### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-21A0245 Original Issue: April 16, 2010 Revision 2: September 27, 2013 ATA System: 2158 2123 SUBJECT:AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic And Main Cargo Air Distribution System Change And Flight Deck Air Relief System Installation Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2010 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 1 of 121 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 2 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT

BLANK PAGETable of Contents Revision Transmittal Sheet............................................ 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 21 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 21 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 22 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 42 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 43 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE [Group 1-3, Configuration 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION [Group 1-3, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 FIGURE 3: WIRE BUNDLE W176 CHANGE [Group 1-3, Configuration 1]. . . . . . . . . . . . . . . . 59 FIGURE 4: WIRE BUNDLE W596 AND W1702 CHANGE [Group 1-3, Configuration 1]. . . . . . . . 61 FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE [Group 1-3, Configuration 1]. . . . . . . . 62 FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING [Group 1-3, Configuration 1]. . . . . . . 64 FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING [Group 1-3, Configuration 1]. . . . . . 72

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 3 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT. . . . . . . . 77 FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83 FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION . 93 FIGURE 12: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 FIGURE 13: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE [Group 3] . 103 FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING [Group 1-3, Configuration 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE . . . 110 FIGURE 16: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113 FIGURE 17: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 115 FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION. . . . . . . . . . . . 117

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 4 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT

### Commercial Airplanes 

# 767 Service Bulletin ALERT Revision Transmittal Sheet Number: 767-21A0245 Original Issue: April 16, 2010 Revision 2: September 27, 2013 ATA System: 2158 2123 SUBJECT:AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic And Main Cargo Air Distribution System Change And Flight Deck Air Relief System Installation This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION More work is necessary on the airplanes changed in accordance with the original issue or Revision 1 of this service bulletin. Flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck cargo compartment must be removed and caps and an orifice installed. In addition, a Flight Deck Air Relief System (FDARS) must be installed. This work is identified as configuration 2 for Group 1, 2, and 3 airplanes. Airplane Variable Numbers VR251 and VR256 are moved from airplane Group 1 to new airplane Group 3. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. REASON FOR REVISION This revision is sent to change the service bulletin release classification from "Standard" to "Alert" as it is related to a safety Service Related Problem (SRP). This revision also makes sure cargo smoke detection performance in the main deck cargo compartment continues to agree with European Aviation Safety Agency (EASA) validation requirements. As a result of this requirement, instructions are added to remove flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck cargo compartment and install caps and an orifice assy. This change reduces the airflow to the aft section of the main deck cargo compartment. This revision also installs a Flight Deck Air Relief System (FDARS) to reduce flight deck noise caused by excessive airflow into the flight deck when the 3-way valve is closed and the flight deck equipment is being cooled by the Electrical Equipment (EE) cooling fans. This change addresses the issues in Information Notice 767-21A0245 R01 IN01. As part of these changes, the EASA/Joint Aviation Authorities (JAA) approval statement, new kits, and new figures are added. Also, the background information, compliance data, and manpower data is updated. These sections are changed: 1. Subject: Updated to include the additional work. 2. Summary Background: Updated to include information about the additional work necessary and to update the existing information. A summary evaluation table is added.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 5 of 1213. Summary Action: Added actions for new groups and configurations. Existing data is updated. 4. Summary Compliance: An Airworthiness Directive (AD) statement is added and the compliance statement is changed. 5. Summary Manpower: Changed to refer to Paragraph 1.G., Manpower. 6. Summary Illustration: Updated to include additional work. 7. Paragraph 1.A., Effectivity: Group 3 and Configuration 2 for Group 1 and Group 2 are added. 8. Paragraph 1.B., Concurrent Requirements: The concurrent requirements are updated. 9. Paragraph 1.C., Reason: Updated to include information about the additional work necessary and to update the existing information. Fleet Team Digest (FTD) reference is added. 10. Paragraph 1.D., Description: Added actions for new groups and configurations. Existing data is updated. 11. Paragraph 1.E., Compliance: An Airworthiness Directive (AD) statement is added and the compliance statement is changed. 12. Paragraph 1.F., Approval: The approval statement is updated. 13. Paragraph 1.G., Manpower: Tables added for all groups and configurations. The existing data is updated. 14. Paragraph 1.H., Weight and Balance Changes: Weight and balance tables are added. 15. Paragraph 1.J., References: The reference list and the installation drawings reference table are updated. 16. Paragraph 1.K., Publications Affected: The publications affected table is updated. 17. Paragraph 1.M., Software Accomplishment Summary: A software accomplishment statement is added. 18. Paragraph 2.A., Material - Price and Availability: New top kits and supplemental kits are added. Kit pricing data is updated. 19. Paragraph 2.C.1., Kits/parts: New top kits and supplemental kits are added. 20. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Operator supplied materials are added. 21. Paragraph 3.A., General Information: The general information notes are updated. 22. Paragraph 3.B., Work Instructions: Instructions for configuration 1 airplanes are updated and instructions for configuration 2 airplanes are added. 23. Figures 1 thru 7: The applicability is updated. 24. Figures 6 and 7: The wire routing is updated. 25. Figures 8 thru 18: Added for additional work necessary. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 6 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTPages with no vertical lines have no important changes. REVISION HISTORY April 16, 2010 Original Issue: September 30, 2010 Revision 1: September 27, 2013 Revision 2:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 7 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 8 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT

BLANK PAGE

### Commercial Airplanes 

# 767 Service Bulletin ALERT Summary Number: 767-21A0245 Original Issue: April 16, 2010 Revision 2: September 27, 2013 ATA System: 2158 2123 SUBJECT:AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic And Main Cargo Air Distribution System Change And Flight Deck Air Relief System Installation THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS Refer to Paragraph 1.B., Concurrent Requirements. BACKGROUND This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring, or loss of color caused by moisture or condensation being collected inside the display units in the flight compartment can occur during operation in hot and humid environments. If this service bulletin is not done, there is an increased risk that the flight compartment display units could malfunction and become unserviceable because of moisture ingress. Loss of the primary attitude information on both primary display units could lead to flight crew confusion and difficulty in the transition to standby attitude indication. Flight compartment indication blanking can also cause unscheduled maintenance and airplane downtime. The inability of the flight crew to transition from primary attitude indication to standby attitude indication during a critical phase of flight could contribute to an unsafe flight condition. In addition, this service bulletin reduces airflow to the aft part of the main cargo compartment to make sure that cargo smoke detection system performance continues to agree with European Aviation Safety Agency (EASA) validation requirements. Operators of 767-300F airplanes have reported display unit malfunctions such as blanking, blurring, or loss of color caused by moisture or condensation being collected inside the display units during operation in hot and humid environments. The reports have included single display unit and multiple display unit malfunctions. Boeing is aware of several instances that are the likely causes of display unit malfunctions related to moisture or condensation ingress. The most frequent instance was display units being cold soaked by the air conditioned air delivered from the air conditioning packs by the Electrical/Electronic cooling system through the 3-way valve in hot and humid conditions. Another instance was an unserviceable air conditioning pack water separation system, which allowed water to be delivered to the flight compartment in the air conditioned air. The other instance was a malfunction of an air conditioning pack, which caused ice to be delivered to the flight compartment in the air conditioned air. As a result of these findings, the control logic of the 3-way valve is changed so that the valve will open after five minutes at an altitude above 10,000 feet, and close at an altitude below 10,000

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 9 of 121feet. Limiting the 3-way valve to open after five minutes above 10,000 feet will decrease the amount of moisture or condensation that can collect in the display units because of the reduced water content in the atmosphere at higher altitudes. As a consequence of the 3-way valve closure below 10,000 feet, excessive airflow in the flight deck air distribution system causes increased flight deck noise which makes the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. To prevent this, a Flight Deck Air Relief System (FDARS) is installed to exhaust the excessive airflow into the Electrical Equipment (EE) bay when the 3-way valve is closed. Accomplishment of this service bulletin changes the Environmental Control System (ECS) Flight Deck Cooling System Logic to use EE cooling rather than airplane pack cooling on the ground and up to 10,000 feet. This change reduces the amount of moisture or condensation that can collect in the flight compartment display units and results in reduced flight compartment display unit malfunction occurrences. In addition, accomplishment of this service bulletin installs a FDARS to exhaust excessive airflow into the right side tunnel of the EE bay when the 3-way valve is in the closed position. This is to reduce flight deck noise caused by excessive airflow in the flight deck air distribution system when the 3-way valve is closed and the flight deck equipment is being cooled by the EE cooling fans. This service bulletin also removes flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck cargo compartment and installs caps and an orifice assy. This change reduces airflow to the aft part of the main cargo compartment to make sure the cargo smoke detection system performance continues to agree with European Aviation Safety Agency (EASA) validation requirements. Boeing Service Related Problem (SRP) 767-SRP-21-179 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 21-09003 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. Reference Affected Planning Data Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 10 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTACTION (PRR B12900-260) Group 1-3, Configuration 1: 1. In the Main Equipment Center (MEC) change wire bundles W596, W756, and W1702. 2. In the P36 Panel install new relays, decals, ID tape, marker, and change wire bundles W176 and W184. 3. In the E8 EICAS rack, install two diodes and change wire bundles W2000 and W2006. 4. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies. 5. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts of the air distribution diffuser and install caps and an orifice assy. Group 1-3, Configuration 2: 1. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies. Change wire bundle W756. Install new relays, ID tape, marker, and change wire bundles W176 and W184 in the P36 panel. 2. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts of the air distribution diffuser and install caps and an orifice assy. EFFECTIVITY 767-300F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the changes given in this service bulletin be done within 6 years after the Revision 2 date of this service bulletin. 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 Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 11 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 12 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT

### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-21A0245 Original Issue: April 16, 2010 Revision 2: September 27, 2013 ATA System: 2158 2123 SUBJECT:AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic And Main Cargo Air Distribution System Change And Flight Deck Air Relief System Installation THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes 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 Boeing Service Bulletin 767-21-0235 before or concurrently with this service bulletin that have wire bundles W756 and W176 with a unique configuration. - 1
Airplanes that have not incorporated the original issue, or revision 1 of this service bulletin. 1 Airplanes that have incorporated the original issue, or revision 1 of this service bulletin. 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 13 of 121DESCRIPTION CONFIGURATION GROUP 767-300F airplanes that had the intent of Boeing Service Bulletin 767-21-0235 incorporated in production - 2 Airplanes that have not incorporated the original issue, or revision 1 of this service bulletin. 1 Airplanes that have incorporated the original issue, or revision 1 of this service bulletin. 2 767-300F airplanes that must incorporate Boeing Service Bulletin 767-21-0235 before or concurrently with this service bulletin that have wire bundles W756 and W176 with a unique configuration. - 3
Airplanes that have not incorporated the original issue, or revision 1 of this service bulletin. 1 Airplanes that have incorporated the original issue, or revision 1 of this service bulletin. 2

Airplane Models: 767-300F Group Variable Number3 VR251 3 VR256 1 VR257 - VR2601 VT501 1 VT511 - VT513 1 VT521 - VT523 1 VT531 - VT5332 VT541 - VT543 1 VW851 2. Spares Affected None. B. Concurrent Requirements Group 1, 3: The service bulletin listed below must be done on Group 1 and Group 3 airplanes before or at the same time as this service bulletin:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 14 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1, 3: Description Service Bulletin Company 3-Way Valve Control Logic Change. 767-21-0235, Original Issue, or Revision 1. BoeingGroup 2: None C. Reason This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring, or loss of color caused by moisture or condensation being collected inside the display units in the flight compartment can occur during operation in hot and humid environments. If this service bulletin is not done, there is an increased risk that the flight compartment display units could malfunction and become unserviceable because of moisture ingress. Loss of the primary attitude information on both primary display units could lead to flight crew confusion and difficulty in the transition to standby attitude indication. Flight compartment indication blanking can also cause unscheduled maintenance and airplane downtime. The inability of the flight crew to transition from primary attitude indication to standby attitude indication during a critical phase of flight could contribute to an unsafe flight condition. In addition, this service bulletin reduces airflow to the aft part of the main cargo compartment to make sure that cargo smoke detection system performance continues to agree with European Aviation Safety Agency (EASA) validation requirements. Operators of 767-300F airplanes have reported display unit malfunctions such as blanking, blurring, or loss of color caused by moisture or condensation being collected inside the display units during operation in hot and humid environments. The reports have included single display unit and multiple display unit malfunctions. Boeing is aware of several instances that are the likely causes of display unit malfunctions related to moisture or condensation ingress. The most frequent instance was display units being cold soaked by the air conditioned air delivered from the air conditioning packs by the Electrical/Electronic cooling system through the 3-way valve in hot and humid conditions. Another instance was an unserviceable air conditioning pack water separation system, which allowed water to be delivered to the flight compartment in the air conditioned air. The other instance was a malfunction of an air conditioning pack, which caused ice to be delivered to the flight compartment in the air conditioned air. As a result of these findings, the control logic of the 3-way valve is changed so that the valve will open after five minutes at an altitude above 10,000 feet, and close at an altitude below 10,000 feet. Limiting the 3-way valve to open after five minutes above 10,000 feet will decrease the amount of moisture or condensation that can collect in the display units because of the reduced water content in the atmosphere at higher altitudes. As a consequence of the 3-way valve closure below 10,000 feet, excessive airflow in the flight deck air distribution system causes increased flight deck noise which makes the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. To prevent this, a Flight Deck Air Relief System (FDARS) is installed to exhaust the excessive airflow into the Electrical Equipment (EE) bay when the 3-way valve is closed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 15 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTAccomplishment of this service bulletin changes the Environmental Control System (ECS) Flight Deck Cooling System Logic to use EE cooling rather than airplane pack cooling on the ground and up to 10,000 feet. This change reduces the amount of moisture or condensation that can collect in the flight compartment display units and results in reduced flight compartment display unit malfunction occurrences. In addition, accomplishment of this service bulletin installs a FDARS to exhaust excessive airflow into the right side tunnel of the EE bay when the 3-way valve is in the closed position. This is to reduce flight deck noise caused by excessive airflow in the flight deck air distribution system when the 3-way valve is closed and the flight deck equipment is being cooled by the EE cooling fans. This service bulletin also removes flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck cargo compartment and installs caps and an orifice assy. This change reduces airflow to the aft part of the main cargo compartment to make sure the cargo smoke detection system performance continues to agree with European Aviation Safety Agency (EASA) validation requirements. Boeing Service Related Problem (SRP) 767-SRP-21-179 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 21-09003 is related to this service bulletin. Revision 1 was sent 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. Revision 2 is sent to change the service bulletin release classification from "Standard" to "Alert" as it is related to a safety Service Related Problem (SRP). Revision 2 also makes sure cargo smoke detection performance in the main deck cargo compartment continues to agree with European Aviation Safety Agency (EASA) validation requirements. As a result of this requirement, instructions are added to remove flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck cargo compartment and install caps and an orifice assy. This change reduces the airflow to the aft section of the main deck cargo compartment. Revision 2 also installs a Flight Deck Air Relief System (FDARS) to reduce flight deck noise caused by excessive airflow into the flight deck when the 3-way valve is closed and the flight deck equipment is being cooled by the Electrical Equipment (EE) cooling fans. This change addresses the issues in Information Notice 767-21A0245 R01 IN01. As part of these changes, the EASA/Joint Aviation Authorities (JAA) approval statement, new kits, and new figures are added. Also, the background information, compliance data, and manpower data is updated. D. Description Group 1-3, Configuration 1: 1. In the Main Equipment Center (MEC) change wire bundles W596, W756, and W1702. 2. In the P36 Panel install new relays, decals, ID tape, marker, and change wire bundles W176 and W184. 3. In the E8 EICAS rack, install two diodes and change wire bundles W2000 and W2006. 4. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies. 5. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts of the air distribution diffuser and install caps and an orifice assy.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 16 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-3, Configuration 2: 1. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies. Change wire bundle W756. Install new relays, ID tape, marker, and change wire bundles W176 and W184 in the P36 panel. 2. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts of the air distribution diffuser and install caps and an orifice assy. Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. Revision 2 - More work is necessary on the airplanes changed in accordance with the original issue or Revision 1 of this service bulletin. Flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck cargo compartment must be removed and caps and an orifice installed. In addition, a Flight Deck Air Relief System (FDARS) must be installed. This work is identified as configuration 2 for Group 1, 2, and 3 airplanes. Revision 2 - Airplanes VR251 and VR256 are moved from airplane Group 1 to new airplane Group 3. The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance ZonesZone Model 119, 253, 254 767-300F E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the changes given in this service bulletin be done within 6 years after the Revision 2 date of this service bulletin. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. Included in the service bulletin approval is an FAA finding of compliance with the Fuel Tank Ignition Prevention rule (14 CFR section 25.981(a)(3) Amendment 102 or higher).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 17 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTG. Manpower The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace. • Time to schedule the work. • Time to inspect the work. • Time to cure the materials. • Time to make the parts. • Time to find the tools. Group 1-2, Configuration 1: Elapsed Hours Task Hours Number of Persons Task 1.00 1.00 1 Access 2.10 2.10 1 FIGURE 9 4.00 4.00 1 FIGURE 10 0.50 0.50 1 FIGURE 1 0.80 0.80 1 FIGURE 18 0.30 0.30 1 FIGURE 2 3.50 3.50 1 FIGURE 3 2.75 5.50 2 FIGURE 16 2.10 2.10 1 FIGURE 4 2.65 5.30 2 FIGURE 5 5.45 10.90 2 FIGURE 15 12.35 24.70 2 FIGURE 12 SHOWS ROUTE ONLY FIGURE 6 SHOWS ROUTE ONLY FIGURE 11 SHOWS ROUTE ONLY FIGURE 7 1.00 1.00 1 FIGURE 8 1.00 1.00 1 Close Access 2.25 2.25 1 Test 41.75 64.95 TOTAL FOR EACH AIRPLANE Group 1, Configuration 1: This estimate does not include the task hour data given in the service bulletin in Paragraph 1.B., Concurrent Requirements.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 18 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3, Configuration 1: Elapsed Hours Task Hours Number of Persons Task 1.00 1.00 1 Access 2.10 2.10 1 FIGURE 9 4.00 4.00 1 FIGURE 10 0.50 0.50 1 FIGURE 1 0.80 0.80 1 FIGURE 18 0.30 0.30 1 FIGURE 2 3.50 3.50 1 FIGURE 3 2.75 5.50 2 FIGURE 17 2.10 2.10 1 FIGURE 4 2.65 5.30 2 FIGURE 5 5.45 10.90 2 FIGURE 15 12.35 24.70 2 FIGURE 13 SHOWS ROUTE ONLY FIGURE 6 SHOWS ROUTE ONLY FIGURE 11 SHOWS ROUTE ONLY FIGURE 7 1.00 1.00 1 FIGURE 8 1.00 1.00 1 Close Access 2.25 2.25 1 Test 41.75 64.95 TOTAL FOR EACH AIRPLANE Group 3, Configuration 1: This estimate does not include the task hour data given in the service bulletin in Paragraph 1.B., Concurrent Requirements. Group 1-2, Configuration 2: Elapsed Hours Task Hours Number of Persons Task 1.00 1.00 1 Open Access 1.00 1.00 1 FIGURE 8 2.10 2.10 1 FIGURE 9 4.00 4.00 1 FIGURE 10 SHOWS ROUTE ONLY FIGURE 11 12.35 24.70 2 FIGURE 12 SHOWS ROUTE ONLY FIGURE 14

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 19 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 2: Elapsed Hours Task Hours Number of Persons Task 5.45 10.90 2 FIGURE 15 2.75 5.50 2 FIGURE 16 0.80 0.80 1 FIGURE 18 2.25 2.25 1 Test 1.00 1.00 1 Close Access 32.70 53.25 TOTAL FOR EACH AIRPLANE Group 3, Configuration 2: Elapsed Hours Task Hours Number of Persons Task 1.00 1.00 1 Open Access 1.00 1.00 1 FIGURE 8 2.10 2.10 1 FIGURE 9 4.00 4.00 1 FIGURE 10 SHOWS ROUTE ONLY FIGURE 11 12.35 24.70 2 FIGURE 13 SHOWS ROUTE ONLY FIGURE 14 5.45 10.90 2 FIGURE 15 2.75 5.50 2 FIGURE 17 0.80 0.80 1 FIGURE 18 2.25 2.25 1 Test 1.00 1.00 1 Close Access 32.70 53.25 TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Group 1-3, Configuration 1: Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +596.4 +4.9 767-300F

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 20 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-3, Configuration 2: Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +556.3 +4.6 767-300F 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 Letter 767-SL-00-014 d. Boeing Service Related Problem (SRP) 767-SRP-21-179 e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-50-02, 20-50-05, 20-50-10, 20-50-12 f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-10, 20-20-11, 20-30-16, 20-61-11, 20-71-11, 20-81-12, 20-81-19, 20-81-22, 20-90-11, 21-58-16, 21-61-11 g. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 21-22-02, 21-58-00, 21-58-16, 24-22-00, 25-00-00, 25-59-01, 32-09-02, 36-00-00 h. 767 Fleet Team Digest (FTD) 21-09003 i. 767 Wiring Diagram Manual (WDM) 21-58-16, 21-58-41, 31-41-13 j. 767-300F Structural Repair Manual (SRM) 51-40-02, 51-40-05 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: Title Drawing NumberDUCT INSTL - FLIGHT DECK, SECT 41 214T1011 DUCT INSTL - AIR DISTRIBUTION SYSTEM, SECTION 46 214T2006 SENSOR INSTL - FWD E/E COMPT 215T3001 DUCT INSTL - INSTRUMENT PANEL COOLING SUPPLY (VARIABLE) 2 CREW 3 ALT 217T2013

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 21 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTTitle Drawing NumberMODULAR WIRE BUNDLE INSTALLATION P36, MISCELLANEOUS RELAY PANEL, LEFT 288T2036 MODULAR WIRE BUNDLE INSTALLATION - E8 EICAS RACK 288T2280 WIRE BUNDLE INSTL - LOWER LOBE SIDEWALL LH, (STA 132.5 THRU 290) 288T4107 WIRE BUNDLE INSTL - LOWER LOBE SIDEWALL RH, STA 132.5 THRU 290 288T4108 WIRE BUNDLE INSTALLATION CREW AND MAIN DECK FLOOR BEAMS LH, (STA 139 THRU 344) 288T4115 WIRE BUNDLE INSTL - CREW AND MAIN DECK FLOOR BEAMS RH, (STA 139 THRU 344) 288T4116 WIRE BUNDLE INSTL - LOWER LOBE SIDEWALL LH, (STA 290 THRU 431) 288T4117 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. 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, 31-41 767 System Schematic Manual 21-58 767 Fault Isolation Manual 21-22, 21-23, 21-58, 31-41 767 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. M. Software Accomplishment Summary Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 22 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT2. 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. Group 1-2: 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 2date of this Service Bulletin (US Dollars) ROLT as of the Revision 2 date ofthis Service Bulletin (Calendar Days) QTY Date Name Kit Number

No Longer Available Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-1 (a)
$1.10 139 - - Supplemental Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-2 (b)
No Longer Available Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-3 (c)
$11,612.00 139 - - Supplemental Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-5 (d) (e)
$18,315.00 149 4 Jul 31/13 Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-10 (f) 2 Sep 03/13 1 Oct 02/13 (a) Top kit 015T1853-1 is replaced by top kit 015T1853-10 for airplanes that have not accomplished the original issue, or Revision 1 of this service bulletin. Top kit 015T1853-1, plus supplemental kits 015T1853- 2 and 015T1853-5 are equivalent to top kit 015T1853-10. (b) Supplemental kit 015T1853-2 is necessary for operators that have received top kit 015T1853-1, but have not accomplished the original issue, or Revision 1 of this service bulletin. (c) Top kit 015T1853-3 is replaced by top kit 015T1853-10 for airplanes that have not accomplished the original issue, or Revision 1 of this service bulletin. Top kit 015T1853-3, plus supplemental kit 015T1853- 5 are equivalent to top kit 015T1853-10.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 23 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2: 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 2date of this Service Bulletin (US Dollars) ROLT as of the Revision 2 date ofthis Service Bulletin (Calendar Days) QTY Date Name Kit Number

(d) Supplemental kit 015T1853-5 is necessary for operators that have received top kit 015T1853-1 or top kit 015T1853-3, but have not accomplished the original issue, or Revision 1 of this service bulletin. (e) Supplemental kit 015T1853-5 is necessary for operators that have accomplished the original issue, or Revision 1 of this service bulletin in order to incorporate the additional work necessary in Revision 2 of this service bulletin. (f) Top kit 015T1853-10 replaces top kits 015T1853-1 and 015T1853-3 for airplanes that have not accomplished the original issue, or Revision 1 of this service bulletin. Group 3: 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 2date of this Service Bulletin (US Dollars) ROLT as of the Revision 2 date ofthis Service Bulletin (Calendar Days) QTY Date Name Kit Number

No Longer Available Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-1 (a)
$1.10 139 - - Supplemental Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-2 (b)
No Longer Available Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-3 (c)
$11,612.00 139 - - Supplemental Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-6 (d) (e)
$18,315.00 149 1 Jul 31/13 Top Kit - 767 Freighters 3 - Way Valve Logic Change 015T1853-11 (f)
(a) Top kit 015T1853-1 is replaced by top kit 015T1853-11 for airplanes that have not accomplished the original issue, or Revision 1 of this service bulletin. Top kit 015T1853-1, plus supplemental kits 015T1853- 2 and 015T1853-6 are equivalent to top kit 015T1853-11.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 24 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3: 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 2date of this Service Bulletin (US Dollars) ROLT as of the Revision 2 date ofthis Service Bulletin (Calendar Days) QTY Date Name Kit Number

(b) Supplemental kit 015T1853-2 is necessary for operators that have received top kit 015T1853-1, but havenot accomplished the original issue, or Revision 1 of this service bulletin. Top kit 015T1853-1, plus supplemental kits 015T1853-2 and 015T1853-6 are equivalent to top kit 015T1853-11. (c) Top kit 015T1853-3 is replaced by top kit 015T1853-11 for airplanes that have not accomplished the original issue, or Revision 1 of this service bulletin. Top kit 015T1853-3, plus supplemental kit 015T1853- 6 are equivalent to top kit 015T1853-11. (d) Supplemental kit 015T1853-6 is necessary for operators that have received top kit 015T1853-1 or top kit 015T1853-3, but have not accomplished the original issue, or Revision 1 of this service bulletin. (e) Supplemental kit 015T1853-6 is necessary for operators that have accomplished the original issue, or Revision 1 of this service bulletin in order to incorporate the additional work necessary in Revision 2 of this service bulletin. (f) Top kit 015T1853-11 replaces top kits 015T1853-1 and 015T1853-3 for airplanes that have not accomplished the original issue, or Revision 1 of this service bulletin. 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/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE:One top kit, applicable supplemental kits, and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. Figure Kit 8 5 4 3 2 1 Top Kit 1 - - - - - 015T1853-5 1 - - - - - 015T1853-6 1 1 1 1 1 1 015T1853-10

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 25 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFigure Kit 8 5 4 3 2 1 Top Kit 1 1 1 1 1 1 015T1853-11 Figure Kit 15 13 12 11 10 9 Top Kit 1 - 1 1 1 1 015T1853-5 1 1 - 1 1 1 015T1853-6 1 - 1 1 1 1 015T1853-10 1 1 - 1 1 1 015T1853-11 Figure Kit18 17 16 Top Kit 1 - - 015T1853-5 1 - - 015T1853-6 1 - 1 015T1853-10 1 1 - 015T1853-11 Top Kit 015T1853-10 015T1853-6 015T1853-5 Wire Kit 1 1 1 289T1169-112 1 1 1 289T1169-113 1 1 1 289T1169-114 Top Kit 015T1853-11 Wire Kit 1 289T1169-112 1 289T1169-113 1 289T1169-114 Group 1-2, Configuration 2: KIT 015T1853-5

Notes Existing Part Number Name Figure
New Part Number 15 12 11 10 9 8 Qty (a) STIFFENER

. . . 1

. . 141T1226Y33

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 26 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 2: KIT 015T1853-5

Notes Existing Part Number Name Figure
New Part Number 15 12 11 10 9 8 Qty DUCT ASSY

. . . 1

. . 214T1120-313 duct assy

. . . 1

. . 214T1120-315 DUCT ASSY

. . . . 1

. 214T1120-3311 ORIFICE ASSY

. . . . . 1 214T3436-1139 ORIFICE ASSY

. . . 1

. . 214T3436-1187 (a) BRACKET

. . . 1

. . 214T6419Y40 (a) BRACKET

. . . 1

. . 217T2434U10 RETAINER CLIP ASSY . . 2

. . . 411A4902-7 VALVE - AIR SHUTOFF . . . 1

. . 67-2951-001 SCREEN ASSY

. . . 1

. . 69B42275-4 (b) LACING TAPE -RED - PRESSURIZED (TEMP 135 DEG) . 1

. . . . 829A9001-2

LACING TAPE -BLUE - PRESSURIZED (TEMP 135 DEG) 1

. . . . . 829A9001-5

HOSEDUCT, SLEEVE . . . 1

. . AS1506-14D30 CLAMP, MISCELLANEOUS . . . 2

. . BACC10DU500ABE SUPPORT, DUCT

. . . 2

. . BACC10ME20-1 BONDING JUMPER . . . 1

. . BACJ40A20-7 NUTPLATE

. . . 4

. . BACN10YD1G NUT

. . . 2

. . BACN10YR3CD RIVET, UNIVERSAL HD . . . 6

. . BACR15FT6KE5C RIVET, UNIVERSAL HD . . . 2

. . BACR15FT6KE6C

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 27 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 2: KIT 015T1853-5

Notes Existing Part Number Name Figure
New Part Number 15 12 11 10 9 8 Qty RIVET

. . . 1

. . BACR15FT6KE7C SCREW, CAP

. . . 6

. . BACS12GU3K7 RELAY SOCKET 1

. . . . . BACS16AG1 RELAY SOCKET 1

. . . . . BACS16AH1 STRAP

. . . . 2 10 BACS38K2 STRAP

. . . 1 3

. BACS38K6 CAP

. . . . . 6 BOE2221-0007 PACKING, PREFORMED . . . . 1

. MS29512-08 WASHER

. . . 4

. . NAS1149D0316J WASHER, PLAIN

. . . 6

. . NAS1149D0332H CLAMP, HOSE

. . . 2

. . NAS1922-0350-3 CLAMP, HOSE

. . . 3

. . NAS1922-0525-3 TERMINAL BLOCKRESISTOR ASSEMBLY MODULE 1

. . . . . YHLZR-17
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 767-SL-00-014 for more information. (b) Lacing tape P/N 829A9001-2 is also used in FIGURE 16. Group 1-2, Configuration 2: KIT 015T1853-5

Notes Existing Part Number Name Figure
New Part Number18QtyVINYL MARKER (12 3...30) VERTICAL 1 BAC27TEX4697

RELAY 1 BACR13CD2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 28 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 2: KIT 015T1853-5

Notes Existing Part Number Name Figure
New Part Number18QtyTAPE, ID 5 BACT19J4 TIME DELAY RELAY 1 TDH-1852-3002 Group 3, Configuration 2: KIT 015T1853-6

Notes Existing Part Number Name Figure
New Part Number 15 13 11 10 9 8 Qty (a) STIFFENER

. . . 1

. . 141T1226Y33 DUCT ASSY

. . . 1

. . 214T1120-313 duct assy

. . . 1

. . 214T1120-315 DUCT ASSY

. . . . 1

. 214T1120-3311 ORIFICE ASSY

. . . . . 1 214T3436-1139 ORIFICE ASSY

. . . 1

. . 214T3436-1187 (a) BRACKET

. . . 1

. . 214T6419Y40 (a) BRACKET

. . . 1

. . 217T2434U10 RETAINER CLIP ASSY . . 2

. . . 411A4902-7 VALVE - AIR SHUTOFF . . . 1

. . 67-2951-001 SCREEN ASSY

. . . 1

. . 69B42275-4 (b) LACING TAPE -RED - PRESSURIZED (TEMP 135 DEG) . 1

. . . . 829A9001-2

LACING TAPE -BLUE - PRESSURIZED (TEMP 135 DEG) 1

. . . . . 829A9001-5

HOSEDUCT, SLEEVE . . . 1

. . AS1506-14D30

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 29 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3, Configuration 2: KIT 015T1853-6

Notes Existing Part Number Name Figure
New Part Number 15 13 11 10 9 8 Qty CLAMP, MISCELLANEOUS . . . 2

. . BACC10DU500ABE SUPPORT, DUCT

. . . 2

. . BACC10ME20-1 BONDING JUMPER . . . 1

. . BACJ40A20-7 NUTPLATE

. . . 4

. . BACN10YD1G NUT

. . . 2

. . BACN10YR3CD RIVET, UNIVERSAL HD . . . 6

. . BACR15FT6KE5C RIVET, UNIVERSAL HD . . . 2

. . BACR15FT6KE6C RIVET

. . . 1

. . BACR15FT6KE7C SCREW, CAP

. . . 6

. . BACS12GU3K7 RELAY SOCKET 1

. . . . . BACS16AG1 RELAY SOCKET 1

. . . . . BACS16AH1 STRAP

. . . . 2 10 BACS38K2 STRAP

. . . 1 3

. BACS38K6 CAP

. . . . . 6 BOE2221-0007 PACKING, PREFORMED . . . . 1

. MS29512-08 WASHER

. . . 4

. . NAS1149D0316J WASHER, PLAIN

. . . 6

. . NAS1149D0332H CLAMP, HOSE

. . . 2

. . NAS1922-0350-3 CLAMP, HOSE

. . . 3

. . NAS1922-0525-3 TERMINAL BLOCKRESISTOR ASSEMBLY MODULE 1

. . . . . YHLZR-17
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 767-SL-00-014 for more information. (b) Lacing tape P/N 829A9001-2 is also used in FIGURE 17.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 30 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3, Configuration 2: KIT 015T1853-6

Notes Existing Part Number Name Figure
New Part Number18QtyVINYL MARKER (12 3...30) VERTICAL 1 BAC27TEX4697

RELAY 1 BACR13CD2 TAPE, ID 5 BACT19J4 TIME DELAY RELAY 1 TDH-1852-3002 Group 1-2, Configuration 1: KIT 015T1853-10

Notes Existing Part Number Name Figure
New Part Number 8 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 DECAL K10718

. . . . . 1 015T1853-10101 DECAL R1197

. . . . 1

. 015T1853-10102 DECAL R1196

. . . . 1

. 015T1853-10103 DECAL D31620

. . . . . 1 015T1853-10104 ORIFICE ASSY 1

. . . . . 214T3436-1139 ID - CONNECTOR

. . . 1

. . 826T5075-00401 CONTACT, PIN

. . 2

. . . BACC47CN1S CONTACT, SOCKET . 2

. 1

. . BACC47CP1S CONTACT

. 6

. . . . BACC47DE8A

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 31 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 1: KIT 015T1853-10

Notes Existing Part Number Name Figure
New Part Number 8 5 4 3 2 1 Qty CONTACT, SOCKET . . . 4

. . BACC47DJ1 RELAY SOCKET

. . . 1

. . BACS16W1A SPACER

. . . . 4

. BACS18AR6 STRAP 10

. . . . . BACS38K2 CAP 6

. . . . . BOE2221-0007 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
Group 1-2, Configuration 1: KIT 015T1853-10

Notes Existing Part Number Name Figure
New Part Number 16 15 12 11 10 9 Qty (a) STIFFENER

. . . . 1

. 141T1226Y33 DUCT ASSY

. . . . 1

. 214T1120-313 duct assy

. . . . 1

. 214T1120-315 DUCT ASSY

. . . . . 1 214T1120-3311 ORIFICE ASSY

. . . . 1

. 214T3436-1187 (a) BRACKET

. . . . 1

. 214T6419Y40 (a) BRACKET

. . . . 1

. 217T2434U10 RETAINER CLIP ASSY . . . 2

. . 411A4902-7 VALVE - AIR SHUTOFF . . . . 1

. 67-2951-001

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 32 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 1: KIT 015T1853-10

Notes Existing Part Number Name Figure
New Part Number 16 15 12 11 10 9 Qty SCREEN ASSY

. . . . 1

. 69B42275-4 (b) LACING TAPE -RED - PRESSURIZED (TEMP 135 DEG) . . 1

. . . 829A9001-2

LACING TAPE -BLUE - PRESSURIZED (TEMP 135 DEG) . 1

. . . . 829A9001-5

HOSEDUCT, SLEEVE . . . . 1

. AS1506-14D30 CLAMP, MISCELLANEOUS . . . . 2

. BACC10DU500ABE SUPPORT, DUCT

. . . . 2

. BACC10ME20-1 (c) CONTACT, PIN 6

. . . . . BACC47CN1S (d) CONTACT, SOCK- ET . . 14

. . . BACC47CP1S (e) CONTACT

. 3

. . . . BACC47DE8A (e) CONTACT, SOCK- ET . 4

. . . . BACC47DJ1 BONDING JUMPER . . . . 1

. BACJ40A20-7 NUTPLATE

. . . . 4

. BACN10YD1G NUT

. . . . 2

. BACN10YR3CD RIVET, UNIVERSAL HD . . . . 6

. BACR15FT6KE5C RIVET, UNIVERSAL HD . . . . 2

. BACR15FT6KE6C RIVET

. . . . 1

. BACR15FT6KE7C SCREW, CAP

. . . . 6

. BACS12GU3K7 RELAY SOCKET

. 1

. . . . BACS16AG1 RELAY SOCKET

. 1

. . . . BACS16AH1 STRAP

. . . . . 2 BACS38K2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 33 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 1: KIT 015T1853-10

Notes Existing Part Number Name Figure
New Part Number 16 15 12 11 10 9 Qty STRAP

. . . . 1 3 BACS38K6 (c) (e) CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 6 12

. . . . M39029/11-145

PACKING, PREFORMED . . . . . 1 MS29512-08 WASHER

. . . . 4

. NAS1149D0316J WASHER, PLAIN

. . . . 6

. NAS1149D0332H CLAMP, HOSE

. . . . 2

. NAS1922-0350-3 CLAMP, HOSE

. . . . 3

. NAS1922-0525-3 TERMINAL BLOCKRESISTOR ASSEMBLY MODULE . 1

. . . . YHLZR-17
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 767-SL-00-014 for more information. (b) Lacing tape P/N 829A9001-2 is also used in FIGURE 16. (c) For operator convenience, this part is provided in both this kit and wire kit 289T1169-114. There are more parts supplied than are necessary. (d) For operator convenience, this part is provided in both this kit and wire kit 289T1169-112. There are more parts supplied than are necessary. (e) For operator convenience, this part is provided in both this kit and wire kit 289T1169-113. There are more parts supplied than are necessary.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 34 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 1-2, Configuration 1: KIT 015T1853-10

Notes Existing Part Number Name Figure
New Part Number18QtyVINYL MARKER (12 3...30) VERTICAL 1 BAC27TEX4697

RELAY 1 BACR13CD2 TAPE, ID 5 BACT19J4 TIME DELAY RELAY 1 TDH-1852-3002 Group 3, Configuration 1: KIT 015T1853-11

Notes Existing Part Number Name Figure
New Part Number 8 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 DECAL K10718

. . . . . 1 015T1853-10101 DECAL R1197

. . . . 1

. 015T1853-10102 DECAL R1196

. . . . 1

. 015T1853-10103 DECAL D31620

. . . . . 1 015T1853-10104 ORIFICE ASSY 1

. . . . . 214T3436-1139 ID - CONNECTOR

. . . 1

. . 826T5075-00401 CONTACT, PIN

. . 2

. . . BACC47CN1S CONTACT, SOCKET . 2

. 1

. . BACC47CP1S CONTACT

. 6

. . . . BACC47DE8A

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 35 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3, Configuration 1: KIT 015T1853-11

Notes Existing Part Number Name Figure
New Part Number 8 5 4 3 2 1 Qty CONTACT, SOCKET . . . 4

. . BACC47DJ1 RELAY SOCKET

. . . 1

. . BACS16W1A SPACER

. . . . 4

. BACS18AR6 STRAP 10

. . . . . BACS38K2 CAP 6

. . . . . BOE2221-0007 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
Group 3, Configuration 1: KIT 015T1853-11

Notes Existing Part Number Name Figure
New Part Number 17 15 13 11 10 9 Qty (a) STIFFENER

. . . . 1

. 141T1226Y33 DUCT ASSY

. . . . 1

. 214T1120-313 duct assy

. . . . 1

. 214T1120-315 DUCT ASSY

. . . . . 1 214T1120-3311 ORIFICE ASSY

. . . . 1

. 214T3436-1187 (a) BRACKET

. . . . 1

. 214T6419Y40 (a) BRACKET

. . . . 1

. 217T2434U10 RETAINER CLIP ASSY . . . 2

. . 411A4902-7 VALVE - AIR SHUTOFF . . . . 1

. 67-2951-001

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 36 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3, Configuration 1: KIT 015T1853-11

Notes Existing Part Number Name Figure
New Part Number 17 15 13 11 10 9 Qty SCREEN ASSY

. . . . 1

. 69B42275-4 (b) LACING TAPE -RED - PRESSURIZED (TEMP 135 DEG) . . 1

. . . 829A9001-2

LACING TAPE -BLUE - PRESSURIZED (TEMP 135 DEG) . 1

. . . . 829A9001-5

HOSEDUCT, SLEEVE . . . . 1

. AS1506-14D30 CLAMP, MISCELLANEOUS . . . . 2

. BACC10DU500ABE SUPPORT, DUCT

. . . . 2

. BACC10ME20-1 (c) CONTACT, PIN 6

. . . . . BACC47CN1S (d) CONTACT, SOCK- ET . . 14

. . . BACC47CP1S (e) CONTACT

. 3

. . . . BACC47DE8A (e) CONTACT, SOCK- ET . 4

. . . . BACC47DJ1 BONDING JUMPER . . . . 1

. BACJ40A20-7 NUTPLATE

. . . . 4

. BACN10YD1G NUT

. . . . 2

. BACN10YR3CD RIVET, UNIVERSAL HD . . . . 6

. BACR15FT6KE5C RIVET, UNIVERSAL HD . . . . 2

. BACR15FT6KE6C RIVET

. . . . 1

. BACR15FT6KE7C SCREW, CAP

. . . . 6

. BACS12GU3K7 RELAY SOCKET

. 1

. . . . BACS16AG1 RELAY SOCKET

. 1

. . . . BACS16AH1 STRAP

. . . . . 2 BACS38K2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 37 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3, Configuration 1: KIT 015T1853-11

Notes Existing Part Number Name Figure
New Part Number 17 15 13 11 10 9 Qty STRAP

. . . . 1 3 BACS38K6 (c) (e) CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 6 12

. . . . M39029/11-145

PACKING, PREFORMED . . . . . 1 MS29512-08 WASHER

. . . . 4

. NAS1149D0316J WASHER, PLAIN

. . . . 6

. NAS1149D0332H CLAMP, HOSE

. . . . 2

. NAS1922-0350-3 CLAMP, HOSE

. . . . 3

. NAS1922-0525-3 TERMINAL BLOCKRESISTOR ASSEMBLY MODULE . 1

. . . . YHLZR-17
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 767-SL-00-014 for more information. (b) Lacing tape P/N 829A9001-2 is also used in FIGURE 17. (c) For operator convenience, this part is provided in both this kit and wire kit 289T1169-114. There are more parts supplied than are necessary. (d) For operator convenience, this part is provided in both this kit and wire kit 289T1169-112. There are more parts supplied than are necessary. (e) For operator convenience, this part is provided in both this kit and wire kit 289T1169-113. There are more parts supplied than are necessary.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 38 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTGroup 3, Configuration 1: KIT 015T1853-11

Notes Existing Part Number Name Figure
New Part Number18QtyVINYL MARKER (12 3...30) VERTICAL 1 BAC27TEX4697

RELAY 1 BACR13CD2 TAPE, ID 5 BACT19J4 TIME DELAY RELAY 1 TDH-1852-3002

KIT 289T1169-112 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-112W ID - CONNECTOR 1 289T1169-10301 CONNECTOR, ELECTRICAL, PLUG, STRAIGHT,BAYONET COUPLING 1 BACC45FT12C12S6

CONTACT, SOCKET 14 BACC47CP1S CONTACT, PIN 5 BACC47DE7A KIT 289T1169-113 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-113W ID - CONNECTOR 1 289T1169-10401 ID - CONNECTOR 1 289T1169-10402 ID - DIODE 1 289T1169-10403 CONTACT, PIN 3 BACC47DE7A CONTACT 3 BACC47DE8A CONTACT, SOCKET 4 BACC47DJ1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 39 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTKIT 289T1169-113 Notes Name Qty New Part Number CONTACT, SOCKET 12 BACC47ER1 TERMINAL BLOCK 1 BACM15C3F RELAY SOCKET 1 BACS16AG1 RELAY SOCKET 1 BACS16AH1 CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 12 M39029/11-145

TERMINAL BLOCKRESISTOR ASSEMBLY MODULE 1 YHLZR-17

KIT 289T1169-114 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-114W CONTACT, PIN 6 BACC47CN1S CONTACT, SOCKET 5 BACC47ER1 CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 6 M39029/11-145

Not Available For Procurement KIT 015T1853-1 Notes Name Qty New Part Number 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 DECAL K10718 1 015T1853-10101

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 40 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTNot Available For Procurement KIT 015T1853-1 Notes Name Qty New Part Number DECAL R1197 1 015T1853-10102 DECAL R1196 1 015T1853-10103 DECAL D31620 1 015T1853-10104 ID - CONNECTOR 1 826T5075-00401 CONTACT, SOCKET 3 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 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
Group 1-3, Configuration 1: KIT 015T1853-2 Notes Name Qty New Part Number CONTACT, PIN 2 BACC47CN1S CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 1 M39029/11-145

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 41 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTNot Available For Procurement KIT 015T1853-3 Notes Name Qty New Part Number 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 DECAL K10718 1 015T1853-10101 DECAL R1197 1 015T1853-10102 DECAL R1196 1 015T1853-10103 DECAL D31620 1 015T1853-10104 ID - CONNECTOR 1 826T5075-00401 CONTACT, PIN 2 BACC47CN1S CONTACT, SOCKET 3 BACC47CP1S CONTACT 6 BACC47DE8A CONTACT, SOCKET 4 BACC47DJ1 RELAY SOCKET 1 BACS16W1A SPACER 4 BACS18AR6 CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 2 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 The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 42 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTNotes Name QTY Part Number / Specification (a) ADHESIVE
- BMS5-30, TYPE 1 (a) TAPE
- BMS5-157, TYPE I, CLASS 1, GRADE A LOCKWIRE
- MS20995NC32 (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. 3. Parts Modified and Reidentified None 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 43 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 44 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT

BLANK PAGE3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION:KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE:1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 7. 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. 8. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 9. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 45 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT10. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 11. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-' (dash) part number. Boeing Drawing 005W0900 contains more data. 12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 13. If this service bulletin is accomplished concurrently with service bulletin 767-21-0235, the functional test, the Flight Deck Air Relief System (FDARS) installation, and the flex duct change listed in this service bulletin are all that is required. B. WORK INSTRUCTIONS Group 1-3, Configuration 1: 3-Way Valve Control Logic Change, Flight Deck Air Relief System (FDARS), and Main Deck Cargo Compartment Flex Duct Change 1. Get access to the Main Equipment Center (MEC). Refer to 767 AMM 06-41-00 for access location. 2. In the MEC, open the circuit breaker shown in the table below and attach a "DO-NOT-CLOSE" tag: Number Name Location Panel C00679 CB-EQUIP COOL OVERRIDE C019 P11-4 3. Depressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure. 4. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in the 'OFF' position. 5. Remove electrical power from the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 6. In the Main Equipment Center (MEC), replace the Flight Deck Air Relief System (FDARS) duct assembly in accordance with FIGURE 9. 7. In the MEC, install a FDARS air shutoff valve and new duct assemblies in accordance with FIGURE 10. 8. Change relays, decals, ID tape, and marker in the P36 Panel in accordance with FIGURE 1 and FIGURE 18. 9. Add two diodes in the E8 EICAS rack in accordance with FIGURE 2. 10. Change wire bundle W176:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 46 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTa.Group 1-2, Configuration 1: in accordance with FIGURE 3 and FIGURE 16. b.Group 3, Configuration 1: in accordance with FIGURE 3 and FIGURE 17. 11. Change wire bundle W1702 and wire bundle W596 in accordance with FIGURE 4. 12. Change wire bundles W2000 and W2006 in accordance with FIGURE 5. 13. Change wire bundle W184 in accordance with FIGURE 15. 14. Change wire bundle W756:
a.Group 1-2, Configuration 1: In accordance with FIGURE 12. b.Group 3, Configuration 1: In accordance with FIGURE 13. 15. Route wire bundles W176, W1702, and W184 in accordance with FIGURE 6. 16. Route wire bundle W756 in accordance with FIGURE 11. 17. Route wire bundles W2000 and W2006 in accordance with FIGURE 7. 18. In the main deck cargo compartment do the steps that follow to change the flex duct: a. Remove ceiling panels to get access to the flex ducts that connect the center and aft parts of the air distribution diffuser at STA 1502. Refer to 767 AMM 25-59-01 as an accepted procedure. b. Remove flex ducts and install caps and an orifice assy in accordance with FIGURE 8. 19. Supply electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 20. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in the 'ON' position. 21. Pressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure. 22. In the main deck cargo compartment, install ceiling panels. Refer to 767 AMM 25-59-01 as an accepted procedure. 23. In the MEC, remove the "DO-NOT-CLOSE" tag and close the circuit breaker shown in the table below: Number Name Location Panel C00679 CB-EQUIP COOL OVERRIDE C019 P11-4 24. Do a Manifold Interconnect Valve Reconfiguration Test. Refer to 767 AMM 21-58-00 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 47 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT25. Do the following functional test: Functional Test of Manifold Interconnect Valve Control Logic Modification 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 to GROUND Mode. c. Make sure these circuit breakers on the P11 panel are closed: NOMENCLATURE LOC CB NO. LEFT PACK CONT A13 C00653 RIGHT PACK CONT A26 C00704 LDG GR POS AIR/GND SYS 1 C30 C01175 L EICAS CMPTR J2 C4078 R EICAS CMPTR J29 C4079 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. Make sure 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. Make sure 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. Install 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. Make sure that the 3-way valve is in the condition specified in the table below:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 48 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTEquip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) o. Disconnect Connector (D2770) from Left Flow Control Valve (V16). NOTE:This simulates the Left Pack is ON. p. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) q. Disconnect Connector (D1276) from Right Flow Control Valve (V17). NOTE:This simulates the Right Pack is ON. r. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) s. Make sure that there is 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. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) 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. y. Make sure 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 do the four (4) sub-steps which follow:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 49 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT(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. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) 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. Make sure 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. Make sure that the recorded value in the previous step is between the minimum and maximum allowable value. af. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve OPEN (C-B) 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 let the equipment to cool down.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 50 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTai. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) aj. Make sure 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. Make sure 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. Install relay K10718 in the P36 panel. ap. Set the equipment cooling rotary switch on P5 overhead panel to OVRD aq. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve OPEN (C-B) 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. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve OPEN (C-B)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 51 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTCAUTION: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. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) av. Connect Pin 2 of Connector (D20950) on the 10K FT Altitude Pressure Switch (S921) if it was disconnected in a previous step. aw. Connect Connector (D20950) to the 10K FT Altitude Pressure Switch (S921) on the E8 EICAS Rack. ax. Make sure that the 3-way valve is in the condition specified in the table below: Equip No Nomenclature Condition V90 Manifold Interconnect Valve CLOSED (A-B) ay. Make sure 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. Make sure 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. Install relay K10718 in the P36 panel.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 52 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTbf. Connect Connector (D2770) to the Left Control Valve (V16). bg. Connect Connector (D1276) to Right Flow Control Valve (V17). bh. Disconnect jumper from Pins 1 and 2 of Connector (D20366). bi. Connect 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 do the sub-steps which follow: (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. Put the airplane back to the configuration before the test. 26. Put the airplane back in a serviceable condition.

Group 1-3, Configuration 2: More Work - Flight Deck Air Relief System (FDARS) and Main Deck Cargo Compartment Flex Duct Change 1. Depressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure. 2. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in the 'OFF' position. 3. Remove electrical power from the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 4. In the main deck cargo compartment do the steps that follow to change the flex duct: a. Remove ceiling panels to get access to the flex ducts that connect the center and aft parts of the air distribution diffuser at STA 1502. Refer to 767 AMM 25-59-01 as an accepted procedure. b. Remove flex ducts and install caps and an orifice assy in accordance with FIGURE 8. 5. In the Main Equipment Center (MEC), do the steps that follow to change the Flight Deck Air Relief System (FDARS): a. Replace FDARS duct assembly in accordance with FIGURE 9. b. Install a FDARS air shutoff valve and new duct assemblies in accordance with FIGURE 10.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 53 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTc. Change wire bundle W756 between the air shutoff valve and the P36 panel: (1)Group 1-2, Configuration 2: in accordance with FIGURE 11 and FIGURE 12. (2)Group 3, Configuration 2: in accordance with FIGURE 11 and FIGURE 13. d. Change wire bundle W184 in the P36 panel in accordance with FIGURE 14 and FIGURE 15 e. Change wire bundle W176 in the P36 panel: (1)Group 1-2, Configuration 2: in accordance with FIGURE 14 and FIGURE 16. (2)Group 3, Configuration 2: in accordance with FIGURE 14 and FIGURE 17. f. Install new relays, marker, and ID tape on the P36 panel in accordance with FIGURE 18. 6. Supply electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 7. Pressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure. 8. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in the 'ON' position. 9. In the main deck cargo compartment, install ceiling panels. Refer to 767 AMM 25-59-01 as an accepted procedure. 10. Do a Manifold Interconnect Valve Reconfiguration Test. Refer to 767 AMM 21-58-00 as an accepted procedure. 11. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2: September 27, 2013 54 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 1.

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 55 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 56 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 1.

FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 57 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 58 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 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.
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 W176 CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 59 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore 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 W176 CHANGE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 60 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 1.

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 accepted 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 61 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 1.

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

FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 62 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Flag Note 1 015T1853-106W WIRE 6 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 63 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 1.

FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 1 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 64 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 2 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 65 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 3 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 66 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 4 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 67 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 5 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 68 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 6 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 69 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 7 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 70 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING (SHEET 8 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 71 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 1.

FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 72 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 73 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS CHANGE (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 74 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS CHANGE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 75 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe 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 214T2550-11 GAP COVER Remove / Keep 1 6 BACS38K2 STRAP Remove 2 3 AS4804-12-0040A FLEX DUCT Remove 2 BACS38K2 STRAP Remove 3 1 AS4804-12-0040A FLEX DUCT Remove / Keep to the mating surfaces of the orifice assy and the duct assembly. Refer to SOPM 20-50-12 asan accepted procedure. (a) - BMS5-30, TYPE 1 ADHESIVE Apply 4

make sure the orifice assy part numberand diameter identification tags are outside of the duct assembly. Refer to 767 AMM 21-22-02 asan accepted procedure. 1 214T3436-1139 ORIFICE ASSY Install (New)

1 AS4804-12-0040A FLEX DUCT Install (Kept) 5 (b) 2 BACS38K2 STRAP Install (New) 6 BOE2221-0007 CAP Install (New) 6 (b) 6 BACS38K2 STRAP Install (New) 1 214T2550-11 GAP COVER Install (Kept) 7 (a) Do not apply adhesive to the orifice assy part number or diameter identification tags. (b) To apply the correct tension to the strap, use panduit tool GS4H or equivalent. Set the selector knob to HEAVY EK position and set the tension indicator to 5 for BACS38K2 straps. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 2 BACS38K2 STRAP

FIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS CHANGE (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 76 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 77 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 78 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 79 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe 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 from the temperature sensor. (a) 1 - ELECTRICAL CON- NECTOR Disconnect 1 (a)
- - LOCKWIRE Remove 2 (a) 1 3000-46-41 TEMPERATURE SEN- SOR Remove / Keep (a) 1 MS29512-08 PACKING, PRE- FORMED Remove

FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 80 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Task Step 3 BACS12GU( ) SCREW Remove / Keep 3 do not remove the marker from the bracket. 1 217T1438-3 BRACKET Remove / Keep

2 BACS38K2 STRAP Remove 4 1 AS1506-06D32 SLEEVE Remove / Keep 2 BACS38K6 STRAP Remove 5 1 AS1506-15D23 SLEEVE Remove / Keep 1 BACS38K6 STRAP Remove 6 1 NH102689-0450 CLAMP Remove / Keep 7 1 214T1120-( ) DUCT ASSY Remove 1 214T1120-3311 DUCT ASSY Install (New) 8 1 NH102689-0450 CLAMP Install (Kept) to 40 in-lbs. 1 NH102689-0450 CLAMP Torque (b) 1 BACS38K6 STRAP Install (New) 9 1 AS1506-15D23 SLEEVE Install (Kept) 10 (b) 2 BACS38K6 STRAP Install (New) 1 AS1506-06D32 SLEEVE Install (Kept) 11 (c) 2 BACS38K2 STRAP Install (New) 1 217T1438-3 BRACKET Install (Kept) 12 3 BACS12GU( ) SCREW Install (Kept) to 10-15 in-lbs. 3 BACS12GU( ) SCREW Torque (a) 1 MS29512-08 PACKING, PRE- FORMED Install (New) 13 (a) 1 3000-46-41 TEMPERATURE SEN- SOR Install (Kept) Refer to SOPM 20-50-02 as an accepted procedure. - MS20995NC32 LOCKWIRE Install (New)
(a) 1 - ELECTRICAL CON- NECTOR Connect 14 (a) Refer to 767 AMM 21-58-16 as an accepted procedure. (b) To apply the correct tension to the strap, use panduit installation tool GS4H or equivalent. Set panduit installation tool to the 'HVY' position and the tension indicator to '8'.

FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 81 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Task Step (c) To apply the correct tension to the strap, use panduit installation tool GS4H or equivalent. Set panduit installation tool to the 'HVY' position and the tension indicator to '5'.

FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 82 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 1 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 83 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 2 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 84 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 3 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 85 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 4 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 86 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 5 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 87 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe 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 to get access to the frames. - - INSULATION Remove / Keep 1 1 - STRAP Remove 2 to get access to install brackets. Make sure the orifice is not removed. 1 - DUCT ASSY Disconnect

locate as shown on the aft side of the frame. 1 214T6419Y40 BRACKET Put / Hold 3
use pilot hole in the bracket to drill the first hole and locate the remaining holes as shown. Refer to 767-300F SRM 51-40-05 as an accepted procedure. 3 - HOLE Drill

1 214T6419Y40 BRACKET Install (New) 4 see fastener table below. (a) 3 - FASTENER Install (New) from the frame andthe chord at the location shown. 1 - RIVET Remove 5

locate as shown on the fwd side of the frame. 1 141T1226Y33 STIFFENER Put / Hold 6
align pilot hole with the existing fastener hole. Refer to 767- 300F SRM 51-40-05as an accepted procedure. 1 - HOLE Drill

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 6 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 88 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Task Step locate as shown on the aft side of the frame. 1 217T2434U10 BRACKET Put / Hold 7
use pilot hole in the stiffener to drill the first hole and locate the remaining holes as shown. Refer to 767-300F SRM 51-40-05 as an accepted procedure. 5 - HOLE Drill

1 141T1226Y33 STIFFENER Install (New) 8 1 217T2434U10 BRACKET Install (New) see fastener table below. (a) 6 - FASTENER Install (New) on the new brackets. 2 BACC10ME20-1 SUPPORT, DUCT Install (New) 9 4 BACN10YD1G NUTPLATE Install (New) 4 NAS1149D0316J WASHER Install (New) 4 BACS12GU3K7 SCREW, CAP Install (New) to the mating surfaces of the orifice assy and the duct assy. Refer to SOPM 20-50-12,Type 48 as an accepted procedure. (b) - BMS5-30, TYPE 1 ADHESIVE Apply 10

to duct assy P/N 214T1120-313. Make sure the orifice assy part numberand diameter identification tags are outside of the duct assy. Refer to 767 AMM 21-22-02 asan accepted procedure. 1 214T3436-1187 ORIFICE ASSY Install (New)

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 7 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 89 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Task Step connect to duct assembly P/N 214T1120-3311 as shown. 1 214T1120-313 DUCT ASSY Install (New) 11

1 AS1506-14D30 HOSEDUCT, SLEEVE Install (New) 2 NAS1922-0350-3 CLAMP, HOSE Install (New) to attach duct assembly to frame. 1 NAS1922-0525-3 CLAMP, HOSE Install (New) 12 between duct assemblies P/N 214T1120- 313 and P/N 214T1120-315 as shown. 1 67-2951-001 VALVE - AIR SHUT- OFF Install (New) 13

align the alignmentmark on the duct assy to the top of the duct support to make sure that the airflow is exhausted downward as shown. 1 214T1120-315 duct assy Install (New)

torque to 62-67 inch pounds. 2 BACC10DU500ABE CLAMP, MISCELLA- NEOUS Install (New) to attach duct assembly to frame. 1 NAS1922-0525-3 CLAMP, HOSE Install (New) 14 connect to duct assembly P/N 214T1120-315 as shown. 1 69B42275-4 SCREEN ASSY Install (New) 15

1 NAS1922-0525-3 CLAMP, HOSE Install (New) 0.218 - 0.229 inch diameter in thebracket at the location shown. Refer to 767-300F SRM 51-40-05 as an accepted procedure. 1 - HOLE Drill 16

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 8 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 90 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Task Step where the bonding jumper terminal lugs are to be located. Refer to SOPM 20- 30-03, abrasive cleaning method, asan accepted procedure. - - STRUCTURE Clean 17

Refer to SOPM 20- 30-03, solvent cleaning method, asan accepted procedure. 2 - TERMINAL LUG Clean 18

parts stack-up as shown. (c) 2 BACS12GU3K7 SCREW, CAP Install (New) 19 parts stack-up as shown. (c) 6 NAS1149D0332H WASHER, PLAIN Install (New) parts stack-up as shown. (c) 1 BACJ40A20-7 BONDING JUMPER Install (New) parts stack-up as shown. (c) 2 BACN10YR3CD NUT Install (New) between the terminallug and the structure. Make sure the bonding resistance is not more than 1.0 milliohms. If the bond resistance ismore than 1.0 milliohms, remove the bonding jumper and do steps 17 thru 20 again. (c) - - BOND RESISTANCE Measure 20

1 - DUCT ASSY Connect 21 (d) 1 BACS38K6 STRAP Install (New)

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 9 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 91 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Task Step that was removed to get access to the frames for bracket installation. Adjust insulation so that it fits around new brackets. - - INSULATION Install (Kept) 22

use tape to repair the insulation and to seal the insulation to the brackets. Refer to 767 AMM 25-00- 00 as an accepted procedure. - BMS5-157, TYPE I, CLASS 1, GRADE A TAPE Apply

(a) Refer to 767-300F SRM 51-40-02 as an accepted procedure. (b) Do not apply adhesive to the orifice assy part number or diameter identification tags. (c) Refer to SWPM 20-20-10 as an accepted procedure. (d) To apply the correct tension to the strap, use panduit installation tool GS4H or equivalent. Set panduit installation tool to the 'HVY' position and the tension indicator to '8'. The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code

- 3 BACR15FT6KE5C RIVET, UNIVERSAL HD A

- 2 BACR15FT6KE5C RIVET, UNIVERSAL HD B

- 2 BACR15FT6KE6C RIVET, UNIVERSAL HD C

- 1 BACR15FT6KE5C RIVET, UNIVERSAL HD D

- 1 BACR15FT6KE7C RIVET E

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES INSTALLATION (SHEET 10 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 92 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 1 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 93 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 2 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 94 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 3 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 95 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 4 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 96 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 5 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 97 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 6 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 98 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 7 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 99 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe 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 locate and install approximately as shown between orover insulation blanket. 2 411A4902-7 RETAINER CLIP ASSY Install (New) 1

FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION (SHEET 8 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 100 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-2.

REFERENCE: 767 WDM 21-58-41 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 Use lacing tape to tie wires. Refer to SWPM 20-10-11 as an accepted procedure. Do not use plastic ties. 1 829A9001-2 LACING TAPE - RED - PRESSURIZED (TEMP 135 DEG) 1

Refer to cut and code table. 1 289T1169-112W WIRE - RAW MATERIAL Refer to SWPM 20-20-11 as an accepted procedure. 4 BACC47DE7A CONTACT, PIN 2

FIGURE 12: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 101 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Flag Note Refer to SWPM 20-61-11 as an accepted procedure. (a) 12 BACC47CP1S CONTACT, SOCKET 3 Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT12C12S6 CONNECTOR, ELECTRI- CAL, PLUG, STRAIGHT, BAYONET COUPLING 4
Install equipment ID within 6 inches of equipment. Refer to SWPM20-10-11 as an accepted procedure. 1 289T1169-10301 ID - CONNECTOR

(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 2 BACC47CP1S CONTACT, SOCKET 1 BACC47DE7A CONTACT, PIN WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-112W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 132 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 133 W756 BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 135 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 136 W756 BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 137 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 138 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 139 W756 BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 140 W756

FIGURE 12: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 102 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 3.

REFERENCE: 767 WDM 21-58-41 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 Use lacing tape to tie wires. Refer to SWPM 20-10-11 as an accepted procedure. Do not use plastic ties. 1 829A9001-2 LACING TAPE - RED - PRESSURIZED (TEMP 135 DEG) 1

Refer to cut and code table. 1 289T1169-112W WIRE - RAW MATERIAL Refer to SWPM 20-20-11 as an accepted procedure. 4 BACC47DE7A CONTACT, PIN 2

FIGURE 13: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 103 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Flag Note Refer to SWPM 20-61-11 as an accepted procedure. (a) 12 BACC47CP1S CONTACT, SOCKET 3 Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT12C12S6 CONNECTOR, ELECTRI- CAL, PLUG, STRAIGHT, BAYONET COUPLING 4
Install equipment ID within 6 inches of equipment. Refer to SWPM20-10-11 as an accepted procedure. 1 289T1169-10301 ID - CONNECTOR

(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 2 BACC47CP1S CONTACT, SOCKET 1 BACC47DE7A CONTACT, PIN WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-112W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 132 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 133 W756 BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 135 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 136 W756 BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 137 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 138 W756 BMS13-48 TYPE 11 CLASS 1, AWG 24 436 PK 24 139 W756 BMS13-48 TYPE 10 CLASS 1, AWG 20 207 PA 20 140 W756

FIGURE 13: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 104 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-3, Configuration 2.

FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 105 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 106 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 107 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 108 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 109 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTREFERENCE: 767 WDM 21-58-41, SWPM 21-58-16

FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 110 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More Data Qty Identification Name Flag Note Use lacing tape to tie wires. Refer to SWPM 20-10-11 as an accepted procedure. Do not use plastic ties. 1 829A9001-5 LACING TAPE - BLUE - PRESSURIZED (TEMP 135 DEG) 1

Refer to cut and code table. 1 289T1169-113W WIRE - RAW MATERIAL Refer to SWPM 20-81-19 as an accepted procedure. 9 BACC47ER1 CONTACT, SOCKET 2 Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE7A CONTACT, PIN 3 Refer to SWPM 20-90-11 as an accepted procedure. 9 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 4

Refer to SWPM 20-81-22 as an accepted procedure. 1 BACS16AG1 RELAY SOCKET 5 Install equipment ID within 6 inches of equipment. Refer to SWPM20-10-11 as an accepted procedure. 1 289T1169-10401 ID - CONNECTOR

Refer to SWPM 20-81-22 as an accepted procedure. 1 BACS16AH1 RELAY SOCKET 6 Install equipment ID within 6 inches of equipment. Refer to SWPM20-10-11 as an accepted procedure. 1 289T1169-10402 ID - CONNECTOR

Refer to SWPM 20-81-12 as an accepted procedure. (a) 3 BACC47DJ1 CONTACT, SOCKET 7 Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE8A CONTACT 8 Refer to SWPM 20-90-11 as an accepted procedure. 1 YHLZR-17 TERMINAL BLOCK RESIS- TOR ASSEMBLY MODULE 9 (b) 1 289T1169-10403 ID - DIODE Install Z block at position 21-22 of TB216. Refer to SWPM 20-90-11 as an accepted procedure. 1 BACM15C3F TERMINAL BLOCK 10
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 111 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Flag Note (b) Install ID tape on top of module so that the first character of ID tape is nearest the 'B' side identification mark on the module. If necessary, trim the ID tape so that it does not overlap the sides of the module and does not cover the 'A' and 'B' side. Refer to SWPM 20-10-11 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACC47DE7A CONTACT, PIN 1 BACC47DE8A CONTACT 1 BACC47DJ1 CONTACT, SOCKET 3 BACC47ER1 CONTACT, SOCKET 3 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11 WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-113W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS13-48 TYPE 11 CLASS 1, AWG 24 16 PK 24 597 W184 BMS13-48 TYPE 10 CLASS 1, AWG 20 93 PA 20 734 W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 80 PK 24 737 W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 40 PK 24 735 W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 45 PK 24 736 W184 BMS13-48 TYPE 10 CLASS 1, AWG 20 93 PA 20 731 W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 45 PK 24 732 W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 45 PK 24 733 W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 50 PK 24 18N W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 50 PK 24 18M W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 55 PK 24 18L W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 30 PK 24 55P W184 BMS13-48 TYPE 11 CLASS 1, AWG 24 22 PK 24 55R W184

FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 112 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 1-2.

REFERENCE: 767 WDM 21-58-41, 767 WDM 21-58-16

FIGURE 16: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 113 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More Data Qty Identification Name Flag Note Use lacing tape to tie wires. Refer to SWPM 20-10-11 as an accepted procedure. Do not use plastic ties. - 829A9001-2 LACING TAPE - RED - PRESSURIZED (TEMP 135 DEG) 1

Refer to cut and code table. 1 289T1169-114W WIRE - RAW MATERIAL Refer to SWPM 20-81-19 as an accepted procedure. (a) 4 BACC47ER1 CONTACT, SOCKET 2 Refer to SWPM 21-61-11 as an accepted procedure. (a) 5 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-90-11 as an accepted procedure. 4 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 4
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACC47CN1S CONTACT, PIN 1 BACC47ER1 CONTACT, SOCKET 2 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11 WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-114W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 89K W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68G W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68H W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 45 PK 24 69K W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68F W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68K W176

FIGURE 16: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 114 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThis Figure applies only to: Group 3.

REFERENCE: 767 WDM 21-58-41, 767 WDM 21-58-16

FIGURE 17: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 115 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More Data Qty Identification Name Flag Note Use lacing tape to tie wires. Refer to SWPM 20-10-11 as an accepted procedure. Do not use plastic ties. - 829A9001-2 LACING TAPE - RED - PRESSURIZED (TEMP 135 DEG) 1

Refer to cut and code table. 1 289T1169-114W WIRE - RAW MATERIAL Refer to SWPM 20-81-19 as an accepted procedure. (a) 4 BACC47ER1 CONTACT, SOCKET 2 Refer to SWPM 21-61-11 as an accepted procedure. (a) 5 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-90-11 as an accepted procedure. 4 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 4
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACC47CN1S CONTACT, PIN 1 BACC47ER1 CONTACT, SOCKET 2 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11 WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-114W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 89K W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68G W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68H W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 45 PK 24 69K W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68F W176 BMS13-48 TYPE 11 CLASS 1, AWG 24 60 PK 24 68K W176

FIGURE 17: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 116 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 117 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 118 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTFIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 119 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTThe 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 as K10725. Refer to SOPM 20-50-10 asan accepted procedure. 1 BACT19J4 TAPE, ID Identify 1

identified as K10725. Refer to SOPM 20-50-05 asan accepted procedure. 1 BACT19J4 TAPE, ID Install (New)

as D20325. Refer to SOPM 20-50-10 asan accepted procedure. 1 BACT19J4 TAPE, ID Identify 2

identified as D20325. Refer to SOPM 20-50-05 asan accepted procedure. 1 BACT19J4 TAPE, ID Install (New)

Refer to SWPM 20-81-22 as an accepted procedure. 1 TDH-1852-3002 TIME DELAY RELAY Install (New) 3

as K10723. Refer to SOPM 20-50-10 asan accepted procedure. 1 BACT19J4 TAPE, ID Identify 4

identified as K10723. Refer to SOPM 20-50-05 asan accepted procedure. 1 BACT19J4 TAPE, ID Install (New)

as D20323. Refer to SOPM 20-50-10 asan accepted procedure. 1 BACT19J4 TAPE, ID Identify 5

identified as D20323. Refer to SOPM 20-50-05 asan accepted procedure. 1 BACT19J4 TAPE, ID Install (New)

FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 120 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERTMore Data Qty Identification Name Task Step Refer to SWPM 20-81-22 as an accepted procedure. 1 BACR13CD2 RELAY Install (New) 6

as R1270. Refer to SOPM 20-50-10 asan accepted procedure. 1 BACT19J4 TAPE, ID Identify 7

identified as R1270. Refer to SOPM 20-50-05 as an accepted procedure. 1 BACT19J4 TAPE, ID Install (New)

Refer to SOPM 20-50-05 as an accepted procedure. 1 BAC27TEX4697 VINYL MARKER (1 2 3...30) VERTICAL Install (New) 8

FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2010 767-21A0245 Revision 2 September 27, 2013 121 of 121 BOEING SERVICE BULLETIN 767-21A0245 ALERT ALERT