@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

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 - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT

(ALTERNATE MOD : NONE)

MODIFICATION No.: None

This page transmits Revision No.03 of Service Bulletin No.A300-53-6042

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No.03 issued to revise the inspection threshold and intervals due to the life extension program.

CHANGES

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

Fig. A-GSAAA Minor editorial or document structure change N

Fig. A-GSAAA Sheet 01 Minor editorial or document structure change N

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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REVISION TRANSMITTAL SHEET

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Thresholds and Intervals amended N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

Kit 536042D01R00 Minor editorial or document structure change N

Kit 536042D02R00 Minor editorial or document structure change N

Kit 536042D03R00 Minor editorial or document structure change N

Kit 536042D04R00 Minor editorial or document structure change N

Kit 536042D05R00 Minor editorial or document structure change N

Kit 536042D06R00 Minor editorial or document structure change N

Kit 536042D07R00 Minor editorial or document structure change N

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 2

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REVISION TRANSMITTAL SHEET

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLD01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

Tooling - Price and Availability Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 536042- 832-848-001-Inspection Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 536042-910-201-001 Minor editorial or document structure change N

Subtask 536042-839-201-001 Minor editorial or document structure change N

Subtask 536042-941-201-001 Minor editorial or document structure change N

Subtask 536042-210-201-001 Minor editorial or document structure change N

Subtask 536042-250-201-001 Minor editorial or document structure change N

Subtask 536042-250-202-001 Minor editorial or document structure change N

Subtask 536042-220-201-001 Minor editorial or document structure change N

Subtask 536042-250-204-001 Minor editorial or document structure change N

Subtask 536042-250-203-001 Minor editorial or document structure change N

TASK 536042- 833-848-001-Repair Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 536042-941-202-001 Minor editorial or document structure change N

Subtask 536042-911-202-001 Minor editorial or document structure change N

Subtask 536042-942-202-001 Minor editorial or document structure change N

Fig. A-GBAAA Minor editorial or document structure change N

Fig. A-GBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-GFAAA Minor editorial or document structure change N

Fig. A-GFAAA Sheet 01 Minor editorial or document structure change N

Fig. A-GFBAA Minor editorial or document structure change N

Fig. A-GFBAA Sheet 01 Minor editorial or document structure change N

Fig. A-GFBAA Sheet 02 Minor editorial or document structure change N

Fig. A-GFCAA Minor editorial or document structure change N

Fig. A-GFCAA Sheet 01 Minor editorial or document structure change N

Fig. A-GFDAA Minor editorial or document structure change N

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 3

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REVISION TRANSMITTAL SHEET

Fig. A-GFDAA Sheet 01 Minor editorial or document structure change N

Fig. A-GFDAA Sheet 02 Minor editorial or document structure change N

Fig. A-GFEAA Minor editorial or document structure change N

Fig. A-GFEAA Sheet 01 Minor editorial or document structure change N

Fig. A-GFEAA Sheet 02 Minor editorial or document structure change N

Fig. A-GBBAA Minor editorial or document structure change N

Fig. A-GBBAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBCAA Minor editorial or document structure change N

Fig. A-GBCAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 02 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 03 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 04 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 05 Minor editorial or document structure change N

Fig. A-GBDAA Minor editorial or document structure change N

Fig. A-GBDAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBEAA Minor editorial or document structure change N

Fig. A-GBEAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBFAA Minor editorial or document structure change N

Fig. A-GBFAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBGAA Minor editorial or document structure change N

Fig. A-GBGAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBHAA Minor editorial or document structure change N

Fig. A-GBHAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBJAA Minor editorial or document structure change N

Fig. A-GBJAA Sheet 01 Minor editorial or document structure change N

Fig. A-GBJAA Sheet 02 Minor editorial or document structure change N

Fig. A-GBJAA Sheet 03 Minor editorial or document structure change N

Fig. A-GBJAA Sheet 04 Minor editorial or document structure change N

FILLING 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

Revision 01 was issued:

to change the NTM procedure, for inspection Area 2, from X-ray to Eddy current

to change the special Rotating probe procedure, for inspection Area 3, to a general Rotating probe

procedure.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 4

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

to change the hole diameters, for fasteners which have to be installed after cold expansion, in Area 3.

to make reference to the Service Information Letter 5SIL) 53-042 for the removal of possible corrosion

in the inspection area after the removal of the anti-chafing plates.

Revision 02 was issued to simplify the inspection procedure and to add the corner fitting replacement

procedure.

REVISION SEQUENCE

ORIGINAL: May 06/94

REVISION No. : 01 - Feb 20/95

REVISION No. : 02 - Apr 28/98

REVISION No. : 03 - Aug 30/12

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 5

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REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 6

6

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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 - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT

(ALTERNATE MOD : NONE)

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During a full scale fatigue test, after 87675 simulated flights, a crack was found at the lower corner of

the assembly of the horizontal-stabilizer cutout, between FR87 and FR89 and between STGR24 and

STGR27, LH and RH.

This Service Bulletin has been issued:

- to inspect visually, without removal of sealant, the lower horizontal-stabilizer cutout longeron, the

corner fitting, the skin strap and the skin between FR87 and FR89 and between STGR24 and

STGR27, LH and RH, for cracks and corrosion.

- to inspect with eddy current the flanges of the lower corner fittings and the edges of the outer skin

which is designated Area 1.

- to inspect with eddy current the edges of the longeron, the skin strap and the skin at the runout of

the corner fitting above the last eight fasteners which is designated Area 2.

- to inspect Area 3 by removing the specified fasteners from the assembly of the lower corner

fittings, longerons, skin straps and skin, and do a rotating probe inspection of the fastener holes.

When the fastener holes prove to be crack free, a cold expansion procedure is to be done as

detailed in this Service Bulletin.

NOTE: If cracks are detected in any of the affected areas, follow the repair solution as detailed

in this Service Bulletin.

The accomplishment of this Service Bulletin will prevent undetected cracks that could lead to extensive

repairs and could reduce the flight loading residual strength capacity of the structure.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 1

6

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SERVICE BULLETIN

SUMMARY

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

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 536042D01R00 2 5,700.00 Pin, collar, washer

Kit 536042D02R00 2 1,360.00 Pin, collar, washer

Kit 536042D03R00 2 8,300.00 Pin, collar, washer

Kit 536042D04R00 1 3,870.00 Fitting

Kit 536042D05R00 1 3,870.00 Fitting

Kit 536042D06R00 2 4,280.00 Pin, collar, washer

Kit 536042D07R00 2 7,940.00 Pin, collar, washer

TOTAL 35,320.00

EFFECTIVITY

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

83V F2I FDX IRM KAC

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

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

Task 536042-832-848-001: Inspection

TOTAL MANHOURS 88.00

ELAPSED TIME (HOURS) 44.00

Task 536042-833-848-001: Repair

TOTAL MANHOURS 243.00

ELAPSED TIME (HOURS) 121.5

APPENDICES

None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

SUMMARY

**CONF ALL

INSPECTION AREA2

INSPECTION AREA1

SKIN STRAP

INSPECTION AREA1

INSPECTION AREA2

INSPECTION AREA3

LONGERON

CORNER FITTING

LOWER

OUTER SKIN

FR86

FR91

FR87

STGR24LH FR89

STGR27LH

STGR24RH

STGR27RH

A

C

C

A

NOTE:

Z310

B

RH SHOWN

LH SYMMETRICAL

B

RH SHOWN

LH SYMMETRICAL

FWD INSPECTION AREA3

D_SB_536042_6_SAAA_01_00

Figure A-GSAAA - Sheet 01

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 4

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
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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 - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT

(ALTERNATE MOD : NONE)

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

B4-603 B4-605R B4-620 B4-622 C4-620

(2) Effectivity by MSN

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0380

0388 0401 0405 0408 0411 0414 0417 0423

(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

83V 0423

F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351

FDX 0358 0361 0365 0388 0417

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

OPERATOR MSN

IRM 0380 0401 0405 0408 0411 0414

KAC 0344

(4) Configuration by MSN

MSN CONFIGURATION

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351

0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417

0423

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft which do not have Modification No. 06146D5198

(FUSELAGE - TAIL CONE - REINFORCE LOWER TAIL PLACE CUTOUT) embodied.

Modification No. 06146D5198 has been embodied, prior to delivery, on aircraft MSN 459

and subsequent.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 536042D01R00 2

Kit 536042D02R00 2

Kit 536042D03R00 2

Kit 536042D04R00 1

Kit 536042D05R00 1

Kit 536042D06R00 2

Kit 536042D07R00 2

Consumable CMLD01 1

NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area

3 (rotating probe inspection and cold expansion of specified fastener

holes).

Kit D01 is to do the work on one side only.

Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A01 equals 2 Kits D01.

NOTE: Kit D02 is only applicable if cutouts are to be made in the FWD and

lower anti-chafing plates instead of the complete removal of the antichafing plates. The cutout procedure reduces the manpower for the "Get

Access" and "Close-Up" procedures.

Kit D02 is to do the work on one side only.

Kit A02 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A02 equals 2 Kits D02.

NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area

3 (rotating probe inspection and cold expansion of specified fastener

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 2

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SERVICE BULLETIN

holes), if the next oversize is required.

This kit should only be ordered if cracks are found during the rotating

probe inspection.

Kit D03 is to do the work on one side only.

Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A03 equals 2 Kits D03.

NOTE: Kit D04 is only applicable if the LH lower corner fitting has to be

replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm

(1.969 in.) between the cracks, are found in the fitting.

Kit A04 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A04 equals 1 Kit D04.

NOTE: Kit D05 is only applicable if the RH lower corner fitting has to be

replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm

(1.969 in.) between the cracks, are found in the fitting.

Kit A05 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A05 equals 1 Kit D05.

NOTE: Kit D06 is only applicable if the LH or RH corner fitting has to be

replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm

(1.969 in.) between the cracks, are found in the fitting.

The quantity of fasteners in this kit is sufficient only for the replacement

of one corner fitting.

The kit does not include the special bull-nose fasteners which are

installed in the cold-expanded holes. These fasteners are to be found in

Kit D01.

Kit D06 is to do the work on one side only.

Kit A06 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A06 equals 1 Kit D06.

NOTE: Kit D07 is only applicable if the lower corner fitting has been removed

and a crack found in Area 1 after the fastener holes in Area 3 have been

cold expanded.

The quantity of fasteners in this kit is sufficient one side only.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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This kit should only be ordered if a crack, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0

mm (1.969 in.) between the cracks, are found in Area 1 after the cold

expansion of Area 3.

Kit D07 is to do the work on one side only.

Kit A07 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A07 equals 1 Kit D07.

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During a full scale fatigue test, after 87675 simulated flights, a crack was found at the

lower corner of the assembly of the horizontal-stabilizer cutout, between FR87 and FR89

and between STGR24 and STGR27, LH and RH.

(2) Objective/Action

This Service Bulletin has been issued:

- to inspect visually, without removal of sealant, the lower horizontal-stabilizer cutout

longeron, the corner fitting, the skin strap and the skin between FR87 and FR89 and

between STGR24 and STGR27, LH and RH, for cracks and corrosion.

- to inspect with eddy current the flanges of the lower corner fittings and the edges of

the outer skin which is designated Area 1.

- to inspect with eddy current the edges of the longeron, the skin strap and the skin at

the runout of the corner fitting above the last eight fasteners which is designated

Area 2.

- to inspect Area 3 by removing the specified fasteners from the assembly of the

lower corner fittings, longerons, skin straps and skin, and do a rotating probe

inspection of the fastener holes. When the fastener holes prove to be crack free, a

cold expansion procedure is to be done as detailed in this Service Bulletin.

NOTE: If cracks are detected in any of the affected areas, follow the repair

solution as detailed in this Service Bulletin.

(3) Advantages

The accomplishment of this Service Bulletin will prevent undetected cracks that could

lead to extensive repairs and could reduce the flight loading residual strength capacity of

the structure.

(4) Operational/Maintenance Consequences

None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 4

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D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 536042-832-848-001: Inspection

(1) Visual inspection in Areas 1, 2 and 3, LH and RH

(2) Eddy current inspection in Area 1, LH and RH

(3) Eddy current inspection in Area 2, LH and RH

(4) Rotating probe inspection of specified fastener holes in Area 3, LH and RH, and cold

expansion of specified fastener holes

(5) Eddy current inspection in area 3

(6) Eddy current inspection of the longeron and outer skin

Task 536042-833-848-001: Repair

(1) Replacement of the lower corner fitting

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Table 1 (Aircraft with Average Flight Time above 1.5 hours)

Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks

1 18000/38100 6000/12700 -

2 18000/38100 6000/12700 -

3 24000/50800 - To be combined with

cold expansion, not

before

18000FC/38100FH *

NOTE: * If for any reason, the cold expansion in Area 3 is to be accomplished

before the specified minimum number of flights or hours, contact Airbus

for instructions.

After reaching the subsequent thresholds, the intervals changes as given in Table 2

Table 2 (Aircraft with Average Flight Time above 1.5 hours)

Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks

1 30000/63500 3900/8200 -

2 30000/63500 3900/8200 -

3 42500/89000 3900/8200 -

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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NOTE: For the requirements given in Table 2 a grace period of 1950FC/4100FH

is allowed.

Table 1 (Aircraft with an Average Flight Time up to or equal to 1.5 hours)

Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks

1 19900/29800 6600/9900 -

2 19900/29800 6600/9900 -

3 26600/39800 - To be combined with

cold expansion, not

before

19900FC/29800FH *

NOTE: * If for any reason, the cold expansion in Area 3 is to be accomplished

before the specified minimum number of flights or hours, contact Airbus

for instructions.

After reaching the subsequent thresholds, the intervals changes as given in Table 2

Table 2 (Aircraft with an Average Flight Time up to or equal to 1.5 hours)

Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks

1 33300/49800 4300/6400 -

2 33300/49800 4300/6400 -

3 47100/70500 4300/6400 -

NOTE: For the requirements given in Table 2 a grace period of 2150FC/3200FH

is allowed.

NOTE: These mandatory inspections are required on all aircraft listed in this

Service Bulletin not later than the corresponding total flight cycles or

total flight hours, whichever comes first, applying to the configuration as

detailed in Table 1 and Table 2.

Repeat inspections are required at intervals not exceeding the related

interval applying to the configuration as detailed in Table 1 and Table 2.

NOTE: For area identification, refer to Fig. A-GBAAA of this Service Bulletin.

NOTE: Aircraft which are approaching or have exceeded the threshold detailed

in Table 1 should be inspected in accordance with the subsequent limits:

- If aircraft are between 1500FC/2000FH less than the threshold or

have exceeded the threshold by less than 1500FC/2000FH the first

inspection is to be done within 1500FC/2000FH after receipt of this

Service Bulletin.

- For aircraft which have exceeded the threshold by more than

1500FC/2000FH the first inspection is to be done within

750FC/1000FH after receipt of this Service Bulletin.

NOTE: The number of "Touch and Go flights" can be ignored when they are less

than five percent of the total number of flights between two consecutive

inspections. Each "Touch and Go flight" beyond five percent has to be

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

counted as a flight cycle.

A "Touch and Go flight" is a landing in which an aircraft touches the

runway and does not come to a complete stop prior to commencing an

additional flight.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

F. APPROVAL

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

Organization Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 536042-832-848-001: Inspection

Get Access 58.00

On Aircraft

Visual inspection in Areas 1, 2 and 3, LH and RH 2.00

Eddy current inspection in Area 1, LH and RH 8.00

Eddy current inspection in Area 2, LH and RH 2.00

Rotating probe inspection of specified fastener holes in

Area 3, LH and RH, and cold expansion of specified

fastener holes

10.00

Eddy current inspection in area 3 2.00

Eddy current inspection of the longeron and outer skin 6.00

TOTAL MANHOURS 88.00

ELAPSED TIME (HOURS) 44.00

NOTE: Add the drying and vacuum process time for the anti-chafing plates to the

elapsed time (Refer to SRM 53-19-12 for the recommended times).

Task 536042-833-848-001: Repair

Get Access 60.00

On Aircraft

Replacement of the lower corner fitting 60.00

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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Task 536042-833-848-001: Repair

Close-Up 123.0

TOTAL MANHOURS 243.00

ELAPSED TIME (HOURS) 121.5

NOTE: Add the drying and vacuum process time for the anti-chafing plates to the

elapsed time (Refer to SRM 53-19-12 for the recommended times).

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-31-53 24-00-00 52-41-00

55-12-11 55-15-11

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-01 53-19-26

Standards Manual (SM)

Structural Repair Manual (SRM) 51-29-00 51-40-21 51-40-30

51-40-41 51-40-44 51-40-47

51-74-10 51-75-10 51-76-10

53-10-00 53-19-12

American Federal Specification: RR-S-366E

FTI Tool List: FTI-A300-53-6042-1

Military Specification: MIL-G-9954A, MIL-S-13165B

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 536042D01R00

Kit 536042D02R00

Kit 536042D03R00

Kit 536042D04R00

Kit 536042D05R00

Kit 536042D06R00

Kit 536042D07R00

Customers with aircraft shown in the

effectivity of this Service Bulletin should send

a purchase order to AIRBUS. Quote the

number of this Service Bulletin. The address

is:

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering modification kits by fax: +49 40

50 76 25 90

For ordering of single spares by fax: +49 40

50 76 40 13

(2) Price and Availability

Kit 536042D01R00

Cost 2,850.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 536042D02R00

Cost 680.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 536042D03R00

Cost 4,150.00 USD

Availability 90 calendar days from receipt of order

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The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 536042D04R00

Cost 3,870.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 536042D05R00

Cost 3,870.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 536042D06R00

Cost 2,140.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 536042D07R00

Cost 3,970.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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B. INDUSTRY SUPPORT INFORMATION

Refer to the paragraph: ’Price and Availability’.

C. LIST OF COMPONENTS

Kit 536042D01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 HLT637AP6-14 4 PIN

2 HLT637AP8-13 12 PIN

3 HLT286-6 4 COLLAR

4 HLT286-8 12 COLLAR

5 NAS1149D1165K 4 WASHER (1)

6 NSA5368PD416B 12 WASHER (1)

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area 3

(rotating probe inspection and cold expansion of specified fastener holes).

Kit D01 is to do the work on one side only.

Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for this

revision. The content of 1 Kit A01 equals 2 Kits D01.

NOTE (1): Install only if necessary.

Kit 536042D02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

21 DAN6-5-4 9 PIN

22 DAN8-6-6X 3 PIN

23 DAN8-6-11X 1 PIN

24 DAN8-6-12X 1 PIN

25 DAN8-8-9X 1 PIN

26 DAN8-8-11X 1 PIN

27 DAN8-8-12X 1 PIN

28 DAN8-8-13X 3 PIN (1)

29 DAN12-6X 5 COLLAR

30 DAN12-8X 6 COLLAR

32 HL70-5 9 COLLAR

33 A5398402120000 9 WASHER

34 A5398402120200 5 WASHER

35 A5398402120400 6 WASHER

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NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

NOTE: Kit D02 is only applicable if cutouts are to be made in the FWD and lower

anti-chafing plates instead of the complete removal of the anti-chafing plates.

The cutout procedure reduces the manpower for the "Get Access" and

"Close-Up" procedures.

Kit D02 is to do the work on one side only.

Kit A02 from revision 02 or earlier of this Service Bulletin is still valid for this

revision. The content of 1 Kit A02 equals 2 Kits D02.

NOTE (1): Alternative to Item 27 if a longer fastener is required.

Kit 536042D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

11 HLT337AP8-14 4 PIN

12 HLT337AP10-13 12 PIN

13 HLT86-8 4 COLLAR

14 HLT86-10 12 COLLAR

15 NAS1149D0463K 4 WASHER (1)

16 NAS1149D0563K 12 WASHER (1)

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area 3

(rotating probe inspection and cold expansion of specified fastener holes), if

the next oversize is required.

This kit should only be ordered if cracks are found during the rotating probe

inspection.

Kit D03 is to do the work on one side only.

Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for this

revision. The content of 1 Kit A03 equals 2 Kits D03.

NOTE (1): Install only if necessary.

Kit 536042D04R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

40 A5398613520290 1 FITTING

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NOTE: Kit D04 is only applicable if the LH corner fitting has to be replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or

more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969

in.) between the cracks, are found in the fitting.

Kit A04 from revision 02 or earlier of this Service Bulletin is still valid for this

revision. The content of 1 Kit A04 equals 1 Kit D04.

Kit 536042D05R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

50 A5398613520390 1 FITTING

NOTE: Kit D05 is only applicable if the RH corner fitting has to be replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or

more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969

in.) between the cracks, are found in the fitting.

Kit A05 from revision 02 or earlier of this Service Bulletin is still valid for this

revision. The content of 1 Kit A05 equals 1 Kit D05.

Kit 536042D06R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

22 DAN8-6-6X 27 PIN

23 DAN8-6-11X 7 PIN

27 DAN8-8-12X 12 PIN

28 DAN8-8-13X 12 PIN (1)

29 DAN12-6X 97 COLLAR

30 DAN12-8X 28 COLLAR

61 DAN7-6-5 10 PIN

62 DAN7-6-6X 16 PIN

63 DAN7-6-7X 11 PIN

64 DAN7-6-8X 7 PIN

66 DAN8-6-8X 17 PIN

67 DAN8-6-9X 22 PIN

69 DAN8-8-8X 16 PIN

72 DAN12-6 10 COLLAR

75 DAN14-6 10 COLLAR

76 LN9198-4012CF 20 RIVET

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

NOTE: Kit D06 is only applicable if the LH or RH corner fitting has to be replaced.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or

more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969

in.) between the cracks, are found in the fitting.

The quantity of fasteners in this kit is sufficient only for the replacement of one

corner fitting.

The kit does not include the special bull-nose fasteners which are installed in

the cold-expanded holes. These fasteners are to be found in Kit D01.

Kit D06 is to do the work on one side only.

Kit A06 from revision 02 or earlier of this Service Bulletin is still valid for this

revision. The content of 1 Kit A06 equals 1 Kit D06.

NOTE (1): Alternative to Item 27 if a longer fastener is required.

Kit 536042D07R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

100 HLT637AP6-12 2 PIN

101 HLT337AP8-12 2 PIN (1)

102 HLT337AP8-14 4 PIN

103 HLT337AP10-13 22 PIN

104 HLT86-8 6 COLLAR

105 HLT86-10 22 COLLAR

106 HLT286-6 2 COLLAR

107 NAS1149D1165K 2 WASHER (2)

108 NAS1149D0463K 6 WASHER (2)

109 NAS1149D0563K 22 WASHER (2)

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

NOTE: Kit D07 is only applicable if the lower corner fitting has been removed and a

crack found in Area 1 after the fastener holes in Area 3 have been cold

expanded.

The quantity of fasteners in this kit is sufficient one side only.

This kit should only be ordered if a crack, longer than 2.0 mm (0.079 in.) or

more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969

in.) between the cracks, are found in Area 1 after the cold expansion of Area

3.

Kit D07 is to do the work on one side only.

Kit A07 from revision 02 or earlier of this Service Bulletin is still valid for this

revision. The content of 1 Kit A07 equals 1 Kit D07.

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NOTE (1): Alternative to Item 100 if the next oversize is required.

NOTE (2): Install only if necessary.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Rust Inhibitor (for Corrosion Use

15-004)

05-027 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibitingfillet Consistency 09-016 As required

Corrosion Inhibitingsealant

Sprayable

09-025 As required

Polysulphide Sealant For Interfay 09-048 As required

Methyl Alcohol 11-006 As required

Solvent General Purpose 11-026 As required

Corrosion Preventive compound 15-004 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoatgrey (for

Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

Flexible Polyurethane 16-021 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

(a) Procurement Addresses

For the details of the tooling required for the cold expansion procedure of this

Service Bulletin, refer to FTI Tool List No. FTI-A300-53-6042-1.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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- The tooling details in the FTI Tool List is supplied by:

FATIGUE TECHNOLOGY INC. (FTI)

150 ANDOVER PARK WEST

P.O. BOX 88388

SEATTLE, WASHINGTON 98188

USA

TELEPHONE : (206) 246-2010

TELEX : 321004

TELEFAX : (206) 244-9886

- The tool and the material required to carry out the shot peening process are:

1 shot propellant machine - VACU-Blast PHA 06-2 and Glass Beads Size 70.

0.1778 mm (0.007 in.) dia.

- The shot propellant machine and the Glass Beads are supplied by :

MUNK AND SCHMITZ

Oberflaechentechnik

Poller Kirchweg 92-104

51105 Koln

Germany

Telefon : (49) 0221 83908-33

Telefax : (49) 0221 83908-39

- The circular saw, DESOUTER RC 90, which is necessary to do the cutout

procedure at the anti-chafing plates is supplied by :

Desouter GmbH

Druckluftwerkzeuge

Edisonstrasse 1

63477 Maintal

Germany

Telefon : (49) 06181 4110

Telefax : (49) 06181 411187

NOTE: Any similar circular saw, which is available by local procurement,

can be used.

(b) Price and Availability

None

(2) Tools

None

(3) Special Tools

None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 536042-832-848-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR

MECHANICAL FLIGHT CONTROL SURFACES OR ANY MOVING

COMPONENTS, MAKE SURE THAT GROUND SAFETY LOCKS AND/OR

WARNING NOTICES ARE IN THE CORRECT POSITION TO PREVENT

ACCIDENTAL OPERATION.

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.

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

Task Associated Data

Zone

310

Manpower

TOTAL MANHOURS 88.00

ELAPSED TIME (HOURS) 44.00

A. GENERAL

(1) Subtask 536042-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-21

51-40-30

51-40-44

51-75-10

Fig. A-GFAAA

Flow Chart -A- (Visual Inspection - All

Areas)

Sheet 01

Fig. A-GFBAA

Flow Chart -B- (Eddy Current Inspection

- Area 1)

Sheet 01

Sheet 02

Fig. A-GFCAA

Flow Chart -C- (Eddy Current Inspection

- Area 2)

Sheet 01

Fig. A-GFDAA

Flow Chart -D- (Rotating Probe

Inspection and Cold Expansion - Area 3)

Sheet 01

Sheet 02

Fig. A-GFEAA

Flow Chart -E- (Eddy Current Inspection

and Secondary Cold Expansion)

Sheet 01

Sheet 02

(a) The following standard procedures apply only if a removal of the anti-chafing plates

and/or a removal of rivets and/or a repair is required.

1 For the specification of materials (Mat. No.) given in this Service Bulletin

(Refer to Consumable Material List (CML)).

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

3 If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the

installation standards given in SRM Chapter 51 may be used. In addition,

washers may be installed for fastener grip length in accordance with SRM

Chapter 51.

4 For the removal and installation of the fasteners (Refer to SRM 51-40-21).

5 For alternative and substitute fasteners (Refer to SRM 51-40-30).

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6 For the repair of the paint coatings (Refer to SRM 51-75-10).

7 For the drill and deburr data (Refer to SRM 51-40-44).

8 Before you do the rotating probe inspection, clean all holes with:

Solvent General

Purpose

11-026 As required

9 Wet install fasteners with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

(b) Work Breakdown

1 For the various inspection/repair phases described in this Inspection Service

Bulletin (ISB), refer to the Flow Charts Fig. A-GFAAA, Fig. A-GFBAA, Fig. AGFCAA, Fig. A-GFDAA and Fig. A-GFEAA.

(2) Subtask 536042-839-201-001 - 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 536042-941-201-001 - Preparation

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

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

52-41-00, Page Block 001

55-12-11, Page Block 401

55-15-11, Page Block 401

Structural Repair Manual (SRM) 53-19-12

Fig. A-GBBAA

Preparation of Circular Saw

Sheet 01

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References

Fig. A-GBCAA

Make Cutouts in the FWD and Lower

Anti-Chafing Plates

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

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

Block 301).

(b) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU FAC1/28VDC 306CC1 103/G3

21VU FAC1/115VAC 309CC1 103/G5

21VU FAC1/26VAC 305CC1 103/G7

21VU FAC2/26VAC 305CC2 103/G8

21VU FAC2/115VAC 309CC2 103/G10

21VU FAC2/28VDC 306CC2 103/G12

(c) Put an access platform in position at the access door 312AR and at the horizontal

stabilizer.

(d) Open the access door 312AR (Refer to AMM 52-41-00, Page Block 001).

(e) If the inspection in Area 3 is to be done using Solution 1 (Removal of the FWD and

lower anti-chafing plates completely for access to the inspection area):

1 Remove and retain the Trimmable Horizontal Stabilizer (THS) aprons (LH and

RH) adjacent to the inspection area (Refer to AMM 55-15-11, Page Block

401).

2 Remove and retain the THS leading edges (LH and RH) adjacent to the

inspection area (Refer to AMM 55-12-11, Page Block 401).

3

CAUTION: TO PREVENT DAMAGE DURING THE REMOVAL OF THE

ANTI-CHAFING PLATES, A HOT-AIR BLOWER MUST BE

USED TO SOFTEN THE SEALANT.

Remove the FWD and lower anti-chafing plates (LH and RH) (Refer to SRM

53-19-12).

(f) If the inspection in Area 3 is to be done using Solution 2 (Make cutouts in the FWD

and lower anti-chafing plates for access to the inspection area):

Refer to Fig. A-GBCAA

NOTE: The following worksteps are applicable for both sides of the aircraft

(LH and RH).

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

1 Remove and retain the trimmable horizontal stabilizer aprons (LH and RH)

adjacent to the inspection area (Refer to AMM 55-15-11, Page Block 401).

2 On the FWD and lower anti-chafing plates, draw the cut lines using the

dimensions shown in Detail C. Use a soft lead pencil.

3 From the area of the FWD and lower cutouts, remove and discard the existing

fasteners.

4 Prepare the circular saw to cut to the correct depth:

Refer to Fig. A-GBBAA

a Remove the cutting disc from the circular saw.

b Grind the edge of the cutting disk to an angle of 15 degrees.

c Install the cutting disc in the circular saw.

d Adjust the depth of cut so that it does not exceed 0.55 mm (0.0217 in.).

e To make sure that the depth of cut is correct, make a sample cut in a

strip of metal which is 0.6 mm (0.0236 in.) thick.

5

CAUTION: MAKE SURE THAT THE DEPTH OF CUT IS DEEPER ON

THE ANTI-CHAFING PLATE SIDE OF THE CUT THAN

THE CUTOUT SIDE. THIS WILL ENSURE THAT A CLEAN

BREAK WILL BE MADE AT THE ANTI-CHAFING PLATE.

THE EXCESS MATERIAL ATTACHED TO THE CUTOUT

WILL BE REMOVED BEFORE RE-INSTALLATION.

CAUTION: TO GUIDE THE CIRCULAR SAW, IT IS RECOMMENDED

TO CLAMP STRAIGHT EDGES PARALLEL TO THE CUT

LINES.

Cut the FWD and lower anti-chafing plates as shown in Detail B, Sections A-A

and B-B.

6

CAUTION: MAKE SURE THAT THE CUTOUTS ARE NOT DAMAGED

DURING REMOVAL. THEY WILL BE RE-INSTALLED AFTER

THE INSPECTION.

Remove and retain the cutouts:

a Heat the edge of the cutout with a hot-air blower.

b Carefully insert non-metallic wedges under the edge of the cutout.

Continue heating the area directly in front of the wedges until the cutout

is completely removed.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

7 Remove any old sealant from the fuselage skin with a non-metallic scraper.

8 Clean the fuselage skin with

Solvent General

Purpose

11-026 As required

C. PROCEDURE

NOTE: For the accomplishment of the cold working procedures, as necessary for

this inspection, use the tools as listed in the Tool List Kit Number FTIA300-53-6042-1.

NOTE: Inspection results must be reported to Airbus.

If cracks are found, report in accordance with the related Service Bulletin

instructions:

- immediately (maximum 48 hours) if the damage exceeds allowable or

rework limits. For more instructions contact Airbus before the next flight.

- after completion of the corrective action when damage is within allowable

or rework limits, or repaired in accordance with the related Service

Bulletin instructions.

If no cracks are found, the inspection record has to be sent as soon as the

maintenance check or visit report, which involves the related Service Bulletin,

has been completed.

NOTE: All inspections are to be done in accordance with the thresholds given in

Para. 1.E.(2) Compliance, Table 1 or Table 2.

NOTE: The visual inspections have to be done every time a NDT inspection in Area

1, 2 or 3 has to be done. Only if the NDT inspection in Area 3 has to be

done, the anti-chafing plates in the inspection area must be removed and the

outer skin in this area visually inspected.

NOTE: If corrosion is found on the outer skin in the inspection area, remove the

corrosion (Refer to SRM 51-74-10 and SRM 53-10-00).

NOTE: If an anti-chafing plate has not been removed and the corrosion extends

under it, remove the anti-chafing plate and remove the corrosion (Refer to

SRM 51-74-10 and SRM 53-10-00).

(1) Subtask 536042-210-201-001 - Visual inspection in Areas 1, 2 and 3, LH and RH

Work Zones and Access Panels

Zone Access/Work location

310

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 22

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@A300-600

SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Rust Inhibitor (for Corrosion

Use 15-004)

05-027 As required

Corrosion Inhibitingfillet

Consistency

09-016 As required

Corrosion Inhibitingsealant

Sprayable

09-025 As required

Solvent General Purpose 11-026 As required

Flexible Polyurethane 16-021 As required

References

Structural Repair Manual (SRM) 51-74-10

51-76-10

53-10-00

Fig. A-GBAAA

Areas to be Inspected

Sheet 01

Fig. A-GFAAA

Flow Chart -A- (Visual Inspection - All

Areas)

Sheet 01

NOTE: Only if the rotating probe inspection in Area 3 has to be done, the antichafing plates must be removed and the outer skin in this area can be

visually inspected.

(a) Clean the inspection area with:

Solvent General

Purpose

11-026 As required

(b) Visually inspect for cracks and corrosion, without the removal of the sealant, the

lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap and the

skin between Frame 87 and Frame 89 and between STGR24 and STGR27, LH and

RH.

NOTE: This visual inspection has to be done every time a Non Destructive

Testing (NDT) inspection in Area 1, 2 or 3 has to be done.

Only if the inspection in Area 3 has to be done, then the FWD and

lower anti-chafing plates have to be removed (or cutouts made in

the FWD and lower anti-chafing plates) and the visual inspection of

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

the outer skin in this area is required.

1 If corrosion is found on the outer skin in the inspection area it is recommended

to remove the corrosion (Refer to SRM 51-74-10 and SRM 53-10-00).

2 If an anti-chafing plate is not removed and the corrosion extends under it,

remove the anti-chafing plate and remove the corrosion (Refer to SRM

51-74-10 and SRM 53-10-00).

3 If cracks are detected, contact Airbus for instructions before the next flight.

(c) Visually inspect for damaged sealant between Frame 87 and Frame 89 and

between STGR24 and STGR27, LH and RH.

1 If the sealant is damaged, carefully remove the damaged sealant

approximately 100.0 mm (3.9 in.) from both sides of the damage. Use a nonmetallic scraper (Refer to SRM 51-76-10).

2 Clean the area, where the sealant has been removed, with

Solvent General

Purpose

11-026 As required

3 Apply

Corrosion

Inhibitingfillet

Consistency

09-016 As required

or

Corrosion

Inhibitingsealant

Sprayable

09-025 As required

to the areas where the sealant has been removed and apply

Flexible

Polyurethane

16-021 As required

to the sealing beads (Refer to SRM 51-76-10).

4 Apply

Rust Inhibitor (for

Corrosion Use

15-004)

05-027 As required

to the inspection area.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 24

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SERVICE BULLETIN

(2) Subtask 536042-250-201-001 - Eddy current inspection in Area 1, LH and RH

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibitingfillet

Consistency

09-016 As required

Corrosion Inhibitingsealant

Sprayable

09-025 As required

Solvent General Purpose 11-026 As required

Corrosion Preventive

compound

15-004

Flexible Polyurethane 16-021 As required

References

Non Destructive Test Manual (NTM) 53-19-26, Page Block 601

Structural Repair Manual (SRM) 51-76-10

Fig. A-GFBAA

Flow Chart -B- (Eddy Current Inspection

- Area 1)

Sheet 01

Sheet 02

Fig. A-GBAAA

Areas to be Inspected

Sheet 01

Fig. A-GBFAA

Example of Crack Removal in Inspection

Area 1

Sheet 01

(a) Do an eddy current inspection of inspection Area 1 (Refer to NTM 53-19-26, Page

Block 601).

(b) Compare the results of the inspection with the Flow Chart

Refer to Fig. A-GBAAA

Refer to Fig. A-GFBAA

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 25

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@A300-600

SERVICE BULLETIN

1 If no crack(s) is (are) found:

a Clean the inspection area with

Solvent General

Purpose

11-026 As required

b Apply

Corrosion

Inhibitingfillet

Consistency

09-016 As required

or

Corrosion

Inhibitingsealant

Sprayable

09-025 As required

to the areas where the sealant has been removed and apply

Flexible

Polyurethane

16-021 As required

to the sealing beads (Refer to SRM 51-76-10).

c Apply

Corrosion

Preventive

compound

15-004 As required

to the inspection area where the corrosion preventive compound has

been removed.

d Repeat the inspection at the interval specified in Para. 1.E.(2)

Compliance, Table 1 or Table 2.

2 If crack(s) is (are) found:

a Cracks are less than or equal to 2.0 mm (0.079 in.) long and not more

than 2 cracks with a minimum distance of 50.0 mm (1.969 in.) between

the cracks:

<1> Remove the crack damage by milling a radius of between 10.0 mm

(0.394 in.) minimum and 20.0 mm (0.787 in.) maximum, refer to Fig.

A-GBFAA.

<2> Clean the reworked area.

<3> Do an eddy current inspection of the reworked area (Refer to NTM

53-19-26, Page Block 601).

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

<4> Compare the results of the inspection with the Flow Chart, refer to

Fig. A-GFBAA.

<a> If no crack(s) is (are) found:

[1] Shot peen the reworked area, refer to Fig. A-GBFAA, as

detailed in TASK 536042-833-848 001 Repair .

[2] Repeat the inspection at the intervals detailed in Para.

1.E.(2) Compliance, Table 1 or Table 2.

<b> If crack(s) is (are) found:

[1] If the radius of the rework is less than the 20.0 mm (0.787

in.) minimum, increase the radius to 20.0 mm (0.787 in.),

refer to Fig. A-GBFAA.

[2] Clean the reworked area with:

Solvent General

Purpose

11-026 As required

[3] Do an eddy current inspection of the reworked area (Refer

to NTM 53-19-26, Page Block 601).

[4] Compare the results of the inspection with the Flow Chart,

refer to Fig. A-GFBAA.

[a] If no crack(s) is (are) found:

- Shot peen the reworked area, refer to Fig. AGBFAA, as detailed in TASK 536042-833-848

001 Repair .

- Repeat the inspection at the intervals detailed in

Para. 1.E.(2) Compliance, Table 1 or Table 2.

[b] If crack(s) is (are) found in the outer skin:

- Contact Airbus for further instructions.

[c] If crack(s) is (are) found in the corner fitting:

- Remove the corner fitting as described in TASK

536042-833-848 001 Repair .

[d] If Area 3 has not been cold expanded:

- Install the new corner fitting as detailed in TASK

536042-833-848 001 Repair . Do not install the

fasteners in Area 3.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 27

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SERVICE BULLETIN

- Do a rotating probe inspection in Area 3

as detailed in SUBTASK 536042-220-201 001

Rotating probe inspection of specified fastener

holes in Area 3, LH and RH, and cold expansion

of specified fastener holes .

[e] If Area 3 has been cold expanded:

- Do an eddy current inspection of the longeron

and outer skin as detailed in SUBTASK

536042-250-203 001 Eddy current inspection of

the longeron and outer skin .

[5] Cracks are longer than 2.0 mm (0.08 in.) or more than 2

cracks or 2 cracks with a distance of less than 50.0 mm

(1.97 in.) between the cracks.

[a] Remove the corner fitting as described in TASK

536042-833-848 001 Repair .

[b] If Area 3 has not been cold expanded:

- Install the new corner fitting as detailed in TASK

536042-833-848 001 Repair . Do not install the

fasteners in Area 3.

- Do a rotating probe inspection in Area 3

as detailed in SUBTASK 536042-220-201 001

Rotating probe inspection of specified fastener

holes in Area 3, LH and RH, and cold expansion

of specified fastener holes .

[c] If Area 3 has been cold expanded:

- Do an eddy current inspection of the longeron

and outer skin as detailed in SUBTASK

536042-250-203 001 Eddy current inspection of

the longeron and outer skin .

(3) Subtask 536042-250-202-001 - Eddy current inspection in Area 2, LH and RH

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 28

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SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 53-19-26, Page Block 601

Fig. A-GBAAA

Areas to be Inspected

Sheet 01

Fig. A-GFCAA

Flow Chart -C- (Eddy Current Inspection

- Area 2)

Sheet 01

Refer to Fig. A-GBAAA

Refer to Fig. A-GFCAA

(a) Do an eddy current inspection of inspection Area 2 (Refer to NTM 53-19-26, Page

Block 601).

(b) Compare the results of the inspection with the Flow Chart, refer to Fig. A-GFCAA.

1 If no crack(s) is (are) found:

a Repeat the inspection at the interval specified in Para. 1.E.(2)

Compliance, Table 1 or Table 2.

2 If crack(s) is (are) found:

a Contact Airbus before the next flight.

(4) Subtask 536042-220-201-001 - Rotating probe inspection of specified fastener

holes in Area 3, LH and RH, and cold expansion of specified fastener holes

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 10.00

Minimum number of person 2

Subtask elapsed time 5.00

Skills AIRFRAME

Material necessary to do the job

Kit 536042D01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 HLT637AP6-14 4 PIN

2 HLT637AP8-13 12 PIN

3 HLT286-6 4 COLLAR

4 HLT286-8 12 COLLAR

5 NAS1149D1165K 4 WASHER (1)

6 NSA5368PD416B 12 WASHER (1)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area

3 (rotating probe inspection and cold expansion of specified fastener

holes).

Kit D01 is to do the work on one side only.

Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A01 equals 2 Kits D01.

NOTE (1): Install only if necessary.

Kit 536042D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 HLT337AP8-14 4 PIN

12 HLT337AP10-13 12 PIN

13 HLT86-8 4 COLLAR

14 HLT86-10 12 COLLAR

15 NAS1149D0463K 4 WASHER (1)

16 NAS1149D0563K 12 WASHER (1)

NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area

3 (rotating probe inspection and cold expansion of specified fastener

holes), if the next oversize is required.

This kit should only be ordered if cracks are found during the rotating

probe inspection.

Kit D03 is to do the work on one side only.

Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A03 equals 2 Kits D03.

NOTE (1): Install only if necessary.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-01, Page Block 601

Structural Repair Manual (SRM) 51-40-41

Fig. A-GBAAA

Areas to be Inspected

Sheet 01

Fig. A-GFDAA

Flow Chart -D- (Rotating Probe

Inspection and Cold Expansion - Area 3)

Sheet 01

Sheet 02

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SERVICE BULLETIN

References

Fig. A-GBDAA

Inspection Area 3 - Cold Expansion of

the Fastener Holes

Sheet 01

Refer to Fig. A-GBAAA

Refer to Fig. A-GFDAA

Refer to Fig. A-GBDAA

NOTE: It is recommended that all inspections, as detailed in this Service

Bulletin, be completed before cold expanding the holes. This will avoid

having to install the next oversize fasteners in the event of a crack being

found in the corner fitting, which would then have to be replaced.

(a) From inspection Area 3, remove and discard:

4 Pins Item (1)

12 Pins Item (2)

4 Collars Item (3)

12 Collars Item (4)

(b) Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

(c) Do a rotating probe inspection of the fastener holes (Refer to NTM 51-10-01, Page

Block 601).

(d) Compare the results of the inspection with the Flow Chart, refer to Fig. A-GFDAA.

1 If no crack(s) is (are) found:

a Drill/ream the fastener holes to the applicable start diameters STDN 6-1-

N and 8-1-N.

NOTE: The minimum permitted fastener spacing, up to a fastener

diameter of 6.4 mm (0.252 in.), is 14.0 mm (0.551 in.)

measured from rivet hole center to rivet hole center. If

the fastener diameter is equal to or exceeds 6.4 mm

(0.252 in.), with a minimum spacing of 14.0 mm (0.551

in.), contact Airbus for instructions.

NOTE: The distance between the hole center and the material

edge should not be less than 1.5 x hole diameter. If this

distance cannot be kept, contact Airbus for instructions.

NOTE: If the distance between fastener holes to be cold

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

expanded is less than 2 x hole diameter, install skin

clamps in the adjacent holes and do the cold working

procedure, step by step, one fastener hole after the other.

b Cold expand the fastener holes and countersinks (Refer to SRM

51-40-41).

c Ream the fastener holes with the applicable gage finish reamer.

d Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

e In the applicable fastener holes, wet install:

4 Pin HLT637AP6-14 Item 1

12 Pin HLT637AP8-13 Item 2

4 Collar HLT286-6 Item 3

12 Collar HLT286-8 Item 4

with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

f If necessary, install:

4 Washer NAS1149D1165K Item 5

12 Washer NSA5368PD416B Item 6

under the collars, Item 3 and Item 4, to allow for slight variations in the

structure.

2 If crack(s) is (are) found:

a Drill/ream the fastener holes to the applicable start diameters STDN 6-3-

N and 8-3-N.

NOTE: The minimum permitted fastener spacing, up to a fastener

diameter of 6.4 mm (0.252 in.), is 14.0 mm (0.551 in.)

measured from rivet hole center to rivet hole center. If

the fastener diameter is equal to or exceeds 6.4 mm

(0.252 in.), with a minimum spacing of 14.0 mm (0.551

in.), contact Airbus for instructions.

NOTE: The distance between the hole center and the material

edge should not be less than 1.5 x hole diameter. If this

distance cannot be kept, contact Airbus for instructions.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 32

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SERVICE BULLETIN

NOTE: If the distance between fastener holes to be cold

expanded is less than 2 x hole diameter, install skin

clamps in the adjacent holes and do the cold working

procedure, step by step, one fastener hole after the other.

b Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

c Do a rotating probe inspection of the fastener holes (Refer to NTM

51-10-01, Page Block 601).

d Compare the results of the inspection with the Flow Chart, refer to Fig. AGFDAA.

<1> If no crack(s) is (are) found:

<a> Cold expand the fastener holes and countersinks (Refer to

SRM 51-40-41).

<b> Ream the fastener holes with the applicable gage finish

reamer.

<c> Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

<d> In the applicable fastener holes, wet install:

4 Pin HLT337AP8-14 Item 11

12 Pin HLT337AP10-13 Item 12

4 Collar HLT86-8 Item 13

12 Collar HLT86-10 Item 14

with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

<e> If necessary, install:

4 Washer NAS1149D0463K Item 15

12 Washer NAS1149D0563K Item 16

under the collars, Item 13 and Item 14, to allow for slight

variations in the structure.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

<2> If crack(s) is (are) found:

<a> Contact Airbus for further instructions before the next flight.

(5) Subtask 536042-250-204-001 - Eddy current inspection in area 3

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026

References

Non Destructive Test Manual (NTM) 53-19-26, Page Block 601

Structural Repair Manual (SRM) 53-19-12

Fig. A-GBAAA

Areas to be Inspected

Sheet 01

Refer to Fig. A-GBAAA

NOTE: Eddy current inspection in area 3 at the threshold and interval as given

in table 2 in para. E.(2) Accomplishment Timescale.

(a) Completely remove the FWD and lower anti-Chafing plates as per SRM 53-19-12.

(b) Clean the area to be inspected with:

Solvent General

Purpose

11-026 As required

(c) Do an Eddy current inspection around each fastener head in area 3 (Refer to NTM

53-19-26, Page Block 601).

1 If no crack(s) is (are) found:

a Install the FWD and lower Anti-Chafing plates as per SRM 53-19-12.

2 If crack(s) is (are) found:

a Contact Airbus for further instructions before the next flight.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 34

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SERVICE BULLETIN

(6) Subtask 536042-250-203-001 - Eddy current inspection of the longeron and outer

skin

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 536042D07R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

100 HLT637AP6-12 2 PIN

101 HLT337AP8-12 2 PIN (1)

102 HLT337AP8-14 4 PIN

103 HLT337AP10-13 22 PIN

104 HLT86-8 6 COLLAR

105 HLT86-10 22 COLLAR

106 HLT286-6 2 COLLAR

107 NAS1149D1165K 2 WASHER (2)

108 NAS1149D0463K 6 WASHER (2)

109 NAS1149D0563K 22 WASHER (2)

NOTE: Kit D07 is only applicable if the lower corner fitting has been removed

and a crack found in Area 1 after the fastener holes in Area 3 have been

cold expanded.

The quantity of fasteners in this kit is sufficient one side only.

This kit should only be ordered if a crack, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0

mm (1.969 in.) between the cracks, are found in Area 1 after the cold

expansion of Area 3.

Kit D07 is to do the work on one side only.

Kit A07 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A07 equals 1 Kit D07.

NOTE (1): Alternative to Item 100 if the next oversize is required.

NOTE (2): Install only if necessary.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 35

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SERVICE BULLETIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-01, Page Block 601

53-19-26, Page Block 601

Structural Repair Manual (SRM) 51-40-41

Fig. A-GBAAA

Areas to be Inspected

Sheet 01

Fig. A-GFEAA

Flow Chart -E- (Eddy Current Inspection

and Secondary Cold Expansion)

Sheet 01

Sheet 02

Fig. A-GBEAA

Inspection Area 3 - Secondary Cold

Expansion of the Fastener Holes if a

Crack is Found in Area 1 after Primary

Cold Expansion in Area 3

Sheet 01

Refer to Fig. A-GBAAA

Refer to Fig. A-GFEAA

Refer to Fig. A-GBEAA

NOTE: This inspection is only required if the corner fitting has to be replaced

and the fastener holes in Area 3 have already been cold expanded.

(a) Clean the area to be inspected with:

Solvent General

Purpose

11-026 As required

(b) Do an eddy current inspection (Refer to NTM 53-19-26, Page Block 601), in the

area of three fastener holes, of each fastener row, both sides of the crack, where

the corner fitting was attached to the longeron.

1 If no crack(s) is (are) found:

a Install the new corner fitting as detailed in TASK 536042-833-848 001

Repair . Do not install the fasteners in the area which has just been

inspected.

b Clean the fastener holes in the inspection area with:

Solvent General

Purpose

11-026 As required

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

c Do a rotating probe inspection of the fastener holes (Refer to NTM

51-10-01, Page Block 601).

<1> If no crack(s) is (are) found:

<a> Drill/ream the fastener holes to the applicable start diameters

STDN 6-1-N, 6-3-N and 8-3-N.

<b> Cold expand the fastener holes and countersinks (Refer to

SRM 51-40-41).

<c> Ream the fastener holes with the applicable gage finish

reamer.

<d> Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

<e> In the applicable fastener holes, wet install:

2 Pin HLT637AP6-12 Item 100

4 Pin HLT337AP8-14 Item 102

22 Pin HLT337AP10-13 Item 103

2 Collar HLT286-6 Item 106

4 Collar HLT86-8 Item 104

22 Collar HLT86-10 Item 105

with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

<f> If necessary, install:

2 Washer NAS1149D1165K Item 107

6 Washer NAS1149D0463K Item 108

22 Washer NAS1149D0563K Item 109

under the collars, Item 106, Item 104 and Item 105, to allow for

slight variations in the structure.

<2> If crack(s) is (are) found in either or both of the two holes where it is

possible to go to the next oversize:

<a> Drill/ream the fastener holes to the applicable start diameters

STDN 6-3-N.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

<b> Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

<c> Do a rotating probe inspection of the fastener holes (Refer to

NTM 51-10-01, Page Block 601).

[1] If no crack(s) is (are) found:

[a] Cold expand the fastener holes and countersinks

(Refer to SRM 51-40-41).

[b] Ream the fastener holes with the applicable gage

finish reamer.

[c] Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

[d] In the applicable fastener holes, wet install:

2 Pin HLT337AP8-12 Item 101

2 Collar HLT86-8 Item 104

with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

[2] If crack(s) is (are) found:

[a] Contact Airbus for further instructions before the next

flight.

<3> If crack(s) is (are) found in any of the other holes:

<a> Contact Airbus for further instructions before the next flight.

D. TEST

None

E. CLOSE-UP

None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

Task 536042-833-848-001 - Repair

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THE

MATERIALS SPECIFIED IN THE PROCEDURE.

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 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

310

Manpower

TOTAL MANHOURS 243.00

ELAPSED TIME (HOURS) 121.5

A. GENERAL

None

B. PREPARATION

(1) Subtask 536042-941-202-001 - Preparation

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Methyl Alcohol 11-006 As required

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 39

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoatgrey

(for Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Structural Repair Manual (SRM) 51-29-00

51-75-10

Fig. A-GBFAA

Example of Crack Removal in Inspection

Area 1

Sheet 01

Fig. A-GBHAA

Deflection Measurement Tool for Almen

Test Piece

Sheet 01

Fig. A-GBGAA

Holding Fixture for Almen Test Piece

Sheet 01

Refer to Fig. A-GBFAA

Refer to Fig. A-GBGAA

Refer to Fig. A-GBHAA

NOTE: If necessary, flap peening, as detailed in SRM 51-29-00, can be used as

an alternative to shot peening with the same intensity.

NOTE: Operators who for any reason cannot accomplish the shot peening

procedure or the alternative flap peening must contact Airbus for

instructions.

NOTE: Operators must be specifically trained to use the shot peening machine

and to check test specimen deflection.

NOTE: Crack detection inspection must be done prior to shot peening.

NOTE: Where the name shot peening is given in the subsequent procedures, it

refers to shot manufactured from glass. The specification for glass is

given in MIL-G-9954A and MIL-S-13165B.

NOTE: Shot must only be used again on materials that are of the same type.

(a) Preparation

1 Make sure that the equipment and materials to be used are in good

condition and that the machine keeps a constant blast pressure, to ensure the

necessary precision.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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2 Pass the shot through the applicable series of sieves fitted with screens (Refer

to the subsequent table). The screens must conform to American Federal

Specification RR-S-366E. This will make sure that the shot is correct.

NOMINAL BEAD

SIZE

SCREEN SIZE 70

(1)

SCREEN SIZE 80

(1)

SCREEN SIZE 120

(1)

SCREEN SIZE 140

(1)(2)

70

0.1778 mm (0.007

in.) dia.

100% SHALL

PASS THRU

SIEVE

98% SHALL PASS

THRU SIEVE

MAX 8% SHALL

PASS THRU

SIEVE

0% SHALL PASS

THRU SIEVE

NOTE (1): THE NUMBERS IN THESE COLUMNS ARE THE SCREEN

SIZES TO BE USED IN THE SIEVES (REFER TO FED.

SPEC. RR-S-366E).

NOTE (2): WHEN THE SHOT IS IN USE IT MUST BE CHECKED ONCE

EVERY 2 HOURS. IF MORE THAN 15% (BY WEIGHT)

PASSES THROUGH THE SIEVE, CHANGE THE SHOT.

3 If the shot has been used before, one of the conditions which follow must be

applied:

- If the shot is to be used in a machine which has a continuous removal

separator, make sure that the separator is correct for the shot dimension.

- If the machine does not have a continuous removal separator, check of

the shot at least once every 2 hours that it is in use.

- If more than 15% (by weight) pass through the 0% sieve change the shot.

4 To shot peen the affected area correctly, blast it with the correct dimension

shot to the correct intensity. To establish the correct intensity of 0.25 N, do a

test on an Almen test strip. The result of this test gives an arc height, usually

in millimeters (mm).

Saturation time is the period of time in minutes that is required to peen the

area to get:

- the required intensity

- the required coverage.

The minimum time required is that time which, if doubled, would only give a

10% or less increase to the arc height (intensity). For example, if 4 minutes

gives an arc height of 0.25 mm, after 8 minutes the arc height should not be

more than 0.275 mm. If its is, repeat the test but with an increase of the first

time (4 minutes). Repeat the test until the correct saturation time is found.

NOTE: Use the Almen test strip once only for this test.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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@A300-600

SERVICE BULLETIN

Full coverage of the peened area must be checked visually, if necessary use a

10X magnifying glass. Coverage is specified as all the surface in the area

showing identations which overlap. A repair procedure will usually specify a

100% coverage, this means that at least 98% of the surface must show

evidence of peening.

5 Remove the paint/primer from the specified area (Refer to SRM 51-75-10).

6 Mask the structure around the specified area. Use masking tape (several

layers), or rubber mats held in position with adhesive tape.

(b)

CAUTION: MAKE SURE THAT THERE IS NO RISK OF STRAY SHOT

DAMAGING THE SURROUNDING STRUCTURE.

Procedure for finding the intensity and saturation point required.

1 Put the applicable Almen test strip on the deflection measuring tool, refer to

Fig. A-GBHAA. Set the dial test indicator of the tool to zero.

2 Put the test strip in the holding fixture, refer to Fig. A-GBGAA.

3 Adjust the shot propellant machine to give the shot velocity specified in the

repair procedure. If the velocity is not specified, adjust the machine to the

manufacturer’s recommended working pressure or wheel speed.

4

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS FOR

THE MACHINE AND WEAR APPROVED PROTECTIVE

CLOTHING. SHOT PEENING CAN BE DANGEROUS.

Peen the test strip. To do this, for example, pass the shot stream across the

test strip for 2 minutes.

NOTE: Pass the shot stream across the test strip at a constant and

continuous speed.

5 Remove the test strip from the holding tool and put it on the deflection

measuring tool. Put the side of the strip which is not peened nearest to the

indicator stem. Note this reading on the dial test indicator, this is the arc

height.

6 Plot the graph to verify the arc height and exposure time.

7 If necessary, do the test procedure again but with a reduced or increased

velocity as indicated by the graph. Use a new test strip for every test. Do the

procedure again until you have the correct arc height. To make sure that the

saturation point is correct (to give full coverage), do the test again but with

double the final exposure time. The arc height should not increase more than

10%, if it does, start the test procedure again but with a longer exposure time.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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8 Make a record of the arc height, saturation point, velocity and exposure time.

Pass this record with the test strips to Quality Assurance Department for

approval.

(c) Peening the repaired area(s).

1 Load the shot propellent machine with shot that is the correct dimension and

has been checked that it is free from defects. Fit the specified nozzle to the

machine. Adjust the machine to give the shot the same velocity as in the test.

2 Peen the specified area. Make sure that the nozzle moves over the area at

the same speed and time as in the test.

3 Examine the peened area to make sure that the correct coverage has been

obtained. Continue the peening operation if necessary.

NOTE: It is recommended to use a 10X magnifying glass or equivalent

aid to do the examination.

4 Use a vacuum cleaner to remove any loose shot from the surrounding area,

including the peened surface and any hidden areas.

5 Remove the tools from the work area.

6 Remove the masking tape and rubber mats.

7

WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE

MATERIAL(S). YOU MUST OBEY THE OPERATOR’S AND

MANUFACTURER’S HEALTH AND SAFETY INSTRUCTIONS.

Clean the treated area using

Methyl Alcohol 11-006 As required

and apply

Wash Primer 16-020 As required

,

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Polyurethane

Topcoatgrey (for

Internal Applic.)

16-002 As required

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 43

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SERVICE BULLETIN

C. PROCEDURE

(1) Subtask 536042-911-202-001 - Replacement of the lower corner fitting

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 60.00

Minimum number of person 1

Subtask elapsed time 60.00

Skills AIRFRAME

Material necessary to do the job

Kit 536042D01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 HLT637AP6-14 4 PIN

2 HLT637AP8-13 12 PIN

3 HLT286-6 4 COLLAR

4 HLT286-8 12 COLLAR

NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area

3 (rotating probe inspection and cold expansion of specified fastener

holes).

Kit D01 is to do the work on one side only.

Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A01 equals 2 Kits D01.

Kit 536042D03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 HLT337AP8-14 4 PIN

12 HLT337AP10-13 12 PIN

13 HLT86-8 4 COLLAR

14 HLT86-10 12 COLLAR

NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area

3 (rotating probe inspection and cold expansion of specified fastener

holes), if the next oversize is required.

This kit should only be ordered if cracks are found during the rotating

probe inspection.

Kit D03 is to do the work on one side only.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A03 equals 2 Kits D03.

Kit 536042D04R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

40 A5398613520290 2 FITTING

NOTE: Kit D04 is only applicable if the LH corner fitting has to be replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm

(1.969 in.) between the cracks, are found in the fitting.

Kit A04 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A04 equals 1 Kit D04.

Kit 536042D05R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

50 A5398613520390 2 FITTING

NOTE: Kit D05 is only applicable if the RH corner fitting has to be replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm

(1.969 in.) between the cracks, are found in the fitting.

Kit A05 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A05 equals 1 Kit D05.

Kit 536042D06R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

22 DAN8-6-6X 27 PIN

23 DAN8-6-11X 7 PIN

27 DAN8-8-12X 12 PIN

28 DAN8-8-13X 12 PIN (1)

29 DAN12-6X 97 COLLAR

30 DAN12-8X 28 COLLAR

61 DAN7-6-5 10 PIN

62 DAN7-6-6X 16 PIN

63 DAN7-6-7X 11 PIN

64 DAN7-6-8X 7 PIN

66 DAN8-6-8X 17 PIN

67 DAN8-6-9X 22 PIN

69 DAN8-8-8X 16 PIN

72 DAN12-6 10 COLLAR

75 DAN14-6 10 COLLAR

76 LN9198-4012CF 20 RIVET

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SERVICE BULLETIN

NOTE: Kit D06 is only applicable if the LH or RH corner fitting has to be

replaced.

This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.)

or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm

(1.969 in.) between the cracks, are found in the fitting.

The quantity of fasteners in this kit is sufficient only for the replacement

of one corner fitting.

The kit does not include the special bull-nose fasteners which are

installed in the cold-expanded holes. These fasteners are to be found in

Kit D01.

Kit D06 is to do the work on one side only.

Kit A06 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A06 equals 1 Kit D06.

NOTE (1): Alternative to Item 27 if a longer fastener is required.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibitingfillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoatgrey

(for Internal Applic.)

16-002 As required

References

Structural Repair Manual (SRM) 51-40-41

51-40-47

53-19-12

Fig. A-GBJAA

Replacement of the Lower Corner Fitting

Sheet 01

Sheet 02

Sheet 03

Sheet 04

CAUTION: TO PREVENT DAMAGE DURING THE REMOVAL OF THE ANTICHAFING PLATES, A HOT-AIR BLOWER MUST BE USED TO

SOFTEN THE SEALANT.

NOTE: For the replacement of a LH corner fitting, use Kit D04 and Kit D06.

NOTE: For the replacement of a RH corner fitting, use Kit D05 and Kit D06.

NOTE: The procedure for the replacement of a corner fitting, is the same for

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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@A300-600

SERVICE BULLETIN

both sides.

Refer to Fig. A-GBJAA

(a) Remove the FWD anti-chafing plate, if not already removed (Refer to SRM

53-19-12).

(b) Remove the lower anti-chafing plate, if not already removed (Refer to SRM

53-19-12) or make a cutout in the lower anti-chafing plate as described in

SUBTASK 536042-941-201 001 Preparation .

(c) Remove all old sealant from the work area with a non-metallic scraper.

(d) Clean the work area with:

Solvent General

Purpose

11-026 As required

(e) Remove:

4 Pin-Rivet HLT637AP6-14 Item (1) Discard

4 Collar-Hi-Lok HLT286-6 Item (3) Discard

12 Pin-Rivet HLT637AP8-13 Item (2) Discard

12 Collar-Hi Lok HLT286-8 Item (4) Discard

10 Pin-Rivet DAN7-6-5 Item (61) Discard

16 Pin-Rivet DAN7-6-6X Item (62) Discard

11 Pin-Rivet DAN7-6-7X Item (63) Discard

7 Pin-Rivet DAN7-6-8X Item (64) Discard

27 Pin-Rivet DAN8-6-6X Item (65) Discard

17 Pin-Rivet DAN8-6-8X Item (66) Discard

21 Pin-Rivet DAN8-6-9X Item (67) Discard

7 Pin-Rivet DAN8-6-11X Item (68) Discard

16 Pin-Rivet DAN8-8-8X Item (69) Discard

12 Pin-Rivet DAN8-8-12 Item (70) Discard

10 Collar DAN12-6 Item (72) Discard

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97 Collar DAN12-6X Item (73) Discard

28 Collar DAN12-8X Item (74) Discard

10 Collar-Hi-Lok DAN14-6 Item (75) Discard

(f) Remove:

20 Rivet LN9198-4012CF Item (76) Discard

(g) Remove and retain the connecting angle, Item (41) (LH) or Item (51) (RH).

(h) Remove and retain the T-profile, Item (42) (LH) or Item (52) (RH).

(i) Remove and retain the fitting, Item (43) (LH) or Item (53) (RH).

(j) Remove all the old sealant from the retained items with a non-metallic scraper.

(k) Clean the retained items with:

Solvent General

Purpose

11-026 As required

(l)

CAUTION: TO AVOID DAMAGE TO THE FUSELAGE STRUCTURE, USE

NON-METALLIC TOOLS TO REMOVE THE CORNER FITTING.

Remove and discard the corner fitting, Item (40) (LH) or Item (50) (RH).

(m) Remove all the old sealant from the fuselage structure with a non-metallic scraper.

(n) Clean the fuselage structure with:

Solvent General

Purpose

11-026 As required

(o) Temporarily install:

1 Fitting (LH) A5398613520290 Item 40

or

1 Fitting (RH) A5398613520390 Item 50

NOTE: Make sure that the corner fitting aligns with the contour of the

horizontal stabilizer cutout.

(p) Mark the fastener hole positions with a soft-lead pencil.

(q) Remove the corner fitting and make sure there is enough edge clearance.

(r) Install the corner fitting in the same position.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

(s) Transfer drill the holes from the fuselage structure to the corner fitting with a pilot

drill bush.

(t) Open up the holes, which will not be cold-expanded, as necessary for the specified

fasteners.

(u) Remove the corner fitting, deburr the fastener holes and clean with:

Solvent General

Purpose

11-026 As required

(v) Wet install:

1 Fitting (LH) A5398613520290 Item 40

1 Connecting angle (LH) Item (41)

(Retained

at removal)

1 T-Profile (LH) Item (42)

(Retained

at removal)

1 Fitting (LH) Item (43)

(Retained

at removal)

or

1 Fitting (RH) A5398613520390 Item 50

1 Connecting angle (RH) Item (51)

(Retained

at removal)

1 T-Profile (RH) Item (52)

(Retained

at removal)

1 Fitting (RH) Item (53)

(Retained

at removal)

with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

NOTE: Use skin clamps to hold all items in the correct position

(w) Drill/ream the fastener holes, which are to be cold expanded, to the correct start

diameters.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

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SERVICE BULLETIN

(x) Cold expand the fastener holes (Refer to SRM 51-40-41).

(y) Ream the fastener holes to the correct finish diameters.

(z) Re-countersink the fastener holes as necessary (Refer to SRM 51-40-47).

(aa) Clean the fastener holes with:

Solvent General

Purpose

11-026 As required

(ab) Wet install the fasteners:

4 Pin HLT637AP6-14 Item 1

4 Collar HLT286-6 Item 3

12 Pin HLT637AP8-13 Item 2

12 Collar HLT286-8 Item 4

4 Pin HLT337AP8-14 Item 11

12 Pin HLT337AP10-13 Item 12

4 Collar HLT86-8 Item 13

12 Collar HLT86-10 Item 14

27 Pin DAN8-6-6X Item 22

7 Pin DAN8-6-11X Item 23

12 Pin DAN8-8-12X Item 27

12 Pin DAN8-8-13X Item 28

97 Collar DAN12-6X Item 29

28 Collar DAN12-8X Item 30

10 Pin DAN7-6-5 Item 61

16 Pin DAN7-6-6X Item 62

11 Pin DAN7-6-7X Item 63

7 Pin DAN7-6-8X Item 64

17 Pin DAN8-6-8X Item 66

22 Pin DAN8-6-9X Item 67

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 50

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16 Pin DAN8-8-8X Item 69

10 Collar DAN12-6 Item 72

10 Collar DAN14-6 Item 75

20 Rivet LN9198-4012CF Item 76

with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

(ac) Clean the work area with:

Solvent General

Purpose

11-026 As required

(ad) Apply:

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Polyurethane

Topcoatgrey (for

Internal Applic.)

16-002 As required

to the heads and collars of the fasteners.

(ae) Apply:

Corrosion

Inhibitingfillet

Consistency

09-016 As required

around all edges of the corner fitting, connecting angle, T-profile and fitting.

(af) Install the FWD anti-chafing plate (Refer to SRM 53-19-12).

(ag) Install the lower anti-chafing plate or cutout as applicable (Refer to SRM 53-19-12).

D. TEST

None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 51

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SERVICE BULLETIN

E. CLOSE-UP

(1) Subtask 536042-942-202-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Kit 536042D02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

21 DAN6-5-4 9 PIN

22 DAN8-6-6X 3 PIN

23 DAN8-6-11X 1 PIN

24 DAN8-6-12X 1 PIN

25 DAN8-8-9X 1 PIN

26 DAN8-8-11X 1 PIN

27 DAN8-8-12X 1 PIN

28 DAN8-8-13X 3 PIN (1)

29 DAN12-6X 5 COLLAR

30 DAN12-8X 6 COLLAR

32 HL70-5 9 COLLAR

33 A5398402120000 9 WASHER

34 A5398402120200 5 WASHER

35 A5398402120400 6 WASHER

NOTE: Kit D02 is only applicable if cutouts are to be made in the FWD and

lower anti-chafing plates instead of the complete removal of the antichafing plates. The cutout procedure reduces the manpower for the "Get

Access" and "Close-Up" procedures.

Kit D02 is to do the work on one side only.

Kit A02 from revision 02 or earlier of this Service Bulletin is still valid for

this revision. The content of 1 Kit A02 equals 2 Kits D02.

NOTE (1): Alternative to Item 27 if a longer fastener is required.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Polysulphide Sealant For

Interfay

09-048 As required

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 52

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 52-41-00, Page Block 001

55-12-11, Page Block 401

55-15-11, Page Block 401

Structural Repair Manual (SRM) 51-75-10

53-19-12

Fig. A-GBCAA

Make Cutouts in the FWD and Lower

Anti-Chafing Plates

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

NOTE: Only if the rotating probe inspection in Area 3 has been done is the reinstallation of the removed anti-chafing plates or the re-installation of the

removed cutouts necessary.

(a) If the inspection in Area 3 has been done using Solution 1 (FWD and lower antichafing plates removed completely for access to the inspection area).

1 Do a visual inspection of the fuselage skin protective treatment in area of the

anti-chafing plates (LH and RH). Repair the protective treatment if necessary

(Refer to SRM 51-75-10).

2 Install the retained anti-chafing plates (LH and RH) (Refer to SRM 53-19-12).

3 Install the retained THS aprons (LH and RH) (Refer to AMM 55-15-11, Page

Block 401).

4 Install the retained THS leading edges (LH and RH) (Refer to AMM 55-12-11,

Page Block 401).

5 Make sure that the work area is clean and clear of tools and other items of

equipment.

6 Close the access door 312AR (Refer to AMM 52-41-00, Page Block 001).

7 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU FAC1/28VDC 306CC1 103/G3

21VU FAC1/115VAC 309CC1 103/G5

21VU FAC1/26VAC 305CC1 103/G7

21VU FAC2/26VAC 305CC2 103/G8

21VU FAC2/115VAC 309CC2 103/G10

21VU FAC2/28VDC 306CC2 103/G12

8 Remove the access platform(s).

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 53

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(b) If the inspection in Area 3 has been done using Solution 2 (Cutouts made in the

FWD and lower anti-chafing plates for access to the inspection area).

NOTE: The following worksteps are applicable for both sides of the aircraft

(LH and RH).

1 Do a visual inspection of the fuselage skin protective treatment in area of the

cutouts. Repair the protective treatment if necessary (Refer to SRM 51-75-10).

2 Mark on the fuselage skin, with a soft-lead pencil, the positions for the four

fasteners indicated with NOTE 2 (Refer to Fig. A-GBCAA Sheet 02).

3 Pilot drill the dour new holes.

4 Open up the four holes to 4.12 mm (0.162 in.) minimum 4.16 mm (0.164 in.)

maximum diameter.

5 Remove the existing fasteners from the three holes indicated with NOTES 1

and 5 (Refer to Fig. A-GBCAA Sheet 02).

6 Make the new attachment hole in the FWD anti-chafing plate:

a Insert a thin sheet of metal between the skin and the FWD anti-chafing

plate in the area of the existing fastener indicated with the NOTES 1 and

6 (Refer to Fig. A-GBCAA Sheet 02).

b Back drill through the existing fastener.

c Open up the hole in the FWD anti-chafing plate to 13.5 mm (0.53 in.).

NOTE: Use a spot facing tool to open up the hole in the antichafing plate.

d Remove the metal sheet and the remains of the fastener.

7 Make the new attachment hole in the lower anti-chafing plate:

a Insert a thin sheet of metal between the skin and the lower anti-chafing

plate in the area of the pilot hole indicated with the NOTES 2, 3 and 7

(Refer to Fig. A-GBCAA Sheet 02).

b Open up the hole in the fuselage to 4.12 mm (0.162 in.) minimum 4.16

mm (0.164 in.) maximum diameter.

c Open up the hole in the lower anti-chafing plate to 10.0 mm (0.39 in.).

NOTE: Use a spot facing tool to open up the hole in the antichafing plate.

d Remove the metal sheet.

8 Temporarily install the cutouts.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 54

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9 Transfer drill the new fastener holes to the cutouts.

NOTE: Use a pilot drill bush to prevent damage to the existing holes.

10 Remove the cutouts.

11 Open up the holes in the cutouts marked with NOTE 4 to 10.0 mm (0.39 in.)

(Refer to Fig. A-GBCAA Sheet 02).

12 Open up the holes in the cutouts marked with NOTE 5 to 13.5 mm (0.53 in.)

(Refer to Fig. A-GBCAA Sheet 02).

13 Deburr the holes and edges of the cutouts.

14 Clean the cutouts and the fuselage skin with:

Solvent General

Purpose

11-026 As required

15 Apply:

Polysulphide

Sealant For Interfay

09-048 As required

to the contact surfaces of the cutouts.

16 Put the cutouts in position on the fuselage and remove any air trapped

between the cutouts and the skin with a roller.

17 Wet install:

9 Pin DAN6-5-4 Item 21

9 Collar HL70-5 Item 32

9 Washer A5398402120000 Item 33

3 Pin DAN8-6-6X Item 22

3 Collar DAN12-6X Item 29

3 Washer A5398402120200 Item 34

1 Pin DAN8-6-11X Item 23

1 Collar DAN12-6X Item 29

1 Washer A5398402120200 Item 34

1 Pin DAN8-6-12X Item 24

1 Collar DAN12-6X Item 29

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 55

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1 Washer A5398402120200 Item 34

1 Pin DAN8-8-9X Item 25

1 Collar DAN12-8X Item 30

1 Washer A5398402120400 Item 35

1 Pin DAN8-8-11X Item 26

1 Collar DAN12-8X Item 30

1 Washer A5398402120400 Item 35

1 Pin DAN8-8-12X Item 27

1 Collar DAN12-8X Item 30

1 Washer A5398402120400 Item 35

3 Pin DAN8-8-13X Item 28

3 Collar DAN12-8X Item 30

3 Washer A5398402120400 Item 35

with:

Corrosion Inhibiting

Brush Consistency

09-013 As required

18 Remove any excess sealant.

19 Vacuum clamp the cutouts to the fuselage (Refer to SRM 53-19-12).

20 Install the retained THS apron (Refer to AMM 55-15-11, Page Block 401).

21 Make sure that the work area is clean and clear of tools and other items of

equipment.

22 Close the access door 312AR (Refer to AMM 52-41-00, Page Block 001).

23 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU FAC1/28VDC 306CC1 103/G3

21VU FAC1/115VAC 309CC1 103/G5

21VU FAC1/26VAC 305CC1 103/G7

21VU FAC2/26VAC 305CC2 103/G8

21VU FAC2/115VAC 309CC2 103/G10

21VU FAC2/28VDC 306CC2 103/G12

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 56

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24 Remove the access platform(s).

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 57

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**CONF ALL

SKIN STRAP

RH SHOWN

LH SYMMETRICAL

LONGERON

CORNER FITTING

LOWER

OUTER SKIN

B

C

A

Z310

FR86

FR91

FR87

STGR24LH FR89

STGR27LH

STGR24RH

STGR27RH

B

A

INSPECTION AREA2

INSPECTION AREA1

INSPECTION AREA3

VISUAL INSPECTION

INSPECTION AREA1

INSPECTION AREA2

INSPECTION AREA3

NOTE:

VISUAL INSPECTION

20.0 mm (0.787 in)

20.0 mm (0.787 in)

STGR24RH

STGR26RH

STGR27RH

20.0 mm (0.787 in)

FR87 FR88 FR89

20.0 mm (0.787 in)

C

RH SHOWN

LH SYMMETRICAL

FWD

D_SB_536042_6_BAAA_01_00

Figure A-GBAAA - Sheet 01

Areas to be Inspected

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 58

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**CONF ALL

CRACK (S) 

FOUND

CLEAN THE AREAS TO BE INSPECTED

YES

CORROSION

FOUND

01 VISUAL INSPECTION IN AREAS 1, 2 AND 3 (LH/RH)

NO KIT REQUIRED

01 VISUALLY INSPECT AREAS 1, 2 AND 3

FOR CRACKS AND CORROSION

SEALANT

DAMAGED

REMOVE CORROSION

NO NO YES

01 VISUALLY INSPECT AREAS 1, 2 AND 3

FOR DAMAGED SEALANT

YES NO

REPAIR SEALANT

REPEAT THE INSPECTIONS

AT THE INTERVALS DETAILED IN PARA. 1.E. (2)

AND THE OUTER SKIN IN THIS AREA VISUALLY INSPECTED

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

NOTE:

01 ONLY IF THE ROTATING PROBE INSPECTION IN AREA 3 HAS TO BE DONE,

THE ANTI−CHAFING PLATES MUST BE REMOVED

D_SB_536042_6_FAAA_01_01

Figure A-GFAAA - Sheet 01

Flow Chart -A- (Visual Inspection - All Areas)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 59

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**CONF ALL

CLEAN THE AREA TO BE INSPECTED

EDDY CURRENT INSPECTION IN AREA 1 (LH/RH)

NO KIT REQUIRED

DO AN EDDY CURRENT INSPECTION IN AREA 1

CORNER FITTING FLANGE AND EDGE

OF OUTER SKIN

CRACK (S) 

FOUND

NO YES

REPEAT THE INSPECTIONS

AT THE INTERVALS DETAILED IN PARA. 1.E. (2)

CRACK LENGTH LESS THAN OR EQUAL TO

2.0 mm (0.079 in)

AND NOT MORE THAN TWO CRACKS WITH A

MINIMUM DISTANCE OF 50.0 mm (1.968 in)

BETWEEN THE CRACKS

CRACK LENGTH MORE THAN 2.0 mm (0.079 in)

OR

MORE THAN TWO CRACKS

OR

TWO CRACKS WITH A DISTANCE OF LESS THAN

50.0 mm (1.968 in) BETWEEN THE CRACKS

REMOVE DAMAGE FROM CORNER FITTING

FLANGE OR EDGE OF OUTER SKIN BY MILLING

A RADIUS OF BETWEEN 10.0 mm (0.394 in) MIN

AND 20.0 mm (0.787 in) MAX

CLEAN THE REWORKED AREA

SEE SHEET 2

SEE SHEET 2

D_SB_536042_6_FBAA_01_01

Figure A-GFBAA - Sheet 01

Flow Chart -B- (Eddy Current Inspection - Area 1)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 60

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**CONF ALL

REPEAT THE EDDY CURRENT INSPECTION OF

THE REWORKED AREA

CRACK (S) 

FOUND

NO YES

SHOT PEEN THE REWORKED AREA

SEE SHEET 1

REPEAT THE INSPECTIONS

NOTE:

01 IF, FOR ANY REASON, SHOT OR FLAP PEENING CANNOT BE

01

ACCOMPLISHED, CONTACT AIRBUS

CLEAN THE REWORKED AREA

IF RADIUS IS LESS THAN THE

20.0 mm (0.787 in) MAX,

INCREASE THE RADIUS TO

20.0 mm (0.787 in)

REPEAT THE EDDY CURRENT INSPECTION OF

THE REWORKED AREA

NO

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

REMOVE CORNER FITTING

NO YES

SEE SHEET 1

INSTALL NEW CORNER FITTING

DO NOT INSTALL THE FASTENER

IN INSPECTION AREA 3

DO A ROTATING PROBE

INSPECTION IN AREA 3

(REFER TO FLOW CHART−

FIGURE FDAA−01)

DO AN EDDY CURRENT INSPECTION

OF THE LONGERON AND OUTER

SKIN, IN THE AREA OF THREE

FASTENER HOLES OF EACH

FASTENER ROW, BOTH SIDES OF

THE CRACK, WHERE THE CORNER

FITTING WAS ATTACHED TO THE

LONGERON (REFER TO FLOW

CHART−FIGURE A−GFEAA)

CRACK (S)

FOUND IN 

CORNER 

FITTING

CRACK (S)

FOUND IN 

OUTER SKIN

CRACK (S)

FOUND

AREA 3

CLOD EXPANDED

AT THE INTERVALS

IN PARA. 1. E. (2)

D_SB_536042_6_FBAA_02_02

Figure A-GFBAA - Sheet 02

Flow Chart -B- (Eddy Current Inspection - Area 1)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 61

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**CONF ALL

CRACK (S) 

FOUND

CLEAN THE AREAS TO BE INSPECTED

EDDY CURRENT INSPECTION IN AREAS 2(LH/RH)

NO KIT REQUIRED

NO YES

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

REPEAT THE INSPECTIONS

DO AN EDDY CURRENT INSPECTION IN AREA 2

AT THE INTERVALS DETAILED IN PARA. 1.E. (2)

D_SB_536042_6_FCAA_01_01

Figure A-GFCAA - Sheet 01

Flow Chart -C- (Eddy Current Inspection - Area 2)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 62

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**CONF ALL

ROTATING PROBE INSPECTION OF SPECIFIED

FASTENER HOLES IN AREA 3 (LH/RH)

REMOVE THE FASTENERS FROM THE SPECIFIED HOLES

CRACK (S) 

FOUND

NO YES

DRILL/REAM THE FASTENER

HOLES TO THE NEXT

APPLICABLE START DIAMETER

COLD EXPAND THE FASTENER

HOLES AND COUNTERSINKS

CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION

CRACK (S) 

FOUND

NO YES

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

DRILL/REAM THE FASTENER

HOLES TO THE APPLICABLE

START DIAMETER

DRILL/REAM THE FASTENER

HOLES TO THE APPLICABLE

FINAL DIAMETER

CLEAN THE FASTENER HOLES

WET INSTALL THE

APPLICABLE FASTENERS

CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION

COMPLETELY REMOVE THE FWD AND LOWER

ANTI−CHAFING PLATES

OR

MAKE CUTOUTS IN THE FWD AND LOWER

ANTI−CHAFING PLATES

FURTHER INSPECTIONS ARE REQUIRED

IN AREA 3 AT THE THRESHOLD AND

INTERVALS GIVEN IN TABLE 2

SEE SHEET 2

D_SB_536042_6_FDAA_01_02

Figure A-GFDAA - Sheet 01

Flow Chart -D- (Rotating Probe Inspection and Cold Expansion - Area 3)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 63

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**CONF ALL

CRACK (S) 

FOUND

NO YES

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

PERFORM HFEC INSPECTION

IN AREA 3 AROUND EACH

FASTENER HEAD

COMPLETELY REMOVE THE

FORWARD AND LOWER

ANTI−CHAFING PLATES

REPEAT INSPECTION

AT INTERVALS GIVEN IN

TABLE 2

HFEC INSPECTION IN

AREA 3 AROUND EACH

FASTENER HEAD (LH/RH)

SEE SHEET 1

D_SB_536042_6_FDAA_02_01

Figure A-GFDAA - Sheet 02

Flow Chart -D- (Rotating Probe Inspection and Cold Expansion - Area 3)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 64

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**CONF ALL

NO

DRILL/REAM THE FASTENER

HOLES TO THE NEXT

APPLICABLE START DIAMETER

COLD EXPAND THE FASTENER

HOLES AND COUNTERSINKS

CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION

CRACK (S) 

FOUND

NO YES

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

DRILL/REAM THE FASTENER

HOLES TO THE APPLICABLE

START DIAMETER

DRILL/REAM THE FASTENER

HOLES TO THE APPLICABLE

FINAL DIAMETER

CLEAN THE FASTENER HOLES

WET INSTALL THE

APPLICABLE FASTENERS

FURTHER INSPECTIONS ARE REQUIRED

IN AREA 3 AT THE THRESHOLD AND

INTERVALS GIVEN IN TABLE 2

CRACK (S) 

FOUND

NO YES

EDDY CURRENT INSPECTION OF

THE LONGERON AND

OUTER SKIN

CLEAN THE AREA TO BE INSPECTED

DO AN EDDY CURRENT INSPECTION IN

THE AREA OF THREE FASTENER HOLES OF

EACH FASTENER ROW, BOTH SIDES OF THE

CRACK, WHERE THE CORNER FITTING WAS

ATTACHED TO THE LONGERON

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION

INSTALL THE NEW CORNER FITTING

BUT DO NOT INSTALL THE

FASTENERS IN THE HOLES WHICH

WILL BE COLD EXPANDED

IF CRACK(S) ARE

FOUND IN ANY OF

THE OTHER HOLES

IF CRACK(S) ARE FOUND IN

EITHER OR BOTH OF THE TWO

HOLES WHERE IT IS POSSIBLE

TO GO TO THE NEXT OVERSIZE

CRACK (S) 

FOUND YES

SEE SHEET 2

D_SB_536042_6_FEAA_01_04

Figure A-GFEAA - Sheet 01

Flow Chart -E- (Eddy Current Inspection and Secondary Cold Expansion)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 65

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**CONF ALL

CRACK (S) 

FOUND

NO YES

CONTACT AIRBUS

FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

PERFORM HFEC INSPECTION

IN AREA 3 AROUND EACH

FASTENER HEAD

COMPLETELY REMOVE THE

FORWARD AND LOWER

ANTI−CHAFING PLATES

REPEAT INSPECTION

AT INTERVALS GIVEN IN

TABLE 2

HFEC INSPECTION IN

AREA 3 AROUND EACH

FASTENER HEAD (LH/RH)

SEE SHEET 1

D_SB_536042_6_FEAA_02_01

Figure A-GFEAA - Sheet 02

Flow Chart -E- (Eddy Current Inspection and Secondary Cold Expansion)

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 66

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**CONF ALL

CIRCULAR SAW

(DESOUTER RC90 OR SIMILAR)

0.55 mm (0.022 in)

CUTTING DISC GROUND TO AN ANGLE OF 15°

DEPTH OF CUT

01

NOTE:

TEST STRIP

FOR SAMPLE CUT

200.0 mm

(7.87 in)

50.0 mm

(1.968 in)

0.60 mm

(0.024 in)

0.55 mm

(0.022 in)

CORRECT METHOD

OF CUTTING AN

ANTI−CHAFING PLATE

CUTOUT ANTI−CHAFING PLATE

STRAIGHT EDGE

A

A

A A

01 15°

0.55 mm

(0.022 in)

D_SB_536042_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

Preparation of Circular Saw

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 67

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**CONF ALL

CUTOUT

REMOVE THIS WEDGE OF MATERIAL AFTER THE REMOVAL

MAKE THE CUTS AS SHOWN IN SECTION B−B TO MAKE

CUTOUT

CUTLINE CUTLINE

LOWER

FWD

ANTI−CHAFING PLATE

ANTI−CHAFING PLATE

LOWER

FWD

CUTOUT

CUTOUT

ANTI−CHAFING PLATE

ANTI−CHAFING PLATE

OF THE CUTOUTS

SURE THE WEDGES ARE ATTACHED TO THE CUTOUTS AND NOT

TO THE REMAINING ANTI−CHAFING PLATES.

FR86

FR91

FR87

STGR24LH FR89

STGR27LH

STGR24RH

STGR27RH

A

Z310

B

01

02

NOTE:

A

A B

B

B

B A

A

A

01

02

B

0.60 mm

(0.024 in) 0.55 mm

(0.022 in)

RH SHOWN

LH SYMMETRICAL

A A

B B

TYPICAL

TYPICAL

C D

D_SB_536042_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

Make Cutouts in the FWD and Lower Anti-Chafing Plates

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 68

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SERVICE BULLETIN

**CONF ALL

PLATE ATTACHMENT

HOLES

REMARKS

PLATE ATTACHMENT

EXISTING FASTENERS

HOLES

20.0 mm

(0.787 in)

20.0 mm

(0.787 in)

15.0 mm

(0.59 in)

= =

20.0 mm

(0.787 in)

20.0 mm

(0.787 in)

20.0 mm

(0.787 in)

NEW ANTI−CHAFING

EXISTING ANTI−CHAFING

STGR29LH

STGR30LH

FR88

01

02

03

04

05

06

07

NOTE:

USE EXISTING FASTENER HOLE

NEW FASTENER HOLE

OPEN UP TO 4.12 mm (0.162 in) MIN 4.16 mm (0.164 in) MAX IN FUSELAGE

OPEN UP TO 10.0 mm (0.39 in) IN ANTI−CHAFING PLATE

OPEN UP TO 13.5 mm (0.53 in) IN ANTI−CHAFING PLATE

BACK DRILL THROUGH EXISTING FASTENER

INSERT THIN METAL SHEET BETWEEN SKIN AND ANTI−CHAFING PLATE

OPEN UP HOLE IN ANTI−CHAFING PLATE TO 13.5 mm (0.53 in). USE SPOT FACING TOOL

REMOVE METAL SHEET AND REMAINS OF FASTENER

INSERT THIN METAL SHEET BETWEEN SKIN AND ANTI−CHAFING PLATE

OPEN UP HOLE IN ANTI−CHAFING PLATE TO 10.0 mm (0.39 in). USE

SPOT FACING TOOL REMOVE METAL SHEET

02

03

07

02

03

04

01

01 05

06

01

05

01

05

D D

02

03

04

02

03

04

BEFORE

C

C

C

HOLE

SYMBOL

FWD

D_SB_536042_6_BCAA_02_00

Figure A-GBCAA - Sheet 02

Make Cutouts in the FWD and Lower Anti-Chafing Plates

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 69

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

C C

BEFORE

2.5 mm

(0.10 in)

13.5 mm DIA

(0.53 in)

0.3 mm

(0.01 in)

2.5 mm

(0.10 in)

10.0 mm DIA

(0.39 in)

0.3 mm

(0.01 in)

D D

TYPICAL

TYPICAL

D_SB_536042_6_BCAA_03_00

Figure A-GBCAA - Sheet 03

Make Cutouts in the FWD and Lower Anti-Chafing Plates

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 70

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

STGR29LH

STGR30LH

FR88

AFTER

FWD D

FOR FASTENER SYMBOLS, REFER TO SHEET 5

NOTE:

D_SB_536042_6_BCAA_04_01

Figure A-GBCAA - Sheet 04

Make Cutouts in the FWD and Lower Anti-Chafing Plates

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 71

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

HOLE

SYMBOL ITEM P/N DESCRIPTION

NSA5075−5

PIN

COLLAR

DAN6−5−4

A5393402120000 WASHER

DAN12−6X

PIN

COLLAR

DAN8−6−6X

A5398402120200 WASHER

DAN12−6X

PIN

COLLAR

DAN8−6−11X

A5398402120200 WASHER

DAN12−6X

PIN

COLLAR

DAN8−6−12X

A5398402120200 WASHER

DAN12−8X

PIN

COLLAR

DAN8−8−9X

A5398402120400 WASHER

DAN12−8X

PIN

COLLAR

DAN8−8−11X

A5398402120400 WASHER

DAN12−8X

PIN

COLLAR

DAN8−8−12X

A5398402120400 WASHER

DAN12−8X

PIN

COLLAR

DAN8−8−13X

A5398402120400 WASHER

EXISTING ANTICHAFING PLATE FASTENERS

KIT

D02

QTY

9

21

32

33

22

29

34

3

23

29

34

1

24

29

34

1

25

30

35

1

1

1

3

26

30

35

27

30

35

FASTENERS NOT AFFECTED

28

30

35

D_SB_536042_6_BCAA_05_00

Figure A-GBCAA - Sheet 05

Make Cutouts in the FWD and Lower Anti-Chafing Plates

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 72

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

INSPECTION AREA2

INSPECTION AREA1

INSPECTION AREA3

FR86

FR91

FR87

STGR24LH FR89

STGR27LH

STGR24RH

STGR27RH

A

A

Z310

B

B

REMARKS

MIN MAX

5.45 mm

(0.215 in)

5.49 mm

(0.216 in) FIT

HOLE FINAL HOLE DIAMETER

SYMBOL ITEM P/N DESCRIPTION

HLT286−6

PIN

COLLAR

HLT637AP6−14

AN960KD11 WASHER

HLT86−8

PIN

COLLAR

HLT337AP8−14

AN960KD416 WASHER

HLT286−8

PIN

COLLAR

HLT637AP8−13

NSA368PD416B WASHER

HL86−10

PIN

COLLAR

HLT337AP10−13

AN960KD516 WASHER

UNAFFECTED ANTI−CHAFING PLATE ATTACHMENT HOLES

KIT

D03

QTY

4

11

13

12

HOLES NOT AFFECTED

D01

D01

D03

1 (1)

3 (3)

5

01 INSTALL IF NECESSARY

NOTE:

01

15 01

12

14

2 (2)

4 (4)

6 01

16 01

1ST OVERSIZE

INTERFERENCE

FIT

2ND OVERSIZE

INTERFERENCE

FIT

1ST OVERSIZE

INTERFERENCE

FIT

2ND OVERSIZE

INTERFERENCE

6.25 mm

(0.246 in)

6.29 mm

(0.248 in)

7.04 mm

(0.277 in)

7.08 mm

(0.279 in)

7.85 mm

(0.309 in)

7.88 mm

(0.310 in)

6−3−N

6−1−N

8−1−N

8−3−N

START DRILL

CBSD−6−1−N−1

CBSD−6−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

START REAMER

CBSR−6−1−N−1

CBSR−6−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

STDN GAGE FINISH REAMER

CBR−6−1−N−1−.2146

CBR−6−3−N−1−.2461

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

D_SB_536042_6_BDAA_01_01

Figure A-GBDAA - Sheet 01

Inspection Area 3 - Cold Expansion of the Fastener Holes

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 73

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

INSPECTION AREA2

INSPECTION AREA1

INSPECTION AREA3

FR86

FR91

FR87

STGR24LH FR89

STGR27LH

STGR24RH

STGR27RH

A

A

Z310

B

B

REMARKS

MIN MAX

5.45 mm

(0.215 in)

5.49 mm

(0.216 in) FIT

HOLE FINAL HOLE DIAMETER

SYMBOL ITEM P/N DESCRIPTION

HLT286−6

PIN

COLLAR

HLT637AP6−12

AN960KD11 WASHER

HLT86−8

PIN

COLLAR

HLT337AP8−12

AN960KD416 WASHER

HLT86−8

PIN

COLLAR

HLT337AP8−14

AN960KD416 WASHER

HLT86−10

PIN

COLLAR

HLT337AP10−13

AN960KD516 WASHER

UNAFFECTED ANTI−CHAFING PLATE ATTACHMENT HOLES

KIT

D07

QTY

2

22

HOLES NOT AFFECTED

107

01 INSTALL IF NECESSARY

NOTE:

01

01

01

01

1ST OVERSIZE

INTERFERENCE

FIT

2ND OVERSIZE

INTERFERENCE

FIT

2ND OVERSIZE

INTERFERENCE

FIT

2ND OVERSIZE

INTERFERENCE

6.25 mm

(0.246 in)

6.29 mm

(0.248 in)

6.25 mm

(0.246 in)

6.29 mm

(0.248 in)

7.85 mm

(0.309 in)

7.88 mm

(0.310 in)

6−3−N

6−1−N

6−3−N

8−3−N

START DRILL

CBSD−6−1−N−1

CBSD−6−3−N−1

CBSD−6−3−N−1

CBSD−8−3−N−1

START REAMER

CBSR−6−1−N−1

CBSR−6−3−N−1

CBSR−6−3−N−1

CBSR−8−3−N−1

STDN GAGE FINISH REAMER

CBR−6−1−N−1−.2146

CBR−6−3−N−1−.2461

CBR−6−3−N−1−.2461

CBR−8−3−N−1−.3088

4

106

100

108

104

101

108

104

102

109

105

103

D_SB_536042_6_BEAA_01_00

Figure A-GBEAA - Sheet 01

Inspection Area 3 - Secondary Cold Expansion of the Fastener Holes if a Crack is Found in Area

1 after Primary Cold Expansion in Area 3

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 74

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

THE REPAIRED AREA PLUS

10.0 mm (0.394 in) AROUND

THE REPAIR IS BE SHOT PEENED

AREA TO BE SHOT PEENED

OF 50.0 mm (1.969 in) BETWEEN EACH CRACK

MAX 2 CRACKS WITH MIN

TOTAL LENGTH OF CRACK TO BE REPAIRED

MUST NOT EXCEED 2.0 mm (0.079 in)

EXAMPLE OF CRACK REPAIR

MAX 2.0 mm (0.079 in)

MIN R 10.0 mm (0.394 in)

MAX R 20.0 mm (0.787 in)

SKIN STRAP

RH SHOWN

LH SYMMETRICAL

LONGERON

CORNER FITTING

LOWER

OUTER SKIN

B

A

Z310

01

MIN R 10.0 mm (0.394 in)

MAX R 20.0 mm (0.787 in)

AFTER BEFORE

NOTE:

FR86

FR91

FR87

STGR24LH FR89

STGR27LH

STGR24RH

STGR27RH

A

A

E D C

A A

01 01

E

B

A

C D

D_SB_536042_6_BFAA_01_00

Figure A-GBFAA - Sheet 01

Example of Crack Removal in Inspection Area 1

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 75

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

24.0 mm

(0.944 in)

38.0 mm

(1.496 in)

ALTERNATIVELY A NEAREST EQUIVALENT ROUND HEAD BOLTS

CAN BE USED (THE BOLT HEADS MUST BE HARDENED).

ONLY TIGHTEN THE BOLTS ENOUGH TO HOLD

BOLTS 5.0 mm DIA (0.197 in)

ALMEN

TEST STRIP

THE TEST STRIP IN POSITION.

01

NOTE:

01 1.265 mm TO 1.315 mm

(0.050 in TO 0.052 in)

19.0 mm

(0.748 in)

75.82 mm TO 76.58 mm

(2.985 in TO 3.015 in)

(0.709 in)

18.0 mm

(0.709 in)

18.0 mm

(1.575 in)

40.0 mm

18.92 mm TO 19.05 mm

(0.745 in TO 0.750 in)

(0.275 in)

7.0 mm

(0.275 in)

7.0 mm

D_SB_536042_6_BGAA_01_01

Figure A-GBGAA - Sheet 01

Holding Fixture for Almen Test Piece

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 76

6

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@A300-600

SERVICE BULLETIN

**CONF ALL

ALMEN TEST PIECE. THE FACE WHICH IS NOT

PEENED IS PUT NEAREST TO THE DIAL INDICATOR

THE DIAL TEST INDICATOR SHOULD BE

THIS ILLUSTRATION SHOWS THE GENERAL ARRANGEMENT

DIMENSIONS ARE SHOWN).

GRADUATED TO 0.025 mm (0.001 in)

FOR CHECKING THE DEFLECTION OF AN ALMEN TEST

PIECE WITH A DIAL INDICATOR (ONLY THE IMPORTANT

DIAL TEST INDICATOR

CONTACT SURFACE

OF ALL BALLS TO BE

IN ONE PLANE

GUIDE PINS

GUIDE PINS 6.0 mm DIA (0.236 in)

HARDENED STEEL BALLS

01

NOTE:

02

01

5.0 mm (0.197 in)

HARDENED STEEL BALLS

5.0 mm (0.197 in)

GUIDE PINS 6.0 mm DIA (0.236 in)

02

(0.366 in TO 0.374 in)

9.4 mm TO 9.6 mm

(0.366 in TO 0.374 in)

9.4 mm TO 9.6 mm

(0.0788 in TO 0.0792 in)

1.95 mm TO 2.05 mm

(0.624 in) MAX

15.874 mm MAX

(1.575 in)

40.0 mm

(0.622 in TO 0.626 in)

15.78 mm TO 15.97 mm

(0.624 in) MAX

15.874 mm MAX

(2.520 in)

64.0 mm

(1.246 in TO 1.248 in)

31.70 mm TO 31.75 mm

(0.307 in TO 0.317 in)

7.81 mm TO 8.06 mm

D_SB_536042_6_BHAA_01_00

Figure A-GBHAA - Sheet 01

Deflection Measurement Tool for Almen Test Piece

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 77

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

EDGE BEAM STRAP

LOWER CORNER FITTING

SKIN

ARE TO BE COLD EXPANDED

IN LOWER CORNER FITTING ONLY

FASTENER HOLES WITH A SQUARE SYMBOL

LONGERON

B

A

Z310

01

NOTE:

FR86

FR91

FR87

STGR24LH FR89

STGR27LH

STGR24RH

STGR27RH

B

A

A A

FR87

(41)

B

B

C

C

A

A

D

C

5.6 mm TO 5.9 mm DIA

(0.220 in TO 0.232 in) DIA

MIN 5.11 mm (0.201 in) DIA

MAX 5.15 mm (0.203 in) DIA

C C

B B

FOR FASTENER SYMBOLS, REFER TO SHEET 3 AND 4

LH SYMMETRICAL

RH SHOWN

5.2 mm TO 5.5 mm DIA

(0.205 in TO 0.217 in) DIA

MIN 5.11 mm (0.201 in) DIA

MAX 5.15 mm (0.203 in) DIA

01

01

LH

(51)RH

LH

RH

40

(40)

50 LH

(50)RH

D_SB_536042_6_BJAA_01_02

FWD

VIEW LOOKING OUTBOARD

Figure A-GBJAA - Sheet 01

Replacement of the Lower Corner Fitting

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 78

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

STGR21

STGR22

STGR23

STGR24

STGR25

STGR26

E

C

D

E

42

43

FR87

FR87

FR88

NOTE:

FOR FASTENER SYMBOLS, REFER TO SHEET 4

D D

D

D

52

53

LH

RH LH

RH

D_SB_536042_6_BJAA_02_00

Figure A-GBJAA - Sheet 02

Replacement of the Lower Corner Fitting

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 79

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

REMARKS

MIN MAX

5.45 mm

(0.215 in)

5.49 mm

(0.216 in)

HOLE FINAL HOLE DIAMETER

SYMBOL ITEM P/N DESCRIPTION

HLT286−6

PIN

COLLAR

HLT637AP6−14

HLT86−8

PIN

COLLAR

HLT337AP8−14

KIT QTY

4

1ST OVERSIZE

INTERFERENCE FIT 6−1−N

START DRILL

CBSD−6−1−N−1

START REAMER

CBSR−6−1−N−1

STDN GAGE FINISH REAMER

CBR−6−1−N−1−.2146

13

11

1 (1)

3 (3)

D01

D03 6−3−N CBSD−6−3−N−1 CBSR−6−3−N−1 CBR−6−3−N−1−.2461 6.25 mm

(0.246 in)

6.29 mm

(0.248 in)

2ND OVERSIZE

INTERFERENCE FIT

7.04 mm

(0.277 in)

7.08 mm

HLT286−8 (0.279 in)

PIN

COLLAR

HLT637AP8−13

HL86−10

PIN

COLLAR

HLT337AP10−13

12

1ST OVERSIZE

INTERFERENCE FIT 8−1−N CBSD−8−1−N−1 CBSR−8−1−N−1 CBR−8−1−N−1−.2773

14

12

2 (2)

4 (4)

D01

D03 8−3−N CBSD−8−3−N−1 CBSR−8−3−N−1 CBR−8−3−N−1−.3088 7.85 mm

(0.309 in)

7.88 mm

(0.310 in)

2ND OVERSIZE

INTERFERENCE FIT

DAN12−8X

PIN

COLLAR

DAN8−8−12X

DAN12−8X

PIN

COLLAR

DAN8−8−13X

12

1ST OVERSIZE

TRANSITION FIT

HOLE NOT COLD EXPANDED

74

71

70(70)

74(74) D06 6.71 mm

(0.264 in)

6.75 mm

(0.265 in)

OVERSIZE LONG

TRANSITION FIT

6.71 mm

(0.264 in)

6.75 mm

DAN12−8X (0.265 in)

PIN

COLLAR

DAN8−8−8X

DAN14−6

PIN

COLLAR

DAN8−6−11X

16 1ST OVERSIZE

TRANSITION FIT HOLE NOT COLD EXPANDED

69(69)

74(74)

D06

D06 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

1ST OVERSIZE

TRANSITION FIT

68(68)

75(75)

7 HOLE NOT COLD EXPANDED

ALT. 1ST

5.11 mm

(0.201 in)

5.15 mm

DAN12−6X (0.203 in)

PIN

COLLAR

DAN8−6−9X

DAN14−6

PIN

COLLAR

DAN8−6−9X

19 1ST OVERSIZE

TRANSITION FIT HOLE NOT COLD EXPANDED

67(67)

73(73)

D06

D06 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

1ST OVERSIZE

TRANSITION FIT

67(67)

75(75)

3 HOLE NOT COLD EXPANDED

5.11 mm

(0.201 in)

5.15 mm

DAN12−6X (0.203 in)

PIN

COLLAR

DAN8−6−8X

DAN12−6X

PIN

COLLAR

DAN8−6−6X

17 1ST OVERSIZE

TRANSITION FIT HOLE NOT COLD EXPANDED

66(66)

73(73)

D06

D06 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

1ST OVERSIZE

TRANSITION FIT

65(65)

73(73)

27 HOLE NOT COLD EXPANDED

D_SB_536042_6_BJAA_03_00

Figure A-GBJAA - Sheet 03

Replacement of the Lower Corner Fitting

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 80

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

**CONF ALL

ANTI−CHAFING PLATE ATTACHMENT HOLES

TOOLING AND DRAIN HOLES

REMARKS

MIN MAX

HOLE FINAL HOLE DIAMETER

SYMBOL ITEM P/N DESCRIPTION KIT QTY STDN START DRILL START REAMER GAGE FINISH REAMER

5.11 mm

(0.201 in)

5.15 mm

DAN12−6X (0.203 in)

PIN

COLLAR

DAN7−6−8X

DAN12−6X

PIN

COLLAR

DAN7−6−7X

7 1ST OVERSIZE

TRANSITION FIT HOLE NOT COLD EXPANDED

64(64)

73(73)

D06

D06 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

1ST OVERSIZE

TRANSITION FIT

63(63)

73(73)

11 HOLE NOT COLD EXPANDED

5.11 mm

(0.201 in)

5.15 mm

DAN12−6X (0.203 in)

PIN

COLLAR

DAN7−6−6X

DAN12−6

PIN

COLLAR

DAN7−6−5

16 1ST OVERSIZE

TRANSITION FIT HOLE NOT COLD EXPANDED

62(62)

73(73)

D06

D06 4.78 mm

(0.188 in)

4.82 mm

(0.190 in)

STANDARD

TRANSITION FIT

61(61)

72(72)

10 HOLE NOT COLD EXPANDED

LN9198−4012CF RIVET D06 4.06 mm

(0.160 in)

4.17 mm

(0.164 in) 76(76) 20 HOLE NOT COLD EXPANDED STANDARD

HOLES NOT AFFECTED

D_SB_536042_6_BJAA_04_01

Figure A-GBJAA - Sheet 04

Replacement of the Lower Corner Fitting

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 81

6

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@A300-600

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT

(ALTERNATE MOD : NONE)

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 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 1

6

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@A300-600

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 06/94 SERVICE BULLETIN No.: A300-53-6042

REVISION No.: 03 - Aug 30/12 Page: 1

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