# Boeing Alert Service Bulletin 737-55A1099: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0473; AD 2017-25-10 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 737-55A1099](https://openairdocs.org/service-documents/boeing/737-55a1099.md) - Title as filed: SB-737-55A1099, Rev. 1 - BOEING - Pages: 227 - PDF: https://openairdocs.org/files/sha256/f6/20/f620624097b3318072adf0eda940810a93e9f7f7ec83eed160c18f279f4b76fe - Page: https://openairdocs.org/service-documents/boeing/737-55a1099/file/f620624097b3 ## Text Some pages are 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 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-55A1099 Original Issue: July 05, 2016 Revision 1: October 21, 2016 ATA System: 5510 5520 SUBJECT: STABILIZERS - Horizontal Stabilizer - Elevator Hinge Numbers 3, 4, 5, and 6 Inspection and Repair 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 © 2016 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 Unpublished Work.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 05, 2016 737-55A1099Revision 1: October 21, 2016 1 of 227 2.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 2 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 7 S u m m a r y ...................................................... 9 1. PLANNING INFORMATION ........................................ 1 7 A . E f f e c t i v i t y ............................................... 1 7 1. Airplanes ............................................ 1 7 2 . S p a r e s A f f e c t e d ........................................ 2 9 B. Concurrent Requirements ...................................... 2 9 C. Reason ................................................ 2 9 D. Description .............................................. 3 0 E. Compliance .............................................. 3 5 F . A p p r o v a l ............................................... 4 7 G. Manpower .............................................. 4 8 H. Weight and Balance Changes .................................... 5 4 I. Electrical Load Data ......................................... 5 4 J . R e f e r e n c e s .............................................. 5 4 1. Existing Data: ......................................... 5 4 2. Data Supplied with this Service Bulletin: ........................... 5 4 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 5 5 K. Publications Affected ........................................ 5 5 L. Interchangeability and Intermixability of Parts ........................... 5 5 M. Software Accomplishment Summary ................................ 5 5 2. MATERIAL INFORMATION ........................................ 5 7 A. Material - Price and Availability ................................... 5 7 B. Industry Support Information .................................... 5 8 C. Parts Necessary for Each Airplane ................................. 5 8 1 . K i t s / P a r t s ............................................ 5 8 2. Parts and Materials Supplied by the Operator ........................ 5 8 3. Parts Modified and Reidentified ................................ 6 4 4. Parts Removed and Not Replaced .............................. 6 4 D. Parts Necessary to Change Spares ................................. 6 4 E. Special Tooling - Price and Availability ............................... 6 4 F. Special Tooling Necessary to do this Service Bulletin ....................... 6 4 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 5 A. GENERAL INFORMATION ..................................... 6 5 B. WORK INSTRUCTIONS ....................................... 6 7 FIGURE 1: ELEVATOR HINGE FITTING NUMBERS 4 AND 6 - HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 2, Configuration 1] ........................... 8 3 FIGURE 2: ELEVATOR HINGE FITTING NUMBERS 4 AND 6 - HIGH FREQUENCY EDDY CURRENT INSPECTION [Group 2, Configuration 2; Group 3] ...................... 8 7 FIGURE 3: ELEVATOR HINGE NUMBER 6 FITTING - DETAILED INSPECTION [Group 2, Configuration 2; Group 3] ........................................... 9 2 FIGURE 4: ELEVATOR HINGE NUMBERS 4 AND 6 - LOOSE BOLT CHECK [Group 2, Configuration 1] .................................................. 9 4 FIGURE 5: ELEVATOR HINGE NUMBERS 4 AND 6 - LOOSE BOLT CHECK [Group 2, Configuration 2; Group 3] ............................................. 9 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 3 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 4 FIGURE 6: ATTACH PLATES AT ELEVATOR HINGE NUMBERS 4 AND 6 - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 2-3] ....................... 1 0 3 FIGURE 7: HORIZONTAL STABILIZER - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 3] ...... 1 0 7 FIGURE 8: HORIZONTAL STABILIZER - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 2] ...... 1 0 9 FIGURE 9: ATTACH PLATES AT ELEVATOR HINGE NUMBERS 4 AND 6 - LOOSE BOLT CHECK [Group 2 - 3 ] ............................................... 1 1 3 FIGURE 10: HORIZONTAL STABILIZER REAR SPAR, GUSSET, AND INSPAR SKIN - DETAILED INSPECTION [Group 2-3] .................................. 1 1 7 FIGURE 11: ELEVATOR FRONT SPAR AT HINGE NUMBERS 4 AND 6 - GENERAL VISUAL INSPECTION [Group 2, Configuration 2; Group 3] ............................. 1 2 0 FIGURE 12: ELEVATOR SKIN AT HINGE NUMBERS 4 AND 6 - TAP TEST INSPECTION [Group 2-3] . 123 FIGURE 13: ELEVATOR HINGE FITTING NUMBERS 4 AND 6 - BEARING PLATE REPLACEMENT [Group 2, Configuration 2; Group 3] ................................. 1 2 6 FIGURE 14: ELEVATOR HINGE - BEARING PLATE BINDING TEST [Group 2, Configuration 2; Group 3] ................................................. 1 3 0 FIGURE 15: ELEVATOR HINGE NUMBER 6 FITTING - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 2, Configuration 2; Group 3] ..................... 1 3 2 FIGURE 16: HINGE FITTING ASSEMBLY AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION AND MEASUREMENT [Group 2, Configuration 2; Group 3] ........ 1 3 4 FIGURE 17: ELEVATOR HINGE BEARING PLATE - BUSHING REPLACEMENT [Group 2, Configuration 2; Group 3] ............................................ 1 4 0 FIGURE 18: HINGE FITTING AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION AND MEASUREMENT [Group 2, Configuration 2; Group 3] ................... 1 4 4 FIGURE 19: ELEVATOR HINGE NUMBERS 4 AND 6 - BEARING PLATE INSTALLATION [Group 2, Configuration 2; Group 3] ................................... 1 4 9 FIGURE 20: HORIZONTAL STABILIZER HINGE FITTING AND ATTACH PLATES AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION [Group 2-3] ................ 1 5 4 FIGURE 21: HORIZONTAL STABILIZER HINGE FITTING AND ATTACH PLATES AT ELEVATOR HINGE NUMBER 4 - REPAIR [Group 2-3] .............................. 1 5 7 FIGURE 22: HORIZONTAL STABILIZER HINGE FITTING AND ATTACH PLATES AT ELEVATOR HINGE NUMBER 6 - REPAIR [Group 2-3] .............................. 1 6 2 FIGURE 23: ATTACH PLATES AT ELEVATOR HINGE NUMBERS 4 AND 6 - INSTALLATION [Group 2-3] ................................................. 1 6 7 FIGURE 24: HORIZONTAL STABILIZER HINGE FITTING AND ATTACH PLATES AT HINGE NUMBERS 3 AND 5 - DETAILED INSPECTION [Group 2-3] ...................... 1 7 2 FIGURE 25: ELEVATOR HINGE NUMBERS 3 AND 5 - BEARING PLATE INSTALLATION [Group 2, Configuration 2; Group 3] ................................... 1 7 5 FIGURE 26: HORIZONTAL STABILIZER HINGE FITTING AND ATTACH PLATES AT HINGE NUMBER 3 - REPAIR [Group 2-3] ..................................... 1 7 8 FIGURE 27: HORIZONTAL STABILIZER HINGE FITTING AND ATTACH PLATES AT HINGE NUMBER 5 - REPAIR [Group 2-3] ..................................... 1 8 3 FIGURE 28: ATTACH PLATES AT ELEVATOR HINGE NUMBERS 3 AND 5 - INSTALLATION [Group 2-3] ................................................. 1 8 8 FIGURE 29: HINGE FITTING ASSEMBLY AT ELEVATOR HINGE NUMBERS 4 AND 6 - BUSHING INSTALLATION [Group 2, Configuration 2; Group 3] .................... 1 9 3 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: WORK PACKAGE 1: ELEVATOR HINGE NUMBERS 4 AND 6 – HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK AND LOOSE BOLT CHECK .............. 1 9 9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 4 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 5 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: WORK PACKAGE 1: ELEVATOR HINGE NUMBERS 4 AND 6 – HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK AND LOOSE BOLT CHECK .............. 2 0 2 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 3: WORK PACKAGE 2: HORIZONTAL STABILIZER AT ELEVATOR HINGE NUMBERS 4 AND 6 – HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION FOR ANY CRACK AND LOOSE BOLT CHECK .............. 2 0 5 APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 4: WORK PACKAGE 2: HORIZONTAL STABILIZER AT ELEVATOR HINGE NUMBERS 4 AND 6 – HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION FOR ANY CRACK AND LOOSE BOLT CHECK .............. 2 0 8 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 5: WORK PACKAGE 3: HORIZONTAL STABILIZER REAR SPAR, GUSSET PLATE, AND INSPAR SKIN FORWARD OF ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION FOR ANY CORROSION ................................................. 2 1 1 APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 6: WORK PACKAGE 4: ELEVATOR FRONT SPAR AT HINGE NUMBERS 4 AND 6 - GENERAL VISUAL INSPECTION (GVI) FOR ANY PLY DAMAGE ............................... 2 1 3 APPENDIX G: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 6: WORK PACKAGE 5: ELEVATOR SKIN AT HINGE NUMBERS 4 AND 6 - TAP TEST INSPECTION FOR ANY DELAMINATION ....................................... 2 1 5 APPENDIX H: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 8: WORK PACKAGE 6: ELEVATOR HINGE NUMBERS 4 AND 6 - BEARING PLATE REPLACEMENT ..... 2 1 7 APPENDIX I: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 9: WORK PACKAGE 7: ELEVATOR HINGE NUMBER 6 FITTING - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK .............................. 2 1 9 APPENDIX J: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 10: PART 6: ELEVATOR HINGE FITTING NUMBERS 4 AND 6 - DETAILED INSPECTION FOR ANY DAMAGE - RESULTING CONDITIONS AND CORRECTIVE ACTIONS ................ 2 2 1 APPENDIX K: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 11: PART 7: ELEVATOR HINGE FITTING - BUSHING REPLACEMENT- RESULTING CONDITIONS AND CORRECTIVE ACTIONS ........................................... 2 2 3 APPENDIX L: L OGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 12: PART 8: ATTACH PLATE AND HORIZONTAL STABILIZER AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION - RESULTING CONDITIONS AND CORRECTIVE ACTIONS ....... 2 2 5 APPENDIX M: L OGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 13: PART 8: ATTACH PLATE AND HORIZONTAL STABILIZER AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION - RESULTING CONDITIONS AND CORRECTIVE ACTIONS ....... 2 2 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 5 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 6 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT BLANK PAGE ### Page 7 Commercial Airplanes 737 Service Bulletin ALERT Revision Transmittal SheetNumber: 737-55A1099Original Issue: July 05, 2016 Revision 1: October 21, 2016 ATA System: 5510 5520 SUBJECT: STABILIZERS - Horizontal Stabilizer - Elevator Hinge Numbers 3, 4, 5, and 6 Inspection and Repair This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Airplane line number 1109 was added to Group 2 and airplanes line numbers 1258 and 1259 were added to Group 3 of this service bulletin effectivity. Effects of this Revision on airplanes on which Original Issue was previously done: None. REASON FOR REVISION This revision is sent to update the effectivity of this service bulletin to include additional airplanes. Airplane line number 1109 was added to Group 2 and airplanes line numbers 1258 and 1259 were added to Group 3 of this service bulletin effectivity. These sections were changed: 1. Paragraph 1.A.1., Effectivity, has been updated, airplane line number 1109 was added to Group 2 and airplanes line numbers 1258 and 1259 were added to Group 3. 2. Paragraph 1.C., Reason, added reason for revision statement. 3. Paragraph 1.D., Description, added effects of revision statement. 4. Paragraph 1.H., Weight and Balance Changes, paragraph has been updated. 5. Paragraph 2.A., Material - Price and Availability, table has been updated. 6. Figure 28, Step table has been updated. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 7 of 227 ### Page 8 Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. REVISION HISTORY July 05, 2016Original Issue: October 21, 2016Revision 1: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 8 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 9 Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-55A1099Original Issue: July 05, 2016 Revision 1: October 21, 2016 ATA System: 5510 5520 SUBJECT: STABILIZERS - Horizontal Stabilizer - Elevator Hinge Numbers 3, 4, 5, and 6 Inspection and Repair 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 Following a special certification review for the 737-100, -200, -300, -400, -500 horizontal stabilizer, The Boeing Company determined through analysis that a disconnect of either elevator hinge number 4 or number 6 could result in flutter within the airplane flight envelope. As the horizontal stabilizer expands and contracts relative to the elevator, Teflon-lined sliding bearing plates at the elevator hinges are designed to adjust for the thermally-induced spanwise thrust loads. Wear and tight tolerancing of the Teflon-lined bearing plate slider bushings can cause binding of the sliding bearing plates. Binding of the sliding bearing plates causes the spanwise thrust loads to be absorbed by the elevator hinges, including the hinge support fittings on the horizontal stabilizer, which could lead to damage of the elevator hinge fitting and surrounding structure and cause a disconnect of the elevator hinge. Any crack, corrosion, delamination, or bolt looseness at the elevator hinges and surrounding structure could result in airplane vibration and damage. This service bulletin provides instructions to do repetitive inspections for any crack, corrosion, delamination, or bolt looseness at the elevator hinges and surrounding structure and provides instructions to do repetitive bearing plate replacements at the elevator hinges using an improved bearing plate. If the work in this service bulletin is not done, flutter resulting from disconnection of elevator hinge number 4 or number 6 could excite the horizontal stabilizer under certain in-flight speed/altitude conditions and degradation of the structure due to tab flutter, hinge wear, spar chord corrosion, hinge rib web chafing, hinge rib chord cracking, and inspar lower skin cracking could result in heavy airplane vibration and damage, which could lead to departure of the elevator and/or horizontal stabilizer from the airplane. This will lead to loss of continued safe flight and landing. To date, there have been no reports of an in-flight disconnection of either elevator hinge number 4 or number 6, but there have been multiple reports of wear induced vibration that validates the analysis findings of The Boeing Company. In addition, The Boeing Company has received one report of a disconnected joint found during maintenance with no report of in-flight vibration. These reports indicate that the level of structural stiffness and redundancy may not preclude failure at elevator hinge number 4 or hinge number 6 and possible flutter if appropriate maintenance and repair procedures are not followed. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 9 of 227 ### Page 10 Boeing has received 15 reports of out-of-round hinge support fitting holes caused by loose attach plate bolts on the horizontal stabilizer. Of the 15 reports received, 11 hinge support fittings required repair at the number 6 location, 3 required repair at the number 5 location, and 1 required repair at the number 4 location. Repairs have occurred on both the left and right side stabilizers. The elongation of the hinge support fitting holes has been found on airplanes ranging from 3,370 hours to 18,050 hours and 2,860 flight cycles to 15,915 flight cycles. This service bulletin supersedes service bulletin 737-55-1054, which gives instructions to inspect, repair, or replace the elevator hinge support fitting, attach plates, and sliding bearing plate assembly at elevator hinge numbers 3, 4, 5, and 6. Boeing Service Related Problem (SRP) 737-55-0032 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737 FTD 55-03002 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 AffectedYesSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane 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 Group 1: Boeing endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplane upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Line numbers 1-291 have accumulated flight cycles beyond the LOV of the airplane. 14 Code of Federal Regulations (CFR) Part 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV. Group 2-3: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection for Any Crack and Loose Bolt Check 1. Do an HFEC inspection of the elevator hinge fittings for any crack. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 10 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 11 a. If no crack is found, repeat the HFEC inspection of the elevator hinge fittings for any crack at the repeat interval given in Paragraph 1.E., Compliance. b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the elevator hinge fittings for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. 2. Do a loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt. a. If no loose bolt is found, repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. b. Group 2, Configuration 2; Group 3: If any loose slider bolt is found, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment, repair any damage or misalignment, and repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. c. If any loose hinge fitting attachment fastener is found, remove and replace the fastener with a new or serviceable fastener and repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. d. If any loose elevator hinge bolt is found, do the following: (1) Do a detailed inspection of the attach plates and horizontal stabilizer hinge fitting for any damage at the affected location and repair any damage (2) Group 2, Configuration 2; Group 3: Do the elevator hinge bearing plate binding test at the affected hinge location. (a) If the bearing plate binds, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment and repair any damage or misalignment. (b) If the bearing plate does not bind, do a detailed inspection of the bearing plate bearing for any damage and replace the bearing plate if any damage is found. (3) Repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance Group 2-3: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check 1. Do an HFEC inspection of the attach plates for any crack. a. If no crack is found, repeat the HFEC inspection of the attach plates for any crack at the repeat interval given in Paragraph 1.E., Compliance. b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the attach plates for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 11 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 12 2. Do an HFEC inspection and LFEC inspection of the gusset plates and horizontal stabilizer inspar skin fastener locations for any crack. a. If no crack is found, repeat the HFEC inspection and LFEC inspection of the gusset plates and horizontal stabilizer inspar skin fastener locations for any crack at the repeat interval given in Paragraph 1.E., Compliance. b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the attach plates for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. 3. Do a loose bolt check of the attach plate bolts at elevator hinge numbers 4 and 6 for any loose bolt. a. If no loose bolt is found, repeat the loose bolt check of the attach plate bolts at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. b. If any loose bolt is found, do the following: (1) Do a detailed inspection of the attach plates and horizontal stabilizer hinge fitting for any damage at the affected location and repair any damage. (2) Group 2, Configuration 2; Group 3: Do the elevator hinge bearing plate binding test at the affected hinge location. (a) If the bearing plate binds, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment and repair any damage or misalignment. (b) If the bearing plate does not bind, do a detailed inspection of the bearing plate bearing for any damage and replace the bearing plate if any damage is found. (3) Repeat the loose bolt check of the attach plate bolts at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance Group 2-3: Work Package 3: Horizontal Stabilizer Rear Spar, Gusset Plate, and Inspar Skin Forward of Elevator Hinge Numbers 4 and 6 - Detailed Inspection for Any Corrosion 1. Do a detailed inspection of the horizontal stabilizer rear spar outer mold line for any corrosion. a. If no corrosion is found, repeat the detailed inspection for any corrosion at the repeat interval given in Paragraph 1.E., Compliance. b. If any corrosion is found that is within the structural repair manual repair limits, repair the corrosion and repeat the detailed inspection for any corrosion at the repeat interval given in Paragraph 1.E., Compliance. c. If any corrosion is found that is not within the structural repair manual repair limits, contact The Boeing Company for repair instructions and do the repair and repeat the detailed inspection for any corrosion at the unrepair areas and areas repaired in accordance with the structural repair manual at repeat interval given in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 12 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 13 Group 2, Configuration 2; Group 3: Work Package 4: Elevator Front Spar at Hinge Numbers 4 and 6 - General Visual Inspection (GVI) for Any Ply Damage 1. Do a GVI of the elevator front spar around hinge numbers 4 and 6 for any ply damage. a. If no ply damage is found, repeat the GVI for any ply damage at the repeat interval given in Paragraph 1.E., Compliance. b. If any ply damage is found, Contact The Boeing Company for repair instructions and do the repair and repeat the GVI for any ply damage at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. Group 2-3: Work Package 5: Elevator Skin at Hinge Numbers 4 and 6 - Tap Test Inspection for Any Delamination 1. Do an Tap Test Inspection for any delamination. a. If no delamination is found, repeat the Tap Test Inspection for any delamination at the repeat interval given in Paragraph 1.E., Compliance. b. If any delamination is found that is within the structural repair manual repair limits, repair the delamination and repeat the Tap Test Inspection for any delamination at the repeat interval given in Paragraph 1.E., Compliance. c. If any delamination is found that is not within the structural repair manual repair limits, contact The Boeing Company for repair instructions and do the repair and repeat the Tap Test Inspection for any delamination at the unrepaired areas and areas in accordance with the structural repair manual at the repeat interval given in Paragraph 1.E., Compliance. Group 2, Configuration 2; Group 3: Work Package 6: Elevator Hinge Numbers 4 and 6 - Bearing Plate Replacement 1. Replace the bearing plates and do a bearing plate binding test at elevator hinge numbers 4 and 6 as follows: a. Remove the bearing plates and install new bearing plates. b. Do the elevator hinge bearing plate binding test at hinge numbers 4 and 6. (1) If the bearing plate binds, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment and repair any damage or misalignment. c. Repeat the bearing plate replacement and bearing plate binding test at elevator hinge numbers 4 and 6 at the repeat interval given in Paragraph 1.E., Compliance. Group 2, Configuration 2; Group 3: Work Package 7: Elevator Hinge Number 6 Fitting - High Frequency Eddy Current (HFEC) Inspection for Any Crack 1. Do an HFEC inspection of the elevator hinge number 6 fitting for any crack. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 13 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 14 a. If no crack is found, repeat the HFEC inspection of the elevator hinge number 6 fitting for any crack at the repeat interval given in Paragraph 1.E., Compliance. b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the elevator hinge number 6 fitting for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. Group 2-3: Work Package 8: Work at Elevator Hinge Numbers 3 and 5 1. Group 2, Configuration 2; Group 3: Do the elevator hinge bearing plate binding test at elevator hinge Numbers 3 and 5. a. If any bearing plate is bound, install a new bearing plate and repeat the bearing plate binding test at the affected location. (1) If the bearing plate is bound, contact The Boeing Company for work instructions and do the work. 2. Group 2-3: Do a Detailed Inspection of the attach plates and horizontal stabilizer hinge fitting for any damage. a. If any damage is found, repair the damage. EFFECTIVITY 737-100, -200, -200C, -300, -400, -500 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 inspection and 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 05, 2016 737-55A1099Revision 1: October 21, 2016 14 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 15 (OCR) BOEING SERVICE BULLETIN 737-55A1099 ALERT ALERT INSPECT FOR ANY INSPECT FOR ANY CORROSION AND ANY DELAMINATION AROUND CRACK AT HORIZONTAL HINGE NUMBERS 4 AND 6 STABILIZER REAR SPAR DO A BEARING PLATE BINDING TEST AND INSPECT FOR ANY DAMAGE AT HINGE NUMBERS 3 AND 5 FWD Original Issue: July 05, 2016 Revision 1: October 21, 2016 INSPECT FOR ANY LOOSE BOLT OR ANY CRACK OR ANY FRONT SPAR PLY DAMAGE AND REPLACE BEARING PLATES AT HINGE NUMBERS 4 AND 6 LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-55A1099 Work - See page 1 for details. 15 of 227 ### Page 16 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 16 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT BLANK PAGE ### Page 17 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-55A1099 Original Issue: July 05, 2016 Revision 1: October 21, 2016 ATA System: 5510 5520 SUBJECT: STABILIZERS - Horizontal Stabilizer - Elevator Hinge Numbers 3, 4, 5, and 6 Inspection and Repair 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 737-100, -200, -200C, -300, -400, -500 airplanes, line numbers 1-3132 in 3 Groups. The Variable Numbers and Group Information for the applicable airplanes is given below. Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 737-100, -200, -200C airplanes, line number 1-291.-1 737-200, -200C airplanes, line number 292 and on. These airplanes can have either fiberglass or graphite elevators installed. -2 Airplanes that have fiberglass elevators installed.1 Airplanes that have graphite elevators installed.2 737-300, -400, -500 airplanes. These airplanes have graphite elevators installed. -3 Airplane Models: 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 17 of 227 ### Page 18 GroupVariable Number 1PA001 - PA022 1PA099 1PA231 - PA232 1PC001 - PC005 1PG001 - PG075 1PG199 1PG201 - PG230 1PG251 - PG255 1PG271 - PG279 1PG301 - PG314 1PG331 - PG332 1PG351 - PG356 1PG375 1PG401 - PG403 1PG431 - PG442 1PG471 - PG475 1PG501 - PG505 1PG571 - PG583 2PG584 - PG586 1PG621 - PG630 1PG651 - PG652 1PG701 - PG705 2PH001 2PH011 - PH013 2PH021 - PH024 1PH701 - PH715 1PH731 - PH732 1PH741 - PH742 2PH743 1PJ001 - PJ002 2PJ003 - PJ009 1PJ031 - PJ032 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 18 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 19 GroupVariable Number 1PJ071 - PJ072 1PJ101 - PJ104 2PJ105 - PJ119 2PJ201 - PJ219 3PJ301 - PJ302 3PJ551 - PJ561 3PJ601 - PJ615 3PJ811 3PJ816 - PJ817 2PK026 - PK029 2PK041 - PK053 2PK061 - PK070 2PK081 - PK082 2PK091 - PK099 2PK101 - PK103 2PK111 - PK120 2PK141 - PK146 2PK201 - PK204 2PK211 - PK223 2PK231 - PK241 2PK251 - PK258 2PK271 - PK274 2PK281 - PK289 2PK291 2PK301 - PK318 2PK341 2PK351 - PK361 2PK391 2PK431 - PK433 2PK451 - PK452 2PK461 - PK469 2PK495 2PK501 - PK504 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 19 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 20 GroupVariable Number 2PK511 - PK515 2PK519 2PK521 - PK528 2PK541 - PK565 2PK581 2PK591 - PK599 2PK601 - PK617 2PK621 - PK637 2PK641 - PK642 2PK661 - PK666 2PK671 - PK681 2PK691 - PK697 2PK711 - PK716 2PK731 - PK765 2PK771 - PK779 2PK801 - PK804 2PK819 - PK827 2PK830 2PK861 - PK863 2PK871 - PK874 2PK881 - PK884 2PK901 - PK938 2PK971 - PK974 2PL001 - PL028 2PL061 2PL081 2PL101 - PL113 2PL151 2PL171 - PL172 2PL201 - PL203 2PL221 2PL401 - PL417 2PL421 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 20 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 21 GroupVariable Number 2PL441 2PL451 - PL456 2PL471 2PL491 2PL501 - PL506 2PL551 - PL562 2PL581 2PL601 - PL603 2PL611 2PL621 - PL626 2PL631 - PL632 1PL711 - PL712 1PL716 2PL717 - PL747 2PL756 2PL758 2PL761 - PL770 2PL781 - PL788 2PL793 1PL801 - PL803 2PM001 - PM006 2PM016 - PM017 2PM021 - PM023 2PM051 - PM066 2PM101 - PM119 2PM141 - PM142 2PM171 2PM181 2PM251 - PM255 2PM281 - PM283 3PM381 - PM399 3PM401 - PM417 3PM541 - PM564 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 21 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 22 GroupVariable Number 2PN001 - PN002 2PN021 - PN043 2PN081 - PN086 2PN101 - PN117 2PN131 - PN163 2PN401 - PN420 2PN431 - PN433 2PN451 - PN456 2PN471 - PN474 2PN481 2PN491 - PN493 2PN501 - PN502 2PN511 - PN512 2PN521 3PP001 - PP054 3PP101 - PP169 3PP181 - PP199 3PP201 - PP203 3PP205 3PP221 3PP231 - PP243 3PP281 - PP286 3PP301 - PP305 3PP351 - PP353 3PP376 - PP384 3PP391 - PP393 3PP401 - PP440 3PP471 - PP475 3PP501 - PP522 3PP631 - PP634 3PP651 - PP652 3PP671 - PP699 3PP701 - PP733 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 22 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 23 GroupVariable Number 3PP771 - PP779 3PP801 - PP808 3PP821 - PP827 3PP831 - PP848 3PP851 - PP852 3PP861 - PP877 3PP891 - PP899 3PP901 - PP936 3PP946 - PP948 3PP951 - PP952 3PP961 - PP967 3PP981 - PP991 3PP993 3PQ002 - PQ016 3PQ026 - PQ041 3PQ051 - PQ092 3PQ101 - PQ199 3PQ201 - PQ202 3PQ221 - PQ237 3PQ241 - PQ243 3PQ251 - PQ267 3PQ281 - PQ299 3PQ301 - PQ307 3PQ331 - PQ332 3PQ341 - PQ348 3PQ361 - PQ373 3PQ391 - PQ395 3PQ401 - PQ418 3PQ421 3PQ431 - PQ438 3PQ447 - PQ448 3PQ451 3PQ454 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 23 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 24 GroupVariable Number 3PQ471 - PQ475 3PQ479 - PQ481 3PQ486 - PQ487 3PQ491 - PQ493 3PQ771 - PQ772 3PQ791 - PQ793 3PQ801 - PQ805 3PQ931 - PQ935 3PQ951 3PQ971 - PQ997 3PR001 - PR017 3PR021 - PR034 3PR041 - PR045 3PR061 - PR072 3PR077 - PR082 3PR091 - PR092 3PR096 3PR101 3PR121 - PR122 3PR131 - PR132 3PR141 - PR143 3PR161 - PR172 3PR181 3PS601 - PS631 3PS636 - PS638 3PS641 - PS644 3PS651 - PS657 3PS666 - PS669 3PS691 - PS692 3PS701 - PS706 3PS751 - PS799 3PS811 3PS836 - PS837 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 24 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 25 GroupVariable Number 3PS841 - PS846 3PS851 - PS852 3PS856 3PS861 - PS863 3PS866 - PS868 3PS871 - PS874 3PS896 - PS897 3PS901 - PS941 3PS956 - PS957 3PS961 - PS963 3PS971 - PS978 3PT001 - PT015 3PT021 - PT031 3PT041 - PT064 3PT101 - PT105 3PT121 - PT138 3PT146 - PT148 3PT161 - PT170 3PT181 - PT188 3PT211 - PT220 3PT295 3PT301 - PT309 3PT331 - PT360 3PT381 - PT399 3PT401 - PT438 3PT501 - PT517 3PT561 - PT565 3PT581 - PT586 3PT611 - PT621 3PT641 - PT644 3PT651 - PT656 3PT671 - PT672 3PT681 - PT685 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 25 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 26 GroupVariable Number 3PT701 - PT703 3PT716 - PT717 3PT721 - PT725 3PT801 - PT834 3PT851 - PT854 3PT871 - PT886 3PT901 - PT930 3PT971 - PT973 3PT981 - PT985 3PT996 3PU001 - PU025 3PU301 3PU311 - PU313 3PV001 - PV055 3PV201 - PV209 3PV226 - PV229 3PV231 - PV237 3PV271 - PV272 3PV281 - PV287 3PV296 3PV301 - PV302 3PV351 3PV356 - PV357 3PW001 - PW054 3PW061 - PW068 3PW072 3PW086 - PW088 3PW091 - PW094 3PW101 - PW102 3PW106 3PW111 - PW120 3PW156 - PW157 3PW161 - PW171 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 26 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 27 GroupVariable Number 3PW201 - PW252 3PW261 - PW268 3PW271 - PW276 3PW278 3PW281 - PW293 3PW296 3PW301 - PW327 3PW401 - PW408 3PW411 - PW418 3PW421 - PW424 3PW431 - PW435 3PW441 - PW450 3PW461 - PW467 3PW501 - PW504 3PW511 - PW522 3PW524 - PW550 3PW556 - PW557 3PW561 - PW564 3PW571 - PW576 3PW591 - PW596 3PW611 - PW622 3PW631 - PW637 3PW661 - PW662 3PW681 - PW683 3PW701 - PW702 3PW711 - PW717 3PW741 - PW742 3PW761 3PW771 3PW831 3PW851 - PW856 1PX071 1PX701 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 27 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 28 GroupVariable Number 1PY001 - PY008 1PY021 2PY022 1PY031 2PY036 - PY037 2PY046 - PY048 2PY051 - PY053 2PY056 - PY057 2PY101 - PY103 2PY111 - PY113 2PY131 - PY135 2PY141 - PY143 2PY151 - PY154 2PY156 - PY157 2PY161 - PY162 2PY166 2PY191 2PY201 2PY221 - PY222 2PY231 2PY241 - PY244 2PY270 - PY275 2PY281 2PY286 1PY301 - PY304 1PY321 - PY323 1PY341 - PY346 1PY361 - PY362 1PY381 2PY401 2PY409 - PY411 2PY421 - PY422 2PY441 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 28 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 29 GroupVariable Number 2PY451 2PY461 - PY463 2PY591 - PY595 2PY611 - PY612 2PY621 2PY631 2PY651 2PY671 - PY672 2PY721 2PY741 2. Spares Affected Examine your spares supply for the parts or components identified below. If any parts or components are found, refer to Paragraph 3.B., Work Instructions for the recommended action. Group 2, Configuration 2; Group 3: Part NamePart Number Elevator Assembly and Tab Assembly65C25746-() Group 1; Group 2, Configuration 1: None. B. Concurrent Requirements None. C. Reason Following a special certification review for the 737-100, -200, -300, -400, -500 horizontal stabilizer, The Boeing Company determined through analysis that a disconnect of either elevator hinge number 4 or number 6 could result in flutter within the airplane flight envelope. As the horizontal stabilizer expands and contracts relative to the elevator, Teflon-lined sliding bearing plates at the elevator hinges are designed to adjust for the thermally-induced spanwise thrust loads. Wear and tight tolerancing of the Teflon-lined bearing plate slider bushings can cause binding of the sliding bearing plates. Binding of the sliding bearing plates causes the spanwise thrust loads to be absorbed by the elevator hinges, including the hinge support fittings on the horizontal stabilizer, which could lead to damage of the elevator hinge fitting and surrounding structure and cause a disconnect of the elevator hinge. Any crack, corrosion, delamination, or bolt looseness at the elevator hinges and surrounding structure could result in airplane vibration and damage. This service bulletin provides instructions to do repetitive inspections for any crack, corrosion, delamination, or bolt looseness at the elevator hinges and surrounding structure and provides instructions to do repetitive bearing plate replacements at the elevator hinges using an improved bearing plate. If the work in this service bulletin is not done, flutter resulting from disconnection of elevator hinge number 4 or number 6 could excite the horizontal stabilizer Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 29 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 30 under certain in-flight speed/altitude conditions and degradation of the structure due to tab flutter, hinge wear, spar chord corrosion, hinge rib web chafing, hinge rib chord cracking, and inspar lower skin cracking could result in heavy airplane vibration and damage, which could lead to departure of the elevator and/or horizontal stabilizer from the airplane. This will lead to loss of continued safe flight and landing. To date, there have been no reports of an in-flight disconnection of either elevator hinge number 4 or number 6, but there have been multiple reports of wear induced vibration that validates the analysis findings of The Boeing Company. In addition, The Boeing Company has received one report of a disconnected joint found during maintenance with no report of in-flight vibration. These reports indicate that the level of structural stiffness and redundancy may not preclude failure at elevator hinge number 4 or hinge number 6 if appropriate maintenance and repair procedures are not followed. Boeing has received 15 reports of out-of-round hinge support fitting holes caused by loose attach plate bolts on the horizontal stabilizer. Of the 15 reports received, 11 hinge support fittings required repair at the number 6 location, 3 required repair at the number 5 location, and 1 required repair at the number 4 location. Repairs have occurred on both the left and right side stabilizers. The elongation of the hinge support fitting holes has been found on airplanes ranging from 3,370 hours to 18,050 hours and 2,860 flight cycles to 15,915 flight cycles. This service bulletin supersedes service bulletin 737-55-1054, which gives instructions to inspect, repair, or replace the elevator hinge support fitting, attach plates, and sliding bearing plate assembly at elevator hinge numbers 3, 4, 5, and 6. Boeing Service Related Problem (SRP) 737-55-0032 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737 FTD 55-03002 is related to this service bulletin. Revision 1 is sent to update the effectivity of this service bulletin to include additional airplanes. D. Description Group 1: Boeing endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplane upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Line numbers 1-291 have accumulated flight cycles beyond the LOV of the airplane. 14 Code of Federal Regulations (CFR) Part 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV. Group 2-3: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection for Any Crack and Loose Bolt Check 1. Do an HFEC inspection of the elevator hinge fittings for any crack. a. If no crack is found, repeat the HFEC inspection of the elevator hinge fittings for any crack at the repeat interval given in Paragraph 1.E., Compliance. b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the elevator hinge fittings for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 30 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 31 2. Do a loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt. a. If no loose bolt is found, repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. b. Group 2, Configuration 2; Group 3: If any loose slider bolt is found, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment, repair any damage or misalignment, and repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. c. If any loose hinge fitting attachment fastener is found, remove and replace the fastener with a new or serviceable fastener and repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. d. If any loose elevator hinge bolt is found, do the following: (1) Do a detailed inspection of the attach plates and horizontal stabilizer hinge fitting for any damage at the affected location and repair any damage (2) Group 2, Configuration 2; Group 3: Do the elevator hinge bearing plate binding test at the affected hinge location. (a) If the bearing plate binds, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment and repair any damage or misalignment. (b) If the bearing plate does not bind, do a detailed inspection of the bearing plate bearing for any damage and replace the bearing plate if any damage is found. (3) Repeat the loose bolt check at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance Group 2-3: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check 1. Do an HFEC inspection of the attach plates for any crack. a. If no crack is found, repeat the HFEC inspection of the attach plates for any crack at the repeat interval given in Paragraph 1.E., Compliance. b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the attach plates for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. 2. Do an HFEC inspection and LFEC inspection of the gusset plates and horizontal stabilizer inspar skin fastener locations for any crack. a. If no crack is found, repeat the HFEC inspection and LFEC inspection of the gusset plates and horizontal stabilizer inspar skin fastener locations for any crack at the repeat interval given in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 31 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 32 b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the attach plates for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. 3. Do a loose bolt check of the attach plate bolts at elevator hinge numbers 4 and 6 for any loose bolt. a. If no loose bolt is found, repeat the loose bolt check of the attach plate bolts at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance. b. If any loose bolt is found, do the following: (1) Do a detailed inspection of the attach plates and horizontal stabilizer hinge fitting for any damage at the affected location and repair any damage. (2) Group 2, Configuration 2; Group 3: Do the elevator hinge bearing plate binding test at the affected hinge location. (a) If the bearing plate binds, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment and repair any damage or misalignment. (b) If the bearing plate does not bind, do a detailed inspection of the bearing plate bearing for any damage and replace the bearing plate if any damage is found. (3) Repeat the loose bolt check of the attach plate bolts at elevator hinge numbers 4 and 6 for any loose bolt at the repeat interval given in Paragraph 1.E., Compliance Group 2-3: Work Package 3: Horizontal Stabilizer Rear Spar, Gusset Plate, and Inspar Skin Forward of Elevator Hinge Numbers 4 and 6 - Detailed Inspection for Any Corrosion 1. Do a detailed inspection of the horizontal stabilizer rear spar outer mold line for any corrosion. a. If no corrosion is found, repeat the detailed inspection for any corrosion at the repeat interval given in Paragraph 1.E., Compliance. b. If any corrosion is found that is within the structural repair manual repair limits, repair the corrosion and repeat the detailed inspection for any corrosion at the repeat interval given in Paragraph 1.E., Compliance. c. If any corrosion is found that is not within the structural repair manual repair limits, contact The Boeing Company for repair instructions and do the repair and repeat the detailed inspection for any corrosion at the unrepair areas and areas repaired in accordance with the structural repair manual at repeat interval given in Paragraph 1.E., Compliance. Group 2, Configuration 2; Group 3: Work Package 4: Elevator Front Spar at Hinge Numbers 4 and 6 - General Visual Inspection (GVI) for Any Ply Damage 1. Do a GVI of the elevator front spar around hinge numbers 4 and 6 for any ply damage. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 32 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 33 a. If no ply damage is found, repeat the GVI for any ply damage at the repeat interval given in Paragraph 1.E., Compliance. b. If any ply damage is found, Contact The Boeing Company for repair instructions and do the repair and repeat the GVI for any ply damage at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. Group 2-3: Work Package 5: Elevator Skin at Hinge Numbers 4 and 6 - Tap Test Inspection for Any Delamination 1. Do an Tap Test Inspection for any delamination. a. If no delamination is found, repeat the Tap Test Inspection for any delamination at the repeat interval given in Paragraph 1.E., Compliance. b. If any delamination is found that is within the structural repair manual repair limits, repair the delamination and repeat the Tap Test Inspection for any delamination at the repeat interval given in Paragraph 1.E., Compliance. c. If any delamination is found that is not within the structural repair manual repair limits, contact The Boeing Company for repair instructions and do the repair and repeat the Tap Test Inspection for any delamination at the unrepaired areas and areas in accordance with the structural repair manual at the repeat interval given in Paragraph 1.E., Compliance. Group 2, Configuration 2; Group 3: Work Package 6: Elevator Hinge Numbers 4 and 6 - Bearing Plate Replacement 1. Replace the bearing plates and do a bearing plate binding test at elevator hinge numbers 4 and 6 as follows: a. Remove the bearing plates and install new bearing plates. b. Do the elevator hinge bearing plate binding test at hinge numbers 4 and 6. (1) If the bearing plate binds, do a detailed inspection and measurement of the hinge fitting assembly at the affected location for any damage or misalignment and repair any damage or misalignment. c. Repeat the bearing plate replacement and bearing plate binding test at elevator hinge numbers 4 and 6 at the repeat interval given in Paragraph 1.E., Compliance. Group 2, Configuration 2; Group 3: Work Package 7: Elevator Hinge Number 6 Fitting - High Frequency Eddy Current (HFEC) Inspection for Any Crack 1. Do an HFEC inspection of the elevator hinge number 6 fitting for any crack. a. If no crack is found, repeat the HFEC inspection of the elevator hinge number 6 fitting for any crack at the repeat interval given in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 33 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 34 b. If any crack is found, Contact The Boeing Company for repair instructions and do the repair and repeat the HFEC inspection of the elevator hinge number 6 fitting for any crack at the unrepaired areas at the repeat interval given in Paragraph 1.E., Compliance. Group 2-3: Work Package 8: Work at Elevator Hinge Numbers 3 and 5 1. Group 2, Configuration 2; Group 3: Do the elevator hinge bearing plate binding test at elevator hinge Numbers 3 and 5. a. If any bearing plate is bound, install a new bearing plate and repeat the bearing plate binding test at the affected location. (1) If the bearing plate is bound, contact The Boeing Company for work instructions and do the work. 2. Group 2-3: Do a Detailed Inspection of the attach plates and horizontal stabilizer hinge fitting for any damage. a. If any damage is found, repair the damage. Effects of this Revision on airplanes on which Original Issue was previously done: None. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 7-9, 7-10, 7-11, 7-12737-100, 737-200, 737-200C Group 2: Affected Maintenance Zones ZoneModel 7-9, 7-10, 7-11, 7-12737-200, 737-200C Group 3: Affected Maintenance Zones ZoneModel 709, 710, 711, 712737-300, 737-400, 737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 34 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 35 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. 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. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. Logic diagrams showing compliance tasks and compliance times are included as aids in Appendices A through M. Logic diagrams are provided as an aid only. Group 1: Boeing endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplane upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Line numbers 1-291 have accumulated flight cycles beyond the LOV of the airplane. 14 Code of Federal Regulations (CFR) Part 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV. Group 2-3: No compliance time is given for Work Package 8: Work at Elevator Hinge Number 3 and 5. Group 2-3: The table that follows immediately below describes the service bulletin PARTS noted in the compliance tables. Group 2-3: DescriptionTitle ELEVATOR HINGE NUMBERS 4 AND 6 - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION PART 2 ELEVATOR HINGE NUMBERS 4 AND 6 - LOOSE BOLT CHECKPART 3 HORIZONTAL STABILIZER FORWARD OF ELEVATOR HINGE NUMBERS 4 AND 6 - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION PART 4 HORIZONTAL STABILIZER ATTACH PLATES AT ELEVATOR HINGE NUMBERS 4 AND 6 - LOOSE BOLT CHECK PART 5 ELEVATOR HINGE FITTING AND BEARING PLATE AT HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION AND MEASUREMENT PART 6 ELEVATOR HINGE FITTING - BUSHING REPLACEMENTPART 7 ATTACH PLATE AND HORIZONTAL STABILIZER AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION PART 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 35 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 36 Group 2, Configuration 1: Table 1: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) In- spection for Any Crack and Loose Bolt Check Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 27 months after the original issue date of this Ser- vice Bulletin Within 7,000 ele- vator assembly flight cycles af- ter the original issue date of this Service Bul- letin ACTION 1: Do PART 2 for any crack. All airplanes ACTION 2: Do PART 3 for any loose bolt. 4,500 elevator as- sembly flight cycles --Repeat PART 2 for any crack. CONDITION 1: NO CRACK FOUND --Before further flight ACTION 1: Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 2: ANY CRACK FOUND 4,500 elevator as- sembly flight cycles --ACTION 2: Repeat PART 2 for any crack at the un- repaired areas. 4,500 elevator as- sembly flight cycles --Repeat PART 3 for any loose bolt. CONDITION 3: NO LOOSE BOLT FOUND --Before further flight ACTION 1: Remove the bolt and replace with a new or serviceable bolt. CONDITION 5: ANY LOOSE HINGE FITTING ATTACHMENT BOLT FOUND 4,500 elevator as- sembly flight cycles --ACTION 2: Repeat PART 3 for any loose bolt. --Before further flight ACTION 1: Do PART 8 for any damage. (a) CONDITION 6: ANY LOOSE ELEVATOR HINGE BOLT FOUND 4,500 elevator as- sembly flight cycles --ACTION 2: Repeat PART 3 for any loose bolt. (a) See Table 13 for resulting conditions and corrective actions. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 36 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 37 Group 2, Configuration 2; Group 3: Table 2: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) In- spection for Any Crack and Loose Bolt Check Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 27 months after the original issue date of this Ser- vice Bulletin Within 7,000 ele- vator assembly flight cycles af- ter the original issue date of this Service Bul- letin ACTION 1: Do PART 2 for any crack. All airplanes ACTION 2: Do PART 3 for any loose bolt. 4,500 elevator as- sembly flight cycles --Repeat PART 2 for any crack. CONDITION 1: NO CRACK FOUND --Before further flight ACTION 1: Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 2: ANY CRACK FOUND 4,500 elevator as- sembly flight cycles --ACTION 2: Repeat PART 2 for any crack at the un- repaired hinge locations. 4,500 elevator as- sembly flight cycles --Repeat PART 3 for any loose bolt. CONDITION 3: NO LOOSE BOLT FOUND --Before further flight ACTION 1: Do PART 6 for any damage or mis- alignment. (a) CONDITION 4: ANY LOOSE SLIDER BOLT FOUND 4,500 elevator as- sembly flight cycles --ACTION 2: Repeat PART 3 for any loose bolt. --Before further flight ACTION 1: Remove the bolt and collar and re- place with a new or ser- viceable bolt and collar. CONDITION 5: ANY LOOSE HINGE FITTING ATTACHMENT BOLT FOUND 4,500 elevator as- sembly flight cycles --ACTION 2: Repeat PART 3 for any loose bolt. --Before further flight ACTION 1: Do PART 8 for any bearing plate binding and any damage. (b) CONDITION 6: ANY LOOSE ELEVATOR HINGE BOLT FOUND 4,500 elevator as- sembly flight cycles --ACTION 2: Repeat PART 3 for any damage. (a) See Table 10 for resulting conditions and corrective actions. (b) See Table 12 for resulting conditions and corrective actions. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 37 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 38 Group 2, Configuration 1: Table 3: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 27 months after the original issue date of this Ser- vice Bulletin Within 7,000 horizontal stabi- lizer assembly flight cycles af- ter the original issue date of this Service Bul- letin ACTION 1: Do PART 4 for any crack. All airplanes ACTION 2: Do PART 5 for any loose bolt. 4,500 horizontal stabilizer assembly flight cycles --Repeat PART 4 for any crack. CONDITION 7: NO CRACK FOUND --Before further flight ACTION 1: Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 8: ANY CRACK FOUND 4,500 horizontal stabilizer assembly flight cycles --ACTION 2: Repeat PART 4 for any crack at the un- repaired areas. 4,500 horizontal stabilizer assembly flight cycles --Repeat PART 5 for any loose bolt. CONDITION 9: NO LOOSE BOLT FOUND --Before further flight ACTION 1: Do PART 8 for any damage. (a) CONDITION 10: ANY LOOSE BOLT FOUND 4,500 horizontal stabilizer assembly flight cycles --ACTION 2: Repeat PART 5 for any loose bolt. (a) See Table 13 for resulting conditions and corrective actions. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 38 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 39 Group 2, Configuration 2; Group 3: Table 4: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 27 months after the original issue date of this Ser- vice Bulletin Within 7,000 horizontal stabi- lizer assembly flight cycles af- ter the original issue date of this Service Bul- letin ACTION 1: Do PART 4 for any crack. All airplanes ACTION 2: Do PART 5 for any loose bolt. 4,500 horizontal stabilizer assembly flight cycles --Repeat PART 4 for any crack. CONDITION 7: NO CRACK FOUND --Before further flight ACTION 1: Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 8: ANY CRACK FOUND 4,500 horizontal stabilizer assembly flight cycles --ACTION 2: Repeat PART 4 for any crack at the un- repaired areas. 4,500 horizontal stabilizer assembly flight cycles --Repeat PART 5 for any loose bolt. CONDITION 9: NO LOOSE BOLT FOUND --Before further flight ACTION 1: Do PART 8 for any bearing plate binding or any damage. (a) CONDITION 10: ANY LOOSE BOLT FOUND 4,500 horizontal stabilizer assembly flight cycles --ACTION 2: Repeat PART 5 for any loose bolt. (a) See Table 12 for resulting conditions and corrective actions. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 39 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 40 Group 2-3: Table 5: Work Package 3: Horizontal Stabilizer Rear Spar, Gusset Plate, and Inspar Skin Forward of El- evator Hinge Numbers 4 and 6 - Detailed Inspection for Any Corrosion Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 27 months after the original issue date of this Ser- vice Bulletin Within 7,000 horizontal stabi- lizer assembly flight cycles af- ter the original issue date of this Service Bul- letin Do a Detailed Inspection of the horizontal stabilizer rear spar outer mold line, gusset plate, and inspar skin for any corrosion. All airplanes 24 months--Repeat the Detailed In- spection of the horizontal stabilizer rear spar outer mold line, gusset plate, and inspar skin for any corrosion. CONDITION 11: NO COR- ROSION FOUND --Before further flight ACTION 1: Repair the corrosion. CONDITION 12: ANY CORROSION FOUND ON SKIN OR GUSSET - WITHIN STRUCTURAL REPAIR MANUAL REPAIR LIMITS 24 months--ACTION 2: Repeat the Detailed Inspection of the horizontal stabilizer rear spar outer mold line, gus- set plate, and inspar skin for any corrosion. --Before further flight ACTION 1: Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 13: ANY CORROSION FOUND ON SKIN OR GUSSET - NOT WITHIN STRUCTURAL REPAIR MANUAL REPAIR LIMITS OR ANY CORRO- SION FOUND ON HORI- ZONTAL STABILIZER REAR SPAR OUTER MOLD LINE 24 months--ACTION 2: Repeat the Detailed Inspection of the horizontal stabilizer rear spar outer mold line, gus- set plate, and inspar skin for any corrosion at the unrepaired areas and ar- eas repaired in accor- dance with 737-100/200 Structural Repair Manual or 737-300/400/500 Structural Repair Manual. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 40 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 41 Group 2, Configuration 2; Group 3: Table 6: Work Package 4: Elevator Front Spar at Hinge Numbers 4 and 6 - General Visual Inspection (GVI) for Any Ply Damage Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 27 months after the original issue date of this Ser- vice Bulletin Within 7,000 ele- vator assembly flight cycles af- ter the original issue date of this Service Bul- letin Do a GVI of the elevator front spar around hinge numbers 4 and 6 for any ply damage. All airplanes 4,500 elevator as- sembly flight cycles or 36 months, whichever occurs first --Repeat the GVI of the el- evator front spar around hinge numbers 4 and 6 for any ply damage. CONDITION 14: NO PLY DAMAGE FOUND --Before further flight ACTION 1: Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 15: ANY PLY DAMAGE FOUND 4,500 elevator as- sembly flight cycles or 36 months, whichever occurs first --ACTION 2: Repeat the GVI of the elevator front spar around hinge num- bers 4 and 6 for any ply damage at the unrepaired areas. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 41 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 42 Group 2-3: Table 7: Work Package 5: Elevator Skin at Hinge Numbers 4 and 6 - Tap Test Inspection for Any Delam- ination Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 27 months after the original issue date of this Ser- vice Bulletin Within 7,000 ele- vator assembly flight cycles af- ter the original issue date of this Service Bul- letin Do a Tap Test Inspection of the elevator skin for any delamination. All airplanes 4,500 elevator as- sembly flight cycles or 36 months, whichever occurs first --Repeat the Tap Test In- spection of the elevator skin for any delamination. CONDITION 16: NO DE- LAMINATION FOUND --Before further flight ACTION 1: Repair the delamination. CONDITION 17: ANY DE- LAMINATION FOUND - WITHIN STRUCTURAL REPAIR MANUAL REPAIR LIMITS 4,500 elevator as- sembly flight cycles or 36 months, whichever occurs first --ACTION 2: Repeat the Tap Test Inspection of the elevator skin for any delamination. --Before further flight ACTION 1: Contact The Boeing Company for re- pair instructions and do the repair. CONDITION 18: ANY DE- LAMINATION FOUND - NOT WITHIN STRUC- TURAL REPAIR MANUAL REPAIR LIMITS 4,500 elevator as- sembly flight cycles or 36 months, whichever occurs first --ACTION 2: Repeat the Tap Test Inspection of the elevator skin for any delamination at the unre- paired areas and areas repaired in accordance with 737-100/200 Struc- tural Repair Manual (SRM) 55-20-03 or 737- 300/400/500 Structural Repair Manual (SRM) 55- 20-01. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 42 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 43 Group 2, Configuration 2; Group 3: Table 8: Work Package 6: Elevator Hinge Numbers 4 and 6 - Bearing Plate Replacement Repeat Interval (Not to Exceed) Compliance Time ActionCondition -Within 18,000 bearing plate flight cycles af- ter the original issue date of this Service Bul- letin ACTION 1: Replace the bearing plates at elevator hinge numbers 4 and 6. All airplanes ACTION 2: Do the elevator hinge bearing plate binding test at hinge numbers 4 and 6 18,000 total bear- ing plate flight cy- cles -ACTION 1: Repeat the bearing plate re- placement at elevator hinge numbers 4 and 6. CONDITION 19: NO BEARING PLATE BIND- ING ACTION 2: Repeat the elevator hinge bearing plate binding test at hinge numbers 4 and 6 -Before further flight ACTION 1: Do PART 6 for any damage or misalignment. (a) CONDITION 20: BEARING PLATE BINDING 18,000 total bear- ing plate flight cy- cles -ACTION 2: Repeat the bearing plate re- placement at elevator hinge numbers 4 and 6. ACTION 3: Repeat the elevator hinge bearing plate binding test at hinge numbers 4 and 6 (a) See Table 10 for resulting conditions and corrective actions. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 43 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 44 Group 2, Configuration 2; Group 3: Table 9: Work Package 7: Elevator Hinge Number 6 Fitting - High Frequency Eddy Current (HFEC) In- spection for Any Crack Repeat Interval (Not to Exceed) Compliance Time ActionCondition -Within 18,000 elevator assem- bly flight cycles after the original issue date of this Service Bul- letin If elevator hinge fitting assembly 65C31307-() is installed at elevator hinge number 6, do an HFEC inspection of the hinge fitting for any crack. All airplanes with elevator hinge fitting assembly 65C31307-() installed at elevator hinge number 6 18,000 elevator assembly flight cy- cles -Repeat the HFEC inspection of the hinge fitting at elevator hinge number 6 for any crack. CONDITION 21: NO CRACK FOUND -Before further flight ACTION 1: Contact The Boeing Company for repair instructions and do the repair. CONDITION 22: ANY CRACK FOUND 18,000 elevator assembly flight cy- cles -ACTION 2: Repeat the HFEC inspection of the hinge fitting at elevator hinge number 6 for any crack at the unrepaired hinge fit- tings. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 44 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 45 Group 2, Configuration 2; Group 3: Table 10: PART 6: ELEVATOR HINGE FITTING AND BEARING PLATE AT HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION AND MEASUREMENT - Resulting Conditions and Corrective Actions Repeat Interval (Not to Exceed) Compliance Time ActionCondition --No corrective action required.CONDITION 23: NO SLID- ER BUSHING OR SLIDER BOLT DAMAGE FOUND -Before further flight Replace with a new or serviceable part.CONDITION 24: ANY SLIDER BUSHING OR SLIDER BOLT DAMAGE FOUND -Before further flight OPTION 1: Replace the bearing plate bushings. CONDITION 25: NO BEARING PLATE BEAR- ING DAMAGE FOUND OPTION 2: Install a new or serviceable bearing plate at the affected location. -Before further flight Install a new or serviceable bearing plate at the affected location. CONDITION 26: ANY BEARING PLATE BEAR- ING DAMAGE FOUND -Before further flight ACTION 1: Install a new or serviceable bearing plate at the affected location. CONDITION 27: NO ELE- VATOR HINGE FITTING BUSHING DAMAGE OR MISALIGNMENT FOUND -Before furtherflightACTION 2: Do the elevator hinge bearingplate binding test at the affected location. --No corrective action required.CONDITION 27.1: NO BEARING PLATE BIND- ING -Before further flight OPTION 1: Do PART 6 for any damage or misalignment at the affected location. CONDITION 27.2: BEAR- ING PLATE BINDING -Before further flight OPTION 2: Contact The Boeing Company for repair instructions and do the repair. -Before further flight ACTION 1: Do PART 7. (a)CONDITION 28: ANY ELE- VATOR HINGE FITTING BUSHING DAMAGE OR MISALIGNMENT FOUND -Before furtherflightACTION 2: Install a new or serviceablebearing plate at the affected location. -Before further flight ACTION 3: Do the elevator hinge bearing plate binding test at the affected location. --No corrective action required.CONDITION 28.1: NO BEARING PLATE BIND- ING -Before further flight OPTION 1: Do PART 6 for any damage or misalignment. CONDITION 28.2: BEAR- ING PLATE BINDING -Before furtherOPTION 2: Contact The Boeing Company Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 45 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 46 Group 2, Configuration 2; Group 3: Table 10: PART 6: ELEVATOR HINGE FITTING AND BEARING PLATE AT HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION AND MEASUREMENT - Resulting Conditions and Corrective Actions Repeat Interval (Not to Exceed) Compliance Time ActionCondition flightfor repair instructions and do the repair. (a) See Table 11 for resulting conditions and corrective actions. Group 2, Configuration 2; Group 3: Table 11: PART 7: ELEVATOR HINGE FITTING - BUSHING REPLACEMENT - Resulting Conditions and Corrective Actions Repeat Interval (Not to Exceed) Compliance Time ActionCondition -Before further flight ACTION 1: Hone the bore to a 63 microinch surface finish. CONDITION 29: NO CRACK OR DAMAGE FOUND -Before further flight ACTION 2: Measure the bore at the affect- ed location for any oversize condition and make sure that the bores are not mis- aligned. -Before further flight Install a new bushing at the affected loca- tion. CONDITION 29.1: NO BORE MISALIGNMENT OR OVERSIZE CONDI- TION FOUND -Before further flight Replace the hinge fitting with a new or ser- viceable hinge fitting at the affected loca- tion. CONDITION 29.2: ANY BORE MISALIGNMENT OR OVERSIZE CONDI- TION FOUND -Before further flight OPTION 1: Replace the hinge fitting with a new or serviceable hinge fitting at the affect- ed location. CONDITION 30: ANY CRACK OR DAMAGE FOUND -Before further flight OPTION 2: Contact The Boeing Company for repair instructions and do the repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 46 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 47 Group 2, Configuration 2; Group 3: Table 12: PART 8: ATTACH PLATE AND HORIZONTAL STABILIZER AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION - Resulting Conditions and Corrective Actions Repeat Interval (Not to Exceed) Compliance Time ActionCondition --No corrective action required.CONDITION 31: NO DAM- AGE FOUND -Before further flight Repair the damage at the affected location.CONDITION 32: ANY DAMAGE FOUND -Before further flight Do a Detailed Inspection of the bearing plate bearing for any damage. CONDITION 33: NO BEARING PLATE BIND- ING --No corrective action required.CONDITION 33.1: NO BEARING PLATE BEAR- ING DAMAGE FOUND -Before further flight Replace the bearing plate at the affected location. CONDITION 33.2: ANY BEARING PLATE BEAR- ING DAMAGE FOUND -Before further flight Do PART 6 for any damage or misalign- ment. (a) CONDITION 34: BEARING PLATE BINDING (a) See Table 10 for resulting conditions and corrective actions. Group 2, Configuration 1: Table 13: PART 8: ATTACH PLATE AND HORIZONTAL STABILIZER AT ELEVATOR HINGE NUMBERS 4 AND 6 - DETAILED INSPECTION - Resulting Conditions and Corrective Actions Repeat Interval (Not to Exceed) Compliance Time ActionCondition --No corrective action required.CONDITION 31: NO DAM- AGE FOUND -Before further flight Repair the damage at the affected location.CONDITION 32: ANY DAMAGE FOUND --No corrective action required.CONDITION 35: NO ELE- VATOR HINGE FITTING BEARING DAMAGE FOUND -Before further flight OPTION 1: Replace the damaged elevator hinge fitting bearing. CONDITION 36: ANY ELE- VATOR HINGE FITTING BEARING DAMAGE FOUND -Before furtherflightOPTION 2: Replace the elevator hinge fit-ting assembly at the affected location. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 47 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 48 in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The tables below show an estimate of the task hours necessary to do the required inspections and conditional repairs for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. Group 1: None. Group 2, Configuration 2; Group 3: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) In- spection for Any Crack and Loose Bolt Check Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 9.309.301FIGURE 2 1.001.001FIGURE 3 1.001.001FIGURE 5 1.501.501Restoration 14.3014.30TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 48 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 49 Group 2, Configuration 2; Group 3: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) In- spection for Any Crack and Loose Bolt Check - Conditional Inspections and Repairs Elapsed HoursTask HoursNumber of PersonsTask 2.002.001FIGURE 14 3.003.001FIGURE 16 2.002.001FIGURE 17 4.004.001FIGURE 18 2.002.001FIGURE 19 3.003.001FIGURE 20 3.003.001FIGURE 21 3.003.001FIGURE 22 2.002.001FIGURE 23 4.004.001FIGURE 29 28.0028.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 1: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) In- spection for Any Crack and Loose Bolt Check Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 6.106.101FIGURE 1 1.001.001FIGURE 4 1.501.501Restoration 10.1010.10TOTAL FOR EACH AIRPLANE Group 2, Configuration 1: Work Package 1: Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) In- spection for Any Crack and Loose Bolt Check - Conditional Inspections and Repairs Elapsed HoursTask HoursNumber of PersonsTask 3.003.001FIGURE 20 3.003.001FIGURE 21 3.003.001FIGURE 22 2.002.001FIGURE 23 11.0011.00TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 49 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 50 Group 2: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 6.106.101FIGURE 6 2.002.001FIGURE 8 1.001.001FIGURE 9 1.501.501Restoration 12.1012.10TOTAL FOR EACH AIRPLANE Group 3: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 6.106.101FIGURE 6 2.002.001FIGURE 7 1.001.001FIGURE 9 1.501.501Restoration 12.1012.10TOTAL FOR EACH AIRPLANE Group 2, Configuration 2; Group 3: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check - Conditional Inspections and Repairs Elapsed HoursTask HoursNumber of PersonsTask 2.002.001FIGURE 14 3.003.001FIGURE 16 2.002.001FIGURE 17 4.004.001FIGURE 18 2.002.001FIGURE 19 3.003.001FIGURE 20 3.003.001FIGURE 21 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 50 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 51 Group 2, Configuration 2; Group 3: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check - Conditional Inspections and Repairs Elapsed HoursTask HoursNumber of PersonsTask 3.003.001FIGURE 22 2.002.001FIGURE 23 4.004.001FIGURE 29 28.0028.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 1: Work Package 2: Horizontal Stabilizer at Elevator Hinge Numbers 4 and 6 - High Frequency Eddy Current (HFEC) Inspection and Low Frequency Eddy Current (LFEC) Inspection for Any Crack and Loose Bolt Check - Conditional Inspections and Repairs Elapsed HoursTask HoursNumber of PersonsTask 3.003.001FIGURE 20 3.003.001FIGURE 21 3.003.001FIGURE 22 2.002.001FIGURE 23 11.0011.00TOTAL FOR EACH AIRPLANE Group 2-3: Work Package 3: Horizontal Stabilizer Rear Spar, Gusset Plate, and Inspar Skin at Elevator Hinge Numbers 4 and 6 - Detailed Inspection for Any Corrosion Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 2.002.001FIGURE 10 1.501.501Restoration 5.005.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 2; Group 3: Work Package 4: Elevator Front Spar at Hinge Numbers 4 and 6 - General Visual Inspection (GVI) for Any Ply Damage Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 0.500.501FIGURE 11 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 51 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 52 Group 2, Configuration 2; Group 3: Work Package 4: Elevator Front Spar at Hinge Numbers 4 and 6 - General Visual Inspection (GVI) for Any Ply Damage Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Restoration 3.503.50TOTAL FOR EACH AIRPLANE Group 2-3: Work Package 5: Elevator Skin at Hinge Numbers 4 and 6 - Tap Test Inspection for Any Delam- ination Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 2.502.501FIGURE 12 1.501.501Restoration 5.505.50TOTAL FOR EACH AIRPLANE Group 2, Configuration 2; Group 3: Work Package 6: Elevator Hinge Numbers 4 and 6 - Bearing Plate Replacement Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 2.002.001FIGURE 13 2.002.001FIGURE 14 3.003.001FIGURE 16 2.002.001FIGURE 17 4.004.001FIGURE 18 4.004.001FIGURE 29 1.501.501Restoration 20.0020.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 2; Group 3: Work Package 7: Elevator Hinge Number 6 Fitting - High Frequency Eddy Current (HFEC) In- spection for Any Crack Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 52 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 53 Group 2, Configuration 2; Group 3: Work Package 7: Elevator Hinge Number 6 Fitting - High Frequency Eddy Current (HFEC) In- spection for Any Crack Elapsed HoursTask HoursNumber of PersonsTask 2.002.001FIGURE 15 1.501.501Restoration 5.005.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 2; Group 3: Work Package 8: Work at Elevator Hinge Numbers 3 and 5 Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 2.002.001FIGURE 14 3.003.001FIGURE 24 2.002.001FIGURE 25 3.003.001FIGURE 26 3.003.001FIGURE 27 2.002.001FIGURE 28 1.501.501Restoration 18.0018.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 1: Work Package 8: Work at Elevator Hinge Numbers 3 and 5 Elapsed HoursTask HoursNumber of PersonsTask 1.501.501Preparation and Ac- cess 3.003.001FIGURE 24 3.003.001FIGURE 26 3.003.001FIGURE 27 2.002.001FIGURE 28 1.501.501Restoration 14.0014.00TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 53 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 54 H. Weight and Balance Changes Weight and Balance changes affected by incorporation of this service bulletin are dependent on the type, number and location of repairs done on each particular airplane. Weight and Balance are to be calculated by the operator by weighing parts installed or removed. Operators should make necessary revisions to the appropriate weight and balance report. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Bulletin 737-55-1054 b. Boeing Service Related Problem (SRP) 737-55-0032 c. Component Maintenance Manual (CMM) 55-20-10, 55-20-16 d. Service Bulletin Index D6-19567 e. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-01, 20-50-03, 20-50-18, 20-50-19 f. 737 Fleet Team Digest (FTD) 55-03002 g. 737 Non-Destructive Testing (NDT) Manual Part 1, 51-05-01, Part 6, 51-00-00, Procedure 23, Part 6, 55-10-64, Part 6, 55-10-65 h. 737-100/200 Aircraft Maintenance Manual (AMM) 27-31-00, 27-31-11 i. 737-200 Maintenance Planning Data (MPD) Section 1 j. 737-300/400/500 Aircraft Maintenance Manual (AMM) 27-31-00, 27-31-11 k. 737-300/400/500 Maintenance Planning Data (MPD) Section 4 l. 737-100/200 SRM 51-20-01, 55-10-03, 55-10-04, 55-20-03 m. 737-300 SRM 51-30-01, 55-10-01, 55-10-09, 55-20-01 n. 737-400 SRM 51-30-01, 55-10-01, 55-10-09, 55-20-01 o. 737-500 SRM 51-30-01, 55-10-01, 55-10-09, 55-20-01 2. Data Supplied with this Service Bulletin: None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 54 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 55 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Front Spar Installation, Elevator65C25756 Rib Installation, Hinge Support, Elevator Station 66.54, Stabilizer65-47526 Rib Installation, Hinge Support, Elevator Station 121.59, Stabilizer65-47528 Rib Installation, Hinge Support, Elevator Station 176.64, Stabilizer65-47530 Rib Installation, Hinge Support, Elevator Station 213.32, Stabilizer65-47522 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-SectionPublication Part 6, 55-10-64Non-Destructive Testing Manual Part 6, 55-10-65 55-20-16Component Maintenance Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance. Any rework that will require Boeing contact for an approved repair plan will, accordingly, require a Damage Tolerance Evaluation. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 55 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 56 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 56 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT BLANK PAGE ### Page 57 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 Group 2, Configuration 1: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) NamePart Number $214.81197Attach Plate (Hinge Numbers 3 and 4)69-56027-1 $200.00186Attach Plate (Hinge Numbers 5 and 6)69-56027-3 $948.00(a)Hinge Fitting Assembly69-40300-1 (a) ROLT currently unavailable and to be provided at a later date. Group 2, Configuration 2; Group 3: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) NamePart Number $214.81197Attach Plate (Hinge Numbers 3 and 4)69-56027-1 $200.00186Attach Plate (Hinge Numbers 5 and 6)69-56027-3 $1,215.0099Bearing Plate Assembly (Hinge Numbers 3 and 4) 65C26481-3 $1,215.0099Bearing Plate Assembly (Hinge Numbers 5 and 6) 65C26482-3 $3,750.00284Hinge Fitting Assembly (Hinge Number 4)65C25763-7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 57 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 58 Group 2, Configuration 2; Group 3: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) NamePart Number $9,000.00214Hinge Fitting Assembly (Hinge Number 6, Right Side) 65C31307-15 (a) $9,000.00284Hinge Fitting Assembly (Hinge Number 6, Left Side) 65C31307-16 (a) $1,183.00(b)Hinge Fitting Assembly (Hinge Number 6)65C25767-1 (a) (a) Elevators have either 65C25767-1 or 65C31307-() hinge fitting assemblies installed at hinge number 6. (b) ROLT currently unavailable and to be provided at a later date. B. Industry Support Information Boeing warranty remedies are not available for the inspection and 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 Group 1: None. Group 2-3: The following parts or materials are necessary to do the change in this service bulletin. Maximum quantities are given. Required parts are dependent on inspection findings. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 58 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 59 Group 2, Configuration 2; Group 3: Work Package 1, Work Package 2, Work Package 6: Elevator Hinge Numbers 4 and 6 - Bearing Plate Installation or Replacement NotesNameQTYPart Number / Specification Hinge Number 4 (a)Bearing Plate Assembly265C26481-3 Bushing4BACB28AK05-187 Bolt4BACB30NR5K36 Nut4BACN10JC5CD Washer4BACW10BN5AC Washer4NAS1149D0563J Hinge Number 6 (a)Bearing Plate Assembly265C26482-3 Bushing4BACB28AK04-190 Bolt4BACB30NR4K36 Nut4BACN10JC4CD Washer4BACW10BN4AC Washer4NAS1149D0463J (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 59 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT ### Page 60 Group 2-3: Work Package 1, Work Package 2: Elevator Hinge Numbers 4 and 6 - Attach Plate Installation NotesNameQTYPart Number / Specification Hinge Number 4 (a)Attach Plate469-56027-1 Bolt6BACB30LJ4-21 Bolt6BACB30LJ4-21X Nut6BACN11AG4 Washer6NAS1149D0463H Bolt6BACB30LJ5-21 Nut6BACN11AG5 Washer6NAS1149D0563H Hinge Number 6 (a)Attach Plate469-56027-3 Bolt4BACB30LJ4-21 Bolt4BACB30LJ4-21X Nut4BACN11AG4 Washer4NAS1149D0463H Bolt4BACB30LJ5-21 Nut4BACN11AG5 Washer4NAS1149D0563H (c)Bushing10- (b)Sealant - Pressure and Environmen- tal - Chromate Type -BMS 5-95 (b)Coating - Chemical and Solvent Re- sistant Finish, Corrosion Inhibiting Primer -BMS 10-11, Type I (d)Shim8- -Bolt4BACB30LJ5CD22 Washer4BACW10BP5CD Washer4BACW10BP5DP Nut4BACN10JD5CD Cotter Pin4BACP18BC02C06P (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. (b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c) Fabricate from 7075-T6 aluminum in accordance with FIGURE 21 and FIGURE 22. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 60 of 227 BOEING SERVICE BULLETIN 737-55A1099 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/737-55a1099/file/f620624097b3.md?from=61 --- 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.