### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-53A2835**  Original Issue: October 28, 2010 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.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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 1 of 81 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 2 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 28 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 29 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 31 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 32 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 FIGURE 1: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN INSPECTIONS . . 37 FIGURE 2: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1-2, Configuration 1; Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 FIGURE 3: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1-2, Configuration 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 FIGURE 4: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1, Configuration 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 FIGURE 5: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT [Group 1, Configuration 4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT [Group 1, Configuration 3]. . . . . . . . . . . . . . 60 FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT [Group 1, Configuration 4]. . . . . . . . . . . . . . 71

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 3 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 4 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Summary**  **Number: 747-53A2835** Original Issue: October 28, 2010 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. The inspections for broken or cracked latch pins provided by this service bulletin do not replace inspections for latch pin wear. OHM 52-34-11 and OHM 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 5 of 81**ACTION (PRR 85901-105RS) Group 1, Configuration 1-2; Group 2-3:**  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:** 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. **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** Refer to Paragraph 1.E., Compliance. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. **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** 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: October 28, 2010 747-53A2835 6 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 7 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 8 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-53A2835**  Original Issue: October 28, 2010 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 9 of 81**DESCRIPTION CONFIGURATION**  **GROUP** 747 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. 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. 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. 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. 4

747 airplanes line numbers 264 and 266 through 1078.

- 2 Airplanes that have accomplished Boeing Service Bulletin 747-52-2260 Original Issue or Revision 1. 1
Airplanes that have not accomplished Boeing Service Bulletin 747-52-2260 Original Issue or Revision 1. 2
747 airplanes line numbers 1079 through 1419.

- 3

Airplane Models: 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR **Group Variable Number** 1 RA001 - RA034

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 10 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**1 RA101 - RA115 1 RA161 - RA164 1 RA201 - RA203 1 RA216 - RA217 1 RA245 - RA246 1 RA251 - RA265 2 RA266 1 RA301 - RA317 2 RA318 1 RA351 - RA360 1 RA369 - RA373 1 RA401 - RA418 1 RA501 - RA502 1 RA521 - RA528 1 RA532 - RA543 2 RA544 - RA548 1 RA551 - RA552 1 RA559 - RA561 1 RA581 - RA582 1 RA585 1 RA601 - RA602 1 RA631 - RA635 1 RA651 - RA652 1 RA671 - RA677 1 RA701 - RA702 1 RA721 - RA724 2 RA725 - RA731 1 RA741 - RA745 1 RA749 2 RA750 1 RA761 - RA762 1 RA781 - RA783 2 RA784

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 11 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**1 RA901 - RA916 1 RB001 - RB010 2 RB011 - RB012 1 RB013 - RB016 1 RB041 - RB044 1 RB071 - RB075 1 RB101 - RB102 2 RB411 - RB413 2 RB421 1 RB601 - RB607 2 RB681 - RB697 2 RB711 2 RB721 - RB723 2 RB741 - RB748 1 RD001 - RD004 1 RD021 - RD022 1 RD041 - RD044 2 RD045 - RD059 1 RD071 - RD072 2 RD081 - RD083 2 RD091 - RD092 1 RD101 - RD104 2 RD121 - RD127 2 RD131 - RD144 2 RD166 - RD167 2 RD171 - RD172 2 RD181 - RD183 2 RD201 - RD204 2 RD221 - RD227 2 RD231 - RD235 2 RD241 - RD243 2 RD251 - RD262 2 RD271 - RD272

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 12 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**2 RD291 - RD292 2 RD301 - RD302 2 RD311 2 RD351 - RD358 2 RD361 - RD366 2 RD381 - RD383 2 RD411 - RD414 2 RD421 - RD426 2 RD431 - RD435 2 RD441 - RD442 2 RD451 - RD456 2 RD461 2 RD471 - RD475 2 RD513 - RD519 2 RD531 - RD533 2 RD551 2 RD561 2 RD571 2 RD581 - RD583 2 RD591 - RD593 2 RD601 - RD607 1 RD621 - RD622 2 RD623 2 RD641 - RD649 2 RD651 - RD659 2 RD661 2 RD671 2 RD681 - RD682 2 RD691 - RD692 2 RD701 - RD702 2 RD721 - RD722 2 RD741 - RD742 2 RD751 - RD755

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 13 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**2 RD761 2 RD771 - RD775 2 RD781 - RD783 2 RD791 - RD792 2 RE001 3 RF001 - RF006 1 RG001 2 RG002 - RG009 2 RG091 2 RG095 2 RG101 - RG104 2 RG121 - RG126 2 RG141 - RG142 2 RG161 - RG164 2 RG171 - RG174 2 RG191 - RG193 2 RG211 - RG213 2 RG221 - RG222 2 RH101 - RH102 2 RH111 - RH112 2 RH121 - RH122 1 RJ131 - RJ133 2 RJ151 - RJ152 2 RJ301 - RJ303 2 RJ321 - RJ322 2 RJ331 - RJ333 3 RL401 - RL403 3 RL411 - RL436 3 RL451 - RL456 3 RL461 - RL462 3 RL471 - RL481 3 RL491 - RL492 3 RL501 - RL502

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 14 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**3 RL511 - RL516 3 RL521 - RL522 3 RL531 - RL534 3 RL551 3 RL561 - RL568 3 RL571 - RL572 3 RL576 - RL577 3 RL579 3 RL581 - RL586 3 RL651 - RL655 3 RL671 - RL675 3 RL681 - RL684 3 RL751 - RL752 3 RM001 - RM007 3 RM010 - RM013 3 RM021 - RM024 3 RM026 - RM030 3 RM036 - RM045 3 RM051 - RM053 3 RM071 3 RM081 - RM084 3 RM091 3 RM096 - RM097 3 RM116 - RM117 3 RM126 - RM132 3 RM136 - RM147 3 RM156 - RM158 3 RM166 - RM177 3 RM191 - RM192 3 RM231 - RM233 3 RM241 - RM246 3 RM261 - RM264 3 RM316 - RM318

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 15 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**3 RM331 - RM333 3 RM341 3 RM351 - RM355 3 RM366 - RM367 3 RM401 - RM403 3 RM426 3 RM431 3 RM441 - RM443 3 RM445 3 RM801 - RM803 3 RM811 - RM813 3 RM851 - RM859 3 RM861 - RM863 3 RM871 - RM899 3 RM901 - RM906 3 RM911 2 RR001 - RR005 2 RR021 - RR025 2 RR031 1 RR201 2 RR202 - RR206 1 RR221 2 RR222 - RR226 1 RR261 2 RR262 - RR267 1 RR301 2 RR302 - RR310 2 RR331 - RR332 2 RR336 1 RR341 - RR342 2 RR343 - RR345 2 RR361 - RR362 2 RR421 - RR422

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 16 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**2 RR431 - RR432 2 RR441 - RR442 2 RR451 2 RR501 - RR504 2 RR521 - RR522 2 RR526 2 RR531 2 RR551 - RR556 2 RR561 2 RR566 2 RR701 2 RR721 - RR722 3 RR723 - RR724 2 RR746 - RR747 3 RR748 2 RR851 - RR854 3 RR855 - RR856 3 RR861 - RR862 2 RR951 - RR952 2 RS001 - RS002 2 RS201 2 RS211 - RS212 2 RS221 - RS222 2 RS231 - RS241 2 RS251 - RS259 2 RS263 2 RS265 - RS268 2 RS271 - RS276 2 RS291 - RS292 2 RS301 - RS306 2 RS311 - RS320 2 RS331 - RS333 2 RS341 - RS342

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 17 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**2 RS699 2 RS701 - RS703 2 RS711 - RS713 2 RS721 - RS722 2 RS731 - RS732 2 RS741 - RS743 2 RS751 - RS752 2 RS761 - RS762 2 RS771 2 RS781 - RS782 2 RS786 2 RT001 - RT011 3 RT012 - RT014 2 RT021 - RT022 2 RT031 - RT033 3 RT034 - RT035 2 RT041 - RT047 2 RT061 2 RT071 - RT075 2 RT101 - RT103 2 RT121 2 RT131 - RT134 3 RT135 - RT137 2 RT151 - RT152 2 RT161 - RT168 2 RT401 - RT412 2 RT431 - RT441 3 RT442 - RT447 2 RT451 - RT469 2 RT471 - RT499 2 RT501 - RT535 2 RT551 - RT568 2 RT571 - RT588

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 18 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**3 RT589 - RT590 2 RT591 2 RT601 - RT622 3 RT623 - RT630 2 RT631 - RT636 3 RT637 - RT640 2 RT641 - RT657 2 RT671 - RT673 2 RT681 - RT682 2 RT691 - RT699 2 RT701 - RT704 2 RT711 - RT717 2 RT741 - RT755 3 RT756 - RT757 2 RT776 - RT777 2 RT781 - RT784 3 RT801 - RT803 3 RT811 - RT814 2 RT831 - RT833 3 RT834 - RT837 2 RT861 - RT864 2 RT876 - RT880 2 RT931 - RT932 2 RT945 - RT946 3 RT947 - RT949 2 RT951 - RT954 3 RT955 2 RT966 - RT967 2 RU001 - RU004 3 RU005 - RU006 3 RU016 - RU017 2 RU031 - RU032 2 RU051 - RU052

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 19 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group**  **Variable Number**2 RU059 - RU062 2 RU081 - RU083 3 RU101 - RU102 2 RU121 - RU124 3 RU125 - RU132 2 RU801 - RU809 2 RU831 - RU841 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. **B. Concurrent Requirements** None. **C. Reason** 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. The inspections for broken or cracked latch pins provided by this service bulletin do not replace inspections for latch pin wear. OHM 52-34-11 and OHM 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 20 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT D. Description**  **Group 1, Configuration 1-2; Group 2-3:** 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 or missing, 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:** 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 or missing, 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. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 122, 142 747-100, 747-200B, 747-200C, 747-200F, 747SP, 747SR **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 122, 142 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 122, 142 747-400, 747-400F **E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 21 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group 1-2, Configuration 1; Group 3:**  **Table 1: Forward and Aft Lower Lobe Cargo Door - Latch Pin Inspection and Replacement Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs Later) Action**  **Condition**

- Within 1,000flight cycles after the original issue date of this service bulletin Before 6,000total flight cycles Do a general visual inspection for broken or missing latch pins and a detailed inspection of thelatch pins for cracking in accordance with Paragraph 3.B., Work Instructions, Step 2. All airplanes

- Before further flight. Replace each broken or missing latch pin and replace the latch pin(s) adjacent to each brokenor missing latch pin in accordance with Paragraph 3.B., Work Instructions, Step 2.a. If a latch pin is broken into two or more pieces

- Before further flight Replace each cracked latch pin in accordance with Paragraph 3.B., Work Instructions, Step 2.b. If any crack is found in a latch pin

1,600 flight cycles (a) Within 6,000 flight cycles after replacement of latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 2. Doors with all latch pins replaced with new latch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. 1,600 flight cycles (a) Within 1,600 flight cycles after the previous inspection of all latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 2. Doors without all latch pins replaced with newlatch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. (a) Replacement of a latch pin is not terminating action for the inspections of that latch pin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 22 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group 1-2, Configuration 2:**  **Table 2: Forward and Aft Lower Lobe Cargo Door - Latch Pin Inspection and Replacement Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs Later) Action**  **Condition**

- Within 1,000flight cycles after the original issue date of this service bulletin Before 6,000total flight cycles Do a general visual inspection for broken or missing latch pins and a detailed inspection of thelatch pins for cracking in accordance with Paragraph 3.B., Work Instructions, Step 3. All airplanes

- Before further flight. Replace each broken or missing latch pin and replace the latch pin(s) adjacent to each brokenor missing latch pin in accordance with Paragraph 3.B., Work Instructions, Step 3.a. If a latch pin is broken into two or more pieces

- Before further flight Replace each cracked latch pin in accordance with Paragraph 3.B., Work Instructions, Step 3.b. If any crack is found in a latch pin

1,600 flight cycles (a) Within 6,000 flight cycles after replacement of latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 3. Doors with all latch pins replaced with new latch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. 1,600 flight cycles (a) Within 1,600 flight cycles after the previous inspection of all latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 3. Doors without all latch pins replaced with newlatch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. (a) Replacement of a latch pin is not terminating action for the inspections of that latch pin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 23 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group 1, Configuration 3:**  **Table 3: Forward and Aft Lower Lobe Cargo Door - Latch Pin Inspection and Replacement Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs Later) Action**  **Condition**

- Within 1,000flight cycles after the original issue date of this service bulletin Before 6,000total flight cycles Do a general visual inspection for broken or missing latch pins and a detailed inspection of thelatch pins for cracking in accordance with Paragraph 3.B., Work Instructions, Step 4. All airplanes

- Before further flight. Replace each broken or missing latch pin and replace the latch pin(s) adjacent to each brokenor missing latch pin in accordance with Paragraph 3.B., Work Instructions, Step 4.a. OPTION 1 or OPTION 2. If a latch pin is broken into two or more pieces

- Before further flight Replace each cracked latch pin in accordance with Paragraph 3.B., Work Instructions, Step 4.a. OPTION 1 or OPTION 2. If any crack is found in a latch pin

1,600 flight cycles (a) Within 6,000 flight cycles after replacement of latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 4. Doors with all latch pins replaced with new latch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. 1,600 flight cycles (a) Within 1,600 flight cycles after the previous inspection of all latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 4. Doors without all latch pins replaced with newlatch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. (a) Replacement of a latch pin is not terminating action for the inspections of that latch pin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 24 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group 1, Configuration 4:**  **Table 4: Forward and Aft Lower Lobe Cargo Door - Latch Pin Inspection and Replacement Repeat Interval**  **(Not to Exceed) Compliance Time**  **(Whichever Occurs Later) Action**  **Condition**

- Within 1,000flight cycles after the original issue date of this service bulletin Before 6,000total flight cycles Do a general visual inspection for broken or missing latch pins and a detailed inspection of thelatch pins for cracking in accordance with Paragraph 3.B., Work Instructions, Step 5. All airplanes

- Before further flight. Replace each broken or missing latch pin and replace the latch pin(s) adjacent to each brokenor missing latch pin in accordance with Paragraph 3.B., Work Instructions, Step 5.a. OPTION 1 or OPTION 2. If a latch pin is broken into two or more pieces

- Before further flight Replace each cracked latch pin in accordance with Paragraph 3.B., Work Instructions, Step 5.a. OPTION 1 or OPTION 2. If any crack is found in a latch pin

1,600 flight cycles (a) Within 6,000 flight cycles after replacement of latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 5. Doors with all latch pins replaced with new latch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. 1,600 flight cycles (a) Within 1,600 flight cycles after the previous inspection of all latch pins. For each door:Repeat the general visual inspection for broken or missinglatch pins and the detailed inspection of the latch pins for cracking in accordance withParagraph 3.B., Work Instructions, Step 5. Doors without all latch pins replaced with newlatch pins at all latch fitting locations and at the same maintenance visit in accordance with this service bulletin. (a) Replacement of a latch pin is not terminating action for the inspections of that latch pin. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 25 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**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 inspection 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. **Group 1-2, Configuration 1; Group 3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access 1.00 1.00 1 FIGURE 1 4.00 8.00 2 FIGURE 2 (a) 0.25 0.25 1 Close Access 5.50 9.50 TOTAL FOR EACH AIRPLANE (a) (a) This estimate includes replacement of all 16 latch pins. It may not be necessary to replace all 16 latch pins. **Group 1-2, Configuration 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access 1.00 1.00 1 FIGURE 1 4.00 8.00 2 FIGURE 3 (a) 0.25 0.25 1 Close Access 5.50 9.50 TOTAL FOR EACH AIRPLANE (a) (a) This estimate includes replacement of all 16 latch pins. It may not be necessary to replace all 16 latch pins.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 26 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group 1, Configuration 3:**  **OPTION 1: DO NOT MODIFY THE LATCH FITTINGS Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access 1.00 1.00 1 FIGURE 1 4.00 8.00 2 FIGURE 4 (a) 0.25 0.25 1 Close Access 5.50 9.50 TOTAL FOR EACH AIRPLANE (a) (a) This estimate includes replacement of all 16 latch pins. It may not be necessary to replace all 16 latch pins. **Group 1, Configuration 3: OPTION 2: MODIFY THE LATCH FITTINGS**  **Elapsed Hours Task Hours**  **Number of Persons Task**  0.25 0.25 1 Open Access 1.00 1.00 1 FIGURE 1 18.00 36.00 2 FIGURE 6 (a) 0.25 0.25 1 Close Access 19.50 37.50 TOTAL FOR EACH AIRPLANE (a) (a) This estimate includes modification of all latch pins and latch fitting bearing plates. It is acceptable to replace latch pins and bearing plates with new parts. **Group 1, Configuration 4: OPTION 1: DO NOT MODIFY THE LATCH FITTINGS**  **Elapsed Hours Task Hours**  **Number of Persons Task**  0.25 0.25 1 Open Access 1.00 1.00 1 FIGURE 1 4.00 8.00 2 FIGURE 5 (a) 0.25 0.25 1 Close Access 5.50 9.50 TOTAL FOR EACH AIRPLANE (a) (a) This estimate includes replacement of all 16 latch pins. It may not be necessary to replace all 16 latch pins.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 27 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group 1, Configuration 4:**  **OPTION 2: MODIFY THE LATCH FITTINGS Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access 1.00 1.00 1 FIGURE 1 18.00 36.00 2 FIGURE 7 (a) 0.25 0.25 1 Close Access 19.50 37.50 TOTAL FOR EACH AIRPLANE (a) (a) This estimate includes modification of all latch pins and latch fitting bearing plates. It is acceptable to replace latch pins and bearing plates with new parts. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 85901-105RS b. Service Related Problem (SRP) 747-SRP-53-0351 c. Boeing Service Bulletin 747-52-2105 and 747-52-2260 d. Overhaul Manual (OHM) 52-34-11, 52-35-11 e. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-20-01, 20-30-02, 20-42-03, 20-42-05, 20-50-08, 20-50-10, 20-50-19 f. 747 Maintenance Planning Document (MPD) 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  SILL INSTL - LOWER MAIN, FWD CARGO DOOR 65B04216 SILL INSTALLATION - LOWER MAIN, AFT CARGO DOOR 65B04642

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 28 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. **L. Interchangeability and Intermixability of Parts** Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 29 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 30 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**

BLANK PAGE**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. **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator **Group 1, Configuration 1-2; Group 2-3:**
**Notes Existing Part**  **Number Name**  **QTY Part Number / Specification**  (a) (b) 69B02005-4 OR PIN, LATCH 16 69B02005-6 (69B02005-4 or 65B02005-5 optional) 69B02005-5 OR 69B02005-6 (c)

- PRESSURE AND ENVIRON-MENTAL SEALANT-CHROMATE TYPE 8 Oz BMS5-95 TYPE 1, CLASS B

(a) One new latch pin is required for each latch pin location where the existing latch pin is broken or missing. There are 16 latch pins on each airplane. (b) Discard existing latch pins that are broken or cracked and discard existing latch pins adjacent to broken latch pins. (c) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. **Group 1, Configuration 3-4:**
**Notes Existing Part**  **Number Name**  **QTY Part Number / Specification**  (a) 65B04299-1 OR 65B04299-5 BEARING PLATE 8 65B04299-15 (65B04299-7 or 65B04299-13 optional) (a) 65B04299-2 OR 65B04299-6 BEARING PLATE 8 65B04299-16 (65B04299-8 or 65B04299-14 optional)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 31 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT Group 1, Configuration 3-4:** 
**Notes Existing Part**  **Number Name**  **QTY Part Number / Specification**  (b) (c) (d) 69B02005-3 LATCH PIN 16 69B02005-6 (69B02005-3,69B02005-4 or 65B02005-5 optional) (e)

- SOLID FILM LUBRICANT, LIQUID DISPERSED 8 Oz BMS3-8 TYPE I (e)

- PRESSURE AND ENVIRON-MENTAL SEALANT-CHROMATE TYPE 8 Oz BMS5-95 TYPE 1, CLASS B

(e)

- PRESSURE AND ENVIRON-MENTAL SEALANT-CHROMATE TYPE 8 Oz BMS5-95 TYPE 1, CLASS C

(a) New bearing plates are required if Option 2, 'Modify the latch fittings', is selected. Alternatively, the existing bearing plates can be modified. (b) One new latch pin is required for each latch pin location where the existing latch pin is broken or missing. There are 16 latch pins on each airplane. (c) Discard existing latch pins that are broken or cracked and discard existing latch pins adjacent to broken latch pins. (d) If a 69B02005-3 latch pin is removed, it is necessary to rework the latch fitting before installing a 69B02005-4, 69B02005-5 or 69B02005-6 latch pin. (e) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 32 of 81 **BOEING SERVICE BULLETIN 747-53A2835 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. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Torque limits to tighten nuts and bolts are in 747 SRM 51. 5. Use the approved fastener and process material substitutions in accordance with 747 SRM 51. Alternate fasteners are listed in 747 SRM 51 and Boeing Drawing 012W6100. 6. If the length of any fastener specified in this service bulletin does not meet the installation standards in 747 SRM 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards in 747 SRM 51 may be used. 7. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 33 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**8. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 9. 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. 10. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. The removed part can be discarded if a new or serviceable part is installed. **B. WORK INSTRUCTIONS** 1. Open the lower lobe forward and aft cargo doors to get access to the latch pins on the lower sill.
2.**Group 1-2, Configuration 1; Group 3:** Do a general visual inspection for broken or missing latch pins and a detailed inspection of the latch pins for cracking in accordance with FIGURE 1. **NOTE:**It is optional to replace all latch pins with new latch pins at all latch fitting locations in accordance with FIGURE 2. Refer to Paragraph 1.E., Compliance. a. If a latch pin is broken into two or more pieces or is missing, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s) in accordance with FIGURE 2. b. If any crack is found in a latch pin, replace the cracked latch pin in accordance with FIGURE 2. c. Repeat the inspections at the time given in Paragraph 1.E., Compliance. **NOTE:**The inspections for broken or cracked latch pins provided by this service bulletin do not replace inspections for latch pin wear. OHM 52-34-11 and OHM 52-35-11 give wear limits for the latch pins. 3.**Group 1-2, Configuration 2:** Do a general visual inspection for broken latch pins and a detailed inspection of the latch pins for cracking in accordance with FIGURE 1. **NOTE:**It is optional to replace all latch pins with new latch pins at all latch fitting locations in accordance with FIGURE 3. Refer to Paragraph 1.E., Compliance.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 34 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**a. If a latch pin is broken into two or more pieces or is missing, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s) in accordance with FIGURE 3. b. If any crack is found in a latch pin, replace the cracked latch pin in accordance with FIGURE 3. c. Repeat the inspections at the time given in Paragraph 1.E., Compliance. **NOTE:**The inspections for broken or cracked latch pins provided by this service bulletin do not replace inspections for latch pin wear. OHM 52-34-11 and OHM 52-35-11 give wear limits for the latch pins. 4.**Group 1, Configuration 3:** Do a general visual inspection for broken or missing latch pins and a detailed inspection of the latch pins for cracking in accordance with FIGURE 1. **NOTE:**It is optional to replace all latch pins with new latch pins at all latch fitting locations in accordance with FIGURE 4 or FIGURE 6. Refer to Paragraph 1.E., Compliance. a. If a latch pin is broken or missing or if any crack is found in a latch pin, do one of the following: (1) OPTION 1 - DO NOT MODIFY THE LATCH FITTINGS **NOTE:**This option requires that 69B02005-3 latch pins are installed. 69B02005-3 latch pins are not available from Boeing Spares. (a) If a latch pin is broken into two or more pieces or is missing, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s) in accordance with FIGURE 4. (b) If any crack is found in a latch pin, replace the cracked latch pin in accordance with FIGURE 4. (2) OPTION 2 - MODIFY THE LATCH FITTINGS **NOTE:**Accomplishment of this option will change the configuration of the airplane. Refer to Paragraph 1.A., Effectivity. (a) Modify or replace the latch pins and bearing plates at all latch fitting locations in accordance with FIGURE 6. 1) If a latch pin is broken into two or more pieces or is missing, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s). Do not modify these latch pins. 2) If any crack is found in a latch pin, replace the cracked latch pin. Do not modify the latch pin. b. Repeat the inspections at the time given in Paragraph 1.E., Compliance.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 35 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT NOTE:** The inspections for broken or cracked latch pins provided by this service bulletin do not replace inspections for latch pin wear. OHM 52-34-11 and OHM 52-35-11 give wear limits for the latch pins. 5.**Group 1, Configuration 4:** Do a general visual inspection for broken or missing latch pins and a detailed inspection of the latch pins for cracking in accordance with FIGURE 1. **NOTE:**It is optional to replace all latch pins with new latch pins at all latch fitting locations in accordance with FIGURE 5 or FIGURE 7. Refer to Paragraph 1.E., Compliance. a. If a latch pin is broken or missing or if any crack is found in a latch pin, do one of the following: (1) OPTION 1 - DO NOT MODIFY THE LATCH FITTINGS **NOTE:**This option requires that 69B02005-3 latch pins are installed. 69B02005-3 latch pins are not available from Boeing Spares. (a) If a latch pin is broken into two or more pieces or is missing, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s) in accordance with FIGURE 5. (b) If any crack is found in a latch pin, replace the cracked latch pin in accordance with FIGURE 5. (2) OPTION 2 - MODIFY THE LATCH FITTINGS **NOTE:**Accomplishment of this option will change the configuration of the airplane. Refer to Paragraph 1.A., Effectivity. (a) Modify or replace the latch pins and modify the bearing plates at all latch fitting locations in accordance with FIGURE 7. 1) If a latch pin is broken into two or more pieces or is missing, replace the latch pin and replace the latch pin(s) at the adjacent latch fitting location(s). Do not modify these latch pins. 2) If any crack is found in a latch pin, replace the cracked latch pin. Do not modify the latch pin. b. Repeat the inspections at the time given in Paragraph 1.E., Compliance. **NOTE:**The inspections for broken or cracked latch pins provided by this service bulletin do not replace inspections for latch pin wear. OHM 52-34-11 and OHM 52-35-11 give wear limits for the latch pins. 6. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 36 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 1: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN INSPECTIONS**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 37 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 1: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN INSPECTIONS**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 38 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) 8 69B02005-( ) LATCH PIN Inspect 1 (b) 8 69B02005-( ) LATCH PIN Inspect 2 (a) Do a general visual inspection of the latch pin to find if the pin is broken into two or more pieces or is missing. (b) Do a detailed inspection of the visible external surfaces of the latch pin for cracking. Removal of the bearing plate is not required. This step is not necessary if the latch pin is broken.

**FIGURE 1: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN INSPECTIONS (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 39 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT This Figure applies only to: Group 1-2, Configuration 1; Group 3.** 

**FIGURE 2: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 1 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 40 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 2: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 41 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 2: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 42 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary to replace all latch pins in this figure. It may not be necessary to replace all latch pins.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - SEALANT Remove 1 (a) 8
- BOLT Remove / Keep 2 (a) 8
- WASHER Remove / Keep (a) 8
- BRACKET ASSY Remove / Keep (a) (b) 8 69B02005-( ) LATCH PIN Remove 3 (a) (c) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 4

(a) 8
- BOLT Install (Kept) 5 (a) 8
- WASHER Install (Kept) (a) 8
- BRACKET ASSY Install (Kept) (a) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 6

(e)

- - SEALANT Remove 7 (e) 8
- BOLT Remove / Keep 8 (e) 8
- WASHER Remove / Keep (e) 8
- BRACKET ASSY Remove / Keep (e) (b) 8 69B02005-( ) LATCH PIN Remove 9 (e) (c) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 10

(e) 8
- BOLT Install (Kept) 11 (e) 8
- WASHER Install (Kept) (e) 8
- BRACKET ASSY Install (Kept) (e) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 12

(a) Do this step where a new latch pin is being installed at latch fitting locations 1, 3, 5 and/or 7. (b) Discard broken or cracked latch pins and discard latch pins adjacent to broken latch pins.

**FIGURE 2: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 43 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (c) Install latch pin wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Make sure sealant is applied to both the outside diameter of the latch pin and the inside diameter of the latch fitting. Make sure all excess sealant is removed. Refer to SOPM 20-50-19 as an accepted procedure. (d) Refer to SOPM 20-50-19 as an accepted procedure. (e) Do this step where a new latch pin is being installed at latch fitting locations 2, 4, 6 and/or 8.

**FIGURE 2: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 44 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT This Figure applies only to: Group 1-2, Configuration 2.** 

**FIGURE 3: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 1 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 45 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 3: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 46 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 3: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 47 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary to replace all latch pins in this figure. It may not be necessary to replace all latch pins.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - SEALANT Remove 1 (a) 8
- BOLT Remove / Keep 2 (a) 8
- WASHER Remove / Keep (a) 8
- NUT Remove / Keep (a) (b) 8 69B02005-( ) LATCH PIN Remove 3 (a) (c) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 4

(a) 8
- BOLT Install (Kept) 5 (a) 8
- WASHER Install (Kept) (a) 8
- NUT Install (Kept) (a) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 6

(e)

- - SEALANT Remove 7 (e) 8
- BOLT Remove / Keep 8 (e) 8
- WASHER Remove / Keep (e) 8
- NUT Remove / Keep (e) (b) 8 69B02005-( ) LATCH PIN Remove 9 (e) (c) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 10

(e) 8
- BOLT Install (Kept) 11 (e) 8
- WASHER Install (Kept) (e) 8
- NUT Install (Kept) (e) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 12

(a) Do this step where a new latch pin is being installed at latch fitting locations 1, 3, 5 and/or 7. (b) Discard broken or cracked latch pins and discard latch pins adjacent to broken latch pins.

**FIGURE 3: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 48 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (c) Install latch pin wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Make sure sealant is applied to both the outside diameter of the latch pin and the inside diameter of the latch fitting. Make sure all excess sealant is removed. Refer to SOPM 20-50-19 as an accepted procedure. (d) Refer to SOPM 20-50-19 as an accepted procedure. (e) Do this step where a new latch pin is being installed at latch fitting locations 2, 4, 6 and/or 8.

**FIGURE 3: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 49 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT This Figure applies only to: Group 1, Configuration 3.** 

**FIGURE 4: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 1 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 50 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 4: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 51 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 4: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 52 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary to replace all latch pins in this figure. It may not be necessary to replace all latch pins.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - SEALANT Remove 1 (a) 8
- BOLT Remove / Keep 2 (a) 8
- WASHER Remove / Keep (a) 8
- BRACKET ASSY Remove / Keep (a) (b) 8 69B02005-( ) LATCH PIN Remove 3 (a) (c) 8 69B02005-3 LATCH PIN Install (New) 4 (a) 8
- BOLT Install (Kept) 5 (a) 8
- WASHER Install (Kept) (a) 8
- BRACKET ASSY Install (Kept) (a) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 6

(e)

- - SEALANT Remove 7 (e) 8
- BOLT Remove / Keep 8 (e) 8
- WASHER Remove / Keep (e) 8
- BRACKET ASSY Remove / Keep (e) (b) 8 69B02005-( ) LATCH PIN Remove 9 (e) (c) 8 69B02005-3 LATCH PIN Install (New) 10 (e) 8
- BOLT Install (Kept) 11 (e) 8
- WASHER Install (Kept) (e) 8
- BRACKET ASSY Install (Kept) (e) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 12

(a) Do this step where a new latch pin is being installed at latch fitting locations 1, 3, 5 and/or 7. (b) Discard broken or cracked latch pins and discard latch pins adjacent to broken latch pins. (c) Install latch pin wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Make sure sealant is applied to both the outside diameter of the latch pin and the inside diameter of the latch fitting. Make sure all excess sealant is removed. Refer to SOPM 20-50-19 as an accepted procedure.

**FIGURE 4: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 53 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (d) Refer to SOPM 20-50-19 as an accepted procedure. (e) Do this step where a new latch pin is being installed at latch fitting locations 2, 4, 6 and/or 8.

**FIGURE 4: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 54 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT This Figure applies only to: Group 1, Configuration 4.** 

**FIGURE 5: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 1 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 55 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 5: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 56 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 5: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 57 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary to replace all latch pins in this figure. It may not be necessary to replace all latch pins.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a)

- - SEALANT Remove 1 (a) 8
- BOLT Remove / Keep 2 (a) 8
- WASHER Remove / Keep (a) 8
- NUT Remove / Keep (a) (b) 8 69B02005-( ) LATCH PIN Remove 3 (a) (c) 8 69B02005-3 LATCH PIN Install (New) 4 (a) 8
- BOLT Install (Kept) 5 (a) 8
- WASHER Install (Kept) (a) 8
- NUT Install (Kept) (a) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 6

(e)

- - SEALANT Remove 7 (e) 8
- BOLT Remove / Keep 8 (e) 8
- WASHER Remove / Keep (e) 8
- NUT Remove / Keep (e) (b) 8 69B02005-( ) LATCH PIN Remove 9 (e) (c) 8 69B02005-3 LATCH PIN Install (New) 10 (e) 8
- BOLT Install (Kept) 11 (e) 8
- WASHER Install (Kept) (e) 8
- NUT Install (Kept) (e) (d)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 12

(a) Do this step where a new latch pin is being installed at latch fitting locations 1, 3, 5 and/or 7. (b) Discard broken or cracked latch pins and discard latch pins adjacent to broken latch pins. (c) Install latch pin wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Make sure sealant is applied to both the outside diameter of the latch pin and the inside diameter of the latch fitting. Make sure all excess sealant is removed. Refer to SOPM 20-50-19 as an accepted procedure.

**FIGURE 5: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 58 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (d) Refer to SOPM 20-50-19 as an accepted procedure. (e) Do this step where a new latch pin is being installed at latch fitting locations 2, 4, 6 and/or 8.

**FIGURE 5: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN REPLACEMENT (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 59 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT This Figure applies only to: Group 1, Configuration 3.** 

**FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 1 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 60 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 2 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 61 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 3 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 62 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 4 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 63 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 5 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 64 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 6 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 65 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP** 

- - SEALANT Remove 1 8
- BOLT Remove / Keep 2 8
- WASHER Remove / Keep 8
- BRACKET ASSY Remove / Keep (a) 8 69B02005-3 LATCH PIN Remove / Keep 3 8 65B04299-1 OR 65B04299-5 BEARING PLATE Remove / Keep 4

24
- BOLT Remove / Keep 24
- WASHER Remove / Keep 24
- NUT Remove / Keep (b) (c) 8 69B02005-3 LATCH PIN Grind 5 (b) (d) 8 69B02005-3 LATCH PIN Inspect (b) (e) 8 69B02005-3 LATCH PIN Shot Peen (b) (f)

- - CADMIUM PLATE Apply (b) (g) 8 69B02005-3 LATCH PIN Identify (b) (h)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply

(i) (k)

- - Old finish and plating Remove 6 (i) (l) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Grind (i) (d) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Inspect (i) (e) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Shot Peen (i) (m)

- - HARD CHROME PLATE Apply (i) (n) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Identify (i) (p)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply 7

**FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 7 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 66 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (q) (s) 8 65B04299-15 (65B04299-13 or 65B04299-7 optional) BEARING PLATE Install (New) 8

(q) (s) 8 65B04299-7-747- 53A2835 BEARING PLATE Install (Changed) (t) 24
- BOLT Install (Kept) (t) 24
- WASHER Install (Kept) (t) 24
- NUT Install (Kept) (u) (v) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 9

(u) (v) 8 69B02005-4-747- 53A2835 LATCH PIN Install (Changed)
8
- BOLT Install (Kept) 10 8
- WASHER Install (Kept) 8
- BRACKET ASSY Install (Kept) (w)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 11

- - SEALANT Remove 12 8
- BOLT Remove / Keep 13 8
- WASHER Remove / Keep 8
- BRACKET ASSY Remove / Keep (a) 8 69B02005-3 LATCH PIN Remove / Keep 14 8 65B04299-2 OR 65B04299-6 BEARING PLATE Remove / Keep 15

24
- BOLT Remove / Keep 24
- WASHER Remove / Keep 24
- NUT Remove / Keep

**FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 8 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 67 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (b) (c) 8 69B02005-3 LATCH PIN Grind 16 (b) (d) 8 69B02005-3 LATCH PIN Inspect (b) (e) 8 69B02005-3 LATCH PIN Shot Peen (b) (f)

- - CADMIUM PLATE Apply (b) (g) 8 69B02005-3 LATCH PIN Identify (b) (h)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply

(j) (k)

- - Old finish and plating Remove 17 (j) (l) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Grind (j) (d) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Inspect (j) (e) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Shot Peen (j) (m)

- - HARD CHROME PLATE Apply (j) (o) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Identify (j) (p)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply 18

(r) (s) 8 65B04299-16 (65B04299-14 or 65B04299-8 optional) BEARING PLATE Install (New) 19

(r) (s) 8 65B04299-8-747- 53A2835 BEARING PLATE Install (Changed) (t) 24
- BOLT Install (Kept) (t) 24
- WASHER Install (Kept) (t) 24
- NUT Install (Kept) (u) (v) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 20

(u) (v) 8 69B02005-4-747- 53A2835 LATCH PIN Install (Changed)

**FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 9 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 68 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 8
- BOLT Install (Kept) 21 8
- WASHER Install (Kept) 8
- BRACKET ASSY Install (Kept) (w)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 22

(a) Discard broken or cracked latch pins and discard latch pins adjacent to broken latch pins. (b) As an alternative to modifying the existing latch pins, it is acceptable to replace the existing latch pins with 69B02005-4, 69B02005-5 or 69B02005-6 latch pins. (c) Grind latch pin to the dimensions shown. It is acceptable to use other methods of machining. Maintain a surface roughness of 63 microinches RA or better. Refer to SOPM 20-10-02 as an accepted procedure.(d) Do a magnetic particle inspection to make sure there are no cracks. Refer to SOPM 20-20-01 as an accepted procedure. (e) Shot peen the reworked area. Refer to SOPM 20-10-03 as an accepted procedure. (f) Apply Type 2 Class 3 cadmium plating to all surfaces of the latch pin. Refer to SOPM 20-42-05 as an accepted procedure. (g) Mark the part with the part number 69B02005-4-747-53A2835 to show that it has been modified by this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure. The equivalent production part number is 69B02005-4. (h) Apply solid film lubricant to the reworked area. Refer to SOPM 20-50-08 Type 8, Class 1 as an accepted procedure. (i) As an alternative to modifying the existing bearing plates, it is acceptable to replace the existing bearing plates with 65B04299-7, 65B04299-13 or 65B04299-15 bearing plates. (j) As an alternative to modifying the existing bearing plates, it is acceptable to replace the existing bearing plates with 65B04299-8, 65B04299-14 or 65B04299-16 bearing plates. (k) Refer to SOPM 20-30-02 as an accepted procedure. (l) Grind bearing plate to the dimensions shown. It is acceptable to use other methods of machining. Maintain a surface roughness of 125 microinches RA or better. Refer to SOPM 20-10-02 as an accepted procedure. (m) Apply hard chrome plating to the reworked area only, thickness 0.002 to 0.004 inches. Refer to SOPM 20-42-03 as an accepted procedure. (n) Mark the part with the part number 65B04299-7-747-53A2835 to show that it has been modified by this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure. The equivalent production part number is 65B04299-7. (o) Mark the part with the part number 65B04299-8-747-53A2835 to show that it has been modified by this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure. The equivalent production part number is 65B04299-8.

**FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 10 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 69 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (p) Apply solid film lubricant to the surfaces shown. Refer to SOPM 20-50-08 Type 8, Class 1 as an accepted procedure. (q) OPTION A: Install 65B04299-7, 65B04299-13 or 65B04299-15 bearing plates. OPTION B: Install 65B04299- 7-747-53A2835 bearing plates. (r) OPTION A: Install 65B04299-8, 65B04299-14 or 65B04299-16 bearing plates. OPTION B: Install 65B04299- 8-747-53A2835 bearing plates. (s) Install bearing plate wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Refer to SOPM 20-50-19 as an accepted procedure. (t) Install fastener wet with BMS5-95 TYPE 1, CLASS C sealant. Make sure threads, shank and countersink are completely coated. Fillet seal nut with BMS5-95 TYPE 1, CLASS B sealant. Make sure the nut is completely covered. Refer to SOPM 20-50-19 as an accepted procedure. (u) OPTION A: Install 69B02005-4, 69B02005-5 or 69B02005-6 latch pins. OPTION B: Install 69B02005-4- 747-53A2835 latch pins. (v) Install latch pin wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Make sure sealant is applied to both the outside diameter of the latch pin and the inside diameter of the latch fitting. Make sure all excess sealant is removed. Refer to SOPM 20-50-19 as an accepted procedure. (w) Refer to SOPM 20-50-19 as an accepted procedure.

**FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 11 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 70 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT This Figure applies only to: Group 1, Configuration 4.** 

**FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 1 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 71 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 2 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 72 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 3 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 73 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 4 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 74 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 5 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 75 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE**  **MODIFICATION OR REPLACEMENT (SHEET 6 OF 11)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 76 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP** 

- - SEALANT Remove 1 8
- BOLT Remove / Keep 2 8
- WASHER Remove / Keep 8
- NUT Remove / Keep (a) 8 69B02005-3 LATCH PIN Remove / Keep 3 8 65B04299-1 OR 65B04299-5 BEARING PLATE Remove / Keep 4

24
- BOLT Remove / Keep 24
- WASHER Remove / Keep 24
- NUT Remove / Keep (b) (c) 8 69B02005-3 LATCH PIN Grind 5 (b) (d) 8 69B02005-3 LATCH PIN Inspect (b) (e) 8 69B02005-3 LATCH PIN Shot Peen (b) (f)

- - CADMIUM PLATE Apply (b) (g) 8 69B02005-3 LATCH PIN Identify (b) (h)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply

(i) (k)

- - Old finish and plating Remove 6 (i) (l) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Grind (i) (d) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Inspect (i) (e) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Shot Peen (i) (m)

- - HARD CHROME PLATE Apply (i) (n) 8 65B04299-1 OR 65B04299-5 BEARING PLATE Identify (i) (p)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply 7

**FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 7 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 77 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (q) (s) 8 65B04299-15 (65B04299-13 or 65B04299-7 optional) BEARING PLATE Install (New) 8

(q) (s) 8 65B04299-7-747- 53A2835 BEARING PLATE Install (Changed) (t) 24
- BOLT Install (Kept) (t) 24
- WASHER Install (Kept) (t) 24
- NUT Install (Kept) (u) (v) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 9

(u) (v) 8 69B02005-4-747- 53A2835 LATCH PIN Install (Changed)
8
- BOLT Install (Kept) 10 8
- WASHER Install (Kept) 8
- NUT Install (Kept) (w)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 11

- - SEALANT Remove 12 8
- BOLT Remove / Keep 13 8
- WASHER Remove / Keep 8
- NUT Remove / Keep (a) 8 69B02005-3 LATCH PIN Remove / Keep 14 8 65B04299-2 OR 65B04299-6 BEARING PLATE Remove / Keep 15

24
- BOLT Remove / Keep 24
- WASHER Remove / Keep 24
- NUT Remove / Keep

**FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 8 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 78 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (b) (c) 8 69B02005-3 LATCH PIN Grind 16 (b) (d) 8 69B02005-3 LATCH PIN Inspect (b) (e) 8 69B02005-3 LATCH PIN Shot Peen (b) (f)

- - CADMIUM PLATE Apply (b) (g) 8 69B02005-3 LATCH PIN Identify (b) (h)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply

(j) (k)

- - Old finish and plating Remove 17 (j) (l) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Grind (j) (d) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Inspect (j) (e) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Shot Peen (j) (m)

- - HARD CHROME PLATE Apply (j) (o) 8 65B04299-2 OR 65B04299-6 BEARING PLATE Identify (j) (p)

- BMS3-8, TYPE I SOLID FILM LUBRI-CANT, LIQUID DISPERSED Apply 18

(r) (s) 8 65B04299-16 (65B04299-14 or 65B04299-8 optional) BEARING PLATE Install (New) 19

(r) (s) 8 65B04299-8-747- 53A2835 BEARING PLATE Install (Changed) (t) 24
- BOLT Install (Kept) (t) 24
- WASHER Install (Kept) (t) 24
- NUT Install (Kept) (u) (v) 8 69B02005-6 (69B02005-4 or 69B02005-5 optional) LATCH PIN Install (New) 20

(u) (v) 8 69B02005-4-747- 53A2835 LATCH PIN Install (Changed)

**FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 9 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 79 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 8
- BOLT Install (Kept) 21 8
- WASHER Install (Kept) 8
- NUT Install (Kept) (w)

- BMS5-95 TYPE 1, CLASS BPRESSURE AND ENVIRONMENTAL SEALANT-CHROMATE TYPE Apply 22

(a) Discard broken or cracked latch pins and discard latch pins adjacent to broken latch pins. (b) As an alternative to modifying the existing latch pins, it is acceptable to replace the existing latch pins with 69B02005-4, 69B02005-5 or 69B02005-6 latch pins. (c) Grind latch pin to the dimensions shown. It is acceptable to use other methods of machining. Maintain a surface roughness of 63 microinches RA or better. Refer to SOPM 20-10-02 as an accepted procedure.(d) Do a magnetic particle inspection to make sure there are no cracks. Refer to SOPM 20-20-01 as an accepted procedure. (e) Shot peen the reworked area. Refer to SOPM 20-10-03 as an accepted procedure. (f) Apply Type 2 Class 3 cadmium plating to all surfaces of the latch pin. Refer to SOPM 20-42-05 as an accepted procedure. (g) Mark the part with the part number 69B02005-4-747-53A2835 to show that it has been modified by this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure. The equivalent production part number is 69B02005-4. (h) Apply solid film lubricant to the reworked area. Refer to SOPM 20-50-08 Type 8, Class 1 as an accepted procedure. (i) As an alternative to modifying the existing bearing plates, it is acceptable to replace the existing bearing plates with 65B04299-7, 65B04299-13 or 65B04299-15 bearing plates. (j) As an alternative to modifying the existing bearing plates, it is acceptable to replace the existing bearing plates with 65B04299-8, 65B04299-14 or 65B04299-16 bearing plates. (k) Refer to SOPM 20-30-02 as an accepted procedure. (l) Grind bearing plate to the dimensions shown. It is acceptable to use other methods of machining. Maintain a surface roughness of 125 microinches RA or better. Refer to SOPM 20-10-02 as an accepted procedure. (m) Apply hard chrome plating to the reworked area only, thickness 0.002 to 0.004 inches. Refer to SOPM 20-42-03 as an accepted procedure. (n) Mark the part with the part number 65B04299-7-747-53A2835 to show that it has been modified by this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure. The equivalent production part number is 65B04299-7. (o) Mark the part with the part number 65B04299-8-747-53A2835 to show that it has been modified by this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure. The equivalent production part number is 65B04299-8.

**FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 10 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 80 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (p) Apply solid film lubricant to the surfaces shown. Refer to SOPM 20-50-08 Type 8, Class 1 as an accepted procedure. (q) OPTION A: Install 65B04299-7, 65B04299-13 or 65B04299-15 bearing plates. OPTION B: Install 65B04299- 7-747-53A2835 bearing plates. (r) OPTION A: Install 65B04299-8, 65B04299-14 or 65B04299-16 bearing plates. OPTION B: Install 65B04299- 8-747-53A2835 bearing plates. (s) Install bearing plate wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Refer to SOPM 20-50-19 as an accepted procedure. (t) Install fastener wet with BMS5-95 TYPE 1, CLASS C sealant. Make sure threads, shank and countersink are completely coated. Fillet seal nut with BMS5-95 TYPE 1, CLASS B sealant. Make sure the nut is completely covered. Refer to SOPM 20-50-19 as an accepted procedure. (u) OPTION A: Install 69B02005-4, 69B02005-5 or 69B02005-6 latch pins. OPTION B: Install 69B02005-4- 747-53A2835 latch pins. (v) Install latch pin wet with BMS5-95 TYPE 1, CLASS B sealant on the faying surface. Make sure sealant is applied to both the outside diameter of the latch pin and the inside diameter of the latch fitting. Make sure all excess sealant is removed. Refer to SOPM 20-50-19 as an accepted procedure. (w) Refer to SOPM 20-50-19 as an accepted procedure.

**FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE MODIFICATION OR REPLACEMENT**  **(SHEET 11 OF 11)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 28, 2010 747-53A2835 81 of 81 **BOEING SERVICE BULLETIN 747-53A2835 ALERT**  **ALERT**