SB 601R---25---198

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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 ---198

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

Liners in the Cargo Compartment (European 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

European lining installation in the cargo compartment.

NOTE: To find out if your aircraft has a European lining

installation in the cargo compartment and if this

service bulletin is applicable to your aircraft, refer to

Figure 1 of this service bulletin.

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.
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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 B301003---25---01 and B301003---25---02.

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 B301003---25---01 and B301003---25---02 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.
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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 B301003---25---01 and B301003---25---02.
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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---198K1 Structural Components, Baggage Bay

Liners --- European Configuration

601R25---198K350 Baggage Bay Liners --- European

Configuration

For aircraft that have a cargo-compartment load divider

KIT NUMBER NAME

601R25---198K351 Baggage Bay Liners --- European

Configuration

For aircraft that do not have a cargo-compartment load divider

KIT NUMBER NAME

601R25---198K352 Baggage Bay Liners --- European

Configuration

For aircraft that have Piccolo Tube P/N 601R99011 ---13

KIT NUMBER NAME

601R25---198K353 Baggage Bay Liners --- European

Configuration
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For aircraft that have Piccolo Tube P/N 601R99011 ---1 or ---9

KIT NUMBER NAME

601R25---198K354 Baggage Bay Liners --- European

Configuration

For aircraft post-service bulletin 601R ---21 ---059 or that have CR25 ---359 (Cargo

Compartment --- Temperature Control)

KIT NUMBER NAME

601R25---198K355 Baggage Bay Liners --- European

Configuration

For aircraft pre-service bulletin 601R ---21 ---059 or that do not have CR25 ---359 (Cargo

Compartment --- Temperature Control)

KIT NUMBER NAME

601R25---198K356 Baggage Bay Liners --- European

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
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(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 B301003---25---01 and B301003---25---02 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.
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I. Weight and Balance

WEIGHT ARM MOMENT ¡

20 lb 701.00 in. 14.020 (1000 lb---in.)

9.07 kg 17.81 m 0.1615 (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 TC601R17982, Revision D.

Restriction and/or Special Instruction (RSI) C ---A265, Revision A.

C&D Zodiac Service Bulletin B301003---25---01, dated Apr 19/11.

C&D Zodiac Service Bulletin B301003---25---02. Revision 1, dated Aug 31/11

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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M. Relationship Chart

PRE ---SB

PART NUMBER NAME POST ---SB

PART NUMBER NAME

601R31668---241 Floor panel

assembly K601R45035---2053 Floor panelassembly

601R31668---243 Floor panel

assembly K601R45035---2055 Floor panelassembly

601R31668---245 Floor panel

assembly K601R45035---2051 Floor panelassembly

601R31668---247 Floor panel

assembly K601R45035---2057 Floor panelassembly

601R31668---249 Floor panel

assembly K601R45035---2059 Floor panelassembly

601R31668---273 Floor panel

assembly K601R45035---2063 Floor panelassembly

601R31668---275 Floor panel

assembly K601R45035---2065 Floor panelassembly

601R31668---277 Floor panel

assembly K601R45035---2061 Floor panelassembly

601R31668---279 Floor panel

assembly K601R45035---2067 Floor panelassembly

601R31668---281 Floor panel

assembly K601R45035---2069 Floor panelassembly

601R31668---323 Floor panel

assembly K601R45035---2077 Floor panelassembly

601R31668---325 Floor panel

assembly K601R45035---2071 Floor panelassembly

601R31668---333 Floor panel

assembly K601R45035---2075 Floor panelassembly

601R31668---345 Floor panel

assembly K601R45035---2073 Floor panelassembly

601R31668---361 Floor panel

assembly K601R45035---2079 Floor panelassembly
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PRE ---SB

PART NUMBER NAME POST ---SB

PART NUMBER NAME

601R31668---495 Floor panel

assembly K601R45035---2087 Floor panelassembly

601R31668---497 Floor panel

assembly K601R45035---2081 Floor panelassembly

601R31668---499 Floor panel

assembly K601R45035---2085 Floor panelassembly

601R31668---501 Floor panel

assembly K601R45035---2083 Floor panelassembly

601R31668---503 Floor panel

assembly K601R45035---2089 Floor panelassembly

601R31668---9037 Floor panel

assembly K601R45035---2097 Floor panelassembly

601R31668---9063 Floor panel

assembly K601R45035---2107 Floor panelassembly

601R45103---13 Clip K601R45035---2029 Clip

601R45103---19 Clip K601R45035---2111 Clip

601R45103---29 Clip K601R45035---2113 Clip

601R45103---33 Clip K601R45035---2031 Clip

601R45103---35 Clip K601R45035---2033 Clip

601R45552---17 Channel

assembly K601R45035---2105 Channelassembly

601R45552---13 Channel

assembly

K601R45035---2043 or

---2047 or ---2101

Channel

assembly

601R45552---59 Channel

assembly K601R45035---2003 Channelassembly

601R45552---125 Channel

assembly K601R45035---2001 Channelassembly

601R45105---15 Channel

assembly K601R45035---2011 Channelassembly

601R45105---21 Channel

assembly K601R45035---2015 Channelassembly
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PRE ---SB

PART NUMBER NAME POST ---SB

PART NUMBER NAME

601R45102---117 Channel

assembly K601R45035---2013 Channelassembly

601R45102---119 Channel

assembly K601R45035---2009 Channelassembly

601R45102---121 Channel

assembly K601R45035---2103 Channelassembly

601R45102---123 Channel

assembly

K601R45035---2041 or

---2109

Channel

assembly

601R45102---127 Channel

assembly K601R45035---2039 Channelassembly

601R45102---131 Channel

assembly K601R45035---2017 Channelassembly

601R45102---133 Channel

assembly

K601R45035---2021 or

---2025 or ---2035

Channel

assembly

601R45102---135 Channel

assembly

K601R45035---2045 or

---2049

Channel

assembly

601R45102---139 Channel

assembly K601R45035---2007 Channelassembly

601R45102---147 Channel

assembly K601R45035---2005 Channelassembly

601R45102---165 Channel

assembly

K601R45035---2023 or

---2027 or ---2037

Channel

assembly

601R45102---963 Channel

assembly K601R45035---2019 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

601R45151---1 Liner assembly B302123---101 Liner assembly

601R455532---19 or

601R45151---3 or ---23 or

---2506

Liner assembly B302122---101 Liner assembly
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PRE ---SB

PART NUMBER NAME POST ---SB

PART NUMBER NAME

601R45151---5 or

601R45570---1 Liner assembly B303122---101 Liner assembly

601R45151---13 or ---21

or ---2503 or

601R45571---1 or

601R45578---1

Liner assembly B303121---101 or ---103 Liner assembly

601R45151---15 or ---25

or 601R45572---1 Liner assembly B302124---101 Liner assembly

601R45151---11 or ---191

or ---2502 or ---2519 or

601R48946---1

Liner assembly B302121---101 Liner assembly

601R45573---1 or

601R45158---13 or

601R45554---23 or

K601R45002---9

Tie rod cap

assembly B306126---101 Tie rod capassembly

601R48901---1 or

601R45158---13 or

601R45554---23 or

K601R45002---9

Tie rod cap

assembly B306105---103 Tie rod capassembly

601R48902---1 or

601R45158---7 or ---33 or

K601R5002---7 or

601R45002---5 or

601R45158---3 or ---5 or

---31

Tie rod cap

assembly B306123---101 or ---105 Tie rod capassembly

601R48902---1 or

601R45002---5 or

601R45158---3 or ---5 or

---31

Tie rod cap

assembly B306123---103 Tie rod capassembly

601R48905---1 or

601R45002---3 or

601R45158---3 or ---29

Tie rod cap

assembly B306122---101 Tie rod capassembly

601R48903---1 or

601R45158---1 or

601R45554---21 or

601R45001---5

Tie rod cap

assembly B306121---101 Tie rod capassembly
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PRE ---SB

PART NUMBER NAME POST ---SB

PART NUMBER NAME

601R45152---11 or

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

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

---2501 or

601R45400---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 Liner 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

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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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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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---801 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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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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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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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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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 D---D).

(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 E).

(d) Remove the burrs and sharp edges.

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

(f) Install the blind nut assemblies (1) on the intercostal (2).
SERVICE BULLETIN 601R---25 ---198

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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 7.

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

WARNING: BEFORE YOU DISCONNECT A PNEUMATIC DUCT COUPLING, MAKE

SURE THAT YOU RELEASE PRESSURE FROM THE MANIFOLD AND

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

CAN CAUSE INJURIES TO PERSONS.

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

the adaptor and the duct (1).

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

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

(c) Remove the boot (2).

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

duct (1) and the bleed air duct.

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

adaptor.
SERVICE BULLETIN 601R---25 ---198

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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 converter mounting

tray (4).

(c) Remove the screws (7) from the radio altimeter mounting-tray (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 (8).

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

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

follows:

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

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

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

bracket (1).

(27) Remove the APU fire extinguisher (Refer to AMM 26---22---07---000---801).
SERVICE BULLETIN 601R---25 ---198

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B. Procedure

For Aircraft 7003 ---7310

Refer to Figure 5 (Sheet 1 of 8).

(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 --198

Incorporation

601R45103 ---19

or

601R45103 ---29

K601R45035 ---2111

or

K601R45035 ---2113
SERVICE BULLETIN 601R---25 ---198

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For all aircraft

Refer to Figure 5 (Sheet 2 of 8)

(10) Near FS 621.00, at STGR5R and STGR6R, cut the clips (3) and (5) as follows:

(a) Near FS621.00 and STGR5R, remove the rivets from the channel and the

clip (3).

(b) Near FS621.00 and STGR6R, 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

K601R45035---2031.

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

K601R45035---2033.
SERVICE BULLETIN 601R---25 ---198

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Refer to Figure 5 (Sheet 3 of 8).

(11) 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

K601R45035---2029.

(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).

Refer to Figure 5 (Sheet 4 of 8).

(12) At FS574.00, STGR3R, STGR5R, STGR6R, STGR9R, and STGR10R, cut the

channels (6), (7), (8), (9), and (10) as follows:

(a) Make a line on the channels (6), (7), (8), (9), and (10) with a marker at

0.36 in. (9.14 mm) from FS574.00 (Refer to View H)

(b) Cut the channels (6), (7), (8), (9), and (10) at the marked locations.

(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.
SERVICE BULLETIN 601R---25 ---198

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Sept 01/2011

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

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---147

or

601R45102 ---139

K601R45035 ---2005

or

K601R45035 ---2007

(g) With a permanent ink pen or equivalent, identify the channel (7) as

K601R45035 ---2009.

(h) With a permanent ink pen or equivalent, identify the channel (8) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---133

or

601R45102 ---165

K601R45035 ---2021

or

K601R45035 ---2023

(i) With a permanent ink pen or equivalent, identify the channel (9) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---133

or

601R45102 ---165

K601R45035 ---2025

or

K601R45035 ---2027
SERVICE BULLETIN 601R---25 ---198

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(j) With a permanent ink pen or equivalent, identify the channel (10) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---133

or

601R45102 ---165

K601R45035 ---2035

or

K601R45035 ---2037

Refer to Figure 5 (Sheet 6 of 8).

(13) At FS559+96, STGR6L, STGR7L, STGR9L, STGR10L, and STGR12L, cut the

channels (12), (13), (14), (15), and (16) as follows:

(a) Make a line on the channels (12), (13), (14), (15), (16), and (18) with a

marker at 0.15 in. (3.81 mm) from FS559+96 (Refer to View M).

(b) Make a line on the channel (17) with a marker at 6.60 in. (167.6 mm)

from FS559+96 (Refer to View N).

(c) Cut the channels (12), (13), (14), (15), (16), (17), and (18) at the marked

locations.

(d) Remove the sharp edges.

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

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

(g) 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 --198

Incorporation

601R45102 ---123

or

601R45102 ---125

or

601R45552 ---59

K601R45035 ---2041

or

K601R45035 ---2001

or

K601R45035 ---2003
SERVICE BULLETIN 601R---25 ---198

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(h) With a permanent ink pen or equivalent, identify the channel (13) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---135

or

601R45552 ---13

K601R45035 ---2049

or

K601R45035 ---2101

(i) With a permanent ink pen or equivalent, identify the channel (14) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---135

or

601R45552 ---13

K601R45035 ---2045

or

K601R45035 ---2047

(j) With a permanent ink pen or equivalent, identify the channel (15) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---123

or

601R45552 ---13

K601R45035 ---2041

or

K601R45035 ---2043

(k) With a permanent ink pen or equivalent, identify the channel (16) as

K601R45035---2039.

(l) With a permanent ink pen or equivalent, identify the channel (17) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---121

or

601R45552 ---17

K601R45035 ---2103

or

K601R45035 ---2105
SERVICE BULLETIN 601R---25 ---198

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Sept 01/2011

(m) With a permanent ink pen or equivalent, identify the channel (18) as

K601R45035---2109.

Refer to Figure 5 (Sheet 5 of 8).

(14) At FS559.0+96.0 and FS559.0+112.0, STGR2L, remove the clips and the

channel assembly (11) from the structure (Refer to View K).

(15) At FS559.00+112.00 and FS559.00+96.00, install the rivets (19) in the holes

in the frames (Refer to View L).

(16) Apply fluid-resistant primer on the rivets (19).

(17) Apply polyurethane topcoat on the rivets (19).

Refer to Figure 5 (Sheet 7 of 8).

(18) Near FS621.00, install the nutplate (21) on the channel (20) 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 (20) at 5.90 in. (149.9 mm) from the fastener hole of the nutplate

installed on the channel (20) and at 0.60 in. (15.2 mm) from the flange of

the channel (20) (Refer to View P).

(b) Temporarily install the nutplate (21) on the channel (20) 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 (21) through the channel (20).

(d) Do a countersink in the two holes on the channel (20) for the installation

of the rivets (22).

(e) Remove the burrs and sharp edges.

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

(g) Install the nutplate (21) with the rivets (22) on the channel (20).

(h) Apply fluid-resistant primer on the rivets (22).

(i) Apply polyurethane topcoat on the rivets (22).
SERVICE BULLETIN 601R---25 ---198

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(j) With a permanent ink pen or equivalent, identify the channel (20) as

shown in the table below.

Original Part Number After S.B. 601R --25 --198

Incorporation

601R45102 ---117

or

601R45102 ---131

or

601R45102 ---963

or

601R45105 ---15

or

601R45105 ---21

K601R45035 ---2013

or

K601R45035 ---2017

or

K601R45035 ---2019

or

K601R45035 ---2011

or

K601R45035 ---2015

For Aircraft 7003 ---7679

Refer to Figure 5 (Sheet 8 of 8).

(19) At FS605.00, FS589.00, and FS574.00, and STGR0, replace the channel (23)

as follows:

(a) Remove and discard the rivets and the channel (23) from the three clips

(Refer to View T).

(b) Temporarily install the new channel (23) on the three clips

(Refer to View T).

(c) 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 (23).

(d) Do a countersink in the six holes on the channel (23) for the installation

of the rivets (24).

(e) Remove the burrs and sharp edges.

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

(g) Install the channel (23) on the three clips with the rivets (24).

(h) Apply fluid-resistant primer on the rivets (24).

(i) Apply polyurethane topcoat on the rivets (24).
SERVICE BULLETIN 601R---25 ---198

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For all aircraft

Refer to Figure 6 (Sheet 1 of 4).

(20) At FS589.00 and FS605.00, STGR9L, remove and discard the clips (2) and (1)

from the frames.

(21) At FS589.00 and FS605.00, STGR7L, remove and discard two rivets (1) from

each frame.

Refer to Figure 6 (Sheet 2 of 4).

(22) 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.

(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).
SERVICE BULLETIN 601R---25 ---198

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Refer to Figure 6 (Sheet 3 of 4).

(23) At FS589.00, install the clips (8), (7), and (6) on the frame as follows:

(a) Temporarily install the clip (8) at the location of the two holes on the

frame at STGR9L.

(b) Temporarily install the clip (6) at the location of the two holes on the

frame at STGR7L.

(c) Temporarily install the clip (7) at 1.02 in. (25.9 mm) from the doubler and

at 1.0 in. (25.4 mm) from the flange of the frame.

(d) Temporarily install the clip (6) at 0.44 in. (11.2 mm) from the doubler and

at 0.89 in. (22.6 mm) from the flange of the frame.

(e) Backdrill two holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)

from the frame through the clips (6) at STGR7L and clip (8) at STGR9L.

(f) Backdrill two holes to a diameter of 0.160 to 0.164 in. (4.06 to 4.17 mm)

from the clips (6) at STGR5L and clip (7) through the frame.

(g) Remove the burrs and sharp edges.

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

(i) At STGR7L, install the clip (6) on the frame with the rivets (14)

(Refer to view F).

(j) Install the clips (8), (7), and (6) on the frame with the rivets (10).
SERVICE BULLETIN 601R---25 ---198

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Refer to Figure 6 (Sheet 4 of 4).

(24) 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).

(25) At FS589.00 and FS605.00, install the channel (11) on the clips (7) and (4) as

follows:

(a) Install the channel (11) in position on the clips (7) and (4) at 1.50 in.

(38.1 mm) from the aft face of the frame at FS605.00.

(b) Make sure that the channel (11) is in the middle of the clips (7) and (4).

(c) Backdrill two holes to a diameter of 0.128 to 0.132 in. (3.25 to 3.35 mm)

from the clips (7) and (4) through the channel (11).

(d) Do a countersink in the four holes in the channel (11) for the installation

of the rivets (13).

(e) Remove the burrs and sharp edges.

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

(g) Install the channel (11) on the clips (7) and (4) with the rivets (13).
SERVICE BULLETIN 601R---25 ---198

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Refer to Figure 6.

(26) Apply fluid-resistant primer on the new rivets (10), (13), and (14).

(27) 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

(28) At FS621.00, wet-install 24 rivets (2) on the bulkhead (Refer to View A).

For aircraft that have Modification Summary IS601R25520054 incorporated

(29) At FS621.00, wet-install 24 screws (3) and washers (4) on the bulkhead

(Refer to View A).

(30) Remove the clickbond (1) from the bulkhead.

For aircraft that have provisions for holes in the bulkhead

Refer to Figure 9.

(31) 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).

(h) Temporarily install the liners (3), (4), and (5) on the bulkhead with the

screws (6).
SERVICE BULLETIN 601R---25 ---198

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Sept 01/2011

(i) Make sure that you drill only through the pilot holes on the liners (3), (4),

and (5), which are necessary for their installation on the bulkhead

(Refer to Sheet 2).

(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 ---198

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Sept 01/2011

For aircraft that do not have provisions for holes in the bulkhead

Refer to Figure 10.

(32) 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 on 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).
SERVICE BULLETIN 601R---25 ---198

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Page 36 of 118

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For all aircraft

Refer to Figure 11 (Sheet 1 of 3).

(33) 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 ---198

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Page 37 of 118

Sept 01/2011

(34) 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 --198

Incorporation

601R31668 ---249

OR

601R31668 ---281

OR

601R31668 ---361

OR

601R31668 ---503

K601R45035 ---2059

OR

K601R45035 ---2069

OR

K601R45035 ---2079

OR

K601R45035 ---2089

Refer to Figure 11 (Sheet 2 of 3).

(35) 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 ---198

SB 601R---25---198

Page 38 of 118

Sept 01/2011

(36) 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 --198

Incorporation

601R31668 ---241

OR

601R31668 ---273

OR

601R31668 ---345

OR

601R31668 ---501

OR

601R31668 ---245

OR

601R31668 ---277

OR

601R31668 ---325

OR

601R31668 ---497

K601R45035 ---2053

OR

K601R45035 ---2063

OR

K601R45035 ---2073

OR

K601R45035 ---2083

OR

K601R45035 ---2051

OR

K601R45035 ---2061

OR

K601R45035 ---2071

OR

K601R45035 ---2081

(37) 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 ---198

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Page 39 of 118

Sept 01/2011

(g) Slowly push the two inserts (6) with the tab into the holes and make sure

that the inserts (6) are flush with the upper and lower surfaces of the

panel (3).

(h) Apply pressure-sensitive tape to the opposite surface of the two inserts

(6) and the floor panel (3).

(i) With a syringe or equivalent, fill the holes and the cavities with adhesive

(CMS 532---02 Typ I).

(j) Clean the area to remove the unwanted adhesive from the inserts (6)

and floor panel (3).

NOTE: The adhesive must be cured before you can clean the insert (6).

(38) 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 --198

Incorporation

601R31668 ---243

OR

601R31668 ---275

OR

601R31668 ---333

OR

601R31668 ---499

K601R45035 ---2055

OR

K601R45035 ---2065

OR

K601R45035 ---2075

OR

K601R45035 ---2085

Refer to Figure 11 (Sheet 3 of 3).

(39) 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 ---198

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Page 40 of 118

Sept 01/2011

(d) Mill the core of the floor panel (4) to increase the diameter of the potting

cavity to a minimum of three core cells or to a maximum of four core

cells or to 1.5 times the diameter of the holes drilled for the installation of

the inserts (6).

(e) Remove debris and clean the holes and cavities.

(f) Put the inserts (6) in position on the tabs and make sure that the fill/vent

holes are aligned.

(g) Slowly push the two inserts (6) with the tab into the holes and make sure

that the inserts (6) are flush with the upper and lower surfaces of the

panel (4).

(h) Apply pressure-sensitive tape to the opposite surface of the two inserts

(6) and the floor panel (4).

(i) With a syringe or equivalent, fill the holes and the cavities with adhesive

(CMS 532---02 Typ I).

(j) Clean the area to remove the unwanted adhesive from the inserts (6)

and floor panel (4).

NOTE: The adhesive must be cured before you can clean the insert (6).

(40) 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 --198

Incorporation

601R31668 ---245

OR

601R31668 ---277

OR

601R31668 ---325

OR

601R31668 ---497

OR

601R31668 ---241

OR

601R31668 ---273

OR

601R31668 ---345

OR

601R31668 ---501

K601R45035 ---2051

OR

K601R45035 ---2061

OR

K601R45035 ---2071

OR

K601R45035 ---2081

OR

K601R45035 ---2053

OR

K601R45035 ---2063

OR

K601R45035 ---2073

OR

K601R45035 ---2083
SERVICE BULLETIN 601R---25 ---198

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Page 41 of 118

Sept 01/2011

(41) 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 ---198

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Page 42 of 118

Sept 01/2011

(42) 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 --198

Incorporation

601R31668 ---247

OR

601R31668 ---279

OR

601R31668 ---323

OR

601R31668 ---495

OR

601R31668 ---9037

OR

601R31668 ---9063

K601R45035 ---2057

OR

K601R45035 ---2067

OR

K601R45035 ---2077

OR

K601R45035 ---2087

OR

K601R45035 ---2097

OR

K601R45035 ---2107

(43) 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 ---198

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Sept 01/2011

Refer to Figure 4.

NOTE: For the steps that follow, it is not necessary to install the liner assemblies,

the angle assemblies, and the tie-rod cover assemblies with all their

mounting hardware.

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

(57) on the liners assemblies (16), (17), (18), (21), (22), and (23) on the 9G

bulkhead with the screws (12), (33), (34) and (43), and the washers (14).

(45) 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).

(46) 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.

(47) 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 ---198

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Page 44 of 118

Sept 01/2011

For Aircraft 7003 ---7389 that do not have liner assemblies installed on the 9G bulkhead

(Reference REO 601R ---25 ---53 ---003)

(48) Do steps 3.A (1), (2), (3), and (4) of C&D Zodiac Service Bulletin

B301003---25---02.

Refer to Figure 4.

(49) Remove the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)

from the 9G bulkhead.

(50) Remove the liner assemblies (16), (17), (18), (21), (22), and (23) from the 9G

bulkhead.

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

(57) from the 9G bulkhead.

(52) Do the remaining steps of C&D Zodiac Service Bulletin B301003---25---02 to

install the necessary inserts and the rivnuts on the 9G bulkhead.

For Aircraft 7390 ---7857

(53) Do steps 3.A (1), (2), (3), and (4) of C&D Zodiac Service Bulletin

B301003---25---01.

Refer to Figure 4.

(54) Remove the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)

from the 9G bulkhead.

(55) Remove the liner assemblies (16), (17), (18), (21), (22), and (23) from the 9G

bulkhead.

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

(57) from the 9G bulkhead.

(57) Do the remaining steps of C&D Zodiac Service Bulletin B301003---25---01 to

install the necessary inserts and the rivnuts on the 9G bulkhead.
SERVICE BULLETIN 601R---25 ---198

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Page 45 of 118

Sept 01/2011

For Aircraft 7003 ---7389 that have liner assemblies installed on the 9G bulkhead

(Reference REO 601R ---25 ---53 ---003)

(58) Do steps 3.A (1), (2), (3), and (4) of C&D Zodiac Service Bulletin

B301003---25---02.

(59) From the applicable holes in the angle assemblies (35), (36), (37), (38), (39),

(40), (41), (42), and (57) 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 B301003---25---02).

(60) Make a mark to show the pattern of the angle assemblies (35), (36), (37), (38),

(39), (40), (41), (42), and (57) on the liners of 9G bulkhead.

(61) 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.

(62) Remove the tie-rod cover assemblies (20), (24), (25), (26), (27), (28), and (52)

from the liners of the 9G bulkhead.

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

(57) from the liners of the 9G bulkhead.

(64) Remove the liner assemblies (16), (17), (18), (21), (22), and (23) from the

liners of the 9G bulkhead.

(65) Remove the applicable unwanted rivets (Refer to SRM 51---42---06).

(66) Remove the liners on the 9G bulkhead and cut them along the patterns.

(67) Do the remaining steps of C&D Zodiac Service Bulletin B301003---25---02 to

install the necessary inserts and the rivnuts on the 9G bulkhead.

(68) 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 ---198

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Page 46 of 118

Sept 01/2011

Refer to Figure 12.

(69) 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 outlet 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 17.

(70) 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 Hi-Lite pins.

(g) Fill voids and gaps on the Hi-Lite pins and between the Hi-Lite pins and

the liner assembly (2) with TAFB101---006S firewall-sealant.
SERVICE BULLETIN 601R---25 ---198

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Page 47 of 118

Sept 01/2011

For all aircraft

(h) Install the washers (5) and the screws (4) on the liner assemblies (1), (2),

and (3).

(i) Apply a fillet seal of TAFB101---006S firewall-sealant around the liner

assemblies (1), (2), and (3) (Refer to AMM 51---23---00---390---807).

(j) Put the FPC foam sheet (6) on the rear pressure bulkhead at its

installation position around the beam and the door track.

(k) If necessary, cut the FPC foam sheet (6) to make it fit correctly.

(l) Apply a fillet seal of TAFB101---006S firewall-sealant around the FPC

foam sheet (6) (Refer to AMM 51---23---00---390---807).

(m) Fill all gaps and holes with TAFB101---006S firewall-sealant

(Refer to AMM 51---23---00---390---807).

(71) Make sure that the decompression blow-out membrane on the 9G bulkhead

is not damaged.

(72) Make sure that the decompression blow-out membrane behind the last floor

panel at FS621.00 is not damaged.

Refer to Figure 4.

(73) 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 ---198

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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).

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

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

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

(b) 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.

(c) Install the washers (14) and the screws (11) that hold the forward flanges

of the floor angles (4) to the liner assembly (6).

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

angle (3) to the liner assemblies (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).

(75) Install the duct skirt (2) on the compartment floor with the washers (15) and

the bolts (13).

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

(57) on the 9G bulkhead as follows:

(a) Install the angle assemblies (35), (36), (37), (38), (39), (40), (41), (42),

and (57) 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), (42), and (57)

(Refer to AMM 51---22---28---340---801).
SERVICE BULLETIN 601R---25 ---198

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Sept 01/2011

(77) 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).

(m) Torque the bolts (32) to 20---25 lbfSin. (2.26---2.82 N.m).

(n) Put the strip assembly (19) at its installation position.

NOTE: Strip assembly (19) P/N B303021---101 is for aircraft that have

piccolo tube P/N 601R99011---13.

Strip assembly (19) P/N B303021---103 is for aircraft that have

piccolo tube 601R99011---1 or ---9.
SERVICE BULLETIN 601R---25 ---198

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(o) Put the liner assembly (17) at its installation position.

(p) Install the liner assembly (17) on the aircraft structure with the washers

(14) and the screws (33).

For aircraft that have the cargo-compartment load divider

(q) Install the anchor plates (30) on the liner assemblies (21), (22), and (23)

with the screws (29) (Refer to Views G and J).

(r) Apply a fillet seal of TAFB101---006S firewall-sealant around the anchor

plates (30) as shown on View Y (Refer to AMM 51---23---00---390---807).

For all aircraft

Refer to Figure 12.

(s) Install the liner assembly and the top strip assembly on 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).

(aa) Install the liner assembly (18) on the floor panel with the washers (14)

and the bolts (32).

(ab) Torque the bolts (32) to 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).
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 51 of 118

Sept 01/2011

(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).

(78) 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 (11) and (12).

(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).

(79) 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.

(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 W (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 W (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).
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 52 of 118

Sept 01/2011

Refer to Figures 4 and 17.

(80) 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.

(h) Install the door shroud (49) on the structure with the washers (14) and

the screws (12), (33), (34), (43), (54), and (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

(81) Install the end fittings and the cargo restraint netting in the cargo

compartment (Refer to AMM 25---51---01---400---801).

(82) Install the cargo restraint posts in the cargo compartment

(Refer to AMM 25---51---01---400---802).
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 53 of 118

Sept 01/2011

For all aircraft

(83) Install the cargo smoke detectors (Refer to AMM 26---15---01---400---801).

Refer to Figure 16.

(84) 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 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 the spacer (3) between the

ceiling liner and the firex cover.

(d) At F569.12, 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 firex cover.

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.

For all aircraft

Refer to Figure 4, View X.

(85) Install cargo lights P/N BR7203---804---1 with the kept hardware

(Refer to AMM 33---31---01---400---801).

(86) 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.

(87) Install the placard (45) or (46) on the liner assembly (16)

(Refer to AMM 11---30---00---400---801).

NOTE: The placard that is installed must be the same as the one that was

installed on the removed liner.

(88) Make sure that there is a clearance of ¦0.50 in (¦12.7 mm) between the

placard (45) or (46) and the adjacent fasteners.
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 54 of 118

Sept 01/2011

Cargo Compartment --- European Configuration

Figure 1

A

56.00 in.

(1422.40 mm)

FS559.00

+84.00

REF

FS621.00

REF

rsb601r25198_047.dg, mgr, 06/07/11

FWD

88.50 in.

(2247.90 mm)

A
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 55 of 118

Sept 01/2011

Liner Assemblies and FPC Foam Sheet --- Removal

Figure 2 (Sheet 1 of 3)

2

4

3

1

rsb601r25198_001.dg, sc, 27May 2011

1. Liner assembly.

LEGEND

5. Washer.

2. Liner assembly.

3. Liner assembly.

4. FPC foam sheet.

6. Blind rivet.

FS621.00

5

6

5

6

5

6

5

6
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 56 of 118

Sept 01/2011

Liner Assemblies and FPC Foam Sheet --- Removal

Figure 2 (Sheet 2 of 3)

rsb601r25198_002.dg, sc, 27May 2011

1. Liner assembly.

LEGEND

5. Washer.

2. Liner assembly.

3. Liner assembly.

4. FPC 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 ---198

SB 601R---25---198

Page 57 of 118

Sept 01/2011

Liner Assemblies and FPC Foam Sheet --- Removal

Figure 2 (Sheet 3 of 3)

rsb601r25198_003.dg, sd, 1Sept 2011

1. Liner assembly.

LEGEND

2. Liner assembly.

3. Liner assembly.

4. FPC foam sheet.

2

FS621.00

4

3

1

For aircraft that do not have holes

on the pressure bulkhead.

NOTE
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 58 of 118

Sept 01/2011

Foam Sheet --- Removal

Figure 3 (Sheet 1 of 2)

rsb601r25198_004.dg, sc, 27May 2011

LEGEND

2. Rivet CR3214--4--2.

RIVET

(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 ---198

SB 601R---25---198

Page 59 of 118

Sept 01/2011

Blind Nut Assembly --- Installation

Figure 3 (Sheet 2 of 2)

rsb601r25198_005.dg, sc, 27May 2011

LEGEND

1. Blind nut assembly

2. Intercostal

B0203034PB1032DU1.

601R35212.

1

2

TYPICAL INSTALLATION

(7 PLACES)

FS621.00 FS574.00

2.50 in.

(6.4 cm)

0.80 in.

(20.3 mm)

9.78 in.

(24.8 cm)

18.10 in.

(46 cm)

25.10 in.

(63.8 cm)

33.75 in.

(85.7 cm)

38.79 in.

(98.5 cm)

44.08 in.

(112.0 cm)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 60 of 118

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.

CHANNEL

ASSEMBLY

(REF)

CHANNEL

ASSEMBLY

(REF)

rsb601r25198_007.dg, sc, 27May 2011

12

12
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 61 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 2 of 14)

CHANNEL

(REF)

FS621.00

17

16

18

19

1

14

11

SCREW

(REF)

WASHER

(REF)

SCREW

(REF)

WASHER

(REF)

WASHER

(REF)

WASHER

(REF)

FS621.00

C

C

WASHER

(REF)

SCREW

(REF)

WASHER

(REF)

SCREW

(REF)

SUPPORT

ASSEMBLY

(REF)

LEGEND

1. Duct

B305104--101.

14. Washer

B0202013S1328--63.

11. Screw

MS27039--1--08.

16. Liner assembly

B302123--101.

17. Liner assembly

B303122--101.

18. Liner assembly

B302124--101.

19. Strip assembly

B303021--101 or

B303021--103.

On aircraft that have piccolo tube

601R99011--13.

On aircraft that have piccolo tube

601R99011--1 or --9.

NOTES

rsb601r25198_008.dg, sc, Aug 2011
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 62 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 3 of 14)

rsb601r25198_009.dg, sc, 27May 2011

19 17

20

52

1

LEGEND

1. Duct

B305104--101.

17. Liner assembly

B303122--101.

19. Strip assembly

B303021--101 or

20. Cover assembly, tie rod

B306123--101.

52. Cover assembly, tie rod

B306123--105.

B303021--103.

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

BL0.00

FS621.00

On aircraft that have piccolo tube

601R99011--13.

On aircraft that have piccolo tube

601R99011--1 or --9.

NOTES

FS574.00 FS621.00

BL0.00
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 63 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 4 of 14)

rsb601r25198_010.dg, sc, 30 May 2011

16

18

25

24

E

BL0.00

FS621.00

LEGEND

16. Liner assembly

B302123--101.

18. Liner assembly

B302124--101.

24. Cover assembly, tie rod

B306126--101.

25. Cover assembly, tie rod

B306105--103.

34 Screw MS27039--1--11

14 Washer B0202013S1328--63

33 MS27039--1--09 Screw

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 Screw MS27039--1--12

14 Washer B0202013S1328--63

FS621.00

WL73.59

FS574.00

NOTE

Sealant TAFB101--006S on panel edge.
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 64 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 5 of 14)

rsb601r25198_011.dg, sc, 31May 2011

45. Placard S1604--2.

46. Placard S5312--1.

B302123--101.

LEGEND

16. Liner assembly

F

16

FS621.00

17.82 in.

(452.63 mm)

50.80 in.

(1290.32 mm)

WL73.59

45 16

FS621.00

17.82 in.

(452.63 mm)

50.80 in.

(1290.32 mm)

WL73.59

46

OR

BL0.00

FS621.00
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 65 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 6 of 14)

rsb601r25198_012.cgm, sc, 2June 2011

23

22

21

CHANNEL

(REF) 19

CHANNEL

(REF)

SCREW

(REF)

WASHER

(REF)

WASHER

(REF)

SCREW

(REF)

WASHER

(REF)

SCREW

(REF)

WASHER

(REF)

FS621.00

G

FS621.00

LEGEND

19. Strip assembly B303021--101.

or B303021--103.

21. Liner assembly B302121--101.

22. Liner assembly B302122--101.

23. Liner assembly B303121--101

or B303121--103.

6

7

G

On aircraft that have piccolo tube

601R99011--13.

On aircraft that have piccolo tube

601R99011--1 or --9.

On aircraft that do not have a load divider.

On aircraft that have a load divider.

6

7

NOTES

SCREEN ASSY

(REF)

1

1

2

2
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 66 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 7 of 14)

rsb601r25198_013, sc, 2June 2011

BL0.00

23

26

LEGEND

23. Liner assembly

B303121--101 or

B303121--103.

26. Cover assembly, tie rod

B306123--101.

6

7

47. Cover assembly, tie rod

B306123--103.

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

6

7

FS621.00 FS574.00 FS559.00

+96.00

47
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 67 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 8 of 14)

rsb601r25198_014.dg, sc, 3June 2011

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

43 Screw MS27039--1--12

14 Washer B0202013S1328--63

LEGEND

21. Liner assembly

B302121--101.

22. Liner assembly

B302122--101.

27. Cover assembly, tie rod

B306122--101.

28. Cover assembly, tie rod

B306121--101.

29. Screw NAS517--3--4.

30. Anchor plate 20050.

30

29

LINER ASSEMBLY (REF)

J TYPICAL 5 PLACES

22

27

28

21

FLOOR (REF)

WL73.59

9G

K

FS621.00

BL0.00

G

J

K

SCREEN ASSY

(REF)

On aircraft that have a load divider.

NOTE

7

7

7

FS574.00 FS559.00

+84.00

BULKHEAD

(REF)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 68 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 9 of 14)

rsb601r25198_015.cgm, sc/cr, 13 June 2011

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.

32. Bolt NAS6203--11.

33. Screw MS27039--1--09.

ANGLE

ASSEMBLY

(REF)

LINER

ASSEMBLY

(REF)

N

TYPICAL INSTALLATION

TYPICAL TIE--ROD COVER

INSTALLATION

9G BULKHEAD

(REF)

L

L

M

M

N

(REF)

ANGLE

ASSEMBLY

N

M

M

M
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 69 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 10 of 14)

rsb601r25198_016.cgm, sc/cr, 20 June 2011

LEGEND

20. Cover assembly, tie rod B306123--101.

24. Cover assembly, tie rod B306126--101.

25. Cover assembly, tie rod B306105--103.

26. Cover assembly, tie rod B306123--103.

27. Cover assembly, tie rod B306122--101

28. Cover assembly, tie rod B306121--101.

35. Angle assembly, 9G bulkhead B306215--101.

36. Angle assembly, 9G bulkhead B306116--101.

37. Angle assembly, 9G bulkhead B306217--101.

38. Angle assembly, 9G bulkhead B306218--101.

39. Angle assembly, 9G bulkhead B306211--101.

40. Angle assembly, 9G bulkhead B306212--101.

41. Angle assembly, 9G bulkhead B306213--101.

or B306214--103.

6

7

42. Angle assembly, 9G bulkhead B306214--101.

52. Cover assembly, tie--rod B306123--105.

L

24

37

25

36

52

20 35

42

26

57

20

41

39

28

40

27

38

P

On aircraft that do not have a load divider.

On aircraft that have a load divider.

6

7

NOTES 57. Angle assembly, 9G bulkhead B306219--101.
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 70 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 11 of 14)

rsb601r25198_017.cgm, sc, 13June 2011

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

FS621.00

BL0.00
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 71 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 12 of 14)

rsb601r25198_018.cgm, sc, 20June 2011

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

50 51

53 Washer NAS1169--10L

56 Screw MS24693--S273

ITEM NAME PART NUMBER FASTENER

CODE

LEGEND

50. Liner assembly

B302105--101.

51. Liner assembly

B302106--101.

G

FS621.00

BL0.00
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 72 of 118

Sept 01/2011

Liner Assemblies --- Installation

Figure 4 (Sheet 13 of 14)

rsb601r25198_019.cgm, sc, 20June 2011

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

49

51

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

49

NAME

G

FS621.00

BL0.00
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 73 of 118

Sept 01/2011

Tie Rod Cover, Cargo Light, and Anchor Plate --- Application of Sealant

Figure 4 (Sheet 14 of 14)

rsb601r25198_020.cgm, sc, July 2011

9G BULKHEAD

(REF)

TIE ROD

COVER (REF)

TYPICAL 8 PLACES

SEALANT

RTV 106 (REF)

LINER

ASSEMBLY

(REF)

ANCHOR

PLATE

(REF)

CARGO LIGHT

(REF)

NOTE

Sealant TAFB101--006S.

TYPICAL 6 PLACES
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 74 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 1 of 8)

rsb601r25198_021.cgm,sc,21June 2011

STGR10R

RIVET (REF) 1

FS621.00

POST--MOD

FS621.00

C

LEGEND

1. Rivet B0205017AD4--4S.

2. Clip

601R45103--19 (Pre--Mod)

K601R45035--2111 (Post--Mod) or

601R45103--29 (Pre--Mod)

K601R45035--2113 (Post--Mod).

CHANNEL

(REF)

PRE--MOD

CHANNEL

(REF)

2

0.80 in.

(20.3 mm) 2

2

A

MATERIAL TO BE REMOVED

STGR0

FS621.00

FS559.00

+80.00

FS574.00
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 75 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 2 of 8)

rsb601r25198_022.cgm,sc,22jUNE 2011

1 RIVET (REF)

RIVET (REF) 1

FS621.00

D PRE--MOD D POST--MOD

E

CHANNEL

(REF)

CHANNEL

(REF)

FS621.00

LEGEND

1. Rivet B0205017AD4--4S.

3. Clip

601R45103--33 (Pre--Mod)

K601R45035--2031 (Post--Mod).

5. Clip

601R45103--35 (Pre--Mod)

K601R45035--2033 (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

D

STGR10R

A

STGR0

FS621.00

FS559.00

+80.00

STGR5R FS574.00

STGR6R
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 76 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 3 of 8)

rsb601r25198_023.cgm,sc,22June 2011

RIVET (REF) 1

FS621.00 FS621.00

F PRE--MOD F POST--MOD

G

G

1.00 in.

(25.4 mm)

4

LEGEND

1. Rivet B0205017AD4--4S.

4. Clip

601R45103--13 (Pre--Mod)

K601R45035--2029 (Post--Mod).

4 4

MATERIAL TO BE REMOVED

STGR10R

STGR3R

A

STGR0

FS621.00

FS559.00

+80.00

FS574.00

F

CHANNEL

(REF) CHANNEL

(REF)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 77 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 4 of 8)

rsb601r25198_024.cgm,sc,22June 2011

FS574.00 FS589.00

0.36 in.

(9.14 mm)

H TYPICAL (5 PLACES)

LEGEND

K601R45035--2005 (Post--Mod) or

6. Channel

601R45102--147 (Pre--Mod)

K601R45035--2009 (Post--Mod).

7. Channel

601R45102--119 (Pre--Mod)

K601R45035--2021 (Post--Mod) or

8. Channel

601R45102--133 (Pre--Mod)

K601R45035--2025 (Post--Mod) or

9. Channel

601R45102--133 (Pre--Mod)

10. Channel

601R45102--133 (Pre--Mod)

K601R45035--2035 (Post--Mod) or

K601R45035--2007 (Post--Mod).

601R45102--139 (Pre--Mod)

K601R45035--2023 (Post--Mod).

601R45102--165 (Pre--Mod)

K601R45035--2027 (Post--Mod).

601R45102--165 (Pre--Mod)

601R45102--165 (Pre--Mod)

K601R45035--2037 (Post--Mod).

MATERIAL TO BE REMOVED

STGR10R

STGR3R

A

STGR0

FS621.00

FS559.00

+80.00

FS574.00

FS565.00

H

STGR5R

STGR6R

STGR9R

6

7 8

9

10

CHANNEL

(REF)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 78 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 5 of 8)

rsb601r25198_025.cgm, sc, 07/2011

FS621.00

FS559.00

+80.00

FS574.00

STGR0

STGR2L

STGR12L

FS559.00

+96.00

FS559.00

+112.00

FS559.00

+112.00

FS559.00

+96.00

CHANNEL ASSY

RIVET

(REF)

FRAME

(REF)

19

(TYPICAL

2 PLACES)

LEGEND

19. Rivet MS20470AD5--4A.

11. Clip.

RIVET

(REF)

11

11

(REF)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 79 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 6 of 8)

rsb601r25198_026.cgm, sc/rb, 23/06/2011

0.15 in.

(3.81 mm)

LEGEND

12. Channel

601R45102--123 (Pre--Mod)

K601R45035--2041 (Post--Mod) or

601R45552--59 (Pre--Mod)

K601R45035--2003 (Post--Mod) or

601R45102--125 (Pre--Mod)

K601R45035--2001 (Post--Mod).

K601R45035--2049 (Post--Mod) or

13. Channel

601R45102--135 (Pre--Mod)

K601R45035--2045 (Post--Mod) or

14. Channel

601R45102--135 (Pre--Mod)

K601R45035--2041 (Post--Mod) or

15. Channel

601R45102--123 (Pre--Mod)

K601R45035--2039 (Post--Mod).

16. Channel

601R45102--127 (Pre--Mod)

K601R45035-- 2101(Post--Mod).

601R45552--13 (Pre--Mod)

K601R45035--2047 (Post--Mod).

601R45552--13 (Pre--Mod)

K601R45035--2043 (Post--Mod).

601R45552--13 (Pre--Mod)

K601R45035--2109 (Post--Mod).

18. Channel

601R45102--123 (Pre--Mod)

K601R45035--2103 (Post--Mod) or

17. Channel

601R45102--121 (Pre--Mod)

K601R45035-- 2105 (Post--Mod).

601R45552--17 (Pre--Mod)

MATERIAL TO BE REMOVED

FS621.00

FS559.00

+80.00

FS574.00

STGR0

STGR12L

FS559.00

+96.00

FS559.00

+112.00

TYPICAL (6 PLACES)

STGR6

CHANNEL

(REF)

FS559.00

FS574.00 +96.00

13 14

15

16 12

STGR14L

STGR16L

18 17

6.60 in.

(167.64 mm)

CHANNEL

(REF)

FS559.00

FS574.00 +96.00
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 80 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 7 of 8)

rsb601r25198_027.cgm, sc/rb, 23/06/2011

STGR3L

5.90 in.

(149.9 mm)

0.60 in.

(15.2 mm)

DIAMETER

FS621.00

FS621.00

20

20

21

22

0.256 TO 0.261 in.

6.50 TO 6.63 mm)

FS621.00

FS559.00

+80.00

FS574.00

STGR0

STGR12L

LEGEND

20. Channel

K601R45035--2011 (Post--Mod) or

601R45102--117 (Pre--Mod)

K601R45035--2013 (Post--Mod) or

601R45105--21 (Pre--Mod)

K601R45035--2015 (Post--Mod) or

601R45102--131 (Pre--Mod)

K601R45035--2017 (Post--Mod) or

601R45102--963 (Pre--Mod)

K601R45035--2019 (Post--Mod).

21. Nutplate MS21059L3.

22. Rivet B0205017AD3--4S.

601R45105--15 (Pre--Mod)

FASTENER HOLE

(REF)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 81 of 118

Sept 01/2011

Structural Changes

Figure 5 (Sheet 8 of 8)

rsb601r25198_028.cgm, sc/rb, 23/06/2011

FS621.00

FS605.00

FS589.00

FS574.00

23

24

24

24

VIEW ROTATED FOR CLARITY

CLIP

(REF)

CLIP

(REF)

CLIP

(REF)

LEGEND

23. Channel.

24. Rivet B0205017AD4--4S.

601R45102--143 (Pre--Mod) or

601R45102--159 (Pre--Mod),

601R45102--169 (Post--Mod).

STGR3L

FS621.00

FS559.00

+80.00

FS565.00

STGR0

STGR12L
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 82 of 118

Sept 01/2011

Structural Changes

Figure 6 (Sheet 1 of 4)

rsb601r25198_029.cgm, sc, 23/06/2011

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 ---198

SB 601R---25---198

Page 83 of 118

Sept 01/2011

Structural Changes

Figure 6 (Sheet 2 of 4)

rsb601r25198_030.cgm, sc, 23/06/2011

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 3

3

4

VIEW LOOKING FWD

AT FS605.00

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 ---198

SB 601R---25---198

Page 84 of 118

Sept 01/2011

Structural Changes

Figure 6 (Sheet 3 of 4)

rsb601r25198_031.cgm, sc, 23/06/2011

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.

STGR 8L

F

14. Rivet, MS20470AD5--6A.

DOUBLER

(REF)

(REF)

(REF) (REF)

(REF)

STGR 9L
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 85 of 118

Sept 01/2011

Structural Changes

Figure 6 (Sheet 4 of 4)

rsb601r25198_032.cgm, sc, 23/06/2011

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 ---198

SB 601R---25---198

Page 86 of 118

Sept 01/2011

Ground Connection Duct --- Removal

Figure 7

BLEED AIR

1

3

2

3

rsb601r25198_006.dg, sc, 27May 2011

1. Ground connection duct.

2. Boot.

3. Coupling.

LEGEND

DUCT (REF)

ADAPTER (REF)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 87 of 118

Sept 01/2011

Rear Pressure Bulkhead --- Changes

Figure 8

rsb601r25198_033.cgm, sc, 23/06/2011

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.

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

WL79.00

WL120.43

TYPICAL 4 PLACES

BULKHEAD

(REF)

1

LEGEND

1. Clickbond nutplate.
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 88 of 118

Sept 01/2011

Rear Pressure Bulkhead --- Changes

Figure 9 (Sheet 1 of 3)

rsb601r25198_034.cgm, sc, 23/06/2011

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 provision for holes.

NOTE
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 89 of 118

Sept 01/2011

Rear Pressure Bulkhead --- Changes

Figure 9 (Sheet 2 of 3)

rsb601r25198_035.cgm, sc, 23/06/2011

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

1

1

NOTE

Do not drill through pilot hole.

1
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 90 of 118

Sept 01/2011

Rear Pressure Bulkhead --- Changes

Figure 9 (Sheet 3 of 3)

rsb601r25198_036.cgm, sc, 23/06/2011

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 ---198

SB 601R---25---198

Page 91 of 118

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

1

2

rsb601r25198_037.cgm, sc, 23/06/2011

A

FS621.00

3

TYPICAL 8 PLACES

C

AT DRILL CODE LOCATIONS

BULKHEAD

(REF)

4

5

C

1

1

1

NOTE

Do not drill through

pilot hole.

A
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 92 of 118

Sept 01/2011

Floor Panels --- Changes

Figure 11 (Sheet 1 of 3)

A

G

F

E

D

C

A

rsb601r25198_038.cgm, sc, 23/06/2011

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)

K601R45035--2059 (Post--Mod) or

601R31668--281 (Pre--Mod)

K601R45035--2069 (Post--Mod) or

601R31668--361 (Pre--Mod)

K601R45035--2079 (Post--Mod) or

601R31668--503 (Pre--Mod)

K601R45035--2089 (Post--Mod).

6. Insert NAS1833C3--400.

6

(REF)

POSITIONING TAB NAS1837G3

3 CORE CELLS MINIMUM OR

4 CORE CELLS MAXIMUM OR

1.5 TIMES HOLE DIAMETER
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 93 of 118

Sept 01/2011

Floor Panels --- Changes

Figure 11 (Sheet 2 of 3)

D

rsb601r25198_039.cgm, sc, 23/06/2011

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)

K601R45035--2055 (Post--Mod) or

601R31668--275 (Pre--Mod)

K601R45035--2065 (Post--Mod) or

601R31668--333 (Pre--Mod)

K601R45035--2075 (Post--Mod) or

601R31668--499 (Pre--Mod)

K601R45035--2085 (Post--Mod).

601R31668--245 (Pre--Mod)

K601R45035--2051 (Post--Mod) or

601R31668--277 (Pre--Mod)

K601R45035--2061 (Post--Mod) or

601R31668--325 (Pre--Mod)

K601R45035--2071 (Post--Mod) or

601R31668--497 (Pre--Mod)

K601R45035--2081 (Post--Mod).

601R31668--241 (Pre--Mod)

K601R45035--2053 (Post--Mod) or

601R31668--273 (Pre--Mod)

K601R45035--2063 (Post--Mod) or

601R31668--345 (Pre--Mod)

K601R45035--2073 (Post--Mod) or

601R31668--501 (Pre--Mod)

K601R45035--2083 (Post--Mod).
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 94 of 118

Sept 01/2011

Floor Panels --- Changes

Figure 11 (Sheet 3 of 3)

rsb601r25198_040.cgm, sc, 23/06/2011

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)

K601R45035--2051 (Post--Mod) or

601R31668--277 (Pre--Mod)

K601R45035--2061 (Post--Mod) or

601R31668--325 (Pre--Mod)

K601R45035--2071 (Post--Mod) or

601R31668--497 (Pre--Mod)

K601R45035--2081 (Post--Mod).

5. Floor panel

601R31668--247 (Pre--Mod)

K601R45035--2057 (Post--Mod) or

601R31668--279 (Pre--Mod)

K601R45035--2067 (Post--Mod) or

601R31668--323 (Pre--Mod)

K601R45035--2077 (Post--Mod) or

601R31668--495 (Pre--Mod)

K601R45035--2087 (Post--Mod).

601R31668--241 (Pre--Mod)

K601R45035--2053 (Post--Mod) or

601R31668--273 (Pre--Mod)

K601R45035--2063 (Post--Mod) or

601R31668--345 (Pre--Mod)

K601R45035--2073 (Post--Mod) or

601R31668--501 (Pre--Mod)

K601R45035--2083 (Post--Mod).

601R31668--9037 (Pre--Mod)

K601R45035--2097 (Post--Mod) or

601R31668--9063 (Pre--Mod)

K601R45035--2107 (Post--Mod).
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 95 of 118

Sept 01/2011

Plenum Duct, Overheat Switch, and Control Switch --- Installation

Figure 12

rsb601r25198_041.cgm, sc, 23/06/2011

NOTE

On aircraft that have CR25--359.

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).

4

1

4 DUCT

(REF)

3

2

1

LINER

ASSEMBLY

(REF)

TOP STRIP

ASSEMBLY

6 (REF)

5

5.Washer B202013S1328--63.

6. Screw MS27039--1--08.
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 96 of 118

Sept 01/2011

Tie Rods --- Removal/Installation

Figure 13

rsb601r25198_042.cgm, sc, 23/06/2011

1. Tie rod.

2. Bolt.

3. Washer.

4. Nut.

5. Jam nut.

LEGEND 3

2

4

3

3

2

1

5

5

4

3

1

FITTING (REF)

FITTING (REF)

4

3

2

3

5 1

FITTING (REF)
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 97 of 118

Sept 01/2011

Liner Assemblies and FPC Foam Sheet --- Installation

Figure 14

rsb601r25198_043.cgm, sc, 23/06/2011

A

A

FS621.00

1

2

3

LEGEND

1. Liner assembly

B305123--101.

2. Liner assembly

B305122--101.

3. Liner assembly

B305121--101.

6. FPC 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 ---198

SB 601R---25---198

Page 98 of 118

Sept 01/2011

Mounting Trays and Bracket --- Removal/Installation

Figure 15

rsb601r25198_044.cgm, sc, 23/06/2011

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 ---198

SB 601R---25---198

Page 99 of 118

Sept 01/2011

Piccolo Tube --- Installation

Figure 16

rsb601r25198_046.cgm, sc, 07/2011

LEGEND

NAS43DD3--52N (Pre--Mod).

NAS43DD3--68FC (Post--Mod).

1. Washer

B0202013S1328--32.

2. Spacer

NAS43DD3--11FC.

3. Spacer

FIXER COVER

(REF)

A

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)

STGR10R

STGR0

FS621.00

FS559.00 +80.00

FS574.00

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 ---198

SB 601R---25---198

Page 100 of 118

Sept 01/2011

Application of TAFB101 ---006S Sealant

Figure 17 (Sheet 1 of 2)

FS589.00

FS574.00

FS605.00

NOTE

Sealant TAFB101--006S

around edges.

1

FS621.00

rsb601r25198_048.cgm, sc, 9Jul 2011

A 1

1

A

B

B
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 101 of 118

Sept 01/2011

Application of TAFB101 ---006S Sealant

Figure 17 (Sheet 2 of 2)

NOTE

Sealant TAFB101--006S

around edges.

1

rsb601r25198_049.cgm, sc, 9Jul 2011

C

1

PULLEY

BOX

(REF) C

D

D

1

E

E

1
SERVICE BULLETIN 601R---25 ---198

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Page 102 of 118

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 7.

(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 ---198

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Page 103 of 118

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 ---198

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Page 104 of 118

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 ---198

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Page 105 of 118

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---198, Equipment/Furnishing --- Cargo

Compartment Linings --- Replacement of Liners in the Cargo Compartment ---

(European Configuration), incorporated.”
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 106 of 118

Sept 01/2011

3. MATERIAL INFORMATION

A. Kit Information

KIT 601R25 ---198K1

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

601R36040---1 9 Nutplate assy, sealed --- ---

601R45102---169 1 Channel assembly --- ---

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

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

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 --- ---

B0202013S1328-32 10 Washer --- ---

B0202013S1328-63 441 Washer --- ---

B0202013S1332-63 32 Washer --- ---

B0203034PB1032DU1 8 Nut assy, blind --- ---

B0205017AD3---4S 5 Rivet --- ---

B0205017AD4---4S 18 Rivet --- ---

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

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

CR2663CW---4---03 66 Rivet, blind --- ---

CR2673CW---3---03 17 Rivet, blind --- ---

CR3214---4---2 15 Rivet, blind --- ---
SERVICE BULLETIN 601R---25 ---198

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Page 107 of 118

Sept 01/2011

PART NUMBER NOTES ALTERNATE

PARTS QUANTITY NAME

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

MS20470AD5---4A 5 Rivet --- ---

MS20470AD5---5A 12 Rivet --- ---

MS20470AD5---6A 7 Rivet --- ---

MS21042L3 7 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 92 Screw --- ---

MS27039---1---10 138 Screw --- ---

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

MS27039---1---12 4 Screw --- ---

NAS1837G3 10 Tab --- ---

NAS1149CN516R 66 Washer, flat

NAS1149F0363P 11 Washer --- ---

NAS1149FN832P 31 Washer --- ---

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

NAS1801---3---8 5 Screw, hex head --- ---

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

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

NAS43DD3---68FC 7 Spacer --- ---

NAS6203---11 33 Bolt --- ---

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

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

NAS623---2---2 22 Screw, pan head --- ---
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 108 of 118

Sept 01/2011

PART NUMBER NOTES ALTERNATE

PARTS QUANTITY NAME

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

S1604---2 1 Placard --- ---

S5312---1 1 Placard --- ---

SL215---3---1 10 Nut, clip --- ---

KIT 601R25 ---198K350

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

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

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

B302121---101 1 Liner assembly --- ---

B302122---101 1 Liner assembly --- ---

B302123---101 1 Liner assembly --- ---

B302124---101 1 Liner assembly --- ---

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

B303122---101 1 Liner assembly --- ---

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

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

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 --- ---
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 109 of 118

Sept 01/2011

PART NUMBER NOTES ALTERNATE

PARTS QUANTITY NAME

B306105---103 1 Cover, tie rod --- ---

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

B306121---101 1 Cover, tie rod --- ---

B306122---101 1 Cover, tie rod --- ---

B306123---101 2 Cover, tie rod --- ---

B306123---103 1 Cover, tie rod --- ---

B306123---105 1 Cover, tie rod --- ---

B306126---101 1 Cover, tie rod --- ---

B306211---101 1 Angle, 9G bulkhead --- ---

B306212---101 1 Angle, 9G bulkhead --- ---

B306213---101 1 Angle, 9G bulkhead --- ---

B306215---101 1 Angle, 9G bulkhead --- ---

B306217---101 1 Angle, 9G bulkhead --- ---

B306218---101 1 Angle, 9G bulkhead --- ---

B306219---101 1 Angle, 9G bulkhead --- ---

KIT 601R25 ---198K351

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

B303121---103 1 Liner assy, ceiling --- ---

B306214---103 1 Liner assy, ceiling --- ---
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 110 of 118

Sept 01/2011

KIT 601R25 ---198K352

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

B303121---101 1 Liner assy, ceiling --- ---

B306214---101 1 Liner assy, ceiling --- ---

KIT 601R25 ---198K353

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

B303021---101 1 Strip assy, top --- ---

KIT 601R25 ---198K354

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

B303021---103 1 Strip assy, top --- ---

KIT 601R25 ---198K355

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

B303601---103 1 Duct assy, plenum --- ---

KIT 601R25 ---198K356

PART NUMBER QUANTITY NAME ALTERNATE

PARTS NOTES

B303601---101 1 Duct assy, plenum --- ---
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 111 of 118

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.
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 112 of 118

Sept 01/2011

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 K601R45035---2053 Floor panelassembly

601R31668---243 Floor panel

assembly 1 RWK K601R45035---2055 Floor panelassembly

601R31668---245 Floor panel

assembly 1 RWK K601R45035---2051 Floor panelassembly

601R31668---247 Floor panel

assembly 1 RWK K601R45035---2057 Floor panelassembly

601R31668---249 Floor panel

assembly 1 RWK K601R45035---2059 Floor panelassembly

601R31668---273 Floor panel

assembly 1 RWK K601R45035---2063 Floor panelassembly

601R31668---275 Floor panel

assembly 1 RWK K601R45035---2065 Floor panelassembly

601R31668---277 Floor panel

assembly 1 RWK K601R45035---2061 Floor panelassembly

601R31668---279 Floor panel

assembly 1 RWK K601R45035---2067 Floor panelassembly

601R31668---281 Floor panel

assembly 1 RWK K601R45035---2069 Floor panelassembly

601R31668---323 Floor panel

assembly 1 RWK K601R45035---2077 Floor panelassembly

601R31668---325 Floor panel

assembly 1 RWK K601R45035---2071 Floor panelassembly

601R31668---333 Floor panel

assembly 1 RWK K601R45035---2075 Floor panelassembly
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 113 of 118

Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R31668---345 Floor panel

assembly 1 RWK K601R45035---2073 Floor panelassembly

601R31668---361 Floor panel

assembly 1 RWK K601R45035---2079 Floor panelassembly

601R31668---495 Floor panel

assembly 1 RWK K601R45035---2087 Floor panelassembly

601R31668---497 Floor panel

assembly 1 RWK K601R45035---2081 Floor panelassembly

601R31668---499 Floor panel

assembly 1 RWK K601R45035---2085 Floor panelassembly

601R31668---501 Floor panel

assembly 1 RWK K601R45035---2083 Floor panelassembly

601R31668---503 Floor panel

assembly 1 RWK K601R45035---2089 Floor panelassembly

601R31668---9037 Floor panel

assembly 1 RWK K601R45035---2097 Floor panelassembly

601R31668---9063 Floor panel

assembly 1 RWK K601R45035---2107 Floor panelassembly

601R45103---13 Clip 1 RWK K601R45035---2029 Clip

601R45103---19 Clip 1 RWK K601R45035---2111 Clip

601R45103---29 Clip 1 RWK K601R45035---2113 Clip

601R45103---33 Clip 1 RWK K601R45035---2031 Clip

601R45103---35 Clip 1 RWK K601R45035---2033 Clip

601R45552---17 Channel

assembly 1 RWK K601R45035---2105 Channelassembly

601R45552---13 Channel

assembly 3 RWK K601R45035---2043or ---2047 or ---2101

Channel

assembly

601R45552---59 Channel

assembly 1 RWK K601R45035---2003 Channelassembly

601R45552---125 Channel

assembly 1 RWK K601R45035---2001 Channelassembly
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 114 of 118

Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R45105---15 Channel

assembly 1 RWK K601R45035---2011 Channelassembly

601R45105---21 Channel

assembly 1 RWK K601R45035---2015 Channelassembly

601R45102---117 Channel

assembly 1 RWK K601R45035---2013 Channelassembly

601R45102---119 Channel

assembly 1 RWK K601R45035---2009 Channelassembly

601R45102---121 Channel

assembly 1 RWK K601R45035---2103 Channelassembly

601R45102---123 Channel

assembly 3 RWK K601R45035---2041or ---2109

Channel

assembly

601R45102---127 Channel

assembly 1 RWK K601R45035---2039 Channelassembly

601R45102---131 Channel

assembly 1 RWK K601R45035---2017 Channelassembly

601R45102---133 Channel

assembly 3 RWK K601R45035---2021or ---2025 or ---2035

Channel

assembly

601R45102---135 Channel

assembly 2 RWK K601R45035---2045or ---2049

Channel

assembly

601R45102---139 Channel

assembly 1 RWK K601R45035---2007 Channelassembly

601R45102---147 Channel

assembly 1 RWK K601R45035---2005 Channelassembly

601R45102---165 Channel

assembly 3 RWK K601R45035---2023or ---2027 or ---2037

Channel

assembly

601R45102---963 Channel

assembly 1 RWK K601R45035---2019 Channelassembly

601R96385---19 or

---27 or ---35 Duct, plenum 1 DIS B303601---101 or---103 Duct, plenum

BR7203---804 Light, cargo 2 DIS BR7203---804---1 Light, cargo
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 115 of 118

Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R45151---1 Liner

assembly 1 DIS B302123---101 Linerassembly

601R455532---19 or

601R45151---3 or

---23 or ---2506

Liner

assembly 1 DIS B302122---101 Linerassembly

601R45151---5 or

601R45570---1

Liner

assembly 1 DIS B303122---101 Linerassembly

601R45151---13 or

---21 or ---2503 or

601R45571---1 or

601R45578---1

Liner

assembly 1 DIS B303121---101 or---103

Liner

assembly

601R45151---15 or

---25 or

601R45572---1

Liner

assembly 1 DIS B302124---101 Linerassembly

601R45151---11 or

---191 or ---2502 or

---2519 or

601R48946---1

Liner

assembly 1 DIS B302121---101 Linerassembly

601R45573---1 or

601R45158---13 or

601R45554---23 or

K601R45002---9

Tie-rod cap

assembly 1 DIS B306126---101 Tie-rod capassembly

601R48901---1 or

601R45158---13 or

601R45554---23 or

K601R45002---9

Tie-rod cap

assembly 1 DIS B306105---103 Tie-rod capassembly

601R48902---1 or

601R45158---7 or

---33 or

K601R45002---7 or

601R45002---5 or

601R45158---3 or

---5 or ---31

Tie-rod cap

assembly 1 DIS B306123---101 or---105

Tie-rod cap

assembly
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 116 of 118

Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R48902---1 or

601R45002---5 or

601R45158---3 or

---5 or ---31

Tie-rod cap

assembly 1 DIS B306123---103 Tie-rod capassembly

601R48905---1 or

601R45002---3 or

601R45158---3 or

---29

Tie-rod cap

assembly 1 DIS B306122---101 Tie-rod capassembly

601R48903---1 or

601R45158---1 or

601R45554---21 or

601R45001---5

Tie-rod cap

assembly 1 DIS B306121---101 Tie-rod capassembly

601R45152---11 or

601R45400---977

Liner

assembly 1 DIS B305103---101 Linerassembly

601R45152---9 or

---19 or ---2501 or

601R45400---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

Liner

assembly 1 DIS B305112---101 Angle, floor

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
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 117 of 118

Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

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

601R45102---129 or

601R45552---9

Channel

assembly 1 DIS --- ---

601R45102---143 or

601R45102---159

Channel

assembly 1 DIS --- ---

601R45102---115 Support assy 1 DIS --- ---

601R45159---73 Angle

assembly 1 DIS --- ---

601R45159---75 Angle

assembly 1 DIS --- ---

601R45153---3 or

---7 or ---9 or ---11

or ---13 or ---15 or

---17 or ---19 or ---25

or ---27 or ---29 or

601R45511---951 or

601R45555---27

Cap assembly 4 DIS --- ---
SERVICE BULLETIN 601R---25 ---198

SB 601R---25---198

Page 118 of 118

Sept 01/2011

PRE ---SB

PART NUMBER

POST ---SB NAME

PART NUMBER

NAME QTY DC

601R45155---3 or ---5

or ---9 Extrusion 1 DIS --- ---

601R45151---17 or

---27 Panel 1 DIS --- ---

601R45274---3 or

---5 or ---7 or ---9 or

---11 or ---951 or

601R45100---29 or

---30

Cargo net cap

assembly 2 DIS --- ---

601R45274---1 and

601R45104---1

Cargo net cap

and retainer 5 DIS --- ---

601R45159---107 Foam sheet 1 DIS --- ---

601R96383---7 Screen,

exhaust duct 1 DIS --- ---

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-25-198 ISSUE: NC

 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