A600-0763

Page 1 of 1

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

MODEL CL-600-1A11

Discard the Revision 01 of this Service Bulletin dated Feb 26/2013, and replace in its

entirety with this Revision 02.

Service Bulletin No. A600-0763

Date of Basic Issue Sep 26/2013

Revision No. 01 Dated Feb 26/2014

Revision No. 02 Dated Dec 09/2014

For action applicable to aircraft on which the Basic Issue or Revision 01 of this

Service Bulletin was done, refer to the retroactive action box on Page 1 of this

Service Bulletin.

This revision has no effect for aircraft on which PART B or PART C 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:

1. Change the Service Bulletin Summary Sheet and Paragraph 1.D., Compliance Time,

to reflect the Restriction and/or Special Instruction (RSI), C-4095, Rev. D.

2. Add in the Service Bulletin Summary Sheet, in the Planning Information note and in

Paragraph 1.D., Compliance, a note for the Airworthiness Directive

3. Add a retroactive action box.

4. Change, in Paragraph 1.K., the revision of the Restriction and/or Special Instruction

(RSI), C-4095, to Rev. D.

5. Make miscellaneous minor changes, as necessary, with no change of context.
Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 1 of 1

ALERT SERVICE BULLETIN SUMMARY

This Service Bulletin is available at:

www.cic.bombardier.com

MODEL CL-600-1A11

ATA 57-40

WINGS

SPECIAL CHECK/MODIFICATION – ATTACHMENT FITTINGS –

INBOARD FLAP HINGE BOX FORWARD ATTACHMENT FITTINGS FASTENERS

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

see corresponding paragraph contained within this bulletin.

ALERT

SPECIFIED TIME COMPLIANCE

COMPLIANCE TIME

PART A is recommended within 100 landings

from this Alert Service Bulletin release date

(Basic Issue) or within 50 landings from this

Alert Service Bulletin release date (Revision 02)

and must be repeated every 10 landings until

modification in PART B is complied with or

PART C is completed.

PART B is recommended no later than

24 months from this Alert Service Bulletin

release date (Revision 02).

EFFECTIVITY: A/C Serial No. 1004 to 1085

MANPOWER: 1 man-hour for the special check in PART A

58 man-hours for the modification in 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

NOTES 1. Defueling and venting of the fuel tanks must be done to do PART B of this

Service Bulletin.

2. To minimize aircraft downtime and cost, it is recommended to do Service Bulletin

600-0762, in conjunction with PART B of this Service Bulletin.

3. This Service Bulletin is mandated by Airworthiness Directive (AD) CF-2013-39R1.

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 A600-0763

Revision 02: Dec 09/2014 Page 1 of 19

ALERT SERVICE BULLETIN

This Alert Service Bulletin is available at:

www.cic.bombardier.com

MODEL CL-600-1A11

ATA 57-40

WINGS

SPECIAL CHECK/MODIFICATION – ATTACHMENT FITTINGS –

INBOARD FLAP HINGE BOX FORWARD ATTACHMENT FITTINGS FASTENERS

RETROACTIVE ACTION

1. RETROACTIVE ACTION APPLICABLE TO AIRCRAFT THAT HAVE

INCORPORATED THE BASIC ISSUE OR REVISION 01 OF PART A OF THIS

SERVICE BULLETIN:

A. FOR THE AIRCRAFT WITH THE INCORRECTLY ORIENTED FORWARD

FASTENERS HEADS (FIGURE 2 in PART A), PART A MUST BE DONE

WITHIN 10 LANDINGS FROM THIS ALERT SERVICE BULLETIN RELEASE

DATE (REVISION 02) AND MUST BE REPEATED EVERY 10 LANDINGS

UNTIL PART B IS COMPLIED WITH.

– NO FURTHER ACTION IS REQUIRED, ONCE PART B IS

INCORPORATED.

OR

B. FOR THE AIRCRAFT WITH THE CORRECTLY ORIENTED FORWARD

FASTENERS HEADS (FIGURE 1 in PART A).

– NO FURTHER ACTION IS REQUIRED, ONCE PART C IS COMPLETED.

2. NO RETROACTIVE ACTION IS REQUIRED FOR AIRCRAFT THAT HAVE

INCORPORATED PART B OR PART C OF THE BASIC ISSUE OR REVISION 01

OF THIS SERVICE BULLETIN.
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Revision 02: Dec 09/2014 Page 2 of 19

2. PLANNING INFORMATION

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

Bulletin 600-0762, in conjunction with PART B of this Service Bulletin.

2. This Service Bulletin is mandated by Airworthiness Directive (AD)

CF-2013-39R1.

A. Effectivity

CL-600-1A11 aircraft, Serial No. 1004 to 1085.

NOTE: The instructions given in this Alert 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 Alert 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

On a Challenger 605 zonal inspection, one of the two forward fasteners attaching

the inboard flap hinge box forward hinge fitting at Wing Station (WS) 76.50 was

found with its head missing.

The investigation shows that when installed with their head outside, those

fasteners will experience premature failure caused by higher pre-load due to

clamping and alignment.

This Alert Service Bulletin provides instruction to inspect and repair the forward

fasteners attaching the forward fittings at WS 76.50 and WS 127.25 at both

wings.

C. Description

This Alert Service Bulletin gives instructions in:

PART A, to:

– Do the inspection of the forward inboard flap fasteners on the hinge box wing

forward fitting.

PART B, to:

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

– Remove the applicable upper and lower access panels,

– Do the inboard flap fasteners modifications as per APPENDIX 1 on the hinge

box wing forward fittings,

– Install the removed wing upper and lower access panels, and

– Re-install the forward and aft inboard flap hinge-fairings.

PART C, to:

– Confirm that the forward fasteners heads are correctly oriented.

Testing, to:

– Do the necessary testing to ensure that the inboard flaps operate correctly.
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 3 of 19

D. Compliance

PART A is recommended within 100 landings from this Alert Service Bulletin

release date (Basic Issue) or within 50 landings from this Alert Service Bulletin

release date (Revision 02) and must be repeated every 10 landings until

modification in PART B is complied with or until PART C is completed to confirm

that the forward fasteners heads are correctly oriented.

PART B is recommended no later than 24 months from this Alert Service Bulletin

release date (Revision 02).

NOTES: 1. At any time, if any of the forward fasteners heads are found missing,

PART B must be implemented before further flight.

2. If the modification in PART B is incorporated or if the forward

fasteners heads are correctly oriented as per PART C, no further

action is required.

3. This Service Bulletin is mandated by Airworthiness Directive (AD)

CF-2013-39R1.

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 Alert 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 Alert 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 Alert

Service Bulletin.

1 man-hour is necessary to do the special check in PART A.

58 man-hours are necessary to do this modification in PART B.

Bombardier does not pay for the special check in PART A and the Fuel Disposal

fee at any time.
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 4 of 19

The labor required to do the modification in PART B is at no cost if:

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

or Authorized Service Facilities (ASF), and

(ii) this Service Bulletin is scheduled in less than 48 months from

its release date (Basic Issue).

G. Material - Cost and Availability

No kits or parts are necessary to do the special check in PART A or to confirm

that the forward fasteners heads are correctly oriented as per PART C.

When applicable, submit an SRPSA to Customer Support Engineering (CSE)

to obtain kit and parts details necessary to do PART B of this modification.

If applicable, the kit for PART B is available at no cost if a no-charge purchase

order is sent to Bombardier Aerospace in less than 48 months from this Service

Bulletin release date (Basic Issue).

Bombardier does not pay for the bushings that may be necessary, to do PART B,

of this Service Bulletin.

Bombardier does not pay for the Fuel Disposal fee at any time.

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

H. Tooling

The tools that follow, or equivalent, are necessary to do PART A of this Alert

Service Bulletin:

GSE REFERENCE NO. PART NO. DESCRIPTION

24-00-24 S4933959−501 Tag, Circuit Breaker

Commercially Available - Borescope

The tools that follow, or equivalent, are necessary to do PART B of this Alert

Service Bulletin:

GSE REFERENCE NO. PART NO. DESCRIPTION

24-00-24 S4933959−501 Tag, Circuit Breaker

28-00-06 8320000 Fuel Fumes Detector

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)
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 5 of 19

The tools listed below or commercially available equivalent tools are required for

the removal of the bushings.

REFERENCE NO. PART NO. DESCRIPTION

Commercially Available - C-Clamp

See Note 3 - 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. 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-4095, Rev. D.

– CL-600 Maintenance Manual, PSP 602, Chapters 6, 12, 24, 28, and 57.

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

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

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

and 28.

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

– Bombardier Aerospace, Repair Engineering Order (REO), 600-57-26-001.

– Bombardier Aerospace, Appendix 1 (attached).

– Bombardier Aerospace, Appendix 2 (attached).

L. Other Publications Affected

None

M. Equivalent Service Bulletins

– For the Challenger 605 aircraft, use SB A605-57-004.

– For the Challenger 604 aircraft, use SB A604-57-006.

– For the Challenger 601 aircraft, use SB A601-0627.
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 6 of 19

3. 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.

A. Aircraft Setup

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

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 the external ac power. Refer to Chapter 12-00-00, SERVICING –

General.

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

extended.

(5) Remove the external ac power. Refer to 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

CBP-B 188 (187, 189) BATT CHGR 222
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 7 of 19

B. PART A: Special Check − Inboard Flap Fasteners on the Hinge Box Wing

Forward Fitting

(1) Do a detailed borescope inspection of the inboard flap fasteners of the hinge

box wing forward fitting of both wings. Refer to the steps that follow, Figure 1

and Figure 2.

NOTE: If the fairing is already removed, a visual inspection can be carried

out instead of a borescope inspection.

(a) Examine the orientation of the forward attachments of the inboard flap

hinge boxes at WS 76.50 and WS 127.25. Refer to Figure 1 and Figure 2.

Figure 1

(i) If all of the forward fasteners heads of the inboard flap hinge boxes at

WS 76.50 and WS 127.25 of both wings are correctly oriented as per

Figure 1, proceed to PART C in Paragraph 2.D.

Figure 2
MODEL CL-600-1A11

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Revision 02: Dec 09/2014 Page 8 of 19

(ii) If any of the forward fastener heads are found missing as per Figure 2,

|proceed to PART B in Paragraph 2.C.

(iii) If any of the forward fasteners heads are incorrectly oriented as per

Figure 2 but no fasteners heads are found missing, then the

borescope inspection of the forward inboard flap fasteners, hinge

box wing forward fitting, must be repeated every 100 landings, until

the modification, provided in PART B of this SB is complied with. As

applicable, Proceed to PART B or to the Close-out in Paragraph 2.F.

C. PART B: Modification − Incorrectly Oriented Inboard Flap Fasteners on the

Hinge Box Wing Forward Fitting

(1) Remove fillet seal from perimeter around the forward and aft inboard flap

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

respectively. Refer to SRM, Chapter 51-57-00, SEALING - Description.

(2) Remove the forward and aft inboard flap hinge-fairings that follow, to gain

access to inboard flap hinge boxes. Refer to Chapter 6-53-00, REMOVABLE

FAIRINGS - General:

ACCESS DESIGNATION

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

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

572-DB (672-DB) Fairing, Rear Inboard Flap Hinge

572-GB (672-GB) Fairing, Rear Inboard Flap Hinge

(3) Obey all the fuel system safety precautions. Refer to Chapter 28-10-11,

FUEL TANKS - Maintenance Practices.

(4) Defuel the aircraft. Refer to Chapter 12-10-28, FUEL SYSTEM -

Replenishing.

(5) Drain, purge and prepare the main left and right fuel tanks for access. Refer

to Chapter 28-10-11, FUEL TANKS – Maintenance Practices.

(6) Remove the access panels that follow. Refer to Chapter 6-51-00, ACCESS

PANELS AND DOORS:

ACCESS DESIGNATION

571BB (671BB) Wing Lower Surface – Access Panel

571AB (671AB) Wing Lower Surface – Access Panel

540FB (640FB) Fuel Tank – Access Panels

540GB (640GB) Fuel Tank – Access Panels

NOTE: You can use the Fuel Fumes Detector, Part No. 8320000, as an

alternative to the explosiometer.
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 9 of 19

(7) Remove and isolate the electrical power from the aircraft. Refer to Chapter

24-00-00, ELECTRICAL POWER - Maintenance Practices.

(8) Put a DO NOT CONNECT − FUEL TANK MAINTENANCE placard on the

battery.

(9) Put a DO NOT CONNECT − FUEL TANK MAINTENANCE placard on the ac

and the dc ground power receptacles.

(10) Remove and replace each of the HI-LOK/Hi-LITE forward fasteners on the left

and right wing at WS 76.50 and WS 127.25 as per Appendix 1, PART A, and

Figure 3.

(11) If it is not possible to follow all instructions from Appendix 1, Part A or Part B

(REO 600-57-26-001) 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

Figure 3

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

attachment fitting and aft attachment fitting. Refer to the steps that follow:
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 10 of 19

CAUTION: ONLY ONE FLAP HINGE BOX IS TO BE DISCONNECTED AT A

TIME. THE FLAP HINGE BOX MUST BE SUPPORTED DURING

THE MODIFICATION SO AS NOT TO DAMAGE THE FLAPS AND

ATTACHED COMPONENTS.

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 4.

Figure 4

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

WS 127.25 as follows: Refer to Figure 5 and Figure 6.

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

jumpers to the flap hinge box (1).

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

(aa) If necessary, disconnect the electrical connector wire from

any attached location on the structure, to allow downward

movement of the flap hinge box.

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

Manual (PSP 602), 20-80-00 SAFETYING DEVICES, Cotter

Pins.

(cc) Remove and keep the nut (5), washer (6) and bolt (7) and

disconnect the control rod (2) from the lever (8) of the flap

position transmitter.

(dd) If necessary, put protective covers on the open ends of the

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

position transmitter.
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Revision 02: Dec 09/2014 Page 11 of 19

(iii) For the flap hinge box (1) located WS 76.50 and WS 127.25, remove

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

bushings (13), to disconnect the flap hinge box (1) from the forward

attachment fitting. Refer to Figure 5 and Figure 6.

CAUTION: TO REMOVE AND INSTALL THE HINGE

BUSHINGS USE A C-CLAMP METHOD WITH

THE SUPPORT BLOCK. USE LIGHT ANTISEIZE 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 5

(aa) Inspect the hinge bushings, Part No. 600-10300-611 (13) for

damage and/or corrosion, if applicable, replace any damaged

or corroded hinge bushings.

(iv) For the flap hinge box (1) located WS 76.50 and WS 127.25, remove

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

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

attachment fitting. Refer to Figure 5 and Figure 6.

(aa) Inspect the hinge bushings, Part No. 600-10300-609 (18) for

damage and/or corrosion, if applicable, replace any damaged

or corroded hinge bushings.

Install the support block,

manufactured as per

Appendix 2 or an

equivalent commercially

available tool between

the fittings.

Shim all gaps as

required.
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(b) Carefully pull the flap hinge box (1) downward to allow access to the

forward attachment fitting.

Figure 6
MODEL CL-600-1A11

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Revision 02: Dec 09/2014 Page 13 of 19

(13) Remove and replace each of the HI-LOK/Hi-LITE AFT fasteners on the left

and right wing at WS 76.50 and WS 127.25 as per Appendix 1, PART B,

and Figure 7.

(14) If it is not possible to follow all instructions from Appendix 1, Part A or Part B

(REO 600-57-26-001) 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

Figure 7

(15) Attach the inboard flap hinge box (1) at locations WS 76.50 and WS 127.25.

Refer to the steps that follow, Figure 5 and Figure 6:

(a) Apply one layer of Mastinox 6856K to the hinge bushings (13) and hinge

bushings (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.
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(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.

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

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

(v) Remove the protective covers from the open ends of the electrical

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

transmitter.

(vi) 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) 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) Do the electrical bonding test for the applicable flap hinge box (1). Refer

to Maintenance Manual, PSP 602, Chapter 51-80-00, ELECTRICAL

BONDING.
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(16) Install the access panels that follow:

ACCESS DESIGNATION

571BB (671BB) Wing Lower Surface – Access Panel

571AB (671AB) Wing Lower Surface – Access Panel

540FB (640FB) Fuel Tank – Access Panels

540GB (640GB) Fuel Tank – Access Panels

(17) Remove the DO NOT CONNECT − FUEL TANK MAINTENANCE placard

from the battery.

(18) Remove the DO NOT CONNECT − FUEL TANK MAINTENANCE placard

from the ac and the dc ground power receptacles.

(19) Restore the electrical power on the aircraft. Refer to Chapter 24-00-00,

ELECTRICAL POWER - Maintenance Practices.

(20) Proceed to the Testing in Paragraph 2.E.

D. PART C: Correctly Oriented Inboard Flap Fasteners on the Hinge Box Wing

Forward Fitting

If the forward fasteners heads are correctly oriented as per Figure 1, you already

meet the intention of this Service Bulletin and no further action is required,

proceed to the Close-out in Paragraph 2.F.

E. Testing

(1) Remove the tags and close 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

CBP-B 188 (187, 189) BATT CHGR 222

(2) Connect the external ac power. Refer to Chapter 12-00-00, SERVICING –

General.

(3) Do an operational test of the inboard flaps to make sure the flap hinge box

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

Chapter 27-50-00, WING FLAP SYSTEM – Maintenance Practices.
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(4) Remove the external ac power. Refer to Chapter 12-00-00, SERVICING.

(5) 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

CBP-B 188 (187, 189) BATT CHGR 222

(6) Install the forward and aft inboard flap hinge-fairings that follow. Refer to

Chapter 6-53-00, REMOVABLE FAIRINGS - General:

ACCESS DESIGNATION

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

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

572-DB (672-DB) Fairing, Rear Inboard Flap Hinge

572-GB (672-GB) Fairing, Rear Inboard Flap Hinge

(7) Install fillet seal around perimeter of forward and aft inboard flap hingefairings making contact with the wing surface and the inboard flap

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

Aerodynamic Sealing.

(8) Connect the external ac power. Refer to Chapter 12-00-00, SERVICING –

General.

(9) Carry out a flap operational test and check corresponding flap position

indications in the flight compartment. Refer to Chapter 27-50-00, WING

FLAP SYSTEM – Maintenance Practices.

F. Close-out

(1) If not already done, remove the tags and close 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

CBP-B 188 (187, 189) BATT CHGR 222

(2) Remove all tools, equipment and unwanted materials from the aircraft.
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 17 of 19

G. Recording

You can do each PART of this Alert Service Bulletin independently. When any

PART of this Alert 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 Alert Service Bulletin must be repeated every 100 landings and can only be

closed when:

- The modification in PART B is completed.

or

- PART C is completed to confirm that the forward fasteners heads are correctly

oriented.

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 Alert

Service Bulletin survey:

http://csefeedback.aero.bombardier.com

4. MATERIAL INFORMATION

A. Kit

When applicable, submit an SRPSA to Customer Support Engineering (CSE) to

obtain kit and parts details necessary to do PART B of this modification.

B. Parts

When applicable, submit an SRPSA to Customer Support Engineering (CSE) to

obtain kit and parts details necessary to do PART B of this modification.
MODEL CL-600-1A11

Basic Issue: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 18 of 19

C. Material

The materials that follow, or equivalent, are necessary to do PART B of this

Alert 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)

Corrosion

inhibitor

Compound

Mastinox 6856K -

As

Necessary Code: A

Integral Fuel

Tank Sealant

CT: (9 hours) B1/2

(20 hours) B2

P/S 870B MIL-PRF-81733

Type II

As

Necessary Code: A

Sealant

CT: (12 hours) B1/2

(24 hours) B2

PR1776M B1/2

or

PR1776M B2

-

As

Necessary Code: A

Durathane High

Gloss Enamel

CT: (12 hours)

7600 line BAMS 565-002 As

Necessary Code: B

Epoxy Primer

Grey

CT: (2 hours)

4500-P-40B

(16473, FS 595B) BAMS 565-001 AsNecessary Code: B

Conversion

Coating Alodine 1201 MIL-DTL81706B Type II

As

Necessary Code: C

Epoxy Resin

CT: (24 hours)

Hysol

EA9309.3NA AS9354002 AsNecessary Code: C

Fuel Tank

Coatings

(Primer Yellow)

CT: (24 hours)

20P1-10 BAMS 565-010 As

Necessary Code: D

Anti-Seize

Lubricant LPS-1 -

As

Necessary Code: E

Brush, Natural or

Synthetic Bristle - -

As

Necessary Code: E

Scraper,

Non-Metallic - -

As

Necessary Code: E

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 Alert 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: Sep 26/2013 A600-0763

Revision 02: Dec 09/2014 Page 19 of 19

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

Code: B

Tempo Aerospace Inc

205 Fenmar Drive,

Toronto, Ontario, Canada

M9L 2X4

Tel.: 1-416-746-2233

Fax.: 1-416-746-2235

E-mail: sales@tempo-aerospace.com

Web Site: www.tempo-aerospace.com

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

AkzoNobel Aerospace Coatings.

1 East Water Street

Waukegan, IL 60085

USA

Tel.: 1-847-623-4200

Fax.: 1-847-625-3200

E-mail: customer.service@akzonobel.com

Web Site: www.akzonobel.com

Code: E

Commercially Available

D. Publications

No publications required.
ALERT SERVICE BULLETIN EVALUATION FORM

(Your ideas will help us provide better bulletins)

SERVICE BULLETIN: A600-0763 ISSUE: Rev. 02 DATED: Dec 09/2014

TITLE: Special Check/Modification – Attachment Fittings – Inboard Flap Hinge Box Forward

Attachment Fittings Fasteners

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 –

“A600-0763”

B

O

M

B

A

R

DIE

R

S

U

B

MIS

SIO

N

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

Alert Service

Bulletin Number

Rev. * Parts

Completed

YES NO N/A Remarks/Reason

A600-0763 02 PART A

“ “ PART B

“ “ PART C

Actual hours to accomplish Service Bulletin:

* NOTES: 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.

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

Signature not required if sent by E-Mail (dd/mm/yy)
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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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