A310

A310

REVISION No. : 

7 -2038

03

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR

CRACKS

MODIFICATION No. : NONE ATA SYSTEM : 57

This page transmits Revision No. 03 of Service Bulletin No. A310-57-2038.

ADDITIONAL WORK

No additional work is required by this revision for aircraft inspected by

any previous revision.

REASON

Revision No. 03 is issued to cancel the Airworthiness Directive (Consigne

de Navigabilite) No. 89-195-100(B) and to add the Airworthiness Directive

(Consigne de Navigabilite) No. 92-106-132(B). The effectivity has also

been updated.

CHANGES

Lay-out changes due to computerization of this revision are not

identified.

SUMMARY

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES : The Airworthiness

Directive (Consigne de Navigabilite) No. 92-106-132(B) is added.

- EFFECTIVITY : The effectivity is updated.

SERVICE BULLETIN

Planning Information

- EFFECTIVITY : The effectivity is updated. The Standard sentence

concerning Airbus Industrie proprietary information is added.

- REASON, para.(5)(a) : The Airworthiness Directive (Consigne de

Navigabilite) No. 89-195-100(B) is replaced by the Airworthiness

Directive (Consigne de Navigabilite) No. 92-106-132(B).

- REASON, para.(5)(c) : The MRB document reference is amended.

- APPROVAL : The approval sentence is updated.

Accomplishment Instructions

- GENERAL : A WARNING is added to make sure that the aircraft is

electrically grounded. A WARNING is added to make sure that all the

warnings and all the cautions given in the referenced procedures are

obeyed.

- CLOSE-UP : The CML reference for the sealant is specified.

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

- Sep 04/98 PAGE : 1 of 2

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A310

A310

REVISION No. : 

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03

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Material Information

- LIST OF MATERIALS - OPERATOR SUPPLIED : The sealant and the CML

reference for the sealant is specified.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as

a complete document. Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service

Bulletin.

HISTORY OF PREVIOUS REVISIONS

This is only applicable for Revision No. 2 and subsequent. If

information is required for Revisions issued previous to this,

please check your copies of the Revision Transmittal Sheets or

contact Airbus Industrie.

Revision No. 2 was issued to include the use of High Frequency Eddy

Current (HFEC) inspection as an alternative to X-ray inspection.

REVISION SEQUENCE

ORIGINAL : Nov 06/89

REVISION No. : 01 - Dec 05/90

REVISION No. : 02 - Jan 04/96

REVISION No. : 03 - Sep 04/98

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

- Sep 04/98 PAGE : 2

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A310

A310

REVISION No. : 

7 -2038

03

SERVICE BULLETIN

SUMMARY

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

This summary is for information only

and is not approved for modification of the aircraft

TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR

CRACKS

MODIFICATION No. : NONE ATA SYSTEM : 57

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During full scale fatigue testing, cracks were discovered in the bottom

skin stringers adjacent to rib 14 at 50,000 simulated flight cycles (FC).

There is a possibility of similar cracks appearing in service which will

lead to rupture of the stringers. This may be followed by cracking of the

bottom skin which will require extensive repairs.

At rib 14 on the bottom skin, mandatory X-ray or HFEC inspections of the

stringer runouts are required at stringers 6, 7, 8 and 9.

Accomplishment of this Inspection Service Bulletin is mandatory in

accordance with Airworthiness Directive (Consigne de Navigabilite) No.

92-106-132(B).

EFFECTIVITY

This Service Bulletin is applicable to these customer(s):

FDX, THY

SERVICE BULLETIN TO BE ACCOMPLISHED 

PREVIOUSLY OR SIMULTANEOUSLY

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : None

OTHER : None

NATURE OF THE WORK

AIRCRAFT : YES

EQUIPMENT : NO

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

SUMMARY

HARD : NO

SOFT : NO

OBRM : NO

COMPLIANCE

Mandatory

MANPOWER

MANHOURS

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

MATERIAL INFORMATION

AIRCRAFT DATA

None

EQUIPMENT DATA

None

APPENDICES

None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

- Sep 04/98 PAGE : 2

Printed in France
A310

A310

REVISION No. : 

7 -2038

03

SERVICE BULLETIN

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR

CRACKS

MODIFICATION No. : NONE ATA SYSTEM : 57

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Aircraft models : A310-203, A310-222

(2) Aircraft

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

572038 No.

THY008 172

FDX401-405 191,201,230,233,237

407-408 254,257

424-426 241,264,245

428 248

446-450 224,251,260,217,162

This document contains Airbus Industrie PROPRIETARY INFORMATION and

shall at all times remain the property of Airbus Industrie; no

intellectual property right or licence is granted by Airbus

Industrie 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

purpose of performing the tasks described hereunder and provided

that any recipient of such document shall comply with the

conditions herein), without Airbus Industrie’s prior written

consent.

(3) Spares

None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

- Sep 04/98 PAGE : 1 of 9

Printed in France
Inspection Method Inspection Threshold Inspection Interval

X-Ray 12,000 FC 9,200 FC

HFEC 12,000 FC 12,000 FC

A310

A310

REVISION No. : 

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SERVICE BULLETIN

B. REASON

(1) History

During full scale fatigue testing, cracks were discovered in the

bottom skin stringers adjacent to rib 14 at 50,000 simulated flight

cycles (FC).

There is a possibility of similar cracks appearing in service which

will lead to rupture of the stringers. This may be followed by

cracking of the bottom skin which will require extensive repairs.

(2) Objective/Action

Mandatory X-ray or High Frequency Eddy Current (HFEC) inspections

of the stringer runouts are required at stringers 6, 7, 8 and 9

adjacent to rib 14.

(3) Advantages

Early detection of cracks can prevent costly and time consuming

repairs.

(4) Operational/Maintenance Consequences

None

(5) Accomplishment Timescale

(a) Accomplishment of this Inspection Service Bulletin is mandatory

in accordance with Airworthiness Directive (Consigne de

Navigabilite) No. 92-106-132(B).

At rib 14 on the bottom skin, mandatory X-ray or HFEC

inspections of the stringer runouts are required at stringers

6, 7, 8 and 9 within the number of FC which follow:

(b) For aircraft which have exceeded the first inspection threshold

detailed in paragraph (5)(a), this inspection is required

within 1,500 FC from the receipt of this Service Bulletin.

(c) Thresholds and intervals given in this Service Bulletin are

established and valid for aircraft operated with the individual

average airborne flight time of 96 min (1.6h). Therefore when

aircraft are operated with an average airborne flight time

greater than 96 min (1.6h), inspection thresholds and intervals

should be adjusted in accordance with the instructions given in

the A310 Maintenance Review Board Document, Section D, para.

8.

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

NOTE : When an aircraft is operated with an average airborne

flight time of less than 96 min (1.6h), inspection

thresholds and intervals are valid and should not be

adjusted.

For this Service Bulletin, the Fatigue Rating (FR) to be

applied to determine the adjustment factor is 0.13.

Additional flight flexibility, as given in paragraph (5)(b) for

aircraft over the inspection threshold, is not to be adjusted

by this adjustment factor.

(d) The number of touch and go flights can be neglected when they

are less than five percent of the total number of flights

between two consecutive inspections.

When the percentage of touch and go flights is more than five

percent of the total number of flights between two consecutive

inspections, each touch and go flight beyond five percent has

to be counted as a flight cycle. A touch and go is a landing in

which an aircraft touches the runway and does not come to a

complete stop before commencing an additional flight.

C. DESCRIPTION

To accomplish this Service Bulletin it is necessary to:

(1) Defuel the aircraft.

(2) Gain access to the LH and RH outer wing fuel tanks.

(3) Remove sealant from the inspection area.

(4) Do an X-ray or HFEC inspection of the bottom skin stringer runouts

adjacent to rib 14.

(5) Repair as necessary.

(6) Replace any removed sealant.

(7) Close up.

D. APPROVAL

The technical content of this Service Bulletin has been approved under

the Authority of the DGAC Design Organisation Approval No. F.JA.02.

E. MANPOWER

This Service Bulletin is written for an aircraft in a maintenance

status. The manhours/elapsed time estimates do not include the time to

prepare for the inspection, non-productive elapsed time or

administration.

MANHOURS

Gain Access 2.0

Inspection 2.0

Close up 2.0

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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A310

REVISION No. : 

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SERVICE BULLETIN

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

F. MATERIAL - COST AND AVAILABILITY

None

G. TOOLING - PRICE AND AVAILABILITY

None

H. WEIGHT AND BALANCE

None

I. REFERENCES

Aircraft Maintenance Manual (AMM) : 12-11-28, 28-11-22, 28-11-24,

28-25-00

Nondestructive Testing Manual (NTM) : Part 2, 57-25-66, Part 6,

57-25-66

Structural Repair Manual (SRM) : 51-76-20

J. PUBLICATIONS AFFECTED

None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

2. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

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

CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION : MAKE SURE THAT THE AIRCRAFT IS ELECTRICALLY GROUNDED.

(1) Preparation

(a) Defuel the aircraft (Refer to AMM: 28-25-00, P. Block 301).

(b) Put the access platforms in position.

(c) Remove access doors 540HB, 550AB (LH) and 640HB,

650AB (RH) (Refer to AMM: 28-11-22, P. Block 401 andAMM:

28-11-24, P. Block 401).

(d) Remove sealant from the inspection area with a nonmetalic

spatula (Refer to SRM: 51-76-20, P. Block 201 and Refer to

Figure 1 ).

(2) Standard Practices

None

B. INSPECTION

(1) For the X-ray inspection do the instructions that follow :

(a) Do an X-ray inspection of the stringer runouts at stringers 6,

7, 8 and 9 (Refer to Figure 1 and NTM Part 2: 57-25-66).

(b) If no cracks are found, repeat the inspection at intervals of

no more than 9 200 FC.

(c) If a crack is found, refer to the REPAIR paragraph.

(2) For the HFEC inspection do the instructions that follow :

(a) Do an HFEC inspection of the stringer runouts at stringers 6,

7, 8 and 9 (Refer to Figure 1 and NTM Part 6: 57-25-66).

(b) If no cracks are found, repeat the inspection at intervals of

no more than 12 000 FC.

(c) If a crack is found, refer to the REPAIR paragraph.

C. REPAIR

If a crack is found, contact AIRBUS INDUSTRIE and carry out an approved

repair before further flight.

D. TEST

None

E. CLOSE-UP

(1) Reseal the fuel tanks by applying a fillet ofSealant (Mat. No.

09-002) at the junction of the rib and the stringer runout where

sealant has been removed in paragraph A.(1)(d) (Refer to Figure 1 

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

and SRM: 51-76-20, P. Block 201).

(2) Replace access doors 540HB, 550AB (LH) and 640HB, 650AB (RH) (Refer

toAMM: 28-11-22, P. Block 401 andAMM: 28-11-24, P. Block 401).

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

items of equipment.

(4) Refuel the aircraft (Refer to AMM: 12-11-28, P. Block 301).

(5) Do an external inspection of any repaired areas for leaks.

(6) Remove the access platforms.

(7) Report all findings including nil findings to AIRBUS INDUSTRIE.

F. DOCUMENTATION

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

given in this Service Bulletin.

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

Figure 1 Sheet 1

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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Inspection Area
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A310

REVISION No. : 

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SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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This Page Intentionally Left Blank
A310

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REVISION No. : 

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SERVICE BULLETIN

3. MATERIAL INFORMATION

A. LIST OF COMPONENTS

None

B. SPECIAL TOOLS

None

C. LIST OF MATERIAL - OPERATOR SUPPLIED

DESCRIPTION REFERENCE TO CML QTY PER A/C

Sealant (Mat. No. 09-002) As required

D. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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A310

REVISION No. : 

7 -2038

03

SERVICE BULLETIN

ACCEPTANCE/REJECTION SHEET

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR

CRACKS

MODIFICATION No. : NONE ATA SYSTEM : 57

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW

Please fill : ...REJECTED

...WILL BE EMBODIED

...EFFECTIVITY

This SB can only be incorporated in your "customized"

documentation within the agreed time schedule in so far as this

sheet returned to us on purchase date and signed by a duly

authorized and empowered officer or representative.

FROM :

AIRLINE :

NAME :

DATE :

Please return to :

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : AI/SE-D32 Technical Data

and Documentation Services

FAX : (+33) 5 61 93 28 06

DATE : Nov 06/89 SERVICE BULLETIN No. : -57

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Printed in France