@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 - AFT SECTION - INSPECT PAX DOOR FRAME HOLES AT

FR73A

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During the preparation phase for conversion of an A300-600 aircraft from PAX to Freighter, a crack was

detected in Door Frame(FR) 73A, between STGR24 to STGR25, LH/RH. The crack initiation was found

on the seal retainer run out rivet hole, near the frame web of door stops No.8. Because the A310 and

A300-600 aircraft have the same structural door frame design, AIRBUS has decided to do a special

detailed inspection of FR73A on A310 aircraft.

This Service Bulletin requires the operator to introduce a High Frequency Eddy Current (HFEC)

inspection of the seal retainer run out rivet hole at FR73A.

Accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible

crack propagation and will contribute to ensure the structural integrity of the door frame FR73A.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

No Material

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SERVICE BULLETIN

SUMMARY

EFFECTIVITY

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

82Z 85Z 98W 99Y AFG BBC C9L F2I FDX GAF HFY IRA IRM

IYE K1P KAC KZU MGL PIA QAF R1T RJA ROT RZO SGX TSC

UBD UZB WHT

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 532138-832-848-001: Inspection

TOTAL MANHOURS 3.75

ELAPSED TIME (HOURS) 2.75

APPENDICES

Appendix 01 - Elapsed Time Assumption

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SERVICE BULLETIN

SUMMARY

**CONF ALL

STGR18

STGR22X

STGR22A

STGR23

STGR24

STGR25

STGR26

STGR27

STGR28

STGR29

FR73

FR73A

FR74

FR75

FR75A

FR76

A

Z260

A

INSPECTION OF 

DOOR FRAME HOLES

LH SHOWN

RH SYMMETRICAL

B_SB_532138_6_SAAA_01_00

Figure A-GSAAA - 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 - AFT SECTION - INSPECT PAX DOOR FRAME HOLES AT

FR73A

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

310-304 310-308 310-324 310-325

(2) Effectivity by MSN

0489-0492 0494-0500 0503 0519-0520 0522-0524 0526-0527 0537 0539 0545 0547

0549-0552 0562 0564-0565 0567-0568 0571 0574 0576 0585-0588 0590-0595 0597

0599-0600 0620 0622 0624 0636 0644 0646-0649 0651-0653 0656 0658 0660-0661

0663 0667 0671-0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

82Z 0550 0551

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SERVICE BULLETIN

OPERATOR MSN

85Z 0527

98W 0495

99Y 0489

AFG 0496 0497

BBC 0594 0700

C9L 0652

F2I 0520

FDX 0492 0500 0539 0549 0552 0593

GAF 0498 0503 0522 0523

HFY 0565

IRA 0671

IRM 0499 0524 0537 0547 0564 0567 0586 0595 0620

IYE 0568 0702 0704

K1P 0648

KAC 0647 0649 0663

KZU 0592 0622 0646

MGL 0526

PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691

QAF 0667

R1T 0591

RJA 0490 0491

ROT 0636 0644

RZO 0571 0624 0651 0661

SGX 0519 0562

TSC 0545 0588 0597 0599 0600 0658

UBD 0672 0674

UZB 0574 0576 0706

WHT 0494

(4) Configuration by MSN

MSN CONFIGURATION

0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0500

0503 0519 0520 0522 0523 0524 0526 0527 0537 0539 0545

0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571

0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594

0595 0597 0599 0600 0620 0622 0624 0636 0644 0646 0647

0648 0649 0651 0652 0653 0656 0658 0660 0661 0663 0667

0671 0672 0674 0676 0678 0682 0687 0689 0691 0700 0702

0704 0706

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

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SERVICE BULLETIN

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During the preparation phase for conversion of an A300-600 aircraft from PAX to

Freighter, a crack was detected in Door Frame(FR) 73A, between STGR24 to STGR25,

LH/RH. The crack initiation was found on the seal retainer run out rivet hole, near the

frame web of door stops No.8. Because the A310 and A300-600 aircraft have the same

structural door frame design, AIRBUS has decided to do a special detailed inspection of

FR73A on A310 aircraft.

(2) Objective/Action

This Service Bulletin requires the operator to introduce a High Frequency Eddy Current

(HFEC) inspection of the seal retainer run out rivet hole at FR73A.

(3) Advantages

Accomplishment of this Service Bulletin will allow early detection of cracks in order to

avoid possible crack propagation and will contribute to ensure the structural integrity of

the door frame FR73A.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 532138-832-848-001: Inspection

(1) Do a HFEC inspection for cracks at FR73A LH

(2) Do a HFEC inspection for cracks at FR73A RH

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

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SERVICE BULLETIN

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given below but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

Table 01: Config 001- Inspection of seal retainer run out rivet hole at frame 73A

Compliance Time

Whichever occurs later

Condition Action

Threshold: Grace Period:

Repetitive interval

All aircraft Do a HFEC

inspection of the

seal retainer run

out rivet hole at

frame 73A

32000 FC from

aircraft first flight

Whichever occurs

first between a)

and b)

a)Before 36000 FC

from aircraft first

flight

or

b) within 36

months after the

Service Bulletin

issue date

7500 FC

Contact AIRBUS

Repair support

Before the next

flight

Crack findings none none

Report inspection

result to AIRBUS

Within 10 days none none

Report inspection

result to AIRBUS

No crack findings Within 1 month none none

Next HFEC

inspection of the

seal retainer run

out rivet hole at

frame 73A

none none 7500FC

F. APPROVAL

The technical content of this document is approved under the authority of 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.

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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 532138-832-848-001: Inspection

Get Access 1.00

On Aircraft

Do a HFEC inspection for cracks at FR73A LH 0.50

Do a HFEC inspection for cracks at FR73A RH 0.50

Tests 1.50

Close-Up 0.25

TOTAL MANHOURS 3.75

ELAPSED TIME (HOURS) 2.75

NOTE: For a breakdown of the manhours and elapsed time, refer to the Gantt Chart

Fig. A-GAAAA as given in Appendix 01

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

20-21-12 24-00-00 24-41-00

25-00-00 25-12-11 25-22-11

25-23-41 52-10-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-52-10 20-55-00

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

Structural Repair Manual (SRM) 51-24-00 51-40-20

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 531814-02-1

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

No Material Set

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

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

Non Aqueous Cleaner-General - - 08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use the tools listed in NTM

51-10-08, Page Block 601.

(3) Special Tools

None

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 532138-832-848-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: INSTALL A SAFETY BARRIER OR MAKE SURE THAT THE ACCESS

PLATFORM IS IN POSITION BEFORE YOU OPEN A DOOR. A FALL FROM THE

DOOR OPENING CAN BE DANGEROUS.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

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SERVICE BULLETIN

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

Task Associated Data

Zone

260

Manpower

TOTAL MANHOURS 3.75

ELAPSED TIME (HOURS) 2.75

A. GENERAL

(1) Subtask 532138-910-201-001 - Standard Practices

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-52-10

Structural Repair Manual (SRM) 51-24-00

51-40-20

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

Consumable Material List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(e) Do a check of the electrical connectors before you connect them, refer to ESPM

20-52-10.

(f) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(g) Remove and install fasteners in accordance with SRM 51-40-20.

(h) Use a non-metallic spatula to remove the sealant and clean the surface.

(i) Apply sealant in accordance with SRM 51-24-00.

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SERVICE BULLETIN

(2) Subtask 532138-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 532138-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 73A LH/RH

Manpower Resources

Skills NON SPECIFIC

References

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

24-41-00, Page Block 301

25-00-00, Page Block 801

25-22-11, Page Block 401

25-23-41, Page Block 401

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

Block 301.

(c) Energize the ground service network, refer to AMM 24-41-00, Page Block 301.

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(d) Put an access platform in position at the AFT passenger/crew doors 833 and 843.

(e) Open the AFT passenger/crew doors 833 and 843, refer to AMM 52-10-00, Page

Block 001.

(f) Open, safety/lock and tag the applicable circuit breakers as specified in the removal

of door frame linings, refer to AMM 25-23-41, Page Block 401.

(g) At Frame 73A, remove the door frame linings for access, refer to AMM 25-23-41,

Page Block 401.

(h) Put blanking caps on the disconnected electrical connectors.

(i) Between Frame 73 and Frame 73A, remove the heat and sound insulation blankets

for access, refer to AMM 25-22-11, Page Block 401.

(j) If necessary for repair of insulation blankets, refer to AMM 25-00-00, Page Block

801.

C. PROCEDURE

(1) Subtask 532138-250-201-001 - Do a HFEC inspection for cracks at FR73A LH

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 73A LH

from Stringer 24 to Stringer 25

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GBAAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

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References

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

(a) At Frame 73A LH, between STGR 24 and STGR 25 as shown on Fig. A-GBAAA

Sheet 01, Detail A and Fig. A-GBAAA Sheet 02, Detail B, clean the inspection

surface with:

Textile-Lint Free

Cotton -

14SBA1 As required

Non Aqueous

Cleaner-General -

08BAA9 As required

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of the seal retainer run out hole at Frame 73A LH, refer to NTM 51-10-08,

Page Block 601, Fig. A-GBAAA Sheet 01, View A, Fig. A-GBAAA Sheet 02, View B

and the on flow chart Fig. A-GFAAA Sheet 01, at the threshold given in Para

1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet

01, View A and Fig. A-GBAAA Sheet 02, View B.

2 If there are no cracks:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

(2) Subtask 532138-250-202-001 - Do a HFEC inspection for cracks at FR73A RH

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 73A RH

from Stringer 24 to Stringer 25

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Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GBAAA

HFEC Inspection from the seal retainer

run out rivet hole

Sheet 01

Sheet 02

Fig. A-GFAAA

HFEC Inspection Flow Chart

Sheet 01

Fig. A-GRAAA

HFEC inspection Reporting Sheet

Sheet 01

(a) At Frame 73A RH, between STGR 24 and STGR 25 as shown on Fig. A-GBAAA

Sheet 01, Detail A and Fig. A-GBAAA Sheet 02, Detail B, clean the inspection

surface with:

Textile-Lint Free

Cotton -

14SBA1 As required

Non Aqueous

Cleaner-General -

08BAA9 As required

(b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet

head of the seal retainer run out hole at Frame 73A RH, refer to NTM 51-10-08,

Page Block 601, Fig. A-GBAAA Sheet 01, View A, Fig. A-GBAAA Sheet 02, View B

and the flow chart Fig. A-GFAAA Sheet 01 at the threshold given in Para 1.E.(2).

1 Scanning probe to be circled around the rivet head of seal retainer run out

hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet

01, View A and Fig. A-GBAAA Sheet 02, View B.

2 If there are no cracks:

a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01.

b Repeat the HFEC inspection at intervals given in Para 1.E.(2).

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3 If there are cracks:

a Contact AIRBUS repair support for further instructions, before next flight.

b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01.

D. TEST

(1) Subtask 532138-720-201-001 - Functional

Work Zones and Access Panels

Zone Access/Work location

260 Work location Frame 73A LH/RH

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401

25-23-41, Page Block 401

(a) Between Frame 73A and Frame 73 LH/RH, install the heat and insulation blankets,

refer to AMM 25-12-11, Page Block 401.

(b) Remove the blanking caps from the disconnected electrical connectors.

(c) Install the door frame linings, refer to AMM 25-23-41, Page Block 401.

(d) Remove the safety clips and/or the tags and close/unlock the applicable circuit

breakers as specified after installation of the door frame linings, refer to AMM

25-23-41, Page Block 401.

(e) Do a functional test of exit lights as specified after installation on the door frame

linings, refer to AMM 25-23-41, Page Block 401.

E. CLOSE-UP

(1) Subtask 532138-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

260

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00, Page Block 001

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

equipment.

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SERVICE BULLETIN

(b) Close the AFT passenger/crew doors 833 and 843, refer to AMM 52-10-00, Page

Block 001.

(c) Remove the access platform(s).

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SERVICE BULLETIN

**CONF ALL

STGR18

STGR22X

STGR22A

STGR23

STGR24

STGR25

STGR26

STGR27

STGR28

STGR29

FR73

FR73A

FR74

FR75

FR75A

FR76

B

A LH SHOWN

RH SYMMETRICAL

SEAL

REATAINER

A

Z260

B_SB_532138_6_BAAA_01_00

Figure A-GBAAA - Sheet 01

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138

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SERVICE BULLETIN

**CONF ALL

STGR22A

STGR23

STGR24

STGR25

FR73A

AREA TO BE INSPECTED.

MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD.

DOOR STOP 8

10.0 mm

(0.39 in)

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING AFT

SEAL RETAINER

B

B_SB_532138_6_BAAA_02_01

Figure A-GBAAA - Sheet 02

HFEC Inspection from the seal retainer run out rivet hole

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138

REVISION No.: 00 - May 28/14 Page: 18

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SERVICE BULLETIN

**CONF ALL

CRACKS FOUND NO

CONTACT AIRBUS REPAIR SUPPORT

BEFORE NEXT FLIGHT

REPORT INSPECTION RESULT WITHIN

10 DAYS TO AIRBUS

1 MONTH TO AIRBUS

REPORT INSPECTION RESULT WITHIN

AT INTERVAL

DO A REPETITIVE INSPECTION

DO A SPECIAL DETAILED INSPECTION OF THE HOLES

AT THRESHOLD

DETAILED IN PARA. 1.E.(2)

YES

DETAILED IN PARA. 1.E.(2)

FOR THE CRACKED FRAME(S)

ON NON−REPAIRED FRAME(S)

NOTE: THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN

PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE

B_SB_532138_6_FAAA_01_03

Figure A-GFAAA - Sheet 01

HFEC Inspection Flow Chart

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138

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SERVICE BULLETIN

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A310−53−2138

DATE OF INSPECTION :

INSPECTION METHOD :

GENERAL

INSPECTION

DETAILED

INSPECTION DETAILED

INSPECTION

VISUAL

x SPECIAL

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE 

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Structure.sbinspectionresult@airbus.com

FAX +33 (0)5 61 93 36 14

E−mail:

CENTER WING BOX (WB/LR)

YES NO

RESULT OF INSPECTION

CRACK ON

FRAME

LEFT SIDE RIGHT SIDE

73A

YES NO

DISCRIPTION OF FINDINGS

B_SB_532138_6_RAAA_01_01

Figure A-GRAAA - Sheet 01

HFEC inspection Reporting Sheet

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138

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SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A310−53−2138

ON DOOR 833

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

3.75

2.75

STEPS

0.50 0.50

0 10

INSPECTION DOOR 843 0.50 0.50

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

PER

1

1

:

:

SB ELAPSED TIME

(HOURS)

2 4 6 8 12

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

REMOVE FRAME LININGS 

ON DOOR 843 0.50 0.50 1

REMOVE FRAME LININGS 

INSPECTION DOOR 833 0.50 0.50 1

ON DOOR 833 0.75 0.75 1

INSTALL FRAME LININGS 

INSTALL FRAME LININGS 0.75 0.75 1

ON DOOR 843

CLOSE UP 0.25 0.25 1

B_SB_532138_6_AAAA_01_02

Figure A-GAAAA - Sheet 01

Gantt chart

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - AFT SECTION - INSPECT PAX DOOR FRAME HOLES AT

FR73A

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: May 28/14 SERVICE BULLETIN No.: A310-53-2138

REVISION No.: 00 - May 28/14 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 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138

REVISION No.: 00 - May 28/14 Page: 1

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