### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-21A0254 Original Issue: June 07, 2013 ATA System: 2158 SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief System (FDARS) and Activation of 3-way Valve 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 © 2013 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: June 07, 2013 767-21A0254 1 of 67 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 2 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT

BLANK PAGETable of Contents Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. Airplanes............................................. 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 B. Concurrent Requirements....................................... 9 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 13 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 13 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 13 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 19 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 20 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 FIGURE 1: EXISTING DUCT REPLACEMENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION. . . . . . . . . . . . . . . . . . . . . 29 FIGURE 3: WIRE DELETION IN PANEL P50. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 FIGURE 4: WIRE DELETION BETWEEN PANEL P36 AND PANEL P50. . . . . . . . . . . . . . . . 37 FIGURE 5: WIRE AND CONNECTOR ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM) . 40 FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM) . . . . . . . . . . . . . . . . . . . . . . 43 FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36. . . . . . . . . . . . . . . . . . . . 46 FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT. . . . . . . . . . . . 50 FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36. . . . . . . . . . . . . . . . . . . . . . . 58

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 3 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL. . . . . . . . . . . . . . . . . . . . . . . . 64 FIGURE 12: DIODE WIRE CONNECTION AT E8 EICAS PANEL. . . . . . . . . . . . . . . . . . . . . 67

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 4 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT

### Commercial Airplanes 

# 767 Service Bulletin ALERT Summary Number: 767-21A0254 Original Issue: June 07, 2013 ATA System: 2158 SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief System (FDARS) and Activation of 3-way Valve 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 None. 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 can result in 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: June 07, 2013 767-21A0254 5 of 67The changes described above were implemented in the affected airplanes during production but were found to cause unacceptable airflow noise on the flight deck when transitioning 10,000 feet altitude. This increased noise made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Because a solution to reduce airflow noise in the flight deck was not immediately available, the 3-way valve logic changes and 10,000 foot altitude switch were deactivated before airplane delivery. The noise is resolved by adding a Flight Deck Air Relief System (FDARS) consisting of ducting, an outlet valve, and related wiring, relays, and diodes. Airflow noise is reduced on the flight deck by the outlet valve exhausting a portion of equipment cooling air into the area below the flight deck when the 3-way-valve is activated at 10,000 feet. This service bulletin describes installation of FDARS components and activation of the 10,000 foot altitude switch and related logic changes. Boeing Service Related Problem (SRP) 767-SRP-21-0179 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
ACTION (PRR B12900-260) In the area forward of the main equipment center 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. Modify relay installation in P36. Install diodes in E8 EICAS panel. 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. EFFECTIVITY 767-300F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 6 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTCOMPLIANCE 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 72 months after the original issue 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 31.50 54.95 All MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 7 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 8 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT

### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-21A0254 Original Issue: June 07, 2013 ATA System: 2158 SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief System (FDARS) and Activation of 3-way Valve 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 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 identified below.
- 1
Airplane Models: 767-300F Group Variable Number 1 VT551 - VT552 2. Spares Affected None. B. Concurrent Requirements None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 9 of 67C. 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 can result in 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. The changes described above were implemented in the affected airplanes during production but were found to cause unacceptable airflow noise on the flight deck when transitioning 10,000 feet altitude. This increased noise made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Because a solution to reduce airflow noise in the flight deck was not immediately available, the 3-way valve logic changes and 10,000 foot altitude switch were deactivated before airplane delivery. The noise is resolved by adding a Flight Deck Air Relief System (FDARS) consisting of ducting, an outlet valve, and related wiring, relays, and diodes. Airflow noise is reduced on the flight deck by the outlet valve exhausting a portion of equipment cooling air into the area below the flight deck when the 3-way-valve is activated at 10,000 feet. This service bulletin describes installation of FDARS components and activation of the 10,000 foot altitude switch and related logic changes. Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin. D. Description In the area forward of the main equipment center 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. Modify relay installation in P36. Install diodes in E8 EICAS panel. 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).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 10 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTThe work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance Zones Zone Model 117, 118, 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 72 months after the original issue date of this service bulletin. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. Elapsed Hours Task Hours Number of Persons Task 0.50 1.00 2 Open Access 2.00 2.00 1 FIGURE 1 3.10 3.10 1 FIGURE 2 0.10 0.10 1 FIGURE 3 0.10 0.10 1 FIGURE 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 11 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTElapsed Hours Task Hours Number of Persons Task 12.35 24.70 2 FIGURE 5 (Wire Dia- gram) and FIGURE 9 (Wire Installation) 8.60 17.20 2 FIGURE 6 and FIG-URE 7, (Wire Diagrams) and FIGURE 10, (Wire Installation) 1.00 1.00 1 FIGURE 8 1.75 1.75 1 FIGURE 11 (DiodeInstallation) and FIGURE 12, (Wire Diagram) 1.50 3.00 2 Test 0.50 1.00 2 Close Access 31.50 54.95 TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +927.9 +6.7 All I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR B12900-260 b. Boeing Service Related Problem (SRP) 767-SRP-21-0179 c. Service Bulletin Index D624T001 d. Standard Overhaul Practices Manual (SOPM) 20-50-10 e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-10, 20-61-11, 20-81-19, 20-81-22, 20-90-11 f. 767 Aircraft Maintenance Manual (AMM) 20-10-33, 21-22-02, 21-58-00, 24-22-00, 25-00-00 g. 767 Wiring Diagram Manual (WDM) 21-58-16, 21-58-41

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 12 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT2. 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 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-Section Publication 21-58 767 Aircraft Maintenance Manual 21-58, Equipment List 767 Wiring Diagram Manual 21-58 767 Fault Isolation Manual 21-22, 21-58 767 Illustrated Parts Catalog 21-58 767 System Schematic 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: June 07, 2013 767-21A0254 13 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 14 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT

BLANK PAGE2. 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 issuedate of this Service Bulletin (US Dollars) ROLT as of the original issuedate of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$16,338.00 308 2 April 30, 2013 TOP KIT - FLIGHT DECK AIR RELIEF SYSTEM 015T1884-1

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 Warranty & Product Assurance Contracts. 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 Material Management. Please refer to this service bulletin number and reference the airplane variable number(s) in your purchase order. The warranty remedies will expire eight years from the original issue date of this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. Figure Kit 11 10 9 8 2 1 Top Kit 1 1 1 1 1 1 015T1884-1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 15 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTTop Kit 015T1884-1 Wire Kit 1 289T1169-1091 289T1169-1101 289T1169-111
ALL KIT 015T1884-1

Notes Existing Part Number Name Figure

New Part Number 11 10 9 8 2 1 Qty (a), (b) STIFFENER

. . . . 1

. 141T1226Y33 DUCT ASSY

. . . . 1

. 214T1120-313 DUCT ASSY

. . . . 1

. 214T1120-315 (c) 214T1120-3218 DUCT ASSY

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

. . . . 1

. 214T3436-1187 (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

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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 16 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTALL KIT 015T1884-1

Notes Existing Part Number Name Figure

New Part Number 11 10 9 8 2 1 Qty 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 2

. . 8

. . 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 TIME DELAY RELAY . . . 1

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

. . TDH-8050-3003P
TERMINAL BLOCKDIODE ASSEMBLY MODULE 2

. . . . . YHLZD-30
(a) This part not used in production.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 17 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTALL KIT 015T1884-1

Notes Existing Part Number Name Figure

New Part Number 11 10 9 8 2 1 Qty (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.
KIT 289T1169-109 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-109W
ID - CONNECTOR 1 289T1169-10301 CONNECTOR, ELECTRICAL, PLUG, STRAIGHT,BAYONET COUPLING 1 BACC45FT12C12S6

(a) CONTACT, SOCK- ET 14 BACC47CP1S (a) CONTACT, PIN 5 BACC47DE7A (a) There are more parts than are necessary.
KIT 289T1169-110 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-110W
ID - CONNECTOR 1 289T1169-10401 ID - CONNECTOR 1 289T1169-10402 ID - DIODE 1 289T1169-10403 (a) CONTACT, PIN 3 BACC47DE7A

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 18 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTKIT 289T1169-110 Notes Name Qty New Part Number (a) CONTACT 3 BACC47DE8A (a) CONTACT, SOCK- ET 4 BACC47DJ1 (a) CONTACT, SOCK- ET 12 BACC47ER1
TERMINAL BLOCK 1 BACM15C3F 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 289T1169-111 Notes Name Qty New Part Number WIRE - RAW MATERIAL 1 289T1169-111W (a) CONTACT, PIN 6 BACC47CN1S (a) CONTACT, SOCK- ET 5 BACC47ER1 (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 The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. Notes Name QTY Part Number / Specification (a) SEALANT 4 oz BMS5-95 (a) PRIMER 4 oz BMS10-11, TYPE I

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 19 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTNotes Name QTY Part Number / Specification (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 None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 20 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly. 7. 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. 8. 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. 9. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 21 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT10. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 11. 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. B. WORK INSTRUCTIONS 1. Remove electrical power. 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 1. 4. Install new Flight Deck Air Relief System (FDARS) components including mounting brackets, ducts, orifice, outlet valve and screen in accordance with FIGURE 2. 5. Modify wiring as follows: a. Delete wire in panel P50 in accordance with FIGURE 3. b. Delete wire between panel P36 and panel P50 in accordance with FIGURE 4. c. Add wires and connector between panel P36 and new valve in accordance with FIGURE 5 (wire diagram) and FIGURE 9 (wire installation). d. Modify wiring within Panel P36 in accordance with FIGURE 6 and FIGURE 7 (wire diagrams) and FIGURE 10 (wire installation). 6. Modify relay installation in panel P36 in accordance with FIGURE 8. 7. Install diodes in accordance with FIGURE 11, (installation) and FIGURE 12, (wire diagram). 8. Restore electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure. 9. Do an Operational Test - Manifold Interconnect Valve (Reconfiguration) - Post SB 767-25-0254. Refer to 767 AMM 21-58-00 as an acceptable procedure. NOTE: This tests operating logic of the existing 3-way-valve (also called the manifold interconnect valve) in conjunction with the new outlet valve. 10. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 22 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 1: EXISTING DUCT REPLACEMENT (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 23 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 1: EXISTING DUCT REPLACEMENT (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 24 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 1: EXISTING DUCT REPLACEMENT (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 25 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 1: EXISTING DUCT REPLACEMENT (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 26 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 214T1120-3218 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 1: EXISTING DUCT REPLACEMENT (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 27 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 1: EXISTING DUCT REPLACEMENT (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 28 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION (SHEET 1 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 29 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 30 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 31 of 67 BOEING SERVICE BULLETIN 767-21A0254 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.

FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION (SHEET 4 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 32 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTMore 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 214T3436-1187 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 2: ADDITIONAL DUCT AND VALVE INSTALLATION (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 33 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 Install (New)
(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 2: ADDITIONAL DUCT AND VALVE INSTALLATION (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 34 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTMore Data Qty Identification Name 2 BACR15FT6KE5C RIVET, UNIVERSAL HD 2 BACR15FT6KE6C RIVET, UNIVERSAL HD 2 BACR15FT6KE7C RIVET 2 NAS1149D0332H WASHER, PLAIN

FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION (SHEET 7 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 35 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTReference : 767 WDM 21-58-16 No parts are installed in this figure.

FIGURE 3: WIRE DELETION IN PANEL P50 (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 36 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTReference : 767 WDM 21-58-16 No parts are installed in this figure.

FIGURE 4: WIRE DELETION BETWEEN PANEL P36 AND PANEL P50 (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 37 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTReference : 767 WDM 21-58-41 NOTE: The parts are in Wire Kit 289T1169-109. The wire is identified as 289T1169-109W. 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 5: WIRE AND CONNECTOR 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: June 07, 2013 767-21A0254 38 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 5: WIRE AND CONNECTOR 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: June 07, 2013 767-21A0254 39 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTReference : 767 WDM 21-58-41

FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM) (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 40 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTNOTE: The parts are in Wire Kit 289T1169-110. The wire is identified as 289T1169-110W. 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) 8 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 (b), Refer to SWPM 20-90-11 as an accepted procedure. 1 BACM15C3F TERMINAL BLOCK 9 (a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11 as an accepted procedure. (b) INSTALL Z BLOCK AT POSITION 21-22 OF TB216
NOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE BMS 13-48, TYPE 11, CLASS 1, AWG 24 16 PK 24 597 W0184 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
FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM) (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 41 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTNOTES MATERIAL SPECIFICATION LENGTH (INCHES) TYPE CODE GAGE COLOR WIRE NUMBER WIRE BUNDLE 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 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 2 BACC47ER1 CONTACT, SOCKET 1 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11

FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM) (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 42 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTReference : 767 WDM 21-58-16

FIGURE 7: WIRE 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: June 07, 2013 767-21A0254 43 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTReference : 767 WDM 21-58-16 NOTE: The parts are in Wire Kit 289T1169-111. The wire is identified as 289T1169-111W. 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 7: WIRE 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: June 07, 2013 767-21A0254 44 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTMore Data Qty Identification Name Flag Note Refer to SWPM 20-90-11 as an accepted procedure. (a) 5 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 1 M39029/11-145 CONTACT, PIN, CRIMP REMOVABLE, PER MIL-C-39029/11

FIGURE 7: WIRE 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: June 07, 2013 767-21A0254 45 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36 (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 46 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36 (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 47 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36 (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 48 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 K10718 Near Side, (a) 1 BACT19J4 TAPE, ID Install (New) 6 D31620 Far Side, (a) - BACT19J4 TAPE, ID Install (New) Alternate part number TDH8050-3003P 1 TDH-8050-3003P TIME DELAY RELAY Install (New) 7
1 BACR13CD2 RELAY Remove 8 D21730 Far Side 1 BACT19J4 TAPE, ID Remove 9 K10355 Near Side 1 BACT19J4 TAPE, ID Remove (a) Mark the ID tape with this ID. Refer to SOPM 20-50-10 as an accepted procedure. The parts shown in the table below are provided as extra parts for this figure. More Data Qty Identification Name 3 BACT19J4 TAPE, ID

FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36 (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 49 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 1 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 50 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 2 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 51 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 3 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 52 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 4 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 53 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 5 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 54 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 6 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 55 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 7 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 56 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 2 411A4902-7 RETAINER CLIP ASSY Install (New) 1 W0756 1 829A9001-2 LACING TAPE - RED - PRESSURIZED (TEMP 135 DEG) Install (New) 2

FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT (SHEET 8 OF 8) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 57 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36 (SHEET 1 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 58 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36 (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 59 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36 (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 60 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36 (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 61 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36 (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 62 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 10: INSTALLATION OF WIRE WITHIN PANEL P36 (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 63 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 64 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTFIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 65 of 67 BOEING SERVICE BULLETIN 767-21A0254 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 Refer to SWPM 20-90-11 as an accepted procedure. 1 YHLZD-30 TERMINAL BLOCK DIODE ASSEMBLY MODULE Install (New) 1
R1196 (a) 1 BACT19J4 TAPE, ID Install (New) 2 Refer to SWPM 20-90-11 as an accepted procedure. 1 YHLZD-30 TERMINAL BLOCK DIODE ASSEMBLY MODULE Install (New) 3
R1197 (a) 1 BACT19J4 TAPE, ID Install (New) 4 (a) Mark the ID tape with this ID. Refer to SOPM 20-50-10 as an accepted procedure.

FIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 66 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERTReference : 767 WDM 21-58-16 No parts are installed in this figure.

FIGURE 12: DIODE WIRE CONNECTION AT E8 EICAS PANEL (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 07, 2013 767-21A0254 67 of 67 BOEING SERVICE BULLETIN 767-21A0254 ALERT ALERT