# Boeing Alert Service Bulletin 767-57A0134: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0531; AD 2017-12-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 767-57A0134](https://openairdocs.org/service-documents/boeing/767-57a0134.md) - Title as filed: SB-767-57A0134 - Pages: 61 - PDF: https://openairdocs.org/files/sha256/c7/f7/c7f7662cdee7ae4056d7ebf0830e81b22bdbbc5e2c1920713a8b54ff5bcb52ea - Page: https://openairdocs.org/service-documents/boeing/767-57a0134/file/c7f7662cdee7 ## 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 767 Service Bulletin ALERT Number: 767-57A0134 Original Issue: May 27, 2016 ATA System: 5750 SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap Outboard Support Assembly Number 3 and 6 - Inspection and Repair, Replacement or Modification 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 Unpublished Work.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Issue: May 27, 2016 767-57A0134 1 of 61 3.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 2 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 16 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19 3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 20 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 FIGURE 1: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 2: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 3: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM - INTERIM BLEND REPAIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 FIGURE 4: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM - INTERIM BLEND REPAIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 FIGURE 5: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM ASSEMBLY REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 FIGURE 6: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM ASSEMBLY REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 3 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 4 FIGURE 7: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 FIGURE 8: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 FIGURE 9: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 FIGURE 10: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 FIGURE 11: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 FIGURE 12: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: GENERAL VISUAL INSPECTION OF THE 6-9 DRIVE ARM ASSEMBLY AND REPAIR, REPLACEMENT OR MODIFICATION OF THE 4-5 ACTUATOR CRANK ARM ASSEMBLY AT INBOARD FLAP OUTBOARD SUPPORT NUMBER 3 AND 6 . . . . . . . . . . . . . . . . . . . . . . . . . 58 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 4 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 5 Commercial Airplanes 767 Service Bulletin ALERT SummaryNumber: 767-57A0134Original Issue: May 27, 2016 ATA System: 5750 SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap Outboard Support Assembly Number 3 and 6 - Inspection and Repair, Replacement or Modification THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND This Service Bulletin is sent to give instructions to inspect for damage caused by interference between the 6-9 drive arm assembly and the 4-5 actuator crank arm assembly on the inboard flap outboard support assembly number 3 and number 6. Instructions are also given for an interim blend repair, and modification or replacement of the 4-5 actuator crank arm assembly to terminate repeat inspections. If this service bulletin is not accomplished, interference between the 6-9 drive arm assembly and the 4-5 actuator crank arm assembly will cause a fatigue load on the 5-7 link which could result in failure of the 5-7 link and subsequent loss of the inboard flap, continued safe flight and landing could be affected after the departure of a flap during takeoff or landing. The Boeing Company received a report from an operator that while inspecting the left wing, inboard flap, outboard support assembly number 3, it was seen that the extend overtravel stops on the 4-5 actuator crank arm assembly were touching the adjacent 6-9 drive arm assembly when the flaps were fully retracted. The cause of this problem occurred with the installation of 767-400ER flaps on 767-200 airplanes which have crank arms that have extend overtravel stops that are too large. The problem did not occur during the fitting of the 767-400ER flaps in production as the 4-5 actuator crank arm assembly had been redesigned. Accomplishment of this service bulletin will prevent interference between the 6-9 drive arm assembly and the 4-5 actuator crank arm assembly. Boeing Service Related Problem (SRP) 767-57-0282 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 57-16001 is related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 5 of 61 ### Page 6 This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications 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 (PRR B12901-124RS) Get access to the inboard flap outboard support assembly at the number 3 and number 6 positions. Do a general visual inspection of the 6-9 drive arm assembly for any damage caused by interference with the 4-5 actuator crank arm assembly. If any damage is found on the 6-9 drive arm assembly, do a repair of the 6-9 drive arm assembly, do an interim blend repair of the 4-5 actuator crank arm assembly, and do a repeat general visual inspection of the 6-9 drive arm assembly. As an option, replace or modify the 4-5 actuator crank arm assembly. If no damage is found on the 6-9 drive arm assembly, repeat the general visual inspection of the 6-9 drive arm assembly, or do replacement or modification of the 4-5 actuator crank arm assembly. EFFECTIVITY 767-200 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 6 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 7 INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for airplanes in warranty as of August 12, 2015. Please refer to Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of 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: May 27, 2016 767-57A0134 7 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 8 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 4-5 ACTUATOR CRANK ARM ASSEMBLY 6-9 DRIVE ARM 5-7 LINK DO A GENERAL VISUAL INSPECTION OF THE 6-9 DRIVE ARMS FOR ANY DAMAGE CAUSED BY INTERFERENCE WITH THE 4-5 ACTUATOR CRANK ARM ASSEMBLY INBOARD FLAP, OUTBOARD SUPPORT ASSEMBLY (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) A-A 2481278 Original Issue: May 27, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 767-57A0134 Work - See page 1 for details. 8 of 61 ### Page 9 Commercial Airplanes 767 Service Bulletin ALERT Number: 767-57A0134 Original Issue: May 27, 2016 ATA System: 5750 SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap Outboard Support Assembly Number 3 and 6 - Inspection and Repair, Replacement or Modification 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 767-200 Airplanes, line numbers 912, 930, 932, 941, 943, 952, 963 and 966 in 1 Group. The Variable Numbers and Group Information for the applicable airplanes is given below. An equivalent change is on subsequent production airplanes. Refer to PRR B12901-124RS for data about this change. Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 767-200 Tanker Transport Airplanes-1 Airplane Models: 767-200 GroupVariable Number 1VR086 - VR089 1VR106 - VR109 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 9 of 61 ### Page 10 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. Part Number 113T1227-29 113T1227-30 B. Concurrent Requirements None. C. Reason This Service Bulletin is sent to give instructions to inspect for damage caused by interference between the 6-9 drive arm assembly and the 4-5 actuator crank arm assembly on the inboard flap outboard support assembly number 3 and number 6. Instructions are also given for an interim blend repair, and modification or replacement of the 4-5 actuator crank arm assembly to terminate repeat inspections. If this service bulletin is not accomplished, interference between the 6-9 drive arm assembly and the 4-5 actuator crank arm assembly will cause a fatigue load on the 5-7 link which could result in failure of the 5-7 link and subsequent loss of the inboard flap, continued safe flight and landing could be affected after the departure of a flap during takeoff or landing. The Boeing Company received a report from an operator that while inspecting the left wing, inboard flap, outboard support assembly number 3, it was seen that the extend overtravel stops on the 4-5 actuator crank arm assembly were touching the adjacent 6-9 drive arm assembly when the flaps were fully retracted. The cause of this problem occurred with the installation of 767-400ER flaps on 767-200 airplanes which have crank arms that have extend overtravel stops that are too large. The problem did not occur during the fitting of the 767-400ER flaps in production as the 4-5 actuator crank arm assembly had been redesigned. If no damage is found on the 6-9 drive arm assembly, repeat the general visual inspection of the 6-9 drive arm assembly, or do replacement or modification of the 4-5 actuator crank arm assembly. Boeing Service Related Problem (SRP) 767-57-0282 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 57-16001 is related to this service bulletin. D. Description Get access to the inboard flap outboard support assembly at the number 3 and number 6 positions. Do a general visual inspection of the 6-9 drive arm assembly for any damage caused by interference with the 4-5 actuator crank arm assembly. If any damage is found on the 6-9 drive arm assembly, do a repair of the 6-9 drive arm assembly, do an interim blend repair of the 4-5 actuator crank arm assembly, and do a repeat general visual inspection of the 6-9 drive arm assembly. As an option, replace or modify the 4-5 actuator crank arm assembly. If no damage is found on the 6-9 drive arms, repeat the general visual inspection of the 6-9 drive arms, or do replacement or modification of the 4-5 actuator crank arm assembly. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 10 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 11 The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance Zones ZoneModel 571, 671767-200 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. A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX A. 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. Table 1: General Visual Inspection of the 6-9 Drive Arm Assembly and Repair, Replacement or Modifi- cation of the 4-5 Actuator Crank Arm Assembly at Inboard Flap Outboard Support Number 3 and 6 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 36 months after the original issue date of this ser- vice bulletin. Before 5,000 to- tal flight cycles. Do PART 1: 6-9 DRIVE ARM ASSEMBLY GENER- AL VISUAL INSPECTION for any damage caused by interference with the 4-5 ac- tuator crank arm assembly. (a) All airplanes Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 11 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 12 Table 1: General Visual Inspection of the 6-9 Drive Arm Assembly and Repair, Replacement or Modifi- cation of the 4-5 Actuator Crank Arm Assembly at Inboard Flap Outboard Support Number 3 and 6 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 1 (ACTION 1):CONDITION 1: ANY DAMAGE FOUND ON 6- 9 DRIVE ARM ASSEM- BLY Do PART 2: 4-5 ACTUA- TOR CRANK ARM ASSEM- BLY INTERIM BLEND RE- PAIR on the crank arms as- sociated with the damaged 6-9 drive arm assembly. -Before further flight.OPTION 1 (ACTION 2): Do PART 3: 6-9 DRIVE ARM ASSEMBLY REPAIR. 2,500 flight cy- cles. (b) -OPTION 1 (ACTION 3): Repeat PART 1: 6-9 DRIVE ARM ASSEMBLY GENER- AL VISUAL INSPECTION for any damage caused by interference with the 4-5 ac- tuator crank arm assembly. (a) -Before further flight.OPTION 2 (ACTION 1): Do PART 3: 6-9 DRIVE ARM ASSEMBLY REPAIR. -Before further flight.OPTION 2 (ACTION 2): Do PART 4: 4-5 ACTUA- TOR CRANK ARM ASSEM- BLY REPLACEMENT (TERMINATING ACTION) on the crank arms associat- ed with the damaged 6-9 drive arm assembly. -Before further flight.OPTION 3 (ACTION 1): Do PART 3: 6-9 DRIVE ARM ASSEMBLY REPAIR. -Before further flight.OPTION 3 (ACTION 2): Do PART 5: 4-5 ACTUA- TOR CRANK ARM ASSEM- BLY MODIFICATION (TER- MINATING ACTION) on the crank arms associated with the damaged 6-9 drive arm assembly. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 12 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 13 Table 1: General Visual Inspection of the 6-9 Drive Arm Assembly and Repair, Replacement or Modifi- cation of the 4-5 Actuator Crank Arm Assembly at Inboard Flap Outboard Support Number 3 and 6 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 2,500 flight cy- cles. (b) -OPTION 4: Repeat PART 1: 6-9 DRIVE ARM ASSEMBLY GENER- AL VISUAL INSPECTION for any damage caused by interference with the 4-5 ac- tuator crank arm assembly. (a) CONDITION 2: NO DAMAGE FOUND ON 6- 9 DRIVE ARM ASSEM- BLY -Before further flight.OPTION 5: Do PART 4: 4-5 ACTUA- TOR CRANK ARM ASSEM- BLY REPLACEMENT (TERMINATING ACTION) on the crank arms associat- ed with the undamaged 6-9 drive arm assembly. -Before further flight.OPTION 6: Do PART 5: 4-5 ACTUA- TOR CRANK ARM ASSEM- BLY MODIFICATION (TER- MINATING ACTION) on the crank arms associated with the undamaged 6-9 drive arm assembly. (a) Damage caused by interference with the 4-5 actuator crank arm assembly is defined as: Worn paint or primer, or worn paint, worn primer and bare metal. (b) Accomplishment of PART 4: 4-5 ACTUATOR CRANK ARM ASSEMBLY REPLACEMENT or PART 5: 4-5 ACTUATOR CRANK ARM ASSEMBLY MODIFICATION is a terminating action to the repeat inspec- tions, for the associated 6-9 drive arm assembly. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 13 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 14 G. Manpower The table below shows an estimate of the task hours necessary to do the inspections, repairs or replacement 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. Inboard Flap Outboard Support Assembly Number 3 and Number 6 - Inspection of 6-9 Drive Arm Assembly Elapsed HoursTask HoursNumber of PersonsTask 1.001.001Open Access 0.200.201FIGURE 1 0.200.201FIGURE 2 1.001.001Close Access (a)(a)TOTAL FOR EACH AIRPLANE (a) Total time required may vary depending on conditions found during inspections and actions taken. 4-5 Actuator Crank Arm Assembly Interim Blend Repair Elapsed HoursTask HoursNumber of PersonsTask 2.004.002FIGURE 3 2.004.002FIGURE 4 4.008.00TOTAL FOR EACH AIRPLANE 6-9 Drive Arm Assembly Repair Elapsed HoursTask HoursNumber of PersonsTask (a)(a)-Finishes Repair (a)(a)-Bare Metal Repair (a)(a)TOTAL FOR EACH AIRPLANE (a) The time required for repair depends on the damage found. Therefore no es- timate is given. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 14 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 15 4-5 Actuator Crank Arm Assembly Removal, Disassembly, Modification and Installation Elapsed HoursTask HoursNumber of PersonsTask 2.004.002FIGURE 5 2.004.002FIGURE 6 0.700.701FIGURE 7 0.700.701FIGURE 8 4.008.002FIGURE 9 4.008.002FIGURE 10 2.004.002FIGURE 11 2.004.002FIGURE 12 17.4033.40TOTAL FOR EACH AIRPLANE 4-5 Actuator Crank Arm Assembly Replacement Elapsed HoursTask HoursNumber of PersonsTask 2.004.002FIGURE 5 2.004.002FIGURE 6 2.004.002FIGURE 11 2.004.002FIGURE 12 8.0016.00TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR B12901-124RS b. Boeing Service Letter 767-SL-51-036 c. Boeing Service Related Problem (SRP) 767-57-0282 d. Component Maintenance Manual (CMM) 57-53-31, Repair 3-1 e. Service Bulletin Index D624T001 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 15 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 16 f. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-15-19, 20-20-01, 20-20-02, 20-30-02, 20-41-02, 20-42-02, 20-42-10, 20-50-01, 20-50-03, 20-50-10 g. 767 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-04, 27-51-15, 51-21 h. 767 Fleet Team Digest (FTD) 57-16001 i. 767-200 Structural Repair Manual (SRM) 51-20-01, 57-53-02 2. Data Supplied with this Service Bulletin: a. Drawings: ADCNDCN/REVSheetTitleDrawing No --64-5 ARM ASSY-SUPPORT NO. 3 IN- BOARD T.E. FLAP 113T1227 -CPSDL -APL4-5 ARM ASSY113T1227-35 -APL4-5 ARM ASSY113T1227-36 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number 4-5 ARM ASSY - SUPPORT NO. 3 INBOARD T.E. FLAP113T1227 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 27-51767 Aircraft Maintenance Manual 57-53767 Component Maintenance Manual 57-51767 Illustrated Parts Catalog 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 does not affect FCS, therefore DTIs are not necessary. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 16 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 17 M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 17 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 18 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 18 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT BLANK PAGE ### Page 19 2. MATERIAL INFORMATION A. Material - Price and Availability The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane . As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. B. Industry Support Information Boeing warranty remedies are available for 767 airplanes in warranty as of August 12, 2015. For task hour and material reimbursement for airplanes in warranty as of that date, send a warranty claim to BCA Contracts - Warranty. The warranty remedies will expire eight years from the original issue date of this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. 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. NotesExisting Part NumberNameQTYPart Number / Specification (a)-Primer8 ozBMS 10-11, Type I (a)-Gloss Enamel8 ozBMS 10-60, Type I (b) (c)-Crank Arm Assembly - Left Side1113T1227-35 (b) (c)-Crank Arm Assembly - Right Side1113T1227-36 (b) (d)-Bushing2113T1347-66 (b) (d)-Bushing4113T1347-51 (b) (d)-Bushing4113T1347-52 (b) (d)-Nut4BACN10JC4CD (a)-Sealant12 ozBMS 5-95 (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) This part is used in production. (c) This part is only necessary for the replacement of the existing 4-5 actuator crank arm assembly. (d) This part is only necessary for the modification of the existing 4-5 actuator crank arm assembly. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 19 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 20 3. Parts Modified and Reidentified NotesNew Part NumberNameQTYExisting Part Number (a)113T1227-35 (b)Crank Arm Assembly - Left Side 1113T1227-29 (c) (a)113T1227-36 (b)Crank Arm Assembly - Right Side 1113T1227-30 (c) (a)113T1227-31 (b)Crank Arm - Left Side1113T1227-25 (c) (a)113T1227-32 (b)Crank Arm - Right Side1113T1227-26 (c) (a)113T1227-33 (b)Crank Arm - Left Side1113T1227-27 (c) (a)113T1227-34 (b)Crank Arm - Right Side1113T1227-28 (c) (a) Make the change in accordance with this service bulletin. (b) This is the part number after the change is done in accordance with this service bulletin. (c) This part is not used in production. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 20 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 21 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 767 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 767 Aircraft Maintenance Manual (AMM). — Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). — Values for engine maintenance tasks are included in Chapter 70 of 767 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 21 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 22 7. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 8. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 9. Boeing Service Letter 767-SL-51-036, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 10. Refer to APPENDIX A for logic diagram. Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 11. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 12. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 13. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 14. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 15. 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. 16. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 22 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 23 17. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. B. WORK INSTRUCTIONS WARNING: TRAILING EDGE FLAPS ARE FAST ACTING. MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF TRAILING EDGE FLAPS AND THE FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. ONCE THE TRAILING FLAPS ARE DEPLOYED LOCKS MUST BE INSTALLED TO PREVENT POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF THE FLAPS. 1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 2. Remove and keep the mid section of the inboard flap outboard fairing at support assembly number 3 and number 6. Refer to 767 AMM 27-51-15 as an accepted procedure. 3. RC - Do PART 1: 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION for any damage caused by interference with the 4-5 actuator crank arm assembly. a. CONDITION 1: ANY DAMAGE FOUND ON 6-9 DRIVE ARM ASSEMBLY (1) OPTION 1: (a) OPTION 1 (ACTION 1): Do PART 2: 4-5 ACTUATOR CRANK ARM ASSEMBLY INTERIM BLEND REPAIR on the crank arms associated with the damaged 6-9 drive arm assembly. (b) OPTION 1 (ACTION 2): Do PART 3: 6-9 DRIVE ARM ASSEMBLY REPAIR. (c) OPTION 1 (ACTION 3): Repeat PART 1: 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION for any damage caused by interference with the 4-5 actuator crank arm assembly. (2) OPTION 2: (a) OPTION 2 (ACTION 1): Do PART 3: 6-9 DRIVE ARM ASSEMBLY REPAIR. (b) OPTION 2 (ACTION 2): Do PART 4: 4-5 ACTUATOR CRANK ARM ASSEMBLY REPLACEMENT (TERMINATING ACTION) on the crank arms associated with the damaged 6-9 drive arm assembly. (3) OPTION 3: (a) OPTION 3 (ACTION 1): Do PART 3: 6-9 DRIVE ARM ASSEMBLY REPAIR. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 23 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 24 (b) OPTION 3 (ACTION 2): Do PART 5: 4-5 ACTUATOR CRANK ARM ASSEMBLY MODIFICATION (TERMINATING ACTION) on the crank arms associated with the damaged 6-9 drive arm assembly. b. CONDITION 2: NO DAMAGE FOUND ON 6-9 DRIVE ARM ASSEMBLY (1) OPTION 4: Repeat PART 1: 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION for any damage caused by interference with the 4-5 actuator crank arm assembly. (2) OPTION 5: Do PART 4: 4-5 ACTUATOR CRANK ARM ASSEMBLY REPLACEMENT (TERMINATING ACTION) on the crank arms associated with the undamaged 6-9 drive arm assembly. (3) OPTION 6: Do PART 5: 4-5 ACTUATOR CRANK ARM ASSEMBLY MODIFICATION (TERMINATING ACTION) on the crank arms associated with the undamaged 6-9 drive arm assembly. 4. Install the kept mid section of the inboard flap outboard fairing at support assembly number 3 and number 6. Refer to 767 AMM 27-51-15 as an accepted procedure. 5. Activate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 6. Put the airplane back to a serviceable condition. PART 1: 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION 1. Do a General Visual Inspection of the 6-9 drive arm assembly on the left and right wing for any damage caused by interference with the 4-5 actuator crank arm assembly in accordance with FIGURE 1 and FIGURE 2. NOTE: Damage caused by interference with the 4-5 actuator crank arm assembly is defined as: Worn paint or primer, or worn paint, worn primer and bare metal. NOTE: If a terminating action has been accomplished on only the left wing or right wing 6-9 drive arm assembly, then any repeat inspection is only in accordance with FIGURE 1 or FIGURE 2 as applicable. PART 2: 4-5 ACTUATOR CRANK ARM ASSEMBLY INTERIM BLEND REPAIR 1. Do the repair of the 4-5 actuator crank arm assembly in accordance with FIGURE 3 left side, or FIGURE 4 right side. PART 3: 6-9 DRIVE ARM ASSEMBLY REPAIR 1. If the damage to the 6-9 drive arm assembly caused by interference with the 4-5 actuator crank arm assembly is worn paint, or worn paint and primer, then repair the worn finishes. Refer to 767-200 SRM 51-20-01 as an accepted procedure. If the damage to the 6-9 drive arm assembly caused by interference with the 4-5 actuator crank arm assembly is worn paint, worn primer and bare metal, then: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 24 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 25 a. Repair the bare metal in accordance with 767-200 SRM 57-53-02, Allowable Damage 2. If the damage is more than allowable in accordance with 767-200 SRM 57-53-02, Allowable Damage 2, contact The Boeing Company for instructions, and do the instructions. b. Repair the worn finishes. Refer to 767-200 SRM 51-20-01 as an accepted procedure. PART 4: 4-5 ACTUATOR CRANK ARM ASSEMBLY REPLACEMENT 1. Remove the damaged 4-5 actuator crank arm assembly in accordance with FIGURE 5 left side, or FIGURE 6 right side. 2. Install a new 4-5 actuator crank arm assembly in accordance with and FIGURE 11 left side, or FIGURE 12 right side. PART 5: 4-5 ACTUATOR CRANK ARM ASSEMBLY MODIFICATION 1. Remove the 4-5 actuator crank arm assembly in accordance with FIGURE 5 left side, or FIGURE 6 right side. 2. Disassemble the 4-5 actuator crank arm assembly in accordance with FIGURE 7 left side, or FIGURE 8 right side. 3. Do the modification of the 4-5 crank arms and assemble the 4-5 actuator crank arm assembly in accordance with FIGURE 9 left side, or FIGURE 10 right side. 4. Install the modified 4-5 actuator crank arm assembly in accordance with FIGURE 11 left side, or FIGURE 12 right side. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 25 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 26 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 4-5 ACTUATOR 6-9 DRIVE ARM CRANK ARM WD A-A STIFFENER 1.00 STIFFENER CENTERLINE FWD 2481558 FIGURE 1: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION (SHEET 1 OF 2) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 26 of 61 ### Page 27 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Left Wing Inboard Flap Support - 6-9 Drive Arm Assembly General Visual Inspection. More DataQtyIdentificationNameTaskStep Do a General Visual Inspection for any damage caused by interference with the 4-5 actuator crank arm assembly. 1-6-9 Drive Arm Assem- bly Inspect1 FIGURE 1: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 27 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 28 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 6-9 DRIVE ARM 4-5 ACTUATOR CRANK ARM FWD A-A STIFFENER 1.00 STIFFENER CENTERLINE 2481596 FIGURE 2: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION (SHEET 1 OF 2) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 28 of 61 ### Page 29 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Right Wing Inboard Flap Support - 6-9 Drive Arm Assembly General Visual Inspection. More DataQtyIdentificationNameTaskStep Do a General Visual Inspection for any damage caused by interference with the 4-5 actuator crank arm assembly. 1-6-9 Drive Arm Assem- bly Inspect1 FIGURE 2: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 29 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 30 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 6-9 DRIVE ARM FWD FLAPS EXTENDED A-A -0.58- MINIMUM 0.10 4-5 ACTUATOR CRANK ARM ASSEMBLY 2482279 (FLAPS RETRACTED) FIGURE 3: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM - INTERIM BLEND REPAIR (SHEET 1 OF 2) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 30 of 61 ### Page 31 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Left Wing Inboard Flap Support - 4-5 Actuator Crank Arm - Interim Blend Repair. More DataQtyIdentificationNameTaskStep (a)2113T1227-25/-27Crank ArmChamfer1 (b)2113T1227-25/-27Crank ArmInspect2 Flap peen the re- paired area using an intensity of 0.012A and a coverage of 2.0. Refer to SOPM 20-10-03 as an ac- cepted procedure. 2113T1227-25/-27Crank ArmPrepare3 Stylus cadmium plate the repaired area. Refer to SOPM 20-42-10 as an accepted proce- dure. --Cadmium PlateApply4 Apply one layer of primer to the re- paired area. Refer to SOPM 20-41-02 as an accepted proce- dure. -BMS 10-11 TYPE IPrimerApply5 Apply one layer of gloss enamel to the repaired area. Refer to 767 AMM 51-21 as an accepted pro- cedure. -BMS 10-60 TYPE IGloss EnamelApply6 (a) Chamfer the extend overtravel stops as shown to remove all damage. Use hand tools or portable hand- held motors with abrasive tools to break all sharp edges caused by the repair. Refer to SOPM 20-10-03 as an accepted procedure for hand tools. Make sure that a surface roughness of 125 Ra or better is achieved. Material removal using hand-held motors must be followed with a local etch for heat damage inspection. If any discoloration is found, the part must be replaced. Refer to SOPM 20-10-02 as an accepted procedure. (b) Do a local penetrant inspection of the repaired area for surface defects. Refer to SOPM 20-20-02 as an accepted procedure. If any surface defect is found, contact The Boeing Company for instructions, and do the instructions. FIGURE 3: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM - INTERIM BLEND REPAIR (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 31 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 32 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 6-9 DRIVE ARM FWD FLAPS EXTENDED A-A + 0.58 MINIMUM 0.10 VD 4-5 ACTUATOR CRANK ARM ASSEMBLY (FLAPS RETRACTED) FIGURE 4: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM - INTERIM BLEND REPAIR (SHEET 1 OF 2) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 32 of 61 ### Page 33 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Right Wing Inboard Flap Support - 4-5 Actuator Crank Arm - Interim Blend Repair. More DataQtyIdentificationNameTaskStep (a)2113T1227-26/-28Crank ArmChamfer1 (b)2113T1227-26/-28Crank ArmInspect2 Flap peen the re- paired area using an intensity of 0.012A and a coverage of 2.0. Refer to SOPM 20-10-03 as an ac- cepted procedure. 2113T1227-26/-28Crank ArmPrepare3 Stylus cadmium plate the repaired area. Refer to SOPM 20-42-10 as an accepted proce- dure. --Cadmium PlateApply4 Apply one layer of primer to the re- paired area. Refer to SOPM 20-41-02 as an accepted proce- dure. -BMS 10-11 TYPE IPrimerApply5 Apply one layer of gloss enamel to the repaired area. Refer to 767 AMM 51-21 as an accepted pro- cedure. -BMS 10-60 TYPE IGloss EnamelApply6 (a) Chamfer the extend overtravel stops as shown to remove all damage. Use hand tools or portable hand- held motors with abrasive tools to break all sharp edges caused by the repair. Refer to SOPM 20-10-03 as an accepted procedure for hand tools. Make sure that a surface roughness of 125 Ra or better is achieved. Material removal using hand-held motors must be followed with a local etch for heat damage inspection. If any discoloration is found, the part must be replaced. Refer to SOPM 20-10-02 as an accepted procedure. (b) Do a local penetrant inspection of the repaired area for surface defects. Refer to SOPM 20-20-02 as an accepted procedure. If any surface defect is found, contact The Boeing Company for instructions, and do the instructions. FIGURE 4: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM - INTERIM BLEND REPAIR (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 33 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 34 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 1) 4-5 ACTUATOR CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481808 FIGURE 5: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM ASSEMBLY REMOVAL (SHEET 1 OF 2) Original Issue: May 27, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 767-57A0134 Work - See page 1 for details. 34 of 61 ### Page 35 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Left Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep Refer to 767 AMM 27-51-04 as an ac- cepted procedure. 1113T1227-294-5 Actuator Crank Arm Assembly Remove1 FIGURE 5: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM ASSEMBLY REMOVAL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 35 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 36 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 4-5 ACTUATOR 1 CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481810 FIGURE 6: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM ASSEMBLY REMOVAL (SHEET 1 OF 2) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 36 of 61 ### Page 37 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Right Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep Refer to 767 AMM 27-51-04 as an ac- cepted procedure. 1113T1227-304-5 Actuator Crank Arm Assembly Remove1 FIGURE 6: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM ASSEMBLY REMOVAL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 37 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 38 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 4-5 ACTUATOR CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481815 FIGURE 7: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY (SHEET 1 OF 3) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 38 of 61 ### Page 39 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT • B C-C B-B 2481819 FIGURE 7: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY (SHEET 2 OF 3) Original Issue: May 27, 2016 Export Controlled ECCN: 9E991 - BOEING 767-57A0134 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 61 ### Page 40 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Left Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep -2BACN10JC4CDNutRemove1 -2BACB30NR4K14BoltRemove / Keep -2BACW10BP4CDWasherRemove / Keep -2BACW10BP4DPWasherRemove / Keep -1113T1227-294-5 Actuator Crank Arm Assembly Disassemble2 Discard removed bushing. 1113T1347-66BushingRemove3 Discard removed bushing. 2113T1347-51BushingRemove Discard removed bushing. 2113T1347-52BushingRemove FIGURE 7: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 40 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 41 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT LA 4-5 ACTUATOR CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481818 FIGURE 8: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY (SHEET 1 OF 3) Original Issue: May 27, 2016 Export Controlled ECCN: 9E991 - BOEING 767-57A0134 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 61 ### Page 42 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT B — B C-C B-B 2481843 FIGURE 8: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY (SHEET 2 OF 3) Original Issue: May 27, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 767-57A0134 Work - See page 1 for details. 42 of 61 ### Page 43 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Right Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep -2BACN10JC4CDNutRemove1 -2BACB30NR4K14BoltRemove / Keep -2BACW10BP4CDWasherRemove / Keep -2BACW10BP4DPWasherRemove / Keep -1113T1227-294-5 Actuator Crank Arm Assembly Disassemble2 Discard removed bushing. 1113T1347-66BushingRemove3 Discard removed bushing. 2113T1347-51BushingRemove Discard removed bushing. 2113T1347-52BushingRemove FIGURE 8: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM DISASSEMBLY (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 43 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 44 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 4-5 ACTUATOR CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481849 FIGURE 9: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 1 OF 5) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 44 of 61 ### Page 45 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT B (6 7 8 9 13 14 15 16 (12_ 12) 0.16- • RADIUS 0.10 0.05 CHAMFER 0.164 × 19.70 DEG EXTEND OVERTRAVEL STOP NUMBER LOCATIO CRANK ARM PAR C-C B-B 2481854 FIGURE 9: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 2 OF 5) Original Issue: May 27, 2016 Export Controlled ECCN: 9E991 - BOEING 767-57A0134 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 61 ### Page 46 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Left Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep (a)3-Bushing BoreInspect1 Remove all finishes from the crank arms. Refer to SOPM 20- 30-02 as an accept- ed procedure. -113T1227-25/-27Crank ArmClean2 (b)2113T1227-25/-27Crank ArmMachine3 (c)2113T1227-31/-33Crank ArmIdentify4 (d)2113T1227-31/-33Crank ArmInspect5 (e)2113T1227-31/-33Crank ArmInspect All areas except splines. Intensity 0.012A, coverage 2.0. Refer to SOPM 20-10-03 as an ac- cepted procedure. Do not peen part numbers. 2113T1227-31/-33Crank ArmShot Peen6 Glass bead peen the splines. Intensity 0.003 - 0.005A, cov- erage 2.0. Refer to SOPM 20-10-03 as an accepted proce- dure. 2113T1227-31/-33Crank ArmPrepare7 Apply cadmium-tita- nium alloy plate and apply chromate treatment all over. 0.0005 - 0.0007 inch. Refer to SOPM 20-42-02 as an ac- cepted procedure. --Cadmium PlateApply8 One coat all areas except bolt holes, splines and 4.75 inch bore. Refer to SOPM 20-41-02 as an accepted proce- dure. -BMS 10-11, TYPE 1PrimerApply9 FIGURE 9: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 46 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 47 More DataQtyIdentificationNameTaskStep Install bushing by shrink fit method with BMS 5-95 sealant. Refer to SOPM 20-50-03 as an accepted proce- dure. 2113T1347-52BushingInstall (New)10 -2113T1347-51BushingInstall (New) -1113T1347-66BushingInstall (New) In accordance with Boeing Drawing 113T1227. 1113T1227-354-5 Actuator Crank Arm Assembly Assemble11 Apply BMS 5-95 sealant to thread, shank and beneath head of bolts. Refer to SOPM 20-15-19 as an accepted pro- cedure. 2BACB30NR4K14BoltInstall (Kept)12 -2BACN10JC4CDNutInstall (New) -2BACW10BP4CDWasherInstall (Kept) -2BACW10BP4DPWasherInstall (Kept) Clean and reactivate the primed surfaces. Refer to SOPM 20- 41-02 as an accept- ed procedure. 2113T1227-31/-33Crank ArmClean13 (f)-BMS 10-11, TYPE 1PrimerApply14 All areas except bolt holes, splines, 4.75 inch bore and bush- ing flanges. Refer to 767 AMM 51-21 as an accepted proce- dure. -BMS 10-60 TYPE IGloss EnamelApply15 Re-number the actu- ator crank arm as- sembly. Rubber stamp Code RH. Refer to SOPM 20- 50-10 as an accept- ed procedure. 1113T1227-354-5 Actuator Crank Arm Assembly Identify16 FIGURE 9: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 47 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 48 More DataQtyIdentificationNameTaskStep (a) Do a detailed inspection with a 10-power magnifying glass, or do a magnetic particle inspection for any crack, scratch or corrosion. Refer to SOPM 20-20-01 as an accepted procedure. If any crack, scratch or corrosion is found, overhaul the crank arm. Refer to CMM 57-53-31, Repair 3-1 as an accepted procedure. If any crack, scratch or corrosion is larger than the rework limits in CMM 57-53-31, Repair 3-1, contact The Boeing Company for instructions, and do the instructions. (b) Remove material from the extend overtravel stops as shown. Refer to SOPM 20-10-02 as an accepted procedure. Make sure that a surface roughness of 125 Ra or better is achieved. Stress relieve the part. Refer to SOPM 20-10-02 as an accepted procedure. (c) Re-number the two crank arms. Vibro-engrave, steel stamp, or dot peen part number in the indicated area only. Characters shall be placed no closer than 0.050 inch to the edge of the indicated area, and a maximum of 0.015 inch deep. Refer to SOPM 20-50-10 as an accepted procedure. (d) Do a heat damage inspection. Refer to SOPM 20-10-02 as an accepted procedure. If any discoloration is found, the part must be replaced. (e) Do a Magnetic Particle Inspection for any surface defects (crack, corrosion or other irregularities). Refer to SOPM 20-20-01 as an accepted procedure. If any surface defect is found, do the repair in accordance with 767-200 SRM 57-53-02 Allowable Damage 2. If any surface defect is larger than the rework limits in 767-200 SRM 57-53-02 Allowable Damage 2, contact The Boeing Company for instructions, and do the instructions. (f) All areas except bolt holes, splines, 4.75 inch bore and bushing flanges. Refer to SOPM 20-41-02 as an accepted procedure. It is not necessary to apply primer to areas that cannot be seen without a mirror. FIGURE 9: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 48 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 49 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 4-5 ACTUATOR CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481852 FIGURE 10: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 1 OF 5) Original Issue: May 27, 2016 Export Controlled ECCN: 9E991 - BOEING 767-57A0134 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 61 ### Page 50 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT B - 911 1 1 12 .0.16 RADIUS 0.10 0.05 CHAMFER 0.164 × 19.70 DEG EXTEND OVERTRAVEL STOP CRANK ARM PART I NUMBER LOCATION C-C B-B 2481879 FIGURE 10: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 2 OF 5) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 50 of 61 ### Page 51 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Right Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep (a)3-Bushing BoreInspect1 Remove all finishes from the crank arms. Refer to SOPM 20- 30-02 as an accept- ed procedure. -113T1227-26/-28Crank ArmClean2 (b)2113T1227-26/-28Crank ArmMachine3 (c)2113T1227-32/-34Crank ArmIdentify4 (d)2113T1227-32/-34Crank ArmInspect5 (e)2113T1227-32/-34Crank ArmInspect All areas except splines. Intensity 0.012A, coverage 2.0. Refer to SOPM 20-10-03 as an ac- cepted procedure. Do not peen part numbers. 2113T1227-32/-34Crank ArmShot Peen6 Glass bead peen the splines. Intensity 0.003 - 0.005A, cov- erage 2.0. Refer to SOPM 20-10-03 as an accepted proce- dure. 2113T1227-32/-34Crank ArmPrepare7 Apply cadmium-tita- nium alloy plate and apply chromate treatment all over. 0.0005 - 0.0007 Inch. Refer to SOPM 20-42-02 as an ac- cepted procedure. --Cadmium PlateApply8 One coat all areas except bolt holes, splines and 4.75 inch bore. Refer to SOPM 20-41-02 as an accepted proce- dure. -BMS 10-11, TYPE 1PrimerApply9 FIGURE 10: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 51 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 52 More DataQtyIdentificationNameTaskStep Install bushing by shrink fit method with BMS 5-95 sealant. Refer to SOPM 20-50-10 as an accepted proce- dure. 2113T1347-52BushingInstall (New)10 -2113T1347-51BushingInstall (New) -1113T1347-66BushingInstall (New) In accordance with Boeing Drawing 113T1227. 1113T1227-364-5 Actuator Crank Arm Assembly Assemble11 Apply BMS 5-95 sealant to thread, shank and beneath head of bolts. Refer to SOPM 20-15-19 as an accepted pro- cedure. 2BACB30NR4K14BoltInstall (Kept)12 -2BACN10JC4CDNutInstall (New) -2BACW10BP4CDWasherInstall (Kept) -2BACW10BP4DPWasherInstall (Kept) Clean and reactivate the primed surfaces. Refer to SOPM 20- 41-02 as an accept- ed procedure. 2113T1227-32/-34Crank ArmClean13 (f)-BMS 10-11, TYPE 1PrimerApply14 All areas except bolt holes, splines, 4.75 inch bore and bush- ing flanges. Refer to 767 AMM 51-21 as an accepted proce- dure. -BMS 10-60 TYPE IGloss EnamelApply15 Re-number the actu- ator crank arm as- sembly. Rubber stamp Code RH. Refer to SOPM 20- 50-10 as an accept- ed procedure. 1113T1227-364-5 Actuator Crank Arm Assembly Identify16 FIGURE 10: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 52 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 53 More DataQtyIdentificationNameTaskStep (a) Do a detailed inspection with a 10-power magnifying glass, or do a magnetic particle inspection for any crack, scratch or corrosion. Refer to SOPM 20-20-01 as an accepted procedure. If any crack, scratch or corrosion is found, overhaul the crank arm. Refer to CMM 57-53-31, Repair 3-1 as an accepted procedure. If any crack, scratch or corrosion is larger than the rework limits in CMM 57-53-31, Repair 3-1, contact The Boeing Company for instructions, and do the instructions. (b) Remove material from the extend overtravel stops as shown. Refer to SOPM 20-10-02 as an accepted procedure. Make sure that a surface roughness of 125 Ra or better is achieved. Stress relieve the part. Refer to SOPM 20-10-02 as an accepted procedure. (c) Re-number the two crank arms. Vibro-engrave, steel stamp, or dot peen part number in the indicated area only. Characters shall be placed no closer than 0.050 inch to the edge of the indicated area, and a maximum of 0.015 inch deep. Refer to SOPM 20-50-10 as an accepted procedure. (d) Do a heat damage inspection. Refer to SOPM 20-10-02 as an accepted procedure. If any discoloration is found, the part must be replaced. (e) Do a Magnetic Particle Inspection for any surface defects (crack, corrosion or other irregularities). Refer to SOPM 20-20-01 as an accepted procedure. If any surface defect is found, do the repair in accordance with 767-200 SRM 57-53-02 Allowable Damage 2. If any surface defect is larger than the rework limits in 767-200 SRM 57-53-02 Allowable Damage 2, contact The Boeing Company for instructions, and do the instructions. (f) All areas except bolt holes, splines, 4.75 inch bore and bushing flanges. Refer to SOPM 20-41-02 as an accepted procedure. It is not necessary to apply primer to areas that cannot be seen without a mirror. FIGURE 10: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM MODIFICATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 53 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 54 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 1) 4-5 ACTUATOR CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481809 FIGURE 11: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM INSTALLATION (SHEET 1 OF 2) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 54 of 61 ### Page 55 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Left Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep (a) Refer to 767 AMM 27-51-04 as an accepted proce- dure. 1113T1227-354-5 Actuator Crank Arm Assembly Install (Changed)1 (a) Applicable for modified or new 4-5 actuator crank arm assembly. FIGURE 11: LEFT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM INSTALLATION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 55 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 56 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT 4-5 ACTUATOR (1 CRANK ARM ASSEMBLY 6-9 DRIVE ARM FWD A-A 2481814 FIGURE 12: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM INSTALLATION (SHEET 1 OF 2) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 Work - See page 1 for details. 56 of 61 ### Page 57 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for Right Wing Inboard Flap Support. More DataQtyIdentificationNameTaskStep (a) Refer to 767 AMM 27-51-04 as an accepted proce- dure. 1113T1227-364-5 Actuator Crank Arm Assembly Install (Changed)1 (a) Applicable for modified or new 4-5 actuator crank arm assembly. FIGURE 12: RIGHT WING INBOARD FLAP OUTBOARD SUPPORT - 4-5 ACTUATOR CRANK ARM INSTALLATION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 57 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 58 Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 1. The table below gives the description for the parts and conditions called out in the logic diagrams. DescriptionTitle 6-9 DRIVE ARM ASSEMBLY GENERAL VISUAL INSPECTIONPART 1 4-5 ACTUATOR CRANK ARM ASSEMBLY INTERIM BLEND REPAIRPART 2 6-9 DRIVE ARM ASSEMBLY REPAIRPART 3 4-5 ACTUATOR CRANK ARM ASSEMBLY REPLACEMENTPART 4 4-5 ACTUATOR CRANK ARM ASSEMBLY MODIFICATIONPART 5 ANY DAMAGE FOUND ON 6-9 DRIVE ARM ASSEMBLYCONDITION 1 NO DAMAGE FOUND ON 6-9 DRIVE ARM ASSEMBLYCONDITION 2 2. The table below gives the description for the flag notes called out in the logic diagram. DescriptionFlag Note Letter Damage caused by interference with the 4-5 actuator crank arm assembly is defined as: Worn paint or primer, or worn paint, primer and bare metal. (a) Accomplishment of PART 4: 4-5 ACTUATOR CRANK ARM ASSEMBLY REPLACEMENT or PART 5: 4-5 ACTUATOR CRANK ARM ASSEMBLY MODIFICATION is a terminating action to the repeat inspections, for the as- sociated 6-9 drive arm assembly. (b) APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: GENERAL VISUAL INSPECTION OF THE 6-9 DRIVE ARM ASSEMBLY AND REPAIR, REPLACEMENT OR MODIFICATION OF THE 4-5 ACTUATOR CRANK ARM ASSEMBLY AT INBOARD FLAP OUTBOARD SUPPORT NUMBER 3 AND 6 (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 58 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 59 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: GENERAL VISUAL INSPECTION OF THE 6-9 DRIVE ARM ASSEMBLY AND REPAIR, REPLACEMENT OR MODIFICATION OF THE 4-5 ACTUATOR CRANK ARM ASSEMBLY AT INBOARD FLAP OUTBOARD SUPPORT NUMBER 3 AND 6 (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 27, 2016 767-57A0134 59 of 61 BOEING SERVICE BULLETIN 767-57A0134 ALERTALERT ### Page 60 (OCR) BOEING SERVICE BULLETIN 767-57A0134 ALERT ALERT BEFORE FURTHER BEFORE FURTHER BEFORE FURTHER FLIGHT FLIGHT FLIGHT OPTION 1: OPTION 2: OPTION 3: (ACTION 1): (ACTION 1): (ACTION 1): DO PART 2 DO PART 3 DO PART 3 OPTION 1: OPTION 2: OPTION 3: (ACTION 2): (ACTION 2): (ACTION 2): DO PART 3 DO PART 4 DO PART 5 (TERMINATING ACTION) (TERMINATING ACTION) NOT TO EXCEED 2,500 FLIGHT CYCLES OPTION 1: (ACTION 3): REPEAT PART 1 2482311 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: GENERAL VISUAL INSPECTION OF THE 6-9 DRIVE ARM ASSEMBLY AND REPAIR, REPLACEMENT OR MODIFICATION OF THE 4-5 ACTUATOR CRANK ARM ASSEMBLY AT INBOARD FLAP OUTBOARD SUPPORT NUMBER 3 AND 6 (SHEET 3 OF 4) Original Issue: May 27, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-57A0134 60 of 61 The text continues at https://openairdocs.org/service-documents/boeing/767-57a0134/file/c7f7662cdee7.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.