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ALERT ALERT

Commercial

Airplanes 767

ALERT ALERT

Service Bulletin

Number: 767-53A0193

Original Issue: November 25, 2008

Revision 1: April 09, 2009

ATA System: 5311

SUBJECT: FUSELAGE - Skins - Inspections of the Fuselage Skin for Scribe Lines

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2008 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable 

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third 

parties. Treatment of the document and the information it contains is governed by contract with Boeing. For 

more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

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Table of Contents

Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 76

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 76

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 77

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 79

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 80

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83

FIGURE 1: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 1) . . . . . . . . . . . 107

FIGURE 2: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 2) . . . . . . . . . . . 109

FIGURE 3: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 3) . . . . . . . . . . . 111

FIGURE 4: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 4) . . . . . . . . . . . 113

FIGURE 5: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 5) . . . . . . . . . . . 115

FIGURE 6: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 6) . . . . . . . . . . . 117

FIGURE 7: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 7) . . . . . . . . . . . 119

FIGURE 8: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 8) . . . . . . . . . . . 121

FIGURE 9: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 9) . . . . . . . . . . . 123

FIGURE 10: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 10) . . . . . . . . . . 125

FIGURE 11: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 11) . . . . . . . . . . 127
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FIGURE 12: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 12) . . . . . . . . . 129

FIGURE 13: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 1) . . . . . . . . . . 131

FIGURE 14: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 2) . . . . . . . . . . 133

FIGURE 15: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 3) . . . . . . . . . . 135

FIGURE 16: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 4) . . . . . . . . . . 137

FIGURE 17: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 5) . . . . . . . . . . 139

FIGURE 18: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 6) . . . . . . . . . . 141

FIGURE 19: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 7) . . . . . . . . . . 143

FIGURE 20: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 8) . . . . . . . . . . 145

FIGURE 21: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 9) . . . . . . . . . . 147

FIGURE 22: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 10) . . . . . . . . . 149

FIGURE 23: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 11) . . . . . . . . . 151

FIGURE 24: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 12) . . . . . . . . . 153

FIGURE 25: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 1) . . . . . . . . . . 155

FIGURE 26: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 2) . . . . . . . . . . 157

FIGURE 27: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 3) . . . . . . . . . . 159

FIGURE 28: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 4) . . . . . . . . . . 161

FIGURE 29: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 5) . . . . . . . . . . 163

FIGURE 30: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 6) . . . . . . . . . . 166

FIGURE 31: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 7) . . . . . . . . . . 169

FIGURE 32: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 8) . . . . . . . . . . 172

FIGURE 33: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 9) . . . . . . . . . . 175

FIGURE 34: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 10) . . . . . . . . . 178

FIGURE 35: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 11) . . . . . . . . . 181

FIGURE 36: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 12) . . . . . . . . . 183

FIGURE 37: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 1) 185

FIGURE 38: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 2) 187

FIGURE 39: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 3) 189

FIGURE 40: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 4) 191

FIGURE 41: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 5) 193

FIGURE 42: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 6) 195

FIGURE 43: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 7) 197

FIGURE 44: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 8) 199

FIGURE 45: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 9) 201

FIGURE 46: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 10) 203

FIGURE 47: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 11) 205

FIGURE 48: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 12) 207

FIGURE 49: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 1) . . . . . . 209

FIGURE 50: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 2) . . . . . . 211

FIGURE 51: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 3) . . . . . . 213

FIGURE 52: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 4) . . . . . . 215

FIGURE 53: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 5) . . . . . . 217

FIGURE 54: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 6) . . . . . . 219

FIGURE 55: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 7) . . . . . . 221

FIGURE 56: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 8) . . . . . . 223

FIGURE 57: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 9) . . . . . . 225
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FIGURE 58: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 10) . . . . . . 227

FIGURE 59: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 11) . . . . . . 229

FIGURE 60: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 12) . . . . . . 231

FIGURE 61: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 1) . . . . . . . . . . . . . . . 233

FIGURE 62: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 2) . . . . . . . . . . . . . . . 235

FIGURE 63: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 3) . . . . . . . . . . . . . . . 237

FIGURE 64: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 4) . . . . . . . . . . . . . . . 239

FIGURE 65: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 5) . . . . . . . . . . . . . . . 241

FIGURE 66: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 6) . . . . . . . . . . . . . . . 243

FIGURE 67: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 7) . . . . . . . . . . . . . . . 245

FIGURE 68: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 8) . . . . . . . . . . . . . . . 247

FIGURE 69: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 9) . . . . . . . . . . . . . . . 249

FIGURE 70: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 10) . . . . . . . . . . . . . . 251

FIGURE 71: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 11) . . . . . . . . . . . . . . 253

FIGURE 72: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 12) . . . . . . . . . . . . . . 255

APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

257

APPENDIX B: REPORTING SYSTEM - LIMITED RETURN TO SERVICE PROCEDURE FOR

AIRPLANES WITH SCRIBE LINES . . . . . . . . . . . . . . . . . . . . . . . . . . . 263

APPENDIX C: AIRPLANE FUSELAGE SCRIBE LINE MARK SUMMARY TABLES . . . . . . . . . . 265

APPENDIX D: SCRIBE LINE SAMPLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 267
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ALERT ALERT

Commercial

Airplanes 767

ALERT ALERT

Service Bulletin

Number: 767-53A0193 Revision Transmittal Sheet

Original Issue: November 25, 2008

Revision 1: April 09, 2009

ATA System: 5311

SUBJECT: FUSELAGE - Skins - Inspections of the Fuselage Skin for Scribe Lines

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service 

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin 

mandatory.

More work is necessary for airplanes that have accomplished skin lap joint inspections as shown in the original 

issue of this service bulletin. Operators that have incorporated the original issue of this service bulletin for the 

skin lap joint inspections must review the REASON FOR REVISION information below, and do additional skin 

lap joint inspections, as necessary, to comply with Revision 1 of this service bulletin. 

If scribe lines were found as a result of the skin lap joint inspections, but not repaired, and the Limited Return to 

Service (LRTS) program was elected, operators must review the LRTS Compliance tables for changes in 

inspection locations and repeat inspection intervals. 

More work may be required if external approved repair inspections were exempted by Compliance Table 2, Note 

(g). Operators that have incorporated the original issue of this service bulletin for the external approved repair 

inspections must review the REASON FOR REVISION information below, and do additional external approved 

repair inspections, as necessary, to comply with Revision 1 of this service bulletin. 

More work may be required if external feature inspections were exempted by Compliance Table 3, Note (e). 

Operators that have incorporated the original issue of this service bulletin for the external feature inspections 

must review the REASON FOR REVISION information below, and do additional external feature inspections, 

as necessary, to comply with Revision 1 of this service bulletin. 

No more work is required for inspections to decals.
 

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REASON FOR REVISION

This revision is sent to change initial inspection locations and LRTS inspection locations and repeat inspection 

intervals for skin lap joint inspections. In addition, caution notes are added to advise operators not to blend 

scribe lines. 

These sections were changed:

1. In Paragraph 1.E., Compliance, Table 1 was changed to clarify footnote (f). 

2. In Paragraph 1.E., Compliance, Table 2 was changed to clarify footnotes (f) and (g) and added footnote (h). 

3. In Paragraph 1.E., Compliance, Table 3 was changed to clarify footnote (e) and added footnote (f). 

4. In Paragraph 1.E., Compliance, Table 4 was changed to clarify footnotes (a) and (d) and remove footnotes 

(b) and (e). 

5. In Paragraph 1.E., Compliance, Tables 5 through 14 were changed for LRTS inspection locations and 

repeat inspection intervals for skin lap joint inspections. 

6. In Paragraph 1.K., Publications Affected, added Damage Tolerance Based Structural Inspection 

information. 

7. In Paragraph 3.A., General Information, Note 16 was added to recommend operators not to blend scribe 

lines.

8. In Paragraph 3.B., Work Instructions, Figures 1 through 36 were changed to reflect changes in affected 

skin lap joint inspection locations.

9. In Paragraph 3.B., Work Instructions, added a Caution to recommend that operators not to blend scribe 

lines to Figures 1 through 72. 

Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity 

paragraph for changes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location 

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

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Revision 1: April 09, 2009
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ALERT ALERT

Commercial

Airplanes 767

ALERT ALERT

Service Bulletin

Number: 767-53A0193 Summary

Original Issue: November 25, 2008

Revision 1: April 09, 2009

ATA System: 5311

SUBJECT: FUSELAGE - Skins - Inspections of the Fuselage Skin for Scribe Lines

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN 

PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE 

BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE 

BULLETIN TO THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect for scribe lines in the fuselage skin at skin lap joints, the skin 

at certain external approved repairs, the skin around external features such as antennas, and the skin at decals. 

Fatigue cracks can develop at scribe line locations. Any crack that remains undetected could grow large and 

cause a rapid decompression.

Thirteen (13) 767 airplanes have been found with scribe line damage by 11 operators. Scribe lines were found 

at skin lap joints, butt joints, around external repairs and antennas, and at locations where decals were cut. 

Many of the scribe lines appear to have been made when sealant was removed as part of preparation of the 

airplane for repainting. The 767 airplanes had between 6300 flight cycles and 24,600 flight cycles. No cracks as 

a result of scribe lines on 767 airplanes have been reported to Boeing. 

A scribe line is a narrow, shallow, distinct line of damage (typically up to 0.006 inch deep), usually associated 

with the removal of a fillet or gap seal (lap joints and butt joints, respectively). A more detailed definition of a 

scribe line is included in Accomplishment Instructions Paragraph 3.B. - Identification of a "Typical" Scribe Line.

A review of fleet activity yields two separate scenarios that are suspected to have caused scribe lines to the 

fuselage skin. 

The first scenario involves the paint stripping and repainting of airplanes. In the process of stripping and 

preparing the airplane for paint, tools were used to remove sealant and paint buildup at lap joints, at certain 

external approved repair doublers or door scuff plates, or around external features. Tools like scrapers (steel, 

wood, hard plastic etc.), knives, or utility knives can damage the skin. Fatigue cracks can develop at scribe line 

locations.
 

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The second scenario is decal application on/or removal from the fuselage. To install the decals across lap joint 

steps or repairs, investigation into maintenance practices has shown that decals have been cut in place, using 

some form of knife, to allow the decal to lie flush to the skin at these stepped locations. This operation results 

in scribe lines at the decal cut location. Based on service reports, sharp tools have also been used for close 

trimming of the decal’s outline. This type of decal trimming has also left scribe lines on the fuselage skin.

The above maintenance operations can each lead to the same type of scribe line damage and subsequent 

premature fatigue cracks.

Boeing Service Related Problem (SRP) 767-SRP-53-0244 is related to this service bulletin.

ACTION

At or before the scribe line inspection thresholds shown in this service bulletin, remove paint and sealant at the 

applicable locations. Do a detailed inspection of the fuselage skin at applicable skin lap joints, external approved 

repairs, external features, and decals for any scribe line or any crack. If any crack is found, contact Boeing for 

repair instructions and do the repair.

When scribe lines are found, they shall be repaired before further flight. As an alternative to immediate repair, 

for a scribe line that qualifies, the provided Limited Return To Service (LRTS) program may be used to allow 

airplanes to return to revenue flight for a limited period before scribe lines are repaired. This service bulletin 

contains a LRTS program.

The LRTS program consists of repeat inspections to detect any crack where scribe lines were found. Total 

airplane flight cycles, location, and extent of scribe line must meet specific criteria in order for a scribe line to 

qualify for a LRTS program. Each affected structural location within a LRTS program will be terminated with a 

repair.

This service bulletin has specific instructions for calculating separate inspection thresholds based on fatigue life 

for the identified locations. With the use of maintenance records, operators can implement the inspection 

program based on potential scribe line opportunities in an airplane’s maintenance history. If this maintenance 

records-based threshold program is not used, then 6,000 flight cycles shall be assigned as the cycle level when 

potential scribing first occurred.

Since a scribe line can occur at any time during the service life of an airplane and at many locations, this program 

uses both total flight cycles and structural criticality of location to determine the inspection requirements. 

Criticality of location allows this service bulletin to address the most critical areas first and to provide less critical 

areas with appropriately reduced compliance requirements. Criticality of location determines the inspection 

thresholds for each location. This service bulletin uses figures and compliance times to address all of the critical 

locations and ranges of inspection thresholds. Each critical piece of structure susceptible to a scribe line is 

assigned to a figure. The affected structure for each group of airplanes is identified in individual figures in this 

service bulletin. 

EFFECTIVITY

767-200, -300, -300F, and -400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected 

airplanes.
 

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COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service 

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin 

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspections or repair procedures given in this service bulletin.

MANPOWER

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

Refer to Paragraph 2.A., Material - Price and Availability.

Airplanes Total Task Hours Elapsed Hours

767-200, 767-300, 767-300F, and 767-400ER 340.0 50.0
 

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DO A DETAILED INSPECTION FOR ANY SCRIBE LINE ALONG SKIN

LAP JOINTS, EXTERNAL FEATURES, EXTERNAL APPROVED

REPAIRS AND DECALS. IF A SCRIBE LINE IS FOUND, DO A

SPECIAL DETAILED INSPECTION FOR ANY CRACK.

1560615
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ALERT ALERT

Commercial

Airplanes 767

ALERT ALERT

Service Bulletin

Number: 767-53A0193

Original Issue: November 25, 2008

Revision 1: April 09, 2009

ATA System: 5311

SUBJECT: FUSELAGE - Skins - Inspections of the Fuselage Skin for Scribe Lines

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN 

PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE 

BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE 

BULLETIN TO THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below. Aircraft Maintenance Manual (AMM) 

changes were released after line number 928 to address proper methods of paint and sealant 

removal to reduce the possibility of scribe damage. 

Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line 

Number, and Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 767-200B, 767-200ER, 767-200ER3 airplanes 

with one Type III over wing exit door and 

forward large cargo door

2 - 767-200B, 767-200ER3 airplanes with one Type 

III over wing exit door and forward small cargo 

door

3 - 767-200ER3 airplanes with two Type III over 

wing exit doors with forward large cargo door

4 - 767-200B airplanes with two Type III over wing 

exit doors with forward small cargo door

5 - 767-300ER4 airplanes with forward entry door, 

Type I emergency exit door, and forward large 

cargo door
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Airplane models:

767-200 767-300 767-300F 767-400ER

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AA 767 LLC (SVX)

1 VE067

ABX AIR (ABX)

2 VA301 VA304–VA305 VA309–VA312 VA314–VA315

VA509 VA803 VA807–VA809 VB101–VB123

VB125

4 VB302

AEROFLOT (ARO)

5 VL896–VL897 VN471–VN472 VS216–VS217 VS321–VS324

9 VS392

AEROMEXICO (AMX)

1 VF071 VF093 VF162

5 VN531 VS211

9 VN166

AEROSVIT (UKA)

9 VN154–VN155 VN157 VS206

AEROTURBINE (AUB)

2 VB051 VB054–VB055

4 VB321 VB331–VB332

6 - 767-300B3 airplanes with forward entry door, 

Type I emergency exit door, and forward small 

cargo door

7 - 767-300ER3 airplanes with forward entry doors, 

one Type III over wing exit door, and forward 

large cargo door

8 - 767-300ER4 airplanes with forward entry doors, 

one Type III over wing exit door, and forward 

small cargo door

9 - 767-300B3, 767-300ER4 airplanes with two 

Type III over wing exit doors with forward large 

cargo door

10 - 767-300B, 767-300B3 airplanes with two Type 

III over wing exit doors with forward small cargo 

door

11 - All 767-300F airplanes

12 - All 767-400ER airplanes

GROUP CONFIGURATION DESCRIPTION
 

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ALERT ALERT

AIR ALGERIE (ALG)

6 VK131–VK133

AIR ASTANA (AKZ)

5 VL899–VL900

AIR CANADA (ACN)

1 VA701–VA709 VA711–VA719 VB001–VB002

2 VB201–VB202

5 VN541 VN546–VN547

9 VN051–VN054 VN056–VN062 VN751–VN752 VN811–VN812

VN931–VN936 VS381–VS382 VS546–VS549

AIR CHINA (BEJ)

1 VE085–VE086

7 VK161–VK164

9 VS208 VS274

AIR DO (HIA)

9 VS176–VS177

AIR EUROPA (ARE)

9 VS292–VS293

AIR ITALY (RIT)

1 VF001–VF002

5 VL913

AIR MADAGASCAR (MAD)

5 VN556

9 VN167

AIR NEW ZEALAND (ANZ)

9 VN653 VN655–VN658

AIR PACIFIC (APC)

9 VN676

AIR SEYCHELLES (ASY)

1 VE104

4 VB301

9 VL941 VS526

AIR TRANSPORT INTERNATIONAL (TIN)

2 VA313 VA511–VA512

AIR ZIMBABWE (ZMB)

1 VF061–VF062

ALITALIA (ALI)

9 VN424 VN427
 

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ALERT ALERT

ALITALIA COMPAGNIA AEREA ITALIANA SPA (ILQ)

9 VL701–VL702 VN426 VN732 VN813

VS367

ALL NIPPON AIRWAYS (ANA)

10 VK081–VK113 VR401

11 VT501

9 VN191–VN198 VS721–VS731

AMERICAN AIRLINES (AAL)

2 VA501–VA505 VA514–VA523 VA525 VA527–VA530

9 VN001–VN041 VS196–VS203 VS751–VS759

AMERIJET INTERNATIONAL (AMJ)

2 VA303 VA306

ARAMCO ASSOCIATED COMPANY (RAS)

1 VR084

ARKEFLY (HXL)

9 VN156 VN164–VN165

ASIANA AIRLINES (AAR)

11 VW851

9 VK143–VK148 VR426

ATLANT-SOYUZ (AYZ)

1 VF051

AUSTRIAN AIRLINES AG (AUL)

7 VN242–VN243

9 VN671 VS301–VS303

AVIANCA (AVI)

1 VE171–VE172 VF072 VF092 VF161

5 VN532

9 VN152

AWAS (AWW)

4 VB325

5 VS308

9 VN651

BELAIR AIRLINES (BLB)

9 VL932

BELLVIEW AIRLINES (BEB)

1 VE125–VE126

BLUE CITY HOLDING (BCY)

1 VE069
 

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ALERT ALERT

BLUE PANORAMA AIRLINES (BPA)

10 VN681

7 VN174 VS061

BOEING (TBC)

2 VA001

BOEING CAPITAL CORPORATION (ZMF)

1 VE117

BRISTOL AIR LIMITED (BMD)

2 VA804

BRITISH AIRWAYS (BAB)

5 VN111–VN114 VN118–VN122 VN124–VN127 VN133–VN137

VS246–VS248

CARGOJET AIRWAYS LTD. (WNT)

2 VA510 VA513

CHILEAN AIR FORCE (CHF)

5 VN561

CHINA EASTERN AIRLINES (CEA)

5 VL871–VL873

CONDOR (CDF)

10 VN683–VN691

CONTINENTAL AIRLINES (CAL)

1 VR051–VR060

12 VQ071–VQ086

CROCUS CORPORATION (CCS)

9 VS825

CSDS AVIATION (CSO)

2 VA506–VA507

DELTA AIR LINES (DAL)

10 VK036 VK039–VK056 VR471–VR472

12 VQ001–VQ021

2 VA302

7 VL753 VN301–VN306

9 VN251–VN276 VS066–VS070 VS073–VS078 VS266–VS273

VS466–VS472

EL AL ISRAEL AIRLINES (ELA)

10 VN682

2 VB281 VB283–VB284

3 VF101–VF102

5 VN537

9 VN972
 

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ALERT ALERT

ERITREAN AIR LINES (ERJ)

1 VE066

ETHIOPIAN AIRLINES (ETH)

5 VL898 VN388 VS306 VS881–VS882

7 VS496–VS497 VS506–VS507

EUROATLANTIC AIRWAYS (MAE)

5 VN551 VN562

9 VN055 VN151

EVERGREEN MAINTENANCE CENTER (EAC)

1 VE061

FIRST AIR (BRS)

2 VA508

FLORIDA WEST INTERNATIONAL (PAI)

11 VR260

FLYGLOBESPAN.COM (FGS)

5 VL891

9 VN654 VS112–VS113

GA TELESIS, LLC (GTG)

4 VB326

GABON AIRLINES (GBO)

2 VA017–VA018

GECAS (GEF)

9 VN731 VS366

GENERIC CUSTOMER/SUPPLIER (XXX)

1 VE002 VE041 VE063

2 VA005

GOL AIRLINES (GOT)

1 VF171

5 VN557 VN637 VS307

9 VN163 VN225 VN753

GUGGENHEIM AVIATION PARTNERS (GPR)

9 VN153

GULF AIR (GUL)

7 VN310 VN314

HAINAN AIRLINES (HNA)

5 VS426–VS428
 

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ALERT ALERT

HAWAIIAN AIRLINES (HWI)

10 VK031–VK034

5 VN381 VS309–VS311

8 VN171–VN173

9 VS821–VS824 VS841–VS843

HEWA BORA AIRWAYS (EXD)

1 VE021

HIS MAJESTY THE SULTAN'S FLIGHT (BWN)

1 VF180

ICELANDAIR (ICE)

7 VN211

9 VN158

ILFC (ILF)

5 VL893

7 VN635

9 VS401

INTEGRATED DEFENSE SYSTEMS (BAC)

1 VV001

2 VA806

ITALIAN AIR FORCE (ZSV)

1 VR086

ITOCHU CORPORATION (CIT)

2 VF181–VF184

JAL INTERNATIONAL (JAL)

10 VK001–VK016 VR441

2 VB371–VB373

9 VK021–VK022 VK181 VK186 VR461

VS701–VS711

JETAIRFLY (TLB)

7 VN234

JORDAN AVIATION (JOR)

4 VB327 VB329–VB330

KALAIR (BERMUDA) (KLB)

7 VN311

KAM AIR (KMC)

2 VA019

KENYA AIRWAYS (KEN)

5 VN421 VS331–VS333

7 VL003

9 VK141
 

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ALERT ALERT

KRASAIR (ZXD)

1 VE001 VE022–VE023

LAN AIRLINES (LAN)

11 VR251 VR256–VR259

9 VL703 VN063–VN064 VN168 VN966–VN971

VS111 VS131–VS133

LOT POLISH AIRLINES (LOT)

7 VN233

9 VN291–VN293 VN652

MALEV HUNGARIAN AIRLINES LTD. (HGA)

1 VF172

MARTINAIR HOLLAND (MTH)

5 VN385

9 VN221–VN224 VN672

MEXICANA (CMA)

1 VF041–VF042

7 VL001–VL002

MID EAST JET (SKL)

1 VF251

NEOS (NEO)

5 VL892 VL894

NORTH AMERICAN AIRLINES (NNA)

5 VL895 VL911 VN922 VS316

7 VL755 VN634

OCEANAIR AIRLINES (OAL)

5 VN376

9 VN495 VN500

PACE AIRLINES (PIE)

2 VB053

PHOENIX AIRCRAFT LEASING, INC. (PLB)

2 VA810

PRESIDENTIAL FLIGHT (ABD)

9 VS391

PRIVATAIR (PTS)

5 VS137

PTC AEROSPACE (PTE)

2 VB282
 

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ALERT ALERT

QANTAS (QAN)

5 VN115–VN117 VN123 VN130–VN132

9 VN081–VN099 VS186–VS187 VS486

ROSSIYA RUSSIAN AIRLINES (STG)

5 VS261–VS263

ROYAL AIR MAROC (RAM)

5 VS336–VS337

7 VN636

9 VS291

ROYAL BRUNEI AIRLINES (RBA)

5 VN372 VN382–VN384 VN386–VN387

RYAN INTERNATIONAL AIRLINES (RYN)

10 VK035 VK038

7 VL011

S7 AIRLINES (SBR)

5 VN638 VS136

9 VN436

SAFI AIRWAYS (FFI)

1 VE084

SHANGHAI AIRLINES (SHA)

9 VK171 VR421–VR423 VS207

SKY HOLDING COMPANY (PSH)

9 VL931

SKY KING (SKN)

1 VE064

SKYMARK AIRLINES (SKM)

9 VS231 VS861

SKYSTAR (SYW)

2 VA008 VA011–VA012 VA020

SMARTLYNX AIRLINES (LCH)

5 VN536 VN542

SOJITZ CORPORATION (SOJ)

7 VN231–VN232

STAR AIR (SBJ)

1 VE101–VE103

2 VA307–VA308 VB441–VB444

4 VB323 VB328
 

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ALERT ALERT

STATE AIR COMPANY "BERKUT" (ORE)

1 VR081

TAA (TNL)

2 VA002–VA004 VA007 VA014–VA015

TAM (TPR)

9 VN422–VN423 VN425

TAMPA CARGO (TMP)

1 VE121–VE124

TEEBAH AIRLINES (EBH)

1 VA710

THOMAS COOK AIRLINES UK (JMA)

5 VN951–VN953

THOMSON AIRWAYS (BRI)

5 VL914 VN921 VS051–VS056

7 VL751–VL752 VL754 VN791–VN792

TRANSAERO AIRLINES (TRX)

1 VE116 VE118 VE143

5 VN371 VN631–VN633

7 VN307–VN309 VN313

TRANSATLANTIC INTL AIRLINES (TIB)

2 VA016

TUIFLY NORDIC (TNS)

5 VL912

TURKMENISTAN AIRLINES (TUE)

5 VS891

UNITED AIR LINES (UAL)

9 VN491–VN494 VN496–VN499 VN501–VN513 VS091–VS104

UPS (UPS)

11 VR201–VR211 VW701–VW721

US AIRWAYS (USA)

1 VE141–VE142 VE144–VE149 VE151–VE152

UZBEKISTAN AIRWAYS (UZB)

5 VL806–VL807

9 VS844 VS896

VISION AIR (VEG)

2 VA006 VA009–VA010
 

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ALERT ALERT

VIVA MACAU (VMC)

1 VF091

9 VK142

WELLS FARGO (FSB)

7 VL004–VL006

WELLS FARGO BANK (ZWR)

1 VE068

WEST DOVER LLC (WDR)

10 VK037

YONA (IOP)

7 VN312

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

VA001–VA020 2

VA301–VA315 2

VA501–VA530 2

VA701–VA719 1

VA801–VA810 2

VB001–VB002 1

VB051–VB055 2

VB101–VB125 2

VB201–VB202 2

VB251–VB253 2

VB281–VB284 2

VB301–VB302 4

VB321–VB332 4

VB371–VB373 2

VB401 1

VB441–VB444 2

VE001–VE003 1

VE021–VE023 1

VE041–VE043 1

VE061–VE069 1

VE083–VE086 1

VE101–VE104 1

VE116–VE118 1

VE121–VE126 1

VE141–VE152 1
 

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ALERT ALERT

VE171–VE172 1

VF001–VF002 1

VF041–VF042 1

VF051 1

VF061–VF062 1

VF071–VF072 1

VF091–VF093 1

VF101–VF102 3

VF161–VF162 1

VF171–VF172 1

VF180 1

VF181–VF184 2

VF251 1

VK001–VK016 10

VK021–VK022 9

VK031–VK056 10

VK081–VK113 10

VK131–VK133 6

VK141–VK148 9

VK161–VK164 7

VK171 9

VK181 9

VK186 9

VL001–VL006 7

VL011 7

VL701–VL703 9

VL751–VL755 7

VL806–VL807 5

VL871–VL873 5

VL891–VL900 5

VL911–VL914 5

VL931–VL932 9

VL941 9

VN001–VN041 9

VN051–VN064 9

VN081–VN099 9

VN111–VN127 5

VN130–VN137 5

VN151–VN158 9

Variable Group
 

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VN163–VN168 9

VN171–VN173 8

VN174 7

VN191–VN198 9

VN211–VN212 7

VN221–VN225 9

VN231–VN234 7

VN241–VN243 7

VN251–VN276 9

VN291–VN293 9

VN301–VN314 7

VN371–VN372 5

VN376 5

VN381–VN388 5

VN421 5

VN422–VN427 9

VN436 9

VN471–VN472 5

VN491–VN513 9

VN531–VN532 5

VN536–VN537 5

VN541–VN542 5

VN546–VN547 5

VN551 5

VN556–VN557 5

VN561–VN562 5

VN631–VN633 5

VN634–VN636 7

VN637–VN638 5

VN651–VN658 9

VN671–VN672 9

VN676 9

VN681–VN691 10

VN731–VN732 9

VN751–VN753 9

VN791–VN792 7

VN811–VN813 9

VN921–VN922 5

VN931–VN936 9

Variable Group
 

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ALERT ALERT

VN951–VN953 5

VN966–VN972 9

VQ001–VQ021 12

VQ071–VQ086 12

VR051–VR060 1

VR081 1

VR084 1

VR086 1

VR201–VR211 11

VR251 11

VR256–VR260 11

VR401 10

VR421–VR423 9

VR426 9

VR441 10

VR461 9

VR471–VR472 10

VS051–VS056 5

VS061 7

VS066–VS070 9

VS073–VS078 9

VS091–VS104 9

VS111–VS113 9

VS131–VS133 9

VS136–VS137 5

VS176–VS177 9

VS186–VS187 9

VS196–VS203 9

VS206–VS208 9

VS211 5

VS216–VS217 5

VS231 9

VS246–VS248 5

VS261–VS263 5

VS266–VS274 9

VS291–VS293 9

VS301–VS303 9

VS306–VS311 5

VS316 5

Variable Group
 

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ALERT ALERT

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect for scribe lines in the fuselage skin at skin lap joints, 

the skin at certain external approved repairs, the skin around external features such as antennas, and 

the skin at decals. Fatigue cracks can develop at scribe line locations. Any crack that remains 

undetected could grow large and cause a rapid decompression.

VS321–VS324 5

VS331–VS333 5

VS336–VS337 5

VS366–VS367 9

VS381–VS382 9

VS391–VS392 9

VS401 9

VS426–VS428 5

VS466–VS472 9

VS486 9

VS496–VS497 7

VS506–VS507 7

VS526 9

VS546–VS549 9

VS701–VS711 9

VS721–VS731 9

VS751–VS759 9

VS821–VS825 9

VS841–VS844 9

VS861 9

VS881–VS882 5

VS891 5

VS896 9

VT501 11

VV001 1

VW701–VW721 11

VW851 11

Variable Group
 

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ALERT ALERT

Thirteen (13) 767 airplanes have been found with scribe line damage by 11 operators. Scribe lines 

were found at skin lap joints, butt joints, around external repairs and antennas, and at locations where 

decals were cut. Many of the scribe lines appear to have been made when sealant was removed as 

part of preparation of the airplane for repainting. The 767 airplanes had between 6300 flight cycles 

and 24,600 flight cycles. No cracks as a result of scribe lines on 767 airplanes have been reported to 

Boeing. 

A scribe line is a narrow, shallow, distinct line of damage (typically up to 0.006 inch deep), usually 

associated with the removal of a fillet or gap seal (lap joints and butt joints, respectively). A more 

detailed definition of a scribe line is included in Accomplishment Instructions Paragraph 3.B. - 

Identification of a "Typical" Scribe Line.

A review of fleet activity yields two separate scenarios that are suspected to have caused scribe lines 

to the fuselage skin. 

The first scenario involves the paint stripping and repainting of airplanes. In the process of stripping 

and preparing the airplane for paint, tools were used to remove sealant and paint buildup at lap joints, 

at certain external approved repair doublers or door scuff plates, or around external features. Tools 

like scrapers (steel, wood, hard plastic etc.), knives, or utility knives can damage the skin. Fatigue 

cracks can develop at scribe line locations.

The second scenario is decal application on/or removal from the fuselage. To install the decals across 

lap joint steps or repairs, investigation into maintenance practices has shown that decals have been 

cut in place, using some form of knife, to allow the decal to lie flush to the skin at these stepped 

locations. This operation results in scribe lines at the decal cut location. Based on service reports, 

sharp tools have also been used for close trimming of the decal’s outline. This type of decal trimming 

has also left scribe lines on the fuselage skin.

The above maintenance operations can each lead to the same type of scribe line damage and 

subsequent premature fatigue cracks.

Boeing Service Related Problem (SRP) 767-SRP-53-0244 is related to this service bulletin.

This revision is sent to change initial inspection locations and LRTS inspection locations and repeat 

inspection intervals for skin lap joint inspections. In addition, caution notes are added to advise 

operators not to blend scribe lines. 

These sections were changed:

1. In Paragraph 1.E., Compliance, Table 1 was changed to clarify footnote (f). 

2. In Paragraph 1.E., Compliance, Table 2 was changed to clarify footnotes (f) and (g) and add 

footnote (h). 

3. In Paragraph 1.E., Compliance, Table 3 was changed to clarify footnote (e) and add footnote (f). 

4. In Paragraph 1.E., Compliance, Table 4 was changed to clarify footnotes (a) and (d) and remove 

footnotes (b) and (e). 

5. In Paragraph 1.E., Compliance, Tables 5 through 14 were changed for LRTS inspection locations 

and repeat inspection intervals for skin lap joint inspections. 
 

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ALERT ALERT

6. In Paragraph 1.K., Publications Affected, added Damage Tolerance Based Structural Inspection 

information. 

7. In Paragraph 3.A., General Information, Note 16 was added to advise operators not to blend 

scribe lines.

8. In Paragraph 3.B., Work Instructions, Figures 1 through 36 were changed to reflect changes in 

affected skin lap joint inspection locations.

9. In Paragraph 3.B., Work Instructions, a Caution note that advises operators not to blend scribe 

lines was added to Figures 1 through 72. 

D. Description

At or before the scribe line inspection thresholds shown in this service bulletin, remove paint and 

sealant at the applicable locations. Do a detailed inspection of the fuselage skin at applicable skin lap 

joints, external approved repairs, external features, and decals for any scribe line or any crack. If any 

crack is found, contact Boeing for repair instructions and do the repair.

When scribe lines are found, they shall be repaired before further flight. As an alternative to immediate 

repair, for a scribe line that qualifies, the provided Limited Return To Service (LRTS) program may be 

used to allow airplanes to return to revenue flight for a limited period before scribe lines are repaired. 

This service bulletin contains a LRTS program.

The LRTS program consists of repeat inspections to detect any crack where scribe lines were found. 

Total airplane flight cycles, location, and extent of scribe line must meet specific criteria in order for a 

scribe line to qualify for a LRTS program. Each affected structural location within a LRTS program will 

be terminated with a repair.

This service bulletin has specific instructions for calculating separate inspection thresholds based on 

fatigue life for the identified locations. With the use of maintenance records, operators can implement 

the inspection program based on potential scribe line opportunities in an airplane’s maintenance 

history. If this maintenance records-based threshold program is not used, then 6,000 flight cycles shall 

be assigned as the cycle level when potential scribing first occurred.

Since a scribe line can occur at any time during the service life of an airplane and at many locations, 

this program uses both total flight cycles and structural criticality of location to determine the 

inspection requirements. 

Criticality of location allows this service bulletin to address the most critical areas first and to provide 

less critical areas with appropriately reduced compliance requirements. Criticality of location 

determines the inspection thresholds for each location. This service bulletin uses figures and 

compliance times to address all of the critical locations and ranges of inspection thresholds. Each 

critical piece of structure susceptible to a scribe line is assigned to a figure. The affected structure for 

each group of airplanes is identified in individual figures in this service bulletin. 

Revision 1 - More work is necessary for airplanes that have accomplished skin lap joint inspections 

as shown in the original issue of this service bulletin. Operators that have incorporated the original 

issue of this service bulletin for the skin lap joint inspections must review the REASON FOR 

REVISION information below, and do additional skin lap joint inspections, as necessary, to comply 

with Revision 1 of this service bulletin. 
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

If scribe lines were found as a result of the skin lap joint inspections, but not repaired, and the Limited 

Return to Service (LRTS) program was elected, operators must review the LRTS Compliance tables 

for changes in inspection locations and repeat inspection intervals. 

More work may be required if external approved repair inspections were exempted by Compliance 

Table 2, Note (g). Operators that have incorporated the original issue of this service bulletin for the 

external approved repair inspections must review the REASON FOR REVISION information below, 

and do additional external approved repair inspections, as necessary, to comply with Revision 1 of 

this service bulletin. 

More work may be required if external feature inspections were exempted by Compliance Table 3, 

Note (e). Operators that have incorporated the original issue of this service bulletin for the external 

feature inspections must review the REASON FOR REVISION information below, and do additional 

external feature inspections, as necessary, to comply with Revision 1 of this service bulletin. 

No more work is required for inspections to decals.

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to 

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in 

this service bulletin mandatory.

Inspection zone thresholds are based upon analysis of fuselage geometry and loads. Zone 1 has the 

lowest inspection threshold and Zone 3 has the highest inspection threshold. 

This service bulletin has four (4) areas for scribe line inspections. The areas are as follows:

— Skin Lap Joints

— External Approved Repairs

— External Features

— Decals

The Compliance tables are broken down into three main sections as follows:

1. Tables 1 through 4 are used to show the initial scribe line inspection for the four (4) areas to be 

inspected. 

2. Tables 5 through 20 are used to show the LRTS repeat inspection intervals for the four (4) areas 

to be inspected. 

NOTE: Pay close attention to the Group Number and Inspection Area in the title of the table.

3. Table 21 is used to show the repeat inspection intervals for Accomplishment Instructions 

Paragraph 3.B - Part 8. 
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 1-12: Table 1 - Skin Lap Joint - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)

All Airplanes

Skin Lap Joints

Zone 1

Do a detailed inspection for any 

scribe line using the tables as given 

in the Accomplishment Instructions 

Paragraph 3.B - Part 2. 

(d) (e) (f) (g)

Before 25,000 

total flight 

cycles plus first 

scribe line 

opportunity. (a)

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service bulletin.

-

All Airplanes

Skin Lap Joints

Zone 2

Do a detailed inspection for any 

scribe line using the tables as given 

in the Accomplishment Instructions 

Paragraph 3.B - Part 2. 

(d) (e) (f) (g)

Before 37,500 

total flight 

cycles plus first 

scribe line 

opportunity. (a)

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service bulletin.

-

All Airplanes

Skin Lap Joints

Zone 3

Do a detailed inspection for any 

scribe line using the tables as given 

in the Accomplishment Instructions 

Paragraph 3.B - Part 2.

(d) (e) (f) (g)

Before 50,000 

total flight 

cycles plus first 

scribe line 

opportunity. (a)

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service bulletin.

-

No scribe line or 

damage is 

found.(c) 

No further inspections are required.

(b)

---

Any scribe line is 

found. (c)

Measure the scribe line depth as 

given in Accomplishment 

Instructions Paragraph 3.B - Part 4.

Before further 

flight.

- -

Scribe line is 

found less than 

0.001 inch deep. 

(c)

No further inspections are required. 

(b)

---

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch 

deep. (c)

Do High Frequency Eddy Current 

(HFEC) and/or Ultrasonic (UT) 

special detailed inspections for any 

crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5. 

Before further 

flight.

- -

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than 0.006 

inch deep. (c)

Do High Frequency Eddy Current 

(HFEC) and/or Ultrasonic (UT) 

special detailed inspections for any 

crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5. 

Before further 

flight.

- -

And

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If no crack is 

found and the 

scribe line is 

greater than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch.

Do the repeat inspections as given 

in Accomplishment Instructions 

Paragraph 3.B - Part 6.

Before repeat 

intervals in 

Tables 5-14.

- Refer to the 

LRTS Tables 5-

14 for repeat 

intervals.

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If any crack is 

found.

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

All airplanes with 

scribe line using 

a LRTS program 

inspection.

Contact Boeing for additional 

inspections or repair.

Before 50,000 

total flight 

cycles.

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service bulletin.

-

(a) First scribe line opportunity is provided by maintenance records. Adjust the compliance time as given 

below: 

1. If record of first paint since delivery is available, then add the airplane flight cycles at first paint to 

the threshold.

2. If record of first paint since delivery is not available, add 6,000 flight cycles to the threshold.

(b) No further inspections are required at this location, provided that the correct sealant removal procedure 

is used for all future work. Refer to Appendix A of this service bulletin as an accepted sealant removal 

procedure. 

(c) Refer to Accomplishment Instructions Paragraph 3.B for identification of a typical scribe line.

(d) If operator’s records show that the airplane has never been stripped or repainted since delivery from 

Boeing and correct sealant removal procedure is implemented for all future work, then the skin lap joint 

inspections are not required, except as noted in (g) below. Refer to Appendix A of this service bulletin as 

an accepted sealant removal procedure.

Group 1-12: Table 1 - Skin Lap Joint - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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ALERT ALERT

(e) If the operator’s records show that the airplane has never been stripped or repainted under the wing-tobody fairings since delivery from Boeing and correct sealant removal procedure is implemented for all 

future work, then the skin lap joint inspections in the areas under the wing-to-body fairing are not 

required. Refer to Appendix A of this service bulletin as an accepted sealant removal procedure.

(f) If the operator’s records show that correct sealant removal procedures have been used at all times 

since delivery, then the skin lap joint inspections are not required, except as noted in (g) below. Refer to 

Appendix A of this service bulletin as an accepted sealant removal procedure.

(g) If a decal is installed, or was previously installed, across a skin lap joint that requires inspection, the 

inspection exemption per note (d) and (f) does not apply. The skin lap joint inspection must still be done 

for the affected skin lap joint at the threshold as given in this table.

Group 1-12: Table 2 - External Approved Repairs - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)

All Airplanes

External 

Approved 

Repairs - 20 

inches or longer 

on any side

Zone 1

Do a detailed inspection for any 

scribe line using the tables as given 

in the Accomplishment Instructions 

Paragraph 3.B - Part 2. 

(d) (e) (f) (g) (h)

Before 25,000 

total flight 

cycles plus first 

scribe line 

opportunity. (a)

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

All Airplanes

External 

Approved 

Repairs - Less 

than 20 inches on 

all sides

Zone 1

Do a detailed inspection for any 

scribe line using the tables as given 

in the Accomplishment Instructions 

Paragraph 3.B - Part 2.

(d) (e) (f) (g) (h)

Before 25,000 

total flight 

cycles plus first 

scribe line 

opportunity. (a)

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

No scribe line or 

damage is 

found.(c) 

No further inspections are 

required.(b)

- --

Any scribe line is 

found. (c)

Measure the scribe line depth as 

given in Accomplishment 

Instructions Paragraph 3.B - Part 4.

Before further 

flight.

- -

Scribe line is 

found less than 

0.001 inch deep. 

(c)

No further inspections are required. 

(b)

- --

Group 1-12: Table 1 - Skin Lap Joint - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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ALERT ALERT

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch 

deep. (c)

Do High Frequency Eddy Current 

(HFEC) and/or Ultrasonic (UT) 

special detailed inspections for any 

crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5.

Before further 

flight.

- -

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than 0.006 

inch deep. (c)

Do High Frequency Eddy Current 

(HFEC) and/or Ultrasonic (UT) 

special detailed inspections for any 

crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5.

Before further 

flight.

- -

And 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If no crack is 

found and the 

scribe line is 

greater than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch. 

Do the repeat inspections as given 

in Accomplishment Instructions 

Paragraph 3.B - Part 6.

Before the 

compliance 

times in Table 

15.

- Refer to the LRTS 

Table 15 for repeat 

intervals.

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If any crack is 

found.

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

All airplanes with 

scribe line using 

a LRTS program 

inspection.

Contact Boeing for additional 

inspections or repair.

Before 50,000 

total flight 

cycles.

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

(a) First scribe line opportunity is provided by maintenance records. Adjust the compliance time as given 

below: 

1. If record of first paint since delivery is available, then add the airplane flight cycles at first paint to 

the threshold.

2. If record of first paint since delivery is not available, add 6,000 flight cycles to the threshold.

(b) No further inspections are required at this location, provided that the correct sealant removal procedure 

is used for all future work. Refer to Appendix A of this service bulletin as an accepted sealant removal 

procedure. 

Group 1-12: Table 2 - External Approved Repairs - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

(c) Refer to Accomplishment Instructions Paragraph 3.B for identification of a typical scribe line.

(d) If operator’s records show that the airplane has never been stripped or repainted since delivery from 

Boeing and correct sealant removal procedure is implemented for all future work, then the external 

approved repair inspections are not required, except as noted in (g) below. Refer to Appendix A of this 

service bulletin as an accepted sealant removal procedure.

(e) If the operator’s records show that the airplane has never been stripped or repainted under the wing-tobody fairings since delivery from Boeing and correct sealant removal procedure is implemented for all 

future work, then the external approved repair inspections in the areas under the wing-to-body fairing 

are not required. Refer to Appendix A of this service bulletin as an accepted sealant removal procedure.

(f) If the operator’s records show that correct sealant removal procedures have been used at all times 

since delivery, then the external approved repair inspections are not required, except as noted in (g) 

below. Refer to Appendix A of this service bulletin as an accepted sealant removal procedure.

(g) For each repair, if operator’s records show that the airplane has never been stripped or repainted since 

the repair has been installed, then the external approved repair inspections for the specific repair are not 

required, except as noted in (h) below. 

(h) If a decal is installed, or was previously installed across an external approved repair, the exemption per 

note (g) does not apply. The external approved repair inspection must still be done for the affected 

external approved repair at the threshold as given in this table.

Group 1-12: Table 3 - External Features - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)

All Airplanes

External 

Features

Zone 2

Do a detailed inspection for any 

scribe line using the tables as given 

in the Accomplishment Instructions 

Paragraph 3.B - Part 2. 

(d) (e) (f)

Before 37,500 

total flight 

cycles plus first 

scribe line 

opportunity. (a)

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service bulletin.

-

No scribe line or 

damage is 

found.(c) 

No further inspections are 

required.(b)

---

Any scribe line is 

found. (c)

Measure the scribe line depth as 

given in Accomplishment 

Instructions Paragraph 3.B - Part 4.

Before further 

flight.

- -

Scribe line is 

found less than 

0.001 inch deep. 

(c)

No further inspections are required. 

(b)

---

Group 1-12: Table 2 - External Approved Repairs - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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ALERT ALERT

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch 

deep. (c)

Do High Frequency Eddy Current 

(HFEC) and/or Ultrasonic (UT) 

special detailed inspections for any 

crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5.

Before further 

flight.

- -

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than 0.006 

inch deep. (c)

Do High Frequency Eddy Current 

(HFEC) and/or Ultrasonic (UT) 

special detailed inspections for any 

crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5.

Before further 

flight.

- -

And 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If no crack is 

found and the 

scribe line is 

greater than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch. 

Do the repeat inspections as given 

in Accomplishment Instructions 

Paragraph 3.B - Part 6.

Before repeat 

intervals in 

Tables 16-19.

- Refer to the LRTS 

Tables 16-19 for 

repeat intervals.

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If any crack is 

found.

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

All airplanes with 

scribe line using 

a LRTS program 

inspection.

Contact Boeing for additional 

inspections or repair.

Before 50,000 

total flight 

cycles.

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service bulletin.

-

(a) First scribe line opportunity is provided by maintenance records. Adjust the compliance time as given 

below: 

1. If record of first paint since delivery is available, then add the airplane flight cycles at first paint to 

the threshold.

2. If record of first paint since delivery is not available, add 6,000 flight cycles to the threshold.

(b) No further inspections are required at this location, provided that the correct sealant removal procedure 

is used for all future work. Refer to Appendix A of this service bulletin as an accepted sealant removal 

procedure. 

(c) Refer to Accomplishment Instructions Paragraph 3.B for identification of a typical scribe line.

Group 1-12: Table 3 - External Features - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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ALERT ALERT

(d) If operator’s records show that the airplane has never been stripped or repainted since delivery from 

Boeing and correct sealant removal procedures have been and continue to be implemented for all future 

work, then the external feature inspections are not required. Refer to Appendix A of this service bulletin 

as an accepted sealant removal procedure.

(e) If the operator’s records show that correct sealant removal procedures have been used at all times since 

delivery, then the external feature inspections are not required, except as noted in (f) below. Refer to 

Appendix A of this service bulletin as an accepted sealant removal procedure.

(f) If a decal is installed, or was previously installed across an external feature, the exemption per note (e) 

does not apply. The external feature inspection must still be done for the affected external feature at the 

threshold as given in this table.

Group 1-12: Table 4 - Decals - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)

All Airplanes

Decals

Zone 3

Do a detailed inspection for any 

scribe line using the tables as given 

in the Accomplishment Instructions 

Paragraph 3.B - Part 2. 

(d) 

Before 50,000 

total flight 

cycles plus first 

scribe line 

opportunity. (a)

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

No scribe line or 

damage is 

found.(c) 

No further inspections are required. - - -

Any scribe line is 

found. (c)

Measure the scribe line depth as 

given in Accomplishment 

Instructions Paragraph 3.B - Part 4.

Before further 

flight.

- -

Scribe line is 

found less than 

0.001 inch deep. 

(c)

No further inspections are required. - - -

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch 

deep.(c)

Do High Frequency Eddy Current 

(HFEC) special detailed inspection 

for any crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5.

Before further 

flight.

- -

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

Group 1-12: Table 3 - External Features - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Scribe line is 

found within the 

limits of a typical 

scribe line and 

more than 0.006 

inch deep. (c)

Do High Frequency Eddy Current 

(HFEC) special detailed inspection 

for any crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 5.

Before further 

flight.

- -

And

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If no crack is 

found and the 

scribe line is 

greater than or 

equal to 0.001 

inch deep and 

less than or equal 

to 0.006 inch. 

Do the repeat inspections as given 

in Accomplishment Instructions 

Paragraph 3.B - Part 6.

Before 

compliance 

times in Table 

20.

- Refer to the LRTS 

Table 20 for repeat 

intervals.

Or 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

If any crack is 

found.

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

- -

All airplanes with 

scribe line using 

a LRTS program 

inspection.

Contact Boeing for additional 

inspections or repair.

Before 50,000 

total flight 

cycles.

Within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

(a) First scribe line opportunity is provided by maintenance records. Adjust the compliance time as given 

below. Operator is to use the lowest of the three below adjustments to the threshold in determining first 

scribe line opportunity.

1. If record of first paint since delivery is available, then add the airplane flight cycles at first paint to 

the threshold. 

2. If record of first decal installation is available, then add the airplane flight cycles at first decal 

installation to the threshold.

3. If neither first paint nor first decal installation records are available since delivery, add 6,000 flight 

cycles to the threshold.

(b) Removed at Revision 1 of this Service Bulletin. 

Group 1-12: Table 4 - Decals - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

(c) Refer to Accomplishment Instructions Paragraph 3.B for identification of a typical scribe line.

(d) Decal inspections are not required:

If the operator’s records show the airplane has never had decals installed in the area of inspection since 

delivery.

and

If operator’s records show that the airplane has never been stripped or repainted since delivery from 

Boeing. 

(e) Removed at Revision 1 of this Service Bulletin. 

Group 1, 3: Table 5 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return To Service 

(LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for the 

skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 456 - 2,000

STA 456 - 500 - 2,300

STA 632 - 676 - 2,000

STA 676 - 786 - 2,300

STA 1395 - 1540 - 2,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 434 - 456 - 3,000

STA 654 - 742 - 3,000

STA 1109 - 1175 - 3,000

STA 1175 - 1219 - 4,300

STA 1417 - 1582 - 4,300

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 676 - 764 - 4,000

STA 1087 - 1241 - 4,300

Group 1-12: Table 4 - Decals - Fuselage Skin Scribe Line Inspection

Condition Action

Compliance Time

(Whichever Occurs Later)

Repeat Interval 

(Not to Exceed)
 

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1417 - 1461 - 4,000

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 764 - 3,400

STA 1087 - 1373 - 3,500

STA 1417 - 1461 - 3,000

S-2R STA 434 - 720 - 3,000

STA 720 - 764 - 3,500

STA 1417 - 1562 - 2,500

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 786 - 3,300

STA 1087 - 1373 - 3,400

STA 1373 - 1461 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 632 - 3,500

STA 654 - 742 - 2,600

STA 742 - 786 - 3,000

STA 1065 - 1263 - 3,800

STA 1263 - 1307 - 3,400

STA 1307 - 1329 - 3,000

STA 1329 - 1461 - 3,000

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 588 - 3,500

STA 588 - 632 - 2,400

STA 632 - 764 - 3,300

STA 1153 - 1307 - 3,500

STA 1307 - 1395 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 764 - 2,200

STA 1263 - 1307 - 3,200

STA 1307 - 1351 - 2,200

STA 1417 - 1461 - 3,000

Group 1, 3: Table 5 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1480 - 1540 - 2,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and 

do the repair.

Before further 

flight.

-

All airplanes with scribe 

lines using a LRTS 

program inspection.

Contact Boeing for repair instructions and 

do the repair.

Before 50,000 

total flight cycles 

or within 4,000 

flight cycles after 

the original issue 

date on this 

service bulletin.

-

Group 2, 4: Table 6 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return To Service 

(LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for the 

skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 500 - 2,000 

STA 500 - 544 - 3,500

STA 654 - 786 - 2,500

STA 1395 - 1540 - 2,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 434 - 478 - 2,800

STA 676 - 742 - 3,000

STA 1109 - 1175 - 3,000

STA 1175 - 1219 - 4,300

STA 1417 - 1582 - 4,300

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 500 - 4,000

Group 1, 3: Table 5 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 676 - 764 - 4,000

STA 1087 - 1241 - 4,300

STA 1417 - 1461 - 4,000

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 764 - 3,400

STA 1087 - 1373 - 3,500

STA 1417 - 1461 - 3,000

S-2R STA 434 - 720 - 3,000

STA 720 - 764 - 3,500

STA 1417 - 1562 - 2,500

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 786 - 3,300

STA 1087 - 1373 - 3,400

STA 1373 - 1461 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 632 - 3,500

STA 654 - 742 - 2,600

STA 742 - 786 - 3,000

STA 1065 - 1263 - 3,800

STA 1263 - 1307 - 3,400

STA 1307 - 1329 - 3,000

STA 1329 - 1461 - 3,000

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 588 - 3,500

STA 588 - 632 - 2,400

STA 632 - 764 - 3,300

STA 1153 - 1307 - 3,500

STA 1307 - 1395 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 764 - 2,200

STA 1263 - 1307 - 3,200

Group 2, 4: Table 6 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1307 - 1351 - 2,200

STA 1417 - 1461 - 3,000

STA 1480 - 1540 - 2,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and 

do the repair.

Before further 

flight.

-

All airplanes with scribe 

lines using a LRTS 

program inspection.

Contact Boeing for repair instructions and 

do the repair.

Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

Group 5: Table 7 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return To Service (LRTS) 

Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for the 

skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 478 - 3,000 

STA 654 - 698 - 3,000

STA 1197+66 - 1219 - 3,000

STA 1373 - 1417 - 3,500

STA 1417 - 1562 - 2,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 434 - 456 - 3,800

STA 654+22 - 654+88 - 3,800

STA 654+88 - 698 - 3,000

STA 698 - 764 - 5,000

STA 1153 - 1219 - 4,000

Group 2, 4: Table 6 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1417 - 1582 - 4,500

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 456 - 4,300

STA 1197+22 - 1197+132 - 3,000

STA 1395 - 1461 - 4,000

STA 1562 - 1582 - 4,500

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 654 - 3,400

STA 654+110 - 675 - 4,800

STA 1197+22 - 1197+132 - 2,000

STA 1241 - 1373 - 3,500

STA 1417 - 1461 - 3,400

STA 1562 - 1582 - 4,500

S-2R STA 434 - 654+44 - 3,000

STA 654+44 - 654+88 - 3,500

STA 654+88 - 720 - 4,000

STA 1241 - 1307 - 4,000

STA 1417 - 1582 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 654 - 3,500

STA 1197+22 - 1197+132 - 2,000

STA 1241 - 1373 - 3,500

STA 1562 - 1582 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 654 - 3,500

STA 676 - 720 - 3,500

STA 1197+110 - 1219 - 3,500

STA 1219 - 1263 - 4,000

STA 1307 - 1461 - 3,000

STA 1562 - 1582 - 4,500

Group 5: Table 7 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 610 - 3,500

STA 610 - 654+88 - 2,000

STA 654+88 - 676 - 3,000

STA 676 - 742 - 4,500

STA 1153 - 1285 - 4,000

STA 1285 - 1373 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654 - 2,400

STA 654 - 654+88 - 2,000

STA 654+88 - 654+121 - 3,300

STA 698 - 764 - 3,000

STA 1197+88 - 1219 - 4,000

STA 1241 - 1307 - 3,000

STA 1307 - 1351 - 2,000

STA 1351 - 1461 - 3,000

STA 1502 - 1582 - 2,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and 

do the repair.

Before 

further flight.

-

All airplanes with scribe 

lines using a LRTS program 

inspection.

Contact Boeing for repair instructions and 

do the repair.

Before 

50,000 total 

flight cycles 

or within 

4,000 flight 

cycles after 

the original 

issue date on 

this service 

bulletin.

-

Group 5: Table 7 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 6: Table 8 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return To Service (LRTS) 

Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic (UT) 

special detailed inspections for any crack as 

given in the Accomplishment Instructions 

Paragraph 3.B - Part 6 for the skin lap joint 

areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 522 - 3,000 

STA 566 - 698 - 3,000

STA 1197+66 - 1219 - 3,000

STA 1373 - 1417 - 3,500

STA 1417 - 1562 - 2,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 434 - 478 - 3,000

STA 654+22 - 654+88 - 4,000

STA 654+88 - 698 - 3,000

STA 698 - 764 - 5,000

STA 1153 - 1219 - 4,000

STA 1417 - 1582 - 4,500

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 522 - 4,000

STA 1197+22 - 1197+132 - 3,000

STA 1395 - 1461 - 4,000

STA 1562 - 1582 - 4,500

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 654 - 3,500

STA 654+110 - 676 - 4,500

STA 1197+22 - 1197+132 - 2,000

STA 1241 - 1373 - 3,500

STA 1417 - 1461 - 3,400

STA 1562 - 1582 - 4,500

S-2R STA 434 - 654+44 - 3,000
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 654+44 - 654+88 - 3,500

STA 654+88 - 720 - 4,000

STA 1241 - 1307 - 4,000

STA 1417 - 1582 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 654 - 3,500

STA 654+121 - 764 - 5,000

STA 1197+22 - 1197+132 - 2,000

STA 1241 - 1373 - 3,500

STA 1562 - 1582 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 654 - 3,500

STA 676 - 720 - 4,000

STA 1197+110 - 1219 - 3,500

STA 1219 - 1263 - 4,000

STA 1307 - 1461 - 3,000

STA 1562 - 1582 - 4,500

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 610 - 3,500

STA 610 - 654+88 - 2,000

STA 654+88 - 676 - 3,000

STA 676 - 742 - 5,000

STA 1153 - 1285 - 4,000

STA 1285 - 1373 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654 - 2,400

STA 654 - 654+88 - 2,000

STA 654+88 - 654+121 - 3,300

STA 698 - 764 - 3,000

STA 1197+88 - 1219 - 4,000

STA 1241 - 1307 - 3,000

Group 6: Table 8 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1307 - 1351 - 2,000

STA 1351 - 1461 - 3,000

STA 1502 - 1582 - 2,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and do 

the repair.

Before 

further flight.

-

All airplanes with scribe 

lines using a LRTS 

program inspection.

Contact Boeing for repair instructions and do 

the repair.

Before 

50,000 total 

flight cycles 

or within 

4,000 flight 

cycles after 

the original 

issue date on 

this service 

bulletin.

-

Group 7: Table 9 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe Lines 

using a Limited Return To 

Service (LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for the 

skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 478 - 3,000 

STA 654 - 698 - 3,000

STA 1197+66 - 1219 - 3,000

STA 1373 - 1417 - 3,500

STA 1417 - 1502 - 2,000

STA 1518 - 1562 - 3,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000

STA 434 - 456 - 3,800

STA 654+22 - 654+88 - 3,800

STA 654+88 - 698 - 3,000

STA 698 - 764 - 5,000

Group 6: Table 8 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1175 - 1219 - 4,000

STA 1417 - 1582 - 4,500

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 456 - 4,300

STA 1109 - 1197+22 - 3,000

STA 1395 - 1461 - 3,500

STA 1562 - 1582 - 4,500

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 654 - 3,400

STA 654+110 - 676 - 4,800

STA 1087 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,300

STA 1241 - 1373 - 3,500

STA 1417 - 1461 - 3,500

STA 1562 - 1582 - 4,500

S-2R STA 434 - 654+44 - 3,000

STA 654+44 - 654+88 - 3,500

STA 654+88 - 720 - 4,000

STA 1241 - 1307 - 4,000

STA 1417 - 1582 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 654 - 3,500

STA 1109 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,500

STA 1197+132 - 1241 - 4,000

STA 1241 - 1373 - 3,500

STA 1562 - 1582 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 654 - 3,500

STA 676 - 720 - 3,500

STA 1109 - 1197+22 - 3,000

Group 7: Table 9 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1197+110 - 1219 - 3,500

STA 1219 - 1263 - 4,000

STA 1307 - 1461 - 3,000

STA 1562 - 1582 - 4,500

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 610 - 3,500

STA 610 - 654+88 - 2,000

STA 654+88 - 676 - 3,000

STA 676 - 742 - 4,500

STA 1153 - 1285 - 4,000

STA 1285 - 1373 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654 - 2,400

STA 654 - 654+88 - 2,000

STA 654+88 - 654+121 - 3,300

STA 698 - 764 - 3,000

STA 1241 - 1307 - 3,000

STA 1307 - 1351 - 2,200

STA 1351 - 1461 - 3,000

STA 1502 - 1582 - 2,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and 

do the repair.

Before 

further flight.

-

All airplanes with scribe lines 

using a LRTS program 

inspection.

Contact Boeing for repair instructions and 

do the repair.

Before 

50,000 total 

flight cycles 

or within 

4,000 flight 

cycles after 

the original 

issue date 

on this 

service 

bulletin.

-

Group 7: Table 9 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 8: Table 10 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited Return 

To Service (LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for the 

skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 522 - 3,000 

STA 566 - 698 - 3,000

STA 1197+66 - 1219 - 3,000

STA 1373 - 1417 - 3,500

STA 1417 - 1502 - 2,000

STA 1518 - 1562 - 3,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 434 - 478 - 3,000

STA 654+22 - 654+88 - 4,000

STA 654+88 - 698 - 3,000

STA 698 - 764 - 5,000

STA 1175 - 1219 - 4,000

STA 1417 - 1582 - 4,500

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 522 - 4,000

STA 1109 - 1197+22 - 3,000

STA 1395 - 1461 - 3,500

STA 1562 - 1582 - 4,500

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 654 - 3,500

STA 654+110 - 676 - 4,500

STA 1087 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,300

STA 1241 - 1373 - 3,500

STA 1417 - 1461 - 3,500
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1562 - 1582 - 4,500

S-2R STA 434 - 654+44 - 3,000

STA 654+44 - 654+88 - 3,500

STA 654+88 - 720 - 4,000

STA 1241 - 1307 - 4,000

STA 1417 - 1582 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 654 - 3,500

STA 654+121 - 764 - 5,000

STA 1109 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,500

STA 1197+132 - 1241 - 4,000

STA 1241 - 1373 - 3,500

STA 1562 - 1582 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 654 - 3,500

STA 676 - 720 - 4,000

STA 1109 - 1197+22 - 3,000

STA 1197+110 - 1219 - 3,500

STA 1219 - 1263 - 4,000

STA 1307 - 1461 - 3,000

STA 1562 - 1582 - 4,500

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 610 - 3,500

STA 610 - 654+88 - 2,000

STA 654+88 - 676 - 3,000

STA 676 - 742 - 5,000

STA 1153 - 1285 - 4,000

STA 1285 - 1373 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654 - 2,400

Group 8: Table 10 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 654 - 654+88 - 2,000

STA 654+88 - 654+121 - 3,300

STA 698 - 765 - 3,000

STA 1241 - 1307 - 3,000

STA 1307 - 1351 - 2,200

STA 1351 - 1461 - 3,000

STA 1502 - 1582 - 2,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and 

do the repair.

Before further 

flight.

-

All airplanes with scribe lines 

using a LRTS program 

inspection.

Contact Boeing for repair instructions and 

do the repair.

Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

Group 9: Table 11 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe Lines 

using a Limited Return To 

Service (LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for the 

skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 478 - 3,000 

STA 654 - 654+110 - 3,000

STA 1197+66 - 1219 - 3,000

STA 1373 - 1417 - 3,500

STA 1417 - 1502 - 2,000

STA 1518 - 1562 - 3,000

S-30R STA 132.5 - 246 - 6,000 

Group 8: Table 10 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

S-26R STA 246 - 434 - 6,000 

STA 434 - 456 - 3,800

STA 654+22 - 654+88 - 4,500

STA 654+88 - 698 - 3,500

STA 698 - 764 - 4,200

STA 1175 - 1219 - 4,000

STA 1417 - 1582 - 4,500

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 456 - 4,300

STA 654+44 - 720 - 3,000

STA 1109 - 1197+22 - 3,000

STA 1395 - 1461 - 3,500

STA 1562 - 1582 - 4,500

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 632 - 3,400

STA 632 - 654+66 - 4,500

STA 654+66 - 654+121 - 3,500

STA 1087 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,300

STA 1241 - 1373 - 3,500

STA 1417 - 1461 - 3,500

STA 1562 - 1582 - 4,500

S-2R STA 434 - 654+44 - 3,000

STA 654+44 - 654+88 - 3,500

STA 654+88 - 720 - 4,000

STA 1241 - 1307 - 4,000

STA 1417 - 1582 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000

STA 434 - 654+121 - 3,500

STA 720 - 764 - 5,000

STA 1109 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,500

Group 9: Table 11 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1197+132 - 1241 - 4,000

STA 1241 - 1373 - 3,500

STA 1562 - 1582 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 654 - 3,500

STA 654 - 654+66 - 3,500

STA 654+66 - 720 - 3,000

STA 1109 - 1197+22 - 3,000

STA 1197+110 - 1219 - 3,500

STA 1219 - 1263 - 4,000

STA 1307 - 1461 - 3,000

STA 1562 - 1582 - 4,500

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 610 - 3,500

STA 610 - 654 - 2,000

STA 654 - 676 - 3,500

STA 676 - 742 - 5,000

STA 1153 - 1285 - 4,000

STA 1285 - 1373 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654 - 2,400

STA 654 - 654+88 - 2,000

STA 654+88 - 654+121 - 3,300

STA 698 - 764 - 3,000

STA 1241 - 1307 - 3,000

STA 1307 - 1351 - 2,200

STA 1351 - 1461 - 3,000

STA 1502 - 1582 - 2,000

Group 9: Table 11 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and 

do the repair.

Before further 

flight.

-

All airplanes with scribe lines 

using a LRTS program 

inspection.

Contact Boeing for repair instructions and 

do the repair.

Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

Group 10: Table 12 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe Lines 

using a Limited Return To 

Service (LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for 

the skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 522 - 3,000 

STA 566 - 698 - 3,000

STA 1197+66 - 1219 - 3,000

STA 1373 - 1417 - 3,500

STA 1417 - 1502 - 2,000

STA 1518 - 1562 - 3,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 434 - 478 - 3,000

STA 654+22 - 654+88 - 4,500

STA 654+88 - 698 - 3,500

STA 698 - 764 - 4,500

STA 1175 - 1219 - 4,000

STA 1417 - 1582 - 4,500

S-21R STA 132.5 - 246 - 4,000 

Group 9: Table 11 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 522 - 4,500

STA 654+44 - 720 - 3,000

STA 1109 - 1197+22 - 3,000

STA 1395 - 1461 - 3,500

STA 1562 - 1582 - 4,500

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 632 - 3,500

STA 632 - 654+66 - 4,500

STA 654+66 - 654+121 - 3,500

STA 1087 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,300

STA 1241 - 1373 - 3,500

STA 1417 - 1461 - 3,500

STA 1562 - 1582 - 4,500

S-2R STA 434 - 654+44 - 3,000

STA 654+44 - 654+88 - 3,500

STA 654+88 - 720 - 4,000

STA 1241 - 1307 - 4,000

STA 1417 - 1582 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 654+121 - 3,500

STA 720 - 764 - 5,000

STA 1109 - 1197+44 - 3,000

STA 1197+44 - 1197+132 - 2,500

STA 1197+132 - 1241 - 4,000

STA 1241 - 1373 - 3,500

STA 1562 - 1582 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 654 - 3,500

STA 654 - 654+66 - 3,500

STA 654+66 - 720 - 3,000

Group 10: Table 12 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1109 - 1197+22 - 3,000

STA 1197+110 - 1219 - 3,500

STA 1219 - 1263 - 4,000

STA 1307 - 1461 - 3,000

STA 1562 - 1582 - 4,500

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 610 - 3,500

STA 610 - 654 - 2,000

STA 654 - 676 - 3,500

STA 676 - 742 - 5,000

STA 1153 - 1285 - 4,000

STA 1285 - 1373 - 3,000

STA 1502 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654 - 2,400

STA 654 - 654+88 - 2,000

STA 654+88 - 654+121 - 3,300

STA 698 - 764 - 3,000

STA 1241 - 1307 - 3,000

STA 1307 - 1351 - 2,200

STA 1351 - 1461 - 3,000

STA 1502 - 1582 - 2,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions and 

do the repair.

Before further 

flight.

-

All airplanes with scribe lines 

using a LRTS program 

inspection.

Contact Boeing for repair instructions and 

do the repair.

Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

Group 10: Table 12 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 11: Table 13 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe Lines 

using a Limited Return To 

Service (LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for 

the skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 500 - 4,000 

STA 654 - 654+121 - 4,000

STA 1417 - 1582 - 2,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 434 - 456 - 4,000

STA 654+22 - 654+110 - 4,500

STA 654+110 - 742 - 3,000

STA 1153 - 1197+66 - 4,000

STA 1417 - 1582 - 5,000

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 654+66 - 676 - 3,000

STA 676 - 720 - 4,000

STA 1175 - 1197+22 - 4,000

STA 1197+22 - 1197+66 - 3,000

STA 1395 - 1461 - 3,500

STA 1461 - 1562 - 4,000

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 632 - 3,400

STA 632 - 654+44 - 4,500

STA 1153 - 1197+88 - 3,000

STA 1197+88 - 1219 - 3,000

STA 1241 - 1373 - 3,500

STA 1417 - 1562 - 3,500

S-2R STA 1241- 1285 - 5,000

STA 1285 - 1351 - 3,000
 

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 1351 - 1417 - 4,000

STA 1417 - 1582 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 1175 - 1197+132 - 2,000

STA 1219 - 1373 - 3,500

STA 1417 - 1461 - 4,000

STA 1461 - 1562 - 4,000

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 654+110 - 720 - 3,500

STA 1175 - 1197+44 - 3,500

STA 1197+132 - 1263 - 3,500

STA 1263 - 1307 - 4,500

STA 1307 - 1461 - 4,000

STA 1461 - 1562 - 4,000

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 654+110 - 698 - 2,200

STA 698 - 742 - 3,000

STA 1065 - 1109 - 3,000

STA 1197 - 1263 - 4,000

STA 1263 - 1373 - 3,000

STA 1502 - 1582 - 4,000

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654 - 2,200

STA 654 - 654+88 - 3,000

STA 1197+110 - 1219 - 3,000

STA 1241 - 1307 - 2,600

STA 1307 - 1373 - 2,000

STA 1417 - 1461 - 3,000

STA 1502 - 1540 - 2,000

STA 1540 - 1582 - 3,000

Group 11: Table 13 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 61 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions 

and do the repair.

Before further 

flight.

-

All airplanes with scribe lines 

using a LRTS program 

inspection.

Contact Boeing for repair instructions 

and do the repair.

Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-

Group 12: Table 14 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return To Service 

(LRTS) Program

Skin Lap Joints

Do a detailed inspection, High Frequency 

Eddy Current (HFEC) and/or Ultrasonic 

(UT) special detailed inspections for any 

crack as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6 for 

the skin lap joint areas that follow:

Stringer

Location

Station Location

From - To

Flight Cycles

S-37R STA 287 - 434 - 2,000 

S-36R STA 434 - 478 - 2,000 

STA 654A - 654 - 2,000

STA 1197+110 - 1197+154 - 2,200

STA 1197+165 - 1197+209 - 4,000

STA 1373 - 1439 - 2,500

STA 1518 - 1582 - 3,000

S-30R STA 132.5 - 246 - 6,000 

S-26R STA 246 - 434 - 6,000 

STA 654A+22 - 654A+110 - 3,000

STA 654A+110 - 654+22 - 3,000

STA 654+22 - 654+110 - 2,400

STA 654+110 - 676 - 3,000

STA 1197 - 1197+187 - 4,500

STA 1197+209 - 1219 - 3,000

STA 1417 - 1480 - 5,000

STA 1518 - 1582 - 4,500

Group 11: Table 13 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 62 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

S-21R STA 132.5 - 246 - 4,000 

S-17R STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 654A+22 - 654A+110 - 3,500

STA 1197+154 - 1219 - 4,000

STA 1395 - 1439 - 3,000

S-13R STA 212 - 246 - 4,500

S-8R STA 246 - 434 - 4,000 

STA 434 - 654A+110 - 3,400

STA 1197+22 - 1197+253 - 4,000

STA 1197+253 - 1461 - 3,500

S-2R STA 434 - 654A+110 - 3,000

STA 654A+110 - 654+44 - 3,300

STA 654+44 - 654+110 - 4,000

STA 1197+209 - 1285 - 4,000

STA 1285 - 1373 - 3,000

STA 1417 - 1518 - 3,000

STA 1518 - 1562 - 3,000

BL 0 STA 188.9 - 246 - 6,000 

S-8L STA 246 - 434 - 4,000 

STA 434 - 654A+110 - 3,400

STA 1197+22 - 1197+66 - 4,000

STA 1197+66 - 1197+132 - 3,500

STA 1197+165 - 1197+253 - 4,500

STA 1197+253 - 1373 - 3,500

STA 1417 - 1461 - 4,000

STA 1540 - 1582 - 4,500

S-13L STA 212 - 246 - 4,500

S-17L STA 246 - Door Cutout - 2,000 

STA Door Cutout - 434 - 2,000 

STA 434 - 654 - 3,500

STA 1197+154 - 1263 - 3,500

STA 1307 - 1439 - 3,500

S-21L STA 132.5 - 246 - 4,000 

S-26L STA 246 - 434 - 6,000 

STA 434 - 566 - 3,500

STA 566 - 654A - 2,400

Group 12: Table 14 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

STA 654A - 654A+110 - 3,500

STA 654A+110 - 676 - 2,400

STA 1197 - 1197+187 - 4,500

STA 1197+187 - 1241 - 3,500

STA 1241 - 1351 - 3,000

STA 1351 - 1417 - 3,000

STA 1540 - 1582 - 4,500

S-30L STA 132.5 - 246 - 6,000 

S-36L STA 434 - 654A+88 - 2,400

STA 654A+88 - 654A+44 - 3,000

STA 1197+110 - 1197+154 - 2,200

STA 1197+187 - 1219 - 4,000

STA 1285 - 1351 - 4,000

S-37L STA 287 - 434 - 2,000 

If any crack is found. Contact Boeing for repair instructions 

and do the repair.

Before further 

flight.

-

All airplanes with scribe 

lines using a LRTS 

program inspection.

Contact Boeing for repair instructions 

and do the repair.

Before 50,000 

total flight cycles 

or within 4,000 

flight cycles after 

the original issue 

date on this 

service bulletin.

-

Group 12: Table 14 - Skin Lap Joints - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 64 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 1-12: Table 15 - External Approved Repairs - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance Time

Repeat Interval 

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return To Service (LRTS) 

Program

External Approved 

Repairs - 20 inches or 

longer on any side.

Do a detailed inspection, High 

Frequency Eddy Current (HFEC) and/or 

Ultrasonic (UT) special detailed 

inspections for any crack as given in the 

Accomplishment Instructions Paragraph 

3.B - Part 6.

Within 1500 flight 

cycles after scribe 

line found.

1500 flight cycles

All Airplanes with Scribe 

Lines using a LRTS 

Program

External Approved 

Repairs - Less than 20 

inches on all sides. 

Do a detailed inspection, HFEC and UT 

special detailed inspections for any crack 

as given in the Accomplishment 

Instructions Paragraph 3.B - Part 6.

Within 3000 flight 

cycles after scribe 

line found.

3000 flight cycles

If any crack is found. Contact Boeing for repair instructions 

and do the repair.

Before further 

flight.

-

All airplanes with scribe 

lines using a LRTS 

program inspection.

Contact Boeing for additional inspections 

or repair.

Before 50,000 

total flight cycles 

or within 4,000 

flight cycles after 

the original issue 

date on this 

service bulletin.

-
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 65 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 1-4: Table 16 - External Features - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

 (Not to Exceed)

All Airplanes with 

Scribe Lines using a 

Limited Return To 

Service (LRTS) 

Program

External Features

Do a detailed inspection, High Frequency Eddy 

Current (HFEC) and/or Ultrasonic (UT) special 

detailed inspections for any crack as given in the 

Accomplishment Instructions Paragraph 3.B - Part 

6 for the External Features that follow:

Stringer 

Location

Station 

Location

External Feature

1L-1R 445 Upper ATC Antenna - 4100 flight cycles 

1L-1R 555 Anti-Collision Light - 2700 flight cycles

1L-1R 600 GPS Antenna - 1600 flight cycles

1L-1R 622 GPS Antenna - 1600 flight cycles 

1L-1R 665 VHF Antenna - 3200 flight cycles 

1L-1R 1122 ADF Antenna - 3100 flight cycles 

1L-1R 1166 ADF Antenna - 3400 flight cycles 

CL 555 DME Antenna - 7100 flight cycles 

CL 577 Fwd LRRA Antenna - 3800 flight cycles 

CL 621 Aft LRRA Antenna - 5000 flight cycles 

CL 665 DME Antenna - 6100 flight cycles 

CL 680 Marker Beacon Antenna - 5000 flight cycles 

If any crack is found. Contact Boeing for repair instructions and do the 

repair.

Before further 

flight.

-

All airplanes with 

scribe lines using a 

LTRS program 

inspection.

Contact Boeing for additional inspections or repair. Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 66 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 5-10: Table 17 - External Features - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with 

Scribe Lines using a 

Limited Return To 

Service (LRTS) 

Program

External Features

Do a detailed inspection, High Frequency Eddy 

Current (HFEC) and/or Ultrasonic (UT) special 

detailed inspections for any crack as given in the 

Accomplishment Instructions Paragraph 3.B - 

Part 6 for the External Features that follow:

Stringer 

Location

Station 

Location

External 

Feature

1L-1R 448 ATC Antenna - 5900 flight cycles

1L-1R 600 GPS Antenna - 1900 flight cycles

1L-1R 622 GPS Antenna - 3400 flight cycles

1L-1R 654+33 VHF Antenna - 1600 flight cycles

1L-1R 1122 ADF Antenna - 3100 flight cycles

1L-1R 1166 ADF Antenna - 3400 flight cycles

CL 513 VHF Antenna - 5500 flight cycles

CL 555 DME Antenna - 3600 flight cycles

CL 577 RA Antenna - 2600 flight cycles

CL 621 RA Antenna - 2100 flight cycles

CL 1197+99 VHF Antenna - 5600 flight cycles

If any crack is found. Contact Boeing for repair instructions and do the 

repair.

Before further 

flight.

-

All airplanes with 

scribe lines using a 

LTRS program 

inspection.

Contact Boeing for additional inspections or 

repair.

Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-
 

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 67 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Group 11: Table 18 - External Features - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with 

Scribe Lines using a 

Limited Return To 

Service (LRTS) 

Program

External Features

Do a detailed inspection, High Frequency Eddy 

Current (HFEC) and/or Ultrasonic (UT) special 

detailed inspections for any crack as given in 

the Accomplishment Instructions Paragraph 3.B 

- Part 6 for the External Features that follow:

Stringer 

Location

Station 

Location

External Feature

1L-1R 654+33 VHF Antenna - 5000 flight cycles

1L-1R 1122 ADF Antenna - 3100 flight cycles 

1L-1R 1166 ADF Antenna - 3400 flight cycles

CL 513 VHF Antenna - 7400 flight cycles

CL 555 DME Antenna - 7100 flight cycles

CL 577 RA Antenna - 6600 flight cycles

CL 621 RA Antenna - 5100 flight cycles

CL 654+26 Marker Beacon 

Antenna

- 5100 flight cycles 

If any crack is found. Contact Boeing for repair instructions and do 

the repair.

Before further 

flight.

-

All airplanes with 

scribe lines using a 

LTRS program 

inspection.

Contact Boeing for additional inspections or 

repair.

Before 50,000 

total flight 

cycles or 

within 4,000 

flight cycles 

after the 

original issue 

date on this 

service 

bulletin.

-
 

Original Issue: November 25, 2008

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ALERT ALERT

Group 12: Table 19 - External Features - Limited Return To Service Repeat Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return To Service 

(LRTS) Program

External Features

Do a detailed inspection, High Frequency Eddy 

Current (HFEC) and/or Ultrasonic (UT) special 

detailed inspections for any crack as given in 

the Accomplishment Instructions Paragraph 3.B 

- Part 6 for the External Features that follow.

Stringer 

Location

Station 

Location

External Feature

1L-1R 448 ATC Antenna - 5300 flight cycles

1L-1R 600 GPS Antenna - 3700 flight cycles

1L-1R 622 GPS Antenna - 3800 flight cycles

1L-1R 654+33 VHF Antenna - 2000 flight cycles

CL 555 DME Antenna - 3200 flight cycles

CL 577 LRRA Antenna - 3300 flight cycles

CL 621 LRRA Antenna - 2800 flight cycles

If any crack is found. Contact Boeing for repair instructions and do 

the repair.

Before further 

flight.

-

All airplanes with scribe 

lines using a LTRS 

program inspection.

Contact Boeing for additional inspections or 

repair.

Before 

50,000 total 

flight cycles 

or within 

4,000 flight 

cycles after 

the original 

issue date on 

this service 

bulletin.

-
 

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Group 1-12: Table 20 - Decals - Limited Return To Service Repeat Inspection Intervals 

Condition Action

Compliance Time

(Whichever Occurs 

Last)

Repeat Interval 

(Not to Exceed)

All Airplanes with Scribe 

Lines using a Limited 

Return to Service 

(LRTS) Program

Decals

Do a detailed inspection and High 

Frequency Eddy Current (HFEC) 

special detailed inspection for any 

crack as given in the 

Accomplishment Instructions 

Paragraph 3.B - Part 6.

Within 3,000 flight cycles 

after scribe line found.

3,000 flight cycles

If any crack is found. Contact Boeing for repair 

instructions and do the repair.

Before further flight. -

All airplanes with scribe 

lines using a LRTS 

program inspection.

Contact Boeing for additional 

inspections or repair.

Before 50,000 total flight 

cycles or within 4,000 

flight cycles after the 

original issue date on 

this service bulletin.

-

Group 1-12: Table 21 - Existing Scribe Line Damage - Outside of Zones 1,2, and 3 - LRTS Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)

All Airplanes with Existing Scribe 

Line Damage outside Zones 1,2, 

and 3 (a)

Measure the scribe line depth 

as given Accomplishment 

Instructions Paragraph 3.B - 

Part 8 for the fuselage areas 

that follow.

Within 4,000 flight 

cycles after the 

original issue date 

on this service 

bulletin.

-

Skin Lap Splices - 3,000 flight cycles

Butt Joints - 9,000 flight cycles

External Approved Repairs - 4,000 flight cycles

External Features - 4,000 flight cycles

Decals - 4,000 flight cycles

Scribe line is less than 0.001 inch 

deep.

No further inspections are 

required. (b)

- -

Scribe line is greater than or 

equal to 0.001 inch deep.

Do a High Frequency Eddy 

Current (HFEC) and/or 

Ultrasonic (UT) special detailed 

inspections for any crack as 

given in the Accomplishment 

Instructions Paragraph 3.B - 

Part 8. 

Before further 

flight.

-

Or

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

-
 

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F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes 

specified in this service bulletin comply with the applicable regulations and are FAA approved, as well 

as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/

JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval 

were based on the airplane in its original Boeing delivery configuration or as modified by other 

approved Boeing changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected 

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency 

approval before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection for each airplane. 

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator 

task hour data if necessary. The estimate does not include lost time. These are some examples of lost 

time:

If no crack is found and the 

scribe line is greater than or 

equal to 0.001 inch deep and 

less than or equal to 0.004 inch. 

No further work or inspections 

are required. (b)

- -

If no crack is found and the 

scribe line is greater than 0.004 

inch deep and less than or equal 

to 0.006 inch. 

Do the repeat inspections as 

given in Accomplishment 

Instructions Paragraph 3.B - 

Part 8.

Before repeat 

intervals in Table 

21.

Refer to the LRTS 

Table 21 for 

repeat intervals.

Or

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

-

If no crack is found and the 

scribe line is greater than 0.006 

inch deep. 

Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

-

If any crack is found. Contact Boeing for repair 

instructions and do the repair.

Before further 

flight.

-

All airplanes with scribe lines 

using a LRTS program 

inspection.

Contact Boeing for additional 

inspections or repair.

Before 50,000 

total flight cycles 

or within 4,000 

flight cycles after 

the original issue 

date on this 

service bulletin.

-

(a) Refer to Accomplishment Instructions Paragraph 3.B for identification of a typical scribe line.

(b) No further inspections are required at this location, provided that the correct sealant removal procedure 

is used for all future work. Refer to Appendix A of this service bulletin as an accepted sealant removal 

procedure.

Group 1-12: Table 21 - Existing Scribe Line Damage - Outside of Zones 1,2, and 3 - LRTS Inspection Intervals 

Condition Action Compliance 

Time

Repeat Interval

(Not to Exceed)
 

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— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Group 1: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 1 10 80.0 8.0

Figure 13 10 80.0 8.0

Figure 25 10 80.0 8.0

Figure 37 2 20.0 10.0

Figure 49 2 20.0 10.0

Figure 61 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 2: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 2 10 80.0 8.0

Figure 14 10 80.0 8.0

Figure 26 10 80.0 8.0

Figure 38 2 20.0 10.0

Figure 50 2 20.0 10.0

Figure 62 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.
 

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ALERT ALERT

Group 3: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 3 10 80.0 8.0

Figure 15 10 80.0 8.0

Figure 27 10 80.0 8.0

Figure 39 2 20.0 10.0

Figure 51 2 20.0 10.0

Figure 63 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 4: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 4 10 80.0 8.0

Figure 16 10 80.0 8.0

Figure 28 10 80.0 8.0

Figure 40 2 20.0 10.0

Figure 52 2 20.0 10.0

Figure 64 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 5: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 5 10 80.0 8.0

Figure 17 10 80.0 8.0

Figure 29 10 80.0 8.0

Figure 41 2 20.0 10.0

Figure 53 2 20.0 10.0
 

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Figure 65 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 6: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 6 10 80.0 8.0

Figure 18 10 80.0 8.0

Figure 30 10 80.0 8.0

Figure 42 2 20.0 10.0

Figure 54 2 20.0 10.0

Figure 66 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 7: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 7 10 80.0 8.0

Figure 19 10 80.0 8.0

Figure 31 10 80.0 8.0

Figure 43 2 20.0 10.0

Figure 55 2 20.0 10.0

Figure 67 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Group 5: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours
 

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Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 8: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 8 10 80.0 8.0

Figure 20 10 80.0 8.0

Figure 32 10 80.0 8.0

Figure 44 2 20.0 10.0

Figure 56 2 20.0 10.0

Figure 68 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 9: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 9 10 80.0 8.0

Figure 21 10 80.0 8.0

Figure 33 10 80.0 8.0

Figure 45 2 20.0 10.0

Figure 57 2 20.0 10.0

Figure 69 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 7: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours
 

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Group 10: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 10 10 80.0 8.0

Figure 22 10 80.0 8.0

Figure 34 10 80.0 8.0

Figure 46 2 20.0 10.0

Figure 58 2 20.0 10.0

Figure 70 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 11: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 11 10 80.0 8.0

Figure 23 10 80.0 8.0

Figure 35 10 80.0 8.0

Figure 47 2 20.0 10.0

Figure 59 2 20.0 10.0

Figure 71 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 12: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours

Figure 12 10 80.0 8.0

Figure 24 10 80.0 8.0

Figure 36 10 80.0 8.0

Figure 48 2 20.0 10.0
 

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ALERT ALERT

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 23-12-03, 33-44-02, 34-32-01, 

34-33-02, 34-53-03, 34-55-02, 34-57-03, 34-58-02, 51-21-10, 51-31-00, 51-31-01.

b. 767 Non-Destructive Testing (NDT) Manual, Part 10, 53-30-01, Part 4, 53-00-01, Part 4, 

53-00-02, Part 6, 51-00-01, Part 6, 51-00-19, Part 6, 53-00-09.

c. Boeing Drawing 012W6100.

d. Boeing Parts Standards Document D-590.

e. Service Related Problem (SRP) 767-SRP-53-0244. 

f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-43-03.

2. Data supplied with this Service Bulletin:

None.

3. Installation Drawings Used in the Preparation of this Service Bulletin:

None.

Figure 60 2 20.0 10.0

Figure 72 10 60.0 6.0

TOTAL FOR EACH AIRPLANE 340.0 * 50.0 *

* Total Task Hours and Elapsed Hours dependent upon total number of 

fuselage areas and zones being inspected. 

Additional time is required for paint and sealant removal.

More time will be required for additional inspections and repairs if scribe lines 

or other damage is found.

More time may be required for inspections around large approved repairs.

Group 12: Scribe Line Inspection

Task

Number of 

Persons Task Hours Elapsed Hours
 

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ALERT ALERT

K. Publications Affected

1. Publications

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue 

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the 

Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
 

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ALERT ALERT

BLANK PAGE
 

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2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the inspections or repair procedures given in this 

service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts:

None.

2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

None.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

Part Number / 

Specification QTY Name Notes

Type 2, Class A 10 Ounces Chemical Conversion Coating (b) (c) (g)

BMS 10-11 Type 1 24 Ounces Primer (a) (c) (g)

BMS 10-72 24 Ounces Primer Plus Enamel (a) (c) (d) (e) (f) (g)

BMS 10-79, Type II 24 Ounces Primer (a) (c) (d) (e) (f) (g)

BMS 10-60, Type II 24 Ounces Topcoat (a) (c) (d) (e) (f) (g)

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier 

data.

(b) Refer to SOPM 20-43-03 or 767 Structural Repair Manual (SRM), Chapter 51 as an accepted 

procedure for material sources.

(c) This part is only necessary if paint is removed.

(d) This part is only necessary if BMS 10-79 and BMS 10-60 or the operators normal decorative paint 

system is not used.

(e) This part is only necessary if BMS 10-72 or the operators normal decorative paint system is not used.

(f) Refer to 767 AMM 51-21-10 as an accepted procedure for decorative exterior paint system application.

(g) The quantity given is an approximation. The actual quantity required will vary depending on the results 

of the scribe line inspections.
 

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E. Special Tooling - Price and Availability

The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this 

Service Bulletin. Tool price and supply data are not given.

F. Special Tooling Necessary to do this Service Bulletin

No special tooling is necessary to accomplish this bulletin. However, the following standard tools may 

be needed to measure scribe line depth. These tools are unusual and may not be available at all shops 

as standard tools. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., 

References, can also be necessary. Examine operator tool supply to make sure all necessary tools 

are available.

Number Name

Model Number 8400K Digital Optical Micrometer (a) (b)

Model 966 (Part Number 125632-1) or 

Model 966A (Part Number 125632)

Optical Micrometer (a) (c)

Inspect Cam Model SDMS Laser Measurement System (d)

(a) These are typical optical micrometers.

(b) Rene Company

1005 South Mountain Avenue 

Monrovia, California 91016 

USA

Toll free: 866.358.9955 

Tel: 626.358.9955 Fax: 626.358.1448 

Email: info@renecompany.com 

(c) Taber® Industries 

455 Bryant Street

North Tonawanda, New York 14120

USA

Toll-Free: 800.333.5300 (in USA or Canada)

Phone: 716.694.4000

Fax: 716.694.1450

(d) Remote Vision Solutions PTY LTD

Unit 1

118 Church Street

Hawthorn, 3122, Victoria AUSTRALIA 

Phone: +61 3 9815 0933

Fax: +61 3 9818 5597

sales@remotevs.com
 

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ALERT ALERT

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED

MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES

CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE

SPARKS OR OTHER ELECTRICAL DAMAGE.

NOTE:

1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for 

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. Unless shown differently, these dimensions and tolerances are used:

— Linear dimensions are in inches

— Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or 

minus 0.03 inch.

4. These work instructions refer to procedures included in other Boeing documents. When 

the words "refer to" are used and the operator has an accepted alternative procedure, 

the accepted alternative procedure can be used. When the words "as given in" are 

included in the instruction, the procedure in the Boeing document must be used.

5. Inspections are not required in lap joint areas where an existing external approved repair 

covers a potential scribe line, provided the repair spans a minimum of three fastener 

rows below the potential scribe line location and three fastener rows above the upper 

fastener row of the skin lap joint. 

6. Appendix D includes information for the fabrication or purchase of a scribe line sample 

for use as a training aid. The use of this sample is not required when performing actions 

of this service bulletin. This sample is an aid in identifying what a scribe line may look 

and feel like but is not intended to show all damage that is considered a scribe line. 

When identifying scribe lines, see the definition of a typical scribe line in the 

Accomplishment Instructions of this service bulletin.

7. If an optical micrometer or laser measurement system cannot be used because the 

upper skin of the lap joint covers a scribe line, then the scribe line depth does not need 

to be determined at that location. These scribe lines must be considered typical and 

therefore all inspection and other requirements for a typical scribe line apply.

8. It is required that individuals performing ultrasonic inspections on airplanes with scribe 

lines to detect cracks per the relevant procedures must be recognized by the operator 

or repair station as qualified to perform ultrasonic inspections on their airplanes AND 

meet at least one of the following criteria:

— The individual must be qualified to at least Level 2 in the ultrasonic method in 

accordance with an accepted industry standard, i.e. ATA Specification 105, MilStd.-410, NAS-410, SNT-TC-1A, or EN-4179 or equivalent. or

— The individual has received specific Boeing training with Boeing providing a 

certificate stating that the individual has satisfactorily completed the training in the 
 

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specific techniques. or

— The individual has a Level 1 rating in the ultrasonic method in accordance with an 

accepted industry standard and has received specific training and a statement from 

the qualifying entity (employer) that the individual is qualified for this particular 

inspection.

9. If scribe lines are found during any of the inspections contained in this service bulletin, 

when determining the requirements for inspection and repair, each scribe line shall be 

considered individually.

10. An approved repair is identified as any SRM repair, repair provided and approved by 

Boeing for specific cases that were requested by the operator, or operator developed 

repair that has Boeing approved Damage Tolerance Analysis. 

11. Contact Boeing if any scribe line is detected at a non-Boeing approved repair.

12. A Special Detailed Inspection is defined as: An intensive examination of a specific item, 

installation, or assembly to detect damage, failure, or irregularity. The examination is 

likely to make extensive use of specialized inspection techniques and/or equipment. 

Intricate cleaning and substantial access or disassembly procedure may be required.

13. A Detailed Inspection is defined as: An intensive examination of a specific item, 

installation, or assembly to detect damage, failure, or irregularity. Available lighting is 

normally supplemented with a direct source of good lighting at an intensity deemed 

appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. 

Surface cleaning and elaborate procedures may be required.

14. This service bulletin has four (4) areas for scribe line inspections. The areas are as 

follows:

— Skin Lap Joints

— External Approved Repairs

— External Features

— Decals

A "Zone" consists of structure from any of the four inspection areas and has been 

assigned a number based upon critical location and inspection threshold. Zone 1 has 

the lowest inspection threshold and Zone 3 has the highest inspection threshold. 

15. Operators should thoroughly familiarize themselves with all Parts and Work Instructions 

in this service bulletin prior to starting their scribe line inspection program. In addition, it 

is recommended that all Non-Destructive Testing (NDT) procedures be reviewed and 

limitations understood prior to the use of the NDT inspection. This will aid in 

understanding all available options in the event a scribe line is discovered. 

16. Do not blend scribe lines. Blending a scribe line may hinder inspection techniques 

necessary to determine the presence or absence of fatigue cracks. 
 

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B. WORK INSTRUCTIONS

1. IDENTIFICATION OF A "TYPICAL" SCRIBE LINE

Determine if the Scribe Line is "typical".

A scribe line is defined as a narrow, shallow, distinct line of damage (typically up to 0.006 inch 

deep), usually associated with the removal of a fillet or gap seal (lap joints and butt joints, 

respectively). Scribe lines can be both tactile and non-tactile. Discoloration of the aluminum clad 

layer or small surface imperfections do not qualify as a scribe line. A lightning strike at a lap joint 

or butt joint does not qualify as a scribe line. In certain cases the scribe lines have also been 

associated with the trimming of fuselage skin decals. Scribe lines that create a potential safety 

concern are generally long continuous scribe lines or several adjacent scribe lines in a critical 

orientation at specific locations with relatively high stresses. 

If an optical micrometer or laser measurement system cannot be used because the upper skin of 

the lap joint covers a scribe line, then the scribe line depth does not need to be determined at 

that location. These scribe lines must be considered typical and therefore all inspection and other 

requirements for a typical scribe line apply.

Grinding, gouging, or other "non-typical" damage, which is more significant (deeper or locally 

more extensive) than the typical scribe line must be repaired. Localized scratches, nicks and 

dents that might be induced in other areas of the fuselage skin during either manufacture or 

maintenance operations are not considered scribe lines. This type of damage should be 

addressed via the acceptable maintenance practices detailed in the Structural Repair Manual.

2. LOCATIONS OF "TYPICAL" SCRIBE LINES

a. Skin Lap Joints 

In areas near skin lap joints, scribe lines normally run parallel to the lap joint in the lower skin 

along the edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower 

edge of the upper skin. In some cases, portions of the scribe lines may be directly adjacent 

to or slightly under the lower edge of the upper skin resulting in hidden lines that cannot be 

viewed without disassembly. The ends of these scribe lines sometimes may also turn 

slightly away from the lap joint.

b. External Approved Repairs 

In areas around external approved repairs, scribe lines normally follow the periphery of the 

external approved repair doubler.

c. External Features 

In areas around external features, scribe lines normally follow the periphery of the external 

feature.

d. Decals 

In areas around decals, scribe lines normally follow the periphery of the decal. Scribe lines 

may be located anywhere on a skin panel where decals are currently installed or were 

previously were installed.
 

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3. PART 1 - SURFACE PREPARATION - SCRIBE LINE INSPECTIONS 

NOTE: Refer to Appendix A of this service bulletin for an accepted procedure for sealant

removal during surface preparation.

a. Skin Lap Joint Surface Preparation 

(1) Remove the sealant as required from the lower edge of all affected lap joints. 

(2) Remove the paint as required from below the lower edge of all affected lap joints. The 

bared area should be at least one (1.0) inch wide, as measured from the lower edge of 

the upper skin.

(3) If any section of the affected lap joints is under the wing-to-body fairing, remove the 

appropriate fairing panel(s) for access. Refer to 767 AMM 06-41-00 as an accepted 

procedure.

NOTE: If the operator’s records show that the airplane has never been stripped or

repainted under the wing-to-body fairings since delivery from Boeing and

correct sealant removal procedures are implemented for all future work, then

the skin lap joint inspections in the areas under the wing-to-body fairing are

not required.

b. External Approved Repair Surface Preparation

Remove paint and sealant from the area of the skin around the periphery of the external 

approved repair. The bared area should be at least one (1.0) inch wide, around the 

periphery of the external approved repair. 

c. External Feature Surface Preparation

Remove paint and sealant from the area of the skin around the periphery of the external 

feature. The bared area should be at least one (1.0) inch wide, around the periphery of the 

external feature. 

d. Decal Surface Preparation

Remove the paint as required from the applicable area of the skin around the edges of the 

decal as follows: 

(1) If decals were previously installed, and it can be determined where the edges of the 

decals previously were, remove the paint from the area of the skin around the edges of 

the decal. The bared area should be at least one half (0.5) inch wide on both sides of 

the edge of the decal.

(2) If decals were previously installed, but it cannot be determined where the edges of the 

decal were, remove the paint from all of the affected decal locations.
 

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4. PART 2 - DETAILED INSPECTION FOR SCRIBE LINES 

a. From the tables that follow, which correspond to airplane group numbers, determine the 

applicable figures for the inspection areas for each zone to be inspected. 

b. Do Part 1 - Surface Preparation - Scribe Line Inspections as necessary for each scribe line 

inspection area.

c. Do a detailed inspection of the fuselage skin for scribe lines. Use a minimum 10X magnifying 

lens to aid the inspection.

d. If no scribe line is found, do Part 3 - No Scribe Line Found. 

e. If any scribe line is found, do Part 4 - Scribe Line Found. 

Group 1: 

Group 1 - Table 1 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 1 Figure 13 Figure 25

External Approved 

Repairs

Figure 37 (a) (a)

External Features (a) Figure 49 (a)

Decals (a) (a) Figure 61

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 2: 

Group 2 - Table 2 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 2 Figure 14 Figure 26

External Approved 

Repairs

Figure 38 (a) (a)

External Features (a) Figure 50 (a)

Decals (a) (a) Figure 62

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 3: 

Group 3 - Table 3 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 3 Figure 15 Figure 27

External Approved 

Repairs

Figure 39 (a) (a)

External Features (a) Figure 51 (a)

Decals (a) (a) Figure 63

(a) No inspection is required for this area and zone at this inspection threshold. 
 

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Group 4: 

Group 4 - Table 4 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 4 Figure 16 Figure 28

External Approved 

Repairs

Figure 40 (a) (a)

External Features (a) Figure 52 (a)

Decals (a) (a) Figure 64

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 5: 

Group 5 - Table 5 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 5 Figure 17 Figure 29

External Approved 

Repairs

Figure 41 (a) (a)

External Features (a) Figure 53 (a)

Decals (a) (a) Figure 65

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 6: 

Group 6 - Table 6 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 6 Figure 18 Figure 30

External Approved 

Repairs

Figure 42 (a) (a)

External Features (a) Figure 54 (a)

Decals (a) (a) Figure 66

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 7: 

Group 7 - Table 7 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 7 Figure 19 Figure 31

External Approved 

Repairs

Figure 43 (a) (a)

External Features (a) Figure 55 (a)

Decals (a) (a) Figure 67

(a) No inspection is required for this area and zone at this inspection threshold. 
 

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Group 8: 

Group 8 - Table 8 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 8 Figure 20 Figure 32

External Approved 

Repairs

Figure 44 (a) (a)

External Features (a) Figure 56 (a)

Decals (a) (a) Figure 68

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 9: 

Group 9 - Table 9 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 9 Figure 21 Figure 33

External Approved 

Repairs

Figure 45 (a) (a)

External Features (a) Figure 57 (a)

Decals (a) (a) Figure 69

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 10: 

Group 10 - Table 10 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 10 Figure 22 Figure 34

External Approved 

Repairs

Figure 46 (a) (a)

External Features (a) Figure 58 (a)

Decals (a) (a) Figure 70

(a) No inspection is required for this area and zone at this inspection threshold. 

Group 11: 

Group 11 - Table 11 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 11 Figure 23 Figure 35

External Approved 

Repairs

Figure 47 (a) (a)

External Features (a) Figure 59 (a)

Decals (a) (a) Figure 71

(a) No inspection is required for this area and zone at this inspection threshold. 
 

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5. PART 3 - NO SCRIBE LINE FOUND 

a. If no scribe lines are found, no further inspection is required at that location, provided the 

correct sealant removal procedure is implemented for all future work. Refer to Appendix A 

of this service bulletin for an accepted sealant removal procedure. 

b. Do Part 7 - Surface Finish Restoration.

6. PART 4 - SCRIBE LINE FOUND 

NOTE: DO NOT BLEND ANY SCRIBE LINE. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS. 

a. Measure and document the location and depth of all scribe lines that are found. It is 

recommended that you use the format outlined in Appendix C to document the scribe line.

b. Do a laser measurement inspection or the optical micrometer inspection to measure the 

maximum depth of the scribe line.

NOTE: Only the laser measurement inspection as given in 767 NDT, Part 10, 53-30-01 can

be used to confirm scribe line depth less than 0.001 inch.

c. If the scribe line is at a skin lap joint, document the minimum distance between the upper 

skin lower edge and the scribe line.

(1) At skin lap joint locations, if the minimum distance between the upper skin lower edge 

and the scribe line is less than or equal to 0.10 inch, a detailed inspection must be 

performed along the skin lap joint from the butt joint forward of the damaged area to the 

butt joint aft of the damaged area. If the scribe line is located greater than 0.10 inch 

from the upper skin lower edge, then a detailed inspection is only required in the local 

area common to the scribe line. 

(2) If a door cutout breaks up a skin panel between butt joints, then do a detailed inspection 

from butt joint to door cutout instead of butt joint to butt joint. 

d. If the scribe line depth is less than 0.001 inch, no further work or inspection is required at 

that location provided: 

(1) No depth along this scribe line is greater than or equal to 0.001 inch.

Group 12: 

Group 12 - Table 12 - Scribe Line Inspections

Area Zone 1 Zone 2 Zone 3

Skin Lap Joints Figure 12 Figure 24 Figure 36

External Approved 

Repairs

Figure 48 (a) (a)

External Features (a) Figure 60 (a)

Decals (a) (a) Figure 72

(a) No inspection is required for this area and zone at this inspection threshold. 
 

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(2) The correct sealant removal procedure is implemented for all future work. Refer to 

Appendix A of this service bulletin for an accepted sealant removal procedure.

(3) Do Part 7 - Surface Finish Restoration of this Service Bulletin.

e. At any location, if the scribe line is greater than or equal to 0.001 inch, do special detailed 

inspection(s) of the scribe line as given in Part 5 - Special Detailed Inspections - Scribe Lines 

of this service bulletin to detect any crack. 

NOTE: The applicable special detailed inspection(s) of the scribe line must be

accomplished prior to a repair proposal to verify that no crack exists in or around

the scribe line. 

7. PART 5 - SPECIAL DETAILED INSPECTIONS - SCRIBE LINES

NOTE: The special detailed inspections are for areas where scribe line depth is greater than or

equal to 0.001 inches. 

a. Scribe line at Skin Lap Joint Location:

NOTE: At skin lap joint locations, if the minimum distance between the upper skin lower

edge and the scribe line is less than or equal to 0.10 inch, a special detailed

inspection must be performed along the skin lap joint from the butt joint forward of

the damaged area to the butt joint aft of the damaged area. The butt joint to butt

joint special detailed inspection must include an ultrasonic inspection or an

ultrasonic phased array inspection to detect cracks in any hidden scribe lines. If the

scribe line is located greater than 0.10 inch from the upper skin lower edge, then a

special detailed inspection is only required in the local area common to the scribe

line. 

If any zone or area along a skin lap joint is inspected as given in Part 5 - SPECIAL 

DETAILED INSPECTIONS - SCRIBE LINES, during any initial zone inspection 

caused by the requirement to inspect from butt joint to butt joint for findings of a 

scribe line within 0.10 inch of the upper skin lower edge, then that zone or area 

does not require inspection during any subsequent initial zone inspection. 

If a door cutout breaks up a skin panel between butt joints, then do a special 

detailed inspection from butt joint to door cutout instead of butt joint to butt joint. 

(1) Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected skin lap joints as follows:

(a) Do a High Frequency Eddy Current (HFEC) inspection as given in 767 NDT, Part 

6, 51-00-01 or 767 NDT, Part 6, 51-00-19 to detect any cracks that are located 

greater than 0.063 inch from the upper skin lower edge. 

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the upper skin lower edge. 

(c) Do an Ultrasonic (UT) inspection as given in 767 NDT, Part 4, 53-00-01 to detect 

any cracks located at the upper skin lower edge and up to 0.03 inch under the 

upper skin in the lap joint faying surface area.
 

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NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the upper skin lower edge and up to 0.03 inch under the upper skin 

in the skin lap joint faying surface area.

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(2) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(3) If no crack is found and the scribe line is greater than or equal to 0.001 inch and less 

than or equal to 0.006 inch, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 

NOTE: A repair is not required until the repair threshold is reached, provided the

operator chooses to do the Limited Return To Service (LRTS) repeat

inspection program as given in Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to do the 

LRTS repeat inspection program.

or

(b) Do the LRTS repeat inspection program as given in Part 6 of this service bulletin. 

(4) If no crack is found and the scribe line is greater than 0.006 inch deep, document and 

propose a repair to Boeing. This will assist Boeing in the analysis of the scribe line 

damage and repair proposal. 

NOTE: The LRTS repeat inspection program is not an option for scribe lines greater

than 0.006 inch deep.

(5) Do Part 7 - Surface Finish Restoration of this service bulletin. 
 

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b. Scribe Line at External Approved Repair:

NOTE: If a scribe line is detected and is within 0.10 inch of an external approved repair, the

entire periphery of the external approved repair must be inspected. The special

detailed inspection for the entire periphery of the external approved repair must

include an ultrasonic inspection or an ultrasonic phased array inspection to detect

cracks in any hidden scribe lines. If the scribe line is located greater than 0.10 inch

from the external approved repair, then the inspection is only required in the local

area common to the scribe line.

(1) Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected external approved repairs as follows: 

(a) Do a HFEC inspection as given in 767 NDT, Part 6, 51-00-01 or 767 NDT, Part 6, 

51-00-19 to detect any cracks that are located greater than 0.063 inch from the 

external approved repair.

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inches of the external approved repair.

(c) Do an UT inspection as given in 767 NDT, Part 4, 53-00-01 to detect any cracks 

located at the external approved repair edge and up to 0.03 inch under the 

external approved repair in the repair faying surface area.

NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the external approved repair and up to 0.03 inch under the external 

approved repair in the repair faying surface area.

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(2) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(3) If no crack is found and the scribe line is greater than or equal to 0.001 inch and less 

than or equal to 0.006 inch, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 
 

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NOTE: A repair is not required until the repair threshold is reached, provided the

operator chooses to do the LRTS repeat inspection program as given in

Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to do the 

LRTS repeat inspection program.

or

(b) Do the LRTS repeat inspection program as given in Part 6 of this service bulletin. 

(4) If no crack is found and the scribe line is greater than 0.006 inch deep, document and 

propose a repair to Boeing. This will assist Boeing in the analysis of the scribe line 

damage and repair proposal. 

NOTE: The LRTS repeat inspection program is not an option for scribe lines greater

than 0.006 inch deep.

(5) Do Part 7 - Surface Finish Restoration of this service bulletin. 

c. Scribe Line at External Feature:

NOTE: If a scribe line is detected and is within 0.10 inch of an external feature, the entire

periphery of the external feature must be inspected. The special detailed inspection

for the entire periphery of the external feature must include an ultrasonic inspection

or an ultrasonic phased array inspection to detect cracks in any hidden scribe lines.

If the scribe line is located greater than 0.10 inch from the external feature, then the

inspection is only required in the local area common to the scribe line.

(1) Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected external features as follows: 

(a) Do a HFEC inspection as given in 767 NDT, Part 6, 51-00-01 or 767 NDT, Part 6, 

51-00-19 to detect any cracks that are located greater than 0.063 inch from the 

external feature.

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the external feature. 

(c) Do an UT inspection as given in 767 NDT, Part 4, 53-00-01 to detect any cracks 

located at the external feature and up to 0.03 inch under the external feature in the 

mating surface area.
 

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NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the external feature and up to 0.03 inch under the external feature 

in the mating surface area.

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(2) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(3) If no crack is found and the scribe line is greater than or equal to 0.001 inch and less 

than or equal to 0.006 inch, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 

NOTE: A repair is not required until the repair threshold is reached, provided the

operator chooses to do the LRTS repeat inspection program as given in

Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to do the 

LRTS repeat inspection program.

or

(b) Do the LRTS repeat inspection program as given in Part 6 of this service bulletin. 

(4) If no crack is found and the scribe line is greater than 0.006 inch deep, document and 

propose a repair to Boeing. This will assist Boeing in the analysis of the scribe line 

damage and repair proposal. 

NOTE: The LRTS repeat inspection program is not an option for scribe lines greater

than 0.006 inch deep.

(5) Do Part 7 - Surface Finish Restoration of this service bulletin. 
 

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d. Scribe Line at Decals: 

(1) Do the special detailed inspection of the fuselage skin to detect any crack at all affected 

decals as follows: 

(a) Do a HFEC inspection as given in 767 NDT, Part 6, 51-00-01 or 767 NDT, Part 6, 

51-00-19 to detect any crack at all affected decals.

(2) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(3) If no crack is found and the scribe line is greater than or equal to 0.001 inch and less 

than or equal to 0.006 inch, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 

NOTE: A repair is not required until the repair threshold is reached, provided the

operator chooses to do the LRTS repeat inspection program as given in

Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to do the 

LRTS repeat inspection program.

or

(b) Do the LRTS repeat inspection program as given in Part 6 of this service bulletin. 

(4) If no crack is found and the scribe line is greater than 0.006 inch deep, document and 

propose a repair to Boeing. This will assist Boeing in the analysis of the scribe line 

damage and repair proposal. 

NOTE: The LRTS repeat inspection program is not an option for scribe lines greater

than 0.006 inch deep.

(5) Do Part 7 - Surface Finish Restoration of this service bulletin. 

8. PART 6 - LIMITED RETURN TO SERVICE (LRTS) PROGRAM 

a. Skin Lap Joints - Repeat Inspection:

(1) Determine which areas of the skin lap joints require inspection. 

NOTE: If any scribe line is found within 0.10 inch of the skin lap joint upper skin lower

edge, then the LRTS inspections for cracks must be accomplished for the

entire skin lap joint from butt joint to butt joint. The butt joint to butt joint special

detailed inspection must include an ultrasonic inspection or an ultrasonic

phased array inspection to detect cracks in any hidden scribe lines. However,

the entire lap joint does not need to be inspected at the same time. Each area

along the lap joint may be inspected at its associated LRTS inspection interval.

(2) If applicable, do Part 1 - Surface Preparation - Scribe Line Inspection as given in this 

service bulletin.
 

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NOTE: As given in 767 NDT, Part 4, 53-00-02, accomplishment of the UT phased

array inspection does not require paint removal provided the paint is less than

0.007 inch thick. 

(3) Do a detailed inspection of the fuselage skin to detect any crack at all affected lap 

joints. The use of a minimum 10X magnifying lens is required for this inspection.

(4) Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected skin lap joints as follows:

(a) Do a High Frequency Eddy Current (HFEC) inspection as given in 767 NDT, Part 

6, 51-00-01 or 767 NDT, Part 6, 51-00-19 to detect any cracks that are located 

greater than 0.063 inch from the upper skin lower edge. 

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the upper skin lower edge. 

(c) Do an Ultrasonic (UT) inspection as given in 767 NDT, Part 4, 53-00-01 to detect 

any cracks located at the upper skin lower edge and up to 0.030 inch under the 

upper skin in the lap joint faying surface area.

NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the upper skin lower edge and up to 0.03 inch under the upper skin 

in the skin lap joint faying surface area.

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(5) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(6) If no crack is found, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 

or

(b) Repeat the LRTS program as given in this service bulletin. 
 

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ALERT ALERT

(7) Do Part 7 - Surface Finish Restoration of this service bulletin. 

b. External Approved Repair - Repeat Inspection:

(1) Determine which external approved repairs require inspections. 

NOTE: If a scribe line is detected and is within 0.10 inch of an external approved

repair, the entire periphery of the external approved repair must be inspected.

The special detailed inspection for the entire periphery of the external

approved repair must include an ultrasonic inspection or an ultrasonic phased

array inspection to detect cracks in any hidden scribe lines. If the scribe line is

located greater than 0.10 inch from the external approved repair, then the

inspection is only required in the local area common to the scribe line.

(2) If applicable, do Part 1 - Surface Preparation - Scribe Line Inspection as given in this 

service bulletin.

NOTE: As given in 767 NDT, Part 4, 53-00-02, accomplishment of the UT phased

array inspection does not require paint removal provided the paint is less than

0.007 inch thick. 

(3) Do a detailed inspection of the fuselage skin to detect any crack at all affected external 

approved repair areas. The use of a minimum 10X magnifying lens is required for this 

inspection.

(4) Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected external approved repairs as follows:

(a) Do a High Frequency Eddy Current (HFEC) inspection as given in 767 NDT, Part 

6, 51-00-01 or 767 NDT, Part 6, 51-00-19 to detect any cracks that are located 

greater than 0.063 inch from the external approved repair. 

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the external approved repair. 

(c) Do an Ultrasonic (UT) inspection as given in 767 NDT, Part 4, 53-00-01 to detect 

any cracks located at the external approved repair edge and up to 0.03 inch under 

the external approved repair in the repair faying surface area.

NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the external approved repair and up to 0.03 inch under the external 

approved repair in the faying surface area.
 

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NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(5) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(6) If no crack is found, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 

or

(b) Repeat the LRTS program as given in this service bulletin. 

(7) Do Part 7 - Surface Finish Restoration of this service bulletin. 

c. External Features - Repeat Inspection:

(1) Determine which external features require inspections. 

NOTE: If a scribe line is detected and is within 0.10 inch of an external feature, the

entire periphery of the external feature must be inspected. The special

detailed inspection for the entire periphery of the external feature must include

an ultrasonic inspection or an ultrasonic phased array inspection to detect

cracks in any hidden scribe lines If the scribe line is located greater than 0.10

inch from the external feature, then the inspection is only required in the local

area common to the scribe line.

(2) If applicable, do Part 1 - Surface Preparation - Scribe Line Inspection as given in this 

service bulletin.

NOTE: As given in 767 NDT, Part 4, 53-00-02, accomplishment of the UT phased

array inspection does not require paint removal provided the paint is less than

0.007 inch thick. 

(3) Do a detailed inspection of the fuselage skin to detect any crack at all affected external 

approved repair areas. The use of a minimum 10X magnifying lens is required for this 

inspection.

(4) Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected external features as follows:

(a) Do a High Frequency Eddy Current (HFEC) inspection as given in 767 NDT, Part 

6, 51-00-01 or 767 NDT, Part 6, 51-00-19 to detect any cracks that are located 

greater than 0.063 inch from the external feature. 

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the external feature. 
 

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(c) Do an Ultrasonic (UT) inspection as given in 767 NDT, Part 4, 53-00-01 to detect 

any cracks located at the external feature and up to 0.03 inch under the external 

feature in the mating surface area.

NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the external feature and up to 0.03 inch under the external feature 

in the mating surface area.

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(5) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(6) If no crack is found, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 

or

(b) Repeat the LRTS program as given in this service bulletin. 

(7) Do Part 7 - Surface Finish Restoration of this service bulletin. 

d. Decals - Repeat Inspection:

(1) Determine which decal areas require inspections. 

(2) If applicable, do Part 1 - Surface Preparation - Scribe Line Inspection as given in this 

service bulletin.

(3) Do a detailed inspection of the fuselage skin to detect any crack at all affected decal 

areas. The use of a minimum 10X magnifying lens is required for this inspection.

(4) Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected decal areas as follows:
 

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(a) Do a High Frequency Eddy Current (HFEC) inspection as given in 767 NDT, Part 

6, 51-00-01 or 767 NDT, Part 6, 51-00-19 to detect any crack at all affected decal 

areas. 

(5) If any crack is found, document and propose a repair to Boeing. This will assist Boeing 

in the analysis of the crack and repair proposal. 

(6) If no crack is found, do one of the options that follows: 

(a) Document and propose a repair to Boeing. This will assist Boeing in the analysis 

of the scribe line damage and repair proposal. 

or

(b) Repeat the LRTS program as given in this service bulletin. 

(7) Do Part 7 - Surface Finish Restoration of this service bulletin. 

9. PART 7 - SURFACE FINISH RESTORATION

NOTE: To reduce the possibility of future scribing, Boeing recommends that the BMS 5-95 fillet

seal not be reapplied except as follows:

1. In the gap at butt joints.

2. The leading edge of the external approved repair doublers for repairs that will be 

inspected under the LRTS program.

3. Around external features as given in the applicable AMM section.

a. Refinish the external surface finish as follows:

(1) Apply Type 2, Class A chemical conversion coating. Refer to SOPM 20-43-03 as an 

accepted procedure.

(2) Apply BMS 10-72 paint system (primer plus enamel), or BMS 10-79 Type II (primer) 

plus BMS 10-60 Type II (topcoat), or the operator’s normal decorative paint system. 

Refer to 767 AMM 51-21-10 as an accepted procedure.

b. If applicable, refinish the internal surface finish as follows:

(1) Apply Type 2, Class A chemical conversion coating. Refer to SOPM 20-43-03 as an 

accepted procedure.

(2) Apply BMS 10-11 Type 1 primer. 

c. For external approved repairs that will be inspected under the LRTS program, apply a fillet 

seal of BMS 5-95 sealant at the leading edge of the external approved repair. Refer to 767 

AMM 51-31-01 as an accepted procedure.

d. For external approved repairs around which no scribe lines were found, apply a fillet seal 

around the periphery of the external approved repair. Refer to 767 AMM 51-31-01 as an 

accepted procedure.
 

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e. Put the airplane back to a serviceable condition.

10. PART 8 - EXISTING SCRIBE LINE DAMAGE - OUTSIDE OF ZONES 1, 2, AND 3

If scribe lines are found outside of Zones 1, 2, and 3, do what follows: 

a. Do Part 1 - Surface Preparation - Scribe Line Inspections of this service bulletin. 

b. Measure and document the location and depth of all scribe lines that are found. It is 

recommended that you use the format outlined in Appendix C to document the scribe line.

c. Do a laser measurement inspection or the optical micrometer inspection to measure the 

maximum depth of the scribe line.

NOTE: Only the laser measurement inspection as given in 767 NDT, PART 10, 53-30-01

can be used to confirm scribe line depth less than 0.001 inch.

d. If the scribe line depth is less than 0.001 inch, no further work or inspection is required at 

that location provided: 

(1) No depth along this scribe line is greater than or equal to 0.001 inch.

(2) The correct sealant removal procedure is implemented for all future work. Refer to 

Appendix A of this service bulletin for an accepted sealant removal procedure.

(3) Do Part 7 - Surface Finish Restoration of this service bulletin. 

e. At any location, if the scribe line is greater than or equal to 0.001 inch, do what follows: 

(1) Scribe Line at Skin Lap Joint Location - Special Detailed Inspection 
 

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NOTE:

1. If a scribe line is detected and is within 0.10 inch of the upper skin lower 

edge, a special detailed inspection must be performed along the skin lap 

joint from the butt joint forward of the damaged area to the butt joint aft of 

the damaged area. The butt joint to butt joint special detailed inspection 

must include an ultrasonic inspection or an ultrasonic phased array 

inspection to detect cracks in any hidden scribe lines. If the scribe line is 

located greater than 0.10 inch from the upper skin lower edge, then a 

special detailed inspection is only required in the local area common to 

the scribe line. 

2. If any zone or area along a skin lap joint is inspected as given in Part 5 - 

SPECIAL DETAILED INSPECTIONS - SCRIBE LINES, during any initial 

zone inspection caused by the requirement to inspect from butt joint to 

butt joint for findings of a scribe line within 0.10 inch of the upper skin 

lower edge, then that zone or area does not require inspection during any 

subsequent initial zone inspection, including its own.

3. If a door cutout breaks up a skin panel between butt joints, then do a 

special detailed inspection from butt joint to door cutout instead of butt 

joint to butt joint. 

Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected skin lap joints as follows:

(a) Do a High Frequency Eddy Current (HFEC) inspection as given in 767 NDT, Part 

6, 51-00-01 or 767 NDT, Part 6, 51-00-19 to detect any cracks that are located 

greater than 0.063 inch from the upper skin lower edge. 

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the upper skin lower edge. 

(c) Do an Ultrasonic (UT) inspection as given in 767 NDT, Part 4, 53-00-01 to detect 

any cracks located at the upper skin lower edge and up to 0.03 inch under the 

upper skin in the skin lap joint faying surface area.

NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the upper skin lower edge and up to 0.03 inch under the upper skin 

in the skin lap joint faying surface area.
 

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ALERT ALERT

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(e) If any crack is found, document and propose a repair to Boeing. This will assist 

Boeing in the analysis of the crack and repair proposal. 

(f) If no crack is found and the scribe line is greater than or equal to 0.001 inch and 

less than or equal to 0.004 inch, no further work or inspection is required at that 

location, provided the correct sealant removal procedure is implemented for all 

future work. Refer to Appendix A of this service bulletin for an accepted sealant 

removal procedure

(g) If no crack is found and the scribe line is greater than 0.004 inch and less than or 

equal to 0.006 inch, do one of the options that follows: 

1) Document and propose a repair to Boeing. This will assist Boeing in the 

analysis of the scribe line damage and repair proposal. 

NOTE: A repair is not required until the repair threshold is reached, provided

the operator chooses to do the Limited Return To Service (LRTS)

program repeat inspection as given in Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to 

do the LRTS repeat inspection program.

or

2) Do the LRTS repeat inspection program as given in Part 6 of this service 

bulletin. 

(h) If no crack is found and the scribe line is greater than 0.006 inch deep, document 

and propose a repair to Boeing. This will assist Boeing in the analysis of the scribe 

line damage and repair proposal. 

NOTE: The LRTS repeat inspection program is not an option for scribe lines

greater than 0.006 inch deep.

(i) Do Part 7 - Surface Finish Restoration of this service bulletin. 

(2) Scribe Line at External Approved Repair - Special Detailed Inspection:
 

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ALERT ALERT

NOTE: If a scribe line is detected and is within 0.10 inch of an external approved

repair, the entire periphery of the external approved repair must be inspected.

The special detailed inspection for the entire periphery of the external

approved repair must include an ultrasonic inspection or an ultrasonic phased

array inspection to detect cracks in any hidden scribe lines. If the scribe line is

located greater than 0.10 inch from the external approved repair, then the

inspection is only required in the local area common to the scribe line.

Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected external approved repairs as follows: 

(a) Do a HFEC inspection as given in 767 NDT, Part 6, 51-00-01 or 767 NDT, Part 6, 

51-00-19 to detect any cracks that are located greater than 0.063 inch from the 

external approved repair.

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the external approved repair.

(c) Do an UT inspection as given in 767 NDT, Part 4, 53-00-01 to detect any cracks 

located at the external approved repair edge and up to 0.03 inch under the 

external approved repair in the repair faying surface area.

NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the external approved repair and up to 0.03 inch under the external 

approved repair in the repair faying surface area.

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(e) If any crack is found, document and propose a repair to Boeing. This will assist 

Boeing in the analysis of the crack and repair proposal. 

(f) If no crack is found and the scribe line is greater than or equal to 0.001 inch and 

less than or equal to 0.004 inch, no further work or inspection is required at that 

location, provided the correct sealant removal procedure is implemented for all 

future work. Refer to Appendix A of this service bulletin for an accepted sealant 

removal procedure
 

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(g) If no crack is found and the scribe line is greater than 0.004 inch and less than or 

equal to 0.006 inch, do one of the options that follows: 

1) Document and propose a repair to Boeing. This will assist Boeing in the 

analysis of the scribe line damage and repair proposal. 

NOTE: A repair is not required until the repair threshold is reached, provided

the operator chooses to do the Limited Return To Service (LRTS)

program repeat inspection as given in Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to 

do the LRTS repeat inspection program.

or

2) Do the LRTS program repeat inspection as given in Part 6 of this service 

bulletin. 

(h) If no crack is found and the scribe line is greater than 0.006 inch deep, document 

and propose a repair to Boeing. This will assist Boeing in the analysis of the scribe 

line damage and repair proposal. 

NOTE: The LRTS repeat inspection program is not an option for scribe lines

greater than 0.006 inch deep.

(i) Do Part 7 - Surface Finish Restoration of this service bulletin. 

(3) Scribe Line at External Feature - Special Detailed Inspection:

NOTE: If a scribe line is detected and is within 0.10 inch of an external feature, the

entire periphery of the external feature must be inspected. The special

detailed inspection for the entire periphery of the external feature must include

an ultrasonic inspection or an ultrasonic phased array inspection to detect

cracks in any hidden scribe lines. If the scribe line is located greater than 0.10

inch from the external feature, then the inspection is only required in the local

area common to the scribe line.

Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected external features as follows: 

(a) Do a HFEC inspection as given in 767 NDT, Part 6, 51-00-01 or 767 NDT, Part 6, 

51-00-19 to detect any cracks that are located greater than 0.063 inch from the 

external feature.

(b) Do a HFEC inspection as given in 767 NDT, Part 6, 53-00-09 to detect any cracks 

that are located within 0.063 inch of the external feature.

(c) Do an UT inspection as given in 767 NDT, Part 4, 53-00-01o detect any cracks 

located at the external feature and up to 0.03 inch under the external feature in the 

mating surface area.
 

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NOTE: The skin thickness must be known when conducting the UT inspection as

the technique has application limitations based upon skin thickness as

given in 767 NDT, Part 4, 53-00-01. Refer to applicable Boeing drawings

if the skin thickness is not known. Contact Boeing for procedures to

inspect skin with thickness greater than that allowed in the UT inspection

techniques.

(d) As an alternative, an UT phased array inspection as given in 767 NDT, Part 4, 

53-00-02 can be used to replace the above UT inspection as given in 767 NDT, 

Part 4, 53-00-01 and the above HFEC inspection as given in 767 NDT, Part 6, 

53-00-09. This UT phased array inspection is to detect any cracks located within 

0.063 inch of the external feature and up to 0.03 inch under the external feature 

in the external feature mating surface area.

NOTE: The skin thickness must be known when conducting the UT phased array

inspection as the technique has application limitations based upon skin

thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable

Boeing drawings if the skin thickness is not known. Contact Boeing for

procedures to inspect skin with thickness greater than that allowed in the

UT phased array inspection techniques.

(e) If any crack is found, document and propose a repair to Boeing. This will assist 

Boeing in the analysis of the crack and repair proposal. 

(f) If no crack is found and the scribe line is greater than or equal to 0.001 inch and 

less than or equal to 0.004 inch, no further work or inspection is required at that 

location, provided the correct sealant removal procedure is implemented for all 

future work. Refer to Appendix A of this service bulletin for an accepted sealant 

removal procedure

(g) If no crack is found and the scribe line is greater than 0.004 inch and less than or 

equal to 0.006 inch, do one of the options that follows: 

1) Document and propose a repair to Boeing. This will assist Boeing in the 

analysis of the scribe line damage and repair proposal. 

NOTE: A repair is not required until the repair threshold is reached, provided

the operator chooses to do the Limited Return To Service (LRTS)

program repeat inspection as given in Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to 

do the LRTS repeat inspection program.

or

2) Do the LRTS repeat inspection program as given in Part 6 of this service 

bulletin. 

(h) If no crack is found and the scribe line is greater than 0.006 inch deep, document 

and propose a repair to Boeing. This will assist Boeing in the analysis of the scribe 

line damage and repair proposal. 
 

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NOTE: The LRTS repeat inspection program is not an option for scribe lines

greater than 0.006 inch deep.

(i) Do Part 7 - Surface Finish Restoration of this service bulletin. 

(4) Scribe Line at Decals - Special Detailed Inspection:

Do the special detailed inspections of the fuselage skin to detect any crack at all 

affected decals as follows: 

(a) Do a HFEC inspection as given in 767 NDT, Part 6, 51-00-01 or 767 NDT, Part 6, 

51-00-19 to detect any crack at all affected decals.

(b) If any crack is found, document and propose a repair to Boeing. This will assist 

Boeing in the analysis of the crack and repair proposal. 

(c) If no crack is found and the scribe line is greater than or equal to 0.001 inch and 

less than or equal to 0.004 inch, no further work or inspection is required at that 

location, provided the correct sealant removal procedure is implemented for all 

future work. Refer to Appendix A of this service bulletin for an accepted sealant 

removal procedure

(d) If no crack is found and the scribe line is greater than 0.004 inch and less than or 

equal to 0.006 inch, do one of the options that follows: 

1) Document and propose a repair to Boeing. This will assist Boeing in the 

analysis of the scribe line damage and repair proposal. 

NOTE: A repair is not required until the repair threshold is reached, provided

the operator chooses to do the Limited Return to Service (LRTS)

program repeat inspection as given in Part 6 of this service bulletin.

A repair proposal is only required if the operator has chosen not to 

do the Limited Return to Service (LRTS) repeat inspection program.

or

2) Do the Limited Return to Service (LRTS) program repeat inspection as given 

in Part 6 of this service bulletin. 

(e) If no crack is found and the scribe line is greater than 0.006 inch deep, document 

and propose a repair to Boeing. This will assist Boeing in the analysis of the scribe 

line damage and repair proposal. 

NOTE: The Limited Return to Service (LRTS) repeat inspection program is not

an option for scribe lines greater than 0.006 inch deep.

(f) Do Part 7 - Surface Finish Restoration of this service bulletin. 
 FIGURE 1: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 1)

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 1: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 1) STA 246 STA 434 STA 618 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 212 STA 287 STA 676 STA 654 STA 456 STA 610 STA 698 STA 764 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 720 STA 188.9 S-13R S-13L STA 1540STA 1562

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 1:

STA

132.5

STA

632

STA

742

STA

588

STA

1351

STA

1480

STA

1329

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1508551

(SHEET 1 OF 2)
 FIGURE 1: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 1)

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-36R, STA 434 To STA 456

S-36R, STA 632 To STA 676

S-26R, STA 434 To STA 456

S-26R, STA 654 To STA 742

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 720

S-17L, STA 246 To STA 434

S-17L, STA 654 To STA 742

S-26L, STA 588 To STA 632

S-36L, STA 434 To STA 764

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1395 To STA 1540 - (a)

S-8R, STA 1417 To STA 1461

S-2R, STA 1417 To STA 1562

S-17L, STA 1307 To STA 1329

S-26L, STA 1307 To STA 1395

S-36L, STA 1307 To STA 1351

S-36L, STA 1480 To STA 1540

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens 

to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS. 

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along

the edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of

the upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly

under the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn

slightly away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 2: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 2)

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ALERT ALERT

FIGURE 2: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 2) STA 246 STA 434 STA 610 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 632 STA 500 STA 698 STA 764 STA 1065 STA 1582 STA 1832 STA 1307 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 615 STA 478 STA 654STA 676STA 720 STA 1540 STA 1562

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 2:

STA

212

STA

287

STA

132.5

STA

1480

STA

1351

STA

1329

STA

742

STA

588

LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1509796

(SHEET 1 OF 2)
 FIGURE 2: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-36R, STA 434 To STA 500

S-26R, STA 434 To STA 478

S-26R, STA 676 To STA 742

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 720

S-17L, STA 246 To STA 434

S-17L, STA 654 To STA 742

S-26L, STA 588 To STA 632

S-36L, STA 434 To STA 764

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1395 To STA 1540 - (a)

S-8R, STA 1417 To STA 1461

S-2R, STA 1417 To STA 1562

S-17L, STA 1307 To STA 1329

S-26L, STA 1307 To STA 1395

S-36L, STA 1307 To STA 1351

S-36L, STA 1480 To STA 1540

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens 

to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along

the edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of

the upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly

under the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn

slightly away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 3: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 3)

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ALERT ALERT

FIGURE 3: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 3) STA 246 STA 434 STA 618 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 676 STA 632 STA 456STA 588 STA 698 STA 764 STA 1065 STA 1582 STA 1832 STA 1307 STA 1480 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 STA 1540 INSPECTION AREA EXISTING BUTT JOINT STA 720 STA 1562

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 3:

STA

212

STA

287

S-13R

S-13L

STA

132.5

STA

742

STA

654 STA

1351

STA

1329

LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1520587

(SHEET 1 OF 2)
 FIGURE 3: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-36R, STA 434 To STA 456

S-36R, STA 632 To STA 676

S-26R, STA 434 To STA 456

S-26R, STA 654 To STA 742

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 720

S-17L, STA 246 To STA 434

S-17L, STA 654 To STA 742

S-26L, STA 588 To STA 632

S-36L, STA 434 To STA 764

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1395 To STA 1540 - (a)

S-8R, STA 1417 To STA 1461

S-2R, STA 1417 To STA 1562

S-17L, STA 1307 To STA 1329

S-26L, STA 1307 To STA 1395

S-36L, STA 1307 To STA 1351

S-36L, STA 1480 To STA 1540

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens 

to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along

the edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of

the upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly

under the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn

slightly away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 4: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 4)

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ALERT ALERT

FIGURE 4: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 4) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 632 STA 500 STA 610 STA 676 STA 1065 STA 1582 STA 1832 STA 1307 STA 1351 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 654 STA 188.9 INSPECTION AREA EXISTING BUTT JOINT S-13L STA 698 STA 764 STA 720 STA 478 STA 1540 STA 1562 STA 615

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 4:

STA

212

STA

287

S-13R

STA

132.5

STA

742

STA

588

STA

1480

STA

1329

LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1521783

(SHEET 1 OF 2)
 FIGURE 4: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-36R, STA 434 To STA 500

S-26R, STA 434 To STA 478

S-26R, STA 676 To STA 742

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 720

S-17L, STA 246 To STA 434

S-17L, STA 654 To STA 742

S-26L, STA 588 To STA 632

S-36L, STA 434 To STA 764

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1395 To STA 1540 - (a)

S-8R, STA 1417 To STA 1461

S-2R, STA 1417 To STA 1562

S-17L, STA 1307 To STA 1329

S-26L, STA 1307 To STA 1395

S-36L, STA 1307 To STA 1351

S-36L, STA 1480 To STA 1540

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens 

to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along

the edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of

the upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly

under the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn

slightly away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 5: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 5)

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ALERT ALERT

FIGURE 5: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 5) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 654+88 STA 1065 STA 1832 STA 1307STA 1351 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 1562 STA 1417 STA 618 STA 632 STA 654+44STA 654+110 STA 654 STA 1197+22 STA 1197+132 STA 1582 STA 1346 STA 1270 INSPECTION AREA EXISTING BUTT JOINT STA 456 STA 1219 STA 1502STA 1518 STA 1285 STA 610

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 5:

STA

188.9

S-13L

STA

212

STA

287

S-13R

STA

132.5

STA

698

STA

1373

LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1521792

(SHEET 1 OF 2)
 FIGURE 5: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 5)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. 

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-26R, STA 654+88 To STA 698

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 654+44

S-17L, STA 246 To STA 434

S-26L, STA 610 To STA 654+88

S-36L, STA 654 To STA 654+88

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1417 To STA 1562 - (a)

S-8R, STA 1197+22 To STA 1197+132

S-2R, STA 1417 To STA 1582

S-8L, STA 1197+22 To STA 1197+132

S-26L, STA 1285 To STA 1373

S-36L, STA 1307 To STA 1351

S-36L, STA 1502 To STA 1582

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 6: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 6)

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ALERT ALERT

FIGURE 6: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 6) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 654+88 STA 1065 STA 1832 STA 1285 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 1540 STA 1439 STA 615 STA 610 STA 654+44STA 654+110 STA 632STA 654 STA 1197+22 STA 1197+132 STA 1562STA 1582 STA 1417 STA 1346 STA 1270 STA 1197+110 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1219 STA 1502 STA 500 STA 478 STA 1307

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 6:

STA

188.9

STA

212

STA

287

S-13R

STA

132.5

STA

1351

STA

698

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1521802

(SHEET 1 OF 2)
 FIGURE 6: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-26R, STA 434 To STA 478

S-26R, STA 654+88 To STA 698

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 654+44

S-17L, STA 246 To STA 434

S-26L, STA 610 To STA 654+88

S-36L, STA 654 To STA 654+88

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1417 To STA 1562 - (a)

S-8R, STA 1197+22 To STA 1197+132

S-2R, STA 1417 To STA 1582

S-8L, STA 1197+22 To STA 1197+132

S-26L, STA 1285 To STA 1373

S-36L, STA 1307 To STA 1351

S-36L, STA 1502 To STA 1582

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 7: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 7)

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ALERT ALERT

FIGURE 7: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 7) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 212 STA 287 STA 1065 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1439 STA 188.9 STA 618 STA 610 STA 654+44 STA 632STA 654 STA 1582 STA 1417 STA 1346 STA 1270 STA 1197+132 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 456 STA 1219 STA 1153 STA 654+88 STA 654+110 STA 1518 STA 1480STA 1502 STA 1285 STA 1175

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 7:

STA

1197+44

STA

698

STA

1351

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1521987

(SHEET 1 OF 2)
 FIGURE 7: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-26R, STA 654+88 To STA 698 

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 654+44

S-17L, STA 246 To STA 434

S-26L, STA 610 To STA 654+88

S-36L, STA 654 To STA 654+88

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1417 To STA 1502 - (a)

S-8R, STA 1197+44 To STA 1197+132

S-2R, STA 1417 To STA 1582

S-8L, STA 1197+44 To STA 1197+132

S-26L, STA 1285 To STA 1373

S-36L, STA 1307 To STA 1351

S-36L, STA 1502 To STA 1582

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 8: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 8)

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Revision 1: April 09, 2009 767-53A0193

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ALERT ALERT

FIGURE 8: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 8) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 1065 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1439 STA 615 STA 610 STA 654+44 STA 632STA 654 STA 1197+132 STA 1582 STA 1417 STA 1346 STA 1270 STA 1197+110 STA STA 1518 1502 STA 1219 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1153 STA 654+88 STA 654+88 STA 1480 STA 1285 STA 1175 STA 500 STA 478

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

STA

1461

This Figure applies to Group 8:

STA

132.5

STA

212

STA

287

STA

188.9

STA

698

STA

1197.44

STA

1351

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1521992

(SHEET 1 OF 2)
 FIGURE 8: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 8)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-26R, STA 434 To STA 478

S-26R, STA 654+88 To STA 698 

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 654+44

S-17L, STA 246 To STA 434

S-26L, STA 610 To STA 654+88

S-36L, STA 654 To STA 654+88

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1417 To STA 1502 - (a)

S-8R, STA 1197+44 To STA 1197+132

S-2R, STA 1417 To STA 1582

S-8L, STA 1197+44 To STA 1197+132

S-26L, STA 1285 To STA 1373

S-36L, STA 1307 To STA 1351

S-36L, STA 1502 To STA 1582

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 9: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 9)

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ALERT ALERT

FIGURE 9: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 9) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 1065 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 618 STA 610 STA 654+44 STA 676 STA 632STA 654 STA 1197+132 STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1502 STA 1518 STA 1219 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1197+44 STA 456 STA 654+22 STA 1480 STA 1285 STA 654+88

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 9:

STA

132.5

STA

212

STA

287

STA

188.9

STA

1351

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1522001

(SHEET 1 OF 2)
 FIGURE 9: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 9)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 654+44

S-17L, STA 246 To STA 434

S-26L, STA 610 To STA 654

S-36L, STA 654 To STA 654+88

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1417 To STA 1502 - (a)

S-8R, STA 1197+44 To STA 1197+132

S-2R, STA 1417 To STA 1582

S-8L, STA 1197+44 To STA 1197+132

S-26L, STA 1285 To STA 1373

S-36L, STA 1307 To STA 1351

S-36L, STA 1502 To STA 1582

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 10: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 10)

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ALERT ALERT

FIGURE 10: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 10) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 1065 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 615 STA 610 STA 654+44 STA 676 STA 632STA 654 STA 1197+132 STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1502 STA 1518 STA 1175 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1197+44 STA 1480 STA 1219 STA 654+22STA 654+88 STA 500 STA 478 STA 1285

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 10:

STA

132.5

STA

212

STA

287

STA

188.9

STA

1351

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1522005

(SHEET 1 OF 2)
 FIGURE 10: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 10)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-26R, STA 434 To STA 478

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 654+44

S-17L, STA 246 To STA 434

S-26L, STA 610 To STA 654

S-36L, STA 654 To STA 654+88

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1417 To STA 1502 - (a)

S-8R, STA 1197+44 To STA 1197+132

S-2R, STA 1417 To STA 1582

S-8L, STA 1197+44 To STA 1197+132

S-26L, STA 1285 To STA 1373

S-36L, STA 1307 To STA 1351

S-36L, STA 1502 To STA 1582

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 11: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 11)

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ALERT ALERT

FIGURE 11: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 11) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 1065 STA 1832 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 1439 STA 456 STA 654 STA 1582 STA 1417 STA 1219 STA 654+22 STA 1175 STA 1197+132 STA 1197+88 STA 1654 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1461 STA 1540 STA 1307

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 11:

STA

132.5

STA

212

STA

287

STA

188.9

STA

654+110

STA

742

STA

698

STA

1285

STA

1351

STA

1502

STA

1263

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1522008

(SHEET 1 OF 2)
 FIGURE 11: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 11)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-26R, STA 654+110 To STA 742

S-17R, STA 246 To STA 434

S-17L, STA 246 To STA 434

S-26L, STA 654+110 To STA 698

S-36L, STA 434 To STA 654+0

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-36R, STA 1417 To STA 1582 - (a)

S-8R, STA 1197+88 To STA 1219 

S-2R, STA 1285 To STA 1351

S-2R, STA 1417 To STA 1582

S-8L, STA 1175 To STA 1197+132

S-26L, STA 1263 To STA 1373

S-36L, STA 1307 To STA 1373

S-36L, STA 1502 To STA 1540

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 12: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 12)

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ALERT ALERT

FIGURE 12: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 12) STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 1065 STA 1832 STA 1241 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1307 STA 1395 STA 566 STA 654 STA 1373 STA 1197+154STA 1197+231 STA 654A+110 STA 1197+88 STA 1197+22STA 1197+110STA 1197+132 STA 1582 STA 654+22 STA 1197+66 STA 1417 STA 1461 STA 610STA 654A INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1285STA 1351 STA 654A+22 STA 478

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 12:

STA

132.5

STA

212

STA

287

STA

188.9

STA

654+110

STA

676

STA

1518

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1522010

(SHEET 1 OF 2)
 FIGURE 12: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 12)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-21R, STA 132.5 To STA 246 - (a)

S-13R, STA 212 To STA 246

S-13L, STA 212 To STA 246

S-21L, STA 132.5 To STA 246

2

Inspect Lower Skin S-37R, STA 287 To STA 434 - (a)

S-36R, STA 434 To STA 478

S-36R, STA 654A To STA 654

S-26R, STA 654A+22 To STA 654A+110

S-26R, STA 654+22 To STA 654+110

S-17R, STA 246 To STA 434

S-2R, STA 434 To STA 654A+110

S-17L, STA 246 To STA 434

S-26L, STA 566 To STA 654A

S-26L, STA 654A+110 To STA 676

S-37L, STA 287 To STA 434

3

Inspect Lower Skin S-2R, STA 1417 To STA 1518 - (a)

S-17L, STA 1307 To STA 1395

S-26L, STA 1241 To STA 1351

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 13: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 1)

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ALERT ALERT

FIGURE 13: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 1) STA 246 STA 434 STA 618 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 676 STA 654 STA 632 STA 610 STA 720STA 764 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 1109STA 1153 STA 1329 STA 1263 STA 1518STA 1540 STA 1175STA 1219 STA 1351 STA 500 STA 456

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 1:

STA

132.5

STA

196.5

STA

188.9

STA

1087

STA

742

STA

588

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1522011

(SHEET 1 OF 2)
 FIGURE 13: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 1)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-36R, STA 456 To STA 500 - (a)

S-36R, STA 676 To STA 786.1

S-8R, STA 434 To STA 764

S-2R, STA 720 To STA 764

S-8L, STA 434 To STA 786.1

S-17L, STA 434 To STA 632 

S-17L, STA 742 To STA 786.1 

S-26L, STA 434 To STA 588

S-26L, STA 632 To STA 764

2

Inspect Lower Skin S-26R, STA 1109 To STA 1175 - (a)

S-8R, STA 1087 To STA 1373

S-8L, STA 1087 To STA 1373 

S-17L, STA 1263 To STA 1307

S-17L, STA 1329 To STA 1461

S-26L, STA 1153 To STA 1307 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 14: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 2)

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ALERT ALERT

FIGURE 14: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 2) STA 132.5 STA 246 STA 434 STA 610 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 287 STA 632 STA 500STA 539 STA 720STA 764 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 1461 STA 188.9 STA 478 STA 654STA 676 STA 1417 STA 1263 STA 1175 STA 1219 STA 1351 STA 522

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 2:

STA

1329

STA

1087

STA

1109

STA

1153

STA

588

STA

742

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1522017

(SHEET 1 OF 2)
 FIGURE 14: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-36R, STA 654 To STA 786.1 - (a)

S-8R, STA 434 To STA 764

S-2R, STA 720 To STA 764

S-8L, STA 434 To STA 786.1

S-17L, STA 434 To STA 632

S-17L, STA 742 To STA 786.1

S-26L, STA 434 To STA 588

S-26L, STA 632 To STA 764

2

Inspect Lower Skin S-26R, STA 1109 To STA 1175 - (a)

S-8R, STA 1087 To STA 1373

S-8L, STA 1087 To STA 1373 

S-17L, STA 1263 To STA 1307

S-17L, STA 1329 To STA 1461

S-26L, STA 1153 To STA 1307

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 15: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 3)

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 15: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 3) STA 132.5 STA 246 STA 434 STA 618 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 287 STA 676 STA 654 STA 610 STA 720STA 764 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 STA 1329 STA 1263 STA 1153 STA 1109 STA 1219 STA 1351 STA 632 STA 456STA 500 STA 1175

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 3:

STA

1087

STA

742

STA

588

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1531120

(SHEET 1 OF 2)
 FIGURE 15: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 3)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-36R, STA 456 To STA 500 - (a)

S-36R, STA 676 To STA 786.1

S-8R, STA 434 To STA 764

S-2R, STA 720 To STA 764

S-8L, STA 434 To STA 786.1

S-17L, STA 434 To STA 632

S-17L, STA 742 To STA 786.1

S-26L, STA 434 To STA 588

S-26L, STA 632 To STA 764

2

Inspect Lower Skin S-26R, STA 1109 To STA 1175 - (a)

S-8R, STA 1087 To STA 1373

S-8L, STA 1087 To STA 1373 

S-17L, STA 1263 To STA 1307

S-17L, STA 1329 To STA 1461

S-26L, STA 1153 To STA 1307

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 16: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 4)

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ALERT ALERT

FIGURE 16: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 4) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 287 STA 610 STA 500 STA 632 STA 720STA 764 STA 1065 STA 1582 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 INSPECTION AREA EXISTING BUTT JOINT STA 1518 STA 1087 STA 1263 STA 676 STA 522 STA 478 STA 1175 STA 1153 STA 654 STA 1351 STA 1219 STA 539 STA 1109

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 4:

STA

1329

STA

742

STA

588

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1531195

(SHEET 1 OF 2)
 FIGURE 16: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 4)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-36R, STA 654 To STA 786.1 - (a)

S-8R, STA 434 To STA 764

S-2R, STA 720 To STA 764

S-8L, STA 434 To STA 786.1

S-17L, STA 434 To STA 632 

S-17L, STA 742 To STA 786.1 

S-26L, STA 434 To STA 588

S-26L, STA 632 To STA 764

2

Inspect Lower Skin S-26R, STA 1109 To STA 1175 - (a)

S-8R, STA 1087 To STA 1373

S-8L, STA 1087 To STA 1373 

S-17L, STA 1263 To STA 1307

S-17L, STA 1329 To STA 1461

S-26L, STA 1153 To STA 1307

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 17: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 5)

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ALERT ALERT

FIGURE 17: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 5) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 287 STA 654+88 STA 1065 STA 1832 STA 1307STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1461 STA 188.5 STA 618 STA 654+44 STA 742 STA 654 STA 1197+22 STA 1241 STA 1562STA 1582 STA 1417 STA 1346 STA 1270 STA 1197+110 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1219 STA 1540 STA 1197+66 STA 764 STA 1263 STA 1197+132 STA 1518 STA 1480STA 1502 STA 1285 STA 676 STA 654+121 STA 698 STA 1439 STA 610

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 5:

STA

654+22

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538570

(SHEET 1 OF 2)
 FIGURE 17: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 5)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-26R, STA 654+22 To STA 654+88 - (a)

S-8R, STA 434 To STA 654

S-2R, STA 654+44 To STA 654+88

S-8L, STA 434 To STA 654

S-17L, STA 434 To STA 654 

S-26L, STA 434 To STA 610

S-26L, STA 654+88 To STA 676 

S-36L, STA 434 To STA 654 

2

Inspect Lower Skin S-36R, STA 1197+66 To STA 1219 - (a)

S-17R, STA 1197+22 To STA 1197+132 

S-17R, STA 1395 To STA 1461

S-8R, STA 1241 To STA 1373

S-8R, STA 1417 To STA 1461

S-8L, STA 1241 To STA 1373 

S-17L, STA 1197+110 To STA 1219

S-17L, STA 1307 To STA 1461

S-36L, STA 1241 To STA 1307 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 18: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 6)

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ALERT ALERT

FIGURE 18: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 6) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 287 STA 654+88 STA 1065 STA 1832 STA 1307STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 1540 STA 1439 STA 188.5 STA 615 STA 654+44 STA 764 STA 654 STA 1197+22STA 1197+132 STA 1562STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1197+110 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1219 STA 1197+66 STA 1263 STA 632 STA 500 STA 742 STA 1241 STA 1285 STA 676STA 698 STA 478 STA 1480STA 1518 STA 1502 STA 610

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 6:

STA

654+22

STA

522

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538690

(SHEET 1 OF 2)
 FIGURE 18: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-36R, STA 434 To STA 522 - (a)

S-26R, STA 654+22 To STA 654+88

S-8R, STA 434 To STA 654

S-2R, STA 654+44 To STA 654+88

S-8L, STA 434 To STA 654

S-17L, STA 434 To STA 654 

S-26L, STA 434 To STA 610

S-26L, STA 654+88 To STA 676

S-36L, STA 434 To STA 654

2

Inspect Lower Skin S-36R, STA 1197+66 To STA 1219 - (a)

S-17R, STA 1197+22 To STA 1197+132 

S-17R, STA 1395 To STA 1461 

S-8R, STA 1241 To STA 1373 

S-8R, STA 1417 To STA 1461

S-8L, STA 1241 To STA 1373 

S-17L, STA 1197+110 To STA 1219 

S-17L, STA 1307 To STA 1461

S-36L, STA 1241 To STA 1307 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 19: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 7)

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ALERT ALERT

FIGURE 19: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 7) STA 132.5 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1065 STA 1832 STA 1307STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 1540 STA 188.5 STA 1562STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1197+110 STA 1197+66 INSPECTION AREA

EXISTING BUTT JOINT

S-13R

S-13L

STA

1219

STA

1109

STA

1518

STA

1263

STA

1285

STA

246

STA434

STA

786.1

STA

287

STA

654+88

STA

618

STA

654+22

STA

764

STA

654

STA

742

STA

654+44

STA

676

STA

698

STA

610

STA

1241

STA

654+121

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 7:

STA

1087

STA

1197+22

STA

1197+44

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538693

(SHEET 1 OF 2)
 FIGURE 19: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-26R, STA 654+22 To STA 654+88 - (a)

S-8R, STA 434 To STA 654

S-2R, STA 654+44 To STA 654+88

S-8L, STA 434 To STA 654

S-17L, STA 434 To STA 654 

S-26L, STA 434 To STA 610

S-26L, STA 654+88 To STA 676

S-36L, STA 434 To STA 654

2

Inspect Lower Skin S-36R, STA 1197+66 To STA 1219 - (a)

S-36R, STA 1518 To STA 1562 

S-17R, STA 1109 To STA 1197+22 

S-17R, STA 1395 To STA 1461 

S-8R, STA 1087 To STA 1197+44 

S-8R, STA 1241 To STA 1373

S-8R, STA 1417 To STA 1461

S-8L, STA 1109 To STA 1197+44 

S-8L, STA 1241 To STA 1373 

S-17L, STA 1109 To STA 1197+22

S-17L, STA 1197+110 To STA 1219

S-17L, STA 1307 To STA 1461

S-36L, STA 1241 To STA 1307

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 20: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 8)

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ALERT ALERT

FIGURE 20: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 8) STA 132.5 STA 246 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1065 STA 1832 STA 1307STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 1518 STA 188.5 STA 1197+44 STA 1562STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1197+110 STA 1263 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1219 STA 1285 STA 1241 STA 786.1 STA 654+88 STA 764 STA 742 STA 654+44STA 676STA 698 STA 434 STA 615 STA 654+22 STA 654 STA 610 STA 500STA 522 STA 1109STA 1153 STA 1540

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 8:

STA

1087

STA

1197+22

STA

1197+66

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538695

(SHEET 1 OF 2)
 FIGURE 20: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 8)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-36R, STA 434 To STA 522 - (a)

S-26R, STA 654+22 To STA 654+88

S-8R, STA 434 To STA 654

S-2R, STA 654+44 To STA 654+88

S-8L, STA 434 To STA 654

S-17L, STA 434 To STA 654 

S-26L, STA 434 To STA 610

S-26L, STA 654+88 To STA 676

S-36L, STA 434 To STA 654

2

Inspect Lower Skin S-36R, STA 1197+66 To STA 1219 - (a)

S-36R, STA 1518 To STA 1562 

S-17R, STA 1109 To STA 1197+22 

S-17R, STA 1395 To STA 1461 

S-8R, STA 1087 To STA 1197+44 

S-8R, STA 1241 To STA 1373

S-8R, STA 1417 To STA 1461

S-8L, STA 1109 To STA 1197+44 

S-8L, STA 1241 To STA 1373 

S-17L, STA 1109 To STA 1197+22

S-17L, STA 1197+110 To STA 1219

S-17L, STA 1307 To STA 1461

S-36L, STA 1241 To STA 1307 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 21: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 21: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 9) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 287 STA 1832S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 188.9 STA 618 STA 654+66 STA 720 STA 654 INSPECTION AREA

EXISTING BUTT JOINT

S-13R

S-13L

STA

654+44

STA

654+88

STA

654+121

STA

764

STA

1307

STA

1373

STA

1395

STA

1540

STA

1562

STA

1582

STA

1461

STA

1417

STA

1346

STA

1219

STA

1518

STA

1285

STA

1197+110

STA

1065

STA

1087

STA

1241

STA

1270

STA

1109

STA

698

STA

676

STA

654+22

STA

610

STA632

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 9:

STA

1197+22

STA

1197+44

STA

1197+66

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538696

(SHEET 1 OF 2)
 FIGURE 21: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-26R, STA 654+88 To STA 698 - (a)

S-17R, STA 654+44 To STA 720

S-8R, STA 434 To STA 632

S-8R, STA 654+66 To STA 654+121

S-2R, STA 654+44 To STA 654+88

S-8L, STA 434 To STA 654+121

S-17L, STA 434 To STA 654 

S-17L, STA 654+66 To STA 720 

S-26L, STA 434 To STA 610

S-26L, STA 654 To STA 676

S-36L, STA 434 To STA 654

2

Inspect Lower Skin S-36R, STA 1197+66 To STA 1219 - (a)

S-36R, STA 1518 To STA 1562 

S-17R, STA 1109 To STA 1197+22 

S-17R, STA 1395 To STA 1461 

S-8R, STA 1087 To STA 1197+44 

S-8R, STA 1241 To STA 1373

S-8R, STA 1417 To STA 1461

S-8L, STA 1109 To STA 1197+44 

S-8L, STA 1241 To STA 1373 

S-17L, STA 1109 To STA 1197+22

S-17L, STA 1197+110 To STA 1219

S-17L, STA 1307 To STA 1461

S-36L, STA 1241 To STA 1307 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 22: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 10)

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ALERT ALERT

FIGURE 22: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 10) STA 132.5 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1065 STA 1832S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 188.9 STA 1109 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1087 STA 1307STA 1373STA 1395 STA 1540STA 1562STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1197+22 STA 1197+66 STA 1219 STA 1518 STA STA 1285 1241 STA 246 STA 434 STA 786.1 STA 287 STA 615 STA 654+66 STA 720 STA 654 STA 654+44STA 654+88STA 654+121 STA 764 STA 698 STA 676 STA 632 STA 500 STA 478 STA 654+22 STA 610

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 10:

STA

522

STA

1197+44

STA

1197+110

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538698

(SHEET 1 OF 2)
 FIGURE 22: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 10)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-36R, STA 434 To STA 522 - (a)

S-26R, STA 654+88 To STA 698

S-17R, STA 654+44 To STA 720

S-8R, STA 434 To STA 632

S-8R, STA 654+66 To STA 654+121

S-2R, STA 654+44 To STA 654+88

S-8L, STA 434 To STA 654+121

S-17L, STA 434 To STA 654 

S-17L, STA 654+66 To STA 720 

S-26L, STA 434 To STA 610

S-26L, STA 654 To STA 676

S-36L, STA 434 To STA 654

2

Inspect Lower Skin S-36R, STA 1197+66 To STA 1219 - (a)

S-36R, STA 1518 To STA 1562 

S-17R, STA 1109 To STA 1197+22 

S-17R, STA 1395 To STA 1461

S-8R, STA 1087 To STA 1197+44 

S-8R, STA 1241 To STA 1373

S-8R, STA 1417 To STA 1461

S-8L, STA 1109 To STA 1197+44 

S-8L, STA 1241 To STA 1373 

S-17L, STA 1109 To STA 1197+22

S-17L, STA 1197+110 To STA 1219

S-17L, STA 1307 To STA 1461

S-36L, STA 1241 To STA 1307 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 23: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 11)

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ALERT ALERT

FIGURE 23: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 11) STA 126.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1065 STA 1832 STA 1307STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 188.9 STA 456 STA 654+110 STA 742 STA 654 STA 1197+132 STA 1582 STA 1417 STA 1219 STA 654+22 STA 1175 STA 1153 STA 1197+66 STA 1654 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1263 STA 1502STA 1562 STA 676 STA 654+66 STA 1540 STA 1351 STA 1241 STA 1197+88 STA 1197+22 STA 698 STA 478 STA 632 STA 1109

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 11:

STA

1461

STA

1197+44

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538699

(SHEET 1 OF 2)
 FIGURE 23: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 11)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Lower Skin S-17R, STA 654+66 To STA 676 - (a)

S-8R, STA 434 To STA 632

2

Inspect Lower Skin S-17R, STA 1197+22 To STA 1197+66 - (a)

S-17R, STA 1395 To STA 1461 

S-8R, STA 1153 To STA 1197+88 

S-8R, STA 1241 To STA 1373

S-8R, STA 1417 To STA 1562

S-8L, STA 1219 To STA 1373 

S-8L, STA 1417 To STA 1461 

S-17L, STA 1175 To STA 1194+44

S-17L, STA 1197+132 To STA 1263

S-17L, STA 1307 To STA 1461

S-26L, STA 1065 To STA 1109

S-26L, STA 1502 To STA 1582

S-36L, STA 1241 To STA 1307 

S-36L, STA 1540 To STA 1582 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 24: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 12)

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ALERT ALERT

FIGURE 24: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 12) STA 126.5 STA 246 STA 434 STA 786 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1065 STA 1832S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 188.9 STA 456 STA 654 STA 654A STA 1373 STA 1197+154 STA 1197+253 STA 654A+110 STA 1197+132 STA 1582 STA 654+44 STA 654+22 STA 1197+110 STA 1417STA 1461 STA 610 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 654A+22STA 654A+88 STA 1197+88 STA 1562 STA 1351 STA 1285 STA 1241 STA 1197+187 STA 1197+209 STA 654A+44 STA 1307 STA 1219

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 12:

STA

1439

STA

1518

STA

1263

STA

1197+66

STA

654+110

STA

676

STA

566

LAP JOINT

1 2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538746

(SHEET 1 OF 2)
 FIGURE 24: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 12)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-26R, STA 654A+110 To STA 654+22 - (a)

S-26R, STA 654+110 To STA 676

S-17R, STA 654A+22 To STA 654A+110

S-8R, STA 434 To STA 654A+110

S-2R, STA 654A+110 To STA 654+44

S-8L, STA 434 To STA 654A+110

S-17L, STA 434 To STA 654 

S-26L, STA 434 To STA 566 

S-26L, STA 654A To STA 654A+110

S-36L, STA 434 To STA 654A+88

2

Inspect Lower Skin S-36R, STA 1197+110 To STA 1197+154 - (a)

S-36R, STA 1373 To STA 1439 

S-26R, STA 1197+209 To STA 1219 

S-17R, STA 1395 To STA 1439 

S-8R, STA 1197+253 To STA 1461 

S-2R, STA 1285 To STA 1373

S-2R, STA 1518 To STA 1562

S-8L, STA 1197+66 To STA 1197+132 

S-8L, STA 1197+253 To STA 1373 

S-8L, STA 1417 To STA 1461 

S-17L, STA 1197+154 To STA 1263

S-17L, STA 1395 To STA 1439

S-26L, STA 1197+187 To STA 1241

S-26L, STA 1351 To STA 1417

S-36L, STA 1197+110 To STA 1197+154 

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 25: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 1)

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ALERT ALERT

FIGURE 25: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 1) STA 132.5 STA 246 STA 434 STA 618 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 676 STA 654 STA 456 STA 698 STA 764 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 S-13R S-13L STA 1540STA 1562 STA 1518 STA 1502 STA 1263 STA 1175 STA 1109STA 1131 STA 1219STA 1241 STA 478 STA 808 STA 852 STA 1351 STA 1285 STA 1087

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 1: LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538871

(SHEET 1 OF 2)
 FIGURE 25: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 1)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-26R, STA 246 To STA 434 - (a)

S-17R, STA 676 To STA 764

S-8R, STA 246 To STA 434

S-8L, STA 246 To STA 434

S-26L, STA 246 To STA 434

3

Inspect Lower Skin S-26R, STA 1175 To STA 1219 - (a)

S-26R, STA 1417 To STA 1582 

S-17R, STA 1087 To STA 1241

S-17R, STA 1417 To STA 1461

S-8L, STA 1373 To STA 1461

S-17L, STA 1065 To STA 1263

S-26L, STA 1502 To STA 1582

S-36L, STA 1263 To STA 1307

S-36L, STA 1417 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 26: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 2)

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ALERT ALERT

FIGURE 26: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 2) STA 132.5 STA 246 STA 434 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 544 STA 500STA 539 STA 698 STA 1065 STA 1582 STA 1832 STA 1307 STA 1263 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1562 STA 1540 STA 1502 STA 1480 STA 1373 STA 1241 STA 1219 STA 1153 STA 1109STA 1131 STA 1087 STA 1351 STA 1285 STA 1175 STA 786.1 STA 676 STA 764

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 2: LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538875

(SHEET 1 OF 2)
 FIGURE 26: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 500 To STA 544 - (a)

S-26R, STA 246 To STA 434

S-17R, STA 434 To STA 500

S-17R, STA 676 To STA 764

S-8R, STA 246 To STA 434

S-8L, STA 246 To STA 434

S-26L, STA 246 To STA 434

3

Inspect Lower Skin S-26R, STA 1175 To STA 1219 - (a)

S-26R, STA 1417 To STA 1582

S-17R, STA 1087 To STA 1241

S-17R, STA 1417 To STA 1461

S-8L, STA 1373 To STA 1461

S-17L, STA 1065 To STA 1263

S-26L, STA 1502 To STA 1582

S-36L, STA 1263 To STA 1307

S-36L, STA 1417 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 27: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 3)

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 27: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 3) STA 132.5 STA 246 STA 434 STA 618 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 676 STA 478 STA 654 STA 1582 STA 1832 STA 1307STA 1373 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1562 STA 1540 STA 1502 STA 1263 STA 1241 STA 1219 STA 1109STA 1131 STA 456 STA 1065 STA 1087 STA 1351 STA 1175 STA 1285 STA 698STA 764

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 3: LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538877

(SHEET 1 OF 2)
 FIGURE 27: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-26R, STA 246 To STA 434 - (a)

S-17R, STA 676 To STA 764

S-8R, STA 246 To STA 434

S-8L, STA 246 To STA 434

S-26L, STA 246 To STA 434

3

Inspect Lower Skin S-26R, STA 1175 To STA 1219 - (a)

S-26R, STA 1417 To STA 1582 

S-17R, STA 1087 To STA 1241

S-17R, STA 1417 To STA 1461

S-8L, STA 1373 To STA 1461

S-17L, STA 1065 To STA 1263

S-26L, STA 1502 To STA 1582

S-36L, STA 1263 To STA 1307

S-36L, STA 1417 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 28: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 28: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 4) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 500 STA 610STA 654 STA 764 STA 1065 STA 1582 STA 1832 STA 1307 STA 1263 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395STA 1417STA 1461 STA 188.9 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1562 STA 1540 STA 1502 STA 1373 STA 1241 STA 1219 STA 1109STA 1131 STA 676 STA 1087 STA 698 STA 1175 STA 1285STA 1351

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 4:

STA

544

LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538880

(SHEET 1 OF 2)
 FIGURE 28: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 500 To STA 544 - (a)

S-26R, STA 246 To STA 434

S-17R, STA 434 To STA 500

S-17R, STA 676 To STA 764

S-8R, STA 246 To STA 434

S-8L, STA 246 To STA 434

S-26L, STA 246 To STA 434

3

Inspect Lower Skin S-26R, STA 1175 To STA 1219 - (a)

S-26R, STA 1417 To STA 1582 

S-17R, STA 1087 To STA 1241

S-17R, STA 1417 To STA 1461

S-8L, STA 1373 To STA 1461

S-17L, STA 1065 To STA 1263

S-26L, STA 1502 To STA 1582

S-36L, STA 1263 To STA 1307

S-36L, STA 1417 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 29: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 5)

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ALERT ALERT

FIGURE 29: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 5) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 654+88 STA 1065 STA 1832 STA 1285 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1373 STA 188.9 STA 618 STA 610 STA 654+110 STA 632STA 654 STA 1197+132 STA 1562STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1197+88 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 456 STA 1219 STA STA 1241 1263 STA 1153 STA 1109 STA 1087 STA 720 STA 654+121 STA 654+22 STA 676 STA 1241 STA 1395 STA 1307 STA 698 STA 764 STA 742 STA 1502

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 5:

STA

478

STA

1351

LAP JOINT

1 3

2

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1538883

(SHEET 1 OF 3)
 FIGURE 29: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 5)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 434 To STA 478 - (a)

S-36R, STA 654 To STA 698

S-26R, STA 246 To STA 456

S-26R, STA 698 To STA 764

S-17R, STA 434 To STA 456

S-8R, STA 246 To STA 434

S-8R, STA 654+110 To STA 676

S-2R, STA 654+88 To STA 720

S-8L, STA 246 To STA 434

S-17L, STA 676 To STA 720

S-26L, STA 246 To STA 434

S-26L, STA 676 To STA 742

S-36L, STA 654+88 To STA 654+121 

S-36L, STA 698 To STA 764

(SHEET 2 OF 3)
 FIGURE 29: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 5)

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ALERT ALERT

3

Inspect Lower Skin S-36R, STA 1373 To STA 1417 - (a)

S-26R, STA 1153 To STA 1219 

S-26R, STA 1417 To STA 1582 

S-17R, STA 1562 To STA 1582

S-8R, STA 1562 To STA 1582 

S-2R, STA 1241 To STA 1307 

S-8L, STA 1562 To STA 1582

S-17L, STA 1219 To STA 1263

S-17L, STA 1562 To STA 1582

S-26L, STA 1153 To STA 1285 

S-26L, STA 1502 To STA 1582

S-36L, STA 1197+88 To STA 1219

S-36L, STA 1351 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

(SHEET 3 OF 3)
 FIGURE 30: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 6)

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ALERT ALERT

FIGURE 30: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 6) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 654+88 STA 1065 STA 1832 STA 1307 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 188.9 STA 615 STA 654+44STA 654+110 STA 654 STA 1197+132 STA 1562STA 1582 STA 1461 STA 1417 STA 1346 STA 1270 STA 1197+88 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1219 STA 1480 STA 1241STA 1263 STA 1153 STA STA 1109 1087 STA 522 STA 500 STA 456 STA 654+121 STA 698STA 720 STA 676 STA 654+22 STA 1502 STA 764 STA 742 STA 1285

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 6:

STA

STA

1373

1351

STA

566

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1539317

(SHEET 1 OF 3)
 FIGURE 30: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 566 To STA 698 - (a)

S-26R, STA 246 To STA 434

S-26R, STA 698 To STA 764

S-17R, STA 434 To STA 522

S-8R, STA 246 To STA 434

S-8R, STA 654+110 To STA 676

S-2R, STA 654+88 To STA 720

S-8L, STA 246 To STA 434

S-8L, STA 654+121 To STA 764

S-17L, STA 676 To STA 720

S-26L, STA 246 To STA 434

S-26L, STA 676 To STA 742

S-36L, STA 654+88 To STA 654+121 

S-36L, STA 698 To STA 764

(SHEET 2 OF 3)
 FIGURE 30: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 6)

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ALERT ALERT

3

Inspect Lower Skin S-36R, STA 1373 To STA 1417 - (a)

S-26R, STA 1153 To STA 1219 

S-26R, STA 1417 To STA 1582 

S-17R, STA 1562 To STA 1582

S-8R, STA 1562 To STA 1582 

S-2R, STA 1241 To STA 1307 

S-8L, STA 1562 To STA 1582

S-17L, STA 1219 To STA 1263

S-17L, STA 1562 To STA 1582

S-26L, STA 1153 To STA 1285 

S-26L, STA 1502 To STA 1582

S-36L, STA 1197+88 To STA 1219

S-36L, STA 1351 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

(SHEET 3 OF 3)
 FIGURE 31: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 7)

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ALERT ALERT

FIGURE 31: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 7) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 654+88 STA 1065 STA 1263 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1373 STA 1502 STA 188.9 S5A 618STA 610 STA 654+110 STA 654 STA 1461 STA 1351 STA 1346 STA 1270 STA 1197+132 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 456 STA 1219 STA 1480 STA 1241 STA 1197+88 STA 1131 STA 698 STA 654+121 STA 676STA 720 STA 654+22 STA 1109 STA 1087 STA 1832 STA 1540STA 1582 STA 764 STA 742 STA 1518 STA 1562 STA 1307STA 1285

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 7:

STA

478

STA

1395

STA

1417

STA

1175

STA

1153

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1539318

(SHEET 1 OF 3)
 FIGURE 31: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 434 To STA 478 - (a)

S-36R, STA 654 To STA 698 

S-26R, STA 246 To STA 456

S-26R, STA 698 To STA 764

S-17R, STA 434 To STA 456 

S-8R, STA 246 To STA 434

S-8R, STA 654+110 To STA 676

S-2R, STA 654+88 To STA 720

S-8L, STA 246 To STA 434

S-17L, STA 676 To STA 720

S-26L, STA 246 To STA 434

S-26L, STA 676 To STA 742

S-36L, STA 654+88 To STA 654+121 

S-36L, STA 698 To STA 764

(SHEET 2 OF 3)
 FIGURE 31: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 7)

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ALERT ALERT

3

Inspect Lower Skin S-36R, STA 1373 To STA 1417 - (a)

S-26R, STA 1175 To STA 1219 

S-26R, STA 1417 To STA 1582 

S-17R, STA 1562 To STA 1582

S-8R, STA 1562 To STA 1582 

S-2R, STA 1241 To STA 1307 

S-8L, STA 1197+132 To STA 1241

S-8L, STA 1562 To STA 1582

S-17L, STA 1219 To STA 1263

S-17L, STA 1562 To STA 1582

S-26L, STA 1153 To STA 1285 

S-26L, STA 1502 To STA 1582

S-36L, STA 1351 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

(SHEET 3 OF 3)
 FIGURE 32: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 8)

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ALERT ALERT

FIGURE 32: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 8) STA 132.5 STA 246 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 188.9 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 1832 STA 1373 STA 1502 STA 1461 STA 1417 STA 1346 STA 1582 STA 1562 STA 1307 STA 1065 STA 1263 STA 1270 STA 1197+132 STA 1219STA 1241 STA 1153 STA 1109 STA 1087 STA 1285 STA 434 STA 786.1 STA 654+88 STA 615 STA 566 STA 654+110 STA 654 STA 456 STA 698 STA 654+121 STA 676STA 720 STA 654+22 STA 764 STA 742 STA 522

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 8:

STA

1175

STA

1395

STA

1351

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1539321

(SHEET 1 OF 3)
 FIGURE 32: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 8)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 566 To STA 698 - (a)

S-26R, STA 246 To STA 434

S-26R, STA 698 To STA 764

S-17R, STA 434 To STA 522

S-8R, STA 246 To STA 434

S-8R, STA 654+110 To STA 676

S-2R, STA 654+88 To STA 720

S-8L, STA 246 To STA 434

S-8L, STA 654+121 To STA 764

S-17L, STA 676 To STA 720

S-26L, STA 246 To STA 434

S-26L, STA 676 To STA 742

S-36L, STA 654+88 To STA 654+121 

S-36L, STA 698 To STA 764

(SHEET 2 OF 3)
 FIGURE 32: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 8)

Original Issue: November 25, 2008

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ALERT ALERT

3

Inspect Lower Skin S-36R, STA 1373 To STA 1417 - (a)

S-26R, STA 1175 To STA 1219 

S-26R, STA 1417 To STA 1582 

S-17R, STA 1562 To STA 1582

S-8R, STA 1562 To STA 1582 

S-2R, STA 1241 To STA 1307 

S-8L, STA 1197+132 To STA 1241

S-8L, STA 1562 To STA 1582

S-17L, STA 1219 To STA 1263

S-17L, STA 1562 To STA 1582

S-26L, STA 1153 To STA 1285 

S-26L, STA 1502 To STA 1582

S-36L, STA 1351 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

(SHEET 3 OF 3)
 FIGURE 33: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 9)

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ALERT ALERT

FIGURE 33: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 9) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1832S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 188.9 STA 618 STA 654+110 STA 654 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 720 STA 698 STA STA 654+121 654+88 STA 654+22 STA 456 STA 1395 STA 1502 STA 1461 STA 1417 STA 1346 STA 1480 STA 1582 STA 1518 STA 1562 STA 1307 STA 1065 STA 1270 STA 1197+132 STA 1219STA 1241 STA 1175 STA 1153 STA 1109 STA 1285 STA 764 STA 676 STA 1263

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 9:

STA

1351

STA

1373

STA632

STA

654+66

STA

742

STA

478

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1539322

(SHEET 1 OF 3)
 FIGURE 33: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 434 To STA 478 - (a)

S-36R, STA 654 To STA 654+110 

S-26R, STA 246 To STA 456

S-26R, STA 654+22 To STA 654+88

S-26R, STA 698 To STA 764

S-17R, STA 434 To STA 456

S-8R, STA 246 To STA 434

S-8R, STA 632 To STA 654+66

S-2R, STA 654+88 To STA 720

S-8L, STA 246 To STA 434

S-8L, STA 720 To STA 764

S-17L, STA 654 To STA 654+66

S-26L, STA 246 To STA 434

S-26L, STA 676 To STA 742

S-36L, STA 654+88 To STA 654+121 

S-36L, STA 698 To STA 764

(SHEET 2 OF 3)
 FIGURE 33: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

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ALERT ALERT

3

Inspect Lower Skin S-36R, STA 1373 To STA 1417 - (a)

S-26R, STA 1175 To STA 1219

S-26R, STA 1417 To STA 1582 

S-17R, STA 1562 To STA 1582

S-8R, STA 1562 To STA 1582 

S-2R, STA 1241 To STA 1307 

S-8L, STA 1197+132 To STA 1241

S-8L, STA 1562 To STA 1582

S-17L, STA 1219 To STA 1263

S-17L, STA 1562 To STA 1582

S-26L, STA 1153 To STA 1285 

S-26L, STA 1502 To STA 1582

S-36L, STA 1351 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

(SHEET 3 OF 3)
 FIGURE 34: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 10)

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ALERT ALERT

FIGURE 34: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 10) STA 132.5 STA 246 STA 434 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1832S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 188.9 INSPECTION AREA EXISTING BUTT JOINT S-13R S-13L STA 654+66 STA 698 STA 654+121 STA 786.1 STA 615 STA 676 STA 654 STA 720 STA 654+88 STA 654+22 STA 500 STA 1395 STA 1502 STA 1461 STA 1417 STA 1346 STA 1480 STA 1582 STA 1518 STA 1562 STA 1307 STA 1065 STA 1351 STA 1270 STA 1197+132 STA 1219STA 1241 STA 1197+88 STA 1153 STA 1109 STA 1087 STA 1373 STA 544 STA 742

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 10:

STA

522

STA

566

STA

632

STA

764

STA

1175

STA

1285

STA

1263

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1539323

(SHEET 1 OF 3)
 FIGURE 34: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 10)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 566 To STA 698 - (a)

S-26R, STA 246 To STA 434

S-26R, STA 654+22 To STA 654+88

S-26R, STA 698 To STA 764

S-17R, STA 434 To STA 522

S-8R, STA 246 To STA 434

S-8R, STA 632 To STA 654+66

S-2R, STA 654+88 To STA 720

S-8L, STA 246 To STA 434

S-8L, STA 720 To STA 764

S-17L, STA 654 To STA 654+66

S-26L, STA 246 To STA 434

S-26L, STA 676 To STA 742

S-36L, STA 654+88 To STA 654+121 

S-36L, STA 698 To STA 764

(SHEET 2 OF 3)
 FIGURE 34: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 10)

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ALERT ALERT

3

Inspect Lower Skin S-36R, STA 1373 To STA 1417 - (a)

S-26R, STA 1175 To STA 1219 

S-26R, STA 1417 To STA 1582 

S-17R, STA 1562 To STA 1582

S-8R, STA 1562 To STA 1582 

S-2R, STA 1241 To STA 1307 

S-8L, STA 1197+132 To STA 1241

S-8L, STA 1562 To STA 1582

S-17L, STA 1219 To STA 1263

S-17L, STA 1562 To STA 1582

S-26L, STA 1153 To STA 1285 

S-26L, STA 1502 To STA 1582

S-36L, STA 1351 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

(SHEET 3 OF 3)
 FIGURE 35: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 11)

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ALERT ALERT

FIGURE 35: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 11) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1065 STA 1832 STA 1307

STA

1351

S-36R

S-26RS-17R

S-8RS-2R

S-8L

S-17L

S-26L

S-36L

STA

1395

STA

1439

STA

188.9

STA

456

STA

654+66

STA

676

STA

654

STA

1197+132

STA

1582

STA

1417

STA

1197+110

STA

1219 STA

654+22

STA

1175

STA

1197

STA

1197+66

STA

1197+88

INSPECTION AREA

EXISTING BUTT JOINT

S-13R

S-13L

STA

1502

STA

1461

STA

1263

STA

1131

STA

1087

STA

1197+22

STA

1197+44

STA

720

STA

742

STA

698

STA

654+121

STA

654+110

STA

STA

654+88

654+44

STA

1109

STA

1153

STA

1241

STA

1373

STA

1480

STA

1540 STA

632

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

STA

1562

This Figure applies to Group 11:

STA

1285

STA

500

LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1552233

(SHEET 1 OF 2)
 FIGURE 35: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 11)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-36R, STA 434 To STA 500 - (a)

S-36R, STA 654 To STA 654+121

S-26R, STA 246 To STA 456

S-26R, STA 654+22 To STA 654+110

S-17R, STA 676 To STA 720 

S-8R, STA 246 To STA 434

S-8R, STA 632 To STA 654+44

S-8L, STA 246 To STA 434

S-17L, STA 654+110 To STA 720

S-26L, STA 246 To STA 434

S-26L, STA 698 To STA 742

S-36L, STA 654 To STA 654+88

3

Inspect Lower Skin S-26R, STA 1153 To STA 1197+66 - (a)

S-26R, STA 1417 To STA 1582 

S-17R, STA 1175 To STA 1197+22

S-17R, STA 1461 To STA 1562

S-2R, STA 1241 To STA 1285 

S-2R, STA 1351 To STA 1417 

S-8L, STA 1461 To STA 1562

S-17L, STA 1263 To STA 1307

S-17L, STA 1461 To STA 1562

S-26L, STA 1197 To STA 1263

S-36L, STA 1197+110 To STA 1219

S-36L, STA 1417 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 36: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 12)

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ALERT ALERT

FIGURE 36: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 12) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 1197 STA 1832S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L

STA

1307

STA

1395

STA

188.9

STA

456

STA

654

STA

654+110

STA

1373

STA

1197+187

STA

1197+209

STA

654A+88

STA

1197+154

STA

1197+187

STA

1582

STA

654+44

STA

676

STA

1197+66

STA

1417

STA

1461

STA

1480

INSPECTION AREA

EXISTING BUTT JOINT

S-13R

S-13L

STA

1562

STA

1540

STA

1518

STA

1351

STA

1285

STA

1219

STA

1197+22

STA

1197+88

STA

1065

STA

698

STA

720

STA

1197+253

STA

1197+132

STA

1197+165

STA

654+121

TYPICAL SKIN LAP JOINT

TYPICAL SKINSCRIBE LINE

This Figure applies to Group 12: LAP JOINT

1 2

3

FRAME

UPPER SKIN

STRINGER

LOWER SKIN

1539594

(SHEET 1 OF 2)
 FIGURE 36: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 12)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Lower Skin S-30R, STA 132.5 To STA 246 - (a)

BL 0, STA 188.9 To STA 246

S-30L, STA 132.5 To STA 246

2

Inspect Lower Skin S-26R, STA 246 To STA 434 - (a)

S-8R, STA 246 To STA 434

S-2R, STA 654+44 To STA 654+110

S-8L, STA 246 To STA 434

S-26L, STA 246 To STA 434

S-36L, STA 654A+88 To STA 654+44

3

Inspect Lower Skin S-36R, STA 1197+165 To STA 1197+209 - (a)

S-36R, STA 1518 To STA 1582 

S-26R, STA 1197 To STA 1197+187 

S-26R, STA 1417 To STA 1480 

S-26R, STA 1518 To STA 1582 

S-17R, STA 1197+154 To STA 1219

S-8R, STA 1197+22 To STA 1197+253 

S-2R, STA 1197+209 To STA 1285 

S-8L, STA 1197+22 To STA 1197+66

S-8L, STA 1197+165 To STA 1197+253

S-8L, STA 1540 To STA 1582

S-26L, STA 1197 To STA 1197+187 

S-26L, STA 1540 To STA 1582 

S-36L, STA 1197+187 To STA 1219

S-36L, STA 1285 To STA 1351

S-36L, STA 1417 To STA 1461

(a) Do a detailed inspection of the fuselage skin for any scribe line. Use a minimum 10X magnifying lens to 

aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the lap joint in the lower skin along the

edge of the upper skin. These scribe lines are typically within 0.25 inch of the lower edge of the

upper skin. In some cases, portions of the scribe lines may be directly adjacent to or slightly under

the lower edge of the upper skin. The ends of these scribe lines sometimes may also turn slightly

away from the lap joint.

(SHEET 2 OF 2)
 FIGURE 37: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 1)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 37: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 1) STA 132.5 STA 246 STA 434 STA 618 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 188.9 S-13R S-13L STA 149

This Figure applies to Group 1:

1

1 1

TYPICAL EXTERNAL APPROVED REPAIR

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

1540456

(SHEET 1 OF 2)
 FIGURE 37: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 1)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 38: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 2)

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ALERT ALERT

FIGURE 38: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 2) S-36R S-26R S-26L S-36L

This Figure applies to Group 2:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

STA

132.5

BL 0

S-37R

S-36RS-30R

S-21RS-21L

S-30L

S-36L

S-37L

S-36R

S-26RS-17R

S-8RS-2RS-8L

S-17LS-26L

S-36L

S-13R

S-13L

STA

246

STA

434

STA

615

STA

786.1

STA

196.5

STA

1065

STA

1582

STA

1832

STA

1307

STA

1395

STA

188.9

INSPECTION AREA

EXISTING BUTT JOINT

STA

149

STA539

A

A REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1540458

(SHEET 1 OF 2)
 FIGURE 38: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 39: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 39: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 3) STA 132.5 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 188.9 S-13R S-13L STA 246 STA 434 STA 618 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 INSPECTION AREA EXISTING BUTT JOINT STA 149

This Figure applies to Group 3:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1540459

(SHEET 1 OF 2)
 FIGURE 39: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 40: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 40: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 4) STA 132.5 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13L STA 246 STA 434 STA 615 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.5 INSPECTION AREA EXISTING BUTT JOINT STA 149 STA 539

This Figure applies to Group 4:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1540461

(SHEET 1 OF 2)
 FIGURE 40: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 41: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 5)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 41: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 5) STA 132.5 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 188.9 S-13R S-13L STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 1219 INSPECTION AREA EXISTING BUTT JOINT STA 149

This Figure applies to Group 5:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1540462

(SHEET 1 OF 2)
 FIGURE 41: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 5)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 42: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 42: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 6) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 188.5 STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 1219 INSPECTION AREA EXISTING BUTT JOINT STA 149

This Figure applies to Group 6:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1543330

(SHEET 1 OF 2)
 FIGURE 42: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 6)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 43: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 7)

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ALERT ALERT

FIGURE 43: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 7) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 188.9 STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 1219 INSPECTION AREA EXISTING BUTT JOINT STA 149

This Figure applies to Group 7:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1543331

(SHEET 1 OF 2)
 FIGURE 43: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 44: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 8)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 44: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 8) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 188.9 STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 1219 INSPECTION AREA EXISTING BUTT JOINT STA 149

This Figure applies to Group 8:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1543333

(SHEET 1 OF 2)
 FIGURE 44: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 8)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 45: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 45: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 9) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 188.9 STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 1219 INSPECTION AREA EXISTING BUTT JOINT STA 149

This Figure applies to Group 9:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1543335

(SHEET 1 OF 2)
 FIGURE 45: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 46: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 10)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 46: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 10) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 188.9 STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 1219 INSPECTION AREA EXISTING BUTT JOINT STA 149

This Figure applies to Group 10:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1543336

(SHEET 1 OF 2)
 FIGURE 46: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 10)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 47: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 11)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 47: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 11) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 188.9 STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 1219 STA 1197+88 INSPECTION AREA EXISTING BUTT JOINT STA 149 STA 654+22

This Figure applies to Group 11:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1543340

(SHEET 1 OF 2)
 FIGURE 47: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 11)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 48: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 12)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 48: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 12) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 188.9 STA 246 STA 434 STA 654 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1197+154 INSPECTION AREA EXISTING BUTT JOINT STA 149 STA 1395

This Figure applies to Group 12:

1

1 1

TYPICAL SCRIBE LINES

REPAIRDOUBLER

SKIN PANEL

A

A

REPAIR DOUBLER

SKIN A-A

TYPICAL EXTERNAL APPROVED REPAIR

1543342

(SHEET 1 OF 2)
 FIGURE 48: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 12)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Skin STA 149 To STA 1582 - (a)

(a) Do a detailed inspection of the fuselage skin around external approved repairs for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION

TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR ABSENCE OF

FATIGUE CRACKS.

NOTE: Scribe lines normally run parallel to the external approved repair doubler along the edge of the

repair. These scribe lines are typically within 0.25 inch of the doubler. In some cases, portions of

the scribe lines may be directly adjacent to or slightly under the edge of the repair doubler.

(SHEET 2 OF 2)
 FIGURE 49: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 1)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 49: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 1) STA 132.5 STA 246 STA 434 STA 786.1 BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L STA 196.5 STA 588 STA 676 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L STA 1395 STA 188.9 S-13R S-13L STA 1131 STA 1109STA 1153 STA 1175 STA 544STA 566 STA 456 STA 610STA 654 STA 632 STA 698

This Figure applies to Group 1: TYPICAL SCRIBE LINES

TYPICAL EXTERNAL FEATURE

1

1543344

(SHEET 1 OF 2)
 FIGURE 49: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 1)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 445 1 (a) (b)

Upper Anti-Collision 

(Strobe) Light

S-1L-1R, STA 555 1 (a) (c)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (d)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (d)

Very High Frequency 

(VHF) Antenna

S-1L-1R, STA 665 1 (a) (e)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (f)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (f)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (g)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 665 1 (a) (g)

Fwd Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 577 3 (a) (h)

Aft Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 621 3 (a) (h)

Marker Beacon Antenna Lower Fuselage C/L, STA 680 1 (a) (i)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 33-44-02.

(d) Refer to 767 AMM 34-58-02.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-57-03.

(g) Refer to 767 AMM 34-55-02.

(h) Refer to 767 AMM 34-33-02.

(i) Refer to 767 AMM 34-32-01.

(SHEET 2 OF 2)
 FIGURE 50: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 50: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 2) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13L INSPECTION AREA EXISTING BUTT JOINT STA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 588 STA 676 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 544 STA 566 STA 456 STA 610 STA 654 STA 632 STA 698

This Figure applies to Group 2: TYPICAL SCRIBE LINES TYPICAL EXTERNAL FEATURE

1

1543347

(SHEET 1 OF 2)
 FIGURE 50: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 445 1 (a) (b)

Upper Anti-Collision 

(Strobe) Light

S-1L-1R, STA 555 1 (a) (c)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (d)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (d)

Very High Frequency 

(VHF) Antenna

S-1L-1R, STA 665 1 (a) (e)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (f)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (f)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (g)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 665 1 (a) (g)

Fwd Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 577 3 (a) (h)

Aft Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 621 3 (a) (h)

Marker Beacon Antenna Lower Fuselage C/L, STA 680 1 (a) (i)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 33-44-02.

(d) Refer to 767 AMM 34-58-02.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-57-03.

(g) Refer to 767 AMM 34-55-02.

(h) Refer to 767 AMM 34-33-02.

(i) Refer to 767 AMM 34-32-01.

(SHEET 2 OF 2)
 FIGURE 51: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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ALERT ALERT

FIGURE 51: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 3) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13L INSPECTION AREA EXISTING BUTT JOINT STA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 588 STA 676 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 544STA 566 STA 456 STA 610STA 654 STA 632 STA 698

This Figure applies to Group 3: TYPICAL SCRIBE LINES TYPICAL EXTERNAL FEATURE

1

1543348

(SHEET 1 OF 2)
 FIGURE 51: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 445 1 (a) (b)

Upper Anti-Collision 

(Strobe) Light

S-1L-1R, STA 555 1 (a) (c)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (d)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (d)

Very High Frequency 

(VHF) Antenna

S-1L-1R, STA 665 1 (a) (e)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (f)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (f)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (g)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 665 1 (a) (g)

Fwd Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 577 3 (a) (h)

Aft Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 621 3 (a) (h)

Marker Beacon Antenna Lower Fuselage C/L, STA 680 1 (a) (i)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 33-44-02.

(d) Refer to 767 AMM 34-58-02.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-57-03.

(g) Refer to 767 AMM 34-55-02.

(h) Refer to 767 AMM 34-33-02.

(i) Refer to 767 AMM 34-32-01.

(SHEET 2 OF 2)
 FIGURE 52: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 52: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 4) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13L INSPECTION AREA EXISTING BUTT JOINT STA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 588 STA 676 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 544STA 566 STA 456 STA 610STA 654 STA 632 STA 698

This Figure applies to Group 4: TYPICAL SCRIBE LINES TYPICAL EXTERNAL FEATURE

1

1543350

(SHEET 1 OF 2)
 FIGURE 52: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 445 1 (a) (b)

Upper Anti-Collision 

(Strobe) Light

S-1L-1R, STA 555 1 (a) (c)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (d)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (d)

Very High Frequency 

(VHF) Antenna

S-1L-1R, STA 665 1 (a) (e)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (f)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (f)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (g)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 665 1 (a) (g)

Fwd Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 577 3 (a) (h)

Aft Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 621 3 (a) (h)

Marker Beacon Antenna Lower Fuselage C/L, STA 680 1 (a) (i)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 33-44-02.

(d) Refer to 767 AMM 34-58-02.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-57-03.

(g) Refer to 767 AMM 34-55-02.

(h) Refer to 767 AMM 34-33-02.

(i) Refer to 767 AMM 34-32-01.

(SHEET 2 OF 2)
 FIGURE 53: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 5)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 53: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 5) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 632 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 588 STA 522 STA 500 STA 610STA 654STA 654+22 STA 654+44 STA 456 STA 544 STA 1241 STA 1219

This Figure applies to Group 5: TYPICAL SCRIBE LINES

TYPICAL EXTERNAL FEATURE

1

1543351

(SHEET 1 OF 2)
 FIGURE 53: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 5)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 448 1 (a) (b)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (c)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (c)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (d)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (d)

Upper Very High 

Frequency (VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 513 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 

1197+99

1 (a) (e)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (f)

Fwd Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 577 3 (a) (g)

Aft Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 621 3 (a) (g)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 34-58-02.

(d) Refer to 767 AMM 34-57-03.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-55-02.

(g) Refer to 767 AMM 34-33-02.

(SHEET 2 OF 2)
 FIGURE 54: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 54: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 6) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 632 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 588 STA 522 STA 500 STA 610STA 654STA 654+22 STA 654+44 STA 456 STA 544 STA 1241 STA 1219

This Figure applies to Group 6: TYPICAL SCRIBE LINES

TYPICAL EXTERNAL FEATURE

1

1543353

(SHEET 1 OF 2)
 FIGURE 54: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 220 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 448 1 (a) (b)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (c)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (c)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (d)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (d)

Upper Very High 

Frequency (VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 513 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 

1197+99

1 (a) (e)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (f)

Fwd Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 577 3 (a) (g)

Aft Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 621 3 (a) (g)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 34-58-02.

(d) Refer to 767 AMM 34-57-03.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-55-02.

(g) Refer to 767 AMM 34-33-02.

(SHEET 2 OF 2)
 FIGURE 55: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 55: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 7) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 632 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 588 STA 522 STA 500 STA 610STA 654STA 654+22 STA 654+44 STA 456 STA 544 STA 1241 STA 1219

This Figure applies to Group 7: TYPICAL SCRIBE LINES

TYPICAL EXTERNAL FEATURE

1

1543355

(SHEET 1 OF 2)
 FIGURE 55: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 222 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 448 1 (a) (b)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (c)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (c)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (d)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (d)

Upper Very High 

Frequency (VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 513 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 

1197+99

1 (a) (e)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (f)

Fwd Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 577 3 (a) (g)

Aft Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 621 3 (a) (g)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 34-58-02.

(d) Refer to 767 AMM 34-57-03.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-55-02.

(g) Refer to 767 AMM 34-33-02.

(SHEET 2 OF 2)
 FIGURE 56: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 8)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 223 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 56: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 8) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 632 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 588 STA 522 STA 500 STA 610STA 654STA 654+22 STA 654+44 STA 456 STA 544 STA 1241 STA 1219

This Figure applies to Group 8: TYPICAL SCRIBE LINES

TYPICAL EXTERNAL FEATURE

1

1543362

(SHEET 1 OF 2)
 FIGURE 56: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 8)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 224 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 448 1 (a) (b)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (c)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (c)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (d)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (d)

Upper Very High 

Frequency (VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 513 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 

1197+99

1 (a) (e)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (f)

Fwd Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 577 3 (a) (g)

Aft Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 621 3 (a) (g)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 34-58-02.

(d) Refer to 767 AMM 34-57-03.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-55-02.

(g) Refer to 767 AMM 34-33-02.

(SHEET 2 OF 2)
 FIGURE 57: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 225 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 57: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 9) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 632 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 588 STA 522 STA 500 STA 610STA 654STA 654+22 STA 654+44 STA 456 STA 544 STA 1241 STA 1219

This Figure applies to Group 9: TYPICAL SCRIBE LINES TYPICAL EXTERNAL FEATURE

1

1543364

(SHEET 1 OF 2)
 FIGURE 57: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 9)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 226 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 448 1 (a) (b)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (c)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (c)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (d)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (d)

Upper Very High 

Frequency (VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 513 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 

1197+99

1 (a) (e)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (f)

Fwd Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 577 3 (a) (g)

Aft Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 621 3 (a) (g)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 34-58-02.

(d) Refer to 767 AMM 34-57-03.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-55-02.

(g) Refer to 767 AMM 34-33-02.

(SHEET 2 OF 2)
 FIGURE 58: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 10)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 227 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 58: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 10) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 632 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 588 STA 522 STA 500 STA 610STA 654STA 654+22 STA 654+44 STA 456 STA 544 STA 1241 STA 1219

This Figure applies to Group 10: TYPICAL SCRIBE LINES TYPICAL EXTERNAL FEATURE

1

1543365

(SHEET 1 OF 2)
 FIGURE 58: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 10)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 228 of 268

BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 448 1 (a) (b)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (c)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (c)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (d)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (d)

Upper Very High 

Frequency (VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 513 1 (a) (e)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 

1197+99

1 (a) (e)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (f)

Fwd Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 577 3 (a) (g)

Aft Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 621 3 (a) (g)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 34-58-02.

(d) Refer to 767 AMM 34-57-03.

(e) Refer to 767 AMM 23-12-03.

(f) Refer to 767 AMM 34-55-02.

(g) Refer to 767 AMM 34-33-02.

(SHEET 2 OF 2)
 FIGURE 59: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 11)

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ALERT ALERT

FIGURE 59: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 11) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 632 INSPECTION AREA EXISTING BUTT JOINT STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 188.9 STA 1131 STA 1109STA 1153 STA 1175 STA 588 STA 522 STA 500 STA 610 STA 654+22 STA 654+44 STA 456 STA 544 STA 654+66 STA 654

This Figure applies to Group 11: TYPICAL SCRIBE LINES TYPICAL EXTERNAL FEATURE

1

1543366

(SHEET 1 OF 2)
 FIGURE 59: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 11)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1122 1 (a) (b)

Automatic Direction Finder 

(ADF) Antenna

S-1L-1R, STA 1166 1 (a) (b)

Upper Very High 

Frequency (VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (c)

Lower Very High 

Frequency (VHF) Antenna

Lower Fuselage C/L, STA 513 1 (a) (c)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (d)

Fwd Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 577 3 (a) (e)

Aft Radio Altimeter (RA) 

Antenna

Lower Fuselage C/L, STA 621 3 (a) (e)

Marker Beacon Antenna Lower Fuselage C/L, STA 

654+26

1 (a) (f)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-57-03.

(c) Refer to 767 AMM 23-12-03.

(d) Refer to 767 AMM 34-55-02.

(e) Refer to 767 AMM 34-33-02.

(f) Refer to 767 AMM 34-32-01.

(SHEET 2 OF 2)
 FIGURE 60: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 12)

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ALERT ALERT

FIGURE 60: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 12) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 610 STA 654 STA 188.9 STA 632 STA 544 STA 654+22STA 654+44 STA 456 STA 588

This Figure applies to Group 12: TYPICAL SCRIBE LINES TYPICAL EXTERNAL FEATURE

1

1543368

(SHEET 1 OF 2)
 FIGURE 60: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECTION (GROUP 12)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Upper Air Traffic Control 

(ATC) Antenna

S-1L-1R, STA 448 1 (a) (b)

Global Positioning System 

(GPS) Antenna Right

S-1L-1R, STA 600 1 (a) (c)

Global Positioning System 

(GPS) Antenna Left

S-1L-1R, STA 622 1 (a) (c)

Very High Frequency 

(VHF) Antenna

S-1L-1R, STA 654+33 1 (a) (d)

Distance Measuring 

Equipment (DME) Antenna

Lower Fuselage C/L, STA 555 1 (a) (e)

Fwd Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 577 3 (a) (f)

Aft Low Range Radio 

Altimeter (LRRA) Antenna

Lower Fuselage C/L, STA 621 3 (a) (f)

(a) Do a detailed inspection of the fuselage skin around the external feature for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around external features, scribe lines normally follow the periphery of the external

feature.

(b) Refer to 767 AMM 34-53-03.

(c) Refer to 767 AMM 34-58-02.

(d) Refer to 767 AMM 23-12-03.

(e) Refer to 767 AMM 34-55-02.

(f) Refer to 767 AMM 34-33-02.

(SHEET 2 OF 2)
 FIGURE 61: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 1)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 61: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 1) S-21R

This Figure applies to Group 1:

1

STA

132.5

STA

246

STA

434

STA

618

STA

786.1

BL 0

S-36RS-26RS-26L

S-36L

S-37R

S-36RS-30R

S-21L

S-30L

S-36L

S-37L

STA

196.5

STA

676

STA

654

STA

1065

STA

1582

STA

1832

STA

1307

STA

1373

S-36RS-26RS-17R

S-8RS-2RS-8L

S-17LS-26LS-36L

STA

1395

STA

1417

STA

188.9

S-13R

S-13L

STA

1087

STA

808

STA

1043

STA

566

INSPECTION AREA

EXISTING BUTT JOINT

1543373

(SHEET 1 OF 2)
 FIGURE 61: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 1)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 676

1 (a) 

S-8R To S-8L and STA 654 To 

STA 808

1 (a) 

S-2R To S-8L and STA 1043 To 

STA 1087

1 (a) 

S-8R To S-8L and STA 1373 To 

STA 1417

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 62: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 62: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 2) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 615 STA 786.1 STA 196.5 STA 676 STA 654 STA 1065 STA 1582 STA 1832 STA 1307 STA 1373STA 1395STA 1417 STA 188.9 STA 1087 STA 808 STA 1043 STA 566

This Figure applies to Group 2:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543374

(SHEET 1 OF 2)
 FIGURE 62: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 2)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 676

1 (a) 

S-8R To S-8L and STA 654 To 

STA 808

1 (a) 

S-2R To S-8L and STA 1043 To 

STA 1087

1 (a) 

S-8R To S-8L and STA 1373 To 

STA 1417

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 63: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 63: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 3) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 618 STA 786.1 STA 196.5 STA 676 STA 654 STA 1065 STA 1582 STA 1832 STA 1307 STA 1373STA 1395STA 1417 STA 188.9 STA 1087 STA 808 STA 1043 STA 566

This Figure applies to Group 3:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543375

(SHEET 1 OF 2)
 FIGURE 63: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 3)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 676

1 (a) 

S-8R To S-8L and STA 654 To 

STA 808

1 (a) 

S-2R To S-8L and STA 1043 To 

STA 1087

1 (a) 

S-8R To S-8L and STA 1373 To 

STA 1417

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 64: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

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ALERT ALERT

FIGURE 64: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 4) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 615 STA 786.1 STA 196.5 STA 676 STA 654STA 698 STA 1065 STA 1582 STA 1832 STA 1307 STA 1373STA 1395STA 1417 STA 742 STA 188.9 STA 1087 STA 808 STA 1043 STA 588 STA 566

This Figure applies to Group 4:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543376

(SHEET 1 OF 2)
 FIGURE 64: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 4)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 676

1 (a) 

S-8R To S-8L and STA 654 To 

STA 808

1 (a) 

S-2R To S-8L and STA 1043 To 

STA 1087

1 (a) 

S-8R To S-8L and STA 1373 To 

STA 1417

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 65: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 5)

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ALERT ALERT

FIGURE 65: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 5) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 618 STA 786.1 STA 196.5 STA 654STA 654+22STA 654+88 STA 1065 STA 1582 STA 1832 STA 1307STA 1373STA 1395 STA 1285 STA 742 STA 188.9 STA 808 STA 1043 STA 566 STA 1197+132 STA 764 STA 698 STA 676 STA 654+44 STA 588 STA 1241

This Figure applies to Group 5:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543378

(SHEET 1 OF 2)
 FIGURE 65: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 5)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 654+22

1 (a) 

S-10R To S-13L and STA 588 To 

STA 676

1 (a) 

B/L 0 To S-8L and STA 786.1 To 

STA 808

1 (a) 

B/L 0 To S-8L and STA 1043 To 

STA 1065

1 (a) 

S-8R To S-12L and STA 

1197+132 To STA 1285

1 (a) 

B/L 0 To S-8L and STA 1373 To 

STA 1395

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 66: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 66: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 6) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 615 STA 786.1 STA 196.5 STA 654STA 654+22STA 654+88 STA 1065 STA 1582 STA 1832 STA 1307STA 1373STA 1395 STA 1285 STA 742 STA 188.9 STA 808 STA 1043 STA 566 STA 1197+132 STA 764 STA 698 STA 676 STA 654+44 STA 588 STA 1241

This Figure applies to Group 6:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543380

(SHEET 1 OF 2)
 FIGURE 66: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 6)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 654+22

1 (a) 

S-10R To S-13L and STA 588 To 

STA 676

1 (a) 

B/L 0 To S-8L and STA 786.1 To 

STA 808

1 (a) 

B/L 0 To S-8L and STA 1043 To 

STA 1065

1 (a) 

S-8R To S-12L and STA 

1197+132 To STA 1285

1 (a) 

B/L 0 To S-8L and STA 1373 To 

STA 1395

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 67: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

FIGURE 67: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 7) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 618 STA 786.1 STA 196.5 STA 654STA 654+22STA 654+88 STA 1065 STA 1582 STA 1832 STA 1307STA 1373STA 1395 STA 1285 STA 742 STA 188.9 STA 808 STA 1043 STA 566 STA 1197+132 STA 764 STA 698 STA 676 STA 654+44 STA 588 STA 1241

This Figure applies to Group 7:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543383

(SHEET 1 OF 2)
 FIGURE 67: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 7)

Original Issue: November 25, 2008

Revision 1: April 09, 2009 767-53A0193

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 654+22

1 (a) 

S-10R To S-13L and STA 588 To 

STA 676

1 (a) 

B/L 0 To S-8L and STA 786.1 To 

STA 808

1 (a) 

B/L 0 To S-8L and STA 1043 To 

STA 1065

1 (a) 

S-8R To S-12L and STA 

1197+132 To STA 1285

1 (a) 

B/L 0 To S-8L and STA 1373 To 

STA 1395

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 68: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 8)

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FIGURE 68: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 8) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 615 STA 786.1 STA 196.5 STA 654STA 654+22STA 654+88 STA 1065 STA 1582 STA 1832 STA 1307STA 1373STA 1395 STA 1285 STA 742 STA 188.9 STA 808 STA 1043 STA 566 STA 1197+132 STA 764 STA 698 STA 676 STA 654+44 STA 588 STA 1241

This Figure applies to Group 8:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543384

(SHEET 1 OF 2)
 FIGURE 68: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 8)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 654+22

1 (a) 

S-10R To S-13L and STA 588 To 

STA 676

1 (a) 

B/L 0 To S-8L and STA 786.1 To 

STA 808

1 (a) 

B/L 0 To S-8L and STA 1043 To 

STA 1065

1 (a) 

S-8R To S-12L and STA 

1197+132 To STA 1285

1 (a) 

B/L 0 To S-8L and STA 1373 To 

STA 1395

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 69: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 9)

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FIGURE 69: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 9) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 618 STA 786.1 STA 196.5 STA 654STA 654+22STA 654+88 STA 1065 STA 1582 STA 1832 STA 1307STA 1373STA 1395 STA 1285 STA 742 STA 188.9 STA 808 STA 1043 STA 566 STA 1197+132 STA 764 STA 698 STA 676 STA 654+44 STA 588 STA 1241

This Figure applies to Group 9:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543385

(SHEET 1 OF 2)
 FIGURE 69: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 9)

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 654+22

1 (a) 

S-10R To S-13L and STA 588 To 

STA 676

1 (a) 

B/L 0 To S-8L and STA 786.1 To 

STA 808

1 (a) 

B/L 0 To S-8L and STA 1043 To 

STA 1065

1 (a) 

S-8R To S-12L and STA 

1197+132 To STA 1285

1 (a) 

B/L 0 To S-8L and STA 1373 To 

STA 1395

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 70: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 10)

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FIGURE 70: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 10) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 615 STA 786.1 STA 196.5 STA 654STA 654+22STA 654+88 STA 1065 STA 1582 STA 1832 STA 1307STA 1373STA 1395 STA 1285 STA 742 STA 188.9 STA 808 STA 1043 STA 566 STA 1197+132 STA 764 STA 698 STA 676 STA 654+44 STA 588 STA 1241

This Figure applies to Group 10:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543387

(SHEET 1 OF 2)
 FIGURE 70: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 10)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 654+22

1 (a) 

S-10R To S-13L and STA 588 To 

STA 676

1 (a) 

B/L 0 To S-8L and STA 786.1 To 

STA 808

1 (a) 

B/L 0 To S-8L and STA 1043 To 

STA 1065

1 (a) 

S-8R To S-12L and STA 

1197+132 To STA 1285

1 (a) 

B/L 0 To S-8L and STA 1373 To 

STA 1395

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 71: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 11)

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FIGURE 71: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 11) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 618 STA 786.1 STA 196.5 STA 654STA 654+22STA 654+88 STA 1065 STA 1582 STA 1832 STA 1307 STA 1480 STA 1395 STA 188.9 STA 808 STA 566 STA 676 STA 654+44 STA 588 STA 1241 STA 889 STA 1153

This Figure applies to Group 11:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543388

(SHEET 1 OF 2)
 FIGURE 71: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 11)

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1

Inspect Decals S-17L To S-26L and STA 566 To 

STA 654+22

1 (a) 

S-10R To S-10L and STA 654 To 

STA 676

1 (a) 

S-2R To S-2L and STA 676 To 

STA 786.1

1 (a) 

B/L 0 To S-8L and STA 786.1 To 

STA 889

1 (a) 

S-4R To S-6L and STA 1065 To 

STA 1153

1 (a) 

S-4R To S-6L and STA 1395 To 

STA 1480

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 FIGURE 72: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 12)

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FIGURE 72: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 12) BL 0 S-36R S-26R S-26L S-36L S-37R S-36R S-30R S-21R S-21L S-30L S-36L S-37L S-36R S-26R S-17R S-8R S-2R S-8L S-17L S-26L S-36L S-13R S-13LSTA 132.5 STA 246 STA 434 STA 786.1 STA 196.5 STA 654A+22 STA 654 STA 1065 STA 1582 STA 1832 STA 1307 STA 1395 STA 676 STA 188.9 STA 654+88 STA 1197+154 STA 566

This Figure applies to Group 12:

1

INSPECTION AREA

EXISTING BUTT JOINT

1543391

(SHEET 1 OF 2)
 FIGURE 72: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 12)

Original Issue: November 25, 2008

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY

MORE 

DATA

1 Inspect Decals S-17L To S-26L and STA 566 To 

STA 654A+22

1 (a) 

S-10R To S-10L and STA 654 To 

STA 676

1 (a) 

(a) Do a detailed inspection of the fuselage skin around the decal areas for any scribe line. Use a 

minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLENDING A SCRIBE LINE MAY HINDER

INSPECTION TECHNIQUES NECESSARY TO DETERMINE THE PRESENCE OR

ABSENCE OF FATIGUE CRACKS.

NOTE: In areas around decals, scribe lines normally follow the periphery of the decal. 

(SHEET 2 OF 2)
 APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

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ALERT ALERT

APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

1. MATERIAL AND EQUIPMENT

A. Scrapers

1. AC Tech Scraper, TS 1275-4 (6 inch length)

Supplier: Advanced Chemistry & Technology (AC TECH)

Address: 7341 Anaconda Avenue, Garden Grove, CA 92841, USA

Phone: 714-373-2837 extension 119 or 117

Fax: 714-373-1913, Attn: Customer Service

email: rosie.cruze@actechaero.com

NOTE: Handles are also available for these products for better comfort and control. The handle

best suited for the TS 1275-4 scraper can be purchased under the part number SHR

0272-T from AC Tech.

2. SEMCO Scraper: P/N 234350 (6 inch length)

Supplier: PPG Aerospace: SEMCO Division

Address: PPG-Aerospace (ASC-Seattle), 14126 NE 190th Street, Woodinville, WA 98072, USA

Phone: North America 800 237-6649 (This connects to the closest PPG Aerospace facility in

 North America. For North America and International contacts visit the web site.)

 China (Suzhou) 86 512 6661 5858

 Dubai UAE 971 4 883 9666

 France 33 0 5 6149 4849

 Germany 49 40 742 193 10

 Hong Kong 852 2861 0918

 South Africa 27 11 608 5656

 Singapore 65 861 1119

 United Kingdom 44 0 1388 770222

Web Site: www.ppg.com/prc-desoto/main.asp?img=asc

email: Cheryl.Chittenden@PPG.com?subject=Semco Scrapers (PN-234350)

3. Jus N Tyme Scrapers: P/N JNT 411B60 (6 inch length), P/N JNT 411B90 (9 inch length -tapered)

Supplier: Jus N Tyme Tooling

Address: 2167 Green Canyon Road, Fallbrook, CA 92028, USA

Phone: 760 723-5985

Fax: 760 723-5820

Contacts: Cheryl or Bob Hancock

Web Site: www.JusNTyme.com

email: Bob@JusNTyme.com

NOTE: Scraper P/N JNT 411B90 is designed for removing sealant from butt joints with a 1/4

inch or larger gap.

4. PnJ Scrapers: P/N DFD5019, SCD5019, SFD7519, DAD5013 (5 and 9 inch lengths of varying 

widths); Plastic handles: P/N SHN0272, SHW0215, SHR0272
 APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

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ALERT ALERT

Supplier: PnJ Machining, Inc.

Address: 2601 Inter Avenue, Puyallup, WA 98372, USA

Phone: 253 841-0500

Fax: 253 840-1695

Contact: Paul Hogeboom

Web site: www.pnjmachining.com

NOTE: Scraper P/N DAD5013 is designed for removing sealant from butt joints with a 1/8 inch

or larger gap.

5. Elixair Scrapers: P/N 311/03/04, 311/06/06, 311/12/04, 311/12/06, 311/24/04, 311/24/06, 311/

38/04, and 311/38/06 (7.5 inch length with handle of varying widths); Skyholder Rubber Handle: 

P/N 310/1; Skymill Pneumatic Scraper Sharpener: P/N 309/3; Skybag for sharpener: P/N 309/

3B

Supplier: Elixair International Limited

Address: Roman Hill Business Park, Broadmayne, Dorset DT2 8LY, United Kingdom

Phone: 44 0 1305 853019 (within the UK); 44 1305 853019 (within the USA)

Fax: 44 0 1305 852060 (within the UK); 44 1305 852060 (within the USA)

Contact: Len McLaughlin

Web site: www.elixair.co.uk

email: sales@elixair.com or lenmclaughlin@elixair.co.uk

NOTE:

1. Scraper P/N 311/03/06 is designed for removing sealant from butt joints with a 3 

mm or larger gap.

2. The pneumatic sharpener can be used to sharpen most plastic scrapers.

6. Custom Components LTD Scraper: P/N 10810 (6 inch length)

Supplier: Custom Components LTD

Address: Unit 3, Feltrim Business Park, Swords Co., Dublin Ireland

Phone: 353 1 8901909

Fax: 353 1 8901907

7. Bomatic, Inc. Scraper: P/N 1-6390-A (9 inch length - tapered)

Supplier: Bomatic, Inc.

Address: 1841 E. Acacia St., Ontario, CA 91761, USA

Phone: 909 947 3900

Fax: 909 947 5969

Contact: Kjeld Hestehave, Cathy Macri

Web site: www.bomatic.com

NOTE: Scraper P/N 1-6390-A is designed for removing sealant from butt joints with a 1/4 inch

or larger gap.

8. General Tool & Supply Scraper: P/N ST982L-9ACE (9 inch length)
 APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

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ALERT ALERT

Supplier: General Tool & Supply

Address: 355 Trek Drive, Tukwila, WA 98188, USA

Phone: 206 762-1500

Toll: 1 800-321-3305

Fax: 206 767-7026

Contact: Dean Zetty

Web site: www.generaltool.com

email: dzetty@generaltool.com

B. Power Tools

1. 3M SR cutter - No. 3, 0.40 inch diameter, P/N 48011-30096-2

NOTE: Any power tool that will accept the 3M SR Cutter and has a maximum speed of 850 RPM

(at the cutter) can be used.

C. Solvents

1. Methyl Ethyl Ketone (MEK), ASTM D740

2. Methyl Propyl Ketone (MPK), BMS 11-9, Grades 1 and 2

3. Aliphatic Naptha, TT-N-95, Type I and Type III

4. Toluene, TT-T-548 or ASTM D362

5. Isopropyl Alcohol TT-I-736

D. Miscellaneous

1. Aluminum Oxide abrasive paper, 400 grit or finer

2. Paper or wipers that meet the requirements of BSM 15-5

2. SEALANT REMOVAL NOTES:

This appendix provides procedures for removing sealant from the exterior pressurized fuselage. Using 

these procedures will minimize the risk of damaging clad aluminum surfaces during sealant removal. The 

main areas of concern are:

A. Lap joints

B. Butt joints (including underlying splice plates)

C. Other areas where sealant is present (i.e. wing to body fairings, windows, access doors, etc.)

Boeing recommends only approved scrapers and tools listed in Paragraph 1 of this appendix be used for 

removing sealant from the exterior fuselage. Alternately, it is acceptable to use other scrapers provided 

they meet the requirements of BSS7384 (Method for Evaluating Tool Materials for use on Unpainted Clad 

Aluminum). Commonly used scraper materials such as Lexan polycarbonate, acrylic (Plexiglas), Micarta 

fiber reinforced phenolic resins, metal, wood, and other hard plastics have been tested and found to scratch 

clad aluminum.
 APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

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ALERT ALERT

3. SEALANT REMOVAL PROCESS: LAP JOINT FILLET

A. To remove the lap joint fillet, follow this procedure:

CAUTION: PLEASE NOTE THAT THERE IS A POTENTIAL FOR THE SR CUTTER TO "RUN

AWAY" AND CAUSE DAMAGE AT THE LAP JOINT AND SURROUNDING AREA.

ALSO, IF THE CUTTER CONTACTS BARE METAL BENEATH THE SEALANT, THE

CLAD ALUMINUM SKIN COULD BE DAMAGED. BEFORE USING THE 3M SR

CUTTER, OPERATORS SHOULD BE TRAINED ON PROPER USAGE OF THIS TOOL

AND SHOULD PRACTICE ON TEST PANELS OR PIECES TO PERFECT THEIR

SKILLS IN WORKING WITH THE TOOL.

1. Remove the majority of the fillet seal at the lap joint using any of the approved scrapers listed in 

Paragraph 1.A. of this appendix.

As an alternative, the 0.4 inch diameter 3M SR Cutter listed in Paragraph 1.B. of this appendix 

can be used. To prevent the cutter from damaging the clad aluminum surface, do not remove 

the sealant to bare metal. There should be a thin layer of sealant remaining on the surface after 

removing the majority of the sealant with the 3M SR Cutter.

2. After removing the majority of the sealant with approved scrapers or the 3M SR Cutter, remove 

the remaining sealant with any of the solvents listed in Paragraph 1.C. of this appendix. An 

approved scraper (Paragraph 1.A.) or wiper (Paragraph 1.D.) can be used along with the solvent 

to help with the removal.

4. SEALANT REMOVAL: BUTT JOINTS AND OTHER AREAS WHERE SEALANT IS PRESENT ON THE 

EXTERIOR FUSELAGE

A. To remove sealant in butt joints and other areas on the exterior fuselage, follow this procedure:

CAUTION: THE 3M SR CUTTER IS RECOMMENDED FOR REMOVING SEALANT FROM LAP

JOINTS, BUT NOT FROM BUTT JOINTS OR OTHER AREAS.

1. Remove the bulk of the sealant using any of the approved scrapers in Paragraph 1.A. of this 

appendix. Scrapers designed specifically for removing sealant from butt joints are available (i.e. 

PnJ, Elixair, Bomatic, Jus N Tyme). The shape of an approved scraper can be modified to fit a 

butt joint or other areas, as required. One possible modification is shown below.
 APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

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ALERT ALERT

2. After removing the majority of the sealant with approved scrapers or the 3M SR Cutter, remove 

the remaining sealant with any of the solvents listed in Paragraph 1.C. of this appendix. An 

approved scraper (Paragraph 1.A.) or wiper (Paragraph 1.D.) can be used along with the solvent 

to help with the removal.

5. SCRAPER MAINTENANCE

Scrapers dulled from use can be sharpened with 400 grit or finer aluminum oxide paper. Before using a 

sharpened scraper, the scraper should be rubbed on paper or cheesecloth (Paragraph 1.D.2.) to remove 

loose sanding particles. If an alternate method of sharpening is used, such as a metal sharpening wheel 

(including the Elixair International Limited pneumatic scraper sharpener), rub the scraper on 400 grit or 

finer aluminum oxide paper after sharpening to remove debris, and then rub the scraper on paper or 

cheesecloth to remove loose particles.

6. USE OF CHEMICAL STRIPPERS TO ASSIST IN SEALANT REMOVAL FOR SCRIBE LINE INSPECTION

A. MATERIALS

1. Cee-Bee E-1058, McGean-Rohco, Inc. Atlanta GA.

2. Eldorado PR-5044, Eldorado Chemical Company, Inc. San Antonio TX.

3. Elixair - Skyrestore (Thick), Elixair International Limited, Dorchester, England.

4. Naftosolv FN, Chemetall GMBH, Frankfurt, Germany.

5. Skycleen 2000 Aviation Cleaner, Solutia Inc. St. Louis, MO.

6. Turco 5351, Henkel Corporation, Madison Heights, MI.

B. SEALANT REMOVAL

Use one of the following methods to remove sealant along lap and butt joints on the exterior fuselage.

1. Method 1 - Mechanical/Chemical

POSSIBLE SCRAPER

MODIFICATION TO FIT

A BUTT JOINT

SCRAPER WIDTH

BUTT JOINT

GAP WIDTH

1554791
 APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN

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ALERT ALERT

Remove sealant fillet with an approved scraper in accordance with Paragraph 1.A., above. 

Chemically strip any sealant remaining on the surface as follows:

a. Mask surrounding areas as necessary to prevent contact with chemical strippers. Do not 

allow chemical strippers to contact substrates other than aluminum. Do not use chemical 

strippers on reverse lap joints.

NOTE: Chemical strippers will soften and remove paint.

b. Using a natural bristle brush, apply a thin coating of chemical stripper on the sealant.

CAUTION: CHEMICAL STRIPPER MAY PENETRATE INTO JOINTS IF GAPS ARE

PRESENT DUE TO MISSING FAYING SURFACE SEALANT.

(1) Do not apply excessive chemical stripper. Stripper should hang and not flow.

(2) Let the stripper dwell until the sealant can be easily removed by dry wiping, but do not 

exceed 40 minutes dwell time.

(3) Remove softened sealant with clean dry wipers (BMS 15-5 Class A). Approved 

scrapers may be used as given in 767 AMM 51-31-00 to facilitate removal.

c. After chemical stripping is complete, remove stripper by thoroughly washing with a waterbased alkaline cleaner approved for painted surfaces in accordance with SOPM 20-30-03. 

Rinse off alkaline cleaner with water.

2. Method 2 - Chemical/Mechanical/Chemical

a. Mask surrounding areas as necessary to prevent contact with chemical strippers. Do not 

allow chemical strippers to contact substrates other than aluminum.

b. Using a natural bristle brush, apply a thin coating of chemical stripper on the sealant fillet.

c. Let the chemical stripper dwell for a maximum of 4 hours, except use a maximum dwell time 

of 2 hours if Turco 5351 is used. A thin coat of stripper may be brushed on every hour as 

necessary to maintain a wet surface. Do not apply excessive stripper. Stripper should hang 

and not flow.

d. Do not apply chemical stripper to areas where the joint is exposed.

e. Remove softened sealant with an approved scraper as given in 767 AMM 51-31-00 and 

clean dry wipers (BMS 15-5 Class A).

f. Repeat steps b., c., d., and e. if necessary, but do not apply chemical stripper to areas where 

the joint is exposed.

g. If any sealant remains on the surface after removing the sealant fillet, follow the procedure 

outlined in Method 1.

h. After chemical stripping is complete, remove stripper by thoroughly washing with a waterbased alkaline cleaner approved for painted surfaces in accordance with SOPM 20-30-03. 

Rinse off alkaline cleaner with water.
 APPENDIX B: REPORTING SYSTEM - LIMITED RETURN TO SERVICE PROCEDURE FOR AIRPLANES 

WITH SCRIBE LINES

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

APPENDIX B: REPORTING SYSTEM - LIMITED RETURN TO SERVICE PROCEDURE FOR AIRPLANES 

WITH SCRIBE LINES 

Boeing recommends that operators use the format that follows to report the results of the inspections in this 

service bulletin to Boeing. Use of this standard format will result in a more rapid review and approval of the data. 

A Return to Service Proposal will be provided by Boeing after review of the data.

INTRODUCTION:

The following is a summary of the work carried out on airplane ___________ as part of a return to 

service workpack.

Airplane Model:

Airplane Registration:

Airplane Variable Number:

Airplane Line Number:

Airplane Serial Number:

Airplane Total Hours / Flight Cycles:

Airplane Flight Cycles Since Scribe Line Introduction:

BACKGROUND:

____________ has completed the following work on airplane ___________:

INSPECTIONS:

The following inspections were completed on airplane ___________:

Detailed Visual Inspections:

Lap Joints:

Fuselage lap joints between STA _______ To STA _________

Findings: (Include a detailed description of any damage found, including locations, 

message numbers, etc. Attach additional pages as necessary.)

Action: 

External Approved Repairs:

Fuselage skin around certain external doublers/repairs.

Findings: (Include a detailed description of any damage found, including locations, 

message numbers, etc. Attach additional pages as necessary.)

Action: 

External Features:

Fuselage skin around certain external features.

Findings: (Include a detailed description of any damage found, including locations, 

message numbers, etc. Attach additional pages as necessary.)

Action: 
 APPENDIX B: REPORTING SYSTEM - LIMITED RETURN TO SERVICE PROCEDURE FOR AIRPLANES 

WITH SCRIBE LINES

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Decals:

Fuselage skin around decals.

Findings: (Include a detailed description of any damage found, including locations, 

message numbers, etc. Attach additional pages as necessary.)

Action: 

Maximum Observed Scribe line Depth:

The maximum scribe line depth for all locations (skin lap joints, external approved 

repairs, external features, and decals) is ______ inches.

NDT Inspections:

All NDT inspections for cracks at scribe line locations have been accomplished as shown in 

the Accomplishment Instructions of Service Bulletin 767-53A0193.

Findings: (Include a detailed description of any damage found, including locations, message 

numbers, etc. Attach additional pages as necessary.)

Action:
 APPENDIX C: AIRPLANE FUSELAGE SCRIBE LINE MARK SUMMARY TABLES

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

APPENDIX C: AIRPLANE FUSELAGE SCRIBE LINE MARK SUMMARY TABLES

Table 1 - Skin Lap Joints

Location Length 

(inches)

Distance From Lap (Inches) Depth 

(inches)

Stringer Forward 

Body 

Station

Aft Body 

Station

L d_fwd 

(a)

d_min 

(b)

d_aft 

(c)

(a) d_fwd = Distance from the edge of the upper skin of the forward end of the scribe line.

(b) d_min = Minimum distance of the scribe line at any point along the entire length of the 

scribe line from the edge of the upper skin.

(c) d_aft = Distance from the edge of the upper skin of the aft end of the scribe line.

L

d_fwd d_min d_aft

SCRIBE

LINE

LAP JOINT

UPPER SKIN

LOWER SKIN

1554792
 APPENDIX C: AIRPLANE FUSELAGE SCRIBE LINE MARK SUMMARY TABLES

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

Table 2 - Locations other than Skin Lap Joints

Forward 

Body 

Station

Aft Body 

Station

Stringer Length 

(inches)

Distance From Stringer 

(Inches)

Depth 

(inches)

L d_fwd (a) d_aft (b)

SSSS- 

(a) d_fwd = Distance of the forward end of the scribe from the stringer.

(b) d_aft = Distance of the aft end of the scribe from the stringer.

STRINGER X

CENTER LINE

d_fwd d_aft

L

SCRIBE

FUSELAGE

SKIN

1554793
 APPENDIX D: SCRIBE LINE SAMPLE

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

APPENDIX D: SCRIBE LINE SAMPLE

The instructions that follow can be used to make representative samples of the kinds of scribe line marks that 

may be found during the inspections specified in this service bulletin.

This design is a visual inspection aid that can be used to familiarize visual inspectors with scribe lines and 

assure consistency between visual inspectors. The flag note 1 scribe line is intended to show the inspector how 

a scribe line can be hidden under a lap chamfer, requiring the inspector to look at an oblique angle to the lap 

joint edge to detect some scribes lines. The flag note 2 scribe line is intended to demonstrate a typical tactile 

scribe line. The flag note 3 scribe line is intended to demonstrate a shallow non-tactile scribe line.

NOTE:

1. Minimum surface roughness is 125 microinches.

2. Break all sharp edges.

3. Unless otherwise noted, the following dimensions and tolerances are used:

— All dimensions are in inches.

— Tolerance on linear dimensions, other than rivet or bolt edge margins, is plus or minus 0.03 

inch.

— Tolerance on rivet or bolt edge margin is plus or minus 0.05 inch.

— Angular tolerance is plus or minus 2 degrees.

— Hole dimensions for standard solid rivets are given in 767 Structural Repair Manual, Chapter 

51.

1. Make part A from bare 2024-T3 aluminum, 0.040 inch thick. 0.060 inch thick bare 2024-T3 is an acceptable 

substitute.

2. Make part B from bare 2024-T3 aluminum, 0.071 inch thick.

3. Fasten part B to part A with five - 5/32 inch diameter countersunk rivets. Make the countersinks in part B.

4. Make three typical scribe line marks on part A as follows:

A. Flag Note 1: Scribe part A with the tip of a razor knife, using one to two pounds down load with finger 

pressure on the knife handle. Displaced material from the scribing operation should remain on part A. 

Make sure that the scribe line is under the 20 degree chamfer on the edge of part B. Make sure the 

scribe line can be seen visually.

B. Flag Note 2: Scribe part A with the tip of a razor knife, using one to two pounds down load with finger 

pressure on the knife handle. Displaced material from the scribing operation should remain on part A. 

Make sure the scribe line is tactile (a fingernail can catch on the scribe line).

C. Flag Note 3: Scribe part A with one pass from the tip of a ball point pen, using 0.25 to 0.5 pound down 

load. Make sure the scribe line is not tactile (a fingernail does not catch on the scribe line). As an 

alternative to a ball point pen, use the edge of a 0.040 inch wide CRES plate, with 0.25 inch diameter 

radii at the corners of the plate.
 APPENDIX D: SCRIBE LINE SAMPLE

Original Issue: November 25, 2008

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BOEING SERVICE BULLETIN 767-53A0193

ALERT ALERT

This sample can be obtained from the following vendors:

EC/NDT

1020 South 344th St.

Suite 214

Federal Way, WA 98003

USA

Phone: [253] 815-0797

Fax: [253] 815-0827

DT ENGINEERING CORP

19620 Russell Road

Kent, WA 98032

USA

Phone: [253] 872-3565

Fax: [253] 872-0857

2.0

(TYPICAL)

2.0

(TYPICAL)

1.0 2.0 1.0 2.0

12.0

4.00

3.50

2.90

FASTENER (TYPICAL, 5 LOCATIONS)

PART B

PART A

A-A

CHAMFER 20°

SCRIBE SAMPLE

A

A

1 2 3

1

1554794