### Commercial **Airplanes** 

# 747 Service Bulletin **Number: 747-24A2360** Original Issue: January 18, 2012 Revision 2: October 02, 2013 ATA System: 2421 **SUBJECT:** ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power Feeder Cable Inspection and Clamp Change 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 © 2012 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 Unpublished Work.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: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 1 of 52 5.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 2 of 52 **BOEING SERVICE BULLETIN 747-24A2360**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 19 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 20 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 20 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 23 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 24 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD STA 2638 [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638 [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD STA 2638 [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638 [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD STA 2638 [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 3 of 52 **BOEING SERVICE BULLETIN 747-24A2360**FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638 [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD STA 2638 [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638 [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 4 of 52 **BOEING SERVICE BULLETIN 747-24A2360**

### Commercial **Airplanes** 

# 747 Service Bulletin **Revision Transmittal Sheet Number: 747-24A2360**  Original Issue: January 18, 2012 Revision 2: October 02, 2013 ATA System: 2421 **SUBJECT:** ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power Feeder Cable Inspection and Clamp Change This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-166-AD is related to this service bulletin. No more work is necessary on the airplane(s) in accordance with the Original Issue or Revision 1 of this service bulletin. **REASON FOR REVISION** Revision 2 is sent to add the Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2012-NM-166-AD. Extend compliance times for all groups as requested by FAA. Additional, this revision corrects discrepancies found by operators during the accomplishment of this service bulletin. These sections were changed: Summary Background: Updated planning table for this revision. Summary Action: Changed detailed visual inspection to detailed inspection. Summary Compliance: Added FAA NPRM 2012-NM-166-AD and update compliance time. Paragraph 1.C Reason: Added reason for revision. Paragraph 1.D Description: Changed detailed visual inspection to detailed inspection. Paragraph 1.D Description: Added "No more work is necessary" statement. Paragraph 1.E Compliance: Added FAA NPRM 2012-NM-166-AD, compliance information tables and updated compliance time paragraph. Paragraph 1.E Compliance: Table 1 and table 2, update "all airplane" compliance time. Paragraph 1.J Reference: Added FAA NPRM 2012-NM-166-AD. Paragraph 1.K.1 Publications Affected: Added chapter-section.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 5 of 52Paragraph 1.M Software Accomplishment Summary: Added "Not affected". Paragraph 2.B Industry Support Information: Updated warranty statement. Paragraph 3.A General Information: Notes have been added or deleted to meet new requirements. Paragraph 3.B Work Instructions: Through out work instructions changed detailed visual inspection to detailed inspection. Paragraph 3.B Work Instructions: Item 3.a, removed referenced figures and added steps for group 1. Paragraph 3.B Work Instructions: Item 3.b.(1)(a)1) updated to new requirements. Paragraph 3.B Work Instructions: Item 3.b.(1)(b) added statement for no damage found. Paragraph 3.B Work Instructions: Item 4.a, removed referenced figures and added steps for group 2. Paragraph 3.B Work Instructions: Item 4.b.(1)(a)1) updated to new requirements. Paragraph 3.B Work Instructions: Item 4.b.(1)(b) added statement for no damage found. Paragraph 3.B Work Instructions: Item 6, revised to close accesses. Paragraph 3.B Work Instructions: Added item 7 to return airplane to serviceable condition. Figure 1: Changed detailed visual inspection to detailed inspection, in the more data column. Figure 3: Changed detailed visual inspection to detailed inspection, in the more data column. Figure 5: Changed detailed visual inspection to detailed inspection, in the more data column. Figure 6: Added Note (b) to step 1 in step table. Figure 7: Correct figure and changed detailed visual inspection to detailed inspection, in the more data column. The data given in Information Notice (IN) 747-24A2360 IN 03 is included in this revision. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. **REVISION HISTORY** January 18, 2012 Original Issue: May 02, 2012 Revision 1: October 02, 2013 Revision 2:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 6 of 52 **BOEING SERVICE BULLETIN 747-24A2360**

### Commercial **Airplanes** 

# 747 Service Bulletin **Summary Number: 747-24A2360**  Original Issue: January 18, 2012 Revision 2: October 02, 2013 ATA System: 2421 **SUBJECT:** ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power Feeder Cable Inspection and Clamp Change **CONCURRENT REQUIREMENTS** None **BACKGROUND** Accomplishment of this service bulletin will prevent possible damage to Auxiliary Power Unit (APU) power feeder cables from chafing against the forward flange of the frame inner chord on the structure near Station 2638 on the left and right sides. If the power feeders have damage, arcs can occur and introduce an ignition source in a flammable fluid leakage zone which does not have smoke detectors or fire extinguishers. Arcing in a flammable fluid leakage zone can be an ignition source for fuel vapors and cause a fire. Operators have given reports of faults of the APU. Investigations showed that the power feeder cables on APU generator number 2 had damage from chafing at Station 2638. The cables showed evidence of a hot short to the adjacent structure. Reports show that the adjacent structure had damage from arcs. An investigation shows that the location and configuration of the existing clamps must be changed. Also, the protective grommets must be installed on the structure to prevent possible chafing. The chafing and subsequent arcing occurred in a flammable leakage zone. This service bulletin gives the instructions to inspect the APU power feeder cables for damage and to inspect the structure for damage. Also, this bulletin gives instructions to install protection on edges of the structure, and change the clamp configuration on the wire bundles to give sufficient clearance from the structure. These changes will prevent chafing and remove the risk of a fire. Boeing Service Related Problem (SRP) 747-SRP-24-0142 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 No Spares Affected Paragraph 1.E., Compliance Yes AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No Publications Affected

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 7 of 52**Reference Affected**  **Planning Data** 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 No Operator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**ACTION** Get access to the in the area just forward of the APU bulkhead STA 2638. Do a detailed inspection of APU power feeders W866 or W944 on the left side and W868 or W946 on the right side for damage. If damage to the power feeder cable is found, do a detailed inspection of the adjacent structure for damage. If damage is found to the power feeder cables and/or the structure, repair the damage. Replace certain clamps on the power feeder cables and install grommets on the structure. Close access. **EFFECTIVITY** 747-400 Airplanes with a horizontal stabilizer fuel tank. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **COMPLIANCE** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-166-AD is related to this service bulletin. Boeing recommends that the inspection, change and/or repair given in this service bulletin be done within 18 months after the Revision 2 date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of July 13, 2011. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  5.70 5.70 Group 1 airplanes 5.85 5.85 Group 2 airplanes
**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: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 8 of 52 **BOEING SERVICE BULLETIN 747-24A2360**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 9 of 52 **BOEING SERVICE BULLETIN 747-24A2360**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 10 of 52 **BOEING SERVICE BULLETIN 747-24A2360**

BLANK PAGE

### Commercial **Airplanes** 

# 747 Service Bulletin **Number: 747-24A2360** Original Issue: January 18, 2012 Revision 2: October 02, 2013 ATA System: 2421 **SUBJECT:** ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power Feeder Cable Inspection and Clamp Change **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplane(s) shown below. Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
**DESCRIPTION CONFIGURATION**  **GROUP** 747-400 Airplanes with a certain clamp configuration

- 1 747-400 Airplanes with a certain clamp configuration

- 2

Airplane Models: 747-400 **Group Variable Number**  2 RF001 - RF006 2 RM010 - RM013 2 RM021 - RM024 2 RM026 - RM030 2 RM036 - RM045 2 RM051 - RM053 2 RM071 2 RM081 - RM084 2 RM091

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 11 of 52**Group Variable Number**  2 RM096 - RM097 2 RM116 - RM117 2 RM136 - RM147 2 RM156 - RM158 2 RM166 - RM177 2 RM191 - RM192 2 RM231 - RM233 2 RM241 - RM246 2 RM261 - RM264 2 RM331 - RM333 2 RM341 2 RM351 - RM355 2 RM366 - RM367 2 RM401 - RM403 2 RM426 2 RM431 2 RM441 - RM443 2 RM445 2 RM801 - RM803 1 RT001 - RT011 2 RT012 - RT014 1 RT043 - RT047 1 RT073 1 RT101 - RT103 1 RT121 1 RT131 - RT134 2 RT135 - RT137 2 RT151 - RT152 1 RT162 - RT163 2 RT165 - RT168 1 RT401 - RT412 1 RT431 - RT441 2 RT442 - RT447

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 12 of 52 **BOEING SERVICE BULLETIN 747-24A2360 Group**  **Variable Number** 1 RT452 - RT455 1 RT457 - RT460 1 RT462 - RT467 2 RT468 - RT469 1 RT471 - RT498 2 RT499 1 RT502 - RT505 1 RT511 - RT512 1 RT514 - RT515 1 RT517 1 RT521 - RT523 2 RT525 2 RT527 2 RT529 1 RT551 - RT568 1 RT571 1 RT580 - RT583 2 RT584 - RT588 2 RT590 1 RT591 1 RT601 - RT614 1 RT616 - RT622 2 RT623 - RT630 1 RT633 - RT634 2 RT636 - RT640 1 RT672 - RT673 1 RT693 - RT697 2 RT698 - RT699 1 RT701 - RT704 1 RT741 1 RT744 - RT748 2 RT749 - RT750 1 RT753 - RT755

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 13 of 52 **BOEING SERVICE BULLETIN 747-24A2360 Group**  **Variable Number** 1 RT783 - RT784 2 RT801 - RT803 2 RT811 - RT814 2 RT831 - RT835 1 RT931 - RT932 2 RT945 - RT949 1 RT951 - RT954 2 RT955 2 RU016 - RU017 1 RU031 2 RU032 1 RU051 - RU052 2 RU059 - RU060 1 RU061 2 RU062 2 RU081 - RU083 2 RU101 - RU102 2 RU121 2 RU126 - RU132 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** Accomplishment of this service bulletin will prevent possible damage to Auxiliary Power Unit (APU) power feeder cables from chafing against the forward flange of the frame inner chord on the structure near Station 2638 on the left and right sides. If the power feeders have damage, arcs can occur and introduce an ignition source in a flammable fluid leakage zone which does not have smoke detectors or fire extinguishers. Arcing in a flammable fluid leakage zone can be an ignition source for fuel vapors and cause a fire.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 14 of 52 **BOEING SERVICE BULLETIN 747-24A2360**Operators have given reports of faults of the APU. Investigations showed that the power feeder cables on APU generator number 2 had damage from chafing at Station 2638. The cables showed evidence of a hot short to the adjacent structure. Reports show that the adjacent structure had damage from arcs. An investigation shows that the location and configuration of the existing clamps must be changed. Also, the protective grommets must be installed on the structure to prevent possible chafing. The chafing and subsequent arcing occurred in a flammable leakage zone. This service bulletin gives the instructions to inspect the APU power feeder cables for damage and to inspect the structure for damage. Also, this bulletin gives instructions to install protection on edges of the structure, and change the clamp configuration on the wire bundles to give sufficient clearance from the structure. These changes will prevent chafing and remove the risk of a fire. Revision 1 is sent to revise the Original Issued service bulletin to delete airplanes from this service bulletin. Also, to revise the kits and the work instruction. The data given in Information Notice 747-24A2360 IN01 and 747-24A2360 IN02 are included in this revision. Revision 2 is sent to add the Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2012-NM-166-AD. Extend compliance times for all groups as requested by FAA. Additional, this revision corrects discrepancies found by operators during the accomplishment of this service bulletin. The data given in Information Notice 747-24A2360 IN03 is included in this revision. Boeing Service Related Problem (SRP) 747-SRP-24-0142 is related to this service bulletin. **D. Description** Get access to the in the area just forward of the APU bulkhead STA 2638. Do a detailed inspection of APU power feeders W866 or W944 on the left side and W868 or W946 on the right side for damage. If damage to the power feeder cable is found, do a detailed inspection of the adjacent structure for damage. If damage is found to the power feeder cables and/or the structure, repair the damage. Replace certain clamps on the power feeder cables and install grommets on the structure. Close access. Revision 1 - No more work is necessary on airplanes changed in accordance with the Original Issue of this service bulletin. Revision 2 - No more work is necessary on the airplane(s) in accordance with the Original Issue or Revision 1 of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 315, 316 747-400 **E. Compliance** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-166-AD is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 15 of 52 **BOEING SERVICE BULLETIN 747-24A2360**Boeing recommends that the inspection, change and/or repair given in this service bulletin be done within 18 months after the Revision 2 date of this service bulletin. **Group 1: Table 1: BULKHEAD STATION 2638, Inspection APU power feeder cables and adjacent structure**  **for damage Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

-- Within 18 months after the Revision2 date of this service bulletin. Do a detailed inspectionof APU power feeder cable for damage in accordance with 3.B.3, left and right side of bulkhead. All airplanes

-- Before further flight Replace the clamps and install the grommets in accordance with 3.B.3.a. No damage to APU power feeder cable is found

-- Before further flight Do a detailed inspection adjacent structure for damage in accordance with 3.B.3.b.(1). Any damage to APU power feeder cable is found

And Repair the damage to the cable in accordance with 3.B.3.b.(2) And Replace the clamps and install the grommets in accordance with 3.B.3.c. through 3.B.3.f.

-- Before further flight Do the repair in accor- dance with 3.B.3.b.(1)(a)1).Any damage to the adjacent structure is found

or Contact Boeing for repair instructions and do the repair.

-- -- No further action is re- quired. No damage to the adjacent structure is found

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 16 of 52 **BOEING SERVICE BULLETIN 747-24A2360 Group 2:**  **Table 2: BULKHEAD STATION 2638, Inspection APU power feeder cables and adjacent structure for damage**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

-- Within 18 months after the Revision2 date of this service bulletin. Do a detailed inspectionof APU power feeder cable for damage in accordance with 3.B.4, left and right side of bulkhead. All airplanes

-- Before further flight Replace the clamps and install the grommets in accordance with 3.B.4.a. No damage to APU power feeder cable is found

-- Before further flight Do a detailed inspection adjacent structure for damage in accordance with 3.B.4.b.(1). Any damage to APU power feeder cable is found

And Repair the damage to the cable in accordance with 3.B.4.b.(2) And Replace the clamps and install the grommets in accordance with 3.B.4.c. through 3.B.4.f.

-- Before further flight Do the repair in accor- dance with 3.B.4.b.(1)(a)1).Any damage to the adjacent structure is found

or Contact Boeing for repair instructions and do the repair.

-- -- No further action is re- quired. No damage to the adjacent structure is found **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 17 of 52 **BOEING SERVICE BULLETIN 747-24A2360 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 • Time to make the parts • Time to find the tools. **Group 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open access 2.00 2.00 1 Inspect/Repair (Left Side) FIGURE 1 0.30 0.30 1 Inspect/Repair (Right Side) FIGURE 3 0.40 0.40 1 Remove & Replaceclamp/Install grommet (Left Side) FIGURE 2 0.50 0.50 1 Remove & Replaceclamp/Install grommet (Right Side) FIGURE 4 .50 .50 1 Close access 5.70 5.70 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open access 2.00 2.00 1 Inspect/Repair (Left Side) FIGURE 5 2.00 2.00 1 Inspect/Repair (Right Side) FIGURE 7

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 18 of 52 **BOEING SERVICE BULLETIN 747-24A2360 Group 2:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  0.50 0.50 1 Remove & Replaceclamp/Install grommet (Left Side) FIGURE 6 0.35 0.35 1 Remove & Replaceclamp/Install grommet (Right Side) FIGURE 8 .50 .50 1 Close access 5.85 5.85 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  +317.76 +0.1 Group 1 and 2
**I. Electrical Load Data** Not applicable. **J. References** 1. Existing Data: a. Boeing Service Letter 747-SL-747-51-48 b. Service Related Problem (SRP) 747-SRP-24-0142 c. Service Bulletin Index D6-30300 d. Standard Overhaul Practices Manual (SOPM) 20-50-09 e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-19 f. 747-400 Aircraft Maintenance Manual (AMM) 24-22-00, 52-49-00 g. 747-400 Structural Repair Manual (SRM) 51-10-02, 51-20-01, 51-20-02, 51-20-03, 51-70-11, 51-70-12, 51-70-13, 53-80-07 h. Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-166-AD 2. Data Supplied with this Service Bulletin: None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 19 of 52 **BOEING SERVICE BULLETIN 747-24A2360**3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  WIRE BUNDLE INSTALLATION 48 SEC RH, LH BULKHEAD STA 2598-2658 288U4806
WIRE PROVISIONS INSTL - SECT 48 FRAMES STA 2598 TO 2777 287U4804
The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  53-13, 53-44 747 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 does not affect FCS, therefore DTIs are not 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: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 20 of 52 **BOEING SERVICE BULLETIN 747-24A2360 2. 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 kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the Original Issue** 

**date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Original Issue date of this Ser** **vice Bulletin (Cal endar Days)**  **QTY Date**  **Name Kit Number** 

61.00 385 15 5/31/2012 TOP KIT - APU GEN- ERATOR POWER FEEDER CLAMPS 015U1924-1

61.00 385 5 6/28/2012 TOP KIT - APU GEN- ERATOR POWER FEEDER CLAMPS 015U1924-1

61.00 385 5 7/27/2012 TOP KIT - APU GEN- ERATOR POWER FEEDER CLAMPS 015U1924-1

71.00 385 25 5/31/2012 TOP KIT - APU GEN- ERATOR POWER FEEDER CLAMPS 015U1924-2

**B. Industry Support Information** Boeing warranty remedies are available for 747 airplanes in warranty as of July 13, 2011. For inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty & Product Assurance Contracts. If the condition described in this service bulletin is found during the inspection for airplanes in warranty as of that date and additional task hours are required, send a warranty claim to Boeing Warranty & Product Assurance Contracts. Please refer to this service bulletin number and reference the airplane number in your purchase order. **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 21 of 52 **BOEING SERVICE BULLETIN 747-24A2360 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 8**  **6 4**  **2 Top Kit** 

- - 1 1 015U1924-1 1 1
- - 015U1924-2 **Group 1:**
**KIT 015U1924-1**

**Notes Existing Part**  **Number Name**  **Figure**

**New Part Number 4**  **2 Qty**  (b) GROMMET

. 1 BACG20Z- P001900B (b) GROMMET

. 1 BACG20Z- Q001900B NUT 1 1 BACN10YR3CD (a) BOLT

. 1 BACS12HN3-12 (a) Screw 1

. BACS12HN3-22 (a) WASHER, PLAIN

. 1 BACW10P391AA (a) WASHER, FLAT 2 1 BACW10P411CG SPACERS FOR BOLTS . 1 NAS43DD3-15FC
SPACERS FOR BOLTS 2

. NAS43DD3-24FC
CLAMP 2 1 TA025097L16 (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. (b) Kit part number is bulk coil of grommet material.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 22 of 52 **BOEING SERVICE BULLETIN 747-24A2360 Group 2:** 
**KIT 015U1924-2**

**Notes Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **6 Qty**  (b) GROMMET 1

. BACG20Z- N001900B (b) GROMMET

. 1 BACG20Z- P001900B (b) GROMMET

. 1 BACG20Z- Q001900B NUT 1 2 BACN10YR3CD (a) BOLT 1

. BACS12HN3-10 (a) BOLT

. 2 BACS12HN3-12 (a) WASHER, PLAIN

. 2 BACW10P391AA (a) WASHER, FLAT

. 2 BACW10P411CG (a) WASHER 1

. NAS1149D0332J SPACERS FOR BOLTS . 2 NAS43DD3-15FC
SPACERS FOR BOLTS 1

. NAS43DD3-4FC
CLAMP 2 2 TA025097L16 (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. (b) Kit part number is bulk coil of grommet material. 2. Parts and Materials Supplied by the Operator None. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 23 of 52 **BOEING SERVICE BULLETIN 747-24A2360 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: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 24 of 52 **BOEING SERVICE BULLETIN 747-24A2360 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION 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 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 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. 7. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 8. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 9. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 10. 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. 11. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 25 of 52 **BOEING SERVICE BULLETIN 747-24A2360**12. 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. 13. 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. **B. WORK INSTRUCTIONS** 1. Remove electrical airplane power form the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 2. Open the Auxiliary Power Unit (APU) battery access door. Refer to 747-400 AMM 52-49-00 as an accepted procedure. 3. **Group 1:** Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage on the left of the bulkhead in accordance with FIGURE 1. Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage on the right side of the bulkhead in accordance with FIGURE 3.
a. If the power feeder cables do not have damage, then replace the clamp(s) and install the grommets in accordance with steps 3.c through 3.f. b. If a cable has damage: (1) Do a detailed inspection of the adjacent structure for damage. Inspect for surface finish integrity, excessive wear, and possible heat damage. Refer to 747-400 SRM 53-80-07 frame identification and allowable damage limits. (a) If the structure has damage: 1) Repair any damage in accordance with the 747-400 SRM listed below before further flight, or contact Boeing with damage findings for repair instructions and do the repairs. – 747-400 SRM 51-10-02 for inspection and damage removal procedures. – 747-400 SRM 51-20-03 for heat damage evaluation. – 747-400 SRM 51-20-02 for heat treatment verification. – 747-SL-747-51-48 for damage reporting instructions. – 747-400 SRM 51-70-11 for typical repair of formed sections. – 747-400 SRM 51-70-12 for typical repair of extruded sections. – 747-400 SRM 51-70-13 for typical repair of webs. – 747-400 SRM 51-20-01 for restoring surface finish. (b) If the structure has no damage: No further action is required. (2) Repair the cable. Refer to SWPM 20-10-13 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 26 of 52 **BOEING SERVICE BULLETIN 747-24A2360**c. Remove and replace the clamp(s) on power feeder cable W866 or W944 on the left side of STA 2638, between the bulkhead and the APU firewall in accordance with FIGURE 2. d. Install the grommets on the left side of frame APU bulkhead at STA 2638 in accordance with FIGURE 2 e. Remove and replace the clamp(s) on power feeder cables W4610 and W868 or W946 on the right side of STA 2638, between the bulkhead and the APU firewall in accordance with FIGURE 4. f. Install the grommets on the right side of frame APU bulkhead at STA 2638 in accordance with FIGURE 4.
4. **Group 2:** Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage on the left side of the bulkhead in accordance with FIGURE 5. Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage on the right side of the bulkhead in accordance with FIGURE 7.
a. If the power feeder cables do not have damage, then replace the clamp(s) and install the grommets in accordance with steps 4.c through 4.f. b. If a cable has damage: (1) Do a detailed inspection of the adjacent structure for damage. Inspect for surface finish integrity, excessive wear, and possible heat damage. Refer to 747-400 SRM 53-80-07 frame identification and allowable damage limits. (a) If the structure has damage: 1) Repair any damage in accordance with the 747-400 SRM listed below before further flight, or contact Boeing with damage findings for repair instructions and do the repair. – 747-400 SRM 51-10-02 for inspection and damage removal procedures. – 747-400 SRM 51-20-03 for heat damage evaluation. – 747-400 SRM 51-20-02 for heat treatment verification. – 747-SL-747-51-48 for damage reporting instructions. – 747-400 SRM 51-70-11 for typical repair of formed sections. – 747-400 SRM 51-70-12 for typical repair of extruded sections. – 747-400 SRM 51-70-13 for typical repair of webs. – 747-400 SRM 51-20-01 for restoring surface finish. (b) If the structure has no damage: No further action is required. (2) Repair the cable. Refer to SWPM 20-10-13 as an accepted procedure. c. Remove and replace the clamp(s) on power feeder cable W944 on the left side of STA 2638, between the bulkhead and the APU firewall in accordance with FIGURE 6.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 27 of 52 **BOEING SERVICE BULLETIN 747-24A2360**d. Install the grommets on the left side of frame APU bulkhead at STA 2638 in accordance with FIGURE 6 e. Remove and replace the clamp(s) on power feeder cables W4610 and W946 on the right side of STA 2638, between the bulkhead and the APU firewall in accordance with FIGURE 8. f. Install the grommets on the right side of frame APU bulkhead at STA 2638 in accordance with FIGURE 8 5. Restore electrical power back to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 6. Close access. Refer to 747-400 AMM 52-49-00 as an accepted procedure. 7. Put airplane into a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2: October 02, 2013 28 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 1.** 

**FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD STA 2638**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 29 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD**  **STA 2638 (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 30 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a detailed inspection. Refer to SWPM 20-10-13 as an accepted procedure. 1
- Wire Bundle Inspect 1

Do a detailed inspection. - - Structure Inspect 2

**FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD STA 2638**  **(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 31 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 1.** 

**FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638 (SHEET 1 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 32 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 33 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  1
- Clamp Remove 1 1
- Screw Remove 2
- Washer Remove 1
- Nut Remove 1 TA025097L16 CLAMP Install (New) 2 1 BACS12HN3-12 BOLT Install (New) 1 NAS43DD3-15FC SPACERS FOR BOLTS Install (New)
Install washer between the bracket and spacer 1 BACW10P411CG WASHER, FLAT Install (New)

1 BACN10YR3CD NUT Install (New) Install washer between the bolt head and bracket 1 BACW10P391AA WASHER, PLAIN Install (New)

Refer to SOPM 20-50-09 as an accepted procedure. (a) 1 BACG20Z-Q001900B GROMMET Install (New) 3

Refer to SOPM 20-50-09 as an accepted procedure. (a) 1 BACG20Z-P001900B GROMMET Install (New) 4

(a) Cut the length of the grommet to fit the location. Keep the remainder of the length of the grommet for other use. Trim as required.

**FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638 (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 34 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 1.** 

**FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD STA 2638**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 35 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD**  **STA 2638 (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 36 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a detailed inspection. Refer to SWPM 20-10-13 as an accepted procedure. 1
- Wire Bundle Inspect 1

Do a detailed inspection. - - Structure Inspect 2

**FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD STA 2638**  **(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 37 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 1.** 

**FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638 (SHEET 1 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 38 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 39 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  2
- Clamp Remove 1 1
- Screw Remove 2
- Washer Remove 1
- Nut Remove 2 TA025097L16 CLAMP Install (New) 2 1 BACS12HN3-22 Screw Install (New) Install washer between the bracket and spacer. 2 BACW10P411CG WASHER, FLAT Install (New)

2 NAS43DD3-24FC SPACERS FOR BOLTS Install (New)

1 BACN10YR3CD NUT Install (New) Refer to SOPM 20-50-09 as an accepted procedure. (a) - BACG20Z-Q001900B GROMMET Install (New) 3

Refer to SOPM 20-50-09 as an accepted procedure. (a) - BACG20Z-P001900B GROMMET Install (New) 4

(a) Use the remainder of the length of the grommet in the kit. Cut the length of the grommet to fit location. Trim as required.

**FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638 (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 40 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 2.** 

**FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD STA 2638**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 41 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD**  **STA 2638 (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 42 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure..
**More Data Qty**  **Identification Name**  **Task Step**  Do a detailed inspection. Refer to SWPM 20-10-13 as an accepted procedure. 1
- Wire Bundle Inspect 1

Do a detailed inspection. - - Structure Inspect 2

**FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD STA 2638**  **(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 43 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 2.** 

**FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638 (SHEET 1 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 44 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 45 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  (b) 2
- Clamp Remove 1 2
- Screw Remove 4
- Washer Remove 2
- Nut Remove 2 TA025097L16 CLAMP Install (New) 2 2 BACS12HN3-12 BOLT Install (New) 2 NAS43DD3-15FC SPACERS FOR BOLTS Install (New)
Install washer between the bolt head and bracket. 2 BACW10P391AA WASHER, PLAIN Install (New)

2 BACN10YR3CD NUT Install (New) Install washer between the bracket and spacer. 2 BACW10P411CG WASHER, FLAT Install (New)

Refer to SOPM 20-50-09 as an accepted procedure. 1 BACG20Z-P001900B GROMMET Install (New) 3

Refer to SOPM 20-50-09 as an accepted procedure. (a) 1 BACG20Z-Q001900B GROMMET Install (New) 4

(a) Cut the length of the grommet to fit the location. Keep the remainder of the length of the grommet for other use. Trim as required. (b) Some configurations may require the removal of 1 clamp and mounting hardware. Two clamp configuration shown.

**FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638 (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 46 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 2.** 

**FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD STA 2638**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 47 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD**  **STA 2638 (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 48 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a detailed inspection. Refer to SWPM 20-10-13 as an accepted procedure. 1
- Wire Bundle Inspect 1

Do a detailed inspection. - - Structure Inspect 2

**FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD STA 2638**  **(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 49 of 52 **BOEING SERVICE BULLETIN 747-24A2360 This Figure applies only to: Group 2.** 

**FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638 (SHEET 1 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 50 of 52 **BOEING SERVICE BULLETIN 747-24A2360 FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 51 of 52 **BOEING SERVICE BULLETIN 747-24A2360**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  2
- Clamp Remove 1 1
- Screw Remove 2
- Washer Remove 1
- Nut Remove 2 TA025097L16 CLAMP Install (New) 2 1 BACS12HN3-10 BOLT Install (New) 1 NAS43DD3-4FC SPACERS FOR BOLTS Install (New)

1 NAS1149D0332J WASHER Install (New) 1 BACN10YR3CD NUT Install (New) Refer to SOPM 20-50-09 as an accepted procedure. (a) - BACG20Z-Q001900B GROMMET Install (New) 3

Refer to SOPM 20-50-09 as an accepted procedure. 1 BACG20Z-N001900B GROMMET Install (New) 4

(a) Use the remainder of the length of the grommet in the kit. Cut the length of the grommet to fit location. Trim as required.

**FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638 (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 18, 2012 747-24A2360 Revision 2 October 02, 2013 52 of 52 **BOEING SERVICE BULLETIN 747-24A2360**