A55471710

BR1

BR2

BR3

BR4

BR5

BR6

BR7

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

B_SB_552051_6_BHAA_03_01

Figure A-GBHAA - Sheet 03

Report sheet and sketches

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 87

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

RH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

A55471730

A55471710

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR1

BR2

BR3

BR4

BR5

BR6

BR7

B_SB_552051_6_BHAA_04_01

Figure A-GBHAA - Sheet 04

Report sheet and sketches

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 88

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

LH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

A55471500

BR1

BR2

BR3

BR4

BR5

BR6

BR7

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

B_SB_552051_6_BHAA_05_01

Figure A-GBHAA - Sheet 05

Report sheet and sketches

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 89

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

RH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

A55471500

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR1

BR2

BR3

BR4

BR5

BR6

BR7

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

B_SB_552051_6_BHAA_06_00

Figure A-GBHAA - Sheet 06

Report sheet and sketches

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 90

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Z326

A

B_SB_552051_6_BJAA_01_00

B C

B C

A

Figure A-GBJAA - Sheet 01

GFRP area location

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 91

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

B LH SHOWN

378.0 mm

(14.88 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

RH SYMMETRICAL

924.0 mm

(36.38 in)

GFRP AREA

CFRP AREA

A55471730

A55471710

B_SB_552051_6_BJAA_02_00

Figure A-GBJAA - Sheet 02

GFRP area location

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 92

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

A55471500

LH SHOWN

RH SYMMETRICAL

BR1

BR3

BR4

BR5

BR6

BR2

512.0 mm

(20.16 in)

BR7 985.0 mm

(38.78 in)

GFRP AREA

CFRP AREA

B_SB_552051_6_BJAA_03_00

C

Figure A-GBJAA - Sheet 03

GFRP area location

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 93

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

CHECK THE RUDDER RECORDS IF REPAIRS

(AIRBUS RAS , SRM AND OTHER ) 

NO YES

PERFORM PULSE THERMOGRAPHY

INSPECTION ON COMPLETE

FLUID REPAIR TYPE

INSPECTED IN ACCORDANCE WITH THE SB.

02 IDENTIFIED TO BE

REPORT THE INFORMATION TO AIRBUS.

01

PERFORMED

SINCE RUDDER EIS ?

REPAIR

DETECTED, WHICH

NO

YES

REPAIR 

YES NO

REPORT THE

INFORMATION TO AIRBUS.

PERFORM PULSE THERMOGRAPHY ON REPAIR 

LOCATION TO PRECISE LOCATION AND SIZE.

REPORT THE INFORMATION TO AIRBUS.

PERFORM ELCH AND/OR UT 

AROUND THE IDENTIFIED

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

REFER TO FLOW CHART 2 FOR 

ACTIONS ON IDENTIFIED REPAIRS.

YES

NO

COMPLETE REPAIR

RECORDS AVAILABLE

SINCE RUDDER EIS ?

NO YES

NO FURTHER 

ACTIONS.

CONTINUE WITH

ACTIONS AS PER

FLOW CHART 3.

REPAIRS.

NO

YES

REPORT THE INFORMATION TO AIRBUS.

SIDE SHELLS TO IDENTIFY REPAIRS:

MARK THE REPAIRS.

MARK THE REPAIRS.

YES

REPAIRS IN THE BOOSTER

AREA

REPAIR SIZE 55000mm2

03 LARGER THAN

(85.25 sq.in.)

NO

 ARE RECORDED SINCE RUDDER EIS AND

04

05

06

OR NOT IN THE BOOSTER

AREA. 03

REPAIRS IN THE BOOSTER

AREA

REPAIR SIZE 55000mm2

03 LARGER THAN

(85.25 sq.in.) 06

OR NOT IN THE BOOSTER

AREA. 03

REPORT UNDOCUMENTED RUDDER 

S/N LIST TO AIRBUS SEES2 TO GET

RELATED RUDDER MANUFACTURING

REWORK DATA 07

IS NOT MANUFACTURING

REWORK ?

08

12

12

FOR PAINT THICKNESS IDENTIFICATION

REFER TO FLOW CHART 5

FOR PAINT THICKNESS IDENTIFICATION

REFER TO FLOW CHART 5

INGRESS

DETECTED

AND

PERFORM LOCAL SANDING ON TOP AND

REPAIR PLY

OF THE REPAIR

LARGEST 

VISIBLE?

YES

NO

AROUND THE PEPAIR UP TO PRIMER. 28

PERFORM LOCAL SANDING

ON TOP AROUND THE REPAIR

UP TO ADHESIVE. 24 25

REPAIR PLY

OF THE REPAIR

LARGEST 

VISIBLE?

YES

OR

NO

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

26

LOCAL PAINT THICKNESS IDENTIFICATION 27

MARK REPAIR SIZE ON SURFACE

22 23

25

B_SB_552051_6_FAAA_01_06

Figure A-GFAAA - Sheet 01

Flow Chart - Flow Chart 1

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 94

6

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@A310

SERVICE BULLETIN

**CONF ALL

ACTIONS ON IDENTIFIED

REPAIRS

DAMAGE

DETECTED YES NO

PROVIDE DETAILED 

DAMAGE REPORT AND

REPAIR SIZE 

10000mm2, (15.50 sq.in.) −

PROVIDE DETAILED

INFORMATION TO AIRBUS 

AVAILABLE.

PERFORM REPETITIVE 

ELCH AND/OR UT

INSPECTION AROUND THE

IDENTIFIED REPAIR.

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

OR

ON IDENTIFIED REPAIR

DETAILED INFORMATION ON IDENTIFIED REPAIR IF

REPORT TO AIRBUS

AND FOLLOW THEIR

INSTRUCTIONS.

FINDINGS

YES NO

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

REPAIR IN ACCORDANCE WITH

SRM AT THE IDENTIFIED

REPAIR LOCATION.

REPAIR IN ACCORDANCE WITH

SRM AND WITH ADDITIONAL 

INSTRUCTIONS FROM AIRBUS.

REPLACE AFFECTED 

RUDDER SHELL 

OR REPLACE THE RUDDER.

09 REPAIR SIZE 09 REPAIR SIZE 09 REPAIR SIZE 09

10

10

11

TO AIRBUS SEOE 1/2/3 OR

TERMINATING ACTION

10000mm2, (15.50 sq.in.). 20000mm2, (31.00 sq.in.). 20000mm2, (31.00 sq.in.) − 80000mm2, (124.00 sq.in.). 80000mm2, (124.00 sq.in.).

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

AIRTAC AND FOLLOW

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

REPAIR TO AIRBUS SBO 5, COPY SEES2

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

TERMINATING ACTION

REPAIR SIZE 30000mm2, (46.50 sq.in.).

REPAIR SIZE 30000mm2, (46.50 sq.in.).

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

THEIR INSTRUCTIONS

REPAIR TO AIRBUS SBO 5, COPY SEES2 REPAIR TO AIRBUS SBO 5, COPY SEES2

19

19

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

B_SB_552051_6_FAAA_02_06

Figure A-GFAAA - Sheet 02

Flow Chart - Flow Chart 2

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 95

6

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@A310

SERVICE BULLETIN

**CONF ALL

ACTIONS ON DETECTED FLUID INGRESS.

LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.) AND 

5000 mm2, (7.75 sq.in.)

LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.)

LOCAL SPOT FLUID INGRESS

5000 mm2, (7.75 sq.in.)

DRAIN BY CORE VENTING.

REPORT TO AIRBUS SEOE 1/2/3 OR AIRTAC

AND FOLLOW THEIR INSTRUCTIONS.

REPORT TO

AIRBUS.

NO FURTHER ACTION REQUIRED

IN ACCORDANCE WITH THIS ISB.

REPETITIVE THERMOGRAPHY

RE− INSPECTION.

DO THE REPAIR.

ACTIONS ON DETECTED FLUID INGRESS.

PERFORM ELCH AND/OR UT AROUND THE

IDENTIFIED FLUID INDICATION

DAMAGE

DETECTED YES

NO

THAN 5 SPOTS PER

NO REPORT TO AIRBUS SEOE 1/2/3 OR AIRTAC

AND FOLLOW THEIR INSTRUCTIONS.

MORE

SIDE SHELL YES

NO

DETECTED

THAN 5 SPOTS PER

SIDE SHELL YES

MORE

DETECTED

NO

B_SB_552051_6_FAAA_03_07

Figure A-GFAAA - Sheet 03

Flow Chart - Flow Chart 3

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 96

6

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@A310

SERVICE BULLETIN

**CONF ALL

INSPECT THE RUDDER SIDE SHELL

YES KNOWN IN THE NO

PERFORM 

ON REPAIR LOCATION AND 

YES TYPE A−A NO

IN CASE OF FINDINGS,

TAP TEST INSPECTION

OR WOODPECKER

ALL OTHER REPAIR TYPES:

PERFORM ELCH

IDENTIFIED REPAIRS

CONTINUE WITH

ACTIONS IN FLOW CHART 2

UPPER GFRP AREA

GFRP AREA

REPAIRS

PULSE THERMOGRAPHY INSPECTION

MARK THE REPAIR

REPAIR

REPORTED

PERFORM

INSPECTION

AND/OR UT

AROUND THE

PERFORM 

ON THE COMPLETE

PULSE THERMOGRAPHY INSPECTION

GFRP AREA

TAP TEST INSPECTION OR

WOODPECKER INSPECTION

PERFORM

ON THE COMPLETE GFRP AREA

MARK THE REPAIRS

YES CORE DISBONDING

NO

SKIN TO

IDENTIFIED

ALL OTHER REPAIR TYPES:

PERFORM ELCH

IDENTIFIED REPAIRS

AND/OR UT

AROUND THE

18

WHICH ARE NOT

MANUFACTURING REWORKS

20

20

21

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

B_SB_552051_6_FAAA_04_04

Figure A-GFAAA - Sheet 04

Flow Chart - Flow Chart 4

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 97

6

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@A310

SERVICE BULLETIN

**CONF ALL

PULSE THERMOGRAPHY PAINT

OPERATOR

IS SURE THAT THE 

NO

GFRP−AREA

400.00 microns

THICKNESS LIMITATION

RUDDER PAINT THICKNESS

IS BELOW THE GIVEN

LIMITS

YES

APPLY PAINT THICKNESS

MEASUREMENT TOOL

NO

LOCAL PAINT REMOVAL

RUDDER

PAINT THICKNESS

IS BELOW 

THE GIVEN

LIMITS

YES

CONTINUE WITH ACTIONS

DEFINED IN FLOW CHART 1 PAINT RESTORATION IS REQUIRED

AFTER PULSE THERMOGRAPHY

AND/OR ELCH/UT INSPECTION

13 14

16

15 17

PAINT RESTORATION

IS REQUIRED AFTER

PULSE THERMOGRAPHY

AND/OR ELCH/UT

INSPECTION

CFRP−AREA

800.00 microns

OR

400.00 microns

BELOW DECAL FOIL

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

B_SB_552051_6_FAAA_05_04

Figure A-GFAAA - Sheet 05

Flow Chart - Flow Chart 5

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 98

6

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@A310

SERVICE BULLETIN

**CONF ALL

SEE AIRBUS LIST WITH A/C MSN, RUDDER S/N

SEE AIRBUS DEFINITION OF REPAIR TYPES AFFECTED

BY THE ISB INSPECTION. REFER TO FIGURE A−GBBAA.

SEE AIRBUS BOOSTER DEFINITION. 

NOTE:

01

02

03

AND RAS NUMBER, REFER TO FIGURE A−GBCAA.

IF AN AIRCRAFT LISTED IN THE SB EFFECTIVITY HAS A

REPAIR EMBODIED THAT IS NOT OF AIRBUS ORIGIN, 

04

AND WHICH AFFECTS THE CONTENT OF THIS SB, THE

APPROVAL BY ITS AIRWORTHINESS AUTHORITY FOR

ANY ADAPTATION NECESSARY BEFORE 

THIS ACTION IS NOT NECESSARY, IF THE INFORMATION

HAS BEEN ALREADY SENT TO AIRBUS IN ACCORDANCE

05

NEXT STEP.

REFER TO FIGURE A−GBDAA.

OPERATOR IS RESPONSIBLE FOR OBTAINING THE

INCORPORATION OF THE SB.

WITH THE OIT SE 999.0070/10 CONTINUE WITH THE 

06 REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY.

ONLY MANUFACTURING HOT−CURING REWORKS ARE

DOCUMENTED IN AOT 55A2048 AND ISB 55−2049.

07

MANUFACTURING REWORK COMPLETE DATA.

AIRBUS MUST BE CONTACTED FOR

08 BASED ON PROVIDED AIRBUS EVALUATION OF RUDDER

S/N MANUFACTURING REWORK DATA.

12 FOR GFRP−AREA INSPECTION REFER TO FLOW CHART 4

REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY.

PENDING AVAILABILITY OF SRM IMPROVED REPAIR, AIRBUS IS TO BE

CONTACTED FOR INSTRUCTIONS.

SIDE SHELL REPLACEMENT CAN BE DONE ONLY AT THE AIRBUS STADE FACILITY.

09

10

11

REFER TO FIGURE A−GBEAA.

19 THE NEW REPAIR CUTOUT IS EQUAL TO

THE LARGEST OUTER SKIN REPAIR PLY.

18 REFER TO FIGURE A−GBBAA

20 IN CASE OF FLUID INGRESS REFER TO

FLOW CHART 3 FOR FURTHER INSTRUCTIONS

21 FOR PAINT THICKNESS IDENTIFICATION REFER TO

FLOW CHART 5

13 PRIOR TO THE APPLICATION OF THE PULSE THERMOGRAPHY

METHOD NTM 55−40−50 THE OPERATOR HAS TO CHECK

THE SIDE SHELL PAINT THICKNESS. IT IS THE 

OPERATORS RESPONSIBILITY TO ENSURE THAT THE

RUDDER SIDE SHELL PAINT THICKNESS IS BELOW THE

GIVEN LIMITS.

PLEASE CONSIDER THE INFORMATION FOR PAINT

RESTORATION PROVIDED WITH THE OIT 999.0130/06

DATED 21 NOV 2006.

SRM 51−75−20 RECOMMENDS ABRADING COMPOSITE

SURFACE UP TO THE FIRST PRIMER COATING IN ORDER

TO AVOID SURFACE DAMAGE OF THE COMPOSITE.

IN CASE OF A SMOOTH AND EVEN PAINT THICKNESS

DISTRIBUTION FIG. A−GABAA PROVIDE GUIDANCE

MATERIAL ABOUT A FEASIBLE PAINT BORER LOCATION 

DISTRIBUTION OVER THE SIDE SHELL.

IN CASE PAINT REMOVAL LARGER THAN 2m2 IS REQUIRED

IT IS RECOMMENDED TO REMOVE THE RUDDER FROM

THE A/C.

14

15

16

17

22 CLEAN THE PREVIOUS REPAIR AREA.

REFER TO SRM 51−77−10 PARA 2.C.

PERFORM A LOCAL MECHANICAL SANDING

A STEP BY STEP BASIS UP TO INITIAL BASIC PRIMER LAYER.

AS PER SRM 51−77−10 PARA 2.D. ON 

23

ON TOP/AROUND THE REPAIR

NO VISIBLE REPAIR: 

USING ABRASIVE CLOTH GRADE 100, 220, 280, 400.

MECHANICAL SANDING ON A STEP BY STEP BASIS

24

CONTINUE LOCAL SANDING UP TO PORE FILLER/ADHESIVE.

REFER TO SRM 51−77−10 PARA 2.D.

25 ENSURE NO DAMAGE TO CFRP OR GFRP BASE MATERIAL.

IF THE LARGEST REPAIR PLY IS NOT VISIBLE,

BEYOUND THE INITIAL DETECTED REPAIR PATCH.

26

CONTINUE LOCAL SANDING ON AND AROUND THE REPAIR WITH A RADIUS APPROX. 50.0mm (1.97in)

27 USE PAINT BORER TO ASSESS LOCAL PAINT SCHEME, THICKNESS AND INITIAL BASIC PRIMER

PRIOR SANDING. USE ON TOP OF REPAIR AND BESIDE REPAIR LOCATION.

28 MAX. 1m2 (10.76 sq.ft.) SANDED AREA PER LOCAL REPAIR IS ALLOWED.

SRM 51−77−10 AND SEND A DETAILED REFERENCE REPORT TO SEOE DEPARTMENT.

IN CASE OF DAMAGE, PERFORM ASSESSMENT AS PER

IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT THE STRUCTURAL SIDE SHELL OUTER SKIN PLY

(CFRP OR GFRP) IN ACCORDANCE TO THE DESIGN DRAWING IS NOT DAMAGED DURING THE LOCAL 

SANDING PROCESS.

REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY!

IN CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT FLIGHT IS REQUIRED. AN AREA DAMAGED

BY THE LOCAL SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD TO A NON−REPAIRABLE SIZE

AND SUBSEQUENT SIDE SHELL REPLACEMENT!

B_SB_552051_6_FAAA_06_01

Figure A-GFAAA - Sheet 06

Flow Chart

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 99

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Closing of ventilation holes in outer skin

Method 1 − Application of a bonded cover

NOTE: This repair needs to be re−inspected. Correct cover application has to be ensured by frequent

detailed visual inspection during the application period at intervals not exceeding 500 FH or 4 months,

1. Apply high speed tape over the ventilation hole, refer to Chapter 51−77−11 Paragraph 2..

Method 2 − Application of laminated cover

NOTE: This repair needs no re−inspection.

2. Prepare the repair area, refer to Chapter 51−77−10 Paragraph 2.M.(2)., apply only step

1 to 2 and 10 to 17.

3. Protect the area adjacent to the repair area with flash tape (Material No. 05RFB1), refer to

Chapter 51−77−00, Paragraph 3.D

4. Prepare the laminating resin (Material No. 13EBC1), refer to Chapter 51−77−10, Paragraph 

2.A

5. Prepare the repair plies (MIL−C−9084C TYPE VIIIA or B − style 7781 dry glass fabric), refer to

Chapter 51−77−10, Paragraph 2.H. For ply dimensions and orientation refer to Figure 1.

NOTE: Round all corners with radii 12mm (0.5 in.) minimum.

6. Prepare the laminating resin, refer to Chapter 51−77−10, Paragraph 2.A

7. Apply repair plies to the repair area as shown in Figure 1, refer to Chapter 51−77−10, 

Paragraph 2.H

8. If the repair cure shall be accelerated by heat:

− Install the vaccum bag, refer to Chapter 51−77−10, Paragraph 3.D, respect modificatons

shown on Figure 2 and the heating equipment.

− Allow repair to cure under vacuum pressure, refer to Chapter 51−77−10, Paragraph 3.E,

use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin gel for one hour at room

temperature, then cure for 4 hours at 60 C, refer to Chapter 51−77−10, Paragraph 3.E.

− Remove the vacuum bag and the heating equipment.

− Continue with step 10.

9. If the repair cure shall be performed at room temperature:

− Install the vacuum bag, refer to Chapter 51−77−10, Paragraph 3.D. and respect modifications

shown on Figure 2.

− Allow repair to cure under vacuum pressure, refer to Chapter 51−77−10, Paragraph 3.E,

use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin cure for six hours at room

temperature or perform resin gelation test outside the repair area, after resin gelation perform

cure for two hours (the latter approach must be applied if RT is below 18 C (65 F)).

− Remove the vacuum bag and continue with step 10 during the next stop.

10. Remove the flash tape. Ensure that the glass ply is correctly located and cured, refer to

Chapter 51−77−00, Paragraph 6.

11. Remove any resin remnants from the border area of the glass ply, use abrasive paper. Start with

280 grade and finish with 400 grade.

WARNING: CLEANING AGENT (MATERIAL NO. 08BBF1 or 08BBU9) IS DANGEROUS.

12. Clean the repair area with cleaning agent (Material No. 08BBF1 or 08BBU1), refer to Chapter 51−

77−10, Paragraph 2.E.

13. Restore the surface protection, refer to Chapter 51−75−10.

whichever occurs later.

B_SB_552051_6_AAAA_01_04

Figure A-GAAAA - Sheet 01

Closing of ventilation holes

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 100

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@A310

SERVICE BULLETIN

**CONF ALL

Figure 1 − Ply lay−up

Ply 2 0/90 42 x 42mm

Ply 1 45 30 x 30mm

Ply 3 45 54 x 54mm

NON PERFORATING GLASS PLY FLASH TAPE

PARTING FILM

RUBBER CAUL

PLATE

BREATHER

DRY GLASS FABRIC

OR PEEL PLY

VACUUM GAGE VACUUM SOURCE

VACUUM BAG FILM

VACCUM BAG

SEALANT TAPE

NOTE:

01 RUBBER CAUL PLATE IS MANDATORY, 

01

REFER TO CHAPTER 51−77−10, PARAGRAPH 3.D.

Figure 2 − Bagging for curing process

B_SB_552051_6_AAAA_02_01

Figure A-GAAAA - Sheet 02

Closing of ventilation holes

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 101

6

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SERVICE BULLETIN

**CONF ALL

PAINT THICKNESS MEASUREMENT USING THE PAINT BORER ON THE RUDDER SIDE SHELL

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE

PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN

DETERMINE THE THICKNESS WITH THE TNO PAINT BORER.

DESCRIPTION

1. GENERAL

A. THIS PROCEDURE CONTAINS THE INSPECTION PROCEDURE DESCRIBING

PAINT THICKNESS MEASUREMENT USING THE TNO PAINT BORER ON

THE RUDDER SIDE SHELL.

PROCEDURE

1 TASK SUPPORTING DATA

A. AREA OF APPLICABILITY

ALL RUDDER INSPECTED WITH NTM 55−40−50

B. DESCRIPTION OF POSSIBLE DAMAGE

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE

PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN

DETERMINE THE THICKNESS WITH THE TNO PAINT BORER.

C. JOB SETUP INFORMATION

(1) TOOLING LIST

INSPECTION: PAINT THICKNESS MEASUREMENT TNO PAINT

TOOL: BORER KIT MODEL 518 OR 518S OR 518MC WITH

 DIFFERENT DRILLS PREFERABLY THE FOLLOWING:

 DRILL DRILL

 MEASURING RANGE

 CUTTING ANGLE 26.6° 45°

 FACTOR ( m/sc.div) 10 20

ADDITIONAL DOCUMENT: OPERATING MANUAL TNO PAINT BORER

NOTE: FOR THIS INSPECTION ALSO OLDER OR NEWER VERSIONS OF THE TNO

PAINT BORER MIGHT BE USED. IT IS IMPORTANT TO HAVE THE ABOVE

CAUTION: DO NOT USE ULTRASONIC OR EDDY CURRENT BASED PAINT THICKNESS

MEASUREMENT DEVICES, AS EDDY CURRENT ONLY WORKS ON METALLIC

AND FOR ULTRASONIC BASED DEVICES THE NUMBER OF POSSIBLE PAINT

LAYERS IS TOO HIGH TO GET RELIABLE RESULTS.

SPECIFIED DRILLS AVAILABLE.

( m) 10−1000 20−2000

B_SB_552051_6_ABAA_01_04

Figure A-GABAA - Sheet 01

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 102

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@A310

SERVICE BULLETIN

**CONF ALL

2 PROCEDURE:

1. PREPARE THE TNO PAINT BORER ACCORDING TO THE OPERATING

1. PLACE THE PAINT BORER ON THE AREA, WHERE THE THICKNESS OF THE

 RUDDER PAINT HAS TO BE MEASURED, SEE FIG. A−GABAA SHEET 3+4

2. DO THE DRILLING AND THE PAINT THICKNESS MEASUREMENT ACCORDING TNO

 PAINT BORER 518 OPERATING INSTRUCTIONS, REFER ALSO

 CAUTION: DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). ONLY A

TINY BASE MATERIAL SPOT IS ENOUGH TO MEASURE THE PAINT

THICKNESS, REFER TO FIG. A−GABAA SHEET 5+6

3. APPLY A CONTRAST MARK (WITH A NON PERMANENT MARKER PEN) ON THE

 THE SPOT OF MEASUREMENT. IF THE RUDDER PAINT IS LIGHT (E.G. YELLOW, 

 WHITE ...), USE A DARK (BLACK) PEN TO ENHANCE CONTRAST OF THE TOP

 COATING, IN CASE OF A DARK TOP COAT USE A LIGHT (WHITE) PEN. SEE

A. PREPARATION FOR INSPECTION

B. INSTRUMENT ADJUSTMENT

1. NO

C: INSPECTION PROCEDURE

 INSTRUCTIONS.

4. RECORD ALL THE MEASURED PAINT THICKNESS VALUES FOR THE

 PULSE THERMOGRAPHY INSPECTION.

5. AFTER MEASUREMENT SEAL THE SPOT WHERE DRILLED − REFER TO

 SRM 51−75−10.

 FIG. A−GABAA SHEET 7+8

 TO FIGURE A−GABAA SHEET 3−8

− IF THE LAYER THICKNESS IS NOT KNOWN,

INITIALLY USE A DRILL WITH 20−2000 m ( CUT ANGLE: 45°)

TO BRING THE FULL SECTION INTO VIEW;

CHANGE TO 10−1000 m (CUT ANGLE: 26.6°) IF THICKNESS

TURNS OUT TO BE 1000 m OR LESS

μ 

μ 

μ 

B_SB_552051_6_ABAA_02_04

Figure A-GABAA - Sheet 02

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 103

6

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@A310

SERVICE BULLETIN

**CONF ALL

Z326

A

A

LH SHOWN

RH SIMILAR

CFRP

AREA

GFRP

AREA

C D E

B D E

B_SB_552051_6_ABAA_03_00

Figure A-GABAA - Sheet 03

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 104

6

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@A310

SERVICE BULLETIN

**CONF ALL

PAINT SYSTEM

DIFFERENT LAYERS

(E.G. FILLER, PRIMER,

TOP COAT, ...)

CFRP

HONEYCOMB

CORE

d

NOTE:

01 DRILL HOLE

01

d = PAINT SYSTEM

THICKNESS

SPOT DRILLING

DETERMINATION OF

PAINT THICKNESS

PAINT SYSTEM

DIFFERENT LAYERS

(E.G. FILLER, PRIMER,

TOP COAT, ...)

GFRP

HONEYCOMB

CORE

d 01

B

C

D E

F

G

B_SB_552051_6_ABAA_04_01

Figure A-GABAA - Sheet 04

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 105

6

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@A310

SERVICE BULLETIN

**CONF ALL

F

1) NOT DRILLED DEEP

ENOUGH

2) GOOD DRILLED DEPTH 

(TINY CFRP SPOT)

3) DRILLED TO DEEP

(BIG CFRP SPOT)

7) DRILLED TO DEEP

(DAMAGE OF THE HONEYCOMB

6) DRILLED TO DEEP

(BIG CFRP SPOT)

5) GOOD DRILLED

DEPTH (TINY

4) NOT DRILLED

DEEP ENOUGH

CFRP SPOT) CORE)

B_SB_552051_6_ABAA_05_00

Figure A-GABAA - Sheet 05

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 106

6

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@A310

SERVICE BULLETIN

**CONF ALL

8) NOT DRILLED DEEP

ENOUGH

9) NOT DRILLED DEEP

ENOUGH

10) GOOD DRILLED

DEPTH

11) DRILLED TOO DEEP

(BIG GFRP SPOT)

12) GOOD DRILLED DEPTH

(DAMAGE OF THE

13) DRILLED TOO DEEP

(TINY GFRP SPOT)

14) DRILLED TOO DEEP

(DAMAGE OF THE

(TINY GFRP SPOT)

HONEYCOMB CORE) HONEYCOMB CORE)

G

B_SB_552051_6_ABAA_06_00

Figure A-GABAA - Sheet 06

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 107

6

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@A310

SERVICE BULLETIN

**CONF ALL

B_SB_552051_6_ABAA_07_00

Figure A-GABAA - Sheet 07

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 108

6

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@A310

SERVICE BULLETIN

**CONF ALL

BR1

BR2

BR3

BR4

BR5

BR6

BR7

200.0mm (7.87in.) AFT OF BR7 RIVET CENTER

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

200.00mm (7.87in.) FROM

BR2 RIVET CENTER LINE

PROPOSAL:

1SPOT IN GFRP AREA

6SPOTS IN CFRP AREA

A

B

C

A

B

C

D

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

D

600.0mm (23.62in.)

600.0mm (23.62in.)

B_SB_552051_6_ABAA_08_02

Figure A-GABAA - Sheet 08

Paint borer instructions

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 109

6

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@A310

SERVICE BULLETIN

REPORTING SHEET

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

INSPECTION

MODIFICATION No.: None

Please complete the appropriate item (A or B):

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

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

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

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

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

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

Or : Intermediate revision YES/NO

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

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

the next feasible revision, this will result in

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

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

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

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

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

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

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 1

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@A310

SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Sep 11/12 SERVICE BULLETIN No.: A310-55-2051

REVISION No.: 01 - Aug 20/14 Page: 1

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