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.

ECCN: 9E991

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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Unpublished Work - All Rights Reserved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,

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4.0
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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

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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.

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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

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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.

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GROUP CONFIGURATION DESCRIPTION

1 - 747 airplanes line numbers 1 through 263 and 265.

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

2 - 747 airplanes line numbers 264 and 266 through 1078.

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

3 - 747 airplanes line numbers 1079 through 1419.

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

Variable Number Group

RA001 - RA034 1

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Variable Number Group

RA101 - RA115 1

RA161 - RA164 1

RA201 - RA203 1

RA216 - RA217 1

RA245 - RA246 1

RA251 - RA265 1

RA266 2

RA301 - RA317 1

RA318 2

RA351 - RA360 1

RA369 - RA373 1

RA401 - RA418 1

RA501 - RA502 1

RA521 - RA528 1

RA532 - RA543 1

RA544 - RA548 2

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 1

RA725 - RA731 2

RA741 - RA745 1

RA749 1

RA750 2

RA761 - RA762 1

RA781 - RA783 1

RA784 2

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Variable Number Group

RA901 - RA916 1

RB001 - RB010 1

RB011 - RB012 2

RB013 - RB016 1

RB041 - RB044 1

RB071 - RB075 1

RB101 - RB102 1

RB411 - RB413 2

RB421 2

RB601 - RB607 1

RB681 - RB697 2

RB711 2

RB721 - RB723 2

RB741 - RB748 2

RD001 - RD004 1

RD021 - RD022 1

RD041 - RD044 1

RD045 - RD059 2

RD071 - RD072 1

RD081 - RD083 2

RD091 - RD092 2

RD101 - RD104 1

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 2

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Variable Number Group

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 2

RD621 - RD622 1

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 2

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Variable Number Group

RD761 2

RD771 - RD775 2

RD781 - RD783 2

RD791 - RD792 2

RE001 2

RF001 - RF006 3

RG001 1

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 2

RJ131 - RJ133 1

RJ151 - RJ152 2

RJ301 - RJ303 2

RJ321 - RJ322 2

RJ331 - RJ333 2

RL401 - RL403 3

RL411 - RL436 3

RL451 - RL456 3

RL461 - RL462 3

RL471 - RL481 3

RL491 - RL492 3

RL501 - RL502 3

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Variable Number Group

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 3

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Variable Number Group

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 3

RR001 - RR005 2

RR021 - RR025 2

RR031 2

RR201 1

RR202 - RR206 2

RR221 1

RR222 - RR226 2

RR261 1

RR262 - RR267 2

RR301 1

RR302 - RR310 2

RR331 - RR332 2

RR336 2

RR341 - RR342 1

RR343 - RR345 2

RR361 - RR362 2

RR421 - RR422 2

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ALERT ALERT
Variable Number Group

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 2

RR723 - RR724 3

RR746 - RR747 2

RR748 3

RR851 - RR854 2

RR855 - RR856 3

RR861 - RR862 3

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 2

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ALERT ALERT
Variable Number Group

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 2

RT012 - RT014 3

RT021 - RT022 2

RT031 - RT033 2

RT034 - RT035 3

RT041 - RT047 2

RT061 2

RT071 - RT075 2

RT101 - RT103 2

RT121 2

RT131 - RT134 2

RT135 - RT137 3

RT151 - RT152 2

RT161 - RT168 2

RT401 - RT412 2

RT431 - RT441 2

RT442 - RT447 3

RT451 - RT469 2

RT471 - RT499 2

RT501 - RT535 2

RT551 - RT568 2

RT571 - RT588 2

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ALERT ALERT
Variable Number Group

RT589 - RT590 3

RT591 2

RT601 - RT622 2

RT623 - RT630 3

RT631 - RT636 2

RT637 - RT640 3

RT641 - RT657 2

RT671 - RT673 2

RT681 - RT682 2

RT691 - RT699 2

RT701 - RT704 2

RT711 - RT717 2

RT741 - RT755 2

RT756 - RT757 3

RT776 - RT777 2

RT781 - RT784 2

RT801 - RT803 3

RT811 - RT814 3

RT831 - RT833 2

RT834 - RT837 3

RT861 - RT864 2

RT876 - RT880 2

RT931 - RT932 2

RT945 - RT946 2

RT947 - RT949 3

RT951 - RT954 2

RT955 3

RT966 - RT967 2

RU001 - RU004 2

RU005 - RU006 3

RU016 - RU017 3

RU031 - RU032 2

RU051 - RU052 2

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Variable Number Group

RU059 - RU062 2

RU081 - RU083 2

RU101 - RU102 3

RU121 - RU124 2

RU125 - RU132 3

RU801 - RU809 2

RU831 - RU841 2

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.

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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

Model Zone

747-100, 747-200B, 747-200C, 122, 142

747-200F, 747SP, 747SR

Group 2:

Affected Maintenance Zones

Model Zone

747-100, 747-100B, 747-100B 122, 142

SUD, 747-200B, 747-200C,

747-200F, 747-300, 747-400,

747-400D, 747-400F, 747SP,

747SR

Group 3:

Affected Maintenance Zones

Model Zone

747-400, 747-400F 122, 142

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.

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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)

Condition Action

Within 1,000 -

flight cycles after the original

issue date of

this service

bulletin

Before 6,000

total flight cycles

Do a general visual inspection

for broken or missing latch pins

and a detailed inspection of the

latch pins for cracking in accordance with Paragraph 3.B.,

Work Instructions, Step 2.

All airplanes

Replace each broken or missing Before further flight. -

latch pin and replace the latch

pin(s) adjacent to each broken

or 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

Replace each cracked latch pin Before further flight -

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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 3.B., Work Instructions, Step 2.

Doors without 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.

(a) Replacement of a latch pin is not terminating action for the inspections of that latch pin.

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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)

Condition Action

Within 1,000 -

flight cycles after the original

issue date of

this service

bulletin

Before 6,000

total flight cycles

Do a general visual inspection

for broken or missing latch pins

and a detailed inspection of the

latch pins for cracking in accordance with Paragraph 3.B.,

Work Instructions, Step 3.

All airplanes

Replace each broken or missing Before further flight. -

latch pin and replace the latch

pin(s) adjacent to each broken

or 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

Replace each cracked latch pin Before further flight -

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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 3.B., Work Instructions, Step 3.

Doors without 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.

(a) Replacement of a latch pin is not terminating action for the inspections of that latch pin.

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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)

Condition Action

Within 1,000 -

flight cycles after the original

issue date of

this service

bulletin

Before 6,000

total flight cycles

Do a general visual inspection

for broken or missing latch pins

and a detailed inspection of the

latch pins for cracking in accordance with Paragraph 3.B.,

Work Instructions, Step 4.

All airplanes

Replace each broken or missing Before further flight. -

latch pin and replace the latch

pin(s) adjacent to each broken

or 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

Replace each cracked latch pin Before further flight -

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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 3.B., Work Instructions, Step 4.

Doors without 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.

(a) Replacement of a latch pin is not terminating action for the inspections of that latch pin.

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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)

Condition Action

Within 1,000 -

flight cycles after the original

issue date of

this service

bulletin

Before 6,000

total flight cycles

Do a general visual inspection

for broken or missing latch pins

and a detailed inspection of the

latch pins for cracking in accordance with Paragraph 3.B.,

Work Instructions, Step 5.

All airplanes

Replace each broken or missing Before further flight. -

latch pin and replace the latch

pin(s) adjacent to each broken

or 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

Replace each cracked latch pin Before further flight -

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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 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 missing

latch pins and the detailed inspection of the latch pins for

cracking in accordance with

Paragraph 3.B., Work Instructions, Step 5.

Doors without 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.

(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.

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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:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 1 1.00 1.00

FIGURE 2 (a) 2 8.00 4.00

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE (a) 9.50 5.50

(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:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 1 1.00 1.00

FIGURE 3 (a) 2 8.00 4.00

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE (a) 9.50 5.50

(a) This estimate includes replacement of all 16 latch pins. It may not be necessary

to replace all 16 latch pins.

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BOEING SERVICE BULLETIN 747-53A2835

ALERT ALERT
Group 1, Configuration 3:

OPTION 1: DO NOT MODIFY THE LATCH FITTINGS

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 1 1.00 1.00

FIGURE 4 (a) 2 8.00 4.00

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE (a) 9.50 5.50

(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

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 1 1.00 1.00

FIGURE 6 (a) 2 36.00 18.00

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE (a) 37.50 19.50

(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

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 1 1.00 1.00

FIGURE 5 (a) 2 8.00 4.00

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE (a) 9.50 5.50

(a) This estimate includes replacement of all 16 latch pins. It may not be necessary

to replace all 16 latch pins.

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ALERT ALERT
Group 1, Configuration 4:

OPTION 2: MODIFY THE LATCH FITTINGS

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 1 1.00 1.00

FIGURE 7 (a) 2 36.00 18.00

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE (a) 37.50 19.50

(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

Drawing Number Title

65B04216 SILL INSTL - LOWER MAIN, FWD CARGO DOOR

65B04642 SILL INSTALLATION - LOWER MAIN, AFT CARGO DOOR

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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.

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ALERT ALERT
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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:

Existing Part Notes

Number

Part Number / Specification QTY Name

69B02005-6 (69B02005-4 or 16 PIN, LATCH 69B02005-4 OR (a) (b)

65B02005-5 optional) 69B02005-5 OR

69B02005-6

PRESSURE AND ENVIRON- - (c)

MENTAL SEALANT-CHROMATE TYPE

BMS5-95 TYPE 1, CLASS B 8 Oz

(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:

Existing Part Notes

Number

Part Number / Specification QTY Name

65B04299-1 OR (a)

65B04299-5

65B04299-15 (65B04299-7 or 8 BEARING PLATE

65B04299-13 optional)

65B04299-2 OR (a)

65B04299-6

65B04299-16 (65B04299-8 or 8 BEARING PLATE

65B04299-14 optional)

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ALERT ALERT
Group 1, Configuration 3-4:

Existing Part Notes

Number

Part Number / Specification QTY Name

69B02005-6 (69B02005-3, 16 LATCH PIN 69B02005-3 (b) (c) (d)

69B02005-4 or 65B02005-5 optional)

SOLID FILM LUBRICANT, - (e)

LIQUID DISPERSED

BMS3-8 TYPE I 8 Oz

PRESSURE AND ENVIRON- - (e)

MENTAL SEALANT-CHROMATE TYPE

BMS5-95 TYPE 1, CLASS B 8 Oz

PRESSURE AND ENVIRON- - (e)

MENTAL SEALANT-CHROMATE TYPE

BMS5-95 TYPE 1, CLASS C 8 Oz

(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.

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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.

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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.

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect LATCH PIN 69B02005-( ) 8 (a)

2 Inspect LATCH PIN 69B02005-( ) 8 (b)

(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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove SEALANT - - (a)

2 Remove / Keep BOLT - 8 (a)

Remove / Keep WASHER - 8 (a)

Remove / Keep BRACKET ASSY - 8 (a)

3 Remove LATCH PIN 69B02005-( ) 8 (a) (b)

69B02005-6 8 (a) (c)

(69B02005-4 or

69B02005-5 optional)

4 Install (New) LATCH PIN

5 Install (Kept) BOLT - 8 (a)

Install (Kept) WASHER - 8 (a)

Install (Kept) BRACKET ASSY - 8 (a)

BMS5-95 TYPE 1, - (a) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

6 Apply

7 Remove SEALANT - - (e)

8 Remove / Keep BOLT - 8 (e)

Remove / Keep WASHER - 8 (e)

Remove / Keep BRACKET ASSY - 8 (e)

9 Remove LATCH PIN 69B02005-( ) 8 (e) (b)

69B02005-6 8 (e) (c)

(69B02005-4 or

69B02005-5 optional)

10 Install (New) LATCH PIN

11 Install (Kept) BOLT - 8 (e)

Install (Kept) WASHER - 8 (e)

Install (Kept) BRACKET ASSY - 8 (e)

BMS5-95 TYPE 1, - (e) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

12 Apply

(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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove SEALANT - - (a)

2 Remove / Keep BOLT - 8 (a)

Remove / Keep WASHER - 8 (a)

Remove / Keep NUT - 8 (a)

3 Remove LATCH PIN 69B02005-( ) 8 (a) (b)

69B02005-6 8 (a) (c)

(69B02005-4 or

69B02005-5 optional)

4 Install (New) LATCH PIN

5 Install (Kept) BOLT - 8 (a)

Install (Kept) WASHER - 8 (a)

Install (Kept) NUT - 8 (a)

BMS5-95 TYPE 1, - (a) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

6 Apply

7 Remove SEALANT - - (e)

8 Remove / Keep BOLT - 8 (e)

Remove / Keep WASHER - 8 (e)

Remove / Keep NUT - 8 (e)

9 Remove LATCH PIN 69B02005-( ) 8 (e) (b)

69B02005-6 8 (e) (c)

(69B02005-4 or

69B02005-5 optional)

10 Install (New) LATCH PIN

11 Install (Kept) BOLT - 8 (e)

Install (Kept) WASHER - 8 (e)

Install (Kept) NUT - 8 (e)

BMS5-95 TYPE 1, - (e) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

12 Apply

(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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove SEALANT - - (a)

2 Remove / Keep BOLT - 8 (a)

Remove / Keep WASHER - 8 (a)

Remove / Keep BRACKET ASSY - 8 (a)

3 Remove LATCH PIN 69B02005-( ) 8 (a) (b)

4 Install (New) LATCH PIN 69B02005-3 8 (a) (c)

5 Install (Kept) BOLT - 8 (a)

Install (Kept) WASHER - 8 (a)

Install (Kept) BRACKET ASSY - 8 (a)

BMS5-95 TYPE 1, - (a) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

6 Apply

7 Remove SEALANT - - (e)

8 Remove / Keep BOLT - 8 (e)

Remove / Keep WASHER - 8 (e)

Remove / Keep BRACKET ASSY - 8 (e)

9 Remove LATCH PIN 69B02005-( ) 8 (e) (b)

10 Install (New) LATCH PIN 69B02005-3 8 (e) (c)

11 Install (Kept) BOLT - 8 (e)

Install (Kept) WASHER - 8 (e)

Install (Kept) BRACKET ASSY - 8 (e)

BMS5-95 TYPE 1, - (e) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

12 Apply

(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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove SEALANT - - (a)

2 Remove / Keep BOLT - 8 (a)

Remove / Keep WASHER - 8 (a)

Remove / Keep NUT - 8 (a)

3 Remove LATCH PIN 69B02005-( ) 8 (a) (b)

4 Install (New) LATCH PIN 69B02005-3 8 (a) (c)

5 Install (Kept) BOLT - 8 (a)

Install (Kept) WASHER - 8 (a)

Install (Kept) NUT - 8 (a)

BMS5-95 TYPE 1, - (a) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

6 Apply

7 Remove SEALANT - - (e)

8 Remove / Keep BOLT - 8 (e)

Remove / Keep WASHER - 8 (e)

Remove / Keep NUT - 8 (e)

9 Remove LATCH PIN 69B02005-( ) 8 (e) (b)

10 Install (New) LATCH PIN 69B02005-3 8 (e) (c)

11 Install (Kept) BOLT - 8 (e)

Install (Kept) WASHER - 8 (e)

Install (Kept) NUT - 8 (e)

BMS5-95 TYPE 1, - (e) (d)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

12 Apply

(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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove SEALANT - -

2 Remove / Keep BOLT - 8

Remove / Keep WASHER - 8

Remove / Keep BRACKET ASSY - 8

3 Remove / Keep LATCH PIN 69B02005-3 8 (a)

65B04299-1 OR 8

65B04299-5

4 Remove / Keep BEARING PLATE

Remove / Keep BOLT - 24

Remove / Keep WASHER - 24

Remove / Keep NUT - 24

5 Grind LATCH PIN 69B02005-3 8 (b) (c)

Inspect LATCH PIN 69B02005-3 8 (b) (d)

Shot Peen LATCH PIN 69B02005-3 8 (b) (e)

Apply CADMIUM PLATE - - (b) (f)

Identify LATCH PIN 69B02005-3 8 (b) (g)

SOLID FILM LUBRI- BMS3-8, TYPE I - (b) (h)

CANT, LIQUID DISPERSED

Apply

6 Remove Old finish and plating - - (i) (k)

65B04299-1 OR 8 (i) (l)

65B04299-5

Grind BEARING PLATE

65B04299-1 OR 8 (i) (d)

65B04299-5

Inspect BEARING PLATE

65B04299-1 OR 8 (i) (e)

65B04299-5

Shot Peen BEARING PLATE

HARD CHROME - - (i) (m)

PLATE

Apply

65B04299-1 OR 8 (i) (n)

65B04299-5

Identify BEARING PLATE

SOLID FILM LUBRI- BMS3-8, TYPE I - (i) (p)

CANT, LIQUID DISPERSED

7 Apply

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

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BOEING SERVICE BULLETIN 747-53A2835

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

65B04299-15 8 (q) (s)

(65B04299-13 or

65B04299-7 optional)

8 Install (New) BEARING PLATE

65B04299-7-747- 8 (q) (s)

53A2835

Install (Changed) BEARING PLATE

Install (Kept) BOLT - 24 (t)

Install (Kept) WASHER - 24 (t)

Install (Kept) NUT - 24 (t)

69B02005-6 8 (u) (v)

(69B02005-4 or

69B02005-5 optional)

9 Install (New) LATCH PIN

69B02005-4-747- 8 (u) (v)

53A2835

Install (Changed) LATCH PIN

10 Install (Kept) BOLT - 8

Install (Kept) WASHER - 8

Install (Kept) BRACKET ASSY - 8

BMS5-95 TYPE 1, - (w)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

11 Apply

12 Remove SEALANT - -

13 Remove / Keep BOLT - 8

Remove / Keep WASHER - 8

Remove / Keep BRACKET ASSY - 8

14 Remove / Keep LATCH PIN 69B02005-3 8 (a)

65B04299-2 OR 8

65B04299-6

15 Remove / Keep BEARING PLATE

Remove / Keep BOLT - 24

Remove / Keep WASHER - 24

Remove / Keep NUT - 24

FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE

MODIFICATION OR REPLACEMENT

(SHEET 8 OF 11)

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67 of 81

BOEING SERVICE BULLETIN 747-53A2835

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

16 Grind LATCH PIN 69B02005-3 8 (b) (c)

Inspect LATCH PIN 69B02005-3 8 (b) (d)

Shot Peen LATCH PIN 69B02005-3 8 (b) (e)

Apply CADMIUM PLATE - - (b) (f)

Identify LATCH PIN 69B02005-3 8 (b) (g)

SOLID FILM LUBRI- BMS3-8, TYPE I - (b) (h)

CANT, LIQUID DISPERSED

Apply

17 Remove Old finish and plating - - (j) (k)

65B04299-2 OR 8 (j) (l)

65B04299-6

Grind BEARING PLATE

65B04299-2 OR 8 (j) (d)

65B04299-6

Inspect BEARING PLATE

65B04299-2 OR 8 (j) (e)

65B04299-6

Shot Peen BEARING PLATE

HARD CHROME - - (j) (m)

PLATE

Apply

65B04299-2 OR 8 (j) (o)

65B04299-6

Identify BEARING PLATE

SOLID FILM LUBRI- BMS3-8, TYPE I - (j) (p)

CANT, LIQUID DISPERSED

18 Apply

65B04299-16 8 (r) (s)

(65B04299-14 or

65B04299-8 optional)

19 Install (New) BEARING PLATE

65B04299-8-747- 8 (r) (s)

53A2835

Install (Changed) BEARING PLATE

Install (Kept) BOLT - 24 (t)

Install (Kept) WASHER - 24 (t)

Install (Kept) NUT - 24 (t)

69B02005-6 8 (u) (v)

(69B02005-4 or

69B02005-5 optional)

20 Install (New) LATCH PIN

69B02005-4-747- 8 (u) (v)

53A2835

Install (Changed) LATCH PIN

FIGURE 6: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE

MODIFICATION OR REPLACEMENT

(SHEET 9 OF 11)

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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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

21 Install (Kept) BOLT - 8

Install (Kept) WASHER - 8

Install (Kept) BRACKET ASSY - 8

BMS5-95 TYPE 1, - (w)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

22 Apply

(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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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)

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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

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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

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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

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove SEALANT - -

2 Remove / Keep BOLT - 8

Remove / Keep WASHER - 8

Remove / Keep NUT - 8

3 Remove / Keep LATCH PIN 69B02005-3 8 (a)

65B04299-1 OR 8

65B04299-5

4 Remove / Keep BEARING PLATE

Remove / Keep BOLT - 24

Remove / Keep WASHER - 24

Remove / Keep NUT - 24

5 Grind LATCH PIN 69B02005-3 8 (b) (c)

Inspect LATCH PIN 69B02005-3 8 (b) (d)

Shot Peen LATCH PIN 69B02005-3 8 (b) (e)

Apply CADMIUM PLATE - - (b) (f)

Identify LATCH PIN 69B02005-3 8 (b) (g)

SOLID FILM LUBRI- BMS3-8, TYPE I - (b) (h)

CANT, LIQUID DISPERSED

Apply

6 Remove Old finish and plating - - (i) (k)

65B04299-1 OR 8 (i) (l)

65B04299-5

Grind BEARING PLATE

65B04299-1 OR 8 (i) (d)

65B04299-5

Inspect BEARING PLATE

65B04299-1 OR 8 (i) (e)

65B04299-5

Shot Peen BEARING PLATE

HARD CHROME - - (i) (m)

PLATE

Apply

65B04299-1 OR 8 (i) (n)

65B04299-5

Identify BEARING PLATE

SOLID FILM LUBRI- BMS3-8, TYPE I - (i) (p)

CANT, LIQUID DISPERSED

7 Apply

FIGURE 7: LOWER LOBE FORWARD AND AFT CARGO DOORS - LATCH PIN AND BEARING PLATE

MODIFICATION OR REPLACEMENT

(SHEET 7 OF 11)

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Copyright © Unpublished Work - See page 1 for details.

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BOEING SERVICE BULLETIN 747-53A2835

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

65B04299-15 8 (q) (s)

(65B04299-13 or

65B04299-7 optional)

8 Install (New) BEARING PLATE

65B04299-7-747- 8 (q) (s)

53A2835

Install (Changed) BEARING PLATE

Install (Kept) BOLT - 24 (t)

Install (Kept) WASHER - 24 (t)

Install (Kept) NUT - 24 (t)

69B02005-6 8 (u) (v)

(69B02005-4 or

69B02005-5 optional)

9 Install (New) LATCH PIN

69B02005-4-747- 8 (u) (v)

53A2835

Install (Changed) LATCH PIN

10 Install (Kept) BOLT - 8

Install (Kept) WASHER - 8

Install (Kept) NUT - 8

BMS5-95 TYPE 1, - (w)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

11 Apply

12 Remove SEALANT - -

13 Remove / Keep BOLT - 8

Remove / Keep WASHER - 8

Remove / Keep NUT - 8

14 Remove / Keep LATCH PIN 69B02005-3 8 (a)

65B04299-2 OR 8

65B04299-6

15 Remove / Keep BEARING PLATE

Remove / Keep BOLT - 24

Remove / Keep WASHER - 24

Remove / Keep NUT - 24

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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

16 Grind LATCH PIN 69B02005-3 8 (b) (c)

Inspect LATCH PIN 69B02005-3 8 (b) (d)

Shot Peen LATCH PIN 69B02005-3 8 (b) (e)

Apply CADMIUM PLATE - - (b) (f)

Identify LATCH PIN 69B02005-3 8 (b) (g)

SOLID FILM LUBRI- BMS3-8, TYPE I - (b) (h)

CANT, LIQUID DISPERSED

Apply

17 Remove Old finish and plating - - (j) (k)

65B04299-2 OR 8 (j) (l)

65B04299-6

Grind BEARING PLATE

65B04299-2 OR 8 (j) (d)

65B04299-6

Inspect BEARING PLATE

65B04299-2 OR 8 (j) (e)

65B04299-6

Shot Peen BEARING PLATE

HARD CHROME - - (j) (m)

PLATE

Apply

65B04299-2 OR 8 (j) (o)

65B04299-6

Identify BEARING PLATE

SOLID FILM LUBRI- BMS3-8, TYPE I - (j) (p)

CANT, LIQUID DISPERSED

18 Apply

65B04299-16 8 (r) (s)

(65B04299-14 or

65B04299-8 optional)

19 Install (New) BEARING PLATE

65B04299-8-747- 8 (r) (s)

53A2835

Install (Changed) BEARING PLATE

Install (Kept) BOLT - 24 (t)

Install (Kept) WASHER - 24 (t)

Install (Kept) NUT - 24 (t)

69B02005-6 8 (u) (v)

(69B02005-4 or

69B02005-5 optional)

20 Install (New) LATCH PIN

69B02005-4-747- 8 (u) (v)

53A2835

Install (Changed) LATCH PIN

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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

21 Install (Kept) BOLT - 8

Install (Kept) WASHER - 8

Install (Kept) NUT - 8

BMS5-95 TYPE 1, - (w)

CLASS B

PRESSURE AND ENVIRONMENTAL

SEALANT-CHROMATE

TYPE

22 Apply

(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
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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