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Discard the Basic Issue of this Service Bulletin dated Jul 23/2020, the Information Sheets dated Aug 27/2020, Nov 12/2020 and Nov 24/2020 and replace in its entirety with this Revision 01.
Service Bulletin No. 700−27−083 Date of Basic Issue Jul 23/2020 Revision No. 01 Dated Dec 07/2020 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:
1. Revise, in Service Bulletin Summary sheet the Compliance Time as Reference to Paragraph 1.D.
2. Revise, in Paragraph 1.(C)., to delete the “if required” from the for manual inspection of the bearings statement.
3. Revise, in Paragraph 1.(D)., Compliance Time as No earlier than 57 months.
4. Add, in Paragraph 1.(F)., work done during new aircraft warranty period.
5. Add, in Paragraph 1.(G)., kit ordered during new aircraft warranty period.
6. Delete, in Paragraph 1.(H)., Tool, Skating and Drill Press.
7. Revise, in Paragraph 1.(H)., Tool, Skating Part number.
8. Delete, in Paragraph 1.(H)., a NOTE 4.
9. Add, in Paragraph 1.(K)., Airworthiness Directive details.
10.Add, in Paragraph 2.A.(13) (d) and (e)., word trailing edge.
SERVICE BULLETIN MODEL BD−700−1A10 (BD−700) 700−27−083 Page 1 of 2
REVISION TRANSMITTAL SHEET
11.Revise, in Paragraph 2.A.(20)., for a typographical error.
12.Add, in Paragraph 2.B.(1)., Bearing rejection criteria.
13.Add, in Paragraph 2.B.(4)., a NOTE.
14.Revise, in Paragraph 2.B.(5).(d).(ii)., reference to step (9).
15.Revise, in Paragraph 2.B.(5).(d).(iii)−(iv)., reference to step (6).
16.Add, in Figure 2, the section view of the bearing and torque tube.
17.Delete, in Paragraph 2.B., step 6.
18.Revise, in Figure 4, the orientation of the bolts.
19.Add, in Paragraph 2.B.(9), Steps (b) and (c).
20.Delete, in Paragraph 2.B.(10) and (11), reference of step (4)(d).
21.Add, in Paragraph 2.B.(10), a NOTE.
22.Revise, in Paragraph 2.B.(11).(c)., application of sealant.
23.Add, in Paragraph 2.B.(11)., a step (f).
24.Add, in Paragraph 2.C., a NOTE for Bearing rejection criteria.
25.Revise, in Figure 5, the orientation of the brackets.
26.Add, in Paragraph 2.C.(2), lower brackets.
27.Revise, in Paragraph 2.C.(16).(b)., application of sealant.
28.Revise, in Paragraph 3.A.Kit, QTY of Tapered Pins Part No. AN386−1−10 and AN386−1−11 from 2 to 4, Washer Part No. AN975−3 from 4 to 8, Nut Part No.
MS17826−3 from 4 to 8 and Cotter Pin Part No. MS24665−136 from 10 to 12.
29.Revise, in Paragraph 3.B.Parts, QTY of Cotter Pin Part No. MS24665−136 from 2 to 4.
30.Revise, in TABLE 4, Column FRICTION as POTENTIAL FRICTION and SEIZED as POTENTIALLY SEIZED.
31.Make miscellaneous minor changes, as necessary, with no change of context.
MODEL BD−700−1A10 (BD−700) 700−27−083 Page 2 of 2
SPECIAL CHECK — ELEVATOR CONTROL SYSTEM —
INSPECTION OF TORQUE TUBE BEARINGS The information below is provided for your reference. For full details, including labor and part coverage, please see corresponding paragraph contained within this bulletin.
RECOMMENDED
SPECIFIED TIME COMPLIANCE
COMPLIANCE TIME Refer to Paragraph 1.D.
EFFECTIVITY: A/C Serial No. 9002 to 9312, 9314 to 9380, and 9384 to 9429 MANPOWER: Refer to Paragraph 1.F.
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES TLMC, CH 5 AFFECTED NOYES 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 NOYES PREREQUISITE SERVICE BULLETINS: N/A NOTE: This Service Bulletin may be subject to an Airworthiness Directive, which will make it necessary to implement this Service Bulletin.
To place an order for parts or kits, please call Bombardier Aviation Parts Services at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY my.businessaircraft.bombardier.com MODEL BD−700−1A10 (BD−700) ATA 27−31
FLIGHT CONTROLS Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK — ELEVATOR CONTROL SYSTEM —
INSPECTION OF TORQUE TUBE BEARINGS
1. PLANNING INFORMATION NOTES:1 . Before you do this Service Bulletin, examine all STC, STA or equivalent action changes to make sure that this Service Bulletin can be completed.
2. This Recommended Service Bulletin is intended as an interim solution.
The data collected from Appendix A will be used to evaluate in service aircraft condition, and provide guidance toward a permanent solution.
Thus Appendix A of this Service Bulletin must be filled out and returned to Bombardier Aerospace.
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 follows with the Service Requests for Product Support Action (SRPSA) listed in the table that follows:
AIRCRAFT SERIAL NO. SRPSA NO.
9237 396225
SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL BD−700−1A10 (BD−700) ATA 27−31
FLIGHT CONTROLS 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.
2020 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 1 of 38 This Service Bulletin is available at:
B. Reason
1. Condition:
Bombardier has received 2 reported cases of sand and dust accumulation in the location of the elevator torque tube installation, in the center aft area of the horizontal stabilizer. Both RHS and LHS torque tubes were not rotating freely and showed signs of contamination.
2. Evidence:
The torque tube assemblies were returned to Bombardier for a full teardown inspection and it was concluded that one of the four bearings was found seized due to sand contamination. The other three bearings had higher than normal rolling resistance but were considered free to rotate. Corrosion was found between inner races and torque tubes.
A coating of dust in this area is not unusual, but appreciable accumulation of sand and dust on the bearings/housings and torque tube assembly, may increase the risk of contamination of the bearings and potential seizure.
3. Objective/Benefit:
The objective is to inspect for sand and dust contamination in the location of the elevator torque tube installation in order to prevent bearings contamination and/or seizures. Replacing any bearing that would show signs of contamination.
Report back finding to Bombardier Aerospace, to be able to properly assess the fleet in the engineering evaluation.
C. Description This Service Bulletin gives instructions in PART A to:
− Do a functional test of the elevator control system, − Get access to the elevator torque tubes, − Do a visual inspection of the torque tubes, − Clean the area, − Repeat 25 cycles of the elevator surfaces, − Inspect the bearings, − Disconnect the input and output control rods, − Do a manual inspection of the bearings, − Record the inspection results on Appendix A (attached), and − Return Appendix A to Bombardier Aerospace, This Service Bulletin gives instructions in PART B to:
− Remove the torque tube assemblies from the aircraft, − Disassemble the torque tubes, MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 2 of 38
− Remove bearings from the bracket assemblies, − Perform NDT on the brackets, − Stake the new bearings, − Assemble the torque tubes, − Install the torque tube assemblies on the aircraft, − Reconnect the input and output control rods, and − Do the necessary tests to make sure that the system operates correctly.
D. Compliance Recommended whichever is later:
− Within 36 months from Service Bulletin release (Basic Issue).
− No earlier than 57 months and no later than 63 months from the date of aircraft manufacture, as identified on the identification plate of the aircraft.
NOTES: 1. If it is not possible to complete all the instructions in this Service Bulletin because of the aircraft configuration, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
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 under the Canada/EU bilateral Aviation Safety Agreement.
MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 3 of 38
F. Manpower NOTES: 1. The man−hours given are to help you schedule the tasks given in this Service Bulletin. The man−hours 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, 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 man−hours and should be considered for planning purposes before you schedule this Service Bulletin.
3. Labor hours are based on the fact that the modification will be done at the next scheduled maintenance task or inspection Therefore no man−hours are allotted to prepare the aircraft for maintenance or to prepare for this Service Bulletin.
12 man−hours are necessary to do PART A of this special check.
5 man−hours are necessary to do PART B of this special check.
The labor required to do this Service Bulletin is at no cost if:
− the work is done during new aircraft warranty period, − the work is done at Bombardier Business Aviation Services (BBAS) or Authorized Service Facilities (ASF), and − this Service Bulletin is scheduled within 36 months from its release date (Basic Issue), or within 63 months of aircraft Certificate of Airworthiness issuance, whichever is later.
G. Material − Cost and Availability Kit 700K27−6503 is necessary to do PART B of this special check.
KIT NO. PRICE 700K27−6503 Please contact Bombardier Aerospace Parts Services, in Montreal, for delivery lead times and confirmation of prices.
In addition to the kit shown above, the parts in Paragraph 3 are necessary to do this special check.
The kit is available at no cost if:
− ordered during new aircraft warranty period, and MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 4 of 38
− a no−charge purchase order is sent to Bombardier Aerospace within 36 months from this Service Bulletin release date (Basic Issue), or within 63 months of aircraft Certificate of Airworthiness issuance, whichever is later.
During or after the above free period, Smart Parts does not pay for the kit.
H. Tooling The equipment and tools listed below are necessary to do this special check:
GSE REFERENCE NO. PART NO. DESCRIPTION 20−00−04 950−315 Digital Inclinometer 20X−10−01 S4933959−501 Tag, Circuit Breaker 27X−00−03 G700−270003−1 Kit − Rudder/Elevator Rigging Pins 27X−31−01 ACS76050 Elevator Rigging−Kit 27X−63−02 92A99107 Kit − Rigging Spoiler/Aileron (Clinometer) − GT995040−28 (See Note 4) Tool, Skating Commercially Available − Glass, Magnifying 10X−25X Commercially Available − Press, Hydraulic (See Note 5) Commercially Available − Vacuum Commercially Available − Wrench, Torque 25 to 30 lbf in (2.83 to 3.38 Nm) MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 5 of 38
GSE REFERENCE NO. PART NO. DESCRIPTION Commercially Available − Wrench, Torque 30 to 40 lbf in (3.39 to 4.51 Nm) NOTES: 1. Refer to the Global Express or Global Express XRS 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 the GX or XRS for acceptable GSE equivalents.
3. This list is provided for quick reference. In case of discrepancy between this list and the tools called in the SPM, WM, Chapter 20, then the tools called in the SPM, WM prevail. Other approved alternative tools are acceptable and can also be used.
4. Bombardier Aerospace part number.
5. Capacity as applicable. The highest possible load value necessary in this subject is 72,188 lb (32,744 Kg) I. Weight and Balance No change.
J. Electrical Load Data No change.
K. References − TCCA Airworthiness Directive, CF−2020−29 − BOMBARDIER: Flight Controls − Elevator Control System − Vertical Torque Tube Seizure − Sand Contamination of Bearing.
− EASA Airworthiness Directive, CF−2020−29 − BOMBARDIER: Flight Controls − Elevator Control System − Vertical Torque Tube Seizure − Sand Contamination of Bearing.
− FAA Airworthiness Directive, (pending).
− AW700−27−0786 Release of AD CF−2020−29, Flight Controls − Elevator Control System − Vertical Torque Tube Seizure − Sand Contamination of Bearing.
− Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−01782, Rev. −−.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapters 20 and 51.
− Bombardier Aerospace, Drawing GC413−3650, Rev. NC.
− Appendix A − Information Feedback Sheet (attached).
MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 6 of 38
− Global Express BD−700 Aircraft Maintenance Manual (AMM), Chapters 24, 27, 29 and 55.
− Global Express BD−700 Aircraft Illustrated Parts Catalog (AIPC), Chapters 27 and 55.
− Global Express BD−700 Illustrated Tool and Equipment Manual (ITEM), Chapters 20 and 27.
− Global Express BD−700 Nondestructive Testing Manual (NDT), Part 1, SECTION 8.
− Global Express BD−700 Structural Repair Manual (SRM), Chapter 51.
− Global Express XRS BD−700 Aircraft Maintenance Manual (AMM), Chapters 24, 27, 29 and 55.
− Global Express XRS BD−700 Aircraft Illustrated Parts Catalog (AIPC), Chapters 27 and 55.
− Global Express XRS BD−700 Illustrated Tool and Equipment Manual (ITEM), Chapters 20 and 27.
− Global Express XRS BD−700 Nondestructive Testing Manual (NDT), Part 1, SECTION 8.
− Global Express XRS BD−700 Structural Repair Manual (SRM), Chapter 51.
L. Other Publications Affected None.
M. Equivalent Service Bulletins For the Global 5000 BD−700−1A11 aircraft, use SB 700−1A11−27−041.
For the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck aircraft, use SB 700−27−5012.
For the Global 6000 BD−700−1A10 aircraft, use SB 700−27−6012.
For the Global 5500 BD−700−1A11 aircraft, use SB 700−27−5503.
For the Global 6500 BD−700−1A10 aircraft, use SB 700−27−6503.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures 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 (AMM), Chapter 6.
MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 7 of 38
A. Aircraft Setup NOTE: The steps in the Aircraft Setup section of this Service Bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator’s discretion.
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801
(2) Obey all flight control safety precautions. Refer to AMM 27−00−00−910−801.
(3) Obey all hydraulic safety precautions. Refer to AMM 29−00−00−910−801.
(4) Obey all hydraulic technical safety precautions. Refer to AMM 29−00−00−910−802.
(5) Install warning tags on the pilot and copilot control wheels and rudder pedals, and on the AIL/RUD/STAB TRIMS control panel.
(6) Remove lower visors (346JL/346JR). Refer to AMM 55−10−05−000−810.
(7) Remove upper visors (346KL/346KR). Refer to AMM 55−10−05−000−809.
(8) Remove lower trailing−edge access−panels (352AB/362AB). Refer to AMM 55−10−17−000−802.
(9) Remove access panel for the elevator control bellcrank (345EL). Refer to AMM 55−30−13−000−805.
(10) Connect the electrical power to the aircraft. Refer to AMM 24−00−00−861−801.
(11) Make sure the pitch trim is set as follows:
REFERENCE POSITION/INDICATION EICAS primary page STAB indicator shows position pointer at 2 degrees ±0.1 degree
(12) Install a clinometer on each elevator control surface at BL35.00 at a distance of
2.00 in (50.80 mm) from the elevator trailing edge.
NOTE: Make sure the clinometers are at the center of and parallel to the axes of the PCU actuators.
(13) Set the clinometer to zero as follows. Refer to AMM 27−31−00−720−801:
(a) Pressurize the aircraft hydraulic systems No. 1 and No. 2. Refer to AMM 29−10−00−862−801.
(b) Pressurize the No. 3 hydraulic system. Refer to AMM 29−10−00−862−803.
(c) Cycle the elevators 5 times.
(d) Make sure that the upper surface trailing−edge of the elevator is flush ±0.120 in (±3.04 mm) with the tip fairing.
MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 8 of 38
(e) The elevator trailing−edge inner−corners mismatch should be less than or equal to 0.280 in (7.11 mm).
(f) Set the clinometer to zero.
(g) If the upper surface of the elevator is not flush with the tip fairing and the center mismatch is more than 0.280 in (7.11 mm), use of elevator rigging fixture GSE 27X−31−01, and set the clinometer to zero as follows:
(i) Release the hydraulic pressure from the No. 1 and No. 2 hydraulic systems. Refer to AMM 29−10−00−862−802.
(ii) Release the hydraulic pressure from the No. 3 hydraulic system.
Refer to AMM 29−10−00−862−804.
(iii) Install the elevator rigging fixture on the horizontal stabilizer to set the elevator control surfaces to zero.
NOTE: Make sure the stabilizer and the elevator are touching the rigging fixture contour.
(iv) Set the clinometer to zero.
(v) Remove the elevator rigging fixture from the horizontal stabilizer.
(14) In the flight compartment, on the EMS CDU, set the circuit breakers that follow to OUT. Refer to AMM 24−00−00−863−801:
SYSTEM NAME CIRCUIT BREAKER NAME
BUS NAME ENGINE L ENG IGN 1 BATT ENGINE L ENG IGN 2 BATT ENGINE R ENG IGN 1 BATT ENGINE R ENG IGN 2 BATT
(15) Pressurize the No. 1 and No. 2 hydraulic systems. Refer to AMM 29−10−00−862−801.
(16) Pressurize the No. 3 hydraulic system. Refer to AMM 29−10−00−862−803.
(17) On the control columns, do as follows:
PROCEDURE APPLICABLE RESULT Pull and hold the control columns fully aft.
On the clinometers, the two elevators show 24 degrees ±0.5 degree up.
On the EICAS, on the FLIGHT CONTROLS page, ELEV position pointers go fully up.
MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 23/2020 Revision 01: Dec 07/2020 700−27−083 Page 9 of 38