# Boeing Alert Service Bulletin 717-29A0009: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2008-1155; AD 2009-07-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 717-29A0009](https://openairdocs.org/service-documents/boeing/717-29a0009.md) - Title as filed: U.S. DOT/FAA - Service Bulletin - Pages: 45 - PDF: https://openairdocs.org/files/sha256/60/f0/60f06658a1bdef6ccda55a4e35e8b8049acbb3df6d74f499fcb4dd106f2c4930 - Page: https://openairdocs.org/service-documents/boeing/717-29a0009/file/60f06658a1bd ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 45 ALERT ALERT Commercial Airplane Group 717 ALERTALERT Service Bulletin Number: 717-29A0009 Date: July 31, 2008 ATA System: 2921 SUBJECT: HYDRAULIC POWER - Pump, Auxiliary Hydraulic - Auxiliary Hydraulic Pump Wire Installation Change BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-and-blue Boeing livery 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. ### Page 2 BLANK PAGE July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT BLANK PAGE ### Page 3 Table of Contents July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT Table of Contents Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 10 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 10 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 16 3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 16 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP . . . . . . . . . . . . . . . . . . . . . . 20 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP . . . . . . . . . . . . . . . . . . . . . . 33 ### Page 4 Table of Contents July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT BLANK PAGE ### Page 5 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 45 ALERT ALERT Commercial Airplane Group 717 ALERTALERT Service Bulletin Number: 717-29A0009 Summary Date: July 31, 2008 ATA System: 2921 SUBJECT: HYDRAULIC POWER - Pump, Auxiliary Hydraulic - Auxiliary Hydraulic Pump Wire Installation Change THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND Boeing has determined that the auxiliary hydraulic pump wire assembly located in the right wheel well is in immediate proximity to the center wing fuel tank, within the tire burst area. Moving the auxiliary hydraulic pump wire assembly away from the tire burst debris area will minimize the possibility of wire damage and consequent arcing to center wing fuel tank. Additionally, other wire assembly installations affected by this change must be rerouted. If not corrected, in the event of a tire burst, when the Main Landing Gear (MLG) is in the retracted position, the auxiliary hydraulic pump wire assembly could become severely damaged, causing wire-to-wire or wire-to-structure arcing, resulting in a potential ignition source to the center wing fuel tank and consequent fire or explosion. This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation SFAR 88, Fuel Tank System Fault Tolerance Evaluation Requirements. ACTION This service bulletin provides instructions to change the auxiliary hydraulic pump wire installation in the right wheel well. EFFECTIVITY 717-200 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. ### Page 6 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 45 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 5 years, after the date on this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Airplanes Total Task Hours Elapsed Hours 717-200 12.4 11.9 AUXILIARY HYDRAULIC PUMP WIRE INSTALLATION CHANGE ### Page 7 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 45 ALERT ALERT Commercial Airplane Group 717 ALERTALERT Service Bulletin Number: 717-29A0009 Date: July 31, 2008 ATA System: 2921 SUBJECT: HYDRAULIC POWER - Pump, Auxiliary Hydraulic - Auxiliary Hydraulic Pump Wire Installation Change THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplanes shown below. An equivalent change is on 717 production airplanes, fuselage number 5019 and subsequent. Airplane manufacturer’s fuselage numbers 5004, 5007, and 5018 had an equivalent modification incorporated at the operators facility as an installation verification. Airplane models: 717-200 IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND FUSELAGE NUMBER AIRTRAN AIRWAYS (CQT) 1 5005–5006 2 5008–5012 5017 GROUP CONFIGURATION DESCRIPTION 1 - Applicable to airplanes with wire assemblies 7957939620 and 7957939623 routed along the lower aft edge of the center fuel tank. 2 - Applicable to airplanes with wire assemblies 7957939620 and 7957939623 routed along the auxiliary hydraulic pump support. ### Page 8 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT NATIONAL JET SYSTEMS (NJS) 1 5002–5003 2 5013–5014 SPANAIR (SPP) 2 5015–5016 IDENTIFICATION BY FUSELAGE NUMBER 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Boeing has determined that the auxiliary hydraulic pump wire assembly located in the right wheel well is in immediate proximity to the center wing fuel tank, within the tire burst area. Moving the auxiliary hydraulic pump wire assembly away from the tire burst debris area will minimize the possibility of wire damage and consequent arcing to center wing fuel tank. Additionally, other wire assembly installations affected by this change must be rerouted. If not corrected, in the event of a tire burst, when the Main Landing Gear (MLG) is in the retracted position, the auxiliary hydraulic pump wire assembly could become severely damaged, causing wire-to-wire or wire-to-structure arcing, resulting in a potential ignition source to the center wing fuel tank and consequent fire or explosion. An equivalent change is on 717 production airplanes, fuselage number 5019 and subsequent. Airplane manufacturer’s fuselage numbers 5004, 5007, and 5018 had an equivalent modification incorporated at the operators facility as an installation verification. This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation SFAR 88, Fuel Tank System Fault Tolerance Evaluation Requirements. D. Description This service bulletin provides instructions to change the auxiliary hydraulic pump wire installation in the right wheel well. 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. Fuselage Group 5002–5003 1 5005–5006 1 5008–5017 2 ### Page 9 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 45 Boeing recommends that the change given in this service bulletin be done within 5 years, after the date on this service bulletin. F. Approval The resultant modification described in Paragraph 1.D has been shown to comply with the applicable Federal Aviation Regulations and is approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region. 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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. Task Number of Persons Task Hours Elapsed Hours De-energize 1 0.3 0.3 Open Access 1 0.2 0.2 Figure 1 or 2 1 10.4 10.4 Energize 1 0.3 0.3 Check 2 1.0 0.5 Close Access 1 0.2 0.2 TOTAL FOR EACH AIRPLANE 12.4 11.9 ### Page 10 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 45 H. Weight and Balance Changes I. Electrical Load Data Not changed. J. References 1. Existing Data: a. 717 Aircraft Maintenance Manual (AMM) 20-20-20, 24-00-00, 29-00-00, 32-00-00, and 32-44-01. b. 717 Structural Repair Manual (SRM) Chapter 51-00-00. c. Standard Wiring Practices Manual (SWPM) 20-10-01, 20-20-03, and 20-50-01. 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators. Group 1: Airplane Approximate Station (Inches) Mfr’s Empty Weight (MEW) LBS Moment Change (MEW) IN.-LBS 717-200 750.0 +2.7 +2025.0 Group 2: Airplane Approximate Station (Inches) Mfr’s Empty Weight (MEW) LBS Moment Change (MEW) IN.-LBS 717-200 750.0 +2.5 +1875.0 Document Number Title Change SR95290009 Reroute Auxiliary Hydraulic Pump Wire Assembly - Right Main Wheel Well K ### Page 11 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT K. Publications Affected L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. Publication Chapter-Section Illustrated Parts Catalog 29-21 Aircraft Maintenance Manual 29-21 ### Page 12 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT BLANK PAGE ### Page 13 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. Kit availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page. 2. Fax to (206) 662-7145. 3. Spares Customer Support - MC 36-65. Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. 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. Kit Number Name ROLT (Weeks) Unit Price thru December 31, 2008 SA95290009-3 Service Kit 13 $7,257.00 SA95290009-5 Service Kit 13 7,292.00 Group 1: Kit SA95290009-3 New Part Number QTY Name Existing Part Number Notes 3D0039-14 17 NUT-CLIP (a) 9D0062-3F08-40 1 BRACKET (a) 9D0062-3R08-18 1 BRACKET (a) 9D0062-3R32-08 1 BRACKET (a) 9D0230-1E101013 2 BRACKET (a) ### Page 14 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT AN315-3R 4 NUT MS20470AD3-5D 6 RIVET MS21042L04 2 LOCKNUT MS21042L3 12 LOCKNUT MS35338-43 4 LOCKWASHER NAS1096-3-10 5 SCREW NAS1096-3-11 1 SCREW NAS1096-3-12 1 SCREW NAS1096-3-17 2 SCREW NAS1096-3-18 1 SCREW NAS1096-3-8 10 SCREW NAS1096-3-9 12 SCREW NAS1149CN416R 4 WASHER NAS1149F0332P 6 WASHER NAS1252-10L 54 WASHER NAS1801-04-7 2 SCREW NAS43DD3-32FC 3 SPACER S7913536-4 1 CLAMP (a) S7913536-8 7 CLAMP (a) S7934111-10SA 13 CLAMP (a) S7934111-2SA 2 CLAMP (a) S7934111-3SA 4 CLAMP (a) S7934111-4SA 1 CLAMP (a) S7934111-6SA 9 CLAMP (a) S7934111-8SA 2 CLAMP (a) SR95290009-9 1 WIRE ASSY 7957939622 (b) TA4012B32 1 BRACKET TA4051F1006 1 BRACKET TA4064G0612 2 BRACKET (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Discard existing part. Group 1: Kit SA95290009-3 New Part Number QTY Name Existing Part Number Notes ### Page 15 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT Group 2: Kit SA95290009-5 New Part Number QTY Name Existing Part Number Notes 3D0039-14 16 NUT-CLIP (a) 9D0062-3F08-40 1 BRACKET (a) 9D0062-3R08-18 1 BRACKET (a) 9D0062-3R32-08 1 BRACKET (a) 9D0230-1E101013 3 BRACKET (a) AN315-3R 4 NUT MS20470AD3-5D 8 RIVET MS21042L04 2 LOCKNUT MS21042L3 8 LOCKNUT MS35338-43 4 LOCKWASHER NAS1096-3-10 3 SCREW NAS1096-3-12 1 SCREW NAS1096-3-17 2 SCREW NAS1096-3-18 1 SCREW NAS1096-3-34 1 SCREW NAS1096-3-8 9 SCREW NAS1096-3-9 10 SCREW NAS1149CN416R 4 WASHER NAS1149F0332P 6 WASHER NAS1252-10L 45 WASHER NAS1801-04-7 2 SCREW NAS43DD3-32FC 3 SPACER NAS43DD3-96FC 1 SPACER S7913536-4 2 CLAMP (a) S7913536-8 2 CLAMP (a) S7934111-10SA 12 CLAMP (a) S7934111-2SA 4 CLAMP (a) S7934111-3SA 4 CLAMP (a) S7934111-4SA 4 CLAMP (a) S7934111-6SA 3 CLAMP (a) S7934111-8SA 1 CLAMP (a) SR95290009-9 1 WIRE ASSY 7957939622 (b) TA4012B32 1 BRACKET TA4051F1006 1 BRACKET ### Page 16 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 2. Parts and Materials Supplied by the Operator: 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. TA4064G0612 3 BRACKET (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Discard existing part. Part Number / Specification QTY Name D P M 6 8 4 ( N A S M 2 0 9 9 5 N 2 0 ) or DPM 5865 (NASM20995C20) 3 FT Lockwire Group 2: Kit SA95290009-5 New Part Number QTY Name Existing Part Number Notes ### Page 17 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. 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. CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE TO THE AIRPLANE OR EQUIPMENT. NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give the recommended sequences of steps. The sequences of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. For approved fastener and process material substitutions, refer to 717 SRM Chapter 51. 4. 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 5. For equivalent parts, refer to AEPL, Drawing 7595071. 6. Any protrusion of threads is acceptable provided that the threads do not rub or ride against nearby wire assemblies or components. 7. A 1/8-inch thick stack of the same type washers called for in this service bulletin is the maximum thickness which may be used under fastener head or nut to counteract accumulation of tolerances. EXCEPTION: When the available fastener length increments are greater than 1/16-inch, a 3/16-inch thick stack of the same type washers may be used. 8. Refer to the following standard documents as accepted procedures: ### Page 18 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 9. Obey all of the warnings and cautions given in the specified manual sections. 10. If an existing clamp specified in this service bulletin is too large or too small, a smaller or larger clamp with the same basic part number can be used to provide a snug fit. 11. Locate/position clamps as required to clear structure and adjacent hydraulic piping except as noted. 12. These work instructions refer to procedures included on 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. 13. Reference structure in Figures may not represent existing airplane configuration. B. WORK INSTRUCTIONS Group 1: 1. De-energize the airplane electrical power system. Refer to 717 AMM 24-00-00, as an accepted procedure. 2. Open/safety the Right Main Landing Gear Inboard Door for access. Refer to 717 AMM 32-00-00, as an accepted procedure. 3. Change auxiliary hydraulic pump wire installation in accordance with Figure 1. 4. Do pressurization of the left and/or right hydraulic system with the electric auxiliary hydraulic pump. Refer to 717 AMM 29-00-00, “Pressurization of the Left and/or Right Hydraulic System with an External Pressure Source,” as an accepted procedure. 5. Close access. 6. Put the airplane back to a serviceable condition. Group 2: 1. De-energize the airplane electrical power system. Refer to 717 AMM 24-00-00, as an accepted procedure. 2. Open/safety the Right Main Landing Gear Inboard Door for access. Refer to 717 AMM 32-00-00, as an accepted procedure. Chapter/Section Title SWPM 20-10-01 Wiring Installation - Maintenance Practices SWPM 20-20-03 Electrical Grounding and Ground Stud Installation SWPM 20-50-01 Electrical Bonding - Maintenance Practices 717 AMM 20-20-20 Lockwire Safetying - Maintenance Practices ### Page 19 July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 3. Change auxiliary hydraulic pump wire installation in accordance with Figure 2. 4. Do pressurization of the left and/or right hydraulic system with the electric auxiliary hydraulic pump. Refer to 717 AMM 29-00-00, “Pressurization of the Left and/or Right Hydraulic System with an External Pressure Source,” as an accepted procedure. 5. Close access. 6. Put the airplane back to a serviceable condition. ### Page 20 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP FWDFWD OUTBDOUTBD 3 6 15 14 13 8 18 19 19 9 11 17 2 5 7 2012 4 8 16 10 BEFORE MODIFICATION RIGHT SIDE MAIN WHEEL WELL (SHEET 1 OF 13) ### Page 21 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT A A C C ESEE FWD OUTBD JSEE AFTER MODIFICATION RIGHT SIDE MAIN WHEEL WELL (SHEET 2 OF 13) ### Page 22 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT X = -40.000 X = -30.000 X = -20.000 0.38 0.38 0.50 A-A LOOKING DOWN AT Z = -50.000 B B B-B 21 22 23 2.75 2.50 5.00 4.75 3.38 3.13 (SHEET 3 OF 13) ### Page 23 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT X = -60.000X = -50.000X = -40.000 Z = -40.000 Z = -50.000 9.75 C-C LOOKING FORWARD D D D-D 0.50 24 (SHEET 4 OF 13) ### Page 24 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT GSEE E FWDFWD OUTBDOUTBD 28 27 34 HSEE 36 FSEE 25 26 SEE I 39 40 35 3.75 2.75 4.50 3.50 5.50 4.50 EDS 9623 EBR 9620 SDN 9623 (SHEET 5 OF 13) ### Page 25 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 31 30 33 SHORT SIDE OF BRACKET G OUTBD FWD 1.56 H FWD OUTBD 38 1.50 F FWD OUTBD 29 41 I FWD OUTBD ROTATED 90° CCW 32 37 LONG SIDE OF BRACKET LONG SIDE OF BRACKET LONG SIDE OF BRACKET SHORT SIDE OF BRACKET (SHEET 6 OF 13) ### Page 26 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 42 45 42 43 49 J FWD OUTBD 48 K KSEE NUT NUT WASHER WASHER WASHER LUG SCREW STRUCTURE 47 44 46 42 ELECTRICAL BOND LOCKWASHER LOCKWASHER (2 LOCATIONS) GND 548 GND 549 (SHEET 7 OF 13) ### Page 27 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 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 one airplane. STEP TASK NAME IDENTIFICATION QTY MORE DATA 1 Remove/Keep Brake Accumulator - 1 Refer to 717 AMM 32-44-01, as an accepted procedure. (Not Shown) 2 Disconnect Plug (P1-32) 1 3 Disconnect/ Remove Screw NAS1096-3-10 2 GND548 and GND549. Lockwasher MS35338-43 4 Washer NAS1149F0332P 6 Nut AN315-3R 4 4 Remove Screw NAS1096-2-10 1 Washer NAS1252-8L 1 Remove/Keep Clamp S7934111-3SA 1 Clamp S7934111-10SA 1 Remove Nut Clip 3D0039-5 1 5 Remove Screw NAS1096-2-8 1 Washer NAS1252-8L 1 Remove/Keep Clamp S7934111-1SA 1 Remove Nut Clip 3D0039-5 1 6 Disconnect Plug (P1-6008) 1 7 Remove Screw NAS1096-2-8 1 May not be installed on all airplanes.Washer NAS1149DN816H 1 Clamp S7934111-4SA 1 Nut Clip 3D0039-5 1 8 Remove Screw NAS1096-2-10 3 Clamp S7913536-9 3 S7934111-8SA 3 Washer NAS1149DN816H 6 Locknut MS21042L08 3 9 Remove Screw NAS1096-2-8 2 Clamp S7934111-8SA 2 Washer NAS1252-8L 2 Nut Clip 3D0039-5 2 (SHEET 8 OF 13) ### Page 28 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 10 Remove Screw NAS1096-2-14 1 Clamp S7934111-8SA 1 Spacer NAS43DD3-24FC 1 Washer NAS1149DN816H 2 Nut Clip 3D0039-5 1 11 Remove Screw NAS1096-2-8 1 Clamp S7913536-8 1 Washer NAS1149DN816H 2 Locknut MS21042L08 1 12 Remove Screw NAS1096-2-16 1 Washer NAS1149DN816H 3 Clamp S7934111-8SA 1 Spacer NAS43DD3-32FC 1 Nut Clip 3D0039-5 1 13 Remove Screw NAS1096-2-8 2 Washer NAS1252-8L 2 Clamp S7934111-8SA 2 Nut Clip 3D0039-5 2 14 Remove Screw NAS1096-2-8 1 Washer NAS1252-8L 1 Clamp S7934111-8SA 1 Nut Clip 3D0039-5 1 15 Remove Screw NAS1096-2-12 2 Washer NAS1252-8L 6 Clamp S7913536-9 2 Clamp S7934111-8SA 4 Locknut MS21042L08 2 16 Remove Screw NAS1096-2-12 1 Washer NAS1149DN816H 3 Clamp S7934111-8SA 1 S7934111-4SA 1 S7934111-3SA 1 Locknut MS21042L08 1 17 Remove Wire Assembly 7957939622 1 18 Remove Bracket 9D0062-3-08-08 2 19 Plug As Required open holes with “AD” material per standard shop practice. STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 9 OF 13) ### Page 29 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 20 Apply FR Prime DMS1786 As Required open hole. 21 Locate/Install Bracket 9D0230-1E101013 1 Rivet MS20470AD3-5D 2 Nut Clip 3D0039-14 1 22 Locate/Install Bracket 9D0230-1E101013 1 Drill .152/.140 diameter holes two places.Screw NAS1801-04-7 2 Washer NAS1149CN416R 4 Locknut MS21042L04 2 Nut Clip 3D0039-14 1 23 Locate/Install Bracket 9D0062-3F08-40 1 Rivet MS20470AD3-5D 2 Nut Clip 3D0039-14 1 24 Locate/Install Bracket TA4012B32 1 Rivet MS20470AD3-5D 2 Nut Clip 3D0039-14 1 25 Install Wire Assembly (New) SR95290009-9 1 Connect P1-6008 to R5-6008. 26 Install/Kept Clamp S7934111-3SA 1 Clamp S7934111-10SA 1 Install/new Clamp S7934111-10SA 1 Nut Clip 3D0039-14 1 Washer NAS1252-10L 3 Spacer NAS43DD3-32FC 1 Screw NAS1096-3-18 1 27 Install/Kept Clamp S7934111-1SA 1 Install Clamp S7934111-10SA 1 Spacer NAS43DD3-32FC 1 Nut Clip 3D0039-14 1 Washer NAS1252-10L 3 Screw NAS1096-3-17 1 28 Install Clamp S7934111-4SA 1 May not be installed on all airplanes. Clamp S7934111-10SA 1 Push wire slack towards the auxiliary hydraulic pump.Screw NAS1096-3-17 1 Washer NAS1252-10L 3 Spacer NAS43DD3-32FC 1 Nut Clip 3D0039-14 1 STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 10 OF 13) ### Page 30 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 29 Install Bracket TA4064G0612 1 Pick up existing riv-nut. Washer NAS1252-10L 2 Screw NAS1096-3-12 1 Nut Clip 3D0039-14 1 Clamp S7934111-10SA 1 Screw NAS1096-3-8 1 Common to clamp and bracket. 30 Install Nut Clip 3D0039-14 1 Use existing hole. Bracket 9D0062-3R08-18 1 Washer NAS1252-10L 1 Screw NAS1096-3-8 1 31 Install Nut Clip 3D0039-14 1 Push wire slack towards the auxiliary hydraulic pump.Clamp S7934111-10SA 1 Washer NAS1252-10L 1 Screw NAS1096-3-8 1 32 Install Bracket 9D0062-3R32-08 1 Use second hole from bottom. Washer NAS1252-10L 2 Screw NAS1096-3-8 1 Locknut MS21042L3 1 33 Install Nut Clip 3D0039-14 1 Push wire slack towards the auxiliary hydraulic pump.Clamp S7934111-10SA 1 Washer NAS1252-10L 1 Screw NAS1096-3-8 1 34 Install Clamp S7913536-8 2 Push wire slack towards the auxiliary hydraulic pump.Clamp S7934111-10SA 2 Screw NAS1096-3-9 2 Washer NAS1252-10L 4 Locknut MS21042L3 2 35 Install Clamp S7934111-6SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 1 Nut Clip 3D0039-14 1 36 Install Clamp S7934111-6SA 1 Push wire slack towards the door frame. Clamp S7934111-3SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 3 Locknut MS21042L3 1 STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 11 OF 13) ### Page 31 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 37 Install Bracket TA4064G0612 1 Remove drain support hardware if installed.Screw NAS1096-3-10 1 Washer NAS1252-10L 2 Locknut MS21042L3 1 38 Install Nut Clip 3D0039-14 1 Push wire slack towards the door frame. Clamp S7934111-6SA 1 Clamp S7934111-3SA 1 Washer NAS1252-10L 2 Screw NAS1096-3-10 1 39 Install Clamp S7913536-8 1 Push wire slack towards the door frame. Clamp S7934111-6SA 1 Using existing hole. Clamp S7934111-3SA 1 Washer NAS1252-10L 4 Screw NAS1096-3-11 1 Locknut MS21042L3 1 40 Install Clamp S7934111-3SA 1 Push wire slack towards the door frame.Clamp S7934111-6SA 1 Washer NAS1252-10L 3 Screw NAS1096-3-9 1 Locknut MS21042L3 1 41 Install Nut Clip 3D0039-14 2 Push wire slack towards the door frame.Bracket TA4051F1006 1 Washer NAS1252-10L 3 Screw NAS1096-3-8 1 Screw NAS1096-3-10 1 Common to clamps and bracket. Clamp S7934111-6SA 1 Clamp S7934111-10SA 1 42 Install Clamp S7934111-10SA 4 Push wire slack towards the auxiliary hydraulic pump.Washer NAS1252-10L 4 Screw NAS1096-3-8 4 43 Install Screw NAS1096-3-10 2 Install screw head on bottom side of structure.Lockwasher MS35338-43 4 Washer NAS1149F0332P 6 Nut AN315-3R 4 STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 12 OF 13) ### Page 32 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 44 Install Clamp S7913536-8 2 Clamp S7934111-8SA 2 Washer NAS1252-10L 4 Screw NAS1096-3-9 2 Locknut MS21042L3 2 45 Install Clamp S7934111-6SA 2 Push wire slack towards the auxiliary hydraulic pump. Screw NAS1096-3-9 2 Washer NAS1252-10L 2 Nut Clip 3D0039-14 2 46 Install Clamp S7913536-8 1 Clamp S7934111-6SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Locknut MS21042L3 1 47 Install Clamp S7913536-4 1 Clamp S7934111-2SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Locknut MS21042L3 1 48 Install Clamp S7913536-8 1 Clamp S7934111-2SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Locknut MS21042L3 1 49 Install Plug (P1-32) 1 L o c k w i r e D P M 6 8 4 (NASM20995N20) or DPM 5865 (NASM20995C20) As Required 50 Install/Kept Brake Accumulator - 1 Refer to 717 AMM 32-44-01, as an accepted procedure. (Not Shown) STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 13 OF 13) ### Page 33 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP FWDFWD OUTBDOUTBD 2 3 15 11 11 16 18 17 20 20 20 9 10 65 7 4 8 19 20 14 13 12 BEFORE MODIFICATION RIGHT SIDE MAIN WHEEL WELL (SHEET 1 OF 13) ### Page 34 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT C C FWDFWD OUTBDOUTBD KSEE AFTER MODIFICATION RIGHT SIDE MAIN WHEEL WELL A ESEE A (SHEET 2 OF 13) ### Page 35 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT X = -40.000 X = -30.000 X = -20.000 0.38 0.38 0.38 0.50 A-A LOOKING DOWN AT Z = -50.000 B B B-B 22 23 24 21 2.75 2.50 5.00 4.75 3.12 2.87 3.38 3.13 (SHEET 3 OF 13) ### Page 36 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT X = -60.000X = -50.000X = -40.000 Z = -40.000 Z = -50.000 9.75 C-C LOOKING FORWARD D D D-D 0.50 25 (SHEET 4 OF 13) ### Page 37 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 27 28 26 29 37 ISEE SEE J FSEE GSEE FWD OUTBD 35 E SEE H EBR 9620 SDN 9623 EDS 9623 (SHEET 5 OF 13) ### Page 38 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 1.56 I FWD OUTBD 39 1.50 F FWD OUTBD 30 0.25 J FWD OUTBD 36 40 32 31 34 33 G OUTBD FWD ROTATED 90° CCW FWD OUTBD H 38 SHORT SIDE OF BRACKET LONG SIDE OF BRACKET LONG SIDE OF BRACKET LONG SIDE OF BRACKET SHORT SIDE OF BRACKET (SHEET 6 OF 13) ### Page 39 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 50 4748 K FWD OUTBD 45 42 43 49 44 41 46 NUT NUT WASHER WASHER WASHER LUG SCREW STRUCTURE L ELECTRICAL BOND LOCKWASHER LOCKWASHER (2 LOCATIONS) LSEE GND 548 GND 549 (SHEET 7 OF 13) ### Page 40 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 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 one airplane. STEP TASK NAME IDENTIFICATION QTY MORE DATA 1 Remove/Keep Brake Accumulator - 1 Refer to 717 AMM 32-44-01, as an accepted procedure. (Not Shown) 2 Disconnect Plug (P1-32) 1 3 Disconnect/ Remove/ Discard Screw NAS1096-3-10 2 GND548 and GND549. Lockwasher MS35338-43 4 Washer NAS1149F0332P 6 Nut AN315-3R 4 4 Remove Screw NAS1096-2-10 1 Washer NAS1252-8L 1 Remove/Keep Clamp S7934111-3SA 1 Clamp S7934111-10SA 1 Remove Nut Clip 3D0039-5 1 5 Remove Screw NAS1096-2-8 1 Washer NAS1252-8L 1 Remove/Keep Clamp S7934111-1SA 1 Remove Nut Clip 3D0039-5 1 6 Disconnect Plug (P1-6008) 1 7 Remove Screw NAS1096-2-8 1 May not be installed on all airplanes.Washer NAS1149DN816H 1 Clamp S7934111-4SA 1 Nut Clip 3D0039-5 1 8 Remove Screw NAS1096-2-8 1 Washer NAS1252-8L 1 Clamp S7934111-2SA 1 Nut Clip 3D0039-5 1 9 Remove Screw NAS1096-2-10 1 Washer NAS1252-8L 2 Clamp S7934111-8SA 1 Clamp S7913536-9 1 Locknut MS21042L08 1 (SHEET 8 OF 13) ### Page 41 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 10 Remove Screw NAS1096-2-10 1 Washer NAS1252-8L 2 Clamp MS25281R8 1 Clamp S7934111-4SA 1 Locknut MS21042L08 1 11 Remove Screw NAS1096-2-10 2 Washer NAS1252-8L 4 Clamp S7934111-2SA 2 Clamp S7934111-10SA 2 Nut Clip 3D0039-5 2 12 Remove Screw NAS1096-2-10 1 Washer NAS1149DN816H 3 Clamp S7934111-4SA 1 Clamp S7934111-10SA 1 Locknut MS21042L08 1 13 Remove Screw NAS1096-2-10 2 Washer NAS1252-8L 4 Clamp S7934111-6SA 2 Clamp S7934111-10SA 2 Nut Clip 3D0039-5 2 14 Remove Screw NAS1096-2-10 1 Washer NAS1252-8L 2 Clamp S7934111-6SA 1 Clamp S7934111-10SA 1 Nut Clip 3D0039-5 1 15 Remove Wire Assembly 7957939622 1 16 Remove Bracket 9D0062-3-08-08 2 Nut Clip 3D0039-5 2 17 Remove Bracket 9D0241-2-J 1 18 Remove Bracket 9D0062-3-08-06 1 19 Remove Bracket 9D0062-3-08-16 1 20 Plug As Required open holes with “AD” material per standard shop practice. 21 Locate/Install Bracket 9D0230-1E101013 1 Rivet MS20470AD3-5D 2 22 Locate/Install Bracket 9D0230-1E101013 1 Rivet MS20470AD3-5D 2 Nut Clip 3D0039-14 1 STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 9 OF 13) ### Page 42 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 23 Locate/Install Bracket 9D0230-1E101013 1 Drill .152/.140 diameter holes two places.Screw NAS1801-04-7 2 Washer NAS1149CN416R 4 Nut MS21042L04 2 Nut Clip 3D0039-14 1 24 Locate/Install Bracket 9D0062-3F08-40 1 Rivet MS20470AD3-5D 2 Nut Clip 3D0039-14 1 25 Locate/Install Bracket TA4012B32 1 Rivet MS20470AD3-5D 2 Nut Clip 3D0039-14 1 26 Install Wire Assembly (New) SR95290009-9 1 Connect P1-6008 to R5-6008. 27 Install/Kept Clamp S7934111-3SA 1 Clamp S7934111-10SA 1 Install/new Clamp S7934111-10SA 1 Nut Clip 3D0039-14 1 Washer NAS1252-10L 3 Spacer NAS43DD3-32FC 1 Screw NAS1096-3-18 1 28 Install/Kept Clamp S7934111-1SA 1 Install Clamp S7934111-10SA 1 Spacer NAS43DD3-32FC 1 Nut Clip 3D0039-14 1 Washer NAS1252-10L 3 Screw NAS1096-3-17 1 29 Install Clamp S7934111-4SA 1 This clamp may not be installed on all airplanes. Clamp S7934111-10SA 1 Push wire slack towards the auxiliary hydraulic pump.Screw NAS1096-3-17 1 Washer NAS1252-10L 3 Spacer NAS43DD3-32FC 1 Nut Clip 3D0039-14 1 30 Install Bracket TA4064G0612 1 Pick up existing riv-nut. Washer NAS1252-10L 2 Screw NAS1096-3-12 1 Nut Clip 3D0039-14 1 Clamp S7934111-10SA 1 Screw NAS1096-3-8 1 Common to clamp and bracket. STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 10 OF 13) ### Page 43 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 31 Install Nut Clip 3D0039-14 1 Use existing hole. Bracket 9D0062-3R08-18 1 Washer NAS1252-10L 1 Screw NAS1096-3-8 1 32 Install Nut Clip 3D0039-14 1 Push wire slack towards the door frame.Clamp S7934111-10SA 1 Washer NAS1252-10L 1 Screw NAS1096-3-8 1 33 Install Bracket 9D0062-3R32-08 1 Use second hole from bottom. Washer NAS1252-10L 2 Screw NAS1096-3-8 1 Locknut MS21042L3 1 34 Install Nut Clip 3D0039-14 1 Push wire slack towards the door frame.Clamp S7934111-10SA 1 Washer NAS1252-10L 1 Screw NAS1096-3-8 1 35 Install Clamp S7913536-8 1 Push wire slack towards the auxiliary hydraulic pump.Clamp S7934111-10SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Locknut MS21042L3 1 36 Install Screw NAS1096-3-8 2 Push wire slack towards the door frame.Washer NAS1252-10L 2 Bracket TA4051F1006 1 Nut Clip 3D0039-14 2 Clamp S7934111-10SA 1 37 Install Clamp S7934111-6SA 1 Push wire slack down towards the door frame. Clamp S7934111-3SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Nut Clip 3D0039-14 1 38 Install Bracket TA4064G0612 1 Remove drain support hardware if installed.Screw NAS1096-3-10 1 Washer NAS1252-10L 2 Locknut MS21042L3 1 STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 11 OF 13) ### Page 44 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 39 Install Clamp S7934111-6SA 1 Push wire slack down towards the door frame. Clamp S7934111-3SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Nut Clip 3D0039-14 1 40 Install Bracket TA4064G0612 1 Use existing attach hardware. Clamp S7934111-6SA 1 Push wire slack down towards the door frame.Clamp S7934111-3SA 1 Washer NAS1252-10L 2 Screw NAS1096-3-9 1 Locknut MS21042L3 1 41 Install Clamp S7913536-4 1 Push wire slack towards the door frame.Clamp S7934111-8SA 1 Washer NAS1252-10L 2 Screw NAS1096-3-9 1 Locknut MS21042L3 1 42 Install Clamp S7934111-3SA 1 Screw NAS1096-3-8 1 Washer NAS1252-10L 1 Nut Clip 3D0039-14 1 43 Install Clamp S7934111-10SA 1 Push wire slack towards the auxiliary hydraulic pump.Washer NAS1252-10L 1 Screw NAS1096-3-8 1 44 Install Clamp S7934111-4SA 1 Clamp S7934111-10SA 1 Screw NAS1096-3-34 1 Washer NAS1252-10L 3 Spacer NAS43DD3-96FC 1 45 Install Screw NAS1096-3-9 2 Washer NAS1252-10L 4 Clamp S7934111-10SA 2 Clamp S7934111-4SA 2 46 Install Screw NAS1096-3-10 2 Install screw head on bottom side of structure.Lockwasher MS35338-43 4 Washer NAS1149F0332P 6 Nut AN315-3R 4 STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 12 OF 13) ### Page 45 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 45 BOEING SERVICE BULLETIN 717-29A0009 ALERT ALERT 47 Install Clamp S7934111-2SA 2 Washer NAS1252-10L 2 Screw NAS1096-3-9 1 Locknut MS21042L3 1 48 Install Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Clamp S7913536-8 1 Clamp S7934111-2SA 1 Locknut MS21042L3 1 49 Install Clamp S7913536-4 1 Clamp S7934111-2SA 1 Screw NAS1096-3-9 1 Washer NAS1252-10L 2 Locknut MS21042L3 1 50 Install Plug (P1-32) 1 Lockwire DPM 684 (NASM20995N20) or DPM 5865 (NASM20995C20) As Required 51 Install/Kept Brake Accumulator - 1 Refer to 717 AMM 32-44-01, as an accepted procedure. (Not Shown) STEP TASK NAME IDENTIFICATION QTY MORE DATA (SHEET 13 OF 13) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.