SERVICE BULLETIN

This service bulletin is sent to each operator that has purchased the affected equipment 

from Comtek. If an operator has leased or purchased the equipment from a source 

other than Comtek, the operator that originally purchased the equipment must forward 

this service bulletin to the lessee or new owner.

CL-600-2B19 Canadair Regional Jet (CRJ) 100/200/440

ATA System: 25-52 Document Number: COMSB-25-52-001

Revision: A

Date: 29 December 2011

SUBJECT: Equipment/Furnishings – Cargo Compartment Linings – Modification 

and Replacement of Liners in the Cargo Compartment
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 2 of 92

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected

CL-600-2B19 Canadair Regional Jet (CRJ) 100/200/440 aircraft with serial 

numbers 7003 through 7067, 7069 through 7857 and 7877 that are fitted 

with Comtek Advanced Structures aftermarket cargo liners produced 

under any of the following STCs. Only the aircraft that have a cargo 

compartment with the dimensions below are affected. These aircraft are 

referred to as the “North American Configuration” in the Bombardier 

documentation. 

Applicable STC Approvals

 TCCA: SA01-19 (Issue 1, dated 26-Jan-2001)

 FAA: ST01292NY (Issued 22-Feb-2001)

 EASA: 208-SI-0077 (Issued 12-Dec-2001)

TA0606 (Issue 1, dated 24-Jun-2002)

92.00 in

FS559.00+80.50 FWD FS621.00
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 3 of 92

B. Reason

(1) Condition

The Comtek aftermarket cargo liners produced under the STC approvals 

listed in Section A for the CL-600-2B19 CRJ 100/200/440 do not meet the 

flammability requirements of FAR 25.855.

(2) Objective/Benefit

This service bulletin provides the procedure to rework or replace the liners 

in the cargo compartment and modify some floor panels.

After incorporation of this service bulletin, the Comtek aftermarket cargo 

liners will fully comply with the FAR 25.855 requirements.

C. Description

The cargo compartment door is opened. The sidewall liners and rear bulkhead 

liners are removed. Existing Comtek liner panels are reworked and reidentified. At the option of each operator, parts can be replaced instead of 

being reworked. New Comtek panels are installed to replace any remaining 

OEM panels. Panels are installed and various existing functional tests are 

performed.

D. Compliance

This is a required Service Bulletin. This service bulletin should be incorporated 

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. Approvals

This service bulletin is approved by Transport Canada and by TCCA Design 

Approval Organization 96-O-02.

F. Labor Requirement

This service bulletin requires approximately 80 person-hours.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 4 of 92

G. Materials

All kits are available from Comtek Advanced Structures. Submit requests for 

quotation to:

Comtek Advanced Structures

1360 Artisans Court

Burlington, Ontario, L7L 5Y2, Canada

Phone: (905) 331-8121

Fax: (905) 331-8125

H. Tooling

Refer to paragraph 3.C for a list of special tools and equipment required to 

incorporate this service bulletin.

I. Weight and Balance

This service bulletin affects the weight and balance of the aircraft. The weight 

of each component removed or installed and the FS location of that

component should be recorded. The change in weight and balance should be 

determined from these measurements and entered into the weight and 

balance records for the aircraft.

J. Electrical Load Data

Not Changed.

K. References

 Bombardier Aircraft Maintenance Manual (CSP A-001 Revision 44 or 

later approved revision)

 Bombardier Structural Repair Manual (CSP A-008 Revision 31 or later 

approved revision)

 Comtek Aircraft Maintenance Manual Supplement, Component 

Maintenance Manual and Illustrated Parts Catalog (COMAMM-011

Revision F or later approved revision)
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 5 of 92

L. Other Publications Affected

 Comtek Aircraft Maintenance Manual Supplement, Component 

Maintenance Manual and Illustrated Parts Catalog (COMAMM-011). 

Discard and destroy COMAMM-011 Revision E or earlier revision and 

replace with COMAMM-011 Revision F or later approved revision.

M. Nomenclature

In the context of this Service Bulletin, the term “Pre-SB” means prior to 

incorporation of this service bulletin. The term “Post-SB” means after the 

incorporation of this service bulletin or re-identification of parts according to 

this service bulletin.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 6 of 92

2. IMPLEMENTATION INSTRUCTIONS

A. Job Setup

Reference Information:

Reference Description

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 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 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

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 26-25-00-710-801 Operational Test of the Cargo FireExtinguishing 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
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 7 of 92

Reference Description

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 51-23-00 Pressure, Environmental, Fuel Tank and 

Fire-Wall Sealing

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

SRM 51-42-13 Cherrymax Blind Rivets

SRM 51-45-00 Nutplate (Anchor Nuts) – General
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 8 of 92

Tolerance Information:

Linear Tolerances Angular Tolerances

X.XX in (X.X mm) X.X in (X mm) ± 0.5 ̊

± 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 otherwise specified.

(1) Obey all 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) If required for access, remove the cargo compartment door

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

(5) Open the aft equipment compartment door.

(6) Open, safety, and tag the circuit breakers that follow plus any others that 

provide power to the cargo compartment or that may affect worker safety.

CB Panel CB Number Name Zone

CBP-1 F11 10 TH 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

CBP-1 N12 XFER/APU APU ECU 221

CBP-1 P1 CARGO FIREX 1 221
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 9 of 92

CB Panel CB Number Name Zone

CBP-1 R5 APU FIRE EXT A 221

CBP-1 R6 APU FIRE EXT B 221

CBP-2 F11 10 TH ST B/AIR SOV R 222

CBP-2 J1 R AIR COND UNIT 222

CBP-2 T1 SERV LTS 222

CBP-2 T3 SRV LTS 222

CBP-4 B1 10 TH ST B/AIR ISOL 222

CBP-4 B12 DOOR INDICATION 222

CBP-5 A1 APU ACT 311

CBP-5 A13 LIGHTS SERV 311

(7) Remove and retain the Inlet Duct screen assembly located near 

FS559+112L and STGR 17.

(8) Remove and retain Exhaust Duct screen assembly located near the center 

of the cargo compartment ceiling.

(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).

(12) Removed the louvered window cage from the forward bulkhead.

(13) If angles have been installed on the forward bulkhead (per C&D Zodiac 

Service Bulletin B301002-25-01, B301002-25-02. B301003-25-01 or 

B301003-25-02), remove and discard the angles.

(14) Remove tie rod caps and harness caps.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 10 of 92

For step (15), Refer to Figure 1 (Sheet 1) on Page 59:

(15) Remove the cargo compartment sidewall linings on the right-hand and lefthand side of the cargo compartment. Keep items (1), (2), (3), (4), (5), (6) 

and (7). Remove cargo compartment ceiling panels.

(16) For each part, look up the part number in the “Disposition of Parts” Table 

starting on Page 50 of this Service Bulletin. Parts with the Disposition 

Code (DC) “DIS” should be discarded and do not need to be reworked 

according to the instructions of this Service Bulletin. Parts with the 

Disposition Code “RWK” must be reworked according to this Service 

Bulletin. All new and reworked parts must be installed according to the 

instructions of this Service Bulletin. All non-Comtek cargo liner panels are 

to be removed and discarded and replaced with Comtek parts.

(17) Remove any sealant used to seal the lining panels that have been 

removed.

NOTE: Use only non-metallic scrapers. Metal scrapers may cause 

damage to the structure.

(18) Remove and discard the liner assemblies and the FPC foam sheet on the 

rear bulkhead near the door track.

(19) Remove and discard the door shroud.

For Steps (20) through (22), Refer to Figure 1 (Sheet 2) on Page 60:

(20) Remove and discard the Center Aft Wall Kickplate (8).

(21) Remove the Duct (9). Refer to “Disposition of Parts” starting on Page 50 of 

this Service Bulletin. If the Disposition Code for the part number of the 

Duct (9) is listed as DIS, discard the duct and obtain the part listed as 

“Post-SB P/N.” If the Disposition Code is RWK, retain the Duct. If the duct 

is a non-Comtek part, remove and discard the duct.

(22) Remove and discard the aft wall angles (10) and (11).

(23) Check the part number of the aft wall panels (12), (13) and (14) against 

the table “Disposition of Parts” starting on Page 50 of this Service Bulletin. 

For all panels with the Disposition Code RWK, do not remove the panel. 
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 11 of 92

For non-Comtek panels and for panels with the Disposition Code DIS, 

remove and discard the panel and install new parts per steps (90) through 

(92) of the Procedure section.

(24) Remove and discard the ceiling liner panels and tie rod caps.

(25) Remove and discard the forward liners, if they have been installed.

B. Procedure

Refer to Figure 1 (Sheet 1) on Page 59:

(1) Remove the P-Seals and foam tape as follows:

NOTE: Use only non-metallic scrapers when removing P-Seals and foam 

tape. Metal scrapers or other sharp tools may damage the panels, 

harness caps and tie rod caps.

(a) Remove the P-Seal from the right-hand lower sidewall panel (2).

(b) Remove the foam tape from the right-hand lower sidewall panel (2).

(c) Remove the P-Seal from the right-hand upper sidewall panel (3).

(d) Remove the P-Seal from the lower right-hand harness cap (4).

(e) Remove the foam tape from the lower right-hand harness cap (4)

(f) Remove the P-Seal from the upper right-hand harness cap (5).

(g) Remove the foam tape from the upper right-hand harness cap (5).

(h) Remove the foam tape from the edge of the lower right-hand tie rod 

cap (6).

(i) Remove the foam tape from the edge of the upper right-hand sidewall 

tie rod cap (7).

(j) Ensure that all adhesive residue is removed from the panels, harness 

caps and tie rod covers.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 12 of 92

(2) Reinstall foam tape as follows:

(a) Clean the surface and install HT-805(A) foam tape to the right-hand 

lower sidewall panel (2) in the same location as the original foam tape.

(b) Clean the surface and install HT-805(A) foam tape to the lower righthand harness cap (4) in the same location as the original foam tape.

(c) Clean the surface and install HT-805(A) foam tape to the right-hand 

upper harness cap (5) in the same location as the original foam tape.

(d) Clean the surface and install HT-805(A) foam tape to the lower righthand tie rod cap (6) in the same location as the original foam tape.

(e) Clean the surface and install HT-805(A) foam tape to the upper righthand tie rod cap (7) in the same location as the original foam tape.

On aircraft fitted with duct assy CRJLA09-03 or -07 (Pre-SB)

Refer to Figure 1 (Sheet 2) on Page 60:

(3) Remove the P-Seals and foam tape from the duct (9) as follows:

NOTE: Use only non-metallic scrapers when removing P-Seals and foam 

tape. Metal scrapers or other sharp tools may damage the panels, 

harness caps and tie rod caps.

(a) Remove the P-Seal from the duct (9).

(b) Ensure that all adhesive residue is removed from the panels.

(4) Reinstall foam tape on the duct (9) as follows:

(a) Clean the surface and install HT-805(A) foam tape to the duct (9) in the 

same location as the original tape.

(b) Using a permanent ink pen or equivalent, identify the duct (9) 

according to the following table:
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 13 of 92

Pre-SB Part Number Post-SB Part Number

CRJLA09-03 CRJLA183-003

CRJLA09-07 CRJLA183-007

On all aircraft

Refer to Figure 2 (Sheet 1) on Page 61:

(5) Install the ceiling center support (3) using washers (1) and screws (2).

Refer to Figure 2 (Sheet 2) on Page 62:

(6) Temporarily affix the forward liner panels (4), (5) and (6).

Refer to Figure 2 (Sheet 3) on Page 63:

(7) Temporarily affix the joint overlaps (8) and (9).

(8) Temporarily affix the kickplates (10) and (11).

Refer to Figure 2 (Sheet 4) on Page 64:

(9) Temporarily install the lower right-hand sidewall panel (4).

(10) Temporarily install the upper right-hand sidewall panel (5).

(11) Temporarily install the lower right-hand harness cap (6).

Refer to Figure 2 (Sheet 7) on Page 67:

(12) Temporarily install the right-hand ceiling panel (4).

(13) Temporarily install the right-hand upper harness cap (5).

Refer to Figure 2 (Sheet 6) on Page 66:

(14) Temporarily install the left-hand lower sidewall panel (4).

(15) Temporarily install the left-hand upper sidewall panel (5).

(16) Temporarily install the left-hand lower harness cap (6).
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 14 of 92

On aircraft fitted with tie rod cap CRJLA050-001 (Pre-SB)

Refer to Figure 4 (Sheet 2) on Page 76:

(17) Temporarily install tie rod cap (5) and tie rod cap flange (6).

On all aircraft

Refer to Figure 2 (Sheet 8) on Page 68:

(18) Temporarily install the left-hand ceiling panel (4).

(19) Temporarily install the left-hand upper harness cap (5).

Refer to Figure 3 (Sheet 1) on Page 72:

(20) Temporarily attach the angles (6), (7), (8) and (9).

Refer to Figure 3 (Sheet 3) on Page 74:

(21) Temporarily attach the angles (6) and (7).

Refer to Figure 4 (Sheet 1) on Page 75:

(22) Temporarily attach the tie rod caps (6) and (7)

On aircraft fitted with tie rod cap CRJLA039-001 (Pre-SB)

(23) Temporarily attach tie rod cap flange (9) 

On aircraft fitted with tie rod cap CRJLA049-001 (Pre-SB) or CRJLA048-001 (PreSB)

(24) Temporarily attach tie rod cap flange (8).

On aircraft fitted with harness cap CRJLA11-03 or -07 (Pre-SB)

Refer to Figure 5 (Sheet 1) on Page 77:

(25) Temporarily attach the harness cap flange (5).
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 15 of 92

On aircraft fitted with harness cap CRJLA021-003 (Pre-SB) or -007 (Pre-SB)

Refer to Figure 5 (Sheet 1) on Page 77:

(26) Temporarily attach the harness cap flange (7).

On aircraft fitted with harness cap CRJLA11-03 or -07 (Pre-SB)

Refer to Figure 5 (Sheet 2) on Page 78:

(27) Temporarily attach the harness cap flange (5).

On aircraft fitted with harness cap CRJLA021-003 (Pre-SB) or -007 (Pre-SB)

Refer to Figure 5 (Sheet 2) on Page 78:

(28) Temporarily attach the harness cap flange (7).

On aircraft fitted with harness cap CRJLA043-003 (Pre-SB)

Refer to Figure 5 (Sheet 3) on Page 79:

(29) Temporarily attach the harness cap flange (5).

On aircraft fitted with harness cap CRJLA047-003 or -07 or -015 (Pre-SB)

Refer to Figure 5 (Sheet 3) on Page 79:

(30) Temporarily attach the harness cap flange (7).

On aircraft fitted with right-hand lower sidewall panel CRJLA03-03 or -07 or -11 or 

-15 (Pre-SB) or CRJLA015-003 or -007 (Pre-SB)

Refer to Figure 7 (Sheet 1) on Page 81:

(31) Backdrill the lower right-hand sidewall panel (5) as follows:

(a) Mark the center of the slots in the angles (6), (7), (8) and (9).

(b) At the center of each slot, drill through the sidewall panel (5) with a drill 

of diameter 0.190 in.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 16 of 92

On aircraft fitted with right-hand upper sidewall panel CRJLA023-003 or -007 (PreSB)

Refer to Figure 7 (Sheet 2) on Page 82:

(32) Backdrill the upper right-hand sidewall panel (5) as follows:

(a) Mark the center of the slots in the angles (6) and (7).

(b) At the center of each slot, drill through the sidewall panel (5) with a drill 

of diameter 0.190 in.

On all aircraft

Refer to Figure 6 (Sheet 1) on Page 80:

(33) Backdrill the forward bulkhead as follows:

(a) Use the holes in the liner panels (4), (5) and (6) as a guide.

(b) Drill through the liner panels (4), (5) and (6) and into first skin of the 

bulkhead. Stop drilling once the first skin of the bulkhead has been 

penetrated; do no drill into the opposite skin. Hole diameter should be 

0.190 in.

NOTE: Take care not to damage the opposite face skin.

On aircraft fitted with right-hand aft wall panel CRJLA017-003 (Pre-SB)

Refer to Figure 8 (Sheet 1) on Page 83:

(34) Backdrill the right-hand aft wall panel (5) as follows:

(a) Mark the center of the holes in the angles (8), (9), (10), (11) and (12) 

and the Center Joint Overlap (7).

(b) At the center of each hole, drill through the right-hand aft wall panel (5) 

with a drill of diameter 0.190 in.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 17 of 92

On aircraft fitted with center aft wall panel CRJLA07-03 (Pre-SB)

Refer to Figure 8 (Sheet 1) on Page 83:

(35) Backdrill the center aft wall panel (6) as follows:

(a) Mark the center of the holes in the angles (8) and (16) and the center 

joint overlaps (7) and (15).

(b) At the center of each hole, drill through the center aft wall panel (6) 

with a drill of diameter 0.190 in.

On aircraft fitted with left-hand aft wall panel CRJLA019-003 (Pre-SB)

Refer to Figure 8 (Sheet 2) on Page 84:

(36) Backdrill the left-hand aft wall panel (17) as follows:

(a) Mark the center of the holes in angle (16), center joint overlaps (15) 

and wall extension (18).

(b) At the center of each hole, drill through the center aft wall panel (17) 

with a drill of diameter 0.190 in.

On all aircraft

Refer to Figure 10 (Sheet 1) on Page 86:

(37) Add four holes to the right-hand lower harness cap (7), sidewall panels (5) 

and (6) and channels as follows:

Note: These holes are already present in Post-SB parts CRJLA205-003 

and -007, CRJLA201-003 and -007 and CRJLA206-003 and -007. 

The backdrilled holes are not present in the channels on Pre-SB

aircraft.

(a) Mark two locations 3.00 inches aft of the forward-most existing holes in 

the harness cap (7) as shown. This location must be in-line with the 

existing row of holes.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 18 of 92

(b) Identify the existing holes 8.50 inches apart in the harness cap (7). 

Mark two locations 3.00 aft of the forward-most of these two holes as 

show. The location must be in-line with the existing row of holes.

(c) Drill 0.190 inch holes at the locations marked. Holes pass through the 

harness cap (7), the liner panels (5) and (6) and the channel behind 

the liner panels.

(38) Add four holes to the right-hand upper harness cap, sidewall panel and 

channel as follows:

Note: These holes are already present in Post-SB parts CRJLA207-003, 

CRJLA206-003 and -007 and CRJLA220-003, -007 and -011. The 

holes are not present in the channels of Pre-SB aircraft.

(a) Mark two locations 3.00 inches aft of the forward-most existing holes in 

the harness cap (10) as shown. This location must be in-line with the 

existing row of holes.

(b) Identify the existing holes 8.50 inches apart in the harness cap (10). 

Mark two locations 3.00 aft of the forward-most of these two holes as 

show. The location must be in-line with the existing row of holes.

(c) Drill 0.190 inch holes at the locations marked. Holes pass through the 

harness cap (10), the liner panels (6) and the channel behind the liner 

panels.

On aircraft fitted with harness cap CRJLA11-03 or -07 (Pre-SB)

Refer to Figure 10 (Sheet 1) on Page 86:

(39) Backdrill the right-hand lower harness cap (7) as follows:

(a) Mark the center of the holes in the flanges (8) and (9).

(b) At the center of each hole, drill though the harness cap (7) with a drill 

of diameter 0.190 inch.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 19 of 92

On aircraft fitted with harness cap CRJLA021-003 or -007 (Pre-SB)

(40) Backdrill the right-hand upper harness cap (10) as follows:

(a) Mark the center of the holes in the flanges (11) and (12).

(b) At the center of each hole, drill though the harness cap (10) with a drill 

of diameter 0.190 inch.

On aircraft fitted with harness cap CRJLA021-003 or -007 (Pre-SB)

Refer to Figure 10 (Sheet 2) on Page 87:

(41) Backdrill the right-hand upper harness cap (5) as follows:

(a) Mark the center of the holes in the flanges (6).

(b) At the center of each hole, drill through the harness cap (5) with a drill 

of diameter 0.190 inch.

On aircraft fitted with tie rod cap CRJLA039-001 (Pre-SB)

Refer to Figure 11 (Sheet 1) on Page 89:

(42) Backdrill the lower right-hand tie rod cap (5) as follows:

(a) Mark the center of the holes in the flanges (7).

(b) At the center of each hole, drill through the tie rod cap (5) with a drill of 

diameter 0.190 inch.

On aircraft fitted with tie rod cap CRJLA049-001 (Pre-SB) or CRJLA048-001 (PreSB)

Refer to Figure 11 (Sheet 1) on Page 89:

(43) Backdrill the upper right-hand tie rod cap (6) as follows:

(a) Mark the center of the holes in the flanges (8).

(b) At the center of each hole, drill through the tie rod cap (6) with a drill of 

diameter 0.190 inch.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 20 of 92

On aircraft fitted with tie rod cap CRJLA050-001 (Pre-SB)

Refer to Figure 11 (Sheet 2) on Page 90:

(44) Backdrill the lower left-hand tie rod cap (5) as follows:

(a) Mark the center of the holes in the flange (6).

(b) At the center of each hole, drill through the tie rod cap (5) with a drill of 

diameter 0.190 inch.

On all aircraft

Refer to Figure 10 (Sheet 3) on Page 88:

(45) Add two holes to the left-hand lower harness cap (7) and channel as 

follows:

Note: Harness cap CRJLA242-003 has these holes pre-drilled. Note that 

the channels still need to be drilled.

(a) Mark two locations in the center of 10.00 inch fastener pitch in the 

harness cap (7). This location must be in-line with the existing row of 

holes.

(b) Drill 0.190 inch holes at the locations marked. Holes pass through the 

harness cap (7), the liner panels (5) and the channel behind the liner 

panels.

(46) Add four holes to the left-hand upper harness cap (8) and channel as 

follows:

Note: Harness cap CRJLA240-003 has these holes pre-drilled. Note that 

the channels still need to be drilled.

(a) Identify the fasteners located 8.70 inches apart. Mark a location 4.35 

aft of the forward hole as shown. This location must be in-line with the 

existing row of holes.

(b) Identify the fasteners located 8.24 inches apart. Mark a location 4.12 

forward of the aft hole as shown. This location must be in-line with the 

existing row of holes.
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(c) Identify the fasteners located 5.03 inches apart. Mark a location 4.72 

inches ahead of the forward hole as shown. This location must be inline with the exiting row of holes.

(d) Identify the fasteners located 10.00 inches apart. Mark a location 3.00 

inches forward of the aft hole as shown. This location must be in-line 

with the existing row of holes.

(e) Drill 0.190 inch holes at the locations marked. Holes pass through the 

harness cap (8), the liner panels and the channel behind the liner 

panels.

On aircraft fitted with harness cap CRJLA047-003 or -007 or -015 (Pre-SB)

Refer to Figure 10 (Sheet 3) on Page 88:

(47) Backdrill the harness cap (8) as follows:

(a) Mark the center of the holes in the flange (8).

(b) At the center of each hole, drill through the harness cap (8) with a drill 

of diameter 0.190 inch.

On aircraft fitted with harness cap CRJLA043-003 (Pre-SB)

Refer to Figure 10 (Sheet 3) on Page 88:

(48) Backdrill the harness cap (7) as follows:

(a) Mark the center of the holes in the flange (7).

(b) At the center of each hole, drill through the harness cap (7) with a drill 

of diameter 0.190 inch.

Refer to Figure 9 (Sheet 1) on Page 85:

(49) Backdrill the floor panels through the holes in kickplates (4) and (5). Hole 

diameter to be 0.190”. Drill through top skin of floor only.

NOTE: Be careful not to damage bottom facing of the floor panel.
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Refer to Figure 5 (Sheet 1) on Page 77:

(50) If installed, remove the harness cap flanges (5) and (7).

Refer to Figure 5 (Sheet 2) on Page 78:

(51) If installed, remove the harness cap flanges (5) and (7).

Refer to Figure 4 (Sheet 1) on Page 75:

(52) If installed, remove the tie rod cap flanges (8) and (9).

(53) If installed, remove the tie rod caps (6) and (7).

Refer to Figure 3 (Sheet 1) on Page 72:

(54) Remove the angles (6), (7), (8) and (9).

Refer to Figure 3 (Sheet 3) on Page 74:

(55) Remove the angles (6) and (7).

Refer to Figure 2 (Sheet 7) on Page 67:

(56) Remove the right-hand upper harness cap (5).

(57) Remove the right-hand ceiling panel (4). 

Refer to Figure 2 (Sheet 4) on Page 64:

(58) Remove the right-hand lower harness cap (6).

(59) Remove the right-hand sidewall panels (4) and (5).

Refer to Figure 5 (Sheet 3) on Page 79:

(60) If installed, remove harness cap flange (5).

Refer to Figure 5 (Sheet 3) on Page 79:

(61) If installed, remove the harness cap flange (7).
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Refer to Figure 2 (Sheet 8) on Page 68:

(62) Remove the left-hand upper harness cap (5)

(63) Remove the left-hand ceiling panel (4)

Refer to Figure 2 (Sheet 6) on Page 66:

(64) Remove the left-hand lower harness cap (5).

(65) Remove the left-hand upper sidewall panel (5) and left-hand lower 

sidewall panel (4).

Refer to Figure 2 (Sheet 2) on Page 62:

(66) Remove the forward liner panels (4), (5) and (6).

Refer to Figure 2 (Sheet 3) on Page 63:

(67) Remove joint overlaps (8) and (9), kickplates (10) and (11) and the aft wall 

panels (5), (6) and (7).

Refer to Figure 6 (Sheet 1) on Page 80:

(68) On the forward bulkhead, install inserts (3) in the locations that were 

backdrilled as follows:

(a) Open the holes backdrilled earlier to a diameter of 0.686-0.691 in. and 

0.48” deep with an appropriate hole saw or equivalent cutter.

NOTE: Be careful not to damage opposite face skin.

(b) Undercut core a minimum of 3/16 inch.

(c) Remove all loose debris using a vacuum cleaner or dry compressed 

air.

(d) Clean the inserts (3) by solvent washing or a similar method. Once 

cleaned, handle only with clean gloves and do not allow contact with 

dirty or oily surfaces.

(e) If desired, apply an adhesive backed tab to the insert to aid in 

installation.
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(f) Place the inserts (3) into the holes in forward bulkhead. Orient the 

inserts with the potting holes aligned vertically.

(g) Mix Magnobond 74-3 according to the manufacturer’s mixing 

instructions. Do not mix more than can be used within the pot life of the 

adhesive.

(h) Slowly inject Magnobond 74-3 into the lower potting hole of each 

insert. Stop injecting when adhesive starts to come out of the upper 

hole.

(i) Allow Magnobond 74-3 to cure according to manufacturer’s 

instructions.

(j) Remove the all protruding adhesive from the surface. Take care not to 

damage the insert or bulkhead. Remove the tab, if it was used.

(k) Using a permanent ink pen or equivalent, clearly mark the modified 

bulkhead with the following:

“Modified per Service Bulletin COMSB-25-52-001, Rev A”

Refer to Figure 9 (Sheet 1) on Page 85:

(69) Install inserts in the floor panels as follows:

(a) Open the holes backdrilled earlier to a diameter of 0.686-0.691 in. and 

0.48” deep with an appropriate hole saw or equivalent cutter.

NOTE: Be careful not to damage opposite face skin.

(b) Undercut core a minimum of 3/16 inch.

(c) Remove all loose debris using a vacuum cleaner or dry compressed 

air.

(d) Clean the inserts (3) by solvent washing or a similar method. Once 

cleaned, handle only with clean gloves and do not allow contact with 

dirty or oily surfaces.

(e) If desired, apply an adhesive backed tab to the insert to aid in 

installation.
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(f) Place the inserts (3) into the holes in the floor panels.

(g) Mix Magnobond 74-3 according to the manufacturer’s mixing 

instructions. Do not mix more than can be used within the pot life of the 

adhesive.

(h) Slowly inject Magnobond 74-3 into one potting hole of each insert. 

Stop injecting when adhesive starts to come out of the upper hole.

(i) Allow Magnobond 74-3 to cure according to manufacturer’s 

instructions.

(j) Remove the all protruding adhesive from the surface. Take care not to 

damage the insert or bulkhead. Remove the tab, if it was used.

(k) Re-identify the floor panels by appending the part number with:

-COM011

(l) Using a permanent ink pen or equivalent, clearly mark the modified 

floor panels with the following:

“Modified per Service Bulletin COMSB-25-52-001, Rev A”

On aircraft fitted with right-hand lower sidewall panel CRJLA03-03 or -07 or -11 or 

-15 (Pre-SB) or CRJLA015-003 or -007 (Pre-SB)

Refer to Figure 7 (Sheet 1) on Page 81:

(70) Install nutplate (1) on right-hand lower sidewall panel (5) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the right-hand sidewall (5) earlier to 

a diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the right-hand lower sidewall panel.

(d) Using a permanent ink pen or equivalent, identify the right-hand lower

sidewall panel (5) according to the following table:
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Pre-SB Part Number Post-SB Part Number

CRJLA03-03 CRJLA101-003

CRJLA03-07 CRJLA101-007

CRJLA03-11 CRJLA101-011

CRJLA03-15 CRJLA101-015

CRJLA015-007 CRJLA101-019

CRJLA015-003 CRJLA101-023

On aircraft fitted with right-hand upper sidewall panel CRJLA023-003 or -007 (PreSB)

Refer to Figure 7 (Sheet 2) on Page 82:

(71) Install nutplate (1) on right-hand upper sidewall panel (5) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the sidewall (5) earlier to a diameter 

of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the right-hand lower sidewall panel.

(d) Using a permanent ink pen or equivalent, identify the right-hand upper

sidewall panel (5) according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA023-003 CRJLA106-003

CRJLA023-007 CRJLA106-007

On aircraft fitted with right-hand aft wall panel CRJLA017-003 (Pre-SB)

Refer to Figure 8 (Sheet 1) on Page 83:

(72) Install nutplate (1) on the right-hand aft wall panel (5) as follows:
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(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets (2) for the nutplates.

(b) Open the holes that were drilled in the aft-wall liner (5) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the right-hand lower sidewall panel

(5).

(d) Using a permanent ink pen or equivalent, identify the right-hand aft 

wall liner (5) according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA017-003 CRJLA180-003

On aircraft fitted with center aft wall panel CRJLA07-03 (Pre-SB)

Refer to Figure 8 (Sheet 1) on Page 83:

(73) Install nutplate (1) on the center aft wall panel (6) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the aft-wall liner (6) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the center aft wall panel.

(d) Using a permanent ink pen or equivalent, identify the center aft wall 

liner (6) according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA07-03 CRJLA181-007
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On aircraft fitted with left-hand aft wall panel CRJLA019-003 (Pre-SB)

Refer to Figure 8 (Sheet 2) on Page 84:

(74) Install nutplate (1) on the left-hand aft wall panel (17) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the aft-wall liner (17) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the left-hand lower sidewall panel.

(d) Using a permanent ink pen or equivalent, identify the left-hand aft wall 

liner (17) according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA019-003 CRJLA182-011

On aircraft fitted with harness cap CRJLA11-03 or -07 (Pre-SB)

Refer to Figure 10 (Sheet 1) on Page 86:

(75) Install nutplates (1) in the ends of the harness cap (7) as follows:

Note: This instruction applies only to the holes that were backdrilled 

through the harness cap flanges (8) and (9).

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the harness cap (7) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the harness cap.
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(d) Using a permanent ink pen or equivalent, identify the harness cap (7) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA11-03 CRJLA105-003

CRJLA11-07 CRJLA105-011

On aircraft fitted with harness cap CRJLA021-003 or -007 (Pre-SB)

Refer to Figure 10 (Sheet 1) on Page 86:

(76) Install nutplates (1) in the ends of the harness cap (10) as follows:

Note: This instruction applies only to the holes that were backdrilled 

through the harness cap flanges (11) and (12).

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the harness cap (10) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the harness cap.

(d) Using a permanent ink pen or equivalent, identify the harness cap (10) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA021-003 CRJLA107-003

CRJLA021-007 CRJLA107-007
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On all aircraft

Refer to Figure 10 (Sheet 1) on Page 86:

(77) Install nutplates (1) in the channels as follows:

Note: This instruction applies to the holes drilled in the channels during

steps (37) and (38).

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the channels earlier to a diameter of 

0.250-0.260 in.

(c) Install nutplates with rivets (2) in the channel.

(d) Re-identify the channels by appending the part number with:

-COM011

(e) Using a permanent ink pen or equivalent, clearly mark the modified 

channels with the following:

“Modified per Service Bulletin COMSB-25-52-001, Rev A”

Refer to Figure 10 (Sheet 3) on Page 88:

(78) Install nutplates (1) in the channels as follows:

Note: This instruction applies to the holes drilled in the channels during

steps (45) and (46).

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the channels earlier to a diameter of 

0.250-0.260 in.

(c) Install nutplates with rivets (2) in the channel.
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(d) Re-identify the channels by appending the part number with:

-COM011

(e) Using a permanent ink pen or equivalent, clearly mark the modified 

channels with the following:

“Modified per Service Bulletin COMSB-25-52-001, Rev A”

On aircraft fitted with harness cap CRJLA021-003 or -007 (Pre-SB)

Refer to Figure 10 (Sheet 2) on Page 87:

(79) Install nutplate (1) in the harness cap (5) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the harness cap (5) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the harness cap.

(d) Using a permanent ink pen or equivalent, identify the harness cap (5) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA021-003 CRJLA107-003

CRJLA021-007 CRJLA107-007

On aircraft fitted with harness cap CRJLA043-003 (Pre-SB)

Refer to Figure 10 (Sheet 3) on Page 88:

(80) Install nutplate (1) in the harness cap (7) as follows:

Note: This instruction applies to the holes drilled in step (48)
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(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the harness cap (7) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the harness cap.

(d) Using a permanent ink pen or equivalent, identify the harness cap (7) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA043-003 CRJLA141-003

On aircraft fitted with harness cap CRJLA047-003 or -007 or -015 (Pre-SB)

Refer to Figure 10 (Sheet 3) on Page 88:

(81) Install nutplate (1) in the harness cap (8) as follows:

Note: This instruction applies to the holes drilled in step (47)

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the harness cap (8) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the harness cap.

(d) Using a permanent ink pen or equivalent, identify the harness cap (8) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA047-003 CRJLA140-003
Service Bulletin COMSB-25-52-001

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CRJLA047-007 CRJLA140-007

CRJLA047-015 CRJLA140-013

On aircraft fitted with tie rod cap CRJLA039-001 (Pre-SB) or CJRLA051-001 (PreSB)

Refer to Figure 11 (Sheet 1) on Page 89:

(82) Install nutplates (1) in the tie rod cap (5) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the tie rod cap (5) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the tie rod cap.

(d) Using a permanent ink pen or equivalent, identify the tie rod cap (5) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA039-001 CRJLA103-001

On aircraft fitted with tie rod cap CRJLA049-001 (Pre-SB) or CRJLA048-001 (PreSB)

Refer to Figure 11 (Sheet 1) on Page 89:

(83) Install nutplates (1) in the tie rod cap (6) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the tie rod cap (6) earlier to a 

diameter of 0.250-0.260 in.
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(c) Install nutplates with rivets (2) in the tie rod cap.

(d) Using a permanent ink pen or equivalent, identify the tie rod cap (6) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA049-001 CRJLA104-001

CRJLA048-001 CRJLA104-003

On aircraft fitted with tie rod cap CRJLA050-001 (Pre-SB)

Refer to Figure 11 (Sheet 2) on Page 90:

(84) Install nutplates (1) in the tie rod cap (5) as follows:

(a) Using either a nutplate (1) or a nutplate jig, locate the holes for the 

rivets used to install the nutplates. Drill and countersink #40 holes to 

accept rivets for the nutplates.

(b) Open the holes that were drilled in the tie rod cap (5) earlier to a 

diameter of 0.250-0.260 in.

(c) Install nutplates with rivets (2) in the tie rod cap.

(d) Add two new slots in the tie rod cap as shown.

(e) Using a permanent ink pen or equivalent, identify the tie rod cap (5) 

according to the following table:

Pre-SB Part Number Post-SB Part Number

CRJLA050-001 CRJLA142-001

On aircraft fitted with access panel CRJLA05-03 (Pre-SB) or CRJLA031-003 (PreSB)

Refer to Figure 12 (Sheet 1) on Page 91:
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(85) Modify the access panel (1) according to this step OR step (86):

(a) Mark the outline of all foam tape installed on the backside of the 

access panel (1) using a felt marker or similar

(b) Remove the foam tape from the access panel. Ensure that all adhesive 

residue has been completely removed. 

NOTE: Use only non-metallic scrapers when removing foam tape. 

Metal scrapers or other sharp tools may damage the panel.

(c) Remove one rivets (3) from each end of each row of rivets on the 

access panel (1).

(d) Apply P-629 seam tape over each joint between a stainless steel 

component and an FML panel. Seam tape must be 3 inches wide.

(e) Make a hole in the seam tape at the hole where a rivet was removed to 

allow re-installation of the rivet.

(f) Wet install rivets (3) in the original holes using RTV106.

(g) Apply foam tape (4) in the same location as the original foam tape. Use 

the marked outlines as a guide.

(h) Using a permanent ink pen or equivalent, clearly mark the modified 

access panel (1) with the following:

“Modified per Service Bulletin COMSB-25-52-001 Rev A”

(86) Modify the access panel (1) according to this step OR step (85):

(a) Mark the outline of all foam tape installed on the backside of the 

access panel (1) using a felt marker or similar

(b) Remove the foam tape from the access panel. Ensure that all adhesive 

residue has been completely removed. 

NOTE: Use only non-metallic scrapers when removing foam tape. 

Metal scrapers or other sharp tools may damage the panel.

(c) Remove all rivets (3) from the access panel (1).
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(d) Remove all fay-sealant between the three components that make up 

(1).

(e) Clean all mating surfaces using acetone or methyl-ethyl-keytone.

(f) Fay seal using RTV106 on all mating surfaces.

(g) Wet install rivets (3) using RTV106. Install a washer (2) on the backside of all rivets before squeezing.

(h) Apply fillet of RTV106 around perimeter of joint. Fillet is only required 

on side facing the interior of the cargo compartment.

(i) Allow sealant to cure.

(j) Apply foam tape (4) in the same location as the original foam tape. Use 

the marked outlines as a guide.

(k) Using a permanent ink pen or equivalent, identify the access panel (1) 

according to the following table.

Pre-SB Part Number Post-SB Part Number

CRJLA05-03 CRJLA102-003

CRJLA031-003 CRJLA102-007

On all aircraft

Refer to Figure 2 (Sheet 2) on Page 62:

(87) Install the forward liner panels (4) and (5) using washers (1) and screws 

(2).

(88) Install the center forward liner panel (6) using washers (1) and screws (2) 

and (3).

(89) Install the forward wall access panel (7) using washers (1) and screws (3).

Refer to Figure 2 (Sheet 3):
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(90) Install the right-hand aft wall panel (5) using screws (2) and washers (1). 

Do not install fasteners in the holes that will be used to affix corner angles 

or joint overlaps.

(91) Install the left-hand aft wall panel (6) using screws (2) and washers (1). Do 

not install fasteners in the holes that will be used to affix corner angles or 

joint overlaps.

(92) Install the center aft wall panel (7) and joint overlaps (8) and (9). Use 

washers (1) and screws (3) to pass through the joint overlaps and center 

panel into the aircraft structure. Do not install fasteners that pass through 

the joint overlaps and right-hand aft wall panel or left-hand aft wall panel.

(93) Install the left-hand aft wall kickplate (10). Use washers (1) and screws (2) 

to attach to the aft wall liner. Use washers (1) and screws (4) to attach to 

the floor.

(94) Install the right-hand aft wall kickplate (11). Use washers (1) and screws 

(2) to attach to the aft wall liner. Use washers (1) and screws (4) to attach 

to the floor.

Refer to Figure 2 (Sheet 4) on Page 64:

(95) Install the lower right-hand sidewall panel (4) as follows:

(a) Position the liner panel in the aircraft.

(b) Affix liner panel in place using screws (2) and washers (1).

NOTE: Do not install fasteners along upper edge where harness cap 

is installed or along forward or aft edges where angles are 

installed.

(c) Affix the liner panel to the floor using screws (2) and washers (1).

(96) Install the upper right-hand sidewall panel (5) as follows:

(a) Position the liner panel in the aircraft.

(b) Temporarily affix upper edge using 2 to 3 fasteners or as required.

(97) Install the lower right-hand harness cap (6) as follows:
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(a) Position the harness cap in the aircraft.

(b) Affix harness cap using screws (3) and washers (1). Screws pass 

through harness cap (6), sidewall panels (4) and (5) and into aircraft 

structure.

(c) Fillet seal edges of the harness cap (6) using RTV-106 sealant.

Refer to Figure 2 (Sheet 5) on Page 65:

(98) Install access panel (4) as follows:

(a) Position the access panel in the aircraft.

(b) Affix access panel using washers (1) and screws (2) and (3).

(c) Fillet seal around the edge of the access panel (4) using RTV-106 

sealant.

Refer to Figure 2 (Sheet 6) on Page 66:

(99) Install the left-hand lower sidewall panel (4) as follows:

(a) Position the sidewall panel in the aircraft.

(b) Affix the access panel using washers (1) and screws (2).

NOTE: Do not install fasteners along upper edge where harness cap 

is installed or along forward or aft edges where angles are 

installed.

(100) Install the left-hand upper sidewall panel (5) as follows:

(a) Position the panel in the aircraft.

(b) Temporarily affix upper edge using 2 to 3 fasteners or as required.

(101) Install the left-hand lower harness cap (6) as follows:

(a) Position the harness cap (6) in the aircraft.
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(b) Affix harness cap (6) using screws (3) and washers (1). Screws pass 

through harness cap (6), sidewall panels (4) and (5) and into aircraft 

structure.

(c) Fillet seal the edges of the harness cap (6) using RTV-106 sealant.

Refer to Figure 2 (Sheet 7) on Page 67:

(102) Install the right-hand ceiling panel (4) as follows:

(a) Position the panel in the aircraft.

(b) Affix the panel using screws (2) and washers (1).

NOTE: Do not install fasteners along the lower edge where the 

harness cap attaches. Also, do not install fasteners along the 

forward or aft edges where the corner angles are installed.

(103) Install the upper right-hand harness cap (5) as follows:

(a) Remove the fasteners used to temporarily attach the upper edge of the 

upper sidewall panel.

(b) Position the harness cap (5) in the aircraft.

(c) Affix the harness cap using screws (3) and washers (1). Screws should 

pass through the harness cap, through the liner panels and into the 

aircraft structure.

(d) Fillet seal the edges of the harness cap (6) using RTV-106 sealant.

(104) Fillet seal between the ceiling panel (4) and the ceiling center splice using 

RTV-106 sealant.

Refer to Figure 2 (Sheet 8) on Page 67:

(105) Install the left-hand ceiling panel (4) using washers (1) and screws (2). Do 

not install fasteners in the bottom row of holes.

(106) Fillet seal between the ceiling panel (4) and the ceiling center splice using 

RTV-106 sealant.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 40 of 92

(107) Install the upper left-hand harness cap (5) as follows:

(a) Position the harness cap in the aircraft.

(b) Affix the harness cap using washers (1) and screws (3). Screws should 

pass through the harness cap, through the liner panels and into the 

aircraft structure.

(c) Fillet seal the edges of the harness cap (5) using RTV-106 sealant.

Refer to Figure 2 (Sheet 10) on Page 70:

(108) Install the protective barriers (4), (5), (6) and (8) using washers (1) and 

screws (2).

(109) Install the aft wall extension (7) using washers (1) and screws (3).

(110) Fillet seal the edges of the protective barriers (4), (5), (6) and (8) and the 

aft wall extension (7) using RTV-106 sealant.

Refer to Figure 2 (Sheet 11) on Page 71:

(111) Install the forward above door liner panel (4) using washers (1) and 

screws (2). Do not fasten the forward or top edges of the panel.

(112) Install the aft above door liner panel (5) using washers (1) and screws (2). 

Do not fasten the aft or top edges of the panel.

(113) Fillet seal the joint between the above door liner panels (4) and (5) using 

RTV-106 sealant.

(114) Position the door shroud (6) over the above door liner panels (4) and (5) in 

the aircraft.

(115) Install the door shroud (6) using washers (1) and screws (3).

(116) Fillet seal the perimeter of the above door liner panels (4) and (5) and the 

door shroud using RTV-106 sealant.

Refer to Figure 3 (Sheet 1) on Page 72:

(117) Attach the angles (4), (5) and (6) using washers (1) and screws (2).
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

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(118) Attach the angles (7), (8) and (9) using washers (1) and screws (3).

(119) Fillet seal the edges of the angles (4), (5), (6), (7), (8) and (9) using RTV106 sealant.

Refer to Figure 3 (Sheet 2) on Page 73:

(120) Attach the angles (3), (4), (5), (6), (7) and (8) using washers (1) and 

screws (2).

(121) Fillet seal the edges of the angles (3), (4), (5), (6), (7) and (8) using RTV106 sealant.

Refer to Figure 3 (Sheet 3) on Page 74:

(122) Attach the angles (4), (5) and (6) using washers (1) and screws (2).

(123) Attach the angle (7) using washers (1) and screws (3).

(124) Fillet seal the edges of the angles (4), (5), (6) and (7) using RTV-106 

paste sealant.

Refer to Figure 4 (Sheet 1) on Page 75:

(125) Attach the tie rod caps (4) and (5) using screws (3) and washers (1).

(126) Attach the tie rod caps (6) and (7) using washers (1) and screws (2).

(127) Fillet seal the edges of the tie rod caps (4), (5), (6) and (7) using RTV-106 

sealant.

On aircraft fitted with tie rod cap CRJLA104-001 or -003 (Post-SB)

(128) Attach the tie rod cap flange (8) using washers (1) and screws (3).

(129) Fillet seal the edges of the tie rod cap flanges (8) using RTV-106 sealant.

On aircraft fitted with tie rod cap CRJLA103-001 (Post-SB)

(130) Attach the tie rod cap flange (9) using washers (1) and screws (3).

(131) Fillet seal the edges of the tie rod cap flanges (9) using RTV-106 sealant.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

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On aircraft fitted with tie rod cap CRJLA104-003 (Post-SB)

Refer to Figure 4 (Sheet 1) on Page 75:

(132) Apply P-629 seam tape as follows:

(a) Remove the two screws at the ends of one flange of the tie rod cap 

CRJLA104-003 (6).

(b) Apply seam tape over the joint between the liner and the flange with 

the screws removed. Seam tape must be 3 inches wide.

(c) Make a hole in the seam tape at the locations of the removed screws.

(d) Reinstall removed screws.

(e) Repeat this procedure for all remaining flanges of CRJLA104-003 (6).

On aircraft fitted with harness cap CRJLA105-003 or -011 (Post-SB)

Refer to Figure 5 (Sheet 1) on Page 77:

(133) Install the harness cap flanges (5). Use washers (1) and screws (2) to

attach the flanges (5) to the harness caps (4). Use washers (1) and 

screws (3) to attach the flanges (5) to the angles and panels.

(134) Fillet seal the edges of the harness cap flange (5) using RTV-106 sealant.

On aircraft fitted with harness cap CRJLA107-003 or -007 (Post-SB)

Refer to Figure 5 (Sheet 1) on Page 77:

(135) Install the harness cap flanges (7). Use washers (1) and screws (2) to 

attach the flanges (7) to the harness caps (6). Use washers (1) and 

screws (3) to attach the flanges (7) to the angles and panels.

(136) Fillet seal the edges of the harness cap flange (7) using RTV-106 sealant.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 43 of 92

On aircraft fitted with harness cap CRJLA105-003 or -011 (Post-SB)

Refer to Figure 5 (Sheet 2) on Page 78:

(137) Install the harness cap flanges (5). Use washers (1) and screws (2) to 

attach the flanges (5) to the harness caps (4). Use washers (1) and 

screws (3) to attach the flanges (5) to the angles and panels.

(138) Fillet seal the edges of the harness cap flange (5) using RTV-106 sealant.

On aircraft fitted with harness cap CRJLA107-003 or -007 (Post-SB)

Refer to Figure 5 (Sheet 2) on Page 78:

(139) Install the harness cap flanges (7). Use washers (1) and screws (2) to 

attach the flanges (7) to the harness caps (6). Use washers (1) and 

screws (3) to attach the flanges (7) to the angles and panels.

(140) Fillet seal the edges of the harness cap flange (7) using RTV-106 sealant.

On aircraft fitted with harness cap CRJLA141-003 (Post-SB)

Refer to Figure 5 (Sheet 3) on Page 79:

(141) Install the harness cap flanges (5). Use washers (1) and screws (2) to 

attach the flanges (5) to the harness caps (4). Use washers (1) and 

screws (3) to attach the flanges (5) to the angles and panels.

(142) Fillet seal the edges of the harness cap flange (5) using RTV-106 sealant.

On aircraft fitted with harness cap CRJLA140-003 or -007 or -013 (Post-SB)

Refer to Figure 5 (Sheet 3) on Page 79:

(143) Install the harness cap flanges (7). Use washers (1) and screws (2) to 

attach the flanges (7) to the harness caps (6). Use washers (1) and 

screws (3) to attach the flanges (7) to the angles and panels.

(144) Fillet seal the edges of the harness cap flange (7) using RTV-106 sealant.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 44 of 92

On all aircraft

(145) Install the louvered window cage in the forward bulkhead.

Refer to Figure 4 (Sheet 2) on Page 76:

(146) Attach the tie rod caps (3), (4) and (5) using washers (1) and screws (2).

(147) Fillet seal the edges of the tie rod caps (3), (4) and (5) using RTV-106 

sealant.

Refer to Figure 2 (Sheet 9) on Page 69:

(148) Install the duct (4) using screws (3) and washers (1).

(149) Install the center aft wall kickplate (5) using screws (2) and washers (1).

For aircraft that have a cargo-compartment load divider

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

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

(151) Fillet seal around the end fittings using RTV-106 sealant.

(152) Install the cargo restraint posts in the cargo compartment (Refer to AMM 

25-51-01-400-802).

For all aircraft

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

(154) Fillet seal around the cargo smoke detector using RTV-106 sealant.

Refer to Figure 13 (Sheet 1) on Page 92:

(155) Install the cargo firex discharge-line using the procedure given in AMM 26-

25-07-400-801 with the following amendments:

(a) At FS614.50, FS603.30, FS595.75 and FS586.29, install the washer 

(1) and replace the spacer (3) between the ceiling liner and the firex 

cover.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 45 of 92

(b) At FS611.50 and FS587.79, install the washer (1) and the spacer (2) 

between the ceiling liner and the clamp that attaches the piccolo tube 

to the structure.

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

(c) At FS567.62, install the washer (1) and replace the spacer (3) between 

the ceiling liner and the firex cover.

(d) At FS569.12, install the washer (1) and the spacer (2) between the 

ceiling liner and the clamp that attaches the piccolo tube to the 

structure.

(e) At FS577.60, install the washer (1) and the spacer (3) between the 

ceiling liner and the firex cover.

On aircraft that have piccolo tube 601R99011-13

(f) At FS577.60, install the washer (1) and the spacer (2) between the 

ceiling liner and the clamp that attaches the piccolo tube to the 

structure.

For all aircraft

(156) Install the cargo light with the kept hardware. Refer to AMM 33-31-01-400-

801.

(157) Apply a fillet seal of RTV-106 sealant around the cargo lights. Refer to 

AMM 51-23-00-390-807.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 46 of 92

C. Job Close-Out

(1) Remove all tools, equipment and unwanted materials from the cargo 

compartment.

(2) Install all loose items that were removed from the cargo compartment.

(3) If removed, install the baggage bay door.

(See AMM 52-31-00-400-801)

(4) If removed, install the Inlet Duct Screen.

(5) If removed, install the Exhaust Duct Screen.

(6) Perform the adjustment of the cargo compartment door

(Refer to AMM 52-31-00-820-801)

(7) Reconnect the electrical systems that were disconnected as part of this 

service bulletin.

(8) Apply external AC power to the aircraft.

(Refer to AMM 12-00-07-861-801)

(9) Perform the operational test of the cargo compartment door

(Refer to AMM 52-31-00-710-801)

(10) Perform the operational test of the cargo compartment door warning 

system

(Refer to AMM 52-70-02-710-801)

(11) Perform the Operational Test of the Cargo Smoke Detection System

(Refer to AMM 26-15-00-710-801)

(12) Perform the Operational Test of the Cargo Lights

(Refer to AMM 33-31-00-710-801)

(13) Perform the Leak Test for the Air Conditioning System

(Refer to AMM 21-51-00-790-801)

(14) Perform the Operational Test of the Cargo Fire-Extinguisher System

(Refer to AMM 26-25-00-710-801)
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 47 of 92

(15) When this service bulletin is completed, make this entry in the applicable 

logbook(s):

Service Bulletin COMSB-25-52-001, Rev A, Equipment/Furnishings –

Cargo Compartment Linings – Modification and Replacement of Liners in 

the Cargo Compartment incorporated.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 48 of 92

3. MATERIAL INFORMATION

A. Kit Information

Contact Comtek Advanced Structures for a complete listing of parts required 

to complete this Service Bulletin.

Comtek Advanced Structures

1360 Artisans Court

Burlington, Ontario, L7L 5Y2, Canada

Phone: (905) 331-8121

Fax: (905) 331-8125

B. Consumable Information

Item Suggested Vendor Notes

Non-Solvent 

based cleaner 

or detergent

Commercial

Acetone or 

Methyl Ethyl 

Keytone

Commercial

Nitrile or Latex 

Disposable 

Gloves

Commercial

Masking Tape Commercial

Mixing Cups Commercial Must not have wax or

silicone coating on the 

inner surface. Cups 

must be resistant to 

epoxy

Stir Sticks Commercial

Cotton Wipes Commercial

RTV-106 

Sealant

E.B. Peerless (905) 362-1151

Magnobond 74-

3 Potting 

Compound

Glotrax (905) 377-1441

Magnolia US (800) 831-8031

P-629 Seam 

Tape, 3” Wide

Joli Distrubution (514) 335-3172
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 49 of 92

C. Special Tools and Equipment

Item Suggested Vendor Notes

Weighing Scale Commercial 0.1g Accuracy

Capacity 200g

Hole Saw US Industrial (800) 521 4800 0.686” diameter hole 

saw (diamond or 

carbide grit) With 3/16” 

pilot
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 50 of 92

D. Disposition of Parts

The following table provides a disposition for each Comtek aftermarket part. To use this table, look up the part 

number of each part removed from the aircraft. The Disposition Code (DC) shows whether that part will be 

reworked or discarded. Any relevant notes are shown in the Notes column (such as other parts affected by a 

disposition). New parts added by this service bulletin are also shown in this table.

Note: This table lists all parts produced by Comtek Advanced Structures. Not all parts will be installed on any 

one aircraft.

Pre-SB P/N Name Qty DC Post-SB P/N Notes

CRJLA03-01 Sidewall Assy, Lower, RH 1 DIS CRJLA201-003 Replace CRJLA039-001 with 

CRJLA203-001

Replace CRJLA049-001 with 

CRJLA204-001

CRJLA03-03 Sidewall Assy, Lower, RH 1 RWK CRJLA101-003

CRJLA03-05 Sidewall Assy, Lower, RH 1 DIS CRJLA201-003 Replace CRJLA039-001 with 

CRJLA203-001

CRJLA03-07 Sidewall Assy, Lower, RH 1 RWK CRJLA101-007

CRJLA03-09 Sidewall Assy, Lower, RH 1 DIS CRJLA201-003 Replace CRJLA039-001 with 

CRJLA203-001

Replace CRJLA049-001 with 

CRJLA204-001

CRJLA03-11 Sidewall Assy, Lower, RH 1 RWK CJRLA101-011

CRJLA03-13 Sidewall Assy, Lower, RH 1 DIS CRJLA201-003
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 51 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

CRJLA03-15 Sidewall Assy, Lower, RH 1 RWK CRJLA101-015

CRJLA015-005 Sidewall Assy, Lower, RH 1 DIS CRJLA201-003 Replace CRJLA039-001 with 

CRJLA203-001

Replace CRJLA049-001 with 

CRJLA204-001

CRJLA015-007 Sidewall Assy, Lower, RH 1 RWK CRJLA101-019

CRJLA015-001 Sidewall Assy, Lower, RH 1 DIS CRJLA201-003 Replace CRJLA039-001 with 

CJRLA203-001

Replace CRJLA049-005 with 

CRJLA204-001

CRJLA015-003 Sidewall Assy, Lower, RH 1 RWK CRJLA101-023

CJRLA013-001 Sidewall Assy, Lower, RH 1 DIS CRJLA201-007

CRJLA013-003 Sidewall Assy, Lower, RH 1 RWK CRJLA101-027

CRJLA013-005 Sidewall Assy, Lower, RH 1 DIS CRJLA201-007 Replace CRJLA031-003 with 

CRJLA202-003

CRJLA013-007 Sidewall Assy, Lower, RH 1 RWK CRJLA101-031

CRJLA05-01 Access Panel, Large, RH 1 DIS CRJLA202-003

CRJLA05-01 Access Panel, Large, RH 1 RWK CRJLA05-01 Apply seam tape and foam tape only

CRJLA05-03 Access Panel, Large, RH 1 RWK CRJLA102-003

CRJLA031-001 Access Panel, Small, RH 1 DIS CRJLA202-005

CRJLA031-001 Access Panel, Small, RH 1 RWK CRJLA031-001 Apply seam tape and foam tape only

CRJLA031-003 Access Panel, Small, RH 1 RWK CRJLA102-007
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 52 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

CRJLA039-001 Cap Assy, Lower, RH 1 RWK CRJLA103-001

CRJLA051-001 Cap Assy, Lower, RH 1 DIS CRJLA203-001

CRJLA049-001 Cap Assy, Upper, RH 1 RWK CRJLA104-001

CRJLA048-001 Cap Assy, Upper, RH 1 RWK CRJLA104-003

CRJLA052-001 Cap Assy, Upper, RH 1 RWK CRJLA204-001

- Angle, Aft, Sidewall, RH 1 NEW CRJLA301-001

- Angle, Lower, Fwd, 

Sidewall, RH

1 NEW CRJLA301-003

- Angle, Mid, Fwd, Sidewall, 

RH

1 NEW CRJLA301-005 Install with Sidewall CRJLA101-003 

or -007 or -011 or -019

- Angle, Mid, Fwd, Sidewall, 

RH

1 NEW CRJLA301-009 Install with Sidewall CJRLA101-015 

or -023 or CRJLA202-003

- Angle, Mid, Fwd, Sidewall, 

RH

1 NEW CRJLA301-011 Install with Sidewall CRJLA101-027 

or -031 or CJRLA202-003

- Angle, Upper, Fwd, 

Sidewall, RH

1 NEW CRJLA301-013

- Cap Flange, Lower, 

Sidewall, RH

1 NEW CRJLA302-001 Install with Cap CRJLA103-001

- Cap Flange, Upper, 

Sidewall, RH

1 NEW CRJLA303-001 Install with Cap CRJLA104-001

- Cap Flange, Upper, 

Sidewall, RH

1 NEW CRJLA303-003 Install with Cap CRJLA104-003
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 53 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

CRJLA11-01 Harness Cap, Lower, RH 1 DIS CRJLA205-003

CRJLA11-03 Harness Cap, Lower, RH 1 RWK CJRLA105-003

CRJLA11-05 Harness Cap, Lower, RH 1 DIS CRJLA205-003

CRJLA11-07 Harness Cap, Lower, RH 1 RWK CRJLA105-011

- Cap Flange, Lower, RH, 

Fwd

1 NEW CRJLA304-001

- Cap Flange, Lower, RH, 

Aft

1 NEW CRJLA304-003

CRJLA023-001 Sidewall, Upper, RH 1 DIS CRJLA206-003

CRJLA023-003 Sidewall, Upper, RH 1 RWK CRJLA106-003

CRJLA023-005 Sidewall, Upper, RH 1 DIS CRJLA206-003

CRJLA023-007 Sidewall, Upper, RH 1 RWK CRJLA106-007

- Angle, Aft, Upper, 

Sidewall, RH

1 NEW CRJLA301-015

- Angle, Fwd, Upper 

Sidewall, RH

1 NEW CRJLA301-017

CRJLA021-001 Harness Cap, Upper, RH 1 DIS CRJLA207-003

CRJLA021-003 Harness Cap, Upper, RH 1 RWK CRJLA107-003

CRJLA021-005 Harness Cap, Upper, RH 1 DIS CRJLA207-003

CRJLA021-007 Harness Cap, Upper, RH 1 RWK CRJLA107-007
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 54 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

- Cap Flange, Upper 

Harness Cap. RH

2 NEW CRJLA306-001

- Panel, Ceiling, RH 1 NEW CRJLA220-003

- Panel, Ceiling, RH 1 NEW CRJLA220-007

- Panel, Ceiling, RH 1 NEW CRJLA220-011

- Angle, Aft, Ceiling, RH 1 NEW CRJLA301-023

- Angle, Lwr, Fwd, Ceiling, 

RH

1 NEW CRJLA301-025

- Angle, Upper, Fwd, 

Ceiling, RH

1 NEW CRJLA301-027 Install with CRJLA220-003 or -007

- Angle, Upper, Fwd, 

Ceiling, RH

1 NEW CRJLA301-029 Install with CRJLA220-011

- Panel, Ceiling, LH 1 NEW CRJLA221-003

- Panel, Ceiling, LH 1 NEW CRJLA221-007

- Angle, Aft, Ceiling, LH 1 NEW CRJLA301-033

- Angle, Lwr, Fwd, Ceiling, 

LH

1 NEW CRJLA301-035 Install with CRJLA221-003 or -007

- Angle, Upr, Ceiling, LH 1 NEW CRJLA301-041 Install with CRJLA221-003

- Angle, Upr, Ceiling, LH 1 NEW CRJLA301-043 Install with CRJLA221-007

- Cap Assy, Ceiling, RH 3 NEW CRJLA222-001

- Support, Center, Ceiling 1 NEW CRJLA225-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 55 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

CRJLA047-001 Harness Cap, Upper, LH 1 DIS CRJLA240-003

CRJLA047-005 Harness Cap, Upper, LH 1 DIS CRJLA240-003

CRJLA047-003 Harness Cap, Upper, LH 1 RWK CRJLA140-003

CRJLA047-007 Harness Cap, Upper, LH 1 RWK CRJLA140-007

CRJLA047-013 Harness Cap, Upper, LH 1 DIS CRJLA240-003

CRJLA047-015 Harness Cap, Upper, LH 1 RWK CRJLA140-013

- Sidewall, Upper, LH 1 NEW CRJLA241-003

- Angle, Fwd, Upper 

Sidewall, LH

1 NEW CRJLA301-045

CRJLA043-001 Harness Cap, Lower, LH 1 DIS CRJLA242-003

CRJLA043-003 Harness Cap, Lower, LH 1 RWK CRJLA141-003

- Cap Flange, Upper 

Harness Cap, LH

1 NEW CRJLA340-001

- Cap Flange, Lower 

Harness Cap, LH

1 NEW CRJLA342-001

- Sidewall, Lower, LH 1 NEW CRJLA243-003

- Angle, Lower, Fwd, 

Sidewall, LH

1 NEW CRJLA301-049

- Angle, Mid, Fwd, Sidewall, 

LH

1 NEW CRJLA301-053

- Angle, Upper, Fwd, 

Sidewall, LH

1 NEW CRJLA301-057
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 56 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

CRJLA050-001 Cap, Lower, Sidewall, LH 1 RWK CRJLA142-001

- Cap, Lower, Sidewall, LH 1 NEW CRJLA244-001

- Cap, Upper, Sidewall, LH 1 NEW CRJLA245-001

- Cap Flange, Lower 

Sidewall, LH

1 NEW CRJLA341-001 Install with CRJLA142-001 only 

- Liner, Above Door (Fwd) 1 NEW CRJLA246-001

- Liner, Above Door (Aft) 1 NEW CRJLA247-001

- Shroud, Cargo 

Compartment

1 NEW CRJLA248-001

CRJLA017-001 Liner, Aft Wall, RH 1 DIS CRJLA280-003

CRJLA017-003 Liner, Aft Wall, RH 1 RWK CRJLA180-003

CRJLA07-01 Liner, Aft Wall, Ctr 1 DIS CRJLA281-003

CRJLA07-03 Liner, Aft Wall, Ctr 1 RWK CRJLA181-007

- Joint Overlap, Aft Wall, 

Center, RH

1 NEW CRJLA281-023

- Joint Overlap, Aft Wall, 

Center, LH

1 NEW CRJLA281-027

CRJLA019-001 Liner, Aft Wall, LH 1 DIS CRJLA282-011

CRJLA019-003 Liner, Aft Wall, LH 1 RWK CRJLA182-011

- Wall Extension, Aft Wall, 

LH

1 NEW CRJLA282-021
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 57 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

CRJLA09-01 Duct, Aft Wall, Center 1 DIS CRJLA283-003

CRJLA09-07 Duct, Aft Wall, Center 1 RWK CRJLA183-007

CRJLA09-03 Duct, Aft Wall, Center 1 RWK CRJLA183-003

CRJLA09-05 Duct, Aft Wall, Center 1 DIS CRJLA283-001

CRJLA017-021 Kickplate, Aft Wall, RH 1 DIS CRJLA380-001

CRJLA017-023 Kicplate, Aft Wall, RH 1 DIS CRJLA380-001

CRJLA09-21 Kickplate, Aft Wall, Center 1 DIS CRJLA381-001

CRJLA09-023 Kickplate, Aft Wall, Center 1 DIS CRJLA381-001

CRJLA019-021 Kickplate, Aft Wall, LH 1 DIS CRJLA382-001

CRJLA019-023 Kickplate, Aft Wall, LH 1 DIS CRJLA382-001

- Protective Barrier, Aft 

Wall, Lower

1 NEW CRJLA284-001

- Protective Barrier, Aft 

Wall, Upper

1 NEW CRJLA284-005

- Protective Barrier, Aft 

Wall, Mid Otbd

1 NEW CRJLA284-009

- Protective Barrier, Aft 

Wall, Mid Inbd

1 NEW CRJLA284-013

- Liner, Fwd Wall, RH 1 NEW CRJLA260-003

- Liner, Fwd Wall, RH 1 NEW CRJLA260-007

- Liner, Fwd Wall, Ctr 1 NEW CRJLA261-003
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 58 of 92

Pre-SB P/N Name Qty DC Post-SB P/N Notes

- Liner, Fwd Wall, Ctr 1 NEW CRJLA261-007

- Liner, Fwd Wall, LH 1 NEW CRJLA262-003

- Liner, Fwd Wall, LH 1 NEW CRJLA262-007

- Access Door, Fwd Wall, 

RH

1 NEW CRJLA263-003

Disposition Codes (DC):

 DIS: Discard

 RWK: Rework as shown in this service bulletin

 NEW: New part
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 59 of 92

Figure 1 Pre-SB Liner Removal

Figure 1 (Sheet 1) Pre-SB Liner Removal

LEGEND

1. Access door

CRJLA05-01 or -03 or CRJLA031-001 or -003

2. Right-hand lower sidewall

CRJLA03-01 or -03 or -05 or -07 or -09 or -11 or -13 or -15 or 

CRJLA015-001 or -003 or -005 or -007 or CRJLA013-001 

or -003 or -005 or -007

3. Right-hand upper sidewall

CRJLA023-001 or -003 or -005 or -007 or CRJLA025-001 

or -003

4. Right-hand lower harness cap

CRJLA11-01 or -03 or -05 or -07 or CRJLA027-001 or -003

5. Right-hand upper harness cap

CRJLA021-001 or -003 or -005 or -007 or CRJLA029-001 

or -003

6. Right-hand lower tie rod cap

CRJLA039-001 or CRJLA051-001

7. Right-hand upper tie rod cap

CRJLA039-001 or CRJLA048-001 or CRJLA049-001 or 

CRJLA052-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 60 of 92

Figure 1 (Sheet 2) Pre-SB Liner Removal

LEGEND

8. Center Aft Wall Kickplate 

CRJLA09-21 or -023

9. Duct

CRJLA09-01 or -03 or -05 or -07

10. Right aft wall angle

CRJLA017-021 or -023

11. Left aft wall angle

CRJLA019-021 or -023

12. Right aft wall

CRJLA017-001 or -003

13. Left aft wall

CRJLA019-001 or -003

14. Center aft wall

CRJLA07-01 or -03
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 61 of 92

Figure 2 Liner Installation

Figure 2 (Sheet 1) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-08

3. Center Ceiling Support

CRJLA225-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 62 of 92

Figure 2 (Sheet 2) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-06

3. Screw

MS27039-1-07

4. Left-Hand Forward Wall Liner

CRJLA262-003 or

CRJLA262-007

5. Right-Hand Forward Wall Liner

CRJLA260-003 or

CRJLA260-007

6. Center Forward Wall Liner

CRJLA261-003 or

CRJLA261-007

7. Forward Wall Access Panel

CRJLA263-003
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 63 of 92

Figure 2 (Sheet 3) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-06

3. Screw

MS27039-1-07

4. Screw

MS27039-1-05

5. Right-Hand Aft Wall

CRJLA280-003 or

CRJLA017-003 (Pre-SB)

CRJLA180-003 (Post-SB)

6. Left-Hand Aft Wall

CRJLA282-011 or

CRJLA019-003 (Pre-SB)

CRJLA182-011 (Post-SB)

7. Center Aft Wall

CRJLA281-003 or

CRJLA07-03 (Pre-SB)

CRJLA181-007 (Post-SB)

8. Joint Overlap, RH

CRJLA281-023

9. Joint Overlap, LH

CRJLA281-027

10. Left-Hand Aft Wall Kickplate

CRJLA382-001

11. Right-Hand Aft Wall Kickplate

CRJLA380-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 64 of 92

Figure 2 (Sheet 4) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-06

3. Screw

MS27039-1-09

4. Lower Right-Hand Sidewall Panel

CRJLA201-003 or -007 or

CRJLA03-03 (Pre-SB)

CRJLA101-003 (Post-SB) or 

CRJLA03-07 (Pre-SB)

CRJLA101-007 (Post-SB) or

CRJLA03-11 (Pre-SB)

CRJLA101-011 (Post-SB) or

CRJLA03-15 (Pre-SB)

CRJLA101-015 (Post-SB) or

CRJLA015-007 (Pre-SB)

CRJLA101-019 (Post-SB) or

CRJLA015-003 (Pre-SB)

CRJLA101-023 (Post-SB)

5. Upper Right-Hand Sidewall Panel

CRJLA206-003 or -007 or

CRJLA023-003 (Pre-SB)

CRJLA106-003 (Post-SB) or

CRJLA023-007 (Pre-SB)

CRJLA106-007 (Post-SB)

6. Lower RH Harness Cap

CRJLA205-003 or -007 or

CRJLA11-03 (Pre-SB)

CRJLA105-003 (Post-SB) or

CRJLA11-07 (Pre-SB)

CRJLA105-011 (Post-SB)

NOTES

1. Temporarily affix upper 

edge with 2 to 3 screws as 

required.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 65 of 92

Figure 2 (Sheet 5) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-08

3. Screw

MS27039-1-09

4. Access Panel

CRJLA202-003 or -005 or

CRJLA05-03 (Pre-SB)

CRJLA102-003 (Post-SB) or

CRJLA031-003 (Pre-SB)

CRJLA102-007 (Post-SB)
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 66 of 92

Figure 2 (Sheet 6) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-08

3. Screw

MS27039-1-09

4. LH Lower Sidewall

CRJLA243-001 or -003 or -005 or -007

5. LH Upper Sidewall

CRJLA241-001 or -003 or -005 or -007

6. Harness Cap

CRJLA242-003 or

CRJLA043-003 (Pre-SB)

CRJLA141-003 (Post-SB)

NOTES

1. Temporarily affix upper edge 

with 2 to 3 screws as 

required.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 67 of 92

Figure 2 (Sheet 7) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-08

3. Screw

MS27039-1-09

4. RH Ceiling Panel

CRJLA220-003 or -007 or -011

5. Upper RH Harness Cap

CRJLA207-003 or

CRJLA021 -003 (Pre-SB)

CRJLA107 -003 (Post-SB) or

CRJLA021 -007 (Pre-SB)

CRJLA107 -007 (Post-SB)
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 68 of 92

Figure 2 (Sheet 8) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-08

3. Screw

MS27039-1-09

4. LH Ceiling Panel

CRJLA221-003

5. Upper LH Harness Cap

CRJLA240-003 or

CRJLA047-003 (Pre-SB)

CRJLA140-003 (Post-SB) or

CRJLA047-007 (Pre-SB)

CRJLA140-007 (Post-SB) or

CRJLA047-015 (Pre-SB)

CRJLA140-013 (Post-SB)
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 69 of 92

Figure 2 (Sheet 9) Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-09

3. Screw

MS27039-1-10

4. Duct

CRJLA283-001 or -003 or

CRJLA09-03 or -07 (Pre-SB)

CRJLA183-003 or -007 (Post-SB)

5. Center Aft Wall Kickplate

CRJLA381-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 70 of 92

Figure 2 (Sheet 10)Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-09

3. Screw

MS27039-1-09

4. Protective Barrier, Upper

CRJLA284-005

5. Protective Barrier, Mid, Inbd

CRJLA284-013

6. Protective Barrier, Mid, Otbd

CRJLA284-009

7. Aft Wall Extension

CRJLA282-021

8. Protective Barrier, Lower

CRJLA284-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 71 of 92

Figure 2 (Sheet 11)Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-06

3. Screw

MS27039-1-07

4. Forward Above Door Liner

CRJLA246-001

5. Aft Above Door Liner

CRJLA247-001

6. Door Shroud

CRJLA248-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 72 of 92

Figure 3 Angle Installation

Figure 3 (Sheet 1) Angle Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-07

3. Screw

MS27039-1-07

4. Angle

CRJLA301-027 or -029

5. Angle

CRJLA301-025

6. Angle

CRJLA301-017

7. Angle

CRJLA301-013

8. Angle

CRJLA301-005 or -009

9. Angle

CRJLA301-003
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 73 of 92

Figure 3 (Sheet 2) Angle Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-07

3. Angle

CRJLA301-041 or -043

4. Angle

CRJLA301-035

5. Angle

CRJLA301-045

6. Angle

CRJLA301-057

7. Angle

CRJLA301-053

8. Angle

CRJLA301-049
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 74 of 92

Figure 3 (Sheet 3) Angle Installation 

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-07

3. Screw

MS27039-1-08

4. Angle

CRJLA301-033

5. Angle

CRJLA301-023

6. Angle

CRJLA301-015

7. Angle

CRJLA301-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 75 of 92

Figure 4 Tie Rod Cap Installation

Figure 4 (Sheet 1) Tie Rod Cap Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-07

3. Screw

MS27039-1-06

4. Ceiling Cap Assy

CRJLA222-001

5. Ceiling Cap Assy

CRJLA222-001

6. Right-Hand Upper Sidewall Cap

CRJLA204-001 or

CRJLA049-001 (Pre-SB)

CRJLA104-001 (Post-SB) or

CRJLA048-001 (Pre-SB)

CRJLA104-003 (Post-SB)

7. Right-Hand Lower Sidewall Cap

CRJLA203-001 or

CRJLA039-001 (Pre-SB)

CRJLA103-001 (Post-SB)

8. Right-Hand Upper Cap Flange

CRJLA303-01 or -003

9. Right-Hand Lower Cap Flange

CRJLA302-001

10. P-629 Seam Tape

NOTES

1. Item 9 only installed when item 

6 is CRJLA103-001

2. Item 8 only installed when item 

7 is CRJLA104-001 or -003

3. Item 10 installed on with 

CRJLA104-003
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 76 of 92

Figure 4 (Sheet 2) Tie Rod Cap Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-06

3. Ceiling Cap Assy

CRJLA222-001

4. Left-Hand Upper Cap Assy

CRJLA245-001

5. Left-Hand Lower Cap Assy

CRJLA244-001 or

CRJLA050-001 (Pre-SB)

CRJLA142-001 (Post-SB)

6. Left-Hand Lower Cap Flange

CRJLA341-001

NOTES

1. Item 6 only installed when item 

5 is CRJLA142-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 77 of 92

Figure 5 Harness Cap Flange Installation

Figure 5 (Sheet 1) Harness Cap Flange Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-07

3. Screw

MS27039-1-08

4. Harness Cap

CRJLA205-003 or

CRJLA11-03 (Pre-SB)

CRJLA105-003 (Post-SB) or

CRJLA11-07 (Pre-SB)

CRJLA105-011 (Post-SB)

5. Harness Cap Flange

CRJLA304-001

6. Harness Cap

CRJLA207-003 or

CRJLA021-003 (Pre-SB)

CRJLA107-003 (Post-SB) or

CRJLA021-007 (Pre-SB)

CRJLA107-007 (Post-SB)

7. Harness Cap Flange

CRJLA306-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 78 of 92

Figure 5 (Sheet 2) Harness Cap Flange Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw

MS27039-1-07

3. Screw

MS27039-1-08

4. Harness Cap

CRJLA205-003 or

CRJLA11-03 (Pre-SB)

CRJLA105-003 (Post-SB) or

CRJLA11-07 (Pre-SB)

CRJLA105-011 (Post-SB)

5. Harness Cap Flange

CRJLA304-003

6. Harness Cap

CRJLA207-003 or

CRJLA021-003 (Pre-SB)

CRJLA107-003 (Post-SB) or

CRJLA021-007 (Pre-SB)

CRJLA107-007 (Post-SB)

7. Harness Cap Flange

CRJLA306-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 79 of 92

Figure 5 (Sheet 3) Harness Cap Flange Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw (REF)

3. Screw

MS27039-1-09

4. Harness Cap

CRJLA242-003 or

CRJLA043-003 (Pre-SB)

CRJLA141-003 (Post-SB)

5. Harness Cap Flange

CRJLA342-001

6. Harness Cap

CRJLA240-003 or

CRJLA047-003 (Pre-SB)

CRJLA140-003 (Post-SB) or

CRJLA047-007 (Pre-SB)

CRJLA140-007 (Post-SB) or

CRJLA047-015 (Pre-SB) or

CRJLA140-013 (Post-SB)

7. Harness Cap Flange

CRJLA340-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 80 of 92

Figure 6 Forward Bulkhead Liner Installation

Figure 6 (Sheet 1) Forward Bulkhead Liner Installation

LEGEND

1. Washer

NAS1149F0363P

2. Screw (REF)

3. Insert

NAS1835C3

4. Liner Assy

CRJLA262-003 or -007

5. Liner Assy

CRJLA261-003 or -007

6. Liner Assy

CRJLA260-003 or -007
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 81 of 92

Figure 7 Sidewall Panel – Changes

Figure 7 (Sheet 1) Sidewall Panel – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. Lower Right-Hand Sidewall Panel

CRJLA03-03 (Pre-SB)

CRJLA101-003 (Post-SB) or CRJLA03-07 

(Pre-SB)

CRJLA101-007 (Post-SB) or

CRJLA03-11 (Pre-SB)

CRJLA101-011 (Post-SB) or

CRJLA03-15 (Pre-SB)

CRJLA101-015 (Post-SB) or

CRJLA015-007 (Pre-SB)

CRJLA101-019 (Post-SB) or

CRJLA015-003 (Pre-SB)

CRJLA101-023 (Post-SB)

6. Angle

CRJLA301-005 or -007 or -009

7. Angle

CRJLA301-003

8. Angle

CRJLA301-013

9. Angle

CRJLA301-001

NOTES

1. Locate nutplate using 

backdrilled hole

2. Drill and countersink rivet 

holes using a template or a 

nutplate

3. Backdrill sidewall panel in 

center of slot in angle

4.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 82 of 92

Figure 7 (Sheet 2) Sidewall Panel – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. Upper Right-Hand Sidewall Panel

CRJLA023-003 (Pre-SB)

CRJLA106-003 (Post-SB) or

CRJLA023-007 (Pre-SB)

CRJLA106-007 (Post-SB)

6. Angle

CRJLA301-017

7. Angle

CRJLA301-015

NOTES

1. Locate nutplate using 

backdrilled hole

2. Drill and countersink rivet 

holes using a template or a 

nutplate

3. Backdrill sidewall panel in 

center of slot in angle

4.
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 83 of 92

Figure 8 Aft Wall Panels – Changes

Figure 8 (Sheet 1) Aft Wall Panels – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. RH Aft Wall

CRJLA017-003 (Pre-SB)

CRJLA180-003 (Post-SB)

6. Center Aft Wall

CRJLA07-03 (Pre-SB)

CRJLA181-003 (Post-SB)

7. RH Center Joint Overlap

CRJLA281-023

8. Angle

CRJLA301-023

9. Cap Flange

CRJLA306-001

10. Angle

CRJLA301-015

11. Cap Flange

CRJLA304-003

12. Angle

CRJLA301-001

13. RH Kick Plate

CRJLA380-001

14. LH Kick Plate

CRJLA382-001

15. LH Center Joint Overlap

CRJLA281-027

16. Angle

CRJLA301-033

NOTES

1. Locate nutplate using 

backdrilled hole

2. Drill and countersink rivet 

holes using a template or a 

nutplate
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 84 of 92

Figure 8 (Sheet 2) Aft Wall Panels – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. RH Aft Wall

CRJLA017-003 (Pre-SB)

CRJLA180-003 (Post-SB)

6. Center Aft Wall

CRJLA07-03 (Pre-SB)

CRJLA180-003 (Post-SB)

14. LH Kick Plate

CRJLA382-001

15. LH Center Joint Overlap

CRJLA281-027

16. Angle

CRJLA301-033

17. Aft Wall

CRJLA019-003 (Pre-SB)

CRJLA182-011 (Post-SB)

18. Wall Extension

CRJLA282-021

NOTES

1. Locate nutplate using 

backdrilled hole

2. Drill and countersink rivet 

holes using a template or a 

nutplate
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 85 of 92

Figure 9 Floor Panels – Changes

Figure 9 (Sheet 1) Floor Panels – Changes

LEGEND

1. Washer

NAS1149F0363P

2. Screw (REF)

3. Insert

NAS1835C3

4. Kickplate

CRJLA382-001

5. Kickplate

CRJLA380-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 86 of 92

Figure 10 Harness Cap – Changes

`1

Figure 10 (Sheet 1) Harness Cap – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. Lower Right-Hand Sidewall Panel

CRJLA201-003 or -007 or

CRJLA03-03 or -07 or -11 or -15 (PreSB)

CRJLA101-003 or -007 or -011 or -015 

(Post-SB) or

CRJLA015-003 or -007 (Pre-SB)

CRJLA101-019 or -023 (Post-SB)

6. Upper Right-Hand Sidewall Panel

CRJLA206-003 or -007 or

CRJLA023-003 or -007 (Pre-SB)

CRJLA106-003 or -007 (Post-SB)

7. Lower Right-Hand Harness Cap

CRJLA205-003 or -007

CRJLA11-03 or -07 (Pre-SB)

CRJLA105-003 or -011 (Post-SB)

8. Harness Cap Flange

CRJLA304-001

9. Harness Cap Flange

CRJLA304-003

10. Upper Right-Hand Harness Cap

CRJLA207-003 or

CRJLA021-003 or -007 (Pre-SB)

CRJLA107-003 or -007 (Post-SB)

11. Harness Cap Flange

CRJLA306-001

12. Harness Cap Flange

CJRLA306-005

C D

A B
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 87 of 92

Figure 10 (Sheet 2) Harness Cap – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. Upper Right-Hand Harness Cap

CRJLA021-003 (Pre-SB)

CRJLA107-003 (Post-SB) or

CRJLA021-007 (Pre-SB)

CRJLA107-007 (Post-SB)

6. Harness Cap Flange

CRJLA306-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 88 of 92

Figure 10 (Sheet 3)Harness Cap - Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. LH Lower Sidewall

CRJLA243-001 or -003 or -005 or -007

6. LH Upper Sidewall

CRJLA241-001 or -003 or -005 or -007

7. Harness Cap

CRJLA242-003 or

CRJLA043-003 (Pre-SB)

CRJLA141-003 (Post-SB)

8. CRJLA240-003 or

CRJLA047-003 (Pre-SB)

CRJLA140-003 (Post-SB) or

CRJLA047-007 (Pre-SB)

CRJLA140-007 (Post-SB) or

CRJLA047-015 (Pre-SB)

CRJLA140-013 (Post-SB)

9. Harness Cap Flange

CRJLA342-001

10. Harness Cap Flange

CRJLA340-001

A

C

B
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 89 of 92

Figure 11 Tie Rod Cap – Changes

Figure 11 (Sheet 1) Tie Rod Cap – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. Lower right-hand tie rod cap

CRJLA039-001 (Pre-SB)

CJRLA103-001 (Post-SB)

6. CRJLA049-001 (Pre-SB)

CRJLA104-001 (Post-SB) or

CRJLA048-001 (Pre-SB)

CRJLA104-003 (Post-SB)

7. Lower right-hand tie rod cap flange

CRJLA302-001

8. Upper right-hand tie rod cap flange

CRJLA303-001 or -003
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 90 of 92

Figure 11 (Sheet 2) Tie Rod Cap – Changes

LEGEND

1. Nutplate

MS21075L3N

2. Rivet

MS20426AD3-3 or 

CR2672P-3-03

3. Washer

NAS1149F0363P

4. Screw (REF)

5. Lower left-hand tie rod cap

CRJLA050-001 (Pre-SB)

CRJLA142-001 (Post-SB)

6. Lower left-hand tie rod cap flange

CRJLA341-001
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 91 of 92

Figure 12 Access Panel – Changes

Figure 12 (Sheet 1) Access Panel – Changes

LEGEND

1. Access Panel

CRJLA05-03

CRJLA102-003 (Post-SB) or

CRJLA031-003

CRJLA102-007 (Post-SB)

2. Washer

NAS1149CN632R

3. Rivet

CR3523-4

4. Foam Tape

HT-805(A)

5. P-629 Seam Tape

NOTES

1. Fay-seal between components during 

assembly

2. Item 5 not installed on CRJLA102-003 

or -007
Service Bulletin COMSB-25-52-001

Revision A COMSB-25-52-001

29 December 2011 Page 92 of 92

Figure 13 Piccolo Tube – Installation

Figure 13 (Sheet 1) Piccolo Tube – Installation

LEGEND

1. Washer

NAS1149CO332R

2. Spacer

NAS43DD3-9FC

3. Spacer

NAS43DD3-52N (Pre-SB)

NAS43DD3-63FC (Post-SB)

NOTES

1. On aircraft that have piccolo 

tube 601R99011-1 or -9

2. On aircraft that have piccolo 

tube 601R99011-13