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. 1SB 601R---25---187 Page 1 of 122 Jul 21 /2011 Revision A, Sept 01/2011 

# SERVICE BULLETIN

Technical 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) AircraftAffected: 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 equivalent action changes to make sure this bulletin can be completed.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 2 of 122 Jul 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 Tolerance 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 3 of 122 Jul 21 /2011 Revision A, Sept 01/2011 F. Manpower 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 MAN ---HOURS (1) Job Set ---Up 20.00 (2) Procedure 60.00 (3) Test 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 4 of 122 Jul 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

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 5 of 122 Jul 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 --- Temperature 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 --- Temperature 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

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 6 of 122 Jul 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 Team 123 Garratt Blvd, N42---24 Toronto, Ontario Canada M3K 1Y5 Fax: 416---375---3060 Phone: 416---375---3920 Email: sbkits@aero.bombardier.com Please contact the Service Bulletin Kit Support Team 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). To 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. Tooling --- 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 7 of 122 Jul 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)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 8 of 122 Jul 21 /2011 Revision A, Sept 01/2011 M. Relationship Chart

PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER NAME

601R31668---241 Floor panel assembly K601R45034---2053 Floor panel assembly 601R31668---243 Floor panel assembly K601R45034---2055 Floor panel assembly 601R31668---245 Floor panel assembly K601R45034---2051 Floor panel assembly 601R31668---247 Floor panel assembly K601R45034---2057 Floor panel assembly 601R31668---249 Floor panel assembly K601R45034---2059 Floor panel assembly 601R31668---273 Floor panel assembly K601R45034---2063 Floor panel assembly 601R31668---275 Floor panel assembly K601R45034---2065 Floor panel assembly 601R31668---277 Floor panel assembly K601R45034---2061 Floor panel assembly 601R31668---279 Floor panel assembly K601R45034---2067 Floor panel assembly 601R31668---281 Floor panel assembly K601R45034---2069 Floor panel assembly 601R31668---323 Floor panel assembly K601R45034---2077 Floor panel assembly 601R31668---325 Floor panel assembly K601R45034---2071 Floor panel assembly 601R31668---333 Floor panel assembly K601R45034---2075 Floor panel assembly 601R31668---345 Floor panel assembly K601R45034---2073 Floor panel assembly 601R31668---361 Floor panel assembly K601R45034---2079 Floor panel assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 9 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER NAME

601R31668---495 Floor panel assembly K601R45034---2087 Floor panel assembly 601R31668---497 Floor panel assembly K601R45034---2081 Floor panel assembly 601R31668---499 Floor panel assembly K601R45034---2085 Floor panel assembly 601R31668---501 Floor panel assembly K601R45034---2083 Floor panel assembly 601R31668---503 Floor panel assembly K601R45034---2089 Floor panel assembly 601R31668---9037 Floor panel assembly K601R45034---2097 Floor panel assembly 601R31668---9063 Floor panel assembly K601R45034---2107 Floor panel assembly 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 Channel assembly K601R45034---2007 Channel assembly 601R45552---15 Channel assembly K601R45034---2001 Channel assembly 601R45552---19 or ---67

or 601R45551---951 Channel assembly 601R45552---71 Channel assembly 601R45552---23 or ---951 or 955 Channel assembly K601R45034---2029 Channel assembly 601R45552---59 Channel assembly K601R45034---2003 Channel assembly 601R45552---125 Channel assembly K601R45034---2005 Channel assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 10 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER NAME

601R45105---15 Channel assembly K601R45034---2009 Channel assembly 601R45105---21 Channel assembly K601R45034---2013 Channel assembly 601R45102---117 Channel assembly K601R45034---2011 Channel assembly 601R45102---131 Channel assembly K601R45034---2015 Channel assembly 601R45102---963 Channel assembly K601R45034---2017 Channel assembly 601R96385---19 or ---27 or ---35 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 ---2501 Liner assembly B302102---101 Liner assembly 601R455532---5 or ---17 or ---25 or ---35 or

601R45561---1 Liner assembly B303102---101 Liner assembly
601R455532---1 or ---7 or

---11 or ---13 or ---15 or ---21 or ---2501 or

601R45560---1 Liner assembly B303101---101 or ---103 Liner 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 cap assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 11 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER NAME
601R45158---3 or ---5 or ---17 or ---19 or 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 cap assembly 601R45554---1 or ---13 or 601R45563---1 or K601R45001---3 Tie rod cap assembly B306101---101 Tie rod cap assembly 601R45554---5 or ---11 or 601R45567---1 or K601R45001---11 Tie rod cap assembly B306106---101 Tie rod cap assembly 601R45152---11 or 601R45400---977 Liner assembly B305103---101 Liner assembly 601R45152---9 or ---19 or ---2501 or 601R45400---955 or ---965 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 or ---973 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 ---17 or IS601R25520054---3 Protection barrier 601R45154---21 FPC Foam sheet

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 12 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER NAME
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

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 13 of 122 Jul 21 /2011 Revision A, Sept 01/2011 2. ACCOMPLISHMENT INSTRUCTIONS
A. Job Set ---Up Reference Information
REFERENCE DESIGNATION AMM 11---30---00---400---801 Installation of the Adhesive-Backed Label AMM 12---00---07---861---801 Connect External AC Power AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners AMM 20---21---00---910---802 Torque Procedures for Plumbing Lines AMM 20---30---00---910---802 Wiggins Couplings --- Maintenance Practices AMM 21---51---00---790---801 Leak Test of the Air Conditioning System AMM 21---51---15---000---801 Removal of the Pack Discharge-Ducts AMM 21---51---15---400---801 Installation of the Pack Discharge-Ducts AMM 21---55---13---000---801 Removal of the Compartment Overheat Switch AMM 21---55---13---400---801 Installation of the Compartment Overheat Switch AMM 21---55---13---710---801 Operational Test of the Compartment Overheat Switch AMM 21---55---17---000---801 Removal of the Temperature Control Switch AMM 21---55---17---400---801 Installation of the Temperature Control Switch AMM 21---55---17---710---801 Operational Test of the Temperature Control Switch AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions AMM 25---51---01---400---801 Installation of the Cargo Restraint Netting AMM 25---51---01---400---802 Installation of the Cargo Restraint Posts AMM 25---52---01---000---801 Removal of the Cargo Compartment Sidewall Linings AMM 25---52---01---000---802 Removal of the Cargo Compartment Rear Bulkhead Linings

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 14 of 122 Jul 21 /2011 Revision A, Sept 01/2011 REFERENCE DESIGNATION AMM 26---15---01---000---801 Removal of the Cargo Smoke Detector AMM 26---15---01---400---801 Installation of the Cargo Smoke Detector AMM 26---15---00---710---801 Operational Test of the Cargo Smoke-Detection System AMM 26---22---00---710---802 Operational Test of the APU Fire-Extinguishing System AMM 26---22---07---000---801 Removal of the APU Fire-Extinguisher Container AMM 26---22---07---400---801 Installation of the APU Fire-Extinguisher Container AMM 26---25---00---710---801 Operational Test of the Cargo Fire-Extinguishing System AMM 26---25---07---000---801 Removal of the Cargo Fire-Extinguisher Discharge-Line AMM 26---25---07---400---801 Installation of the Cargo Fire-Extinguisher Discharge-Line AMM 33---31---01---000---801 Removal of the Service Light Assembly AMM 33---31---01---400---801 Installation of the Service Light Assembly AMM 33---31---00---710---801 Operational Test of the Service Lights AMM 34---44---01---000---801 Removal of the Radio Altimeter Transceiver AMM 34---44---01---400---801 Installation of the Radio Altimeter Transceiver AMM 34---44---01---740---801 Built-In Test of the Radio Altimeter AMM 34---44---04---000---801 Removal of the Radio Altimeter Converter AMM 34---44---04---400---801 Installation of the Radio Altimeter Converter

AMM 49---52---01---000---801 Removal of the APU Cooling Air Intake Duct AMM 49---52---01---400---801 Installation of the APU Cooling Air Intake Duct AMM 49---61---01---000---801 Removal of the APU ECU AMM 49---61---01---400---801 Installation of the APU ECU

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 15 of 122 Jul 21 /2011 Revision A, Sept 01/2011 REFERENCE DESIGNATION AMM 49---61---01---970---801 Write Data into the APU Electronic Control Unit (ECU) AMM 51---22---28---340---801 Cementing of Silicone Rubber AMM 51---23---00---100---801 Preparation of Surfaces for Sealing AMM 51---23---00---390---807 Gap Sealing Procedure AMM 51---23---00---390---815 Curing of Sealant AMM 51---23---00---910---801 Sealant Safety Precautions AMM 52---31---00---000---801 Removal of the Cargo Compartment Door AMM 52---31---00---400---801 Installation of the Cargo Compartment Door AMM 52---31---00---710---801 Operational Test of the Cargo Compartment Door AMM 52---31---00---820---801 Adjustment of the Cargo Compartment Door AMM 52---70---02---710---801 Operational Test of the Cargo-Compartment Door Warning-System AMM 53---01---01---000---804 Removal of the Cargo Compartment Floor Panels AMM 53---01---01---400---804 Installation of the Cargo Compartment Floor Panels SRM 51---21---11 Corrosion Prevention Procedures SRM 51---23---00 Pressure, Environmental, Fuel Tank and Fire-Wall Sealing SRM 51---24---36 Cutting of Sheet Metal SRM 51---26---00 Cleaning SRM 51---40---11 How to Prepare Fastener Holes SRM 51---41---02 Bolts, Screws and Related Items SRM 51---42---06 Solid Rivets SRM 51---42---10 Blind Rivets --- General SRM 51---42---11 Cherry Lock Rivets --- General

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 16 of 122 Jul 21 /2011 Revision A, Sept 01/2011 REFERENCE DESIGNATION SRM 51---42---13 Cherrymax Blind Rivets SRM 51---42---34 Blind Nuts SRM 51---45---00 Nutplate (Anchor Nuts) --- General

Tolerance Information Linear Tolerances Angular Tolerance X.XX in. (0.X mm) X.X in. (X mm) +/ ---0° 30” +/ --- 0.03 in. +/--- 0.1 in. +/ --- 0.8 mm +/ --- 3 mm 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

CBP ---1 F11 10TH ST B/AIR SOV L 221 CBP ---1 G1 CARGO FIREX 2 221 CBP ---1 J1 L AIR COND UNIT 221 CBP ---1 K7 RAD ALT 221 CBP ---1 M2 ENG IGN A 221 CBP ---1 M3 ENG IGN B 221 CBP ---1 M4 ENG START R 221 CBP ---1 M5 ENG START L 221

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 17 of 122 Jul 21 /2011 Revision A, Sept 01/2011 CB PANEL ZONE NAME CB NO. CBP ---1 N12 XFER/APU APU ECU 221 CBP ---1 P1 CARGO FIREX 1 221 CBP ---1 R5 APU FIRE EXT A 221 CBP ---1 R6 APU FIRE EXT B 221 CBP ---2 F11 10TH ST B/AIR SOV R 222 CBP ---2 J1 R AIR COND UNIT 222 CBP ---2 T1 SERV LTS 222 CBP ---2 T3 SERV LTS 222 CBP ---4 B1 10TH ST B/AIR ISOL 222 CBP ---4 B12 DOOR INDICATION 222 CBP ---5 A1 APU ACT 311 CBP ---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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 18 of 122 Jul 21 /2011 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 non-metallic scraper around the FPC foam sheet (4). (d) Remove the FPC foam sheet (4) from the rear pressure bulkhead.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 19 of 122 Jul 21 /2011 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 of the intercostal (2) (Refer to view 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 20 of 122 Jul 21 /2011 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 21 of 122 Jul 21 /2011 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 22 of 122 Jul 21 /2011 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) With a permanent ink pen or equivalent, identify the clip (2) as shown in the table below.
Original Part Number After S.B. 601R --25 --187 Incorporation 601R45103 ---19 or 601R45103 ---29 K601R45034 ---2025 or K601R45034 ---2027

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 23 of 122 Jul 21 /2011 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 24 of 122 Jul 21 /2011 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 25 of 122 Jul 21 /2011 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 26 of 122 Jul 21 /2011 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) Temporarily 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 27 of 122 Jul 21 /2011 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 shown in the table below.
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) Temporarily 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) Temporarily 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 28 of 122 Jul 21 /2011 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) Temporarily 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) Temporarily 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 29 of 122 Jul 21 /2011 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 the three clips as follows: (a) Temporarily 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 30 of 122 Jul 21 /2011 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) Temporarily install the clip (5) at the location of the two holes on the frame at STGR9L. (b) Temporarily install the clip (3) at the location of the two holes on the frame at STGR7L. (c) Temporarily 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) Temporarily 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 31 of 122 Jul 21 /2011 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) Temporarily install the clip (8) at the location of the two holes on the frame at STGR9L. (b) Temporarily install the clip (6) at the location of the two holes on the frame at STGR7L. (c) Temporarily 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) Temporarily 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 32 of 122 Jul 21 /2011 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 33 of 122 Jul 21 /2011 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) Temporarily 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 34 of 122 Jul 21 /2011 Revision A, Sept 01/2011 (h) Temporarily 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) Temporarily 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 35 of 122 Jul 21 /2011 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) Temporarily 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) Temporarily 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 36 of 122 Jul 21 /2011 Revision A, Sept 01/2011 For all aircraft Refer to Figure 11 (Sheet 1 of 3). (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: The adhesive must be cured before you can clean the insert (6).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 37 of 122 Jul 21 /2011 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 Refer to Figure 11 (Sheet 2 of 3). (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: The adhesive must be cured before you can clean the insert (6).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 38 of 122 Jul 21 /2011 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 39 of 122 Jul 21 /2011 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: The adhesive must be cured before you can clean the insert (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 Refer to Figure 11 (Sheet 3 of 3). (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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 40 of 122 Jul 21 /2011 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: The adhesive must be cured before you can clean the insert (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

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 41 of 122 Jul 21 /2011 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: The adhesive must be cured before you can clean the insert (6).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 42 of 122 Jul 21 /2011 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

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 43 of 122 Jul 21 /2011 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 44 of 122 Jul 21 /2011 Revision A, Sept 01/2011 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 45 of 122 Jul 21 /2011 Revision A, Sept 01/2011 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 (Refer to SRM ---51---42---06). (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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 46 of 122 Jul 21 /2011 Revision A, Sept 01/2011 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 (Refer to SRM 51---26---00). (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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 47 of 122 Jul 21 /2011 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 48 of 122 Jul 21 /2011 Revision A, Sept 01/2011 (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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 49 of 122 Jul 21 /2011 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 (Refer to SRM 51---26---00). 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 50 of 122 Jul 21 /2011 Revision A, Sept 01/2011 (m) Torque 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).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 51 of 122 Jul 21 /2011 Revision A, Sept 01/2011 (aa) Install the liner assembly (18) on the floor panel with the washers (14) and the bolts (32). (ab) Torque 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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 52 of 122 Jul 21 /2011 Revision A, Sept 01/2011 (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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 53 of 122 Jul 21 /2011 Revision A, Sept 01/2011 (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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 54 of 122 Jul 21 /2011 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 installed on the removed liner. (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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 55 of 122 Jul 21 /2011 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 REFrsb601r25187_055.dg, gb, 06/07/11 FWD

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 56 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies and FPC Foam Sheet --- Removal Figure 2 (Sheet 1 of 3) 2

4

3

1rsb601r25187_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 65 6 5 6

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 57 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies and FPC Foam Sheet --- Removal Figure 2 (Sheet 2 of 3)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 65 6 5 6 FS621.00

For aircraft that have IS601R25520054 incorporated. NOTES

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 58 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies and FPC Foam Sheet --- Removal Figure 2 (Sheet 3 of 3)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

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 59 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Foam Sheet --- Removal Figure 3 (Sheet 1 of 2)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.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 60 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Blind Nut Assembly --- Installation Figure 3 (Sheet 2 of 2)rsb601r25187_052.dg, mt, apr20/2011 LEGEND 1. Blind nut assembly B0203034PB1032DU1. 2. Intercostal. 1

E E 2

TYPICAL INSTALLATION (7 PLACES) FS621.00 FS574.00

2.50 in. (6.4 cm)

44.08 in. (112.0 cm) 38.79 in. (98.5 cm) 33.75 in. (85.7 cm) 25.10 in. (63.8 cm) 18.10 in. (46.0 cm) 9.78 in. (24.8 cm)

0.80 in. (20.3 mm)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 61 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 1 of 14) B A

FS621.00

6 8

4 3 10

14 12

14

1

11 5 (8 PLACES) 14 15

7

14 A 6 1 8

14 11

2 11 14 B

11 13 (10 PLACES)

14 LEGEND

1. Duct B305104--101. 2. Duct skirt B305113--101. 3. Floor angle B305111--101. 4. Floor angle B305112--101. 5. Bolt NAS6203--2. 6. Liner assembly B305103--101. 7. Liner assembly B305102--101. 8. Liner assembly B305101--101. 10.Screw MS27039--1--07. 11. Screw MS27039--1--08. 13. Bolt NAS6203--12. 14. Washer B0202013S1328--63. 15. Washer NAS1149F0363P.

15 13 12. Screw MS27039--1--10.rsb601r25187_035.cgm,sc,10/2010 CHANNEL ASSEMBLY (REF)

CHANNEL ASSEMBLY (REF)

12 12

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 62 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 2 of 14)rsb601r25187_001.cgm, sc, Aug 2011 CHANNEL (REF)

FS621.00 17

16

18 19

1

14 11 SCREW (REF) WASHER (REF)
SCREW (REF) WASHER (REF)

WASHER (REF)

WASHER (REF) LEGEND

1. Duct B305104--101. 9. Washer B0202013S1328--63. 11. Screw MS27039--1--08. 16. Liner assembly B302103--101. 17. Liner assembly B303102--101. 18. Liner assembly B302104--101. 19. Strip assembly B303011--101 or B303011--103. FS621.00

C C On aircraft that have piccolo tube 601R99011--13. On aircraft that have piccolo tube 601R99011--1 or --9. NOTES

WASHER

(REF) SCREW (REF) WASHER (REF) SCREW (REF)

SUPPORT ASSEMBLY (REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 63 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 3 of 14)rsb601r25187_002.cgm, sc, 10/2010 FS559.00 +80.00 FS621.00 FS574.00

BL0.00 19 17 20

52 1 LEGEND

1. Duct B305104--101. 17. Liner assembly B303102--101. 19. Strip assembly B303011--101 or 20. Cover assembly, tie rod B306104--101. 52. Cover assembly, tie rod B306103--102. B303011--103. PART NUMBER NAME ITEM

34 MS27039--1--11 Screw 33 14 12 14 MS27039--1--10 B0202013S1328--63 Screw Washer MS27039--1--09 Screw Washer FASTENER CODE

14 Washer B0202013S1328--63
B0202013S1328--63 D

C

D BL0.00

FS621.00

On aircraft that have piccolo tube 601R99011--13. On aircraft that have piccolo tube 601R99011--1 or --9. NOTES

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 64 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 4 of 14)rsb601r25187_003.cgm FS621.00 FS559.00 +82.00

WL73.59

16

18 25

24 LEGEND 16. Liner assembly B302103--101. 18. Liner assembly B302104--101. 24. Cover assembly, tie rod B306106--101. 25. Cover assembly, tie rod B306105--101. 34 MS27039--1--11 Screw 14 Washer B0202013S1328--63 33 MS27039--1--09 Screw 14 Washer B0202013S1328--63 Clip Nut SL215--3--1 44 PART NUMBER NAME ITEM

33 14 12 14 MS27039--1--10 B0202013S1328--63 Screw Washer MS27039--1--09 Screw Washer FASTENER CODE

B0202013S1328--63

43 MS27039--1--12 Screw 14 Washer B0202013S1328--63 BL0.00

FS621.00

E NOTE Sealant TAFB101--006S on panel edge.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 65 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 5 of 14)rsb601r25187_004.cgm, sc, 10/2010 47

48 45

46 FS621.00 17.82 in. (452.63 mm) 16.50 in. (419.1 mm)

FS621.00 50.80 in. (1290.32 mm)

WL73.59

50.80 in. (1290.32 mm)

WL73.59 45. Placard S7547--1. 46. Placard S5953--1. 47. Placard S5979--1. 48. Placard S7501--1. B302103--101. LEGEND 16. Liner assembly F

C

F

F BL0.00

FS621.00

16

16

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 66 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 6 of 14)rsb601r25187_005.cgm, sc, 10/2010 23

22

21 CHANNEL (REF)

19 CHANNEL (REF)

SCREW (REF) WASHER (REF) WASHER (REF) SCREW (REF) WASHER (REF) SCREW (REF) WASHER (REF)

FS621.00 FS621.00

G G

On aircraft that have piccolo tube 601R99011--13. On aircraft that have piccolo tube 601R99011--1 or --9. NOTES

On aircraft that do not have a load divider. On aircraft that have a load divider. 7 8

SCREEN ASSY (REF) LEGEND 19. Strip assembly B303011--101 or B303011--103. 21. Liner assembly B302101--101. 22. Liner assembly B302102--101. 23. Liner assembly B303101--101 or B303101--103. 7 8

CHANNEL (REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 67 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 7 of 14)rsb601r25187_006.cgm, sc, 10/2010 FS559.00 +80.00 FS621.00 FS574.00

BL0.00

23

26 LEGEND 23. Liner assembly B303101--101 or B303101--103. 26. Cover assembly, tie rod B306103--101.

PART NUMBER NAME ITEM

34 MS27039--1--11 Screw 33 14 12 14 MS27039--1--10 B0202013S1328--63 Screw Washer MS27039--1--09 Screw Washer FASTENER CODE

14 Washer B0202013S1328--63
B0202013S1328--63 H

G

H FS621.00 BL0.00

On aircraft that do not have a load divider. On aircraft that have a load divider. NOTES 7 8

7 8

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 68 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 8 of 14)rsb601r25187_007.cgm PART NUMBER NAME ITEM

34 MS27039--1--11 Screw 33 14 12 14 MS27039--1--10 B0202013S1328--63 Screw Washer MS27039--1--09 Screw Washer FASTENER CODE

14 Washer B0202013S1328--63
B0202013S1328--63

FS574.00 FS559.00 +112.00 FS559.00 +96.00 22

27

28 21

FLOOR (REF) WL73.59

9G BULKHEAD (REF) FS559.00 +80.50 FS621.00 BL0.00

G J

K

SCREEN ASSY (REF) K LEGEND 21. Liner assembly B302101--101. 22. Liner assembly B302102--101. 27. Cover assembly, tie rod B306102--101. 28. Cover assembly, tie rod B306101--101. 29. Screw NAS517--3--4. 30. Anchor plate 20050. TYPICAL 5 PLACES J LINER ASSEMBLY (REF) 30 29 8 8

On aircraft that have a load divider. NOTE 8 43 MS27039--1--12 Screw 14 Washer B0202013S1328--63

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 69 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 9 of 14)rsb601r25187_008.cgm,sc,10/2010 9G BULKHEAD (REF)

SCREW (REF) WASHER (REF)

TIE ROD COVER (REF) ANGLE ASSEMBLY (REF) LINER ASSEMBLY (REF)

14 33 12

14 3312 FLOOR (REF) 14 32 WASHER (REF)SCREW (REF)

LEGEND 12. Screw MS27039--1--10. 14. Washer B0202013S1328--63. 20. Cover assembly, tie rod B306104--101. 24. Cover assembly, tie rod B306106--101. 25. Cover assembly, tie rod B306105--101. 32. Bolt NAS6203--11. 33. Screw MS27039--1--09. 35. Angle assembly, 9G bulkhead B306115--101. 36. Angle assembly, 9G bulkhead B306116--101. 37. Angle assembly, 9G bulkhead B306117--101. 38. Angle assembly, 9G bulkhead B306118--101. ANGLE ASSEMBLY (REF) LINER ASSEMBLY (REF) L L

N TYPICAL INSTALLATION

TYPICAL TIE--ROD COVER INSTALLATION M 24 FS621.00
9G BULKHEAD (REF) BL0.00

25 38 37 3652

35 20 M

N

52. Cover assembly, tie rod B306103--102.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 70 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 10 of 14)rsb601r25187_009.cgm,sc,10/2010 9G BULKHEAD (REF)

SCREW (REF) WASHER (REF)

TIE ROD COVER (REF)

ANGLE ASSEMBLY (REF) LINER ASSEMBLY (REF) ANGLE ASSEMBLY (REF) LINER ASSEMBLY (REF)

14 33 12

14 3312

FLOOR (REF) 14 32 WASHER (REF)SCREW (REF)

LEGEND 12. Screw MS27039--1--10. 14. Washer B0202013S1328--63 26. Cover assembly, tie rod B306103--101. 27. Cover assembly, tie rod B306102--101. 28. Cover assembly, tie rod B306101--101. 32. Bolt NAS6203--11. 33. Screw MS27039--1--09. 39. Angle assembly, 9G bulkhead B306111--101. 40. Angle assembly, 9G bulkhead B306112--101. 41. Angle assembly, 9G bulkhead B306113--101. 42. Angle assembly, 9G bulkhead B306114--101. T P

TYPICAL INSTALLATION

R TYPICAL TIE--ROD COVER INSTALLATION 9G BULKHEAD (REF) BL0.00 42 26 FS621.00

41

27 28 39 40 R

P T

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 71 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 11 of 14)rsb601r25187_010.cgm,sc,10/2010 SCREW (REF) WASHER (REF)

SCREW (REF) WASHER (REF) 49

51

50 LEGEND 49. Door shroud B303110--1. 50. Liner assembly B302105--101. 51. Liner assembly B302106--101. G

U FS621.00 BL0.00

U

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 72 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 12 of 14)rsb601r25187_011.cgm,sc,10/2010 FS621.00 FS605.00 FS589.00 FS574.00

50 51 FS621.00 BL0.00 53 NAS1169--10L Washer 56 Screw MS24693--S273 PART NUMBER NAME ITEM FASTENER CODE

LEGEND 50. Liner assembly B302105--101. 51. Liner assembly B302106--101.

V G V

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 73 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies --- Installation Figure 4 (Sheet 13 of 14)rsb601r25187_012.cgm 12 14 MS27039--1--10 B0202013S1328--63 Screw Washer 33 14 MS27039--1--09 Screw Washer B0202013S1328--63 34 MS27039--1--11 Screw 14 Washer B0202013S1328--63 43 MS27039--1--12 Screw 14 Washer B0202013S1328--63 54 14 MS27039--1--07 B0202013S1328--63 Screw Washer 55 14 MS21042L3 B0202013S1328--63 Nut Washer PART NUMBER ITEM FASTENER CODE

LEGEND 49. Door shroud B303110--1. 51. Liner assembly B302106--101.

LOOKING AFT AT FS621.00 X X 49

51 FS621.00 FS605.00 FS589.00 FS574.00

49

W X

X FS621.00 BL0.00

G W NAME

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 74 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Tie Rod Cover, Cargo Light, and Anchor Plate --- Application of Sealant Figure 4 (Sheet 14 of 14)rsb601r25187_031.cgm AA

NOTE Sealant TAFB101--006S. TIE ROD COVER (REF)

AA TYPICAL 7 PLACES SEALANT RTV 106 (REF)

LINER ASSEMBLY (REF)

ANCHOR PLATE (REF)

AC TYPICAL CARGO LIGHT (REF) AB AB

AC AA

AA

AC

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 75 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 5 (Sheet 1 of 7)rsb601r25187_013.cgm,sc,nov 4 2010 A STGR10R STGR0

1

RIVET (REF)FS621.00

B POST--MOD FS621.00

C FS621.00 FS559.00 +80.00

FS574.00

B LEGEND 1. Rivet B0205017AD4--4S. 2. Clip 601R45103--19 (Pre--Mod) K601R45034--2025 (Post--Mod) or 601R45103--29 (Pre--Mod) K601R45034--2027 (Post--Mod).

CHANNEL (REF) PRE--MOD B CHANNEL (REF) C 2 0.80 in. (20.3 mm) 2 2 A

MATERIAL TO BE REMOVED

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 76 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 5 (Sheet 2 of 7)rsb601r25187_014.cgm,sc,nov 4 2010 A STGR10R STGR6R STGR7R STGR0

1 RIVET (REF)

RIVET (REF) 1 FS621.00

D POST--MOD PRE--MOD D E CHANNEL (REF)

CHANNEL (REF) FS621.00 FS621.00 FS559.00 +80.00

FS574.00

D LEGEND 1. Rivet B0205017AD4--4S. 3. Clip 601R45103--33 (Pre--Mod) K601R45034--2021 (Post--Mod). 5. Clip 601R45103--35 (Pre--Mod) K601R45034--2023 (Post--Mod).

STRG6 CHANNEL (REF)

E 1.00 in. (25.4 mm)

1.00 in. (25.4 mm) 3

5 3

5 3

5

MATERIAL TO BE REMOVED

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 77 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 5 (Sheet 3 of 7)rsb601r25187_015.cgm,sc,nov 4 2010 A STGR10R STGR3R STGR0

1 RIVET (REF) FS621.00 FS621.00 F

F PRE--MOD F POST--MOD G FS621.00 FS559.00 +80.00 FS574.00

FS559.00 +96.00 FS559.00 +112.00

8.45 in. (214.6 mm) 6

6

H H

6 G 1.00 in. (25.4 mm)

4 LEGEND 1. Rivet B0205017AD4--4S. 4. Clip 601R45103--13 (Pre--Mod) K601R45034--2019 (Post--Mod). 6. Channel 601R45552--5 (Pre--Mod) K601R45034--2007 (Post--Mod).

4 4

MATERIAL TO BE REMOVED

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 78 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 5 (Sheet 4 of 7)rsb601r25187_016.cgm, sc, 07/2010 J

J K FS621.00 FS559.00 +80.00

FS574.00 STGR0 STGR2L

STGR12L LEGEND 15. Channel. 16. Clip. 17. Rivet NAS9304E--5--02.

FS605.00

FS589.00

FS574.00

15 CLIP (REF)

CLIP (REF) CLIP (REF) FS621.00

16

RIVET (REF) RIVET (REF)

RIVET (REF) K 17 FS621.00

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 79 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 5 (Sheet 5 of 7)rsb601r25187_017.cgm,sc,nov 4 2010 FS559.00 +112.00

FS559.00 +96.00

7

22.33 in. (567.2 mm)

4.00 in. (101.6 mm) 0.60 in. (15.2 mm) J FS621.00 FS559.00 +96.00 FS559.00 +112.00 STGR0

STGR12L

L LEGEND

1. Rivet B0205017AD4--4S. 7. Channel 601R45552--23, 601R45552--951 or 601R45552--955 (Pre--Mod) K601R45034--2029 (Post--Mod). 8. Rivet MS20470AD5--4A. 9. Rivet B0205017AD3--4S. 10. Nutplate MS21059L3. 13. Clip. 14. Clip.

14

RIVET (REF) RIVET (REF) RIVET (REF)
FRAME (REF)

13

7 8 (TYPICAL 4 PLACES)

1 L N

P M P N N

M 10
9

7

MATERIAL TO BE REMOVED 0.256 TO 0.261 in (6.50 TO 6.63 mm) FS574.00

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 80 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 5 (Sheet 6 of 7)rsb601r25187_018.cgm, sc, 07/2010 J FS559.00 +112.00

FS559.00 +96.00

CHANNEL ASSY RIVET (REF) FS621.00 FS559.00 +96.00 FS559.00 +112.00

STGR12L STGR0STGR3L STGR2L

FRAME (REF) 8 (TYPICAL 2 PLACES) LEGEND

8. Rivet MS20470AD5--4A. 11. Clip.

RIVET (REF)

T R R

T T

11

11 (REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 81 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 5 (Sheet 7 of 7)rsb601r25187_019.cgm,sc,nov 4 2010 J

5.48 in. (139.2 mm) FS559.00 +112.00

FS559.00 +96.00

12 FS574.00 FS621.00 FS559.00 +96.00

FS574.00 STGR0

STGR12L

12 V

U U

V LEGEND 12. Channel 601R45552--15 (Pre--Mod) K601R45034--2001 (Post--Mod) or 601R45552--59 (Pre--Mod) K601R45034--2003 (Post--Mod) or 601R45552--125 (Pre--Mod) K601R45034--2005 (Post--Mod).

MATERIAL TO BE REMOVED

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 82 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 6 (Sheet 1 of 5)rsb601r25187_020.cgm, sc, 07/2010 3 FS559.00 +112.00

FS559.00 +96.00

13 3 A STGR3L

+112.00 STGR0

STGR12L +96.00

A

D B B C

C

D FS621.00

LEGEND 3. Rivet MS20470AD5--5A. 13. Angle assembly. 14. Clip. 15. Clip.

15 14 B B VIEW LOOKING FORWARD AT FS559.00 +112.00

14 0.85 in. (21.6 mm) 0.72 in. 18.3 mm STGR3L

13

VIEW LOOKING FORWARD AT FS559.00 +96.00 C C 15 0.84 in. (21.3 mm) 1.08 in. (27.4 mm) STGR3L

13 FS559.00 FS559.00

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 83 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 6 (Sheet 2 of 5)rsb601r25187_021.cgm, sc, 07/2010 FS559.00 +112.00

FS559.00 +96.00 4 FS574.00

INTERCOSTAL (REF) A FS621.00 FS559.00 +96.00 FS559.00 +112.00 STGR0

STGR12L

3 1

2 3 G

5

5 LEGEND 1. Clip 601R45103--53. 2. Clip 601R45103--51. 3. Rivet MS20470AD5--5A. 4. Channel K601R45034--2029. 5. Rivet B0205017AD4--4S.

1 2

G 0.58 in. (14.7 mm) FS559.00 +112.00

4.41 in. (112.0 mm) 8.37 in. (212.6 mm) INTERCOSTAL (REF)

0.58 in. (14.7 mm) F

E

VIEW ROTATED FOR CLARITY F 2.84 in. (72.1 mm)

4 INTERCOSTAL (REF)

2
E

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 84 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 6 (Sheet 3 of 5)rsb601r25187_022.cgm, sc, 07/2010 A FS621.00 STGR3L FS559.00 +112.00 STGR0

STGR12L

5.90 in. (149.9 mm) 0.60 in. (15.2 mm) DIAMETER FS621.00 FS559.00 +96.00

FS621.00

10

10 H J 11

12 LEGEND 10. Channel 601R45105--15 (Pre--Mod) K601R45034--2009 (Post--Mod) or 601R45102--117 (Pre--Mod) K601R45034--2011 (Post--Mod) or 601R45105--21 (Pre--Mod) K601R45034--2013 (Post--Mod) or 601R45102--131 (Pre--Mod) K601R45034--2015 (Post--Mod) or 601R45102--963 (Pre--Mod) K601R45034--2017 (Post--Mod). 11. Nutplate MS21059L3. 12. Rivet B0205017AD3--4S. J

H 0.256 TO 0.261 in. 6.50 TO 6.63 mm)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 85 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 6 (Sheet 4 of 5)rsb601r25187_023.cgm, sc, 07/2010 FS621.00FS574.00 STGR0

STGR12L FS559.00 +96.00

9.98 in. (253.5 mm) 6 4 FS574.00

STGR0 LEGEND 4. Channel K601R45034--2029. 5. Rivet B0205017AD4--4S. 6. Channel 601R45552--71.

K K

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 86 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 6 (Sheet 5 of 5) Lrsb601r25187_056.cgm CLIP (REF) CLIP (REF) CLIP (REF)

FS605.00 FS589.00 FS574.00

FS621.00 FS621.00FS574.00 STGR0

STGR12L FS559.00 +96.00

5 6

L VIEW LOOKING UP LEGEND 5. Rivet B0205017AD4--4S. 6. Channel assembly 601R45552--71.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 87 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 7 (Sheet 1 of 4)rsb601r25187_027.dg, sd, sept7/2010 A STGR 9L STGR 7L STGR 5L FS589.00FS574.00

FS605.00

A C B

C 1 FRAME (REF) FS605.00 STGR 7L

STGR 8L

STGR 9L RIVET (REF)

LEGEND 1. Clip. 2. Clip.

B FS589.00

2 FRAME (REF) STGR 7L

STGR 8L

STGR 9L RIVET (REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 88 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 7 (Sheet 2 of 4)rsb601r25187_028.dg, sd, sept7/2010 FS605.00

STGR

6L STGR 5L

STGR

7L

STGR

8L

STGR

9L 0.90 in. (22.9 mm) 0.28 in. (7.1 mm) 0.90 in. (22.9 mm)

0.53 in. (13.5 mm) 1.02 in. (25.9 mm)

0.39 in. (9.9 mm)

0.91 in. (23.1 mm) 0.90 in. (22.9 mm) D

5 FS605.00

STGR 7LSTGR 6L

STGR 8L

STGR 9L 5 3 4 3 10

10

14

14 E

D

3 3

4

E VIEW LOOKING FWD AT FS605.00 A LEGEND

3. Clip, 601R45159--131. 4. Clip, 601R45159--119. 5. Clip, 601R45159--135. 14. Rivet, MS20470AD5--6A.

(REF) DOUBLER 10. Rivet, MS20470AD5--5A.

(REF)

(REF) (REF)

(REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 89 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 7 (Sheet 3 of 4)rsb601r25187_029.dg, sd, sept8/2010 FS589.00
FS589.00

STGR 7LSTGR 6L

8 6 7 6 10

10

14

10

VIEW LOOKING FWD AT FS589.00 A

STGR

6L STGR 5L

STGR

7L

STGR

8L

STGR

9L 0.25 in. (6.4 mm) 0.87 in. (22.1 mm)

0.85 in. (21.6 mm) 0.13 in. (3.3 mm) 1.02 in. (25.9 mm) 1.0 in. (25.4 mm) 0.44 in. (11.2 mm) 0.89 in. (22.6 mm)

6 7

8 6 LEGEND

6. Clip, 601R45159--121. 7. Clip, 601R45159--117. 8. Clip, 601R45159--129. 10. Rivet, MS20470AD5--5A.

G F STGR 8L G F 14. Rivet, MS20470AD5--6A.

DOUBLER (REF)

(REF)

(REF) (REF)
(REF) STGR 9L

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 90 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Structural Changes Figure 7 (Sheet 4 of 4)rsb601r25187_030.dg, sd, sept9/2010 A FS605.00 FS589.00

FS621.00 STGR 8L STGR 7L STGR 6L

STGR 9L 11

12 LEGEND

4. Clip, 601R45159--119. 5. Clip, 601R45159--135. 7. Clip, 601R45159--117. 8. Clip, 601R45159--129. 11. Channel, 601R45102--181. 12. Channel, 601R45102--177. 13. Rivet, B0205017AD4--5S.

L 11

13 13

4

7

M 12 8 5

13 13 H

J

K

N P TYPICAL CHANNEL TO CLIP INSTL L M

N P

= = FS605.00
12 5

2.78 in. (70.6 mm)J FS605.00 11 4

1.50 in. (38.1 mm)
H

K

(REF)

(REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 91 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Rear Pressure Bulkhead --- Changes Figure 8rsb601r25187_037.cgm,sc,nov 9 2010 PART NUMBER NAME ITEM

3 4 2 CR4173--4--01 Rivet NAS623--2--2 Screw Washer FASTENER CODE

NAS1149FN832P A

FS621.00

BULKHEAD (REF) BULKHEAD (REF) NOTES For aircraft that do not have modification summary IS601R25520054 incorporated. For aircraft that have modification summary IS601R25520054 incorporated. 1

2 It is possible not to have provisions for holes. 3.

WL79.00 WL120.43

1 2 TYPICAL 4 PLACES BULKHEAD (REF) 1 LEGEND 1. Clickbond nutplate.

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 92 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Rear Pressure Bulkhead --- Changes Figure 9 (Sheet 1 of 3)rsb601r25187_038.cgm,sc,nov 9 2010 A A

FS621.00

WL120.43

WL79.00 B C

C 0.195 TO 0.201 in. (4.95 TO 5.11 mm). DRILL CODE

BULKHEAD (REF) B LEGEND 1. Sealed nutplate 601R36040--1. 2. Rivet CR2673CW--3--03.

TYPICAL 4 PLACES C BULKHEAD (REF)
1 2 For aircraft that have provisions for holes. NOTE

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 93 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Rear Pressure Bulkhead --- Changes Figure 9 (Sheet 2 of 3)rsb601r25187_039.cgm,sc,nov 9 2010 0.195 TO 0.201 in. (4.95 TO 5.11 mm). DRILL CODE LEGEND 3. Liner B305123--101. 4. Liner B305122--101. 5. Liner B305121--101. 6. Screw NAS623--2--5.

BULKHEAD (REF) WL120.43

WL79.00 D A 3

5 6

6 4

6

6 D

NOTE Do not drill through pilot hole. 1 1

1

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 94 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Rear Pressure Bulkhead --- Changes Figure 9 (Sheet 3 of 3)rsb601r25187_040.cgm,sc,nov 9 2010 A E E

LEGEND 1. Sealed nutplate assembly 601R36040--1. 2. Rivet CR2673CW--3--03.

BULKHEAD (REF)

1 2

E TYPICAL 4 PLACES

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 95 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Rear Pressure Bulkhead --- Changes Figure 10 0.195 TO 0.201 in. (4.95 TO 5.11 mm). DRILL CODE LEGEND 1. Liner B305123--101. 2. Liner B305122--101. 3. Liner B305121--101. 4. Nutplate, sealed 601R36040--1. 5. Rivet CR2673CW--3--03.

BULKHEAD (REF) WL120.43

WL79.00 A 1

2rsb601r25187_046.cgm, sc, 03/2011 A

FS621.00

3

TYPICAL 8 PLACES C
AT DRILL CODE LOCATIONS BULKHEAD (REF)
4 5 C

NOTE Do not drill through pilot hole. 1 1

1

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 96 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Floor Panels --- Changes Figure 11 (Sheet 1 of 3) A G F E D

C Arsb601r25187_024.cgm, sc, 08/2010 FS621.00

B TYPICAL VIEW OF INSERT C B

B

1

0.561 TO 0.566 in. (14.25 TO 14.38 mm) DIAMETER 0.86 in. (21.8 mm)

3.44 in. (87.4 mm) LEGEND 1. Floor panel 601R31668--249 (Pre--Mod) K601R45034--2059 (Post--Mod) or 601R31668--281 (Pre--Mod) K601R45034--2069 (Post--Mod) or 601R31668--361 (Pre--Mod) K601R45034--2079 (Post--Mod) or 601R31668--503 (Pre--Mod) K601R45034--2089 (Post--Mod). 6. Insert NAS1833C3--400. 6

3 CORE CELLS MINIMUM OR 4 CORE CELLS MAXIMUM OR 1.5 TIMES HOLE DIAMETER (REF) POSITIONING TAB NAS1837G3

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 97 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Floor Panels --- Changes Figure 11 (Sheet 2 of 3) Drsb601r25187_025.cgm, sc, 08/2010

3.44 in. (87.4 mm)

0.85 in. (21.6 mm)

0.85 in. (21.6 mm) A E D FS621.00

2

0.85 in. (21.6 mm)

0.85 in. (21.6 mm) 0.82 in. (20.8 mm)

E 0.561 TO 0.566 in. (14.25 TO 14.38 mm) DIAMETER 0.561 TO 0.566 in. (14.25 TO 14.38 mm) DIAMETER 3 LEGEND 2. Floor panel

3. Floor panel 601R31668--243 (Pre--Mod) K601R45034--2055 (Post--Mod) or 601R31668--275 (Pre--Mod) K601R45034--2065 (Post--Mod) or 601R31668--333 (Pre--Mod) K601R45034--2075 (Post--Mod) or 601R31668--499 (Pre--Mod) K601R45034--2085 (Post--Mod). 601R31668--245 (Pre--Mod) K601R45034--2051 (Post--Mod) or 601R31668--277 (Pre--Mod) K601R45034--2061 (Post--Mod) or 601R31668--325 (Pre--Mod) K601R45034--2071 (Post--Mod) or 601R31668--497 (Pre--Mod) K601R45034--2081 (Post--Mod). 601R31668--241 (Pre--Mod) K601R45034--2053 (Post--Mod) or 601R31668--273 (Pre--Mod) K601R45034--2063 (Post--Mod) or 601R31668--345 (Pre--Mod) K601R45034--2073 (Post--Mod) or 601R31668--501 (Pre--Mod) K601R45034--2083 (Post--Mod).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 98 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Floor Panels --- Changes Figure 11 (Sheet 3 of 3)rsb601r25187_026.cgm, sc, 08/2010 3.44 in. (87.4 mm)

0.85 in. (21.6 mm) A

G F FS621.00

4

0.86 in. (21.8 mm) 0.561 TO 0.566 in. (14.25 TO 14.38 mm) DIAMETER 0.561 TO 0.566 in. (14.25 TO 14.38 mm) DIAMETER F

G

3.44 in. (87.4 mm) 5

0.85 in. (21.6 mm) LEGEND 4. Floor panel 601R31668--245 (Pre--Mod) K601R45034--2051 (Post--Mod) or 601R31668--277 (Pre--Mod) K601R45034--2061 (Post--Mod) or 601R31668--325 (Pre--Mod) K601R45034--2071 (Post--Mod) or 601R31668--497 (Pre--Mod) K601R45034--2081 (Post--Mod).

5. Floor panel 601R31668--247 (Pre--Mod) K601R45034--2057 (Post--Mod) or 601R31668--279 (Pre--Mod) K601R45034--2067 (Post--Mod) or 601R31668--323 (Pre--Mod) K601R45034--2077 (Post--Mod) or 601R31668--495 (Pre--Mod) K601R45034--2087 (Post--Mod). 601R31668--241 (Pre--Mod) K601R45034--2053 (Post--Mod) or 601R31668--273 (Pre--Mod) K601R45034--2063 (Post--Mod) or 601R31668--345 (Pre--Mod) K601R45034--2073 (Post--Mod) or 601R31668--501 (Pre--Mod) K601R45034--2083 (Post--Mod).

601R31668--9037 (Pre--Mod) K601R45034--2097 (Post--Mod) or 601R31668--9063 (Pre--Mod) K601R45034--2107 (Post--Mod).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 99 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Outlet Duct, Overheat Switch, and Control Switch --- Installation Figure 12rsb601r25187_033.cgm, sc, Aug 2011 NOTE On aircraft that have CR25--359. 4 1

4 DUCT (REF) 3 2
1

LINER ASSEMBLY (REF)

TOP STRIP ASSEMBLY (REF) LEGEND 1. Duct, outlet

2. Overheat switch 3. Control switch 4. Tape MMS01--001 type 1. 601R96385--19 or 601R96385--27 or 601R96385--35 (Pre--Mod), B303601--101 or B303601--103 (Post--Mod).

5. Washer B0202013S1328--63. 6. Screw MS27039--1--08.

5 6

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 100 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Tie Rods --- Removal/Installation Figure 13rsb601r25187_047.dg, sc, 7Mar 2011

FS559.00

+93.80 FS559.00 + 87.00

STRG 15

FITTING (REF) 3 2

1 34 FITTING (REF) 4 31 3 2

4 3 3

2

1 FITTING (REF)

(TYPICAL 4 PLACES) (TYPICAL 2 PLACES) FS559.00 + 87.00

1. Tie rod. 2. Bolt. 3. Washer. 4. Nut. 5. Jam nut. LEGEND 5

5

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 101 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Liner Assemblies and FPC Foam Sheet --- Installation Figure 14rsb601r25187_041.cgm,sc,nov 9 2010

A A

FS621.00

1

2

3 LEGEND 1. Liner assembly B305123--101. 2. Liner assembly B305122--101. 3. Liner assembly B305121--101. 6. SPC foam sheet 601R45154--21. 4. Screw NAS623--2--5. 5. Washer NAS1149FN832P.

4 5

4 5

4

5

4 5 4 5

4 5

4 5

4 5 6

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 102 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Removal / Installation of Electrical Hardware and Structure Figure 15rsb601r25187_049.dg, sc, 19Mar 2011 FS672.20

1 2

3

4 5

6 7 (4 PLACES)

5 8 9

10
11 9

10 11 LEGEND 1. Bracket. 2. Rivet MS20470AD( )--( )A. 3. Mounting tray, radio altimeter. 4. Mounting tray, converter. 5. Screw. 6. Washer. 7. Screw. 8. Mounting tray, ECU. 9. Screw. 10. Washer. 11. Nut. FS621.00

FS672.20 FS682.00

6 FRAME (REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 103 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Ground Connection Duct --- Removal Figure 16 BLEED AIR

1 3 2

3rsb601r25187_048.dg, sc, 18Mar 2011 1. Ground connection duct. 2. Boot. 3. Coupling. LEGEND

DUCT (REF)

ADAPTER (REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 104 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Piccolo Tube --- Installation Figure 17rsb601r25187_051.cgm,mt,avril 14 2011 STGR10R STGR0

FS621.00 FS574.00

A

LEGEND

NAS43DD3--52N (Pre--Mod). NAS43DD3--68FC (Post--Mod). 1. Washer B0202013S1328--32. 2. Spacer NAS43DD3--11FC. 3. Spacer

FIXER COVER (REF) FS614.50 FS611.50 FS603.30 FS595.75 FS587.79 FS586.29 FS577.60

FS621.00

STGR0

D 1 2 1

3

PICCOLO TUBE (REF) D PICCOLO TUBE (REF)

D

On aircraft that have piccolo tube 601R99011--1 or --9. NOTES

On aircraft that have piccolo tube 601R99011--13. FS569.12 FS567.62

2 CLAMP (REF) CLAMP

(REF)

SPACER

(REF)

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 105 of 122 Jul 21 /2011 Revision A, Sept 01/2011Application of TAFB101 ---006S Sealant Figure 18 (Sheet 1 of 2) FS589.00FS574.00

FS605.00

NOTE Sealant TAFB101--006S around edges. 1 FS621.00rsb601r25187_053.cgm A 1 1 A

B

B

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 106 of 122 Jul 21 /2011 Revision A, Sept 01/2011Application of TAFB101 ---006S Sealant Figure 18 (Sheet 2 of 2) NOTE Sealant TAFB101--006S around edges. 1rsb601r25187_054.cgm C 1 PULLEY BOX (REF) C

D D

1E

E 1

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 107 of 122 Jul 21 /2011 Revision A, Sept 01/2011 C. Job Close ---Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Install all loose items that were removed from the cargo compartment. (3) If removed, install the baggage bay door (Refer to AMM 52---31---00---400---801). (4) If removed, install the left discharge duct (Refer to AMM 21---51---15---400---801). Refer to Figure 16. (5) Install the ground connection duct (1) as follows: (a) Remove the protective covers from the duct (1), the adapter, and the bleed air duct. (b) Put the couplings (3) over the lower and upper ends of the duct (1). (c) Align the duct (1) with the adaptor and the bleed air duct. (d) Loosely install the couplings (3) at each end of the duct (1). (e) Torque the nut on the two couplings (1) from 30 to 37.5 lbf·in (3.4 to 4.2 N·m). (f) Make sure that the flanges of the duct (1) engage correctly with the flange of the bleed air duct and the adaptor. (g) Torque the coupling nuts from 40 to 50 lbf·in (4.5 to 5.6N·m). (h) Install the boot (2) over the upper coupling (3). (i) Apply three full turns of silicone tape on each end of the boot (2). (6) Install the APU fire extinguisher (Refer to AMM 26---22---07---400---801). (7) Install the cooler duct (Refer to AMM 49---52---01---400---801).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 108 of 122 Jul 21 /2011 Revision A, Sept 01/2011 Refer to Figure 15. (8) Install the mounting trays (3), (4), and (8) as follows: (a) Make sure that the mating surfaces of the structure are clean and have no corrosion, grease, or fluids. (b) Make sure that the bonding areas on the structure are satisfactory. (c) Install the mounting tray of the converter (4) with the screws (5) and the washers (6). (d) Install the mounting tray of the radio altimeter(3) with the screws (7). (e) Install the electrical connector on the mounting tray of the radio altimeter (3) with the hardware removed before. (f) Install the mounting tray of the ECU (8) with the screws (9), washers (10), and the nuts (11). (g) Install the electrical connector on the mounting tray of the ECU (8) with the hardware removed before. (9) Install the bracket (1) on the frame with eight rivets (2). (10) Install the APU ECU (Refer to AMM 49---61---01---400---801). (11) Install the radio altimeter (Refer to AMM 34---44---01---400---801). (12) Install the radio altimeter converter (Refer to AMM 34---44---04---400---801). (13) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME ZONE

CBP ---1 F11 10TH ST B/AIR SOV L 221 CBP ---1 K7 RAD ALT 221 CBP ---1 M2 ENG IGN A 221 CBP ---1 M3 ENG IGN B 221 CBP ---1 M4 ENG START R 221 CBP ---1 M5 ENG START L 221 CBP ---1 J1 L AIR COND UNIT 221

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 109 of 122 Jul 21 /2011 Revision A, Sept 01/2011 CB PANEL ZONE NAME CB NO. CBP ---1 N12 XFER/APU ECU 221 CBP ---1 R5 APU FIRE EXT A 221 CBP ---1 R6 APU FIRE EXT B 221 CBP ---2 F11 10TH ST B/AIR SOV R 222 CBP ---2 J1 R AIR COND UNIT 222 CBP ---4 B1 10TH ST B/AIR ISOL 222 CBP ---4 B12 DOOR INDICATION 222 CBP ---5 A1 APU ACT 311 (14) Apply external AC power to the aircraft (Refer to AMM 12---00---07---861---801). (15) Do the operational test of the APU fire-extinguishing system (Refer to AMM 26---22---00---710---801). (16) Do the leak test of the air conditioning system (Refer to AMM 21---51---00---790---801). (17) Do the adjustment of the cargo compartment door (Refer to AMM 52---31---00---820---801). (18) Do the operational test of the cargo compartment door (Refer to AMM 52---31---00---710---801). (19) Do the operational test of the cargo-compartment door-warning system (Refer to AMM 52---70---02---710---801). (20) Do the writing of the data into the APU ECU (Refer to AMM 49---61---01---970---801). (21) Do the built-in test of the radio altimeter (Refer to AMM 34---44---01---740---801). (22) Do the operational test of the cargo smoke-detection system (Refer to AMM 26---15---00---710---801).

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 110 of 122 Jul 21 /2011 Revision A, Sept 01/2011 (23) Do the operational test of the cargo fire-extinguishing system (Refer to AMM 26---25---00---710---801). (24) Do the operational test of the service lights (Refer to AMM 33---31---00---710---801). (25) If applicable, do the operational test of the compartment overheat switch (Refer to AMM 21---55---13---710---801). (26) If applicable, do the operational test of the temperature control switch (Refer to AMM 21---55---17---710---801). (27) When this service bulletin is completed, make this entry in the applicable logbook(s): “Service Bulletin 601R---25---187, Revision A, Equipment/Furnishing --- Cargo Compartment Linings --- Replacement of Liners in the Cargo Compartment --- (North American Configuration), incorporated.”

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 111 of 122 Jul 21 /2011 Revision A, Sept 01/2011 3. MATERIAL INFORMATION
A. Kit Information

KIT 601R25 ---187K1
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
601R36040---1 9 Nutplate assy, sealed

--- --- 601R45102---177 1 Channel assembly

--- --- 601R45102---181 1 Channel assembly

--- --- 601R45103---51 1 Clip

--- --- 601R45103---53 1 Clip

--- --- 601R45154---21 1 FPC foam sheet

--- --- 601R45159---117 1 Angle assembly

--- --- 601R45159---119 1 Angle assembly

--- --- 601R45159---121 2 Angle assembly

--- --- 601R45159---129 1 Angle assembly

--- --- 601R45159---131 2 Angle assembly

--- --- 601R45159---135 1 Angle assembly

--- --- 601R45552---71 1 Channel assembly

--- --- BR7203---804---1 2 Dome light

--- ---

KIT 601R25 ---187K2A
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
20050 9 Anchor

--- --- B0202013S1328-32 10 Washer

--- --- B0202013S1328-63 493 Washer

--- --- B0202013S1332-63 32 Washer

--- ---

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 112 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PART NUMBER NOTES ALTERNATE PARTS NAME QUANTITY
B0203034PB1032DU1 8 Nut assy, blind

--- --- B0205017AD3---2S 5 Rivet

--- --- B0205017AD4---4S 22 Rivet

--- --- B0205017AD4---5S 9 Rivet

--- --- CR2663CW---4---03 60 Rivet, blind

--- --- CR2673CW---3---03 20 Rivet, blind

--- --- CR3214---4---2 15 Rivet, blind

--- --- CR4173---4---01 26 Rivet, blind

--- --- MS20470AD5---4A 9 Rivet

--- --- MS20470AD5---5A 21 Rivet

--- --- MS20470AD5---6A 5 Rivet

--- --- MS21042L3 6 Nut, self---locking

--- --- MS21059L3 3 Nut, self---locking

--- --- MS24693---S273 21 Screw

--- --- MS27039---1---07 55 Screw

--- --- MS27039---1---08 57 Screw

--- --- MS27039---1---09 126 Screw

--- --- MS27039---1---10 143 Screw

--- --- MS27039---1---11 48 Screw

--- --- MS27039---1---12 11 Screw

--- --- NAS1149CN516R 60 Washer, flat NAS1149F0363P 11 Washer

--- --- NAS1149FN832P 31 Washer

--- --- NAS1169---10L 21 Washer, dimpled

--- --- NAS1833C3---400 10 Insert

--- --- NAS43DD3---11FC 4 Spacer

--- ---

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 113 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PART NUMBER NOTES ALTERNATE PARTS NAME QUANTITY
NAS43DD3---68FC 7 Spacer

--- --- NAS517---3---4 18 Screw

--- --- NAS6203---11 43 Bolt

--- --- NAS6203---12 11 Bolt

--- --- NAS6203---2 9 Bolt

--- --- NAS623---2---2 22 Screw, pan head

--- --- NAS623---2---5 9 Screw

--- --- S5953---1 1 Placard

--- --- S5979---1 1 Placard

--- --- S7501---1 1 Placard

--- --- S7547---1 1 Placard

--- --- SL215---3---1 20 Nut, clip

--- ---

KIT 601R25 ---187K350
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
B302101---101 1 Liner assembly

--- --- B302102---101 1 Liner assembly

--- --- B302103---101 1 Liner assembly

--- --- B302104---101 1 Liner assembly

--- --- B302105---101 1 Liner assy, above door

--- --- B302106---101 1 Liner assy, above door

--- --- B303102---101 1 Liner assembly

--- --- B303110---1 1 Shroud, door

--- --- B305101---101 1 Liner assembly

--- --- B305102---101 1 Liner assembly

--- ---

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 114 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PART NUMBER NOTES ALTERNATE PARTS NAME QUANTITY
B305103---101 1 Liner assembly

--- --- B305104---101 1 Duct

--- --- B305111---101 1 Angle, floor

--- --- B305112---101 1 Angle, floor

--- --- B305113---101 1 Duct skirt, bulkhead

--- --- B305121---101 1 Liner assembly

--- --- B305122---101 1 Liner assembly

--- --- B305123---101 1 Liner assembly

--- --- B306101---101 1 Cover, tie rod

--- --- B306102---101 1 Cover, tie rod

--- --- B306103---101 1 Cover, tie rod

--- --- B306103---102 1 Cover, tie rod

--- --- B306104---101 1 Cover, tie rod

--- --- B306105---101 1 Cover, tie rod

--- --- B306106---101 1 Cover, tie rod

--- --- B306111---101 1 Angle, 9G bulkhead

--- --- B306112---101 1 Angle, 9G bulkhead

--- --- B306113---101 1 Angle, 9G bulkhead

--- --- B306114---101 1 Angle, 9G bulkhead

--- --- B306115---101 1 Angle, 9G bulkhead

--- --- B306116---101 1 Angle, 9G bulkhead

--- --- B306117---101 1 Angle, 9G bulkhead

--- --- B306118---101 1 Angle, 9G bulkhead

--- ---

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 115 of 122 Jul 21 /2011 Revision A, Sept 01/2011 KIT 601R25 ---187K351
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
B303101---103 1 Liner assy, ceiling

--- ---
KIT 601R25 ---187K352
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
B303101---101 1 Liner assy, ceiling

--- ---
KIT 601R25 ---187K353
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
B303011---101 1 Strip assy, top

--- ---
KIT 601R25 ---187K354
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
B303011---103 1 Strip assy, top

--- ---
KIT 601R25 ---187K355
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
B303601---103 1 Duct assy, plenum

--- ---
KIT 601R25 ---187K356
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
B303601---101 1 Duct assy, plenum

--- ---

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 116 of 122 Jul 21 /2011 Revision A, Sept 01/2011 B. Consumable Information The materials that follow are necessary to do this service bulletin and can be ordered from Bombardier or purchased directly from industry sources. If the material is ordered from Bombardier, there can be some lead time because of shelf life of the material. CONSUMABLES SPECIFICATION QUANTITY NAME REFERENCE MMS---01---001, Type 1 (2.0 in. (5.1 cm) wide) As necessary Tape, pressure sensitive 05---144¡
TAFB101---006S As necessary Sealant, firewall © CMS 532---02 Typ I As necessary Potting compound

--- RTV 106 As necessary Sealant, adhesive 08---015¡ ¡Refer to AMM 51---31---00---990---801. ©Refer to paragraph 1.G.(2) of this service bulletin.

NOTE: To complete this list of consumables, refer to the different tasks and the C&D Zodiac service bulletins given as references in this service bulletin C. Special Tools and Equipment For a list of special tools and equipment, refer to the different tasks and the C&D Zodiac service bulletins given as references in this service bulletin. D. Disposition of Parts The table that follows shows the disposition of installed parts on the aircraft (or spares), and the relation of installed parts (or spares) to the new parts to be installed with this service bulletin.
PRE ---SB PART NUMBER NAME QTY DC POST ---SB PART NUMBER NAME

601R31668---241 Floor panel assembly 1 RWKK601R45034---2053 Floor panel assembly 601R31668---243 Floor panel assembly 1 RWKK601R45034---2055 Floor panel assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 117 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER DC QTY NAME

601R31668---245 Floor panel assembly 1 RWKK601R45034---2051 Floor panel assembly 601R31668---247 Floor panel assembly 1 RWKK601R45034---2057 Floor panel assembly 601R31668---249 Floor panel assembly 1 RWKK601R45034---2059 Floor panel assembly 601R31668---273 Floor panel assembly 1 RWKK601R45034---2063 Floor panel assembly 601R31668---275 Floor panel assembly 1 RWKK601R45034---2065 Floor panel assembly 601R31668---277 Floor panel assembly 1 RWKK601R45034---2061 Floor panel assembly 601R31668---279 Floor panel assembly 1 RWKK601R45034---2067 Floor panel assembly 601R31668---281 Floor panel assembly 1 RWKK601R45034---2069 Floor panel assembly 601R31668---323 Floor panel assembly 1 RWKK601R45034---2077 Floor panel assembly 601R31668---325 Floor panel assembly 1 RWKK601R45034---2071 Floor panel assembly 601R31668---333 Floor panel assembly 1 RWKK601R45034---2075 Floor panel assembly 601R31668---345 Floor panel assembly 1 RWKK601R45034---2073 Floor panel assembly 601R31668---361 Floor panel assembly 1 RWKK601R45034---2079 Floor panel assembly 601R31668---495 Floor panel assembly 1 RWKK601R45034---2087 Floor panel assembly 601R31668---497 Floor panel assembly 1 RWKK601R45034---2081 Floor panel assembly 601R31668---499 Floor panel assembly 1 RWKK601R45034---2085 Floor panel assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 118 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER DC QTY NAME

601R31668---501 Floor panel assembly 1 RWKK601R45034---2083 Floor panel assembly 601R31668---503 Floor panel assembly 1 RWKK601R45034---2089 Floor panel assembly 601R31668---9037 Floor panel assembly 1 RWKK601R45034---2097 Floor panel assembly 601R31668---9063 Floor panel assembly 1 RWKK601R45034---2107 Floor panel assembly 601R45103---13 Clip 1 RWKK601R45034---2019 Clip 601R45103---19 Clip 1 RWKK601R45034---2025 Clip 601R45103---29 Clip 1 RWKK601R45034---2027 Clip 601R45103---33 Clip 1 RWKK601R45034---2021 Clip 601R45103---35 Clip 1 RWKK601R45034---2023 Clip 601R45552---5 Channel assembly 1 RWKK601R45034---2007 Channel assembly 601R45552---15 Channel assembly 1 RWKK601R45034---2001 Channel assembly 601R45552---59 Channel assembly 1 RWKK601R45034---2003 Channel assembly 601R45552---125 Channel assembly 1 RWKK601R45034---2005 Channel assembly 601R45105---15 Channel assembly 1 RWKK601R45034---2009 Channel assembly 601R45105---21 Channel assembly 1 RWKK601R45034---2013 Channel assembly 601R45102---117 Channel assembly 1 RWKK601R45034---2011 Channel assembly 601R45102---131 Channel assembly 1 RWKK601R45034---2015 Channel assembly 601R45102---963 Channel assembly 1 RWKK601R45034---2017 Channel assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 119 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER DC QTY NAME
601R45552---23 or ---951 or ---955 Channel assembly 1 RWKK601R45034---2029 Channel assembly 601R96385---19 or ---27 or ---35 Duct, plenum 1 DIS B303601---101 or ---103 Duct, plenum
601R96383---7 Screen, exhaust duct 1 DIS

--- --- BR7203---804 Light, cargo 2 DIS BR7203---804---1 Light, cargo 601R520701---9 Gasket 2 DIS

--- --- 601R45553---1 Liner assembly 1 DIS B302103---101 Liner assembly 601R45553---3 or ---15, or ---25 or ---29 or ---2501 Liner assembly 1 DIS B302102---101 Liner assembly 601R455532---5 or ---17 or ---25 or ---35 or 601R45561---1 Liner assembly 1 DIS B303102---101 Liner assembly 601R455532---1 or ---7 or ---11 or ---13 or ---15 or ---21 or ---2501 or 601R45560---1 Liner assembly 1 DIS B303101---101 or ---103 Liner assembly

601R45553---13 or ---17 or ---27 or 601R45562---1 Liner assembly 1 DIS B302104---101 Liner assembly 601R455532---3 or ---9 or ---23 or ---2519 Liner assembly 1 DIS B302101---101 Liner assembly 601R45158---11 or ---15 or ---21 or 601R45565---3 or K601R45001---7 Tie-rod cap assembly 1 DIS B306104---101 Tie-rod cap assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 120 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER DC QTY NAME
601R45158---3 or ---5 or ---17 or ---19 or 601R45565---1 or K601R45001---5 Tie-rod cap assembly 1 DIS 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 1 DIS B306105---101 Tie-rod cap assembly
601R45554---1 or ---13 or 601R45563---1 or K601R45001---3 Tie-rod cap assembly 1 DIS B306101---101 Tie-rod cap assembly
601R45554---5 or ---11 or 601R45567---1 or K601R45001---11 Tie-rod cap assembly 1 DIS B306106---101 Tie-rod cap assembly
601R45152---11 or 601R45400---977 Liner assembly 1 DIS B305103---101 Liner assembly 601R45152---9 or ---19 or ---2501 or 601R45400---955 or ---965 Liner assembly 1 DIS B305102---101 Liner assembly
601R45152---13 or 601R45400---981 Liner assembly 1 DIS B305101---101 Liner assembly 601R45401---7 or ---9 or ---11 or 601R45400---971 or ---973 Angle assembly 1 DIS B305113---101 Angle assembly
601R45152---15 or ---21 or 601R45400---967 Angle assembly 1 DIS B305111---101 Angle assembly 601R45152---17 or ---23 or 601R45400---969 Angle assembly 1 DIS B305112---101 Angle assembly

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 121 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER DC QTY NAME
601R45401---5 or ---13 Duct assembly 1 DIS B305104---101 Duct assembly 601R45154---5 or ---13 or IS601R25520054---5 Protection barrier 1 DIS B305123---101 Liner assembly 601R45154---3 or ---9 or ---17 or IS601R25520054---3 Protection barrier 1 DIS 601R45154---21 FPC foam sheet 601R45154---7 or ---15 or IS601R25520054---7 Protection barrier 1 DIS B305122---101 Liner assembly 601R45154---1 or ---11 or ---19 or 601R45400---955 or IS601R25520054---1 Protection barrier 1 DIS B305121---101 Liner assembly
601R45451---1 or ---7 or 601R45350---971 Shroud, door 1 DIS B303110---1 Shroud, door
601R45451---3 or 601R45350---965 Liner assembly 1 DIS B302105---101 Liner assembly 601R45451---5 or 601R45350---967 Liner assembly 1 DIS B302106---101 Liner assembly 601R45555---3 or ---7 or 9 or ---13 or ---17 or ---19 or 31 Cap assembly 4 DIS

--- --- 601R45556---1 or ---3 or ---5 or ---9 Extrusion 2 DIS

--- --- 601R45151---17 or ---27 Panel 1 DIS

--- --- 601R45274---3 or ---5 or ---7 or ---9 or ---11 or ---951 Cap assy, cargo net 1 DIS

--- --- 601R45274---1 and 601R45104---1 Cap assy and retainer 1 DIS

--- ---

### SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187 Page 122 of 122 Jul 21 /2011 Revision A, Sept 01/2011 PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER DC QTY NAME
601R45271---1 or ---3 Post 1 DIS

--- --- 601R45276---1 or ---9 or ---13 Fitting assy 1 DIS

--- --- 601R35224---23 Shim 1 DIS

--- --- 601R45103---43 Clip 1 DIS

--- --- 601R45551---951 or 601R45552---19 or ---67 Channel assembly 1 DIS 601R45552---71 Channel assembly Disposition code (DC): DIS: Discard Part. RWK: Rework part as shown in this service bulletin. 1THANK YOU FOR ANSWERINGTHIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATIONFORM/COMPLIANCE SHEET, FAX TO 450-476-7300 

### SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET (YOUR IDEAS WILL HELP USPROVIDE BETTER BULLETINS)
SERVICE BULLETIN:601R-25-187 ISSUE:A

STRONGLY DISAGREE NEUTRAL AGREE STRONGLY DISAGREE AGREE
• Instructions to do the Service Bulletin were accurate. Comments: 

##     

• Illustration(s), figure(s), picture(s) and/or kit drawing(s) were helpful to carry out instructions. Comments: 

##     

• If a parts kit was required, did the kit contents received agree with the contents listed in the bulletin? Comments: 

##     

• Aircraft hands-on work was accomplished in estimated time. Comments: 

##     

• Overall, I was satisfied with this Service Bulletin. Comments: 

##     

PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: OPERATOR: NAME (Please print) SERVICE CENTER: TELEPHONE: AIRCRAFT SERIAL NO.: FACSIMILE: DATE OF SB INCORPOARTION