# Bombardier Service Bulletin 601R-25-187

Copy: Revision A ("U.S. DOT/FAA - Service Information - 2"), 124 pages: PDF https://openairdocs.org/files/sha256/3e/21/3e21be3b7786b2592a86235dbdd3455441e2538a9e1f0417f7270032bca49e54; text https://openairdocs.org/service-documents/bombardier/601r-25-187/file/3e21be3b7786.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-0721; AD 2013-03-22 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 601R-25-187
- Latest revision known: 601R-25-187, Revision A, dated September 1, 2011 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/601r-25-187

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2013-03-22](https://openairdocs.org/ad/2013-03-22.md), effective Apr 17, 2013: Revision A

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/601r-25-187/proposed.md).

## Text (124 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2012-0721; AD 2013-03-22 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

SB 601R- - - 25- - - 187
Page 1 of 1
Sept 01/2011
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
CL- - -600- - -2B19 Canadair Regional Jet (CRJ) Aircraft
SERVICE BULLETIN 601R - - -25 - - -187
SUBJECT : Equipment/Furnishing - - - Cargo Compartment Linings - - - Replacement of
Liners in the Cargo Compartment (North American Configuration)
This page transmits:
Revision A of Service Bulletin 601R- - - 25- - - 187,
pages 1 thru 122, dated Sept 01/2011
The changes in this revision have no effect on aircraft that have
incorporated a previous issue of this service bulletin.
Reason:
Revised Planning Information, paragraph 1., to:
Change the aircraft affected in service and to add a note.
Revised Accomplishment Instructions, paragraph 2., to:
Add and change some steps and figures.
Revised Material Information, paragraph 3., to:
Change kit 601R25- - - 187K2.
This revision also includes small editorial changes that do not have an effect on the technical
content.
Instructions:
Discard the copy of Service Bulletin 601R- - - 25- - - 187, dated Jul 21/2011. Replace with the
copy attached.
KEEP C&D ZODIAC SERVICE BULLETINS B301002- - - 25- - - 01, B301002- - - 25- - - 02, AND
4652005- - - 25- - - 01.
Service Bulletin History:
Initial issue, dated Jul 21/2011.
1

### Page 2

SB 601R- - - 25- - - 187
Page 1 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
SERVICE BULLETIN
T echnical
Publications
THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED
HAS SOLD AIRCRAFT OR TRANSFERRED SPARES IN THE LAST SIX MONTHS, THIS SERVICE
BULLETIN MUST BE SENT TO THE NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED
THAT BOMBARDIER COMMERCIAL AIRCRAFT HAS INCLUDED THE NEW OPERATOR
AIRCRAFT , THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR
ON THE DISTRIBUTION LIST .
ATA SYSTEM: 25- - -52 NUMBER: 601R - - -25- - -187
SUBJECT : Equipment/Furnishing - - - Cargo Compartment Linings - - - Replacement of
Liners in the Cargo Compartment (North American Configuration)
1. PLANNING INFORMATION
A. Effectivity
(1) Aircraft Affected:
Service Bulletin: CL- - - 600- - - 2B19 Canadair Regional Jet (CRJ) Aircraft Serial
Numbers 7003 thru 7067 and 7069 thru 7857 that have a
North American lining installation in the cargo compartment.
NOTE: To find out if your aircraft has a North American lining
installation in the cargo compartment and if this
service bulletin is applicable to your aircraft, refer to
Figure 1 of this service bulletin.
NOTE: The procedure in this service bulletin was validated on aircraft with serial
number 7362.
Production: This change will be incorporated before delivery on Aircraft
Serial Numbers 7858 and subsequent.
NOTE: The instructions in this service bulletin are only applicable to the
systems and parts installed at the time of delivery of the aircraft or as
changed by Bombardier Service Bulletin(s). Before you do this
bulletin, examine all STC, STA or e quivalent action changes to make
sure this bulletin can be completed.

### Page 3

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 2 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
B. Reason
(1) Condition
The liners, installed in the cargo compartment, do not agree with the
flammability requirements of Federal Aviation Regulation (FAR) Part 25.855.
(2) Evidence
The installed liners were not correctly FAR Part 25.855 certified for
flammability.
(3) Objective/Benefit
This service bulletin gives the procedure to replace the liners in the cargo
compartment, change some floor panels, and do C&D Zodiac Service
Bulletins B301002- - - 25- - - 01, B301002- - - 25- - - 02, and 4652005- - - 25- - - 01.
After incorporation of this service bulletin, the liners in the cargo compartment
will agree with the flammability requirements of FAR Part 25.855.
C. Description
The cargo-compartment door is opened. The sidewall liners and the rear bulkhead
liners are removed. Some sidewall brackets are changed and new ones are
installed. Sealed nutplate assemblies are installed on the rear pressure bulkhead.
C&D Service Bulletins B301002- - - 25- - - 01, B301002- - - 25- - - 02, and 4652005- - - 25- - - 01
are done to change the 9G bulkhead.
Five floor panels are removed and changed. The floor panels are installed. The
rear bulkhead liners and the sidewall liners are installed. Return-to-service tests are
done.
D. Compliance
Recommended Service Bulletin. Bombardier recommends that this service bulletin
be done before 31 July 2014, unless otherwise directed by the airworthiness
authority of the operator.
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage
T olerance inspections (DTIs).
E. Approval
The technical content of this service bulletin has been approved under the authority
of the TCCA Design Approval Organization No: DAO #93- - -Q- - -02.

### Page 4

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 3 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
F. M a n p o w e r
The man-hours given below are an estimate for direct labor done by an
experienced crew on an aircraft prepared for maintenance.
This estimate does not include the time necessary for:
− Administrative functions such as planning, liaison, familiarization, and report writing.
− Non productive elapsed time such as rest time, having meals, and crew shift
changes.
− Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting.
− Preparation for modification (unless specified in the accomplishment
instructions) such as cleaning and getting parts, tools, consumables, and
ground equipment.
− Quality assurance inspections, troubleshooting and/or correction of
discrepancies found when a task is done.
− All other activities that are not considered by Bombardier as directly related to
the accomplishment of this procedure.
NOTE: For on-site labor assistance, please speak with a Fleet Services
representative for a quote. The Fleet Services Team can be
contacted via the CRC at 514- - - 855- - - 8500 or email at
thd.crj@aero.bombardier.com.
It will take an estimated 87.00 man-hours to complete this service bulletin. The
man- - - hours are divided as shown in the table that follows:
TASK M A N --- H O U R S
( 1 ) J o b S e t --- U p 20.00
(2) Procedure 60.00
(3) T est 3.00
(4) Job Close- - -Out 4.00
NOTE: This estimate does not include the man-hours necessary to do C&D
Zodiac Service Bulletins B301002- - - 25- - - 01, B301002- - - 25- - - 02, and
4652005- - - 25- - - 01.

### Page 5

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 4 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
G. Material - - - Price and Availability
(1) The kits in the table that follows are available from Bombardier Commercial
Aircraft.
NOTE: For a list of the kit contents, refer to paragraph 3.A.
KIT NUMBER NAME
601R25- - - 187K1 Structural Components, Baggage Bay
Liners - - - North American Configuration
601R25- - - 187K2A Hardware, Baggage Bay Liners - - - North
American Configuration
601R25- - - 187K350 Baggage Bay Liners - - - North American
Configuration
For aircraft that have a cargo-compartment load divider
KIT NUMBER NAME
601R25- - - 187K351 Baggage Bay Liners - - - North American
Configuration
For aircraft that do not have a cargo-compartment load divider
KIT NUMBER NAME
601R25- - - 187K352 Baggage Bay Liners - - - North American
Configuration
For aircraft that have Piccolo Tube P/N 601R99011 - - -13
KIT NUMBER NAME
601R25- - - 187K353 Baggage Bay Liners - - - North American
Configuration

### Page 6

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 5 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
For aircraft that have Piccolo Tube P/N 601R99011 - - -1 or - - -9
KIT NUMBER NAME
601R25- - - 187K354 Baggage Bay Liners - - - North American
Configuration
For aircraft post-service bulletin 601R - - -21 - - -059 or that have CR25 - - -359 (Cargo
Compartment - - - T emperature Control)
KIT NUMBER NAME
601R25- - - 187K355 Baggage Bay Liners - - - North American
Configuration
For aircraft pre-service bulletin 601R - - -21 - - -059 or that do not have CR25 - - -359 (Cargo
Compartment - - - T emperature Control)
KIT NUMBER NAME
601R25- - - 187K356 Baggage Bay Liners - - - North American
Configuration
For all aircraft
(2) The part in the table that follows is necessary to do this service bulletin and is
available from Bombardier Commercial Aircraft.
PART NUMBER NAME QUANTITY
TAFB101- - - 006S Sealant, firewall (6 oz tube) 3

### Page 7

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 6 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
(3) Please send a purchase order to the address below to schedule the kits:
Bombardier
Service Bulletin Kit Support T eam
123 Garratt Blvd, N42- - - 24
T oronto, Ontario
Canada M3K 1Y5
Fax: 416- - - 375- - - 3060
Phone: 416- - - 375- - - 3920
Email: sbkits@aero.bombardier.com
Please contact the Service Bulletin Kit Support T eam at the address above for
terms and conditions.
(4) Refer to C&D Service Bulletins B301002- - - 25- - - 01, B301002- - - 25- - - 02, and
4652005- - - 25- - - 01 for terms and conditions.
(5) Refer to paragraph 3.B. for a list of consumables for this service bulletin.
For Business/Corporate Operators
All Business/Corporate operators (i.e. operators who do not have a commercial
airline operation) refer to SB 800- - - 00- - - 004 for commercial policy coverage and
logistics/planning arrangements (refer to www.cic.bombardier.com/technical
library/service bulletins/challenger/850/SB 800- - - 00- - - 004).
T o place an order for parts or kits, please call Bombardier Parts Logistics at
514- - - 855- - - 2999 or 1- - - 866- - - 538- - - 1247.
For all aircraft
H. T ooling - - - Price and Availability
There are no tool kits for this service bulletin.
Refer to paragraph 3.C. for a list of special tools and equipment for this service
bulletin.

### Page 8

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 7 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
I. Weight and Balance
WEIGHT ARM MOMENT ¡
25 lb 695.00 in. 17.375 (1000 lb--- in.)
11.34 kg 17.65 m 0.2002 (1000 kg- - - m)
¡ The value in the Moment column is divided by 1000.
Refer to the Weight & Balance Manual CSP A- - - 041.
NOTE: Because of the difference in weight of the different lining panel
configurations, only the heaviest calculation is given. If necessary, weigh
the aircraft after the incorporation of this service bulletin to get more
accurate data.
J. Electrical Load Data
Not changed.
K. References
Modification Summary TC601R17981, Revision D- - - 1.
Restriction and/or Special Instruction (RSI) C- - -A265, Revision A.
C&D Zodiac Service Bulletin B301002- - - 25- - - 01, dated Apr 19/11.
C&D Zodiac Service Bulletin B301002- - - 25- - - 02, Revision 1, dated Jun 16/11.
C&D Zodiac Service Bulletin 4652005- - - 25- - - 01, dated Mar 10/11.
Aircraft Maintenance Manual.
Structural Repair Manual.
For Bombardier reference only: PCA 4625.
L. Other Publications Affected
Aircraft Maintenance Manual (AMM)
Aircraft Illustrated Parts Catalog (AIPC)

### Page 9

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 8 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
M. Relationship Chart
PRE - - -SB
PART NUMBER NAME POST - - -SBPART NUMBER NAME
601R31668- - - 241 Floor panelassembly K601R45034- - - 2053 Floor panelassembly
601R31668- - - 243 Floor panelassembly K601R45034- - - 2055 Floor panelassembly
601R31668- - - 245 Floor panelassembly K601R45034- - - 2051 Floor panelassembly
601R31668- - - 247 Floor panelassembly K601R45034- - - 2057 Floor panelassembly
601R31668- - - 249 Floor panelassembly K601R45034- - - 2059 Floor panelassembly
601R31668- - - 273 Floor panelassembly K601R45034- - - 2063 Floor panelassembly
601R31668- - - 275 Floor panelassembly K601R45034- - - 2065 Floor panelassembly
601R31668- - - 277 Floor panelassembly K601R45034- - - 2061 Floor panelassembly
601R31668- - - 279 Floor panelassembly K601R45034- - - 2067 Floor panelassembly
601R31668- - - 281 Floor panelassembly K601R45034- - - 2069 Floor panelassembly
601R31668- - - 323 Floor panelassembly K601R45034- - - 2077 Floor panelassembly
601R31668- - - 325 Floor panelassembly K601R45034- - - 2071 Floor panelassembly
601R31668- - - 333 Floor panelassembly K601R45034- - - 2075 Floor panelassembly
601R31668- - - 345 Floor panelassembly K601R45034- - - 2073 Floor panelassembly
601R31668- - - 361 Floor panelassembly K601R45034- - - 2079 Floor panelassembly

### Page 10

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 9 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
PRE - - -SB
PART NUMBER NAMEPOST - - -SBPART NUMBERNAME
601R31668- - - 495 Floor panelassembly K601R45034- - - 2087 Floor panelassembly
601R31668- - - 497 Floor panelassembly K601R45034- - - 2081 Floor panelassembly
601R31668- - - 499 Floor panelassembly K601R45034- - - 2085 Floor panelassembly
601R31668- - - 501 Floor panelassembly K601R45034- - - 2083 Floor panelassembly
601R31668- - - 503 Floor panelassembly K601R45034- - - 2089 Floor panelassembly
601R31668- - - 9037 Floor panelassembly K601R45034- - - 2097 Floor panelassembly
601R31668- - - 9063 Floor panelassembly K601R45034- - - 2107 Floor panelassembly
601R45103- - - 13 Clip K601R45034- - - 2019 Clip
601R45103- - - 19 Clip K601R45034- - - 2025 Clip
601R45103- - - 29 Clip K601R45034- - - 2027 Clip
601R45103- - - 33 Clip K601R45034- - - 2021 Clip
601R45103- - - 35 Clip K601R45034- - - 2023 Clip
601R45552- - - 5 Channelassembly K601R45034- - - 2007 Channelassembly
601R45552- - - 15 Channelassembly K601R45034- - - 2001 Channelassembly
601R45552- - - 19 or - - - 67
or 601R45551- - - 951
Channel
assembly 601R45552- - - 71 Channelassembly
601R45552- - - 23
or - - - 951 or 955
Channel
assembly K601R45034- - - 2029 Channelassembly
601R45552- - - 59 Channelassembly K601R45034- - - 2003 Channelassembly
601R45552- - - 125 Channelassembly K601R45034- - - 2005 Channelassembly

### Page 11

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 10 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
PRE - - -SB
PART NUMBER NAMEPOST - - -SBPART NUMBERNAME
601R45105- - - 15 Channelassembly K601R45034- - - 2009 Channelassembly
601R45105- - - 21 Channelassembly K601R45034- - - 2013 Channelassembly
601R45102- - - 117 Channelassembly K601R45034- - - 2011 Channelassembly
601R45102- - - 131 Channelassembly K601R45034- - - 2015 Channelassembly
601R45102- - - 963 Channelassembly K601R45034- - - 2017 Channelassembly
601R96385- - - 19 or - - - 27
o r --- 3 5 Duct, plenum B303601- - - 101 or - - - 103 Duct, plenum
BR7203- - - 804 and
601R520701- - - 9 Light, cargo BR7203- - - 804- - - 1 Light, cargo
601R45553- - - 1 Liner assembly B302103- - - 101 Liner assembly
601R45553- - - 3 or - - - 15, or
- - - 25 or - - - 29 or - - - 2501Liner assembly B302102- - - 101 Liner assembly
601R455532- - - 5 or - - - 17
o r --- 2 5 o r --- 3 5 o r
601R45561- - - 1
Liner assembly B303102- - - 101 Liner assembly
601R455532- - - 1 or - - - 7 or
--- 1 1 o r --- 1 3 o r --- 1 5 o r
- - - 21 or - - - 2501 or
601R45560- - - 1
Liner assembly B303101- - - 101 or - - - 103Liner assembly
601R4553- - - 13 or - - - 17 or
- - - 27 or 601R45562- - - 1 Liner assembly B302104- - - 101 Liner assembly
601R455532- - - 3 or - - - 9 or
- - - 23 or - - - 2519 Liner assembly B302101- - - 101 Liner assembly
601R45158- - - 11 or - - - 15 or
- - - 21 or 601R45565- - - 3 or
K601R45001- - - 7
Tie rod cap
assembly B306104- - - 101 Tie rod capassembly

### Page 12

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 11 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
PRE - - -SB
PART NUMBER NAMEPOST - - -SBPART NUMBERNAME
601R45158- - - 3 or - - - 5 or
--- 1 7 o r --- 1 9 o r
601R45565- - - 1 or
K601R45001- - - 5
Tie rod cap
assembly
B306102- - - 101 or
B306103- - - 101 or - - - 102
Tie rod cap
assembly
601R45554- - - 7 or - - - 9 or
601R45566- - - 1 or
K601R45001- - - 9
Tie rod cap
assembly B306105- - - 101 Tie rod capassembly
601R45554- - - 1 or - - - 13 or
601R45563- - - 1 or
K601R45001- - - 3
Tie rod cap
assembly B306101- - - 101 Tie rod capassembly
601R45554- - - 5 or - - - 11 or
601R45567- - - 1 or
K601R45001- - - 11
Tie rod cap
assembly B306106- - - 101 Tie rod capassembly
601R45152- - - 11 or
601R45400- - - 977 Liner assembly B305103- - - 101 Liner assembly
601R45152- - - 9 or - - - 19 or
- - - 2501 or
601R45400- - - 955 or
--- 9 6 5
Liner assembly B305102- - - 101 Liner assembly
601R45152- - - 13 or
601R45400- - - 981 Liner assembly B305101- - - 101 Liner assembly
601R45401- - - 7 or - - - 9 or
- - - 11 or 601R45400- - - 971
o r --- 9 7 3
Angle assembly B305113- - - 101 Duct skirt,bulkhead
601R45152- - - 15 or - - - 21
or 601R45400- - - 967 Angle assembly B305111- - - 101 Angle, floor
601R45152- - - 17 or - - - 23
or 601R45400- - - 969 Angle assembly B305112- - - 101 Angle, floor
601R45401- - - 5 or - - - 13 Duct assembly B305104- - - 101 Duct assembly
601R45154- - - 5 or - - - 13 or
IS601R25520054- - - 5
Protection
barrier B305123- - - 101 Liner assembly
601R45154- - - 3 or - - - 9 or
--- 1 7 o r
IS601R25520054- - - 3
Protection
barrier 601R45154- - - 21 FPC Foamsheet

### Page 13

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 12 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
PRE - - -SB
PART NUMBER NAMEPOST - - -SBPART NUMBERNAME
601R45154- - - 7 or - - - 15 or
IS601R25520054- - - 7
Protection
barrier B305122- - - 101 Liner assembly
601R45154- - - 1 or - - - 11 or
- - - 19 or 601R45400- - - 955
or IS601R25520054- - - 1
Protection
barrier B305121- - - 101 Liner assembly
601R45451- - - 1 or - - - 7 or
601R45350- - - 971 Shroud, door B303110- - - 1 Shroud, door
601R45451- - - 3 or
601R45350- - - 965 Liner assembly B302105- - - 101 Liner assembly
601R45451- - - 5 or
601R45350- - - 967 Liner assembly B302106- - - 101 Liner assembly

### Page 14

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 13 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
2. ACCOMPLISHMENT INSTRUCTIONS
A . J o b S e t --- U p
Reference Information
REFERENCE DESIGNATION
A M M 1 1 --- 3 0 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Adhesive-Backed Label
A M M 1 2 --- 0 0 --- 0 7 --- 8 6 1 --- 8 0 1 Connect External AC Power
A M M 2 0 --- 2 1 --- 0 0 --- 9 1 0 --- 8 0 1T orque Procedures for Threaded Fasteners
A M M 2 0 --- 2 1 --- 0 0 --- 9 1 0 --- 8 0 2T orque Procedures for Plumbing Lines
A M M 2 0 --- 3 0 --- 0 0 --- 9 1 0 --- 8 0 2Wiggins Couplings - - - Maintenance Practices
A M M 2 1 --- 5 1 --- 0 0 --- 7 9 0 --- 8 0 1Leak T est of the Air Conditioning System
A M M 2 1 --- 5 1 --- 1 5 --- 0 0 0 --- 8 0 1Removal of the Pack Discharge-Ducts
A M M 2 1 --- 5 1 --- 1 5 --- 4 0 0 --- 8 0 1Installation of the Pack Discharge-Ducts
A M M 2 1 --- 5 5 --- 1 3 --- 0 0 0 --- 8 0 1Removal of the Compartment Overheat Switch
A M M 2 1 --- 5 5 --- 1 3 --- 4 0 0 --- 8 0 1Installation of the Compartment Overheat Switch
A M M 2 1 --- 5 5 --- 1 3 --- 7 1 0 --- 8 0 1Operational T est of the Compartment Overheat
Switch
A M M 2 1 --- 5 5 --- 1 7 --- 0 0 0 --- 8 0 1Removal of the T emperature Control Switch
A M M 2 1 --- 5 5 --- 1 7 --- 4 0 0 --- 8 0 1Installation of the T emperature Control Switch
A M M 2 1 --- 5 5 --- 1 7 --- 7 1 0 --- 8 0 1Operational T est of the T emperature Control
Switch
A M M 2 4 --- 0 0 --- 0 0 --- 9 1 0 --- 8 0 1Electrical/Electronic Safety Precautions
A M M 2 5 --- 5 1 --- 0 1 --- 4 0 0 --- 8 0 1Installation of the Cargo Restraint Netting
A M M 2 5 --- 5 1 --- 0 1 --- 4 0 0 --- 8 0 2Installation of the Cargo Restraint Posts
A M M 2 5 --- 5 2 --- 0 1 --- 0 0 0 --- 8 0 1Removal of the Cargo Compartment Sidewall
Linings
A M M 2 5 --- 5 2 --- 0 1 --- 0 0 0 --- 8 0 2Removal of the Cargo Compartment Rear
Bulkhead Linings

### Page 15

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 14 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
REFERENCE DESIGNATION
A M M 2 6 --- 1 5 --- 0 1 --- 0 0 0 --- 8 0 1Removal of the Cargo Smoke Detector
A M M 2 6 --- 1 5 --- 0 1 --- 4 0 0 --- 8 0 1Installation of the Cargo Smoke Detector
A M M 2 6 --- 1 5 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the Cargo Smoke-Detection
System
A M M 2 6 --- 2 2 --- 0 0 --- 7 1 0 --- 8 0 2Operational T est of the APU Fire-Extinguishing
System
A M M 2 6 --- 2 2 --- 0 7 --- 0 0 0 --- 8 0 1Removal of the APU Fire-Extinguisher Container
A M M 2 6 --- 2 2 --- 0 7 --- 4 0 0 --- 8 0 1Installation of the APU Fire-Extinguisher
Container
A M M 2 6 --- 2 5 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the Cargo Fire-Extinguishing
System
A M M 2 6 --- 2 5 --- 0 7 --- 0 0 0 --- 8 0 1Removal of the Cargo Fire-Extinguisher
Discharge-Line
A M M 2 6 --- 2 5 --- 0 7 --- 4 0 0 --- 8 0 1Installation of the Cargo Fire-Extinguisher
Discharge-Line
A M M 3 3 --- 3 1 --- 0 1 --- 0 0 0 --- 8 0 1Removal of the Service Light Assembly
A M M 3 3 --- 3 1 --- 0 1 --- 4 0 0 --- 8 0 1Installation of the Service Light Assembly
A M M 3 3 --- 3 1 --- 0 0 --- 7 1 0 --- 8 0 1 Operational T est of the Service Lights
A M M 3 4 --- 4 4 --- 0 1 --- 0 0 0 --- 8 0 1Removal of the Radio Altimeter Transceiver
A M M 3 4 --- 4 4 --- 0 1 --- 4 0 0 --- 8 0 1Installation of the Radio Altimeter Transceiver
A M M 3 4 --- 4 4 --- 0 1 --- 7 4 0 --- 8 0 1 Built-In T est of the Radio Altimeter
A M M 3 4 --- 4 4 --- 0 4 --- 0 0 0 --- 8 0 1Removal of the Radio Altimeter Converter
A M M 3 4 --- 4 4 --- 0 4 --- 4 0 0 --- 8 0 1Installation of the Radio Altimeter Converter
A M M 4 9 --- 5 2 --- 0 1 --- 0 0 0 --- 8 0 1Removal of the APU Cooling Air Intake Duct
A M M 4 9 --- 5 2 --- 0 1 --- 4 0 0 --- 8 0 1Installation of the APU Cooling Air Intake Duct
A M M 4 9 --- 6 1 --- 0 1 --- 0 0 0 --- 8 0 1 Removal of the APU ECU
A M M 4 9 --- 6 1 --- 0 1 --- 4 0 0 --- 8 0 1 Installation of the APU ECU

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Revision A, Sept 01/2011
REFERENCE DESIGNATION
A M M 4 9 --- 6 1 --- 0 1 --- 9 7 0 --- 8 0 1Write Data into the APU Electronic Control Unit
(ECU)
A M M 5 1 --- 2 2 --- 2 8 --- 3 4 0 --- 8 0 1 Cementing of Silicone Rubber
A M M 5 1 --- 2 3 --- 0 0 --- 1 0 0 --- 8 0 1 Preparation of Surfaces for Sealing
A M M 5 1 --- 2 3 --- 0 0 --- 3 9 0 --- 8 0 7 Gap Sealing Procedure
A M M 5 1 --- 2 3 --- 0 0 --- 3 9 0 --- 8 1 5 Curing of Sealant
A M M 5 1 --- 2 3 --- 0 0 --- 9 1 0 --- 8 0 1 Sealant Safety Precautions
A M M 5 2 --- 3 1 --- 0 0 --- 0 0 0 --- 8 0 1Removal of the Cargo Compartment Door
A M M 5 2 --- 3 1 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Cargo Compartment Door
A M M 5 2 --- 3 1 --- 0 0 --- 7 1 0 --- 8 0 1Operational T est of the Cargo Compartment
Door
A M M 5 2 --- 3 1 --- 0 0 --- 8 2 0 --- 8 0 1Adjustment of the Cargo Compartment Door
A M M 5 2 --- 7 0 --- 0 2 --- 7 1 0 --- 8 0 1Operational T est of the Cargo-Compartment
Door Warning-System
A M M 5 3 --- 0 1 --- 0 1 --- 0 0 0 --- 8 0 4Removal of the Cargo Compartment Floor
Panels
A M M 5 3 --- 0 1 --- 0 1 --- 4 0 0 --- 8 0 4Installation of the Cargo Compartment Floor
Panels
S R M 5 1 --- 2 1 --- 1 1 Corrosion Prevention Procedures
S R M 5 1 --- 2 3 --- 0 0 Pressure, Environmental, Fuel T ank and Fire-Wall
Sealing
S R M 5 1 --- 2 4 --- 3 6 Cutting of Sheet Metal
S R M 5 1 --- 2 6 --- 0 0 Cleaning
S R M 5 1 --- 4 0 --- 1 1 How to Prepare Fastener Holes
S R M 5 1 --- 4 1 --- 0 2 Bolts, Screws and Related Items
S R M 5 1 --- 4 2 --- 0 6 Solid Rivets
S R M 5 1 --- 4 2 --- 1 0 Blind Rivets - - - General
S R M 5 1 --- 4 2 --- 1 1 Cherry Lock Rivets - - - General

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Revision A, Sept 01/2011
REFERENCE DESIGNATION
S R M 5 1 --- 4 2 --- 1 3 Cherrymax Blind Rivets
S R M 5 1 --- 4 2 --- 3 4 Blind Nuts
S R M 5 1 --- 4 5 --- 0 0 Nutplate (Anchor Nuts) - - - General
T olerance Information
Linear T olerances Angular T olerance
X.XX in. (0.X mm) X.X in. (X mm)
+ / --- 0° 30”+/- - - 0.03 in. +/--- 0.1 in.
+ / --- 0 . 8 m m + / --- 3 m m
NOTE: The tolerances above apply to the dimensions given in this service
bulletin except if specified differently.
(1) Obey all the electrical/electronic safety precautions
(Refer to AMM 24- - - 00- - - 00- - - 910- - - 801).
(2) Obey all the sealant safety precautions
(Refer to AMM 51- - - 23- - - 00- - - 910- - - 801).
(3) Open the cargo compartment door .
(4) Open the aft equipment compartment door .
(5) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
C B P --- 1 F11 1 0 T HS TB / A I RS O VL 221
C B P --- 1 G1 CARGO FIREX 2 221
C B P --- 1 J1 L AIR COND UNIT 221
C B P --- 1 K7 RAD ALT 221
C B P --- 1 M2 ENG IGN A 221
C B P --- 1 M3 ENG IGN B 221
C B P --- 1 M4 ENG START R 221
C B P --- 1 M5 ENG START L 221

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Revision A, Sept 01/2011
CB PANEL ZONE NAMECB NO.
C B P --- 1 N12 XFER/APU APU ECU 221
C B P --- 1 P1 CARGO FIREX 1 221
C B P --- 1 R5 APU FIRE EXT A 221
C B P --- 1 R6 APU FIRE EXT B 221
C B P --- 2 F11 1 0 T HS TB / A I RS O VR 222
C B P --- 2 J1 R AIR COND UNIT 222
C B P --- 2 T1 SERV LTS 222
C B P --- 2 T3 SERV LTS 222
C B P --- 4 B1 10TH ST B/AIR ISOL 222
C B P --- 4 B12 DOOR INDICATION 222
C B P --- 5 A1 APU ACT 311
C B P --- 5 A13 LIGHTS SERV 311
(6) Remove and discard the cargo compartment sidewall linings
(Refer to AMM 25- - - 52- - - 01- - - 000- - - 801). Keep the items that follow:
PART NUMBER DESIGNATION LOCATION
¡ 20050 Anchor plates FS567.00L, STGR
4, 9, 11, 13, and 16
601R96360- - - 69 and
601R96361- - - 1
or
601R96362- - - 1
Bracket assembly and
wire screen
or
Screen assembly,
inlet duct
FS559+112L,
STGR 17
¡ On aircraft that have the cargo compartment load divider.

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Revision A, Sept 01/2011
Refer to Figure 4 (Sheet 2 of 14).
(7) Remove and discard the support assembly between the liner assembly (18)
and the structure at FS621.00, WL80.0, RBL47.0.
Refer to Figure 4 (Sheet 1 of 14).
(8) Remove the cargo compartment rear bulkhead linings and record the
installation locations of the channel assemblies on the pressure bulkhead
(Refer to AMM 25- - - 52- - - 01- - - 000- - - 802).
(9) Remove the cargo smoke detector (Refer to AMM 26- - - 15- - - 01- - - 000- - - 801).
(10) Remove the cargo lights (Refer to AMM 33- - - 31- - - 01- - - 000- - - 801).
(11) Remove the fire extinguisher discharge-line
(Refer to AMM 26- - - 25- - - 07- - - 000- - - 801).
For aircraft that have holes in the pressure bulkhead and that do not have Modification
Summary IS601R25520054 incorporated
Refer to Figure 2 (Sheet 1 of 3).
(12) Remove and discard the liner assemblies (1), (2), and (3) and the FPC foam
sheet (4) on the rear pressure bulkhead as follows:
(a) Remove the blind rivets (6) (Refer to SRM 51- - - 42- - - 10).
(b) Remove the washers (5).
(c) Remove the liner assemblies (1), (2), and (3) and the FPC foam sheet (4)
from the rear pressure bulkhead.
For aircraft that have Modification Summary IS601R25520054 incorporated
Refer to Figure 2 (Sheet 2 of 3).
(13) Remove and discard the liner assemblies (1), (2), and (3) and the FPC foam
sheet (4) from the rear pressure bulkhead as follows:
(a) Remove the screws (6) and the washers (5).
(b) Remove the liner assemblies (1), (2), and (3) and the FPC foam sheet (4)
from the rear pressure bulkhead.
CAUTION: DO NOT USE METAL SCRAPERS OR OTHER SHARP TOOLS TO
REMOVE SEALANT . METAL SCRAPERS OR SHARP TOOLS CAN
CAUSE STRUCTURAL DAMAGE TO THE AIRCRAFT SURFACE.
(c) Remove the fillet of sealant with a n on-metallic scraper around the FPC
foam sheet (4).
(d) Remove the FPC foam sheet (4) from the rear pressure bulkhead.

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Revision A, Sept 01/2011
For aircraft that do not have holes in the pressure bulkhead
Refer to Figure 2 (Sheet 3 of 3).
(14) Remove and discard the liner assemblies (1), (2), and (3) and the FPC foam
sheet (4) from the rear pressure bulkhead as follows:
CAUTION: DO NOT USE METAL SCRAPERS OR OTHER SHARP TOOLS TO
REMOVE SEALANT . METAL SCRAPERS OR SHARP TOOLS CAN
CAUSE STRUCTURAL DAMAGE TO THE AIRCRAFT SURFACE.
(a) Remove the fillet of sealant with a non-metallic scraper around the liner
assemblies (1), (2), and (3) and the FPC foam sheet (4).
(b) Remove the liner assemblies (1), (2), and (3) and the FPC foam sheet (4)
from the rear pressure bulkhead.
For Aircraft 7003 - - -7007, 7009 - - -7026 post-SB 601R - - -25 - - -022 and Aircraft 7027 - - -7857
Refer to Figure 3 (Sheet 1 of 2).
(15) On the left side of the cargo compartment, between FS574.00 and FS621.00,
remove the foam sheet (1) as follows:
(a) Remove the 12 rivets (2) and the washers (3) that attach the foam sheet
(1) to the structure.
(b) Remove and discard the foam sheet (1).
(c) Install the rivets (2) in the remaining holes.
For all aircraft
Refer to Figure 3 (Sheet 2 of 2).
(16) Between FS574.00 and FS621.00, install seven blind nut assemblies (1) on
the intercostal (2) as follows:
(a) Between FS574.00 and FS621.00, make a horizontal line on the
intercostal (2) with a marker at 0.80 in. (20.3 mm) from the lower flange
o f t h e i n t e r c o s t a l ( 2 ) ( R e f e r t o v i e w E --- E ) .
(b) Between FS574.00 and FS621.00, make seven vertical lines at the
intersections of the horizontal lines (Refer to view D- - - D).
(c) Drill seven holes to a diameter of 0.313 to 0.319 in. (7.95 to 8.10 mm) at
the intersection of the horizontal and vertical lines on the intercostal (2)
(Refer to View D).
(d) Remove the burrs and sharp edges.
(e) Apply chemical conversion coating on the aluminum bare metal areas.
(f) Install the blind nut assemblies (1) on the intercostal (2).

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Revision A, Sept 01/2011
For all aircraft
(17) Remove the floor panels that follow (Refer to AMM 53- - - 01- - - 01- - - 000- - - 804):
ACCESS DESIGNATION
281LLF Access Panel
281JLF Access Panel
281DLF Access Panel
282GRF Access Panel
282KRF Access Panel
(18) If necessary, remove the baggage bay door
(Refer to AMM 52- - - 31- - - 00- - - 000- - - 801).
(19) If necessary, remove the left discharge duct
(Refer to AMM 21- - - 51- - - 15- - - 000- - - 801).
Refer to Figure 16.
(20) Remove the ground connection duct (1) as follows:
WARNING: BEFORE YOU DISCONNECT A PNEUMATIC DUCT COUPLING, MAKE
SURE THAT YOU RELEASE PRESSURE FROM THE MANIFOLD AND
THAT THE COMPONENTS ARE COOL. IF YOU DO NOT DO THIS YOU
CAN CAUSE INJURIES TO PERSONS.
(a) Loosen the coupling nut on the lower coupling (3) and remove it from
the adaptor and the duct (1).
(b) Remove the silicone tape from around the boot (2) which covers the
upper coupling (3) on the duct (1).
(c) Remove the boot (2).
(d) Loosen the coupling nut and remove the upper coupling (3) from the
duct (1) and the bleed air duct.
(e) Put protective covers on the open ducts and on the flange of the
adaptor.

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Revision A, Sept 01/2011
(21) Remove the cooler duct (Refer to AMM 49- - - 52- - - 01- - - 000- - - 801).
(22) Remove the APU ECU (Refer to AMM 49- - - 61- - - 01- - - 000- - - 801).
(23) Remove the radio altimeter (Refer to AMM 34- - - 44- - - 01- - - 000- - - 801).
(24) Remove the radio altimeter converter (Refer to AMM 34- - - 44- - - 04- - - 000- - - 801).
Refer to Figure 15.
(25) Remove the mounting trays (3), (4), and (8) as follows:
(a) Remove the electrical connector from the mounting tray of the converter
(4).
(b) Remove the screws (5) and the washers (6) from the mounting tray (4) of
the converter.
(c) Remove the screws (7) from the mounting tray of the radio altimeter (3).
(d) Remove the electrical connector from the mounting tray of the ECU (8).
(e) Remove the screws (9), the washers (10), and the nut (11) from the ECU
mounting tray of the ECU (8).
(f) Remove the mounting trays (4), (3), and (8) from the structure.
(26) If necessary, at FS672.20/STGR16, remove the bracket (1) from the frame as
follows:
(a) Remove eight rivets (2) from the bracket (1) and the frame.
(b) Carefully move the bracket (1) along the frame.
(c) Make sure that you do not damage the wire bundle attached to the
bracket (1).
(27) Remove the APU fire extinguisher (Refer to AMM 26- - - 22- - - 07- - - 000- - - 801).

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Revision A, Sept 01/2011
B. Procedure
For Aircraft 7003 - - -7310
Refer to Figure 5 (Sheet 1 of 7).
(1) Near FS621.00 and STGR10R, remove the rivets from the channel and the clip
(2).
(2) Make a line on the clip (2) with a marker at 0.80 in. (20.3 mm) from the mating
surface of the clip (2) and the channel.
(3) Cut the clip (2) at the marked location.
(4) Remove the sharp edges.
(5) Apply chemical conversion coating on the bare metal areas.
(6) Install a rivet (1) in the two holes in the channel.
(7) Apply fluid-resistant primer on the clip (2) and the rivets (1).
(8) Apply polyurethane topcoat on the clip (2) and the rivets (1).
( 9 ) W i t hap e r m a n e n ti n kp e no re q u i v a l e n t ,i d e n t i f yt h ec l i p( 2 )a ss h o w ni nt h e
table below.
Original Part Number After S.B. 601R -- 25 -- 187
Incorporation
601R45103- - -19
or
601R45103- - -29
K601R45034- - -2025
or
K601R45034- - -2027

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Revision A, Sept 01/2011
For all aircraft
Refer to Figure 5 (Sheet 2 of 7)
(10) Near FS 621.00, at STGR6R and STGR7R, cut the clips (3) and (5) as follows:
(a) Near FS621.00 and STGR6R, remove the rivets from the channel and the
clip (3).
(b) Near FS621.00 and STGR7R, remove the rivets from the channel and the
clip (5).
(c) Make a line on the clip (3) with a marker at 1.00 in. (25.4 mm) from the
mating surface of the clip (3) and the channel.
(d) Make a line on the clip (5) with a marker at 1.00 in. (25.4 mm) from the
mating surface of the clip (5) and the channel.
(e) Cut the clips (3) and (5) at the marked locations.
(f) Remove the sharp edges.
(g) Apply chemical conversion coating on the bare metal areas.
(h) Install the rivets (1) in the holes in the two channels.
(i) Apply fluid-resistant primer on the bare metal areas and the rivets (1).
(j) Apply polyurethane topcoat on the bare metal areas and the rivets (1).
(k) With a permanent ink pen or equivalent, identify the clip (3) as
K601R45034- - - 2021.
(l) With a permanent ink pen or equivalent, identify the clip (5) as
K601R45034- - - 2023.

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Revision A, Sept 01/2011
Refer to Figure 5 (Sheet 3 of 7).
(11) Between FS559.00+80- - - FS559+96 and STGR3R, cut the channel (6) as
follows:
(a) Make a line on the channel (6) with a marker at 8.45 in. (214.6 mm) from
the forward end of the channel (6) (Refer to View H).
(b) Cut the channel (6) at the marked location.
(c) Remove the sharp edges.
(d) Apply chemical conversion coating on the bare metal areas.
(e) Apply fluid-resistant primer on the bare metal areas.
(f) Apply polyurethane topcoat on the bare metal areas.
(g) With a permanent ink pen or equivalent, identify the channel (6) as
K601R45034- - - 2007.
(12) Near FS 621.00, at STGR3R, cut the clip (4), as follows:
(a) Remove the two rivets from the channel and the clip (4).
(b) Make a line on the clip (4), with a marker, at 1.00 in. (25.4 mm) from the
mating surface of the clip (4) and the channel (Refer to Views F and G).
(c) Cut the clip (4) at the marked location.
(d) Remove the sharp edges.
(e) Apply chemical conversion coating on the bare metal areas.
(f) With a permanent ink pen or equivalent, identify the clip (4) as
K601R45034- - - 2019.
(g) Near FS621.00 at STGR3R, install the rivets (1) in the holes in the
channel.
(h) Apply fluid-resistant primer on the bare metal areas and the rivets (1).
(i) Apply polyurethane topcoat on the bare metal areas and the rivets (1).

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Revision A, Sept 01/2011
For Aircraft 7003 - - -7293
Refer to Figure 5 (Sheet 4 of 7).
(13) At FS605.00, FS589.00, and FS574.00, and STGR0, remove and discard the
rivets and the channel (15) from the three clips (Refer to View K).
For all aircraft
(14) At FS621.00 and STGR0, remove and discard the clip (17) from the structure
(Refer to View L).
(15) Near FS621.00 and STGR0, install the rivets (16) in the holes in the structure
(Refer to View L).
(16) Apply fluid-resistant primer on the aluminum bare metal areas and the rivets
(16).
(17) Apply polyurethane topcoat on the aluminum bare metal areas and the rivets
(16).
For Aircraft 7003 - - -7293
Refer to Figure 5 (Sheet 5 of 7).
(18) Between FS559.0+96 and FS574.00, at STGR0, remove the channel (7) from
the clips (13) and (14) (Refer to View L).
(19) At FS 559.0+112 and STGR0.0 remove and discard the clip (14) from the
frame (Refer to View L).
(20) At FS 559.0+96 and STGR0.0 remove and discard the clip (13) from the
frame.
(21) At FS559.00+112 and FS559.00+96, install the rivets (8) in the holes in the
frames (Refer to View N).
(22) Make a line on the channel (7) with a marker at 22.33 in. (567.2 mm) from the
aft end of the channel (7) (Refer to View P).
(23) Cut the channel (7) at the marked location.
(24) Remove the sharp edges.
(25) Apply chemical conversion coating to the aluminum bare metal areas.

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Revision A, Sept 01/2011
(26) Install the nutplate (10) on the channel (7) as follows:
(a) At 4.00 in. (101.6 mm) from the nutplate and 0.60 in. (15.2 mm) from the
upper flange of the channel (7), drill one hole to a diameter of 0.256 to
0.261 in. (6.50 to 6.63 mm) in the channel (7).
(b) T emporarily install the nutplate (10) on the channel (7) at the location of
the new hole.
(c) Backdrill two holes to a diameter of 0.097 to 0.100 in. (2.46 to 2.54 mm)
from the nutplate (10) through the channel (7).
(d) Do a countersink in the two holes on the channel (7) for the installation
of the rivets (9).
(e) Apply chemical conversion coating to the aluminum bare metal areas.
(f) Install the nutplate (10) with the rivets (9) on the channel (7).
(27) Install rivets (1) in the two holes in the channel (7).
(28) Apply fluid-resistant primer on the aluminum bare metal areas and the new
rivets (1) and (9).
(29) Apply polyurethane topcoat on the aluminum bare metal areas and the new
rivets (1) and (9).
(30) With a permanent ink pen or equivalent, identify the channel (7) as
K601R45034- - -2029.
For Aircraft 7003 thru 7209
Refer to Figure 5 (Sheet 6 of 7)
(31) At FS559.0+96 and FS559.0+112, STGR2L, remove the clips and the channel
assembly (11) from the frames. Keep the channel assembly and the clips (11)
for a subsequent step (Refer to View R).
NOTE: The two clips (11) must remain installed on the channel assembly.
(32) At FS559.00+112 and FS559.00+96, install the rivets (8) in the holes in the
frames (Refer to View T).
(33) Apply fluid-resistant primer on the rivets (8).
(34) Apply polyurethane topcoat on the rivets (8).

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Revision A, Sept 01/2011
For Aircraft 7210 - - -7857
Refer to Figure 5 (Sheet 7 of 7).
(35) At FS559+96 and STGR12L, cut the channel (12) as follows:
(a) Make a line on the channel (12) with a marker at 5.48 in. (139.2 mm)
from the forward end of the channel (12) (Refer to View V).
(b) Cut the channel (12) at the marked location.
(c) Remove the sharp edges.
(d) Apply chemical conversion coating to the aluminum bare metal areas.
(e) Apply fluid-resistant primer on the aluminum bare metal areas.
(f) With a permanent ink pen or equivalent, identify the channel (12) as
s h o w ni nt h et a b l eb e l o w .
Original Part Number After S.B. 601R -- 25 -- 187
Incorporation
601R45552- - -15
or
601R45552- - -59
or
601R45552- - -125
K601R45034- - -2001
or
K601R45034- - -2003
or
K601R45034- - -2005
For Aircraft 7003 - - -7293
Refer to Figure 6 (Sheet 2 of 5)
(36) Between FS559.00+96 and FS574.00, at STGR0.00, install the clips (1) and
(2) and the channel (4) as follows:
(a) T emporarily install the clip (1) on the intercostal at 4.41 in. (112.0 mm) aft
of the aft face of the frame at FS559.0+112 and at 0.58 in. (14.7 mm)
from the lower flange of the intercostal (Refer to View G).
(b) T emporarily install the clip (2) on the intercostal at 8.37 in. (212.6 mm)
forward of the aft face of the frame at FS559.0+112 and at 0.58 in. (14.7
mm) from the lower flange of the intercostal (Refer to View G).

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Revision A, Sept 01/2011
(c) Backdrill four holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)
from the clips (1) and (2) through the intercostal.
(d) T emporarily install the channel (4) on the clips (1) and (2) at 2.84 in.
(72.1 mm) from the aft edge of the clip (2) (Refer to Views E and F).
(e) Make sure that the channel (4) is in the middle of the clips (1) and (2).
(f) Backdrill four holes to a diameter of 0.128 to 0.132 in. (3.25 to 3.35 mm)
from the clips (1) and (2) through the channel (4).
(g) Do a countersink in the holes on the channel (4) for the installation of the
rivets (5).
(h) Remove the burrs and sharp edges.
(i) Apply chemical conversion coating to the aluminum bare metal areas.
(j) Install the clips (1) and (2) on the intercostal with the rivets (3).
(k) Install the clips (1) and (2) on the channel (4) with the rivets (5).
(l) Apply fluid-resistant primer on the new rivets (3) and (5).
(m) Apply polyurethane topcoat on the new rivets (3) and (5).
For all aircraft
Refer to Figure 6 (Sheet 3 of 5).
(37) Near FS621.00, install the nutplate (11) on the channel (10) as follows:
(a) Drill a hole to a diameter of 0.256 to 0.261 in. (6.50 to 6.63 mm) in the
channel (10) at 5.90 in. (149.9 mm) from the fastener hole of the nutplate
installed on the channel (10) and at 0.60 in. (15.2 mm) from the flange of
the channel (10) (Refer to View H).
(b) T emporarily install the nutplate (11) on the channel (10) at the location of
the new hole.
(c) Backdrill two holes to a diameter of 0.097 to 0.100 in. (2.46 to 2.54 mm)
from the nutplate (11) through the channel (10).
(d) Do a countersink in the two holes on the channel (10) for the installation
of the rivets (12).
(e) Remove the burrs and sharp edges.
(f) Apply chemical conversion coating to the aluminum bare metal areas.
(g) Install the nutplate (11) with the rivets (12) on the channel (10).

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Revision A, Sept 01/2011
For Aircraft 7003 thru 7209
Refer to Figure 6 (Sheet 1 of 5).
(38) At FS 559.0+96 and 559.0+112, install the clips (14) and (15) and the angle
assembly (13) on the frames as follows:
NOTE: Clips (14) and (15) are already installed on the angle assembly (13).
(a) At FS559.0+112, temporarily install the clip (14) on the frame at 0.72 in.
(18.3 mm) from the cutout for STGR3L and 0.85 in. (21.6 mm) from the
flange of the frame (Refer to View B- - -B).
(b) At FS559.0+96, temporarily install the clip (15) on the frame at 1.08 in.
(27.7 mm) from the cutout for STGR3L and 0.84 in. (21.3 mm) from the
flange of the frame (Refer to view C- - -C).
(c) Backdrill four holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)
from the clips (14) and (15) through the frames.
(d) Remove the burrs and sharp edges.
(e) Apply chemical conversion coating to the aluminum bare metal areas.
(f) Install the clips (14) and (15) on the frames with the rivets (3).
For Aircraft 7003 - - -7293
Refer to Figure 6 (Sheets 4 and 5).
(39) Between FS621.00 and FS574.00, at STGR0.0, install the new channel (6) on
t h et h r e ec l i p sa sf o l l o w s :
(a) T emporarily install the channel (6) on the three clips at 9.98 in. (253.5
mm) from the nutplate installed on the channel (4) (Refer to view K).
(b) Backdrill six holes to a diameter of 0.128 to 0.132 in. (3.25 to 3.35 mm)
from the three clips through the channel (6).
(c) Do a countersink in the six holes on the channel (6) for the installation of
the rivets (5).
(d) Remove the burrs and sharp edges.
(e) Apply chemical conversion coating to the aluminum bare metal areas.
(f) Install the channel (6) on the three clips with the rivets (5).

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Revision A, Sept 01/2011
Refer to Figure 6.
(40) Apply fluid-resistant primer on the new rivets (3), (5), and (12).
(41) Apply polyurethane topcoat on the new rivets (3), (5), and (12).
For all aircraft
Refer to Figure 7 (Sheet 1 of 4).
(42) At FS589.00 and FS605.00, STGR9L, remove and discard the clips (2) and (1)
from the frames.
(43) At FS589.00 and FS605.00, STGR7L, remove and discard two rivets (1) from
each frame.
Refer to Figure 7 (Sheet 2 of 4).
(44) At FS605.0, install the clips (5), (4), and (3) on the frame as follows
(Refer to view E):
(a) T emporarily install the clip (5) at the location of the two holes on the
frame at STGR9L.
(b) T emporarily install the clip (3) at the location of the two holes on the
frame at STGR7L.
(c) T emporarily install the clip (4) at 1.02 in. (25.9 mm) from the doubler and
at 0.90 in. (22.9 mm) from the flange of the frame.
(d) T emporarily install the clip (3) at 0.28 in. (7.1 mm) from the doubler and
at 0.90 in. (22.9 mm) from the edge of the frame.
(e) Backdrill two holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)
from the frame through the clips (3) at STGR7L and clip (5) at STGR9L
through the frame.
(f) Backdrill two holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)
from the clip (3) at STGR5L and the clip (4) through the frame.
(g) Remove the burrs and sharp edges.
(h) Apply chemical conversion coating on the bare metal areas.

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Revision A, Sept 01/2011
(i) At STGR7L, install the clip (3) on the frame with the rivets (14)
(Refer to view D).
(j) At STGR9L, install the clip (5) on the frame with the rivets (14)
(Refer to view D).
(k) Install the clips (4) and (3) on the frame with rivets (10).
Refer to Figure 7 (Sheet 3 of 4).
(45) At FS589.00, install the clips (8), (7), and (6) on the frame as follows:
(a) T emporarily install the clip (8) at the location of the two holes on the
frame at STGR9L.
(b) T emporarily install the clip (6) at the location of the two holes on the
frame at STGR7L.
(c) T emporarily install the clip (7) at 1.02 in. (25.9 mm) from the doubler and
at 1.0 in. (25.4 mm) from the flange of the frame.
(d) T emporarily install the clip (6) at 0.44 in. (11.2 mm) from the doubler and
at 0.89 in. (22.6 mm) from the flange of the frame.
(e) Backdrill two holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)
from the frame through the clips (6) at STGR7L and clip (8) at STGR9L.
(f) Backdrill two holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)
from the clips (6) at STGR5L and clip (7) through the frame.
(g) Remove the burrs and sharp edges.
(h) Apply chemical conversion coating on the bare metal areas.
(i) At STGR7L, install the clip (6) on the frame with the rivets (14)
(Refer to view F).
(j) Install the clips (8), (7), and (6) on the frame with the rivets (10).

### Page 33

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Revision A, Sept 01/2011
Refer to Figure 7 (Sheet 4 of 4).
(46) At FS589.00 and FS605.00, install the channel (12) on the clips (8) and (5) as
follows:
(a) Put the channel (12) in position on the clips (8) and (5) at 2.78 in. (70.6
mm) from the aft face of the frame at FS605.00.
(b) Make sure that the channel (12) is in the middle of the clips (8) and (5).
(c) Backdrill two holes to a diameter of 0.128 to 0.132 in. (3.25 to 3.35 mm)
from the clips (8) and (5) through the channel (12).
(d) Do a countersink in the four holes on the channel (12) for the installation
of the rivets (13).
(e) Remove the burrs and sharp edges.
(f) Apply chemical conversion coating to the aluminum bare metal areas.
(g) Install the channel (12) on the clips (8) and (5) with the rivets (13).
(47) At FS589.00 and FS605.00, install the channel (11) on the clips (7) and (4) as
follows:
(a) Install the channel (11) in position on the clips (7) and (4) at 1.50 in.
(38.1 mm) from the aft face of the frame at FS605.00.
(b) Make sure that the channel (11) is in the middle of the clips (7) and (4).
(c) Backdrill two holes to a diameter of 0.128 to 0.132 in. (3.25 to 3.35 mm)
from the clips (7) and (4) through the channel (11).
(d) Do a countersink in the four holes in the channel (11) for the installation
of the rivets (13).
(e) Remove the burrs and sharp edges.
(f) Apply chemical conversion coating to the aluminum bare metal areas.
(g) Install the channel (11) on the clips (7) and (4) with the rivets (13).

### Page 34

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Revision A, Sept 01/2011
Refer to Figure 7.
(48) Apply fluid-resistant primer on the new rivets (10), (13), and (14).
(49) Apply polyurethane topcoat on the new rivets (10), (13), and (14).
Refer to Figure 8.
For aircraft that do not have Modification Summary IS601R25520054 incorporated
(50) At FS621.00, wet-install 24 rivets (2) on the bulkhead (Refer to View A).
For aircraft that have Modification Summary IS601R25520054 incorporated
(51) At FS621.00, wet-install 24 screws (3) and washers (4) on the bulkhead (Refer
to View A).
(52) Remove the clickbond (1) from the bulkhead.
For aircraft that have provisions for holes in the bulkhead
Refer to Figure 9.
(53) At FS621.00, install the sealed nutplate (1) on the bulkhead as follows:
(a) At the locations of the holes in the bulkhead, open four holes to a
diameter of 0.195 to 0.201 in. (4.95 to 5.11 mm).
(b) T emporarily install the sealed nutplate (1) on the aft side of the bulkhead
at the locations of the holes (Refer to View B).
(c) Make sure that the sealed nutplates do not interfere with the adjacent
structure or chem-milled pocket on the bulkhead.
(d) Backdrill two holes to a diameter of 0.097 to 0.100 in. (2.46 to 2.54 mm)
from the sealed nutplates (1) through the bulkhead for the installation of
the rivets (2).
(e) Remove the burrs and sharp edges.
(f) Apply chemical conversion coating on the bare metal areas.
(g) Wet-install the sealed nutplates (1) on the bulkhead with wet installed
rivets (2).

### Page 35

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Revision A, Sept 01/2011
(h) T emporarily install the liners (3), (4), and (5) on the bulkhead with the
screws (6).
(i) Make sure that you drill only through the pilot holes in the liners (3), (4),
and (5), which are necessary for their installation on the bulkhead
(Refer to Sheet 2 of 3).
(j) Backdrill one hole to a diameter of 0.195 to 0.201 in. (4.95 to 5.11 mm)
from the liner (3) through the bulkhead.
(k) Make sure that the hole does not interfere with the adjacent structure or
chem-milled pocket in the bulkhead.
(l) Backdrill one hole to a diameter of 0.195 to 0.201 in. (4.95 to 5.11 mm)
from the liner (4) through the bulkhead.
(m) Make sure that the hole does not interfere with the adjacent structure or
chem-milled pocket in the bulkhead.
(n) Backdrill two holes to a diameter of 0.195 to 0.201 in. (4.95 to 5.11 mm)
from the liner (5) through the bulkhead.
(o) Make sure that the holes do not interfere with the adjacent structure or
chem-milled pocket in the bulkhead.
(p) Remove the liners (3), (4), and (5) and the screws (6) from the bulkhead.
(q) T emporarily install the sealed nutplates (1) on the aft side of the
bulkhead at the location of the new drilled holes.
(r) Make sure that the sealed nutplates (1) do not interfere with the adjacent
structure or chem-milled pocket in the bulkhead.
(s) Backdrill two holes to a diameter of 0.097 to 0.100 in. (2.46 to 2.54 mm)
from the sealed nutplates (1) through the bulkhead for the installation of
rivets (2).
(t) Remove the burrs and sharp edges.
(u) Apply chemical conversion coating on the bare metal areas.
(v) Wet-install the sealed nutplates (1) on the bulkhead with wet installed
rivets (2).

### Page 36

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Revision A, Sept 01/2011
For aircraft that do not have provisions for holes in the bulkhead
Refer to Figure 10.
(54) At FS621.00, install the sealed nutplate (4) on the bulkhead as follows:
(a) T emporarily install the liners (1), (2), and (3) on the bulkhead with
double-sided tape or equivalent.
(b) Make sure that you drill only through the pilot holes in the liners (1), (2),
and (3), which are necessary for their installation on the bulkhead.
(c) Backdrill two holes to a diameter of 0.195 to 0.201 in. (4.95 to 5.11 mm)
from the liner (1) through the bulkhead.
(d) Make sure that the holes do not interfere with the adjacent structure or
chem-milled pocket in the bulkhead.
(e) Backdrill two holes to a diameter of 0.195 to 0.201 in. (4.95 to 5.11 mm)
from the liner (2) through the bulkhead.
(f) Make sure that the holes do not interfere with the adjacent structure or
chem-milled pocket in the bulkhead.
(g) Backdrill four holes to a diameter of 0.195 to 0.201 in. (4.95 to 5.11 mm)
from the liner (3) through the bulkhead.
(h) Make sure that the holes do not interfere with the adjacent structure or
chem-milled pocket in the bulkhead.
(i) Remove the liners (1), (2), and (3) from the bulkhead.
(j) T emporarily install the sealed nutplates (4) on the aft side of the
bulkhead at the location of the new drilled holes.
(k) Make sure that the sealed nutplates (4) do not interfere with the adjacent
structure or chem-milled pocket in the bulkhead.
(l) Backdrill two holes to a diameter of 0.097 to 0.100 in. (2.46 to 2.54 mm)
from the sealed nutplates (4) through the bulkhead for the installation of
rivets (5).
(m) Remove the burrs and sharp edges.
(n) Apply chemical conversion coating on the bare metal areas.
(o) Wet-install the sealed nutplates (4) on the bulkhead with wet installed
rivets (5).
For aircraft that have a cargo-compartment load divider
(55) Install the provisions for anchor plates on the 9G bulkhead with the procedure
given in C&D Service Bulletin 4652005- - - 25- - - 01.

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Page 36 of 122
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Revision A, Sept 01/2011
For all aircraft
R e f e rt oF i g u r e1 1( S h e e t1o f3 ) .
(56) Install one insert (6) in the floor panel (1) as follows:
(a) Make a line on the inboard side of the floor panel (1) with a marker at
3.44 in. (87.4 mm) from the aft edge of the floor panel (1).
(b) At the location of the line, make a line with a marker at 0.86 in. (21.8 mm)
from the inboard edge of the floor panel (1).
(c) At the intersection of the two lines, drill one hole to a diameter of 0.561 to
0.566 in. (14.25 to 14.38 mm) in the floor panel (1).
(d) Mill the core of the floor panel (1) to increase the diameter of the potting
cavity to a minimum of three core cells or to a maximum of four core
cells or to 1.5 times the diameter of the holes drilled for the installation of
the inserts (6).
(e) Remove debris and clean the hole and cavity.
(f) If applicable, put the insert (6) in position on the tab and make sure that
the fill/vent holes are aligned.
(g) Slowly push the insert (6) into the hole and make sure that the insert (6)
is flush with the upper and lower surfaces of the panel (1).
(h) Apply pressure-sensitive tape to the opposite surface of the insert (6)
and the floor panel (1).
(i) With a syringe or equivalent, fill the hole and the cavity with adhesive
(CMS 532- - - 02 Typ I).
(j) Clean the area to remove the unwanted adhesive from the insert (6) and
floor panel (1).
NOTE: T h ea d h e s i v em u s tb ec u r e db e f o r ey o uc a nc l e a nt h ei n s e r t( 6 ) .

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Revision A, Sept 01/2011
(57) With a permanent ink pen or equivalent, identify the floor panel (1) as shown
in the table below.
Original Part Number After S.B. 601R -- 25 -- 187
Incorporation
601R31668- - -249
OR
601R31668- - -281
OR
601R31668- - -361
OR
601R31668- - -503
K601R45034- - -2059
OR
K601R45034- - -2069
OR
K601R45034- - -2079
OR
K601R45034- - -2089
R e f e rt oF i g u r e1 1( S h e e t2o f3 ) .
(58) Install two inserts (6) on the upper surface of the floor panel (2) as follows:
(a) Make a line on the inboard and outboard sides of the floor panel (2) with
a marker at 3.44 in. (87.4 mm) from the aft edge of the floor panel (2).
(b) At the locations of the two lines, make a line with a marker at 0.85 in.
(21.6 mm) from the inboard and outboard edges of the floor panel (2).
(c) At the marked locations, drill two holes to a diameter of 0.561 to 0.566
in. (14.25 to 14.38 mm) in the floor panel (2).
(d) Mill the core of the floor panel (2) to increase the diameter of the potting
cavity to a minimum of three core cells or to a maximum of four core
cells or to 1.5 times the diameter of the holes drilled for the installation of
the inserts (6).
(e) Remove debris and clean the holes and cavities.
(f) If applicable, put the inserts (6) in position on the tabs and make sure
that the fill/vent holes are aligned.
(g) Slowly push the two inserts (6) into the holes and make sure that the
inserts (6) are flush with the upper and lower surfaces of the panel (2).
(h) Apply pressure-sensitive tape to the opposite surface of the two inserts
(6) and the floor panel (2).
(i) With a syringe or equivalent, fill the holes and the cavities with adhesive
(CMS 532- - - 02 Typ I).
(j) Clean the area to remove the unwanted adhesive from the inserts (6)
and floor panel (2) when the adhesive is cured.
NOTE: T h ea d h e s i v em u s tb ec u r e db e f o r ey o uc a nc l e a nt h ei n s e r t( 6 ) .

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Revision A, Sept 01/2011
(59) With a permanent ink pen or equivalent, identify the floor panel (2) as shown
in the table below.
Original Part Number After S.B. 601R -- 25 -- 187
Incorporation
601R31668- - -241
OR
601R31668- - -273
OR
601R31668- - -345
OR
601R31668- - -501
OR
601R31668- - -245
OR
601R31668- - -277
OR
601R31668- - -325
OR
601R31668- - -497
K601R45034- - -2053
OR
K601R45034- - -2063
OR
K601R45034- - -2073
OR
K601R45034- - -2083
OR
K601R45034- - -2051
OR
K601R45034- - -2061
OR
K601R45034- - -2071
OR
K601R45034- - -2081
(60) Install two inserts (6) on the upper surface of the floor panel (3) as follows:
(a) Make a line on the floor panel (3) with a marker at 0.82 in. (20.8 mm)
from the aft edge of the floor panel (3).
(b) At the locations of the two lines, make a line with a marker at 0.85 in.
(21.6 mm) from the inboard and outboard edges of the floor panel (3)
(c) At the marked locations, drill two holes to a diameter of 0.561 to 0.566
in. (14.25 to 14.38 mm) in the floor panel (3).
(d) Mill the core of the floor panel (3) to increase the diameter of the potting
cavity to a minimum of three core cells or to a maximum of four core
cells or to 1.5 times the diameter of the holes drilled for the installation of
the inserts (6).
(e) Remove debris and clean the holes and cavities.
(f) Put the inserts (6) in position on the tabs and make sure that the fill/vent
holes are aligned.

### Page 40

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Page 39 of 122
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Revision A, Sept 01/2011
(g) Slowly push the two inserts (6) with the tab into the holes and make sure
that the inserts (6) are flush with the upper and lower surfaces of the
panel (3).
(h) Apply pressure-sensitive tape to the opposite surface of the two inserts
(6) and the floor panel (3).
(i) With a syringe or equivalent, fill the holes and the cavities with adhesive
(CMS 532- - - 02 Typ I).
(j) Clean the area to remove the unwanted adhesive from the inserts (6)
and floor panel (3).
NOTE: T h ea d h e s i v em u s tb ec u r e db e f o r ey o uc a nc l e a nt h ei n s e r t( 6 ) .
(61) With a permanent ink pen or equivalent, identify the floor panel (3) as shown
in the tables below.
Original Part Number After S.B. 601R -- 25 -- 187
Incorporation
601R31668- - -243
OR
601R31668- - -275
OR
601R31668- - -333
OR
601R31668- - -499
K601R45034- - -2055
OR
K601R45034- - -2065
OR
K601R45034- - -2075
OR
K601R45034- - -2085
R e f e rt oF i g u r e1 1( S h e e t3o f3 ) .
(62) Install two inserts (6) on the upper surface of the floor panel (4) as follows:
(a) Make a line on the floor panel (4) with a marker at 3.44 in. (87.4 mm)
from the aft edge of the floor panel (4).
(b) At the locations of the two lines, make a line with a marker at 0.85 in.
(21.6 mm) from the inboard and outboard edges of the floor panel (4)
(c) At the marked locations, drill two holes to a diameter of 0.561 to 0.566
in. (14.25 to 14.38 mm) in the floor panel (4).

### Page 41

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Revision A, Sept 01/2011
(d) Mill the core of the floor panel (4) to increase the diameter of the potting
cavity to a minimum of three core cells or to a maximum of four core
cells or to 1.5 times the diameter of the holes drilled for the installation of
the inserts (6).
(e) Remove debris and clean the holes and cavities.
(f) Put the inserts (6) in position on the tabs and make sure that the fill/vent
holes are aligned.
(g) Slowly push the two inserts (6) with the tab into the holes and make sure
that the inserts (6) are flush with the upper and lower surfaces of the
panel (4).
(h) Apply pressure-sensitive tape to the opposite surface of the two inserts
(6) and the floor panel (4).
(i) With a syringe or equivalent, fill the holes and the cavities with adhesive
(CMS 532- - - 02 Typ I).
(j) Clean the area to remove the unwanted adhesive from the inserts (6)
and floor panel (4).
NOTE: T h ea d h e s i v em u s tb ec u r e db e f o r ey o uc a nc l e a nt h ei n s e r t( 6 ) .
(63) With a permanent ink pen or equivalent, identify the floor panel (4) as shown
in the table below.
Original Part Number After S.B. 601R -- 25 -- 187
Incorporation
601R31668- - -245
OR
601R31668- - -277
OR
601R31668- - -325
OR
601R31668- - -497
OR
601R31668- - -241
OR
601R31668- - -273
OR
601R31668- - -345
OR
601R31668- - -501
K601R45034- - -2051
OR
K601R45034- - -2061
OR
K601R45034- - -2071
OR
K601R45034- - -2081
OR
K601R45034- - -2053
OR
K601R45034- - -2063
OR
K601R45034- - -2073
OR
K601R45034- - -2083

### Page 42

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Revision A, Sept 01/2011
(64) Install one insert (6) in the floor panel (5) as follows:
(a) Make a line with a marker on the inboard side of the floor panel (5) at
3.44 in. (87.4 mm) from the aft edge of the floor panel (5).
(b) At the location of the line, make a line with a marker at 0.86 in. (21.8 mm)
from the inboard edge of the floor panel (5).
(c) At the intersection of the two lines, drill one hole to a diameter of 0.561 to
0.566 in. (14.25 to 14.38 mm) in the floor panel (5).
(d) Mill the core of the floor panel (5) to increase the diameter of the potting
cavity to a minimum of three core cells or to a maximum of four core
cells or to 1.5 times the diameter of the holes drilled for the installation of
the inserts (6).
(e) Remove debris and clean the hole and cavity.
(f) Put the insert (6) in position on the tab and make sure that the fill/vent
holes are aligned.
(g) Slowly push the insert (6) with the tab into the holes and make sure that
the insert (6) is flush with the upper and lower surfaces of the panel (5).
(h) Apply pressure-sensitive tape to the opposite surface of the insert (6)
and the floor panel (5).
(i) With a syringe or equivalent, fill the hole and the cavity with adhesive
(CMS 532- - - 02 Typ I).
(j) Clean the area to remove the unwanted adhesive from the insert (6) and
floor panel (5).
NOTE: T h ea d h e s i v em u s tb ec u r e db e f o r ey o uc a nc l e a nt h ei n s e r t( 6 ) .

### Page 43

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Revision A, Sept 01/2011
(65) With a permanent ink pen or equivalent, identify the floor panel (5) as shown
in the table below.
Original Part Number After S.B. 601R -- 25 -- 187
Incorporation
601R31668- - -247
OR
601R31668- - -279
OR
601R31668- - -323
OR
601R31668- - -495
OR
601R31668- - -9037
OR
601R31668- - -9063
K601R45034- - -2057
OR
K601R45034- - -2067
OR
K601R45034- - -2077
OR
K601R45034- - -2087
OR
K601R45034- - -2097
OR
K601R45034- - -2107
(66) Install the floor panels that follow (Refer to AMM 53- - - 01- - - 01- - - 400- - - 804):
ACCESS DESIGNATION
281LLF Access Panel
281JLF Access Panel
281DLF Access Panel
282GRF Access Panel
282KRF Access Panel

### Page 44

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Revision A, Sept 01/2011
Refer to Figure 4.
NOTE: For the steps that follow, it is not necessary to install the liner assemblies,
the angle assemblies, and the tie-rod cover assemblies with all their
mounting hardware.
(67) Install the angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42) on
the liner assemblies (16), (17), (18), (21), (22), and (23) on the 9G bulkhead
with the screws (12), (33), (34) and (43), and the washers (14).
(68) Install the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)
with the screws (12), (33), and (34) and the washers (14) on the liner
assemblies (16), (17), (18), (21), (22), and (23).
(69) If the new liners touch the 9G bulkhead, the new angles, and/or tie-rod
covers, locally remove some material from the liners to get a clearance
between the liners and the 9G bulkhead, the new angles, and/or tie-rod
covers.
Refer to Figure 13.
(70) If the holes on the liners do not align with the holes on the channels, adjust
the location of the 9G bulkhead as follows:
(a) Find the applicable tie rod(s) (1) that must be disconnected to adjust the
9G bulkhead.
(b) Remove the bolt (2), the washers (3), and the nut (4) from the applicable
tie rod(s) (1).
(c) Disconnect the applicable tie rod(s) (1) from the 9G bulkhead.
(d) Move the 9G bulkhead to get a correct alignment of the holes on the
liners with the holes on the channels.
(e) Loosen the jam nut (5) of the tie rod(s) (1) and adjust the length of the
tie rod(s) (1) to get a correct alignment of the tie rod(s) (1) with the hole
in the fitting(s).
(f) Adjust the length of the tie rod(s) (1) until the bolt (2) will go through the
hole in the tie rod(s) (1) and the fitting(s).
(g) Install the bolt (2), the washers (3), and the nut (4).
(h) Make sure that washers (3) are installed below the head of the bolt (2)
and the nut (4).
(i) Tighten the jam nut on the tie rod(s) (1) and safety with lockwire.
(j) Tighten the nut(s) (4).

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For Aircraft 7003 - - -7389 that do not have liner assemblies installed on the 9G bulkhead
(Reference REO 601R - - -25 - - -53 - - -003)
(71) Do steps 3.A (1), (2), (3), and (4) of C&D Zodiac Service Bulletin
B301002- - - 25- - - 02.
Refer to Figure 4.
(72) Remove the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)
from the 9G bulkhead.
(73) Remove the liner assemblies (16), (17), (18), (21), (22), and (23) from the 9G
bulkhead.
(74) Remove the angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42)
from the 9G bulkhead.
(75) Do the remaining steps of C&D Zodiac Service Bulletin B301002- - - 25- - - 02 to
install the necessary inserts and the rivnuts on the 9G bulkhead.
For Aircraft 7390 - - -7857
(76) Do steps 3.A (1), (2), (3), and (4) of C&D Zodiac Service Bulletin
B301002- - - 25- - - 01.
Refer to Figure 4.
(77) Remove the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)
from the 9G bulkhead.
(78) Remove the liner assemblies (16), (17), (18), (21), (22), and (23) from the 9G
bulkhead.
(79) Remove the angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42)
from the 9G bulkhead.
(80) Do the remaining steps of C&D Zodiac Service Bulletin B301002- - - 25- - - 01 to
install the necessary inserts and the rivnuts on the 9G bulkhead.

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For Aircraft 7003 - - -7389 that have liner assemblies installed on the 9G bulkhead
(Reference REO 601R - - -25 - - -53 - - -003)
(81) Do steps 3.A (1), (2), (3), and (4) of C&D Zodiac Service Bulletin
B301002- - - 25- - - 02.
(82) From the applicable holes in the angle assemblies (35), (36), (37), (38), (39),
(40), (41), and (42) and tie-rod cover assemblies (20), (24), (25), (26), (27),
(28), and (52), make marks on the liner of the 9G bulkhead to show the
locations of the holes for the installation of the inserts (Refer to C&D Zodiac
Service Bulletin B301002- - - 25- - - 02).
(83) Make a mark to show the pattern of the angle assemblies (35), (36), (37), (38),
(39), (40), (41), and (42) on the liners of 9G bulkhead.
(84) Make a mark to show the pattern of the tie-rod cover assemblies (20), (24),
(25), (26), (27), (28), and (52) on the liners of 9G bulkhead.
(85) Remove the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)
from the liners of the 9G bulkhead.
(86) Remove the angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42)
from the liners of the 9G bulkhead.
(87) Remove the liner assemblies (16), (17), (18), (21), (22), and (23) from the
liners of the 9G bulkhead.
(88) Remove the applicable unwanted rivets, from the 9G bulkhead, that can
interfere with the installation of the liners, angles, and tie-rod covers
( R e f e r t o S R M --- 5 1 --- 4 2 --- 0 6 ) .
(89) Remove the liners on the 9G bulkhead and cut them along the patterns.
(90) Do the remaining steps of C&D Zodiac Service Bulletin B301002- - - 25- - - 02 to
install the necessary inserts and the rivnuts on the 9G bulkhead.
(91) Install the liners on the 9G bulkhead with the applicable washers and rivets
(Refer to REO 601R- - - 25- - - 53- - - 003 and SRM 51- - - 42- - - 06).

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For all aircraft
Refer to Figure 12.
(92) Do the steps that follow to replace the outlet duct (1) in the cargo
compartment:
(a) If applicable, remove the compartment overheat switch (2)
(Refer to AMM 21- - - 55- - - 13- - - 000- - - 801).
(b) If applicable, remove the temperature control switch (3)
(Refer to AMM 21- - - 55- - - 17- - - 000- - - 801).
(c) Replace the outlet duct (1).
(d) Clean the surface of the outlet duct (1) with a lint-free cloth.
(e) Wrap a minimum of three turns of tape (4) around the duct (1).
(f) If applicable, install the compartment overheat switch (2)
(Refer to AMM 21- - - 55- - - 13- - - 400- - - 801).
(g) If applicable, install the temperature control switch (3)
(Refer to AMM 21- - - 55- - - 17- - - 400- - - 801).
Refer to Figures 14 and 18.
(93) Do the steps that follow to install the liner assemblies (1), (2), and (3) and the
FPC foam sheet (6) on the rear pressure bulkhead.
(a) Remove all the remaining sealant from the surfaces adjacent to the lining
panels.
(b) Clean the surfaces with an approved solvent cleaner
( R e f e r t o S R M 5 1 --- 2 6 --- 0 0 ) .
(c) Bond the liner assemblies (1), (2), and (3) on the rear pressure bulkhead
at their installation positions with RTV 106 adhesive-sealant
(Refer to AMM 51- - - 22- - - 28- - - 340- - - 801).
(d) Apply TAFB101- - - 006S firewall-sealant in the holes in the liner assemblies
(1), (2), and (3) that do not have an installed fastener (Refer to AMM
51- - - 23- - - 00- - - 390- - - 807).
(e) Apply TAFB101- - - 006S firewall-sealant on the upper faying surface of
liner assembly (3) (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
.
(f) If necessary, drill through the liner assembly (2) to prevent contact with
installed fasteners.
(g) Fill voids and gaps on the fasteners and between the fasteners and the
liner assembly (2) with TAFB101- - - 006S firewall-sealant.

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Revision A, Sept 01/2011
For all aircraft
(h) Install the washers (5) and the screws (4) on the liner assemblies (1), (2),
and (3).
(i) Apply a fillet seal of TAFB101- - - 006S firewall-sealant around the liner
assemblies (1), (2), and (3) (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(j) Put the FPC foam sheet (6) on the rear pressure bulkhead at its
installation position around the beam and the door track.
(k) If necessary, cut the FPC foam sheet (6) to make it fit correctly.
(l) Apply a fillet seal of TAFB101- - - 006S firewall-sealant around the FPC
foam sheet (6) (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(m) Fill all gaps and holes with TAFB101- - - 006S firewall-sealant
(Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(94) Make sure that the decompression blow-out membrane on the 9G bulkhead
is not damaged.
(95) Make sure that the decompression blow-out membrane behind the last floor
panel at FS621.00 is not damaged.
Refer to Figure 4.
(96) Do the steps that follow to install the liner assemblies (6), (7), and (8) on the
rear pressure bulkhead:
NOTE: If necessary, it is permitted to increase the diameter of the fastener holes
in the liner assemblies (6), (7), and (8) to make them align correctly.
(a) Install the channel assemblies, removed before, on the liner assembly
(6).
(b) Install the liner assembly (6) with the washers (14) and screws (10).
(c) If necessary, increase the diameter of the fastener holes, in the liner
assembly (6), to get a minimum clearance of 0.1 in. (2.5 mm) between
the liner assembly (6) and electrical connectors J258 and J260 on the
pressure bulkhead. Use washers P/N B0202013S1332- - - 63 instead of
the washers (14).

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(d) Install the channel assemblies, removed before, on the liner assembly
(8).
(e) Install the liner assembly (8) with the washers (14) and screws (10).
(f) Install the channel assemblies, removed before, on the liner assembly
(7).
(g) Install the liner assembly (7) with the washers (14) and screws (11).
(h) Apply TAFB101- - - 006S firewall-sealant around the fastener holes in the
liner assemblies (6), (7), and (8) that have been made larger , if the
washer (14) does not fully cover the fastener holes (Refer to AMM
51- - - 23- - - 00- - - 390- - - 807).
(i) Apply a fillet seal of RTV 106 sealant around the liner assemblies (6), (7),
and (8) (Refer to AMM 51- - - 22- - - 28- - - 340- - - 801).
(97) Do the steps that follow to install the floor angles (3) and (4):
(a) At eight places, install the washers (14) and the bolts (5) that hold the
forward flange of the floor angles (4) and (3) to the compartment floor.
(b) At 10 places, install the washers (15) and the bolts (13) that hold the aft
flange of the floor angles (4) and (3) to the compartment floor.
(c) Install the washers (14) and the screws (11) that hold the floor angle (4)
to the bulkhead panel (6).
(d) Install the washers (14) and the screws (11) and (12) that hold the floor
angle (3) to the bulkhead panels (6), (7) and (8).
(e) Apply a fillet seal of RTV 106 sealant around the floor angles (3) and (4)
(Refer to AMM 51- - - 22- - - 28- - - 340- - - 801).
(98) Install the duct skirt (2) to the compartment floor with the washers (15) and the
bolts (13).
(99) Install the angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42) on
the 9G bulkhead as follows:
(a) Install the angle assemblies (35), (36), (37), (38), (39), (40), (41), and
(42) on the 9G bulkhead with the screws (33) and the washers (14).
(b) Apply a fillet seal of RTV 106 sealant around the inboard edge of the
angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42)
(Refer to AMM 51- - - 22- - - 28- - - 340- - - 801).

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Revision A, Sept 01/2011
(100) Do the steps that follow to install the liner assemblies (16), (17), (18), (21),
(22), and (23) and the strip assembly (19):
(a) Remove all the remaining sealant from the surfaces adjacent to the lining
panels.
(b) Clean the surfaces with an approved solvent cleaner
( R e f e r t o S R M 5 1 --- 2 6 --- 0 0 ) .
NOTE: If necessary, it is permitted to increase the diameter of the fastener holes
in the liner assemblies (16), (17), (18), (21), (22), and (23) and the strip
assembly (19) to make them align correctly.
(c) Put the liner assembly (23) at its installation position.
(d) Install the liner assembly (23) on the aircraft structure with the washers
(14) and the screws (33), (34), and (12).
(e) Put the liner assembly (22) at its installation position.
(f) Install the liner assembly (22) on the liner assembly (23) with the
washers (14) and the screws (34) and (12).
(g) Install the liner assembly (22) on the aircraft structure with the washers
(14) and the screws (33) and (12).
(h) Put the liner assembly (21) at its installation position.
(i) Install the liner assembly (21) on the liner assembly (22) with the
washers (14) and the screws (34).
(j) Install the liner assembly (21) on the aircraft structure with the washers
(14) and the screws (33) and (12).
(k) Install the liner assembly (21) on the floor panel with the washers (14)
and the bolts (32).
(l) Install the inlet duct screen assembly on the liner assembly (21) the
washers (14) and the screws (33) (Refer to View K).

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Revision A, Sept 01/2011
(m) T orque the bolts (32) to 20- - - 25 lbfSin. (2.26- - - 2.82 N.m).
For aircraft that have the cargo-compartment load divider
(n) Install the anchor plates (30) on the liner assembly (23) with the screws
(29) (Refer to View J).
(o) Apply a fillet seal of TAFB101- - - 006S firewall-sealant around the anchor
plates (30) as shown on View AC (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
For all aircraft
(p) Put the strip assembly (19) at its installation position.
NOTE: Strip assembly (19) P/N B303011- - - 101 is for aircraft that have
piccolo tube P/N 601R99011- - - 13.
Strip assembly (19) P/N B303011- - - 103 is for aircraft that have
piccolo tube 601R99011- - - 1 or - - - 9.
(q) Put the liner assembly (17) at its installation position.
(r) Install the liner assembly (17) on the aircraft structure with the washers
(14) and the screws (33).
Refer to Figure 12.
(s) Install the liner assembly and the top strip assembly to the outlet duct (1)
with the washers (5) and the screws (6).
Refer to Figure 4.
(t) Install the strip assembly (19) with the washers (14) and the screws (12).
(u) Put the liner assembly (16) at its installation position.
(v) Install the liner assembly (16) on the liner assembly (17) with the
washers (14) and the screws (12) and (43).
(w) Install the liner assembly (16) on the aircraft structure with the washers
(14) and the screws (12) and (33).
(x) Put the liner assembly (18) at its installation position.
(y) Install the liner assembly (18) on the liner assembly (16) with the
washers (14) and the screws (12) and (43).
(z) Install the liner assembly (18) on the aircraft structure with the washers
(14) the screws (12), (33), and (34) and the clip nuts (44).

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(aa) Install the liner assembly (18) on the floor panel with the washers (14)
and the bolts (32).
(ab) T orque the bolts (32) to 20- - - 25 lbfSin. (2.26- - - 2.82 N.m).
(ac) Apply a fillet seal of TAFB101- - -006S firewall-sealant between the liner
assembly (18) and the liner assembly on the pressure bulkhead at the
location shown on View E (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(ad) Apply a fillet seal of RTV 106 sealant around the liner assemblies ( (16),
(17), (18), (21), (22), and (23) and the strip assembly (19)
(Refer to AMM 51- - - 22- - - 28- - - 340- - - 801).
(ae) Apply TAFB101- - - 006S firewall-sealant around the fastener holes in the
liner assemblies 16), (17), (18), (21), (22), and (23) and the strip
assembly (19) that have been made larger, if the washer (14) does not
fully cover the fastener holes (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(101) Do the steps that follow to install the duct (1):
NOTE: If necessary, it is permitted to increase the diameter of the fastener holes
in the duct (1) to make them align correctly.
(a) Put the duct (1) in its installation position.
(b) Install the duct (1) on the bulkhead liner assembly with the washers (14),
the screws (12) and (11).
(c) Install the duct (1) on the strip assembly (19), the liner assembly (17)
and the liner assembly (23) with the washers (14) the screws (33) and
(34) (Refer to View D).
(d) Apply TAFB101- - - 006S firewall-sealant around the fastener holes in the
duct (1) that have been made larger, if the washer (14) does not fully
cover the fastener holes (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(102) Do the steps that follow to install the tie-rod cover assemblies (20), (24), (25),
(26), (27), (28), and (52):
NOTE: If necessary, it is permitted to increase the diameter of the fastener holes
in the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)
to make them align correctly.
(a) Put the tie rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)
at their installation positions.

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(b) Install the tie rod cover assemblies (20), (24), (25), (26), (27), (28), and
(52) with the washers (14) and the screws (12), (33), and (34).
(c) Apply a fillet seal of TAFB101- - - 006S firewall-sealant around tie rod cover
assemblies (20), (24), (25), (26), (27), (28), and (52) at the locations
shown on View AA (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(d) Apply a fillet seal of RTV 106 sealant around tie rod cover assemblies
(20), (24), (25), (26), (27), (28), and (52) at the locations shown on View
AA (Refer to AMM 51- - - 22- - - 28- - - 340- - - 801).
(e) Apply TAFB101- - - 006S firewall-sealant around the fastener holes in the
tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52) that
have been made larger, if the washer (14) does not fully cover the
fastener holes (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
Refer to Figures 4 and 18.
(103) Do the steps that follow to install the door shroud (49) and liner assemblies
(50) and (51):
NOTE: If necessary, it is permitted to increase the diameter of the fastener holes
in the door shroud (49) and liner assemblies (50) and (51) to make them
align correctly.
(a) Put the liner assemblies (50) and (51) at their installation positions.
(b) Install the liner assemblies (50) and (51) on the structure with the
washers (53) and screws (56).
(c) Apply a fillet seal of RTV 106 sealant between the liner assemblies (50)
and (51) (Refer to AMM 51- - - 22- - - 28- - - 340- - - 801).
(d) Apply a fillet seal of TAFB101- - - 006S firewall-sealant around the bottom
edge of the liner assemblies (50) and (51) (Refer to AMM
51- - - 23- - - 00- - - 390- - - 807).
(e) Fillet seal gaps and voids around the door track structure with
TAFB101- - - 006S firewall-sealant (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
(f) Fillet seal gaps and voids with TAFB101- - - 006S firewall-sealant around
the mounting plates of the two spring drums (Refer to AMM
51- - - 23- - - 00- - - 390- - - 807).
(g) Put the door shroud (49) at its installation position.

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(h) Install the door shroud (49) on the structure with the washers (14) and
the screws (12), (33), (34), (43), (54), and the nut (55).
(i) Apply TAFB101- - - 006S firewall-sealant around the fastener holes in the
door shroud (49) and liner assemblies (50) and (51) that have been
made larger, if the washers (14) and (43) do not fully cover the fastener
holes (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
For aircraft that have the cargo-compartment load divider
(104) Install the end fittings and the cargo restraint netting in the cargo
compartment (Refer to AMM 25- - - 51- - - 01- - - 400- - - 801).
(105) Install the cargo restraint posts in the cargo compartment
(Refer to AMM 25- - - 51- - - 01- - - 400- - - 802).
For all aircraft
(106) Install the cargo smoke detectors (Refer to AMM 26- - - 15- - - 01- - - 400- - - 801).
Refer to Figure 17.
(107) Install the cargo firex discharge-line with the procedure given in AMM
26- - - 25- - - 07- - - 400- - - 801 and the steps that follow:
(a) At FS614.50, FS603.30, FS595.75, and FS586.29, install the washer (1)
and replace the spacer (3) between the ceiling liner and the firex cover.
(b) At FS611.50 and FS587.79, install the washer (1) and the spacer (2)
between the ceiling liner and the clamp that attach the piccolo tube to
the structure.
For aircraft that have Piccolo Tube P/N 601R99011 - - -1 or - - -9
(c) At FS567.62, install the washer (1) and replace the spacer (3) between
the ceiling liner and the firex cover.
(d) At FS569.12, install the washer (1) and the spacer (2) between the
ceiling liner and the clamp that attach the piccolo tube to the structure.
(e) At F577.60, install the washer (1) and the spacer (3) between the ceiling
liner and the clamp that attach the piccolo tube to the structure.
For aircraft that have Piccolo Tube P/N 601R99011 - - -13
(f) At F577.60, install the washer (1) and the spacer (2) between the ceiling
liner and the clamp that attach the piccolo tube to the structure.

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Revision A, Sept 01/2011
For all aircraft
Refer to Figure 4, View AB.
(108) Install cargo lights P/N BR7203- - - 804- - - 1 with the kept hardware
(Refer to AMM 33- - - 31- - - 01- - - 400- - - 801).
(109) Apply a fillet seal of TAFB101- - - 006S firewall-sealant around the cargo lights
P/N BR7203- - - 804- - - 1 (Refer to AMM 51- - - 23- - - 00- - - 390- - - 807).
Refer to Figure 4, View F .
.
(110) Install the applicable placard(s) (45) or (46) or (47) or (48) on the liner
assembly (16) (Refer to AMM 11- - - 30- - - 00- - - 400- - - 801).
NOTE: The placard(s) that is installed must be the same as the one(s) that was
i n s t a l l e do nt h er e m o v e dl i n e r .
(111) Make sure that there is a clearance of ¦0.50 in ( ¦12.7 mm) between the
placard (45) or (46) or (47) or (48) and the adjacent fasteners.

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Revision A, Sept 01/2011
Cargo Compartment - - - North American Configuration
Figure 1
A
A
92.00 in.
(2336.80 mm)
FS559.00
+80.50
REF
FS621.00
REF
rsb601r25187_055.dg, gb, 06/07/11
FWD

### Page 57

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Revision A, Sept 01/2011
Liner Assemblies and FPC Foam Sheet - - - Removal
F i g u r e2( S h e e t1o f3 )
2
4
3
1
rsb601r25187_043, sc, 03/2011
1. Liner assembly.
LEGEND
5. Washer.
2. Liner assembly.
3. Liner assembly.
4. SPC foam sheet.
6. Blind rivet.
FS621.00
5
6
5
6
5
6
5
6

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Liner Assemblies and FPC Foam Sheet - - - Removal
F i g u r e2( S h e e t2o f3 )
rsb601r25187_045, sc, 03/2011
1. Liner assembly.
LEGEND
5. Washer.
2. Liner assembly.
3. Liner assembly.
4. SPC foam sheet.
6. Screw.
2
4
3
1
5
6
5
6
5
6
FS621.00
For aircraft that have IS601R25520054 incorporated.
NOTES

### Page 59

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 58 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
Liner Assemblies and FPC Foam Sheet - - - Removal
F i g u r e2( S h e e t3o f3 )
rsb601r25187_044, sc, 03/2011
1. Liner assembly.
LEGEND
2. Liner assembly.
3. Liner assembly.
4. SPC foam sheet.
2
FS621.00
4
3
1
For aircraft that do not have holes
in the pressure bulkhead.
NOTE

### Page 60

SERVICE BULLETIN 601R- - -25- - -187
SB 601R- - - 25- - - 187
Page 59 of 122
Jul 21Jul 21/2011
Revision A, Sept 01/2011
Foam Sheet - - - Removal
F i g u r e3( S h e e t1o f2 )
rsb601r25187_042.cgm, sc, 03/2011
LEGEND
2. Rivet CR3214- -4- -2.
2
(12 PLACES)
1
2
3
FS621.00 FS574.00
3. Washer.
1. Foam sheet.
NOTE
For Aircraft 7003- -7007, 7009- -7026 Post- -SB 601R- -25- -022
and Aircraft 7027- -7857.

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