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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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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 747-78A2184Revision 1: December 23, 2010 1 of 33
4.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 2 of 33 BOEING SERVICE BULLETIN 747-78A2184
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Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 2 B. Concurrent Requirements ...................................... 1 2 C. Reason ................................................ 1 3 D. Description .............................................. 1 4 E. Compliance .............................................. 1 4 F. Approval ............................................... 1 4 G. Manpower .............................................. 1 4 H. Weight and Balance Changes .................................... 1 5 I. Electrical Load Data ......................................... 1 5 J. References .............................................. 1 5
1. Existing Data .......................................... 1 5
2. Data supplied with this Service Bulletin ............................ 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 6 K. Publications Affected ........................................ 1 6 L. Interchangeability and Intermixability of Parts ........................... 1 6
2. MATERIAL INFORMATION ........................................ 1 7 A. Material - Price and Availability ................................... 1 7 B. Industry Support Information .................................... 1 7 C. Parts Necessary For Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 7
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 8 D. Parts Necessary to Change Spares ................................. 1 8 E. Special Tooling - Price and Availability ............................... 1 8 F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9 A. GENERAL INFORMATION ..................................... 1 9 B. WORK INSTRUCTIONS ....................................... 1 9 FIGURE 1: NO.1 AND NO.2 ENGINE THRUST REVERSER CONTROL WIRING - P252 PANEL ROUTING .................................................. 2 8 FIGURE 2: NO.1 AND NO.2 ENGINE THRUST REVERSER CONTROL WIRING, P252 PANEL - CHANGE .................................................. 3 0 FIGURE 3: NO.3 AND NO.4 ENGINE THRUST REVERSER CONTROL WIRING - P253 PANEL ROUTING .................................................. 3 1 FIGURE 4: NO.3 AND NO.4 ENGINE THRUST REVERSER CONTROL WIRING, P253 PANEL - CHANGE .................................................. 3 3
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 3 of 33 BOEING SERVICE BULLETIN 747-78A2184
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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 4 of 33 BOEING SERVICE BULLETIN 747-78A2184
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Commercial Airplanes 747 Service Bulletin ALERT Revision Transmittal SheetNumber: 747-78A2184Original 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, 2010Original Issue:
December 23, 2010Revision 1:
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 5 of 33
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 6 of 33 BOEING SERVICE BULLETIN 747-78A2184
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Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-78A2184Original 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.
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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.
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 HoursTotal Task HoursAirplanes
6.8011.30Group 1
MATERIAL INFORMATION Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 8 of 33 BOEING SERVICE BULLETIN 747-78A2184
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BOEING SERVICE BULLETIN 747-78A2184
ALERT ALERT P253 PANEL P252 PANEL MAKE WIRING CHANGES IN THE P252 AND P253 PANELS TO CAP AND STOW WIRES RELATED TO THE THRUST REVERSER CONTROL SYSTEM 1905895 FOR THE NO. 1 THRU NO. 4 ENGINES Original Issue: January 12, 2010 Revision 1: December 23, 2010 747-78A2184
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 33
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 10 of 33 BOEING SERVICE BULLETIN 747-78A2184
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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.
DESCRIPTIONCONFIGURATIONGROUP 747-400/400F airplanes with Pratt & Whitney (PW) 4000 series engines.
-1 Airplane Models:
747-400, 747-400F GroupVariable Number 1RL431 - RL436 1RL451 - RL456 1RL491 - RL492 1RL501 - RL502 1RL581 - RL586
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Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 11 of 33
GroupVariable Number 1RL751 - RL752 1RM011 - RM013 1RM021 - RM024 1RM036 - RM045 1RM091 1RM166 - RM177 1RM241 - RM246 1RM341 1RM366 - RM367 1RM811 - RM813 1RM851 - RM855 1RM871 - RM880 1RR851 - RR856 1RR861 - RR862 1RT031 - RT035 1RT061 1RT101 - RT103 1RT401 - RT412 1RT501 - RT530 1RT571 - RT590 1RT601 - RT640 1RT743 - RT750 1RT811 - RT814 1RT831 - RT837 1RT876 - RT880 1RU001 - RU006 1RU016 - RU017 1RU081 - RU083
2. Spares Affected None.
B. Concurrent Requirements None.
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Original Issue: January 12, 2010 747-78A2184Revision 1: December 23, 2010 12 of 33 BOEING SERVICE BULLETIN 747-78A2184