Bombardier Service Bulletin 100-27-20

Discard the Basic Issue of this Service Bulletin dated Nov 09/2020, and replace in its entirety with this Revision 01.

Service Bulletin No. 100−27−20 Date of Basic Issue Nov 09/2020 Revision No. 01 Dated Dec 01/2020 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. Add, in Paragraph 1. Planning Information, a new NOTE (5) that this Service Bulletin intent can be checked by verification of the airplane maintenance records.

2. Add, in Paragraph 2. Accomplishment Instruction NOTES, a new NOTE (4), on detail verification instructions.

SERVICE BULLETIN MODEL BD−100−1A10 (CH−300) 100−27−20 Page 1 of 1

REVISION TRANSMITTAL SHEET

SPECIAL CHECK/MODIFICATION – HORIZONTAL STABILIZER –

NO-BACK ASSEMBLY PAWL INSPECTION 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 Within 5 years from this Service Bulletin release date (Basic Issue) EFFECTIVITY: A/C Serial No. 20003 to 20457 MANPOWER: Refer to Paragraph 1.F

CONTINUED AIRWORTHINESS (CAW)

FLEET CAMPAIGN YES NO 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 YES NO PREREQUISITE SERVICE BULLETINS: N/A NOTE: This Service Bulletin may be subject to an Airworthiness Directive (AD) 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−100−1A10 (CH−300) ATA 27−40

FLIGHT CONTROLS Basic Issue: Nov 09/2020 Revision 01: Dec 01/2020 100−27−20 Page 1 of 1 This Service Bulletin is available at:

SPECIAL CHECK/MODIFICATION – HORIZONTAL STABILIZER –

NO-BACK ASSEMBLY PAWL INSPECTION

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 Service Bulletin is covered by a dedicated schedule. Dedicated schedules are used to reserve and manage inventory due to limited availability of rotable stock, parts and/or kits. Parts are limited, therefore, advance part scheduling with our In−Service Implementation Team (ISIT) is recommended prior to a maintenance visit. Please contact your Regional Manager (RM), Field Service Representative (FSR) or Customer Service Representative (CSR) to schedule your aircraft as there is a limited availability. The parts will be allocated on a first come first serve basis. For more information on dedicated schedules, refer to SB 100−00−002.

3. If the Horizontal Stabilizer Trim Actuator (HSTA) is removed, then the personnel necessary is as follows:

− two persons for the removal and installation of the HSTA;

− two persons for the rigging check of the pitch trim system; and − two persons for the operational test of the pitch trim system.

4. This Service Bulletin is also applicable for the HSTA’s in the operator’s stock room.

5. In certain cases, the intent of this Service Bulletin can be satisfied through a verification of the airplane maintenance records. Refer to Paragraph 2.A.

"ACCOMPLISHMENT INSTRUCTIONS" for more details.

SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL BD−100−1A10 (CH−300) ATA 27−40

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: Nov 09/2020 Revision 01: Dec 01/2020 100−27−20 Page 1 of 14 This Service Bulletin is available at:

A. Effectivity BD−100−1A10 aircraft, Serial No. 20003 to 20457 with the HSTA Serial Numbers listed in the table below:

TABLE 1 - HSTA SERIAL NUMBERS PART NO. NOMENCLATURE SERIAL NUMBERS C47100−003 C47100−004

HORIZONTAL

STABILIZER TRIM

ACTUATOR 0001, 0002A, 0003−0096, 0097A, 0098−0146, 0147A, 0148−0167, 0168A, 0169−0236, 0237A, 0238−0241, 0242A, 0243−0302, 0304−0324, 0326−0336, 0337A, 0338−0349, 0350A, 0351−0528, 0529A, 0530−0571, 0572A, 0573−0636, 0637A, 0638−0659, 0660A, 0661−0808, 0809, 0810, 0812−0817, 0818, 0819, 0820, 0821−0854, 0855A, and 0856−0886.

NOTE: The instructions given in this Service Bulletin are only applicable to the systems and parts installed at the time of delivery of the aircraft or as changed by Bombardier Aviation Service Bulletin(s).

B. Reason Condition:

The horizontal stabilizer trim system has three means to prevent un−commanded HSTA motion; the No−Back mechanism and the two motor brakes. Any of these three devices will prevent uncommanded motion of the Horizontal Stabilizer (HSTAB). The No−Back is a mechanical brake device located inside the HSTA.

The No−Back mechanism uses two tension pawls and two compression pawls to prevent movement of the horizontal stabilizer control surface caused by external loads during flight. It is possible that one of these pawls may have been installed upside−down (inverted 180 Degree). Therefore, a one−time inspection of the no−back assembly is necessary and if the installation is found not acceptable, the HSTA will be replaced.

C. Description This Service Bulletin gives instructions in PART A to:

− Get access to the HSTA and identify the serial numbers to make sure this Service Bulletin is applicable to your aircraft.

This Service Bulletin gives instructions in PART B to:

− If applicable, Inspect and identify the HSTA in accordance with the Moog VSB C47100−27−02.

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This Service Bulletin gives instructions in PART C to:

− If applicable, identify the HSTA in accordance with the Moog VSB C47100−27−03.

This Service Bulletin gives instructions in PART D to:

− If applicable, replace the HSTA.

− Do the necessary tests to make sure that the system operates correctly.

D. Compliance Recommended within 5 years from this Service Bulletin release date (Basic Issue).

NOTE: 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.

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 100−00−02.

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.

2 man−hours are necessary to do PART A of this Service Bulletin.

NOTE: 0.5 man−hours is necessary to do PART A of this Service Bulletin if the HSTA is not installed in an aircraft (example: HSTA in the stock room).

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6 man−hours are necessary to do PART B of this Service Bulletin.

NOTE: 3 man−hours is necessary to do PART B of this Service Bulletin (Ref: VSB C47100−27−02, On−bench instructions) if the HSTA is not installed in an aircraft (example: HSTA in the stock room).

1 man−hour is necessary to do PART C of this Service Bulletin.

NOTE: 1 man−hours is necessary to do PART C of this Service Bulletin if the HSTA is not installed in an aircraft (example: HSTA in the stock room).

16 man−hours are necessary to do PART D of this Service Bulletin.

1.5 man−hours are necessary to do Testing of this Service Bulletin.

The labor required to do PART A and PART B of 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 in less than 60 months from its release date (Basic Issue).

The labor required to do PART C and PART D of this Service Bulletin is at no cost if:

− the work is done at Bombardier Business Aviation Services (BBAS) or Authorized Service Facilities (ASF), and − this Service Bulletin is scheduled in less than 60 months from its release date (Basic Issue).

G. Material − Cost and Availability No kit is necessary to do of this modification.

The parts in Paragraph 3.B. are necessary to do PART B, PART C and PART D of this Service Bulletin.

The parts required to do PART B are available at no cost if:

− ordered during new aircraft warranty period, and − a no−charge purchase order is sent to Bombardier Aviation in less than 60 months from this Service Bulletin release date (Basic Issue).

The parts required to do PART C and PART D are available at no cost for in and out of warranty aircraft if a no−charge purchase order is sent to Bombardier Aviation in less than 60 months from this Service Bulletin release date (Basic Issue).

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This Service Bulletin is covered by a dedicated schedule. To ensure a timely and effective return/upgrade program, advance scheduling is required through our In−Service Implementation Team (ISIT). Please contact your Regional Manager (RM), Field Service Representative (FSR) or Customer Service Representative (CSR) as soon as is practical to schedule your aircraft.

Bombardier Aviation is maintaining a rotable pool of replacement HSTA, to be supplied to the operators under the terms and conditions given below:

NOTES: 1. The removed HSTA must be returned to Bombardier Aviation, Parts Services in less than 10 days of receipt of replacement unit, with documentation showing the serial number of the aircraft.

2. If the removed HSTA is not returned in less than 10 days, the operator will be charged for the replacement unit.

Send removed HSTA, Part No. C47100−003 or C47100−004 for rework to Bombardier Aviation at the address given below:

Learjet Inc. − Core Returns 251−A Wille Road, Des Plaines, Illinois 60018−1861 USA For all parts transactions, Bombardier Aviation’s current Spare Parts and Component Repair Price Catalogue General Terms and Conditions apply. These terms and conditions are found on the Bombardier Customer Portal at:

my.businessaircraft.bombardier.com For those aircraft in new aircraft warranty at the time of Service Bulletin distribution, Smart Parts does not pay for the kits or parts at any time.

For those aircraft out of new aircraft warranty at the time of Service Bulletin distribution, Smart Parts pays only for the Kit CC84715−002 for up to 60 months from the Service Bulletin distribution date (Basic Issue).

H. Tooling The equipment and tools listed below are necessary to this modification.

GSE REFERENCE NO. PART NO. DESCRIPTION 20−00−04 − Inclonometer(See Note 4) 24−00−24 S4933959−501 Circuit Breaker Tag 27C−40−01 G1002740054−001 HSTA go−no go Gauge(See Note 4) MODEL BD−100−1A10 (CH−300) Basic Issue: Nov 09/2020 Revision 01: Dec 01/2020 100−27−20 Page 5 of 14

GSE REFERENCE NO. PART NO. DESCRIPTION 27C−40−05 CA14064−001 Tool, HSTA, Spanner, Torque Adapter (See Note 3) 27C−40−06 CA14065−001 Tool, HSTA Spanner Wrench/Torque Adapter (See Note 3) 27C−41−01 C84215−001 Shipping Bar(See Note 3) 27C−43−02 C47961−001 Jack, HSTA Scissor(See Note 3) − CC92487−001 Leak Check Pressure Tool Set (See Note 5) NOTES: 1. Refer to the BD−100 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 BD−100, for acceptable GSE equivalents.

3. These tools are only necessary for PART D of this Service Bulletin.

4. These tools are only required for testing section.

5. This tool is only necessary for PART B of this Service Bulletin.

I. Weight and Balance No change.

J. Electrical Load Data No change.

K. References − TCCA Airworthiness Directive (Pending).

− Bombardier Aviation, Restriction and/or Special Instruction (RSI), C−100−000−27−0320, Rev. −−.

− MOOG, Service Bulletin C47100−27−02 (attached).

− MOOG, Service Bulletin C47100−27−03 (attached).

− Bombardier Aviation, SB 100−00−02, Service Bulletin Description and Policy.

− CH 300 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 27, 52 and 55.

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− CH 300 Aircraft Illustrated Parts Catalog (AIPC), Chapter 27.

− Bombardier Aviation, Standard Practices Manual (SPM), Chapters 20 and 51.

− Bombardier Aviation, Structural Repair Manual (SRM), Chapter 51.

L. Other Publications Affected None.

M. Equivalent Service Bulletin − For the Challenger 350 aircraft, use Service Bulletin 350−27−009.

2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. If the HSTA is not installed in an aircraft (example: HSTA in the stock room), go to step 2.B.(2) of this Service Bulletin.

2. All TASKs given in the procedures that follow are from the BD−100, Aircraft Maintenance Manual unless otherwise specified.

3. All references made to zones, access panels and/or doors, are from the BD−100, Aircraft Maintenance Manual, Chapter 6.

4. The intent of this Service Bulletin can be satisfied through a verification of the airplane maintenance records if the part number of the installed HSTA is C47100−004 and the serial number is found with suffix −K at the end (example SER NO. 0000K). This means that these HSTA were already inspected and repaired by the vendor (Moog) prior to release of the Service Bulletin.

If it is the case, no inspection is required, and aircraft can be considered in compliance with this Service Bulletin. If it is not the case, go to Paragraph

2.A. of this Service Bulletin.

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) Install the applicable warning placards on the control wheels, control columns, TRIM/STALL control panel, and from the area near the elevator control surfaces and the horizontal stabilizer surface.

(4) Connect electrical power to the aircraft. Refer to AMM 24−00−00−861−801.

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(5) On the TRIM/STALL control panel, set the STAB trim switch to PRI.

(6) On the pilots control wheel, do the procedure that follows:

PROCEDURE APPLICABLE RESULT Push in the pitch/roll trim switch, set the switch to NOSE UP or NOSE DOWN, and trim the horizontal stabilizer surface to the neutral position.

On the Engine Indication and Crew Alerting System (EICAS) primary page, make sure that the STAB trim position indicator moves to the neutral position and shows 1.9 to 2.1 units.

(7) Remove the electrical power from the aircraft. Refer to AMM 24−00−00−861−802.

(8) Open the aft equipment−compartment door (182GL). Refer to AMM 52−41−00−010−801.

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

CB PANEL CB NO. NAME ZONE LCBP B15 PRI STAB TRIM / RUD LIM 211 RCBP B13 SEC STAB TRIM / RUD LIM 212 LDCPC A4 PRI STAB MOTOR 311 RDCPC A5 SEC STAB MOTOR 312 B. Special Check/Modification — PART A — Visual Check of the HSTA Serial Numbers and Modification Plate

(1) Remove the forward access panel (346BR). Refer to AMM 55−30−21−000−802.

(2) Examine the HSTA identification plate and make a record of the serial number.

If the serial number is found with suffix −K at the end (example SER NO. 0000K), this means that these HSTA were already inspected and repaired by the vendor (Moog) prior to release of the Service Bulletin and no inspection is required. In this case, go to Paragraph 2.G (close out). If not, go to step 2.B.(3).

(3) Examine the HSTA for modification plate installation as shown in Figure 3−11 of the Moog Service Bulletin C47100−27−02 or in Figure 3−1 of the Moog Service Bulletin C47100−27−03. If the modification plate is not installed or if SB C47100−27−02 or SB C47100−27−03 is not shown, go to step 2.B.(4). If SB C47100−27−02 or SB C47100−27−03 is shown on the modification plate, go to Paragraph 2.G (Close−out).

NOTE: Make sure to record the serial number on the Service Bulletin Evaluation form, and fax or email the completed form to Bombardier Aviation.

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(4) If the HSTA serial number is within the Moog SB C47100−27−02 effectivity list referenced below, go to PART B of this Service Bulletin. If not, go to step

2.B.(5).

TABLE 2 - MOOG SB C47100-27-02 EFFECTIVITY PART NO. NOMENCLATURE SERIAL NUMBERS C47100−003 C47100−004

HORIZONTAL

STABILIZER

TRIM ACTUATOR 0001, 0002A, 0003−0096, 0098−0146, 0147A, 0148−0167, 0169−0236, 0238−0241, 0243−0302, 0304−0324, 0326−0336, 0338−0349, 0351−0528, 0530−0571, 0573−0636, 0638−0659, 0661−0808, 0812−0817, 0819, 0820 and 0825.

(5) If the HSTA serial number is within the Moog SB C47100−27−03 effectivity list referenced below, go to PART C of this Service Bulletin.

TABLE 3 - MOOG SB C47100-27-03 EFFECTIVITY PART NO. NOMENCLATURE SERIAL NUMBERS C47100−003 C47100−004

HORIZONTAL

STABILIZER

TRIM ACTUATOR 0097A, 0168A, 0237A, 0242A, 0337A, 0350A, 0529A, 0572A, 0637A, 0660A, 0809, 0810, 0818, 0821−0824, 0826−0854, 0855A and 0856−0886.

NOTE: If none of the above conditions applies, contact Bombardier Aviation for additional instructions.

C. Special Check/Modification — PART B — Moog SB C47100−27−02 − No−Back Pawl Inspection and Re−identification NOTES: 1. If it is not possible to complete all the instructions of this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.

2. Work instructions from Moog SB C47100−27−02 are separated into two sections for "on−aircraft instructions" and for "on−bench instructions". The on−bench instructions are only applicable if the HSTA is not installed in an aircraft (example: HSTA in the stock room). Refer to the applicable section of the SB C47100−27−02.

(1) Remove the forward access panel (346BL). Refer to AMM 55−30−21−000−802.

(2) Get access to the HSTA no−back pawl assembly to perform visual inspection.

Refer to Moog Service Bulletin C47100−27−02.

(3) Incorporate Moog Service Bulletin C47100−27−02.

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(4) If the installed pawls are correctly installed,

(a) Complete Moog Service Bulletin C47100−27−02 and make sure to re−identify the HSTA in accordance with Moog instruction, and

(b) Go to Paragraph 2.F (Testing).

(5) If the installed pawl are not correctly installed, go to PART D of this Service Bulletin.

D. Special Check/Modification — PART C — Moog SB C47100−27−03 − Modification Plate Addition NOTE: If it is not possible to complete all the instructions of this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.

(1) Get access to the HSTA to do installation of the modification plate. Refer to Moog Service Bulletin C47100−27−03.

(2) Complete Moog Service Bulletin C47100−27−03 and make sure to re−identify the HSTA in accordance with Moog instruction.

(3) Go to Paragraph 2.G (Close out).

E. Special Check/Modification — PART D — Replacement of HSTA

(1) Remove the HSTA, Part No. C47100−003 or C47100−004. Refer to AMM 27−41−05−000−801.

(2) Send the removed HSTA, Part No. C47100−003 or C47100−004 for rework to the address shown in Paragraph 1.G.

(3) Install a replacement unit HSTA, Part No. C47100−004. Refer to AMM 27−41−05−400−801.

NOTE: The replacement HSTA shall have either a modification plate marked with Moog SB C47100−27−02 or C47100−27−03 or identification plate marked with the suffix −K at the end of the serial number.

(4) Go to Paragraph 2.F (Testing).

F. Testing NOTE: Testing section is not applicable when the work is done on the bench.

Testing will be done per AMM instructions during HSTA installation on−aircraft.

(1) Do the rigging check of the pitch trim system. Refer to AMM 27−41−00−220−801.

(2) Do the operational test of the pitch trim system. Refer to AMM 27−41−00−710−801.

(3) Go to Paragraph 2.G (Close out).

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