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700-27-076 Page 1 of 1
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET MODEL BD-700-1A10 (BD-700) Discard the Revision 02 of this Service Bulletin dated Jun 17/2014 and the Information Sheet dated Jul 31/2014 and replace in its entirety with this Revision 04
Service Bulletin No. 700-27-076 Date of Basic Issue Ma r 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 Se p 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. Remove, in Paragraph 1.A., Effectiv ity, SNIEO S09 and SRPSA No for aircraft, Serial No. 9250.
4. Revise, in Paragraph 1.F., Manpower, the man-hours statements for PART A and PART B, for clarification.
5. Add, in Paragraph 1.F., Manpower, a NO TE to clarify the number of man-hours needed to perform re-identification.
6. Revise, in Paragraph 1.K., TCCA Airworthine ss directive, from (Pending) to CF-2014-23.
7. Change, in Paragraph 2.C (1) step (c), nomi nal diameter value, from 0.165 in to
0.165 in (4.2 mm).
8. Make miscellaneous minor changes, as necessary, with no change of context.
Basic Issue: Mar 05/2012 700-27-076 Revision 04: Sep 04/2014 Page 1 of 1
SERVICE BULLETIN SUMMARY This Service Bulletin is available at:
www.cic.bombardier.com MODEL BD-700-1A10 (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. 9002 to 9312, 9314 to 9380 and 9384 to 9429 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 700-27-076 Revision 04: Sep 04/2014 Page 1 of 20
SERVICE BULLETIN This Service Bulletin is available at:
www.cic.bombardier.com MODEL BD-700-1A10 (BD-700) ATA 27-11
FLIGHT CONTROLS ICA – MODIFICATION – AILERON CONTROL SYSTEM – INSTALLATION OF COVER FOR NO.1 AILERON PULLEY
RETROACTIVE ACTION NO ACTION NECESSARY IF REV. 01 OR REV. 02 OF THIS SERVICE BULLETIN WAS DONE.
THE ACTIONS THAT FOLLOW ARE RECOMMENDED ONLY FOR AIRCRAFT ON WHICH ONLY THE BASIC ISSUE OF THIS SERVICE BULLETIN WAS DONE:
(1) Do PART A of this Service Bulletin.
(2) For aircraft which are covered by SRPSA, as mentioned in Table 2 of Paragraph 1.A., operators only have to do 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 A700-57-045.
2. This Service Bulletin includes Inst ructions 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 700-27-076 was issued in error.
MODEL BD-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 Revision 04: Sep 04/2014 Page 2 of 20 A. Effectivity BD-700-1A10 aircraft, Serial No. 9002 to 9312, 9314 to 9380 and 9384 to 9429.
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/SNIEO NO. SRPSA NO.
9013 KGD419-9000 Rev E 43066 9016 KGD419-9000 Rev E 41415 9077 KGD419-9000 Rev E 00180 9121 KGD419-9000 Rev E 41249 9136 KGD419-9000 Rev E 41128 9290 KGD419-9000 Rev E 41515 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 GS297-0130 SNIEO NO. SRPSA NO.
9032 S07 00163 9051 S06 44417 9137 S08 00164 9181 S03 43825 9208 S10 42142 9239 S04 43965 9250 S09 41972 9304 S02 43760 Table 2 NOTES: 1. Operators which are covered by the SRPSA as listed in the Table 2, must only do the re-identification of the over wing panels GS297-0024-X. Refer to PART A, Paragraph 2.B. (2)(g).
MODEL BD-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 Revision 04: Sep 04/2014 Page 3 of 20
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.
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 decent 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 pu lley covers, and trim the edge of the over wing panel to get the required clearance, and – Do the operational test of aileron cont rol 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 cont rol system to make sure that the system operates correctly.
MODEL BD-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 Revision 04: Sep 04/2014 Page 4 of 20 D. Compliance Recommended within 24 months from this Service Bulletin release date (Basic Issue).
NOTE: This Service Bulletin contains Inst ructions 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.
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 700-00-002.
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-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 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 Dr awing KGD419-9000, Rev. E.
– Global Express BD-700-1A10 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 27and 53.
– Global Express BD-700-1A10 Aircraft I llustrated Parts Catalog (AIPC), Chapters 27 and 53.
– Global Express XRS BD-700-1A10 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 27 and 53.
– Global Express XRS BD-700-1A10 Aircraft Illustrated Parts Catalog (AIPC), Chapter 27.
– Global Express BD-700-1A10 Structural Repair Manual (SRM), Chapter 51.
– Global Express XRS BD-700-1A10 Structur al Repair Manual (SRM), Chapter 51.
– Global Express BD-700- Standard Pr actices Manual (SPM), Chapter 53.
– Global Express XRS BD-700 Standard Pr actices Manual (SPM), Chapter 53.
– TCCA Airworthiness Directive CF-2014-23.
MODEL BD-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 Revision 04: Sep 04/2014 Page 6 of 20 L. Other Publications Affected None.
M. Equivalent Service Bulletins – For the Global 6000 BD-700-1A10 aircraft, use SB 700-27-6004.
– For the Global 5000 BD-700-1A11 Featuri ng Global Vision Flight Deck aircraft, use SB 700-27-5004.
– For the Global 5000 BD-700-1A11 aircraft, use SB 700-1A11-27-034.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedur es that follow are from the Global Express or Global Express XRS BD-700-1A10 Aircraft Maintenance Manual (AMM) unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the Global Express or Global Express XRS BD-700-1A10 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 pr ecautions. 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 follo w 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 t he aircraft. Refer to TASK 24-00-00-861-802.
(7) Install the applicable warning placar ds 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 panel s, Items 130A and 135A (GX) or 135 and 140 (XRS). Refer to AIPC 53-30-01 and to TASK 53-30-01-000-801.
MODEL BD-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 Revision 04: Sep 04/2014 Page 7 of 20 B. PART A – Inspection and Rework
(1) For operators which incorporated the Ba sic 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 s pecified 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 bet ween 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 wi ng 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 ½ 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 t he over wing panel as KGD419-9000-6.
(h) Continue with Paragraph 2.D. (Testing).
MODEL BD-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 Revision 04: Sep 04/2014 Page 8 of 20 C. PART B – Modification
(1) For operators which have not incorpor ated 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 lock wire 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 ri vets, item 4. Refer to SRM Chapter 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 t he 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 covers as follows (refer to drawing KGD419-9000):
(a) Install the bottom pulley cover, it ems 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 ½ 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-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 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 ½ 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 plac ards 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 s ealant in the grooves of pulleys or onto the aileron cables.
E. Close-out
(1) Install the shields, Pa rt No. GM597-4810-25/-43/-55 and GM597-4810-26/-44/-56.
(2) Install the MLG wheel bin aft panel s, Items 130A and 135A (GX) or 135 and 140 (XRS). Refer to AIPC 53-30-01 and to TASK 53-30-01-400-801.
(3) Connect the electrical power to the airc raft. Refer to TASK 24-00-00-861-801.
(4) In the flight compartment, on the EM S 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 unw anted materials from the aircraft.
MODEL BD-700-1A10 (BD-700) Basic Issue: Mar 05/2012 700-27-076 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.
B. Parts No parts required.