# Bombardier Service Bulletin 60-53-19 Copy: Revision 3 ("SB 60-53-19_Rev3"), 18 pages: PDF https://openairdocs.org/files/sha256/2f/06/2f0693c072b2869d8d7779f0d3dc3bb71268dc633558f7907fb916b6ba804731; text https://openairdocs.org/service-documents/bombardier/sb-60-53-19/file/2f0693c072b2.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-9505; AD 2017-08-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md) - Type: Service bulletin (Service Bulletin) - Number: 60-53-19 - Latest revision known: 60-53-19, Revision 3, dated August 29, 2016 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/bombardier/sb-60-53-19 ## ADs that cite it (3) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2019-17-01](https://openairdocs.org/ad/2019-17-01.md), effective Oct 2, 2019: Revisions 1, 2 and 3 - [AD 2017-11-09](https://openairdocs.org/ad/2017-11-09.md), effective May 30, 2017: Revisions 1, 2 and 3 - [AD 2017-08-07](https://openairdocs.org/ad/2017-08-07.md), effective May 22, 2017: Revisions 1, 2 and 3 Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/bombardier/sb-60-53-19/proposed.md). ## Text (18 pages) Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-9505; AD 2017-08-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) BOMBARDIER the evolution of mobility LEARJET 60 RT 60-53-19 Revision Transmittal Sheet This page transmits Revision 3 to Service Bulletin No. 60-53-19, "Inspection of Upper Fuselage Skin Under the Aft Oxygen Line Fairing". Rework: No rework is required for aircraft which have complied with previous issues of this document. Summary: This revision rewords the compliance statements, adds a note to the FAA approval statement, removes specific references to stringer locations, changes multiple entries from notes to steps and sub-steps adds a sub-step to state that the requirement for paint removal from the aircraft skin will vary dependent on the extent of corrosion found and the extent of corrosion migration. This revision promotes Step 3.B. (13)(c) to Step 3.B. (13)(d) and corrects references. NOTE: Change bars are placed in the left margin of pages where significant changes are located. This revision incorporates the latest document format for Learjet service instructions. The general arrangement of this document may change from the previous issue. Description of Changes In the Planning Information section: Changed the Compliance instructions as follows: Reworded the compliance statements to be more specific regarding aged aircraft requirements per- taining to airworthiness certifications. Changed the Approval information as follows: Added an informational note to the effect that an Airworthiness Directive may be released, at some future date, with this service bulletin incorporated by reference. In the Accomplishment Instructions section: Changed the Modification Instructions as follows: Changed multiple entries from notes to steps and sub-steps. Removed specific references to stringer locations in Step 3.B.(9) and added a step to state that the requirement for paint removal from the aircraft skin will vary dependent on the extent of corrosion found and the extent of corrosion migration. Changed the note under Step 3.B.(13) to (sub) Step 3.B.(13)(b) which required all subsequent sub- steps to be advanced. Changed wording in Step 3.B.(12) and (13) from "...evidence for corrosion..." to "...evidence of cor- rosion..." in both effectivity statements. Promoted Step 3.B.(13)(c) to Step 3.B.(13)(d) and corrected the references from Details B and D to Views EE and F-F and Details G and H. THIS PUBLICATION IS AVAILABLE AT: RT 60-53-19 www.cic.bombardier.com Page 1 of 2 Aug 29/16 ### Page 2 (OCR) LEARJET 60 Revision Transmittal Sheet Filing Instructions: This is a COMPLETE revision. Remove and discard all pages of the prior issue and replace them with pages of Revision 3. Record of Revisions: ISSUE DISTRIBUTION DATE Basic Nov 23/15 Revision 1 Apr 4/16 Revision 2 Apr 18/16 Revision 3 Aug 29/16 THIS PUBLICATION IS AVAILABLE AT: RT 60-53-19. www.cic.bombardier.com Page 2 of 2 Aug 29/16 ### Page 3 (OCR) BOMBARDIER LEARJET 60 the evolution of mobility Recommended SB 60-53-19 Service Bulletin If the instructions in this publication cannot be completed because of an STC change to the aircraft, speak to the STC holder or the regional Federal Aviation Administration (FAA) office for information and disposition. Contact Information Distribution Date Rev. No. Business Aircraft August 29, 2016 3 Learjet Inc. MS 53 P.O. Box 7707 Wichita, Kansas 67277-7707 Customer Response Center (CRC) 1-866-538-1247 (Toll Free) 1-514-855-2999 (Tel) Push 5 then 2 for Parts Services or push 4 then 2 for Technical Publications. FUSELAGE - INSPECTION OF UPPER FUSELAGE SKIN UNDER THE AFT OXYGEN LINE FAIR- ING 1. Planning Information A. Effectivity (1) Learjet 60-002 thru 60-430 on aircraft with dorsal mounted oxygen bottle or aircraft that have had the dorsal mounted oxygen bottle removed but have retained the oxygen line fairing installed on top of the fuselage. B. Reason (1) Learjet has identified aircraft that may have aircraft skin corrosion located under the oxygen tube fairing on top of the fuselage. C. Description (1) This service bulletin provides instructions to inspect the fuselage for corrosion of aircraft skin under the oxygen line fairing. Th the Export Administration kegulations. Diversion contary no Uned statels prondied. lefer to applicable government agency regulations and requirements and make sure that the work describe n this publication is pertormed in compliance with manufacturer's recommendations and/or acceptable industry standards is document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or I 1y means without the prior written consent of Bombardier Inc. and/or its affiliate © 2015, Bombardier Inc. All rights reserved. Challenger*, Global Express* are Trademarks of Bombardier Inc Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 1 of 12 ### Page 4 (OCR) LEARJET 60 Service Bulletin D. Compliance (1) Recommended - For aircraft with more than 12 years since the date of issuance of the original air- worthiness certificate or the date of the issuance of the original export certificate of airworthiness as of the original issue date of this publication, Bombardier Learjet Inc. recommends the actions specified in this publication be completed within 12 months after the initial distribution date of this publication. (2) Recommended - For aircraft with more than 6 years but equal to or less than 12 years since the date of issuance of the original airworthiness certificate or the date of the issuance of the original export certificate of airworthiness, as of the original issue date of this publication, Bombardier Learjet Inc. recommends the actions specified in this publication be completed within 24 months after the initial distribution date of this publication. (3) Recommended - For aircraft with 6 years or less since the date of issuance of the original airwor- thiness certificate or the date of the issuance of the original export certificate of airworthiness, as of the original issue date of this publication, Bombardier Learjet Inc. recommends the actions specified in this publication be completed within 36 months after the initial distribution date of this publication. E. Approval (1) The Federal Aviation Administration (FAA) has approved the technical content in this publication that has an effect on the airplane type design. NOTE: An Airworthiness Directive may be released, at some future date, with this service bul- letin incorporated by reference. (2) The European Aviation Safety Agency (EASA) has accepted the technical content in this publica- tion that has an effect on the airplane type design. F. Labor Hours - Estimated Accomplishment Time LABOR TASK HOURS 2.5 Labor hours to gain access. 22.0 * Labor hours to do the aircraft modification. 1.0 Labor hours to do a functional test/operational check. 20.0 Labor hours to return the aircraft to airworthy status. 45.5 Total Labor Hours NOTE: * The Labor hours required to modify the aircraft will vary base upon the findings of level three (3) Fluorescent Dye Penetrant Inspection of the fuselage skin. The labor hours provided are estimates to assist scheduling and planning the tasks given in this bulletin. The estimates are for direct labor performed by an experienced crew and do not include the time for familiarization, planning, aircraft preparation in hangar, such as towing and positioning of scaffolds, removal of aircraft loose equipment, acquisition of tools and equipment, training, supervision and inspection. If labor coverage is provided, only the hours above will be paid. Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 2 of 12 ### Page 5 (OCR) LEARJET 60 Service Bulletin When planning to complete these instructions, please contact Bombardier Aerospace, Learjet Inc. Business Aircraft Customer Service, Parts Services for parts availability and shipping times as necessary. (Refer to the title page of this document for contact information.) G. Expense Coverage (1) Labor Coverage (a) Aircraft in the Learjet manufactured warranty period, labor coverage is provided. NOTE: For labor coverage to apply, these instructions must be completed at a Bombardier Business Aviation Service Facility or at a Bombardier Learjet Authorized Service Facility. These instructions must be completed within 36 months from the Basic Issue distribution date of this publication. (b) Aircraft out of the Learjet manufactured warranty period, no labor coverage is provided. (2) Material Coverage (a) Aircraft in the Learjet manufactured warranty period, material coverage is provided. NOTE: For material coverage to apply, an order must be placed for these parts from Bom- bardier Learjet within 36 months from the Basic Issue distribution date of this pub- lication. (b) Aircraft out of the Learjet manufactured warranty period, no material coverage is provided. (3) Smart Parts Plus Coverage (a) None. H. Material Required (1) There are no kits associated with these instructions. (2) Other materials/parts necessary to complete these instructions. PART NUMBER NOMENCLATURE QTY SUPPLIER CR3213-4-02 Rivet 100 (Approx.) Locally Procured CR3213-5-02 Rivet 6 Locally Procured (Refer to Chapter 20 of the Maintenance Manual.) Epoxy Primer As required Locally Procured (Refer to Chapter 20 of the Maintenance Manual.) Exterior Paint As required Locally Procured (Refer to Chapter 20 of the Maintenance Manual.) Sealant As required Locally Procured (Refer to Chapter 20 of the Maintenance Manual.) Paint Stripper As required Locally Procured NOTE: For current prices, availability, ordering and shipping information, please call Bombar- dier Aerospace, Learjet Inc. Business Aircraft Customer Service, Parts Services. (Refer to the title page of this document for contact information.) Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 3 of 12 ### Page 6 (OCR) LEARJET 60 Service Bulletin I. Tools, Equipment and Materials (1) Refer to Chapter 20 of the Maintenance Manual as follows: (a) "Application of Epoxy Primer." (b) "Sealants - Description and Operation." (c) "Exterior Paint - Maintenance Practices." (2) Refer to Chapter 35 of the Maintenance Manual, "Oxygen System." 3) Refer to Chapter 35 of the Supplemental Maintenance Manual, "Oxygen System." (4) Refer to Chapter 51 and Chapter 53 of the Structural Repair Manual, "Corrosion Repair." Refer to Part 3 of the Non-Destructive Inspection Manual, "General." Refer to Part 5 of the Non-Destructive Inspection Manual, "General." J. Weight and Balance (1) Negligible. K. References NOTE: If applicable, referenced third party documentation can be accessed by opening the attachments pane in the Adobe Acrobat Reader software. In the latest version of the software, the attachments pane can be opened by clicking on the paper clip icon at the lower left corner of the screen. (1) Service Bulletin Compliance Response Form. (2) Service Bulletin Evaluation Sheet. (3) Learjet Maintenance Manual, Chapters 20, 24, and 35. (4) Learjet Supplemental Maintenance Manual, Chapter 35. (5) Learjet Customized Completion Manual, Chapter 35. Learjet Structural Repair Manual, Chapters 51 and 53. Learjet Non-Destructive Inspection Manual, Parts 3 and 5. L. Other Publications Affected (1) None 2. Material Information A. Parts Required (1) There are no kits associated with these instructions. Refer to Paragraph 1.H. for more materials/ parts necessary to complete these instructions. 3. Accomplishment Instructions A. Gain Access (1) Set the battery switches to OFF. If necessary, disconnect external electrical power and the aircraft batteries. (Refer to Chapter 24 of the Maintenance Manual.) Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 4 of 12 ### Page 7 (OCR) LEARJET 60 Service Bulletin B. Modification of Aircraft NOTE: For dimensions defined without specific tolerance information, refer to Paragraph 3.G. for standard tolerances. (1) Remove the oxygen line aft fairing, fairing end cap and the center fairing located over the fuel access panel. Retain the fairings and connecting hardware for later installation. (2) If necessary, remove the headliner over the cargo compartment in the cabin to catch debris. Retain for installation. (3) Place a suitable protection, such as drapes, as required under locations where the fairings are removed over the aft equipment bays to prevent debris from accumulating in the aircraft. (4) Remove all riveted sections of the oxygen fairing. (Refer to Chapter 51 of the Structural Repair Manual and Chapter 20 of the Maintenance Manual.) Retain the removed sections for later instal- (5) Inspect and clean accessible area under the fairing to remove debris. (6) Remove the drapes or other protective materials from the aircraft and clean the area where they were placed. (Refer to Chapter 20 of the Maintenance Manual.) Remove the oxygen line, the line clamps and spacers to gain access to the fuselage skin. (Refer to Chapter 20 of the Maintenance Manual and Chapter 35 of the Maintenance Manual.) Retain the remove items and connecting hardware for later installation. (a) Make sure to mark the location of each line clamp and spacer before removal to permit instal- lation after modification in the same place. (8) Visually inspect areas of the aircraft fuselage skin between Stringers 2L and 2R, for missing seal- ant, paint, and/or primer, where the fairing end cap and fairings were removed (a) Inspect the areas of the removed fairing flanges that were in contact with the fuselage skin panels to determine if missing sealant, paint, and/or primer was the result of the component removal process or some other reason that may have subjected the fuselage skin and other components to possible corrosion. NOTE: If missing sealant, paint, and/or primer was the result of the component removal process, it may not necessarily indicate that a corrosion issue exists. (9) Remove paint from aircraft skin and clean all fuselage skin panels where the fairing end cap and fairings were removed for corrosion inspection. (Refer to Chapter 20 of the Maintenance Manual.) (a) The area where paint must be removed from the aircraft skin will vary dependent on the extent of corrosion found and the extent of corrosion migration found on the skin panels. Only use paint strippers that are listed in the aircraft maintenance manual to prevent damage to the aircraft skin panels. (Refer to Chapter 20 of the Maintenance Manual.) (10) Inspect and clean skin panels for surface cleanliness before Fluorescent Dye Penetrant Inspection of the fuselage panels for corrosion. (Refer to Part 5 of the Non-Destructive Inspection Manual, General section.) (a) All NDI evaluations must be performed by an NAS 410 or ASNT equivalent minimum level I (2) inspector who is qualified to accomplish the specific methodology. (11) Perform a sensitivity level three (3) Fluorescent Dye Penetrant Inspection (per NDI-1 Manual, Part 5) of the fuselage skin for corrosion. (Refer to NDI-1 in Part 5 of the Non-Destructive Inspection Manual, General section.) (a) Look for evidence of surface and/or intergranular corrosion. On aircraft where no evidence of corrosion is revealed by the fluorescent dye penetrant inspection, proceed to Step 3.B. (14) of these instructions. Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 5 of 12 ### Page 8 (OCR) LEARJET 60 Service Bulletin (13) On aircraft where evidence of corrosion is revealed by the fluorescent dye penetrant inspection, proceed as follows: (a) Perform a high frequency eddy current inspection of the affected skin sections. (Refer to inspection method NDI-1 or NDI-2 as applicable, Part 3 of the Non-Destructive Inspection Manual, in the General section.) (b) Calibrate on 0.010 notch in the calibration standard (P/N 23-55 or equivalent). (C) Clearly mark all identified corrosion locations on the aircraft. (a) Perform a skin thickness check of the areas that are adjacent to the corroded areas in order to determine the material thickness before material was compromised by the corrosion. (See Figure 1, Views E-E, F-F and Details G and H for map of skin thickness of chemically milled areas.) 1) Use a calibrated direct reading or calibrated A scan ultrasonic equipment to accomplish this check 2) Ultrasonic thickness evaluation must be accomplished by use of a 10-20 MHz delay line transducer no greater than 0.25 in [6.35 mm] diameter and a certified thickness standard of aluminum alloy must be used with thickness steps ranging from less than the minimum skin thickness to greater than the maximum skin thickness for the aircraft in the area of the 3) When inspecting aircraft with milled skin, instrument calibration must be accomplished when moving from one thickness to another of greater than 30%. (e) If corrosion is found, repair affected skin sections. (Refer to Chapter 51 of the Structural Repair After corrosion is removed, recheck the corroded areas repeating the high frequency eddy current inspection. (g) Repeat corrosion removal and high frequency eddy current inspection until all evidence of intergranular corrosion is verified as removed Once it has been verified that all corrosion has been removed, repeat the ultrasonic skin thick- ness check to gauge the remaining material thickness in the corrosion removal area and record these values. 1) Make sure to measure blended areas of parallel and flat surfaces. Thickness measurements must be recorded and retained for submittal to Learjet Engi- neering when required 3) Thickness check must be accomplished in a defined square grid pattern of no greater than 0.5 x 0.5 in [12.7 × 12.7 mm] covering all areas where material has been affected by the corrosion removal process. The grid must extend outside the material removal area to allow verification of the original material thickness If any of these values fall below the minimum thickness table in Chapter 53 of the Struc- tural Repair Manual, stop this inspection/repair and contact Learjet Customer Support Engineering for further instructions. Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 6 of 12 ### Page 9 (OCR) LEARJET 60 Service Bulletin (14) Once the inspection and/or repairs are completed, chemical treat all surfaces where paint was removed and epoxy prime if not already done and paint. (Refer to Chapter 51 of the Structural Repair Manual and Chapter 20 of the Maintenance Manual.) Install the oxygen line, the line clamps and spacers that were removed to gain access to the fuse- lage skin. (Refer to Chapter 20 of the Maintenance Manual and Chapter 35 of the Maintenance Manual.) (a) For oxygen line installation refer to Chapter 35 of the Maintenance Manual, and/or Chapter 35 of the Customized Completion Manual, and/or Chapter 35 of the Supplemental Maintenance Manual for oxygen system maintenance practices. (b) Make sure to install clamps and spacers in the same locations from which they were marked and removed in an earlier step. Perform a leak check of the oxygen system. (Refer to Chapter 35 of the Maintenance Manual.) (17) Install the riveted sections of the oxygen fairings removed in an earlier step. (See Figure 1, (a) Make sure to fay seal each surface before installation. (Refer to Chapter 20 of the Mainte- nance Manual.) (18) Fillet seal around the edges of the fairings. (Refer to Chapter 51 of the Structural Repair Manual and Chapter 20 of the Maintenance Manual.) (19) Install the oxygen line aft fairing, fairing end cap and the center fairing located over the fuel access panel that were removed for access. (a) Make sure to fay seal bolted on caps and covers before installation. (Refer to Chapter 20 of the Maintenance Manual.) (20) Fillet seal around the edges of the fairings. (Refer to Chapter 51 of the Structural Repair Manual and Chapter 20 of the Maintenance Manual.) (21) Touch up paint as required. (22) Install the headliner over the cargo compartment in the cabin, if removed to help catch debris. C. Functional Test/Operational Check (1) Leak check of the oxygen system was accomplished in an earlier step. Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 7 of 12 ### Page 10 (OCR) LEARJET 60 Service Bulletin D. Return Aircraft to Airworthy Status (1) Make sure the batteries are connected to the aircraft. (Refer to Chapter 24 of the Maintenance Manual.) (2) Install any additional items removed for access. E. Compliance Response Form (1) Complete the compliance response form. (2) Send the compliance response form to Learjet Inc. as soon as possible. F. Aircraft Maintenance Records (1) Complete the Aircraft Maintenance Records in accordance with the regulatory requirements of the appropriate aircraft certification authority. G. General Information (1) The table below lists standard tolerances which shall apply to dimensions defined within the instructions or illustrations of this document that do not have specified tolerances. UNLESS OTHERWISE SPECIFIED ALL TOLERANCES ARE AS FOLLOWS: DECIMALS ANGLES 0.0 ‡ 0.1 in [0.0 mm ‡ 2.54 mm] MACHINED FORMED 0.00 ‡ 0.03 in [0.00 mm ‡ 0.76 mm] ‡0°30' ‡ 2° 0.000 ‡ 0.010 in [0.000 mm ‡ 0.254 mm] Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 8 of 12 ### Page 11 (OCR) LEARJET 60 Service Bulletin C FAIRING 6011006-001 FAIRING (REF) | 5411005-002 • G (REF) FS FS FS FS FS FS FS FS FS 346.63 355.16 356.61 367.23 368.68 378.05 382.52 392.50 393.95 STGR 1R BL 0.00 STGR 1L (6 REQUIRED) CR3213-5-02 RIVET (APPROXIMATELY RIVET CR3213-4-02 (REF) STRINGER 6011830 FWD (REF) RIVET .CR3213-4-02 100 REQUIRED) FAIRING INSTALLATION, VIEW LOOKING DOWN, SOME STRUCTURE NOT SHOWN FOR CLARITY View A-A RIVET E CR3213-4-02 COVER FS FS FS FS FS (REF) FS 6011238 FS 401.92. 403.39 410.30- 411.78 421.42 432.77 (REF) 444.12 F _ F STGR 1R BL 0.00 STGR 1L FAIRING - CR3213-4-02 5411005-004 • FWD FAIRING INSTALLATION, VIEW LOOKING DOWN, SOME STRUCTURE NOT SHOWN FOR CLARITY View B-B K60-605319-001-01 Aft Oxygen Line Fairing Corrosion Inspection Figure 1 (Sheet 1 of 4) Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 9 of 12 ### Page 12 (OCR) LEARJET 60 Service Bulletin E FAIRING RIVET 6011006-002 (REF) RIVET CR3213-4-02 455.48 FS 463.79- FS 465.28 FS 470.28 FS 480.28 FS (REF) (REF) CR3213-4-02 STGR 1R - BL 0.00 • • FWD STGR 1L FAIRING INSTALLATION, VIEW LOOKING DOWN, SOME STRUCTURE NOT SHOWN FOR CLARITY View C-C JFWD FAIRING 492.34 FS RIVET CR3213-4-02 503.34 509.66 FS FS 513.34 FS (REF) 6011006-003 _ FS (REF) 527.39 STGR 1R - 10D CD BL 0.00 BL STGR 1L 0.00 FAIRING INSTALLATION, VIEW LOOKING DOWN, SOME STRUCTURE NOT SHOWN FOR CLARITY View D-D 0.125 in FRAME 33 0.040 in FRAME 34 FRAME 30 FRAME 31 0.040 in FRAME 32 (3.175 mm] FS [1.016 mm] FS 413.23 FS 421.42 THICKNESS 432.77 FS [1.016 mm] FS THICKNESS 0.37 in 444.12 THICKNESS 455.48 / 1.38 in - STGR 2R - 9.40 mm] [3.51 cm] 8.19 in 10.27 in 1.02 in [20.80 cm] [26.09 cm] [2.59 cm] 0.90 in STGR 1R - [22.86 mm] BL 0.00 5.54 in _ 5.30 in 0.040 in (14.07 cm] [13.46 cm] STGR 1L - [1.016 mm] THICKNESS 1.02 in [2.59 cm] STGR 2L - 2.81 in 1.56 in RADIUS 0.50 in RADIUS 1.50 in • 0.085 in (7.14 cm] / [3.96 cm) [3.175 mm] 0.125 in • FWD [12.70 mm] [3.80 mm] [2.159 mm] (2 PLACES) (TYPICAL) THICKNESS 0.040 in THICKNESS [1.016 mm] ACCESS PLATE CUTOUT THICKNESS DIMENSIONS ARE APPROXIMATE View E-E K60-605319-001-02 Aft Oxygen Line Fairing Corrosion Inspection Figure 1 (Sheet 2 of 4) Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 10 of 12 ### Page 13 (OCR) LEARJET 60 Service Bulletin • FWD [3.18 mm] 0.125 in 0.085 in 10.39 in - [23.39 cm] [2.16 mm] FS / 0.84 in 0.60 in FS 432.77 [2.13 mm] [1.52 mm] ACCESS PLATE CUTOUT 444.12 DIMENSIONS ARE APPROXIMATE View F-F 0.70 in 0.10 in RADIUS 1.50 in [33.83 cm] 13.32 in [17.78 mm] THICKNESS [2.54 mm] [3.80 mm] (TYPICAL) (REF) CUTOUT STGR 2R 0.04 in 6.06 in 1.24 in [1.016 mm] [15.39 cm] [3.15 cm] THICKNESS STGR 1R 4.17 in [10.59 cm] 0.040 in BL 0.00 - 5.00 in [1.016 mm] 3.45 in 3.36 in [12.70 cm] THICKNESS [8.76 cm] [8.53 cm] STGR 1L 6.77 in 1.24 in [17.20 cm] [3.15 cm] STGR 2L 0.10 in CUTOUT FS (TYPICAL) CHEM MILL LINE FS THICKNESS (2.54 mm] FS FS (REF) 356.61 367.23 378.11 382.52 FRAME 25 • FWD FRAME 26 0.70 in FRAME 27 [17.78 mm] THICKNESS MAP FOR UPPER SKIN PANEL DIMENSIONS ARE APPROXIMATE Detail G K60-605319-001-03 Aft Oxygen Line Fairing Corrosion Inspection Figure 1 (Sheet 3 of 4) Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 11 of 12 ### Page 14 (OCR) LEARJET 60 Service Bulletin 0.040 in 0.10 in [1.016 mm] CHEM MILL LINE [2.54 mm] 0.06 in THICKNESS (TYPICAL) THICKNESS [1.524 mm] THICKNESS STGR 2R CUTOUT (REF) 0.75 in [19.05 mm] STGR 1R 0.040 in 5.00 in BL 0.00 [1.016 mm] [12.70 cm] THICKNESS 1.38 in [3.50 cm] STGR 1L (REF) CUTOUT [14.71 cm] 5.79 in [12.09 cm] 4.76 in _ [9.88 cm] *3.89 in- STGR 2L 0.10 in 4 FWD 2.44 in [2.54 mm] 3.47 in [6.20 cm] FS THICKNESS FS [8.81 cm] FS FS 392.50 401.92 410.30 414.63 FRAME 28 FRAME 29 FRAME 30 THICKNESS MAP FOR UPPER SKIN PANEL DIMENSIONS ARE APPROXIMATE Detail H NOTE • The 0.085 inch [2.16 mm] thickness is not listed in the minumum thickness table in Chapter 53 of the Learjet Structural Repair Manual. The minimum allowed for this skin thickness is 0.081 inch [2.0574 mm]. K60-605319-001-04 Aft Oxygen Line Fairing Corrosion Inspection Figure 1 (Sheet 4 of 4) Basic Issue: Nov 23/15 THIS PUBLICATION IS AVAILABLE AT: SB 60-53-19 Revision 3: Aug 29/16 www.cic.bombardier.com Recommended Page 12 of 12 ### Page 15 (OCR) SERVICE BULLETIN COMPLIANCE RESPONSE b It is necessary that Bombardier Learjet record aircraft having complied with this Service Bulletin. Please fill in the Service Bulletin and aircraft information below, sign and date the form in the space provided, fold on dotted lines, seal with tape, and mail completed form to Bombardier Learjet Maintenance Engineering. If mailed within the United States, this form may be mailed to Bombardier Learjet Maintenance Engineering using business reply mail (see reverse). This form may be faxed or e- mailed if preferred. (See mailing information provided.) *Submit by Email *An email will be opened addressed to Fracas and this form will be attached. Mailing Information: Bombardier Learjet WARRANTY - Completion of this response form is required in order to process the Maintenance Engineering warranty claim. Therefore, if a warranty allowance is provided in the Service Bulletin, (MS #78) (FAX 316 946-2305) return a copy of this form with the warranty claim. fracas_usa@aero.bombardier.com SMART PARTS - Completion of this response form is required in order to remain, Customer Support enroll, or re-enroll in the Smart Parts Program. Learjet, Inc. Service Bulletin Information SB Title: Inspection of Upper Fuselage Skin Under the Aft Oxygen Line Fairing Service Bulletin No. 60-53-19 Rev No. 3 Date August 29, 2016 Aircraft Information Model Serial No. Flight Hours Landings Service Facility Information Facility Incorporating Bulletin Compliance Information The above referenced Service Bulletin was complied with on the referenced serial number aircraft at the listed aircraft flight hours/landings: Actual hours to accomplish Service Bulletin: Access Modify _ Test(s) Restore Name: (Please Print) Date Email: Comments ### Page 16 (OCR) FOLD HERE FIRST NO POSTAGE BOMBARDIER NECESSARY IF MAILED IN THE UNITED STATES BUSINESS REPLY MAIL FIRST-CLASS MAIL PERMIT NO. 2928 WICHITA KS POSTAGE WILL BE PAID BY ADDRESSEE ATTN: MAINTENANCE ENGINEERING (MS #78) LEARJET INC PO BOX 7707 WICHITA KS 67277-9801 * FOLD HERE LAS SEAL WITH TAPE. DO NOT STAPLE ### Page 17 (OCR) SERVICE BULLETIN EVALUATION SHEET YOUR COMMENTS WILL HELP US IMPROVE OUR SERVICE BULLETINS Submit by Email *An email will be opened addressed to the SB Group and this form will be attached. SERVICE BULLETIN: 60-53-19 REVISION: 3 DATED: August 29, 2016 TITLE: Inspection of Upper Fuselage Skin Under the Aft Oxygen Line Fairing LEARJET CONTACT INFORMATION TELEPHONE: (316) 946-2421 FACSIMILE: (316) 946-8876 POOR FAIR GOOD VERY EXCELLENT GOOD HOW EASY IS THE BULLETIN TO UNDERSTAND? COMMENTS DOES THE BULLETIN TELL YOU ALL YOU NEED TO KNOW ABOUT THE JOB? COMMENTS DO YOU THINK THE BULLETIN CONVEYS THE BEST WAY TO DO THE JOB? COMMENTS HOW REALISTIC ARE THE LABOR-HOUR ESTIMATES? COMMENTS WHAT IS YOUR APPRECIATION OF THE ILLUSTRATIONS), FIGURE(S) AND/OR KIT DRAWING(S)? COMMENTS Actual hours to accomplish Service Bulletin: Access: Modify: Test(s): Restore: PLEASE SUPPLY THE FOLLOWING NAME: OPERATOR: EMAIL: AIRCRAFT: TELEPHONE: UPON COMPLETION OF THE EVALUATION FORM, YOU MAY FAX TO (316) 946-8876 OR FOLD AND RETURN TO ADDRESS ON THE REVERSE SIDE OR USE THE SUBMIT BUTTON AT THE TOP TO EMAIL IT. ### Page 18 (OCR) FOLD HERE FIRST BOMBARDIER NO POSTAGE NECESSARY IF MAILED IN THE UNITED STATES BUSINESS REPLY MAIL FIRST-CLASS MAIL PERMIT NO. 2928 WICHITA, KS POSTAGE WILL BE PAID BY ADDRESSEE ATTN: TECHNICAL PUBLICATIONS (MS #35) LEARJET INC PO BOX 7707 WICHITA, KS 67277-9801 Abodedalballadded allel *"FOLD HERE LAST. SEAL WITH TAPE DO NOT STAPLE --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.