### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-21A0247 Original Issue: October 10, 2011 Revision 1: April 09, 2013 ATA System: 2158 SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 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 © 2011 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 Unpublished Work.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, DreamlinerTM, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and 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. BOEING is a trademark of Boeing Management Company.

Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 1 of 114 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 2 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT

BLANK PAGETable of Contents Revision Transmittal Sheet............................................ 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 19 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 19 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 20 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 30 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 31 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION [Group 1-2]. . . . . 37 FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - ROUTING [Group 1-2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - WIRING CHANGE [Group 1-2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING [Group 1-2]. . . . . . . 51 FIGURE 6: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 AND P50 ELECTRICAL SYSTEMS CARD FILE PANEL WIRE BUNDLE W1114 - WIRING CHANGES [Group 1-2]. . . . . . . . . . 59 FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING [Group 1-2]. . . . . . 60

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 3 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 8: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - WIRING CHANGE [Group 1-2] . . 63 FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING [Group 1-2]. . . . . . . . . . . . . 64 FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE [Group 1-2]. . . . . . . . . 66 FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT [Group 1-2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68 FIGURE 12: EXISTING DUCT REPLACEMENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71 FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION. . . . . . . . . . . . . . . . . . . . . . . . 77 FIGURE 14: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84 FIGURE 15: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) [Group 2-3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86 FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 1] . . . . . . . . . . . . . . . . 88 FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 2-3]. . . . . . . . . . . . . . . 91 FIGURE 18: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 1]. . . . . . . . . . . . . . . . 94 FIGURE 19: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 2-3]. . . . . . . . . . . . . . . 96 FIGURE 20: FDARS RELAY INSTALLATION IN P36. . . . . . . . . . . . . . . . . . . . . . . . . . . 98 FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE. . . . . . . . . . . . . . . 102 FIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36. . . . . . . . . . . . . . . . . . . . . 110

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 4 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT

### Commercial Airplanes 

# 767 Service Bulletin ALERT Revision Transmittal Sheet Number: 767-21A0247 Original Issue: October 10, 2011 Revision 1: April 09, 2013 ATA System: 2158 SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION 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. Airplanes VR273-VR279 were added to this service bulletin effectivity. More work is necessary on the airplane(s) changed in accordance with the original issue of this service bulletin. Original modification instruction is now identified as Part 1 and additional modification is identified as Part 2. Original airplanes require both Part 1 and Part 2 modification. Added airplanes require only Part 2 modification. REASON FOR REVISION This revision is issued to reduce noise in the flight compartment resulting when the operating logic of the 3-way-valve (also called the manifold interconnect valve) is changed as described in the original release of this service bulletin. Noise in the flight compartment caused by the increased airflow of the 3-way valve logic system changes made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Noise is reduced by adding a Flight Deck Air Relief System (FDARS) consisting of ducting and an outlet valve and additional relays. The outlet valve reduces airflow noise on the flight deck by exhausting a portion of the flight deck air distribution air into the area below the flight deck floor when the 3-way-valve is closed (nominally below 10,000 feet). These sections were changed: 1. Summary Section: a. Added Revision 1 statement to Background paragraph and revised position of some existing text; b. Added Summary Table to Background paragraph to comply with current standards; c. Added Revision 1 statement to Action paragraph and clarified some existing text; d. Updated Compliance paragraph to refer to Revision 1 date; e. Updated Manpower Table;

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 5 of 114f. Expanded illustration. 2. PLANNING INFORMATION: a. Paragraph 1.A., Effectivity: Added airplanes which had the intent of the original issue of this service bulletin incorporated during production but which still require the FDARS related parts. These airplanes are added as Group 3; b. Paragraph 1.C., Reason - Added Revision 1 statement and revised position of some existing text; c. Paragraph 1.D., Description - Added Revision 1 statement and clarified some existing text; d. Paragraph 1.E., Compliance - Updated paragraph to refer to Revision 1 issue date; e. Paragraph 1.G., Manpower - Added tables for added work; f. Paragraph 1.Weight and Balance Changes - Updated table and added table. 3. MATERIAL INFORMATION - Updated entire section to show that kits for original airplanes (Groups 1 and 2) will be updated, before shipment, to include FDARS related parts. Kits for added airplanes (Group 3) will include only FDARS parts. Also, additional operator-furnished material is identified. 4. ACCOMPLISHMENT INSTRUCTIONS: a. Paragraph 3.B., WORK INSTRUCTIONS - Revised work instructions into Part 1 and Part 2. Part 1 contains original rework instructions applicable to original airplanes. Part 2 contains added rework instructions applicable to original airplanes and added airplanes; b. FIGURES 1-11 - Added applicability to original Figures 1 through 11 to be applicable to original airplanes; c. FIGURES 12-22 - Added these figures with applicability, as marked, for original airplanes and added airplanes. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. REVISION HISTORY October 10, 2011 Original Issue: April 09, 2013 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 6 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT

### Commercial Airplanes 

# 767 Service Bulletin ALERT Summary Number: 767-21A0247 Original Issue: October 10, 2011 Revision 1: April 09, 2013 ATA System: 2158 SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS 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 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. Flight compartment indication blanking can cause unscheduled maintenance and airplane downtime. Also, 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. 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. 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 instances that are the likely causes of display unit malfunctions related to moisture or condensation ingress. These instances are as follows; an unserviceable air conditioning pack water separation system, that allowed water to be delivered to the flight compartment in the air conditioned air, a malfunction of an air conditioning pack which caused ice to be delivered to the flight compartment in the air conditioned air, and 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 (also called the manifold interconnect valve) in hot and humid conditions. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 7 of 114Accomplishment of this service bulletin installs a new relay in the P36 Left Miscellaneous Electrical Equipment Panel, with related wiring changes, and installs a new 10,000 feet altitude pressure switch to the E8 Engine Indication and Crew Alerting System (EICAS) rack to change the control logic of the 3-way valve operation above and below an altitude of 10,000 feet. This change reduces the amount of moisture or condensation that can collect in the flight compartment display units and thus reduce malfunction occurrences. Revision 1 - Incorporation of the equivalent change in production was found to cause excessive noise in the flight compartment caused by the increased flight deck air distribution airflow. This increased noise made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Because a solution to reduce the noise in the flight deck was not immediately available, Information Notice 767-21A0247 IN 01 was issued advising operators to not do this service bulletin until further improvements could be added. This revision adds ducting, an outlet valve, and related wiring to reduce noise in the flight compartment caused by flight deck air distribution air flow. These added components form the Flight Deck Air Relief System (FDARS). Revision 1 also adds airplanes to the effectivity as Group 3 airplanes. These airplanes received changes equivalent to the original release of this service bulletin during production. Therefore, these airplanes require only the FDARS-related additions. Boeing Service Related Problem (SRP) 767-SRP-21-0179 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 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: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 8 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTACTION (PRR B12900-260) Group 1-2: Get access to the airplane Main Equipment Center (MEC). Install a new bracket, new pressure switch, and attach hardware to the E8 Engine Indication and Crew Alerting System (EICAS) rack. Install a tube and fittings between the pressure switch and nearby existing Pitot system tubing. Open the P36 left miscellaneous equipment panel in the MEC and make changes to wire bundle W176. Make changes to wire bundle W596 between the P36 left miscellaneous equipment panel and P50 Electrical Systems Card File panel. In the P50 Electrical Systems Card File panel, make changes to wire bundle W1114. Make changes to wire bundle W1702 between the P36 left miscellaneous equipment panel and E8 EICAS rack. At the E8 EICAS rack, make changes to wire bundle W2000. In the P36 left miscellaneous equipment panel, remove relay K10355 and install new relay K10718. Flush and leak check the disturbed pitot system. Revision 1 - In the area forward of the main equipment bay and under the flight deck floor, replace a duct for equipment cooling with a duct that has an outlet port for the Flight Deck Air Relief System (FDARS) components. Install mounting brackets, FDARS ducts, orifice, outlet valve and screen. Change wiring within panel P36 and among panels and new outlet valve. Do an operational test of the revised system including the control logic of the 3-way valve (also called the manifold interconnect valve) and the added outlet valve. The changes in this service bulletin will not change the Engine Indication and Crew Alerting System (EICAS). 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 change given in this service bulletin be done within 6 years after the Revision 01 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 Elapsed Hours Total Task Hours Airplanes 41.65 61.85 Group 1 - 2 26.20 46.40 Group 3 MATERIAL INFORMATION Boeing Supplied Kits. Operator Supplied Parts/Materials.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 9 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTRefer to Paragraph 2.A., Material - Price and Availability

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 10 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 11 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 12 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT

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### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-21A0247 Original Issue: October 10, 2011 Revision 1: April 09, 2013 ATA System: 2158 SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes 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 airplane(s) 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, Variable Numbers VR201 thru VR211, and VW701 thru VW721 that must do Boeing service bulletin 767-21-0235 prior to or concurrent with this service bulletin. - 1

767-300F airplanes, Variable Numbers VR266 thru VR272 that have had the intent of Boeing service bulletin 767-21-0235 incorporated prior to delivery. - 2

767-300F airplanes, Variable Numbers VR273 thru VR279, that have had the intent of the original issue of this service bulletin incorporated prior to delivery. - 3

Airplane Models: 767-300F

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 13 of 114Group Variable Number 1 VR201 - VR211 2 VR266 - VR272 3 VR273 - VR279 1 VW701 - VW721 2. Spares Affected None. B. Concurrent Requirements Group 1: The service bulletin listed below must be done on Group 1 airplanes before or at the same time as this service bulletin: Group 1: Description Service Bulletin Company This service bulletin gives instructions to installa relay and related wiring in the P36 left miscellaneous equipment panel to change the control logic of the equipment cooling 3-way valve. 767-21-0235 Original Issue or Revision 1 Boeing

Group 2-3: 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 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. Flight compartment indication blanking can cause unscheduled maintenance and airplane downtime. Also, 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. 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. 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 instances that are the likely causes of display unit malfunctions related to moisture or condensation ingress. These instances are as follows; an unserviceable air conditioning pack water separation system, that allowed water to be delivered to the flight compartment in the air conditioned air, a malfunction of an air conditioning pack which caused ice to be delivered to the flight compartment in the air conditioned air, and the most frequent instance was display units being cold soaked by the air conditioned air delivered from the air conditioning packs

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 14 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTby the Electrical/Electronic cooling system through the 3-way valve (also called the manifold interconnect valve) in hot and humid conditions. 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. Accomplishment of this service bulletin installs a new relay in the P36 Left Miscellaneous Electrical Equipment Panel, with related wiring changes, and installs a new 10,000 feet altitude pressure switch to the E8 Engine Indication and Crew Alerting System (EICAS) rack to change the control logic of the 3-way valve operation above and below an altitude of 10,000 feet. This change reduces the amount of moisture or condensation that can collect in the flight compartment display units and thus reduce malfunction occurrences. Revision 1 - Incorporation of the equivalent change in production was found to cause excessive noise in the flight compartment caused by the increased flight deck air distribution airflow. This increased noise made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Because a solution to reduce the noise in the flight deck was not immediately available, Information Notice 767-21A0247 IN 01 was issued advising operators to not do this service bulletin until further improvements could be added. This revision adds ducting, an outlet valve, and related wiring to reduce noise in the flight compartment caused by flight deck air distribution air flow. These added components form the Flight Deck Air Relief System (FDARS). Revision 1 also adds airplanes to the effectivity as Group 3 airplanes. These airplanes received changes equivalent to the original release of this service bulletin during production. Therefore, these airplanes require only the FDARS-related additions. Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 21-09003 is related to this service bulletin. D. Description Group 1-2: Get access to the airplane Main Equipment Center (MEC). Install a new bracket, new pressure switch, and attach hardware to the E8 Engine Indication and Crew Alerting System (EICAS) rack. Install a tube and fittings between the pressure switch and nearby existing Pitot system tubing. Open the P36 left miscellaneous equipment panel in the MEC and make changes to wire bundle W176. Make changes to wire bundle W596 between the P36 left miscellaneous equipment panel and P50 Electrical Systems Card File panel. In the P50 Electrical Systems Card File panel, make changes to wire bundle W1114. Make changes to wire bundle W1702 between the P36 left miscellaneous equipment panel and E8 EICAS rack. At the E8 EICAS rack, make changes to wire bundle W2000. In the P36 left miscellaneous equipment panel, remove relay K10355 and install new relay K10718. Flush and leak check the disturbed pitot system. Revision 1 - More work is necessary on the airplane(s) changed in accordance with the original issue of this service bulletin. These airplanes and the airplanes added to this service bulletin all require the work summarized below and detailed in Paragraph 3.B. Accomplishment Instructions, Part 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 15 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTRevision 1 - In the area forward of the main equipment bay and under the flight deck floor, replace a duct for equipment cooling with a duct that has an outlet port for the Flight Deck Air Relief System (FDARS) components. Install mounting brackets, FDARS ducts, orifice, outlet valve and screen. Change wiring within panel P36 and among panels and new outlet valve. Do an operational test of the revised system including the control logic of the 3-way valve (also called the manifold interconnect valve) and the added outlet valve. The changes in this service bulletin will not change the Engine Indication and Crew Alerting System (EICAS). The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance ZonesZone Model 117, 119 767-300F 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 change given in this service bulletin be done within 6 years after the Revision 01 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. 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). G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 16 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT• Time to find the tools. Group 1-2: Part 1 Elapsed Hours Task Hours Number of Persons Task 0.50 0.50 1 Open Access 1.00 1.00 1 FIGURE 1 1.00 1.00 1 FIGURE 2

- - - FIGURE 3 (Wire routing only) 1.70 1.70 1 FIGURE 4

- - - FIGURE 5 (Wire routing only) 0.20 0.20 1 FIGURE 6

- - - FIGURE 7 (Wire routing only) 2.10 2.10 1 FIGURE 8

- - - FIGURE 9 (Wire routing only) 3.70 3.70 1 FIGURE 10 0.75 0.75 1 FIGURE 11 0.50 0.50 1 Close Access 4.00 4.00 1 Test 15.45 15.45 TOTAL FOR EACH AIRPLANE FOR PART 1 Group 1: Part 2 Elapsed Hours Task Hours Number of Persons Task 0.50 0.50 1 Open Access 1.25 1.25 1 FIGURE 12 2.50 2.50 1 FIGURE 13 12.30 24.60 2 FIGURE 14 (Wire Diagram), FIGURE 21 (Wire Routing) 7.90 15.80 2 FIGURE 16, FIGURE 18, (Wire Diagrams), FIGURE 22, (Wire Routing) 0.50 0.50 1 FIGURE 20 0.50 0.50 1 Close Access 0.75 0.75 1 Test 26.20 46.40 TOTAL FOR EACH AIRPLANE FOR PART 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 17 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 2-3: Part 2 Elapsed Hours Task Hours Number of Persons Task 0.50 0.50 1 Open Access 1.25 1.25 1 FIGURE 12 2.50 2.50 1 FIGURE 13 12.30 24.60 2 FIGURE 15 (Wire Diagram), FIGURE 21 (Wire Routing) 7.90 15.80 2 FIGURE 17, FIGURE 19, (Wire Diagrams), FIGURE 22, (Wire Routing) 0.50 0.50 1 FIGURE 20 0.50 0.50 1 Close Access 0.50 0.75 1 Test 26.20 46.40 TOTAL FOR EACH AIRPLANE FOR PART 2 Elapsed Hours Total Task Hours Total For Each Airplane
41.65 61.85 Group 1 - 2 26.20 46.40 Group 3 H. Weight and Balance Changes Group 1-2: Part 1 and Part 2 Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +848.9 +7.70 767-300F Group 3: Part 2 Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane + 660.1 +6.5 767-300F I. Electrical Load Data Not changed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 18 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTJ. References 1. Existing Data: a. Engineering Change Memo PRR B12900-260 b. Boeing Service Bulletin 767-21-0235 c. Boeing Service Related Problem (SRP) 767-SRP-21-0179 d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-50-05, 20-50-10, 20-50-19 e. Standard Wiring Practices Manual (SWPM) 20-00-11, 20-10-11, 20-10-11, 20-10-12, 20-10-19, 20-20-10, 20-20-11, 20-30-16, 20-60-09, 20-61-11, 20-81-12, 20-81-19, 20-81-22, 20-90-11 f. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 20-10-33, 20-41-01, 21-22-02, 21-58-00, 24-22-00, 25-00-00, 31-01-36, 34-11-00 g. 767 Fleet Team Digest (FTD) 21-09003 h. 767 Wiring Diagram Manual (WDM) 21-58-16, 21-58-41, 31-41-13 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: Title Drawing Number Duct Installation - Flight Deck Section 41 214T1011 Duct Installation - Instrument Panel Cooling System 217T2013 Tubing Installation Lower Lobe Sidewall LH, STA 132.5 Thru 290 278T4107 Rack Instl - E8 284T0971 Support Bracket, E8 Rack Instl 284T1040 Modular Wire Bundle Instl P36, Misc. Relay Panel, Left 288T2036 Modular Wire Bundle Installation E8 EICAS Rack 288T2280 Wire Bundle Installation Lower Lobe Sidewall LH, STA 132.5 288T4107 Wire Bundle Installation 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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 19 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTChapter-Section Publication 21-58 767 Aircraft Maintenance Manual 21-58, 34-11 767 Illustrated Parts Catalog 21-58, 31-41 767 System Schematic Manual 21-58, 31-41, Equipment List 767 Wiring Diagram Manual 21-58 767 Fault Isolation Manual 2.21-58 767 Dispatch Deviations Guide 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 affects FCS but no new DTIs are necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information. M. Software Accomplishment Summary Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 20 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Service Bulletin (US Dollars)ROLT as of the original issue date of thisService Bulletin (Calendar Days) QTY Date Name Kit Number

$21,865.00 179 7 February 28, 2013 Top Kit - 767 Freighters 3-Way Valve Logic Change With FDARS (Group 1 - 2) 015T1860-1
10 March 28, 2013 10 April 25, 2013 10 May 23, 20132 June 21, 2013 $15,959.00 179 7 February 28, 2013 Top Kit - 767 Freighters 3-Way Valve LogicChange FDARS Addition (Group 3) 015T1860-10

B. Industry Support Information Boeing warranty remedies are available for 767 airplanes 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 21 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTNOTE:One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. Figure Kit 20 13 12 11 2 1 Top Kit 1 1 1 1 1 1 015T1860-1 1 1 1
- - - 015T1860-10 Figure Kit 22 21 Top Kit 1 1 015T1860-1 1 1 015T1860-10 Top Kit 015T1860-10 015T1860-1 Wire Kit

- 1 015T1860-3

- 1 015T1860-2

- 1 015T1860-4 1 1 289T1169-106 1 1 289T1169-107 1 1 289T1169-108 Group 1-2: KIT 015T1860-1

Notes Existing Part Number Name Figure

New Part Number 20 13 12 11 2 1 Qty DECAL K10718

. . . 1

. . 015T1860-10101 DECAL D31620

. . . 1

. . 015T1860-10102 CLAMP MOUNTING INSTRUMENT . . . . 1

. 123-2222-F (a), (b) STIFFENER

. 1

. . . . 141T1226Y33 QUICK DISCONNECT . . . . 1

. 1QF2-3-64A
DISCONNECT

. . . . 1

. 1QM1-3-54A DUCT ASSY

. 1

. . . . 214T1120-313

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 22 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 1-2: KIT 015T1860-1

Notes Existing Part Number Name Figure

New Part Number 20 13 12 11 2 1 Qty DUCT ASSY

. 1

. . . . 214T1120-315 (c) 214T1120-218 OR -1218 OR -3218 DUCT ASSY

. . 1

. . . 214T1120-3311
ORIFICE ASSY

. 1

. . . . 214T3436-453 (a), (b) BRACKET

. 1

. . . . 214T6419Y40 (a), (b) BRACKET

. 1

. . . . 217T2434U10 (a), (b) BRACKET

. . . . . 1 233T9118Y105 Pressure Switch

. . . . 1

. 6502-10K VALVE - AIR SHUTOFF . 1

. . . . 67-2951-001
SCREEN ASSY

. 1

. . . . 69B42275-4 HOSEDUCT, SLEEVE . 1

. . . . AS1506-14D30 VINYL MARKER (12 3...30) VERTICAL 1

. . . . . BAC27TEX4697

VINYL DECAL

. . . . 1

. BAC27TFDE534 CLAMP, MISCELLANEOUS . 2

. . . . BACC10DU500ABE SUPPORT, DUCT

. 2

. . . . BACC10ME20-1 HOSE, INSTRUMENT . . . . 1

. BACH30BC06- 0110 BONDING JUMPER . 1

. . . . BACJ40A20-7
NUTPLATE

. 4

. . . . BACN10YD1G (d) NUT

. 3

. . . . BACN10YR3CD RELAY 1

. . . . . BACR13CD2 (e) RIVET, UNIVER- SAL HD . . . . . 4 BACR15FT6AD5C (d), (e) RIVET, UNIVER- SAL HD . 8

. . . . BACR15FT6KE5C (d), (e) RIVET, UNIVER- SAL HD . 4

. . . . BACR15FT6KE6C

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 23 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 1-2: KIT 015T1860-1

Notes Existing Part Number Name Figure

New Part Number 20 13 12 11 2 1 Qty (d), (e) RIVET

. 3

. . . . BACR15FT6KE7C (d) SCREW, CAP

. 7

. . . . BACS12GU3K7 (d) STRAP

. . 3

. . . BACS38K2 (d) STRAP

. 1 4

. . . BACS38K6 (d) TAPE, ID 6

. . . . . BACT19J4 PACKING, PREFORMED . . . . 1

. MS28778-5 PACKING, PREFORMED . . 1

. . . MS29512-08 (d) WASHER

. 6

. . . . NAS1149D0316J (d) WASHER, PLAIN

. 8

. . . . NAS1149D0332H CLAMP, HOSE

. 2

. . . . NAS1922-0350-3 CLAMP, HOSE

. 3

. . . . NAS1922-0525-3 TIME DELAY RELAY 1

. . . . . TDH-1852-3002
TIME DELAY RELAY . . . 1

. . TDH-8050-3003P (a) This part not used in production. (b) 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. (c) You cannot use the existing part to replace the new or changed part. (d) There are more parts than are necessary. (e) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 24 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 1-2: KIT 015T1860-1

Notes Existing Part Number Name Figure

New Part Number 22 21Qty RETAINER CLIP ASSY . 2 411A4902-7
LACING TAPE -RED - PRESSURIZED (TEMP 135 DEG) 1 1 829A9001-2

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

. 829A9001-5

Group 3: KIT 015T1860-10

Notes Existing Part Number Name Figure

New Part Number 22 21 20 13 12 Qty (a), (b) STIFFENER

. . . 1

. 141T1226Y33 DUCT ASSY

. . . 1

. 214T1120-313 DUCT ASSY

. . . 1

. 214T1120-315 (c) 214T1120-218 OR -1218 OR -3218 DUCT ASSY

. . . . 1 214T1120-3311
ORIFICE ASSY

. . . 1

. 214T3436-453 (a), (b) BRACKET

. . . 1

. 214T6419Y40 (a), (b) BRACKET

. . . 1

. 217T2434U10 RETAINER CLIP ASSY . 2

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

. 67-2951-001
SCREEN ASSY

. . . 1

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

. . . 829A9001-2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 25 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 3: KIT 015T1860-10

Notes Existing Part Number Name Figure

New Part Number 22 21 20 13 12 Qty LACING TAPE -BLUE - PRESSURIZED (TEMP 135 DEG) 1

. . . . 829A9001-5

HOSEDUCT, SLEEVE . . . 1

. AS1506-14D30 VINYL MARKER (12 3...30) VERTICAL . . 1

. . BAC27TEX4697

CLAMP, MISCELLANEOUS . . . 2

. BACC10DU500ABE SUPPORT, DUCT

. . . 2

. BACC10ME20-1 BONDING JUMPER . . . 1

. BACJ40A20-7
NUTPLATE

. . . 4

. BACN10YD1G (d) NUT

. . . 3

. BACN10YR3CD RELAY

. . 1

. . BACR13CD2 (d), (e) RIVET, UNIVER- SAL HD . . . 8

. BACR15FT6KE5C (d), (e) RIVET, UNIVER- SAL HD . . . 4

. BACR15FT6KE6C (d), (e) RIVET

. . . 3

. BACR15FT6KE7C (d) SCREW, CAP

. . . 7

. BACS12GU3K7 (d) STRAP

. . . . 3 BACS38K2 (d) STRAP

. . . 1 4 BACS38K6 (d) TAPE, ID

. . 6

. . BACT19J4 PACKING, PREFORMED . . . . 1 MS29512-08 (d) WASHER

. . . 6

. NAS1149D0316J (d) WASHER, PLAIN

. . . 8

. NAS1149D0332H CLAMP, HOSE

. . . 2

. NAS1922-0350-3 CLAMP, HOSE

. . . 3

. NAS1922-0525-3

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 26 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 3: KIT 015T1860-10

Notes Existing Part Number Name Figure

New Part Number 22 21 20 13 12 Qty TIME DELAY RELAY . . 1

. . TDH-1852-3002 (a) This part not used in production. (b) 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. (c) You cannot use the existing part to replace the new or changed part. (d) There are more parts than are necessary. (e) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip lengthlonger than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Group 1-2: KIT 015T1860-2 Notes Name Qty New Part Number WIRE W0176 1 015T1860-101W TAPE, LACING 1 015T1860-10104 SLEEVE IDENTIFICATION, HEAT SHRINKABLE 1 015T1860-10106

CONTACT, SOCKET 1 BACC47CP1S CONTACT, SOCKET 4 BACC47DJ1
RELAY SOCKET 1 BACS16W1A 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: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 27 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 1-2: KIT 015T1860-3 Notes Name Qty New Part Number WIRE W1702 1 015T1860-102W CONTACT, PIN 1 BACC47CN1S CONTACT, PIN 1 BACC47CN1SB SLEEVE, HEAT SHRINK 1 BACT63D1
Group 1-2: KIT 015T1860-4 Notes Name Qty New Part Number WIRE W2000 1 015T1860-103W SLEEVE IDENTIFICATION, HEAT SHRINKABLE 1 015T1860-10105

BACKSHELL CLAMP 1 BACC10GH10 CONNECTOR, ELECTRICAL, PLUG, STRAIGHT,BAYONET COUPLING 1 BACC45FT10A5S

CONTACT, SOCKET 4 BACC47CP1S
CONTACT 2 BACC47DE8A PLUG 1 MS27488-20-1
KIT 289T1169-106 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-106W
ID - CONNECTOR 1 289T1169-10301 CONNECTOR, ELECTRICAL, PLUG, STRAIGHT,BAYONET COUPLING 1 BACC45FT12C12S6

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 28 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTKIT 289T1169-106 Notes Name Qty New Part Number (a) CONTACT, SOCK- ET 14 BACC47CP1S (a) CONTACT, PIN 5 BACC47DE7A (a) There are more parts than are necessary.
KIT 289T1169-107 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-107W
ID - CONNECTOR 1 289T1169-10401 ID - CONNECTOR 1 289T1169-10402 ID - DIODE 1 289T1169-10403 (a) CONTACT, PIN 3 BACC47DE7A (a) CONTACT 3 BACC47DE8A (a) CONTACT, SOCK- ET 4 BACC47DJ1 (a) CONTACT, SOCK- ET 12 BACC47ER1
RELAY SOCKET 1 BACS16AG1 RELAY SOCKET 1 BACS16AH1 (a) CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 12 M39029/11-145

TERMINAL BLOCKRESISTOR ASSEMBLY MODULE 1 YHLZR-17
(a) There are more parts than are necessary.
KIT 289T1169-108 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-108W (a) CONTACT, PIN 6 BACC47CN1S (a) CONTACT, SOCK- ET 5 BACC47ER1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 29 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTKIT 289T1169-108 Notes Name Qty New Part Number (a) CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 6 M39029/11-145

(a) There are more parts than are necessary. 2. Parts and Materials Supplied by the Operator Notes Name QTY Part Number / Specification (a) SEALANT 4 oz BMS5-95 (a) PRIMER 4 oz BMS10-11, TYPE I (a) TAPE 5 ft BMS 5-157 TYPE I, CLASS 1, GRADE A, COMPOSITION MPVF LOCKWIRE 1 ft MS20995N32 (MS20995NC32 optional) (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. 3. Parts Modified and Reidentified Group 1-2: Part 1: Group 1-2: The part shown below is changed as shown in this service bulletin. The quantity (QTY) is the number of parts changed on each airplane. Group 1-2: Notes New Part Number Name QTY Existing Part Number (a) (b) 284T1040-16 SUPPORT BRACKET 1 284T1040-6 (a) Make the change in accordance with this service bulletin. (b) This is the part number after the change is done in accordance with this service bulletin. Part 2: None 4. Parts Removed and Not Replaced Group 1-2: Part 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 30 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTGroup 1-2: Notes QTY Name Existing Part Number (a) 1 CAP BACC14AD06DN (a) 1 RELAY BACR13CD2 (a) 1 RELAY, SOCKET BACS16AG (a) Keep the part if there are other uses for it. Part 2: None D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 31 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 32 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 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. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 33 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT10. The work instructions refer to panel(s) that contain Electro-static Sensitive Devices (ESDS). Make sure you keep contamination or unwanted materials away from the sensitive device. Contamination or unwanted material near the sensitive device can cause a malfunction in the sensitive device. Refer to 767 AMM 20-41-01 as an accepted procedure. 11. Work Instructions are broken into two parts. Part 1, including Figures 1 - 11, consists of the instructions from the original release of the service bulletin. Part 2, including Figures 12 - 19, is the addition of Flight Deck Air Relief System (FDARS) Components with some additional wiring changes. Both Part 1 and Part 2 are required on Group 1 and Group 2 airplanes. Only Part 2 is required for Group 3 airplanes because Group 3 airplanes received a change equivalent to Part 1 in production. B. WORK INSTRUCTIONS Group 1-2: Part 1 - 3-Way-Valve (also called manifold interconnect valve) operating logic change. 1. Remove electrical power from the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 2. Get access to the Main Equipment Center (MEC). Refer to 767 AMM 06-41-00 as an accepted procedure for access locations. 3. In the MEC, open the circuit breaker specified in the table below and attach a "DO-NOT-CLOSE" tag: CIRCUIT BREAKER PANEL ASSEMBLY Number Name Location Panel C00679 EQPT COOL OVERRIDE C019 P11-4 4. In the MEC, install the new bracket to the E8 Engine Indication and Crew Alerting System (EICAS) rack at station 266.5 in accordance with FIGURE 1. 5. At the E8 EICAS rack, install the new pressure switch to the bracket and attach hardware in accordance with FIGURE 2. 6. Open the P36 left miscellaneous equipment panel door to get access to the wiring. Refer to 767 AMM 31-01-36 for component locations. 7. In the P36 left miscellaneous equipment panel, make changes to wire bundle W176 in accordance with FIGURE 3 and FIGURE 4. 8. In the MEC, make changes to wire bundle W596 between the P36 left miscellaneous equipment panel and P50 electrical systems card file panel in accordance with FIGURE 5 and FIGURE 6. 9. In the P50 electrical systems card file panel, make changes to wire bundle W1114 in accordance with FIGURE 6. 10. In the MEC, make changes to wire bundle W1702 between the P36 left miscellaneous equipment panel and E8 EICAS rack in accordance with FIGURE 7 and FIGURE 8.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 34 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT11. At the E8 EICAS rack, make changes to wire bundle W2000 in accordance with FIGURE 9 and FIGURE 10. 12. In the P36 left miscellaneous equipment panel, remove relay K10355 and install new relay K10718 in accordance with FIGURE 11. 13. Close the P36 left miscellaneous equipment panel. 14. In the MEC, remove the "DO-NOT-CLOSE" tag and close the circuit breaker specified in the table below: CIRCUIT BREAKER PANEL ASSEMBLY Number Name Location Panel C00679 EQPT COOL OVERRIDE C019 P11-4 15. Supply electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 16. Flush the pitot/static system. Refer to 767 AMM 34-11-00 as an accepted procedure. 17. Do a leak test of the Auxiliary Static system No. 2 (AS2). Refer to 767 AMM 34-11-00 as an accepted procedure. 18. Continue with Part 2.

Part 2 - Addition of Flight Deck Air Relief System (FDARS) Components. 1. Remove electrical power if not done for Part 1. Refer to 767 AMM 24-22-00 as an accepted procedure. 2. Gain access to the main equipment center and the area under the left and right sides of the flight deck floor. 3. Replace existing duct with new duct in accordance with FIGURE 12. 4. Install new Flight Deck Air Relief System (FDARS) components including mounting brackets, ducts, orifice, outlet valve and screen in accordance with FIGURE 13. 5. Modify wiring as follows: a. Add wires and connector between panel P36 and new valve: (1)Group 1: In accordance with FIGURE 14 (wire diagram) and FIGURE 21 (wire installation). (2)Group 2-3: In accordance with FIGURE 15 (wire diagram) and FIGURE 21 (wire installation).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 35 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTb. Modify wiring within Panel P36: (1)Group 1: In accordance with FIGURE 16 and FIGURE 18 (wire diagrams) and FIGURE 22 (wire installation). (2)Group 2-3: In accordance with FIGURE 17 and FIGURE 19 (wire diagrams) and FIGURE 22 (wire installation). 6. Modify relay installation in panel P36 in accordance with FIGURE 20. 7. Restore electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure. 8. Do an Operational Test - Manifold Interconnect Valve (Reconfiguration) - Post SB 767-21A0247R1. Refer to 767 AMM 21-58-00 as an acceptable procedure. (This will also test operation of the added outlet valve.) 9. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1: April 09, 2013 36 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 37 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 38 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure.MORE DATA QTY IDENTIFICATION NAME TASK STEP on the support bracket at the position shown. 1 233T9118Y105 BRACKET Put / Hold 1 0.129 inch diameter in the support bracket to agree with bracket. 4
- PILOT HOLE Drill 2
0.191 - 0.202 inch diameter in the support bracket and bracket. 4
- HOLE Drill 3 in the support bracket and bracket. Break all sharp edges. 4
- HOLE Deburr to the support bracket and bracket mating surfaces. Refer to SOPM 20- 50-19 as an accepted procedure. - BMS5-95 SEALANT Apply 4

FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 39 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP on the support bracket at the position shown. 1 233T9118Y105 BRACKET Install (New) 5
4 BACR15FT6AD5C RIVET, UNIVERSAL HD Install (New) Apply two coats to all bare metal surfaces of the support bracket and bracket. Refer to SOPM 20-41-02 as an accepted procedure. - BMS10-11, TYPE I PRIMER Apply 6

to the support bracket to identify that this change is done. Refer to SOPM 20-50-10 code RH as an accepted procedure. (a) - - PART NUMBER Apply 7

(a) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for applicable part number.

FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 40 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 41 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 42 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure.MORE DATA QTY IDENTIFICATION NAME TASK STEP to the bracket. 1 123-2222-F CLAMP MOUNTING INSTRUMENT Install (New) 1 in the instrument mounting clamp. 1 6502-10K Pressure Switch Install (New) 2 onto the pneumatic inlet port. 1 MS28778-5 PACKING, PRE- FORMED Install (New) 3 to the pressure switch. 1 1QM1-3-54A DISCONNECT Install (New) to the BACH30BC01-0110 instrument hose. 1 1QF2-3-64A QUICK DISCONNECT Install (New) 4 from the AS2 system tubing tee fitting located at STA 270, LBL70, WL170. 1 BACC14AD06DN CAP Remove 5
between the AS2 system tubing tee fitting and the pressure switch quick disconnect. 1 BACH30BC06-0110 HOSE, INSTRUMENT Install (New) 6
on the bracket below the pressure switch at the position shown. Refer to SOPM 20-50-05 as an accepted procedure. 1 BAC27TFDE534 VINYL DECAL Install (New) 7

FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 43 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - ROUTING (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 44 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - ROUTING (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 45 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - ROUTING (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 46 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - ROUTING (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 47 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - ROUTING (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 48 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - WIRING CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 49 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTREFERENCE: 767 WDM 21-58-16 NOTE:The parts are in Wire Kit 015T1860-2. 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. - 015T1860-10104 TAPE, LACING 1
Refer to cut and code table for wire kit 015T1860- 101W. 1 015T1860-101W WIRE W0176 2
1 BACS16W1A RELAY SOCKET 3 Refer to SWPM 20-81-12 as an accepted procedure. 4 BACC47DJ1 CONTACT, SOCKET 4 Install within 6 inches of equipment. Refer to SWPM 20-10-11 as an accepted procedure. 1 015T1860-10106 SLEEVE IDENTIFICA-TION, HEAT SHRINKABLE 5
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 6 Refer to SWPM 20-90-11 as an accepted procedure. 1 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11 7

WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-101W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE# WBA# BMS 13-48, TYPE 11, CLASS 1, AWG24 100 PK 24 34G W0176 BMS 13-48, TYPE 11, CLASS 1, AWG24 100 PK 24 34H W0176

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - WIRING CHANGE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 50 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 1 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 51 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 2 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 52 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 3 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 53 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 4 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 54 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 5 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 55 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 6 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 56 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 7 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 57 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING (SHEET 8 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 58 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

REFERENCE: 767 WDM 21-58-16 NOTE:The part is in Wire Kit 015T1860-3. 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 Remove and discard wire. 1 W596-606-24 WIRE 1 Refer to SWPM 20-30-16 as an accepted procedure. 1 BACT63D1 SLEEVE, HEAT SHRINK 2

FIGURE 6: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 AND P50 ELECTRICAL SYSTEMS CARD FILE PANEL WIRE BUNDLE W1114 - WIRING CHANGES (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 59 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 60 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 61 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 62 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

REFERENCE: 767 WDM 21-58-16 NOTE:The parts are in Wire Kit 015T1860-2 and 015T1860-3. 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. - 015T1860-10104 TAPE, LACING 1
Refer to cut and code table for wire kit 015T1860- 102W. 1 015T1860-102W WIRE W1702 2 Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1SB CONTACT, PIN 4

WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-102W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE# WBA# BMS13-48, TYPE 11, CLASS 1, AWG24 200 PK 24 021 W1702

FIGURE 8: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - WIRING CHANGE (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 63 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 64 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 65 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 66 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTREFERENCE: 767 WDM 31-41-13 NOTE:The parts are in Wire Kit 015T1860-2 and 015T1860-4. 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. - 015T1860-10104 TAPE, LACING 1
Refer to cut and code table for wire kit 015T1860- 103W 1 015T1860-103W WIRE W2000 2
Install within 6 inches of connector. Refer to SWPM 20-10-11 as an accepted procedure. 1 015T1860-10105 SLEEVE IDENTIFICA-TION, HEAT SHRINKABLE 3
Refer to SWPM 20-61-11 as an accepted procedure. 4 BACC47CP1S CONTACT, SOCKET 4 Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT10A5S CONNECTOR, ELEC- TRICAL, PLUG, STRAIGHT, BAYONET COUPLING 5

Insert contact sockets and seal plugs at each empty contact socket hole. Refer to SWPM 20- 00-11 as an accepted procedure. 2 MS27488-20-1 PLUG
Refer to SWPM 20-60-09 as an accepted procedure. 1 BACC10GH10 BACKSHELL CLAMP Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE8A CONTACT 6

WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-103W NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE# WBA# BMS 13-48, TYPE 11, CLASS 1, AWG24 100 PK 24 0100 W2000 BMS 13-48, TYPE 10, CLASS 1, AWG20 100 PA 20 0110 W2000 BMS 13-48, TYPE 10, CLASS 1, AWG20 100 PA 20 0120 W2000

FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 67 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1-2.

FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 68 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 69 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure. More Data Qty Identification Name Task Step K10355 from the front of the relay plate. (a) 1 BACR13CD2 RELAY Remove 1
Imprinted K10355. 1 BACT19J4 DECAL Remove 2 D21730 from the rear of the relayplate. Lower the relay plate as necessary. (a) 1 BACS16AG SOCKET, RELAY Remove 3

Imprinted D21730. 1 BACT19J4 DECAL Remove 4 on the front of the relay plate. Refer to SOPM 20-50-05 asan accepted procedure. 1 015T1860-10101 DECAL K10718 Install (New) 5

on the rear of the relay plate. Lower therelay plate as necessary. Refer to SOPM20-50-05 as an accepted procedure. 1 015T1860-10102 DECAL D31620 Install (New) 6

K10718 into relay socket D31620. 1 TDH-8050-3003P TIME DELAY RELAY Install (New) 7 (a) Keep this part if there are other uses for it.

FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 70 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 12: EXISTING DUCT REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 71 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 12: EXISTING DUCT REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 72 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 12: EXISTING DUCT REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 73 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure. More Data Qty Identification Name Task Step 5
- STRAP Remove 1 1 AS1506-15D23 SLEEVE Remove / Keep 2 1 AS1506-06D32 SLEEVE Remove / Keep 3 1 NH102689-0450 CLAMP Remove / Keep 4

FIGURE 12: EXISTING DUCT REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 74 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTMore Data Qty Identification Name Task Step

- D20366 CONNECTOR Disconnect 5

- - LOCKWIRE Remove 1 3000-46-41 TEMPERATURE CON- TROL SWITCH Remove / Keep
1 MS29512-08 PACKING, PRE- FORMED Remove
2 BACS12GU( ) SCREW Remove / Keep (a) 1 217T1438-3 BRACKET Remove / Keep 1 214T1120-( ) DUCT ASSY Remove 6 1 214T1120-3311 DUCT ASSY Install (New) 7 (a) 1 217T1438-3 BRACKET Install (Kept) 8 2 BACS12GU( ) SCREW Install (Kept) 1 3000-46-41 TEMPERATURE CON- TROL SWITCH Install (Kept)
1 MS29512-08 PACKING, PRE- FORMED Install (New) (b)
- MS20995N32(MS20995NC32 optional) LOCKWIRE Install (New)

- D20366 CONNECTOR Connect 1 NH102689-0450 CLAMP Install (Kept) 9 (c) 1 BACS38K6 STRAP Install (New) 10 1 AS1506-15D23 SLEEVE Install (Kept) 11 (c) 2 BACS38K6 STRAP Install (New) 1 AS1506-06D32 SLEEVE Install (Kept) 12 (c) 2 BACS38K2 STRAP Install (New) (a) Includes Marker BAC27TEC334. (b) Refer to 767 AMM 20-10-33 as an accepted procedure. (c) TO APPLY CORRECT TENSION TO BACS38K() STRAP, USE PANDUIT INSTALLATION TOOL GS4H OR EQUIVALENT, SET ON -HVY- POSITION AND TENSION INDICATOR ON (5) FOR .19 WIDE STRAPS AND (8) FOR .30 WIDE STRAPS

FIGURE 12: EXISTING DUCT REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 75 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThe parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACS38K2 STRAP 1 BACS38K6 STRAP

FIGURE 12: EXISTING DUCT REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 76 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 13: FDARS DUCTS AND VALVE INSTALLATION (SHEET 1 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 77 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 13: FDARS DUCTS AND VALVE INSTALLATION (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 78 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 13: FDARS DUCTS AND VALVE INSTALLATION (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 79 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 13: FDARS DUCTS AND VALVE INSTALLATION (SHEET 4 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 80 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure. More Data Qty Identification Name Task Step At both frames.
- - INSULATION Retract 1 1
- STRAP Remove 2 For access to install rivets. - - DUCT Disconnect 3
AFT of side of frame. 1 214T6419Y40 BRACKET Install (New) 4
3 BACR15FT6KE5C RIVET, UNIVERSAL HD Install (New) Through frame and chord. 1
- RIVET Remove 5
AFT side of frame. 1 217T2434U10 BRACKET Install (New) 6 FWD side of frame. 1 141T1226Y33 STIFFENER Install (New) Through frame, chord and stiffener. 1 BACR15FT6KE7C RIVET Install (New) Through bracket, frame and stiffener. 2 BACR15FT6KE6C RIVET, UNIVERSAL HD Install (New) Through bracket and frame. 2 BACR15FT6KE5C RIVET, UNIVERSAL HD Install (New) Through frame and stiffener. 1 BACR15FT6KE5C RIVET, UNIVERSAL HD Install (New)
2 BACC10ME20-1 SUPPORT, DUCT Install (New) 7 4 BACS12GU3K7 SCREW, CAP Install (New) 4 NAS1149D0316J WASHER Install (New) 4 BACN10YD1G NUTPLATE Install (New) (a) 1 214T3436-453 ORIFICE ASSY Install (New) 8 1 AS1506-14D30 HOSEDUCT, SLEEVE Install (New) 9 1 NAS1922-0350-3 CLAMP, HOSE Install (New) 1 214T1120-313 DUCT ASSY Install (New) 10 1 NAS1922-0350-3 CLAMP, HOSE Install (New) 1 NAS1922-0525-3 CLAMP, HOSE Install (New) (b) 1 214T1120-315 DUCT ASSY Install (New) 11 1 NAS1922-0525-3 CLAMP, HOSE Install (New)

FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 81 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTMore Data Qty Identification Name Task Step 1 67-2951-001 VALVE - AIR SHUT- OFF Install (New) 12
2 BACC10DU500ABE CLAMP, MISCELLA- NEOUS Install (New)
1 69B42275-4 SCREEN ASSY Install (New) 13 1 NAS1922-0525-3 CLAMP, HOSE Install (New) (c) 1 BACJ40A20-7 BONDING JUMPER Install (New) 14 0.218 - 0.229 IN DIA 1
- HOLE Drill 2 BACS12GU3K7 SCREW, CAP Install (New) 6 NAS1149D0332H WASHER, PLAIN Install (New) 2 BACN10YR3CD NUT Install (New)

- - DUCT Connect 15 (d) 1 BACS38K6 STRAP Install (New) 16

- - INSULATION Repair 17 (e)
- BMS 5-157 TYPE I, CLASS 1, GRADE A, COMPOSITION MPVF TAPE Apply
(a) Refer to 767 AMM 21-22-02 as an accepted procedure. (b) Align the alignment mark on elbow duct to the top of the duct support to make sure that the airflow will be exhausted downward at the catwalk surface.(c) CLEAN, ASSEMBLE AND TEST GROUND. REFER TO SWPM 20-20-10 AS AN ACCEPTED PROCEDURE. MEASURE RESISTANCE BETWEEN VALVE BODY AND FRAME INCLUDING SCREW, NUT AND WASHERS. MAXIMUM RESISTANCE 0.005 OHM. (d) TO APPLY CORRECT TENSION TO BACS38K() STRAP, USE PANDUIT INSTALLATION TOOL GS4H OR EQUIVALENT, SET ON -HVY- POSITION AND TENSION INDICATOR ON (5) FOR .19 WIDE STRAPS AND (8) FOR .30 WIDE STRAPS (e) Use tape to repair insulation and to seal insulation to brackets. Refer to 767 AMM 25-00-00 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 BACN10YR3CD NUT 1 BACS12GU3K7 SCREW, CAP 2 NAS1149D0316J WASHER

FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 82 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTMore Data Qty Identification Name 2 BACR15FT6KE5C RIVET, UNIVERSAL HD 2 BACR15FT6KE6C RIVET, UNIVERSAL HD 2 BACR15FT6KE7C RIVET 2 NAS1149D0332H WASHER, PLAIN

FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION (SHEET 7 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 83 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1.

Reference : 767 WDM 21-58-41 NOTE:The parts are in Wire Kit 289T1169-106. The wire is identified as 289T1169-106W. 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 20-90-11 as an accepted procedure. 4 BACC47DE7A CONTACT, PIN 1
Refer to SWPM 20-61-11 as an accepted procedure. (a) 12 BACC47CP1S CONTACT, SOCKET 2
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT12C12S6 CONNECTOR, ELECTRI- CAL, PLUG, STRAIGHT, BAYONET COUPLING 3

Refer to SWPM 20-10-11 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.

FIGURE 14: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 84 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTNOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 132 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 133 W0756 BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 135 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 136 W0756 BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 137 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 138 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 139 W0756 BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 140 W0756 The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACC47DE7A CONTACT, PIN 2 BACC47CP1S CONTACT, SOCKET

FIGURE 14: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 85 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 2-3.

Reference : 767 WDM 21-58-41 NOTE:The parts are in Wire Kit 289T1169-106. The wire is identified as 289T1169-106W. 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 20-90-11 as an accepted procedure. 4 BACC47DE7A CONTACT, PIN 1
Refer to SWPM 20-61-11 as an accepted procedure. (a) 12 BACC47CP1S CONTACT, SOCKET 2
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT12C12S6 CONNECTOR, ELECTRI- CAL, PLUG, STRAIGHT, BAYONET COUPLING 3

Refer to SWPM 20-10-11 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.

FIGURE 15: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 86 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTNOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 132 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 133 W0756 BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 135 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 136 W0756 BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 137 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 138 W0756 BMS 13-48, TYPE 11, CLASS 1, AWG 24 436 PK 24 139 W0756 BMS 13-48, TYPE 10, CLASS 1, AWG 20 207 PA 20 140 W0756 The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACC47DE7A CONTACT, PIN 2 BACC47CP1S CONTACT, SOCKET

FIGURE 15: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 87 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1.

FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 88 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTReference : 767 WDM 21-58-41 NOTE:The parts are in Wire Kit 289T1169-107. The wire is identified as 289T1169-107W. 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 20-81-19 as an accepted procedure. (a) 9 BACC47ER1 CONTACT, SOCKET 1
Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE7A CONTACT, PIN 2
Refer to SWPM 20-90-11 as an accepted procedure. 9 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 3

Refer to SWPM 20-81-22 as an accepted procedure. 1 BACS16AG1 RELAY SOCKET 4
Refer to SWPM 20-10-11 as an accepted procedure. 1 289T1169-10401 ID - CONNECTOR
Refer to SWPM 20-81-22 as an accepted procedure. 1 BACS16AH1 RELAY SOCKET 5
Refer to SWPM 20-10-11 as an accepted procedure. 1 289T1169-10402 ID - CONNECTOR
Refer to SWPM 20-61-11 as an accepted procedure. (a) 3 BACC47DJ1 CONTACT, SOCKET 6
Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE8A CONTACT 7
Refer to SWPM 20-90-11 as an accepted procedure. 1 YHLZR-17 TERMINAL BLOCK RESIS- TOR ASSEMBLY MODULE 8
Refer to SWPM 20-90-11 as an accepted procedure. 1 289T1169-10403 ID - DIODE (a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure.
NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 10, CLASS 1, AWG 20 93 PA 20 731 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 732 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 733 W0184 BMS 13-48, TYPE 10, CLASS 1, AWG 20 93 PA 20 734 W0184

FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 89 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTNOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 11, CLASS 1, AWG 24 40 PK 24 735 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 736 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 80 PK 24 737 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 55 PK 24 18L W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 50 PK 24 18M W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 50 PK 24 18N W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 30 PK 24 55P W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 22 PK 24 55R W0184 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

FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 90 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 2-3.

FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 91 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTReference : 767 WDM 21-58-41 NOTE:The parts are in Wire Kit 289T1169-107. The wire is identified as 289T1169-107W. 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 20-81-19 as an accepted procedure. (a) 9 BACC47ER1 CONTACT, SOCKET 1
Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE7A CONTACT, PIN 2
Refer to SWPM 20-90-11 as an accepted procedure. 9 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 3

Refer to SWPM 20-81-22 as an accepted procedure. 1 BACS16AG1 RELAY SOCKET 4
Refer to SWPM 20-10-11 as an accepted procedure. 1 289T1169-10401 ID - CONNECTOR
Refer to SWPM 20-81-22 as an accepted procedure. 1 BACS16AH1 RELAY SOCKET 5
Refer to SWPM 20-10-11 as an accepted procedure. 1 289T1169-10402 ID - CONNECTOR
Refer to SWPM 20-61-11 as an accepted procedure. (a) 3 BACC47DJ1 CONTACT, SOCKET 6
Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE8A CONTACT 7
Refer to SWPM 20-90-11 as an accepted procedure. 1 YHLZR-17 TERMINAL BLOCK RESIS- TOR ASSEMBLY MODULE 8
Refer to SWPM 20-90-11 as an accepted procedure. 1 289T1169-10403 ID - DIODE (a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure.
NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 10, CLASS 1, AWG 20 93 PA 20 731 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 732 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 733 W0184 BMS 13-48, TYPE 10, CLASS 1, AWG 20 93 PA 20 734 W0184

FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 92 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTNOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 11, CLASS 1, AWG 24 40 PK 24 735 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 736 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 80 PK 24 737 W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 55 PK 24 18L W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 50 PK 24 18M W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 50 PK 24 18N W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 30 PK 24 55P W0184 BMS 13-48, TYPE 11, CLASS 1, AWG 24 22 PK 24 55R W0184 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

FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 93 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 1.

Reference : 767 WDM 21-58-16 NOTE:The parts are in Wire Kit 289T1169-108. The wire is identified as 289T1169-108W. 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 20-81-19 as an accepted procedure. (a) 4 BACC47ER1 CONTACT, SOCKET 1
Refer to SWPM 20-61-11 as an accepted procedure. (a) 5 BACC47CN1S CONTACT, PIN 2

FIGURE 18: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 94 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTMore Data Qty Identification Name Flag Note Refer to SWPM 20-90-11 as an accepted procedure. (a) 4 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 3
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure.
NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 89K W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68G W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68H W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 69K W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68F W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68K W0176 The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACC47ER1 CONTACT, SOCKET 1 BACC47CN1S CONTACT, PIN 2 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11

FIGURE 18: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 95 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThis Figure applies only to: Group 2-3.

Reference : 767 WDM 21-58-16 NOTE:The parts are in Wire Kit 289T1169-108. The wire is identified as 289T1169-108W. 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 20-81-19 as an accepted procedure. (a) 4 BACC47ER1 CONTACT, SOCKET 1
Refer to SWPM 20-61-11 as an accepted procedure. (a) 5 BACC47CN1S CONTACT, PIN 2

FIGURE 19: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 96 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTMore Data Qty Identification Name Flag Note Refer to SWPM 20-90-11 as an accepted procedure. (a) 4 M39029/11-145 CONTACT, PIN, CRIMPREMOVABLE, PER MIL-C39029/11 3
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure.
NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 89K W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68G W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68H W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 45 PK 24 69K W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68F W0176 BMS 13-48, TYPE 11, CLASS 1, AWG 24 60 PK 24 68K W0176 The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 1 BACC47ER1 CONTACT, SOCKET 1 BACC47CN1S CONTACT, PIN 2 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11

FIGURE 19: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 97 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 20: FDARS RELAY INSTALLATION IN P36 (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 98 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 20: FDARS RELAY INSTALLATION IN P36 (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 99 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure. More Data Qty Identification Name Task Step K10725 Near Side, (a) 1 BACT19J4 TAPE, ID Install (New) 1 D20325 Far Side, (a) 1 BACT19J4 TAPE, ID Install (New) Alternate part number TDH1852-3002 1 TDH-1852-3002 TIME DELAY RELAY Install (New) 2 K10723 Near Side, (a) 1 BACT19J4 TAPE, ID Install (New) 3 D20323 Far Side, (a) 1 BACT19J4 TAPE, ID Install (New)
1 BACR13CD2 RELAY Install (New) 4 17 1 BAC27TEX4697 VINYL MARKER (1 2 3...30) VERTICAL Install (New) 5 (a) Mark the ID tape with this ID. Refer to SOPM 20-50-10 as an accepted procedure.

FIGURE 20: FDARS RELAY INSTALLATION IN P36 (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 100 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTThe parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 2 BACT19J4 TAPE, ID

FIGURE 20: FDARS RELAY INSTALLATION IN P36 (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 101 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 1 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 102 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 2 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 103 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 3 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 104 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 4 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 105 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 5 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 106 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 6 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 107 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 7 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 108 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure. More Data Qty Identification Name Task Step W0756 1 829A9001-2 LACING TAPE - RED - PRESSURIZED (TEMP 135 DEG) Install (New) 1

2 411A4902-7 RETAINER CLIP ASSY Install (New) 2

FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE (SHEET 8 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 109 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36 (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 110 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36 (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 111 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36 (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 112 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERTFIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36 (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 113 of 114 BOEING SERVICE BULLETIN 767-21A0247 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 this figure. More Data Qty Identification Name Task Step W0176 1 829A9001-2 LACING TAPE - RED - PRESSURIZED (TEMP 135 DEG) Install (New) 1

W0184 1 829A9001-5 LACING TAPE - BLUE - PRESSURIZED (TEMP 135 DEG) Install (New) 2

FIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36 (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 10, 2011 767-21A0247 Revision 1 April 09, 2013 114 of 114 BOEING SERVICE BULLETIN 767-21A0247 ALERT ALERT