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Commercial Airplanes 747 Service Bulletin ALERT Number: 747-52A2294 Original Issue: July 08, 2010 Revision 1: August 16, 2011 ATA System: 5232 SUBJECT: DOORS - Side Cargo Doors - Main Deck Side Cargo Door Latch Pin and Latch Pin Retention Bolt Inspection and Modification 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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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: July 08, 2010 747-52A2294Revision 1: August 16, 2011 1 of 97
5.0
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Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 2 of 97 BOEING SERVICE BULLETIN 747-52A2294
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BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
Summary9
1. PLANNING INFORMATION ........................................ 1 3 A. Effectivity ............................................... 1 3
1. Airplanes ............................................ 1 3
2. Spares Affected ........................................ 1 9 B. Concurrent Requirements ...................................... 1 9 C. Reason ................................................ 2 0 D. Description .............................................. 2 1 E. Compliance .............................................. 2 2 F. Approval ............................................... 2 8 G. Manpower .............................................. 2 8 H. Weight and Balance Changes .................................... 3 0 I. Electrical Load Data ......................................... 3 0 J. References .............................................. 3 0
1. Existing Data .......................................... 3 0
2. Data supplied with this Service Bulletin ............................ 3 1
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 3 1 K. Publications Affected ........................................ 3 1 L. Interchangeability and Intermixability of Parts ........................... 3 2
2. MATERIAL INFORMATION ........................................ 3 3 A. Material - Price and Availability ................................... 3 3 B. Industry Support Information .................................... 3 3 C. Parts Necessary For Each Airplane ................................. 3 3
1. Kits/Parts ............................................ 3 3
2. Parts and Materials Supplied by the Operator ........................ 3 5
3. Parts Modified and Reidentified ................................ 3 6
4. Parts Removed and Not Replaced .............................. 3 6 D. Parts Necessary to Change Spares ................................. 3 6 E. Special Tooling - Price and Availability ............................... 3 6 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9 A. GENERAL INFORMATION ..................................... 3 9 B. WORK INSTRUCTIONS ....................................... 4 0 FIGURE 1: DETAILED INSPECTION ................................... 4 7 FIGURE 2: TORQUE CHECK ....................................... 4 9 FIGURE 3: LATCH PIN POSITION CHECK ................................ 5 1 FIGURE 4: PART REPLACEMENT AT LATCH PIN FITTING POSITIONS #1, #3, #7, #8, #9 AND #10 . 54 FIGURE 5: PART REPLACEMENT AT LATCH PIN FITTING POSITION #2 [Group 1-2, Configuration 2] .................................................. 5 7 FIGURE 6: PART REPLACEMENT AT LATCH PIN FITTING POSITION #2 [Group 1-2, Configuration 1;
Group 3] ............................................. 6 0 FIGURE 7: PART REPLACEMENT AT LATCH PIN FITTING POSITION #4 .............. 6 3 FIGURE 8: PART REPLACEMENT AT LATCH PIN FITTING POSITION #5 .............. 6 6 FIGURE 9: PART REPLACEMENT AT LATCH PIN FITTING POSITION #6 .............. 6 9
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Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 3 of 97 BOEING SERVICE BULLETIN 747-52A2294
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FIGURE 10: MODIFICATION AT LATCH PIN FITTING POSITION #1, #3, #7, #8, #9 AND #10 .... 7 2 FIGURE 11: MODIFICATION AT LATCH PIN FITTING POSITION #4 .................. 7 6 FIGURE 12: MODIFICATION AT LATCH PIN FITTING POSITION #5 .................. 8 0 FIGURE 13: MODIFICATION AT LATCH PIN FITTING POSITION #6 .................. 8 4 FIGURE 14: MODIFICATION AT LATCH PIN FITTING POSITION #2 [Group 1-2, Configuration 2] . . 88 FIGURE 15: MODIFICATION AT LATCH PIN FITTING POSITION #2 [Group 1-2, Configuration 1; Group 3] .................................................. 9 2 FIGURE 16: LATCH PIN REWORK ..................................... 9 6
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 4 of 97 BOEING SERVICE BULLETIN 747-52A2294
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Commercial Airplanes 747 Service Bulletin ALERT Revision Transmittal SheetNumber: 747-52A2294Original Issue: July 08, 2010 Revision 1: August 16, 2011 ATA System: 5232 SUBJECT: DOORS - Side Cargo Doors - Main Deck Side Cargo Door Latch Pin and Latch Pin Retention Bolt Inspection and Modification This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION More work is necessary on the airplane(s) inspected in accordance with the original issue of this service bulletin.
Repeat the latch pin retention bolt inspections at the time given in this service bulletin. In addition, at the time given in this service bulletin, Boeing recommends that the 3/16 inch diameter latch pin retention bolts be replaced with 5/16 inch diameter pin retention hardware in accordance with Revision 1.
No airplanes were added to the service bulletin effectivity.
REASON FOR REVISION This revision is sent to change the one-time inspection given in the original issue of this service bulletin into repeat inspections. Also, instructions for replacement of the 3/16 inch diameter latch pin retention bolts with 5/16 inch diameter pin retention hardware has been added. This replacement includes modification of the latch pin fittings and installation of new latch pins. New Figures 10 through 15 have been added.
In addition, this revision identifies another possible configuration for Group 1 and Group 2 airplanes. If the modification given in Boeing Service Bulletin 747-52-2224 was installed, the configuration of the latch pin installation at pin fitting position #4 will be different, and similar to position #4 on Group 3 airplanes.
The data given in Information Notice 747-52A2294 IN 01 is included in this revision. IN 01 was sent to clarify that in Figures 4, 5, 7, 8 and 9 it is acceptable to install an additional washer under the nut if necessary for fastener grip length adjustment.
These sections have changed:
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Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 5 of 97
1. On the Summary page, the "Action" section was changed to show that the detailed inspections should be repeated, and to include the retention bolt modification.
2. The illustration on the Summary page was changed to include the retention bolt modification.
3. The Group/Configuration table in Paragraph 1.A.1., Airplanes, was changed to include Configurations 1 and 2 for Groups 1 and 2. These configurations are dependent whether the modification given in Boeing Service Bulletin 747-52-2224, "Doors - Cargo Doors - Door Warning - Forward and Aft Lower Lobe and Main Deck Side Cargo Door Warning System Revision" has been installed. The modification changes the latch pin and retention bolt configuration at latch pin fitting #2.
4. Paragraph 1.B., Concurrent Requirements was changed to include Boeing Service Bulletin 747-52-2258.
5. Paragraph 1.D., Description was changed to show that the detailed inspections should be repeated, and to include the retention bolt modification.
6. In Paragraph 1.E., Compliance, Table 1 was changed to include repeat inspections, and to include the retention bolt modification as an alternative to inspection. Table 2 was added to give Compliance information for the retention bolt modification. Table 3 was added to include the repeated inspections necessary after the retention bolt modification has been accomplished.
7. In Paragraph 1.G., Manpower, a title was added to the original man-hour table. Tables 2 and 3 were added for the retention bolt modification and the after-modification inspections.
8. Items were added to Paragraph 1.J.1., Existing Data.
9. Tool Drawing MIT140U8005 was added to Paragraph 1.J.2., Data supplied with this Service Bulletin.
10. In Paragraph 1.K.2., Damage Tolerance Based Structural Inspections:, the paragraph was changed to indicate that DTIs are included in Paragraph 1.E., Compliance.
11. Paragraph 2.A., Material - Price and Availability and Paragraph 2.C., Parts Necessary for Each Airplane were changed to include Modification Top Kit 015U1916-1.
12. Paragraph 2.C.3., Parts Modified and Reidentified, was changed to include latch pins that can be reworked.
13. Paragraph 2.E., Special Tooling - Price and Availability and Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin were changed to include the MIT140U8005-1 tool kit necessary for the retention bolt modification.
14. In Paragraph 3.A., General Information, additional general notes have been included.
15. In Paragraph 3.B., Work Instructions, PART 4 was changed to describe the proper figure for latch pin fitting position #2 for the different Configurations of Group 1 and Group 2. PART 5 was changed to specify repeat inspections. PART 6, describing the retention bolt modification was added. PART 7, describing the after-modification inspections, was added.
16. Figures 10 - 15 have been added to show details of the latch pin retention bolt modification. Figure 16 was added to show an optional rework for certain latch pin part numbers.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
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Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 6 of 97 BOEING SERVICE BULLETIN 747-52A2294
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Pages with no vertical lines have no important changes.
REVISION HISTORY July 08, 2010Original Issue:
August 16, 2011Revision 1:
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Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 7 of 97 BOEING SERVICE BULLETIN 747-52A2294
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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 8 of 97 BOEING SERVICE BULLETIN 747-52A2294
ALERTALERT
BLANK PAGE
Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-52A2294Original Issue: July 08, 2010 Revision 1: August 16, 2011 ATA System: 5232 SUBJECT: DOORS - Side Cargo Doors - Main Deck Side Cargo Door Latch Pin and Latch Pin Retention Bolt Inspection and Modification
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.
CONCURRENT REQUIREMENTS Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND Accomplishment of the inspections in this service bulletin will ensure that the latch pin retention bolts in the Main Deck Side Cargo Door lower sill latch pin fittings are not loose, broken or missing. A loose, broken or missing retention bolt can result in a migrated latch pin, which can become disengaged from the cargo door latch cams, and lead to increased loads in the adjacent latch pin fittings and latch cams. Increased loads can cause damage to the cargo door latch mechanism and/or the lower sill structure. The migration of two or more latch pins and subsequent failure of the latch mechanism or lower sill structure can result in the inability of the cargo door to carry limit loads, which could lead to the loss of the cargo door and depressurization of the airplane.
The Main Deck Side Cargo Door has a series of ten latch pin fittings which are attached to the lower sill of the door cutout and numbered 1 through 10 forward to aft. Latch pins are installed in each latch pin fitting, and each is secured with a retention bolt. The latch pins and latch pin fittings carry structural and pressurization loads during flight.
Six operators have reported that broken latch pin retention bolts were found on eight airplanes. On one airplane, with 101,609 flight-hours and 12,862 flight-cycles, the retention bolts on both the #9 and #10 latch pin fittings were found to be broken. Latch pin #10 was found to have migrated aft and was not engaging the latch cam.
On another airplane, with 33,983 flight-hours and 4,723 flight-cycles, the retention bolt on the #10 latch pin fitting was found to be broken and the #9 latch pin was found to be damaged. On another airplane with 67,188 flight-hours and 14,440 flight-cycles, the retention bolt for the #10 latch pin fitting was found to be completely sheared, which allowed the latch pin to migrate aft until it no longer engaged the door latch cam. On four airplanes, only the retention bolt on the #10 latch pin fitting was found to be broken. On one airplane the retention bolt on the #10 latch pin fitting was found to be damaged.
Boeing Service Related Problem (SRP) 747-SRP-52-0093 is related to this service bulletin.
Boeing Fleet Team Digest article 747-FTD-52-09002 is related to this service bulletin.
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Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 9 of 97
ACTION (PRR 85901-112RS) Get access to the lower sill of the Main Deck Side Cargo Door (MDSCD) cutout. Do a Detailed Inspection of all ten latch pin fittings for loose, broken or missing retention bolts and nuts. Measure the latch pins to make sure they are within allowable limits.
At any latch pin fitting that does not have a loose, broken or missing retention bolt and nut, and the latch pin is not damaged beyond the limits given in this service bulletin, remove sealant and do a torque check in accordance with this service bulletin. If the retention bolt passes the torque check, replace the retention bolt sealant. If the retention bolt fails the torque check, consider the bolt to be broken.
At any latch pin location where the retention bolt and nut was not found to be broken, loose, damaged or missing, but the latch pin is damaged beyond the limits given in this service bulletin, replace the latch pin, the retention bolt, and related parts in accordance with this service bulletin.
At any latch pin fitting with a loose, broken or missing retention bolt or nut, do a check for latch pin migration in accordance with this service bulletin. If the latch pin has not migrated, replace parts at the affected latch pin fitting location in accordance with this service bulletin. If the latch pin has migrated, do additional Detailed Inspections of adjacent door and door cutout structure and latch cams within 42 inches of the affected fitting for damage in accordance with this service bulletin. Repair any damage that is found. Replace parts at the affected latch pin fitting location and any adjacent latch pin fitting location in accordance with this service bulletin.
The inspection is complete when the retention bolts at all ten latch pin fitting locations have either passed the torque check or been replaced in accordance with this service bulletin or other Boeing instructions, and all ten MDSCD latch pins are within the damage limits given in this service bulletin. Do the inspections again at the times given in this service bulletin.
At the time given in this service bulletin, Boeing recommends that the 3/16 inch diameter latch pin retention bolts be replaced with 5/16 inch diameter latch pin retention hardware. As part of this replacement, the retention bolt holes in the latch pin fittings must be made larger, and new latch pins with larger diameter retention bolt holes must be installed.
EFFECTIVITY 747-100, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400F, and 747SR Airplanes. Refer to Paragraph
1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspections and configuration changes given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
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Original Issue: July 08, 2010 747-52A2294Revision 1: August 16, 2011 10 of 97 BOEING SERVICE BULLETIN 747-52A2294
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BOEING SERVICE BULLETIN 747-52A2294
ALERT ALERT
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
000000000 NOTE: NUMBERS ADJACENT TO LATCH PIN FITTINGS
DENOTE LATCH POSITIONS
MAIN DECK
SIDE CARGO DOOR DOORWA 000 _OWER SIL 9 10 8
FITTING 2,4,6,8, AND 10
DOORWAY LOWER SILL
RETENTION
BOLT LATCH PIN
FITTING 1,3,5,7, AND 9 A-A Original Issue: July 08, 2010 Revision 1: August 16, 2011 AT EACH LATCH PIN FITTING LOCATION:
1. DO A DETAILED INSPECTION FOR DAMAGED
LATCH PINS AND LOOSE, BROKEN OR MISSING RETENTION BOLTS.
2. REMOVE EXISTING RETENTION BOLTS AND FITTING LATCH PINS. REWORK LATCH PIN FITTINGS BY MAKING THE RETENTION BOLT HOLES 1941535 LARGER. INSTALL NEW LATCH PINS AND RETENTION BOLTS.
747-52A2294
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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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