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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Unpublished Work.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
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Table of Contents
Revision Transmittal Sheet7
S u m m a r y9
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.
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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.
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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.
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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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
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.
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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.
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Original Issue: July 05, 2016 737-55A1099Revision 1: October 21, 2016 9 of 227
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 Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION 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.
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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.
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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.
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