### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-78A2184**  Original Issue: January 12, 2010 Revision 1: December 23, 2010 ATA System: 7834 **SUBJECT:** EXHAUST (PW4000 Series Engines) - Thrust Reverser Control System - Automatic Leading Edge Flap Retraction System Wiring Change Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 1 of 33 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 2 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 16 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 17 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 18 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 FIGURE 1: NO.1 AND NO.2 ENGINE THRUST REVERSER CONTROL WIRING - P252 PANEL ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 2: NO.1 AND NO.2 ENGINE THRUST REVERSER CONTROL WIRING, P252 PANEL - CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 FIGURE 3: NO.3 AND NO.4 ENGINE THRUST REVERSER CONTROL WIRING - P253 PANEL ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 FIGURE 4: NO.3 AND NO.4 ENGINE THRUST REVERSER CONTROL WIRING, P253 PANEL - CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 3 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 4 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Revision Transmittal Sheet**  **Number: 747-78A2184** Original Issue: January 12, 2010 Revision 1: December 23, 2010 ATA System: 7834 **SUBJECT:** EXHAUST (PW4000 Series Engines) - Thrust Reverser Control System - Automatic Leading Edge Flap Retraction System Wiring Change This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-064-AD is related to this service bulletin. No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. **REASON FOR REVISION** This revision is sent to change the functional test in the work instructions to give a better sequence and to better describe the use of pneumatic and electrical power during its accomplishment. These sections are changed: – Summary Manpower and Paragraph 1.G., Manpower; Changed to show adjusted functional test hours. – Summary Compliance and Paragraph 1.E., Compliance; Changed to add FAA NPRM. – Paragraph 2.C.2., Part and Material Supplied by the Operator; Changed to add supplier information for a part. – Paragraph 1.J.1., Existing Data; SWPM, AMM and FAA NPRM references added. – Paragraph 3.B., Work Instructions; Tasks added and sequence changed. – Figure 2 and 4; SWPM references added for the disassembly of equipment related to this change. The data given in Information Notice 747-78A2184 IN 01 is included in this revision. 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** January 12, 2010 Original Issue: December 23, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 5 of 33BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 6 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Summary**  **Number: 747-78A2184** Original Issue: January 12, 2010 Revision 1: December 23, 2010 ATA System: 7834 **SUBJECT:** EXHAUST (PW4000 Series Engines) - Thrust Reverser Control System - Automatic Leading Edge Flap Retraction System Wiring 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 prevent the Group A Leading Edge (LE) flaps from automatically retracting if the Flap Control Unit (FCU) receives dual cowl unstowed indications from the thrust reversers. If this service bulletin is not done, the Group A LE flaps can automatically retract if the FCU gets dual cowl unstowed indications from the thrust reverser which could result in decreased climb performance of the airplane during takeoff. During takeoff roll, an operator of a Rolls-Royce RB211 powered 747-400 airplane had a REV Amber indication occurrence on the No.3 engine thrust reverser. This was followed thirteen seconds later by a REV Amber indication on the No.2 engine thrust reverser. At the time of the second REV amber, the aircraft was beyond V1. To prevent impingement from the thrust reversers, the FCU of the 747-400 is designed to automatically retract the Group A LE flaps when a REV Amber signal is transmitted from the two inboard or the two outboard thrust reversers and the aircraft is on the ground. The FCU performed as designed, and retracted the Group A leading edge flaps. After takeoff, the air/ground logic took over and the Group A LE flaps re-deployed. During the event, the flight crew reported buffeting and momentary stick shaker activation. The aircraft jettisoned fuel and returned to the airport with a usual landing. All four thrust reversers deployed and stowed normally after landing. The automatic LE flap retraction logic for PW4000 engines automatically retracts the Group A LE flaps during reverse thrust operation. This is to prevent thrust reverser efflux air from impinging onto the Group A LE flaps to improve the Group A LE flap panel’s structural life. This function is armed when the airplane is on the ground. The Group A LE flaps retract when the FCU gets a signal from the LE Flap relay in the reverser circuitry on the two inboard engines or the two outboard engines. The LE Flap relay is energized by the microswitch of the reverse thrust lever or the unstow proximity sensor on the thrust reverser cowl. The initial signal to the FCU comes from the microswitch in the aisle stand when thrust reverser deployment is commanded. The signal to the FCU is kept after stow is commanded by the proximity switches. This signal is removed 5 seconds after the thrust reverser is stowed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 7 of 33The Group A LE flaps retract (or extend) in ten seconds. Once auto-retracted, there is a five second time delay after the thrust reverser signal is removed from the FCU before the Group A LE flaps return to the commanded position. The thrust reverser extends in two seconds and stows in three seconds. This time can slightly increase during cold weather operation. Accomplishment of this service bulletin will remove the thrust reverser unstow signal from the FCU. The timing of the thrust reverser stow versus the time delay in the FCU accomplishes the original intent of the design. The thrust reversers are fully stowed prior to the FCU time delay lapsing and Group A LE flap movement starting. The signal from the thrust reverser lever will not be affected by this change, but the CMC message, "ENG X AUTO RESTOW EVENT" will be permanently inhibited. Instead, if there is an auto restow event on an airplane the "ENG X PRESSURE SWITCH FAIL" message will be set. Boeing Service Related Problem (SRP) 747-SRP-78-0069 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD 78-09002 is related to this service bulletin. **ACTION (PRR 85665-R)** Get access to the P252 and P253 Thrust Reverser Relay panels in the Electrical and Electronics Compartment. Make wiring changes in the panels to wires related to the thrust reverser control system of the No.1 thru No.4 engines. Do tests of the thrust reverser control and the Group A Leading Edge (LE) flap systems. **EFFECTIVITY** 747-400/400F Airplanes powered by PW4000 engines. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-064-AD is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 36 months after the original issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  6.80 11.30 Group 1
**MATERIAL INFORMATION** Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 8 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 9 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 10 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-78A2184**  Original Issue: January 12, 2010 Revision 1: December 23, 2010 ATA System: 7834 **SUBJECT:** EXHAUST (PW4000 Series Engines) - Thrust Reverser Control System - Automatic Leading Edge Flap Retraction System Wiring 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 D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. Refer to PRR 85665-R for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 747-400/400F airplanes with Pratt & Whitney (PW) 4000 series engines. - 1

Airplane Models: 747-400, 747-400F **Group Variable Number**  1 RL431 - RL436 1 RL451 - RL456 1 RL491 - RL492 1 RL501 - RL502 1 RL581 - RL586

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 11 of 33**Group Variable Number**  1 RL751 - RL752 1 RM011 - RM013 1 RM021 - RM024 1 RM036 - RM045 1 RM091 1 RM166 - RM177 1 RM241 - RM246 1 RM341 1 RM366 - RM367 1 RM811 - RM813 1 RM851 - RM855 1 RM871 - RM880 1 RR851 - RR856 1 RR861 - RR862 1 RT031 - RT035 1 RT061 1 RT101 - RT103 1 RT401 - RT412 1 RT501 - RT530 1 RT571 - RT590 1 RT601 - RT640 1 RT743 - RT750 1 RT811 - RT814 1 RT831 - RT837 1 RT876 - RT880 1 RU001 - RU006 1 RU016 - RU017 1 RU081 - RU083 2. Spares Affected None. **B. Concurrent Requirements** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 12 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT C. Reason**  This service bulletin is sent to prevent the Group A Leading Edge (LE) flaps from automatically retracting if the Flap Control Unit (FCU) receives dual cowl unstowed indications from the thrust reversers. If this service bulletin is not done, the Group A LE flaps can automatically retract if the FCU gets dual cowl unstowed indications from the thrust reverser which could result in decreased climb performance of the airplane during takeoff. During takeoff roll, an operator of a Rolls-Royce RB211 powered 747-400 airplane had a REV Amber indication occurrence on the No.3 engine thrust reverser. This was followed thirteen seconds later by a REV Amber indication on the No.2 engine thrust reverser. At the time of the second REV amber, the aircraft was beyond V1. To prevent impingement from the thrust reversers, the FCU of the 747-400 is designed to automatically retract the Group A LE flaps when a REV Amber signal is transmitted from the two inboard or the two outboard thrust reversers and the aircraft is on the ground. The FCU performed as designed, and retracted the Group A leading edge flaps. After takeoff, the air/ground logic took over and the Group A LE flaps re-deployed. During the event, the flight crew reported buffeting and momentary stick shaker activation. The aircraft jettisoned fuel and returned to the airport with a usual landing. All four thrust reversers deployed and stowed normally after landing. The automatic LE flap retraction logic for PW4000 engines automatically retracts the Group A LE flaps during reverse thrust operation. This is to prevent thrust reverser efflux air from impinging onto the Group A LE flaps to improve the Group A LE flap panel’s structural life. This function is armed when the airplane is on the ground. The Group A LE flaps retract when the FCU gets a signal from the LE Flap relay in the reverser circuitry on the two inboard engines or the two outboard engines. The LE Flap relay is energized by the microswitch of the reverse thrust lever or the unstow proximity sensor on the thrust reverser cowl. The initial signal to the FCU comes from the microswitch in the aisle stand when thrust reverser deployment is commanded. The signal to the FCU is kept after stow is commanded by the proximity switches. This signal is removed 5 seconds after the thrust reverser is stowed. The Group A LE flaps retract (or extend) in ten seconds. Once auto-retracted, there is a five second time delay after the thrust reverser signal is removed from the FCU before the Group A LE flaps return to the commanded position. The thrust reverser extends in two seconds and stows in three seconds. This time can slightly increase during cold weather operation. Accomplishment of this service bulletin will remove the thrust reverser unstow signal from the FCU. The timing of the thrust reverser stow versus the time delay in the FCU accomplishes the original intent of the design. The thrust reversers are fully stowed prior to the FCU time delay lapsing and Group A LE flap movement starting. The signal from the thrust reverser lever will not be affected by this change, but the CMC message, "ENG X AUTO RESTOW EVENT" will be permanently inhibited. Instead, if there is an auto restow event on an airplane the "ENG X PRESSURE SWITCH FAIL" message will be set. Boeing Service Related Problem (SRP) 747-SRP-78-0069 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD 78-09002 is related to this service bulletin. Revision 1 is sent to change the functional test in the work instructions to give a better sequence and to better describe the use of pneumatic and electrical power during its accomplishment. The data given in Information Notice 747-78A2184 IN 01 is included in Revision 1.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 13 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT D. Description**  Get access to the P252 and P253 Thrust Reverser Relay panels in the Electrical and Electronics Compartment. Make wiring changes in the panels to wires related to the thrust reverser control system of the No.1 thru No.4 engines. Do tests of the thrust reverser control and the Group A Leading Edge (LE) flap systems. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 117, 118 747-400, 747-400F **E. Compliance** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-064-AD is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 36 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 14 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.75 0.75 1 Open Access

- FIGURE 1 (Wire Routing Only) 0.40 0.40 1 FIGURE 2

- FIGURE 3 (Wire Routing Only) 0.40 0.40 1 FIGURE 4 0.75 0.75 1 Close Access 4.50 9.00 2 Test 6.80 11.30 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None. **I. Electrical Load Data** None. **J. References** 1. Existing Data a. Engineering Change Memo PRR 85665-R. b. Boeing Service Related Problem (SRP) 747-SRP-78-0069. c. Boeing Standard Wiring Practices Manual (SWPM) 20-00-11, 20-10-11, 20-10-12, 20-10-14, 20-10-19, 20-30-16, 20-81-12, 20-90-11. d. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2010-NM-064-AD. e. 747 Fleet Team Digest (FTD) 747 FTD 78-09002. f. 747-400 Aircraft Maintenance Manual (AMM) 06-09-09, 24-22-00, 27-62-00, 27-81-00, 36-00-00, 54-62-00, 71-11-04, 78-31-00, 78-34-05, 78-34-13, 78-36-07. g. 747-400 Wiring Diagram Manual (WDM) 78-34-12, 78-34-22, 78-34-32, 78-34-42. 2. Data supplied with this Service Bulletin None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 15 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  PANEL INSTL P252 AND P253 284U4255 This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  78-34 747 Wiring Diagram Manual 71-00 747 Fault Isolation Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary. **L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 16 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. The parts 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 the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Mail to: Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) Insulation Tubing, Heat Shrinkable, Flexible, Adhesive Lined (3/16 Inch Dia., 0.75 Inch Length) 4 DWP-125-3/16-0

(b) End Cap 8 BACT63D2 (a) Refer to Boeing Standard Wiring Practices Manual SWPM 20-00-11 for material and supplier information. (b) Refer to Paragraph 2.A., Material - Price and Availability for procurement information.
3. Parts Modified and Reidentified None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 17 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**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** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 18 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION CAUTION:**  KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 5. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 6. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 7. 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. 8. 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. In the Flight Compartment, open the circuit breakers specified in the table below and attach DO-NOT-CLOSE tags: **MAIN POWER DISTRIBUTION PANEL**
**Number Name**  **Location Panel Number**  C10934 T/R LOCK CONT ENG 1 F11 P6

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 19 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT MAIN POWER DISTRIBUTION PANEL** 
**Number Name**  **Location Panel Number**  C00405 T/R IND ENG 1 F12 P6 C01703 T/R CONT ENG 1 F13 P6 C10935 T/R LOCK CONT ENG 2 E11 P6 C00402 T/R IND ENG 2 E12 P6 C01704 T/R CONT ENG 2 or ENG 2, T/R CONT E13 P6 C10936 T/R LOCK CONT ENG 3 D11 P6 C00403 T/R IND ENG 3 D12 P6 C01442 T/R CONT ENG 3 D13 P6 C10937 T/R LOCK CONT ENG 4 C11 P6 C00404 T/R IND ENG 4 C12 P6 C01441 T/R CONT ENG 4 or ENG 4, T/R CONT C13 P6 2. Get access to the P252 and P253 thrust reverser relay panels in the Electrical and Electronics Compartment. Refer to 747-400 AMM 78-36-07 for the location of the relay panels. 3. Change the thrust reverser control wiring in the P252 and P253 thrust reverser relay panels for each engine in accordance with: **Figure Engine**  FIGURE 1 and FIGURE 2 No.1 and No.2 FIGURE 3 and FIGURE 4 No.3 and No.4 4. In the Flight Compartment, remove the DO-NOT-CLOSE tags and close the circuit breakers specified in the table below: **MAIN POWER DISTRIBUTION PANEL**
**Number Name**  **Location Panel Number**  C10934 T/R LOCK CONT ENG 1 F11 P6 C00405 T/R IND ENG 1 F12 P6 C01703 T/R CONT ENG 1 F13 P6 C10935 T/R LOCK CONT ENG 2 E11 P6 C00402 T/R IND ENG 2 E12 P6 C01704 T/R CONT ENG 2 or ENG 2, T/R CONT E13 P6 C10936 T/R LOCK CONT ENG 3 D11 P6 C00403 T/R IND ENG 3 D12 P6

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 20 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT MAIN POWER DISTRIBUTION PANEL** 
**Number Name**  **Location Panel Number**  C01442 T/R CONT ENG 3 D13 P6 C10937 T/R LOCK CONT ENG 4 C11 P6 C00404 T/R IND ENG 4 C12 P6 C01441 T/R CONT ENG 4 or ENG 4, T/R CONT C13 P6 5. Close access to the P252 and P253 relay panels. **WARNING:** MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LEADING EDGE (LE), TRAILING EDGE (TE) FLAPS AND FLAP DRIVE MECHANISMS BEFORE THE FLAP CONTROL LEVER IS MOVED. WITH HYDRAULIC POWER REMOVED, THE FLAPS WILL MOVE AUTOMATICALLY BY ELECTRICAL POWER WHEN THE FLAP CONTROL LEVER IS MOVED. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. 6. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 7. Do the functional test as follows: a. In the Flight Compartment, make sure the applicable engine START and ENGINE BLEED switches, on the overhead panel, are in the OFF position. b. In the Flight Compartment, make sure the reverse thrust lever is in the forward thrust position. c. Do the 'Automatic Speed Brake System Deactivation'. Refer to 747-400 AMM 27-62-00 as an accepted procedure. **WARNING:** MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE FLAPS AND CONTROL SURFACES BEFORE PNEUMATIC POWER IS SUPPLIED. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE EQUIPMENT. d. Make sure the Leading Edge (LE) flaps are retracted. Refer to 747-400 AMM 27-81-00 as an accepted procedure. **NOTE:** If this task is accomplished by pneumatic power, it is not necessary to remove pneumatics from the airplane at the end of the procedure. e. In the Flight Compartment, open the circuit breakers specified in the table below and attach DO-NOT-CLOSE tags: **MAIN POWER DISTRIBUTION PANEL**
**Number Name**  **Location Panel Number**  C10934 T/R LOCK CONT ENG 1 F11 P6 C01703 T/R CONT ENG 1 F13 P6 C10935 T/R LOCK CONT ENG 2 E11 P6

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 21 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT MAIN POWER DISTRIBUTION PANEL** 
**Number Name**  **Location Panel Number**  C01704 T/R CONT ENG 2 or ENG 2, T/R CONT E13 P6 C10936 T/R LOCK CONT ENG 3 D11 P6 C01442 T/R CONT ENG 3 D13 P6 C10937 T/R LOCK CONT ENG 4 C11 P6 C01441 T/R CONT ENG 4 or ENG 4, T/R CONT C13 P6 f. Make sure pneumatic power is supplied to the airplane. Refer to 747-400 AMM 36-00-00 as an acceptable procedure. g. Remove the access doors on the No.1 thru No.4 engine nacelle struts. Refer to 747-400 AMM 54-62-00 as an accepted procedure. h. Open the access panels specified in the table below. Refer to 747-400 AMM 06-09-09.
**Name/Location Access Panel / Door**  **No.** ACCESS DOOR - THRUST REVERSER ISOLATION VALVE 451BL
THRUST REVERSER ISOLATION VALVE, UPPER MIDSPAR, SPRING BEAM GREASE FITTING, PRESSURE RELIEF (AFT) 462EL

THRUST REVERSER ISOLATION VALVE, UPPER MIDSPAR, SPRING BEAM GREASE FITTING, PRESSURE RELIEF (AFT) 472EL

ACCESS DOOR - CORE COWL TO STRUT (AFT) 481BL i. Deactivate the isolation valves for the No.1 thru No.4 engines as follows. Refer to 747-400 AMM 78-34-05 for the location of the isolation valves. (1) Push the deactivation slide into the isolation valve housing. (2) Install a streamered pin in the deactivation slide. (3) Install a hitch pin the streamered pin. **NOTE:** Use a ground lock, SPL-5635, where necessary. j. Open the bypass valve (of the isolation valve) for the No.1 thru No.4 engines as follows. Refer to 747-400 AMM 78-34-05 for the location of the bypass valves.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 22 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT NOTE:**  The bypass valve must be open before you manually extend or retract the thrust reverser. This will prevent a hydraulic lock, which can prevent the movement of the thrust reverser. But the bypass valve must be closed again if thrust reverser components or hydraulic tubes are removed (after you extend or retract the thrust reverser). If the bypass valve is not closed again, hydraulic fluid leakage will occur when the components or tubing are removed. (1) Remove the lockwire, if applicable, on the bypass valve lever. **NOTE:** There are two types of bypass valves, one that has a spring that controls the position of the lever, and one that does not have a spring. Lockwire is not installed on bypass valve levers that have a spring. (2) Push in the bypass valve lever to open the bypass valve of the isolation valve. (3) Install a streamered pin to hold the bypass valve lever in the open position. (4) Install a hitch pin in the streamered pin. **NOTE:** Use a ground lock, SPL-5635, where necessary. k. After the deactivation procedure is completed, make sure the REMOVE-BEFORE-FLIGHT streamers can be seen outside of the No.1 thru No.4 engine nacelle struts. l. Open the left or right fan cowl panels on the No.1 thru No.4 engines. Refer to 747-400 AMM 71-11-04 as an accepted procedure. **NOTE:** Open and unlock the applicable sleeve. It is only necessary to manually deploy one sleeve for each engine to complete this functional test. **CAUTION:** DO NOT USE A SCREWDRIVER BETWEEN THE LOCK PROXIMITY SENSOR AND THE TARGET TO MOVE THE LOCK LEVER TO THE UNLOCKED POSITION. IF A SCREWDRIVER OR OTHER TOOL IS USED TO SUPPLY A SEPARATION FORCE, DAMAGE CAN BE CAUSED TO THE LOCK PROXIMITY SENSOR OR THE TARGET. m. On the No.1 thru No.4 engines, move the lock lever on the left or right locking actuator away from the sensor. Refer to 747-400 AMM 78-31-00 for the location of the locking actuators. **NOTE:** If the lock lever does not move easily, turn the manual crank counter-clockwise to relieve pressure on the actuator locks. n. In the Flight Compartment, remove the DO-NOT-CLOSE tags and close the circuit breakers specified in the tables below: **MAIN POWER DISTRIBUTION PANEL**
**Number Name**  **Location Panel Number**  C10934 T/R LOCK CONT ENG 1 F11 P6 C01703 T/R CONT ENG 1 F13 P6

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 23 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT MAIN POWER DISTRIBUTION PANEL** 
**Number Name**  **Location Panel Number**  C10935 T/R LOCK CONT ENG 2 E11 P6 C01704 T/R CONT ENG 2 or ENG 2, T/R CONT E13 P6 C10936 T/R LOCK CONT ENG 3 D11 P6 C01442 T/R CONT ENG 3 D13 P6 C10937 T/R LOCK CONT ENG 4 C11 P6 C01441 T/R CONT ENG 4 or ENG 4, T/R CONT C13 P6
**OVERHEAD CIRCUIT BREAKER PANEL**
**Number Name**  **Location Panel Number**  C10263 FLT CONT ELEC 2L-AC C10 P7 C10264 FLT CONT ELEC 2L-DC C11 P7 C08782 FLT CONT ELEC 1L-AC C12 P7 C08783 FLT CONT ELEC 1L-DC C13 P7 C08784 FLT CONT ELEC 1R-AC C14 P7 C08785 FLT CONT ELEC 1R-DC C15 P7 C10265 FLT CONT ELEC 2R-AC C16 P7 C10266 FLT CONT ELEC 2R-DC C17 P7
**CAUTION:** ONLY EXTEND OR RETRACT THE FLAPS ELECTRICALLY ONCE IN A FIVE MINUTE PERIOD TO PREVENT OVERHEATING OF THE MOTOR. o. In the Flight Compartment, move the flap control lever to the 1-unit detent to extend the LE flaps.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 24 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT WARNING:**  MAKE SURE PERSONS AND EQUIPMENT ARE CLEAR OF THE LE FLAPS BEFORE THE THRUST REVERSER SLEEVES ARE MOVED MANUALLY. **CAUTION:** DO NOT MOVE THE THRUST REVERSER WHILE THE THRUST REVERSER OR THE CORE COWL PANELS ARE OPEN. DAMAGE TO THE THRUST REVERSER AND THE CORE COWL PANELS CAN OCCUR. **CAUTION:** DO NOT EXTEND THE THRUST REVERSER SLEEVE WHEN THE THRUST REVERSER IS OPEN MORE THAN 23 DEGREES. DAMAGE TO THE SLEEVE AND THE STRUT CAN OCCUR. **CAUTION:** THE EXTENSION OF THE SLEEVE WITH THE THRUST REVERSER OPEN IS PERMITTED IN THE 23 DEGREE POSITION ONLY. THE CORE COWL PANELS MUST BE REMOVED TO EXTEND THE SLEEVE WITH THE THRUST REVERSER OPEN. **CAUTION:** MAKE SURE THERE IS NO EQUIPMENT IN THE AREA BEHIND THE THRUST REVERSER. DAMAGE CAN OCCUR IF THE THRUST REVERSER HITS THE EQUIPMENT. **CAUTION:** MAKE SURE THE MANUAL DRIVE IS FULLY ENGAGED WITH THE SYNC LOCK DRIVE SHAFT BEFORE IT IS TURNED. DO NOT USE FORCE TO ENGAGE THE MANUAL DRIVE. ALSO, MAKE SURE THE MANUAL DRIVE STAYS FULLY ENGAGED WHILE THE SQUARE DRIVE IS OPERATED. IF THE MANUAL DRIVE IS NOT FULLY ENGAGED OR IF FORCE IS USED TO ENGAGE IT, DAMAGE TO THE SYNC LOCK CAN OCCUR. p. Do the test as follows for the position of the Group A LE flaps during the reverse thrust operation of the inboard engines: (1) Manually extend the left or right sleeve on the No.2 and No.3 engine thrust reversers as follows. Refer to 747-400 AMM 78-34-13 for the location of the sync lock. (a) Put a 3/8 inch square drive into the end of the manual drive mechanism on the sync lock:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 25 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**1) The square drive must be pushed in until it stops and held in that position to manually disengage the synch lock and engage the manual drive shaft. 2) Make small position adjustments of the manual drive as necessary to align it with the sync lock drive shaft. 3) If a 3/8 inch square drive cannot be inserted, use a 5/8 inch hex drive on the outer hex nut and turn counter-clockwise and clockwise a very small amount until a 3/8 inch square drive can be put in. **CAUTION:** MAKE SURE ALL THE ACTUATORS OPERATE CORRECTLY WHEN THE THRUST REVERSER IS EXTENDED. IF THE FLEXSHAFT BETWEEN THE ACTUATORS IS BROKEN, OR IS NOT INSTALLED, ONLY THE BOTTOM ACTUATOR WILL OPERATE. IF THRUST REVERSER OPERATION CONTINUES WITH THIS CONDITION, DAMAGE TO THE THRUST REVERSER CAN OCCUR. (b) At the same time as the sync lock is kept disengaged, turn the square drive to extend the applicable thrust reverser sleeve to between 0.5 and 2.0 inches: 1) Make sure the square drive is turned in the direction that extends the thrust reverser sleeve: a) For the left sleeve, turn the manual drive counter-clockwise. b) For the right sleeve, turn the manual drive clockwise. (2) Make sure the LE flaps do not retract. (3) Manually return the No.2 and No.3 engine thrust reversers to the stowed position. (a) Make sure the square drive is turned in the direction that retracts the thrust reverser sleeve. 1) For the left sleeve, turn the manual drive clockwise. 2) For the right sleeve, turn the manual drive counter-clockwise. q. Do the test as follows for the position of the Group A LE flaps during the reverse thrust operation of the outboard engines: (1) Manually extend the left or right sleeve on the No.1 and No.4 engine thrust reversers as follows. Refer to 747-400 AMM 78-34-13 for the location of the sync lock. (a) Put a 3/8 inch square drive into the end of the manual drive mechanism on the sync lock:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 26 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**1) The square drive must be pushed in until it stops and held in that position to manually disengage the synch lock and engage the manual drive shaft. 2) Make small position adjustments of the manual drive as necessary to align it with the sync lock drive shaft. 3) If a 3/8 inch square drive cannot be inserted, use a 5/8 inch hex drive on the outer hex nut and turn counter-clockwise and clockwise a very small amount until a 3/8 inch square drive can be put in. **CAUTION:** MAKE SURE ALL THE ACTUATORS OPERATE CORRECTLY WHEN THE THRUST REVERSER IS EXTENDED. IF THE FLEXSHAFT BETWEEN THE ACTUATORS IS BROKEN, OR IS NOT INSTALLED, ONLY THE BOTTOM ACTUATOR WILL OPERATE. IF THRUST REVERSER OPERATION CONTINUES WITH THIS CONDITION, DAMAGE TO THE THRUST REVERSER CAN OCCUR. (b) At the same time as the sync lock is kept disengaged, turn the square drive to extend the applicable thrust reverser sleeve to between 0.5 and 2.0 inches: 1) Make sure the square drive is turned in the direction that extends the thrust reverser sleeve: a) For the left sleeve, turn the manual drive counter-clockwise. b) For the right sleeve, turn the manual drive clockwise. (2) Make sure the LE flaps do not retract. (3) Manually return the No.1 and No.4 engine thrust reversers to the stowed position: (a) Make sure the square drive is turned in the direction that retracts the thrust reverser sleeve: 1) For the left sleeve, turn the manual drive clockwise. 2) For the right sleeve, turn the manual drive counter-clockwise. r. Put the LE flaps back to the normal stowed position. s. Do the 'Thrust Reverser Activation After Ground Maintenance' for the No.1 thru No.4 engines. Refer to 747-400 AMM 78-31-00 as an accepted procedure. t. Do the 'Automatic Speed Brake System Reactivation'. Refer to 747-400 AMM 27-62-00 as an accepted procedure. u. Do the 'Group A Leading Edge Flaps during Reverse Thrust Operation - Operational Test'. Refer to 747-400 AMM 27-81-00 as an accepted procedure. v. Do the 'Thrust Reverser Operational Test'. Refer to 747-400 AMM 78-31-00 as an accepted procedure. 8. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1: December 23, 2010 27 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT FIGURE 1: NO.1 AND NO.2 ENGINE THRUST REVERSER CONTROL WIRING - P252 PANEL ROUTING**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1 December 23, 2010 28 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT FIGURE 1: NO.1 AND NO.2 ENGINE THRUST REVERSER CONTROL WIRING - P252 PANEL ROUTING**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1 December 23, 2010 29 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**REFERENCE: 747-400 WDM 78-34-12, 747-400 WDM 78-34-22. 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 20-30-16 as an accepted procedure. (a) 4 BACT63D2 END CAP 1

Refer to SWPM 20-10-14 as an accepted procedure. 2 DWP-125-3/16-0 INSULATION TUBING, HEAT SHRINKABLE, FLEXIBLE, ADHESIVE LINED (3/16 INCH DIA., 0.75 INCH LENGTH) 2

(a) Refer to SWPM 20-81-12 as an accepted procedure for the disassembly of the DR7311 and DR7312 relay sockets. Refer to SWPM 20-90-11 as an accepted procedure for the disassembly of the TD17 and TD18 terminal blocks.

**FIGURE 2: NO.1 AND NO.2 ENGINE THRUST REVERSER CONTROL WIRING, P252 PANEL - CHANGE (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1 December 23, 2010 30 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT FIGURE 3: NO.3 AND NO.4 ENGINE THRUST REVERSER CONTROL WIRING - P253 PANEL ROUTING**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1 December 23, 2010 31 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT FIGURE 3: NO.3 AND NO.4 ENGINE THRUST REVERSER CONTROL WIRING - P253 PANEL ROUTING**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1 December 23, 2010 32 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**REFERENCE: 747-400 WDM 78-34-32, 747-400 WDM 78-34-42. 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 20-30-16 as an accepted procedure. (a) 4 BACT63D2 END CAP 1

Refer to SWPM 20-10-14 as an accepted procedure. 2 DWP-125-3/16-0 INSULATION TUBING, HEAT SHRINKABLE, FLEXIBLE, ADHESIVE LINED (3/16 INCH DIA., 0.75 INCH LENGTH) 2

(a) Refer to SWPM 20-81-12 as an accepted procedure for the disassembly of the DR7313 and DR7314 relay sockets. Refer to SWPM 20-90-11 as an accepted procedure for the disassembly of the TD19 and TD20 terminal blocks.

**FIGURE 4: NO.3 AND NO.4 ENGINE THRUST REVERSER CONTROL WIRING, P253 PANEL - CHANGE (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 12, 2010 747-78A2184 Revision 1 December 23, 2010 33 of 33 **BOEING SERVICE BULLETIN 747-78A2184 ALERT**  **ALERT**