the evolution of mobility

SB 601R−25−201 Page 1 of 12 Jul 21/2015 

# SERVICE BULLETIN

Technical Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT, TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST. SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

ATA SYSTEM: 25−41 NUMBER: 601R−25−201 SUBJECT: Equipment & Furnishings − Bulkhead Panel Assembly − Inspection of the Window-Louver Panel Assembly (WLPA) in the Aft Cargo Compartment

1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected: Service Bulletin: CL−600−2B19 aircraft with serial numbers 7003 thru 7067,and 7069 thru 8999 that have a Class C" cargo compartment. Production: There is no production effectivity. 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 bulletins. Before you do this service bulletin, examine all Supplemental Type Certificates (STCs), and Supplemental Type Approvals (STAs) or equivalent action changes to make sure you can complete this service bulletin.

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 2 of 12 Jul 21/2015 B. Reason (1) Condition Damage to the window-louver panel assembly on the 9G-bulkhead panel can occur. This can prevent the louver panels to do their intended function. (2) Evidence Operators have reported opened, damaged or missing louver panels on window-louver panel assemblies (WLPA). (3) Objective/Benefit This service bulletin gives the procedure to do an inspection of the window-louver panel assembly for damage and to make sure the louver panels are in the closed position. This inspection will make sure that the window-louver panel assembly can do its intended function. C. Description The cargo door is opened. A Detailed Visual Inspection (DVI) of the cage assembly and of the window-louver assembly is done. The cargo door is closed. D. Compliance Recommended service bulletin. Bombardier recommends that this service bulletin be done at no more than 100 flight hours from the release date of this service bulletin and be repeated at intervals of 100 flight hours from the initial inspection date unless otherwise directed by the airworthiness authority of the operator. NOTE: If it is not possible to complete all the instructions in this service bulletin because of the configuration of the aircraft, speak with a representative of Bombardier in the CRC at 1−844−272−2720(1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis and to get an approved disposition to complete this service bulletin. This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections (DTIs). E. Approval The technical content of this service bulletin has been approved under the authority of the TCCA Design Approval Organization No: DAO #93−Q−02.

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 3 of 12 Jul 21/2015 F. Manpower The man-hours given below are estimates for direct labor done by an experienced crew on an aircraft prepared for maintenance. These estimates do not include the time necessary for: −Administrative functions such as planning, liaising, 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 an estimate. Call the Fleet Services Team through the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com. It will take an estimated 1.50 man-hours to complete this service bulletin. The man-hours are divided in the table that follows: TASK MAN-HOURS (1) Job Set-Up 0.25 (2) Procedure 1.0 (3) Test N/A (4) Job Close-Out 0.25 NOTE: The man-hours for the procedure do not include the hours to replace damaged parts. G. Material − Price and Availability There are no kits for this service bulletin. H. Tooling − Price and Availability There are no tool kits for this service bulletin. Refer to paragraph 3.C. for a list of special tools and equipment for this service bulletin.

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 4 of 12 Jul 21/2015 I. Weight and Balance Not changed. J. Electrical Load Data Not changed. K. References Refer to the SB Introduction document for definition or explanation of service bulletin content. Restriction and/or Special Instruction (RSI) CA298 (Revision C) C&D Zodiac CMM 25−52−04, 25−52−19, and 53−10−01 Aircraft Maintenance Manual (AMM) Nondestructive Testing Manual (NDTM) For Bombardier reference only: PCA 6937 L. Other Publications Affected None. M. Relationship Chart Not applicable.

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 5 of 12 Jul 21/2015 2. ACCOMPLISHMENT INSTRUCTIONS Reference Information
REFERENCE DESIGNATION AMM 25−51−01−000−801 Removal of the Cargo Restraint Netting AMM 25−51−01−400−801 Installation of the Cargo Restraint Netting NDTM Part 1 51−20−09 Visual − Inspection Procedures Tolerance Information LINEAR TOLERANCES ANGULAR TOLERANCE X.XX in. (X.X mm) X.XXX in. (XX mm) 0° 30"0.03 in. 0.01 in.0.8 mm mm NOTE: The tolerances above apply to the dimensions given in this service bulletin, except when specified differently. A. Job Set-Up NOTE: The steps in the Job Set-Up section of this service bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator discretion. (1) Open the cargo door. (2) Remove all the loose items from the cargo compartment. (3) If necessary, remove the cargo restraint netting from the cargo compartment (refer to AMM 25−51−01−000−801).

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 6 of 12 Jul 21/2015 B. Procedure For all Aircraft (1) If it is not possible to complete all the instructions in this service bulletin because of the configuration of the aircraft, speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis and to get an approved disposition to complete this service bulletin. Refer to Figure 1 (2) Do a DVI of the cage assembly (1) as follows: (refer to NDTM Part 1 51−20−09). (a) Examine the cage assembly (1) for bent and damaged vertical and horizontal guard rails (3) and (4). (b) If the vertical and/or the horizontal guard rail(s) (3) and/or (4) is/are bent and/or damaged, do as follows: Refer to Figure 2 1 Make sure that the louver panels (6) can open to 45 degrees or more. NOTE: It is permitted to manually move the louver panels (6). NOTE: It is permitted to have bent and/or damaged vertical and/or horizontal guard rail(s) (3) and/or (4) if the louver panels (6) can open to 45 degrees or more. 2 Make sure to keep the louver panels (6) in the open position for a subsequent step. For Aircraft with a welded cage assembly Refer to Figure 1 (c) Examine the frame of the cage assembly (1) for bends. (d) If the frame of the cage assembly (1) is bent, do as follows: 1 Make sure that the clearance between the frame of the cage assembly (1) and the louver frame (5) is less than 0.060 in. (1.52 mm). (e) Examine the weld joints of the cage assembly (1) to make sure that they are not broken.

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 7 of 12 Jul 21/2015 For all Aircraft (f) If necessary repair or replace any damaged part(s) (refer to C&D Zodiac CMM 25−52−04, 25−52−19, and/or 53−10−01). If no instructions are given, speak with a CRC representative at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or send an e-mail at thd.crj@aero.bombardier.com for a disposition. (3) Do a DVI of the window-louver assembly (2) as follows: (refer to NDTM Part 1 51−20−09). Refer to Figure 2 (a) If the louver panels (6) are in the closed position, do as follows: 1 Examine the louver panels (6) and make sure that they are not bent. 2 Examine the support tubes (8) and make sure that they are not bent. 3 Examine the louver panels (6) and make sure that they fully touch the fire-block foams (9) located above and below each louver panel (6). 4 Examine the louver panels (6) and make sure that the clearances between the sides of the louver panels (6) and the frame (10) are less than 0.032 in (0.81 mm). 5 If necessary refer to C&D Zodiac CMM 25−52−04, 25−52−19, and/or 53−10−01 for the repair instructions. If no instructions are given, speak with a CRC representative at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or send an e-mail at thd.crj@aero.bombardier.com for a disposition. (b) If the louver panels (6) are in the opened position, do as follows: 1 Examine the frame (10) for dent(s), bend(s), and deformation(s). 2 If the frame (10) is bent, and/or dented, and/or deformed, do as follows:
a Make sure that the louver panels (6) can operate correctly. NOTE: It is permitted to manually move the louver panels (6). NOTE: It is permitted to have a bent and/or dented, and/or deformed frame (10) if the louver panels (6) can operate correctly.

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 8 of 12 Jul 21/2015 3 Examine the louver panels (6) and make sure that they are not bent. 4 Examine the support tubes (8) and make sure that they are not bent. 5 Examine the the louver panels (6) and make sure that the louver fire-block fabric (7) are attached correctly and are not damaged more than 1.0 sq.in. (645 sq.mm). 6 Examine the inner side of the frame (10) and make sure that the frame fire-block fabric (11) are attached correctly and are not damaged more than 1.0 sq.in. (645 sq. mm). 7 Examine the fire-block foams (9) above and below the louver panels (6) and make sure they are attached correctly and are not damaged. 8 Manually move the louver panels (6) to the closed position. 9 Examine the louver panels (6) and make sure that they fully touch the fire-block foams (9) located above and below each louver (6). 10 Examine the louver panels (6) and make sure that the clearances between the sides of the louver panels (6) and the frame (10) are less than 0.032 in (0.81 mm). 11 If necessary refer to C&D Zodiac CMM 25−52−04, 25−52−19, and/or 53−10−01 for the repair instructions. If no instructions are given, speak with a CRC representative at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or send an e-mail at thd.crj@aero.bombardier.com for a disposition.

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 9 of 12 Jul 21/2015 C. Job Close-Out NOTE: The steps in the Job Close-Out section of this service bulletin, except for the return-to-service tests, are recommended steps. The steps give a recommendation to install components removed during the Job Set-Up. This recommendation is to make sure that the aircraft is safe and ready to return to service. Alternative steps can be used at the operator discretion. (1) If removed, install the cargo restraint netting in the cargo compartment (refer to AMM 25−51−01−400−801). (2) Remove all tools, equipment, and unwanted materials from the work areas. (3) Close the cargo door. (4) When this service bulletin is completed, make this entry in the applicablelogbooks: Service Bulletin 601R−25−201, Equipment & Furnishings − Bulkhead Panel Assembly − Inspection of the Window-Louver Panel Assembly (WLPA)in the Aft Cargo Compartment, incorporated."

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 10 of 12 Jul 21/2015 Cage Assembly − 9G Bulkhead Figure 1 (Sheet 1 of 1)rsb601r25201_006, kp, June 18, 2015

A 1 9G BULKHEAD PANEL (REF) A

2

LEGEND 1. Cage assembly. 2. Window

−louver assembly. 3. Vertical guard rail. 4. Horizontal guard rail. B 0.060 in. (1.52 mm) MAXIMUM DEFORMATION B 1

5

4 3

NOTE For aircraft with a welded cage assembly only. 1 1

5. Louver frame. 5

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 11 of 12 Jul 21/2015 Window−Louver Panel Assembly (WLPA) − Inspection Figure 2 (Sheet 1 of 1)rsb601r25201_002, kp, Apr. 23, 2015

B LEGEND 6. Louver panels. 7. Louver fire

−bloc fabric. 8. Support tube. 9. Fire

− block foam. 10. Frame.

11. Frame fire

−block fabric.

A 9 A

10

6 8 7 11 B

### SERVICE BULLETIN 601R−25−201

SB 601R−25−201 Page 12 of 12 Jul 21/2015 3. MATERIAL INFORMATION
A. Kit Information None. B. Consumable Information For a list of consumables, refer to the different tasks that are given as references in this service bulletin. C. Special Tools and Equipment There are no special tools and equipment for this service bulletin. D. Disposition of Parts Not applicable. 1the evolution of mobility

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Service Bulletin No.: 601R-25-201 Revision:NC Aircraft Serial Number: Date:
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Operator: Service Centre: Name: Telephone or Fax: FAX your comments or feedback to (450) 476---7300 or e-mail to crj_sb_evaluation_form@aero.bombardier.com