Revision Transmittal Sheet

Transcription

1 2 APPROVED WHITE IN LEARJET 31 RT Revision Transmittal Sheet This page transmits Revision 1 to No , Main Landing Gear Torque Link Replacement. Rework: No rework is required for aircraft which have complied with previous issues of this document. Summary: This revision changes the new Apex bushing part number, removes the old torque link bushings, adds requirement to inspect, adds the new part number to the information table, corrects part number in the information table, adds accomplishment instruction procedure steps to remove, inspect, and to install new bushings, and updates the illustration to reflect the part number changes. Change bars are placed in the left margin of pages where significant changes are located. This revision incorporates the latest document format for Learjet service instructions. The general arrangement of this document may change from the previous issue. Description of Changes In the Planning Information section: Changed the Other Materials Required information as follows: Added part information table with Apex Torque Link Bushing part number In the Material Information section: Changed the -802 kit information as follows: Removed the Torque Link Bushing part number from kit. Changed the Identification information as follows: Corrected part number in table from V to V Corrected part number in table from V to V Corrected part number in table from V to V Corrected part number in table from V to V In the Accomplishment Instructions section: Changed the Modification Instructions as follows: Added procedure step to remove and destroy upper torque link. Added procedure step to inspect lower torque link Apex bushings and remove if found out of tolerance. Added procedure step to inspect all removed hardware and bushings and replace if required. Added procedure step if required, to install new Apex Torque Link Bushings on the lower torque link assembly. RT Page 1 of 2 Jan 18/16

2 Revision Transmittal Sheet In the Illustrations section: Changed Figure 1, Sheet 3 as follows: Changed part number of the torque link bushing from to Removed Apex Bushings from the upper torque link illustration. Removed existing washer. Filing Instructions: This is a COMPLETE revision. Remove and discard all pages of the prior issue and replace them with pages of Revision 1. Record of Revisions: ISSUE DISTRIBUTION DATE Basic Jul 20/15 Revision 1 Jan 18/16 RT Page 2 of 2 Jan 18/16

3 2 LEARJET 31 If the instructions in this publication cannot be completed because of an STC change to the aircraft, speak to the STC holder or the regional Federal Aviation Administration (FAA) office for information and disposition. Contact Information Distribution Date Rev. No. Business Aircraft Learjet Inc. MS 53 P.O. Box 7707 Wichita, Kansas January 18, Customer Response Center (CRC) (Toll Free) (Tel) Push 5 then 2 for Parts Services or push 4 then push 2 for Technical Publications. LANDING GEAR - MAIN LANDING GEAR TORQUE LINK REPLACEMENT 1. Planning Information A. Effectivity (1) Learjet thru B. Reason (1) Provide steel replacement torque links with improved corrosion resistance. C. Description (1) This service bulletin provides instructions to rework or replace the lower and upper main landing gear torque link assemblies. These commodities, technology or software were exported from the United States in accordance with the Export Administration Regulations. Diversion contrary to United States law is prohibited. Refer to applicable government agency regulations and requirements and make sure that the work described in this publication 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. 2015, Bombardier Inc. All rights reserved. Challenger*, Global Express*, Learjet*, are Trademarks of Bombardier Inc. Page 1 of 16

4 D. Compliance (1) - Bombardier Learjet Inc. recommends these instructions are completed in less than 1200 flight hours or less than 24 months from the initial distribution date of this publication. E. Approval (1) The Federal Aviation Administration (FAA) has approved the technical content in this publication that has an effect on the airplane type design. (2) The European Aviation Safety Agency (EASA) has accepted the technical content in this publication that has an effect on the airplane type design. F. Labor Hours - Estimated Accomplishment Time -801 KIT -802 KIT TASK Labor hours to gain access Labor hours to do the aircraft modification..5.5 Labor hours to do a functional test/operational check Labor hours to return the aircraft to airworthy status Total Labor Hours The labor hours provided are estimates to assist scheduling and planning 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 aircraft loose equipment, acquisition of tools and equipment, training, supervision and inspection. If labor coverage is provided, only the hours above will be paid. When planning to complete these instructions, please contact Bombardier Aerospace, Learjet Inc. Business Aircraft Customer Service, Parts Services for parts availability and shipping times as necessary. (Refer to the title page of this document for contact information.) G. Expense Coverage (1) None. (2) Labor Coverage - None. (3) Material Coverage - None. (4) Smart Parts Plus Coverage - None. Page 2 of 16

5 H. Material Required PART NUMBER QTY NOMENCLATURE *PRICING Kit $27, Kit $14, The above prices can change. Refer to Paragraph 2.A. to determine which kit is necessary. *For current prices, availability, ordering and shipping information, please call Bombardier Aerospace, Learjet Inc. Business Aircraft Customer Service, Parts Services. (Refer to the title page of this document for contact information.) (1) Other materials/parts necessary to complete these instructions. * PART NUMBER NOMENCLATURE QTY SUPPLIER Apex Bushing As Required Learjet Inc. * If replacement is required. For current prices, availability, ordering and shipping information, please call Bombardier Aerospace, Learjet Inc. Business Aircraft Customer Service, Parts Services. (Refer to the title page of this document for contact information. I. Tools, Equipment and Materials (1) Refer to Section 3 of the Service Manual or Chapter 32 of the Maintenance Manual, Installation of Torque Arms. J. Weight and Balance (1) Change in basic weight and moment for -801 upper and lower torque link kit. CHANGE IN BASIC WEIGHT Plus (+) 3.44 pounds CHANGE IN BASIC MOMENT Plus (+) inch-pounds (2) Change in basic weight and moment for -802 upper torque link kit. CHANGE IN BASIC WEIGHT Plus (+) 1.72 pounds CHANGE IN BASIC MOMENT Plus (+) inch-pounds Page 3 of 16

6 K. References If applicable, referenced third party documentation can be accessed by opening the attachments pane in the Adobe Acrobat Reader software. In the latest version of the software, the attachments pane can be opened by clicking on the paper clip icon at the lower left corner of the screen. (1) Compliance Response Form. (2) Evaluation Sheet. (3) Learjet Service Manual, Section 3. (4) Learjet Maintenance Manual, Chapter 32. L. Other Publications Affected (1) Learjet Illustrated Parts Catalog, Chapter Material Information A. Parts Required (1) The kit is for aircraft that have not accomplished Learjet , "Installation of Main Landing Gear Lower Torque Arms with Jacking Provision" and contains the parts that follow: PART NUMBER QTY NOMENCLATURE NOTE Torque Link Assembly Spacer Shim As Required NAS Screw MS Cotter Pin Replace (Do Not Reuse) Some hardware comes in pre-packaged quantities. When that occurs, the quantity in the kit will be more than the quantity in the parts list. (2) The kit is for aircraft that have accomplished Learjet , "Installation of Main Landing Gear Lower Torque Arms with Jacking Provision" and contains the parts that follow: PART NUMBER QTY NOMENCLATURE NOTE Torque Link Assembly Spacer Shim As Required NAS Screw MS Cotter Pin Replace (Do Not Reuse) Some hardware comes in pre-packaged quantities. When that occurs, the quantity in the kit will be more than the quantity in the parts list. Page 4 of 16

7 B. Parts Removed List REMOVE PART NUMBER NOMENCLATURE DISPOSITION INSTALLED PART NUMBER FOR SPARES ORDER Lower Torque Link Assembly (* See Note) Destroy (** See Note) Upper Torque Link Assembly (* See Note) Destroy (** See Note) Upper Torque Link Assembly (* See Note) Destroy (** See Note) Upper Torque Link Assembly (* See Note) Destroy (** See Note) * Torque Link Assembly may be referred to as Torque Arm Assembly in the Learjet Service Manual. ** New Torque Link Assembly is not intended for jacking purposes. For aircraft that wish to add jacking capability for the lower torque link refer to SB , "Installation of Main Landing Gear Lower Torque Arms with Jacking Provision". C. Identification Table PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly Page 5 of 16

8 PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly Page 6 of 16

9 PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly V3-001 LH Strut Assembly V LH Strut Assembly LH Strut Assembly LH Strut Assembly V LH Strut Assembly V LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly Page 7 of 16

10 PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly LH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly Page 8 of 16

11 PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly Page 9 of 16

12 PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT V3-002 RH Strut Assembly V RH Strut Assembly RH Strut Assembly RH Strut Assembly V RH Strut Assembly V RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly RH Strut Assembly Page 10 of 16

13 PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT RH Strut Assembly Accomplishment Instructions A. Gain Access (1) Set the battery switches to OFF. If necessary, disconnect the aircraft batteries. B. Modification of Aircraft. (1) On Aircraft that install the -801 Torque Link Kit, replace the torque links with additional steps as noted below: (Refer to Section 3 of the Service Manual or Chapter 32 of the Maintenance Manual.) (a) Remove the squat switch and bracket assembly from the existing upper torque link (arm) in accordance with the Service Manual or the Maintenance Manual. Retain bracket for installation on new upper torque link. Retain two (2) existing squat switch bracket screws for installation. Discard the screw that attaches the squat switch wire harness clamp to the bracket. This screw is replaced upon installation. (See Figure 1, Detail D.) Do not disconnect squat switch wiring from the harness. Stow the squat switch in a safe location to prevent damage. (b) Install new upper torque link assembly as follows: (See Figure 1, Detail B and D.) 1) Line ream bushings as required. 2) Use shims provided in the kit as required to eliminate excessive clearance. (See Figure 1, Detail B and DC.) 3) Use the two (2) screws retained above to install the squat switch bracket on the new upper torque link. (See Figure 1, Detail D.) Make sure to leave the wire clamp attach hole open until next step. 4) Unstow the squat switch and install it on the squat switch bracket. (See Figure 1, Detail D.) Use the NAS screw provided in the kit to attach the existing clamp and complete the bracket and switch installation. (c) Install lower torque link assembly as follows: 1) Line ream bushings as required. 2) Use shims provided in the kit as required to eliminate excessive clearance. (See Figure 1, Detail B.) (d) Use a metal stamp to identify strut assembly. (Refer to the identification table in this service bulletin.) (e) Repeat steps (a) thru (h) for RH torque link assemblies. Page 11 of 16

14 (2) On Aircraft that install the -802 Torque Link Kit, replace the torque links with additional steps as noted below: (Refer to Section 3 of the Service Manual or Chapter 32 of the Maintenance Manual.) (a) Remove the squat switch and bracket assembly from the existing upper torque link (arm) in accordance with the Service Manual or the Maintenance Manual. Retain bracket for installation on new upper torque link. Retain two (2) existing squat switch bracket screws for installation. Discard the screw that attaches the squat switch wire harness clamp to the bracket. This screw is replaced upon installation. (See Figure 1, Detail D.) Do not disconnect squat switch wiring from the harness. Stow the squat switch in a safe location to prevent damage. (b) Remove and destroy the upper torque link. (c) Inspect lower torque link Apex bushings and remove if found out of tolerance. (d) Inspect all removed hardware and bushings and replace as required. (e) If required, install new Apex Torque Link Bushings on the lower torque link assemblies. (See Figure 1, Detail C.) (f) Install new upper torque link assembly as follows: (See Figure 1, Detail C and D.) 1) Line ream bushings as required. 2) Use shims provided in the kit as required to eliminate excessive clearance. (See Figure 1, Detail C and D.) 3) Use the two (2) screws retained above to install the squat switch bracket on the new upper torque link. (See Figure 1, Detail D.) Make sure to leave the wire clamp attach hole open until next step. 4) Unstow the squat switch and install it on the squat switch bracket. (See Figure 1, Detail D.) Use the NAS screw provided in the kit to attach the existing clamp and complete the bracket and switch installation. (g) Use a metal stamp to identify strut assembly. (Refer to the identification table in this service bulletin.) (h) Repeat steps (a) thru (g) for RH torque link assemblies. C. Return Aircraft to Airworthy Status (1) Make sure the batteries are connected to the aircraft. (2) Install any additional items removed for access. D. Compliance Response Form (1) Complete the compliance response form. (2) Send the compliance response form to Learjet Inc. as soon as possible. E. Aircraft Maintenance Records (1) Complete the Aircraft Maintenance Records in accordance with the regulatory requirements of the appropriate aircraft certification authority. Page 12 of 16

15 Main Landing Gear Torque Link Replacement Figure 1 (Sheet 1 OF 4) Page 13 of 16

16 Main Landing Gear Torque Link Replacement Figure 1 (Sheet 2 of 4) Page 14 of 16

17 SHIM (AS REQUIRED TO TO ELIMINATE EXCESSIVE CLEARANCE) EXISTING BOLT (REUSE) APEX BUSHING (2 REQUIRED) EXISTING PIN (REUSE) NEW UPPER TORQUE LINK LINK ASSEMBLY (1 REQUIRED) EXISTING WASHER (REUSE) EXISTING LOWER TORQUE LINK ASSEMBLY (REF) SPACER (1 REQUIRED) EXISTING PIN (REUSE) EXISTING WASHER (REUSE) COTTER PIN MS (1 REQUIRED) EXISTING NUT (REUSE) -802 KIT INSTALLATION Detail C K Main Landing Gear Torque Link Replacement Figure 1 (Sheet 3 of 4) Page 15 of 16

18 Main Landing Gear Torque Link Replacement Figure 1 (Sheet 4 of 4) Page 16 of 16

19 SERVICE BULLETIN COMPLIANCE RESPONSE It is necessary that Bombardier Learjet record aircraft having complied with this. Please fill in the and aircraft information below, sign and date the form in the space provided, fold on dotted lines, seal with tape, and mail completed form to Bombardier Learjet Maintenance Engineering. If mailed within the United States, this form may be mailed to Bombardier Learjet Maintenance Engineering using business reply mail (see reverse). This form may be faxed or e- mailed if preferred. (See mailing information provided.) WARRANTY - Completion of this response form is required in order to process the warranty claim. Therefore, if a warranty allowance is provided in the, return a copy of this form with the warranty claim. SMART PARTS - Completion of this response form is required in order to remain, enroll, or re-enroll in the Smart Parts Program. b *Submit by *An will be opened addressed to Fracas and this form will be attached. Mailing Information: Bombardier Learjet Maintenance Engineering (MS #78) (FAX ) fracas_usa@aero.bombardier.com Customer Support Learjet, Inc. Information SB Title: Main Landing Gear Torque Link Replacement No Rev No. 1 Date January 18, 2016 Aircraft Information Model Serial No. Flight Hours Landings Service Facility Information Facility Incorporating Bulletin Compliance Information The above referenced was complied with on the referenced serial number aircraft at the listed aircraft flight hours/landings: Actual hours to accomplish : Access Modify Test(s) Restore Name: (Please Print) Date Comments

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21 SERVICE BULLETIN EVALUATION SHEET YOUR COMMENTS WILL HELP US IMPROVE OUR SERVICE BULLETINS b Submit by *An will be opened addressed to the SB Group and this form will be attached. SERVICE BULLETIN: REVISION: 1 DATED: January 18, 2016 TITLE: Main Landing Gear Torque Link Replacement LEARJET CONTACT INFORMATION TELEPHONE: (316) FACSIMILE: (316) HOW EASY IS THE BULLETIN TO UNDERSTAND? COMMENTS POOR FAIR GOOD VERY GOOD EXCELLENT DOES THE BULLETIN TELL YOU ALL YOU NEED TO KNOW ABOUT THE JOB? COMMENTS DO YOU THINK THE BULLETIN CONVEYS THE BEST WAY TO DO THE JOB? COMMENTS HOW REALISTIC ARE THE LABOR-HOUR ESTIMATES? COMMENTS WHAT IS YOUR APPRECIATION OF THE ILLUSTRATION(S), FIGURE(S) AND/OR KIT DRAWING(S)? COMMENTS Actual hours to accomplish : Access: Modify: Test(s): Restore: PLEASE SUPPLY THE FOLLOWING OPERATOR: AIRCRAFT: NAME: TELEPHONE: UPON COMPLETION OF THE EVALUATION FORM, YOU MAY FAX TO (316) OR FOLD AND RETURN TO ADDRESS ON THE REVERSE SIDE OR USE THE SUBMIT BUTTON AT THE TOP TO IT.

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