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. A600-0769

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, Paragraph 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 instructions are given to secure the TRs in the 

stowed position if any indication 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 20/2014 
Basic 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 your 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 1-866-538-1247
Refer 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 Services (BBAS), Completion Centers, 

Authorized Service Facilities, Spare Parts 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 the TR deployment in flight was caused 

by damaged translating sleeve frame and intercostals 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 intercostals areas at “4 o’clock”, “8 o’clock” 

and “12 o’clock” position, and 

– Reinstall the thrust reversers if no indication 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 inspection. 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 Service Bulletin without incorporating the 

PART A. 

If you incorporate PART B, it is not necessary 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 estimates 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 furnishings, repainting, supervision and 

inspection. 

For more information related to the manpower estimates, refer to 

SB 600-0002. 

2. This Service Bulletin may require consumable materials that have 

specific curing times (refer to Paragraph 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 necessary 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 necessary 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 parts 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 prevail. 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 Engineering 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 Catalog (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 (DOT) 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 (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. 

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, PSP602, unless otherwise specified. 

2. All references made to zones, access panels and/or doors, are 

from the Maintenance Manual 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 COMPONENT 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 Reverser 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 this 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 inspection, 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, THRUST REVERSER – Adjustment/Test. 

NOTE: Make sure that there is no binding 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 attachment to frame and intercostals. Refer to 

Figure 1. 

Thrust Reverser Translating Sleeve 

Figure 1 

(5) Use lint free cloth moist with aliphatic naphtha and thoroughly clean frame and 

intercostals of affected area. Refer to SRM PSP 607, Chapter 51-53-00, 

CLEANING. 

“12 o’clock" 

actuator 

attachment 

“4 o’clock” 

actuator 

attachment 

VIEW SHOWING POSITION OF 

ACTUATORS ATTACHMENTS

“8 o’clock” actuator 

attachment 
 

MODEL 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 actuator 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 

AT “4 O’CLOCK” POSITION
MODEL 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 fully stowed position. Refer to Maintenance 

Manual PSP 602, Chapter 78-30-00, THRUST REVERSER – Adjustment/Test. 

NOTE: Make sure that there is no binding or fouling during cranking. 

(9) Perform steps (1) to (8) to the RH engine. 

(10) If there is no indication of cracks on both thrust reversers, reinstall the thrust 

reversers. Refer to Maintenance Manual 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 aircraft, 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 crack 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 lug 
MODEL CL-600-1A11 

Basic Issue: Jun 19/2014 A600-0769 

Revision 01: Jun 26/2014 Page 11 of 25 

C. PART B – Modification – Installation 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, both 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 reverser 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 translating sleeve. Refer to Chapter 78-30-21, 

FLIPPER DOORS – Removal/Installation. 

(3) Do the modification of the upper flipper 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. Manually apply Alodine 1200, then one 

layer of fluid resistant epoxy primer, all over. Refer to SRM, Chapter 

51-58-138/43, FLUID RESISTANT 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 distance 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 translating 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 FORMING and to SRM PSP 607, Chapter 

51-28-40, STANDARD MACHINING. 

(b) Manually apply Alodine 1200, then one layer 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 distance 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 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 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 DOORS PSP – Removal/Installation. 

NOTE: Apply Alodine and primer on reworked areas of the Translating Sleeve. 

(15) Install the lower flipper door to the translating sleeve. Refer to Maintenance Manual 

PSP 602, chapter 78-30-21, FLIPPER DOORS – Removal/Installation. 

NOTE: Apply Alodine and primer on reworked areas of the Translating Sleeve. 

Doubler

Flipper Door
MODEL 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 stowed position and adjust flipper door to fit flush 

with translating sleeve. 

NOTE: Make sure that there is no binding 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 frame 215-0618-671. 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 all 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 around the doubler contour. Refer to 

SRM PSP 607, Chapter 51-57-00, SEALING. 

(19) Apply polyurethane topcoat on the reworked 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 all 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 around the doubler contour. Refer to 

SRM PSP 607, Chapter 51-57-00, SEALING. 

(21) Apply polyurethane topcoat on the reworked 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 unwanted 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), Completion Centers, Authorized Service 

Facilities, Spare Parts Center, Montreal 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 Business 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 Services, 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 listed 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. Bombardier 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 25 
MODEL 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 25 
MODEL 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 25 
K600-60088 – Kit – Thrust Reverser Locking (Sheet 1 of 4, Rev. --) 

Basic Issue: Jun 19/2014 Revision 01: Jun 26/2014 

A600-0769

Page 22 of 25
K600-60088 – Kit – Thrust Reverser Locking Installation

(Sheet 2 of 4, Rev. --) 

Basic Issue: Jun 19/2014 A600-0769Revision 01: Jun 26/2014 Page 23 of 25 
K600-60088 – Kit – Thrust Reverser Locking Installation

(Sheet 3 of 4, Rev. --) 

 Basic Issue: Jun 19/2014 A600-0769 Revision 01: Jun 26/2014 Page 24 of 25 
K600-60088 – Kit – Thrust Reverser Locking Installation 

(Sheet 4 of 4, Rev. --) 

Basic Issue: Jun 19/2014 Revision 01: Jun 26/2014 

A600-0769

Page 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. Please 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” 

BOMBARDIER 

SUBMISSION

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 

-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --