700-1A11-27-034

Page 1 of 1 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

MODEL BD-700-1A11 (BD-700) 

Discard the Revision 02 of this Service Bulletin dated Jun 27/2014 and the 

Information Sheet dated Jul 31/2014 and replace in its entirety with this Revision 04 

Service Bulletin No. 700-1A11-27-034

Date of Basic Issue Mar 05/2012

Revision No. 01 Dated Jul 16/2012

Revision No. 02 Dated Jun 17/2014

Revision No. 03 Dated Jul 28/2014

 

Revision No. 04 Dated Sep 04/2014

For action applicable to aircraft on which the Basic Issue of this Service Bulletin 

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

This revision is issued to: 

1. Add, in the Retroactive Action Box, a statement to clarify no action is needed if 

Rev 01 or Rev 02 of Service Bulletin was done. 

2. Add, in the Planning Information, Note 3. 

3. Revise, in Paragraph 1.F., Manpower, the man-hours statements for PART A and 

PART B, for clarification. 

4. Add, in Paragraph 1.F., Manpower, a NOTE to clarify the number of man-hours 

needed to perform re-identification. 

5. Revise, in Paragraph 1.K., TCCA Airworthiness directive, from (Pending) to 

CF-2014-23. 

6. Change, in Paragraph 2.C (1) step (c), nominal diameter value, from 0.165 in to 

0.165 in (4.2 mm). 

7. Make miscellaneous minor changes, as necessary, with no change of context. 
Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 1 of 1 

SERVICE BULLETIN SUMMARY 

This Service Bulletin is available at: 

www.cic.bombardier.com

MODEL BD-700-1A11 (BD-700)

ATA 27-11 

FLIGHT CONTROLS 

ICA – MODIFICATION – AILERON CONTROL SYSTEM – 

INSTALLATION OF COVER FOR NO. 1 AILERON PULLEY 

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 

Within 24 months of SB release 

date (Basic Issue)

EFFECTIVITY: A/C Serial No. 9127 to 9383, 9389 to 9400, 9404 to 9431 and 9998 

MANPOWER: Part A: 5 man-hours 

Part B: 9 man-hours 

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 

NOTE: This Service Bulletin includes Instructions for Continued Airworthiness (ICA). 

Refer to Paragraph 1 (Planning Information) and Paragraph 1.D. (Compliance) 

for details.

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. 

© 2012-2014 Bombardier Inc. All rights reserved 

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

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 1 of 20 

SERVICE BULLETIN 

This Service Bulletin is available at: 

www.cic.bombardier.com

MODEL BD-700-1A11 (BD-700) 

ATA 27-11 

FLIGHT CONTROLS 

ICA – MODIFICATION – AILERON CONTROL SYSTEM – 

INSTALLATION OF COVER FOR NO.1 AILERON PULLEY 

RETROACTIVE ACTION 

NO ACTION IS NECESSARY IF REV. 01 OR REV. 02 OF THIS SERVICE BULLETIN 

WAS DONE. 

THE ACTIONS THAT FOLLOW ARE RECOMMENDED FOR AIRCRAFT ON WHICH 

THE BASIC ISSUE OF THIS SERVICE BULLETIN WAS DONE: 

(1) Do PART A of this Service Bulletin. 

(2) For aircraft which were covered by SRPSA, as mentioned in Table 2 of Paragraph 

1.A., operators have to do only the re-identification of the over wing panels 

GS297-0024-X, at their earliest convenience. Refer to PART A, 

Paragraph 2.B. (2)(g). 

1. PLANNING INFORMATION 

NOTES: 1. Aircraft that incorporate this Service Bulletin do not have to do the 

SB A700-1A11-57-011. 

 2. This Service Bulletin includes Instructions for Continued Airworthiness 

(ICA). It is recommended that this Service Bulletin be accomplished by 

the specified time compliance stated in Paragraph 1.D. 

 3. Revision 03 of Service Bulletin 700-1A11-27-034 was issued in error. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 2 of 20 

A. Effectivity 

BD-700-1A11 aircraft, Serial No. 9127 to 9383, 9389 to 9400, 9404 to 9431 

and 9998. 

The intent of this Service Bulletin was met on the aircraft that follow with the Service 

Requests for Product Support Action (SRPSA) listed in the table that follows: 

AIRCRAFT SERIAL NO. DRAWING SRPSA NO. 

9305 KGD419-9000 Rev E 12580 

9224 KGD419-9000 Rev E 12560 

9431 KGD419-9000 Rev E 43066 

Table 1 

The PART A of this Service Bulletin was met (except for the re-identification, 

Paragraph 2.B. (2)(g)) on the aircraft that follow with the incorporation of the 

Service Non-Incorporated Engineering Orders (SNIEO) or Service Requests for 

Product Support Action (SRPSA) listed in the table that follows: 

AIRCRAFT SERIAL NO. DRAWING 

SNIEO NO. 

SRPSA NO. 

9424 SNIEO – S05 44397 

9168 SNIEO – S01 43335 

Table 2 

NOTES: 1. Operators which were covered by SRPSAs as listed in Table 2 

above, must do only the re-identification of the over wing panels 

GS297-0024-X. Refer to PART B, Paragraph 2.B. (2)(g). 

 2. 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. 

For all other aircraft, do Part B of this Service Bulletin. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 3 of 20 

B. Reason 

An operator reported that soon after reaching 37,000 feet altitude, following 

departure under heavy rain, an "AP TRIM IS RWD" CAS message was posted. 

The pilot leveled at 41,000 feet altitude with autopilot disengaged and using 

normal force, the pilot could not turn the control wheel. Following the AFM 

procedures for Aileron System Jammed, the flight crew was able to break the 

control wheel free. During the subsequent descent it was noted that the control 

wheel became progressively easier to turn and the flight crew regained normal 

control of the ailerons as descent continued. The aircraft landed uneventfully. 

Investigation revealed that this was caused by water collecting on top of the 

aileron pulley array in the MLG wheel well and subsequently freezing. 

This Service Bulletin installs a cover around the #1 aileron pulley to prevent 

water from collecting and freezing on top of the pulley. 

C. Description 

This Service Bulletin gives instructions in 

PART A (for aircraft which the Basic Issue of this Service Bulletin was 

incorporated) to: 

– Get access to the aileron pulleys at W.STA 56.00, 

– Make sure that you get the minimum clearance between the top cover pulley 

and the radius of over wing panel, 

– If required, remove the aileron top pulley covers, and trim the edge of the over 

wing panel to get the required clearance, and 

– Do the operational test of aileron control system to make sure that the system 

operates correctly. 

PART B (for aircraft which the Basic Issue of this Service Bulletin was not 

incorporated) to: 

– Get access to the aileron pulleys at W.STA 56.00, 

– Do the modification to rib GM131-1101, 

– Install the aileron pulley covers, and 

– Do the operational test of aileron control system to make sure that the system 

operates correctly. 

D. Compliance 

Recommended within 24 months from this Service Bulletin release date 

(Basic Issue). 

NOTE: This Service Bulletin contains Instructions for Continued Airworthiness 

(ICA). Failure to comply with the SB within the specified time compliance 

stated in this paragraph could result in the issuance of an AD by 

regulatory authorities. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 4 of 20 

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 the 

JAA and 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 700-1A11-00-002. 

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. 

1 man-hour is necessary to do the re-identification for aircraft listed in Table 2 

(Retroactive Action). 

5 man-hours are necessary to do PART A of this Service Bulletin for aircraft on 

which the Basic Issue or Table 1 of this Service Bulletin was incorporated. 

NOTE: The man-hour necessary to do the retroactive action listed above is at no 

cost. 

9 man-hours are necessary to do PART B of this Service Bulletin for aircraft on 

which the Basic Issue of this Service Bulletin was not incorporated. 

The labor required to do PART B of this Service Bulletin 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 24 months from its 

release date (Basic Issue). 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 5 of 20 

G. Material - Cost and Availability 

Kit 700K27-076 is necessary to do this modification. 

KIT NO. PRICE 

700K27-076 Please contact Bombardier 

Aerospace Parts Services, in 

Montreal, for delivery lead times and 

confirmation of prices. 

Sufficient kits will be kept for the estimated amount of orders. 

This kit is available at no cost if a no-charge purchase order is sent to 

Bombardier Aerospace in less than 24 months from this Service Bulletin 

release date (Basic Issue). 

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

H. Tooling 

No equipment or special tools are necessary. 

I. Weight and Balance 

WEIGHT MOMENT 

+1.04 pounds (0.472 kg) +787.5 pound-inches (9.07 kgm) 

J. Electrical Load Data 

No change. 

K. References 

– Bombardier Aerospace, Modification Summary, R700T400358, Rev. F1. 

– Bombardier Aerospace, Kit Drawing KGD419-9000, Rev. E. 

– Global 5000 BD-700-1A11 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 

27 and 53. 

– Global 5000 BD-700-1A11 Aircraft Illustrated Parts Catalog (AIPC), Chapters 

27 and 53. 

– Global 5000 BD-700-1A11 Structural Repair Manual (SRM), Chapter 51. 

– Global 5000 BD-700 Standard Practices Manual (SPM), Chapter 53. 

– TCCA Airworthiness Directive CF-2014-23. 

L. Other Publications Affected 

None. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 6 of 20 

M. Equivalent Service Bulletins 

– For the Global Express and Global Express XRS BD-700-1A10 aircraft, use 

SB 700-27-076. 

– For the Global 6000 BD-700-1A10 aircraft, use SB 700-27-6004. 

– For the Global 5000 BD-700-1A11 Featuring Global Vision Flight Deck aircraft, 

use SB 700-27-5004. 

2. ACCOMPLISHMENT INSTRUCTIONS 

NOTES: 1. All TASKs given in the procedures that follow are from the Global 5000 

BD-700-1A11 Aircraft Maintenance Manual (AMM) unless otherwise 

specified. 

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

the Global 5000 BD-700-1A11 Aircraft Maintenance Manual, Chapter 6. 

A. Aircraft Setup 

(1) Obey all the electrical/electronic safety precautions. Refer to 

TASK 24-00-00-910-801. 

(2) Obey all the flight control safety precautions. Refer to TASK 27-00-00-910-801. 

(3) Connect electrical power to the aircraft. Refer to TASK 24-00-00-861-801. 

(4) Set the FLAP/SLAT control lever to the 30 degree position. 

NOTE: Make sure that the flaps extend fully. 

(5) Set the circuit breakers that follow to OUT (on aircraft pre SB 700-24-045) 

or LOCKED (on aircraft, Serial No. 9123 and subsequent or aircraft post 

SB 700-24-045) (refer to TASK 24-00-00-863-801): 

SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME 

SLAT/FLAP PWR 1 G9 AC BUS 1 

SLAT/FLAP PWR 2 E2 AC ESS BUS 

(6) Remove the electrical power from the aircraft. Refer to TASK 24-00-00-861-802. 

(7) Install the applicable warning placards on the control wheels and the aileron 

control surfaces. 

(8) Remove the shields Part No. GM597-4810-25/-43/-55 and 

GM597-4810-26/-44/-56. Refer to drawing KGD419-9000. 

(9) Remove the MLG wheel bin aft panels, items 135 and 140. Refer to 

AIPC 53-30-01 and to TASK 53-30-01-000-801. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 7 of 20 

B. PART A – Inspection and Rework 

(1) For operators which incorporated the Basic Issue of this Service Bulletin, do 

the inspection and rework if required as follows: 

NOTE: The steps that follow are applicable to the left and right hand side 

installation. 

(a) Make sure that you have the specified clearance between the over wing 

panel, Part No. GS297-0024 and bracket, Part No. GM447-2551. 

Refer to Kit Drawing KGD419-9000, view N. 

(b) If you have the required clearance between the over wing panel, Part No. 

GS297-0024-X and bracket, Part No. GM447-2551, continue with 

Paragraph 2.E. (Close-out). If you do not have the minimum clearance, 

continue with Paragraph 2.B.(2) below. 

(2) Do the rework of the over wing panel, Part No. GS297-0024-X, as follows: 

(a) Remove the top pulley cover. 

(b) Trim the over wing panel, Part No. GS297-0024-X to get the minimum 

clearance of 0.380 in (9.65 mm) between the top pulley cover and the over 

wing panel. Refer to Kit Drawing KGD419-9000, Notes 26 and 27. 

NOTE: When you trim the over wing panel take precautions not to trim 

into the honeycomb core or damage the seal which is part of the 

over wing panel assembly. 

(c) Seal the trimmed edges of the over wing panel. Refer to 

SRM Chapter 51-75-00. 

(d) Inspect and replace all sealant as required. Refer to Kit Drawing 

KGD419-9000, Notes 14, 15 and SPM 53-23-00. 

(e) Install the top pulley cover, to the bottom pulley cover with items 8 and 9 

(refer to drawing KGD419-9000, view B-B). 

NOTE: 1. Make sure that you get a minimum clearance of 0.150 in 

(3.81 mm) between the flight control cables and pulley cover. 

Refer to Kit Drawing KGD419-9000, Note 25. 

 2. Make sure that you check the running torque for each 

fastener and add 4 to 6 lbf in (0.45 to 0.68 Nm) to obtain the 

final torque. Apply the final torque to the fastener. 

(f) Replace the fillet seal between the top pulley cover and bracket 

GM447-2551, use PR1428 Class B, Type 1⁄2 sealant. 

Refer to SPM Chapter 51-23-00. 

(g) Use best shop practice and re-identify the over wing panels Part No. 

GS297-0024 as follows: 

(i) For the L/H side re-identify the over wing panel as KGD419-9000-5. 

(ii) For the R/H side re-identify the over wing panel as KGD419-9000-6. 

(h) Continue with Paragraph 2.D. (Testing). 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 8 of 20 

C. PART B – Modification 

(1) For operators which have not incorporated the Basic Issue of this Service 

Bulletin, do the modification of the rib GM131-1101 and install the associated 

hardware as follows (refer to drawing KGD419-9000): 

(a) Temporarily install the top and bottom pulley cover to the rib. Make 

sure that the covers do not interfere with pulley and cables. 

NOTE: Make sure that there is no lockwire installed to the aileron pulley 

guard pin. 

(b) Verify that the minimum clearance between cable and cover assy is 0.150 

in (3.8 mm) and the top pulley cover is located 0.180 in (4.6 mm) offset 

from bracket GM447-2551. Mark off the position of the holes to the rib. 

NOTE: Use a spacer to get 0.180 in (4.6 mm) distance between the top 

pulley cover and bracket. 

(c) Drill two nominal diameter 0.165 in. (4.2 mm) holes in the rib. Make sure 

that the holes are free from burrs. 

(d) Install the nutplate, item 5, with rivets, item 4. Refer to SRM 51-42-08. 

NOTE: The orientation of the nutplates are shown as reference only, 

each nutplate can be rotated about the axis of fastener hole to 

prevent fouling with the adjacent nutplate and with the chem-mill 

of rib GM131-1101. 

(e) Apply Alodine 1200 and primer to the reworked area. Refer to SRM 

Chapter 51-01-04. 

(2) Make sure that there is the required clearance between wing panel 

GS297-0024 and bracket GM447-2551. Trim, if necessary, and seal edges. 

Refer to drawing KGD419-9000, view ‘N’ and SRM Chapter 51-75-00. 

NOTE: When you trim the over wing panel take precautions not to trim into 

the honeycomb core or damage the seal which is part of the over 

wing panel assembly. 

(3) Install the pulley cover as follows (refer to KGD419-9000): 

(a) Install the bottom pulley cover, items 3 and 12, to the rib GM131-1101, 

with items 6 and 7. Torque the nut from 14 to 16 lbf in (1.58 to 1.81 Nm). 

(b) Apply PR1428 Class B, Type 1⁄2 sealant into the channels of the top pulley 

covers items 2 and 11. Remove any excess sealant. Refer to view J-J. 

NOTE: Do not use PS 870, Type II sealant at this step. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 9 of 20 

(c) Install the top pulley covers, items 2 and 11, to the bottom pulley covers 

with items 8 and 9 (refer to drawing KGD419-9000, view B-B). 

NOTES: 1. Make sure that you check the running torque for each 

fastener and add 4 to 6 lbf in (0.45 to 0.68 Nm) to obtain the 

final torque. Apply the final torque to the fastener. 

2. Use PR1428 Class B, Type 1⁄2 and do fillet seal between top 

pulley cover and bracket GM447-2551. 

3. Use P/S 870, Type II sealant and seal gap between visor 

panel GM134-1110 and wing skin. Refer to KGD419-9000 

section M-M. 

D. Testing 

(1) Remove the applicable warning placards from the control wheels and the 

aileron control surfaces. 

(2) Move the ailerons through their full range of travel and monitor the control 

cables and their components for smooth operation. 

NOTES: 1. Make sure that the cables are correctly installed in the aileron #1 

pulley grooves and that they do not interfere with the electrical 

cables and pulley cover. 

2. The minimum clearance between control cables and cover assy 

must be minimum 0.150 in (3.8 mm). 

3. Make sure that there is no sealant in the grooves of pulleys or 

onto the aileron cables. 

E. Close-out 

(1) Install the shields Part No. GM597-4810-25/-43/-55 and 

GM597-4810-26/-44/-56. 

(2) Install the MLG wheel bin aft panels, items 135 and 140. Refer to 

AIPC 53-30-01 and to TASK 53-30-01-400-801. 

(3) Connect the electrical power to the aircraft. Refer to TASK 24-00-00-861-801. 

(4) In the flight compartment, on the EMS CDU, set the circuit breakers that 

follow to IN (refer to TASK 24-00-00-863-802): 

SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME 

SLAT/FLAP PWR 1 G9 AC BUS 1 

SLAT/FLAP PWR 2 E2 AC ESS BUS 

(5) Set the FLAP/SLAT control lever to the 0 degree position. 

NOTE: Make sure that the flaps retract fully. 

(6) Remove the electrical power from the aircraft. Refer to TASK 24-00-00-861-802. 

(7) Remove all tools, equipment and unwanted materials from the aircraft. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 10 of 20 

F. Recording 

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

of this Service Bulletin is completed, make an entry in the aircraft log and send the 

attached Incorporation Notice to Bombardier Business Aircraft Customer Services 

(BBACS). 

In an effort to improve the quality of our technical communications, we are 

requesting your feedback. Please take a moment to fill out our easy on-line 

Service Bulletin survey: 

http://csefeedback.aero.bombardier.com

3. MATERIAL INFORMATION 

A. Kit 

Kit 700K27-076 is necessary to do this Service Bulletin and contains the parts that 

follow: 

NEW 

PART NO. 

QTY ITEM USED 

PART NO. 

INSTRUCTIONS - 

DISPOSITION 

B0205017AD3-3S 8 Rivet, Solid, CSK - - 

KGD419-9001-1 1 Top Pulley Cover 

Assy, LH 

- - 

KGD419-9001-2 1 Top Pulley Cover 

Assy, RH 

- - 

KGD419-9002-1 1 Bottom Pulley 

Cover Assy, LH 

- - 

KGD419-9002-2 1 Bottom Pulley 

Cover Assy, RH 

- - 

MS21051L08 4 Nut Plate - - 

NAS1149CN816R 4 Washer - - 

NAS1149CN832R 6 Washer - - 

NAS1801-08-6 6 Screw, Hex HD - - 

NAS623-2-3 4 Screw, Pan HD - - 

NOTES: 1. In case of discrepancy between this list and the “Service Bulletin Kit 

Parts List” contained in the respective kit, then the latter list prevails. 

2. The actual quantity for some of the hardware contained in the kit 

can be greater than the amount shown in the table as these items 

are supplied in prepackaged quantities. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 11 of 20 

B. Parts 

No parts required. 

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)

Alodine 1200S MIL-C-81706 As 

Necessary 

Code: A 

Sealant 

CT : 30hrs

PR1428 Class B, 

Type 1⁄2 

- As 

Necessary 

Code: B 

Sealant P/S 870, 

Type II 

MIL-PRF-81733 As 

necessary 

Code: B 

Primer - MIL-P-23377F 

Type I

As 

Necessary 

Code: C 

Solvent Diestone DLS 

or 

Diestone HFP 

or 

HFE-71DA

- As 

Necessary 

Code: D 

Structural 

Adhesive 

CT :8hrs 

or 

CT :24hrs 

Epocast 50A1/946

or 

Epocast 50A/9816 

- As 

Necessary 

Code: E 

Cloth, no lint - - As 

Necessary 

Code: F 

NOTES: 1. Refer to the table that follows for each supplier’s address listed by 

codes. 

2. The Curing Time (CT), if applicable, for each consumable material is 

indicated with the description of each product. 

3. At time of release of this Service Bulletin, the information on the 

supplier was valid and accurate. In the event that this information 

has changed, the operator is encouraged to use the World Wide Web 

to find a local supplier. 
MODEL BD-700-1A11 (BD-700) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 12 of 20 

SUPPLIERS ADDRESSES BY CODES 

Code: A 

Henkel Corporation 

32100 Stephenson Highway 

Madison Heights, MI 48071 

USA 

Tel: (248)-583-9300 

Code: B 

PRC-Desoto International 

5676 Timberlea Blvd. 

Mississauga, Ontario 

Canada, L4W 4M6 

Tel.: (905) 629-7999 

Code: C 

Tempo Paint and Varnish Co. 

205 Fenmar Dr. 

Weston, Ontario 

M9L 2X4 

Canada 

Tel.: (416) 746-2233 

Code: D 

MagChem Inc 

1271 Ampere 

Boucherville, Que. 

Canada, J4B 5Z5 

Tel.: (450) 655-1344 

or 

3M Product Information Center 

3M Center, 

Building 0304-01-01 

St. Paul, MN 55144-1000 

U.S.A. 

Tel.: 1-888-364-3577 

Fax: 1-800-713-6329 

Code: E 

Huntsman Corporation. 

10003 Woodloch Forest Drive 

 The Woodlands, Texas 77380 

USA 

Tel.: 1 281 719 6000 

Fax :1 281-719 6416 

Code: F 

Commercially Available 

D. Publications 

No publications required. 
MODEL BD-700-1A11 (BD-700) 

PL KGD419-9000 – Kit – #1 Aileron Pulley Cover Installation 

(Sheet 1 of 3, Rev. E) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 13 of 20 SB700-27-076-9000-E-S1-PL 
MODEL BD-700-1A11 (BD-700) 

PL KGD419-9000 – Kit – #1 Aileron Pulley Cover Installation 

(Sheet 2 of 3, Rev. E) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 14 of 20 SB700-27-076-9000-E-S2-PL 
MODEL BD-700-1A11 (BD-700) 

PL KGD419-9000 – Kit – #1 Aileron Pulley Cover Installation 

(Sheet 3 of 3, Rev. E) 

Basic Issue: Mar 05/2012 700-1A11-27-034

Revision 04: Sep 04/2014 Page 15 of 20 SB700-27-076-9000-E-S3-PL 
KGD419-9000 – Kit – #1 Aileron Pulley Cover – Installation (Sheet 1 of 2, Rev. E) 

Basic Issue: Mar 05/2012 Revision 04: Sep 04/2014 

700-1A11-27-034

Page 16 of 20
KGD419-9000 – Kit – #1 Aileron Pulley Cover Installation (Sheet 1 of 2, Rev. E, continued) 

Basic Issue: Mar 05/2012 Revision 04: Sep 04/2014 

700-1A11-27-034

Page 17 of 20
KGD419-9000 – Kit – #1 Aileron Pulley Cover Installation 

(Sheet 1 of 2, Rev. E, continued) 

Basic Issue: Mar 05/2012 Revision 04: Sep 04/2014 

700-1A11-27-034

Page 18 of 20
KGD419-9000 – Kit – #1 Aileron Pulley Cover – Installation 

(Sheet 2 of 2, Rev. E) 

Basic Issue: Mar 05/2012 Revision 04: Sep 04/2014 

700-1A11-27-034

Page 19 of 20

1 
KGD419-9000 – Kit – #1 Aileron Pulley Cover Installation (Sheet 2 of 2, Rev. E, continued) 

Basic Issue: Mar 05/2012 Revision 04: Sep 04/2014 

700-1A11-27-034

Page 20 of 20
SERVICE BULLETIN EVALUATION FORM 

(Your ideas will help us provide better bulletins) 

SERVICE BULLETIN: 700-1A11-27-034 ISSUE: Rev. 04 DATED: Sep 04/2014

 

TITLE: ICA – Modification – Aileron Control System – Installation of Cover for No.1 Aileron 

Pulley 

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 – 

“700-1A11-27-034” 

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 

700-1A11-27-034 04 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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