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Commercial Airplanes 757 Service Bulletin ALERT Number: 757-53A0107 Original Issue: July 20, 2017 ATA System: 5300 SUBJECT: FUSELAGE - Skin - Inspections of the Fuselage Skin for Scribe Lines Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2017 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
Original Issue: July 20, 2017 757-53A0107 1 of 166
3.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 20, 2017 757-53A0107 2 of 166 BOEING SERVICE BULLETIN 757-53A0107
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BLANK PAGE
Table of Contents
S u m m a r y5
1. PLANNING INFORMATION9
A . E f f e c t i v i t y9
1. Airplanes9
2 . S p a r e s A f f e c t e d ........................................ 1 0 B. Concurrent Requirements ...................................... 1 0 C. Reason ................................................ 1 0 D. Description .............................................. 1 1 E. Compliance .............................................. 1 1 F . A p p r o v a l ............................................... 3 1 G. Manpower .............................................. 3 2 H. Weight and Balance Changes .................................... 3 3 I. Electrical Load Data ......................................... 3 3 J . R e f e r e n c e s .............................................. 3 3
1. Existing Data: ......................................... 3 3
2. Data Supplied with this Service Bulletin: ........................... 3 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 4 K. Publications Affected ........................................ 3 4 L. Interchangeability and Intermixability of Parts ........................... 3 4 M. Software Accomplishment Summary ................................ 3 4
2. MATERIAL INFORMATION ........................................ 3 5 A. Material - Price and Availability ................................... 3 5 B. Industry Support Information .................................... 3 5 C. Parts Necessary for Each Airplane ................................. 3 5 1 . K i t s / P a r t s ............................................ 3 5
2. Parts and Materials Supplied by the Operator ........................ 3 5
3. Parts Modified and Reidentified ................................ 3 6
4. Parts Removed and Not Replaced .............................. 3 6 D. Parts Necessary to Change Spares ................................. 3 6 E. Special Tooling - Price and Availability ............................... 3 6 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9 A. GENERAL INFORMATION ..................................... 3 9 B. WORK INSTRUCTIONS ....................................... 4 2 FIGURE 1: FUSELAGE - SKIN LAP JOINT - ZONE 1 - DETAILED INSPECTION ........... 6 0 FIGURE 2: FUSELAGE - SKIN LAP JOINT - ZONE 2 - DETAILED INSPECTION ........... 6 3 FIGURE 3: FUSELAGE - SKIN LAP JOINT - ZONE 3 - DETAILED INSPECTION ........... 6 6 FIGURE 4: FUSELAGE - CIRCUMFERENTIAL BUTT JOINT AT STA 440 - DETAILED INSPECTION . 69 FIGURE 5: FUSELAGE - CIRCUMFERENTIAL BUTT JOINT AT STA 660 - DETAILED INSPECTION . 72 FIGURE 6: FUSELAGE - CIRCUMFERENTIAL BUTT JOINT AT STA 780 - DETAILED INSPECTION . 75 FIGURE 7: FUSELAGE - CIRCUMFERENTIAL BUTT JOINT AT STA 1180 - DETAILED INSPECTION .................................................. 7 8 FIGURE 8: FUSELAGE - DECAL - DETAILED INSPECTION ...................... 8 1 FIGURE 9: FUSELAGE - EXTERNAL APPROVED REPAIR - ZONE A, ZONE B AND ZONE C - DETAILED INSPECTION .......................................... 8 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 10: FUSELAGE - INTERNAL APPROVED REPAIR - ZONE C - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTION .................... 8 6 FIGURE 11: FUSELAGE - SKIN LAP JOINT - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS ......................................... 8 8 FIGURE 12: FUSELAGE - CIRCUMFERENTIAL BUTT JOINT - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS ............................... 9 1 FIGURE 13: FUSELAGE - DECAL - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS .................................................. 9 3 FIGURE 14: FUSELAGE - EXTERNAL APPROVED REPAIR - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS ............................... 9 5 FIGURE 15: FUSELAGE - SKIN LAP JOINT - LIMITED RETURN TO SERVICE PROGRAM - ZONE 10 - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS .......... 9 8 FIGURE 16: FUSELAGE - SKIN LAP JOINT - LIMITED RETURN TO SERVICE PROGRAM - ZONE 11 - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS ......... 1 0 2 FIGURE 17: FUSELAGE - SKIN LAP JOINT - LIMITED RETURN TO SERVICE PROGRAM - ZONE 12 - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS ......... 1 0 6 FIGURE 18: FUSELAGE - SKIN LAP JOINT - LIMITED RETURN TO SERVICE PROGRAM - ZONE 13 - DETAILED AND NON-DESTRUCTIVE TESTING (NDT) INSPECTIONS ......... 1 1 0 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1: INITIAL INSPECTIONS F O R A N Y S C R I B E L I N E A T S K I N L A P J O I N T ....................... 1 1 4 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2: INITIAL INSPECTIONS FOR ANY SCRIBE LINE AT CIRCUMFERENTIAL BUTT JOINT ............. 1 1 9 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3: INITIAL INSPECTIONS FOR ANY SCRIBE LINE AT DECAL LOCATIONS ..................... 1 2 4 APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 4: INITIAL INSPECTIONS
FOR ANY SCRIBE LINE AT LOCATIONS WITH EXISTING EXTERNAL APPROVED REPAIR ................................................. 1 2 7 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 5: INITIAL INSPECTIONS
FOR ANY SCRIBE LINE AT LOCATIONS WITH EXISTING INTERNAL APPROVED REPAIR ................................................. 1 3 3 APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 6: LIMITED RETURN TO
SERVICE (LRTS) PROGRAM INSPECTIONS FOR AIRPLANES WITH ANY SCRIBE LINE AT S K I N L A P J O I N T....................................... 1 3 7 APPENDIX G: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 7: LIMITED RETURN TO
SERVICE (LRTS) PROGRAM INSPECTIONS FOR AIRPLANES WITH ANY SCRIBE LINE AT CIRCUMFERENTIAL BUTT JOINT ............................. 1 4 3 APPENDIX H: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 8: LIMITED RETURN TO
SERVICE (LRTS) PROGRAM INSPECTIONS FOR ANY SCRIBE LINE AT DECAL LOCATIONS ................................................. 1 4 9 APPENDIX I: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 9: LIMITED RETURN TO
SERVICE (LRTS) PROGRAM INSPECTIONS FOR ANY SCRIBE LINE AT LOCATIONS WITH EXISTING EXTERNAL APPROVED REPAIR ........................ 1 5 1 APPENDIX J: SEALANT REMO VAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN . 155 APPENDIX K: AIRPLANE FUSELAGE SCRIBE LINE MARK SUMMARY TABLES ............ 1 5 9 APPENDIX L: SCRIBE LINE SAMPLE .................................... 1 6 2 APPENDIX M: FUSELAGE - SKIN LAP JOINT - ZONE INSPECTION SUMMARY TABLE ........ 1 6 5 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes 757 Service Bulletin ALERT SummaryNumber: 757-53A0107Original Issue: July 20, 2017 ATA System: 5300 SUBJECT: FUSELAGE - Skin - Inspections of the Fuselage Skin for Scribe Lines
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.
CONCURRENT REQUIREMENTS None.
BACKGROUND This service bulletin gives instructions to inspect for scribe lines or cracks resulting from scribe lines, on the fuselage skin at lap joints, the splice strap at certain butt joints, the skin or doubler at certain approved repair doublers and the skin at decals. There is no inspection program specific for fuselage scribe line detection on 757-300 airplanes at present. Implementing a periodic inspection program will mitigate the safety issue. Failure to detect and completely remove scribe lines may lead to fatigue cracking. If not corrected, scribe lines and subsequent cracks can potentially lead to rapid decompression and the inability of the principal structural element to sustain limit load.
The Boeing Company has received reports on six different cases of scribe line damage on 757-300 airplanes.
The affected airplanes have accumulated between 4,500 and 14,000 flight cycles. The scribe lines were discovered during scheduled maintenance inspections. No cracks have been reported related to scribe lines.
Scribe line damage is not associated with aircraft service life. A scribe line is a narrow, shallow, distinct line of damage (typically up to 0.006 inch deep), usually associated with the removal of a fillet or gap seal (lap joints and butt joints, respectively).
A review of fleet activity yields two separate scenarios that are suspected to have caused scribe lines to the fuselage skin or butt joint splice straps.
The first scenario involves the paint stripping and repainting of airplanes. In the process of stripping and preparing the airplane for paint, tools were used to remove sealant and paint buildup at lap joints, butt joints, and at certain external or internal doublers or door scuff plates. Tools like scrapers (steel, wood, hard plastic etc.), knives, or utility knives can damage the skin, splice straps, or internal doublers. This operation can result in scribe lines at any of these locations. Fatigue cracks can develop at scribe line locations.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 20, 2017 757-53A0107 5 of 166
The second scenario involves the removal or installation of graphic decals on the fuselage. During the removal and installation of decals across lap joint steps or repairs, investigation into maintenance practices has shown the 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) 757-SRP-53-0494 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 757 FTD 53-06005 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph
1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedNoPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION
1. Initial Inspections:
Do a detailed inspection for any scribe line at skin lap joints, circumferential butt splices, decal locations, and locations with existing external or internal approved repairs.
a. If no scribe line is found, or any scribe line is found less than 0.001 inch deep, no further inspections are required.
b. If any scribe line is found that is within the limits of a typical scribe line and more than or equal to
0.001 inch deep, do a Non-Destructive Testing (NDT) inspection for any crack at each scribe line location.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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(1) If no crack is found, do the Limited Return To Service (LRTS) Program, at the times specified in Paragraph 1.E., Compliance, or contact The Boeing Company for repair instructions and do the repair.
(2) If any crack is found, contact The Boeing Company for repair instructions and do the repair.
c. If any scribe line is found that is not within the limits of a typical scribe line, contact The Boeing Company for repair instructions and do the repair.
2. LRTS Program:
Do an NDT inspection at the times specified in Paragraph 1.E., Compliance for any crack at each location where a scribe line was found. If no crack is found, repeat the NDT inspection. If any crack is found, contact The Boeing Company for repair instructions and do the repair.
EFFECTIVITY All 757-300 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspections or repair procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 20, 2017 757-53A0107 7 of 166 BOEING SERVICE BULLETIN 757-53A0107
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 20, 2017 757-53A0107 8 of 166 BOEING SERVICE BULLETIN 757-53A0107
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Commercial Airplanes 757 Service Bulletin ALERT Number: 757-53A0107 Original Issue: July 20, 2017 ATA System: 5300 SUBJECT: FUSELAGE - Skin - Inspections of the Fuselage Skin for Scribe Lines
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.
1. PLANNING INFORMATION A. Effectivity
1. Airplanes This service bulletin is applicable to all 757-300 airplanes, in 1 Group. The Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP 757-300 Airplanes-1 Airplane Models:
757-300 GroupVariable Number 1NL001 - NL002 1NL006 - NL017 1NL101 - NL109 1NL141 1NL601 - NL616 1NU701 - NU705 1NU721 - NU728 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 20, 2017 757-53A0107 9 of 166
GroupVariable Number 1NU731 - NU732
2. Spares Affected None.
B. Concurrent Requirements None.
C. Reason This service bulletin gives instructions to inspect for scribe lines or cracks resulting from scribe lines, on the fuselage skin at lap joints, the splice strap at certain butt joints, the skin or doubler at certain approved repair doublers and the skin at decals. There is no inspection program specific for fuselage scribe line detection on 757-300 airplanes at present. Implementing a periodic inspection program will mitigate the safety issue. Failure to detect and completely remove scribe lines may lead to fatigue cracking. If not corrected, scribe lines and subsequent cracks can potentially lead to rapid decompression and the inability of the principal structural element to sustain limit load.
The Boeing Company has received reports on six different cases of scribe line damage on 757-300 airplanes. The affected airplanes have accumulated between 4,500 and 14,000 flight cycles. The scribe lines were discovered during scheduled maintenance inspections. No cracks have been reported related to scribe lines.
Scribe line damage is not associated with aircraft service life. A scribe line is a narrow, shallow, distinct line of damage (typically up to 0.006 inch deep), usually associated with the removal of a fillet or gap seal (lap joints and butt joints, respectively).
A review of fleet activity yields two separate scenarios that are suspected to have caused scribe lines to the fuselage skin or butt joint splice straps.
The first scenario involves the paint stripping and repainting of airplanes. In the process of stripping and preparing the airplane for paint, tools were used to remove sealant and paint buildup at lap joints, butt joints, and at certain external or internal doublers or door scuff plates. Tools like scrapers (steel, wood, hard plastic etc.), knives, or utility knives can damage the skin, splice straps, or internal doublers.
This operation can result in scribe lines at any of these locations. Fatigue cracks can develop at scribe line locations.
The second scenario involves the removal or installation of graphic decals on the fuselage. During the removal and installation of decals across lap joint steps or repairs, investigation into maintenance practices has shown the 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) 757-SRP-53-0494 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 20, 2017 757-53A0107 10 of 166 BOEING SERVICE BULLETIN 757-53A0107
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Boeing Fleet Team Digest (FTD) 757 FTD 53-06005 is related to this service bulletin.
D. Description
1. Initial Inspections:
Do a detailed inspection for any scribe line at skin lap joints, circumferential butt splices, decal locations, and locations with existing external or internal approved repairs.
a. If no scribe line is found, or any scribe line is found less than 0.001 inch deep, no further inspections are required.
b. If any scribe line is found that is within the limits of a typical scribe line and more than or equal to 0.001 inch deep, do a Non-Destructive Testing (NDT) inspection for any crack at each scribe line location.
(1) If no crack is found, do the Limited Return To Service (LRTS) Program, at the times specified in Paragraph 1.E., Compliance, or contact The Boeing Company for repair instructions and do the repair.
(2) If any crack is found, contact The Boeing Company for repair instructions and do the repair.
c. If any scribe line is found that is not within the limits of a typical scribe line, contact The Boeing Company for repair instructions and do the repair.
2. LRTS Program:
Do an NDT inspection at the times specified in Paragraph 1.E., Compliance for any crack at each location where a scribe line was found. If no crack is found, repeat the NDT inspection. If any crack is found, contact The Boeing Company for repair instructions and do the repair.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones ZoneModel 117, 118, 119, 121, 122, 123, 124, 125, 126, 131, 132, 133, 134, 135, 136, 139, 141, 142, 143, 144, 149, 151, 152, 153, 154, 155, 156, 161, 162, 163, 164, 165, 166, 221, 222, 223, 224, 231, 232, 233, 234, 241, 242, 243, 244, 251, 252, 253, 254 757-300 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX
A, APPENDIX B, APPENDIX C, APPENDIX D, APPENDIX E, APPENDIX F, APPENDIX G, APPENDIX H, and APPENDIX I.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 9, in accordance with Paragraph 3. Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number.
Table 1: Initial Inspections for any Scribe Line at Skin Lap Joints Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,300 flight cycles after the original issue date of this service bulletin.
Before 20,000 total flight cycles plus first scribe line opportunity. (f) Do PART 2: SKIN LAP
JOINT DETAILED INSPEC- TION for any scribe line in ZONE 1. (d)(e) All Airplanes. (a)(b)(c) -Within 3,300 flight cycles after the original issue date of this service bulletin.
Before 30,000 total flight cycles plus first scribe line opportunity. (f) Do PART 2: SKIN LAP
JOINT DETAILED INSPEC- TION for any scribe line in ZONE 2. (d)(e) -Within 3,300 flight cycles after the original issue date of this service bulletin.
Before 40,000 total flight cycles plus first scribe line opportunity. (f) Do PART 2: SKIN LAP
JOINT DETAILED INSPEC- TION for any scribe line in ZONE 3. (d)(e) --No further inspections are required at this location. (g) CONDITION 1: NO SCRIBE LINE FOUND.
-Before further flight.Do PART 7: SCRIBE LINE MEASUREMENT at each scribe line location.
CONDITION 2: ANY SCRIBE LINE FOUND.
--No further inspections are required at this location. (g) CONDITION 2.1: SCRIBE LINE IS LESS THAN 0.001 INCH DEEP.
-Before further flight.Do PART 8: DETAILED
AND NON-DESTRUCTIVE
TESTING (NDT) INSPEC- TIONS for any crack at each scribe line location common to skin lap joints.
CONDITION 2.2: SCRIBE
LINE IS WITHIN THE LIM-
ITS OF A TYPICAL
SCRIBE LINE AND MORE
THAN OR EQUAL TO
0.001 INCH DEEP.
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