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Commercial Airplanes 747 Service Bulletin ALERT Number: 747-53A2835 Original Issue: October 28, 2010 Revision 1: December 08, 2011 ATA System: 5312 SUBJECT: FUSELAGE - Center Section: Station 520 To Station 2360 - Forward and Aft Lower Lobe Cargo Door Lower Sills - Latch Pin Inspection and Replacement 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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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.
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Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 1 of 324
4.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 2 of 324 BOEING SERVICE BULLETIN 747-53A2835
ALERTALERT
BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 4 B. Concurrent Requirements ...................................... 2 4 C. Reason ................................................ 2 5 D. Description .............................................. 2 5 E. Compliance .............................................. 2 7 F. Approval ............................................... 3 3 G. Manpower .............................................. 3 4 H. Weight and Balance Changes .................................... 4 0 I. Electrical Load Data ......................................... 4 0 J. References .............................................. 4 0
1. Existing Data .......................................... 4 0
2. Data supplied with this Service Bulletin ............................ 4 1
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 4 1 K. Publications Affected ........................................ 4 1 L. Interchangeability and Intermixability of Parts ........................... 4 1
2. MATERIAL INFORMATION ........................................ 4 3 A. Material - Price and Availability ................................... 4 3 B. Industry Support Information .................................... 4 4 C. Parts Necessary For Each Airplane ................................. 4 5
1. Kits/Parts ............................................ 4 5
2. Parts and Materials Supplied by the Operator ........................ 4 6
3. Parts Modified and Reidentified ................................ 4 7
4. Parts Removed and Not Replaced .............................. 4 7 D. Parts Necessary to Change Spares ................................. 4 7 E. Special Tooling - Price and Availability ............................... 4 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 4 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 9 A. GENERAL INFORMATION ..................................... 4 9 B. WORK INSTRUCTIONS ....................................... 5 0 FIGURE 1: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN INSPECTIONS . . 58 FIGURE 2: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1, Configuration 1, 5; Group 2, Configuration 1, 3; Group 3; Group 4-5, Configuration 1] . 61 FIGURE 3: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1, Configuration 2, 6; Group 2, Configuration 2, 4; Group 4-5, Configuration 2] ....... 6 6 FIGURE 4: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1, Configuration 3, 7] ...................................... 7 1 FIGURE 5: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1, Configuration 4, 8] ...................................... 7 6 FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT [Group 1, Configuration 3, 7] ............ 8 1
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FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT [Group 1, Configuration 4, 8] ............ 9 2 FIGURE 8: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1-2, Configuration 1; Group 3; Group 4, Configuration 1] .................... 1 0 3 FIGURE 9: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1-2, Configuration 1; Group 3; Group 4, Configuration 1] ............................ 1 1 2 FIGURE 10: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1-2, 4, Configuration 2] ........................................ 1 2 1 FIGURE 11: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1-2, 4, Configuration 2 ] ................................................ 1 3 0 FIGURE 12: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 3] ........................................ 1 3 9 FIGURE 13: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 3 ] ................................................ 1 5 4 FIGURE 14: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 4] ........................................ 1 6 9 FIGURE 15: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 4 ] ................................................ 1 8 4 FIGURE 16: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 5; Group 2, Configuration 3; Group 5, Configuration 1] ........... 1 9 9 FIGURE 17: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 5; Group 2, Configuration 3; Group 5, Configuration 1] ................... 2 0 8 FIGURE 18: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 6; Group 2, Configuration 4; Group 5, Configuration 2] ........... 2 1 7 FIGURE 19: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 6; Group 2, Configuration 4; Group 5, Configuration 2] ................... 2 2 6 FIGURE 20: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 7] ........................................ 2 3 5 FIGURE 21: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 7 ] ................................................ 2 5 0 FIGURE 22: LOWER LOBE FORWARD CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 8] ........................................ 2 6 5 FIGURE 23: LOWER LOBE AFT CARGO DOORS - LATCH PIN MODIFICATION [Group 1, Configuration 8 ] ................................................ 2 8 0 FIGURE 24: LOWER LOBE FORWARD CARGO DOORS - POST-MODIFICATION INSPECTION . . 295 FIGURE 25: LOWER LOBE AFT CARGO DOORS - POST-MODIFICATION INSPECTION ...... 2 9 8 FIGURE 26: LOWER LOBE FORWARD CARGO DOORS - POST-MODIFICATION LATCH PIN REPLACEMENT [Group 1, Configuration 1-4; Group 2, Configuration 1-2; Group 3-4] . . 301 FIGURE 27: LOWER LOBE AFT CARGO DOORS - POST-MODIFICATION LATCH PIN REPLACEMENT [Group 1, Configuration 1-4; Group 2, Configuration 1-2; Group 3-4] ........... 3 0 7 FIGURE 28: LOWER LOBE FORWARD CARGO DOORS - POST-MODIFICATION LATCH PIN REPLACEMENT [Group 1, Configuration 5-8; Group 2, Configuration 3-4; Group 5] . . . 313 FIGURE 29: LOWER LOBE AFT CARGO DOORS - POST-MODIFICATION LATCH PIN REPLACEMENT [Group 1, Configuration 5-8; Group 2, Configuration 3-4; Group 5] ............. 3 1 9
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Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 4 of 324 BOEING SERVICE BULLETIN 747-53A2835
ALERTALERT
Commercial Airplanes 747 Service Bulletin ALERT Revision Transmittal SheetNumber: 747-53A2835Original Issue: October 28, 2010 Revision 1: December 08, 2011 ATA System: 5312 SUBJECT: FUSELAGE - Center Section: Station 520 To Station 2360 - Forward and Aft Lower Lobe Cargo Door Lower Sills - Latch Pin Inspection and Replacement This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2000-02-37 is related to this service bulletin.
More work is necessary on the airplanes changed in accordance with the original issue of this service bulletin.
The compliance time has been reduced for airplanes that have had all existing latch pins at all latch fitting locations replaced in the same maintenance visit. Also do the latch pin modification, which installs new and improved latch pins, and do the post-modification inspection at the times given in this service bulletin.
No airplanes were added to this service bulletin effectivity. However, certain airplanes in Group 2 were moved to Group 4 and 5, which were added in this service bulletin.
REASON FOR REVISION This revision is sent to give instructions for latch pin modification and post-modification inspections to improve the effectiveness in finding damage before breaking of the latch pins. The original latch pins were made from 17-4PH CRES. The latch pin modification installs new and improved latch pins that are made from 15-5PH CRES, which is more fatigue durable and corrosion resistant, and with increased wall thickness for added strength. Also, the compliance time has been changed for airplanes that have had all existing latch pins at all latch fitting locations replaced in the same maintenance visit; the effectivity was updated to move certain airplanes from Group 2 to new Group 4 and 5; and added additional configurations in the group/configuration table.
These sections were changed:
1. In Summary, Background, added latch pin modification information for this revision and changed overhaul manual (OHM) references to component maintenance manual (CMM).
2. In Summary, Action, updated the group/configuration applicability and added an action statement for the latch pin modification.
3. In Summary, Compliance, added a Federal Aviation Administration (FAA) Airworthiness Directive (AD) reference.
4. In Summary, Material Information, added a reference to Boeing supplied Kits/Parts.
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Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 5 of 324
5. In Summary, Figure, updated to give a description of latch pin modification.
6. In Paragraph 1.A.1., Airplanes, updated group/configuration information; and added Group 4 and 5 airplanes.
7. In Paragraph 1.C., Reason, added a revision description and changed OHM references to CMM.
8. In Paragraph 1.D., Description, updated the group/configuration applicability and added an action statement for the latch pin modification. Also, updated the Affected Maintenance Zones tables.
9. In Paragraph 1.E., Compliance, added an FAA AD reference, Tables 1 through 4, updated the group/configuration applicability, added references to the corresponding "Part" of the work instructions in the action column of the tables, changed one compliance time, and added footnotes. Also added Tables 5 and 6 for the latch pin modification and post-modification inspection, respectively.
10. In Paragraph 1.G., Manpower, updated the group/configuration applicability and titles. Also added manpower information for the latch pin modification and post-modification inspection.
11. In Paragraph 1.J.1., Existing Data, updated the reference list.
12. In Paragraph 1.K., Publications Affected, updated the publications table.
13. In Paragraph 2.A., Material - Price and Availability, added top kit information for the latch pin modification.
14. In Paragraph 2.C.1., Kits/Parts, added top kit information for the latch pin modification.
15. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, updated the group/configuration applicability and added an operator supplied part.
16. In Paragraph 3.B., Work Instructions, added "Part 1" heading for the previous inspection and replacement instructions in the original issue. Added a note to reference the latch pin modification as an alternative action in Part 1. Updated the group/configuration applicability and changed the OHM references to CMM in Part
1. Also, added Part 2 and Part 3 for the latch pin modification and post-modification inspection, respectively.
17. In Figures 2 through 7, updated the group/configuration applicability.
18. Added Figures 8 through 29 for the latch pin modification and post-modification inspection.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY October 28, 2010Original Issue:
December 08, 2011Revision 1:
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Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 6 of 324 BOEING SERVICE BULLETIN 747-53A2835
ALERTALERT
Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-53A2835Original Issue: October 28, 2010 Revision 1: December 08, 2011 ATA System: 5312 SUBJECT: FUSELAGE - Center Section: Station 520 To Station 2360 - Forward and Aft Lower Lobe Cargo Door Lower Sills - Latch Pin Inspection and Replacement
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 A latch pin, from the number 8 (most aft) latch position on aft lower lobe cargo door lower sill, has fractured in service. Investigation revealed the crack initiated by fatigue and propagated by a combination of fatigue and stress corrosion. If the latch pins on the forward and aft cargo door lower sill are not regularly inspected and broken latch pins are not replaced, the forward and/or aft cargo doors could open unexpectedly during service, causing rapid decompression and possible loss of the cargo door.
One operator has reported a fractured latch pin from the lower sill of the aft lower lobe cargo door. Part of the pin was found on the ground during an airplane walk around. The airplane had completed 75,495 flight hours and 9,393 flight cycles. A dye penetrant inspection of the remaining seven latch pins in the aft cargo door was done with no defects found. The number 8 latch pin was assumed to be original. The number 8 latch cam was a reworked/overhauled part. The latch pin fracture initiated on the pin internal diameter.
This service bulletin provides inspections for broken or cracked latch pins on the forward and aft lower lobe cargo door lower sills. Replacing broken or cracked latch pins will mitigate the possibility that a cargo door could open unexpectedly during service.
In addition, Boeing has conducted analysis of broken, as well as intact, latch pins of the current design. The analysis showed a potential for large variations in the modes of crack initiation and propagation in the existing latch pins. The analysis also showed that these variations could result in the existing inspections not finding pin damage before breaking of the pin. Boeing has designed new and improved latch pins that minimize the variations in the mode of crack initiation and propagation. The original latch pins were made from 17-4 CRES. The new and improved latch pins are made from 15-5PH CRES, which is more fatigue durable and corrosion resistant, and with increased wall thickness for added strength. This service bulletin gives instructions for latch pin modification, which installs new and improved latch pins, and instructions for post-modification inspections. The latch pin modification with the post-modification inspections improve the effectiveness in finding damage before breaking of the latch pins.
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Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 7 of 324
The inspections for broken or cracked latch pins provided by this service bulletin do not replace inspections for latch pin wear. CMM 52-34-11 and CMM 52-35-11 give wear limits for the latch pins.
Boeing Service Related Problem (SRP) 747-SRP-53-0351 is related to this service bulletin.
ACTION (PRR 85901-105RS) Group 1, Configuration 1-2, 5-6; Group 2-5:
Open the lower lobe forward and aft cargo doors to get access to the latch pins on the lower sill. Do a general visual inspection for broken or missing latch pins and a detailed inspection of the latch pins for cracking. For each latch fitting location where a latch pin is broken, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s). For each latch pin where any crack is found, replace the latch pin. Put the airplane back to a serviceable condition. Repeat the inspections.
Group 1, Configuration 3-4, 7-8:
Open the lower lobe forward and aft cargo doors to get access to the latch pins on the lower sill. Do a general visual inspection for broken or missing latch pins and a detailed inspection of the latch pins for cracking. Option 1: For each latch fitting location where a latch pin is broken, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s). For each latch pin where any crack is found, replace the latch pin. Option 2: Modify or replace the latch pins and modify the bearing plates at all latch fitting locations. Put the airplane back to a serviceable condition. Repeat the inspections.
For all airplanes, do the latch pin modification at the time given in this service bulletin. The latch pin modification installs new and improved latch pins. Put the airplane back to a serviceable condition. After the latch pin modification, do the post-modification inspection at the time given in this service bulletin.
EFFECTIVITY All 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2000-02-37 is related to this service bulletin.
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 configuration changes, inspection and/or repair procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
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Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 8 of 324 BOEING SERVICE BULLETIN 747-53A2835
ALERTALERT
BOEING SERVICE BULLETIN 747-53A2835
ALERT ALERT Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability
DOORWAY LOWER SILL NOTE:
NUMBERS ADJACENT TO LATCH FITTINGS DENOTE LATCH FITTING LOCATIONS 6 2 LOCATIONS
SOME STRUCTURE
NOT SHOWN FOR CLARITY
INSPECT FOR BROKEN OR CRACKED LATCH PIN.
IF LATCH PIN IS CRACKED, REPLACE THE LATCH PIN.
IF LATCH PIN IS BROKEN OR
MISSING, REPLACE THE LATCH
PIN AND REPLACE THE LATCH
PIN(S) AT ADJACENT LATCH
FITTING LOCATION(S)
AT THE SPECIFIED TIME DO THE
LATCH PIN MODIFICATION IN
TYPICAL ACCORDANCE WITH THIS 16 LOCATIONS TOTAL SERVICE BULLETIN
ODD NUMBERED LATCH FITTING LOCATION SHOWN
EVEN NUMBERED LATCH FITTING LOCATION OPPOSITE B 2085503 Original Issue: October 28, 2010 Revision 1: December 08, 2011 747-53A2835
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 324
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 10 of 324 BOEING SERVICE BULLETIN 747-53A2835
ALERTALERT
BLANK PAGE
Commercial Airplanes 747 Service Bulletin ALERT Number: 747-53A2835 Original Issue: October 28, 2010 Revision 1: December 08, 2011 ATA System: 5312 SUBJECT: FUSELAGE - Center Section: Station 520 To Station 2360 - Forward and Aft Lower Lobe Cargo Door Lower Sills - Latch Pin Inspection and Replacement
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. An equivalent change is on subsequent production airplanes. Refer to PRR 85901-105RS for data about this change.
The group/configuration descriptions give changes that are affected by the following service bulletins:
– Boeing Service Bulletin 747-52-2105 rewords the latch pins and latch fitting bearing plates on the forward and aft lower lobe cargo doors to reduce latch operating friction and improve the engagement on the latch cams.
– Boeing Service Bulletin 747-52-2260 modifies the latch fittings to install bracket assemblies on the forward and aft lower lobe cargo doors to prevent backward installation of latch pins.
– Boeing Service Bulletin 747-52-2224 modifies the door warning system to install new switches on the forward and aft lower lobe and main deck side cargo doors.
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Original Issue: October 28, 2010 747-53A2835Revision 1: December 08, 2011 11 of 324
DESCRIPTIONCONFIGURATIONGROUP 747-100, 747-200B, 747-200C, 747-200F, 747SP, and 747SR airplanes line numbers 1 through 263 and 265.
-1 Airplanes that have modified or replaced latch pins and latch fitting bearing plates in accordance with Boeing Service Bulletin 747-52-2105 Original Issue, Revision 1 or Revision 2 on the lower lobe forward and aft cargo doors, or in accordance with Figure 6 or Figure 7 of this service bulletin, AND have done Boeing Service Bulletin 747-52-2260 Original Issue or Revision 1, AND have not installed auxiliary door-closed switches with brackets on the forward and aft lower lobe cargo doors as shown in Boeing Service Bulletin 747-52-2224 or have not done Boeing Service Bulletin 747-52-2224.
1 Airplanes that have modified or replaced latch pins and latch fitting bearing plates in accordance with Boeing Service Bulletin 747-52-2105 Original Issue, Revision 1 or Revision 2 on the lower lobe forward and aft cargo doors, or in accordance with Figure 6 or Figure 7 of this service bulletin, AND have not done Boeing Service Bulletin 747-52-2260 Original Issue or Revision 1, AND have not installed auxiliary door-closed switches with brackets on the forward and aft lower lobe cargo doors as shown in Boeing Service Bulletin 747-52-2224 or have not done Boeing Service Bulletin 747-52-2224.
2 Airplanes that have not modified or replaced latch pins and latch fitting bearing plates in accordance with Boeing Service Bulletin 747-52-2105 Original Issue, Revision 1 or Revision 2 on the lower lobe forward and aft cargo doors, or in accordance with Figure 6 or Figure 7 of this service bulletin, AND have done Boeing Service Bulletin 747-52-2260 Original Issue or Revision 1, AND have not installed auxiliary door-closed switches with brackets on the forward and aft lower lobe cargo doors as shown in Boeing Service Bulletin 747-52-2224 or have not done Boeing Service Bulletin 747-52-2224.
3 Airplanes that have not modified or replaced latch pins and latch fitting bearing plates in accordance with Boeing Service Bulletin 747-52-2105 Original Issue, Revision 1 or Revision 2 on the lower lobe forward and aft cargo doors, or in accordance with Figure 6 or Figure 7 of this service bulletin, AND have not done Boeing Service Bulletin 747-52-2260 Original Issue or Revision 1, AND have not installed auxiliary door-closed switches with brackets on the forward and aft lower lobe cargo doors as shown in Boeing Service Bulletin 747-52-2224 or have not done Boeing Service Bulletin 747-52-2224.
4 5
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