### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-21-0235** Original Issue: October 08, 2009 Revision 1: July 29, 2011 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Cooling - Freighter 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 1 of 56 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 2 of 56 **BOEING SERVICE BULLETIN 767-21-0235**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 16 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 19 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 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 WIRE BUNDLE W0176 - ROUTING [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 FIGURE 2: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND W0184 - ROUTING [Group 2-3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 FIGURE 5: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES [Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 FIGURE 6: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 - WIRING CHANGES [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 3 of 56 **BOEING SERVICE BULLETIN 767-21-0235**FIGURE 7: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 - WIRING CHANGES [Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 4 of 56 **BOEING SERVICE BULLETIN 767-21-0235**

### Commercial **Airplanes** 

# 767 Service Bulletin **Revision Transmittal Sheet Number: 767-21-0235**  Original Issue: October 08, 2009 Revision 1: July 29, 2011 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Cooling - Freighter 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 the airplane(s) changed in accordance with the original issue of this service bulletin. **REASON FOR REVISION** This revision is sent to tell operators that when they do the change in the P36 left miscellaneous electrical equipment panel electrical power must be removed from the airplane. These sections are changed: 1. Accomplishment Instructions: a. Paragraph B., Work Instructions: A step is added to remove electrical power from the airplane. b. Paragraph B., Work Instructions: A step is added to supply electrical power to the airplane. 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** October 08, 2009 Original Issue: July 29, 2011 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 5 of 56BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 6 of 56 **BOEING SERVICE BULLETIN 767-21-0235**

BLANK PAGE

### Commercial **Airplanes** 

# 767 Service Bulletin **Summary Number: 767-21-0235**  Original Issue: October 08, 2009 Revision 1: July 29, 2011 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Cooling - Freighter Equipment Cooling System 3-Way Valve Control Logic Change **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This service bulletin gives instructions to install a relay and related wiring in the P36 panel to change the control logic for the equipment cooling 3-way valve on freighter airplanes. The logic is changed to make the 3-way valve close when the Electrical/Electronic (E/E) cooling system is put in STBY mode, when selected from the P5 overhead panel in the flight compartment. This will result in the continued supply of cooled air to the flight compartment avionic equipment. If this service bulletin is not done, a loss of air flow from the Air Conditioning (A/C) packs could occur and result in a loss of the displays in the flight compartment. A 767-300F operator experienced an air turn-back event caused by the loss of one of the first officer’s primary displays and the loss of color on two of the captain’s primary displays. The display problems were followed by electrical burning smells in the flight compartment, which was found to be the result of an overheat condition from a decreased supply of cooling air to the avionic equipment in the flight compartment. The cause of the occurrence was found to be ice accumulation in the supply line orifice, which was sufficient in quantity to block the conditioned air flow to the flight compartment. The icing condition is found to start during ground operations in high humidity environments and when the cooling packs are selected to full cold. The packs cannot fully remove all moisture from the air in high humidity environments which subsequently causes small quantities of airborne ice crystals in the released air flow. After a period of time, the ice crystals cause frost to collect on the internal walls of the A/C ducts. If a large quantity of frost collects in the ducts and is not cleared, the frost becomes ice. The combination of one cooling pack in operation above freezing and the other cooling pack in operation below freezing, in humid environments, increases the amount of frost that can accumulate. To give continuous cooling to the flight compartment avionic equipment, Boeing has made changes to the control logic for the equipment cooling 3-way valve, which will give the pilots the option to select to have replacement cooling airflow supplied from the E/E cooling system, if the airflow from the A/C packs becomes unavailable or not sufficient. The changes make the operation of the valve close when the E/E cooling system is put in the STBY mode when selected from the flight compartment. Accomplishment of this service bulletin installs a relay in the lower section of the P36 Left Miscellaneous Electrical Equipment Panel, with related wiring changes to change the operation of the 3-way valve when the E/E cooling system is selected to the STBY mode from the flight compartment. This gives the pilots the option to choose an alternative supply of cooling airflow to prevent overheating of the avionic equipment in the flight compartment. Boeing Service Related Problem (SRP) 767-SRP-21-0173 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 21-08002 and 767 FTD 21-08001 are related to this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 7 of 56**ACTION (PRR B12900-255) Group 1:**  Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment Panel in the Main Equipment Center (MEC). Add new wires and replace a wire in wire bundle W0176 and install a new relay in the lower section of the panel. Do a functional test of the system. **Group 2-3:** Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment Panel in the Main Equipment Center (MEC). Add new wires and replace wires in wire bundles W0176 and W0184 and install a new relay in the lower section of the panel. Do a functional test of the system. **EFFECTIVITY** 767-300F Airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes. **COMPLIANCE** No compliance time is given. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  4.95 7.60 Group 1 6.85 9.50 Group 2 and 3 **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: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 8 of 56 **BOEING SERVICE BULLETIN 767-21-0235**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 9 of 56 **BOEING SERVICE BULLETIN 767-21-0235**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 10 of 56 **BOEING SERVICE BULLETIN 767-21-0235**

BLANK PAGE

### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-21-0235** Original Issue: October 08, 2009 Revision 1: July 29, 2011 ATA System: 2158 **SUBJECT:** AIR CONDITIONING - Cooling - Freighter Equipment Cooling System 3-Way Valve Control Logic Change **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B12900-255 for data about this change. Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. **DESCRIPTION CONFIGURATION**  **GROUP** 767-300F airplanes, delivered with a General Market Freighter configuration, that have P36 panel wiring differences. - 1
767-300F airplanes, delivered with a Manual Freighter configuration, that have P36 panel wiring differences. - 2
767-300F airplanes, delivered with a Manual Freighter configuration, that have P36 panel wiring differences. - 3

Airplane Models: 767-300F **Group Variable Number**  2 VR201 - VR211 1 VR251 1 VR256 - VR260 1 VT501 1 VT511 - VT513

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 11 of 56**Group Variable Number**  1 VT521 - VT523 1 VT531 - VT533 3 VW701 - VW721 1 VW851 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** This service bulletin gives instructions to install a relay and related wiring in the P36 panel to change the control logic for the equipment cooling 3-way valve on freighter airplanes. The logic is changed to make the 3-way valve close when the Electrical/Electronic (E/E) cooling system is put in STBY mode, when selected from the P5 overhead panel in the flight compartment. This will result in the continued supply of cooled air to the flight compartment avionic equipment. If this service bulletin is not done, a loss of air flow from the Air Conditioning (A/C) packs could occur and result in a loss of the displays in the flight compartment. A 767-300F operator experienced an air turn-back event caused by the loss of one of the first officer’s primary displays and the loss of color on two of the captain’s primary displays. The display problems were followed by electrical burning smells in the flight compartment, which was found to be the result of an overheat condition from a decreased supply of cooling air to the avionic equipment in the flight compartment. The cause of the occurrence was found to be ice accumulation in the supply line orifice, which was sufficient in quantity to block the conditioned air flow to the flight compartment. The icing condition is found to start during ground operations in high humidity environments and when the cooling packs are selected to full cold. The packs cannot fully remove all moisture from the air in high humidity environments which subsequently causes small quantities of airborne ice crystals in the released air flow. After a period of time, the ice crystals cause frost to collect on the internal walls of the A/C ducts. If a large quantity of frost collects in the ducts and is not cleared, the frost becomes ice. The combination of one cooling pack in operation above freezing and the other cooling pack in operation below freezing, in humid environments, increases the amount of frost that can accumulate. To give continuous cooling to the flight compartment avionic equipment, Boeing has made changes to the control logic for the equipment cooling 3-way valve, which will give the pilots the option to select to have replacement cooling airflow supplied from the E/E cooling system, if the airflow from the A/C packs becomes unavailable or not sufficient. The changes make the operation of the valve close when the E/E cooling system is put in the STBY mode when selected from the flight compartment. Accomplishment of this service bulletin installs a relay in the lower section of the P36 Left Miscellaneous Electrical Equipment Panel, with related wiring changes to change the operation of the 3-way valve when the E/E cooling system is selected to the STBY mode from the flight compartment. This gives the pilots the option to choose an alternative supply of cooling airflow to prevent overheating of the avionic equipment in the flight compartment.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 12 of 56 **BOEING SERVICE BULLETIN 767-21-0235**Revision 1 is sent to tell operators that when they do the change in the P36 left miscellaneous electrical equipment panel electrical power must be removed from the airplane. Boeing Service Related Problem (SRP) 767-SRP-21-0173 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 21-08002 and 767 FTD 21-08001 are related to this service bulletin. **D. Description Group 1:**  Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment Panel in the Main Equipment Center (MEC). Make changes to wire bundle W0176 and install a new relay in the lower section of the panel. Do a functional test of the system. **Group 2-3:** Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment Panel in the Main Equipment Center (MEC). Make changes to wire bundles W0176 and W0184 and install a new relay in the lower section of the panel. Do a functional test of the system. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. 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, 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 13 of 56 **BOEING SERVICE BULLETIN 767-21-0235 G. Manpower**  The table below shows an estimate of the task hours necessary to do this service bulletin 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 Per-**  **sons Task** 
0.50 0.50 1 Open Access and Prepare Airplane

- FIGURE 1 (Routing Only) 2.65 5.30 2 FIGURE 2 0.30 0.30 1 FIGURE 8 1.00 1.00 1 Test 0.50 0.50 1 Close Access 4.95 7.60 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Per-**  **sons Task** 
0.50 0.50 1 Open Access and Prepare Airplane

- FIGURE 3 (Routing Only) 2.65 5.30 2 FIGURE 4 1.90 1.90 1 FIGURE 6 0.30 0.30 1 FIGURE 8 1.00 1.00 1 Test 0.50 0.50 1 Close Access 6.85 9.50 TOTAL FOR EACH AIRPLANE

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 14 of 56 **BOEING SERVICE BULLETIN 767-21-0235 Group 3:**  **Elapsed Hours Task Hours**  **Number of Per- sons**  **Task**
0.50 0.50 1 Open Access and Prepare Airplane

- FIGURE 3 (Routing Only) 2.65 5.30 2 FIGURE 5 1.90 1.90 1 FIGURE 7 0.30 0.30 1 FIGURE 8 1.00 1.00 1 Test 0.50 0.50 1 Close Access 6.85 9.50 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR B12900-255 b. Boeing Service Related Problem (SRP) 767-SRP-21-0173 c. Standard Overhaul Practices Manual (SOPM) 20-50-05, 20-50-10 d. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-11, 20-10-12, 20-10-19, 20-20-00, 20-20-10, 20-81-12, 20-81-19, 20-81-22, 20-90-11 e. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 31-01-36, 32-09-02 f. 767 Fleet Team Digest (FTD) 21-08001, 21-08002 g. 767 Wiring Diagram Manual (WDM) 21-58-16 2. Data supplied with this Service Bulletin None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 15 of 56 **BOEING SERVICE BULLETIN 767-21-0235**3. Installation Drawings Used in the Preparation of this Service Bulletin **Title Drawing Number**  MODULAR WIRE BUNDLE INSTALLATION P36, MISCELLANEOUS RELAY PANEL, LEFT 288T2036
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. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  21-58 767 Wiring Diagram 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: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 16 of 56 **BOEING SERVICE BULLETIN 767-21-0235 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. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. **Group 1: Unit Price thru**  **May 31/10 ROLT**  **(Weeks) QTY**  **Date Name**  **Kit Number** $715.00 18 5 Jun 15/09 Top Kit - 3-Way Valve Logic Modification 015T1839-1 4 Jul 14/09 **Group 2-3: Unit Price thru**  **May 31/10 ROLT**  **(Weeks) QTY**  **Date Name**  **Kit Number** $955.00 18 5 Jun 23/09 Top Kit - 3-Way Valve Logic Modification 015T1839-2 5 Jul 08/09 5 Jul 22/09 1 Aug 05/09 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. Mail to: 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 17 of 56 **BOEING SERVICE BULLETIN 767-21-0235 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 015T1839 Notes**  **Name QTY**  **New Part Number -2**  **-1** Top Kit - 3-WayValve Logic Modification . - 015T1839-1
Top Kit - 3-WayValve Logic Modification - . 015T1839-2

ASSY -101 (W0176) 1 1 289T1162-101
ASSY -102 (W0184) 1

. 289T1162-102
LACING TAPE - RED (135C) 100 FT 1 1 289T9001-21

LACING TAPE - BLUE (135C) 100 FT 1

. 289T9001-61

RELAY 1 1 BACR13CF2A TAPE, ID 2 2 BACT19J4
**Kit 289T1162 Notes**  **Name QTY**  **New Part Number -102**  **-101** ASSY -101 (W0176) . - 289T1162-101
ASSY -102 (W0184) - . 289T1162-102
ID TAPE - CONNECTOR . 1 289T1162-10101
WIRE - RAW MATERIAL . 1 289T1162-101W

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 18 of 56 **BOEING SERVICE BULLETIN 767-21-0235 Kit 289T1162**  **Notes Name**  **QTY New Part Number**  **-102 -101**  WIRE - RAW MATERIAL 1

. 289T1162-102W CONTACT, SOCKET . 4 BACC47DJ1 CONTACT, SOCKET . 1 BACC47ER1
RELAY SOCKET

. 1 BACS16X1A CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 4 3 M39029/11-145

2. Parts and Materials Supplied by the Operator None. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 19 of 56 **BOEING SERVICE BULLETIN 767-21-0235**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 20 of 56 **BOEING SERVICE BULLETIN 767-21-0235**

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. 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. 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. 4. 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. **B. WORK INSTRUCTIONS** 1. Get access to the Flight Compartment and open the Main Equipment Center (MEC) access door, 119AL, to get access to the MEC. Refer to 767 AMM 06-41-00. 2. Remove electrical power from the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 3. In the Flight Compartment and MEC, open the circuit breakers specified in the tables below and attach 'DO-NOT-CLOSE' tags. **MAIN POWER DISTRIBUTION PANEL Number**  **Name Location**  **Panel** C00331 CB-EQUIP COOL FAN SPLY 1 H018 P6-3 **CIRCUIT BREAKER PANEL ASSEMBLY Number**  **Name Location**  **Panel** C00654 CB-EQUIP COOLING SUPPLY FAN 1 P011 P11-3 4. Open the P36 Left Miscellaneous Electrical Equipment Panel to get access to the wiring and electrical equipment. Refer to 767 AMM 31-01-36. 5. **Group 1:** Make changes to wire bundle W0176 in accordance with FIGURE 1 and FIGURE 2.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 21 of 56 **BOEING SERVICE BULLETIN 767-21-0235**6. **Group 2-3:** Make changes to wire bundles W0176 and W0184 in accordance with: **Group 2:** FIGURE 3, FIGURE 4 and FIGURE 6. **Group 3:** FIGURE 3, FIGURE 5 and FIGURE 7. 7. Install a new relay in the lower section of P36 Left Miscellaneous Electrical Equipment Panel in accordance with FIGURE 8. 8. Close the P36 Left Miscellaneous Electrical Equipment Panel. 9. In the Flight Compartment and the MEC, remove the 'DO-NOT-CLOSE' tags and close the circuit breakers specified in the tables below. **MAIN POWER DISTRIBUTION PANEL Number**  **Name Location**  **Panel** C00331 CB-EQUIP COOL FAN SPLY 1 H018 P6-3 **CIRCUIT BREAKER PANEL ASSEMBLY Number**  **Name Location**  **Panel** C00654 CB-EQUIP COOLING SUPPLY FAN 1 P011 P11-3 10. Supply electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 11. Do the test as follows: **Group 1:** 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. Or to put the Air/Ground Relay System in GROUND mode, refer to 767 AMM 32-09-02 as an accepted procedure. c. In the MEC, make sure the circuit breakers specified in the table below are closed: **CIRCUIT BREAKER PANEL ASSEMBLY Number**  **Name Location**  **Panel** C00653 LEFT PACK FLOW CONT A013 P11-1 C00704 RIGHT PACK FLOW CONT A026 P11-4 C00688 EQUIPMENT COOLING STANDBY B008 P11-1 C00679 EQUIP COOL OVERRIDE C019 P11-4

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 22 of 56 **BOEING SERVICE BULLETIN 767-21-0235 CIRCUIT BREAKER PANEL ASSEMBLY**  **Number Name**  **Location Panel**  C01175 LDG GR POS AIR/GND SYS 1 C030 P11-4 C01426 ENGINE SPEED SENSE L2 D016 P11-1 C01427 ENGINE SPEED SENSE R2 D017 P11-1 d. In the Flight Compartment, set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO. e. Disconnect connector (D20366) to Equipment Cooling Temperature Control switch (S868) at STA 208, WL 172 and RBL 60. f. Install a jumper from pin 1 of connector (D20366) to pin 2 of connector (D20366). g. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) h. Disconnect connector (D2770) from the Left Flow Control Valve (V16). **NOTE:** This simulates the Left Pack is ON. i. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) j. In the MEC, select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel, in the 'TEST' position. **NOTE:** This simulates left and right engines ON. Two of these test switches are momentary toggle switches and must be manually held in the 'TEST' position during all of this test procedure by the person at the P50 Panel. For this test procedure to give correct results, make sure these two test switches are not released from the 'TEST' position until this procedure is complete. k. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) l. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel. m. Make sure the 3-way valve is in the condition specified in the table below:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 23 of 56 **BOEING SERVICE BULLETIN 767-21-0235 Equipment Number**  **Name Condition**  V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) n. Disconnect connector (D1276) from the Right Flow Control Valve (V17). **NOTE:** This simulates the Right Pack is ON. o. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) p. Select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel, in the 'TEST' position. **NOTE:** This simulates left and right engines ON. Two of these test switches are momentary toggle switches and must be manually held in the 'TEST' position during all of this test procedure by the person at the P50 Panel. For this test procedure to give correct results, make sure these two test switches are not released from the 'TEST' position until this procedure is complete. **CAUTION:** EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES. q. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) r. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY. s. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) t. Set the Equipment Cooling rotary switch on the P5 overhead panel to OVRD.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 24 of 56 **BOEING SERVICE BULLETIN 767-21-0235 CAUTION:**  EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. ALSO, EQUIPMENT IN THE MEC WILL BE NOT COOLED WHEN THE EQUIPMENT COOLING ROTARY SWITCH IS SET TO THE 'OVRD' POSITION AS THE E/E COOLING FANS ARE SHUTOFF. DAMAGE TO THE FLIGHT COMPARTMENT INSTRUMENTS AND MEC EQUIPMENT COULD OCCUR IF THE EQUIPMENT COOLING ROTARY SWITCH IS SET IN THE 'OVRD' POSITION FOR MORE THAN 5 MINUTES. u. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) v. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO. **CAUTION:** EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES. w. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) x. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel. y. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) z. Connect connector (D2770) back on to the Left Flow Control Valve (V16). aa. Connect connector (D1276) back on to the Right Flow Control Valve (V17). ab. Remove the jumper from pin 1 and pin 2 in Connector (D20366). ac. Connect connector (D20366) back on to Equipment Cooling Temperature Control Switch (S868) at STA 208, WL 172, and RBL 60. ad. Put the airplane back to the configuration before the test.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 25 of 56 **BOEING SERVICE BULLETIN 767-21-0235 Group 2-3:**  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. Or to put the Air/Ground Relay System in GROUND mode, refer to 767 AMM 32-09-02 as an accepted procedure. c. In the MEC, make sure the circuit breakers specified in the table below are closed: **CIRCUIT BREAKER PANEL ASSEMBLY Number**  **Name Location**  **Panel** C00653 LEFT PACK FLOW CONT A013 P11-1 C00704 RIGHT PACK FLOW CONT A026 P11-4 C00688 EQUIPMENT COOLING STANDBY B008 P11-1 C00679 EQUIP COOL OVERRIDE C019 P11-4 C01175 LDG GR POS AIR/GND SYS 1 C030 P11-4 C01426 ENGINE SPEED SENSE L2 D016 P11-1 C01427 ENGINE SPEED SENSE R2 D017 P11-1 d. In the Flight Compartment, set the Equipment Cooling rotary switch on the the P5 overhead panel to AUTO. e. Disconnect connector (D20366) to Equipment Cooling Temperature Control switch (S868) at STA 208, WL 172 and RBL 60. f. Install a jumper from pin 1 of connector (D20366) to pin 2 of connector (D20366). g. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) h. Disconnect connector (D2770) from the Left Flow Control Valve (V16). **NOTE:** This simulates the Left Pack is ON. i. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) j. In the MEC, select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel, in the 'TEST' position.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 26 of 56 **BOEING SERVICE BULLETIN 767-21-0235 NOTE:**  This simulates left and right engines ON. Two of these test switches are momentary toggle switches and must be manually held in the 'TEST' position during all of this test procedure by the person at the P50 Panel. For this test procedure to give correct results, make sure these two test switches are not released from the 'TEST' position until this procedure is complete. **CAUTION:** EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES. k. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) l. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY. m. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) n. Set the Equipment Cooling rotary switch on the P5 overhead panel to OVRD. **CAUTION:** EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. ALSO, EQUIPMENT IN THE MEC WILL BE NOT COOLED WHEN THE EQUIPMENT COOLING ROTARY SWITCH IS SET TO THE 'OVRD' POSITION AS THE E/E COOLING FANS ARE SHUTOFF. DAMAGE TO THE FLIGHT COMPARTMENT INSTRUMENTS AND MEC EQUIPMENT COULD OCCUR IF THE EQUIPMENT COOLING ROTARY SWITCH IS SET IN THE 'OVRD' POSITION FOR MORE THAN 5 MINUTES. o. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) p. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 27 of 56 **BOEING SERVICE BULLETIN 767-21-0235 CAUTION:**  EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES. q. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) r. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel. s. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) t. Disconnect connector (D1276) from the Right Flow Control Valve (V17). **NOTE:** This simulates the Right Pack is ON. u. Connect connector (D2770) back on to the Left Control Valve (V16). v. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) w. Select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel, in the 'TEST' position. **NOTE:** This simulates left and right engines ON. Two of these test switches are momentary toggle switches and must be manually held in the 'TEST' position during all of this test procedure by the person at the P50 Panel. For this test procedure to give correct results, make sure these two test switches are not released from the 'TEST' position until this procedure is complete. **CAUTION:** EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES. x. Make sure the 3-way valve is in the condition specified in the table below:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 28 of 56 **BOEING SERVICE BULLETIN 767-21-0235 Equipment Number**  **Name Condition**  V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) y. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY. z. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B) aa. Set the equipment cooling rotary switch on the P5 overhead panel to OVRD. **CAUTION:** EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. ALSO, EQUIPMENT IN THE MEC WILL BE NOT COOLED WHEN THE EQUIPMENT COOLING ROTARY SWITCH IS SET TO THE 'OVRD' POSITION AS THE E/E COOLING FANS ARE SHUTOFF. DAMAGE TO THE FLIGHT COMPARTMENT INSTRUMENTS AND MEC EQUIPMENT COULD OCCUR IF THE EQUIPMENT COOLING ROTARY SWITCH IS SET IN THE 'OVRD' POSITION FOR MORE THAN 5 MINUTES. ab. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) ac. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO. **CAUTION:** EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)' CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES. ad. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE OPEN (C-B) ae. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right and (M1093) Left on the P50 Panel. af. Make sure the 3-way valve is in the condition specified in the table below: **Equipment Number Name**  **Condition** V90 MANIFOLD INTERCONNECT VALVE CLOSED (A-B)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 29 of 56 **BOEING SERVICE BULLETIN 767-21-0235**ag. Connect connector (D1276) back on to Right Flow Control Valve (V17). ah. Remove the jumper from pin 1 and pin 2 in Connector (D20366). ai. Connect connector (D20366) back on to Equipment Cooling Temperature Control Switch (S868) at STA 208, WL 172, and RBL 60. aj. Put the airplane back to the configuration before the test. 12. Close the MEC access door, 119AL. 13. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1: July 29, 2011 30 of 56 **BOEING SERVICE BULLETIN 767-21-0235 This Figure applies only to: Group 1.** 

**FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - ROUTING**  **(SHEET 1 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 31 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -**  **ROUTING (SHEET 2 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 32 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -**  **ROUTING (SHEET 3 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 33 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -**  **ROUTING (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 34 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -**  **ROUTING (SHEET 5 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 35 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -**  **ROUTING (SHEET 6 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 36 of 56 **BOEING SERVICE BULLETIN 767-21-0235 This Figure applies only to: Group 1.** 

REFERENCE: 767 WDM 21-58-16. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. **NOTE:** Use the parts supplied in wire kit 289T1162-101 and top kit 015T1839-1 to do the work in this Figure.

**FIGURE 2: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES** 

**(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 37 of 56 **BOEING SERVICE BULLETIN 767-21-0235 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to the wire kit cut and code table, to identify the wires as shown and to cut to the necessary lengths. - 289T1162-101W WIRE - RAW MATERIAL 1

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 2

Refer to SWPM 20-81-12 andSWPM 20-81-22 as accepted procedures. 1 BACS16X1A RELAY SOCKET 3

Refer to SWPM 20-81-12 as an accepted procedure. 4 BACC47DJ1 CONTACT, SOCKET 4
Refer to SWPM 20-81-19 as an accepted procedure. 1 BACC47ER1 CONTACT, SOCKET 5
Identified as D21731 M/W K10717.Install within 6 inches of equipment. 1 289T1162-10101 ID TAPE - CONNECTOR 6

Use to tie the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. - 289T9001-21 LACING TAPE - RED (135C) 100 FT 7

**WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-101W NOTES**  **MATERIAL SPECIFICATION LENGTH**  **(INCHES) TYPE**  **CODE GAGE**  **COLOR WIRE #**  **WBA #** BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 24C W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AC W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AD W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AE W0176

**FIGURE 2: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES** 

**(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 38 of 56 **BOEING SERVICE BULLETIN 767-21-0235 This Figure applies only to: Group 2-3.** 

**FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND W0184 - ROUTING**  **(SHEET 1 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 39 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND**  **W0184 - ROUTING (SHEET 2 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 40 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND**  **W0184 - ROUTING (SHEET 3 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 41 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND**  **W0184 - ROUTING (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 42 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND**  **W0184 - ROUTING (SHEET 5 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 43 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND**  **W0184 - ROUTING (SHEET 6 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 44 of 56 **BOEING SERVICE BULLETIN 767-21-0235 This Figure applies only to: Group 2.** 

REFERENCE: 767 WDM 21-58-16. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. **NOTE:** Use the parts supplied in wire kit 289T1162-101 and top kit 015T1839-2 to do the work in this Figure.

**FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES** 

**(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 45 of 56 **BOEING SERVICE BULLETIN 767-21-0235 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to the wire kit cut and code table, to identify the wires as shown and to cut to the necessary lengths. - 289T1162-101W WIRE - RAW MATERIAL 1

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 2

Refer to SWPM 20-81-12 andSWPM 20-81-22 as accepted procedures. 1 BACS16X1A RELAY SOCKET 3

Refer to SWPM 20-81-12 as an accepted procedure. 4 BACC47DJ1 CONTACT, SOCKET 4
Refer to SWPM 20-81-19 as an accepted procedure. 1 BACC47ER1 CONTACT, SOCKET 5
Identified as D21731 M/W K10717.Install within 6 inches of equipment. 1 289T1162-10101 ID TAPE - CONNECTOR 6

Use to tie the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. - 289T9001-21 LACING TAPE - RED (135C) 100 FT 7

**WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-101W NOTES**  **MATERIAL SPECIFICATION LENGTH**  **(INCHES) TYPE**  **CODE GAGE**  **COLOR WIRE #**  **WBA #** BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 24C W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AC W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AD W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AE W0176

**FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES** 

**(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 46 of 56 **BOEING SERVICE BULLETIN 767-21-0235 This Figure applies only to: Group 3.** 

REFERENCE: 767 WDM 21-58-16. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. **NOTE:** Use the parts supplied in wire kit 289T1162-101 and top kit 015T1839-2 to do the work in this Figure.

**FIGURE 5: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES** 

**(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 47 of 56 **BOEING SERVICE BULLETIN 767-21-0235 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to the wire kit cut and code table, to identify the wires as shown and to cut to the necessary lengths. - 289T1162-101W WIRE - RAW MATERIAL 1

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 2

Refer to SWPM 20-81-12 andSWPM 20-81-22 as accepted procedures. 1 BACS16X1A RELAY SOCKET 3

Refer to SWPM 20-81-12 as an accepted procedure. 4 BACC47DJ1 CONTACT, SOCKET 4
Refer to SWPM 20-81-19 as an accepted procedure. 1 BACC47ER1 CONTACT, SOCKET 5
Identified as D21731 M/W K10717.Install within 6 inches of equipment. 1 289T1162-10101 ID TAPE - CONNECTOR 6

Use to tie the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. - 289T9001-21 LACING TAPE - RED (135C) 100 FT 7

**WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-101W NOTES**  **MATERIAL SPECIFICATION LENGTH**  **(INCHES) TYPE**  **CODE GAGE**  **COLOR WIRE #**  **WBA #** BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 24C W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AC W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AD W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 120 PK 24 0AE W0176

**FIGURE 5: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 - WIRING CHANGES** 

**(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 48 of 56 **BOEING SERVICE BULLETIN 767-21-0235 This Figure applies only to: Group 2.** 

REFERENCE: 767 WDM 21-58-16. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. **NOTE:** Use the parts supplied in wire kit 289T1162-102 and top kit 015T1839-2 to do the work in this Figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to the wire kit cut and code table, to identify the wires as shown and to cut to the necessary lengths. - 289T1162-102W WIRE - RAW MATERIAL 1

Refer to SWPM 20-90-11 as an accepted procedure. 4 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 2

**FIGURE 6: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 - WIRING CHANGES** 

**(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 49 of 56 **BOEING SERVICE BULLETIN 767-21-0235 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Use to tie the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. - 289T9001-61 LACING TAPE - BLUE (135C) 100 FT 3

**WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-102W NOTES**  **MATERIAL SPECIFICATION LENGTH**  **(INCHES) TYPE**  **CODE GAGE**  **COLOR WIRE #**  **WBA #** BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 09D W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 593 W0184

**FIGURE 6: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 - WIRING CHANGES** 

**(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 50 of 56 **BOEING SERVICE BULLETIN 767-21-0235 This Figure applies only to: Group 3.** 

REFERENCE: 767 WDM 21-58-16. The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. **NOTE:** Use the parts supplied in wire kit 289T1162-102 and top kit 015T1839-2 to do the work in this Figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to the wire kit cut and code table, to identify the wires as shown and to cut to the necessary lengths. - 289T1162-102W WIRE - RAW MATERIAL 1

Refer to SWPM 20-90-11 as an accepted procedure. 4 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 2

**FIGURE 7: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 - WIRING CHANGES** 

**(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 51 of 56 **BOEING SERVICE BULLETIN 767-21-0235 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Use to tie the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. - 289T9001-61 LACING TAPE - BLUE (135C) 100 FT 3

**WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-102W NOTES**  **MATERIAL SPECIFICATION LENGTH**  **(INCHES) TYPE**  **CODE GAGE**  **COLOR WIRE #**  **WBA #** BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 09D W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 593 W0184

**FIGURE 7: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 - WIRING CHANGES** 

**(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 52 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION**  **(SHEET 1 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 53 of 56 **BOEING SERVICE BULLETIN 767-21-0235 FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 54 of 56 **BOEING SERVICE BULLETIN 767-21-0235**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.

**FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 55 of 56 **BOEING SERVICE BULLETIN 767-21-0235 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** as D21731. Refer to SOPM 20-50-10 asan accepted procedure. 1 BACT19J4 TAPE, ID Identify 1

Identified as D21731. Refer to SOPM 20-50-05 asan accepted procedure. 1 BACT19J4 TAPE, ID Install (New)

(a) 1 BACR13CF2A RELAY Install (New) 2 as K10717. Refer to SOPM 20-50-10 asan accepted procedure. 1 BACT19J4 TAPE, ID Identify 3

Identified as K10717. Refer to SOPM 20-50-05 asan accepted procedure. 1 BACT19J4 TAPE, ID Install (New)

(a) If the bonding jumper is removed for relay installation, the bonding jumper must be installed and tested after the relay is installed. Refer to SWPM 20-20-00 and SWPM 20-20-10 as accepted procedures to install and test the bonding jumper.

**FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2009 767-21-0235 Revision 1 July 29, 2011 56 of 56 **BOEING SERVICE BULLETIN 767-21-0235**