# Boeing Alert Service Bulletin 727-52A0151: No revision named

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- Document: [Boeing Alert Service Bulletin 727-52A0151](https://openairdocs.org/service-documents/boeing/727-52a0151.md)
- Title as filed: SB-727-52A0151-00--BOEING
- Pages: 66
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## Text

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### Page 1

Commercial 
Airplanes
727
Service Bulletin
ALERT
Number: 727-52A0151
Original Issue: February 12, 2016
ATA System: 5234
SUBJECT: DOORS - Main Cargo Door - Cam Support Assembly Inspection and Replacement
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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2016 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Unpublished Work.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.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
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connection with this document unless provided in writing by Boeing.
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Table of Contents
S u m m a r y  ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A . E f f e c t i v i t y  ................................................ 9
1. Airplanes ............................................. 9
2 . S p a r e s  A f f e c t e d  ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 1
E. Compliance .............................................. 1 1
F . A p p r o v a l  ............................................... 1 2
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 3
J . R e f e r e n c e s  .............................................. 1 3
1. Existing Data: ......................................... 1 3
2. Data Supplied with this Service Bulletin: ........................... 1 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 4
K. Publications Affected ........................................ 1 4
L. Interchangeability and Intermixability of Parts ........................... 1 4
M. Software Accomplishment Summary ................................ 1 4
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary for Each Airplane ................................. 1 5
1 . K i t s / P a r t s  ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 9
3. Parts Modified and Reidentified ................................ 1 9
4. Parts Removed and Not Replaced .............................. 1 9
D. Parts Necessary to Change Spares ................................. 1 9
E. Special Tooling - Price and Availability ............................... 1 9
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 2
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT ........ 2 4
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT ....... 3 6
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT ......... 4 9
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: MAIN CARGO DOOR
CAM SUPPORT ASSEMBLY - INSPECTION ........................ 6 1
APPENDIX B: ADDITIONAL ACCESS .................................... 6 3
APPENDIX C: PART DEMAND INTENT ................................... 6 6
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Commercial 
Airplanes
727
Service Bulletin
ALERT
SummaryNumber: 727-52A0151Original Issue: February 12, 2016
ATA System: 5234
SUBJECT: DOORS - Main Cargo Door - Cam Support Assembly Inspection and Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Boeing analysis of the main cargo door cam support assemblies, part numbers 69-23588-5 and 69-23588-6,
indicated that the repeat High Frequency Eddy Current (HFEC) inspections given in service bulletin 727-52A0124
is not adequate to reliably detect cracks before two adjacent cam support assemblies could fail, which would
reduce the structural integrity of the door. The main cargo door is on the upper left side of the forward fuselage
between body stations 480 and 620. The door is hinged on its upper edge and opens outward to a canopy or a
fully open position. The main cargo door has eight cam support assemblies along the bottom of the door that
support the latch cams. The door latch cams engage with latch pins on the fuselage and hold the door closed.
The main cargo door cam support assemblies are subject to ground loads, flight loads, and cabin pressure
loads. If the work in this service bulletin is not done, undetected cracks at adjacent support assembly part
numbers 69-23588-5 and 69-23588-6, or replacement part numbers 69-23588-9 and 69-23588-10, could result
in reduced structural integrity of the main cargo door and consequent rapid decompression of the airplane.
This service bulletin gives instructions to do a ultrasonic inspection on the main deck cargo door cam support
assemblies, part numbers 69-23588-5 and 69-23588-6, and to replace the cam support if any damage is found.
Instructions are also given to repeat the Ultrasonic Inspection of the main cargo door cam support assembly at
all locations where an affected part number is installed for any crack at the repeat intervals.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
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### Page 6

ReferenceAffectedPlanning Data
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Do an Ultrasonic Inspection of the main cargo door cam support assembly, part numbers 69-23588-5 and
69-23588-6, grease fitting lug area at each location for any crack. If no crack is found, repeat the Ultrasonic
Inspection of the main cargo door cam support assembly at all locations where an affected part number is
installed for any crack at the repeat interval given in Paragraph 1.E., Compliance. If any crack is found, replace
the cam support assembly pair at the affected location and repeat the Ultrasonic Inspection of the main cargo
door cam support assembly at all locations where an affected part number is installed for any crack at the repeat
interval given in Paragraph 1.E., Compliance.
NOTE: 69-23588-5 and 69-23588-6 are affected part numbers. 69-23588-9 and 69-23588-10 are also affected
part numbers if cam support assembly pair is replaced.
EFFECTIVITY
727C/-100C/-200F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
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BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX C of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
DO AN INSPECTION OF THE
CAM SUPPORT ASSEMBLIES
FOR ANY CRACK
Original Issue: February 12, 2016
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Commercial 
Airplanes
727
Service Bulletin
ALERT
Number: 727-52A0151
Original Issue: February 12, 2016
ATA System: 5234
SUBJECT: DOORS - Main Cargo Door - Cam Support Assembly Inspection and Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to 727C/-100C/-200F airplanes in 1 Group. The Variable Numbers
and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-9825 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
727-100C, -200F and 727C airplanes with main deck cargo door cam
support assemblies, part numbers 69-23588-5 and 69-23588-6, or
69-23588-9 and 69-23588-10, installed.
-1
Airplane Models:
727-100C, 727-200F, 727C
GroupVariable Number
1E5001 - E5011
1E5031 - E5068
1E5101 - E5116
1E5141 - E5143
1E5161 - E5164
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GroupVariable Number
1E5201 - E5203
1E5221 - E5245
1E5251 - E5252
1E5271 - E5281
1E5301 - E5306
1E5351 - E5353
1E5381 - E5382
1E5401 - E5424
1E5426 - E5429
1E5433
1E5435
1E5451 - E5455
1E5481 - E5483
1E5501 - E5502
1QL501 - QL515
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Boeing analysis of the main cargo door cam support assemblies, part numbers 69-23588-5 and
69-23588-6, indicated that the repeat High Frequency Eddy Current (HFEC) inspections given in service
bulletin 727-52A0124 is not adequate to reliably detect cracks before two adjacent cam support
assemblies could fail, which would reduce the structural integrity of the door. The main cargo door is
on the upper left side of the forward fuselage between body stations 480 and 620. The door is hinged
on its upper edge and opens outward to a canopy or a fully open position. The main cargo door has
eight cam support assemblies along the bottom of the door that support the latch cams. The door latch
cams engage with latch pins on the fuselage and hold the door closed. The main cargo door cam
support assemblies are subject to ground loads, flight loads, and cabin pressure loads. If the work in
this service bulletin is not done, undetected cracks at adjacent support assembly part numbers
69-23588-5 and 69-23588-6, or replacement part numbers 69-23588-9 and 69-23588-10, could result
in reduced structural integrity of the main cargo door and consequent rapid decompression of the
airplane.
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This service bulletin gives instructions to do a ultrasonic inspection on the main deck cargo door cam
support assemblies, part numbers 69-23588-5 and 69-23588-6, and to replace the cam support if any
damage is found. Instructions are also given to repeat the Ultrasonic Inspection of the main cargo door
cam support assembly at all locations where an affected part number is installed for any crack at the
repeat intervals.
D. Description
Do an Ultrasonic Inspection of the main cargo door cam support assembly, part numbers 69-23588-5
and 69-23588-6, grease fitting lug area at each location for any crack. If no crack is found, repeat the
Ultrasonic Inspection of the main cargo door cam support assembly at all locations where an affected
part number is installed for any crack at the repeat interval given in Paragraph 1.E., Compliance. If any
crack is found, replace the cam support assembly pair at the affected location and repeat the Ultrasonic
Inspection of the main cargo door cam support assembly at all locations where an affected part number
is installed for any crack at the repeat interval given in Paragraph 1.E., Compliance.
NOTE: 69-23588-5 and 69-23588-6 are affected part numbers. 69-23588-9 and 69-23588-10 are
also affected part numbers if cam support assembly pair is replaced.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
2-48727-100C, 727-200F, 727C
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.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
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Table 1: Main Cargo Door Cam Support Assembly - Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,771
flight cycles or
27 months after
the original is-
sue date of this
service bulletin,
whichever oc-
curs later
Before 18,000
total flight cycles
Do an Ultrasonic Inspec-
tion of any affected main
cargo door cam support
assemblies for any crack.
(a)
All airplanes
6,000 flight cycles
or 10 years,
whichever occurs
first
--Repeat the Ultrasonic In-
spection of the main car-
go door cam support as-
semblies at all locations
where an affected part is
installed for any crack. (a)
CONDITION 1: NO
CRACK FOUND
--Before further
flight
ACTION 1: Do PART 1:
MAIN CARGO DOOR
CAM SUPPORT ASSEM-
BLY REPLACEMENT.
CONDITION 2: ANY
CRACK FOUND
6,000 flight cycles
or 10 years,
whichever occurs
first
--ACTION 2: Repeat the
Ultrasonic Inspection of
the main cargo door cam
support assemblies at all
locations where an affect-
ed part is installed for any
crack. (a)
(a) 69-23588-5 and 69-23588-6 are affected part numbers. 69-23588-9 and 69-23588-10 are also affected
part numbers, if installed in accordance with PART 1: MAIN CARGO DOOR CAM SUPPORT ASSEMBLY
REPLACEMENT.
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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G. Manpower
The tables below show an estimate of the task hours necessary to do this inspection for each airplane
and to replace each pair of cam latch support fittings. 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.
Table 1 - Inspection
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501Preparation
2.502.501Inspect
1.501.501Restoration
5.505.50TOTAL FOR EACH AIRPLANE
Table 2 - Replacement
Elapsed HoursTask HoursNumber of PersonsTask
6122Open Access
16322FIGURE 1
16322FIGURE 2
16322FIGURE 3
8162Close Access
3060TOTAL FOR EACH CAM SUPPORT FIT-
TING PAIR
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Letter 727-SL-00-014
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b. Component Maintenance Manual (CMM) 52-36-62
c. Service Bulletin Index D6-9825
d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-41-05, 20-43-03, 20-50-01,
20-50-19
e. 727 Aircraft Maintenance Manual (AMM) 12-25-93, 52-31-00
f. 727 Corrosion Prevention Manual (CPM) 52-30-01
g. 727 Non-Destructive Testing (NDT) Manual Part 4, 52-30-01
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
Part 4, 52-30-01727 Non-Destructive Testing Manual
52-36727 Component Maintenance Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kit shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are
encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The
kit is subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
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 The Boeing PART Page
2. Fax to (206) 662-7145
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
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
14,107.00285TOP KIT - RETROFIT KIT FOR MAIN DECK
CARGO DOOR
65C38659-18
Operators are encouraged to complete the survey provided in APPENDIX C of this service bulletin to
help Boeing predict the quantity and timing of the Boeing supplied kit.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: Up to four (4) top kits are necessary for each airplane based on inspection findings. Top
kit is configured for the replacement of any single pair of cam support assemblies.
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ALL
Kit 65C38659
NotesExisting Part
Number
NameQtyNew Part Number
-18
(a)-TOP KIT -
RETROFIT KIT
FOR MAIN DECK
CARGO DOOR
-65C38659-18
(c)-CAM SUPPORT
ASSEMBLY
169-23588U10
(c)-CAM SUPPORT
ASSEMBLY
169-23588U9
(b)-bolt6BACB30LM3-4X
(b)-BOLT9BACB30LM3-6X
(b)-BOLT2BACB30LM3-8X
(b)-BOLT3BACB30LM4-4X
(b)-BOLT6BACB30LM4-6X
(b)-BOLT2BACB30LM4-7X
(b)-BOLT2BACB30LM4-8X
(b)-BOLT2BACB30LM4-9X
(b)-BOLT, PROTRUD-
ING HD
4BACB30MY10K10X
(b)-BOLT, PROTRUD-
ING HD
4BACB30MY10K11X
(b)-BOLT, PROTRUD-
ING HD
2BACB30MY10K13X
(b)-BOLT, PROTRUD-
ING HD
1BACB30MY10K14X
(b)-BOLT, PROTRUD-
ING HD
2BACB30MY10K15X
(b)-BOLT, PROTRUD-
ING HD
1BACB30MY10K16X
(b)-BOLT, PROTRUD-
ING HD
1BACB30MY10K17X
(b)-BOLT, PROTRUD-
ING HD
2BACB30MY10K18X
(b)-BOLT, PROTRUD-
ING HD
2BACB30MY10K20X
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ALL
Kit 65C38659
NotesExisting Part
Number
NameQtyNew Part Number
-18
(b)-BOLT, PROTRUD-
ING HD
3BACB30MY10K21X
(b)-BOLT, PROTRUD-
ING HD
2BACB30MY10K22X
(b)-BOLT, PROTRUD-
ING HD
2BACB30MY10K23X
(b)-BOLT, PROTRUD-
ING HD
12BACB30MY10K5X
(b)-BOLT, PROTRUD-
ING HD
4BACB30MY10K6X
(b)-BOLT, PROTRUD-
ING HD
2BACB30MY10K7X
(b)-BOLT, PROTRUD-
ING HD
4BACB30MY10K9X
(b)-BOLT, PROTRUD-
ING HD
1BACB30MY12K10X
(b)-BOLT, PROTRUD-
ING HD
4BACB30MY8K5X
(b)-BOLT, PROTRUD-
ING HD
5BACB30MY8K7X
(b)-BOLT, 100 DEG
HEX DR
1BACB30NW10K14X
(b)-BOLT, 100 DEG
HEX DR
1BACB30NW10K15X
(b)-BOLT, 100 DEG
HEX DR
1BACB30NW10K6X
(b)-BOLT, 100 DEG
HEX DR
1BACB30NW10K7X
(b)-BOLT, 100 DEG
HEX DR
2BACB30NW8K5X
(b)-BOLT, 100 DEG
HEX DR
2BACB30NW8K7X
(b)-BOLT, PROTRUD-
ING HD
5BACB30NX6K3X
(b)-BOLT, PROTRUD-
ING HD
6BACB30NX6K4X
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### Page 18

ALL
Kit 65C38659
NotesExisting Part
Number
NameQtyNew Part Number
-18
(b)-BOLT, PROTRUD-
ING HD
1BACB30NX6K5X
(b)-BOLT, PROTRUD-
ING HD
1BACB30NX6K6X
--COLLAR ASSEM-
BLY
12BACC30AG10
--COLLAR20BACC30M10
--COLLAR1BACC30M12
--COLLAR7BACC30M6
--COLLAR13BACC30M8
--NUT16BACN10JC3CD
--NUT,SELF-LOCK-
ING
14BACN10JC4CD
--RIVET, UNIVER-
SAL HD
25BACR15BB6D7C
--RIVET, 100 DEG4BACR15GF8D14
--WASHER, OVER-
SIZE
16BACW10AW3AS
--WASHER, OVER-
SIZE
14BACW10AW4AS
(a) There are more parts than are necessary.
(b) If grip length shown is not available at Boeing, fasteners supplied in kits
may be one grip length longer than indicated. Also, if any fasteners part
numbers listed are not available or have been superseded, substitute
fasteners may be supplied in kits.
(c) To make installation easier, some Boeing parts are sent in an 'interim'
configuration. Boeing will identify these interim configurations with a 'U',
'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are
changed to the 'dash' configuration when installed as given in the Accom-
plishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 727-
SL-00-014 for more information.
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### Page 19

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.
NotesNameQTYPart Number /
Specification
(a)RADIUS FILLER--
(b)SEALANT - PRESSURE AND ENVI-
RONMENTAL - CHROMATE TYPE
-BMS 5-95
(b)COATING - CHEMICAL AND SOL-
VENT RESISTANT FINISH, CORRO-
SION INHIBITING PRIMER
-BMS 10-11, TYPE
I
(b)COATING - CHEMICAL AND SOL-
VENT RESISTANT FINISH - BAC
702 WHITE COLOR, GLOSS
-BMS 10-11, TYPE
II
COATING - ORGANIC CORRO-
SION INHIBITING COMPOUND
BMS 3-23, TYPE II
(b)GREASE - AIRCRAFT GENERAL
PURPOSE
-BMS 3-33
(a) Fabricate from 2024-T3, 2024-T4, or 7075-T6, approximately 0.75 inch square by 0.125
inch thick. Refer to FIGURE 1, FIGURE 2, and FIGURE 3. Optional to make in one piece
rather than 4.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
No special parts or materials are necessary to do the change in this service bulletin. But, parts
and materials in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
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### Page 20

F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 21

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.
— Values for airframe maintenance tasks are included in Chapter 20 of 727
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 727
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
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. 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.
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### Page 22

7. Refer to APPENDIX A for the logic diagram. The logic diagram is provided as an aid
only. Information contained in Paragraph 1.E., Compliance is the primary source for
compliance times. Information in Paragraph 3.B., WORK INSTRUCTIONS is the
primary source for tasks required for compliance.
8. 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.
9. 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.
10. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
11. 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.
12. 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.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. Open the main cargo door. Refer to 727 AMM 52-31-00 as an accepted procedure.
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### Page 23

2. RC - Do an Ultrasonic Inspection of any affected main cargo door cam support assemblies for any
crack in accordance with 727 NDT Manual Part 4, 52-30-01.
NOTE: 69-23588-5 and 69-23588-6 are affected part numbers. 69-23588-9 and 69-23588-10
are also affected part numbers, if installed in accordance with PART 1: MAIN DECK
CARGO DOOR CAM SUPPORT ASSEMBLY REPLACEMENT.
a. CONDITION 1: NO CRACK FOUND
(1) Repeat the Ultrasonic Inspection of the main cargo door cam support assemblies at all
locations where an affected part number is installed for any crack in accordance with 727
NDT Manual Part 4, 52-30-01 at the repeat interval given in Paragraph 1.E., Compliance.
NOTE: 69-23588-5 and 69-23588-6 are affected part numbers. 69-23588-9 and
69-23588-10 are also affected part numbers, if installed in accordance with
PART 1: MAIN CARGO DOOR CAM SUPPORT ASSEMBLY REPLACEMENT.
b. CONDITION 2: ANY CRACK FOUND
(1) CONDITION 2 (ACTION 1): Do PART 1 - MAIN CARGO DOOR CAM SUPPORT
ASSEMBLY REPLACEMENT.
(2) CONDITION 2 (ACTION 2): Repeat the Ultrasonic Inspection of the main cargo door cam
support assemblies at all locations where an affected part number is installed for any
crack in accordance with 727 NDT Manual Part 4, 52-30-01 at the repeat interval given
in Paragraph 1.E., Compliance.
NOTE: 69-23588-5 and 69-23588-6 are affected part numbers. 69-23588-9 and
69-23588-10 are also affected part numbers, if installed in accordance with
PART 1: MAIN CARGO DOOR CAM SUPPORT ASSEMBLY REPLACEMENT.
3. Do an operational test of the main cargo door and check all affected hydraulic tubing and hoses
for leakage. Refer to 727 AMM 52-31-00 as an accepted procedure.
4. Put the airplane back to a serviceable condition.
PART 1: MAIN CARGO DOOR CAM SUPPORT ASSEMBLY REPLACEMENT
1. Replace the main cargo door cam support assembly pair at the affected locations as follows:
NOTE: Refer to APPENDIX B for additional access.
a. Replace the cam support assembly at stations 487.10 and 500 in accordance with FIGURE
1.
b. Replace the cam support assembly at stations 520 and 540 in accordance with FIGURE 2.
c. Replace the cam support assembly at stations 560 and 580 in accordance with FIGURE 2.
d. Replace the cam support assembly at stations 600 and 612.9 in accordance with FIGURE 3.
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### Page 24 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
00
000
INBD  2455183
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 1 OF 12)
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### Page 25 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA
487.10
CAM SUPPORT ASSEMBLY
1 17 16 LOCATIONS
SUPPORT ASSEMBLY
000B D
14 15 18
• BRACKET
6 LOCATIONS (12)
1381
13) RADIUS FILLER  (4 LOCATIONS)
LA  TENSION
TIE CLIP
> PART PROFILE SHOWN IS REFERENCE ONLY
2455184
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 2 OF 12)
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### Page 26 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA
520  €000ULE1
WEB  STA
CAM SUPPORT  500
ASSEMBLY
TU 16 LOCATIONS
(16 17 10 LOCATIONS
13) RADIUS FILLEF
BRACKET  (4 LOCATIONS
1001฿  12 14 6 LOCATIONS
117
TENSION TIE CLIP
(11,15)
9 1 14 15 18
SHEAR WEB
CAM AND BELLCRANK
ASSEMBLY  2455186
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 3 OF 12)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
CAM SUPPORT
ASSEMBLY  STA
487.10
SHEAR WEB
· * 77  TENSION
TIE CLIP
B-B
- BRACKET
SHEAR WEB
B
TENSION TIE CLIP
A-A  2455185
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 4 OF 12)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA
500  CAM SUPPORT
ASSEMBLY
AlES
SHEAR WEB
CAM SUPPORT
ASSEMBLY
ALE
BRACKET
SHEAR WEB
TENSION TIE CLIP
C-c
TENSION
TIE CLIP  D-D  2455187
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 5 OF 12)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
STA
487.10
CAM SUPPORT
ASSEMBLY
SHEAR WEB
STA  500  E-E  487.10  STA  2455190
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 6 OF 12)
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### Page 30

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 each airplane.
More DataQtyIdentificationNameTaskStep
-1-WEBRemove / Keep1
1-CAM AND BELL-
CRANK ASSEMBLY
Keep spacers.2-TENSION TIE CLIP
-1-SHEAR WEB
2-BRACKET
1-SUPPORT ASSEMBLY
Keep cam support
assembly at STA
500 for use as an
aid during alignment
of new cam support
assembly.
2-CAM SUPPORT AS-
SEMBLY
Remove
Temporary install
using existing holes
to maintain original
position.
1-CAM SUPPORT AS-
SEMBLY
Install (Kept)2
-169-23588U9CAM SUPPORT AS-
SEMBLY
Put / Hold (New)3
1-BRACKETPut / Hold (Kept)
(a)1-SUPPORT ASSEMBLY
-1-CAM AND BELL-
CRANK ASSEMBLY
Install (Temporary)
Pick up existing
holes.
-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill4
--BRACKET
Pick up existing
holes. (a)
--SUPPORT ASSEMBLY
-1-CAM AND BELL-
CRANK ASSEMBLY
Remove / Keep5
1-CAM SUPPORT AS-
SEMBLY
Remove (Kept)
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 7 OF 12)
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### Page 31

More DataQtyIdentificationNameTaskStep
-169-23588U10CAM SUPPORT AS-
SEMBLY
Put / Hold (New)6
1-BRACKETPut / Hold (Kept)
1-CAM AND BELL-
CRANK ASSEMBLY
Install (Temporary)
Pick up existing
holes.
-69-23588U10CAM SUPPORT AS-
SEMBLY
Drill7
--BRACKET
-1-CAM AND BELL-
CRANK ASSEMBLY
Remove / Keep8
169-23588U9CAM SUPPORT AS-
SEMBLY
169-23588U10CAM SUPPORT AS-
SEMBLY
2-BRACKET
1-SUPPORT ASSEMBLY
-169-23588U9CAM SUPPORT AS-
SEMBLY
Install (Temporary)9
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
Pick up existing
holes in shear web
and tension tie clip.
-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill (Kept)10
-69-23588U10CAM SUPPORT AS-
SEMBLY
--SHEAR WEB
--TENSION TIE CLIP
-169-23588U9CAM SUPPORT AS-
SEMBLY
Remove / Keep11
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Keep spacers.2-TENSION TIE CLIP
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 8 OF 12)
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### Page 32

More DataQtyIdentificationNameTaskStep
(b)-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill (Kept)12
-69-23588U10CAM SUPPORT AS-
SEMBLY
--SHEAR WEB
----Clean/Deburr
(c)8-RADIUS FILLERMake13
Bench work. Install
radius fillers at 3 lo-
cations on each cam
support assembly.
169-23588U9CAM SUPPORT AS-
SEMBLY
Assemble14
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Assembled cam
support assemblies
and shear web.
169-23588U9CAM SUPPORT AS-
SEMBLY
Put / Hold15
69-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
---SHEAR WEBDrill16
----Clean/Deburr17
(d) (e)169-23588U9CAM SUPPORT AS-
SEMBLY
Install (Kept)18
169-23588U10CAM SUPPORT AS-
SEMBLY
-2-BRACKET
1-SUPPORT ASSEMBLY
Install radius fillers
at remaining loca-
tions.
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
Refer to CMM 52-
36-62 for an accept-
ed procedure.
1-CAM AND BELL-
CRANK ASSEMBLY
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 9 OF 12)
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### Page 33

More DataQtyIdentificationNameTaskStep
Fay and fillet seal
with BMS 5-95
sealant. Refer to
SOPM 20-50-19 for
an accepted proce-
dure.
1-WEBInstall (Kept)19
Refer to 727 AMM
12-25-93 for an ac-
cepted procedure.
-BMS 3-33GREASEApply20
(a) The door hook mechanism can be used as an aid to position the support assembly. Additional put/hold
and drilling tasks may be necessary for the support assembly and are as required.
(b) Bench work. Temporary assemble through holes common to the tension tie clip. Maintain the main cargo
door frame-to-frame mounting surface distance between the cam support assemblies during drilling.
(c) Make from 2024-T3 alclad, 2024-T4 alclad, or 7075-T6 alclad aluminum. Approximately 0.75 inch square
by 0.125 inch thick. Optional to make in one piece rather than 4. Radius bottom of filler to fit curvature of
fitting (0.010 inch maximum gap prior to fastener installation. Apply chemical conversion coating Type 1
or Type 2, Class A or C. Refer to SOPM 20-43-03 as an accepted procedure. Apply two coats of BMS
10-11, Type I primer. Refer to SOPM 20-41-02 for an accepted procedure.
(d) Apply one layer of BMS 10-11, Type II enamel, color BAC 702 white gloss below door lower frame, except
in cam latch bores, prior to installation of cam and bellcrank assembly. Refer to SOPM 20-41-02 for an
accepted procedure.
(e) Apply BMS 3-23, Type II corrosion inhibiting compound above and below door lower frame, except in
cam latch bores, prior to installation of cam and bellcrank assembly. Refer to 727 CPM 52-30-01 and
SOPM 20-41-05 for an accepted procedure.
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 10 OF 12)
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### Page 34

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)0.325-0.32818BACB30MY10K( )XBOLT, PROTRUDING
HD
A
--18BACC30M10COLLAR
(a)0.325-0.3281BACB30NW10K6XBOLT, 100 DEG HEX
DR
B
--1BACC30M10COLLAR
(a)0.388-0.3911BACB30MY12K10XBOLT, PROTRUDING
HD
C
--1BACC30M12COLLAR
(a)0.2651-0.26618BACB30MY8K( )XBOLT, PROTRUDING
HD
D
--8BACC30M8COLLAR
(a)0.2651-0.26614BACB30LM4-( )XBOLTE
--4BACW10AW4ASWASHER, OVERSIZE
--4BACN10JC4CDNUT,SELF-LOCKING
(a)0.2651-0.26614BACB30NW8K( )XBOLT, 100 DEG HEX
DR
F
--4BACC30M8COLLAR
--4BACR15GF8D14RIVET, 100 DEGG
(a) (b)0.2651-0.266110BACB30LM4-( )XBOLTH
(b)-10BACW10AW4ASWASHER, OVERSIZE
(b)-10BACN10JC4CDNUT,SELF-LOCKING
(a) (b)0.263-0.2661BACB30MY8K7XBOLT, PROTRUDING
HD
I
(b)-1BACC30M8COLLAR
(a)0.200-0.2032BACB30NX6K( )XBOLT, PROTRUDING
HD
J
--2BACC30M6COLLAR
(a)0.200-0.2035BACB30NX6K3XBOLT, PROTRUDING
HD
K
-5BACC30M6COLLAR
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 11 OF 12)
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### Page 35

More DataHole DiaQtyIdentificationNameCode
--25BACR15BB6D7CRIVET, UNIVERSAL
HD
L
(a)0.325-0.32811BACB30MY10K( )XBOLT, PROTRUDING
HD
M
--11BACC30AG10COLLAR ASSEMBLY
(a)0.325-0.3281BACB30NW10K14XBOLT, 100 DEG HEX
DR
N
--1BACC30AG10COLLAR ASSEMBLY
Pick up existing hole in
the pressure door hinge
structure. Use the existing
fastener.
0.250-0.254---O
(a) Install wet with BMS 5-95 sealant. Refer to SOPM 20-50-19 as an accepted procedure.
(b) Touch up bolt head, washer/nut, or collar, as applicable, below door lower frame with BMS 10-11, Type
1 primer and BMS 10-11, Type II enamel, color 702 white gloss. Refer to SOPM 20-41-02 as an accepted
procedure.
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 12 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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727-52A0151
35 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
00
000
INBD
2455191
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 1 OF 13)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING  727-52A0151
PROPRIETARY - Copyright © Unpublished
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
C  3630UUD18  STA 500  OR
STA 540
STA 520
OR  WEB
STA 560  CAM SUPPORT  ASSEMBLY  500/520  ONLY  STA
• 16 LOCATIONS (4)17
•
RADIUS FILLES) 13  (4 LOCATIONS)  BRACKET
6 LOCATIONS 12 14-  8 18
10 17
TENSION TIE CLIP
2455194
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 2 OF 13)
Original Issue: February 12, 2016
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PROPRIETARY - Copyright © Unpublished
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA 560
OR
STA 600  3€080UU118
STA 540
OR
CAM SUPPORT  STA 580
ASSEMBLY
TU 16 LOCATIONS
16 17) 10 LOCATIONS
WEB
STA  13 RADIUS FILLES
580/600  BRACKET  (4 LOCATIONS)
ONLY
1O®  X14) 6 LOCATIONS
717
TENSION TIE CLIP
101118
(1 9 11)  14 15 18
SHEAR WEB
CAM AND BELLORANK  ASSEMBLY  2455199
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 3 OF 13)
Original Issue: February 12, 2016
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
STA 520
ASSEMBLY  CAM SUPPORT  STA 560  OR
SHEAR WEB
4 7 7 7 7%  B-B
BRACKET
- STA 520 ONLY
S STA 560 ONLY
SHEAR WEB
TENSION TIE CLIP
A-A  2455196
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 4 OF 13)
Original Issue: February 12, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  121-52A0151
Work - See page 1 for details.  39 of 66

### Page 40 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA 540
OR
STA 580
CAM SUPPORT
ASSEMBLY
G- STA 540 ONLY
- STA 580 ONLY
SHEAR WEB
CAM SUPPORT
ASSEMBLY
B 15
BRACKET
D  SHEAR WEB
TENSION
TENSION TIE CLIP  TIE CLIP  D-D
C-C
2455202
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 5 OF 13)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  727-52A0151
Work - See page 1 for details.  40 of 66

### Page 41 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA
520
STA
580  INBD
CAM SUPPORT
CAM SUPPORT  ASSEMBLY
ASSEMBLY
SHEAR WEB
STA  STA
540  520
E-E  2455204
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 6 OF 13)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  41 of 66

### Page 42

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 each airplane.
More DataQtyIdentificationNameTaskStep
-1-WEBRemove / Keep1
1-CAM AND BELL-
CRANK ASSEMBLY
Keep spacers.2-TENSION TIE CLIP
-1-SHEAR WEB
2-BRACKET
Keep cam support
assembly at STA
540 or STA 580 for
use as an aid during
alignment of new
cam support assem-
bly.
2-CAM SUPPORT AS-
SEMBLY
Remove
Temporary install
using existing holes
to maintain original
position.
1-CAM SUPPORT AS-
SEMBLY
Install (Kept)2
-169-23588U9CAM SUPPORT AS-
SEMBLY
Put / Hold (New)3
1-BRACKETPut / Hold (Kept)
-1-CAM AND BELL-
CRANK ASSEMBLY
Install (Temporary)
Pick up existing
holes.
-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill4
--BRACKET
-1-CAM AND BELL-
CRANK ASSEMBLY
Remove / Keep5
1-CAM SUPPORT AS-
SEMBLY
Remove (Kept)
-169-23588U10CAM SUPPORT AS-
SEMBLY
Put / Hold (New)6
1-BRACKETPut / Hold (Kept)
1-CAM AND BELL-
CRANK ASSEMBLY
Install (Temporary)
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 7 OF 13)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
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BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 43

More DataQtyIdentificationNameTaskStep
Pick up existing
holes.
-69-23588U10CAM SUPPORT AS-
SEMBLY
Drill7
--BRACKET
-1-CAM AND BELL-
CRANK ASSEMBLY
Remove / Keep8
169-23588U9CAM SUPPORT AS-
SEMBLY
169-23588U10CAM SUPPORT AS-
SEMBLY
2-BRACKET
-169-23588U9CAM SUPPORT AS-
SEMBLY
Install (Temporary)9
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
Pick up existing
holes in shear web
and tension tie clip.
-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill (Kept)10
-69-23588U10CAM SUPPORT AS-
SEMBLY
--SHEAR WEB
--TENSION TIE CLIP
-169-23588U9CAM SUPPORT AS-
SEMBLY
Remove / Keep11
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Keep spacers.2-TENSION TIE CLIP
(a)-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill (Kept)12
-69-23588U10CAM SUPPORT AS-
SEMBLY
--SHEAR WEB
----Clean/Deburr
(b)8-RADIUS FILLERMake13
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 8 OF 13)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
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BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 44

More DataQtyIdentificationNameTaskStep
Bench work. Install
radius fillers at 3 lo-
cations on each cam
support assembly.
169-23588U9CAM SUPPORT AS-
SEMBLY
Assemble14
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Assembled cam
support assemblies
and shear web.
169-23588U9CAM SUPPORT AS-
SEMBLY
Put / Hold15
69-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
---SHEAR WEBDrill16
----Clean/Deburr17
(c) (d)169-23588U9CAM SUPPORT AS-
SEMBLY
Install (Kept)18
169-23588U10CAM SUPPORT AS-
SEMBLY
-2-BRACKET
Install radius fillers
at remaining loca-
tions.
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
Refer to CMM 52-
36-62 for an accept-
ed procedure.
1-CAM AND BELL-
CRANK ASSEMBLY
Fay and fillet seal
with BMS 5-95
sealant. Refer to
SOPM 20-50-19 for
an accepted proce-
dure.
1-WEBInstall (Kept)19
Refer to 727 AMM
12-25-93 for an ac-
cepted procedure.
-BMS 3-33GREASEApply20
(a) Bench work. Temporary assemble through holes common to the tension tie clip. Maintain the main cargo
door frame-to-frame mounting surface distance between the cam support assemblies during drilling.
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 9 OF 13)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
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BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 45

More DataQtyIdentificationNameTaskStep
(b) Make from 2024-T3 alclad, 2024-T4 alclad, or 7075-T6 alclad aluminum. Approximately 0.75 inch square
by 0.125 inch thick. Optional to make in one piece rather than 4. Radius bottom of filler to fit curvature of
fitting (0.010 inch maximum gap prior to fastener installation. Apply chemical conversion coating Type 1
or Type 2, Class A or C. Refer to SOPM 20-43-03 as an accepted procedure. Apply two coats of BMS
10-11, Type I primer. Refer to SOPM 20-41-02 for an accepted procedure.
(c) Apply one layer of BMS 10-11, Type II enamel, color BAC 702 white gloss below door lower frame, except
in cam latch bores, prior to installation of cam and bellcrank assembly. Refer to SOPM 20-41-02 for an
accepted procedure.
(d) Apply BMS 3-23, Type II corrosion inhibiting compound above and below door lower frame, except in
cam latch bores, prior to installation of cam and bellcrank assembly. Refer to 727 CPM 52-30-01 and
SOPM 20-41-05 for an accepted procedure.
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 10 OF 13)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
45 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
CAM SUPPORT
CAM SUPPORT  ASSEMBLY
ASSEMBLY
SHEAR WEB
STA  STA
580  560
FWD
F-F
2461749
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 11 OF 13)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING  727-52A0151
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  46 of 66

### Page 47

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)0.325-0.32820BACB30MY10K( )XBOLT, PROTRUDING
HD
A
--20BACC30M10COLLAR
(a)0.2651-0.26618BACB30MY8K( )XBOLT, PROTRUDING
HD
B
--8BACC30M8COLLAR
(a)0.2651-0.26614BACB30LM4-( )XBOLTC
--4BACW10AW4ASWASHER, OVERSIZE
--4BACN10JC4CDNUT,SELF-LOCKING
(a)0.2651-0.26614BACB30NW8K( )XBOLT, 100 DEG HEX
DR
D
--4BACC30M8COLLAR
--4BACR15GF8D14RIVET, 100 DEGE
(a) (b)0.2026-0.203616BACB30LM3-( )XBOLTF
(b)-16BACW10AW3ASWASHER, OVERSIZE
(b)-16BACN10JC3CDNUT
(a) (b)0.263-0.2661BACB30MY8K7XBOLT, PROTRUDING
HD
G
(b)-1BACC30M8COLLAR
(a)0.325-0.32812BACB30MY10K( )XBOLT, PROTRUDING
HD
H
(a)-12BACC30AG10COLLAR ASSEMBLY
Pick up existing hole in
the pressure door hinge
structure. Use the existing
fastener.
0.250-0.254---I
(a)0.200-0.2032BACB30NX6K( )XBOLT, PROTRUDING
HD
J
--2BACC30M6COLLAR
(a)0.200-0.2035BACB30NX6K3XBOLT, PROTRUDING
HD
K
--5BACC30M6COLLAR
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 12 OF 13)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
47 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 48

More DataHole DiaQtyIdentificationNameCode
--25BACR15BB6D7CRIVET, UNIVERSAL
HD
L
(a) Install wet with BMS 5-95 sealant. Refer to SOPM 20-50-19 as an accepted procedure.
(b) Touch up bolt head, washer/nut, or collar, as applicable, below door lower frame with BMS 10-11, Type
I primer and BMS 10-11 Type II enamel, color BAC 702 white gloss. Refer to SOPM 20-41-02 as an ac-
cepted procedure.
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 13 OF 13)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
48 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
000
INBD  2455206
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 1 OF 12)
Original Issue: February 12, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  727-52A0151
Work - See page 1 for details.  49 of 66

### Page 50 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA
612.9
CAM SUPPORT ASSEMBLY
16 LOCATIONS 4 17
SUPPORT ASSEMBLY
103318
1617) 10 LOCATIONS
BRACKET
12 14 6 LOCATIONS
10®  (18
RADIUS FILLER
(4 LOCATIONS)
15118
TENSION
TIE CLIP
• PART PROFILE SHOWN IS REFERENCE ONLY
2462683
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 2 OF 12)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING  727-52A0151
PROPRIETARY - Copyright © Unpublished
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### Page 51 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
14 15 18
STA
580
WEB
STA
600  CAM SUPPORT
ASSEMBLY
16 LOCATIONS TU
PASTIONS 13  (4 LOCATIONS)  • BRACKET
6 LOCATIONS (12 14  8 18
11
TENSION TIE CLIP
90118
13€€ 818
1901 1 18
SHEAR WEB
ASSEMBLY  CAM AND BELLCRANK  2455210
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 3 OF 12)
Original Issue: February 12, 2016
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Work - See page 1 for details.  51 of 66

### Page 52 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
STA
612.9  CAM SUPPORT
ASSEMBLY
SHEAR WEB
CAM SUPPORT
ASSEMBLY
ALE
BRACKET
SHEAR WEB
TENSION TIE CLIP
A-A
TENSION
TIE CLIP  B-B  2455212
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 4 OF 12)
Original Issue: February 12, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  727-52A0151
Work - See page 1 for details.  52 of 66

### Page 53 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
CAM SUPPORT
ASSEMBLY
SHEAR WEB
7 7 7 7 7°  TENSION
TIE CLIP
D-D
- BRACKET
SHEAR WEB
TENSION TIE CLIP
C-C  2455209
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 5 OF 12)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING  727-52A0151
PROPRIETARY - Copyright © Unpublished
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### Page 54 (OCR)

BOEING SERVICE BULLETIN 727-52A0151
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
STA
612.9  CAM SUPPORT
ASSEMBLY
CAM SUPPORT
ASSEMBLY
SHEAR WEB
FWD
STA  STA
612.9  E-E  600
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 6 OF 12)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING  727-52A0151
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  54 of 66

### Page 55

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 each airplane.
More DataQtyIdentificationNameTaskStep
-1-WEBRemove / Keep1
1-CAM AND BELL-
CRANK ASSEMBLY
Keep spacers.2-TENSION TIE CLIP
-1-SHEAR WEB
2-BRACKET
1-SUPPORT ASSEMBLY
Keep cam support
assembly at STA
600 for use as an
aid during alignment
of new cam support
assembly.
2-CAM SUPPORT AS-
SEMBLY
Remove
Temporary install
using existing holes
to maintain original
position.
1-CAM SUPPORT AS-
SEMBLY
Install (Kept)2
-169-23588U10CAM SUPPORT AS-
SEMBLY
Put / Hold (New)3
1-BRACKETPut / Hold (Kept)
(a)1-SUPPORT ASSEMBLY
-1-CAM AND BELL-
CRANK ASSEMBLY
Install (Temporary)
Pick up existing
holes.
-69-23588U10CAM SUPPORT AS-
SEMBLY
Drill4
--BRACKET
Pick up existing
holes. (a)
--SUPPORT ASSEMBLY
-1-CAM AND BELL-
CRANK ASSEMBLY
Remove / Keep5
1-CAM SUPPORT AS-
SEMBLY
Remove (Kept)
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 7 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
55 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 56

More DataQtyIdentificationNameTaskStep
-169-23588U9CAM SUPPORT AS-
SEMBLY
Put / Hold (New)6
1-BRACKETPut / Hold (Kept)
1-CAM AND BELL-
CRANK ASSEMBLY
Install (Temporary)
Pick up existing
holes.
-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill7
--BRACKET
-1-CAM AND BELL-
CRANK ASSEMBLY
Remove / Keep8
169-23588U9CAM SUPPORT AS-
SEMBLY
169-23588U10CAM SUPPORT AS-
SEMBLY
2-BRACKET
1-SUPPORT ASSEMBLY
-169-23588U9CAM SUPPORT AS-
SEMBLY
Install (Temporary)9
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
Pick up existing
holes in shear web
and tension tie clip.
-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill (Kept)10
-69-23588U10CAM SUPPORT AS-
SEMBLY
--SHEAR WEB
--TENSION TIE CLIP
-169-23588U9CAM SUPPORT AS-
SEMBLY
Remove / Keep11
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Keep spacers.2-TENSION TIE CLIP
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 8 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
56 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 57

More DataQtyIdentificationNameTaskStep
(b)-69-23588U9CAM SUPPORT AS-
SEMBLY
Drill (Kept)12
-69-23588U10CAM SUPPORT AS-
SEMBLY
--SHEAR WEB
----Clean/Deburr
(c)8-RADIUS FILLERMake13
Bench work. Install
radius fillers at 3 lo-
cations on each cam
support assembly.
169-23588U9CAM SUPPORT AS-
SEMBLY
Assemble14
169-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Assembled cam
support assemblies
and shear web.
169-23588U9CAM SUPPORT AS-
SEMBLY
Put / Hold15
69-23588U10CAM SUPPORT AS-
SEMBLY
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
---SHEAR WEBDrill16
----Clean/Deburr17
(d) (e)169-23588U9CAM SUPPORT AS-
SEMBLY
Install (Kept)18
169-23588U10CAM SUPPORT AS-
SEMBLY
-2-BRACKET
1-SUPPORT ASSEMBLY
Install radius fillers
at remaining loca-
tions.
1-SHEAR WEB
Install kept spacers.2-TENSION TIE CLIP
Refer to CMM 52-
36-62 for an accept-
ed procedure.
1-CAM AND BELL-
CRANK ASSEMBLY
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 9 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
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BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 58

More DataQtyIdentificationNameTaskStep
Fay and fillet seal
with BMS 5-95
sealant. Refer to
SOPM 20-50-19 for
an accepted proce-
dure.
1-WEBInstall (Kept)19
Refer to 727 AMM
12-25-93 for an ac-
cepted procedure.
-BMS 3-33GREASEApply20
(a) The door hook mechanism can be used as an aid to position the support assembly. Additional put/hold
and drilling tasks may be necessary for the support assembly and are as required.
(b) Bench work. Temporary assemble through holes common to the tension tie clip. Maintain the main cargo
door frame-to-frame mounting surface distance between the cam support assemblies during drilling.
(c) Make from 2024-T3 alclad, 2024-T4 alclad, or 7075-T6 alclad aluminum. Approximately 0.75 inch square
by 0.125 inch thick. Optional to make in one piece rather than 4. Radius bottom of filler to fit curvature of
fitting (0.010 inch maximum gap prior to fastener installation. Apply chemical conversion coating Type 1
or Type 2, Class A or C. Refer to SOPM 20-43-03 as an accepted procedure. Apply two coats of BMS
10-11, Type I primer. Refer to SOPM 20-41-02 for an accepted procedure.
(d) Apply one layer of BMS 10-11, Type II enamel, color BAC 702 white gloss below door lower frame, except
in cam latch bores, prior to installation of cam and bellcrank assembly. Refer to SOPM 20-41-02 for an
accepted procedure.
(e) Apply BMS 3-23, Type II corrosion inhibiting compound above and below door lower frame, except in
cam latch bores, prior to installation of cam and bellcrank assembly. Refer to 727 CPM 52-30-01 and
SOPM 20-41-05 for an accepted procedure.
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 10 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
58 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 59

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)0.325-0.32818BACB30MY10K( )XBOLT, PROTRUDING
HD
A
--18BACC30M10COLLAR
(a)0.325-0.3281BACB30NW10K7XBOLT, 100 DEG HEX
DR
B
--1BACC30M10COLLAR
(a)0.388-0.3911BACB30MY12K10XBOLT, PROTRUDING
HD
C
--1BACC30M12COLLAR
(a)0.2651-0.26618BACB30MY8K( )XBOLT, PROTRUDING
HD
D
--8BACC30M8COLLAR
(a)0.2651-0.26614BACB30LM4-( )XBOLTE
--4BACW10AW4ASWASHER, OVERSIZE
--4BACN10JC4CDNUT,SELF-LOCKING
(a)0.2651-0.26614BACB30NW8K( )XBOLT, 100 DEG HEX
DR
F
--4BACC30M8COLLAR
--4BACR15GF8D14RIVET, 100 DEGG
(a) (b)0.2651-0.266110BACB30LM4-( )XBOLTH
(b)-10BACW10AW4ASWASHER, OVERSIZE
(b)-10BACN10JC4CDNUT,SELF-LOCKING
(a) (b)0.263-0.2661BACB30MY8K7XBOLT, PROTRUDING
HD
I
(b)-1BACC30M8COLLAR
(a)0.200-0.2032BACB30NX6K( )XBOLT, PROTRUDING
HD
J
--2BACC30M6COLLAR
(a)0.200-0.2035BACB30NX6K4XBOLT, PROTRUDING
HD
K
--5BACC30M6COLLAR
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 11 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
59 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

### Page 60

More DataHole DiaQtyIdentificationNameCode
--25BACR15BB6D7CRIVET, UNIVERSAL
HD
L
(a)0.325-0.32811BACB30MY10K( )XBOLT, PROTRUDING
HD
M
--11BACC30AG10COLLAR ASSEMBLY
(a)0.325-0.3281BACB30NW10K15XBOLT, 100 DEG HEX
DR
N
--1BACC30AG10COLLAR ASSEMBLY
Pick up existing hole in
the pressure door hinge
structure. Use the existing
fastener.
0.250-0.254---O
(a) Install wet with BMS 5-95 sealant. Refer to SOPM 20-50-19 as an accepted procedure.
(b) Touch up bolt head, washer/nut, or collar, as applicable, below door lower frame with BMS 10-11, Type
I primer and BMS 10-11 Type II enamel, color BAC 702 white gloss. Refer to SOPM 20-41-02 as an ac-
cepted procedure.
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 12 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
727-52A0151
60 of 66
BOEING SERVICE BULLETIN 727-52A0151
ALERTALERT

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