Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 268 ALERT ALERT 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 th e Fuselage Skin for Scribe Lines



## BOEING PROPRIETARY, CONFID ENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document on ly 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 Compan y, 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, MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or its subsidiaries. No intellectua l property license (express or implied) is granted in connection with this document or otherwise.BLANK PAGE Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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BLANK PAGETable of Contents Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 Intermix ability 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 Spar es . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 L AP JOINT - ZONE 1 INSPEC TION (GROUP 1) . . . . . . . . . . . 107 FIGURE 2: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (GROUP 2) . . . . . . . . . . . 109 FIGURE 3: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (GROUP 3) . . . . . . . . . . . 111 FIGURE 4: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (GROUP 4) . . . . . . . . . . . 113 FIGURE 5: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (GROUP 5) . . . . . . . . . . . 115 FIGURE 6: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (GROUP 6) . . . . . . . . . . . 117 FIGURE 7: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (GROUP 7) . . . . . . . . . . . 119 FIGURE 8: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (GROUP 8) . . . . . . . . . . . 121 FIGURE 9: FUSELAGE - SKIN L AP JOINT - ZONE 1 INSPEC TION (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) . . . . . . . . . . 127Table of Contents Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 1) 185 FIGURE 38: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 2) 187 FIGURE 39: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 3) 189 FIGURE 40: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 4) 191 FIGURE 41: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 5) 193 FIGURE 42: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 6) 195 FIGURE 43: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 7) 197 FIGURE 44: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 8) 199 FIGURE 45: FUSELAGE - EXTER NAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 9) 201 FIGURE 46: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 10) 203 FIGURE 47: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 11) 205 FIGURE 48: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 12) 207 FIGURE 49: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 1) . . . . . . 209 FIGURE 50: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 2) . . . . . . 211 FIGURE 51: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 3) . . . . . . 213 FIGURE 52: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 4) . . . . . . 215 FIGURE 53: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 5) . . . . . . 217 FIGURE 54: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 6) . . . . . . 219 FIGURE 55: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 7) . . . . . . 221 FIGURE 56: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 8) . . . . . . 223 FIGURE 57: FUSELAGE - EXTERNAL FEATURES - ZONE 2 INSPECT ION (GROUP 9) . . . . . . 225Table of Contents Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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FIGURE 58: FUSELAGE - EXTERNAL F EATURES - ZONE 2 INSPECTION (GROUP 10) . . . . . . 227 FIGURE 59: FUSELAGE - EXTERNAL F EATURES - ZONE 2 INSPECTION (GROUP 11) . . . . . . 229 FIGURE 60: FUSELAGE - EXTERNAL F EATURES - 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 FO R EXTERIOR PRESSURIZED FUSELAGE SKIN 257 APPENDIX B: REPORTING SYSTEM - LIMITE D 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 267Table of Contents Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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BLANK PAGEOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### 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 th e Fuselage Skin for Scribe Lines

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORM ATION RELATED TO THIS REVISION

The Federal Aviation Administration (F AA) will possibly release an Airworthin ess Directive related to this service bulletin. The Airworthiness Directiv e will make the compliance tasks and ti mes given in this service bulletin mandatory.

More work is necessary for airplanes that have accomplis hed skin lap joint inspections as shown in the original issue of this service bulletin. Operators that have incor porated the original issue of this service bulletin for the skin lap joint inspections must revi ew the REASON FOR REVISION information belo w, and do additional skin lap joint inspections, as necessary, to comp ly 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 repe at 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 th e 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 inspec tions 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, an d 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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REASON FOR REVISION

This revision is sent to change init ial inspection locations and LRTS insp ection locations and repeat inspection intervals for skin lap joint inspections. In addition, caut ion notes are added to advise operators not to blend scribe lines.

These sections were changed:

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

2. In Paragraph 1.E., Compliance, Table 2 was changed to cl arify footnotes (f) and (g) an d 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 fo r 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 Instructio ns, 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 Caut ion 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, exce pt in Paragraph 1.A., Effectiv ity, to show the location of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: November 25, 2008 Revision 1: April 09, 2009Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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# Service Bulletin

Number: 767-53A0193 

### Summary Original Issue: November 25, 2008 Revision 1: April 09, 2009 ATA System: 5311

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

THIS BULLETIN IS SENT TO THE OPERATOR S OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLA NE HAS BEEN LEASED OR SO LD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLIC ABLE 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 extern al features such as anten nas, 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, di stinct line of damage (typ ically up to 0.006 inch deep), usually associated with the removal of a fillet or gap seal (lap joints and butt joints, respective ly). A more detaile d definition of a scribe line is included in Accomplishmen t Instructions Paragraph 3.B. - Identif ication of a "Typical" Scribe Line.

A review of fleet activity yields tw o separate scenarios that are suspected to have caused scribe lines to the fuselage skin.

The first scenario involves the paint stripping and repain ting of airplanes. In the process of stripping and preparing the airplane for paint, tools were used to remo ve 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. Fa tigue cracks can deve lop at scribe line locations.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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The second scenario is decal application on/or removal fr om the fuselage. To install the decals across lap joint steps or repairs, investigation into maintenance practice s has shown that decals have been cut in place, using some form of knife, to allow the deca l 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 bulle tin, remove paint and sealant at the applicable locations. Do a detailed inspection of the fusel age 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 altern ative to immediate repair, for a scribe line that qualifies, the provided Limited Re turn To Service (LRTS) program may be used to allow airplanes to return to revenue flight for a limited peri od 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 affe cted structural location within a LR TS program will be terminated with a repair.

This service bulletin has specific instru ctions for calculating separate inspec tion 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 f light 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 serv ice bulletin to address the most critical areas first and to provide less critical areas with appropriately reduced compliance requirements. Criticality of location de termines the inspection thresholds for each location. This service bulletin uses fi gures and compliance times to address all of the critical locations and ranges of inspection thresholds. Each crit ical 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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COMPLIANCE

The Federal Aviation Administration (F AA) will possibly release an Airworthin ess Directive related to this service bulletin. The Airworthiness Directiv e will make the compliance tasks and ti mes given in this service bulletin mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspecti ons 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 50.0Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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.1560615Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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# Service Bulletin

Number: 767-53A0193 Original Issue: November 25, 2008 Revision 1: April 09, 2009 ATA System: 5311

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

THIS BULLETIN IS SENT TO THE OPERATOR S OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLA NE HAS BEEN LEASED OR SO LD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLIC ABLE 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 show n below. Aircraft Maintenance Manual (AMM) changes were released after line number 928 to address proper methods of paint and sealant removal to reduce the po ssibility 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 doorOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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Airplane models:

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

IDENTIFICATION BY CUSTOMER, CUSTO MER 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 DESCRIPTIONOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 VN427Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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ALITALIA COMPAGNIA AER EA 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 VE069Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 VN972Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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–VS428Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 VK141Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 VB282Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 VB328Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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–VA010Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 1Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 GroupOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 GroupOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 GroupOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect for scribe lines in th e fuselage skin at skin lap joints, the skin at certain external approved repairs, the sk in 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 GroupOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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Thirteen (13) 767 airplanes have been found with scribe line damage by 11 operators. Scribe lines were found at skin lap jo ints, 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 be tween 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 re moval 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 scena rios that are suspected to have caused scribe lines to the fuselage skin.

The first scenario involves the paint stripping and repa inting 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 doo r scuff plates, or around external features. Tools like scrapers (steel, wood, hard plastic etc.), kniv es, or utility knives can damage the sk in. 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, invest igation 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 sk in 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 wa s 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 interval s for skin lap joint inspections.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 bu lletin, remove paint and sealant at the applicable locations. Do a detailed in spection 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 be fore 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 pr ogram. Each affected stru ctural location within a LRTS program will be terminated with a repair.

This service bulletin has specific in structions 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 stru ctural 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 lo cations and ranges of inspection thresholds. Each critical piece of structure susceptible to a scribe lin e is assigned to a figure. The affected structure for each group of airplanes is identified in indi vidual figures in this service bulletin.

Revision 1 - More work is necess ary for airplanes that have accomplished skin lap joint inspections as shown in the original issue of this service bulle tin. Operators that have incorporated the original issue of this service bulletin for the skin lap joint inspecti ons 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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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, op erators 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 inspecti ons must review the REASON FO R REVISION info rmation 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 in spections were exempted by Compliance Table 3, Note (e). Operators that have incorporated the orig inal issue of this service bulletin for the external feature inspections must review the REASON FOR R EVISION information belo w, and do additional external feature inspections, as necessary, to co mply with Revision 1 of this service bulletin.

No more work is required for inspections to decals.

E. Compliance

The Federal Aviation Admini stration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airwor thiness Directive will ma ke the compliance tas ks 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 in to three main sections as follows:

1. Tables 1 through 4 are used to show the initial scribe line inspection for th e 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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. - -Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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Scribe line is found within the limits of a typical scribe line and more than 0.006 inch deep. (c) Do High Frequenc y 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 mainte nance records. Adjust the compliance time as given below:

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

2. If record of first paint since delivery is not ava ilable, 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 Paragrap h 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) be low. 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)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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(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 correc t sealant removal procedure is implemented for all future work, then the skin lap join t 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 seal ant 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 pr eviously installed, across a skin la p joint that requires inspection, the inspection exemption per note (d) and (f) does not apply. The skin la p 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 Repair s - 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)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 main tenance records. Adjust the compliance time as given below:

1. If record of first paint since deliv ery is available, then add the airpl ane flight cycles at first paint to the threshold.

2. If record of first paint since delivery is not av ailable, 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 Repa irs - Fuselage Skin Scribe Line Inspection

Condition Action Compliance Time (Whichever Occurs Later) Repeat Interval (Not to Exceed)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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(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 correc t 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 bulle tin as an accepted sealant removal procedure. (g) For each repair, if operator’s records show that th e airplane has never been stripped or repainted since the repair has been installed, then the external approve d 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 approve d repair inspection must st ill 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 Repair s - Fuselage Skin Scribe Line Inspection

Condition Action Compliance Time (Whichever Occurs Later) Repeat Interval (Not to Exceed)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 main tenance records. Adjust the compliance time as given below:

1. If record of first paint since deliv ery is available, then add the airpl ane flight cycles at first paint to the threshold.

2. If record of first paint since delivery is not av ailable, 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 Instru ctions 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)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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(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 r equired. 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 pr eviously installed across an external feature, the exemption per note (e) does not apply. The external feature inspection must still be done for the affected ex ternal feature at the threshold as given in this table.

Group 1-12: Table 4 - Decals - Fuse lage 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)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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Scribe line is found within the limits of a typical scribe line and more than 0.006 inch deep. (c) Do High Frequenc y 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 mainte nance records. Adjust the compliance time as given below. Operator is to use the lowest of the three be low adjustments to the thre shold in determining first scribe line opportunity.

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

2. If record of first decal installati on 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)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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(c) Refer to Accomplishment Instructions Paragra ph 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 - Limite d 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 - Fuse lage Skin Scribe Line Inspection

Condition Action Compliance Time (Whichever Occurs Later) Repeat Interval (Not to Exceed)Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 - Limite d 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
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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 - Limite d Return To Service Rep eat 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 - Limite d 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
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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 - Limit ed Return To Service Repea t 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
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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 Servic e 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 - Limite d Return To Service Rep eat 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 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 Repea t 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 Servic e 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 © U npublished 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 - 3,000Original 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 © U npublished 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 ar eas 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 © U npublished 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 - 3,500Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished 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 - Limite d 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 - Limite d 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 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 54 of 268 

### 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 - Limit ed Return To Service Repe at 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. 55 of 268 

### 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 - Limite d 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 © U npublished Work - See page 1 for details. 56 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 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 - Limit ed Return To Service Repe at 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. 57 of 268 

### 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
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 58 of 268 

### 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 - Limite d 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 - 3,000Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 - Limite d 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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S-37L STA 287 - 434 - 2,000 If any crack is found. Contact Bo eing for repair instructions and do the repair. Before further flight. -

All airplanes with scribe lines using a LRTS program inspection. Contact Boeing for re pair 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 - Limite d 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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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 Servic e 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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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 Bo eing 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
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Group 1-12: Table 15 - External Approved Repairs - Li mited 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
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Group 1-4: Table 16 - External Features - Limit ed Return To Service Repe at 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 Li ght - 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
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Group 5-10: Table 17 - External Features - Limite d 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
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Group 11: Table 18 - External Features - Limite d 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 Revision 1: April 09, 2009 767-53A0193
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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. -Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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Group 1-12: Table 20 - Decals - Limited Retu rn 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. -Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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F. Approval

This service bulletin was examined by the Fede ral Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Sa fety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/ JAA approved airplanes listed in the service bulletin e ffectivity. 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 responsi ble 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 in clude 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 Instru ctions Paragraph 3.B for identification of a typical scribe line. (b) No further inspections are required at this locati on, 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 - Outs ide of Zones 1,2, and 3 - LRTS 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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— 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 fo r additional inspections a nd 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 fo r additional inspections a nd repairs if scribe lines or other damage is found. More time may be required for inspections around large approved repairs.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 fo r 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 fo r 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 10.0Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 fo r additional inspections a nd 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 fo r additional inspections a nd 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 HoursOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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Additional time is required for paint and sealant removal. More time will be required fo r 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 fo r 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 fo r 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 HoursOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 fo r additional inspections a nd 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 fo r additional inspections a nd 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 10.0Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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H. Weight and Ba lance 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 (N DT) 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 fo r 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 HoursOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 Dam age 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 bu lletin does not affect interchangeability or intermixability of parts.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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BLANK PAGEOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 proced ure for decorative exterior paint system application. (g) The quantity giv en is an approximation. The actual quantity required will vary depending on the results of the scribe line inspections.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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E. Special Tooling - Pr ice and Availability

The operator can supply the tools shown in Paragr aph 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 nece ssary to accomplish this bulletin. Howe ver, 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 t ools 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.comOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELEC TRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WH EN 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 acrony ms. 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 di mensions 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 operat or has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedur e 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 fabr ication 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 defi nition of a typical scribe line in the Accomplishment Instructions of this service bulletin.

7. If an optical micrometer or laser meas urement system cannot be used because the upper skin of the lap joint covers a scribe lin e, 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 requir ements 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 proc edures must be recognized by the operator or repair station as qualified to perform ul trasonic 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, SN T-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 sa tisfactorily completed the training in theOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 (emplo yer) 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 reques ted 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 examinatio n 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 mirr ors, 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 struct ure 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 fa miliarize themselves with all Parts and Work Instructions in this service bulletin prior to starting their scribe line inspection pr ogram. 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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, dist inct line of damage (typically up to 0.006 inch deep), usually associated with the removal of a f illet or gap seal (lap jo ints and butt joints, respectively). Scribe lines can be both tactile a nd 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 decal s. Scribe lines that create a potential safety concern are generally long continuous scribe lines or several adjacent scrib e lines in a critical orientation at specific locations with relatively high stresses.

If an optical micrometer or laser measurement sys tem cannot be used beca use 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 consider ed 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 practi ces 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, portio ns 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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3. PART 1 - SURFACE PREPARATION - SCRIBE LINE INSPECTIONS

NOTE: Refer to Appendix A of this service bulle tin 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 t he 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 leas t 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 ar eas 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 ac cepted sealant removal procedure.

b. Do Part 7 - Surface Finish Restoration.

6. PART 4 - SCRIBE LINE FOUND

NOTE: DO NOT BLEND ANY SCRIBE LINE. BL ENDING 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 op tical 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, doc ument the minimum distance between the upper skin lower edge and the scribe line.

(1) At skin lap joint locations, if the minimu m 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 Rest oration 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 mini mum 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 in clude 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 ski n 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 join t 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 give n 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 in spection 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 in spection 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 app lication 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 thickne ss greater than that allowed in the UT phased array inspection techniques.

(2) If any crack is found, docum ent and propose a repa ir 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 repa ir 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 repa ir 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 Restor ation of this service bulletin.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 ul trasonic phased array inspection to detect cracks in any hidden scribe lines. If the scr ibe 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 ND T, 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 limit ations 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 in spection 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 app lication limitations based upon skin thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable Boeing drawings if the skin thicknes s 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 propos e 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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NOTE: A repair is not required until the repa ir 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 Restor ation 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 fe ature must include an ultrasonic inspection or an ultrasonic phased arra y 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 dete ct any crack at all affected external features as follows:

(a) Do a HFEC inspection as given in 767 ND T, 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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NOTE: The skin thickness must be known when conducting the UT inspection as the technique has application limit ations 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 in spection 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 app lication limitations based upon skin thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable Boeing drawings if the skin thicknes s 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 propos e 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 assi st Boeing in the anal ysis 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 Restor ation of this service bulletin.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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d. Scribe Line at Decals:

(1) Do the special detailed inspection of the fuse lage skin to detect any crack at all affected decals as follows:

(a) Do a HFEC inspection as given in 767 ND T, 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, docum ent and propose a repa ir 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 repa ir 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 repa ir 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 Restor ation 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 join t 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 magnifyi ng 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 give n 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 limit ations 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 in spection 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 app lication limitations based upon skin thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable Boeing drawings if the skin thicknes s 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 propos e a repair to Boeing. This will assist Boeing in the analysis of the crack and repair proposal.

(6) If no crack is found, do on e 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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(7) Do Part 7 - Surface Finish Restor ation 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 ultras onic 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 dete ct 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 in spection 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 in spection 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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NOTE: The skin thickness must be known when conducting the UT phased array inspection as the technique has app lication limitations based upon skin thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable Boeing drawings if the skin thicknes s 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 propos e a repair to Boeing. This will assist Boeing in the analysis of the crack and repair proposal.

(6) If no crack is found, do on e 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 Restor ation of this service bulletin.

c. External Features - Repeat Inspection:

(1) Determine which external fe atures 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 in spection 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 in spection 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 app lication 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 thickne ss greater than that allowed in the UT phased array inspection techniques.

(5) If any crack is found, docum ent and propose a repa ir 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 repa ir 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 Restor ation of this service bulletin.

d. Decals - Repeat Inspection:

(1) Determine which decal ar eas 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 ski n 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 dete ct any crack at all affected decal areas as follows:Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 propos e a repair to Boeing. This will assist Boeing in the analysis of the crack and repair proposal.

(6) If no crack is found, do on e 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 Restor ation of this service bulletin.

9. PART 7 - SURFACE FINISH RESTORATION

NOTE: To reduce the possibilit y 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 approve d repair doublers for repairs that will be inspected under the LRTS program.

3. Around external features as giv en in the applicable AMM section.

a. Refinish the external su rface 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 dec orative 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 appr oved 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 repair s around which no scribe lines we re found, apply a fillet seal around the periphery of the external approv ed repair. Refer to 767 AMM 51-31-01 as an accepted procedure.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 Rest oration 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 Lo cation - Special Detailed InspectionOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 fo rward of the damaged area to the butt joint aft of the damaged area. The butt joint to bu tt 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 r equired 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 - SCRI BE 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 give n 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 la p joint faying surface area.

NOTE: The skin thickness must be known when conducting the UT inspection as the technique has application limit ations 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 in spection 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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NOTE: The skin thickness must be known when conducting the UT phased array inspection as the technique has app lication 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 thickne ss 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 re moval procedure is implemented for all future work. Refer to Append ix 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 progra m 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 Boei ng. 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 Restor ation of this service bulletin.

(2) Scribe Line at External Approved Repair - Special Detailed Inspection:Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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NOTE: If a scribe line is detected and is wit hin 0.10 inch of an external approved repair, the entire periphery of the extern al approved repair must be inspected. The special detailed inspection for th e entire periphery of the external approved repair must include an ultras onic inspection or an ultrasonic phased array inspection to detect cracks in an y 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 ND T, 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 limit ations 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 in spection 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 app lication limitations based upon skin thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable Boeing drawings if the skin thicknes s 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, docu ment 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 procedureOriginal Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
(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 Boei ng. 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 Restor ation 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 feat ure must be inspected. The special detailed inspection for the entire peripher y of the external feature must include an ultrasonic inspection or an ultrason ic phased array inspection to detect cracks in any hidden scribe lines. If t he scribe line is located greater than 0.10 inch from the external feature, then the in spection is only required in the local area common to the scribe line.

Do the special detailed inspections of the fuselage skin to dete ct any crack at all affected external features as follows:

(a) Do a HFEC inspection as given in 767 ND T, 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.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

NOTE: The skin thickness must be known when conducting the UT inspection as the technique has application limit ations 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 in spection 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 app lication limitations based upon skin thickness as given in 767 NDT, Part 4, 53-00-02. Refer to applicable Boeing drawings if the skin thicknes s 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, docu ment 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 assi st Boeing in the analysis of the scribe line damage and repair proposal.Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

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 Restor ation of this service bulletin.

(4) Scribe Line at Decals - Special Detailed Inspection:

Do the special detailed inspections of the fuselage skin to dete ct any crack at all affected decals as follows:

(a) Do a HFEC inspection as given in 767 ND T, 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 re moval procedure is implemented for all future work. Refer to Append ix 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 Boei ng. 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 Restor ation of this service bulletin.FIGURE 1: FUSELAGE - SKIN LAP JOINT - ZONE 1 IN SPECTION (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

FIGURE 1: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 1)STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA212STA287STA676STA654STA456STA610STA698STA764EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA720STA188.9S-13RS-13LSTA1540STA1562TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 1:STA132.5STA632STA742STA588STA1351STA1480STA1329LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1508551

(SHEET 1 OF 2)FIGURE 1: FUSELAGE - SKIN LAP JOINT - ZONE 1 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 number s 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 fo r any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LIN ES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION TECHNIQUES NECESSARY TO DETERMIN E THE PRESENCE OR ABSENCE OF FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the la p joint in the lower skin along the edge of the upper skin. These scribe lines are ty pically within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scr ibe 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 IN SPECTION (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

FIGURE 2: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 2)STA246STA434STA610STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA632STA500STA698STA764STA1065STA1582STA1832STA1307S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA615STA478STA654STA676STA720STA1540STA1562TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 2:STA212STA287STA132.5STA1480STA1351STA1329STA742STA588LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1509796

(SHEET 1 OF 2)FIGURE 2: FUSELAGE - SKIN LAP JOINT - ZONE 1 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 number s 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 fo r any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LIN ES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION TECHNIQUES NECESSARY TO DETERMIN E THE PRESENCE OR ABSENCE OF FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the la p joint in the lower skin along the edge of the upper skin. These scribe lines are ty pically within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scr ibe 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 IN SPECTION (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

FIGURE 3: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 3)STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA676STA632STA456STA588STA698STA764STA1065STA1582STA1832STA1307STA1480S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9EXISTING BUTT JOINTINSPECTION AREASTA1540STA720STA1562TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 3:STA212STA287S-13RS-13LSTA132.5STA742STA654STA1351STA1329LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1520587

(SHEET 1 OF 2)FIGURE 3: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 3) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 112 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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 fo r any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LIN ES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION TECHNIQUES NECESSARY TO DETERMIN E THE PRESENCE OR ABSENCE OF FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the la p joint in the lower skin along the edge of the upper skin. These scribe lines are ty pically within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scr ibe 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 IN SPECTION (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

FIGURE 4: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 4)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA632STA500STA610STA676STA1065STA1582STA1832STA1307STA1351S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA654STA188.9EXISTING BUTT JOINTINSPECTION AREAS-13LSTA698STA764STA720STA478STA1540STA1562STA615TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 4:STA212STA287S-13RSTA132.5STA742STA588STA1480STA1329LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1521783

(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
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 114 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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 fo r any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LIN ES. BLENDING A SCRIBE LINE MAY HINDER INSPECTION TECHNIQUES NECESSARY TO DETERMIN E THE PRESENCE OR ABSENCE OF FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run parallel to the la p joint in the lower skin along the edge of the upper skin. These scribe lines are ty pically within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scr ibe 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 IN SPECTION (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 5: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 5)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA654+88STA1065STA1832STA1307STA1351S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1562STA1417STA618STA632STA654+44STA654+110STA654STA1197+22STA1197+132STA1582STA1346STA1270EXISTING BUTT JOINTINSPECTION AREASTA456STA1219STA1502STA1518STA1285STA610TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 5:STA188.9S-13LSTA212STA287S-13RSTA132.5STA698STA1373LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1521792

(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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 6: FUSELAGE - SKIN LAP JOINT - ZONE 1 IN SPECTION (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 6: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 6)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37LSTA654+88STA1065STA1832STA1285STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1540STA1439STA615STA610STA654+44STA654+110STA632STA654STA1197+22STA1197+132STA1562STA1582STA1417STA1346STA1270STA1197+110EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1219STA1502STA500STA478STA1307TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 6:STA188.9STA212STA287S-13RSTA132.5STA1351STA698LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1521802

(SHEET 1 OF 2)FIGURE 6: FUSELAGE - SKIN LAP JOINT - ZONE 1 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 7: FUSELAGE - SKIN LAP JOINT - ZONE 1 IN SPECTION (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 7: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 7)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA212STA287STA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1439STA188.9STA618STA610STA654+44STA632STA654STA1582STA1417STA1346STA1270STA1197+132EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA456STA1219STA1153STA654+88STA654+110STA1518STA1480STA1502STA1285STA1175TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 7:STA1197+44STA698STA1351LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1521987

(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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 8: FUSELAGE - SKIN LAP JOINT - ZONE 1 IN SPECTION (GROUP 8) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 8: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 8)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1439STA615STA610STA654+44STA632STA654STA1197+132STA1582STA1417STA1346STA1270STA1197+110STA1502STA1518STA1219EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1153STA654+88STA654+88STA1480STA1285STA1175STA500STA478TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINESTA1461

This Figure applies to Group 8:STA132.5STA212STA287STA188.9STA698STA1197.44STA1351LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1521992

(SHEET 1 OF 2)FIGURE 8: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 8) 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 9: FUSELAGE - SKIN LAP JOINT - ZONE 1 IN SPECTION (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

FIGURE 9: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 9)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA618STA610STA654+44STA676STA632STA654STA1197+132STA1582STA1461STA1417STA1346STA1270STA1502STA1518STA1219EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1197+44STA456STA654+22STA1480STA1285STA654+88TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 9:STA132.5STA212STA287STA188.9STA1351LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1522001

(SHEET 1 OF 2)FIGURE 9: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 10: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPEC TION (GROUP 10) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 10: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 10)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA615STA610STA654+44STA676STA632STA654STA1197+132STA1582STA1461STA1417STA1346STA1270STA1502STA1518STA1175EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1197+44STA1480STA1219STA654+22STA654+88STA500STA478STA1285TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 10:STA132.5STA212STA287STA188.9STA1351LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1522005

(SHEET 1 OF 2)FIGURE 10: FUSELAGE - SKIN LAP JOINT - ZONE 1 INSPECTION (GROUP 10) 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 11: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPEC TION (GROUP 11) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 11: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 11)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA1065STA1832STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1439STA456STA654STA1582STA1417STA1219STA654+22STA1175STA1197+132STA1197+88STA1654EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1461STA1540STA1307TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 11:STA132.5STA212STA287STA188.9STA654+110STA742STA698STA1285STA1351STA1502STA1263LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1522008

(SHEET 1 OF 2)FIGURE 11: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 11) 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 12: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPEC TION (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

FIGURE 12: FUSELAGE - SKIN LAP JO INT - ZONE 1 INSPECTION (GROUP 12)STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA1065STA1832STA1241S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1307STA1395STA566STA654STA1373STA1197+154STA1197+231STA654A+110STA1197+88STA1197+22STA1197+110STA1197+132STA1582STA654+22STA1197+66STA1417STA1461STA610STA654AEXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1285STA1351STA654A+22STA478TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 12:STA132.5STA212STA287STA188.9STA654+110STA676STA1518LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1522010

(SHEET 1 OF 2)FIGURE 12: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 13: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 1)STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA676STA654STA632STA610STA720STA764EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA1109STA1153STA1329STA1263STA1518STA1540STA1175STA1219STA1351STA500STA456TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 1:STA132.5STA196.5STA188.9STA1087STA742STA588LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1522011

(SHEET 1 OF 2)FIGURE 13: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 14: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 2)STA132.5STA246STA434STA610STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA287STA632STA500STA539STA720STA764EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1461STA188.9STA478STA654STA676STA1417STA1263STA1175STA1219STA1351STA522TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure app lies to Group 2:STA1329STA1087STA1109STA1153STA588STA742LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1522017

(SHEET 1 OF 2)FIGURE 14: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 15: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 3)STA132.5STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA287STA676STA654STA610STA720STA764EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9STA1329STA1263STA1153STA1109STA1219STA1351STA632STA456STA500STA1175TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 3:STA1087STA742STA588LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1531120

(SHEET 1 OF 2)FIGURE 15: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 16: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 4)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA287STA610STA500STA632STA720STA764STA1065STA1582STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9EXISTING BUTT JOINTINSPECTION AREASTA1518STA1087STA1263STA676STA522STA478STA1175STA1153STA654STA1351STA1219STA539STA1109TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 4:STA1329STA742STA588LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1531195

(SHEET 1 OF 2)FIGURE 16: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 17: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 5)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA287STA654+88STA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1461STA188.5STA618STA654+44STA742STA654STA1197+22STA1241STA1562STA1582STA1417STA1346STA1270STA1197+110EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1219STA1540STA1197+66STA764STA1263STA1197+132STA1518STA1480STA1502STA1285STA676STA654+121STA698STA1439STA610TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 5:STA654+22LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538570

(SHEET 1 OF 2)FIGURE 17: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 18: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 6)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA287STA654+88STA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1540STA1439STA188.5STA615STA654+44STA764STA654STA1197+22STA1197+132STA1562STA1582STA1461STA1417STA1346STA1270STA1197+110EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1219STA1197+66STA1263STA632STA500STA742STA1241STA1285STA676STA698STA478STA1480STA1518STA1502STA610TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 6:STA654+22STA522LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538690

(SHEET 1 OF 2)FIGURE 18: FUSELAGE - SKIN LAP JOINT - 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
The step numbers shown below agree with the number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 19: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 7)STA132.5BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1540STA188.5STA1562STA1582STA1461STA1417STA1346STA1270STA1197+110STA1197+66EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1219STA1109STA1518STA1263STA1285STA246STA434STA786.1STA287STA654+88STA618STA654+22STA764STA654STA742STA654+44STA676STA698STA610STA1241STA654+121TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 7:STA1087STA1197+22STA1197+44LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538693

(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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 20: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 8)STA132.5STA246BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1518STA188.5STA1197+44STA1562STA1582STA1461STA1417STA1346STA1270STA1197+110STA1263EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1219STA1285STA1241STA786.1STA654+88STA764STA742STA654+44STA676STA698STA434STA615STA654+22STA654STA610STA500STA522STA1109STA1153STA1540TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 8:STA1087STA1197+22STA1197+66LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538695

(SHEET 1 OF 2)FIGURE 20: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 8) 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 21: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 9)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA287STA1832S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA188.9STA618STA654+66STA720STA654EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA654+44STA654+88STA654+121STA764STA1307STA1373STA1395STA1540STA1562STA1582STA1461STA1417STA1346STA1219STA1518STA1285STA1197+110STA1065STA1087STA1241STA1270STA1109STA698STA676STA654+22STA610STA632TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 9:STA1197+22STA1197+44STA1197+66LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538696

(SHEET 1 OF 2)FIGURE 21: FUSELAGE - SKIN LAP JOINT - ZONE 2 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 22: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPEC TION (GROUP 10) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 22: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 10)STA132.5BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1065STA1832S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA188.9STA1109EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1087STA1307STA1373STA1395STA1540STA1562STA1582STA1461STA1417STA1346STA1270STA1197+22STA1197+66STA1219STA1518STA1285STA1241STA246STA434STA786.1STA287STA615STA654+66STA720STA654STA654+44STA654+88STA654+121STA764STA698STA676STA632STA500STA478STA654+22STA610TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 10:STA522STA1197+44STA1197+110LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538698

(SHEET 1 OF 2)FIGURE 22: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 10) 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 23: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 11) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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FIGURE 23: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 11)STA126.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1065STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA188.9STA456STA654+110STA742STA654STA1197+132STA1582STA1417STA1219STA654+22STA1175STA1153STA1197+66STA1654EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1263STA1502STA1562STA676STA654+66STA1540STA1351STA1241STA1197+88STA1197+22STA698STA478STA632STA1109TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 11:STA1461STA1197+44LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538699

(SHEET 1 OF 2)FIGURE 23: FUSELAGE - SKIN LAP JOINT - ZONE 2 INSPECTION (GROUP 11) 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 24: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPEC TION (GROUP 12) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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FIGURE 24: FUSELAGE - SKIN LAP JO INT - ZONE 2 INSPECTION (GROUP 12)STA126.5STA246STA434STA786BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1065STA1832S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA188.9STA456STA654STA654ASTA1373STA1197+154STA1197+253STA654A+110STA1197+132STA1582STA654+44STA654+22STA1197+110STA1417STA1461STA610EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA654A+22STA654A+88STA1197+88STA1562STA1351STA1285STA1241STA1197+187STA1197+209STA654A+44STA1307STA1219TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 12:STA1439STA1518STA1263STA1197+66STA654+110STA676STA566LAP JOINT12FRAMEUPPER SKINSTRINGERLOWER SKIN1538746

(SHEET 1 OF 2)FIGURE 24: FUSELAGE - SKIN LAP JOINT - ZONE 2 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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FIGURE 25: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 1)STA132.5STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA676STA654STA456STA698STA764EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9S-13RS-13LSTA1540STA1562STA1518STA1502STA1263STA1175STA1109STA1131STA1219STA1241STA478STA808STA852STA1351STA1285STA1087TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 1:LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1538871

(SHEET 1 OF 2)FIGURE 25: FUSELAGE - SKIN LAP JOINT - ZONE 3 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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FIGURE 26: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 2)STA132.5STA246STA434BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA544STA500STA539STA698STA1065STA1582STA1832STA1307STA1263S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1562STA1540STA1502STA1480STA1373STA1241STA1219STA1153STA1109STA1131STA1087STA1351STA1285STA1175STA786.1STA676STA764TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 2:LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1538875

(SHEET 1 OF 2)FIGURE 26: FUSELAGE - SKIN LAP JOINT - ZONE 3 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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FIGURE 27: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 3)STA132.5STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA676STA478STA654STA1582STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1562STA1540STA1502STA1263STA1241STA1219STA1109STA1131STA456STA1065STA1087STA1351STA1175STA1285STA698STA764TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 3:LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1538877

(SHEET 1 OF 2)FIGURE 27: FUSELAGE - SKIN LAP JOINT - 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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 Revision 1: April 09, 2009 767-53A0193
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FIGURE 28: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 4)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA500STA610STA654STA764STA1065STA1582STA1832STA1307STA1263S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA1461STA188.9EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1562STA1540STA1502STA1373STA1241STA1219STA1109STA1131STA676STA1087STA698STA1175STA1285STA1351TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 4:STA544LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1538880

(SHEET 1 OF 2)FIGURE 28: FUSELAGE - SKIN LAP JOINT - ZONE 3 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 29: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 5)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA654+88STA1065STA1832STA1285S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1373STA188.9STA618STA610STA654+110STA632STA654STA1197+132STA1562STA1582STA1461STA1417STA1346STA1270STA1197+88EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA456STA1219STA1263STA1241STA1153STA1109STA1087STA720STA654+121STA654+22STA676STA1241STA1395STA1307STA698STA764STA742STA1502TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 5:STA478STA1351LAP JOINT132FRAMEUPPER SKINSTRINGERLOWER SKIN1538883

(SHEET 1 OF 3)FIGURE 29: FUSELAGE - SKIN LAP JOINT - ZONE 3 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 number s 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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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 DETERM INE THE PRESENCE OR ABSENCE OF FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 30: FUSEL AGE - SKIN LAP JOINT - ZO NE 3 INSPECTION (GROUP 6)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA654+88STA1065STA1832STA1307S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA188.9STA615STA654+44STA654+110STA654STA1197+132STA1562STA1582STA1461STA1417STA1346STA1270STA1197+88EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1219STA1480STA1241STA1263STA1153STA1087STA1109STA522STA500STA456STA654+121STA698STA720STA676STA654+22STA1502STA764STA742STA1285TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 6:STA1351STA1373STA566LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1539317

(SHEET 1 OF 3)FIGURE 30: FUSELAGE - SKIN LAP JOINT - 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 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 31: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 7)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA654+88STA1065STA1263S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1373STA1502STA188.9S5A618STA610STA654+110STA654STA1461STA1351STA1346STA1270STA1197+132EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA456STA1219STA1480STA1241STA1197+88STA1131STA698STA654+121STA676STA720STA654+22STA1109STA1087STA1832STA1540STA1582STA764STA742STA1518STA1562STA1307STA1285TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 7:STA478STA1395STA1417STA1175STA1153LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1539318

(SHEET 1 OF 3)FIGURE 31: FUSELAGE - SKIN LAP JOINT - 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 number s 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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 DETERM INE THE PRESENCE OR ABSENCE OF FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 32: FUSEL AGE - SKIN LAP JOINT - ZO NE 3 INSPECTION (GROUP 8)STA132.5STA246BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA188.9EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1832STA1373STA1502STA1461STA1417STA1346STA1582STA1562STA1307STA1065STA1263STA1270STA1197+132STA1219STA1241STA1153STA1109STA1087STA1285STA434STA786.1STA654+88STA615STA566STA654+110STA654STA456STA698STA654+121STA676STA720STA654+22STA764STA742STA522TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 8:STA1175STA1395STA1351LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1539321

(SHEET 1 OF 3)FIGURE 32: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 8) 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-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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 33: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 9)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1832S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA188.9STA618STA654+110STA654EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA698STA720STA654+121STA654+88STA654+22STA456STA1395STA1502STA1461STA1417STA1346STA1480STA1582STA1518STA1562STA1307STA1065STA1270STA1197+132STA1219STA1241STA1175STA1153STA1109STA1285STA764STA676STA1263TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 9:STA1351STA1373STA632STA654+66STA742STA478LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1539322

(SHEET 1 OF 3)FIGURE 33: FUSELAGE - SKIN LAP JOINT - ZONE 3 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 number s 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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 DETERM INE THE PRESENCE OR ABSENCE OF FATIGUE CRACKS.

NOTE: In areas near lap joints, scribe lines normally run pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 34: FUSEL AGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 10)STA132.5STA246STA434BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1832S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA188.9EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA654+66STA698STA654+121STA786.1STA615STA676STA654STA720STA654+88STA654+22STA500STA1395STA1502STA1461STA1417STA1346STA1480STA1582STA1518STA1562STA1307STA1065STA1351STA1270STA1197+132STA1219STA1241STA1197+88STA1153STA1109STA1087STA1373STA544STA742TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 10:STA522STA566STA632STA764STA1175STA1285STA1263LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1539323

(SHEET 1 OF 3)FIGURE 34: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPEC TION (GROUP 10) 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-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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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 JO INT - ZONE 3 INSPECTION (GROUP 11) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 35: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 11)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1065STA1832STA1307STA1351S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1439STA188.9STA456STA654+66STA676STA654STA1197+132STA1582STA1417STA1197+110STA1219STA654+22STA1175STA1197STA1197+66STA1197+88EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1502STA1461STA1263STA1131STA1087STA1197+22STA1197+44STA720STA742STA698STA654+121STA654+110STA654+88STA654+44STA1109STA1153STA1241STA1373STA1480STA1540STA632TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINESTA1562

This Figure applies to Group 11:STA1285STA500LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1552233

(SHEET 1 OF 2)FIGURE 35: FUSELAGE - SKIN LAP JOINT - ZONE 3 INSPECTION (GROUP 11) 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese scribe lines sometimes may also turn slightly away from the lap joint.

(SHEET 2 OF 2)FIGURE 36: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPEC TION (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

FIGURE 36: FUSELAGE - SKIN LAP JO INT - ZONE 3 INSPECTION (GROUP 12)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA1197STA1832S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1307STA1395STA188.9STA456STA654STA654+110STA1373STA1197+187STA1197+209STA654A+88STA1197+154STA1197+187STA1582STA654+44STA676STA1197+66STA1417STA1461STA1480EXISTING BUTT JOINTINSPECTION AREAS-13RS-13LSTA1562STA1540STA1518STA1351STA1285STA1219STA1197+22STA1197+88STA1065STA698STA720STA1197+253STA1197+132STA1197+165STA654+121TYPICAL SKIN LAP JOINTTYPICAL SKINSCRIBE LINE

This Figure applies to Group 12:LAP JOINT123FRAMEUPPER SKINSTRINGERLOWER SKIN1539594

(SHEET 1 OF 2)FIGURE 36: FUSELAGE - SKIN LAP JOINT - ZONE 3 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 number s 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 pa rallel to the lap joint in the lower skin along the edge of the upper skin. These scribe lines are typi cally within 0.25 inch of the lower edge of the upper skin. In some cases, portions of the scribe lin es may be directly adjacent to or slightly under the lower edge of the upper skin. The ends of t hese 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 Revision 1: April 09, 2009 767-53A0193
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FIGURE 37: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 1)STA132.5STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA188.9S-13RS-13LSTA149

This Figure applie s to Group 1:111TYPICAL EXTERNAL APPROVED REPAIRTYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-A1540456

(SHEET 1 OF 2)FIGURE 37: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 1 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 number s 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 aroun d 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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FIGURE 38: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 2)S-26LS-36LS-36RS-26R

This Figure applies to Group 2:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELSTA132.5BL 0S-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA246STA434STA615STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA188.9EXISTING BUTT JOINTINSPECTION AREASTA149STA539AAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1540458

(SHEET 1 OF 2)FIGURE 38: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 1 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 number s 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 aroun d 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 39: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 3)STA132.5BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA188.9S-13RS-13LSTA246STA434STA618STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395EXISTING BUTT JOINTINSPECTION AREASTA149

This Figure applies to Group 3:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1540459

(SHEET 1 OF 2)FIGURE 39: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 1 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 number s 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 aroun d 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 40: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 4)STA132.5BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA246STA434STA615STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA188.5EXISTING BUTT JOINTINSPECTION AREASTA149STA539

This Figure applies to Group 4:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1540461

(SHEET 1 OF 2)FIGURE 40: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 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 number s 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 aroun d 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 41: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 5)STA132.5BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA188.9S-13RS-13LSTA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA1219EXISTING BUTT JOINTINSPECTION AREASTA149

This Figure applies to Group 5:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1540462

(SHEET 1 OF 2)FIGURE 41: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 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 number s 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 aroun d 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 42: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 6)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA188.5STA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA1219EXISTING BUTT JOINTINSPECTION AREASTA149

This Figure appl ies to Group 6:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1543330

(SHEET 1 OF 2)FIGURE 42: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 1 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 number s 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 aroun d 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 43: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 7)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA188.9STA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA1219EXISTING BUTT JOINTINSPECTION AREASTA149

This Figure app lies to Group 7:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1543331

(SHEET 1 OF 2)FIGURE 43: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 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 number s 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 aroun d 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 44: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 8)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA188.9STA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA1219EXISTING BUTT JOINTINSPECTION AREASTA149

This Figure appl ies to Group 8:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1543333

(SHEET 1 OF 2)FIGURE 44: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 1 INSPECTION (GROUP 8) 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 number s 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 aroun d 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 45: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 9)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA188.9STA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA1219EXISTING BUTT JOINTINSPECTION AREASTA149

This Figure applies to Group 9:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1543335

(SHEET 1 OF 2)FIGURE 45: FUSELAGE - EXT ERNAL APPROVED REPAIRS - ZO NE 1 INSPECTION (GROUP 9) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 202 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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 aroun d 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 - EXT ERNAL APPROVED REPAIRS - ZO NE 1 INSPECTION (GROUP 10) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 46: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 10)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA188.9STA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA1219EXISTING BUTT JOINTINSPECTION AREASTA149

This Figure applies to Group 10:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1543336

(SHEET 1 OF 2)FIGURE 46: FUSELAGE - EX TERNAL APPROVED REPAIRS - ZO NE 1 INSPECTION (GROUP 10) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 204 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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 aroun d 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 IN SPECTION (GROUP 11) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 47: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 11)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA188.9STA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA1219STA1197+88EXISTING BUTT JOINTINSPECTION AREASTA149STA654+22

This Figure applies to Group 11:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1543340

(SHEET 1 OF 2)FIGURE 47: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 IN SPECTION (GROUP 11) 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 number s 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 aroun d 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 - EXT ERNAL APPROVED REPAIRS - ZO NE 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

FIGURE 48: FUSELAGE - EXTERNAL APPROVED REPAIRS - ZONE 1 INSPECTION (GROUP 12)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA188.9STA246STA434STA654STA786.1STA196.5STA1065STA1582STA1832STA1307STA1197+154EXISTING BUTT JOINTINSPECTION AREASTA149STA1395

This Figure applies to Group 12:111TYPICALSCRIBELINESREPAIRDOUBLERSKIN PANELAAREPAIR DOUBLERSKINA-ATYPICAL EXTERNAL APPROVED REPAIR1543342

(SHEET 1 OF 2)FIGURE 48: FUSELAGE - EX TERNAL APPROVED REPAIRS - ZO NE 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 number s 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 aroun d 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 FE ATURES - 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

FIGURE 49: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 1)STA132.5STA246STA434STA786.1BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA588STA676EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA188.9S-13RS-13LSTA1131STA1109STA1153STA1175STA544STA566STA456STA610STA654STA632STA698

This Figure applies to Group 1:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543344

(SHEET 1 OF 2)FIGURE 49: FUSELAGE - EXTERNAL FE ATURES - 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 number s 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 Fu selage C/L, STA 680 1 (a) (i) (a) Do a detailed inspection of the fuselage skin ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - 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

FIGURE 50: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 2)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LEXISTING BUTT JOINTINSPECTION AREASTA132.5STA246STA434STA786.1STA196.5STA588STA676STA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA544STA566STA456STA610STA654STA632STA698

This Figure appl ies to Group 2:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543347

(SHEET 1 OF 2)FIGURE 50: FUSELAGE - EXTERNAL FE ATURES - 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 number s 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 Fu selage C/L, STA 680 1 (a) (i) (a) Do a detailed inspection of the fuselage skin ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - 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

FIGURE 51: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 3)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LEXISTING BUTT JOINTINSPECTION AREASTA132.5STA246STA434STA786.1STA196.5STA588STA676STA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA544STA566STA456STA610STA654STA632STA698

This Figure applies to Group 3:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543348

(SHEET 1 OF 2)FIGURE 51: FUSELAGE - EXTERNAL FE ATURES - 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 number s 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 Fu selage C/L, STA 680 1 (a) (i) (a) Do a detailed inspection of the fuselage skin ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - 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

FIGURE 52: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 4)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LEXISTING BUTT JOINTINSPECTION AREASTA132.5STA246STA434STA786.1STA196.5STA588STA676STA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA544STA566STA456STA610STA654STA632STA698

This Figure applies to Group 4:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543350

(SHEET 1 OF 2)FIGURE 52: FUSELAGE - EXTERNAL FE ATURES - ZONE 2 INSPECTION (GROUP 4) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 216 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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 Fu selage C/L, STA 680 1 (a) (i) (a) Do a detailed inspection of the fuselage skin ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - 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 FEAT URES - ZONE 2 INSPECTION (GROUP 5)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA632EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA588STA522STA500STA610STA654STA654+22STA654+44STA456STA544STA1241STA1219

This Figure applies to Group 5:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543351

(SHEET 1 OF 2)FIGURE 53: FUSELAGE - EXTERNAL FE ATURES - 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 number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - 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 FEAT URES - ZONE 2 INSPECTION (GROUP 6)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA632EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA588STA522STA500STA610STA654STA654+22STA654+44STA456STA544STA1241STA1219

This Figure applies to Group 6:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543353

(SHEET 1 OF 2)FIGURE 54: FUSELAGE - EXTERNAL FE ATURES - 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
The step numbers shown below agree with the number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - 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
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FIGURE 55: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 7)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA632EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA588STA522STA500STA610STA654STA654+22STA654+44STA456STA544STA1241STA1219

This Figure applies to Group 7:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543355

(SHEET 1 OF 2)FIGURE 55: FUSELAGE - EXTERNAL FE ATURES - ZONE 2 INSPECTION (GROUP 7) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 222 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - ZONE 2 INSPECTION (GROUP 8) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 56: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 8)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA632EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA588STA522STA500STA610STA654STA654+22STA654+44STA456STA544STA1241STA1219

This Figure applies to Group 8:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543362

(SHEET 1 OF 2)FIGURE 56: FUSELAGE - EXTERNAL FE ATURES - ZONE 2 INSPECTION (GROUP 8) 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 number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FE ATURES - ZONE 2 INSPECTION (GROUP 9) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 57: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 9)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA632EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA588STA522STA500STA610STA654STA654+22STA654+44STA456STA544STA1241STA1219

This Figure applies to Group 9:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543364

(SHEET 1 OF 2)FIGURE 57: FUSELAGE - EXTERNAL FE ATURES - ZONE 2 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 number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 58: FUSELAGE - EXTERNAL FEATURE S - ZONE 2 INSPECTION (GROUP 10)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA632EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA588STA522STA500STA610STA654STA654+22STA654+44STA456STA544STA1241STA1219

This Figure applies to Group 10:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543365

(SHEET 1 OF 2)FIGURE 58: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPECTION (GROUP 10) 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 number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 FEAT URES - ZONE 2 INSPECTION (GROUP 11) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 59: FUSELAGE - EXTERNAL FEATURE S - ZONE 2 INSPECTION (GROUP 11)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA632EXISTING BUTT JOINTINSPECTION AREASTA1065STA1582STA1832STA1307STA1395STA188.9STA1131STA1109STA1153STA1175STA588STA522STA500STA610STA654+22STA654+44STA456STA544STA654+66STA654

This Figure applies to Group 11:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543366

(SHEET 1 OF 2)FIGURE 59: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 INSPEC TION (GROUP 11) 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 number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT

FIGURE 60: FUSELAGE - EXTERNAL FEATURE S - ZONE 2 INSPECTION (GROUP 12)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA1065STA1582STA1832STA1307STA1395STA610STA654STA188.9STA632STA544STA654+22STA654+44STA456STA588

This Figure applies to Group 12:TYPICAL SCRIBE LINESTYPICAL EXTERNAL FEATURE11543368

(SHEET 1 OF 2)FIGURE 60: FUSELAGE - EXTERNAL FEAT URES - ZONE 2 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 number s 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 ar ound the external feature for any scribe line. Use a minimum 10X magnifying lens to aid the inspection.

CAUTION: DO NOT BLEND SCRIBE LINES. BLE NDING 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 61: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 1)S-21R This Figure applies to Group 1:1STA132.5STA246STA434STA618STA786.1BL 0S-26LS-36LS-36RS-26RS-30RS-36RS-21LS-30LS-36LS-37RS-37LSTA196.5STA676STA654STA1065STA1582STA1832STA1307STA1373S-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LSTA1395STA1417STA188.9S-13RS-13LSTA1087STA808STA1043STA566EXISTING BUTT JOINTINSPECTION AREA1543373

(SHEET 1 OF 2)FIGURE 61: FUSELAGE - DECALS - ZONE 3 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 number s 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. BLE NDING 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 62: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 2)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA615STA786.1STA196.5STA676STA654STA1065STA1582STA1832STA1307STA1373STA1395STA1417STA188.9STA1087STA808STA1043STA566

This Figure applies to Group 2:1EXISTING BUTT JOINTINSPECTION AREA1543374

(SHEET 1 OF 2)FIGURE 62: FUSELAGE - DECALS - ZONE 3 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 number s 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. BLE NDING 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 63: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 3)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA618STA786.1STA196.5STA676STA654STA1065STA1582STA1832STA1307STA1373STA1395STA1417STA188.9STA1087STA808STA1043STA566

This Figure appl ies to Group 3:1EXISTING BUTT JOINTINSPECTION AREA1543375

(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 number s 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. BLE NDING 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 64: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 4)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA615STA786.1STA196.5STA676STA654STA698STA1065STA1582STA1832STA1307STA1373STA1395STA1417STA742STA188.9STA1087STA808STA1043STA588STA566

This Figure applies to Group 4:1EXISTING BUTT JOINTINSPECTION AREA1543376

(SHEET 1 OF 2)FIGURE 64: FUSELAGE - DECALS - ZONE 3 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 number s 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. BLE NDING 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 65: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 5)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA618STA786.1STA196.5STA654STA654+22STA654+88STA1065STA1582STA1832STA1307STA1373STA1395STA1285STA742STA188.9STA808STA1043STA566STA1197+132STA764STA698STA676STA654+44STA588STA1241

This Figure applies to Group 5:1EXISTING BUTT JOINTINSPECTION AREA1543378

(SHEET 1 OF 2)FIGURE 65: FUSELAGE - DECALS - ZONE 3 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 number s 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. BLE NDING 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 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 66: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 6)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA615STA786.1STA196.5STA654STA654+22STA654+88STA1065STA1582STA1832STA1307STA1373STA1395STA1285STA742STA188.9STA808STA1043STA566STA1197+132STA764STA698STA676STA654+44STA588STA1241

This Figure appl ies to Group 6:1EXISTING BUTT JOINTINSPECTION AREA1543380

(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 number s 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. BLE NDING 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 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA618STA786.1STA196.5STA654STA654+22STA654+88STA1065STA1582STA1832STA1307STA1373STA1395STA1285STA742STA188.9STA808STA1043STA566STA1197+132STA764STA698STA676STA654+44STA588STA1241

This Figure applies to Group 7:1EXISTING BUTT JOINTINSPECTION AREA1543383

(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 number s 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. BLE NDING 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 68: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 8)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA615STA786.1STA196.5STA654STA654+22STA654+88STA1065STA1582STA1832STA1307STA1373STA1395STA1285STA742STA188.9STA808STA1043STA566STA1197+132STA764STA698STA676STA654+44STA588STA1241

This Figure applies to Group 8:1EXISTING BUTT JOINTINSPECTION AREA1543384

(SHEET 1 OF 2)FIGURE 68: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 8) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 248 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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. BLE NDING 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 69: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 9)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA618STA786.1STA196.5STA654STA654+22STA654+88STA1065STA1582STA1832STA1307STA1373STA1395STA1285STA742STA188.9STA808STA1043STA566STA1197+132STA764STA698STA676STA654+44STA588STA1241

This Figure applies to Group 9:1EXISTING BUTT JOINTINSPECTION AREA1543385

(SHEET 1 OF 2)FIGURE 69: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 9) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 250 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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. BLE NDING 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 70: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 10)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA615STA786.1STA196.5STA654STA654+22STA654+88STA1065STA1582STA1832STA1307STA1373STA1395STA1285STA742STA188.9STA808STA1043STA566STA1197+132STA764STA698STA676STA654+44STA588STA1241

This Figure applies to Group 10:1EXISTING BUTT JOINTINSPECTION AREA1543387

(SHEET 1 OF 2)FIGURE 70: FUSELAGE - DECALS - ZONE 3 INSPECT ION (GROUP 10) 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 number s 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. BLE NDING 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
FIGURE 71: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 11)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA618STA786.1STA196.5STA654STA654+22STA654+88STA1065STA1582STA1832STA1307STA1480STA1395STA188.9STA808STA566STA676STA654+44STA588STA1241STA889STA1153

This Figure applies to Group 11:1EXISTING BUTT JOINTINSPECTION AREA1543388

(SHEET 1 OF 2)FIGURE 71: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 11) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 254 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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. BLE NDING 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) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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FIGURE 72: FUSELAGE - DECALS - ZONE 3 INSPECTION (GROUP 12)BL 0S-26LS-36LS-36RS-26RS-21RS-30RS-36RS-21LS-30LS-36LS-37RS-37LS-36RS-26RS-17RS-8RS-2RS-8LS-26LS-36LS-17LS-13RS-13LSTA132.5STA246STA434STA786.1STA196.5STA654A+22STA654STA1065STA1582STA1832STA1307STA1395STA676STA188.9STA654+88STA1197+154STA566

This Figure applies to Group 12:1EXISTING BUTT JOINTINSPECTION AREA1543391

(SHEET 1 OF 2)FIGURE 72: FUSELAGE - DECALS - ZONE 3 INSPECT ION (GROUP 12) Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 256 of 268 

### BOEING SERVICE BULLETIN 767-53A0193
ALERT ALERT
The step numbers shown below agree with the number s 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. BLE NDING 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 PROCEDUR E FOR EXTERIOR PRESSURIZED FUSELAGE SKIN Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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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 Chemistr y & 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 2 34350 (6 inch length)

Supplier: PPG Aerosp ace: SEMCO Division Address: PPG-Aerospace (ASC-S eattle), 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/pr c-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 re moving 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, SHR0272APPENDIX A: SEALANT REMOVAL PROCEDUR E FOR EXTERIOR PRESSURIZED FUSELAGE SKIN Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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.pn jmachining.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 311/03/0 4, 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 In ternational Limited Address: Roman Hill Business Park, Broa dmayne, 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 remo ving 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 removi ng 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 PROCEDUR E FOR EXTERIOR PRESSURIZED FUSELAGE SKIN Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 maxi mum speed of 850 RPM (at the cutter) can be used.

C. Solvents

1. Methyl Ethyl Ket one (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 seal ant from the exterior pressurized fuselage. Using these procedures will minimize the risk of damaging cl ad aluminum surfaces duri ng 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. Alternat ely, it is acceptable to use other scrapers provided they meet the requirement s of BSS7384 (Method for Ev aluating Tool Materials for use on Unpainted Clad Aluminum). Commonly used scraper materials such as Lexan polycarbonate, acry lic (Plexiglas), Micarta fiber reinforced phenolic resins, metal, wood, and othe r hard plastics have been tested and found to scratch clad aluminum.APPENDIX A: SEALANT REMOVAL PROCEDUR E FOR EXTERIOR PRESSURIZED FUSELAGE SKIN Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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### BOEING SERVICE BULLETIN 767-53A0193
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3. SEALANT REMOVAL PROCESS: LAP JOINT FILLET

A. To remove the lap joint f illet, follow this procedure:

CAUTION: PLEASE NOTE THAT THERE IS A POTE NTIAL FOR THE SR CUTTER TO "RUN AWAY" AND CAUSE DAMAGE AT THE LAP JOINT AND SURROUNDING AREA. ALSO, IF THE CUTTER CONTACTS BAR E METAL BENEATH THE SEALANT, THE CLAD ALUMINUM SKIN COULD BE DAMA GED. BEFORE USING THE 3M SR CUTTER, OPERATORS SHOULD BE TRAINE D ON PROPER USAGE OF THIS TOOL AND SHOULD PRACTICE ON TEST PAN ELS OR PIECES TO PERFECT THEIR SKILLS IN WORKING WITH THE TOOL.

1. Remove the majority of the fillet seal at th e 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 Cu tter listed in Paragraph 1.B. of this appendix can be used. To prevent the cutter from damagi ng 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 se alant 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 lis ted 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 OTHE R 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 BU TT JOINTS OR OTHER AREAS.

1. Remove the bulk of the sealant using any of th e approved scrapers in Paragraph 1.A. of this appendix. Scrapers designed specifically for remo ving 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 PROCEDUR E FOR EXTERIOR PRESSURIZED FUSELAGE SKIN Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 liste d 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-R ohco, Inc. Atlanta GA.

2. Eldorado PR-5044, Eldorado Chemical Company, Inc. San Antonio TX.

3. Elixair - Skyrestore (Thick), Elixair In ternational Limited, Dorchester, England.

4. Naftosolv FN, Chemetall GMBH, Frankfurt, Germany.

5. Skycleen 2000 Aviation Cleaner, Solutia Inc. St. Louis, MO.

6. Turco 5351, Henkel Corporat ion, 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 WIDTH1554791APPENDIX A: SEALANT REMOVAL PROCEDUR E FOR EXTERIOR PRESSURIZED FUSELAGE SKIN Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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Remove sealant fillet with an approved scraper in accordance with Para graph 1.A., above. Chemically strip any sealant rema ining on the surface as follows:

a. Mask surrounding areas as necessary to prev ent 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 so ften 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 76 7 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 prev ent contact with chemical strippers. Do not allow chemical strippers to contac t substrates other than aluminum.

b. Using a natural bristle brush, apply a thin coat ing of chemical stripper on the sealant fillet.

c. Let the chemical stripper dwell for a maximum of 4 hours, except us e 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 re moving the sealant fille t, 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 Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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APPENDIX B: REPORTING SYSTEM - LIMITED RE TURN TO SERVICE PROCEDURE FOR AIRPLANES WITH SCRIBE LINES

Boeing recommends that operators use the format that follo ws to report the results of the inspections in this service bulletin to Boeing. Use of this standard format will re sult in a more rapid review and approval of the data. A Return to Service Proposal will be provided by Boei ng 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 Sinc e 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 Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 an y damage found, including locations, message numbers, etc. Attach additional pages as necessary.)
Action:APPENDIX C: AIRPLANE FUSELAGE SCRIBE LINE MARK SUMMARY TABLES Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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 up per skin of the aft end of the scribe line. 

### L d_fwd d_min d_aft

SCRIBE LINE LAP JOINT UPPER SKIN

LOWER SKIN1554792APPENDIX C: AIRPLANE FUSELAGE SCRIBE LINE MARK SUMMARY TABLES Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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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_aft d_fwd L

SCRIBE FUSELAGE SKIN1554793APPENDIX D: SCRIBE LINE SAMPLE Original Issue: November 25, 2008 Revision 1: April 09, 2009 767-53A0193
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APPENDIX D: SCRIBE LINE SAMPLE

The instructions that follow can be used to make repres entative 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 ai d that can be used to familiarize vi sual 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 diamet er countersunk rive ts. Make the counte rsinks 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 razo r 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 razo r 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 Revision 1: April 09, 2009 767-53A0193
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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

3 2 1

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