@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: 53

TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT

JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Some operators have reported cracks in a crossbeam at the junction with the cargo-door actuator

support-beam. The damage was located at the outboard row of rivets on the crossbeam at FR23. The

laboratory analysis revealed that the cracks are initiated in the fastener hole propagating vertically. The

design of FWD and AFT cargo door attachments are similar to the crossbeams at FR22/23 and

FR61/FR62 and should be inspected.

On passenger aircraft, in case of cracks being present in a crossbeam (upper and lower web), the floor

grid cannot withstand ultimate load condition.

This Service Bulletin details the inspection procedure for aircraft on which the crossbeams are not

previously repaired by the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS).

This inspection procedure details :

- High Frequency Eddy Current inspection which will inspect the crossbeams for cracks at FR22/23

and FR61/62.

before the accumulation of 10000 total aircraft flight cycles.

NOTE: For aircraft on which the crossbeams have been previously repaired by the Structure

Repair Manual (SRM) or a Repair Approval Sheet (RAS) the operator has to contact

AIRBUS before reaching the threshold or the grace period for further instructions.

In the case no crack(s) are found :

- repeat this inspection at an interval not to exceed 600 Flight Cycles (FC)

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SERVICE BULLETIN

SUMMARY

or

- accomplish Modification Service Bulletin No. A310-53-2133 within 600 Flight Cycles (FC) after the

last inspection in accordance with this Inspection Service Bulletin.

. The accomplishment of Modification Service Bulletin No. A310-53-2133 cancels the

requirements of this Inspection Service Bulletin.

In the case crack(s) are found :

- longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their instructions.

- smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their

instructions within 50FC.

The accomplishment of this Service Bulletin :

- monitors the structure surrounding the rivet heads on crossbeams at FR22/23 and FR61/62

- can prevent heavy repair.

The accomplishment of Modification Service Bulletin No. A310-53-2133 cancels the requirements of this

Inspection Service Bulletin.

NOTE: This Service Bulletin is mandatory for all passenger aircraft.

NOTE: If operators have previously accomplished the Modification Service Bulletin No.

A310-53-2133, the accomplishment of this Inspection Service Bulletin is no longer

required.

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

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo

Compartment Doors

EFFECTIVITY

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

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SERVICE BULLETIN

SUMMARY

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 None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 532134-832-848-001: Inspection

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

APPENDICES

None

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SERVICE BULLETIN

SUMMARY

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

HFEC INSPECTION AREA

FWD

A

B_SB_532134_6_SAAA_01_00

Z130

A

Figure A-GSAAA - Sheet 01

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FWD

A

B_SB_532134_6_SBAA_01_00

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

SEAT TRACK 6

FR60 FR61 FR62 FR63

HFEC INSPECTION AREA

A

Z150

Figure A-GSBAA - Sheet 01

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SUMMARY

This Page Intentionally Left Blank

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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: 53

TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT

JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM

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 0260

0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313 0316 0318

0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0349 0353 0355-0357

0359-0360 0362 0364 0367 0369-0370 0372 0375 0378-0379 0386 0389-0390 0392

0394 0397 0399-0400 0406-0407 0410 0413 0416 0418-0419 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 0494-0500 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 0691

0693 0697 0700 0702 0704 0706

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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 0700

BLE 0650

CFC 0425 0441 0444 0446 0482

CSA 0672 0674

DAH 0291 0293

DEC 0684 0693 0697

DGA 0418 0421 0422

F2I 0309

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

0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303

0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346

0349 0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397

0400 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 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 0702 0704

JAB 0320 0419

JAV 0357 0481

KAC 0647 0649 0663

KTC 0524 0567 0620

KYV 0386

KZU 0592 0622 0646

MGL 0526

MWA 0652

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SERVICE BULLETIN

OPERATOR MSN

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

0691

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 0260 0264 0267 0273 0278 0281 0283 0288

0291 0293 0297 0303 0309 0313 0316 0318 0320 0326 0331

0333 0335 0338 0339 0342 0343 0345 0346 0349 0353 0355

0356 0357 0359 0360 0362 0364 0367 0369 0370 0372 0375

0378 0379 0386 0389 0390 0392 0394 0397 0399 0400 0406

0407 0410 0413 0416 0418 0419 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 0500

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 0691 0693 0697 0700 0702 0704 0706

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the passenger aircraft given in the effectivity of this Service

Bulletin as a standard configuration for High Frequency Eddy Current (HFEC)

inspections at the crossbeams between FR22/23 and FR61/62.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Standard tool TOOLD01 2

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SERVICE BULLETIN

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Some operators have reported cracks in a crossbeam at the junction with the cargo-door

actuator support-beam. The damage was located at the outboard row of rivets on

the crossbeam at FR23. The laboratory analysis revealed that the cracks are initiated

in the fastener hole propagating vertically. The design of FWD and AFT cargo door

attachments are similar to the crossbeams at FR22/23 and FR61/FR62 and should be

inspected.

(2) Objective/Action

On passenger aircraft, in case of cracks being present in a crossbeam (upper and lower

web), the floor grid cannot withstand ultimate load condition.

This Service Bulletin details the inspection procedure for aircraft on which the

crossbeams are not previously repaired by the Structure Repair Manual (SRM) or a

Repair Approval Sheet (RAS).

This inspection procedure details :

- High Frequency Eddy Current inspection which will inspect the crossbeams for

cracks at FR22/23 and FR61/62.

before the accumulation of 10000 total aircraft flight cycles.

NOTE: For aircraft on which the crossbeams have been previously repaired by

the Structure Repair Manual (SRM) or a Repair Approval Sheet (RAS)

the operator has to contact AIRBUS before reaching the threshold or the

grace period for further instructions.

In the case no crack(s) are found :

- repeat this inspection at an interval not to exceed 600 Flight Cycles (FC)

or

- accomplish Modification Service Bulletin No. A310-53-2133 within 600 Flight Cycles

(FC) after the last inspection in accordance with this Inspection Service Bulletin.

. The accomplishment of Modification Service Bulletin No. A310-53-2133 cancels

the requirements of this Inspection Service Bulletin.

In the case crack(s) are found :

- longer than 7.0mm 0.27in.) contact AIRBUS before the next flight and follow their

instructions.

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SERVICE BULLETIN

- smaller than or equal to 7.0mm 0.27in.) contact AIRBUS before the next flight and

follow their instructions within 50FC.

(3) Advantages

The accomplishment of this Service Bulletin :

- monitors the structure surrounding the rivet heads on crossbeams at FR22/23 and

FR61/62

- can prevent heavy repair.

The accomplishment of Modification Service Bulletin No. A310-53-2133 cancels the

requirements of this Inspection Service Bulletin.

NOTE: This Service Bulletin is mandatory for all passenger aircraft.

NOTE: If operators have previously accomplished the Modification Service

Bulletin No. A310-53-2133, the accomplishment of this Inspection

Service Bulletin is no longer required.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 532134-832-848-001: Inspection

(1) Special detailed HFEC Inspection at FR22/23 and FR61/62

E. COMPLIANCE

(1) Classification

MANDATORY

(2) Accomplishment Timescale

COMPLIANCE TIME

(whichever occurs later)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

If crossbeams

FR22/23 and

FR61/FR62 have

been repaired

previously by SRM

or RAS

Before reaching the

threshold or grace

period contact

Airbus for further

instructions

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SERVICE BULLETIN

If crossbeams

FR22/23 and

FR61/FR62 have

not been repaired

previously by SRM

or RAS

Inspect in

accordance with

SUBTASK

532134-832-201-001

(Special detailed

HFEC inspection)

for crack(s) at

FR22/23 and

FR61/FR62

Before the

accumulation of

10000 total Flight

Cycles (FC)

600FC from

Service Bulletin

issuance

If the crack length is smaller than or

equal to 7.0mm 0.27in.) contact

AIRBUS before the next flight and

follow their instructions within 50FC

Crack(s) found Contact Airbus for Not applicable

further instructions

If a crack length is longer than 7.0mm

0.27in.) contact AIRBUS before the

next flight and follow their instructions

Not applicable

Accomplish Service

Bulletin No.

A310-53-2133

Accomplish the Modification Service

Bulletin A310-53-2133 within 600FC

after the last inspection in accordance

with this Inspection Service Bulletin

Not applicable

or

No Crack(s) found

Repeat the

inspection

600FC

Table 1 : Special detailed HFEC inspection for cracks at FR22/23 and FR61/FR62

The accomplishment of Modification Service Bulletin Nos. A310-53-2133 cancels the

requirements of this Inspection Service Bulletin.

Accomplishment of this Service Bulletin is expected to be rendered mandatory for

passenger aircraft 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 Organisation 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.

Aircraft that listed in this Service Bulletin and have been converted to freighter aircraft may

have a difference in the affected area. In this event, the operator should contact the relevant

Customer Service to obtain the necessary information about the future/planned Service

Bulletins for the converted aircraft.

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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 532134-832-848-001: Inspection

Get Access 4.00

On Aircraft

Special detailed HFEC Inspection at FR22/23 and

FR61/62

0.50

Close-Up 3.00

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00

25-54-10 25-55-10 52-30-00

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-08

Service Bulletin (SB) A310-53-2133

K. PUBLICATION AFFECTED

Not Applicable

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

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

None

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - Fwd And Aft

Cargo Compartment Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

(3) Special Tools

None

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 532134-832-848-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND

MECHANICALLY SERVICEABLE).

WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS,

ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA

AS CLEAN AS POSSIBLE. TO DO THIS :

- PUT PROTECTION, SUCH AS PlastIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON ELECTRICAL WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

Task Associated Data

Zone

120 130 150

Access

Door 811 812

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 4.00

A. GENERAL

(1) Subtask 532134-910-201-001 - Standard Practices

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Skills NON SPECIFIC

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

(a) For the location of access panels (Refer to AMM 06-41-53, Page Block 001).

(2) Subtask 532134-839-201-001 - Documentation

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 532134-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD And

AFT Cargo Compartment

Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

References

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

24-41-00, Page Block 301

25-54-10, Page Block 201

25-55-10, Page Block 201

52-30-00, Page Block 301

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

Block 301).

(b) Put access platform(s) in position.

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(c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301).

(d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

(f) Secure the FWD and AFT cargo-compartment doors with :

98A52307523000 Support Struts -

FWD And AFT

Cargo

Compartment Doors

2

or with the door actuator safety lock(s).

Refer to AMM 52-30-00, Page Block 301

(g) Remove the FWD cargo-compartment ceiling panels 132AC and 132BC (Refer to

AMM 25-54-10, Page Block 201).

(h) Remove the door actuator lining between FR22 and FR23.

(i) Remove the AFT cargo-compartment ceiling panels 152DC and 152EC (Refer to

AMM 25-55-10, Page Block 201).

(j) Remove the door actuator lining between FR61 and FR62.

(2) Subtask 532134-865-201-001 - C/B Opening

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Skills ELECTRICAL

(a) Open, safety and tag these circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 13

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SERVICE BULLETIN

C. PROCEDURE

(1) Subtask 532134-832-201-001 - Special detailed HFEC Inspection at FR22/23 and

FR61/62

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 811

Work location from Frame 22, Seat Track 4/5 to Frame 23,

Seat Track 4/5

150 Access Door 812

Work location from Frame 61, Seat Track 4/5 to Frame 62,

Seat Track 4/5

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-08

Service Bulletin (SB) A310-53-2133

Fig. A-GBAAA

HFEC Inspection for cracks between

FR22/23

Sheet 01

Sheet 02

Fig. A-GBEAA

HFEC Inspection for cracks between

FR61/62

Sheet 01

Sheet 02

Fig. A-GFAAA

Flow-Chart : HFEC Inspection for cracks

between FR22/23 and FR61/62

Sheet 01

(a) Check if the crossbeams between :

- FR22 and FR23 and

- FR61 and FR62

have been previously repaired by SRM or RAS.

1 In the case the crossbeams are previously repaired by SRM or RAS contact

AIRBUS and follow their instruction.

2 In the case the crossbeams are not previously repaired by SRM or RAS :

a Perform the special detailed HFEC Inspection for crack(s) in the area

around the rivet heads at FR22 and FR23.

Refer to NTM 51-10-08

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

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SERVICE BULLETIN

Refer to Fig. A-GBAAA Sheet 02, Details B and C

Refer to Fig. A-GFAAA Sheet 01

b Perform the special detailed HFEC Inspection for crack(s) in the areas

around the rivet heads at FR61 and FR62.

Refer to NTM 51-10-08

Refer to Fig. A-GBEAA Sheet 02, Details B and C

Refer to Fig. A-GFAAA Sheet 01

c In the case no crack(s) is/are found :

<1> Repeat the inspection at interval not to exceed 600FC

or

<2> Accomplish Service Bulletin No. A310-53-2133 within 600FC after

the last inspection in accordance with this Inspection Service

Bulletin.

No further action is required in accordance with this Service Bulletin.

d In the case crack(s) is/are found :

<1> In the case the crack(s) is/are longer than 7.0mm (0.27in.) :

<a> Contact AIRBUS before the next flight and follow their

instructions.

<b> No further action is required in accordance with this Service

Bulletin.

<2> In the case the crack(s) is/are crack(s) smaller than or equal to

7.0mm (0.27in.) :

<a> Contact AIRBUS before the next flight and follow their

instructions within the next 50FC.

<b> No further action is required in accordance with this Service

Bulletin.

D. TEST

(1) Subtask 532134-700-201-001 - Testing

Manpower Resources

Skills NON SPECIFIC

None

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 15

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SERVICE BULLETIN

E. CLOSE-UP

(1) Subtask 532134-865-202-001 - C/B Closing

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Skills ELECTRICAL

(a) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(2) Subtask 532134-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-54-10, Page Block 201

25-55-10, Page Block 201

52-30-00, Page Block 301

(a) Install the FWD cargo-compartment ceiling panels 132AC and 132BC (Refer to

AMM 25-54-10, Page Block 201).

(b) Install the door actuator lining between FR22 and FR23.

(c) Install the AFT cargo-compartment ceiling panels 152DC and 152EC (Refer to

AMM 25-55-10, Page Block 201).

(d) Install the door actuator lining between FR61 and FR62.

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

equipment.

(f) Make sure that the applicable cargo-door safety-equipment is removed from the

FWD and AFT cargo-compartment door.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 16

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SERVICE BULLETIN

(g) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(h) Close the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

(i) Remove the access platform(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 17

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SERVICE BULLETIN

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

FWD

A

B_SB_532134_6_BAAA_01_00

Z130

A

B C

Figure A-GBAAA - Sheet 01

HFEC Inspection for cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 18

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SERVICE BULLETIN

**CONF ALL

NOTE:

POSSIBLE CRACK IN CROSSBEAM STRUCTURE 

01

VIEW LOOKING AFT

VIEW LOOKING FWD

FR22

FR23

(AROUND RIVET HEADS), REFER TO NTM 51−10−08, PB 601

D

01

01

01

01

D

B

02

INSPECTION AREA FOR THE HFEC INSPECTION

D

TYPICAL

02

C

BENEATH INSPECTION AREA B_SB_532134_6_BAAA_02_01

Figure A-GBAAA - Sheet 02

HFEC Inspection for cracks between FR22/23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 19

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SERVICE BULLETIN

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

SEAT TRACK 6

FR60 FR61 FR62 FR63

FWD

A

B C

B_SB_532134_6_BEAA_01_00

A

Z150

Figure A-GBEAA - Sheet 01

HFEC Inspection for cracks between FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

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SERVICE BULLETIN

**CONF ALL

VIEW LOOKING AFT

VIEW LOOKING FWD

FR61

FR62

01

01

01

01

B

C

D

TYPICAL

02

D

D

B_SB_532134_6_BEAA_02_01

NOTE:

POSSIBLE CRACK IN CROSSBEAM STRUCTURE 

01

(AROUND RIVET HEADS), REFER TO NTM 51−10−08, PB 601

02

INSPECTION AREA FOR THE HFEC INSPECTION

BENEATH INSPECTION AREA

Figure A-GBEAA - Sheet 02

HFEC Inspection for cracks between FR61/62

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SERVICE BULLETIN

**CONF ALL

YES

CRACK FINDINGS

YES

CRACK LENGTH

MORE THAN

7.0mm (0.28 in.)

NO

OR

ACCOMPLISH SERVICE BULLETIN

NO. A310−53−2133 

WITHIN 600FC AFTER THE LAST

NO YES

NO FURTHER ACTION IS 

REQUIRED IN ACCORDANCE

WITH THIS INSPECTION

SERVICE BULLETIN

NO

CROSSBEAMS FR22/23

AND FR61/62 REPAIRED BY 

SRM OR RAS PREVIOUSLY

PARA. 1.E.(2), DO A SPECIAL DETAILED

 HFEC INSPECTION OF THE CROSSBEAMS,

REFER TO NTM 51−10−08, PB 601

AT THE THRESHOLD DETAILED IN 

REPEAT THE 

INSPECTION

AT INTERVAL

NOT TO

EXCEED 600FC

INSPECTION IN ACC. WITH THIS

INSPECTION SERVICE BULLETIN

B_SB_532134_6_FAAA_01_04

BEFORE REACHING

THE THRESHOLD OR

GRACE PERIOD

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

WITHIN 50FC

CONTACT AIRBUS

BEFORE THE NEXT

FLIGHT AND FOLLOW

THEIR INSTRUCTIONS

CONTACT AIRBUS

AND FOLLOW THEIR

INSTRUCTIONS

Figure A-GFAAA - Sheet 01

Flow-Chart : HFEC Inspection for cracks between FR22/23 and FR61/62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 22

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - STRUCTURE - INSPECT FOR CROSSBEAM AT

JUNCTION WITH LOWER DECK CARGO DOOR ACTUATOR BEAM

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: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 1

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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: Jan 15/10 SERVICE BULLETIN No.: A310-53-2134

REVISION No.: 00 - Jan 15/10 Page: 1

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