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 Page 1 of 1 

SERVICE BULLETIN SUMMARY 

This Service Bulletin is available at: 

www.cic.bombardier.com

MODEL CL-600-1A11 

ATA 57-40

WINGS 

SPECIAL CHECK – FLAP HINGE BOX – 

FORWARD LUGS EDGE TO EDGE DISTANCE 

The information below is provided for your reference. For full details, please 

see corresponding paragraph contained within this bulletin. 

RECOMMENDED

SPECIFIED TIME COMPLIANCE

COMPLIANCE TIME 

See Table in Paragraph 1.D. 

EFFECTIVITY: A/C Serial No. 1004 to 1085 

MANPOWER: 45 man-hours 

CONTINUED AIRWORTHINESS (CAW) 

FLEET CAMPAIGN 

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 

NOTE: To minimize aircraft downtime and cost, it is recommended to do Alert Service 

Bulletin A600-0763, Part B in conjunction with this Service Bulletin.

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. 

© 2013 Bombardier Inc. All rights reserved 

Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries. 

Basic Issue: Sep 26/2013 600-0762

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SERVICE BULLETIN 

This Service Bulletin is available at: 

www.cic.bombardier.com 

MODEL CL-600-1A11

ATA 57-40 

WINGS 

SPECIAL CHECK – FLAP HINGE BOX – 

FORWARD LUGS EDGE TO EDGE DISTANCE 

1. PLANNING INFORMATION 

NOTES: 1. To minimize aircraft downtime and cost, it is recommended to do 

Alert Service Bulletin A600-0763, Part B in conjunction with this 

Service Bulletin 

 2. Special tool is required for bushing removal. See Appendix 2 for 

details, or commercially available tool is acceptable. 

A. Effectivity 

CL-600-2B16 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. 

B. Reason 

During production inspection of the flap hinge box assembly, it was found that the 

material around the forward lugs on the inboard and outboard flap hinge boxes 

was below the minimum requirements. 

This Service Bulletin gives instructions to inspect the affected lugs and compare 

them with the limits stated in this Service Bulletin. If necessary, instructions are 

given if the limits are not met. 
MODEL CL-600-1A11 

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C. Description 

This Service Bulletin gives instructions to: 

– Remove the inboard and outboard forward flap-hinge fairings, 

– Disconnect the wing fitting/lugs of the inboard and outboard flap hinge box, 

– Measure the forward lugs of the inboard and outboard flap hinge box, 

– Reconnect the wing fitting/lugs of the inboard and outboard flap hinge box, 

– Install the inboard and outboard forward flap-hinge fairings, and 

– Do the necessary tests to make sure that the inboard and outboard flaps 

operate correctly. 

D. Compliance 

Recommended within 48 months from this Service Bulletin release date 

(Basic Issue) or at the following time compliances, whichever comes first. 

INBOARD FLAPS (WS 76.50 and WS 127.25) 

Accumulated Aircraft Flight 

Cycles 

(Landings)

Compliance Schedule for 

Initial Inspection 

(Landings)

7,400 or less Prior to exceeding 7,900 

More than 7,400 but not 

more than 14,850 

Within the next 500 but not exceeding 

15,100, 

whichever comes first 

More than 14,850 Within 250 flights 

OUTBOARD FLAPS (WS 178.00, WS 220.00 and WS 264.00) 

Accumulated Aircraft Flight 

Cycles 

(Landings) 

Compliance Schedule for 

Initial Inspection 

(Landings) 

7,500 or less Prior to exceeding 8,000 

More than 7,500 but not 

more than 11,350 

Within the next 500 but not exceeding 

11,600, 

whichever comes first 

More than 11,350 Within 250 flights 
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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. 

45 man-hours are necessary to do this Special Check. 

Bombardier Aerospace does not pay for the labor to do this Special Check. 

G. Material - Cost and Availability 

The parts listed in Paragraphs 3.B. may be necessary to do this modification. 

Bombardier Aerospace does not pay for the parts in Paragraph 3.B. to do this 

modification. 

The Smart Parts Plus Program does not pay for the parts in Paragraph 3.B. 

H. Tooling 

The equipment and tools listed below are necessary to do this special check: 

GSE REFERENCE NO. PART NO. DESCRIPTION 

24-00-24 - Tag, Circuit Breaker 

Commercially Available - Torque Wrench 20 to 25 lbf in 

(2.26 to 2.82 Nm) 

Commercially Available - Torque Wrench 30 to 35 lbf in 

(3.39 to 3.95 Nm) 

Commercially Available - C-Clamp 
MODEL CL-600-1A11 

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The tool listed below or a commercially available equivalent tool is required for the 

removal of the bushings. 

REFERENCE NO. PART NO. DESCRIPTION 

See Note 4 - Support Block 

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. 

4. For the support block manufacturing details, refer to Appendix 2. 

I. Weight and Balance 

No change. 

J. Electrical Load Data 

No change. 

K. References 

– Bombardier Aerospace, Restriction and/or Special Instruction (RSI), 

C-4093, Rev. A2. 

– CL-600 Illustrated Parts Catalog (IPC), PSP 604, Chapter 57. 

– CL-600 Illustrated Tool and Equipment Manual (ITEM), PSP 611, Chapter 24. 

– CL-600 Maintenance Manual, PSP 602, Chapters, 6, 12, 27, 51, and 57. 

– CL-600 Structural Repair Manual (SRM), PSP 607, Chapters 51 and 57. 

– CL-600 Time Limits and Maintenance Checks (TLMC), PSP 605, Chapter 5. 

– Bombardier Aerospace, Modification Summary IS600-57-0001, Rev. A. 

– Appendix 1 – Information Feedback Sheet (attached). 

– Appendix 2 – Support Block (attached). 

L. Other Publications Affected 

– None. 

M. Equivalent Service Bulletins 

– For the Challenger 601 aircraft, use SB 601-0631. 

– For the Challenger 604 aircraft, use SB 604-57-007. 

– For the Challenger 605 aircraft, use SB 605-57-005. 
MODEL CL-600-1A11 

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2. ACCOMPLISHMENT INSTRUCTIONS 

NOTES: 1. All TASKs given in the procedures that follow are from the Aircraft 

Maintenance Manual unless otherwise specified. 

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

the Aircraft Maintenance Manual, Chapter 6. 

A. Aircraft Setup 

(1) Install the safety devices and the warning signs in the applicable locations and 

the warning placard on the flap control lever. 

(2) Obey all electrical/electronic safety precautions. Refer to Chapter 24-00-00, 

ELECTRICAL POWER - Removal/Installation. 

(3) Connect and energize the external AC power. Refer to Maintenance Manual, 

PSP 602, Chapter 12-00-00, SERVICING, General. 

(4) Set the flap control lever to 45 degrees and make sure that the flaps are fully 

extended. 

(5) Remove the external AC power. Refer to Maintenance Manual, PSP 602, 

Chapter 12-00-00, SERVICING, General. 

(6) Open and tag the circuit breakers that follow: 

CB PANEL CB NO. NAME ZONE 

CBP-A 20 (19, 21) FLAP MOTOR 1 221 

CBP-A 77 FLAP CONT 1 221 

CBP-B 176 (175, 178) FLAP MOTOR 2 222 

CBP-B 233 FLAP CONT 2 222 

(7) Remove fillet sealant from perimeter around the forward inboard and outboard 

flap hinge-fairings, making contact with the wing surface and the inboard and 

outboard flap respectively. Refer to SRM, Chapter 51-57-00, SEALING – 

Description. 

(8) Remove the left and right flap hinge-fairings that follow: Refer to Maintenance 

Manual, PSP 602, Chapter 6-53-00, REMOVABLE FAIRINGS - General. 

ACCESS DESIGNATION 

571CB (671CB) Fairing, Forward Inboard – Flap Hinge 

571FB (671FB) Fairing, Forward Inboard – Flap Hinge 

581BB (681BB) Fairing, Forward Outboard 

581DB (681DB) Fairing, Forward Outboard 

581FB (681FB) Fairing, Forward Outboard 
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B. Measurement of the Inboard Forward-Lug Edge to Edge Distance of the 

Flap-Hinge-Boxes, Part No. 600-10116, 600-10117. 

CAUTION: ONLY ONE FLAP HINGE BOX IS TO BE DISCONNECTED 

AND INSPECTED AT A TIME. THE FLAP HINGE BOX MUST 

BE SUPPORTED DURING THE INSPECTION SO AS NOT TO 

DAMAGE THE FLAPS AND ATTACHED COMPONENTS. 

(1) For each wing, disconnect one flap hinge box at a time from the wing 

forward-attachment fitting and wing aft-attachment fitting. 

NOTES: 1. The flap will be supported by the other attached flap hinge 

box/arm and both actuators. 

 2. To reduce the load on the other attached flap hinge box/arm 

and actuators, the flaps should also be supported per best 

shop practice or with a bench and padding. Refer to Figure 1. 

Figure 1 

(2) Disconnect the inboard flap hinge box (1) at location WS 76.50 and 

WS 127.25 as follows: Refer to Figures 1, 2, 3 and 4. 

NOTE: It is not necessary to remove the flap hinge boxes from the aircraft for 

the lug edge to edge distance measurement. Refer to Figure 2 for 

the recommendations to disconnect the flap hinge box. 
MODEL CL-600-1A11 

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Flap Hinge Box 

Figure 2 

(a) If necessary, remove and keep the hardware that attach the bonding 

jumpers to the flap hinge box (1). 

(b) For the flap hinge box (1) located at WS 76.50 only, do as follows: 

(i) If necessary, disconnect the electrical connector wire (3) from any 

attached location on the structure, to allow downward movement 

of the flap hinge box. 

Support for the 

flap hinge box 

Disconnect 

flap hinge box 

from fittings. CAUTION: 

Make sure that there is no 

contact between the flap hinge 

box and fairing to avoid 

damage when lowering the 

flap hinge box. 

If required, remove 

flap hinge box 

bonding jumper. 

Lower flap hinge box 

enough to permit 

measurement of the 

lug edge to edge 

distance. 
MODEL CL-600-1A11 

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WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE 

COTTER PIN. WHEN THE COTTER PIN IS CUT, 

PIECES CAN HIT YOUREYES AND CAUSE INJURIES. 

(ii) Remove and discard the cotter pin (4). Refer to Maintenance Manual 

PSP 602, 20-80-00, SAFETYING DEVICES, Cotter Pins. 

(iii) Remove the nut (5), washer (6) and bolt (7) and disconnect the 

control rod (2) from the lever (8) of the flap position transmitter. 

(iv) If disconnected, put protective covers on the open ends of the 

electrical connector (3) and on the electrical connection of the 

position transmitter. 

(c) Remove and keep the nuts (9), washers (10) and (11), and bolts (12), 

to disconnect the forward lugs of the flap hinge box (1) from the forward 

attachment fitting. 

 

CAUTION: TO REMOVE AND INSTALL THE HINGE 

BUSHINGS USE A C-CLAMP METHOD WITH 

THE SUPPORT BLOCK. USE LIGHT ANTI-SEIZE 

LUBRICANT (WD-40 OR SIMILAR) IF THE 

BUSHINGS ARE SEIZED OR DIFFICULT TO 

REMOVE. MAKE SURE THAT THE LATERAL 

FORCE DOES NOT EXCEED 200 LBS AND 

DO NOT USE A HAMMER TO REMOVE THE 

BUSHINGS, THIS CAN CAUSE DAMAGE. 

 BEFORE YOU INSTALL THE C-CLAMP, MAKE 

SURE YOU INSTALL A SUPPORT BLOCK 

BETWEEN THE FITTINGS, SHIMS IN ALL 

GAPS AS REQUIRED TO AVOID BENDING 

AND DAMAGE FROM THE CLAMP FORCE. 

 OTHER METHOD THAN C-CLAMP COULD BE 

USED, PROVIDED LUGS ARE SUPPORTED AND 

LATERAL FORCE DOES NOT EXCEED 200 LBS 

TO AVOID DAMAGE. 

Figure 3 

Install the support block,

manufactured as per 

Appendix 2 or an 

equivalent commercially 

available tool between 

the fittings. 

Shim all gaps as 

required. 
MODEL CL-600-1A11 

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(d) Remove bushings (13) to disconnect the flap hinge box (1) from the 

forward attachment fitting. Keep bushings (13) if not damaged to 

re-install later. Refer to Figures 3 and 4. 

CAUTION: HOLD THE FLAP HINGE BOX WHILE THE BOLTS ARE 

REMOVED. IF THE FLAP HINGE BOX FALLS, IT WILL 

CAUSE DAMAGE TO THE FLAP HINGE BOX AND ATTACHED 

COMPONENTS. 

(e) Remove and keep the nuts (14), washers (15) and (16), and bolts (17), 

to disconnect the hinge box (1) from the aft attachment fitting. 

(f) Remove bushings (18) to disconnect the hinge box (1) from the aft 

attachment fitting. Keep bushings (18) if not damaged to re-install later. 

Refer to Figures 3 and 4. 

CAUTION: MAKE SURE THERE IS NO CONTACT BETWEEN THE FLAP 

HINGE BOX AND AFT FAIRING TO AVOID DAMAGE TO THE 

AIRCRAFT STRUCTURE WHEN YOU LOWER THE FLAP HINGE 

BOX DOWNWARD FOR ACCESS. 

(3) Carefully pull the flap hinge box (1) downward to allow access to the forward 

lugs for the lug edge to edge distance measurement. 
MODEL CL-600-1A11 

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Inboard Flap-Hinge-Box 

Figure 4 
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(4) Measure and record the minimum lug edge to edge distance of the forward 

lugs of the inboard flap hinge boxes at locations WS 76.50 and WS 127.25. 

Refer to Figure 5. 

NOTE: LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE.

WS 76.50 and WS 127.25 

Inboard Flap-Hinge-Box Forward-Lug Edge to Edge Distance Limits 

Figure 5 
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(5) If any of the inboard flap-hinge-box forward lug edge to edge distance is below 

the 0.256 in (6.50 mm) minimum limit do the steps that follow: 

(a) Fill-in Appendix 1 with the data (minimum lug edge to edge distance, hole 

diameter, lug thickness & lug location) applicable to the faulty Flap Hinge 

Box(es), then, 

(b) Submit Appendix 1 with an SRPSA to Customer Support Engineering 

(CSE) for evaluation and an approved repair by e-mail at: 

SRPSA@aero.bombardier.com. 

(6) If the measured forward-lug edge to edge distance of the inboard flap-hingeboxes are equal or above the minimum limit, no corrective action is required. 

Install the inboard flap-hinge-box in the steps that follow.

(7) Install the inboard flap hinge box (1) at locations WS 76.50 and WS 127.25 as 

follows: Refer to Figure 4. 

(a) Apply a layer of Mastinox 6856K to the bushings (13) and (18) on installation. 

(b) Put the flap-hinge-box (1) in position. 

(c) Install the bushings (18) on the flap hinge box (1) and aft attachment fitting. 

(d) Install the bushings (13) on the forward lugs of the flap hinge box (1) and 

forward attachment fitting. 

(e) Install bolts (17), washers (15) and (16), and nuts (14) to attach the flap 

hinge box (1) to the aft attachment fitting. 

NOTE: Make sure the sum of the gap measurement between the aft 

attachment fitting and lower surface of bolt head (17), and 

between the aft attachment fitting and the lower surface of 

washer (15), is 0.020 in to 0.105 in (0.508 mm to 2.667 mm). 

(f) Install the bolts (12), washers (10) and (11), and nuts (9) to attach the flap 

hinge box (1) to the forward attachment fitting. 

NOTE: Make sure the sum of the gap measurement between the 

forward attachment fitting and lower surface of bolt head 

(12), and between the forward attachment fitting and the 

lower surface of washer (10), is 0.015 in to 0.060 in 

(0.381mm to 1.524 mm). 

(g) Torque the nuts (9) and (14) from 30 to 35 lbf in (3.39 to 3.95 Nm). 

Refer to Maintenance Manual, PSP 602, Chapter 20-20-11, THREADED 

FASTENERS. 

(h) Attach the control rod (2) and electrical connector (3) to the flap position 

transmitter as follows: 

(i) Align the eye of the control rod (2) with the lever (8). 

(ii) Install the bolt (7), washer (6) and the nut (5). 

(iii) Torque the nut (5) from 20 to 25 lbf in (2.26 to 2.82 Nm). Refer to 

Maintenance Manual, PSP 602, Chapter 20-20-11, THREADED 

FASTENERS. 
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WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE 

COTTER PIN. WHEN THE COTTER PIN IS CUT, 

PIECES CAN HIT YOUREYES AND CAUSE INJURIES. 

(iv) Install the cotter pin (4). Refer to Maintenance Manual PSP 602, 

20-80-00, SAFETYING DEVICES, Cotter Pins. 

(v) If installed, remove the protective covers from the open ends of 

the electrical connector (3) and from the electrical connection of 

the position transmitter. 

(vi) If disconnected, connect the electrical connector (3) to the flap 

position transmitter. 

NOTE: If detached, attach the electrical connector wire to the 

necessary locations on the structure. 

(i) If removed, install the bonding jumper on the flap hinge box (1). Refer to 

Maintenance Manual, PSP 602, Chapter 57-40-01, FLAP HINGE BOX, 

Removal/Installation. 

(j) If necessary, do the electrical bonding test for the applicable flap hinge 

box (1). Refer to Maintenance Manual, PSP 602, Chapter 51-80-00, 

ELECTRICAL BONDING. 

C. Measurement of the Outboard Forward-Lug Edge to Edge Distance of the 

Flap-Hinge-Boxes, Part No. 600-10118, 600-10119, and 600-10120.

(1) Disconnect the outboard flap hinge box (19) at locations WS 178.00, 

WS 220.00, and WS 264.00 as follows: Refer to Figures 1, 2, 3 and 6. 

NOTE: It is not necessary to remove the flap hinge boxes from the aircraft for 

the lug edge to edge distance measurement. Refer to Figure 2 for 

the recommendations to disconnect the flap hinge box. 

(a) If necessary, remove and keep the hardware that attach the bonding 

jumpers to the flap hinge box (19). 

(b) Disconnect the control rod (23) from the BUTE door fitting in the steps 

that follow: 

WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE COTTER 

PIN. WHEN THE COTTER PIN IS CUT, PIECES CAN HIT 

YOUREYES AND CAUSE INJURIES. 

(i) Remove and discard the cotter pin (20). Refer to Maintenance 

Manual PSP 602, 20-80-00, SAFETYING DEVICES, Cotter Pins. 

(ii) Remove and keep the pin (21) and washer (22) to disconnect the 

control rod (23) from the BUTE door fitting. 

(c) Remove and keep the nuts (24), washers (25) and (26), and bolts (27), 

to disconnect the hinge box (19) from the forward attachment fitting. 
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(d) Remove bushings (28), to disconnect the hinge box (19) from the forward 

attachment fitting. Keep bushings if not damaged to re-install later. Refer 

to Figures 3 and 6. 

CAUTION: HOLD THE FLAP HINGE BOX WHILE THE BOLTS ARE 

REMOVED. IF THE FLAP HINGE BOX FALLS, IT WILL 

CAUSE DAMAGE TO THE FLAP HINGE BOX AND ATTACHED 

COMPONENTS. 

(e) Remove and keep the nuts (29), washers (30) and (31), and bolts (32), 

to disconnect the hinge box (19) from the aft attachment fitting. 

(f) Remove bushings (33), to disconnect the hinge box (19) from the aft 

attachment fitting. Keep bushings if not damaged to re-install later. 

Refer to Figures 3 and 6. 

CAUTION: MAKE SURE THERE IS SUFFICIENT CLEARANCE BETWEEN THE 

FLAP HINGE BOX AND AFT FAIRING TO AVOID DAMAGE TO THE 

AIRCRAFT STRUCTURE WHEN YOU LOWER THE FLAP HINGE 

BOX DOWNWARD FOR ACCESS. 

(2) Carefully pull the flap hinge box (19) downward to allow access to the forward 

lugs for the lug edge to edge distance inspection.
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19

24

27

19

29

30

33

31

32

DSB57050_004

FORWARD ATTACHMENT

FITTTING AFT ATTACHMENT

FITTTING

AREA OF

INSPECTION

25

28

26

27

22

21

20

23

FITTING BUTE DOOR

Outboard Flap-Hinge-Box 

Figure 6
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(3) Measure and record the minimum lug edge to edge distance of the forward 

lugs of the outboard flap hinge boxes at location WS 178.00, WS 220.00, and 

WS 264.00. Refer to Figure 7. 

NOTE: LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE. 

WS 178.00, WS 230.00 and WS 264.00 

Outboard Flap-Hinge-Box Forward-Lug Edge to Edge Distance Limits 

Figure 7
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(4) If any of the outboard flap-hinge-box forward-lug edge to edge distance is 

below the 0.182 in (4.62 mm) minimum limit do the steps that follow: 

(a) Fill-in Appendix 1 with the data (minimum lug edge to edge distance, hole 

diameter, lug thickness & lug location) applicable to the faulty Flap Hinge 

Box(es), then, 

(b) Submit Appendix 1 with an SRPSA to Customer Support Engineering 

(CSE) for evaluation and an approved repair by e-mail at: 

SRPSA@aero.bombardier.com. 

(5) If the measured forward-lug edge to edge distance of the outboard flap-hingeboxes are equal or above the minimum limit, no corrective action is required. 

Follow the next steps to install the outboard flap hinge box. 

(6) Install the outboard flap hinge box (19) at locations WS 178.00, WS 220.00, 

and WS 264.00 as follows: Refer to Figure 6. 

(a) Apply a layer of Mastinox 6856K to the bushings (28) and (33) on 

installation. 

(b) Put the flap-hinge-box (19) in position. 

(c) Install the bushings (33) on the flap hinge box (1) and aft attachment 

fitting. Refer to Figure 3. 

(d) Install the bushings (28) on the forward lugs of the flap hinge box (1) 

and forward attachment fitting. Refer to Figure 3. 

(e) Install bolts (32), washers (30) and (31), and nuts (29) to attach the flap 

hinge box (19) to the aft attachment fitting. 

NOTE: Make sure the sum of the gap measurement between the 

aft attachment fitting and lower surface of bolt head (32), 

and between the aft attachment fitting and the lower surface 

of washer (30), is 0.020 in to 0.105 in (0.508 mm 

to 2.667 mm). 

(f) Install the bolts (27), washers (25) and (26), and nuts (24) to attach 

the flap hinge box (19) to the forward attachment fitting. 

NOTE: Make sure the sum of the gap measurement between the 

forward attachment fitting and lower surface of bolt head 

(27), and between the forward attachment fitting and the 

lower surface of washer (25), is 0.015 in to 0.060 in 

(0.381mm to 1.524 mm). 

(g) Torque the nuts (24) and (29) from 30 to 35 lbf in (3.39 to 3.95 Nm). 

Refer to Maintenance Manual, PSP 602, Chapter 20-20-11, THREADED 

FASTENERS. 

(7) Connect the control rod (23) to the BUTE door fitting in the steps that follow: 

Refer to Figure 6. 

(i) Put the control rod (23) in position on the BUTE door fitting. 

(ii) Install the pin (21) and washer (22) to connect the control rod (23) 

to the BUTE door fitting. 
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WARNING: WEAR EYE PROTECTION WHEN YOU CUT THE 

COTTER PIN. WHEN THE COTTER PIN IS CUT, 

PIECES CAN HIT YOUREYES AND CAUSE INJURIES. 

(iii) Safety the pin (21) with the new cotter pin (20). Refer to 

Maintenance Manual PSP 602, 20-80-00, SAFETYING DEVICES, 

Cotter Pins. 

(8) If removed, install the bonding jumpers on the outboard flap hinge box (19). 

Refer to Maintenance Manual, PSP 602, Chapter 57-40-01, FLAP HINGE 

BOX, Removal/Installation. 

(9) If necessary, do the electrical bonding test for the applicable flap hinge 

box (19). Refer to Maintenance Manual, PSP 602, Chapter 51-80-00, 

ELECTRICAL BONDING. 

D. Testing 

(1) Do an operational test of the inboard and outboard flaps to make sure the 

flap hinge box assemblies move freely, before installing the flap hinge-fairings. 

Refer to TASK 27-54-00-710-801. 

(2) Install the left and right flap hinge-fairings that follow: Refer to Maintenance 

Manual, PSP 602, Chapter 6-53-00, REMOVABLE FAIRINGS - General. 

ACCESS DESIGNATION 

571CB (671CB) Fairing, Forward Inboard – Flap Hinge 

571FB (671FB) Fairing, Forward Inboard – Flap Hinge 

581BB (681BB) Fairing, Forward Outboard 

581DB (681DB) Fairing, Forward Outboard 

581FB (681FB) Fairing, Forward Outboard 

(3) Apply a filet of sealant around the flap hinge fairings. Refer to SRM, Chapter 

51-57-00, SEALING – Description, Aerodynamic Sealing. 

(4) Remove the tags and close the circuit breakers that follow: 

CB PANEL CB NO.

(3001 to 3066) (5001 to 5194)

NAME ZONE

CBP-A 20 20 FLAP MOTOR 1 221 

CBP-A 77 77 FLAP CONT 1 221 

CBP-B 176 20 FLAP MOTOR 2 222 

CBP-B 233 77 FLAP CONT 2 222 

(5) Connect and energize the external AC power. Refer to Maintenance Manual, 

PSP 602, Chapter 12-00-00, SERVICING – General. 

(6) Set the flap control lever lever to 0 and make sure that the flaps retract fully. 
MODEL CL-600-1A11 

Basic Issue: Sep 26/2013 600-0762

 Page 19 of 20 

(7) Do an operational test of the inboard and outboard flaps. Refer to 

Maintenance Manual, PSP 602, Chapter 27-50-11, FLAPS – Maintenance 

Practices. 

(8) Remove the external AC power. Refer to Maintenance Manual, PSP 602, 

Chapter 12-00-00, SERVICING – General. 

E. Close-out 

Remove all tools, equipment and unwanted materials from the aircraft. 

F. Recording 

When 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 required. 

B. Parts 

The parts that follow are necessary to do this Service Bulletin and are available 

from Bombardier Aerospace Parts Services, Montreal: 

NEW 

PART NO. 

QTY ITEM USED 

PART NO. 

INSTRUCTIONS - 

DISPOSITION 

MS24665-151 6 Cotter Pin - - 

MS24665-71 2 Cotter Pin - - 

The parts that follow may be necessary to do this Service Bulletin if the removed 

bushing(s) are damaged or found corroded: 

NEW 

PART NO. 

QTY ITEM USED 

PART NO. 

INSTRUCTIONS - 

DISPOSITION 

600-10300-609 0 - 8 Sleeve Bushing - - 

600-10300-611 0 - 8 Sleeve Bushing - - 

600-10300-613 0 - 12 Sleeve Bushing - - 

600-10300-615 0 - 12 Sleeve Bushing - - 
MODEL CL-600-1A11 

Basic Issue: Sep 26/2013 600-0762

 Page 20 of 20 

C. Material 

The materials that follow, or equivalent, 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)

Compound, 

Sealing 

CT: 2 Hours or 

30 Minutes 

- MIL-S-81733 

Type II, PS 870 

Class B-2 or 

B-1/2 

As 

Necessary 

Code: A 

Compound, 

Corrosion 

Inhibitor 

- Mastinox 6856K As 

Necessary 

Code: A 

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. 

SUPPLIERS ADDRESSES BY CODES 

Code: A 

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

D. Publications 

No publications required. 
SERVICE BULLETIN EVALUATION FORM 

(Your ideas will help us provide better bulletins) 

SERVICE BULLETIN: 600-0762 ISSUE: Basic DATED: Sep 26/2013 

 

TITLE: Special Check – Flap Hinge Box – Forward Lugs Edge to Edge Distance 

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
SERVICE BULLETIN INCORPORATION SHEET – “600-0762 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 

 600-0762 Basic - 

 - - - 

 - - - 

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
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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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