# A600-0769 Page 1 of 1 

# SERVICE BULLETIN REVISION TRANSMITTAL SHEET

MODEL CL-600-1A11

Discard the Basic Issue of this Service Bulletin dated June 19/2014, and replace in its entirety with this Revision 01.

Service Bulletin No. A 600-0769

Date of Basic Issue Jun 19 / 2014

Revision No. 01 Dated Jun 26 / 2014

This revision has no effect for aircraft on which the Basic Issue of this Service Bulletin was done thus no other action is necessary. Do not sign the log book if you have not done this revision. Keep the previous log book entry.

This revision is issued to revise and update the Service Bulletin to add the FAA approval. The changes are as follows:
1. Revise the Service Bulletin Summary Sheet and Paragraph 1.D. of the Service Bulletin, to add “Basic Issue” after the SB release date. 2. Revise Paragraph 1.E., to add the FAA approval statement and remove the related subject note from the Service Bulletin Summary Sheet. 3. Revise, in Paragraph 1.K., the revision of the Repair Engineering Order (REO), 600-78-30-240, to Rev. C. 4. Revise the Pilot Info Sheet, Pa ragraph 1.L. and Paragraph 3.D. to add the Airplane Flight Manuals, PSP 600 (US) and PSP 600-1 (US). 5. Make miscellaneous minor changes, as necessary, with no change of context.Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 1 of 1 

# PILOTS INFORMATION SHEET

MODEL CL-600-1A11

ATA 78-30

EXHAUST SYSTEM

SPECIAL CHECK/MODIFICATION – EXHAUST – THRUST REVERSER ACTUATOR ATTACHMENTS LOCKING INSTALLATION TO PREVENT INADVERTENT THRUST REVERSER DEPLOYMENT

This Service Bulletin gives instructions to do a detailed visual inspection and verify if there is any indication of cracks next to the TR actuator clevis area on the translating sleeve frame and intercostals. Further instruct ions are given to secure the TRs in the stowed position if any indi cation of cracks are found.
NOTE : When you incorporate this Service Bulletin, the AFM issues that follow MUST be used:

–PSP600, Model CL-600-1A11, RAG-600-101 (CDN) DOT, Temporary Revision 600/30 dated Jun 06/2014.

–PSP600-1, Model CL-600-1A11, RAG-600-101 (CDN) DOT, Temporary Revision 600-1/ 26 dated Jun 06/2014.

–PSP 600, Model CL600-1A11, RAG-600-101 (US), Temporary Revision 600/29 dated Jun 20/2014.

–PSP 600-1, Model CL600-1A11, RAG-600-101 (US), Temporary Revision 600-1/24 dated Jun 20/2014Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 1 of 1



# ALERT SERVICE BULLETIN SUMMARY

This Service Bulletin is available at: www.cic.bombardier.com


### CL-600-1A11

ATA 78-30

EXHAUST SYSTEM

SPECIAL CHECK/MODIFICATION – EXHAUST – THRUST REVERSER ACTUATOR ATTACHMENTS LOCKING INSTALLATION TO PREVENT INADVERTENT THRUST REVERSER DEPLOYMENT
The information below is provided for y our reference. For full details, please see corresponding paragraph contained within this bulletin Basic Issue. 

# ALERT

SPECIFIED TIME COMPLIANCE 

## COMPLIANCE TIME
Within 25 flight cycles or 90 days whichever comes first from the SB release date (Basic Issue)
EFFECTIVITY: A/C Serial No. 1004 to 1085

MANPOWER: 14 man-hours per Thrust Reverser for Part A and 36 man-hours per Thrust Reverser for Part B CONTINUED AIRWORTHINESS (CAW) FLEET CAMPAIGN YES NO

TLMC, CH 5 AFFECTED YES NO

KITS and/or PARTS YES NO

TOOLING/GSE YES NO

PLANNING INFORMATION: See important information at the start of Paragraph 1. YES NO

DEDICATED SCHEDULE YES NO

PREREQUISITE SERVICE BULLETINS: N/A

To place an order for parts or kits, please call Bombardier Aerospace Parts Services at:

514-855-2999 or 1-866-538-1247Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations and/or acceptable industry standards. This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior written consent of Bombardier Inc. and/or its affiliates. © 2014 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 1 of 25



# ALERT SERVICE BULLETIN

This Service Bulletin is available at: www.cic.bombardier.com


### CL-600-1A11

ATA 78-30

EXHAUST SYSTEM

SPECIAL CHECK/MODIFICATION – EXHAUST – THRUST REVERSER ACTUATOR ATTACHMENTS LOCKING INSTALLATION TO PREVENT INADVERTENT THRUST REVERSER DEPLOYMENT



### 1. PLANNING INFORMATION NOTE : The instructions in PART A of this Alert Service Bulletin are applicable to Bombardier Business Aviation Serv ices (BBAS), Completion Centers, Authorized Service Facilities, Spare Pa rts Center, Montreal and operator’s stock rooms. If any indication of cracks is found, perform the PART B of the Service Bulletin. You can incorporate PART B of this Service Bulletin without doing the inspection in PART A. PART B is a temporary repair and is valid for 24 months from this Service Bulletin PART B incorporation date or until damaged parts are replaced, first to occur. A. Effectivity CL-600-1A11 aircraft, Serial No. 1004 to 1085

. NOTE : The instructions given 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 Aerospace Service Bulletin(s). Before you do this bulletin, examine all STC, STA or equivalent action changes to make sure that this bulletin can be completed.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 2 of 25 B. Reason There have been two reported incidents where a Thrust Reverser (TR) inadvertently partly deployed in flight. The aircraft declared for an emergency landing and were able to land safely. After investigation it has been found that t he TR deployment in flight was caused by damaged translating sleeve frame and intercosta ls at the actuator clevis areas. This Service Bulletin gives instructions to do a detailed visual inspection and verify if there is any indication of cracks next to the TR actuator clevis area on the translating sleeve frame and intercostals. Further instructions are given to secure the TRs in stowed position if any indication of cracks are found. C. Description This Service Bulletin gives instructions in PART A, to:

–Remove the thrust reversers

–Do the detailed visual inspection of the thrust reverser translating sleeve actuator clevis attachments to frame and to intercos tals areas at “4 o’clock”, “8 o’clock” and “12 o’clock” position, and

–Reinstall the thrust reversers if no indi cation of cracks are found or do Part B if cracks are found. PART B, to:

–Deactivate Thrust Reversers

–Manufacture the Shims, Angles and Doublers,

–Do the installation of shims and angles to reinforce the flipper doors tracks.

–Reinstall the TRs or translating sleeves if removed and install the doublers to prevent inadvertent TR deployment. D. Compliance PART A is recommended in less than 25 flight cycles or 90 days from this Service Bulletin release date (Basic Issue), then every 100 Flight Cycles if no crack indications are found during the Part A ins pection. If you find indication of cracks, incorporate PART B to both thrust reversers, before the next flight. PART B is a temporary repair and is valid for 24 months from the incorporation date of PART B of this Service Bulletin, until the damaged parts are replaced. You can incorporate PART B of this Serv ice Bulletin without incorporating the PART A. If you incorporate PART B, it is not necessa ry to repeat the inspection in PART A every 100 Flight Cycles.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 3 of 25 E. Approval The technical content of this Service Bulletin has been approved under the authority of Transport Canada Civil Aviation (TCCA) Design Approval Organization (DAO) No. DAO #93-Q-02.
NOTES : 1. The technical content of this Service Bulletin is accepted by the FAA under the Canada/USA bilateral Aviation Safety Agreement. 2. The technical content of this Service Bulletin is accepted by EASA in accordance with established procedures. F. Manpower
NOTES : 1. The man-hours given are estimates to help you schedule the tasks given in this bulletin. The estimate s are for direct labor performed by an experienced crew and do not include the time for familiarization, planning, aircraft preparation in hangar such as towing and positioning of scaffolds, removal of interior fu rnishings, repainting, supervision and inspection.
For more information related to t he manpower estimates, refer to SB 600-0002. 2. This Service Bulletin may require consumable materials that have specific curing times (refer to Par agraph 3). The accumulated curing time is not included in the labor estimates and should be considered for planning purposes before you schedule this Service Bulletin.
3. Labor hours are based on the fact that the modification will be done at the next scheduled maintenance task or inspection. Therefore no man-hours are allotted to prepare the aircraft for maintenance or to prepare for this Service Bulletin. 14 man-hours per thrust reverser are necessa ry to do the inspection in PART A of this Service Bulletin if you remove/install the Thrust Reverser. 36 man-hours per thrust reverser are necessa ry to do the modification in PART B of this Service Bulletin. Bombardier Aerospace does not pay for the labor to do the inspection in PART A and/or modification in PART B of this Service Bulletin. G. Material - Cost and Availability No kit is necessary to do this Service Bulletin Bombardier Aerospace does not pay for the par ts listed in Paragraph 3.B. or for the materials listed in Paragraph 3.C. to do this Service Bulletin.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 4 of 25 H. Tooling The equipment and tools listed below are necessary to do this modification:

GSE REFERENCE NO. PART NO. DESCRIPTION 24-00-24 S4933959-501 Tag, Circuit Breaker 71-00-01 G600-710008-101 Sling 71-00-07 G600-710001-265 Power Plant Rigging Kit Commercially Available - Borescope Tool

NOTES : 1. Refer to the Illustrated Tool and Equipment Manual (ITEM), PSP611 to make sure that you use the correct equipment configuration. 2. Refer to the Introduction of the publication listed in NOTE 1 for acceptable GSE equivalents. 3. This list is provided for quick reference. In case of discrepancy between this list and the tools called in the SPM, WM, Chapter 20, then the tools called in the SPM, WM pr evail. Other approved alternative tools are acceptable and can also be used. I. Weight and Balance This modification is applicable for PART B only, as follows:

WEIGHT MOMENT +5.4 pounds (2.45 kg) +3693 pound-inches (42.54 kgm)

J. Electrical Load Data No change.
K. References

–Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C-4120, Rev. B.

–Bombardier Aerospace, Repair Engi neering Order (REO), 600-78-30-240, Rev. C.

–Bombardier Aerospace, Kit Drawing K600-60088, Rev. --.

–CL-600 Maintenance Manual, PSP 602, Chapters 24 and 78.

–CL-600 Illustrated Parts Catal og (IPC), Chapter 24 and 78.

–CL-600 Structural Repair Manual (SRM), PSP 607, Chapter 51.

–CL-600 Illustrated Tool and Equipment Manual (ITEM), PSP 611, Chapter 78.

–Airplane Flight Manual, PSP 600 (DOT), Temporary Revision 600/30 dated Jun 06/2014.

–Airplane Flight Manual, PSP 600-1 (D OT) Temporary Revision 600-1/26 dated Jun 06/2014.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 5 of 25 L. Other Publications Affected

–Airplane Flight Manual, PSP 600 (DOT), Temporary Revision 600/30 dated Jun 06/2014.

–Airplane Flight Manual, PSP 600-1 (D OT) Temporary Revision 600-1/26 dated Jun 06/2014.

–Airplane Flight Manual, PSP 600 (US) , Temporary Revision 600/29 dated Jun 20/2014.

–Airplane Flight Manual, PSP 600-1 (US), Temporary Revision 600-1/24 dated Jun 20/2014. M. Equivalent Service Bulletins
None.


### 2. ACCOMPLISHMENT INSTRUCTIONS

NOTES : 1. If no other manual references are given, the procedures that follow are from the Maintenance Manual, PSP 602, unless otherwise specified. 2. All references made to zones, access panels and/or doors, are from the Maintenance M anual PSP602, Chapter 6. 3. The procedures that follow apply to both left and right engine. A. Aircraft Setup
WARNING : TO PREVENT DAMAGE TO EQUIPMENT AND INJURY TO PERSONNEL, ENSURE PERSONNEL AND EQUIPMENT ARE CLEAR OF AREA BEFORE INITIATING MOVEMENT OF THRUST REVERSER.
CAUTION : DO NOT OPERATE THRUST REVERSER UNTIL ALL RIGGING PROCEDURES HAVE BEEN ACCOMPLISHED, OR UNLESS DIRECTED TO DO SO BY MAINTENANCE PROCEDURES.
DO NOT ALLOW FLEXSHAFTS TO BEND OR TO COIL TO A RADIUS OF LESS THAN 18 INCHES OR PERMANENT DEFORMATION OF FLEXSHAFTS WILL OCCUR.
A MANUALLY OPERATED SPEED HANDLE MUST BE USED IN CRANKING THRUST REVERSER. USE OF ELECTRICAL OR PNEUMATIC POWER TOOLS COULD CAUSE DAMAGE.
IF BOTH FLEXSHAFTS ARE DISCONNECTED FROM ANY COMPONENT, THAT COMPON ENT MUST BE RIGGED.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 6 of 25 B. PART A – Inspection of Thrust Rever ser Translating Sleeve Actuator Clevis attachment to frame and to intercostals at “4 o’clock”, “8 o’clock” and “12 o’clock” positions.
NOTES : 1. You can incorporate PART B of th is Service Bulletin without doing the inspection in PART A. 2. Removal, inspection and installation procedures for the thrust reverser on left and right engines are similar and must be done on both engines. The procedures that follow are given for the left engine. (1) Remove the power plant upper and lower access cowl doors. Refer to Chapter 71-10-11, ACCESS COWL DOORS - Removal/Installation.
(2) Remove the thrust reverser and install it in maintenance stand. Refer to Chapter 78-30-00, THRUST REVERSER – Removal/Installation.

NOTE : If necessary, remove the translating sleeve to clean area of inspection and for better access for the inspecti on, Refer to Chapter 78-30-11, TRANSLATING SLEEVE – Removal/Installation. (3) Manually crank thrust reverser to fully deployed position. Refer to Maintenance Manual PSP 602, Chapter 78-30-00, T HRUST REVERSER – Adjustment/Test.
NOTE : Make sure that there is no bi nding or fouling during cranking.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 7 of 25 (4) Get access to the actuator clevis attach ment to frame and intercostals. Refer to Figure 1.

Thrust Reverser Translating Sleeve Figure 1

(5) Use lint free cloth moist with ali phatic naphtha and thoroughly clean frame and intercostals of affected area. Re fer to SRM PSP 607, Chapter 51-53-00, CLEANING. “12 o’clock" actuator attachment “4 o’clock” actuator attachment

VIEW SHOWING POSITION OF A CTUATORS ATTACHMENTS “8 o’clock” actuator attachmentMODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 8 of 25 (6) Do a detail visual inspection in the act uator clevis area and of frame and intercostals adjacent to clevis area for indications of cracks. Refer to Figures 2 and 3.
NOTE : Check for cracks, sheared, popped or loose rivets or elongated holes.

Thrust Reverser Translating Sleeve Figure 2 (8 o’clock position is similar) Frame Actuator Clevis

Insert borescope probe here.

Area to be inspected is under the frame and behind the actuator clevis and along the full length of the intercostals.

VIEW OF ACTUATOR ATTACHMENT A T “4 O’CLOCK” POSITIONMODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 9 of 25 (7) Use the borescope and inspect the area along full length of intercostals and frame in the area behind the frame of the actuator clevis. Refer to Figure 3 and 4.
NOTE : Do not remove the actuator clevis in order to perform inspection.

Thrust Reverser Translating Sleeve Figure 3 Insert borescope probe here.

Area to be inspected is under the frame and behind the actuator clevis and along the full length of the intercostals.

At 12 o’clock position, clip needs to be inspected. The clip is located between two intercostals and under the frame. Frame

VIEW OF ACTUATOR ATTACHMENT AT “12 O’CLOCK” POSITION Intercostal NOTE : Do not remove the actuator clevis in order to perform the inspection. The actuator clevis was removed for clarity purposes only.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 10 of 25 Thrust Reverser Translating Sleeve Figure 4 (8) Manually crank thrust reverser to fu lly stowed position. Refer to Maintenance Manual PSP 602, Chapter 78-30-00, THRUS T REVERSER – Adjustment/Test.
NOTE : Make sure that there is no bi nding or fouling during cranking. (9) Perform steps (1) to (8) to the RH engine. (10) If there is no indication of cracks on bot h thrust reversers, reinstall the thrust reversers. Refer to Maintenance M anual PSP 602, Chapter 78-30-00, THRUST REVERSER – Removal/Installation.
NOTES : 1. When you have completed PART A

− Inspection, submit an email to Bombardier Aerospace with the aircra ft, Serial Number, Aircraft Flight Hours, Aircraft Flight Cycles, whether indication of crack was found on Left or Right Translating Sleeve (Yes or No), the position (4, 8 or 12 o’clock), dimension and photos of cra ck and the date of the inspection, by email at: se_hotline@aero.bombardier.com

. 2. If the translating sleeve was removed to clean area of inspection, reinstall the translating sleeve. Refer to Chapter 78-30-11, TRANSLATING SLEEVE – Removal/Installation. (11) If you find any indication of cracks on either or both thrust reversers, perform Paragraph 2.C. PART B on both thrust reversers (incorporate Kit Drawing K600-60088 to both engines before next flight in order to temporarily block thrust reverser in stowed position). TYPICAL BORESCOPE VIEW OF INTERCOSTAL UNDER THE FRAME AT “12 O’CLOCK” POSITION Clip

Intercostal
Inspect the area around the nutplate for crack indications Possible location of crack at the intercostal lugMODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 11 of 25

C. PART B – Modification – Installati on of Left and Right Thrust Reverser Translating Sleeve Angles, Shims and Doublers to prevent inadvertent Thrust Reverser deployment (refer to drawing K600-60088)
NOTES : 1. If Part B is incorporated, bot h thrust reversers must be modified. 2. Modification procedures for thrust reverser on left and right engines are similar. The procedures that follow are given for left engine. 3. Make sure you install the doublers when the thrust reversers are installed on the aircraft and the thrust reversers are in the stowed position. 4. If it is not possible to follow all instructions from PART B (Kit Drawing K600-60088) due to the configuration of the aircraft structures, submit an SRPSA to Customer Support Engineering (CSE) for evaluation and to obtain an Approved Repair in order to allow completion of the Service Bulletin, by email at: SRPSA@aero.bombardier.com

. (1) Deactivate the Thrust Reverser. Refer to Chapter 78-30-00, THRUST REVERSER – Deactivation and Activation.
NOTES : 1. You may deactivate the thrust re verser without installation of clamp Part No. G600-780005-1. 2. Make sure that you install a decal, printed on red tape, THRUST REVERSERS DEACTIVATED, on centre pedestal to rear of throttle quadrant. (2) Remove the upper flipper doors from transla ting sleeve. Refer to Chapter 78-30-21, FLIPPER DOORS – Removal/Installation. (3) Do the modification of the upper fli pper doors as per Kit Drawing K600-60088 and do as follows: (a) Manufacture shims Part No. K600 60088-009, qty 4. Refer to SRM PSP 607, Chapter 51-28-40, STANDARD MACHINING. NOTE: Do not apply Alodine and Primer to Shim at this step. (b) Trim and shape shims Part No. K600-60088-009 to fit between track 215-0624-5 and flipper door skin. Manua lly apply Alodine 1200, then one layer of fluid resistant epoxy primer, all over. Refer to SRM, Chapter 51-58-138/43, FLUID RESIST ANT EPOXY PRIMER. (c) Identify the Shims as per best shop practices. (d) Once the shims are trimmed and shaped, remove tracks 215-0624-5 from the flipper door.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 12 of 25 (e) Wet install rivets (qty. 6) Part No . NAS1097AD4 and attach shims Part No. K600-60088 to the door skin. Refer to SRM PSP 607, Chapter 51-57-00, SEALING and Chapter 51-42-11, SOLID RIVETS.
NOTES : 1. Make sure that the edge distanc e is minimum 1.5 times the rivet diameter. 2. Make sure that the pitch distance is from 4 times the rivet diameter to 6 times the rivet diameter. (f) Reinstall tracks 215-0624-5 to the flipper door. (4) Remove the lower flipper door from trans lating sleeve. Refer to Chapter 78-30-21, FLIPPER DOORS - Removal/Installation. (5) Do the modification of the lower flipper door as follows: (a) Manufacture Angles Part No. K600- 60088-007, qty 4. Refer to SRM PSP607, Chapter 51-31-11, SHEET METAL FO RMING and to SRM PSP 607, Chapter 51-28-40, STANDARD MACHINING. (b) Manually apply Alodine 1200, then one laye r of fluid resistant epoxy primer to the angles. Refer to SRM PSP 607, Chapter 51-58-138/43, FLUID RESISTANT EPOXY PRIMER. (c) Trim angle Part No. K600-60088-007 to fit the installation to zee Part No. 215-0619-5/-6. Do touch up on reworked area (Alodine 1200, then fluid resistant epoxy primer). Refer to SRM PSP 607, Chapter 51-58-138/43, FLUID RESISTANT EPOXY PRIMER. (d) Wet install rivets (qty. 7) Part No. MS20470AD4 to attach angle Part No. K600-60088-007 to zee Part No. 215-0619-5/-6. Refer to SRM PSP 607, Chapter 51-57-00 SEALING and Chapter 51-42-11, SOLID RIVETS.
NOTES : 1. Make sure that the edge distanc e is minimum 1.5 times the rivet diameter. 2. Make sure that the pitch distance is from 4 times the rivet diameter to 6 times the rivet diameter. (6) Remove the paint only from the area of the translating sleeve (each longeron side and cap-upper frame) where the rivets must be removed. Refer to Figure 5 and do as follows: a) Install protection around the area where you remove the paint to prevent FOD from entering. b) Soak clean cloth with the MEK or the toluene and apply the MEK or toluene on the paint. c) When the paint becomes soft remove the soft paint with a clean cloth soaked with MEK or toluene.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 13 of 25 (7) Remove at least 7 rivets each side of longerons 215-0618-127/-128 and 10 rivets from cap-upper frame 215-0618-671, to allow t he installation of doubler. Refer to SRM Chapter 51-42-11, SOLI D RIVETS and Chapter 51-42-16, BLIND RIVETS.
CAUTION : Make sure that you clean translating sleeve installation areas of all debris, rivet shanks and heads.

Preparation of Area for Doubler Installation Figure 5

(8) Use the holes pattern in longerons 215-0618-127/-128 and cap frame 215-0618-671 and mark-up their position to the doubler Part No. K600-60088-003. Refer to Figure 6. (9) Remove at least 7 rivets each side of longerons 215-0618-129/-131 and 10 rivets from cap-frame 215-0618-57, to allow the installation of doubler. Refer to SRM Chapter 51-42-11, SOLID RIVETS and Chapter 51-42-16, BLIND RIVETS.
CAUTION : Make sure that you clean Translation Sleeve installation areas of all debris, rivet shanks and heads. (10) Use the holes pattern in longerons 215-0618-129/-131 and cap frame 215-0618-57 and mark-up their position to the doubler Part No. K600-60088-005. Refer to Figure 6. Longeron area with paint removed to facilitate the removal of rivets. Cap upper frame area with paint removed to facilitate the removal of rivets.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 14 of 25 Prefit of Doubler on Flipper Door Figure 6
(11) Manufacture Doubler-Upper Part No . K600-60088-003, qty. 2, Doubler-Lower Part No. K600-60088-005, qty 2. Refer to SRM PSP607, Chapter 51-31-11, SHEET METAL FORMING and to SRM PSP 607, Chapter 51-28-40, STANDARD MACHINING. (12) Manually apply Alodine 1200, then one layer of fluid resistant epoxy primer to doublers. Refer to SRM, Chapter 51-58-138/43, FLUID RESISTANT EPOXY PRIMER. (13) Identify the Doublers as per best shop practices. (14) Install the upper flipper door to the translating sleeve. Refer to Maintenance Manual PSP 602, Chapter 78-30-21, FLIPPER DOOR S PSP – Removal/Installation.
NOTE : Apply Alodine and primer on reworked areas of the Translating Sleeve. (15) Install the lower flipper door to the trans lating sleeve. Refer to Maintenance Manual PSP 602, chapter 78-30-21, FLIPPER D OORS – Removal/Installation.
NOTE : Apply Alodine and primer on reworked areas of the Translating Sleeve. Double r

Flipper Doo rMODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 15 of 25 (16) Install the thrust reverser. Refer to Maintenance Manual PSP 602, Chapter 78-30-00, THRUST REVERSER – Removal/Installation.
NOTE : Do not perform the operational test of Thrust Reverser. (17) Manually crank thrust reverser to stow ed position and adjust flipper door to fit flush with translating sleeve.
NOTE : Make sure that there is no bi nding or fouling during cranking. (18) Use rivets NAS9302E4 and install doubler Part No. K600-60088-003 to the longerons 215-0618-127/-128 and cap fram e 215-0618-671. Refer to SRM PSP 607, Chapter 51-57-06, SEL F CONTOURING SEALING and Chapter 51-42-18, CHERRY MAX BLIND RIVETS.
NOTES : 1. Apply self-contouring sealant a ll over the doubler area, and releasing agent to longerons, cap frame and flipper door areas. Refer to SRM PSP 607, Chapter 51-57-06, SELF- CONTOURING SEALANT. 2. Apply aerodynamic sealing all ar ound the doubler contour. Refer to SRM PSP 607, Chapter 51-57-00, SEALING. (19) Apply polyurethane topcoat on the rework ed area to match the existing color. (20) Use rivets NAS9302E4 and install doubler Part No. K600-60088-005 to the longerons 215-0618-129/-131 and cap frame 215- 0618-57. Refer to SRM PSP 607, Chapter 51-57-06, SELF- CONTOURING SEALING and Chapter 51-42-18, CHERRY MAX BLIND RIVETS. .
NOTES : 1. Apply self-contouring sealant a ll over the doubler area, and releasing agent to longerons, cap frame and flipper door areas. Refer to SRM PSP 607, Chapter 51-57-06, SELF- CONTOURING SEALANT. 2. Apply aerodynamic sealing all ar ound the doubler contour. Refer to SRM PSP 607, Chapter 51-57-00, SEALING. (21) Apply polyurethane topcoat on the re worked area to match the existing color (22) Make sure you perform Part B procedure to the RH thrust reverser.
D. Close-out (1) Install the power plant upper and lower access cowl doors. Refer to Chapter 71-10-11, ACCESS COWL DOORS - Removal/Installation. (2) Remove all tools, equipment and unw anted materials from the aircraft. (3) Do not carry out thrust reverser operational test. E. Stock Purge Make sure that you incorporate the PART A of this Alert Service Bulletin to all thrust reverser spare parts. If you find any indication of cracks, mark the part “UNSERVICEABLE”, and place it in quarantine.
NOTE : The instructions in this Alert Service Bulletin are applicable to Bombardier Business Aviation Services (BBAS), Comple tion Centers, Authorized Service Facilities, Spare Parts Center, Mont real and operator’s stock room.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 16 of 25 F. Recording You can do each PART of this Service Bulletin independently. When any PART of this Service Bulletin is completed, make an entry in the aircraft log and send the attached Incorporation Notice to Bombardier Busi ness Aircraft Customer Services (BBACS). In an effort to improve the quality of our technical communications, we are requesting your feedback. Please take a moment to fill out our easy on-line Service Bulletin survey: http://csefeedback.aero.bombardier.com


### 3. MATERIAL INFORMATION

A. Kit No kit is required.
B. Parts The parts that follow are necessary to do this Service Bulletin and are available from Bombardier Aerospace Parts Servic es, Montreal or from local suppliers:

NEW PART NO. QTY ITEM USED PART NO. INSTRUCTIONS - DISPOSITION

MS20470AD4-5A 28 Solid rivet - - NAS1097AD4-8A 24 Solid rived, CSK reduced head - -

NAS9302E4-2 110 Blind rivet, Flush Head - -

NAS9302E4-3 124 Blind rivet, Flush Head - -

NOTE : The part numbers for the items list ed above are subject to change without revision to this Service Bulletin. In case of discrepancy between this list and any other list, the Illustrated Parts Catalog prevails and shall be used to determine the latest part number.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 17 of 25 C. Material The materials that follow are necessary to do this Service Bulletin. These can be purchased from a local supplier. Bombar dier Aerospace does not pay for these consumables.

DESCRIPTION PART No./NAME SPECIFICATION QUANTITY SUPPLIER (See Note)
Methyl Ethyl Ketone (MEK) - - As Necessary Code: A

Polyurethane Topcoat - - As Necessary For PART B Code: A

Primer CT: (2 hours) 4500-P-40B BAMS 565-001 As Necessary Code: A

Toluene - - As Necessary Code: A

Release Agent - MS-122 As Necessary For PART B Code: B

Sealant CT: ( 14 days at 25 C or 6 hrs at 55 C) P/S 870B MIL-PRF-81733 Type II, Class 1, Grade A As necessary For Part B Code: B

Aliphatic Naphtha - TT-N-95, Type II As Necessary Code: C

Conversion

Coating Alodine 1200 MIL-DTL81706B, Class 1A As Necessary Code: C

White Lint Free

Cotton Cloths - - - Code: D

NOTES : 1. Refer to the table that follows for each supplier’s address listed by codes. 2. The Curing Time (CT), if applicable, for each consumable material is indicated with the description of each product. 3. At time of release of this Service Bulletin, the information on the supplier was valid and accurate. In the event that this information has changed, the operator is encouraged to use the World Wide Web to find a local supplier.MODEL CL-600-1A11

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 18 of 25 SUPPLIERS ADDRESSES BY CODES

Code: A Tempo Paint and Varnish Co. 205 Fenmar Dr. Weston, Ontario M9L 2X4 Canada Tel.: (416) 746-2233 Fax.: 1-416-746-2235 E-mail: sales@tempo-aerospace.com Web Site: www.tempo-aerospace.com Code: B
PRC – Desoto International 5430 San Fernando Road,

PO Box 1800, Glendale, CA, U.S.A. 91209 Tel.: 1-800-228-5635 Fax: (818)-549-7790 Web Site: www.ppg.com/prc-desoto

Code: C Henkel Corporation 2850 Willow Pass Road Bay Point, California 94565 Tel.: 1-925-458-8000 Fax: 1-925-458-8030 Web Site: www.henkelna.com Code D
Commercially Available

D. Publications The publications that follow are required after this Service Bulletin has been incorporated.

–Airplane Flight Manual, PSP 600 (DOT), Temporary Revision 600/30 dated Jun 06/2014.

–Airplane Flight Manual, PSP 600-1 (DOT ) Temporary Revision 600-1/26 dated Jun 06/2014.

–Airplane Flight Manual, PSP 600 (US) , Temporary Revision 600/29 dated Jun 20/2014.

–Airplane Flight Manual, PSP 600-1 (US), Temporary Revision 600-1/24 dated Jun 20/2014.MODEL CL-600-1A11



## PL K600-60088

– Kit – Thrust Reverser Locking (Sheet 1 of 3, Rev. --)

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 19 of 25MODEL CL-600-2B16 MODEL CL-600-1A11



## K600-60088

– Kit – Thrust Reverser Locking (Sheet 2 of 3, Rev. --)

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 20 of 25MODEL CL-600-1A11



## PL K600-60088

– Kit – Thrust Reverser Locking (Sheet 3 of 3, Rev. --)

Basic Issue: Jun 19/2014 

# A600-0769 Revision 01: Jun 26/2014 Page 21 of 25K600-60088–Kit – Thrust Reverser Locking(Sheet 1 of 4, Rev. --)Basic Issue: Jun 19/2014Revision 01: Jun 26/2014A600-0769Page 22 of 25K600-60088–Kit – Thrust Reverser Locking Installation(Sheet 2 of 4, Rev. --)Basic Issue: Jun 19/2014A600-0769Revision 01: Jun 26/2014 Page 23 of 25K600-60088–Kit – Thrust Reverser Locking Installation(Sheet 3 of 4, Rev. --)Basic Issue: Jun 19/2014A600-0769Revision 01: Jun 26/2014 Page 24 of 25K600-60088–Kit – Thrust Reverser Locking Installation(Sheet 4 of 4, Rev. --)Basic Issue: Jun 19/2014Revision 01: Jun 26/2014A600-0769Page 25 of 25

### ALERT SERVICE BULLETIN EVALUATION FORM (Your ideas will help us provide better bulletins)

SERVICE BULLETIN: A600-0769 ISSUE: Rev. 01 DATED: Jun 26/2014

TITLE: Special Check/Modification – Exhaust – Thrust Reverser Actuator Attachments Locking Installation to Prevent Inadvertent Trust Reverser Deployment

In an effort to improve the quality of our technical communications, we are replacing the standard Service Bulletin Evaluation Form with an on-line Service Bulletin Survey and we are requesting your feedback. Pl ease take a moment to fill out our easy on-line Service Bulletin survey:



### http://csefeedback.aero.bombardier.com

## ALERT SERVICE BULLETIN INCORPORATION SHEET – “A600-0769”BOMBARDIERSUBMISSION Upon completion of the Service Bulletin, please fill-in, fax to (514) 855-8798 or e-mail to Fracas at fracas.montreal@aero.bombardier.com
If your aircraft is registered on CAMP and you are reporting to them, please do not send the incorporation sheet to Bombardier. If your aircraft is on another tracking system, please contact Bombardier to make arrangements for automated data submission.

COMPLIED WITH Service Bulletin Number Rev. * Parts Completed YES NO N/A Remarks/Reason

A600-0769 01 PART A

“ “ PART B

- - -

Actual hours to accomplish Service Bulletin:

1. Where the Service Bulletin is divided into a number of parts (e.g., PARTS A, B, C, D, etc.) which can be carried out separately, indicate only those parts completed at this time.
2. For repetitive checks (usually PART A) only the initial check should be reported unless otherwise stated in the Service Bulletin. * NOTES :

3. When more than one part is carried out at the same time, each part should be reported.

Aircraft Serial No. Aircraft Reg. No. Airframe Hours: Airframe Landings S.B. Incorporation date Service Order No. (dd/mm/yy) Facility Incorporating S.B.
Name Signature Date (dd/mm/yy) Signature not required if sent by E-Mail-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --



### Bombardier Business Aircraft Customer Services (BBACS) P.O. Box 6087, Station Centre-ville Montreal, Québec, Canada H3C 3G9

Attention : Customer Support Department, Maintenance Engineering

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