SB 601R---25---187

Page 1 of 1

Sept 01/2011

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CL ---600 ---2B19 Canadair Regional Jet (CRJ) Aircraft

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

SUBJECT: Equipment/Furnishing --- Cargo Compartment Linings --- Replacement of

Liners in the Cargo Compartment (North American Configuration)

This page transmits:

Revision A of Service Bulletin 601R --- 25 --- 187,

pages 1 thru 122, dated Sept 01/2011

The changes in this revision have no effect on aircraft that have

incorporated a previous issue of this service bulletin.

Reason:

Revised Planning Information, paragraph 1., to:

Change the aircraft affected in service and to add a note.

Revised Accomplishment Instructions, paragraph 2., to:

Add and change some steps and figures.

Revised Material Information, paragraph 3., to:

Change kit 601R25---187K2.

This revision also includes small editorial changes that do not have an effect on the technical

content.

Instructions:

Discard the copy of Service Bulletin 601R --- 25 --- 187, dated Jul 21/2011. Replace with the

copy attached.

KEEP C&D ZODIAC SERVICE BULLETINS B301002---25---01, B301002---25---02, AND

4652005---25---01.

Service Bulletin History:

Initial issue, dated Jul 21/2011.

1
SB 601R---25---187

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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) Aircraft Affected:

Service Bulletin: CL ---600---2B19 Canadair Regional Jet (CRJ) Aircraft Serial

Numbers 7003 thru 7067 and 7069 thru 7857 that have a

North American lining installation in the cargo compartment.

NOTE: To find out if your aircraft has a North American lining

installation in the cargo compartment and if this

service bulletin is applicable to your aircraft, refer to

Figure 1 of this service bulletin.

NOTE: The procedure in this service bulletin was validated on aircraft with serial

number 7362.

Production: This change will be incorporated before delivery on Aircraft

Serial Numbers 7858 and subsequent.

NOTE: The instructions in this service bulletin are only applicable to the

systems and parts installed at the time of delivery of the aircraft or as

changed by Bombardier Service Bulletin(s). Before you do this

bulletin, examine all STC, STA or equivalent action changes to make

sure this bulletin can be completed.
SERVICE BULLETIN 601R---25 ---187

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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

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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.
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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

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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

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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

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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)
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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 panelassembly

601R31668---243 Floor panel

assembly K601R45034---2055 Floor panelassembly

601R31668---245 Floor panel

assembly K601R45034---2051 Floor panelassembly

601R31668---247 Floor panel

assembly K601R45034---2057 Floor panelassembly

601R31668---249 Floor panel

assembly K601R45034---2059 Floor panelassembly

601R31668---273 Floor panel

assembly K601R45034---2063 Floor panelassembly

601R31668---275 Floor panel

assembly K601R45034---2065 Floor panelassembly

601R31668---277 Floor panel

assembly K601R45034---2061 Floor panelassembly

601R31668---279 Floor panel

assembly K601R45034---2067 Floor panelassembly

601R31668---281 Floor panel

assembly K601R45034---2069 Floor panelassembly

601R31668---323 Floor panel

assembly K601R45034---2077 Floor panelassembly

601R31668---325 Floor panel

assembly K601R45034---2071 Floor panelassembly

601R31668---333 Floor panel

assembly K601R45034---2075 Floor panelassembly

601R31668---345 Floor panel

assembly K601R45034---2073 Floor panelassembly

601R31668---361 Floor panel

assembly K601R45034---2079 Floor panelassembly
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Revision A, Sept 01/2011

PRE ---SB

PART NUMBER NAME POST ---SBPART NUMBER NAME

601R31668---495 Floor panel

assembly K601R45034---2087 Floor panelassembly

601R31668---497 Floor panel

assembly K601R45034---2081 Floor panelassembly

601R31668---499 Floor panel

assembly K601R45034---2085 Floor panelassembly

601R31668---501 Floor panel

assembly K601R45034---2083 Floor panelassembly

601R31668---503 Floor panel

assembly K601R45034---2089 Floor panelassembly

601R31668---9037 Floor panel

assembly K601R45034---2097 Floor panelassembly

601R31668---9063 Floor panel

assembly K601R45034---2107 Floor panelassembly

601R45103---13 Clip K601R45034---2019 Clip

601R45103---19 Clip K601R45034---2025 Clip

601R45103---29 Clip K601R45034---2027 Clip

601R45103---33 Clip K601R45034---2021 Clip

601R45103---35 Clip K601R45034---2023 Clip

601R45552---5 Channel

assembly K601R45034---2007 Channelassembly

601R45552---15 Channel

assembly K601R45034---2001 Channelassembly

601R45552---19 or ---67

or 601R45551---951

Channel

assembly 601R45552---71 Channelassembly

601R45552---23

or ---951 or 955

Channel

assembly K601R45034---2029 Channelassembly

601R45552---59 Channel

assembly K601R45034---2003 Channelassembly

601R45552---125 Channel

assembly K601R45034---2005 Channelassembly
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Revision A, Sept 01/2011

PRE ---SB

PART NUMBER NAME POST ---SBPART NUMBER NAME

601R45105---15 Channel

assembly K601R45034---2009 Channelassembly

601R45105---21 Channel

assembly K601R45034---2013 Channelassembly

601R45102---117 Channel

assembly K601R45034---2011 Channelassembly

601R45102---131 Channel

assembly K601R45034---2015 Channelassembly

601R45102---963 Channel

assembly K601R45034---2017 Channelassembly

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 capassembly
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Revision A, Sept 01/2011

PRE ---SB

PART NUMBER NAME POST ---SBPART 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 capassembly

601R45554---1 or ---13 or

601R45563---1 or

K601R45001---3

Tie rod cap

assembly B306101---101 Tie rod capassembly

601R45554---5 or ---11 or

601R45567---1 or

K601R45001---11

Tie rod cap

assembly B306106---101 Tie rod capassembly

601R45152---11 or

601R45400---977 Liner assembly B305103---101 Liner assembly

601R45152---9 or ---19 or

---2501 or

601R45400---955 or

---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 Foamsheet
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Revision A, Sept 01/2011

PRE ---SB

PART NUMBER NAME POST ---SBPART 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
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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
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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
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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
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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
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Revision A, Sept 01/2011

CB PANEL ZONE CB NO. NAME

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.
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Revision A, Sept 01/2011

Refer to Figure 4 (Sheet 2 of 14).

(7) Remove and discard the support assembly between the liner assembly (18)

and the structure at FS621.00, WL80.0, RBL47.0.

Refer to Figure 4 (Sheet 1 of 14).

(8) Remove the cargo compartment rear bulkhead linings and record the

installation locations of the channel assemblies on the pressure bulkhead

(Refer to AMM 25---52---01---000---802).

(9) Remove the cargo smoke detector (Refer to AMM 26---15---01---000---801).

(10) Remove the cargo lights (Refer to AMM 33---31---01---000---801).

(11) Remove the fire extinguisher discharge-line

(Refer to AMM 26---25---07---000---801).

For aircraft that have holes in the pressure bulkhead and that do not have Modification

Summary IS601R25520054 incorporated

Refer to Figure 2 (Sheet 1 of 3).

(12) Remove and discard the liner assemblies (1), (2), and (3) and the FPC foam

sheet (4) on the rear pressure bulkhead as follows:

(a) Remove the blind rivets (6) (Refer to SRM 51---42---10).

(b) Remove the washers (5).

(c) Remove the liner assemblies (1), (2), and (3) and the FPC foam sheet (4)

from the rear pressure bulkhead.

For aircraft that have Modification Summary IS601R25520054 incorporated

Refer to Figure 2 (Sheet 2 of 3).

(13) Remove and discard the liner assemblies (1), (2), and (3) and the FPC foam

sheet (4) from the rear pressure bulkhead as follows:

(a) Remove the screws (6) and the washers (5).

(b) Remove the liner assemblies (1), (2), and (3) and the FPC foam sheet (4)

from the rear pressure bulkhead.

CAUTION: DO NOT USE METAL SCRAPERS OR OTHER SHARP TOOLS TO

REMOVE SEALANT. METAL SCRAPERS OR SHARP TOOLS CAN

CAUSE STRUCTURAL DAMAGE TO THE AIRCRAFT SURFACE.

(c) Remove the fillet of sealant with a non-metallic scraper around the FPC

foam sheet (4).

(d) Remove the FPC foam sheet (4) from the rear pressure bulkhead.
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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).
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For all aircraft

(17) Remove the floor panels that follow (Refer to AMM 53---01---01---000---804):

ACCESS DESIGNATION

281LLF Access Panel

281JLF Access Panel

281DLF Access Panel

282GRF Access Panel

282KRF Access Panel

(18) If necessary, remove the baggage bay door

(Refer to AMM 52---31---00---000---801).

(19) If necessary, remove the left discharge duct

(Refer to AMM 21---51---15---000---801).

Refer to Figure 16.

(20) Remove the ground connection duct (1) as follows:

WARNING: BEFORE YOU DISCONNECT A PNEUMATIC DUCT COUPLING, MAKE

SURE THAT YOU RELEASE PRESSURE FROM THE MANIFOLD AND

THAT THE COMPONENTS ARE COOL. IF YOU DO NOT DO THIS YOU

CAN CAUSE INJURIES TO PERSONS.

(a) Loosen the coupling nut on the lower coupling (3) and remove it from

the adaptor and the duct (1).

(b) Remove the silicone tape from around the boot (2) which covers the

upper coupling (3) on the duct (1).

(c) Remove the boot (2).

(d) Loosen the coupling nut and remove the upper coupling (3) from the

duct (1) and the bleed air duct.

(e) Put protective covers on the open ducts and on the flange of the

adaptor.
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(21) Remove the cooler duct (Refer to AMM 49---52---01---000---801).

(22) Remove the APU ECU (Refer to AMM 49---61---01---000---801).

(23) Remove the radio altimeter (Refer to AMM 34---44---01---000---801).

(24) Remove the radio altimeter converter (Refer to AMM 34---44---04---000---801).

Refer to Figure 15.

(25) Remove the mounting trays (3), (4), and (8) as follows:

(a) Remove the electrical connector from the mounting tray of the converter

(4).

(b) Remove the screws (5) and the washers (6) from the mounting tray (4) of

the converter.

(c) Remove the screws (7) from the mounting tray of the radio altimeter (3).

(d) Remove the electrical connector from the mounting tray of the ECU (8).

(e) Remove the screws (9), the washers (10), and the nut (11) from the ECU

mounting tray of the ECU (8).

(f) Remove the mounting trays (4), (3), and (8) from the structure.

(26) If necessary, at FS672.20/STGR16, remove the bracket (1) from the frame as

follows:

(a) Remove eight rivets (2) from the bracket (1) and the frame.

(b) Carefully move the bracket (1) along the frame.

(c) Make sure that you do not damage the wire bundle attached to the

bracket (1).

(27) Remove the APU fire extinguisher (Refer to AMM 26---22---07---000---801).
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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
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For all aircraft

Refer to Figure 5 (Sheet 2 of 7)

(10) Near FS 621.00, at STGR6R and STGR7R, cut the clips (3) and (5) as follows:

(a) Near FS621.00 and STGR6R, remove the rivets from the channel and the

clip (3).

(b) Near FS621.00 and STGR7R, remove the rivets from the channel and the

clip (5).

(c) Make a line on the clip (3) with a marker at 1.00 in. (25.4 mm) from the

mating surface of the clip (3) and the channel.

(d) Make a line on the clip (5) with a marker at 1.00 in. (25.4 mm) from the

mating surface of the clip (5) and the channel.

(e) Cut the clips (3) and (5) at the marked locations.

(f) Remove the sharp edges.

(g) Apply chemical conversion coating on the bare metal areas.

(h) Install the rivets (1) in the holes in the two channels.

(i) Apply fluid-resistant primer on the bare metal areas and the rivets (1).

(j) Apply polyurethane topcoat on the bare metal areas and the rivets (1).

(k) With a permanent ink pen or equivalent, identify the clip (3) as

K601R45034---2021.

(l) With a permanent ink pen or equivalent, identify the clip (5) as

K601R45034---2023.
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Refer to Figure 5 (Sheet 3 of 7).

(11) Between FS559.00+80---FS559+96 and STGR3R, cut the channel (6) as

follows:

(a) Make a line on the channel (6) with a marker at 8.45 in. (214.6 mm) from

the forward end of the channel (6) (Refer to View H).

(b) Cut the channel (6) at the marked location.

(c) Remove the sharp edges.

(d) Apply chemical conversion coating on the bare metal areas.

(e) Apply fluid-resistant primer on the bare metal areas.

(f) Apply polyurethane topcoat on the bare metal areas.

(g) With a permanent ink pen or equivalent, identify the channel (6) as

K601R45034---2007.

(12) Near FS 621.00, at STGR3R, cut the clip (4), as follows:

(a) Remove the two rivets from the channel and the clip (4).

(b) Make a line on the clip (4), with a marker, at 1.00 in. (25.4 mm) from the

mating surface of the clip (4) and the channel (Refer to Views F and G).

(c) Cut the clip (4) at the marked location.

(d) Remove the sharp edges.

(e) Apply chemical conversion coating on the bare metal areas.

(f) With a permanent ink pen or equivalent, identify the clip (4) as

K601R45034---2019.

(g) Near FS621.00 at STGR3R, install the rivets (1) in the holes in the

channel.

(h) Apply fluid-resistant primer on the bare metal areas and the rivets (1).

(i) Apply polyurethane topcoat on the bare metal areas and the rivets (1).
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For Aircraft 7003 ---7293

Refer to Figure 5 (Sheet 4 of 7).

(13) At FS605.00, FS589.00, and FS574.00, and STGR0, remove and discard the

rivets and the channel (15) from the three clips (Refer to View K).

For all aircraft

(14) At FS621.00 and STGR0, remove and discard the clip (17) from the structure

(Refer to View L).

(15) Near FS621.00 and STGR0, install the rivets (16) in the holes in the structure

(Refer to View L).

(16) Apply fluid-resistant primer on the aluminum bare metal areas and the rivets

(16).

(17) Apply polyurethane topcoat on the aluminum bare metal areas and the rivets

(16).

For Aircraft 7003 ---7293

Refer to Figure 5 (Sheet 5 of 7).

(18) Between FS559.0+96 and FS574.00, at STGR0, remove the channel (7) from

the clips (13) and (14) (Refer to View L).

(19) At FS 559.0+112 and STGR0.0 remove and discard the clip (14) from the

frame (Refer to View L).

(20) At FS 559.0+96 and STGR0.0 remove and discard the clip (13) from the

frame.

(21) At FS559.00+112 and FS559.00+96, install the rivets (8) in the holes in the

frames (Refer to View N).

(22) Make a line on the channel (7) with a marker at 22.33 in. (567.2 mm) from the

aft end of the channel (7) (Refer to View P).

(23) Cut the channel (7) at the marked location.

(24) Remove the sharp edges.

(25) Apply chemical conversion coating to the aluminum bare metal areas.
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(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).
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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).
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(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).
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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).
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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.
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(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).
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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).
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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

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(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

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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

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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

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(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

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(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

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(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

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(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

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(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

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(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

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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

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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

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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

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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

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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

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(d) Install the channel assemblies, removed before, on the liner assembly

(8).

(e) Install the liner assembly (8) with the washers (14) and screws (10).

(f) Install the channel assemblies, removed before, on the liner assembly

(7).

(g) Install the liner assembly (7) with the washers (14) and screws (11).

(h) Apply TAFB101---006S firewall-sealant around the fastener holes in the

liner assemblies (6), (7), and (8) that have been made larger, if the

washer (14) does not fully cover the fastener holes (Refer to AMM

51---23---00---390---807).

(i) Apply a fillet seal of RTV 106 sealant around the liner assemblies (6), (7),

and (8) (Refer to AMM 51---22---28---340---801).

(97) Do the steps that follow to install the floor angles (3) and (4):

(a) At eight places, install the washers (14) and the bolts (5) that hold the

forward flange of the floor angles (4) and (3) to the compartment floor.

(b) At 10 places, install the washers (15) and the bolts (13) that hold the aft

flange of the floor angles (4) and (3) to the compartment floor.

(c) Install the washers (14) and the screws (11) that hold the floor angle (4)

to the bulkhead panel (6).

(d) Install the washers (14) and the screws (11) and (12) that hold the floor

angle (3) to the bulkhead panels (6), (7) and (8).

(e) Apply a fillet seal of RTV 106 sealant around the floor angles (3) and (4)

(Refer to AMM 51---22---28---340---801).

(98) Install the duct skirt (2) to the compartment floor with the washers (15) and the

bolts (13).

(99) Install the angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42) on

the 9G bulkhead as follows:

(a) Install the angle assemblies (35), (36), (37), (38), (39), (40), (41), and

(42) on the 9G bulkhead with the screws (33) and the washers (14).

(b) Apply a fillet seal of RTV 106 sealant around the inboard edge of the

angle assemblies (35), (36), (37), (38), (39), (40), (41), and (42)

(Refer to AMM 51---22---28---340---801).
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

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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

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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

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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

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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

REF

rsb601r25187_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

1

rsb601r25187_043, sc, 03/2011

1. Liner assembly.

LEGEND

5. Washer.

2. Liner assembly.

3. Liner assembly.

4. SPC foam sheet.

6. Blind rivet.

FS621.00

5

6

5

6

5

6

5

6
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

6

5

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

FS574.00 FS621.00

BL0.00

17 19 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.

ITEM NAME PART NUMBER

34 MS27039--1--11 Screw

33

14

12

14

MS27039--1--10

B0202013S1328--63

Screw

Washer

Screw MS27039--1--09

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

FS559.00 +82.00 FS621.00

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 Screw MS27039--1--11

14 Washer B0202013S1328--63

33 Screw MS27039--1--09

14 Washer B0202013S1328--63

44 Clip Nut SL215--3--1

ITEM NAME PART NUMBER

33

14

12

14

MS27039--1--10

B0202013S1328--63

Screw

Washer

Screw MS27039--1--09

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.

ITEM NAME PART NUMBER

34 Screw MS27039--1--11

33

14

12

14

MS27039--1--10

B0202013S1328--63

Screw

Washer

Screw MS27039--1--09

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

ITEM NAME PART NUMBER

34 MS27039--1--11 Screw

33

14

12

14

MS27039--1--10

B0202013S1328--63

Screw

Washer

Screw MS27039--1--09

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.

J TYPICAL 5 PLACES

LINER ASSEMBLY (REF)

30

29

8

8

On aircraft that have

a load divider.

NOTE

8

43 Screw MS27039--1--12

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

33

12

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

36

52

35

M 20

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

33

12

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

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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

WASHER (REF)

(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

ITEM NAME PART NUMBER 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

Screw MS27039--1--09

Washer B0202013S1328--63

34 Screw MS27039--1--11

14 Washer B0202013S1328--63

43 Screw MS27039--1--12

14 Washer B0202013S1328--63

54

14

MS27039--1--07

B0202013S1328--63

Screw

Washer

55

14

MS21042L3

B0202013S1328--63

Nut

Washer

ITEM PART NUMBER 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

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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

RIVET (REF) 1

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)

B PRE--MOD

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 PRE--MOD D POST--MOD

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

RIVET (REF) 1

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

STGR0

STGR3L

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

1 3

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

FS621.00

FS574.00

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)

L

rsb601r25187_056.cgm

CLIP

(REF)

CLIP

(REF)

CLIP

(REF)

FS605.00

FS589.00

FS574.00

FS621.00

FS621.00

FS574.00

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 FS589.00

FS574.00

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 7L

STGR 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 7L

STGR 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

STGR 8L F

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

5 12

2.78 in.

(70.6 mm)

J

FS605.00

4 11

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 8

rsb601r25187_037.cgm,sc,nov 9 2010

ITEM NAME PART NUMBER

3

4

2 Rivet CR4173--4--01

Screw NAS623--2--2

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

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

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.

C TYPICAL 4 PLACES

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

2

rsb601r25187_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

A

rsb601r25187_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)

D

rsb601r25187_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 12

rsb601r25187_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 13

rsb601r25187_047.dg, sc, 7Mar 2011

FS559.00

+93.80

FS559.00

+ 87.00

STRG 15

FITTING (REF)

3

2

1

3 4

FITTING (REF) 4

3

1

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 14

rsb601r25187_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 15

rsb601r25187_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

3

rsb601r25187_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 17

rsb601r25187_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

FS587.79 FS595.75 FS603.30 FS611.50

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 01/2011

Application of TAFB101 ---006S Sealant

Figure 18 (Sheet 1 of 2)

FS589.00

FS574.00

FS605.00

NOTE

Sealant TAFB101--006S

around edges.

1

FS621.00

rsb601r25187_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 01/2011

Application of TAFB101 ---006S Sealant

Figure 18 (Sheet 2 of 2)

NOTE

Sealant TAFB101--006S

around edges.

1

rsb601r25187_054.cgm

C

1

PULLEY

BOX

(REF) C

D

D

1

E

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

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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

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Page 109 of 122

Jul 21 /2011

Revision A, Sept 01/2011

CB PANEL ZONE CB NO. NAME

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

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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

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Page 112 of 122

Jul 21 /2011

Revision A, Sept 01/2011

PART NUMBER NOTES ALTERNATE

PARTS QUANTITY NAME

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

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Page 113 of 122

Jul 21 /2011

Revision A, Sept 01/2011

PART NUMBER NOTES ALTERNATE

PARTS QUANTITY NAME

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 QUANTITY NAME

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 RWK K601R45034---2053 Floor panelassembly

601R31668---243 Floor panel

assembly 1 RWK K601R45034---2055 Floor panelassembly
SERVICE BULLETIN 601R---25 ---187

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Page 117 of 122

Jul 21 /2011

Revision A, Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R31668---245 Floor panel

assembly 1 RWK K601R45034---2051 Floor panelassembly

601R31668---247 Floor panel

assembly 1 RWK K601R45034---2057 Floor panelassembly

601R31668---249 Floor panel

assembly 1 RWK K601R45034---2059 Floor panelassembly

601R31668---273 Floor panel

assembly 1 RWK K601R45034---2063 Floor panelassembly

601R31668---275 Floor panel

assembly 1 RWK K601R45034---2065 Floor panelassembly

601R31668---277 Floor panel

assembly 1 RWK K601R45034---2061 Floor panelassembly

601R31668---279 Floor panel

assembly 1 RWK K601R45034---2067 Floor panelassembly

601R31668---281 Floor panel

assembly 1 RWK K601R45034---2069 Floor panelassembly

601R31668---323 Floor panel

assembly 1 RWK K601R45034---2077 Floor panelassembly

601R31668---325 Floor panel

assembly 1 RWK K601R45034---2071 Floor panelassembly

601R31668---333 Floor panel

assembly 1 RWK K601R45034---2075 Floor panelassembly

601R31668---345 Floor panel

assembly 1 RWK K601R45034---2073 Floor panelassembly

601R31668---361 Floor panel

assembly 1 RWK K601R45034---2079 Floor panelassembly

601R31668---495 Floor panel

assembly 1 RWK K601R45034---2087 Floor panelassembly

601R31668---497 Floor panel

assembly 1 RWK K601R45034---2081 Floor panelassembly

601R31668---499 Floor panel

assembly 1 RWK K601R45034---2085 Floor panelassembly
SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187

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Revision A, Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R31668---501 Floor panel

assembly 1 RWK K601R45034---2083 Floor panelassembly

601R31668---503 Floor panel

assembly 1 RWK K601R45034---2089 Floor panelassembly

601R31668---9037 Floor panel

assembly 1 RWK K601R45034---2097 Floor panelassembly

601R31668---9063 Floor panel

assembly 1 RWK K601R45034---2107 Floor panelassembly

601R45103---13 Clip 1 RWK K601R45034---2019 Clip

601R45103---19 Clip 1 RWK K601R45034---2025 Clip

601R45103---29 Clip 1 RWK K601R45034---2027 Clip

601R45103---33 Clip 1 RWK K601R45034---2021 Clip

601R45103---35 Clip 1 RWK K601R45034---2023 Clip

601R45552---5 Channel

assembly 1 RWK K601R45034---2007 Channelassembly

601R45552---15 Channel

assembly 1 RWK K601R45034---2001 Channelassembly

601R45552---59 Channel

assembly 1 RWK K601R45034---2003 Channelassembly

601R45552---125 Channel

assembly 1 RWK K601R45034---2005 Channelassembly

601R45105---15 Channel

assembly 1 RWK K601R45034---2009 Channelassembly

601R45105---21 Channel

assembly 1 RWK K601R45034---2013 Channelassembly

601R45102---117 Channel

assembly 1 RWK K601R45034---2011 Channelassembly

601R45102---131 Channel

assembly 1 RWK K601R45034---2015 Channelassembly

601R45102---963 Channel

assembly 1 RWK K601R45034---2017 Channelassembly
SERVICE BULLETIN 601R---25 ---187

SB 601R---25---187

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Jul 21 /2011

Revision A, Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R45552---23 or

---951 or ---955

Channel

assembly 1 RWK K601R45034---2029 Channelassembly

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 Linerassembly

601R45553---3 or

---15, or ---25 or

---29 or ---2501

Liner

assembly 1 DIS B302102---101 Linerassembly

601R455532---5 or

---17 or ---25 or ---35

or 601R45561---1

Liner

assembly 1 DIS B303102---101 Linerassembly

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 Linerassembly

601R455532---3 or

---9 or ---23 or

---2519

Liner

assembly 1 DIS B302101---101 Linerassembly

601R45158---11

or ---15 or ---21 or

601R45565---3 or

K601R45001---7

Tie-rod cap

assembly 1 DIS B306104---101 Tie-rod capassembly
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

POST ---SB NAME

PART NUMBER

NAME QTY DC

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 capassembly

601R45554---1 or

---13 or

601R45563---1 or

K601R45001---3

Tie-rod cap

assembly 1 DIS B306101---101 Tie-rod capassembly

601R45554---5 or

---11 or

601R45567---1 or

K601R45001---11

Tie-rod cap

assembly 1 DIS B306106---101 Tie-rod capassembly

601R45152---11 or

601R45400---977

Liner

assembly 1 DIS B305103---101 Linerassembly

601R45152---9 or

---19 or ---2501 or

601R45400---955 or

---965

Liner

assembly 1 DIS B305102---101 Linerassembly

601R45152---13 or

601R45400---981

Liner

assembly 1 DIS B305101---101 Linerassembly

601R45401---7 or

---9 or ---11 or

601R45400---971 or

---973

Angle

assembly 1 DIS B305113---101 Angleassembly

601R45152---15 or

---21 or

601R45400---967

Angle

assembly 1 DIS B305111---101 Angleassembly

601R45152---17 or

---23 or

601R45400---969

Angle

assembly 1 DIS B305112---101 Angleassembly
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

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R45401---5 or

---13

Duct

assembly 1 DIS B305104---101 Ductassembly

601R45154---5 or

---13 or

IS601R25520054---5

Protection

barrier 1 DIS B305123---101 Linerassembly

601R45154---3 or ---9

or ---17 or

IS601R25520054---3

Protection

barrier 1 DIS 601R45154---21 FPC foamsheet

601R45154---7 or

---15 or

IS601R25520054---7

Protection

barrier 1 DIS B305122---101 Linerassembly

601R45154---1 or

---11 or ---19 or

601R45400---955 or

IS601R25520054---1

Protection

barrier 1 DIS B305121---101 Linerassembly

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 Linerassembly

601R45451---5 or

601R45350---967

Liner

assembly 1 DIS B302106---101 Linerassembly

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

POST ---SB NAME

PART NUMBER

NAME QTY DC

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 Channelassembly

Disposition code (DC):

DIS: Discard Part.

RWK: Rework part as shown in this service bulletin.

1
THANK YOU FOR ANSWERING THIS EVALUATION FORM 

UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 

450-476-7300 

SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET 

(YOUR IDEAS WILL HELP US PROVIDE 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