Commercial 

Airplanes 727

Service Bulletin

ALERT

Number: 727-52A0150

Original Issue: January 30, 2012

Revision 1: November 05, 2015

ATA System: 5211

SUBJECT: DOORS - Main Cargo Door - Cam Latch and Latch Pin Inspection and Modification

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). 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

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2012 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and

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2.0
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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 26

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 29

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 31

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 1: MAIN CARGO DOOR - CAM LATCHES AND LATCH PINS INSPECTION . . . . . . . . . 39

FIGURE 2: MAIN CARGO DOOR - LATCH PIN CROSS BOLT TORQUE . . . . . . . . . . . . . . . . 42

FIGURE 3: MAIN CARGO DOOR - LATCH PIN EXTENSION MEASUREMENT . . . . . . . . . . . . 44

FIGURE 4: MAIN CARGO DOOR - CAM LATCH 1 AND CAM LATCH 2 INSPECTION . . . . . . . . 46

FIGURE 5: MAIN CARGO DOOR - LATCH PIN CROSS BOLT REPLACEMENT . . . . . . . . . . . 48

FIGURE 6: MAIN CARGO DOOR - CAM LATCH REPLACEMENT . . . . . . . . . . . . . . . . . . . 50

FIGURE 7: MAIN CARGO DOOR - LATCH PIN REPLACEMENT . . . . . . . . . . . . . . . . . . . . 53

FIGURE 8: MAIN CARGO DOOR - CAM LATCH REMOVAL AND INSPECTION . . . . . . . . . . . 55

FIGURE 9: MAIN CARGO DOOR - CAM LATCHES. LATCH PINS AND LATCH PIN CROSS BOLTS

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
FIGURE 10: MAIN CARGO DOOR - CAM LATCH AND LATCH PIN RIGGING . . . . . . . . . . . . . 61

FIGURE 11: MAIN CARGO DOOR - MAIN CARGO DOOR EDGE FLUSHNESS MEASUREMENT . . 64

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST . . . . . . . . . . . . . . . . . . . . . . . . . 66

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
Commercial 

Airplanes 727

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 727-52A0150

Original Issue: January 30, 2012

Revision 1: November 05, 2015

ATA System: 5211

SUBJECT: DOORS - Main Cargo Door - Cam Latch and Latch Pin Inspection and Modification

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-132-AD, is related to

this service bulletin.

Effects of this Revision on airplanes on which Original Issue was previously done:

None.

REASON FOR REVISION

This revision is sent to clarify the requirements of the compliance tables.

These sections were changed:

1. Summary - BACKGROUND: Text revised to include more detailed information. Summary Evaluation

Table revised to reflect this revision.

2. Summary - ACTION: Text revised to include more detailed information.

3. Summary - COMPLIANCE: Notice of Proposed Rule Making added.

4. Summary - Graphic: Illustration revised to align with the changes made in this revision.

5. Paragraph 1.C. Reason: Text revised to include more detailed information.

6. Paragraph 1.B. Concurrent Requirements: Test revised to clarify requirement.

7. Paragraph 1.D. Description: Text revised to include more detailed information.

8. Paragraph 1.E. Compliance: NPRM statement added. Compliance Tables 1 and 2 revised to clarify

inspections, conditions and actions.

9. Paragraph 1.G. Manpower: Footnote in table revised to show NDI inspection.

10. Paragraph 1.H. Weight and Balance: Table added to show 727-100C/-200F and 727C airplanes.

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11. Paragraph 1.J. References: Component Maintenance Manual (CMM), Illustrated Parts Catalog (IPC)

and Structural Repair Manual (SRM) references added, and, Notice of Proposed Rule Making and

Standard Overhaul Practices Manual revised.

12. Paragraph 1.K. Publications Affected: Added a table to show the different publications affected and

information on cam latch repairs.

13. Paragraph 1.M. Software Accomplishment. Added.

14. Paragraph 2.C.2. Parts and Materials Supplied by the Operator: Added footnote (g).

15. Paragraph 3.A. General Information: Added new information.

16. Paragraph 3.B. Work Instructions: Revised to show new conditions and text.

17. Figures 1 thru 10: Illustrations and step tables revised to align with the changes made in this revision.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
Commercial 

Airplanes 727

Service Bulletin

ALERT

Summary Number: 727-52A0150

Original Issue: January 30, 2012

Revision 1: November 05, 2015

ATA System: 5211

SUBJECT: DOORS - Main Cargo Door - Cam Latch and Latch Pin Inspection and Modification

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

Accomplishment of the inspections in this service bulletin will make sure the Main Cargo Door (MCD) cam latches

are inspected for damage and the latch pins are inspected for damage and migration. The inspections are

necessary in order to find and replace damaged cam latches, latch pins and latch pin cross bolts. If not replaced,

damaged cam latches, latch pins and latch pin cross bolts could lead to a failure of the cam latches and may

result in a possible rapid decompression and potential separation of the main cargo door from the airplane.

Boeing has received one report from one 757 operator that the MCD forward most cam latch on the forward

center cam latch pair (cam latch number 3) broke during flight. The 757 airplane with the reported broken cam

latch had accumulated 20,000 flight hours and 9,500 flight cycles when the cam latch broke. The crew heard a

loud noise coming from the MCD shortly after reaching cruise. Upon landing, an inspection was performed and

a cam latch was found broken. The broken cam latch mating latch pin was also found to have significant wear

as evidenced by the loss of the plating on the surface that is normally in contact with the cam latch. The latch

pin was also deformed approximately 0.05 inch in the area of the wear surface. The latch pin cross bolt was

unserviceable.

The 727 MCD is of similar design to the 757 MCD. Boeing has not received any reports of a broken cam latch

on a 727 MCD.

The cause of the broken cam latch has been determined to be from a poorly rigged MCD. Although properly

rigged per the original Aircraft Maintenance Manual (AMM) procedures, significant variation was allowed in the

rigging dimensions. This variation can cause some of the latch pin/cam latch locations to have a significant

preload placed on them during engagement and rotation of the cam latches during latching and unlatching

operations. This preload is believed to have imparted a torque on the latch pin from the cam latch rotation during

latching and unlatching operations. The torque transmitted to the latch pin is then believed to have caused the

latch pin cross bolt to fail in shear.

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If the latch pin cross bolt fails, the latch pin could migrate either towards the cam latch or away from the cam

latch. Latch pin migration towards the cam latch can cause significant interference with the mating cam latch

leading to cam latch damage. In the 757 case, the latch pin migrated into the cam latch and caused damage to

the cam latch. The crack initiated at the damage site caused by the latch pin and then led to the cam latch

breaking. Latch pin migration away from the cam latch could cause disengagement from the cam latch, resulting

in no load transfer between the cam latch and the mating latch pin and may not be noticed before critical

conditions are exceeded in adjacent cam latches or latch pins.

Accomplishment of the work given in this service bulletin will make sure the cam latches, latch pins and latch

pins cross bolts are inspected and repaired or replaced as required. The MCD rig will be verified to the Service

Bulletin requirements and if necessary, the MCD will be re-rigged to the AMM requirements.

Boeing Service Related Problem (SRP) 727-SRP-52-0088 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 727 FTD 52-09001 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight No Paragraph 1.K., Publications Affected

Crew Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required No Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required Yes

ACTION

Get access to the MCD. Do a general visual inspection of the cam latches, latch pins and latch pin cross bolts.

Torque the cross bolts in the latch pins. Measure the extension of the latch pins. Replace all alloy steel cross

bolts through the latch pins with Corrosion Resistant Steel (CRES) cross bolts. Check for lip deformation on all

cam latches. Do a High Frequency Eddy Current (HFEC) or magnetic particle inspection of cam latch 1 and

cam latch 2 for cracks. Replace any cracked or broken parts. Check the rig of the MCD to the requirements of

the Service Bulletin and if necessary, the MCD will be re-rigged to the latest AMM requirements. Do repetitive

general visual and detailed inspections of the cam latches and latch pins after the rig is verified or adjusted. Do

repetitive HFEC or magnetic particle inspections of cam latch 1 and cam latch 2 for cracks after the rig is verified

or adjusted.

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
EFFECTIVITY

727-100C, 727-200F and 727C airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-132-AD, is related to

this service bulletin.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspections and modifications 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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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
Commercial 

Airplanes 727

Service Bulletin

ALERT

Number: 727-52A0150

Original Issue: January 30, 2012

Revision 1: November 05, 2015

ATA System: 5211

SUBJECT: DOORS - Main Cargo Door - Cam Latch and Latch Pin Inspection and Modification

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624N001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

1 - 727-100C, 727-200F and 727C airplanes with a Main Cargo Door.

Airplane Models:

727-100C, 727-200F, 727C

Variable Number Group

E5001 - E5011 1

E5031 - E5068 1

E5101 - E5116 1

E5141 - E5143 1

E5161 - E5164 1

E5201 - E5203 1

E5221 - E5245 1

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Variable Number Group

E5251 - E5252 1

E5271 - E5281 1

E5301 - E5306 1

E5351 - E5353 1

E5381 - E5382 1

E5401 - E5424 1

E5426 - E5429 1

E5433 1

E5435 1

E5451 - E5455 1

E5481 - E5483 1

E5501 - E5502 1

QL501 - QL515 1

2. Spares Affected

None.

B. Concurrent Requirements

The service bulletin listed below must be done before or at the same time as this service bulletin.

Company Service Bulletin Description

Latch Cam Replacement and Pressure Relief

Door Hinge Fitting Replacement.

727-52-0142, Original Issue, or Revision 01, or Revision 02 (a)Boeing

(a) Federal Aviation Administration (FAA) Airworthiness Directive AD 91-22-04 is related

to service bulletin 727-52-0142.

C. Reason

Accomplishment of the inspections in this service bulletin will make sure the Main Cargo Door (MCD)

cam latches are inspected for damage and the latch pins are inspected for damage and migration. The

inspections are necessary in order to find and replace damaged cam latches, latch pins and latch pin

cross bolts. If not replaced, damaged cam latches, latch pins and latch pin cross bolts could lead to a

failure of the cam latches and may result in a possible rapid decompression and potential separation

of the main cargo door from the airplane.

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
Boeing has received one report from one 757 operator that the MCD forward most cam latch on the

forward center cam latch pair (cam latch number 3) broke during flight. The 757 airplane with the

reported broken cam latch had accumulated 20,000 flight hours and 9,500 flight cycles when the cam

latch broke. The crew heard a loud noise coming from the MCD shortly after reaching cruise. Upon

landing, an inspection was performed and a cam latch was found broken. The broken cam latch mating

latch pin was also found to have significant wear as evidenced by the loss of the plating on the surface

that is normally in contact with the cam latch. The latch pin was also deformed approximately 0.05 inch

in the area of the wear surface. The latch pin cross bolt was unserviceable.

The 727 MCD is of similar design to the 757 MCD. Boeing has not received any reports of a broken

cam latch on a 727 MCD.

The cause of the broken cam latch has been determined to be from a poorly rigged MCD. Although

properly rigged per the original Aircraft Maintenance Manual (AMM) procedures, significant variation

was allowed in the rigging dimensions. This variation can cause some of the latch pin/cam latch locations

to have a significant preload placed on them during engagement and rotation of the cam latches during

latching and unlatching operations. This preload is believed to have imparted a torque on the latch pin

from the cam latch rotation during latching and unlatching operations. The torque transmitted to the

latch pin is then believed to have caused the latch pin cross bolt to fail in shear.

If the latch pin cross bolt fails, the latch pin could migrate either towards the cam latch or away from

the cam latch. Latch pin migration towards the cam latch can cause significant interference with the

mating cam latch leading to cam latch damage. In the 757 case, the latch pin migrated into the cam

latch and caused damage to the cam latch. The crack initiated at the damage site caused by the latch

pin and then led to the cam latch breaking. Latch pin migration away from the cam latch could cause

disengagement from the cam latch, resulting in no load transfer between the cam latch and the mating

latch pin and may not be noticed before critical conditions are exceeded in adjacent cam latches or

latch pins.

Accomplishment of the work given in this service bulletin will make sure the cam latches, latch pins

and latch pins cross bolts are inspected and repaired or replaced as required. The MCD rig will be

verified to the Service Bulletin requirements and if necessary, the MCD will be re-rigged to the AMM

requirements.

Boeing Service Related Problem (SRP) 727-SRP-52-0088 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 727 FTD 52-09001 is related to this service bulletin.

D. Description

Get access to the MCD. Do a general visual inspection of the cam latches, latch pins and latch pin

cross bolts. Torque the cross bolts in the latch pins. Measure the extension of the latch pins. Replace

all alloy steel cross bolts through the latch pins with Corrosion Resistant Steel (CRES) cross bolts.

Check for lip deformation on all cam latches. Do a High Frequency Eddy Current (HFEC) or magnetic

particle inspection of cam latch 1 and cam latch 2 for cracks. Replace any cracked or broken parts.

Check the rig of the MCD to the requirements of the Service Bulletin and if necessary, the MCD will

be re-rigged to the latest AMM requirements. Do repetitive general visual and detailed inspections of

the cam latches and latch pins after the rig is verified or adjusted. Do repetitive HFEC or magnetic

particle inspections of cam latch 1 and cam latch 2 for cracks after the rig is verified or adjusted.

Effects of this Revision on airplanes on which Original Issue was previously done:

None.

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

727-100C, 727-200F, 727C 2-48

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.

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-132-AD, is

related to this service bulletin.

If all Table 1 requirements, including rigging of the main cargo door, have been accomplished in

accordance with the original issue of this service bulletin, continue repetitive inspections in accordance

with Table 2.

If Table 1 requirements have not been accomplished in accordance with the original issue of this service

bulletin, then all Table 1 requirements, including rigging of the main cargo door, must be accomplished

before starting Table 2 requirements.

Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

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BOEING SERVICE BULLETIN 727-52A0150

ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Within 150 days -

after the original

issue date of

this service bulletin.

Within 330 flight

cycles after the

original issue

date of this service bulletin.

Do the following for all

MCD cam latches and

latch pins:

Do a general visual inspection for any broken

cam latches, latch pins

and latch pin cross bolts,

and for any missing cam

latches, latch pins and

latch pin cross bolts in

accordance with Step 1.b.

All airplanes

AND

Torque the cross bolts in

the latch pins in accordance with Step 1.c.

AND

Measure the extension of

the latch pins in accordance with Step 1.d.

AND

Do a general visual inspection of all cam latches for lip deformation in

accordance with Step 1.e.

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ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Replace broken and Before further flight. -

missing cam latches,

latch pins and latch pin

cross bolts in accordance

with Step 2.a.

Condition 1: One or more

of the following is found:

1. Broken or missing

cam latch(es).

2. Broken or missing

latch pin(s).

3. Broken or missing

latch pin cross

bolt(s).

AND

Do a detailed inspection

of mating part(s) and immediately adjacent cam

latch(es) and latch pin(s)

for any cracks, or any

gouges in critical areas in

accordance with Step 2.b.

AND

Unless replaced with new

or reworked parts,do a

HFEC or magnetic particle inspection of cam

latch 1 and cam latch 2

for any cracks in critical

areas in accordance with

Step 2.c. (b)

AND

Check the rig of the MCD

and do the latch mechanism adjustment test in

accordance with Step 2.d.

AND

Replace all alloy steel

cross bolts through the

latch pins with CRES

cross bolts in accordance

with Step 2.d.

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ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Within 150 days -

after the latch

pin extension

was measured.

Within 330 flight

cycles after the

latch pin extension was measured.

Replace the discrepant

latch pin in accordance

with Step 3.a.

AND

Do a detailed inspection

of the mating cam latch

for any cracks, or gouges

in critical areas in accordance with Step 3.b.

Condition 2: The latch pin

extension is less than 0.89

inches or greater than 0.91

inches.

330 flight cycles or

150 days,

whichever occurs

first. (a)

Do the following for all -

MCD cam latches and

latch pins:

Do a general visual inspection for any broken

cam latches, latch pins

and latch pin cross bolts,

and for any missing cam

latches, latch pins and

latch pin cross bolts in

accordance with Step 3.c.

AND

Within 24 -

months after the

original issue

date of this service bulletin.

Within 3,000

flight cycles after the original

issue date of

this service bulletin.

Do a detailed inspection

of all the latch pin(s) and

mating cam latch(es) for

any cracks, or gouges in

critical areas in accordance with Step 3.d.

Within 24 -

months after the

original issue

date of this service bulletin.

Within 3,000

flight cycles after the original

issue date of

this service bulletin.

Unless replaced with new

or reworked parts, do a

HFEC or magnetic particle inspection of cam

latch 1 and cam latch 2

for any cracks in critical

areas in accordance with

Step 3.e. (b)

AND

Check the rig of the MCD

and do the latch mechanism adjustment test in

accordance with Step 3.f.

AND

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ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Replace all alloy steel

cross bolts through the

latch pins with CRES

cross bolts in accordance

with Step 3.f.

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ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

330 flight cycles or

150 days,

whichever occurs

first. (a)

Within 150 days

after the initial

inspection.

Within 330 flight

cycles after the

initial inspection.

Do a detailed inspection

of the discrepant cam

latch and mating latch pin

for any cracks, or gouges

in critical areas in accordance with Step 4.a.

Condition 3: If a cam latch

is found with lip deformation.

AND

330 flight cycles or

150 days,

whichever occurs

first. (a)

Do the following for all -

MCD cam latches and

latch pins:

Do a general visual inspection for any broken

cam latches, latch pins

and latch pin cross bolts,

and for any missing cam

latches, latch pins and

latch pin cross bolts in

accordance with Step 4.b.

AND

Within 24 -

months after the

original issue

date of the service bulletin.

Within 3,000

flight cycles after the original

issue date of the

service bulletin.

Do a detailed inspection

of latch pin(s) and mating

cam latch(es) for any

cracks, or gouges in critical areas in accordance

with Step 4.c.

AND

Within 24 -

months after the

original issue

date of the service bulletin.

Within 3,000

flight cycles after the original

issue date of the

service bulletin.

Unless replaced with new

or reworked parts, do a

HFEC or magnetic particle inspection of cam

latch 1 and cam latch 2

for any cracks in critical

areas in accordance with

Step 4.d. (b)

AND

Check the rig of the MCD

and do the latch mechanism adjustment test in

accordance with Step 4.e.

AND

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ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Replace all alloy steel

cross bolts through the

latch pins with CRES

cross bolts in accordance

with Step 4.e.

330 flight cycles or

150 days,

whichever occurs

first. (a)

Do a general visual in- -

spection for any broken

or missing cam latches,

latch pins and latch pin

cross bolts in accordance

with Step 5.a.

Condition 4: No discrepancies found. (c)

3,000 flight cycles

or 24 months,

whichever occurs

first. (a)

Within 24

months after the

initial inspection.

Within 3,000

flight cycles after the initial inspection.

Do a detailed inspection

of the cam latches and

latch pins for any cracks,

or any gouges in critical

areas in accordance with

Step 5.b.

AND

Unless replaced with new

or reworked parts, do a

HFEC or magnetic particle inspection of cam

latch 1 and cam latch 2

for any cracks in critical

areas in accordance with

Step 5.c. (b)

Within 48 -

months after the

original issue

date of this service bulletin.

Within 6,000

flight cycles after the original

issue date of

this service bulletin.

Check the rig of the MCD

and do the latch mechanism adjustment test in

accordance with Step 5.d.

AND

Replace all alloy steel

cross bolts through the

latch pins with CRES

cross bolts in accordance

with Step 5.d.

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ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Replace cracked and Before further flight. -

gouged cam latch(es)

and latch pin(s) in accordance with Step 6.a.

Condition 5: If the detailed,

HFEC or magnetic particle

inspections specified in the

Actions of Conditions 1 thru

4 reveal any of the following:AND

Do a detailed inspection

of mating part(s) and immediately adjacent cam

latch(es) and latch pin(s)

for any cracks, or any

gouges in critical areas in

accordance with Step 6.b.

Do all applicable corrective actions as described

in Condition 5.

1. Cracked or

gouged cam

latch(es) in critical

areas.

2. Cracked or

gouged latch

pin(s) in critical

areas.

AND

Unless replaced with new

or reworked parts, do a

HFEC or magnetic particle inspection of cam

latch 1 and cam latch 2

for any cracks in critical

areas in accordance with

Step 6.c. Do all applicable corrective actions as

described in Condition 5.

(b)

AND

Check the rig of the MCD

and do the latch mechanism adjustment test in

accordance with Step 6.d.

AND

Replace all alloy steel

cross bolts through the

latch pins with CRES

cross bolts in accordance

with Step 6.d.

(a) All Table 1 repeat inspections are terminated when the rig of the MCD has been checked in accordance

with Paragraph 3.B., Work Instructions. Refer to Table 2 for post-rig check inspection requirements.

(b) A reworked cam latch is defined as a cam latch that has been reworked within limits of CMM 52-36-61,

or CMM 52-36-62 and/or a Boeing ODA approved repair via FAA Form 8100-9 and has been HFEC or

magnetic particle inspected, and has no crack(s) or gouge(s) in critical area(s).

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ALERT ALERT
Table 1: Initial and Repetitive Inspections of the Cam Latches, Latch Pins and Latch Pin Cross Bolts

for the Main Cargo Door (Pre-Rig Check)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

(c) Discrepancy is defined as: Any broken, cracked, missing or gouged cam latches or latch pins, broken or

missing latch pin cross bolts, latch pin extension less than 0.89 inches or greater than 0.91 inches, or

cam latch lip deformation.

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ALERT ALERT
Table 2: Repetitive Inspection Requirements for Airplanes that have accomplished All Table 1 Requirements, Including Rigging of the Main Cargo Door in accordance with the Original Issue or Revision 1

of this service bulletin.

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 375 flight cycles after the 375 flight cycles.

rig of the MCD was checked.

Do a general visual inspection for any broken

or missing cam latch(es),

latch pin(s) and latch pin

cross bolt(s) in accordance with Step 7.a.(1).

All airplanes that have accomplished all Table 1 requirements, including rigging of the main cargo door

in accordance with the

original issue or revision 1

of this service bulletin and

no rigging adjustment of

any latch pin or any latch

pin fitting was required.

If latch pin flight cycles are known: 3000 flight cycles.

Before 40,000 total latch pin flight

cycles.

Do a detailed inspection

of the latch pins for any

cracks, or any gouges in

critical areas in accordance with Step 7.a.(2). If latch pin flight cycles are un- 3000 flight cycles.

known:

AND

During previous pre-rig

check inspection no discrepancy was found. (b)

Within 3,000 flight cycles after the

rig of the MCD was checked.

If cam latch flight cycles are 3,000 flight cycles.

known and cam latch is not a reworked part: (a)

Do a detailed inspection

of the cam latches for any

cracks, or any gouges in

critical areas in accordance with Step 7.a.(2).Before 40,000 total cam latch flight

cycles.

If cam latch flight cycles are un- 3,000 flight cycles.

known or if cam latch is a reworked part: (a)

Within 3,000 flight cycles after the

rig of the MCD was checked.

If cam latch flight cycles are 6,000 flight cycles.

known and cam latch is not a reworked part: (a)

Do a HFEC or magnetic

particle inspection of cam

latch 1 and cam latch 2

for any cracks in critical

areas in accordance with

Step 7.a.(3).

Before 40,000 total cam latch flight

cycles.

If cam latch flight cycles are un- 6,000 flight cycles.

known or if cam latch is a reworked part: (a)

Within 6,000 flight cycles after the

rig of the MCD was checked.

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ALERT ALERT
Table 2: Repetitive Inspection Requirements for Airplanes that have accomplished All Table 1 Requirements, Including Rigging of the Main Cargo Door in accordance with the Original Issue or Revision 1

of this service bulletin.

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 375 flight cycles after the 375 flight cycles.

rig of the MCD was checked.

Do a general visual inspection for any broken

or missing cam latch(es),

latch pin(s) and latch pin

cross bolt(s) in accordance with Step 8.a.(1).

All airplanes that have accomplished all Table 1 requirements, including rigging of the main cargo door

in accordance with the

original issue or revision 1

of this service bulletin and

rigging adjustment of any

latch pin or any latch pin

fitting was required.

Within 3,000 flight cycles after the 3,000 flight cycles.

rig of the MCD was checked.

Do a detailed inspection

of the cam latches and

latch pins for any cracks,

or any gouges in critical

areas in accordance with

Step 8.a.(2).

OR

During previous pre-rig

check inspection, any discrepancy was found. (b) Within 6,000 flight cycles after the 6,000 flight cycles.

rig of the MCD was checked.

Do a HFEC or magnetic

particle inspection of cam

latch 1 and cam latch 2

for any cracks in critical

areas in accordance with

Step 8.a.(3).

Contact The Boeing Before further flight. -

Company for repair instructions and do the repair.

Any discrepancy found.

(a) A reworked cam latch is defined as a cam latch that has been reworked within limits of CMM 52-36-61,

or CMM 52-36-62 and/or a Boeing ODA approved repair via FAA Form 8100-9 and has been HFEC or

magnetic particle inspected, and has no crack(s) or gouge(s) in critical area(s).

(b) Discrepancy is defined as: Any broken, cracked, missing or gouged cam latches or latch pins, broken or

missing latch pin cross bolts, latch pin extension less than 0.89 inches or greater than 0.91 inches, or

cam latch lip deformation.

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.

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.

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ALERT ALERT
G. Manpower

The table below shows an estimate of the task hours necessary to do the inspections and modifications

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.

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 1 1.60 1.60

FIGURE 2 1 0.50 0.50

FIGURE 3 1 0.50 0.50

FIGURE 4 1 1.00 (h) 1.00 (h)

FIGURE 5 1 1.00 1.00

FIGURE 6 1 (i) 0.50 (a) (f) (i) 0.50 (a) (f) (i)

FIGURE 7 1 0.10 (b) (g) 0.10 (b) (g)

FIGURE 8 1 0.60 (c) 0.60 (c)

FIGURE 9 1 0.10 (d) 0.10 (d)

FIGURE 10 - FIGURE 2-3 48.00 20.00

11

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE (e) (e)

(a) Estimate is per cam latch requiring replacement.

(b) Estimate is per latch pin requiring replacement.

(c) Estimate is per cam latch requiring inspection.

(d) Estimate is per cam latch.

(e) Total time required may vary depending upon conditions found during inspections.

(f) Does not include time to match drill cam shaft.

(g) Does not include time to match drill latch pin.

(h) Does not include NDI inspection time.

(i) Cam latch 4 will require 2 hours and a second person to remove.

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ALERT ALERT
H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

727-100C Negligible Negligible

727-200F Negligible Negligible

727C Negligible Negligible

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Boeing Service Bulletin 727-52-0142

b. Boeing Service Related Problem (SRP) 727-SRP-52-0088

c. Component Maintenance Manual (CMM) 52-36-61, 52-36-62,

d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 91-22-04

e. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2012-NM-132-AD.

f. Standard Overhaul Practices Manual (SOPM) 20-20-01, 20-50-01

g. 727 Aircraft Maintenance Manual (AMM) 52-34-00

h. 727 Illustrated Parts Catalog (IPC) 52-30

i. 727 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00

j. 727 Structural Repair Manual (SRM) 51-00-6

2. Data Supplied with this Service Bulletin:

None.

3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

65-25326 DOOR INSTALLATION - MAIN CARGO

65-25339 LATCH MECHANISM INSTALLATION - MAIN CARGO DOOR

65-40507 SILL INSTL - LOWER, MAIN CARGO DOOR

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ALERT ALERT
Drawing Number Title

65-67872 LATCH PIN FITTING - ASSY

69-23438 CAM - LATCH MECHANISM CARGO DOOR

The table above lists applicable drawings 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:

Publication Chapter-Section

727 Aircraft Maintenance Manual 727 AMM 52-34

727 Illustrated Parts Catalog 727 IPC 52-30

727 Component Maintenance Manual CMM 52-36-61 or CMM 52-36-62

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 and new DTI requirements for the structure

affected are contained in Paragraph 1.E., Compliance of this service bulletin.

Repairs accomplished on cam latch(es) in accordance with CMM 52-36-61 or CMM 52-36-62 are

structurally acceptable as Category A repairs as defined in 727 SRM 51-00-6, therefore no

supplemental inspections to the mandated damage tolerance inspections contained in Paragraph

1.E., Compliance, Table 2, of this service bulletin, are required.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
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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 inspections and modifications given in this service

bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Part Number / QTY Name Notes

Specification

BOLT, HEX HEAD, 160 KSI MIN (a) (b)

TENSILE, LONG THREAD, A286,

NONLOCKING

BACB30LM3-24 8

OR BACB30LM3-

22

Parts are only needed if existing part cannot be reworked. (c) (g)69-23438-2 - Cam Latch 1

143N8060-1 - Cam Latch 2

143N8027-2 - Cam Latch 3

69-23439-3 - Cam Latch 4

69-23439-4 - Cam Latch 5

143N8027-1 - Cam Latch 6

143N8060-2 - Cam Latch 7

69-23438-1 - Cam Latch 8

6-83137-2 - Latch Pin

BMS 3-27 5 oz Corrosion Inhibiting Compound (d)

BMS 5-95, TYPE 5 oz Pressure and Environmental Sealant (d)

1, CLASS B-1/2

Flexbar ReproRubber Quicksetting (e)

Putty or equivalent.

- 8 oz

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ALERT ALERT
Part Number / QTY Name Notes

Specification

Rod, 3/16 inch diameter., 2 inch (f)

length

- 1

(a) Refer to 727 Structural Repair Manual Chapter 51 for alternate fasteners.

(b) BACB30LM3-24 is used if optional 143N8157-2 Clip Assembly is installed.

(c) Drill attachment holes to the new latch cam to match with the existing bell crank assembly

to ensure proper installation and clocking.

(d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

(e) Available from Flexbar Machine Corp. (2R260), 250 Gibbs Road, Islandia, NY 11749,

USA.

(f) Used for aligning the rigging pin slot with the cross bolt hole in accordance with APPENDIX

A.

(g) Part numbers and quantities necessary are based on inspection findings.

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

Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service

Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of

the service bulletin. The tool(s) are subject to the terms and conditions of the Boeing standard purchase

order acknowledgement. Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

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ALERT ALERT
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Purchase Data:

Unit Price as of the Revision

1 date of this Service Bulletin (US Dollars)

Tool Kit Number Name

Pin Set - Rigging, Main Deck, Main Cargo 8,821.00

Door

B52029-1

Rental Data

Daily Price as of the Revision 1 date of this service

bulletin (US Dollars)

Tool Kit Number Name

Pin Set - Rigging, Main Deck, Main Cargo 180.00

Door

B52029-1

F. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be

necessary. Examine operator tool supply to make sure all necessary tools are available.

Tool Kit Number Name

B52029-1 Pin Set - Rigging, Main Deck, Main Cargo Door

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ALERT ALERT

BLANK PAGE
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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. 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

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 727 Structural Repair Manual,

Chapter 51.

4. Use the approved fastener, process and material substitutions in accordance with

SRM Chapter 51.

5. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

6. Clearance between fasteners and surrounding structures or mechanisms may be

minimal by design at some locations. Use caution when adjusting grip length of

fasteners and make sure no interference conditions exist after installation. Interference

between moving parts may be difficult to detect. Complete full cycle of mechanisms

to ensure no interference conditions exist.

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 procedures may be required.

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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. Refer to Appendix A for LATCH MECHANISM ADJUSTMENT TEST.

11. Boeing Service Letter 727-SL-51-041 Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

12. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

13. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

14. 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.

15. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

16. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is

permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'

(dash) part number. Boeing Drawing 005W0900 contains more data.

17. Damage found on cam latch(es) within the reworkable limits of CMM 52-36-61 or

CMM 52-36-62 can be reworked in accordance with CMM 52-36-61 or CMM 52-36-62.

18. A reworked cam latch is defined as a cam latch that has been reworked within the

limits of CMM 52-36-61 or CMM 52-36-62 and/or a Boeing ODA approved repair via

FAA Form 8100-9 and has been HFEC or magnetic particle inspected, and has no

crack(s) or gouge(s) in critical area(s).

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19. Discrepancy is defined as: Any broken, cracked, missing or gouged cam latches or

latch pins, broken or missing latch pin cross bolts, latch pin extension less than 0.89

inches or greater than 0.91 inches, or cam latch lip deformation.

20. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

B. WORK INSTRUCTIONS

1. Initial (Pre-Rig Check) Inspections

a. Get access to the Main Cargo Door (MCD).

b. Do a general visual inspection for any broken cam latches, latch pins and latch pin cross bolts

and for any missing cam latches, latch pins and latch pin cross bolts in accordance with

FIGURE 9 .

c. Torque the cross bolts in the latch pins in accordance with FIGURE 2.

d. Measure the extension of the latch pins in accordance with FIGURE 3.

e. Do a general visual inspection of all cam latches for lip deformation in accordance with FIGURE

1.

2. Condition 1:

One or more of the following is found:

– Broken or missing cam latch(es)

– Broken or missing latch pin(s)

– Broken or missing latch pin cross bolt(s)

a. Replace broken and missing cam latch(es) in accordance with FIGURE 6, replace broken

and missing latch pin(s) in accordance with FIGURE 7 and replace broken and missing latch

pin cross bolt(s) in accordance with FIGURE 5.

b. Do a detailed inspection of mating part(s) and immediately adjacent cam latches and latch

pins for any cracks, or any gouges in critical areas in accordance with FIGURE 8. Do all

applicable corrective actions as described in Condition 5.

c. Unless replaced with new or reworked parts, do a High Frequency Eddy Current (HFEC)

inspection or magnetic particle inspection of cam latch 1 and cam latch 2 for cracks in critical

areas in accordance with FIGURE 4. Do all applicable corrective actions as described in

Condition 5.

d. Check the rig of the MCD in accordance with FIGURE 10 and FIGURE 11, and replace all

alloy steel cross bolts through the latch pins with CRES cross bolts in accordance with FIGURE

5. If MCD is out of rig and cannot be adjusted in accordance with FIGURE 10 and FIGURE

11, rig the MCD. Refer to 727 AMM 52-34-00 as an accepted procedure for MCD rigging, and

do the latch mechanism adjustment test in accordance with APPENDIX A.

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3. Condition 2:

The latch pin extension is less than 0.89 inches or greater than 0.91 inches:

a. Replace the discrepant latch pin in accordance with FIGURE 7.

b. Do a detailed inspection of the mating cam latch for any cracks, or gouges in critical areas in

accordance with FIGURE 8. Do all applicable corrective actions as described in Condition 5.

c. Do a general visual inspection for any broken cam latches, latch pins and latch pin cross bolts

and for any missing cam latches, latch pins and latch pin cross bolts in accordance with

FIGURE 9. Do all applicable corrective actions as described in Condition 1.

d. Do a detailed inspection of all the latch pin(s) and mating cam latch(es) for any cracks, or any

gouges in critical areas in accordance with FIGURE 1. Do all applicable corrective actions as

described in Condition 5.

e. Unless replaced with new or reworked parts, do a HFEC or magnetic particle inspection of

cam latch 1 and cam latch 2 for any cracks in critical areas in accordance with FIGURE 4. Do

all applicable corrective actions as described in Condition 5.

f. Check the rig of the MCD in accordance with FIGURE 10 and FIGURE 11, and replace all

alloy steel cross bolts through the latch pins with CRES cross bolts in accordance with FIGURE

5. If MCD is out of rig and cannot be adjusted in accordance with FIGURE 10 and FIGURE

11, rig the MCD. Refer to 727 AMM 52-34-00 as an accepted procedure for MCD rigging,

and do the latch mechanism adjustment test in accordance with APPENDIX A.

NOTE: Rigging for the latch pin will require it to be installed with an extension of 0.90 +/-

0.01 inches. A latch pin with an original extension between 0.84 to 0.94 inches, with

no cracks or gouges in critical areas and no other discrepancies may be used by

clocking the latch pin 90 degrees +/- 10 degrees from original position and match

drilling a new cross bolt hole that provides the correct latch pin extension. Fill old

cross bolt hole in pin with BMS 5-95 sealant and install pin with BMS 3-27 corrosion

inhibiting compound.

4. Condition 3:

If a cam latch is found with lip deformation.

a. Do a detailed inspection of the discrepant cam latch and mating latch pin for any cracks, or

gouges in critical areas in accordance with FIGURE 1. Do all applicable corrective actions as

described in Condition 5.

b. Do a general visual inspection for any broken cam latches, latch pins and latch pin cross bolts

and for any missing cam latches, latch pins and latch pin cross bolts in accordance with

FIGURE 9 . Do all applicable corrective actions as described in Condition 1.

c. Do a detailed inspection of the latch pin(s) and mating cam latch(es) for any cracks, or any

gouges in critical areas in accordance with FIGURE 1. Do all applicable corrective actions as

described in Condition 5.

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d. Unless replaced with new or reworked parts, do a HFEC or magnetic particle inspection of

cam latch 1 and cam latch 2 for any cracks in critical areas in accordance with FIGURE 4. Do

all applicable corrective actions as described in Condition 5.

e. Check the rig of the MCD in accordance with FIGURE 10 and FIGURE 11, and replace all

alloy steel cross bolts through the latch pins with CRES cross bolts in accordance with FIGURE

5. If MCD is out of rig and cannot be adjusted in accordance with FIGURE 10 and FIGURE

11, rig the MCD. Refer to 727 AMM 52-34-00 as an accepted procedure for MCD rigging, and

do the latch mechanism adjustment test in accordance with APPENDIX A.

5. Condition 4:

No discrepancies found:

a. Do a general visual inspection for any broken or missing cam latches, latch pins and latch pin

cross bolts in accordance with FIGURE 9. Do all applicable corrective actions as described

in Condition 1.

b. Do a detailed inspection of the cam latches and latch pins for any cracks, or any gouges in

critical areas in accordance with FIGURE 1. Do all applicable corrective actions as described

in Condition 5.

c. Unless replaced with new or reworked parts, do a HFEC or magnetic particle inspection of

cam latch 1 and cam latch 2 for any cracks in critical areas in accordance with FIGURE 4. Do

all applicable corrective actions as described in Condition 5.

d. Check the rig of the MCD in accordance with FIGURE 10 and FIGURE 11, and replace all

alloy steel cross bolts through the latch pins with CRES cross bolts in accordance with FIGURE

5. If MCD is out of rig and cannot be adjusted in accordance with FIGURE 10 and FIGURE

11, rig the MCD. Refer to 727 AMM 52-34-00 as an accepted procedure for MCD rigging,

and do the latch mechanism adjustment test in accordance with APPENDIX A .

6. Condition 5:

If the detailed, HFEC inspection or magnetic particle inspection in Conditions 1 thru 4 reveal any

of the following:

– Cracked or gouged cam latch(es) in critical areas.

– Cracked or gouged latch pin(s) in critical areas.

a. Replace cracked or gouged cam latch(es) in accordance with FIGURE 6, replace cracked or

gouged latch pin(s) in accordance with FIGURE 7.

b. Do a detailed inspection of mating part(s) and immediately adjacent cam latches and latch

pins for any cracks or any gouges in critical areas in accordance with FIGURE 8. Do all

applicable corrective actions as described in Condition 5.

c. Unless replaced with new or reworked parts, do a HFEC or magnetic particle inspection of

cam latch 1 and cam latch 2 for any cracks in critical areas in accordance with FIGURE 4. Do

all applicable corrective actions as described in Condition 5.

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ALERT ALERT
d. Check the rig of the MCD in accordance with FIGURE 10 and FIGURE 11, and replace all

alloy steel cross bolts through the latch pins with CRES cross bolts in accordance with FIGURE

5. If MCD is out of rig and cannot be adjusted in accordance with FIGURE 10 and FIGURE

11, rig the MCD. Refer to 727 AMM 52-34-00 as an accepted procedure for MCD rigging, and

do the latch mechanism adjustment test in accordance with APPENDIX A .

7. Post Rig Check Repetitive Inspections.

a. Airplanes that have accomplished all Table 1 requirements identified in Paragraph 1.E.,

Compliance, including rigging of the MCD in accordance with the original issue or revision 1

of this service bulletin and no rigging adjustment of any latch pin or any latch pin fitting was

required, and during previous pre-rig check inspections there were no discrepancies found:

(1) Do a general visual inspection for any broken or missing cam latches, latch pins and latch

pin cross bolt in accordance with FIGURE 9.

(2) Do a detailed inspection of the cam latches and latch pins for any cracks or any gouges

in critical areas in accordance with FIGURE 1.

(3) Do a HFEC or magnetic particle inspection of cam latch 1 and cam latch 2 for any cracks

in critical areas, in accordance with FIGURE 4.

(4) If any discrepancy is found, contact The Boeing Company for repair instructions and do

the repair.

8. Post Rig Check Repetitive Inspections.

a. Airplanes that have accomplished all Table 1 requirements identified in Paragraph 1.E.,

Compliance, including rigging of the MCD in accordance with the original issue or revision 1

of this service bulletin and rigging adjustment of any latch pin or any latch pin fitting was

required, or during previous pre-rig check inspections there were any discrepancies found.

(1) Do a general visual inspection for any broken or missing cam latches, latch pins and latch

pin cross bolts in accordance with FIGURE 9.

(2) Do a detailed inspection of the cam latches and latch pins for any cracks or any gouges

in critical areas in accordance with FIGURE 1.

(3) Do a HFEC or magnetic particle inspection of cam latch 1 and cam latch 2 for any cracks

in critical areas in accordance with FIGURE 4.

(4) If any discrepancy is found, contact The Boeing Company for repair instructions and do

the repair.

9. Put the airplane back to a serviceable condition.

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FIGURE 1: MAIN CARGO DOOR - CAM LATCHES AND LATCH PINS INSPECTION

(SHEET 1 OF 3)

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FIGURE 1: MAIN CARGO DOOR - CAM LATCHES AND LATCH PINS INSPECTION

(SHEET 2 OF 3)

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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 Inspect Cam Latch 1 69-23438-2 1 (a) (b)

2 Inspect Cam Latch 2 143N8060-1 1 (a) (b)

3 Inspect Cam Latch 3 143N8027-2 1 (a) (b)

4 Inspect Cam Latch 4 69-23439-3 1 (a) (b)

5 Inspect Cam Latch 5 69-23439-4 1 (a) (b)

6 Inspect Cam Latch 6 143N8027-1 1 (a) (b)

7 Inspect Cam Latch 7 143N8060-2 1 (a) (b)

8 Inspect Cam Latch 8 69-23438-1 1 (a) (b)

9 Inspect Latch Pin 6-83137-2 8 (a)

(a) Do a detailed inspection for cracks or gouges in critical areas..

(b) Do a general visual inspection for lip deformation.

FIGURE 1: MAIN CARGO DOOR - CAM LATCHES AND LATCH PINS INSPECTION

(SHEET 3 OF 3)

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FIGURE 2: MAIN CARGO DOOR - LATCH PIN CROSS BOLT TORQUE

(SHEET 1 OF 2)

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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 Torque Cross Bolt - 8 (a)

(a) Make sure the latch pin cross bolt is capable of reaching a 15 pound-inch, +/- 1 pound-inch, torque from

the head side of the bolt and also the nut side if no nutplate is used. The 15 pound-inch, +/- 1 pound-inch,

torque value is approximately one-half of the installation torque and is used to give an indication of a

broken cross bolt.

FIGURE 2: MAIN CARGO DOOR - LATCH PIN CROSS BOLT TORQUE

(SHEET 2 OF 2)

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FIGURE 3: MAIN CARGO DOOR - LATCH PIN EXTENSION MEASUREMENT

(SHEET 1 OF 2)

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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

Make sure the latch

pin extends out 0.90

inch +/- 0.01 inch

from the wear plate.

1 Measure Latch Pin 6-83137-2 8

FIGURE 3: MAIN CARGO DOOR - LATCH PIN EXTENSION MEASUREMENT

(SHEET 2 OF 2)

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FIGURE 4: MAIN CARGO DOOR - CAM LATCH 1 AND CAM LATCH 2 INSPECTION

(SHEET 1 OF 2)

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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 / Keep Cam Latch 1 69-23438-2 1 -

2 Remove / Keep Cam Latch 2 143N8060-1 1 -

Do a HFEC inspection of cam latch 1

for cracks in accordance with 727 NDT

Part 6, 51-00-00

Procedure 13 or

Procedure 24. (a) (b)

(c)

3 Inspect Cam Latch 1 69-23438-2 1

Do a HFEC inspection of cam latch 2

for cracks in accordance with 727 NDT

Part 6, 51-00-00

Procedure 13 or

Procedure 24. (a) (b)

(c)

Inspect Cam Latch 2 143N8060-1 1

4 Install (Kept) Cam Latch 1 69-23438-2 1 -

5 Install (Kept) Cam Latch 2 143N8060-1 1 -

(a) Use a 0.080 inch diameter or smaller HFEC probe. Set the HFEC instrument to operate between 50 KHz

and 75 KHz. If HFEC method indicates a crack, confirm the crack indication using magnetic particle inspection. Refer to SOPM 20-20-01 as an accepted procedure.

(b) An optional magnetic particle inspection can be used. Refer to SOPM 20-20-01 as an accepted procedure.

(c) HFEC crack indications can be confirmed using the magnetic particle inspection. If crack indications are

found with HFEC and could not be confirmed with magnetic particle inspection, the HFEC crack indication

is a non relevant indication due to chrome cracking.

FIGURE 4: MAIN CARGO DOOR - CAM LATCH 1 AND CAM LATCH 2 INSPECTION

(SHEET 2 OF 2)

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FIGURE 5: MAIN CARGO DOOR - LATCH PIN CROSS BOLT REPLACEMENT

(SHEET 1 OF 2)

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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 Latch Pin Cross Bolt NAS6603-24 8 -

2 Remove / Keep Clip Assembly 143N8157-2 8 If installed.

3 Install (New) Latch Pin Cross Bolt BACB30LM3-24 8 (a) (b)

Install (Kept) Clip Assembly 143N8157-2 8 (b)

(a) Install with BMS 3-27 corrosion inhibiting compound on faying surfaces.

(b) Installation of 143N8157-2 clip assembly is optional. Use a BACB30LM3-24 bolt if clip assembly is installed.

Use a BACB30LM3-22 bolt if clip assembly is not installed.

FIGURE 5: MAIN CARGO DOOR - LATCH PIN CROSS BOLT REPLACEMENT

(SHEET 2 OF 2)

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FIGURE 6: MAIN CARGO DOOR - CAM LATCH REPLACEMENT

(SHEET 1 OF 3)

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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 Cam Latch 1 69-23438-2 1 (a)

Remove Cam Latch 2 143N8060-1 1 (a)

Remove Cam Latch 3 143N8027-2 1 (a)

(a) Gusset must be

removed to allow removal of cam latch

number 4.

Remove Cam Latch 4 69-23439-3 1

Remove Cam Latch 5 69-23439-4 1 (a)

Remove Cam Latch 6 143N8027-1 1 (a)

Remove Cam Latch 7 143N8060-2 1 (a)

Remove Cam Latch 8 69-23438-1 1 (a)

FIGURE 6: MAIN CARGO DOOR - CAM LATCH REPLACEMENT

(SHEET 2 OF 3)

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Step Task Name Identification Qty More Data

2 Install (New) Cam Latch 1 69-23438-2 1 (a) (b) (d)

Install (New) Cam Latch 2 143N8060-1 1 (a) (b) (c) (d)

Install (New) Cam Latch 3 143N8027-2 1 (a) (b) (d)

(a) (b) (d) Reinstall

gusset that was removed during the

removal step Latch

4

Install (New) Cam Latch 4 69-23439-3 1

Install (New) Cam Latch 5 69-23439-4 1 (a) (b) (d)

Install (New) Cam Latch 6 143N8027-1 1 (a) (b) (d)

Install (New) Cam Latch 7 143N8060-2 1 (a) (b) (c) (d)

Install (New) Cam Latch 8 69-23438-1 1 (a) (b) (d)

(a) Part numbers and quantities necessary are based on inspection findings.

(b) Use the original removed cam latch as a pattern/template to locate new cross bolt holes. Match hole angularity from existing cam latch.

(c) Cam latch number 2 and cam latch number 7 only have two cross bolt holes.

(d) It is acceptable to install a reworked Cam Latch with the same part number instead of a new part.

FIGURE 6: MAIN CARGO DOOR - CAM LATCH REPLACEMENT

(SHEET 3 OF 3)

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FIGURE 7: MAIN CARGO DOOR - LATCH PIN REPLACEMENT

(SHEET 1 OF 2)

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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

6-83137-2 (6-83137- - -

2000 optional)

1 Remove Latch Pin

Install latch pin wet

with BMS 3-27 corrosion inhibiting compound on faying surfaces. Make sure the

latch pin extends out

0.90 inch +/- 0.01

inch from the wear

plate.

6-83137-2 (6-83137- -

2000 optional)

2 Install (New) Latch Pin

FIGURE 7: MAIN CARGO DOOR - LATCH PIN REPLACEMENT

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 8: MAIN CARGO DOOR - CAM LATCH REMOVAL AND INSPECTION

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 8: MAIN CARGO DOOR - CAM LATCH REMOVAL AND INSPECTION

(SHEET 2 OF 4)

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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 / Keep Cam Latch 1 69-23438-2 1 (a) (b)

Remove / Keep Cam Latch 2 143N8060-1 1 (a) (b)

Remove / Keep Cam Latch 3 143N8027-2 1 (a) (b)

Remove / Keep Cam Latch 4 69-23439-3 1 (a) (b) (c)

Remove / Keep Cam Latch 5 69-23439-4 1 (a) (b)

Remove / Keep Cam Latch 6 143N8027-1 1 (a) (b)

Remove / Keep Cam Latch 7 143N8060-2 1 (a) (b)

Remove / Keep Cam Latch 8 69-23438-1 1 (a) (b)

Detailed inspection

of the cam latch for

cracks or gouges in

critical areas. (d)

2 Inspect Cam Latch - -

3 Install (Kept) Cam Latch 1 69-23438-2 1 (a) (b) (e)

Install (Kept) Cam Latch 2 143N8060-1 1 (a) (b) (e)

Install (Kept) Cam Latch 3 143N8027-2 1 (a) (b) (e)

(a) (b) (e) Reinstall

gusset that was removed during the

Latch 4 removal

step.

Install (Kept) Cam Latch 4 69-23439-3 1

Install (Kept) Cam Latch 5 69-23439-4 1 (a) (b) (e)

Install (Kept) Cam Latch 6 143N8027-1 1 (a) (b) (e)

Install (Kept) Cam Latch 7 143N8060-2 1 (a) (b) (e)

Install (Kept) Cam Latch 8 69-23438-1 1 (a) (b) (e)

Detailed inspection

of the latch pin for

cracks or gouges in

critical areas.

6-83137-2 (6-83137- 8

2000 optional)

4 Inspect Latch Pin

(a) It is important to identify the Cam Latch part locations to make sure the kept parts are installed in correct

locations. Cam latches installed incorrectly may seriously compromise proper door operation.

(b) Part numbers and quantities necessary are based on inspection findings.

(c) Gusset must be removed to allow removal of cam latch number 4.

(d) Only inspect removed cam latch(es).

FIGURE 8: MAIN CARGO DOOR - CAM LATCH REMOVAL AND INSPECTION

(SHEET 3 OF 4)

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ALERT ALERT
Step Task Name Identification Qty More Data

(e) Do not install kept cam latch if cracked or gouged in critical areas.

FIGURE 8: MAIN CARGO DOOR - CAM LATCH REMOVAL AND INSPECTION

(SHEET 4 OF 4)

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ALERT ALERT
FIGURE 9: MAIN CARGO DOOR - CAM LATCHES. LATCH PINS AND LATCH PIN CROSS BOLTS

INSPECTION

(SHEET 1 OF 2)

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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

General visual inspection of the cam

latch.(a)

1 Inspect Cam Latch 1 69-23438-2 1

General visual inspection of the cam

latch.(a)

Inspect Cam Latch 2 143N8060-1 1

General visual inspection of the cam

latch.(a)

Inspect Cam Latch 3 143N8027-2 1

General visual inspection of the cam

latch.(a)

Inspect Cam Latch 4 69-23439-3 1

General visual inspection of the cam

latch.(a)

Inspect Cam Latch 5 69-23439-4 1

General visual inspection of the cam

latch.(a)

Inspect Cam Latch 6 143N8027-1 1

General visual inspection of the cam

latch.(a)

Inspect Cam Latch 7 143N8060-2 1

General visual inspection of the cam

latch.(a)

Inspect Cam Latch 8 69-23438-1 1

General visual inspection of the latch

pins.(a)

6-83137-2 (6-83137- 8

2000 optional)

2 Inspect Latch Pin

General visual inspection of the latch

pin cross bolts. (a)

3 Inspect Latch Pin Cross Bolt - 8

(a) Do a general visual inspection for any broken or missing cam latches, latch pins and latch pin cross bolts.

FIGURE 9: MAIN CARGO DOOR - CAM LATCHES. LATCH PINS AND LATCH PIN CROSS BOLTS

INSPECTION

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 10: MAIN CARGO DOOR - CAM LATCH AND LATCH PIN RIGGING

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 10: MAIN CARGO DOOR - CAM LATCH AND LATCH PIN RIGGING

(SHEET 2 OF 3)

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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 Measure Cam Latch - 8 (a) (b) (d)

6-83137-2 (6-83137- 8 (a) (b) (d)

2000 optional)

Measure Latch Pin

Measure Latch Pin Fitting - 8 (c) (d)

(a) During rigging procedure the latch pin is not to contact the cam latch in any direction.

(b) Wrap a single layer of 0.002 inch thick shim stock around latch pins 1 and 8. Use thin tape to keep shim

in place. With latch pins 1 and 8 engaging their respective cam latches, and with latch pins 2 through 7

not contacting their respective cam latches in any direction, adjust if required, latch pin fittings 2 through

7 such that latch pins 2 through 7 axial centerlines and their respective cam latch axial centerlines are

within the tolerance shown.

(c) Adjust latch pin fittings by moving fitting on serrations and by adjusting shim thickness. On the two forward

and two aft cam latches the Latch Pin Fitting/Cam Latch gap is 0.14 +/- 0.01 inch. On the four center cam

latches the Latch Pin Fitting/Cam Latch gap is 0.08 +/- 0.01 inch. Make sure the maximum allowed shim

thickness of 0.20 inch is not exceeded.

(d) Refer to 727 AMM 52-34-00 as an accepted procedure for rigging.

FIGURE 10: MAIN CARGO DOOR - CAM LATCH AND LATCH PIN RIGGING

(SHEET 3 OF 3)

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FIGURE 11: MAIN CARGO DOOR - MAIN CARGO DOOR EDGE FLUSHNESS MEASUREMENT

(SHEET 1 OF 2)

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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 Measure Main Cargo Door - - (a) (b)

(a) Hold scale 90 degrees to door edge. Make sure the MCD lower edge and lower corner flushness are

within the tolerance shown.

(b) Refer to 727 AMM 52-34-00 as an accepted procedure for flushness measurement.

FIGURE 11: MAIN CARGO DOOR - MAIN CARGO DOOR EDGE FLUSHNESS MEASUREMENT

(SHEET 2 OF 2)

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ALERT ALERT
1. Prepare to Adjust the Latch Mechanisms (Appendix Figure A1.1)

WARNING: MAKE SURE THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR OF THE CARGO

DOOR PATH BEFORE YOU OPERATE THE CARGO DOOR CONTROL SWITCH. THE

CARGO DOOR CAN CONTINUE TO MOVE AFTER YOU RELEASE THE SWITCH.

THIS CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TO EQUIPMENT.

a. Electrically close the door to the "latched-and-locked" position.

b. Use tape to mark the approximate location of the cam latch head, locations 1 through 8, on the

external side of the door.

c. Measure the external cargo door flushness between the sill plate and the door at cam latch heads

1 through 8 (Appendix Figure A3).

d. Record the flushness measurements at cam latch head locations 1 through 8 (Appendix Figure

A4.1).

e. Open the main cargo door to approximately 1/4 of the fully open position.

f. Clean the lower sill area around the latch pins and latch pin fittings with a cotton cloth.

g. Clean the head and throat of the cam latches with a cotton cloth.

h. Remove the cross bolt and clip or the cross bolt and nut from the latch pin fitting at sill locations

2 through 7.

i. Remove the latch pins at sill fitting locations 2 through 7 from the latch pin fittings (Appendix Figure

A1.3).

j. Record the latch pin location to the mating latch pin fitting.

k. Clean the latch pin holes in the latch pin fittings.

l. Wrap a 0.002 in. (0.051 mm) shim fully around the latch pins at sill fitting locations 1 and 8, making

a full circle.

(1) Make sure that you do not overlap the shims.

(2) Use thin tape to hold the ends of the 0.002 in. (0.051 mm) shim.

(3) Turn the shim until the splice points to the inboard side of the latch pin.

m. Electrically close the door to the "latched-and-locked" position.

n. Make sure that the 0.002 in. (0.051 mm) shims are on the pins.

o. Record the external flushness values for cam latch head locations 1 through 8 (Appendix Figure

A4.1).

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST

(SHEET 1 OF 18)

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ALERT ALERT
NOTE: Flushness values show if it is necessary to adjust fittings 1 and 8. You will not rig the door

with these flushness values.

NOTE: Have the same person measure the flushness as measured earlier in the task.

p. Do these steps for latch fittings 1 and 8 if the lower edge flushness values are more than the

tolerances (Appendix Figure A3).

(1) Remove latch fitting fillet seals.

(2) Remove the cap seals.

(3) Remove the leveling compound.

(4) Record the location of the latch pin fitting on the mating serrated plate.

(5) Measure shim thickness to make sure that the latch pin fitting 1 and 8 adjustments can move

the door into the necessary flushness (Appendix Figure A1.3).

NOTE: If you remove 0.10 in. (2.54 mm) of the shim thickness, the door will move

approximately 0.07 in. (1.78 mm) in the inboard direction.

(6) Do these steps if the door is more than the flushness tolerance in this configuration:

(a) Remove only one of the setscrew lock wires.

(b) Loosen the setscrew to loosen the fitting.

(c) You may need to use a 1/4 inch 8 point socket.

(d) Remove the fitting.

(e) Record the location of the fasteners.

(f) Record the corresponding latch pin fitting location number on the serrated plate.

(g) Carefully clean the serrations and all mating surfaces. Be careful to not remove the

recorded location numbers and location marks.

(h) Adjust the latch pin shim thickness.

(i) If you move the latch pin fitting inboard, then increase the clearance between the stop

pin and the stop pad.

(j) Move the latch fitting up one serration if you removed more than 0.071 in. (1.803 mm)

shim thickness.

(k) Move the latch fitting down one serration if you added more than 0.071 in. (1.803 mm)

shim thickness.

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST

(SHEET 2 OF 18)

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(l) If necessary, change the length of the latch pin fitting fasteners for adjusted shim thickness.

(m) Install the latch pin fitting without the fillet seal.

(n) Make sure that the set screw is seated and tight.

(o) Install the three 0.5 in. (12.7 mm) bolts into the latch pin fitting with 200 in-lb (23 N m) to

225 in-lb (25 N m) torque.

(p) Install the 0.625 in. (15.875 mm) bolt into the latch pin fitting with 800 in-lb (90 N m) to

850 in-lb (96 N m) torque.

q. Make sure that the 0.002 in. (0.051 mm) shims are on latch pins 1 and 8.

WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN OR CLOSE THE CARGO

DOOR. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR

DAMAGE TO EQUIPMENT CAN OCCUR.

r. Manually close the door to the "latched and locked" position.

s. Make sure that there is forward/aft clearance between the cam latches and the latch pin fittings

when the door is closed.

t. If there is not forward/aft clearance, then adjust the cam latches and the latch pin fittings (Appendix

Figure A1.1).

u. Repeat the steps for the external flushness door measurements until the door is within the flushness

requirements (Appendix Figure A3).

(1) Use the Interim Flushness Recording Table to record measurements, if more adjustments

are necessary (Appendix Figure A4.1).

v. Electrically open the main cargo door to approximately 1/8 of the fully open position.

w. Make sure that the sequence valve has 0.40 in. (10.16 mm) to 0.50 in. (12.70 mm) clearance

(Appendix Figure A1.2).

x. Make sure that the cam latch hook is adjusted to the correct clearance.

2. Latch Mechanism Adjustment Test (Appendix Figure A4.1 - A4.5)

a. Put a piece of cardboard in front of the tooling hole in the cam latch throat.

NOTE: The cardboard prevents the rubber compound from entering the tooling holes. The

cardboard at the base of the cam latch will not impact the measurement.

(1) Mark the back of the cardboard with the corresponding latch numbers 2 through 7.

(2) Make sure that the cardboard is almost flush with the rear of the cam latch throat.

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST

(SHEET 3 OF 18)

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ALERT ALERT
b. At the latch pin fitting locations 2, 3, 5, 6, and 7, use the rigging pin set, B52029-1 and install the

long rig pins.

(1) Make sure that the end face of the smaller diameter is flush with the bearing plate on the

mating pin fitting.

(2) Align the long slot in the rigging pin with the inboard cross bolt hole on the latch pin fitting.

(3) It is acceptable to use a rod (3/16 Inch Diameter, 2 Inch Length), to align the rigging pin slot

with the cross bolt hole.

c. At latch pin fitting location 4, using the rigging pin set, B52029-1, install the short rig pin.

CAUTION: MAKE SURE THAT THE END OF THE SMALLER DIAMETER IS FLUSH WITH

THE BEARING PLATE ON THE MATING LATCH PIN FITTING. IF IT IS NOT FLUSH,

DAMAGE TO THE DOOR CAN OCCUR.

(1) Make sure that the end of the smaller diameter is flush with the bearing plate on the mating

latch pin fitting.

(2) Align the long slot in the rigging pin with the inboard cross bolt hole on the latch pin fitting.

(3) It is acceptable to use a rod (3/16 Inch Diameter, 2 Inch Length), to align the rigging pin slot

with the cross bolt hole.

d. Prepare door for "power on", but do not close the door.

e. Quickly mix a sufficient quantity of Flexbar ReproRubber Quicksetting Putty to fill each cam throat.

NOTE: In warm weather, you can decrease the catalyst compound by approximately 1/3 to

increase the working time.

f. Quickly put the Flexbar ReproRubber Quicksetting Putty into the cam throats at cam latch locations

2 through 7.

NOTE: This has to be done in less than 45 seconds for all cam latches.

g. Close the door to the "latched and locked" position before the rubber compound paste sets.

h. Quickly move the pins at latch pin fitting locations 2 through 7 into the cam throat.

NOTE: You must close the door and move the pins in less than 1 minute for all cam latch pairs.

(1) Make sure that the larger diameter touches the cam.

i. Let the Flexbar ReproRubber Quicksetting Putty set for 10 minutes at 72 Deg. F (22 Deg. C).

j. If possible, retract the rigging pins until the pins are flush with the bearing plate in the pin fitting.

k. Carefully open the main cargo door to approximately 1/4 of the fully open position.

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST

(SHEET 4 OF 18)

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ALERT ALERT
NOTE: The rubber compound can possibly fall out of the cam when the door moves.

(1) Look for the rubber compound molds. The molds can fall while the door opens.

l. Carefully remove the Flexbar ReproRubber Quicksetting Putty in each of the cams at latch pin

fitting locations 2 through 7.

m. Record the cam latch location onto the rubber compound, near the closed end of the rubber mold.

n. Cut the Flexbar ReproRubber Quicksetting Putty approximately 0.5 in. (12.7 mm) from the closed

end of the rubber compound mold, see Appendix A illustration.

(1) Keep the rubber piece with the cross-hair marks.

(2) Discard the rubber piece without the cross-hair marks.

o. Make extension lines on the cut piece.

(1) Align the extension lines with the cross-hair marks in the rubber compound mold.

p. Measure the thickness of the compound at the one line (measurement "A") and in the middle of

the two lines (measurement "B").

q. Record measurements "A" and "B" from the rubber compound molds, from latch pin locations 2

though 7, onto the Latch Mechanism Adjustment Worksheet.

(1) If measurement "A" is 0.179 in. (4.547 mm) to 0.229 in. (5.817 mm) and if no serration

adjustment is necessary, then do not adjust the latch pin fitting shim thickness.

(2) If measurement "A" is not 0.179 in. (4.547 mm) to 0.229 in. (5.817 mm) then adjust the latch

pin fitting shim thickness by the amount shown on the worksheet.

(3) If measurement "A" is 0.179 in. (4.547 mm) to 0.194 in. (4.928 mm) and if a serration adjustment

is necessary, then adjust the latch pin fitting shim.

(4) If measurement "A" is 0.195 in. (4.953 mm) to 0.213 in. (5.410 mm) and if a serration adjustment

is necessary, then do not adjust the latch pin fitting shim thickness.

(5) If measurement "A" is 0.214 in. (5.436 mm) to 0.229 in. (5.817 mm) and if a serration adjustment

is necessary, then adjust the latch pin fitting shim.

(6) If measurement "B" is 0.179 in. (4.547 mm) to 0.229 in. (5.817 mm) then do not adjust the

latch pin fitting serrations.

r. Calculate shim and serration adjustment values for each cam latch where adjustment is necessary.

s. Record the calculated values.

t. Calculate the shim thickness adjustment.

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST

(SHEET 5 OF 18)

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ALERT ALERT
u. Calculate the number of serrations necessary for adjustment.

3. Latch Mechanism Adjustment

a. If necessary, remove the latch fillet seal, cap seal, and leveling compound on latch pin fittings 2

through 7.

b. Record the location of the latch pin fitting on the mating serrated plate.

c. Record the shim thickness for the latch pin fittings that will be adjusted.

d. Remove only one of the setscrews lock wire.

e. If it is necessary, loosen the bolts sufficiently to adjust the serrations.

f. If it is necessary, remove the bolts to adjust the shims.

g. Loosen the setscrew to loosen the fitting.

(1) You may need to use a 1/4 inch 8 point socket.

h. Remove the fitting.

i. Record the location of the fasteners.

j. Record the corresponding latch pin fitting location number on the serrated plate.

k. Clean the serrations and all mating surfaces.

(1) Be careful to not remove the recorded location numbers and location marks.

l. Adjust the latch pin shim thickness as calculated on the Latch Mechanism Adjustment "A"Dimension

Worksheet (Appendix Figure A4.4).

(1) If necessary, change the length of the sill fitting fasteners for adjusted shim thickness.

m. Adjust the latch pin serrations as calculated on the Latch Mechanism Adjustment "B" Dimension

Worksheet (Appendix Figure A4.5).

(1) Make sure that the serrations are correctly engaged.

(2) Make sure that the set screw is seated and tight.

n. Install the latch fittings without the fillet seal.

(1) Install the three 0.5 in. (12.7 mm) bolts into the latch pin fitting with 200 in-lb (23 N m) to 225

in-lb (25 N m) torque.

(2) Install the 0.625 in. (15.875 mm) bolt into the latch pin fitting with 800 in-lb (90 N m) to 850

in-lb (96 N m) torque.

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST

(SHEET 6 OF 18)

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ALERT ALERT
o. Do the Latch Mechanism Adjustment Test again.

p. Make sure that the adjustment is 0.179 in. (4.547 mm) to 0.229 in. (5.817 mm) for latches #2

through #7.

(1) If latches #2 through #7 are not 0.179 in. (4.547 mm) to 0.229 in. (5.817 mm), do the Latch

Pin Adjustment and Latch Mechanism Adjustment Test.

(2) Use the Interim Flushness Recording Table to record measurements, if necessary.

q. Make sure that the shim thickness is less than 0.20 in. (5.08 mm) at each latch pin fitting location

1 through 8.

r. Remove rigging pin set, B52029-1, used in latch pin fitting locations 2 through 7.

s. Remove the rod (3/16 Inch Diameter, 2 Inch Length), from the latch pin fitting locations 1 through

8, if you used them.

t. Install latch pins for latch pin fitting locations 2 through 7.

(1) Install the cross bolt and clip or the cross bolt and nut to the latch pin fitting.

(2) Make sure that the pin extends 0.89 - 0.91 inches from the bearing plate on all eight latch pin

fittings.

u. Remove the 0.002 in. (0.051 mm) shim and tape around the pins at sill fitting locations 1 and 8.

WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN OR CLOSE THE CARGO

DOOR. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR

DAMAGE TO EQUIPMENT CAN OCCUR.

v. Use the hydraulic hand pump to slowly close the door to the latched-and-locked position.

(1) Make sure that the cam latches smoothly engage the latch pins.

w. Measure the external cargo door flushness between the sill plate and the door at latch cam heads

1 through 8.

(1) Record the flushness at cam latch head locations 1 through 8 (Appendix Figure A4.3).

(2) Make sure that the lower edge of the cargo door skin is within flushness tolerance (Appendix

Figure A3).

(3) Open the main cargo door to approximately 1/2 of the fully open position.

(4) Make sure that the stop pins are adjusted correctly (Appendix Figure A2).

(5) Make sure that the forward/aft clearance for the latch mechanism is correct (Appendix Figure

A1.1).

APPENDIX A: LATCH MECHANISM ADJUSTMENT TEST

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ALERT ALERT
WARNING: MAKE SURE THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR OF THE

CARGO DOOR PATH BEFORE YOU OPERATE THE CARGO DOOR CONTROL

SWITCH. THE CARGO DOOR CAN CONTINUE TO MOVE AFTER YOU RELEASE

THE SWITCH. THIS CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TO

EQUIPMENT.

(6) Close the door to the "latched-and-locked" position.

(7) Monitor the door while it closes for unusual operations.

4. Adjust the Sequence Valve (Appendix Figure A1.1 - A1.3)

a. Close and lock the main cargo door.

(1) Measure the distance between the sequence valve end cap and the striker plate (View A-A).

If the distance is not in the tolerance, do the steps that follow to adjust:

(a) Open the main cargo door.

(b) Loosen the bolts that attach the sequence valve.

(c) Move the sequence valve as necessary to get the dimension shown (View A-A).

(d) Tighten the bolts.

5. Adjust the Stop Fittings and Stop Pins (Appendix Figure A2)

a. Close and lock the main cargo door.

b. See that the stop pins will touch the stop fittings in the area shown.

(1) It is acceptable for the stop pin at the bottom, aft edge of the door to touch the stop pad a

maximum of 0.06 in. (1.52 mm) below the target area shown in (Appendix Figure A2).

c. Make sure the clearances at the stop fittings are as shown.

d. Install the lock spring in the stop pin.

6. Do an operational test of the main cargo door. Refer to 727 AMM 52-34-00 as an accepted procedure.

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