# Boeing Service Bulletin A3542: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-9183; AD 2017-18-20 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin A3542](https://openairdocs.org/service-documents/boeing/a3542.md)
- Title as filed: SB 707-A3542--BOEING
- Pages: 67
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## Text

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### Page 1

Commercial 
Airplanes
707
Service Bulletin
ALERT
Number: A3542
Original Issue: February 12, 2016
ATA System: 5232
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Unpublished Work.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
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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A3542
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4.0

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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 1
B. Concurrent Requirements ...................................... 1 1
C. Reason ................................................ 1 1
D. Description .............................................. 1 2
E. Compliance .............................................. 1 2
F . A p p r o v a l  ............................................... 1 3
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 5
J . R e f e r e n c e s  .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 5
K. Publications Affected ........................................ 1 5
L. Interchangeability and Intermixability of Parts ........................... 1 5
M. Software Accomplishment Summary ................................ 1 5
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1 . K i t s / P a r t s  ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 2 1
3. Parts Modified and Reidentified ................................ 2 1
4. Parts Removed and Not Replaced .............................. 2 1
D. Parts Necessary to Change Spares ................................. 2 1
E. Special Tooling - Price and Availability ............................... 2 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 4
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT ........ 2 6
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT ....... 3 8
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT ......... 5 0
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: MAIN CARGO DOOR
CAM SUPPORT ASSEMBLY - INSPECTION ........................ 6 2
APPENDIX B: ADDITIONAL ACCESS .................................... 6 4
APPENDIX C: PART DEMAND INTENT ................................... 6 7
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Commercial 
Airplanes
707
Service Bulletin
ALERT
SummaryNumber: A3542Original Issue: February 12, 2016
ATA System: 5232
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 assembly part numbers 69-23588-5 and 69-23588-6
indicated that the existing maintenance program for the support assemblies 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 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
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
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### Page 6

ReferenceAffectedPlanning Data
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
1. Do an Ultrasonic Inspection of the grease fitting lug area of affected main cargo door cam support
assemblies for any crack.
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.
a. If no crack is found, repeat the Ultrasonic Inspection of the grease fitting lug area 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 installed.
b. If any crack is found, replace the cam support assembly pair at the affected location and repeat
the Ultrasonic Inspection of the grease fitting lug area 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 installed.
EFFECTIVITY
707-300B, 707-300C Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
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.
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MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
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.
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BOEING SERVICE BULLETIN A3542
ALERT  ALERT
D
DO AN INSPECTION OF THE
CAM SUPPORT ASSEMBLIES
FOR ANY CRACK
2461257
Original Issue: February 12, 2016
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### Page 9

Commercial 
Airplanes
707
Service Bulletin
ALERT
Number: A3542
Original Issue: February 12, 2016
ATA System: 5232
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
DESCRIPTIONCONFIGURATIONGROUP
707-300B, 707-300C 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:
707-300B, 707-300C
GroupVariable Number
105602 - 05605
107001 - 07017
107041 - 07059
107071 - 07081
107101 - 07109
107181
107191
107201 - 07215
107251 - 07271
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GroupVariable Number
107401 - 07407
107451 - 07458
107501 - 07504
107601 - 07626
107661 - 07662
107681 - 07684
107701 - 07702
107801 - 07821
107901 - 07907
108001 - 08008
108021
108051 - 08056
108071 - 08073
108077
108101 - 08103
108121 - 08129
108141 - 08144
108151 - 08153
108171 - 08173
108191 - 08192
108201 - 08204
108209
108221 - 08224
108241 - 08244
108251
108261
108271
108301 - 08320
108324 - 08330
108333
108401 - 08407
108410
108451 - 08452
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GroupVariable Number
108471 - 08475
108501 - 08502
108551 - 08553
108581 - 08582
109002 - 09004
109101 - 09107
109161 - 09167
109202
109223
109227
109231 - 09232
109251
109288 - 09290
109411
109421
109438
109441
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Boeing analysis of the main cargo door cam support assembly part numbers 69-23588-5 and 69-23588-6
indicated that the existing maintenance program for the support assemblies 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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### Page 12

D. Description
1. Do an Ultrasonic Inspection of the grease fitting lug area of affected main cargo door cam support
assemblies for any crack
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.
a. If no crack is found, repeat the Ultrasonic Inspection of the grease fitting lug area 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 installed.
b. If any crack is found, replace the cam support assembly pair at the affected location and
repeat the Ultrasonic Inspection of the grease fitting lug area 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 installed.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
2-49707-300B, 707-300C
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.
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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 1,790
flight cycles or
24 months after
the original is-
sue date of this
service bulletin,
whichever oc-
curs later
Before 18,000
total flight cycles
or within 10
years after instal-
lation of cam
support assem-
bly part num-
bers 69-23588-
5 and 69-23588-
6 in accordance
with Service
Bulletin
707A3387,
whichever oc-
curs first
Do an Ultrasonic Inspec-
tion of the grease fitting
lug area of affected main
cargo door cam support
assemblies for any crack.
(a)
All airplanes
4,000 flight cycles
or 10 years,
whichever occurs
first
--Repeat the Ultrasonic In-
spection of the grease fit-
ting lug area of the main
cargo door cam support
assembly at all locations
where an affected part
number 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
4,000 flight cycles
or 10 years,
whichever occurs
first
--ACTION 2: Repeat the
Ultrasonic Inspection of
the grease fitting lug area
of the main cargo door
cam support assembly at
all locations where an af-
fected part number is in-
stalled 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
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### Page 14

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.
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.
Inspection
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501Preparation
2.502.501Inspect
1.501.501Restoration
5.505.50TOTAL FOR EACH AIRPLANE
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.
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I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Letter 707-SL-00-011
b. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-01, 20-50-19
c. 707 Aircraft Maintenance Manual (AMM) 52-11-0
d. 707 Corrosion Prevention Manual (CPM) 52-30-07
e. 707, 720 Non-Destructive Testing (NDT) Manual Part 4, 52-30-01
f. Component Maintenance Manual (CMM) 52-36-61
g. Boeing Service Bulletin 707A3387
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, 52-30-01707 Non-Destructive Testing 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
TOP KIT - RETROFIT KIT FOR MAIN DECK
CARGO DOOR
65C38659-17
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.
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
-17
(a)-TOP KIT -
RETROFIT KIT
FOR MAIN DECK
CARGO DOOR
-65C38659-17
(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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### Page 19

ALL
Kit 65C38659
NotesExisting Part
Number
NameQtyNew Part Number
-17
(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 20

ALL
Kit 65C38659
NotesExisting Part
Number
NameQtyNew Part Number
-17
(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 707-
SL-00-011 for more information.
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### Page 21

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
Refer to FIGURE 1, FIG-
URE 2, and FIGURE 3. Op-
tional to make in one piece
rather than 4. (b)
RADIUS FILLER-2024-T3 ALCLAD,
2024-T4 ALCLAD,
or 7075-T6 AL-
CLAD
(a)SEALANT - PRESSURE AND ENVI-
RONMENTAL - CHROMATE TYPE
-BMS 5-95
(a)COATING - CHEMICAL AND SOL-
VENT RESISTANT FINISH, CORRO-
SION INHIBITING PRIMER
-BMS 10-11, TYPE
I
(a)COATING - CHEMICAL AND SOL-
VENT RESISTANT FINISH - BAC
702 WHITE COLOR, GLOSS
-BMS 10-11, TYPE
II
(a)COATING - ORGANIC CORRO-
SION INHIBITING COMPOUND
-BMS 3-23, TYPE II
(a)GREASE - AIRCRAFT GENERAL
PURPOSE
-BMS 3-33
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(b) 0.75 Inch X 0.75 Inch X 0.125 Inch
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 22

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 23

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 707 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 707
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 707
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 24

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 707 AMM 52-11-0 for an accepted procedure.
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### Page 25

2. RC - Do an Ultrasonic Inspection of the grease fitting lug area of affected main cargo door cam
support assemblies for any crack in accordance with 707, 720 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 CARGO
DOOR CAM SUPPORT ASSEMBLY REPLACEMENT.
a. CONDITION 1: NO CRACK FOUND
(1) Repeat the Ultrasonic Inspection of the grease fitting lug area of the main cargo door
cam support assembly at all locations where an affected part number is installed for any
crack in accordance with 707, 720 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) Do PART 1: MAIN CARGO DOOR CAM SUPPORT ASSEMBLY REPLACEMENT.
(2) Repeat the Ultrasonic Inspection of the grease fitting lug area of the main cargo door
cam support assembly at all locations where an affected part number is installed for any
crack in accordance with 707, 720 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 707 AMM 52-11-0 for 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 26 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
INBD  2458993
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 1 OF 12)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
STA
487.10
CAM SUPPORT ASSEMBLY
4U 16 LOCATIONS
SUPPORT ASSEMBLY
0001 D
14 15 18
BRACKET
6 LOCATIONS (12)
13 8 18
® (4 LOCATIONS)
LA  TENSION
TIE CLIP
> PART PROFILE SHOWN IS REFERENCE ONLY
2459294
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 2 OF 12)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
STA
520  3€G80ULD18
WEB
STA
CAM SUPPORT  500
ASSEMBLY
TU 16 LOCATIONS
(16 17) 10 LOCATIONS
13) RADIUS FILLE
/ 14 LOCATIONS
BRACKET
1001  12 14) 6 LOCATIONS
X17
TENSION TIE CLIP
19 1 118
19 11 14 15 18
SHEAR WEB
CAM AND BELLCRANK  ASSEMBLY  2459297
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 3 OF 12)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN A3542
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
CAM SUPPORT
ASSEMBLY  STA
487.10
SHEAR WEB
· ·*··*  * * ·  TENSION
TIE CLIP
B-B
- BRACKET
SHEAR WEB
B
TENSION TIE CLIP
A-A  2459400
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 4 OF 12)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
STA
500  CAM SUPPORT
ASSEMBLY
AlES
SHEAR WEB
CAM SUPPORT
AlE  ASSEMBLY
BRACKET
SHEAR WEB
TENSION TIE CLIP
C-C
TENSION
TIE CLIP  D-D  2459473
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 5 OF 12)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN A3542
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
STA
487.10
CAM SUPPORT
ASSEMBLY
STA  STA  2459436
500  E-E  487.10
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 6 OF 12)
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### Page 32

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 33

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 34

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-
36-61 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 35

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 707 AMM
52-11-0 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 707 CPM 52-30-07 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 36

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
-0.325-0.32818BACC30M10COLLAR
(a)0.325-0.3281BACB30NW10K6XBOLT, 100 DEG HEX
DR
B
-0.325-0.3281BACC30M10COLLAR
(a)0.388-0.3911BACB30MY12K10XBOLT, PROTRUDING
HD
C
-0.388-0.3911BACC30M12COLLAR
(a)0.2651-0.26618BACB30MY8K( )XBOLT, PROTRUDING
HD
D
-0.2651-0.26618BACC30M8COLLAR
(a)0.2651-0.26614BACB30LM4-( )XBOLTE
-0.2651-0.26614BACW10AW4ASWASHER, OVERSIZE
-0.2651-0.26614BACN10JC4CDNUT,SELF-LOCKING
(a)0.2651-0.26614BACB30NW8K( )XBOLT, 100 DEG HEX
DR
F
-0.2651-0.26614BACC30M8COLLAR
--4BACR15GF8D14RIVET, 100 DEGG
(a) (b)0.2651-0.266110BACB30LM4-( )XBOLTH
(b)0.2651-0.266110BACW10AW4ASWASHER, OVERSIZE
(b)0.2651-0.266110BACN10JC4CDNUT,SELF-LOCKING
(a) (b)0.263-0.2661BACB30MY8K7XBOLT, PROTRUDING
HD
I
(b)0.263-0.2661BACC30M8COLLAR
(a)0.200-0.2032BACB30NX6K( )XBOLT, PROTRUDING
HD
J
-0.200-0.2032BACC30M6COLLAR
(a)0.200-0.2035BACB30NX6K3XBOLT, PROTRUDING
HD
K
0.200-0.2035BACC30M6COLLAR
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 11 OF 12)
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### Page 37

More DataHole DiaQtyIdentificationNameCode
--25BACR15BB6D7CRIVET, UNIVERSAL
HD
L
(a)0.325-0.32811BACB30MY10K( )XBOLT, PROTRUDING
HD
M
-0.325-0.32811BACC30AG10COLLAR ASSEMBLY
(a)0.325-0.3281BACB30NW10K14XBOLT, 100 DEG HEX
DR
N
-0.325-0.3281BACC30AG10COLLAR 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 for 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 for an ac-
cepted procedure.
FIGURE 1: CAM SUPPORT ASSEMBLY AT STA 487.10 AND 500 - REPLACEMENT
(SHEET 12 OF 12)
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PROPRIETARY - Copyright © Unpublished
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Original Issue: February 12, 2016
A3542
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BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
D
INBD  2459675
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 1 OF 12)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN A3542
ALERT  ALERT
91U1518  STA 500  OR
STA 540
STA 520
OR  WEB
STA 560  ASSEMBLY  CAM SUPPORT  500/520  ONLY  STA
16 LOCATIONS (4 17
(4 LOCATIONS)  RADIUS FILLER 13  BRACKET
6 LOCATIONS (12 14  3 18
10 17
TENSION TIE CLIP
92969P6
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 2 OF 12)
Original Issue: February 12, 2016
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### Page 40 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
STA 560
STA 600  OR  3€080UUD18
STA 540
OR
CAM SUPPORT  STA 580
ASSEMBLY
DO 16 LOCATIONS
(16 17) 10 LOCATIONS
WEB  STA  13) RADIUS FILLE
580/600  BRACKET  / 14 LOCATIONS
ONLY
00®  12 14) 6 LOCATIONS
117
TENSION TIE CLIP
10U118
(15 18
SHEAR WEB
CAM AND BELLCRANK  ASSEMBLY  2459680
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 3 OF 12)
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### Page 41 (OCR)

BOEING SERVICE BULLETIN A3542
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
STA 520
CAM SUPPORT  ASSEMBLY  STA 560  OR
SHEAR WEB
****  7 7 7 7%  B-B  TIE CLIP
+ STA 520 ONLY
G STA 560 ONLY
SHEAR WEB
TENSION TIE CLIP
A-A  2459686
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 4 OF 12)
Original Issue: February 12, 2016
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### Page 42 (OCR)

BOEING SERVICE BULLETIN A3542
ALERT  ALERT
STA 540
OR
STA 580
CAM SUPPORT
ASSEMBLY
G- STA 540 ONLY
- STA 580 ONLY
SHEAR WEB
CAM SUPPORT
ASSEMBLY
ALE
BRACKET
SHEAR WEB
TENSION
TENSION TIE CLIP  TIE CLIP  D-D
C-C
2459687
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 5 OF 12)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN A3542
ALERT  ALERT
STA
520
STA
580
INBD
CAM SUPPORT
CAM SUPPORT  ASSEMBLY
ASSEMBLY
SHEAR WEB
STA  STA
540  520
E-E  2459702
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 6 OF 12)
Original Issue: February 12, 2016
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PROPRIETARY - Copyright © Unpublished
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### Page 44 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
CAM SUPPORT
CAM SUPPORT  ASSEMBLY
ASSEMBLY
SHEAR WEB
STA  STA
580  560
FWD
F-F
2459800
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 7 OF 12)
Original Issue: February 12, 2016
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Work - See page 1 for details.  44 of 67

### Page 45

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 8 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
A3542
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BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 46

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 9 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
A3542
46 of 67
BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 47

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-
36-61 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 707 AMM
52-11-0 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 10 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
A3542
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BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 48

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 707 CPM 52-30-07 and
SOPM 20-41-05 for an accepted procedure.
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
-0.325-0.32820BACC30M10COLLAR
(a)0.2651-0.26618BACB30MY8K( )XBOLT, PROTRUDING
HD
B
-0.2651-0.26618BACC30M8COLLAR
(a)0.2651-0.26614BACB30LM4-( )XBOLTC
-0.2651-0.26614BACW10AW4ASWASHER, OVERSIZE
-0.2651-0.26614BACN10JC4CDNUT,SELF-LOCKING
(a)0.2651-0.26614BACB30NW8K( )XBOLT, 100 DEG HEX
DR
D
-0.2651-0.26614BACC30M8COLLAR
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 11 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
A3542
48 of 67
BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 49

More DataHole DiaQtyIdentificationNameCode
--4BACR15GF8D14RIVET, 100 DEGE
(a) (b)0.2026-0.203616BACB30LM3-( )XBOLTF
(b)0.2026-0.203616BACW10AW3ASWASHER, OVERSIZE
(b)0.2026-0.203616BACN10JC3CDNUT
(a) (b)0.263-0.2661BACB30MY8K7XBOLT, PROTRUDING
HD
G
(b)0.263-0.2661BACC30M8COLLAR
(a)0.325-0.32812BACB30MY10K( )XBOLT, PROTRUDING
HD
H
(a)0.325-0.32812BACC30AG10COLLAR 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
-0.200-0.2032BACC30M6COLLAR
(a)0.200-0.2035BACB30NX6K3XBOLT, PROTRUDING
HD
K
-0.200-0.2035BACC30M6COLLAR
--25BACR15BB6D7CRIVET, UNIVERSAL
HD
L
(a) Install wet with BMS 5-95 sealant. Refer to SOPM 20-50-19 for 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 for an ac-
cepted procedure.
FIGURE 2: CAM SUPPORT ASSEMBLY AT STA 520, 540, 560, 580 - REPLACEMENT
(SHEET 12 OF 12)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 12, 2016
A3542
49 of 67
BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
INBD  2461473
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 1 OF 12)
Original Issue: February 12, 2016
Export Controlled ECCN: 9E991 - BOEING  A3542
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  50 of 67

### Page 51 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
STA
612.9
CAM SUPPORT ASSEMBLY
16 LOCATIONS A 1
SUPPORT ASSEMBLY
D000B
16 17 10 LOCATIONS
BRACKET
12 14 6 LOCATIONS
(4 LOCATIONS)  RADIUS FILLER 13
TENSION
TIE CLIP
> PART PROFILE SHOWN IS REFERENCE ONLY
2461477
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 2 OF 12)
Original Issue: February 12, 2016
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### Page 52 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
8 0UU4 1518  STA
580
WEB
STA
600  CAM SUPPORT
ASSEMBLY
16 LOCATIONS (7 17)
(4 LOCATIONS)  RADIOS FILLER 13  BRACKET
6 LOCATIONS (12) 14  6 3 18
10 17  17
TENSION TIE CLIP
15 18
€031
191  15 18)
SHEAR WEB
ASSEMBLY  CAM AND BELLCRANK  2461478
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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### Page 53 (OCR)

BOEING SERVICE BULLETIN A3542
ALERT  ALERT
STA
612.9  CAM SUPPORT
ASSEMBLY
ME
NIE
ALE
ME  SHEAR WEB
CAM SUPPORT
ASSEMBLY
ALE
B :
BRACKET
SHEAR WEB
TENSION TIE CLIP
A-A
TENSION
TIE CLIP  B-B  2461481
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 4 OF 12)
Original Issue: February 12, 2016
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### Page 54 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
CAM SUPPORT
ASSEMBLY  STA
600
SHEAR WEB
7 7 7 7  TENSION
TIE CLIP
D-D
- BRACKET
SHEAR WEB
TENSION TIE CLIP
C-C  2461482
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 5 OF 12)
Original Issue: February 12, 2016
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### Page 55 (OCR)

BOEING SERVICE BULLETIN А3542
ALERT  ALERT
CAM SUPPORT
ASSEMBLY
STA
612.9  CAM SUPPORT
ASSEMBLY
•
CAM SUPPORT  CAM SUPPORT
ASSEMBLY  ASSEMBLY
SHEAR WEB
612.9  STA  E-E  STA  600  2461483
FIGURE 3: CAM SUPPORT ASSEMBLY AT STA 600 AND 612.9 - REPLACEMENT
(SHEET 6 OF 12)
Original Issue: February 12, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  A3542
Work - See page 1 for details.  55 of 67

### Page 56

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
A3542
56 of 67
BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 57

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
A3542
57 of 67
BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 58

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-
36-61 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
A3542
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BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 59

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 707 AMM
52-11-0 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 707 CPM 52-30-07 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
A3542
59 of 67
BOEING SERVICE BULLETIN A3542
ALERTALERT

### Page 60

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
-0.325-0.32818BACC30M10COLLAR
(a)0.325-0.3281BACB30NW10K7XBOLT, 100 DEG HEX
DR
B
-0.325-0.3281BACC30M10COLLAR
(a)0.388-0.3911BACB30MY12K10XBOLT, PROTRUDING
HD
C
-0.388-0.3911BACC30M12COLLAR
(a)0.2651-0.26618BACB30MY8K( )XBOLT, PROTRUDING
HD
D
-0.2651-0.26618BACC30M8COLLAR
(a)0.2651-0.26614BACB30LM4-( )XBOLTE
-0.2651-0.26614BACW10AW4ASWASHER, OVERSIZE
-0.2651-0.26614BACN10JC4CDNUT,SELF-LOCKING
(a)0.2651-0.26614BACB30NW8K( )XBOLT, 100 DEG HEX
DR
F
-0.2651-0.26614BACC30M8COLLAR
--4BACR15GF8D14RIVET, 100 DEGG
(a) (b)0.2651-0.266110BACB30LM4-( )XBOLTH
(b)0.2651-0.266110BACW10AW4ASWASHER, OVERSIZE
(b)0.2651-0.266110BACN10JC4CDNUT,SELF-LOCKING
(a) (b)0.263-0.2661BACB30MY8K7XBOLT, PROTRUDING
HD
I
(b)0.263-0.2661BACC30M8COLLAR
(a)0.200-0.2032BACB30NX6K( )XBOLT, PROTRUDING
HD
J
-0.200-0.2032BACC30M6COLLAR
(a)0.200-0.2035BACB30NX6K4XBOLT, PROTRUDING
HD
K
-0.200-0.2035BACC30M6COLLAR
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
A3542
60 of 67
BOEING SERVICE BULLETIN A3542
ALERTALERT

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