@A310

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 - A310 RUDDER DEBOND INSPECTION

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

On AIRBUS A310 aircraft, most of the rudder side shells are sandwich structures made of Carbon Fiber

Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core, like on

AIRBUS Single Aisle family aircraft. A debonding in a rudder shell was found on the rudder of an A319

and an A321 aircraft. A large rudder debond, resulting from an undetected damage growth, could affect

the handling quality of the aircraft. Under specific conditions, a large debond could lead to aircraft inflight instability. A review of the production records revealed that the debonding reported on both

rudders correspond to areas that had been reworked in production.

This Service Bulletin details the special detailed inspection procedure to inspect the reworked areas on

affected rudders fitted on A310 aircraft for potential debonding.

Due to the different areas on the rudder to be inspected, different inspection procedures are necessary:

- Vacuum loss inspection

- Elasticity Laminate Checker (ELCH) inspection

- Tap test inspection

- Thermography inspection

- Ultrasound (US) inspection.

The accomplishment of this Service Bulletin will ensure the detection of potential debonding in the

reworked areas.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 1

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@A310

SERVICE BULLETIN

SUMMARY

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY 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

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

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

19U 52X 58X 82Z 85Z 99Y A1L AFG AIB AIC BAF BBC BLE

CFC CSA DAH DEC DGA F2I FDX GAF HFY I2L IRA IRM IYE

JAB JAV KAC KTC KYV KZU MGL MWA PIA QAF R1T RJA ROT

RZO SBI SGX SUD THY TSC UZB WHT

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 55.40.12.001

OEB None

AOT 55A2048

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER SBIT 914.0808/09

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 552049-832-848-001: Inspection

TOTAL MANHOURS 2.00

APPENDICES

None

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 2

6

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@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 - A310 RUDDER DEBOND 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

(1) Models

310-203 310-203C 310-204 310-221 310-222 310-304 310-308 310-322

310-324 310-325

(2) Effectivity by MSN

0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0264

0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0316 0318 0320 0326

0331 0333 0335 0338-0339 0342-0343 0345-0346 0349 0353 0356-0357 0359-0360

0362 0364 0367 0370 0372 0375 0378-0379 0386 0389-0390 0392 0394 0397

0399-0400 0406-0407 0410 0413 0416 0418 0421-0422 0425 0427-0429 0431 0434

0436-0437 0439 0441 0444-0449 0452 0454 0456-0458 0467 0472-0473 0475-0476

0478 0480-0492 0494-0499 0502-0503 0519-0520 0522-0524 0526-0527 0531 0534

0537-0539 0541-0542 0544-0545 0547 0549-0552 0562 0564-0565 0567-0568 0571

0573-0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0638

0640 0642 0644 0646-0654 0656 0658 0660-0661 0663 0665 0667 0669 0671-0672

0674 0676 0678 0680 0682 0684 0686-0687 0689 0697 0706

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

19U 0399

52X 0410

58X 0431

82Z 0550 0551

85Z 0595

99Y 0489

A1L 0648

AFG 0496 0497

AIB 0686

AIC 0392 0406 0407 0413 0428 0429 0538 0544 0654 0665 0669 0680

BAF 0367 0372

BBC 0594

BLE 0650

CFC 0425 0441 0444 0446 0482

CSA 0672 0674

DAH 0291 0293

DEC 0684 0697

DGA 0418 0421 0422

F2I 0309

FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251

0254 0257 0264 0267 0273 0278 0281 0283 0288 0297 0303 0316

0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0349 0353

0356 0359 0360 0362 0364 0378 0394 0397 0400 0439 0449 0452

0454 0456 0457 0458 0467 0492 0534 0539 0542 0549 0552 0593

0638

GAF 0434 0484 0498 0499 0503 0522 0523

HFY 0495 0565

I2L 0640 0642

IRA 0338 0370 0375 0379 0389 0390 0436 0671

IRM 0488 0537 0564 0586

IYE 0568

JAB 0320

JAV 0357 0481

KAC 0647 0649 0663

KTC 0524 0567 0620

KYV 0386

KZU 0592 0622 0646

MGL 0526

MWA 0652

PIA 0473 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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@A310

SERVICE BULLETIN

OPERATOR MSN

QAF 0667

R1T 0591

RJA 0416 0445 0490 0491 0531

ROT 0636 0644

RZO 0571 0624 0651 0661

SBI 0427 0475 0486 0487 0520

SGX 0519 0562

SUD 0437

THY 0476 0478 0480 0502

TSC 0447 0472 0483 0485 0527 0541 0545 0547 0588 0597 0599 0600

0658

UZB 0574 0576 0706

WHT 0448 0494 0573

(4) Configuration by MSN

MSN CONFIGURATION

0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248

0251 0254 0257 0264 0267 0273 0278 0281 0283 0288 0291

0293 0297 0303 0309 0316 0318 0320 0326 0331 0333 0335

0338 0339 0342 0343 0345 0346 0349 0353 0356 0357 0359

0360 0362 0364 0367 0370 0372 0375 0378 0379 0386 0389

0390 0392 0394 0397 0399 0400 0406 0407 0410 0413 0416

0418 0421 0422 0425 0427 0428 0429 0431 0434 0436 0437

0439 0441 0444 0445 0446 0447 0448 0449 0452 0454 0456

0457 0458 0467 0472 0473 0475 0476 0478 0480 0481 0482

0483 0484 0485 0486 0487 0488 0489 0490 0491 0492 0494

0495 0496 0497 0498 0499 0502 0503 0519 0520 0522 0523

0524 0526 0527 0531 0534 0537 0538 0539 0541 0542 0544

0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568

0571 0573 0574 0576 0585 0586 0587 0588 0590 0591 0592

0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0638

0640 0642 0644 0646 0647 0648 0649 0650 0651 0652 0653

0654 0656 0658 0660 0661 0663 0665 0667 0669 0671 0672

0674 0676 0678 0680 0682 0684 0686 0687 0689 0697 0706

001

(5) Configuration definition

**CONF 001

is valid for aircraft with rudders which might have reworked areas to be inspected.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01 1

B. CONCURRENT REQUIREMENTS

None

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 3

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@A310

SERVICE BULLETIN

C. REASON

(1) History

On AIRBUS A310 aircraft, most of the rudder side shells are sandwich structures made

of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP)

with a honeycomb core, like on AIRBUS Single Aisle family aircraft. A debonding in a

rudder shell was found on the rudder of an A319 and an A321 aircraft. A large rudder

debond, resulting from an undetected damage growth, could affect the handling quality

of the aircraft. Under specific conditions, a large debond could lead to aircraft in-flight

instability. A review of the production records revealed that the debonding reported on

both rudders correspond to areas that had been reworked in production.

(2) Objective/Action

This Service Bulletin details the special detailed inspection procedure to inspect the

reworked areas on affected rudders fitted on A310 aircraft for potential debonding.

Due to the different areas on the rudder to be inspected, different inspection procedures

are necessary:

- Vacuum loss inspection

- Elasticity Laminate Checker (ELCH) inspection

- Tap test inspection

- Thermography inspection

- Ultrasound (US) inspection.

(3) Advantages

The accomplishment of this Service Bulletin will ensure the detection of potential

debonding in the reworked areas.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 552049-832-848-001: Inspection

(1) Do the rudder special detailed inspection on aircraft with rudders which will not

exceed 13000 FC within 24 month after the issue of this Service Bulletin

(2) Do the rudder special detailed inspection on aircraft with rudders which have

exceeded or will exceed 13000 FC within 24 month after the issue of this Service

Bulletin

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 4

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@A310

SERVICE BULLETIN

E. COMPLIANCE

(1) Classification

MANDATORY

(2) Accomplishment Timescale

Table 1. Config. 001 - Rudder special detailed inspection on aircraft with rudders which

will not exceed 13000 FC within 24 month after the issue of this Service Bulletin.

Area to be

inspected

Condition Action Compliance time Repetitive interval

N/A N/A Identify the Serial

Number of the

installed rudder

Within 24 month

after the issue of

this SB

N/A

Area 1 N/A Vacuum loss

inspection in

accordance with

Subtask

552049-832-201

-002

Within 24 month

after the issue of

this SB

N/A

Area 1 Damage

indications found

during the vacuum

loss inspection

Report to AIRBUS Before next flight N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Report to AIRBUS Within 10 days

after the vacuum

loss inspection

N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

1: Close the

vacuum loss

inspection holes

with adhesive tape

Before next flight, if

the temporary

option 2 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

1: Do a detailed

inspection of the

restored area for

loose or lost

adhesive tape

N/A At intervals not

exceeding 4

months

Area 1 Loose or lost tape

found

Temporary option

1: Close the

vacuum loss

inspection holes

again with

adhesive tape

Before next flight, if

the temporary

option 2 or the

permanent

restoration have

not been

accomplished

N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

1: Do the

permanent

restoration. Do a

thermography or

ultrasound

inspection before

the resin injection

Within 4500 FC

after the vacuum

loss inspection

N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

2: Close the

vacuum loss

inspection holes

with resin and

adhesive tape. Do

a thermography or

ultrasound

inspection before

the resin injection

Before next flight, if

the temporary

option 1 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 Damage

indications found

during the

thermography or

ultrasound

inspection

Temporary option

2: Report to

AIRBUS

Before next flight N/A

Area 1 No damage

indications found

during the

thermography or

ultrasound

inspection

Temporary option

2: Restore the

surface protection

Within 4500 FC

after the vacuum

loss inspection

N/A

Area 1 No damage

indications found

Permanent

restoration: Do a

thermography or

ultrasound

inspection before

the resin injection

Before next flight

after the vacuum

loss inspection or

within 4500 FC

after the vacuum

loss inspection if

the temporary

option 1 or the

temporary option 2

has been

accomplished

N/A

Area 1 Damage

indications found

during

thermography or

ultrasound

inspection

Permanent

restoration: Report

to AIRBUS

Before next flight N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 1 No damage

indications found

during

thermography or

ultrasound

inspection

No further action

after

accomplishment of

the permanent

restoration

N/A N/A

Area 2 N/A ELCH inspection in

accordance with

Subtask

552049-832-201

-002

within 24 month

after the issue of

this SB

N/A

Area 2 Damage

indications found

during ELCH

inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

Area 2 No damage

indications found

during the ELCH

inspection

Report to AIRBUS

and do 2 additional

repetitive ELCH

inspections

Report within 10

days after the 1.

ELCH inspection

Within intervals

between 4000 and

4500 FC

Area 2 Damage

indications found

during the 1. or 2.

additional repetitive

ELCH inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

Area 2 No damage

indications found

during the 2

additional repetitive

ELCH inspections

Report to AIRBUS

No further action

Report within 10

days after the

ELCH inspections

N/A

Table 2. Config. 001 - Rudder special detailed inspection on aircraft with rudders which

have already exceeded 13000 FC or will exceed 13000 FC within 24 month after the

issue of this Service Bulletin.

Area to be

inspected

Condition Action Compliance time Repetitive interval

N/A N/A Identify the Serial

Number of the

installed rudder

within 8 month

after the issue of

this SB

N/A

Area 1 N/A Vacuum loss

inspection in

accordance with

Subtask

552049-832-202

-002

within 8 month

after the issue of

this SB

N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 1 Damage

indications found

during the vacuum

loss inspection

Report to AIRBUS Before next flight N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

1: Close the

vacuum loss

inspection holes

with adhesive tape

Before next flight, if

the temporary

option 2 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

1: Do a detailed

inspection of the

restored area for

loose or lost

adhesive tape

N/A At intervals not

exceeding 4

months

Area 1 Loose or lost tape

found

Temporary option

1: Close the

vacuum loss

inspection holes

again with

adhesive tape

Before next flight, if

the temporary

option 2 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

1: Do the

permanent

restoration. Do a

thermography or

ultrasound

inspection before

the resin injection

Within 4500 FC

after the vacuum

loss inspection

N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Temporary option

2: Close the

vacuum loss

inspection holes

with resin and

adhesive tape. Do

a thermography or

ultrasound

inspection before

the resin injection

Before next flight, if

the temporary

option 1 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 Damage

indications found

during

thermography or

ultrasound

inspection

Temporary option

2: Report to

AIRBUS

Before next flight N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 1 No damage

indications found

during

thermography or

ultrasound

inspection

Temporary option

2: Restore the

surface protection

Within 4500 FC

after the vacuum

loss inspection

N/A

Area 1 No damage

indications found

during the vacuum

loss inspection

Permanent

restoration: Do a

thermography

inspection before

the resin injection

Before next flight

after the vacuum

loss inspection or

within 4500 FC

after the vacuum

loss inspection if

the temporary

option 1 or the

temporary option 2

has been

accomplished

N/A

Area 1 Damage

indications found

during

thermography or

ultrasound

inspection

Permanent

restoration: Report

to AIRBUS

Before next flight N/A

Area 1 No damage

indications found

during

thermography or

ultrasound

inspection

No further action

after

accomplishment of

the permanent

restoration

N/A N/A

Area 2 N/A ELCH inspection in

accordance with

Subtask

552049-832-202

-002

within 24 month

after the issue of

this SB

N/A

Area 2 Damage

indications found

during ELCH

inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

Area 2 No damage

indications found

during ELCH

inspection

Report to AIRBUS

and do 2 additional

repetitive ELCH

inspections

Report within 10

days after the 1.

ELCH inspection

ELCH inspection

within intervals

between 4000 and

4500 FC

Area 2 Damage

indications found

during the 1. or 2.

additional repetitive

ELCH inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 2 No damage

indications found

during the 2

additional repetitive

ELCH inspections

Report to AIRBUS

No further action

Within 10 days

after the ELCH

inspection

N/A

Accomplishment of this Service Bulletin is expected to be rendered mandatory by the

issue of an Airworthiness Directive (AD) published by the European Aviation Safety

Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals

and/or date) given above but reference should be made to the AD for confirmation of the

mandated accomplishment timescale.

F. APPROVAL

Approved under EASA 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.

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 552049-832-848-001: Inspection

Get Access 1.00

On Aircraft

Do the rudder special detailed inspection on aircraft

with rudders which will not exceed 13000 FC within 24

month after the issue of this Service Bulletin

0

Do the rudder special detailed inspection on aircraft

with rudders which have exceeded or will exceed

13000 FC within 24 month after the issue of this

Service Bulletin

0

Close-Up 1.00

TOTAL MANHOURS 2.00

NOTE: Manhours and elapsed time depend on the size of the area to be inspected.

Find below a table with the information for the manhours, elapsed time and

number of persons per 1 m (39.37 in.) for the different inspection procedures:

Steps Manhours Elapsed time Number of

persons

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

Get access 1.00 0.75 2

Rudder SN

identification

0.25 0.25 1

Vacuum inspection 2.00 1.50 2

Thermography

inspection

0.25 0.25 2

Ultrasound

inspection

0.25 0.25 1

ELCH inspection 0.75 0.75 1

Tap inspection 0.25 0.25 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 24-00-00 29-10-00

55-33-13 55-40-00

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-24

51-10-25 51-10-26 51-10-28

Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are

performed on aircraft in warranty at the time of such inspection. Credit will be at the

operator’s agreed in-house warranty labor rate. Claims for labor allowance should be received

not later than 90 days after completion of the last affected warranted aircraft.

This Service Bulletin is subject of specific support provided by AIRBUS. For details please

contact your Customer Support Director.

For the organisation of this retrofit, operators are kindly requested to contact AIRBUS retrofit

management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point

Maurice Bellonte 31707 BLAGNAC CEDEX France Tel : (33) 5 67 19 06 22 E-mail :

monitored.retrofit@airbus.com Fax : (33) 5 61 93 27 45

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

Self-Adhes. Disks 05-052 As required

Self Adhesive Aluminium Tape 08-052 As required

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

Wet Lay Up Resin 20-022 As required

(2) Components

None

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(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To find the correct tool-PN for the different inspection tools, refer to the subsequent

table:

Inspection tool PN NTM reference

ELCH Elasticity Laminate

Checker Kit

MBBBT100 51-10-26

Vacuum loss Vacuum cup TL3AMB1420T28L 51-10-28

Thermography Thermography kits 99A55407320000

(Camera and monitor)

and

99A55407321000

(complementary tooling

including hot air blower)

51-10-25

Ultrasound US-equipment EPOCH4PLUS

and

search unit K1SM

and

reference block

MBBGCFRPHC200

and

cable PKLL2

51-10-24

tap test tap test inspection test

tool

98A57103013000

or

99A55209001000

51-10-03

tap test Function test block

and

Woodpecker

99A55407291000

and

WP632

or

WP632AM

51-10-19

For more detailed information, refer to the related NTM chapter.

(3) Special Tools

None

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 552049-832-848-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION

BEFORE YOU START A TASK ON OR NEAR :

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

WARNING: MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE

WARNING NOTICES ARE IN POSITION.

CAUTION: DO NOT CAUSE DAMAGE TO THE SURFACES. THE COMPONENTS ARE

MADE OF CARBONFIBER REINFORCED PLASTIC.

Task Associated Data

Manpower

TOTAL MANHOURS 2.00

A. GENERAL

(1) Subtask 552049-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001

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 consumable materials (Mat. No.) that you must use in this

Service Bulletin, (Refer to Consumable Material List (CML)).

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(c) Clean the areas to be inspected with

Solvent General

Purpose

11-026 As required

and

Lint-Free Cotton

Cloth

19-003 As required

(2) Subtask 552049-839-201-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 552049-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

29-10-00, Page Block 301

55-33-13, Page Block 401

55-40-00, Page Block 601

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

Block 301).

(b) Check the documentation of the related aircraft for further repairs on the rudder

during service. If you find documents about further repairs, contact AIRBUS.

(c) In the cockpit, put warning notices in position to tell persons not to operate the flight

controls.

(d) Do the rudder inspection/check Job Set-up procedure (Refer to AMM 55-40-00,

Page Block 601 pata (a) to (d)).

(e) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic

systems.

(f) Put access platform(s) in position at the rudder.

(g) To open the access panels, (Refer to AMM 55-33-13, Page Block 401).

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C. PROCEDURE

(1) Subtask 552049-832-201-002 - Do the rudder special detailed inspection on aircraft

with rudders which will not exceed 13000 FC within 24 month after the issue of

this Service Bulletin

Manpower Resources

Manhours 0

Minimum number of person 0

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

Self-Adhes. Disks 05-052 As required

Self Adhesive Aluminium

Tape

08-052 As required

Solvent General Purpose 11-026 As required

Wet Lay Up Resin 20-022 As required

References

Non Destructive Test Manual (NTM) 51-10-03, Page Block 701

51-10-19, Page Block 701

51-10-24, Page Block 401

51-10-25, Page Block 101 Procedure A and

B

51-10-26, Page Block 701

51-10-28, Page Block 701

Structural Repair Manual (SRM) 51-75-12

51-77-10

51-77-11 Para 4.M.(2)

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

51-77-11 Para 5.

51-77-11 Para 4.E

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References

Fig. A-GAAAA

Rudder inspection

Sheet 01 - Flow Chart 1, vacuum loss

inspection area 1

Sheet 02 - Vacuum loss inspection -

damage assessment

Sheet 03 - Flow Chart 2, ELCH inspection

area 2

Sheet 05 - Reporting sheet

Sheet 06 - Rudder SN identification

Sheet 07 - Inspection areas

Sheet 08 - Typical ELCH procedure

Sheet 09 - Rudder skin thickness LH

Sheet 10 - Rudder skin thickness RH

Sheet 11 - Rudder skin thickness LH

Sheet 12 - Rudder skin thickness RH

Fig. A-GACAA

rudder SN - MSN reference list

Sheet 01

(a) Identify the Serial Number (SN) of the rudder as shown on Fig. A-GAAAA Sheet

06.

(b) If you do not find a SN placard on the rudder, contact AIRBUS for further

instructions.

(c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list

Fig. A-GACAA Sheet 01.

1 If you find a different SN against the MSN as detailed in the rudder SN - MSN

reference list, contact AIRBUS for further instructions.

2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the

Close-up para 3.E. No further action is necessary.

3 If the rudder SN is part of the rudder SN - MSN reference list with the same

indicated MSN, continue with the below instructions.

(d) The Technical Disposition (TD) details the location of the reworked area to be

inspected and includes information about the vacuum loss vacuum loss inspection

holes, if necessary.

1 For the definition of the areas to be inspected refer to the rudder SN - MSN

reference list Fig. A-GACAA Sheet 01 to find the MSN related Technical

Disposition (TD) No.

2 To get the TD, refer to the SB BOOKLET-link on the index page of this

Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and

use ’SB BOOKLET-TD-K45-S1-XXXXX’.

For additional information, refer to SBIT SEMB 914.0808/09

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3 Inspection method for reworked areas:

- For reworked area astride AREA 1 and AREA 2, if TD provides vacuum

loss hole location then rework must be treated as if in AREA 1 only.

- For reworked area astride AREA 1 and AREA 2, if TD does not provide

vacuum loss hole location then rework must be treated as if in AREA 2

only.

(e) If there are only areas on the trailing edge, shown as ’area 2’ on the Fig. A-GAAAA

Sheet 07, to be inspected, refer to Para (g).

(f) If there is another area, shown as ’area 1’ on the Fig. A-GAAAA Sheet 07, to be

inspected, do the subsequent inspection in accordance with the Flow Chart Fig. AGAAAA Sheet 01 and Fig. A-GAAAA Sheet 02:

1 Do the vacuum loss inspection within 24 month after the issue of this Service

Bulletin (Refer to NTM 51-10-28, Page Block 701).

a Temporarily install adhesive tape on the areas to be inspected.

b Mark the grid of holes on the adhesive tape.

c

CAUTION: DRILL PENETRATION INTO THE SANDWICH

STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.)

TO PREVENT INNER SKIN DAMAGE.

Drill the vacuum loss inspection holes with DIA 1.5 mm (0.06 in.) through

the outer skin only.

d Do the Vacuum loss inspection (Refer to NTM 51-10-28, Page Block

701).

e In case of damage indications, report to AIRBUS on the basis of a

detailed referenced damage report for further instructions before next

flight.

f In case of no damage indications, close the vacuum loss inspection

holes as detailed in the subsequent instructions and report the result to

AIRBUS within 10 days.

2 Temporary restoration of the vacuum loss inspection holes option 1:

a Close the holes with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

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b Do a detailed inspection of the restored area at intervals not exceeding 4

month. Inspect the restored area for loose or lost adhesive disks or tape.

c In case of loose or lost tape or disks, close the holes again with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

d This temporary restoration must be replaced by the permanent

restoration within 4500 FC after the vacuum loss inspection.

3

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.

Temporary restoration of the vacuum loss inspection holes option 2:

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to the

subsequent table:

Rudder SN Refer to Figure

HF-1122, HF-1254

TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet

10

TS-2006, TS-2008,. TS-2010

TS-2027, TS-2030, TS-2033

TS-2043, TS-2048, TS-2049

TS-2054, TS-2055 TS-2059

TS-2061

TS-2071 thru TS-2073

TS-2082

TS-2084 thru TS-2087

Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet

12

<2> If the skin thickness of the affected areas, defined by the TD, does

not exceed 1.5 mm (0.06 in.), do a thermography inspection as

detailed in NTM 51-10-25, Page Block 101 Procedure A and B

AND/OR

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If the skin of the affected areas, defined by the TD, is thicker than

1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM

51-10-24, Page Block 401.

NOTE: During the ultrasound inspection, the vacuum loss

inspection holes must be closed with thin adhesive

tape (Material No 08-052 - basic) to prevent couplant

ingress into the holes.

b In case of damage indications contact AIRBUS for further instructions

before next flight.

c Prepare and dry the restoration area (Refer to SRM 51-77-11 Para

4.M.(2)).

d Prepare

Wet Lay Up Resin 20-022 As required

(Refer to SRM 51-77-11 Para 4.A.(3)).

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.

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

f 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 vacuum loss inspection hole.

g Close the filled holes with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

h 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 in

accordance with the resin manufacturer recommendations and perform a

gelation test outside the restoration area. After resin gelation plus 2h, the

aircraft can be released to operations again.

i Within 4500 FC after the vacuum loss inspection, do the final surface

restoration:

<1> Remove the self adhesive tape from the restoration areas.

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<2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.).

<3> Remove any surplus resin from the border area of the restoration.

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

<4> Clean the restoration areas with

Solvent General

Purpose

11-026 As required

(Refer to SRM 51-77-11 Para 4.E).

<5> Restore the surface protection (Refer to SRM 51-75-12).

4 Permanent restoration of the vacuum loss inspection holes:

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to the

subsequent table:

Rudder SN Refer to Figure

HF-1122, HF-1254

TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet

10

TS-2006, TS-2008,. TS-2010

TS-2027, TS-2030, TS-2033

TS-2043, TS-2048, TS-2049

TS-2054, TS-2055 TS-2059

TS-2061

TS-2071 thru TS-2073

TS-2082

TS-2084 thru TS-2087

Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet

12

<2> If the skin thickness of the affected areas, defined by the TD, does

not exceed 1.5 mm (0.06 in.), do a thermography inspection as

detailed in NTM 51-10-25, Page Block 101 Procedure A and B

AND/OR

If the skin of the affected areas, defined by the TD, is thicker than

1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM

51-10-24, Page Block 401.

NOTE: During the ultrasound inspection, the vacuum loss

inspection holes must be closed with thin adhesive

tape (Material No 08-052 - basic) to prevent couplant

ingress into the holes.

b In case of damage indications contact AIRBUS for further instructions

before next flight.

c

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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 (Refer to SRM 51-77-11 Para

4.M.(2)).

d Prepare

Wet Lay Up Resin 20-022 As required

(Refer to SRM 51-77-11 Para 4.A.(3)).

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.

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

f 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 vacuum loss inspection hole.

g Close the filled holes with a self adhesive tape.

h 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 in

accordance with the resin manufacturer recommendations and perform a

gelation test outside the restoration area. After resin gelation plus 4 h,

continue with the subsequent steps:

<1> Remove the self adhesive tape from the restoration areas.

<2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.).

<3> Remove any surplus resin from the border area of the restoration.

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

<4> Clean the restoration areas with

Solvent General

Purpose

11-026 As required

(Refer to SRM 51-77-11 Para 4.E).

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<5> Restore the surface protection (Refer to SRM 51-75-12).

(g) If there are areas on the trailing edge, shown as ’area 2’ on the Fig. A-GAAAA

Sheet 07, to be inspected, do a special detailed inspection (ELCH) in accordance

with the Flow Chart Fig. A-GAAAA Sheet 03:

1 Do the ELCH inspection within 24 month after the issue of this Service Bulletin

(Refer to NTM 51-10-26, Page Block 701).

a For the ELCH inspection behind the fasteners, use one grid line with a

distance of 50 mm (1.97 in.) between the inspection points, as shown on

Fig. A-GAAAA Sheet 08, View D and View E, area 2.

<1> The assessment criteria for the ELCH inspection behind the

fasteners are:

Yellow value 0.30 mm (0.012 in.)

Red value 0.40 mm (0.016 in.)

For the adjustment of the ELCH, refer to NTM 51-10-26, Page Block

701.

b If the ELCH inspection extends ahead of the fasteners, use an inspection

grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as

shown on Fig. A-GAAAA Sheet 08, View D and View E, area 1.

<1> The assessment criteria for the ELCH inspection ahead of the

fasteners are:

Yellow value 0.25 mm (0.010 in.)

Red value 0.35 mm (0.014 in.)

For the adjustment of the ELCH, refer to NTM 51-10-26, Page Block

701.

2 In case of damage indications, re- examine the findings as per tap test

inspection (Refer to NTM 51-10-03, Page Block 701 or NTM 51-10-19, Page

Block 701), contact AIRBUS for further instructions before next flight.

3 In case of no damage indications, report to AIRBUS within 10 days and do 2

additional ELCH inspections at intervals not exceeding 4500 FC and not less

than 4000 FC.

a In case of damage indications during the additional ELCH inspection, reexamine the findings as per tap test inspection (Refer to NTM 51-10-03,

Page Block 701 or NTM 51-10-19, Page Block 701), and contact AIRBUS

for further instructions before next flight.

b In case of no damage indications during the additional ELCH inspections,

report to AIRBUS within 10 days.

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(h) Fill in the reporting sheet, refer to Fig. A-GAAAA Sheet 05.

In case of damage indications, send the inspection report with a referenced mail to:

AIRTAC

Customer Services

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Phone: +33(0)5 61 93 3400 (24 hour)

Fax: +33(0)5 61 93 3500

Mailto: airtac@airbus.com

and in case of damage indications or no damage indications to

Structure Engineering Support

Customer Services - SEES1

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Fax: +33(0)5 61 93 36 14

(2) Subtask 552049-832-202-002 - Do the rudder special detailed inspection on aircraft

with rudders which have exceeded or will exceed 13000 FC within 24 month after

the issue of this Service Bulletin

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Self-Adhes. Disks 05-052 As required

Self Adhesive Aluminium

Tape

08-052 As required

Solvent General Purpose 11-026 As required

Wet Lay Up Resin 20-022 As required

References

Non Destructive Test Manual (NTM) 51-10-03, Page Block 701

51-10-19, Page Block 701

51-10-24, Page Block 401

51-10-25, Page Block 101 Procedure A and

B

51-10-26, Page Block 701

51-10-28, Page Block 701

Structural Repair Manual (SRM) 51-75-12

51-77-10

51-77-11 Para 4.M.(2)

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

51-77-11 Para 5.

51-77-11 Para 4.E

Fig. A-GAAAA

Rudder inspection

Sheet 01 - Flow Chart 1, vacuum loss

inspection area 1

Sheet 02 - Vacuum loss inspection -

damage assessment

Sheet 03 - Flow Chart 2, ELCH inspection

area 2

Sheet 05 - Reporting sheet

Sheet 06 - Rudder SN identification

Sheet 07 - Inspection areas

Sheet 08 - Typical ELCH procedure

Sheet 09 - Rudder skin thickness LH

Sheet 10 - Rudder skin thickness RH

Sheet 11 - Rudder skin thickness LH

Sheet 12 - Rudder skin thickness RH

Fig. A-GACAA

rudder SN - MSN reference list

Sheet 01

(a) Identify the Serial Number (SN) of the rudder as shown on Fig. A-GAAAA Sheet

06.

(b) If you do not find a SN placard on the rudder, contact AIRBUS for further

instructions.

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(c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list

Fig. A-GACAA Sheet 01.

1 If you find a different SN against the MSN as detailed in the rudder SN - MSN

reference list, contact AIRBUS for further instructions.

2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the

Close-up para 3.E. No further action is necessary.

3 If the rudder is part of the rudder SN - MSN reference list with the same

indicated MSN, continue with the below instructions.

(d) The Technical Disposition (TD) details the location of the reworked area to be

inspected and includes information about the vacuum loss vacuum loss inspection

holes, if necessary.

1 For the definition of the areas to be inspected, refer to the rudder SN - MSN

reference list Fig. A-GACAA Sheet 01 to find the MSN related Technical

Disposition (TD) No.

2 To get the TD, refer to the SB BOOKLET-link on the index page of this

Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and

use ’SB BOOKLET-TD-K45-S1-XXXXX’.

For additional information, refer to SBIT SEMB 914.0808/09

3 Inspection method for reworked areas:

- For reworked area astride AREA 1 and AREA 2, if TD provides vacuum

loss hole location then rework must be treated as if in AREA 1 only.

- For reworked area astride AREA 1 and AREA 2, if TD does not provide

vacuum loss hole location then rework must be treated as if in AREA 2

only.

(e) If there are only areas on the trailing edge shown as ’area 2’ on the Fig. A-GAAAA

Sheet 07, to be inspected, refer to Para (g).

(f) If there is another area, shown as ’area 1’ on the Fig. A-GAAAA Sheet 07, to be

inspected, do the subsequent inspection in accordance with the Flow Chart Fig. AGAAAA Sheet 01 and Fig. A-GAAAA Sheet 02:

1 Do the vacuum loss inspection within 8 month after the issue of this Service

Bulletin (Refer to NTM 51-10-28, Page Block 701).

a Temporarily install adhesive tape on the areas to be inspected.

b Mark the grid of holes on the adhesive tape.

c

CAUTION: DRILL PENETRATION INTO THE SANDWICH

STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.)

TO PREVENT INNER SKIN DAMAGE.

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Drill the vacuum loss inspection holes with DIA 1.5 mm (0.06 in.) through

the outer skin only.

d Do the Vacuum loss inspection (Refer to NTM 51-10-28, Page Block

701).

e In case of damage indications, report to AIRBUS on the basis of a

detailed referenced damage report for further instructions before next

flight.

f In case of no damage indications, close the vacuum loss inspection

holes as detailed in the subsequent instructions and report the result to

AIRBUS within 10 days.

2 Temporary restoration of the vacuum loss inspection holes option 1:

a Close the holes with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

b Do a detailed inspection of the restored area at intervals not exceeding 4

month. Inspect the restored area for loose or lost adhesive disks or tape.

c In case of loose or lost tape or disks, close the holes again with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

d This temporary restoration must be replaced by the permanent

restoration within 4500 FC after the vacuum loss inspection.

3

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.

Temporary restoration of the vacuum loss inspection holes option 2:

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 28

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SERVICE BULLETIN

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to the

subsequent table:

Rudder SN Refer to Figure

HF-1122, HF-1254

TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet

10

TS-2006, TS-2008,. TS-2010

TS-2027, TS-2030, TS-2033

TS-2043, TS-2048, TS-2049

TS-2054, TS-2055 TS-2059

TS-2061

TS-2071 thru TS-2073

TS-2082

TS-2084 thru TS-2087

Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet

12

<2> If the skin thickness of the affected areas, defined by the TD, does

not exceed 1.5 mm (0.06 in.), do a thermography inspection as

detailed in NTM 51-10-25, Page Block 101 Procedure A and B

AND/OR

If the skin of the affected areas, defined by the TD, is thicker than

1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM

51-10-24, Page Block 401.

NOTE: During the ultrasound inspection, the vacuum loss

inspection holes must be closed with thin adhesive

tape (Material No 08-052 - basic) to prevent couplant

ingress into the holes.

b In case of damage indications contact AIRBUS for further instructions

before next flight.

c Prepare and dry the restoration area (Refer to SRM 51-77-11 Para

4.M.(2)).

d Prepare

Wet Lay Up Resin 20-022 As required

(Refer to SRM 51-77-11 Para 4.A.(3)).

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.

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

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 29

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f 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 vacuum loss inspection hole.

g Close the filled holes with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

h 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 in

accordance with the resin manufacturer recommendations and perform a

gelation test outside the restoration area. After resin gelation plus 2h, the

aircraft can be released to operations again.

i Within 4500 FC after the vacuum loss inspection, do the final surface

restoration:

<1> Remove the self adhesive tape from the restoration areas.

<2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.).

<3> Remove any surplus resin from the border area of the restoration.

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

<4> Clean the restoration areas with

Solvent General

Purpose

11-026 As required

(Refer to SRM 51-77-11 Para 4.E).

<5> Restore the surface protection (Refer to SRM 51-75-12).

4 Permanent restoration of the vacuum loss inspection holes:

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to the

subsequent table:

Rudder SN Refer to Figure

HF-1122, HF-1254

TS-1362 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet

10

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 30

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@A310

SERVICE BULLETIN

TS-2006, TS-2008,. TS-2010

TS-2027, TS-2030, TS-2033

TS-2043, TS-2048, TS-2049

TS-2054, TS-2055 TS-2059

TS-2061

TS-2071 thru TS-2073

TS-2082

TS-2084 thru TS-2087

Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet

12

<2> If the skin thickness of the affected areas, defined by the TD, does

not exceed 1.5 mm (0.06 in.), do a thermography inspection as

detailed in NTM 51-10-25, Page Block 101 Procedure A and B

AND/OR

If the skin of the affected areas, defined by the TD, is thicker than

1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM

51-10-24, Page Block 401.

NOTE: During the ultrasound inspection, the vacuum loss

inspection holes must be closed with thin adhesive

tape (Material No 08-052 - basic) to prevent couplant

ingress into the holes.

b In case of damage indications contact AIRBUS for further instructions

before next flight.

c

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 (Refer to SRM 51-77-11 Para

4.M.(2)).

d Prepare

Wet Lay Up Resin 20-022 As required

(Refer to SRM 51-77-11 Para 4.A.(3)).

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.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 31

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SERVICE BULLETIN

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

f 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 vacuum loss inspection hole.

g Close the filled holes with a self adhesive tape.

h 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 in

accordance with the resin manufacturer recommendations and perform a

gelation test outside the restoration area. After resin gelation plus 4 h,

continue with the subsequent steps:

<1> Remove the self adhesive tape from the restoration areas.

<2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.).

<3> Remove any surplus resin from the border area of the restoration.

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

<4> Clean the restoration areas with

Solvent General

Purpose

11-026 As required

(Refer to SRM 51-77-11 Para 4.E).

<5> Restore the surface protection (Refer to SRM 51-75-12).

(g) If there are areas on the trailing edge, shown as ’area 2’ on the Fig. A-GAAAA

Sheet 07, to be inspected, do a special detailed inspection (ELCH) in accordance

with the Flow Chart Fig. A-GAAAA Sheet 03:

1 Do the ELCH inspection within 24 month after the issue of this Service Bulletin

(Refer to NTM 51-10-26, Page Block 701).

a For the ELCH inspection behind the fasteners, use one grid line with a

distance of 50 mm (1.97 in.) between the inspection points, as shown on

Fig. A-GAAAA Sheet 08, View D and View E, area 2.

<1> The assessment criteria for the ELCH inspection behind the

fasteners are:

Yellow value 0.30 mm (0.012 in.)

Red value 0.40 mm (0.016 in.)

or the adjustment of the ELCH, refer to NTM 51-10-26, Page Block

701.

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 32

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SERVICE BULLETIN

b If the ELCH inspection extends ahead of the fasteners, use an inspection

grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as

shown on Fig. A-GAAAA Sheet 08, View D and View E, area 1.

<1> The assessment criteria for the ELCH inspection ahead of the

fasteners are:

Yellow value 0.25 mm (0.010 in.)

Red value 0.35 mm (0.014 in.)

For the adjustment of the ELCH, refer to NTM 51-10-26, Page Block

701.

2 In case of damage indications, re- examine the findings as per tap test

inspection (Refer to NTM 51-10-03, Page Block 701 or NTM 51-10-19, Page

Block 701), and contact AIRBUS for further instructions before next flight.

3 In case of no damage indications, report to AIRBUS within 10 days and do 2

additional ELCH inspections at intervals not exceeding 4500 FC and not less

than 4000 FC.

a In case of damage indications during the additional ELCH inspection, reexamine the findings as per tap test inspection (Refer to NTM 51-10-03,

Page Block 701 or NTM 51-10-19, Page Block 701), and contact AIRBUS

for further instructions before next flight.

b In case of no damage indications during the additional ELCH inspections,

report to AIRBUS within 10 days.

(h) Fill in the reporting sheet, refer to Fig. A-GAAAA Sheet 05.

In case of damage indications, send the inspection report with a referenced mail to:

AIRTAC

Customer Services

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Phone: +33(0)5 61 93 3400 (24 hour)

Fax: +33(0)5 61 93 3500

Mailto: airtac@airbus.com

and in case of damage indications or no damage indications to

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 33

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@A310

SERVICE BULLETIN

Structure Engineering Support

Customer Services - SEES1

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Fax: +33(0)5 61 93 36 14

D. TEST

None

E. CLOSE-UP

(1) Subtask 552049-942-201-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 29-10-00, Page Block 301

55-33-13, Page Block 401

55-40-00, Page Block 601

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

equipment.

(b) To close the access panels, (Refer to AMM 55-33-13, 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: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 34

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@A310

SERVICE BULLETIN

**CONF ALL

INDICATION

FOUND

CLOSE INSPECTION HOLES

YES NO

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS

BEFORE NEXT FLIGHT

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

AND REPORT TO AIRBUS

WITHIN 10 DAYS

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT

BEFORE NEXT FLIGHT

NO FURTHER ACTION

REQUIRED

IN AREA 1

TEMPORARY OPTION II PERMANENT RESTORATION

THERMOGRAPHY INSPECTION

TEMPORARY OPTION I

FREQUENT DETAILED

INSPECTION OF RESTORED

NOT EXCEEDING 4 MONTHS

PERMANENT RESTORATION

THERMOGRAPHY INSPECTION

AS PER NTM 51−10−25

CONTACT AIRBUS

BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS.

WITHIN 4500 FC

WITHIN 4500 FC

AREA, AT INTERVALS

REQUIRED BEFORE RESIN INJECTION.

THERMOGRAPHY INSPECTION

RESTORE FINAL

PROTECTION

OR

COMPARE YOUR RUDDER SERIAL NUMBER WITH THE

RUDDER SERIAL NUMBERS IN THE REFERENCE LIST

YES NO

DO THE SPECIAL DETAILED INSPECTION (VACUUM LOSS)

AS PER NTM 51−10−28

IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

FOR EACH RUDDER

NO FURTHER ACTION

REQUIRED IN

ACCORDANCE WITH

THIS INSPECTION SB

SERIAL NUMBER

FOUND IN REFERENCE

LIST

ULTRASOUND INSPECTION

AS PER NTM 51−10−24

AND

AS PER NTM 51−10−25

CONTACT AIRBUS

BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS.

REQUIRED BEFORE RESIN INJECTION.

ULTRASOUND INSPECTION

AS PER NTM 51−10−24

AND

AS PER NTM 51−10−25

CONTACT AIRBUS

BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS.

REQUIRED BEFORE RESIN INJECTION.

ULTRASOUND INSPECTION

AS PER NTM 51−10−24

AND

NOTE:

FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) B_SB_552049_6_AAAA_01_04

Figure A-GAAAA - Sheet 01

Rudder inspection - Flow Chart 1, vacuum loss inspection area 1

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 35

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@A310

SERVICE BULLETIN

**CONF ALL

DAMAGE ASSESSMENT BY VACUUM LOSS INSPECTION:

IF THE VACUUM LOSS INSPECTION REVEALS DAMAGE AN ADD−ON INSPECTION IN MIDFIELD

DIRECTION ONLY MUST BE PERFORMED TO DEFINE THE OVERALL DAMAGE SIZE.

FOR ADD−ON INSPECTION 1, DRILL ONE ADDITIONAL ROW OF INSPECTION HOLES WITH A PITCH

OF 25.0mm (0.98in.) AND ONE EXTRA HOLE AT EACH END OF THE ROW PARALLEL TO THE DETECTED

LEAKAGE, AS PER SKETCH BELOW. DRILL INSPECTION HOLES WITH DIAMETER 1.5mm (0.06in)

THROUGH THE OUTER SKIN ONLY.

WARNING: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO

20.0mm (0.79in.), TO PREVENT INNER SKIN DAMAGE.

PERFORM VACUUM LOSS INSPECTION (SAME PROCEDURE AS APPLIED FOR BASIC INSPECTION),

POSITION THE VACUUM CUP IN A WAY THAT ONLY ONE OF THE NEW HOLES IS COVERED BY

THE CUP, DURING EACH MEASUREMENT.

IF NO EXTRA LEAKAGE IS FOUND, DOCUMENT THE DAMAGE, USING THE REPORTING SHEET.

IF MORE LEAKAGES ARE FOUND, PROCEED WITH ADD−ON INSPECTION 2 (AND IF REQUIRED

FURTHER STEPS UNTIL THE WHOLE DAMAGE EXTEND IS DETECTED), USING THE SAME 

PROCEDURE AS DETAILED ABOVE.

NOTE: THE OVERALL DAMAGE LENGTH AND WIDTH IS BOUNDED BY THOSE ROWS OF

INSPECTION HOLES, WHICH DO NOT INDICATE A VACUUM LOSS.

OVERALL LENGTH

OVERALL

WIDTH

25.0mm

(0.98in.)

ADD−ON INSPECTION 1

ADD−ON INSPECTION 2

ADD−ON INSPECTION 3

BASIC INSPECTION RESULTS

DIRECTION OF

ADD−ON INSPECTION RESTRICTED AREA

OVERALL DAMAGE SIZE

DEBONDING

DEBONDING AREA

HOLES TO BE INSPECTED IN CASE OF FINDINGS.

RESULTS OF VACUUM LOSS INSPECTION NO LEAKAGE

LEAKAGE DETECTED

WARNING: DRILLING IN THE RESTRICTED AREA CAN DAMAGE THE INNER SKIN AND IS NOT ALLOWED.

B_SB_552049_6_AAAA_02_01

Figure A-GAAAA - Sheet 02

Rudder inspection - Vacuum loss inspection - damage assessment

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 36

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@A310

SERVICE BULLETIN

**CONF ALL

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD

ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

INDICATION

FOUND YES NO

REPORT TO AIRBUS

WITHIN 10 DAYS

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS

BEFORE NEXT FLIGHT

RE−EXAMINE THE FINDINGS

AS PER TAP INSPECTION

NTM 51−10−03 OR NTM 51−10−19

AND

INDICATION

FOUND YES NO

NO FURTHER ACTION

REQUIRED

IN AREA 2

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT

BEFORE NEXT FLIGHT

DO 2 ADDITIONAL ELCH INSPECTIONS

AT INTERVALS NOT EXCEEDING

4500FC AND NOT LESS THAN 4000 FC

REPORT TO AIRBUS

WITHIN 10 DAYS

NO

YES

NO FURTHER ACTION

REQUIRED IN

ACCORDANCE WITH

THIS INSPECTION SB

SERIAL NUMBER

FOUND IN REFENCE

LIST

FOR EACH RUDDER

IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

NOTE:

FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2)

DO THE REPETITIVE SPECIAL DETAILED 

INSPECTION (ELCH) AS PER NTM 51−10−26

B_SB_552049_6_AAAA_03_04

Figure A-GAAAA - Sheet 03

Rudder inspection - Flow Chart 2, ELCH inspection area 2

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 37

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SERVICE BULLETIN

**CONF ALL

Inspection Report

Rudder Surface Inspection as per SB in area:

Aircraft type:

MSN:

Rudder S/N:

Rudder P/N:

Inspection date:

Operator:

FC:

FH:

Inspection method

Tap Test 

Thermography

ELCH Inspection

Vacuum Loss

Inspection

Inspection

Inspection

UT Inspection

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

LH RH

Rudder Side

* use sketch from the TD

B_SB_552049_6_AAAA_05_02

Figure A-GAAAA - Sheet 05

Rudder inspection - Reporting sheet

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 38

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@A310

SERVICE BULLETIN

**CONF ALL

NOTE:

OPEN ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201.

CLOSE ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201.

POSITION OF

RUDDER S/N PLACARD

A

Z326

A

B B

326CL

326AL C D

F

G

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

A55471XXXXXXX

TS(HF)−XXXX

B_SB_552049_6_AAAA_06_02

Figure A-GAAAA - Sheet 06

Rudder inspection - Rudder SN identification

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 39

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@A310

SERVICE BULLETIN

**CONF ALL

TRAILING EDGE AREA

AREA 1 AREA 2

OTHER AREA

50.0 mm

(1.97 in)

370.0 mm

(14.57 in)

50.0 mm

(1.97 in)

285.0 mm

(11.22 in)

SR

C

B_SB_552049_6_AAAA_07_00

Figure A-GAAAA - Sheet 07

Rudder inspection - Inspection areas

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 40

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@A310

SERVICE BULLETIN

**CONF ALL

SR

TYPICAL TRAILING EDGE

ELCH INSPECTION

FASTENERS

AREA 1

AREA 2

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

AREA 1 AREA 2

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.)

NOTE:

E

D

E

B_SB_552049_6_AAAA_08_01

Figure A-GAAAA - Sheet 08

Rudder inspection - Typical ELCH procedure

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 41

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@A310

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

NO INSPECTION

T< 1.5mm (0.059in.)

F

B_SB_552049_6_AAAA_09_02

Figure A-GAAAA - Sheet 09

Rudder inspection - Rudder skin thickness LH

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 42

6

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@A310

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

NO INSPECTION

T< 1.5mm (0.059in.)

G

B_SB_552049_6_AAAA_10_02

Figure A-GAAAA - Sheet 10

Rudder inspection - Rudder skin thickness RH

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 43

6

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@A310

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

NO INSPECTION

T< 1.5mm (0.059in.)

T> 1.5mm (0.059in.)

F

B_SB_552049_6_AAAA_11_00

Figure A-GAAAA - Sheet 11

Rudder inspection - Rudder skin thickness LH

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 44

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@A310

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

NO INSPECTION

T< 1.5mm (0.059in.)

T> 1.5mm (0.059in.)

G

B_SB_552049_6_AAAA_12_00

Figure A-GAAAA - Sheet 12

Rudder inspection - Rudder skin thickness RH

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 45

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@A310

SERVICE BULLETIN

**CONF ALL

Rudder−SN MSN TD/K45/S1/XXXXX/2009 Side

NOTE:

The subsequent rudder SN−MSN reference list reflects the rudder SN−MSN relationship

at the date of the aircraft delivery.

B_SB_552049_6_ACAA_01_02

HF−1122 Spare 01546 LH

HF−1254 0555 01435 LH/RH

TS−1362 Spare 01547 RH

TS−2006 0723 01427 RH

TS−2008 0727 01426 LH/RH

TS−2010 0728 01416 LH

TS−2027 0742 01422 LH/RH

TS−2030 0745 01514 LH

TS−2033 Spare 01548 LH/RH

TS−2043 0757 01415 LH/RH

TS−2048 0766 01417 LH/RH

TS−2049 0762 01414 RH

TS−2054 0772 01428 LH

TS−2055 0774 01410 RH

TS−2059 0771 01411 LH/RH

TS−2061 0761 01418 LH/RH

TS−2071 0779 01424 LH

TS−2072 0780 01433 LH/RH

TS−2073 0781 01425 LH/RH

TS−2082 0789 01429 LH

TS−2084 0791 01431 LH/RH

TS−2085 0788 01432 LH

TS−2086 0792 01413 RH

TS−2087 0793 01434 LH/RH

Figure A-GACAA - Sheet 01

rudder SN - MSN reference list

DATE: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 46

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SERVICE BULLETIN

REPORTING SHEET

TITLE: STABILIZERS - RUDDER - A310 RUDDER DEBOND 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: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- 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: Mar 16/10 SERVICE BULLETIN No.: A310-55-2049

REVISION No.: 00 - Mar 16/10 Page: 1

6

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