6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 53

TITLE : FUSELAGE - INSPECT LONGITUDINAL LAP JOINTS FOR CRACKS IN 

THRU 18

MODIFICATION No. : NONE

This page transmits Revision No. 07 of Service Bulletin No. A300-

ADDITIONAL WORK

There are areas which have been defined as new inspection are

Revision. These areas were not included in the previous issue

inspected at the next interval.

REASON

This Revision is issued to :

— inform the affected operators that the inspection program de

Service Bulletin has been refined to allow A300 B2/B4/C4 air

the Limit Of Validity (LOV),

— update the effectivity.

CHANGES

SUMMARY :

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Reason amended.

— EFFECTIVITY

. Effectivity updatedPLANNING INFORMATION :

— EFFECTIVITY

. 1.A. Updated.

— REASON
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— DESCRIPTION

. 1.D. Description amended.

— COMPLIANCE

— Accomplishment Timescale

. 1.E.(2) Sentence updated.

— APPROVAL

. 1.F. First sentence amended.

— REFERENCES

. 1.J. Updated.

— TOOLING - PRICE AND AVAILABILITY

. 2.F. References updated.

ACCOMPLISHMENT INSTRUCTIONS :

— GENERAL

. 3.A.(1)(a) Reference changed to AMM 24-00-00.

. 3.A.(1)(c) Reference changed to AMM.

— Work Breakdown

. 3.A.(3) Figure reference updated.

. 3.A.(3)(a) Wording changed and NOTES relocated/updated.

. 3.A.(3)(b) Revised.

— INSPECTION

. 3.B.(1) NOTE completed.

. 3.B.(1)(a)1 Sentence amended.

. 3.B.(1)(a)2 Special areas added

. 3.B.(1)(a)2a Workstep amended.

2
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

. Sheet 1, Amended.

— Figure 3

. Sheets 1 thru 6, Amended.

— Figure 4

. Sheet 1, Amended.

— Figure 5

. Sheets 1 and 2, Amended.

— Figure 6

. Sheets 1 thru 4, Amended.

— Figure 7

. Sheet 1, New Figure.

— Figure 8

. Sheets 7 and 8, Amended.

— Figure 9

. Sheets 1 and 3, Amended.

NOTE : Layout changes due to computerization of this revision 

identified.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is 

complete document. Replace the complete document.

Put this Revision transmittal Sheet in front of the Service B

HISTORY OF PREVIOUS REVISIONS

This history only describes the previous Revision No. 06 and 

information is required for revisions issued previous to this

your copies of the Revision Transmittal Sheet or contact AIRB

3
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

REVISION No. : 01 — Apr 10/89

REVISION No. : 02 — Jul 15/89

REVISION No. : 03 — Jan 18/91

REVISION No. : 04 — Jul 08/92

REVISION No. : 05 — Apr 29/99

REVISION No. : 06 — Feb 26/03

REVISION No. : 07 — Dec 01/06

4
6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

MANDATORY MANDATORY MAND

ATA SYSTEM : 53

TITLE : FUSELAGE - INSPECT LONGITUDINAL LAP JOINTS FOR CRACKS IN 

THRU 18

MODIFICATION No. : NONE

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

This Service Bulletin contains an inspection program for all long

joints and repairs between FR18 and FR80 due to two major damages 

end of full scale fatigue testing. The joint modifications are cov

Service Bulletins No. A300-53-0126, A300-53-0206, A300-53-0209, A

A300-53-0216 and A300-53-0306.

Test programs performed by the manufacturer on original test stru

specimens have led to a crack inspection which is divided into fo

— Special Areas,

— Standard Areas,

— Repaired Areas,

— Modified Areas.

NOTE : Standard or Special Areas

If Service Bulletin No. A300-53-0223 is not accomplished o

to MSN 0036, the first inspection must be performed as per 

Bulletin No. A300-53-0225.

NOTE : Repair Areas

If repairs do not correspond to the described solutions 1 

contact AIRBUS - SEE81 for an individual inspection program

NOTE : Modified Areas

The inspection program detailed in this Service Bulletin a

B2/B4/C4 aircraft to reach the Limit Of Validity (LOV).
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

non-heat-treated aluminium rivets, contact AIRBUS - SEE81 

instructions.

The inspection program detailed in this Service Bulletin allows A

aircraft to reach the Limit Of Validity (LOV).

EFFECTIVITY

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

50W 73X A2S ABR BCS BHY DHL F2I FLM IRA IRM KZU MNB NTR OHY RUN SG

TSY

This Service Bulletin is not applicable on aircraft MSN 0157 and 

to the production embodiment of Mod. No. 2611 that improves the f

the longitudinal lap joints of the outer skin.

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB 

AD Yes A/C OPERATION AFFECTED 

RELIABILITY AFFECTED No PAX COMFORT AFFECTED 

COST SAVING No ETOPS AFFECTED 

STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED 

KIT PRICE (USD) No kit

2
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANPOWER

MSN 0003 (Special areas)

MSN 0019-0156 (Special areas)

MSN 0003 , 0019-0156 (Standard areas)

NOTE : Estimates are based on one team including two inspectors. 

one team is used, the manhours decrease accordingly.

REPAIRED AREAS All hours listed below are calculated for one fram

solution 1 : SRM solution without cut out

Repair solution 2 : Old SRM solution with cut out

Repair solution 3 : Old SRM solution without cut out (inner skin 

Repair solution 4 : SRM solution with cut out

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 1

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

3
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Repair solution 7 : Aircraft MSN 0095 at STGR52 LH, in Section 16

Repair solution 9 : Aircraft MSN 007 and 0095 solution at STGR44 

Sections 16 and 17

Repair solution 10 : Repair solution in accordance with repair dr

R53772132, issue C or Inspection Service Bulletin No. A300-53-033

A300-53-0341. Post repair inspections have to be carried out in a

this Service Bulletin, refer to figure 13.

MODIFIED AREAS All hours listed below are calculated for one fram

solution 1 : Retrofit lap joint (SB No. A300-53-0206 or A300-53-0

out)

Retrofit solution 2 : Retrofit lower shell (4 panel solution) (SB 

A300-53-0215). Additionally inspect STGR49 LH and STGR47 RH in Se

Retrofit solution 3 : Retrofit lower shell (3 panel solution) (SB 

A300-53-0216). Additionally inspect STGR54 LH in Section 14

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

4
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Retrofit solution 6 : Retrofit lap joint (SB No. A300-53-0306)

MATERIAL INFORMATION

AIRCRAFT DATA

None

APPENDICES

None

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

5
6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 53

TITLE : FUSELAGE - INSPECT LONGITUDINAL LAP JOINTS FOR CRACKS IN 

THRU 18

MODIFICATION No. : NONE

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that the said document and the 

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without AIRBUS prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

B2-1C B2-203 B2K-3C B4-103 B4-120 B4-203 B4-2C C4-20

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

0003 0019 0035 0041 0044 0045 0047 0053 0055 00

0078-0080 0082-0085 0090 0093-0095 0100 0101 010

0117 0121 0123-0126 0128 0129 0133-0141 0146-01

(b) Effectivity by Operator

The Operator/MSN relationship is provided for in

and is correct at the time of issue in accordan

information available to AIRBUS. Any future cha

from transfer of an aircraft from one operator t

not be reflected in this list unless the Service 

revised for another reason.
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(c) Effectivity by MSN and Kit/Configuration

No AIRBUS kit is required for the accomplishment 

Service Bulletin.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

This Service Bulletin contains an inspection program 

longitudinal lap joints and repairs between FR18 and 

two major damages found at the end of full scale fat

The joint modifications are covered by Service Bullet

ABR 0148

BCS 0095 0116 0150 0152

BHY 0094 0128

DHL 0084 0085 0141 0149

F2I 0079 0093 0133 0135 0136 0137 0156

FLM 0082 0151

IRA 0080

IRM 0035 0055

KZU 0041 0044 0101 0106 0117 0139 0140

MNB 0019 0047 0123 0126

NTR 0124 0155

OHY 0138

RUN 0083 0105 0107 0121 0147

SGX 0090

TCN 0073 0125 0134

TDX 0053 0075 0100 0154

TNO 0045 0074 0078

TSY 0129

2
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Special Areas,

— Standard Areas,

— Repaired Areas,

— Modified Areas.

NOTE : Standard or Special Areas

If Service Bulletin No. A300-53-0223 is not ac

aircraft up to MSN 0036, the first inspection 

performed as per Service Bulletin No. A300-53

NOTE : Repair Areas

If repairs do not correspond to the described 

thru 10 please contact AIRBUS - SEE81 for an 

inspection program.

NOTE : Modified Areas

The inspection program detailed in this Servic

allows A300 B2/B4/C4 aircraft to reach the Lim

(LOV).

NOTE : The inspections (threshold and follow-up inspe

based on the use of heat-treated rivets as sta

51-40-30 and that allowable limits (residual t

not been exceeded, if former damages (corrosio

scratches) have been removed with SRM 53-10-00 

NOTE : The use of non-heat-treated aluminium rivets w

inspection threshold significantly. If repair

accomplished with non-heat-treated aluminium r

AIRBUS - SEE81 for further instructions.

(3) Advantages

The inspection program detailed in this Service Bull

A300 B2/B4/C4 aircraft to reach the Limit Of Validity 

(4) Operational/Maintenance Consequences

None

3
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(3) Do the crack classification and follow-up action.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

To allow a sufficient planning an application tolera

counted from receipt of this Service Bulletin is appl

as these values do not exceed 50% of the intervals.

Accomplishment of this Service Bulletin is expected t

mandatory by the issue of an Airworthiness Directive 

by the European Aviation Safety Agency (EASA). It is 

that the AD will confirm the thresholds and/or interv

this Service Bulletin but reference should be made to 

confirmation of the mandated accomplishment timescal

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labor cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operators' circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

procurement of parts and tools, drying time for paints, s

and general administration work are also not included.

MSN 0003 (Special areas)

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

4
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

, ()

NOTE : Estimates are based on one team including two inspe

than one team is used, the manhours decrease accord

REPAIRED AREAS All times listed below calculated for one 

Repair solution 1 : SRM solution without cut out

Repair solution 2 : Old SRM solution with cut out

Repair solution 3 : Old SRM solution without cut out (inn

Repair solution 4 : SRM solution with cut out

Repair solution 4A : SRM solution with cut out

Inspection 1

TOTAL MANHOURS 1

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

5
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

p

LH/RH, in Sections 16 and 17

Repair solution 10 : Repair solution in accordance with r

R53772132, issue C or Inspection Service Bulletin No. A300

A300-53-0341. Post repair inspections have to be carried o

accordance with this Service Bulletin, refer to figure 13

MODIFIED AREAS All times listed below calculated for one 

Retrofit solution 1 : Retrofit lap joint (SB No. A300-53-0

A300-53-0209 with cut out)

Retrofit solution 2 : Retrofit lower shell (4 panel solut

A300-53-0215). Additionally inspect STGR49 LH and STGR47 

14

Retrofit solution 3 : Retrofit lower shell (3 panel solut

A300-53-0216). Additionally inspect STGR54 LH in Section 

Retrofit solution 4 : Retrofit lap joint (SB No. A300-53-0

cut out)

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

6
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Retrofit solution 6 : Retrofit lap joint (SB No. A300-53-0

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

K. PUBLICATIONS AFFECTED

None

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Inspection 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Aircraft Maintenance Manual (AMM) : 24-00-00 53-15-63

Nondestructive Testing Manual (NTM) : PART 1, 51-21-05 

51-31-05 PART 1, 

Nondestructive Testing Manual (NTM) : PART 4, 53-30-10,

Config. 1

PART 4, 53-30-10, 

3

Nondestructive Testing Manual (NTM) : PART 6, 53-30-10, 

1 PART 6, 53-30-1

Config. 2 PART 6, 

Structural Repair Manual (SRM) : 53-10-20

Service Bulletin (SB) : A300-53-0126 A300

A300-53-0209 A300

A300-53-0216 A300

A300-53-0225 A300

A300-53-0336 A300

7
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

8
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

None

C. LIST OF COMPONENTS

None

D. LIST OF MATERIALS — OPERATOR SUPPLIED

None

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

F. TOOLING — PRICE AND AVAILABILITY

To accomplish this Service Bulletin it is necessary to us

listed in :

NTM PART 1, 51-21-05, 51-31-05, and 51-31-08

NTM PART 4, 53-30-10, Config. 01 and 03

NTM PART 6, 53-30-10, Config. 01, and 02, and 53-38-00

G. SPECIAL TOOLS

None

9
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

10
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(a) Make sure that the aircraft is electrically grou

AMM 24-00-00 Page block 301.

(b) Put access platforms in position in the inspect

(c) Remove the wing-to-fuselage fairings, refer to A

Page block 401).

(2) Standard Practices

None

(3) Work Breakdown

(a) Repaired areas

TABLE 1A

REPAIR

SOLUTION

DESCRIPTION THRESHOLD (FLIGHT

CYCLES) FOR THE

FIRST INSPECTION

AFTER APPLICATION

OF CORRESPONDING

REPAIR SOLUTION

FOL

INS

(FL

1 * SRM solution without cut

out, refer to

SRM 53-10-20

, Figure 701, Sheet 1

Refer to

SRM 53-10-20

, Figure 701,

Sheet 1A

Ref

SRM 

, F

She

4 SRM solution with cut

out, refer to

SRM 53-10-20

 up to revision 49

(before Jan 01/88),

Figure 701, Sheet 3

32,000 

4A SRM solution with cut

out, refer to

SRM 53-10-20

 revision 50 (Jan 01/88)

and subsequent, Figure

701, Sheets 2 and 3

Refer to

SRM 53-10-20

, Figure 701,

Sheets 2A or 3A

Ref

SRM 

, F

She

7 Aircraft MSN 0095 at

STGR52 LH, in Section 16

37,000 

11
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

* Solution 1 is also applicable to the solution 

inner doubler.

NOTE : Sections of the Repair solutions are show

and 13 ; except solution 4A.

NOTE : The repair solution 4 can be determined f

only.

0095 solution at STGR44

LH/RH, in Sections 16 and

17

10 Repair solution in

accordance with repair

drawing R53772132, issue

C or Inspection Service

Bulletin No. A300-53-0336

or A300-53-0341. Post

repair inspections have

to be carried out in

accordance with this

Service Bulletin. Refer

to Figure 13

20,000 

12
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : For extended repair solutions, refer to 

NOTE : It is not necessary to inspect the repai

solutions 2 and 3 until replacement by ex

repairs.

NOTE : The new repair solution has to be extende

additional rivet row at both longitudinal 

to Figure 8 , Sheet 7 thru Sheet 9 .

NOTE : Sections of the repair solutions are show

. The repair solutions 2 and 3 can be det

the inside only.

(b) Modified areas

AFTER

APPLICATION

OF EXTENDED

REPAIR

SOLUTION

2 Old SRM solution with

cut out

16,000 Refer to

SRM 53-10-20

, Figure

701, Sheet

3A

3 Old SRM solution without

cut out (outer skin)

16,000 Refer to

SRM 53-10-20

, Figure

701, Sheet

2A

13
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Sections of the retrofit solutions are sh

9

RETROFIT SOLUTION

1 Retrofit lap joint (SB No.

A300-53-0206 or 53-0209

with cut out)

32,000 

2 Retrofit lower shell (4

panel solution) (SB No.

A300-53-0215) STGR43 LH

(FR26-FR39), STGR43 RH

(FR26-FR38) and STGR49 RH

(FR26-FR38)

32,000 

Retrofit lower shell (4

panel solution) (SB No.

A300-53-0215) STGR46 RH

(FR19-FR26) and STGR47 LH

(FR26-FR39) and STGR51 LH

(FR19-FR26)

32,000 

3 Retrofit lower shell (3

panel solution) (SB No.

A300-53-0216) STGR43 LH

(FR26-FR39) and STGR43 RH

(FR26-FR38)

32,000 

Retrofit lower shell (3

panel solution) (SB No.

A300-53-0216) STGR46 RH

(FR19-FR26), STGR51 LH

(FR19-FR26) STGR54 LH

(FR26-FR39)

32,000 

3A STGR43 LH/RH between FR37

and FR39 in Section 14

32,000 

4 Retrofit lap joint (SB No.

A300-53-0209 without cut

out)

42,000 

5 Retrofit lap joint (SB No.

A300-53-0223)

42,000 

6 Retrofit lap joint (SB No.

A300-53-0306)

34,000 

7 Retrofit lap joint (SB No.

A300-53-0126)

Refer to SRM 53-1

708, sheet

14
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

1 Special areas

Refer to Figure 4 , Sheet 1 and Sheet 2

2 Special and standard areas

a MSN 0003 , 0019-0156

— Refer to Figure 3 , Figure 5 and Figure 

— The areas with an inspection period give

must be modified by accomplishment of Mo

Service Bulletins when the application p

reached.

The areas without an application period 

Figure 3 can be inspected by repetitive 

till the Limit Of Validity (LOV) has bee

modification is necessary for these area

3 Repaired areas

Refer to Table 1, Figure 8 , Sheet 1 to Shee

Figure 13 , Sheet 1 and Sheet 2

4 Modified areas

Refer to Table 2 and Figure 9

(b) Inspection method

1 Special and standard areas

Refer to Figure 1 and Figure 3 thru 6 .

— Perform a manual eddy current test on all l

lap joints (except in Section 17 <9> and th

STGR47 RH, between FR58 and FR65 and Sectio

according to NTM PART 6, 53-30-10, Config. 

, Figure 5 and Figure 6 .

Section 17 <9> and the lap joint at STGR47 

FR58 and FR65 have to be inspected in accor

NTM PART 6, 53-30-10, Config. 2.

15
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Section 13 <4> and Section 17 <9> have to b

accordance with the NTM PART 4, 53-30-10, C

— These areas have to be inspected in accorda

PART 4, 53-30-10, Config. 1 :

Where longitudinal joints and circumferenti

intersect, where rivets manufactured from 

aluminium and rivets without countersunk he

installed.

2 Repaired and modified areas

Refer to Figure 2 and Figure 3 , Sheet 2

In principle there are two areas which have t

depending on the repair/retrofit solution :

— The area where cracks are to be expected i

the concealed position in the lower layer.

An inspection in accordance with the NTM

PART 4, PART 4, 53-30-10, Config. 1 must be 

— The area where cracks are to be expected i

the upper layer.

An inspection in accordance with the NTM PA

must be carried out.

Refer to Figure 13

— The areas 1 and 2 have to be inspected in a

the NTM PART 1, 51-21-05).

— The area 3 has to be inspected in accordanc

PART 1, 51-31-08).

(c) Inspection frequency

Refer to Para. A.(3), Table 1A, 1B and 2.

(2) Damage evaluation

(a) If a crack is detected, inspect with ultrasonic 

the complete frame bay, plus the area on both s

frame bay for a distance of 8 rivet pitches.

16
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(b) Follow-up action

1 Special areas and standard areas with bonded 

— Follow-up action after crack findings at lo

joints with bonded doublers, refer to Flow 

Figure 10 .

2 Standard areas without bonded doublers

— Follow-up action after crack findings at lo

joints without bonded doublers, refer to Fl

Figure 11 .

3 Repaired and modified areas

— Follow-up action after crack findings, refe

Chart 4, Figure 12 .

C. TEST

None

D. CLOSE UP

(1) Make sure that the work areas are clean and clear of 

other items of equipment.

(2) Install the wing-to-fuselage fairings, refer to AMM 

block 401.

(3) Remove the access platforms.

E. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in this Service Bulletin.

17
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Inspection Method for Standard and Special Areas

18
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1

Inspection Method for Repaired/Modified Areas and Areas where 

cannot be used

19
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 1

Inspection Threshold

20
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 2

Inspection Threshold

21
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 3

Inspection Threshold

22
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 4

Inspection Threshold

23
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 5

Inspection Threshold

24
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 6

Inspection Threshold

25
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 1

Inspection of Special Areas in Sections 14, 16 and 1

26
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 2

Inspection of Special Areas in Sections 14, 16 and 1

27
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 1

Inspection of Standard Areas in Sections 13 thru 15

28
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 2

Inspection of Standard Areas in Sections 13 thru 15

29
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 1

Inspection of Standard Areas in Sections 16 thru 18

30
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 2

Inspection of Standard Areas in Sections 16 thru 18

31
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 3

Inspection of Standard Areas in Sections 16 thru 18

32
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 4

Inspection of Standard Areas in Sections 16 thru 18

33
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 7 Sheet 1

Additional Inspection of Upper Rivet Row in Sections 13 t

34
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 1

Repaired Areas

35
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 2

Repaired Areas

36
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 3

Repaired Areas

37
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 4

Repaired Areas

38
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 5

Repaired Areas

39
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 6

Repaired Areas

40
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 7

Repaired Areas

41
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 8

Repaired Areas

42
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 9

Repaired Areas

43
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 1

Inspection of Modified Areas

44
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 2

Inspection of Modified Areas

45
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 3

Inspection of Modified Areas

46
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 4

Inspection of Modified Areas

47
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 5

Inspection of Modified Areas

48
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 6

Inspection of Modified Areas

49
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 10 Sheet 1

Flow Chart 2

50
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 11 Sheet 1

Flow Chart 3

51
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 1

Flow Chart 4

52
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 1

Repaired Areas

53
DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 2

Repaired Areas

54
6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(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 th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

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.
6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300

REVISION No. : 07 — Dec 01/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

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

- Quality rating of this SB 

- Quality rating of the Accomplishment Instructions 

- Quality rating of the Illustrations 

- Is this SB easy to understand ? 

If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

X Effectivity X Kit content X Preparat

X Reason X List of Materials X Mod/Insp

X Manpower Operator Supplied X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustra

Comments :

Operator : Date:

Name/Title :

Please return this form to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.