### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-21-0245** Original Issue: April 16, 2010 Revision 1: September 30, 2010 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 1 of 41 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 2 of 41 **BOEING SERVICE BULLETIN 767-21-0245**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 12 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 18 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 19 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE . . 28 FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION. . . . . . . . . . . . . 30 FIGURE 3: WIRE BUNDLE W0176 CHANGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 FIGURE 4: WIRE BUNDLE W596 AND W1702 CHANGE . . . . . . . . . . . . . . . . . . . . . . . . 34 FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE . . . . . . . . . . . . . . . . . . . . . . . 35 FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING . . . . . . . . . . . . . . . . . . . . . 37 FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING . . . . . . . . . . . . . . . . . . . . . . 40

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 3 of 41 **BOEING SERVICE BULLETIN 767-21-0245**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 4 of 41 **BOEING SERVICE BULLETIN 767-21-0245**

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### Commercial **Airplanes** 

# 767 Service Bulletin **Revision Transmittal Sheet Number: 767-21-0245**  Original Issue: April 16, 2010 Revision 1: September 30, 2010 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. **REASON FOR REVISION** This revision is issued to make required changes found when doing this service bulletin for the first time. Three wire contacts are added; two wire contacts are deleted; and two plug and terminal numbers are changed. Kits and instructions are changed accordingly. Some functional test steps are also changed. Also, airplanes VR257-VR260, which were inadvertantly omitted, are added to Group 1. 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** April 16, 2010 Original Issue: September 30, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 5 of 41BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 6 of 41 **BOEING SERVICE BULLETIN 767-21-0245**

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### Commercial **Airplanes** 

# 767 Service Bulletin **Summary Number: 767-21-0245**  Original Issue: April 16, 2010 Revision 1: September 30, 2010 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change **CONCURRENT REQUIREMENTS** Refer to Paragraph 1.B., Concurrent Requirements. **BACKGROUND** This service bulletin and kit of parts change the Environmental Control System (ECS) Flight Deck Cooling System Logic to use Electrical Equipment (EE) Cooling rather than Airplane Pack Cooling on the ground and up to 10,000 feet. This prevents flight deck display unit blanking in hot and humid environments. If the change is not done moisture or condensation could get in the flight deck display units. This could cause intermittent indications in the flight deck display. Operators have reported display unit blanking on 767-300F type airplanes. The reports have included single display units and multiple units blanking during operation in hot and humid environments. This service bulletin will change the opening of the 3-way valve (manifold interconnect valve) with a five minute time delay after climbing past 10,000 feet altitude. The valve will close when descending below 10,000 feet altitude. This change will reduce moisture or condensation in the flight deck display unit. Boeing Service Related Problem (SRP) 767-SRP-21-179 is related to this service bulletin. **ACTION (PRR B12900-260)** In the Main Equipment Center, do the following change: 1. Change wire bundles W596 and W1702. 2. In the P36 Panel change relays, decals and wire bundle W176. 3. In the E8 EICAS rack, install two diodes and change wire bundles W2000 and W2006. **EFFECTIVITY** 767-300F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** No compliance time is given.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 7 of 41**INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of July 29, 2009. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  10.60 13.25 All
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 8 of 41 **BOEING SERVICE BULLETIN 767-21-0245**

### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-21-0245** Original Issue: April 16, 2010 Revision 1: September 30, 2010 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B12900-260 for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 767-300F airplanes that must incorporate 767-21-0235 prior to or concurrently with this bulletin. - 1
767-300F airplanes that had the intent of 767-21-0235 incorporated in production - 2

Airplane Models: 767-300F **Group Variable Number**  1 VR251 1 VR256 - VR260 1 VT501 1 VT511 - VT513 1 VT521 - VT523 1 VT531 - VT533 2 VT541 - VT543 1 VW851

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 9 of 412. Spares Affected None. **B. Concurrent Requirements Group 1:**  The service bulletin listed below must be done on Group 1 airplanes before or at the same time as this service bulletin: **Group 1: Description**  **Service Bulletin Company**  3-Way Valve Control Logic Change 767-21-0235, Original Issue Boeing **Group 2:** None **C. Reason** This service bulletin and kit of parts change the Environmental Control System (ECS) Flight Deck Cooling System Logic to use Electrical Equipment (EE) Cooling rather than Airplane Pack Cooling on the ground and up to 10,000 feet. This prevents flight deck display unit blanking in hot and humid environments. If the change is not done moisture or condensation could get in the flight deck display units. This could cause intermittent indications in the flight deck display. Operators have reported display unit blanking on 767-300F type airplanes. The reports have included single display units and multiple units blanking during operation in hot and humid environments. This service bulletin will change the opening of the 3-way valve (manifold interconnect valve) with a five minute time delay after climbing past 10,000 feet altitude. The valve will close when descending below 10,000 feet altitude. This change will reduce moisture or condensation in the flight deck display unit. Boeing Service Related Problem (SRP) 767-SRP-21-179 is related to this service bulletin. Revision 1 is issued to make required changes found when doing this service bulletin for the first time. Three wire contacts are added; two wire contacts are deleted; and two plug and terminal numbers are changed. Kits and instructions are changed accordingly. Some functional test steps are also changed. Also, airplanes VR257-VR260, which were inadvertantly omitted, are added to Group 1. **D. Description** In the Main Equipment Center, do the following change: 1. Change wire bundles W596 and W1702. 2. In the P36 Panel change relays, decals and wire bundle W176. 3. In the E8 EICAS rack, install two diodes and change wire bundles W2000 and W2006.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 10 of 41 **BOEING SERVICE BULLETIN 767-21-0245**Revision 1 - Airplanes modified in accordance with the original release of this service bulletin do not require additional work. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 119 767-300F **E. Compliance** No compliance time is given. **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. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. **Elapsed Hours Task Hours**  **Number of Persons Task**  0.50 0.50 1 Figure 1 0.35 0.35 1 Figure 2 3.50 3.50 1 Figure 3 2.10 2.10 1 Figure 4 2.65 5.30 2 Figure 5 Only Route Shows Figure 6 Only Route Shows Figure 7

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 11 of 41 **BOEING SERVICE BULLETIN 767-21-0245 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.50 1.50 1 Test 10.60 13.25 TOTAL FOR EACH AIRPLANE This estimate does not include the task hour data given in the service bulletin in Paragraph 1.B., Concurrent Requirements. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR B12900-260 b. Boeing Service Bulletin 767-21-0235 c. Boeing Service Related Problem (SRP) 767-SRP-21-179 d. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-11, 20-30-16, 20-61-11, 20-71-11, 20-81-12, 20-90-11 e. 767 Aircraft Maintenance Manual (AMM) 32-09-02 f. 767 Wiring Diagram Manual (WDM) 21-58-16, 31-41-13 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  MODULAR WIRE BUNDLE INSTALLATION P36, MISCELLANEOUS RELAY PANEL, LEFT 288T2036
MODULAR WIRE BUNDLE INSTALLATION - E8 EICAS RACK 288T2280 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 12 of 41 **BOEING SERVICE BULLETIN 767-21-0245 K. Publications Affected**  1. Publications: **Chapter-Section Publication**  21-58 767 Aircraft Maintenance Manual 21-58, 31-41, 91-02, 91-21, Equipment List 767 Wiring Diagram Manual
21-58 767 System Schematic Manual 21-58 767 Illustrated Parts Catalog 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
**L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 13 of 41 **BOEING SERVICE BULLETIN 767-21-0245**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 14 of 41 **BOEING SERVICE BULLETIN 767-21-0245**

BLANK PAGE**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 Revision 1** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 1 date of this Service Bul** 

**letin (Calendar Days)**  **QTY Date**  **Name Kit Number** 

No Longer Available Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-1

$2.00 120 3 08/13/10 Supplemental Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-2

$1,148.00 199 4 09/30/10 Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-3

**B. Industry Support Information** Boeing warranty remedies are available for 767airplanes in warranty as of July 29, 2009. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable numbers in your purchase order. **C. Parts Necessary For Each Airplane** 1. Kits/Parts To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 15 of 41 **BOEING SERVICE BULLETIN 767-21-0245 NOTE:**  One Top Kit 015T1853-3, or one Top Kit 015T1853-1 plus one Supplemental Kit 015T1853-2, 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. If Top Kit 015T1853-1 has been obtained, one Supplemental Kit 015T1853-2 is also required. **Figure Kit 5**  **4 3**  **2 1**  **Top Kit** 1 1 1 1 1 015T1853-1
**ALL**
**KIT 015T1853-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 5**  **4 3**  **2 1**  **QTY** DECAL K10718

1 015T1853-10101 DECAL R1197 1 015T1853-10102 DECAL R1196 1 015T1853-10103 DECAL D31620 1 015T1853-10104 WIRE 1 015T1853-101W WIRE 1 015T1853-102W WIRE 1 015T1853-103W WIRE 1 015T1853-104W WIRE 1 015T1853-105W WIRE 1 015T1853-106W WIRE 1 015T1853-107W ID - CONNECTOR 1 826T5075-00401 CONTACT, SOCKET 1 1 1 BACC47CP1S
CONTACT 6 BACC47DE8A CONTACT, SOCKET 4 BACC47DJ1
RELAY SOCKET 1 BACS16W1A SPACER 4 BACS18AR6 CONTACT, SOCKET, SIZE 20 1 CTA-0165 CONTACT, PIN, SIZE 20 1 CTA-0166

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 16 of 41 **BOEING SERVICE BULLETIN 767-21-0245 ALL** 
**KIT 015T1853-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 5**  **4 3**  **2 1**  **QTY** CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 1 M39029/11-145

TIME DELAY RELAY 1 TDH-8050-3003P
TERMINAL BLOCKDIODE ASSEMBLY MODULE 2 YHLZD-30

**Kit 015T1853-2 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number** Supplements Top Kit 015T1853-1, Figure 4.CONTACT, SOCKET 2 BACC47CN1S Supplements Top Kit 015T1853-1, Figure 5. CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 1 M39029/11-145

**Figure Kit 5**  **4 3**  **2 1**  **Top Kit** 1 1 1 1 1 015T1853-3
**ALL**
**KIT 015T1853-3**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 5**  **4 3**  **2 1**  **QTY** DECAL K10718

1 015T1853-10101 DECAL R1197 1 015T1853-10102 DECAL R1196 1 015T1853-10103 DECAL D31620 1 015T1853-10104

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 17 of 41 **BOEING SERVICE BULLETIN 767-21-0245 ALL** 
**KIT 015T1853-3**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 5**  **4 3**  **2 1**  **QTY** WIRE 1 015T1853-101W WIRE 1 015T1853-102W WIRE 1 015T1853-103W WIRE 1 015T1853-104W WIRE 1 015T1853-105W WIRE 1 015T1853-106W WIRE 1 015T1853-107W ID - CONNECTOR 1 826T5075-00401 CONTACT, PIN 2 BACC47CN1S CONTACT, SOCKET 2 1 BACC47CP1S
CONTACT 6 BACC47DE8A CONTACT, SOCKET 4 BACC47DJ1
RELAY SOCKET 1 BACS16W1A SPACER 4 BACS18AR6 CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 1 1 M39029/11-145

TIME DELAY RELAY 1 TDH-8050-3003P
TERMINAL BLOCKDIODE ASSEMBLY MODULE 2 YHLZD-30

2. Parts and Materials Supplied by the Operator None 3. Parts Modified and Reidentified None

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 18 of 41 **BOEING SERVICE BULLETIN 767-21-0245**4. Parts Removed and Not Replaced
**Notes QTY**  **Name Existing Part**  **Number** (a) 1 Relay BACR13CD2 (K10355) (a) Keep the part if there are other uses for it. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 19 of 41 **BOEING SERVICE BULLETIN 767-21-0245**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 20 of 41 **BOEING SERVICE BULLETIN 767-21-0245**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s) give the recommended sequence of steps. The sequence 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. Obey all of the warnings and cautions given in the specified manual sections. 4. 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. 5. 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. 6. If this service bulletin is accomplished concurrently with service bulletin 767-21-0235, the functional test listed in this service bulletin is all that is required. **B. WORK INSTRUCTIONS** 1. Change relays in the P36 Panel in accordance with Figure 1. 2. Add two diodes in the E8 EICAS rack in accordance with Figure 2. 3. Change wire bundle W0176 in accordance with Figure 3. 4. Change wire bundle W1702 in accordance with Figure 4. 5. Change wire bundles W2000 and W2006 in accordance with Figure 5. 6. Route wire bundles W0176 and W1702 in accordance with Figure 6. 7. Route wire bundles W2000 and W2006 in accordance with Figure 7. 8. Do the following functional test. Functional Test of Manifold Interconnect Valve Control Logic Modification

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 21 of 41 **BOEING SERVICE BULLETIN 767-21-0245**a. MAKE SURE the airplane is powered, the engines are OFF, and the air conditioning packs are OFF. b. MAKE SURE the Air/Ground Relay System is in GROUND mode. NOTE: If not, then follow AMM procedure 767 AMM 32-09-02 to reconfigure in GROUND mode. c. MAKE SURE the following circuit breakers on the P11 panel are closed: CB NO. LOC NOMENCLATURE

------ --- ------------ C00653 A13 Left Pack Cont C00704 A26 Right Pack Cont C01175 C30 LDG GR POS Air/GND Sys 1 C4078 J2 L EICAS CMPTR C4079 J29 R EICAS CMPTR d. SET the Equipment Cooling rotary switch on the P5 overhead to AUTO. e. MAKE SURE that the EICAS MAINTENANCE ENABLE BYPASS SWITCH (S612) is set to NORMAL. f. VERIFY that ALL of the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). g. REMOVE relay K10718 in the P36 panel. h. INSTALL a jumper from pin X2 of relay K10718 to ground. NOTE: This simulates a failure. i. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). j. REMOVE the jumper from pin X2 of relay K10718 to ground. k. REINSTALL relay K10718 in the P36 panel. l. DISCONNECT Connector (D20366) to Equipment Cooling Temperature Control Switch (S868) at STA 208, WL 172, and RBL 60. m. INSTALL a jumper wire between Pin 1 of Connector (D20366) to Pin 2 of Connector (D20366). n. VERIFY the following valve condition:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 22 of 41 **BOEING SERVICE BULLETIN 767-21-0245**Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 o. DISCONNECT Connector (D2770) from Left Flow Control Valve (V16). NOTE: This simulates the Left Pack is ON. p. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 q. DISCONNECT Connector (D1276) from Right Flow Control Valve (V17). NOTE: This simulates the Right Pack is ON r. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 s. Verify greater than 20VDC measured from TB239D, R1197(C53) to ground. **NOTE:** If the voltage measured is approximately 1.0VDC, diode R1197 is either faulty or installed in reverse polarity. t. Deleted u. Deleted v. Deleted w. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 x. CONFIGURE the Air/Ground Relay System to the AIR Mode. NOTE: Follow AMM Procedure 767 AMM 32-09-02 to reconfigure to AIR Mode.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 23 of 41 **BOEING SERVICE BULLETIN 767-21-0245**y. VERIFY that NONE of the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). z. IF circuit breakers C688 (11B8 on the P11 panel) and C651 (11P13 on the P11 panel) were Opened and the equipment cooling rotary switch on the P5 overhead panel was set to STBY mode from the AMM procedure to reconfigure to AIR Mode, THEN perform the following four (4) sub-steps: (1) REMOVE relay K336 in the P36 panel. (2) REMOVE relay K340 in the P36 panel. (3) CLOSE circuit breaker C688 (11B8 on the P11 panel). (4) SET the equipment cooling rotary switch on the P5 overhead panel to the AUTO mode. **CAUTION:** INSTRUMENTS IN THE FLIGHT DECK AND E/E BAY WILL NOT RECEIVE FORCED AIR COOLING. DAMAGE TO THE FLIGHT DECK INSTRUMENTS AND/OR E/E BAY EQUIPMENT MAY RESULT IF THE SYSTEM REMAINS IN AUTO MODE FOR MORE THAN 10 MINUTES. aa. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 ab. INSTALL a ground on Pin 2 of Connector (D20950). NOTE: This simulates a greater than 10,000 FT altitude. If access to this pin is a problem, remove the wire from Pin 2 of connector (D20950) and ground the wire. ac. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). ad. RECORD the elapsed time from grounding Pin 2 until the Manifold Interconnect Valve (V90) begins to switch to the OPEN (C-B) position. Time = ____________ minutes _____________ seconds Min = 4 minutes 30 seconds Max = 5 minutes 30 seconds ae. VERIFY that the recorded value in the previous step is between the minimum and maximum allowable value. af. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ --------

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 24 of 41 **BOEING SERVICE BULLETIN 767-21-0245**OPEN (C-B) Manifold Interconnect Valve V90 **CAUTION:** INSTRUMENTS IN THE FLIGHT DECK WILL NOT RECEIVE COOLING WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE OPEN (C-B) POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING. DAMAGE TO THE FLIGHT DECK INSTRUMENTS MAY RESULT IF THE VALVE REMAINS OPEN FOR MORE THAN 10 MINUTES. ag. SET the equipment cooling rotary switch on P5 overhead panel to STBY. ah. WAIT for 15 minutes to allow the equipment to cool down. ai. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 aj. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). ak. REMOVE relay K10718 in the P36 panel. al. INSTALL a jumper from pin X2 of relay K10718 to ground. NOTE: This simulates a failure. am. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). an. REMOVE the jumper from pin X2 of relay K10718 to ground. ao. REINSTALL relay K10718 in the P36 panel. ap. SET the equipment cooling rotary switch on P5 overhead panel to OVRD aq. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- OPEN (C-B) Manifold Interconnect Valve V90

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 25 of 41 **BOEING SERVICE BULLETIN 767-21-0245 CAUTION:**  INSTRUMENTS IN THE FLIGHT DECK WILL NOT RECEIVE COOLING WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE OPEN (C-B) POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING. ADDITIONALLY, EQUIPMENT IN THE E/E BAY WILL NOT RECEIVE COOLING WHEN THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5 OVERHEAD PANEL IS SET TO THE OVRD POSITION SINCE THE EQUIPMENT COOLING FANS WILL BE SHUTOFF. DAMAGE MAY RESULT IF THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5 OVERHEAD PANEL IS SET TO THE OVRD POSITION FOR MORE THAN 10 MINUTES. ar. REMOVE the ground from Pin 2 of Connector (D20950). as. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- OPEN (C-B) Manifold Interconnect Valve V90 **CAUTION:** INSTRUMENTS IN THE FLIGHT DECK WILL NOT RECEIVE COOLING WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE OPEN (C-B) POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING. DAMAGE TO THE FLIGHT DECK INSTRUMENTS MAY RESULT IF THE VALVE REMAINS OPEN FOR MORE THAN 10 MINUTES. at. SET the Equipment Cooling rotary switch on the P5 overhead to AUTO. **CAUTION:** IF CIRCUIT BREAKERS C688 (11B8 ON THE P11 PANEL) AND C651 (11P13 ON THE P11 PANEL) WERE OPENED AND THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5 OVERHEAD PANEL WAS SET TO STBY MODE FROM THE AMM PROCEDURE TO RECONFIGURE TO AIR MODE, THEN THE INSTRUMENTS IN THE FLIGHT DECK AND E/E BAY WILL NOT RECEIVE FORCED AIR COOLING. DAMAGE TO THE FLIGHT DECK INSTRUMENTS AND/OR E/E BAY EQUIPMENT MAY RESULT IF THE SYSTEM REMAINS IN AUTO MODE FOR MORE THAN 10 MINUTES. au. VERIFY the following valve condition: Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 av. RECONNECT Pin 2 of Connector (D20950) on the 10K FT Altitude Pressure Switch (S921) if it was disconnected in a previous step. aw. RECONNECT Connector (D20950) to the 10K FT Altitude Pressure Switch (S921) on the E8 EICAS Rack. ax. VERIFY the following valve condition:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 26 of 41 **BOEING SERVICE BULLETIN 767-21-0245**Condition Nomenclature Equip No

--------- ------------ -------- CLOSED (A-B) Manifold Interconnect Valve V90 ay. VERIFY that NONE of the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). az. SET the Equipment Cooling rotary switch on the P5 overhead to STBY. ba. REMOVE relay K10718 in the P36 panel. bb. INSTALL a jumper from pin X2 of relay K10718 to ground. NOTE: This simulates a failure. bc. VERIFY that NONE of the EICAS Maintenance Pages are selectable using the EICAS MAINTENANCE PANEL (M10372). bd. REMOVE the jumper from pin X2 of relay K10718 to ground. be. REINSTALL relay K10718 in the P36 panel. bf. RECONNECT Connector (D2770) to the Left Control Valve (V16). bg. RECONNECT Connector (D1276) to Right Flow Control Valve (V17). bh. DISCONNECT jumper from Pins 1 and 2 of Connector (D20366). bi. RECONNECT Connector (D20366) to Equipment Cooling Temperature Control Switch (S868) at STA 208, WL 172, and RBL 60. bj. IF circuit breaker C688 was Closed and K366 and K340 were Removed in a previous step, THEN perform the following sub-steps: (1) OPEN circuit breaker C688 (11B8 on the P11 panel). (2) INSTALL relay K366 in the P36 panel. (3) INSTALL relay K340 in the P36 panel. (4) CLOSE circuit breaker C688 (11B8 on the P11 panel). bk. CONFIGURE the Air/Ground Relay System to the GROUND Mode. NOTE: Follow AMM Procedure 767 AMM 32-09-02 to reconfigure to GROUND Mode. bl. RESTORE the airplane back to the configuration before the test. 9. Put the airplane back in a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1: September 30, 2010 27 of 41 **BOEING SERVICE BULLETIN 767-21-0245 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 28 of 41 **BOEING SERVICE BULLETIN 767-21-0245**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 airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  1 BACR13CD2 (K10355) RELAY Remove 1 Near Side 1 K10355 DECAL Remove 2 Far Side. Lower the relay bracket as needed. 1 D21730 DECAL Remove 3

(K10718) 1 TDH-8050-3003P TIME DELAY RELAY Install (New) 4 Near Side 1 015T1853-10101 DECAL K10718 Install (New) 5 Far Side. Lower the relay bracket as needed. 1 015T1853-10104 DECAL D31620 Install (New) 6

**FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 29 of 41 **BOEING SERVICE BULLETIN 767-21-0245 FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 30 of 41 **BOEING SERVICE BULLETIN 767-21-0245**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 each airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  1 BACS18AR6 SPACER Install (New) 1 Refer to SWPM 20-90-11 as an accepted procedure. 1 YHLZD-30 TERMINAL BLOCK DIODE ASSEMBLY MODULE Install (New)

1 BACS18AR6 SPACER Install (New) 1 BACS18AR6 SPACER Install (New) 2 Refer to SWPM 20-90-11 as an accepted procedure. 1 YHLZD-30 TERMINAL BLOCK DIODE ASSEMBLY MODULE Install (New)

1 BACS18AR6 SPACER Install (New) 1 015T1853-10103 DECAL R1196 Install (New) 3 1 015T1853-10102 DECAL R1197 Install (New) 4

**FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 31 of 41 **BOEING SERVICE BULLETIN 767-21-0245**Reference: 767 WDM 21-58-16 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-81-12 as an accepted procedure. 1 BACS16W1A RELAY SOCKET 1
Refer to SWPM 20-81-12 as an accepted procedure. 4 BACC47DJ1 CONTACT, SOCKET 2
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 3

1 015T1853-101W WIRE 4

**FIGURE 3: WIRE BUNDLE W0176 CHANGE (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 32 of 41 **BOEING SERVICE BULLETIN 767-21-0245 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-71-11 as an accepted procedure. 1 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 5

1 015T1853-102W WIRE 6 Install within 6 inches of the equipment. 1 826T5075-00401 ID - CONNECTOR 7

**FIGURE 3: WIRE BUNDLE W0176 CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 33 of 41 **BOEING SERVICE BULLETIN 767-21-0245**Reference: 767 WDM 21-58-16 **NOTE:** OPTIONAL: Instead of removing wire W596-606-24 it is acceptable to cap and stow the ends of the wire near connectors D4992P and D8036P. Refer to SWPM 20-10-11 as an acceptable procedure. Refer to SWPM 20-30-16 for end cap part numbers. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-61-11 as an accepted procedure. (a) 1 BACC47CN1S CONTACT, PIN 1
Refer to SWPM 20-61-11 as an accepted procedure. (a) 1 BACC47CN1S CONTACT, PIN 2

1 015T1853-103W WIRE 3 (a) If Top Kit 015T1853-1 is being used, obtain this part from Supplemental Kit 015T1853-2.

**FIGURE 4: WIRE BUNDLE W596 AND W1702 CHANGE (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 34 of 41 **BOEING SERVICE BULLETIN 767-21-0245**Reference: 767 WDM 31-41-13 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-20-11 as an accepted procedure. 6 BACC47DE8A CONTACT 1
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 2

1 015T1853-104W WIRE 3 Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 4

1 015T1853-105W WIRE 5 1 015T1853-106W WIRE 6

**FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 35 of 41 **BOEING SERVICE BULLETIN 767-21-0245 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** 1 015T1853-107W WIRE 7 Refer to SWPM 20-71-11 as an accepted procedure. (a) 1 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 8

(a) If Top Kit 015T1853-1 is being used, obtain this part from Supplemental Kit 015T1853-2.

**FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 36 of 41 **BOEING SERVICE BULLETIN 767-21-0245 FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 37 of 41 **BOEING SERVICE BULLETIN 767-21-0245 FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 38 of 41 **BOEING SERVICE BULLETIN 767-21-0245 FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING**  **(SHEET 3 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 39 of 41 **BOEING SERVICE BULLETIN 767-21-0245 FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 40 of 41 **BOEING SERVICE BULLETIN 767-21-0245 FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21-0245 Revision 1 September 30, 2010 41 of 41 **BOEING SERVICE BULLETIN 767-21-0245**