### Commercial Airplanes 

# 747 Service Bulletin Number: 747-27A2513 Original Issue: February 04, 2014 Revision 1: July 18, 2014 ATA System: 2731 2900 5510 SUBJECT:FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator Installation and Power Control Package Replacement 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.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 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 Unpublished Work.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: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 1 of 108 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 2 of 108 BOEING SERVICE BULLETIN 747-27A2513

BLANK PAGETable of Contents Revision Transmittal Sheet............................................ 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 15 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 15 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 16 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 24 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 25 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE. . . . . . . . . . . . . 34 FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE . . . . . . . . . . . . . . . . . . 36 FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE. . . . 39 FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE . . 47 FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE. . . . . . . 55 FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE. . . . . . . . . . . . . . . . 61 FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 3 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68 FIGURE 10: LOOSEN THE WIRE BUNDLE W1912 AND W4616 - RIGHT SIDE. . . . . . . . . . . . 73 FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE . . . . . . . . . . . . . . . . . 75 FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE . . . 78 FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE . 85 FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE. . . . . . . . . . . . . . . . . . . . . . . . . . 92 FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE. . . . . . 95 FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE. . . . . . . . . . . . . . 102 FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 4 of 108 BOEING SERVICE BULLETIN 747-27A2513

### Commercial Airplanes 

# 747 Service Bulletin Revision Transmittal Sheet Number: 747-27A2513 Original Issue: February 04, 2014 Revision 1: July 18, 2014 ATA System: 2731 2900 5510 SUBJECT:FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator Installation and Power Control Package Replacement 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. No more work is necessary on the airplanes changed in accordance with the original issue of this service bulletin. REASON FOR REVISION This revision is sent to make corrections to fastener length and wire clamp size, revised the manpower as found during the service bulletin validation. As a part of a service bulletin validation program, this change was completed on airplane RC008 by Service Bulletin 747-27A2513, Original Issue, before the release of Revision 1 of this service bulletin. The change completed on airplane RC008 by Service Bulletin 747-27A2513 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane RC008 has the configuration of a Group 1 airplane. These sections were changed: 1. Paragraph 1.A.1., Airplanes: Removed the Notes paragraph. 2. Paragraph 1.G., Manpower: Changed the task hour table. 3. Paragraph 1.J.1., References: Revised Existing Data step h and i. 4. Paragraph 2.B., Industry Support Information: Changed the warranty statement 5. Paragraph 2.C.1., Kits/Parts: Changed the part numbers, added extra quantity to the kit, and added the foot note (c). 6. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Changed the part number. 7. Figures 2 and 10: Revised the step table to add foot note (a). 8. Figures 4 and 7: Changed the step table and fastener table to correct the fastener length and clamp size, and added extra quantity to the extra parts table.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 5 of 1089. Figures 5: Changed sheet 2, step table, and added extra quantity to the extra parts table. 10. Figure 6: Changed sheet 2, step table, and added extra quantity to the extra parts table. Revised the foot note (d). 11. Figure 8: Changed sheet 1. 12. Figures 9: Changed the step table. 13. Figures 12, 13, 14 and 16: Changed the step table and fastener table to correct the fastener length and clamp size and added extra quantity to the extra parts table. 14. Figure 15: Changed sheet 3, step table and added extra quantity to the extra parts table. Revised the foot note (d). The data given in Information Notices 747-27A2513 IN 01 is included in this revision. 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 February 04, 2014 Original Issue: July 18, 2014 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 6 of 108 BOEING SERVICE BULLETIN 747-27A2513

### Commercial Airplanes 

# 747 Service Bulletin Summary Number: 747-27A2513 Original Issue: February 04, 2014 Revision 1: July 18, 2014 ATA System: 2731 2900 5510 SUBJECT:FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator Installation and Power Control Package Replacement CONCURRENT REQUIREMENTS None. BACKGROUND The change given in this service bulletin will help to prevent divergent flutter or unacceptable vibration that can occur in certain parts of the flight envelope if two hydraulic systems are not functional. Divergent flutter could result in the possible loss of control of the airplane. Boeing analysis found that the existing internal compensators to the two inboard elevator power control package (PCP) provided insufficient hydraulic capacity for retained stiffness of the elevator surface when two hydraulic systems are not functional. This service bulletin installs two (2) larger external compensators for each of the two (2) inboard elevator PCP. This replacement provides sufficient hydraulic capacity to prevent divergent flutter or unacceptable vibration. This service bulletin also refers to a Parker service bulletin. The Parker service bulletin gives instructions to rework the existing inboard elevator PCP that has internal compensators into the new inboard elevator PCP with internal compensators removed. This service bulletin gives instructions to replace the existing PCP internal compensators with larger external compensators and new design of inboard elevator PCP. Replace existing brackets and hydraulic tubing to accommodate the new external compensators. Boeing Service Related Problem (SRP) 747-SRP-27-0235 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD 27-13004 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. Reference Affected Planning Data Paragraph 1.A.2., Spares Affected Yes Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 7 of 108Reference Affected Planning Data Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required ACTION (PRR 86601-5) Open access to the left and right inboard elevator PCP. Remove the inboard elevator PCP, hydraulic tubes and associated hardware. Remove the clamps and loosen the wire bundles. Remove the existing electrical brackets and rivets. Install inboard and outboard compensator mounting brackets. Install inboard and outboard compensators, and hydraulic tubes. Route the wire bundles. Install inboard elevator PCP. Bleed the hydraulic systems. Do the operational test. Close access to the left and right inboard elevator PCP. Put the airplane back to a serviceable condition. EFFECTIVITY 747-8 and 747-8F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the change given in this service bulletin be done within 60 months after the Original Issue date of this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for airplanes in warranty as of January 28, 2013. 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 Boeing Supplied Kits/Parts. 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: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 8 of 108 BOEING SERVICE BULLETIN 747-27A2513Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 9 of 108 BOEING SERVICE BULLETIN 747-27A2513Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 10 of 108 BOEING SERVICE BULLETIN 747-27A2513

BLANK PAGE

### Commercial Airplanes 

# 747 Service Bulletin Number: 747-27A2513 Original Issue: February 04, 2014 Revision 1: July 18, 2014 ATA System: 2731 2900 5510 SUBJECT:FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator Installation and Power Control Package Replacement 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 86601-5 for data about this change.
DESCRIPTION CONFIGURATION GROUP 747-8 and 747-8F airplanes line number 1420 through 1434, and 1436 through 1491. - 1

Airplane Models: 747-8, 747-8F Group Variable Number1 RC001 - RC0081 RC022 - RC0301 RC501 - RC5111 RC521 - RC5281 RC541 1 RC546 - RC5491 RC551 - RC5631 RC571 - RC5821 RC601 - RC605

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 11 of 1082. Spares Affected Examine your spares supply for the parts or components identified below . If any parts or components are found, refer to Paragraph 2.C.2., Parts and Materials Supplied by the Operator for the recommended action. Serial Number Part Number N/A 327400-1009 B. Concurrent Requirements None. C. Reason The change given in this service bulletin will help to prevent divergent flutter or unacceptable vibration that can occur in certain parts of the flight envelope if two hydraulic systems are not functional. Divergent flutter could result in the possible loss of control of the airplane. Boeing analysis found that the existing internal compensators to the two inboard elevator power control package (PCP) provided insufficient hydraulic capacity for retained stiffness of the elevator surface when two hydraulic systems are not functional. This service bulletin installs two (2) larger external compensators for each of the two (2) inboard elevator PCP. This replacement provides sufficient hydraulic capacity to prevent divergent flutter or unacceptable vibration. This service bulletin also refers to a Parker service bulletin. The Parker service bulletin gives instructions to rework the existing inboard elevator PCP that has internal compensators into the new inboard elevator PCP with internal compensators removed. This service bulletin gives instructions to replace the existing PCP internal compensators with larger external compensators and new design of inboard elevator PCP. Replace existing brackets and hydraulic tubing to accommodate the new external compensators. Boeing Service Related Problem (SRP) 747-SRP-27-0235 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD 27-13004 is related to this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane RC008 by Service Bulletin 747-27A2513, Original Issue, before the release of Revision 1 of this service bulletin. The change completed on airplane RC008 by Service Bulletin 747-27A2513 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane RC008 has the configuration of a Group 1 airplane. Revision 1 is sent to make corrections to fastener length and wire clamp size, revised the manpower as found during the service bulletin validation. The data given in Information Notices 747-27A2513 IN 01 is included in this revision.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 12 of 108 BOEING SERVICE BULLETIN 747-27A2513D. Description Open access to the left and right inboard elevator PCP. Remove the inboard elevator PCP, hydraulic tubes and associated hardware. Remove the clamps and loosen the wire bundles. Remove the existing electrical brackets and rivets. Install inboard and outboard compensator mounting brackets. Install inboard and outboard compensators, and hydraulic tubes. Route the wire bundles. Install inboard elevator PCP. Bleed the hydraulic systems. Do the operational test. Close access to the left and right inboard elevator PCP. Put the airplane back to a serviceable condition. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue oft his service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance ZonesZone Model 313, 314, 334, 335, 339, 344, 345, 349 747-8, 747-8F 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. Boeing recommends that the change given in this service bulletin be done within 60 months after the Original Issue date of this service bulletin. 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. G. Manpower The table below shows an estimate of the task hours necessary to do this change 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 13 of 108 BOEING SERVICE BULLETIN 747-27A2513• Time to make the parts • Time to find the tools. Elapsed Hours Task Hours Number of Persons Task 1.00 1.00 1 Open Access 2.30 6.90 3 Figure 1 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 2.00 4.00 2 Figure 4 2.00 4.00 2 Figure 5 2.00 4.00 2 Figure 6 3.00 3.00 1 Figure 7 3.00 9.00 3 Figure 8 2.30 6.90 3 Figure 9 1.00 1.00 1 Figure 10 1.00 1.00 1 Figure 11 2.00 4.00 2 Figure 12 2.00 4.00 2 Figure 13 0.50 0.50 1 Figure 14 2.00 4.00 2 Figure 15 3.00 3.00 1 Figure 16 3.00 9.00 3 Figure 17 4.00 8.00 2 Test 1.00 1.00 1 Close Access 39.10 76.30 TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane + 91650.4 lb-in + 34.0 lb Group 1 I. Electrical Load Data Not changed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 14 of 108 BOEING SERVICE BULLETIN 747-27A2513J. References 1. Existing Data: a. Engineering Change Memo PRR 86601-5 b. Boeing Service Related Problem (SRP) 747-SRP-27-0235 c. Service Bulletin Index D6-30300 d. Standard Overhaul Practices Manual (SOPM) 20-41-01, 20-41-02, 20-43-03, 20-44-01, 20-50-01, 20-50-02, 20-50-05, 20-50-19 e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00 f. 747 Fleet Team Digest (FTD) 27-13004 g. 747-8 Aircraft Maintenance Manual (AMM) 06-09-06, 20-11-05, 20-11-18, 20-51-01, 27-31-07, 29-11-00 h. 747-8F Structural Repair Manual (SRM) 51-40-02, 51-40-04 i. 747-8P Structural Repair Manual (SRM) 51-40-02, 51-40-04 j. Parker Service Bulletin 327400-27-001 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: Title Drawing NumberWIRE BUNDLE INSTALLATION LH HORIZONTAL STABILIZER AND HORIZONTAL FUEL 288U8267WIRE BUNDLE INSTALLATION RH HORIZONTAL STABILIZER AND HORIZONTAL FUEL 288U8268POWER CONTROL ACTUATOR INSTL - INBOARD ELEVATOR 251U2500HYDRAULIC TUBING INSTL - SECTION 81 272U8101 HYDRAULIC TUBING INSTL - SECTION 82 272U8201SPAR INSTL - REAR, HORIZONTAL STAB 182U1000TRAILING EDGE ASSY - FIXED HORIZONTAL STABILIZER 183U1000 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 15 of 108 BOEING SERVICE BULLETIN 747-27A2513K. Publications Affected
1. Publications: Chapter-Section Publication 27-31 747 Aircraft Maintenance Manual27-31 747 Fault Isolation Manual 11-32, 27-21, 27-31 747 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 affects FCS but no new DTIs are necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information. M. Software Accomplishment Summary Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 16 of 108 BOEING SERVICE BULLETIN 747-27A25132. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kit is subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 17 of 108 BOEING SERVICE BULLETIN 747-27A2513REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issuedate of this Service Bulletin (US Dollars) ROLT as of the original issuedate of this Service Bulletin (Calendar Days) QTY Date Name Number

$51,789.00 525 2 December 20, 2013Top Kit - 747-8 INBOARD ELEVATORREMOTE COMPENSATOR - REVISION 015U1960-1 1 January 9, 2014 12 March 7, 20142 March 21, 2014 3 April 4, 20142 April 18, 20143 May 5, 20142 May 19, 20143 Jun 5, 20142 Jun 18, 20143 July 7, 20142 July 18, 20143 August 4, 20142 August 18, 2014 3 September 5, 2014 2 September 18, 2014 3 October 3, 2014 3 October 17, 2014 3 November 4, 2014

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 18 of 108 BOEING SERVICE BULLETIN 747-27A2513B. Industry Support Information Boeing warranty remedies are available for 747 airplanes in warranty as of January 28, 2013. For labor hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Fleet Support Contracts - Warranty. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable number(s) in your purchase order. In addition, labor hour and material reimbursement is available for the PCP modification included in this service bulletin for 747 airplanes in warranty as of January 28, 2013. The warranty remedies will expire eight years after the original release date of this service bulletin. A limited number of seed unit PCPs are available to support incorporation of this service bulletin. To inquire about availability and scheduling, please contact Boeing Retrofit and Modification via e-mail at the following address: MMRetrofitMods@boeing.com. Please reference the service bulletin number in your message C. Parts Necessary for Each Airplane 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE:One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. Figure Kit 12 8 7 6 5 4 Top Kit 1 1 1 1 1 1 015U1960-1 Figure Kit 17 16 15 14 13 Top Kit 1 1 1 1 1 015U1960-1 ALL KIT 015U1960-1

Notes Existing Part Number Name Figure
New Part Number 12 8 7 6 5 4 Qty MOUNTING BRACKET, LEFTOUTBD - COMPENSATOR, ELEVATOR PCU . . . . 1
. 252U3102-11

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 19 of 108 BOEING SERVICE BULLETIN 747-27A2513ALL KIT 015U1960-1

Notes Existing Part Number Name Figure
New Part Number 12 8 7 6 5 4 Qty MOUNTING BRACKET ASSY, RIGHT INBD - COMPENSATOR, ELEVATOR PCU 1
. . . . . 252U3102-12

MOUNTING BRACKET ASSY,LEFT INBD - COMPENSATOR, ELEVATOR PCU . . . . . 1 252U3102-13

(a), (b) 272U8190-26 TUBE ASSY

. . . 1
. . 272U8190-32 (a), (b) 272U8190-19 TUBE ASSY

. . . 1
. . 272U8190-34 TUBE ASSY

. . . 1
. . 272U8190-35 TUBE ASSY

. . . 1
. . 272U8190-36 (a), (b) 272U8190-17 TUBE ASSY

. . . 1
. . 272U8190-37 BRACKET ASSEMBLY . . . 1
. . 272U9405-25 BRACKET ASSEMBLY . . . . 1
. 287U0037-33 VALVE ASSY

. . . 2
. . 293W6132-1 REMOTE COMPENSATOR - UPPER RUDDER . . . 2
. . 463430-1001 (a), (b) BACT16BM100810P TEE
. . . 1
. . AS1009W080810 CLAMP,LOOP

. . . 1
. . AS21919WCE08 CLAMP,LOOP

. . . 2
. . AS21919WCE10 TEE
. . . 1
. . AS4140V100808P (BACT16BT100808P optional) NUT, TUBE, BULKHEAD . . . 1
. . AS5178W10 MARKER
. 2
. . . . BAC27EHY242 BOLT, PROTRUDING HD 3
. . . . 3 BACB30MY10K12X

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 20 of 108 BOEING SERVICE BULLETIN 747-27A2513ALL KIT 015U1960-1

Notes Existing Part Number Name Figure
New Part Number 12 8 7 6 5 4 Qty (c) BOLT, PROTRUD- ING HD 8
. . . . 8 BACB30MY10K8X (c) BOLT, PROTRUD- ING HD . . . . 3
. BACB30MY8K11X BOLT, PROTRUDING HD 1
. . . . 2 BACB30MY8K12X (c) BOLT, PROTRUD- ING HD . . . . 5
. BACB30MY8K14X (c) BOLT, PROTRUD- ING HD . . . . 3
. BACB30MY8K6X (c) BOLT, PROTRUD- ING HD . . . . 3
. BACB30MY8K9X (c) BOLT, HEX HEAD

. . . 9
. . BACB30NM4K11 CLAMP, WIRE BUNDLE . . 3
. . . BACC10GU103 (c) COLLAR 13
. . . . 13 BACC30M10 (c) COLLAR 1
. . . 15 1 BACC30M8 ELBOW, SWVLRDCR, 45 . . . 1
. . BACE21AU1010W FILLER, FLAT 1
. . . . 1 BACF3F015X026NN RADIUS FILLER

. . . . 2
. BACF3H10RF010HG FILLER, RECTANGULAR 2
. . . . 2 BACF3H10RF024HF FILLER, RECTANGULAR . . . . 2
. BACF3H10RF040HF NUT
. . . 2
. . BACN10YR3CD NUT
. . . 9
. . BACN11Z4CD SCREW

. . . 5
. . BACS12GU3K10 SCREW

. . 3
. . . BACS12GU3K26 SCREW

. . . 1
. . BACS12GU3K8 SPACER

. . . 2
. . BACS18AF4 TEE, SWIVEL ON RUN . . . 1
. . BACT16AY080808W

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 21 of 108 BOEING SERVICE BULLETIN 747-27A2513ALL KIT 015U1960-1

Notes Existing Part Number Name Figure
New Part Number 12 8 7 6 5 4 Qty WASHER

. . . 9
. . BACW10BP4AC WASHER

. . . 6
. . NAS1149D0316J WASHER

. . 4
. . . NAS1149D0332J WASHER, PLAIN

. . . 1
. . NAS1149D1490J WASHER, PLAIN

. . . 9
. . NAS1149E0432P SPACERS FOR RIVETS . . 2
. . . NAS42DD6-64FC (a) This part is used in production. (b) You cannot use the existing part to replace the new or changed part. (c) There are more parts than are necessary. ALL KIT 015U1960-1

Notes Existing Part Number Name Figure
New Part Number 17 16 15 14 13Qty MOUNTING BRACKET, RIGHTOUTBD - COMPENSATOR, ELEVATOR PCU . . . . 1 252U3102-10

(a), (b) 272U8290-7 TUBE ASSY

. . 1
. . 272U8290-34 (a), (b) 272U8290-9 TUBE ASSY

. . 1
. . 272U8290-35 TUBE ASSY

. . 1
. . 272U8290-36 TUBE ASSY

. . 1
. . 272U8290-37 TUBE ASSY

. . 1
. . 272U8290-38 (a), (b) 272U8290-10 TUBE ASSY

. . 1
. . 272U8290-39 (a), (b) 272U8290-20 TUBE ASSY

. . 1
. . 272U8290-40 VALVE ASSY

. . 2
. . 293W6132-1

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Notes Existing Part Number Name Figure
New Part Number 17 16 15 14 13Qty REMOTE COMPENSATOR - UPPER RUDDER . . 2
. . 463430-1001
BRACKET

. . . 1
. 69B80913-5 TEE, FLARELESS

. . 1
. . AS1005W100808 CLAMP,LOOP

. . 6
. . AS21919WCE08 (a), (b) BACT16BM100810P TEE
. . 1
. . AS4134V100808P (BACT16BN100808P optional) MARKER 2
. . . . BAC27EHY242 BOLT, PROTRUDING HD . . . . 2 BACB30MY8K11X BOLT, PROTRUDING HD . . . . 4 BACB30MY8K14X BOLT, PROTRUDING HD . . . . 2 BACB30MY8K9X (c) BOLT, HEX HEAD

. . 9
. . BACB30NM4K11 CLAMP, WIRE BUNDLE . 2
. . . BACC10GU103 (c) COLLAR

. . . . 13 BACC30M8 ELBOW, SWVLRDCR, 90 . . 4
. . BACE21AW0808W RADIUS FILLER

. . . . 2 BACF3H10RF010HG FILLER, RECTANGULAR . . . . 2 BACF3H10RF040HF NUT,CLIP-ON

. . 1
. . BACN10YD1 NUT 1
. 3
. . BACN10YR3CD NUT
. . 9
. . BACN11Z4CD RIVET, UNIVERSAL HD . . . 4
. BACR15BB5D8C SCREW

. 2
. . . BACS12GU3K26 SCREW

. . 4
. . BACS12GU3K8 (c) SPACER

. . 5
. . BACS18AF4

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Notes Existing Part Number Name Figure
New Part Number 17 16 15 14 13Qty TEE, SWIVEL ON RUN . . 1
. . BACT16AY080808W WASHER

. . 9
. . BACW10BP4AC WASHER

. . 8
. . NAS1149D0316J WASHER

. 4
. . . NAS1149D0332J WASHER, PLAIN

. . 2
. . NAS1149D1432J WASHER, PLAIN

. . 9
. . NAS1149E0432P SPACERS FOR RIVETS . 2
. . . NAS42DD6-64FC (a) This part is used in production. (b) You cannot use the existing part to replace the new or changed part. (c) There are more parts than are necessary. 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.
Notes Existing Part Number Name Qty Part Number/ Specification (b), (c), (d), (e) 327400-1009 POWER CONTROL PACKAGE - INBOARD ELEVATOR 2 327400-1011 (a) Chemical Conversion Coating 5 Oz ALODINE 600 (f) Clear Skydrol Resistant Topcoating 2 Oz BAC5710, TYPE 41 (a) Primer 2 Oz BMS 10-11, TYPE 1 (a) Gloss Enamel 2 Oz BMS10-60, TYPE 1 (a) Sealant 10 Oz BMS5-142, TYPE II (a) Sealant 20 Oz BMS5-45

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 24 of 108 BOEING SERVICE BULLETIN 747-27A2513Notes Existing Part Number Name Qty Part Number/ Specification Lockwire 3 ft MS20995NC40(MS20995C41 optional) (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) You cannot use the existing part to replace the new or changed part. (d) Parker service bulletin 327400-27-001 gives instructions to change the existing part to the new part.(e) The Boeing part specification for the new part is S252U201-4. The Boeing part specification for the existing part is S252U201-3. (f) This is a two part protective coating available from Akzo Nobel Aerospace Coatings 1 East Water Street, Waukegan, IL 60085. Refer to SOPM 20-44-01 for the recommended materials. 3. Parts Modified and Reidentified None. 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: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 25 of 108 BOEING SERVICE BULLETIN 747-27A2513Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 26 of 108 BOEING SERVICE BULLETIN 747-27A2513

BLANK PAGE3. 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 747-8 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 747-8 Airplane 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 747-8 Airplane Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 27 of 108 BOEING SERVICE BULLETIN 747-27A25137. 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. 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. 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. 10. 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. 11. 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. 12. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 13. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 15. Some steps in the Work Instructions are identified as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps identified as RC must be done to comply with the AD. Alternative procedures for steps not identified with RC can be used if the RC steps can still be done as specified, and the airplane can be put back in a serviceable condition. An Alternative Method of Compliance (AMOC) is not necessary for deviations to steps that are not identified as RC. B. WORK INSTRUCTIONS 1. Open access door panels 344HBR, 345DBR, 344AT, 344GBR, 344JBR, and 344KBR, right side. Refer to 747-8 AMM 06-09-06. 2. Open access door panels 334HBL, 335DBL, 334AT, 334GBL, 334JBL, and 334KBL, left side. Refer to 747-8 AMM 06-09-06. 3. Open access door panels 338AZ, 339AZ and 349AZ. Refer to 747-8 AMM 06-09-06.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 28 of 108 BOEING SERVICE BULLETIN 747-27A25134. Horizontal stabilizer rear spar rework - left side. Do these steps: a. RC - Remove the inboard elevator power control package (PCP) and hydraulic tubes in accordance with FIGURE 1. b. Loosen the wire bundles W1656 and W4615 in accordance with FIGURE 2. c. Remove the fasteners and brackets in accordance with FIGURE 3. d. RC - Install the inboard compensator mounting bracket in accordance with FIGURE 4. e. RC - Install the outboard compensator mounting bracket in accordance with FIGURE 5. f. RC - Install the compensators and hydraulic tubes in accordance with FIGURE 6. g. Route the wire bundles W1656 and W4615 in accordance with FIGURE 7. h. RC - Install the inboard elevator PCP in accordance with FIGURE 8. 5. Horizontal stabilizer rear spar rework - right side. Do these steps: a. RC - Remove inboard elevator PCP and hydraulic tubes in accordance with FIGURE 9. b. Loosen the wire bundles W1912 and W4616 in accordance with FIGURE 10. c. Remove the fasteners and brackets in accordance with FIGURE 11. d. RC - Install the inboard compensator mounting bracket in accordance with FIGURE 12. e. RC - Install the outboard compensator mounting bracket in accordance with FIGURE 13. f. RC - Install the bracket in accordance with FIGURE 14. g. RC - Install the compensators and hydraulic tubes in accordance with FIGURE 15. h. Route the wire bundles W1912 and W4616 in accordance with FIGURE 16. i. RC - Install the inboard elevator PCP in accordance with FIGURE 17. 6. Bleed the hydraulic system 1, 2, 3 and 4. Refer to 747-8 AMM 29-11-00 as an accepted procedure. 7. RC - Do an Operational Test of each inboard elevator PCP. Refer to 747-8 AMM 27-31-07 as an accepted procedure. 8. Close access door panels 344HBR, 345DBR, 344AT, 344GBR, 344JBR, and 344KBR, right side. Refer to 747-8 AMM 06-09-06. 9. Close access door panels 334HBL, 335DBL, 334AT, 334GBL, 334JBL, and 334KB, left side. Refer to 747-8 AMM 06-09-06. 10. Close access door panels 338AZ, 339AZ and 349AZ. Refer to 747-8 AMM 06-09-06. 11. Put the airplane back to serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1: July 18, 2014 29 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - LEFT SIDE (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 30 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - LEFT SIDE (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 31 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step Keep all the screw, washers and nut. 2 - Clamp Remove / Keep 1 (a) 4 - Hose Assy Remove / Keep 2 Refer to 747-8 AMM27-31-07 as an accepted procedure. 1 327400-1009 Power Control Package Inboard Elevator Remove 3 Keep all the screws, washers and clip nuts. 2 - Clamp Remove 4 (b) 1 272U8190-19 Tube Assy Remove

FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - LEFT SIDE (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 32 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Keep all the fasteners and hardware. 1 - Clamp Block Assy Remove / Keep 5 Keep all the screws, washers and five (5) clip nuts. 6 - Clamp Remove / Keep 6 (b) 1 272U8190-26 Tube Assy Remove Keep all the screws, washers and clip nuts. 6 - Clamp Remove / Keep 7 (b) 1 272U8190-17 Tube Assy Remove 1 - Lock Nut Remove 8 1 - Washer Remove 1 BACT16BM100810P Tee Remove 1 - Screw Remove 9 1 - Clamp Remove / Keep 1 - Washer Remove / Keep 1 - Clip Nut Remove (a) Refer to 747-8 AMM 20-11-18 as an accepted procedure. (b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.

FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - LEFT SIDE (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 33 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 34 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step 2 - Screw Remove 1 2 - Clamp Remove 2 - Washer Remove 12 - Screw Remove / Keep 2 12 - Washer Remove / Keep 12 - Clamp Remove / Keep (a) - W1656, W4615 Wire Bundle Loosen 3 (a) Make sure cover wire bundle with plastic and tape to protect them from the chips.

FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 35 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 36 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 37 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step 4 - Bolt Remove 1 2 287U0037-17 Bracket Remove 5 - Rivet Remove 2 1 - Bolt Remove 3 2 - Rivet Remove 4 1 287U0037-33 Bracket Remove 8 - Rivet Remove 5

FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 38 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 1 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 39 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 2 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 40 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 3 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 41 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step On the fwd side, the fillers are under the collars. 2 BACF3H10RF024HF FILLER, RECTANGU- LAR Put / Hold 1 Two (2) holes for each location. Back drill the holes through radius filler. Refer to Fastener Code table for the hole diameter. 4 - Hole Drill / Ream 2

- - Hole Clean/Deburr On mating surfaces of filler, web. Refer to SOPM 20-50-19as an accepted procedure. - BMS5-45 Sealant Apply 3

On the fwd side, under the collar. One (1) for each location. 2 BACF3H10RF024HF FILLER, RECTANGU- LAR Install (New)
Refer to FastenerCode table for fastener part number. - - Fastener Install (New) (d) 1 - Rivet Microshave 4

- - Surface Clean (a) - ALODINE 600 Chemical Conversion Coating Apply (b) - BMS 10-11, TYPE 1 Primer Apply Optional, (e)
- BMS10-60, TYPE 1 Gloss Enamel Apply As shown in figure. 1 252U3102-13 MOUNTING BRACKET ASSY, LEFT INBD -COMPENSATOR, ELEVATOR PCU Put / Hold 5
As shown in figure, the filler is between the bracket and the spar. 1 BACF3F015X026NN FILLER, FLAT Put / Hold

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 4 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 42 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Back drill the holes through the filler and bracket. Refer to Fastener Code tablefor the hole diameter. 5 - Hole Drill / Ream 6

Back drill the holes through the bracket.Minimum edge margin of 0.30 is acceptable at this location. Refer to Fastener Code table for the hole diameter. 1 - Hole Drill / Ream 7

- 252U3102-13 MOUNTING BRACKET ASSY, LEFT INBD -COMPENSATOR, ELEVATOR PCU Disassemble 8

- BACF3F015X026NN FILLER, FLAT Disassemble To the bracket, filler and the web - - Hole Clean/Deburr Non-designatedbond. Refer to SWPM 20-20-00, Cleaning Procedure 1, as an accepted procedure. - - Surface Clean 9

(a) - ALODINE 600 Chemical Conversion Coating Apply To mating surface of bracket and web. Refer to SWPM 20- 20-00, Category 2 fay surface bond, asan accepted procedure. - BMS5-45 Sealant Apply

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 5 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 43 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Refer to SWPM 20- 20-00, Procedure 5,as an accepted procedure. - - Surface Clean 10
To mating surface of bracket, filler, web. Refer to SOPM 20-50-19 as an accepted procedure. - BMS5-45 Sealant Apply

1 252U3102-13 MOUNTING BRACKET ASSY, LEFT INBD -COMPENSATOR, ELEVATOR PCU Install (New) 11

The filler is between the bracket and the spar. 1 BACF3F015X026NN FILLER, FLAT Install (New)
Refer to FastenerCode table for fastener part number. - - Fastener Install (New) (c) - - Resistance Measure 12 Apply a fillet seal around the bracket where it connects to the structure. Refer to SOPM 20-50-19as an accepted procedure. - BMS5-142, TYPE II Sealant Apply 13

(a) - ALODINE 600 Chemical Conversion Coating Apply 14 (b) - BMS 10-11, TYPE 1 Primer Apply (a) Apply to bare metal. Refer to SOPM 20-43-03, as an accepted procedure.(b) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure. (c) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as an accepted procedure.(d) Microshave the bucked tail of the existing rivet as necessary to allow the clearance for the bracket installation. Complete removal of bucked tail is acceptable. (e) Refer to SOPM 20-41-01 code F-14.9812, as an accepted procedure.

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 6 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 44 of 108 BOEING SERVICE BULLETIN 747-27A2513The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code Install the fastener wet with sealant BMS5-45. (a) 0.325 - 0.328 7 BACB30MY10K8X BOLT, PROTRUDING HD A (b) - 7 BACC30M10 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.325 - 0.328 2 BACB30MY10K12X BOLT, PROTRUDING HD B (b) - 2 BACC30M10 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 1 BACB30MY8K12X BOLT, PROTRUDING HD C (b) - 1 BACC30M8 COLLAR (a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02 (b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to SOPM 20-50-19 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 4 BACC30M10 COLLAR 1 BACB30MY10K12X BOLT, PROTRUDING HD 1 BACB30MY8K12X BOLT, PROTRUDING HD

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 7 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 45 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name 1 BACB30MY10K8X BOLT, PROTRUDING HD

FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 8 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 46 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 1 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 47 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 2 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 48 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 3 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 49 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step As shown in figure. 1 252U3102-11 MOUNTING BRACK- ET, LEFT OUTBD -COMPENSATOR, ELEVATOR PCU Put / Hold 1

On the fwd side, the fillers are under the collars. 2 BACF3H10RF040HF FILLER, RECTANGU- LAR Put / Hold
The radius fillers are between the head offasteners and bracket. 2 BACF3H10RF010HG RADIUS FILLER Put / Hold

Back drill the holes through bracket and radius fillers. Referto Fastener Code table for the hole diameter. 8 - Hole Drill / Ream 2

To the bracket, fillers and web. - - Hole Deburr Non-designatedbond. Refer to SWPM 20-20-00, Cleaning Procedure 1, as an accepted procedure. - - Surface Clean 3

(b) - ALODINE 600 Chemical Conversion Coating Apply To mating surface of bracket, fillers. Refer to SWPM 20-20-00,Category 2 fay surface bond, as an accepted procedure. - BMS5-45 Sealant Apply

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 4 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 50 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Refer to SWPM 20- 20-00, Procedure 5,as an accepted procedure. - - Surface Clean 4
To mating surface of bracket, fillers, web. Refer to SOPM 20-50-19 as an accepted procedure. - BMS5-45 Sealant Apply

1 252U3102-11 MOUNTING BRACK- ET, LEFT OUTBD -COMPENSATOR, ELEVATOR PCU Install (New) 5

On the fwd side, under the collars. 2 BACF3H10RF040HF FILLER, RECTANGU- LAR Install (New) Refer to FastenerCode table for fastener part number. - - Fastener Install (New) To mating surface of fillers. Refer to SOPM 20-50-19 asan accepted procedure. - BMS5-45 Sealant Apply 6

Under the head of fasteners. 2 BACF3H10RF010HG RADIUS FILLER Install (New) Refer to FastenerCode table for fastener part number. - - Fastener Install (New) (a) - - Resistance Measure 7 As shown in figure. 1 287U0037-33 BRACKET ASSEMBLY Put / Hold 8 Back drill the holesthrough bracket. Refer to Fastener Codetable for the hole diameter. 2 - Hole Drill / Ream 9

- - Hole Deburr

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 5 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 51 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Non-designatedbond. Refer to SWPM 20-20-00, Cleaning Procedure 1, as an accepted procedure. - - Surface Clean 10

(b) - ALODINE 600 Chemical Conversion Coating Apply To mating surface of bracket. Refer to SWPM 20-20-00,Category 2 fay surface bond, as an accepted procedure. - BMS5-45 Sealant Apply

1 287U0037-33 BRACKET ASSEMBLY Install (New) 11 Refer to FastenerCode table for fastener part number. - - Fastener Install (New) (a) - - Resistance Measure 12 Apply a fillet seal around the bracket where it connects to the structure. Refer to SOPM 20-50-19as an accepted procedure. - BMS5-142, TYPE II Sealant Apply 13

(b) - ALODINE 600 Chemical Conversion Coating Apply 14 (c) - BMS 10-11, TYPE 1 Primer Apply (a) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as an accepted procedure. (b) Apply to bare metal surfaces. Refer to SOPM 20-43-03, as an accepted procedure.(c) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure.

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 6 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 52 of 108 BOEING SERVICE BULLETIN 747-27A2513The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 4 BACB30MY8K14X BOLT, PROTRUDING HD D (b) - 4 BACC30M8 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 2 BACB30MY8K9X BOLT, PROTRUDING HD E (b) - 2 BACC30M8 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 2 BACB30MY8K11X BOLT, PROTRUDING HD F (b) - 2 BACC30M8 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 2 BACB30MY8K6X BOLT, PROTRUDING HD G (b) - 2 BACC30M8 COLLAR (a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02 (b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to SOPM 20-50-19 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 5 BACC30M8 COLLAR

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 7 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 53 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name 1 BACB30MY8K14X BOLT, PROTRUDING HD 1 BACB30MY8K9X BOLT, PROTRUDING HD 1 BACB30MY8K11X BOLT, PROTRUDING HD 1 BACB30MY8K6X BOLT, PROTRUDING HD

FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE (SHEET 8 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 54 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 55 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 56 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 57 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step 2 463430-1001 REMOTE COMPEN- SATOR - UPPER RUDDER Install (New) 1
Under the head of fastener. Four (4) per Compensator 8 BACW10BP4AC WASHER Install (New) 2 Four (4) per Compensator 8 BACB30NM4K11 BOLT, HEX HEAD Install (New) Four (4) per Compensator 8 NAS1149E0432P WASHER, PLAIN Install (New) Four (4) per Compensator. Refer to 747-8P SRM 51-40- 04 and 747-8F SRM51-40-04 as an accepted procedure for the torque value. 8 BACN11Z4CD NUT Install (New)

Onto back of existing bracket 272U9405-10 1 272U9405-25 BRACKET ASSEMBLY Install (New) 3
To the tube assembly 272U8190-10. 1 - Clamp Install (Kept) 4 1 - Washer Install (Kept) 1 BACS12GU3K10 SCREW Install (New) Connect the TEE to the Compensator, (b), (c) 1 AS4140V100808P (BACT16BT100808P optional) TEE Install (New) 5 (b), (c) 1 272U8190-32 TUBE ASSY Install (New) 6 Use the kept screws, washers and clipnuts for the installation. 5 - Clamp Install (Kept)

Use the kept fasteners and hardware. 1 - Clamp Block Assy Install (Kept) 7

FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 58 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step (d) 1 BACS18AF4 SPACER Install (New) 8 1 AS21919WCE10 CLAMP,LOOP Install (New) 1 NAS1149D0316J WASHER Install (New) 1 BACS12GU3K10 SCREW Install (New) (b), (c) 1 272U8190-37 TUBE ASSY Install (New) 9 Use all kept screws, washers and clipnuts for the installation. 6 - Clamp Install (New)
(b), (c) 1 AS1009W080810 TEE Install (New) 10 1 NAS1149D1490J WASHER, PLAIN Install (New) 1 AS5178W10 NUT, TUBE, BULK- HEAD Install (New) (b), (c). Torque thevalve to 40-80 inchpounds to make sure the valve is seated. 1 293W6132-1 VALVE ASSY Install (New) 11

(a) - MS20995NC40 (MS20995C41 optional) Lockwire Install (New) Connect the tube assy to the tee and compensator, (b), (c) 1 272U8190-36 TUBE ASSY Install (New) 12

1 - Clamp Install (Kept) 1 - Washer Install (Kept) 1 BACS12GU3K10 SCREW Install (New) Connect the elbow to the tee. (b), (c) 1 BACE21AU1010W ELBOW, SWVL-RDCR, 45 Install (New) 13 Connect the tubeassy to the Compensator, (b), (c) 1 272U8190-34 TUBE ASSY Install (New) 14 Use all kept screw, washer and clip nut for the installation. 1 - Clamp Install (Kept) (b), (c) 1 BACT16AY080808W TEE, SWIVEL ON RUN Install (New) 15

FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 59 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step (b), (c). Torque thevalve to 40-80 inchpounds to make sure the valve is seated. 1 293W6132-1 VALVE ASSY Install (New) 16

(a) - MS20995NC40 (MS20995C41 optional) Lockwire Install (New) Connect the tubeassy to the Compensator and Tee. (b), (c) 1 272U8190-35 TUBE ASSY Install (New) 17

Use all kept screw, washer and clip nut for the installation. 1 - Clamp Install (Kept)

1 AS21919WCE08 CLAMP,LOOP Install (New) 18 (d) 1 BACS18AF4 SPACER Install (New) 2 NAS1149D0316J WASHER Install (New) 1 BACS12GU3K8 SCREW Install (New) 1 BACN10YR3CD NUT Install (New) (a) Double-twist method. Refer to SOPM 20-50-02 as an accepted procedure. (b) Refer to 747-8 AMM 20-11-05 as an accepted procedure. (c) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value. (d) Use spacers as necessary to make sure that the clamp holds the tube with minimum force. The maximum permitted quantity of spacers for each clamp is 4. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACW10BP4AC WASHER 1 NAS1149E0432P WASHER, PLAIN 1 BACN11Z4CD NUT 3 NAS1149D0316J WASHER 2 BACS12GU3K10 SCREW 1 BACN10YR3CD NUT 1 AS21919WCE10 CLAMP,LOOP 1 BACB30NM4K11 BOLT, HEX HEAD

FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 60 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 61 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 62 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step

- W1656, W4615 Wire Bundle Route 1 One for each location 2 BACC10GU103 CLAMP, WIRE BUN- DLE Install (New) 2 One for each location 2 NAS42DD6-64FC SPACERS FOR RIV- ETS Install (New) One for each location 2 NAS1149D0332J WASHER Install (New) One for each location 2 BACS12GU3K26 SCREW Install (New) 12 - Clamp Install (Kept) 3 12 - Washer Install (Kept) 12 - Screw Install (Kept) The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 2 NAS1149D0332J WASHER 1 BACC10GU103 CLAMP, WIRE BUN- DLE 1 BACS12GU3K26 SCREW

FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 63 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 64 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 65 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 66 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step Refer to 747-8 AMM27-31-07 as an accepted procedure. 1 327400-1011 POWER CONTROL PACKAGE - INBOARD ELEVATOR Install (New) 1 (a) (b) 3 - Hose Assy Install (Kept) 2 Rotate the hose and elbow to maintain minimum 0.5 inches clearance from structure and tubing. (a) (b) 1 - Hose Assy Install (Kept) 3

To 360 inch-pounds. - - Nut Torque 4 As shown in figure. Refer to SOPM 20-50-05 as an accepted procedure. 2 BAC27EHY242 MARKER Install (New) 5

Refer to SOPM 20-44-01, as an accepted procedure. - BAC5710, TYPE 41 Clear Skydrol Resistant Topcoating Apply 6 (a) Refer to 747-8 AMM 20-11-18 as an accepted procedure. (b) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value.

FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 67 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - RIGHT SIDE (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 68 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - RIGHT SIDE (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 69 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - RIGHT SIDE (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 70 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - RIGHT SIDE (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 71 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step Keep the screws, washers, nut and clip nut. 3 - Clamp Remove / Keep 1 (a) 4 - Hose Assy Remove / Keep 2 Refer to 747-8 AMM27-31-07 as an accepted procedure. 1 327400-1009 Power Control Package Inboard Elevator Remove 3 Keep all the fasteners and hardware. 1 - Clamp Block Assy Remove / Keep 4 Keep all the screws, washers and clip nuts. 6 - Clamp Remove / Keep 5 (b) 1 272U8290-20 Tube Assy Remove Keep all the screws, washers and clip nuts. 6 - Clamp Remove / Keep 6 (b) 1 272U8290-7 Tube Assy Remove Keep all the screws, washers and clip nuts. 4 - Clamp Remove / Keep 7 (b) 1 272U8290-10 Tube Assy Remove Keep all the screws, washers and clip nuts. 2 - Clamp Remove / Keep 8 (b) 1 272U8290-9 Tube Assy Remove 1 - Lock Nut Remove / Keep 9 1 - Washer Remove 1 BACT16BM100810P Tee Remove 10 (a) Refer to 747-8 AMM 20-11-18 as an accepted procedure. (b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.

FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL - RIGHT SIDE (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 72 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 10: LOOSEN THE WIRE BUNDLE W1912 AND W4616 - RIGHT SIDE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 73 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step 2 - Screw Remove 1 2 - Clamp Remove 2 - Washer Remove 14 - Screw Remove / Keep 2 14 - Washer Remove / Keep 14 - Clamp Remove / Keep (a) - W1912, W4616 Wire Bundle Loosen 3 (a) Make sure cover wire bundle with plastic and tape to protect them from the chips.

FIGURE 10: LOOSEN THE WIRE BUNDLE W1912 AND W4616 - RIGHT SIDE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 74 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 75 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 76 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step 4 - Bolt Remove 1 2 287U0037-17 Bracket Remove 5 - Rivet Remove 2 1 - Bolt Remove 3 3 - Rivet Remove 4 1 272U8212-7 Bracket Remove 5 - Rivet Remove 5

FIGURE 11: FASTENERS AND BRACKETS REMOVAL - RIGHT SIDE (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 77 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 1 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 78 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 79 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 80 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step On the fwd side, the fillers are under the collars. 2 BACF3H10RF024HF FILLER, RECTANGU- LAR Put / Hold 1 Two (2) holes for each location. Back drill the holes through radius filler. Refer to Fastener Code table for the hole diameter. 4 - Hole Drill / Ream 2

- - Hole Clean/Deburr On mating surfaces of filler, web. Refer to SOPM 20-50-19as an accepted procedure. - BMS5-45 Sealant Apply 3

On the fwd side, under the collar. One (1) for each location. 2 BACF3H10RF024HF FILLER, RECTANGU- LAR Install (New)
Refer to FastenerCode table for fastener part number. - - Fastener Install (New) (d) 1 - Rivet Microshave 4

- - Surface Clean (a) - ALODINE 600 Chemical Conversion Coating Apply (b) - BMS 10-11, TYPE 1 Primer Apply Optional, (e)
- BMS10-60, TYPE 1 Gloss Enamel Apply As shown in figure. 1 252U3102-12 MOUNTING BRACKET ASSY, RIGHT INBD -COMPENSATOR, ELEVATOR PCU Put / Hold 5
As shown in figure, the filler is between the bracket and the spar. 1 BACF3F015X026NN FILLER, FLAT Put / Hold

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 4 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 81 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Back drill the holes through the filler and bracket. Refer to Fastener Code tablefor the hole diameter. 5 - Hole Drill / Ream 6

Back drill the holes through the bracket.Reduced edge margin of 0.30 is acceptable at this location. Refer to Fastener Code table for the hole diameter. 1 - Hole Drill / Ream 7

- 252U3102-12 MOUNTING BRACKET ASSY, RIGHT INBD -COMPENSATOR, ELEVATOR PCU Disassemble 8

- BACF3F015X026NN FILLER, FLAT Disassemble To the bracket, filler and the web - - Hole Clean/Deburr Non-designatedbond. Refer to SWPM 20-20-00, Cleaning Procedure 1, as an accepted procedure. - - Surface Clean 9

(a) - ALODINE 600 Chemical Conversion Coating Apply To mating surface of bracket and web. Refer to SWPM 20- 20-00, Category 2 fay surface bond, asan accepted procedure. - BMS5-45 Sealant Apply

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 82 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Refer to SWPM 20- 20-00, Procedure 5,as an accepted procedure. - - Surface Clean 10
To mating surface of bracket, filler, web. Refer to SOPM 20-50-19 as an accepted procedure. - BMS5-45 Sealant Apply

1 252U3102-12 MOUNTING BRACKET ASSY, RIGHT INBD -COMPENSATOR, ELEVATOR PCU Install (New) 11

The filler is between the bracket and the spar. 1 BACF3F015X026NN FILLER, FLAT Install (New)
Refer to FastenerCode table for fastener part number. - - Fastener Install (New) (c) - - Resistance Measure 12 Apply a fillet seal around the bracket where it connects to the structure. Refer to SOPM 20-50-19as an accepted procedure. - BMS5-142, TYPE II Sealant Apply 13

(a) - ALODINE 600 Chemical Conversion Coating Apply 14 (b) - BMS 10-11, TYPE 1 Primer Apply (a) Apply to bare metal. Refer to SOPM 20-43-03, as an accepted procedure.(b) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure. (c) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as an accepted procedure.(d) Microshave the bucked tail of the existing rivet as necessary to allow the clearance for the bracket installation. Complete removal of bucked tail is acceptable. (e) Refer to SOPM 20-41-01 code F-14.9812, as an accepted procedure.

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 83 of 108 BOEING SERVICE BULLETIN 747-27A2513The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code Install the fastener wet with sealant BMS5-45. (a) 0.325 - 0.328 7 BACB30MY10K8X BOLT, PROTRUDING HD A (b) - 7 BACC30M10 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.325 - 0.328 2 BACB30MY10K12X BOLT, PROTRUDING HD B (b) - 2 BACC30M10 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 1 BACB30MY8K12X BOLT, PROTRUDING HD C (b) - 1 BACC30M8 COLLAR (a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02 (b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to SOPM 20-50-19 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 4 BACC30M10 COLLAR 1 BACB30MY10K12X BOLT, PROTRUDING HD 1 BACB30MY10K8X BOLT, PROTRUDING HD

FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 7 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 84 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 1 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 85 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 86 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 87 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step As shown in figure. 1 252U3102-10 MOUNTING BRACK- ET, RIGHT OUTBD -COMPENSATOR, ELEVATOR PCU Put / Hold 1

On the fwd side, the fillers are under the collars. 2 BACF3H10RF040HF FILLER, RECTANGU- LAR Put / Hold
The radius fillers are between the head offasteners and bracket. 2 BACF3H10RF010HG RADIUS FILLER Put / Hold

Back drill the holes through bracket and radius fillers. Referto Fastener Code table for the hole diameter. 8 - Hole Drill / Ream 2

To the bracket, fillers and web. - - Hole Deburr Non-designatedbond. Refer to SWPM 20-20-00, Cleaning Procedure 1, as an accepted procedure. - - Surface Clean 3

(b) - ALODINE 600 Chemical Conversion Coating Apply To mating surface of bracket, fillers, web. Refer to SWPM 20- 20-00, Category 2 fay surface bond, asan accepted procedure. - BMS5-45 Sealant Apply

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 4 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 88 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step Refer to SWPM 20- 20-00, Procedure 5,as an accepted procedure. - - Surface Clean 4
To mating surface of bracket, fillers, web. Refer to SOPM 20-50-19 as an accepted procedure. - BMS5-45 Sealant Apply

1 252U3102-10 MOUNTING BRACK- ET, RIGHT OUTBD -COMPENSATOR, ELEVATOR PCU Install (New) 5

On the fwd side, under the collars 2 BACF3H10RF040HF FILLER, RECTANGU- LAR Install (New) Refer to FastenerCode table for fastener part number. - - Fastener Install (New) To mating surface of fillers, Refer to SOPM 20-50-19 asan accepted procedure. - BMS5-45 Sealant Apply 6

Under the head of fasteners. 2 BACF3H10RF010HG RADIUS FILLER Install (New) Refer to FastenerCode table for fastener part number. - - Fastener Install (New) (a) - - Resistance Measure 7 Apply a fillet seal around the bracket where it connects to the structure. Refer to SOPM 20-50-19as an accepted procedure. - BMS5-142, TYPE II Sealant Apply 8

(b) - ALODINE 600 Chemical Conversion Coating Apply 9 (c) - BMS 10-11, TYPE 1 Primer Apply (a) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 89 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step (b) Apply to bare metal surfaces. Refer to SOPM 20-43-03, as an accepted procedure.(c) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 4 BACB30MY8K14X BOLT, PROTRUDING HD D (b) - 4 BACC30M8 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 2 BACB30MY8K9X BOLT, PROTRUDING HD E (b) - 2 BACC30M8 COLLAR Install the fastener wet with sealant BMS5-45. (a) 0.263 - 0.266 2 BACB30MY8K11X BOLT, PROTRUDING HD F (b) - 2 BACC30M8 COLLAR (a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02 (b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to SOPM 20-50-19 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure.

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 90 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name 5 BACC30M8 COLLAR

FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE (SHEET 7 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 91 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 92 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 93 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step As shown in figure. 1 69B80913-5 BRACKET Put / Hold 1 Up to 0.159 - 0.171 inch diameter. 2 - Hole Drill 2

- - Hole Deburr To the bracket and the frame. Refer to SWPM 20-20-00, Cleaning Procedure 5, as an accepted procedure. - - Surface Clean 3

1 69B80913-5 BRACKET Install (New) 2 BACR15BB5D8C RIVET, UNIVERSAL HD Install (New) 4 (a) - ALODINE 600 Chemical Conversion Coating Apply 5 (b) - BMS 10-11, TYPE 1 Primer Apply (a) Apply to bare metal. Refer to SOPM 20-43-03, as an accepted procedure.(b) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 2 BACR15BB5D8C RIVET, UNIVERSAL HD

FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 94 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE (SHEET 1 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 95 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 96 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 97 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE (SHEET 4 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 98 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step 2 463430-1001 REMOTE COMPEN- SATOR - UPPER RUDDER Install (New) 1
Under the head of fastener. Four (4) per Compensator 8 BACW10BP4AC WASHER Install (New) 2 Four (4) per Compensator. 8 BACB30NM4K11 BOLT, HEX HEAD Install (New) Four (4) per Compensator. 8 NAS1149E0432P WASHER, PLAIN Install (New) Four (4) per Compensator. Refer to 747-8P SRM 51-40- 04 and 747-8F SRM51-40-04 as an accepted procedure for the torque value. 8 BACN11Z4CD NUT Install (New)

(b), (c) 1 BACE21AW0808W ELBOW, SWVL-RDCR, 90 Install (New) 3 (b), (c) 1 272U8290-40 TUBE ASSY Install (New) 4 Use all kept screws, washers and clipnuts for the installation. 5 - Clamp Install (Kept)
(b), (c) 1 272U8290-34 TUBE ASSY Install (New) 5 Use all kept screws, washers and clipnuts for the installation. 5 - Clamp Install (Kept)
(b), (c) 1 272U8290-39 TUBE ASSY Install (New) 6 Use all kept screws, washers and clipnuts for the installation. 5 - Clamp Install (Kept)
(b), (c) 1 AS1005W100808 TEE, FLARELESS Install (New) 7

FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 99 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step (b), (c) 1 272U8290-35 TUBE ASSY Install (New) 8 Use all kept screw, washer and clip nut for the installation. 1 - Clamp Install (Kept) Use all the kept fastener and hardware 1 - Clamp Block Assy Install (Kept) 9 To tubes assy 272U8290-39 and 272U8290-34. 2 AS21919WCE08 CLAMP,LOOP Install (New) 10

2 NAS1149D0316J WASHER Install (New) 1 BACS12GU3K8 SCREW Install (New) 1 BACN10YR3CD NUT Install (New) (b), (c) 2 BACE21AW0808W ELBOW, SWVL-RDCR, 90 Install (New) 11 (b), (c) 1 BACT16AY080808W TEE, SWIVEL ON RUN Install (New) 12 (b), (c). Torque thevalve to 40-80 inchpounds to make sure the valve is seated. 1 293W6132-1 VALVE ASSY Install (New) 13

(a) - MS20995NC40 (MS20995C41 optional) Lockwire Install (New) (b), (c) 1 272U8290-38 TUBE ASSY Install (New) 14 (b), (c) 1 BACE21AW0808W ELBOW, SWVL-RDCR, 90 Install (New) 15 (b), (c) 1 AS4134V100808P (BACT16BN100808P optional) TEE Install (New) 16

2 NAS1149D1432J WASHER, PLAIN Install (New) 1 - Lock Nut Install (Kept) (b), (c). Torque thevalve to 40-80 inchpounds to make sure the valve is seated. 1 293W6132-1 VALVE ASSY Install (New) 17

(a) - MS20995NC40 (MS20995C41 optional) Lockwire Install (New) (b), (c) 1 272U8290-37 TUBE ASSY Install (New) 18

FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 100 of 108 BOEING SERVICE BULLETIN 747-27A2513More Data Qty Identification Name Task Step 1 BACN10YD1 NUT,CLIP-ON Install (New) 19 1 AS21919WCE08 CLAMP,LOOP Install (New) 1 NAS1149D0316J WASHER Install (New) 1 BACS12GU3K8 SCREW Install (New) 1 AS21919WCE08 CLAMP,LOOP Install (New) 20 (d) 1 BACS18AF4 SPACER Install (New) 2 NAS1149D0316J WASHER Install (New) 1 BACS12GU3K8 SCREW Install (New) 1 BACN10YR3CD NUT Install (New) Connect the tubeassy to the Compensator and Tee. (b), (c) 1 272U8290-36 TUBE ASSY Install (New) 21
(a) Double-twist method. Refer to SOPM 20-50-02 as an accepted procedure. (b) Refer to 747-8 AMM 20-11-05 as an accepted procedure. (c) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value. (d) Use spacers as necessary to make sure that the clamp holds the tube with minimum force. The maximum permitted quantity of spacers for each clamp is 4. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACW10BP4AC WASHER 1 NAS1149E0432P WASHER, PLAIN 1 BACN11Z4CD NUT 3 NAS1149D0316J WASHER 1 BACN10YR3CD NUT 1 BACS12GU3K8 SCREW 2 AS21919WCE08 CLAMP,LOOP 1 BACB30NM4K11 BOLT, HEX HEAD 4 BACS18AF4 SPACER

FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE (SHEET 7 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 101 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 102 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 103 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step

- W1912, W4616 Wire Bundle Route 1 One for each location 2 BACC10GU103 CLAMP, WIRE BUN- DLE Install (New) 2 One for each location 2 NAS42DD6-64FC SPACERS FOR RIV- ETS Install (New) One for each location 2 NAS1149D0332J WASHER Install (New) One for each location 2 BACS12GU3K26 SCREW Install (New) 14 - Clamp Install (Kept) 3 14 - Washer Install (Kept) 14 - Screw Install (Kept) The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 2 NAS1149D0332J WASHER

FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 104 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 105 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 106 of 108 BOEING SERVICE BULLETIN 747-27A2513FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 107 of 108 BOEING SERVICE BULLETIN 747-27A2513The 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 this figure. More Data Qty Identification Name Task Step Refer to 747-8 AMM27-31-07 as an accepted procedure 1 327400-1011 POWER CONTROL PACKAGE - INBOARD ELEVATOR Install (New) 1 (a) (b) 2 - Hose Assy Install (Kept) 2 Use the kept screw, washer and clip nut 1 - Clamp Install (Kept) (a) (b) 2 - Hose Assy Install (Kept) 3 2 - Clamp Install (Kept) 2 - Washer Install (Kept) 1 - Screw Install (Kept) 1 BACN10YR3CD NUT Install (New) As shown in figure. Refer to SOPM 20-50-05 as an accepted procedure. 2 BAC27EHY242 MARKER Install (New) 4

Refer to SOPM 20- 44-01 as accepted procedures. - BAC5710, TYPE 41 Clear Skydrol Resistant Topcoating Apply 5 (a) Refer to 747-8 AMM 20-11-18 as an accepted procedure. (b) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value.

FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 04, 2014 747-27A2513 Revision 1 July 18, 2014 108 of 108 BOEING SERVICE BULLETIN 747-27A2513