2 APPROVED WHITE IN LEARJET 31 RT 31-32-24 Revision Transmittal Sheet This page transmits Revision 1 to No. 31-32-24, 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 2341127-1. In the Material Information section: Changed the -802 kit information as follows: Removed the 2341127-2 Torque Link Bushing part number from kit. Changed the Identification information as follows: Corrected part number in table from 54411000V3691-1 to 5441000V3691-1. Corrected part number in table from 54411000V3691-801 to 5441000V3691-801. Corrected part number in table from 54411000V3691-2 to 5441000V3691-2. Corrected part number in table from 54411000V3691-802 to 5441000V3691-802. 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 2341127-1 Apex Torque Link Bushings on the lower torque link assembly. RT 31-32-24 Page 1 of 2 Jan 18/16
Revision Transmittal Sheet In the Illustrations section: Changed Figure 1, Sheet 3 as follows: Changed part number of the torque link bushing from 2341127-2 to 2341127-1. Removed 2341127-2 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 31-32-24 Page 2 of 2 Jan 18/16
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 67277-7707 January 18, 2016 1 Customer Response Center (CRC) 1-866-538-1247 (Toll Free) 1-514-855-2999 (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 31-001 thru 31-242. 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
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 3.0 3.0 Labor hours to gain access. 6.0 7.0 Labor hours to do the aircraft modification..5.5 Labor hours to do a functional test/operational check. 3.5 3.5 Labor hours to return the aircraft to airworthy status. 13.0 14.0 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
H. Material Required PART NUMBER QTY NOMENCLATURE *PRICING 2394208-801 1 Kit $27,163.00 2394208-802 1 Kit $14,776.00 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 2341127-1 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 (+) 1365.0 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 (+) 683.0 inch-pounds Page 3 of 16
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 32. 2. Material Information A. Parts Required (1) The 2394208-801 kit is for aircraft that have not accomplished Learjet 31-32-3, "Installation of Main Landing Gear Lower Torque Arms with Jacking Provision" and contains the parts that follow: PART NUMBER QTY NOMENCLATURE NOTE 2341131-001 4 Torque Link Assembly 2341113-1 2 Spacer 2341124-1 16 Shim As Required NAS1801-3-20 2 Screw MS24665-300 2 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 2394208-802 kit is for aircraft that have accomplished Learjet 31-32-3, "Installation of Main Landing Gear Lower Torque Arms with Jacking Provision" and contains the parts that follow: PART NUMBER QTY NOMENCLATURE NOTE 2341131-001 2 Torque Link Assembly 2341113-1 2 Spacer 2341124-1 8 Shim As Required NAS1801-3-20 2 Screw MS24665-300 2 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
B. Parts Removed List REMOVE PART NUMBER NOMENCLATURE DISPOSITION INSTALLED PART NUMBER FOR SPARES ORDER 2341119-1 Lower Torque Link Assembly (* See Note) Destroy 2341131-001 (** See Note) 2341131-001 2341119-2 Upper Torque Link Assembly (* See Note) Destroy 2341131-001 (** See Note) 2341131-001 2341119-5 Upper Torque Link Assembly (* See Note) Destroy 2341131-001 (** See Note) 2341131-001 2341119-7 Upper Torque Link Assembly (* See Note) Destroy 2341131-001 (** See Note) 2341131-001 * 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 SB31-32-3, "Installation of Main Landing Gear Lower Torque Arms with Jacking Provision". C. Identification Table PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT 2341100-1 LH Strut Assembly 2341100-801 3141100-805 2341100-5 LH Strut Assembly 2341100-803 3141100-805 2341100-7 LH Strut Assembly 2341100-805 3141100-805 2341100-9 LH Strut Assembly 2341100-807 3141100-805 2341100-11 LH Strut Assembly 2341100-809 3141100-805 2341100-13 LH Strut Assembly 2341100-811 3141100-805 2341100-13-2045-21 LH Strut Assembly 2341100-813 3141100-805 2341100-13-2045-23 LH Strut Assembly 2341100-815 3141100-805 2341100-13-2045-24 LH Strut Assembly 2341100-816 3141100-805 2341100-13-2045-25 LH Strut Assembly 2341100-817 3141100-805 2341100-13-2045-26 LH Strut Assembly 2341100-818 3141100-805 2341100-13-2045-27 LH Strut Assembly 2341100-819 3141100-805 2341100-13-2045-28 LH Strut Assembly 2341100-820 3141100-805 Page 5 of 16
PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT 2341100-17 LH Strut Assembly 2341100-825 3141100-805 2341100-21 LH Strut Assembly 2341100-827 3141100-805 2394105-803 LH Strut Assembly 2394105-003 3141100-805 2394105-805 LH Strut Assembly 2394105-005 3141100-805 2394105-807 LH Strut Assembly 2394105-007 3141100-805 2394105-809 LH Strut Assembly 2394105-009 3141100-805 2394105-811 LH Strut Assembly 2394105-011 3141100-805 2394105-813 LH Strut Assembly 2394105-013 3141100-805 2394105-815 LH Strut Assembly 2394105-015 3141100-805 2394105-816 LH Strut Assembly 2394105-016 3141100-805 2394105-817 LH Strut Assembly 2394105-017 3141100-805 2394105-818 LH Strut Assembly 2394105-018 3141100-805 2394105-819 LH Strut Assembly 2394105-019 3141100-805 2394105-820 LH Strut Assembly 2394105-020 3141100-805 2394105-825 LH Strut Assembly 2394105-025 3141100-805 2394105-827 LH Strut Assembly 2394105-027 3141100-805 2394105-829 LH Strut Assembly 2394105-029 3141100-805 2394105-831 LH Strut Assembly 2394105-031 3141100-805 2394105-833 LH Strut Assembly 2394105-033 3141100-805 2394105-835 LH Strut Assembly 2394105-035 3141100-805 2394105-837 LH Strut Assembly 2394105-037 3141100-805 2394105-839 LH Strut Assembly 2394105-039 3141100-805 2394105-841 LH Strut Assembly 2394105-041 3141100-805 2394105-843 LH Strut Assembly 2394105-043 3141100-805 2394105-845 LH Strut Assembly 2394105-045 3141100-805 2394105-847 LH Strut Assembly 2394105-047 3141100-805 2394105-849 LH Strut Assembly 2394105-049 3141100-805 2394105-851 LH Strut Assembly 2394105-051 3141100-805 2394105-853 LH Strut Assembly 2394105-053 3141100-805 2394105-855 LH Strut Assembly 2394105-055 2394105-067 Page 6 of 16
PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT 2394105-857 LH Strut Assembly 2394105-057 2394105-067 2394105-859 LH Strut Assembly 2394105-059 2394105-067 2394105-861 LH Strut Assembly 2394105-061 2394105-067 2394105-863 LH Strut Assembly 2394105-063 2394105-067 2394105-865 LH Strut Assembly 2394105-065 2394105-067 2394105-867 LH Strut Assembly 2394105-067 2394105-067 2394105-869 LH Strut Assembly 2394105-069 2394105-075 2394105-871 LH Strut Assembly 2394105-071 2394105-075 2394105-873 LH Strut Assembly 2394105-073 2394105-075 2394105-875 LH Strut Assembly 2394105-075 2394105-075 2394105-881 LH Strut Assembly 2394105-081 3141100-805 2441000V3-001 LH Strut Assembly 2441000V3-801 3141100-805 3141100-001 LH Strut Assembly 3141100-801 3141100-805 3141100-003 LH Strut Assembly 3141100-803 3141100-805 3141100-005 LH Strut Assembly 3141100-805 3141100-805 5441000V3691-1 LH Strut Assembly 5441000V3691-801 3141100-805 5441100-1 LH Strut Assembly 5441100-801 3141100-805 5441100-5 LH Strut Assembly 5441100-803 3141100-805 5441100-7 LH Strut Assembly 5441100-805 3141100-805 5441100-13 LH Strut Assembly 5441100-807 3141100-805 5441100-15 LH Strut Assembly 5441100-809 3141100-805 5441100-19 LH Strut Assembly 5441100-811 3141100-805 5441100-21 LH Strut Assembly 5441100-813 3141100-805 5441100-33 LH Strut Assembly 5441100-815 3141100-805 5441100-37 LH Strut Assembly 5441100-817 2394105-067 5441100-41 LH Strut Assembly 5441100-819 3141100-805 5441100-43 LH Strut Assembly 5441100-821 2394105-067 5441100-45 LH Strut Assembly 5441100-823 3141100-805 5441100-47 LH Strut Assembly 5441100-825 2394105-067 5441100-49 LH Strut Assembly 5441100-827 3141100-805 Page 7 of 16
PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT 5441100-51 LH Strut Assembly 5441100-829 2394105-067 5441100-61 LH Strut Assembly 5441100-831 2394105-075 5441100-63 LH Strut Assembly 5441100-833 2394105-075 5441100-65 LH Strut Assembly 5441100-835 3141100-805 5441100-67 LH Strut Assembly 5441100-837 2394105-075 5441100-69 LH Strut Assembly 5441100-839 3141100-805 5441100-71 LH Strut Assembly 5441100-841 2394105-075 5441100-73 LH Strut Assembly 5441100-843 3141100-805 5441100-75 LH Strut Assembly 5441100-845 2394105-067 5441100-079 LH Strut Assembly 5441100-847 3141100-805 5584030-3 LH Strut Assembly 5584030-801 2394105-067 5584030-5 LH Strut Assembly 5584030-803 2394105-067 2341100-2 RH Strut Assembly 2341100-802 3141100-806 2341100-6 RH Strut Assembly 2341100-804 3141100-806 2341100-8 RH Strut Assembly 2341100-806 3141100-806 2341100-10 RH Strut Assembly 2341100-808 3141100-806 2341100-12 RH Strut Assembly 2341100-810 3141100-806 2341100-14 RH Strut Assembly 2341100-812 3141100-806 2341100-14-2045-22 RH Strut Assembly 2341100-814 3141100-806 2341100-14-2045-29 RH Strut Assembly 2341100-821 3141100-806 2341100-14-2045-30 RH Strut Assembly 2341100-822 3141100-806 2341100-14-2045-31 RH Strut Assembly 2341100-823 3141100-806 2341100-18 RH Strut Assembly 2341100-826 3141100-806 2341100-22 RH Strut Assembly 2341100-828 3141100-806 2394105-804 RH Strut Assembly 2394105-004 3141100-806 2394105-806 RH Strut Assembly 2394105-006 3141100-806 2394105-808 RH Strut Assembly 2394105-008 3141100-806 2394105-810 RH Strut Assembly 2394105-010 3141100-806 2394105-812 RH Strut Assembly 2394105-012 3141100-806 2394105-814 RH Strut Assembly 2394105-014 3141100-806 Page 8 of 16
PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT 2394105-821 RH Strut Assembly 2394105-021 3141100-806 2394105-822 RH Strut Assembly 2394105-022 3141100-806 2394105-823 RH Strut Assembly 2394105-023 3141100-806 2394105-826 RH Strut Assembly 2394105-026 3141100-806 2394105-828 RH Strut Assembly 2394105-028 3141100-806 2394105-830 RH Strut Assembly 2394105-030 3141100-806 2394105-832 RH Strut Assembly 2394105-032 3141100-806 2394105-834 RH Strut Assembly 2394105-034 3141100-806 2394105-836 RH Strut Assembly 2394105-036 3141100-806 2394105-838 RH Strut Assembly 2394105-038 3141100-806 2394105-840 RH Strut Assembly 2394105-040 3141100-806 2394105-842 RH Strut Assembly 2394105-042 3141100-806 2394105-844 RH Strut Assembly 2394105-044 3141100-806 2394105-846 RH Strut Assembly 2394105-046 3141100-806 2394105-848 RH Strut Assembly 2394105-048 3141100-806 2394105-850 RH Strut Assembly 2394105-050 3141100-806 2394105-852 RH Strut Assembly 2394105-052 3141100-806 2394105-854 RH Strut Assembly 2394105-054 3141100-806 2394105-856 RH Strut Assembly 2394105-056 2394105-068 2394105-858 RH Strut Assembly 2394105-058 2394105-068 2394105-860 RH Strut Assembly 2394105-060 2394105-068 2394105-862 RH Strut Assembly 2394105-062 2394105-068 2394105-864 RH Strut Assembly 2394105-064 2394105-068 2394105-866 RH Strut Assembly 2394105-066 2394105-068 2394105-868 RH Strut Assembly 2394105-068 2394105-068 2394105-870 RH Strut Assembly 2394105-070 2394105-076 2394105-872 RH Strut Assembly 2394105-072 2394105-076 2394105-874 RH Strut Assembly 2394105-074 2394105-076 2394105-876 RH Strut Assembly 2394105-076 2394105-076 2394105-882 RH Strut Assembly 2394105-082 3141100-806 Page 9 of 16
PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT 2441000V3-002 RH Strut Assembly 2441000V3-802 3141100-806 3141100-002 RH Strut Assembly 3141100-802 3141100-806 3141100-004 RH Strut Assembly 3141100-804 3141100-806 3141100-006 RH Strut Assembly 3141100-806 3141100-806 5441000V3691-2 RH Strut Assembly 5441000V3691-802 3141100-806 5441100-2 RH Strut Assembly 5441100-802 3141100-806 5441100-6 RH Strut Assembly 5441100-804 3141100-806 5441100-8 RH Strut Assembly 5441100-806 3141100-806 5441100-14 RH Strut Assembly 5441100-808 3141100-806 5441100-16 RH Strut Assembly 5441100-810 3141100-806 5441100-20 RH Strut Assembly 5441100-812 3141100-806 5441100-22 RH Strut Assembly 5441100-814 3141100-806 5441100-32 RH Strut Assembly 5441100-816 3141100-806 5441100-38 RH Strut Assembly 5441100-818 2394105-068 5441100-42 RH Strut Assembly 5441100-820 3141100-806 5441100-44 RH Strut Assembly 5441100-822 2394105-068 5441100-46 RH Strut Assembly 5441100-824 3141100-806 5441100-48 RH Strut Assembly 5441100-826 2394105-068 5441100-50 RH Strut Assembly 5441100-828 3141100-806 5441100-52 RH Strut Assembly 5441100-830 2394105-068 5441100-62 RH Strut Assembly 5441100-832 2394105-076 5441100-64 RH Strut Assembly 5441100-834 2394105-076 5441100-66 RH Strut Assembly 5441100-836 3141100-806 5441100-68 RH Strut Assembly 5441100-838 2394105-076 5441100-70 RH Strut Assembly 5441100-840 3141100-806 5441100-72 RH Strut Assembly 5441100-842 2394105-076 5441100-74 RH Strut Assembly 5441100-844 3141100-806 5441100-76 RH Strut Assembly 5441100-846 2394105-068 5441100-080 RH Strut Assembly 5441100-848 3141100-806 5584030-4 RH Strut Assembly 5584030-804 2394105-068 Page 10 of 16
PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT 5584030-6 RH Strut Assembly 5584030-806 2394105-068 3. 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 NAS1801-3-20 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
(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 2341127-1 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 NAS1801-3-20 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
Main Landing Gear Torque Link Replacement Figure 1 (Sheet 1 OF 4) Page 13 of 16
Main Landing Gear Torque Link Replacement Figure 1 (Sheet 2 of 4) Page 14 of 16
SHIM 2341124-1 (AS REQUIRED TO TO ELIMINATE EXCESSIVE CLEARANCE) EXISTING BOLT (REUSE) APEX BUSHING 2341127-1 (2 REQUIRED) EXISTING PIN (REUSE) NEW UPPER TORQUE LINK LINK ASSEMBLY 2341131-001 (1 REQUIRED) EXISTING WASHER (REUSE) EXISTING LOWER TORQUE LINK ASSEMBLY 3188857-1 (REF) SPACER 2341113-1 (1 REQUIRED) EXISTING PIN (REUSE) EXISTING WASHER (REUSE) COTTER PIN MS24665-300 (1 REQUIRED) EXISTING NUT (REUSE) -802 KIT INSTALLATION Detail C K60-603240-001-03 Main Landing Gear Torque Link Replacement Figure 1 (Sheet 3 of 4) Page 15 of 16
Main Landing Gear Torque Link Replacement Figure 1 (Sheet 4 of 4) Page 16 of 16
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 Email *An email will be opened addressed to Fracas and this form will be attached. Mailing Information: Bombardier Learjet Maintenance Engineering (MS #78) (FAX 316 946-2305) fracas_usa@aero.bombardier.com Customer Support Learjet, Inc. Information SB Title: Main Landing Gear Torque Link Replacement No. 31-32-24 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 Email: Comments
SERVICE BULLETIN EVALUATION SHEET YOUR COMMENTS WILL HELP US IMPROVE OUR SERVICE BULLETINS b Submit by Email *An email will be opened addressed to the SB Group and this form will be attached. SERVICE BULLETIN: 31-32-24 REVISION: 1 DATED: January 18, 2016 TITLE: Main Landing Gear Torque Link Replacement LEARJET CONTACT INFORMATION TELEPHONE: (316) 946-2421 FACSIMILE: (316) 946-8876 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: EMAIL: TELEPHONE: UPON COMPLETION OF THE EVALUATION FORM, YOU MAY FAX TO (316) 946-8876 OR FOLD AND RETURN TO ADDRESS ON THE REVERSE SIDE OR USE THE SUBMIT BUTTON AT THE TOP TO EMAIL IT.