605-57-005

Page 1 of 1 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

MODEL CL-600-2B16 

Discard the Basic Issue of this Service Bulletin dated Sep 26/2013 and the 

Information Sheet dated Nov 15/2013, and replace in its entirety with this Revision 01. 

Service Bulletin No. 605-57-005

Date of Basic Issue Sep 26/2013

Revision No. 01 Dated Nov 12/2014

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. 

You may make an entry as “Not Applicable” for this revision. 

This revision is issued to separate the procedure into Part A and Part B. The changes 

are as follows: 

1. Change the Service Bulletin Summary Sheet to update the Manpower and add some 

notes. 

2. Change Paragraph 1, Planning Information, to add the Airworthiness Directive data 

and recommendation for Part A. 

3. Change Paragraph 1.C., Description, to add Part A, Part B and Testing. 

4. Change Paragraph 1.F., Manpower, to update the man-hours for Part A and Part B. 

5. Change Paragraph 2.A., Aircraft Setup, to update the access specific for Part A and 

Part B. 

6. Change Paragraph 2.B., to update the procedure specific into Part A and Part B. 

7. Change Paragraph 2.F., to update the Recording instructions. 

8. Change Paragraph 3.B., to split the parts list into Part A and Part B. 

9. Make miscellaneous minor changes, as necessary, with no change of context. 
Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 1 of 1 

SERVICE BULLETIN SUMMARY 

This Service Bulletin is available at: 

www.cic.bombardier.com

MODEL CL-600-2B16

ATA 57-52 

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 

Recommended prior to exceeding 

7,800 flights or within 48 months from 

this Service Bulletin release date 

(Basic Issue), whichever comes first.

EFFECTIVITY: A/C Serial No. 5701 to 5953 

MANPOWER: 0.5 man-hours to do PART A Special check if done in conjunction with 

SB A605-57-004, PART B. 

18 man-hours to do PART A Special check if not done in conjunction with 

SB A605-57-004, PART B. 

27 man-hours to do PART B, Special Check. 

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 

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

this SB in conjunction with the Alert Service Bulletin A605-57-004, PART B. 

2. The Basic Issue of this SB605-57-005 is equivalent to PART A and PART B 

of the current revision of this Service Bulletin. 

3. This Service Bulletin is the subject of the Airworthiness Directive 

CF-2014-01 which makes it necessary to implement 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 - 2014 Bombardier Inc. All rights reserved 

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

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 1 of 22 

SERVICE BULLETIN 

This Service Bulletin is available at: 

www.cic.bombardier.com 

MODEL CL-600-2B16

ATA 57-52 

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 PART A 

of this SB in conjunction with the Alert Service Bulletin A605-57-004, 

PART B. 

 2. The Basic Issue of this SB605-57-005 is equivalent to PART A and 

PART B of the current revision of this Service Bulletin. 

3. You can do PART A or PART B of this Service Bulletin independently. 

This Service Bulletin can only be closed and in compliance with 

Transport Canada Airworthiness Directive CF-2014-01, Paragraph D, 

when the special check in PART A and PART B are completed. 

 4. 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. 5701 to 5953.

Aircraft, Serial No. 5954 and all other subsequent aircraft are scheduled for 

modification in production (Ref.: Restriction and/or Special Instruction (RSI), 

C-4093). 

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-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 2 of 22 

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. 

C. Description 

This Service Bulletin gives instructions to: 

– Remove the inboard and/or outboard forward flap-hinge fairings.

– PART A, to:

– Disconnect the wing fitting/lugs of the inboard flap hinge boxes, 

– Measure the forward lugs of the inboard flap hinge boxes, and 

– Reconnect the wing fitting/lugs of the inboard flap hinge boxes. 

– PART B, to:

– Disconnect the wing fitting/lugs of the outboard flap hinge boxes, 

– Measure the forward lugs of the outboard flap hinge boxes, and 

– Reconnect the wing fitting/lugs of the outboard flap hinge boxes. 

– Testing, to:

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

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

correctly. 

D. Compliance 

Recommended prior to exceeding 7,800 flights or within 48 months from this 

Service Bulletin release date (Basic Issue), whichever comes first. 

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. 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 3 of 22 

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 605-00-002. 

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. 

0.5 man-hours are necessary to do PART A, Special Check, if done in conjunction 

with SB A605-57-004, Part B (not claimable). 

18 man-hours are necessary to do PART A, Special Check if SB A605-57-004, 

PART B does not apply. 

27 man-hours are necessary to do PART B, Special Check. 

27 man-hours to do PART B of this Service Bulletin are at no cost for aircraft, Serial 

numbers 5701 to 5920 in new aircraft warranty at the time of release of this Service 

Bulletin (Basic Issue), 

(i) the work is done at Bombardier Business Aviation Services (BBAS) or 

Authorized Service Facilities (ASF), and 

(ii) this Service Bulletin is scheduled prior to exceeding 7,800 flights or within 

48 months from this Service Bulletin release date (Basic Issue), whichever 

comes first. 

and 

18 man-hours to do PART A of this Service Bulletin are at no cost for aircraft, 

Serial numbers 5701 to 5920 in new aircraft warranty at time of release of this 

Service Bulletin (Basic Issue), if the aircraft has signed PART C and not 

incorporated PART B of SB A605-57-004, and if: 

(iii) the work is done at Bombardier Business Aviation Services (BBAS) or 

Authorized Service Facilities (ASF), and 

(iv) this Service Bulletin is scheduled prior to exceeding 7,800 flights or within 

48 months from this Service Bulletin release date (Basic Issue), whichever 

comes first. 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 4 of 22 

Or 

45 man-hours to do PART A and PART B of this Service Bulletin are at no cost for 

aircraft, Serial numbers 5921 to 5953 in new aircraft warranty at the time of release 

of this Service Bulletin (Basic Issue) and if: 

(i) the work is done at Bombardier Business Aviation Services (BBAS) or 

Authorized Service Facilities (ASF), and 

(ii) this Service Bulletin is scheduled prior to exceeding 7,800 flights or within 

48 months from this Service Bulletin release date (Basic Issue), whichever 

comes first. 

G. Material - Cost and Availability 

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

If necessary, the parts are available at no cost for aircraft in new aircraft warranty 

at the time of release of this Service Bulletin (Basic Issue), if: 

(i) a no-charge purchase order is sent to Bombardier Aerospace prior to 

exceeding 7,800 flights or within 48 months, whichever comes first, from this 

Service Bulletin release date (Basic Issue). 

During or after the above free period, Smart Parts Plus does not pay for the parts. 

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 

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 3 - Support Block 

NOTES: 1. Refer to the CL-605 Illustrated Tool and Equipment Manual (ITEM) 

to make sure that you use the correct equipment configuration. 

2. Refer to the Liability Statement in the ITEM for acceptable GSE 

equivalents. 

3. For the support block manufacturing details, refer to Appendix 2. 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 5 of 22 

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-605 Aircraft Illustrated Parts Catalog (AIPC), Chapter 57. 

– CL-605 Aircraft Illustrated Tool and Equipment Manual, Chapter 24. 

– CL-605 Aircraft Maintenance Manual (AMM), Chapters 6, 12, 27, and 57. 

– CL-605 Standard Practice Manual (SPM), Chapter 51. 

– CL-605 Standard Practice Manual (SRM), Chapter 51. 

– CL-605 Time Limits and Maintenance Checks (TLMC), 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 600 aircraft, use SB 600-0762. 

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

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

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 

3. The Basic Issue of this SB605-57-005 is equivalent to PART A and 

PART B of the current revision of this Service Bulletin. 

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 TASK 24-00-00-910-801. 

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

TASK 12-00-07-861-801. 
MODEL CL-600-2B16

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Revision 01: Nov 12/2014 Page 6 of 22 

(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 TASK 12-00-07-861-802. 

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

CB PANEL CB NO. NAME ZONE 

CBP-2 B5 FLAP MOTOR 2 222 

CBP-2 F3 FLAP CONT 2 222 

CBP-3 B11 FLAP MOTOR 1 221 

CBP-4 A9 FLAP CONT 1 222 

(7) For PART A, remove fillet sealant from perimeter around the forward inboard 

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

respectively. Refer to SPM-MM 51-23-00-100-801. 

Remove the left and right inboard flap hinge-fairings that follow: Refer to 

TASK 57-26-03-000-801. 

ACCESS DESIGNATION 

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

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

(8) For PART B, remove fillet sealant from perimeter around the forward outboard 

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

respectively. Refer to SPM-MM 51-23-00-100-801. 

Remove the left and right outboard forward flap hinge-fairings that follow: Refer 

to TASK 57-26-05-000-801. 

ACCESS DESIGNATION 

581BB (681BB) Fairing, Forward Outboard 

581DB (681DB) Fairing, Forward Outboard 

581FB (681FB) Fairing, Forward Outboard 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 7 of 22 

B. PART A: 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-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 8 of 22 

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. 

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 

SPM-MM 20-50-00-000-802. 

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-600-2B16

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Revision 01: Nov 12/2014 Page 9 of 22 

(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), bolts (12), to 

disconnect 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 (LPS-1 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-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 10 of 22 

(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-600-2B16

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Revision 01: Nov 12/2014 Page 11 of 22 

Inboard Flap-Hinge-Box 

Figure 4
MODEL CL-600-2B16

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Revision 01: Nov 12/2014 Page 12 of 22 

(4) Measure and record the minimum 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 
MODEL CL-600-2B16

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Revision 01: Nov 12/2014 Page 13 of 22 

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

(d) Install 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). 

Refer to TASK 57-52-01-400-801. 

(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). 

Refer to TASK 57-52-01-400-801. 

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

Refer to SPM-MM 20-21-00-910-801. 

(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 

SPM-MM 20-21-00-910-801. 
MODEL CL-600-2B16

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Revision 01: Nov 12/2014 Page 14 of 22 

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 SPM-MM 20-50-00-400-802. 

(v) 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 

SPM 51-80-00-400-801. 

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

(1). Refer to SPM-MM 51-80-00-760-801. 

C. PART B: 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 

SPM-MM 20-50-00-000-802. 

(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. 

(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. 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 15 of 22 

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 inspection.
MODEL CL-600-2B16

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Revision 01: Nov 12/2014 Page 16 of 22 

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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Revision 01: Nov 12/2014 Page 18 of 22 

(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 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. 

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

and forward attachment fitting. 

(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). 

Refer to TASK 57-52-01-400-801. 

(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). 

Refer to TASK 57-52-01-400-801. 

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

to SPM-MM 20-21-00-910-801. 

(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. 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 19 of 22 

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 

SPM-MM 20-50-00-000-802. 

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

Refer to SPM 51-80-00-400-801. 

(9) If necessary, do the electrical bonding test for the applicable flap hinge box (19). 

Refer to SPM-MM 51-80-00-760-801. 

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 inboard flap hinge-fairings that follow: Refer to 

TASK 57-26-03-400-801. 

ACCESS DESIGNATION 

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

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

(3) If removed, install the left and right outboard flap hinge-fairings that follow: 

Refer to TASK 57-26-05-400-801. 

ACCESS DESIGNATION 

581BB (681BB) Fairing, Forward Outboard 

581DB (681DB) Fairing, Forward Outboard 

581FB (681FB) Fairing, Forward Outboard 

(4) Apply a filet of sealant around the flap hinge fairings. Refer to 

SPM-MM 51-23-00-390-805. 

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

CB PANEL CB NO. NAME ZONE 

CBP-2 B5 FLAP MOTOR 2 222 

CBP-2 F3 FLAP CONT 2 222 

CBP-3 B11 FLAP MOTOR 1 221 

CBP-4 A9 FLAP CONT 1 222 

(6) Connect and energize the external AC power. Refer to 

TASK 12-00-07-861-802. 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 20 of 22 

(7) Set the flap control lever to 0 and make sure that the flaps retract fully. 

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

TASK 27-54-00-710-801. 

(9) Remove the external AC power. Refer to TASK 12-00-07-861-802. 

E. Close-out 

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

F. Recording 

You can do PART A or PART B 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). 

This Service Bulletin can only be closed and in compliance with 

Transport Canada Airworthiness Directive CF-2014-01, Paragraph D, when the 

special check in PART A and PART B is completed. 

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
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 21 of 22 

3. MATERIAL INFORMATION 

A. Kit 

No kit required. 

B. Parts 

The parts that follow are necessary to do PART A of this Service Bulletin and are 

available from Bombardier Aerospace Parts Services, Montreal: 

NEW 

PART NO. 

QTY ITEM USED 

PART NO. 

INSTRUCTIONS - 

DISPOSITION 

MS24665-71 2 Cotter Pin - - 

The parts that follow are necessary to do PART B of 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 - - 

The parts that follow may be necessary, to do PART A of 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 - - 

The parts that follow may be necessary to do PART B of this Service Bulletin if the 

removed bushing(s) are damaged or found corroded: 

NEW 

PART NO. 

QTY ITEM USED 

PART NO. 

INSTRUCTIONS - 

DISPOSITION 

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

600-10300-615 0 - 12 Sleeve Bushing - - 
MODEL CL-600-2B16

Basic Issue: Sep 26/2013 605-57-005

Revision 01: Nov 12/2014 Page 22 of 22 

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: 605-57-005 ISSUE: Rev. 01 DATED: Nov 12/2014 

 

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 – “605-57-005” 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 

 605-57-005 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
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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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