# Bombardier Service Bulletin 60-32-33

Copy: No revision named ("U.S. DOT/FAA - SB 60-32-33"), 19 pages: PDF https://openairdocs.org/files/sha256/99/75/9975dd883cc4543dc84e015e504118238826cd7f28e14824d873b44354ee7384; text https://openairdocs.org/service-documents/bombardier/sb-60-32-33/file/9975dd883cc4.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2013-0214; AD 2013-13-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 60-32-33
- Page: https://openairdocs.org/service-documents/bombardier/sb-60-32-33

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2013-13-09](https://openairdocs.org/ad/2013-13-09.md), effective Aug 6, 2013: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-60-32-33/proposed.md).

## Text (19 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2013-0214; AD 2013-13-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

b 2
THIS PUBLICATION IS AVAILABLE AT:
www.cic.bombardier.com
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. 
© 2012, Bombardier Inc. All rights reserved. 
Challenger*, Global Express*, Learjet*, are Trademarks of Bombardier Inc.
SB 60-32-33
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Basic Issue: Jul 23/12
Contact Information Distribution Date
Business Aircraft 
Learjet Inc.
MS 53
P.O. Box 7707
Wichita, Kansas 67277-7707
Customer Response Center (CRC)
1-866-538-0247 (Toll Free)
(316) 946-6100 (Tel)
Push 2 for Parts Services or push 4 then 
push 1 for Technical Publications.
July 23, 2012
LEARJET 60
If you cannot complete the instructions in this publication 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.
Service Bulletin
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.
SB 60-32-33
Recommended
LANDING GEAR - INSTALLATION OF THE MAIN  LANDING GEAR SQUAT SWITCH SHIELDING
IMPROVEMENTS
1. Planning Information
A. Effectivity
(1) Learjet 60-001 thru 60-413.
B. Reason
(1) To improve the protective shielding of the main landing gear squat switches, separate the main
landing gear brake hydraulic tubes and to separate the main landing gear transducer wiring to
improve system separation.
C. Description
(1) This service bulletin provides instructions to mo dify and install protective shielding to the main
landing gear squat switches and to separate the main landing gear transducer wiring.

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LEARJET 60
Service Bulletin
D. Compliance
(1) Recommended - Bombardier Learjet Inc. recommend s that you complete these instructions in less
than 600 flight hours or less than 24 months from the initial distribution da te of this publication,
whichever comes first.
E. Approval
(1) The Federal Aviation Administration (FAA) has ap proved 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 publica-
tion that has an effect on the airplane type design.
F. Labor Hours - Estimated Accomplishment Time
NOTE: These labor hours are an estimate and ar e for planning purposes only. Facility and per-
sonnel capabilities may cause the labor hours to change.
When planning to complete these instructions, please contact Bombardier Aerospace,
Learjet Inc. Business Aircraft  Customer Service, Parts Logi stics for parts availability and
shipping times as necessary. (Refer to the title page of this document for contact informa-
tion.)
G. Expense Coverage
(1) Labor Coverage
(a) Aircraft in the Learjet manufactured warranty period, labor coverage is provided.
NOTE: For labor coverage to apply, you must complete these instructions at a Bombar-
dier Business Aviation Service Facility or at a Bombardier Learjet Authorized Ser-
vice Facility. You must complete these instructions within 24  months from the
Basic Issue date of this publication.
(b) Aircraft out of the Learjet manufactured warranty period, no labor coverage is provided.
(2) Material Coverage - Material coverage applies to  all aircraft affected by this publication.
NOTE: For material coverage to apply, you must  place an order for this kit from Bombardier
Learjet within 12 months from the Basic Issue distribution date of this publication.
LABOR HOURS
 60-001 THRU 60-108
LABOR HOURS 
60-109 THRU 60-413 TASK
2.0 2.0 Labor hours to gain access.
40.0 32.0 Labor hours to do the aircraft modification.
8.0 8.0 Labor hours to do a func tional test/operational check.
3.0 3.0 Labor hours to return the aircraft to airworthy status.
53.0 45.0 Total Labor Hours

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LEARJET 60
Service Bulletin
(3) Smart Parts Plus Coverage
(a) During or after the above free period, Smart Parts Plus does not pay for the kit.
H. Material Required
NOTE: The above price can change. 
For prices, availability, orderin g and shipping info rmation, please ca ll Bombardier Aero-
space, Learjet Inc. Business Aircraft Customer Service, Parts Logistics. (Refer to the title
page of this document for contact information.) 
(1) Other materials/parts that may be nec essary to complete these instructions.
NOTE: For ordering and shipping information, please contact Bombardier Aerospace, Learjet
Inc., Business Aircraft Customer Service, Pa rts Logistics. (Refer to the title page of
this document for contact information.)
I. Tools and Equipment
(1) For tools and equipment required to perform these instructions, refer to the sections of the mainte-
nance manual or wiring manual as follows:
(a) Chapter 20 of the Wiring Manual, "Electrical Connectors".
(b) Chapter 29 of the Maintenance Manual, "Safety Practices".
(c) Chapter 7 of the Maintenance Manual, "Jacking the Aircraft".
(d) Chapter 12 of the Maintenance Manual, "Service the Hydraulic Reservoir".
(e) Chapter 32 of the Maintenance Manual , "Installation of the Squat Switch", "Main Gear Wheel
and Tire - Maintenance Practices" and "Multiple Disc Brake - Maintenance Practices".
PART NUMBER QTY NOMENCLATURE PRICING
6032040001-821 1 Service Bulletin Kit $7,093.00
PART 
NUMBER NOMENCLATURE QTY SUPPLIER
RTV 106 (Red)
or Equivalent Sealant/Adhesive As Required General Electric Co.
FS9473PC-80
3M Peelable Adhesive 
Tape (VHB Type)
(5 inch width tape)
1
GT Sales
Wichita, Ks
(316) 943-2171
F9473PC 
(Alternate for 
FS9473PC-80)
3M Peelable Adhesive 
Tape (VHB Type)
(4 or 5 inch width tape 
required)
1 Commercially Available

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LEARJET 60
Service Bulletin
J. Weight and Balance
(1) Change in basic weight and moment.
K. References
NOTE: If applicable, referenced third party documentation can be found by opening the attach-
ment tab in the Adobe Acrobat Reader software.
(1) Service Bulletin Co mpliance Response Form.
(2) Service Bulletin Evaluation Sheet.
(3) Learjet Maintenance Manual, Chapters 7, 12, 20, 24, 29 and 32.
(4) Learjet Wiring Manual, Chapters 20 and 32.
L. Other Publications Affected
(1) Learjet Illustrated Part s Catalog, Chapter 32.
2. Material Information
A. Parts Required
(1) The 6032040001-821 kit contains the parts that follow:
CHANGE IN BASIC WEIGHT CHANGE IN BASIC MOMENT
Plus (+) 1.75 pounds Plus (+) 651.40 inch-pounds
PART NUMBER QTY NOMENCLATURE
MS3367-2-9 60 Tie Wraps
AN742D12 2 Clamp
AN735D64 6 Clamp
MS21919WDG7 4 Clamp
MS21919WDG16 6 Clamp
MS21042-3 16 Nut
M23053/5-106-9 4 Heat Shrink Tubing (7.0 ft [213.3 cm].)
M23053/5-109-9 2 Heat Shrink Tubing (1.0 ft [30.4 cm].)
NAS1801-3-8 2 Screw
MS35207-268 4 Screw
MS35207-270 2 Screw
NAS1801-3-27 4 Screw
NAS1801-3-29 2 Screw
NAS1149F0332P 12 Washer
320554 4 Terminal Lug
6032040001-814 4 Tubing, Convoluted (24 inch length)

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Service Bulletin
NOTE: 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.
B. Parts Removed List
6032040001-815 2 Tubing, Convoluted (12 inch length)
6032409003-001 1 Bracket, Brake Hose, Anti-Skid, LH
6032409003-002 1 Bracket, Brake Hose, Anti-Skid, RH
6032409004-001 1 Tube Assembly, Hydraulic System, Inbd LH
6032409004-002 1 Tube Assembly, Hydraulic System, Inbd RH
6032409005-005 1 Tube Assembly, Hydraulic System, Outbd LH
6032409005-006 1 Tube Assembly, Hydraulic System, Outbd RH
6032600009-001 1 Bracket, Squat Switch, MLG, LH
6032600010-001 1 Bracket, Squat Switch, MLG, RH
6032600011-001 2 Shim
PART 
NUMBER QTY NOMENCLA-TURE DISPO-SITION EFFECTIVITY REPLACED BY
5407003-160
or
5407002-326
1 Tube Assembly, Outbd Brake, LH Destroy When Installed 6032409005-005
5407003-161
or
5407002-327
1 Tube Assembly, Outbd Brake, RH Destroy When Installed 6032409005-006
2407003-377 1 Tube Assembly, Inbd Brake, LH Destroy When Installed 6032409004-001
2407003-376 1 Tube Assembly, Inbd Brake, RH Destroy When Installed 6032409004-002
2427003-7 1 Bracket Destroy When Installed 6032409003-001
2427003-8 1 Bracket Destroy When Installed 6032409003-002
2348010-23
or
6048010-001
2 Squat Switch Bracket Assembly Destroy When Installed 6032600009-001 and 6032600010-001
MS21919WDG6 2 Clamp Destroy When Installed AN742D12
MS21919WDG8 2 Clamp Destroy When Installed MS21919WDG7
PART NUMBER QTY NOMENCLATURE

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Service Bulletin
3. Accomplishment Instructions
A. Gain Access
NOTE: The instructions that follow are for both the left and right main landing gear.
(1) Put the aircraft on jacks. (Refer to Chapter 7 of the Maintenance Manual.)
(2) Set the battery switches off and disconnect the aircraft batteries. (Refer to Chapter 24 of the Main-
tenance Manual.)
(3) Depressurize the aircraft hydraulic system. (Refer to Chapter 12 of the Maintenance Manual.)
(4) Lower the inboard main landing gear door as follows:
(a) Override the inboard main landing gear door uplock actuator using a screwdriver to release
the uplock hook.
(b) Using another person, pump the brake pedals while pulling inboard gear door to the down
position.
(5) Disconnect the inboard gear door from the door actuator. Retain attaching hardware for installa-
tion.
B. Modification of Aircraft
NOTE: The instructions that follow are for both the left and right main landing gear.
(1) Install new rigid hydraulic tube assemblies to the main landing gear struts as follows: (See Figure
1, View A-A and B-B.)
NOTE: Make sure to cap and plug all disconnected hydraulic fittings.
WARNING: FOLLOW ALL SAFETY PRACTICES ASSOCIATED WITH HYDRAULIC FLUID
AND HYDRAULIC SYSTEMS. REFER TO  CHAPTER 29 OF THE MAINTE-
NANCE MANUAL.
(a) Remove and discard the butterfly clamping a nd attaching hardware located on the flexible
brake lines.
(b) Remove the existing rigid hydraulic tube asse mblies from the main la nding gear strut assem-
bly and discard.
NOTE: Use a container to catch any residual hydraulic fluid trapped in the hydraulic tube
assemblies.
(c) Remove the hydraulic elbow fittings from the ex isting anti-skid brake hose bracket assembly.
Retain the flexible hydraulic lines, hydraulic elbow fittings, washers and jam nuts for later
installation.
NOTE: Keep the elbow fittings attached to the flexible hydraulic lines for installation.
MS21919WDG9 2 Clamp Destroy When Installed MS21919WDG7
PART 
NUMBER QTY NOMENCLA-TURE DISPO-SITION EFFECTIVITY REPLACED BY

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(d) Disconnect the outboard gear door push rod from the anti-skid brake hose bracket assembly.
Retain hardware for later installation. 
(e) Remove the large clamp that supports the electrical harness assemblies just above the anti-
skid brake hose bracket assembly.
(f) Loosen the clamp that secures the anti-skid brake hose bracket assembly. Retain clamp for
later installation. 
(g) Remove and discard the existing anti-skid brake hose bracket assembly.
(h) Install new anti-skid brake hose bracket assembly on the main landing gear strut assembly at
the same location that the existing anti-skid brake hose bracket assembly was removed in pre-
vious step, and use retained clamp to secure in place. 
(i) Install the new hydraulic tube assemblies to the main landing gear hydraulic fittings.
(j) Use retained washers and jam nuts to install the retained flexible hydraulic lines and hydraulic
elbow fittings to the new anti-skid brake hose bracket assembly.
(k) Connect the outboard door push rod to the new anti-skid brake hose bracket assembly with
retained hardware.
(l) Install new butterfly clamps to flexible brake lines. (See Figure 1, View B-B.)
(2) Install the new main landing gear squat switch bracket and modify the main landing gear squat
switch wire harness as follows: (See Figure 1, View D-D and F-F.)
(a) Remove the main landing gear squat switch from  the aircraft. Retain the squat switch for later
installation. (Refer to Chapter 32 of the Maintenance Manual.)
(b) Remove and discard the main landing gear squat switch bracket and attaching hardware.
(c) Cut the 6032040001-815  convoluted tubing to 8.5 inches [21.6 cm] long.
(d) On aircraft where the main landing gear squat switch wire harness assembly has a mating
electrical connector, de-pin the harness from the connector.
(e) Place the convoluted tubing over the main la nding gear squat switch wire harness and position
it next to the squat switch.
(f) Install the main landing gear squat switch to the new bracket and the new bracket to the strut
assembly. (Refer to Chapter 32 of the Maintenance Manual.)
NOTE: Do not do the adjustment of the main landing gear squat switches in accordance
with the aircraft maintenance manual at this  time. Adjustment of the main landing
gear squat switches will be co mpleted in later pr ocedures outlined in this service
bulletin.
(g) Take note of how the main landing gear squat swit ch wiring is routed at the squat switch loca-
tion.
NOTE: The main landing gear squat switch wi ring must not extend past the bottom edge
of the bracket.
(h) Adjust the main landing gear squat switch wiring and clamp in place. (See Figure 1, View F-F.)
NOTE: Make sure the main landing gear squat switch wiring does not extend past the
bottom edge of the bracket.
(i) On aircraft where the main landing gear squat switch wiring fits within the lower edge of the
bracket, proceed to Step 3.B.(2)(k).
(j) On aircraft where the main landing gear squa t switch wiring cannot be adjusted and clamped
to fit within the edge of the bracket, do the steps that follow:

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Service Bulletin
1) Trim the heat shrink tubing on the main land ing gear squat switch wiring 4 inches up from
the main landing gear squat switch.
NOTE: Be careful not to damage the squat switch electrical wire harness during the
removal of heat shrink tubing.
2) Place 5.0 inches [12.7 cm] of heat shrink t ubing over the wire harness of the main landing
gear squat switch and set next to the squat switch.
3) Hold the main landing gear squat switch wi re harness in position and heat shrink the tub-
ing onto the harness.
NOTE: Heat shrink tubing must be placed next to the main landing gear squat switch
before heating to protect wires up to the switch.
(k) Install the convoluted tubing over the main landing gear squat switch wiring harness and
clamp the harness to the bracket with hardware provided in the kit. (See Figure 1, View F-F.)
(l) On aircraft that have performed Learjet Service Bulletin 60-32-16, Installation of Squat
Switches with Quick Disconnects , refer to Learjet Service Bulletin 60-32-16 to re-pin the wire
harness to the electrical connector. 
(m) On aircraft that have not performed Learjet Service Bulletin 60-32-16, Installation of Squat
Switches with Quick Disconnects , refer to Chapter 20 of the Wiring Manual  to re-pin the wire
harness to the electrical connector.
(n) Route the wire harness of the main landing gear squat switch upward along the strut and back
to the mating connector or terminal jack as required.
NOTE: Follow the same path for routing the squat switch wiring harness and secure in
same manner as before.
(3) Modify the main landing gear anti-skid wheel transducer electrical wire harnesses as follows: (See
Figure 1, View D-D and E-E.)
(a) On aircraft 60-001 thru 60-108, do the steps that follow:
1) Remove the main landing gear wheel and tire assemblies from the main landing gear
strut. (Refer to Chapter 32 of the Maintenance Manual.)
2) Remove the main landing gear brake assemblies from the main landing gear strut. (Refer
to Chapter 32 of the Maintenance Manual.)
3) Remove the anti-skid wheel transducers (MT19, LH Outbd; MT21, LH Inbd; MT20, RH
Outbd, MT22, RH Inbd). Retain for installation.
4) Desolder the anti-skid wheel transducer electrical wiring from the connectors. (Refer to
Chapter 32 of the Wiring Manual.) Retain connectors for installation.
5) Remove the anti-skid wheel transducer electrical wire harnesses from the main landing
gear strut assembly.
NOTE: Be careful not to damage the wire harness during removal.
6) Remove the fire sleeve from the anti-ski d wheel transducer electrical wire harnesses.
Retain the fire sleeve for later installation.
7) On the left anti-skid wheel transducer electrical wire harness, carefully remove the exterior
heat shrink sleeve from the anti-skid wirin g as necessary to separate MT19, LH (Outbd)
and MT21 (LH Inbd) transducer wiring for approximately 40.0 inches [101.6 cm] to extend
past the anti-skid brake hose bracket.

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Service Bulletin
NOTE: When separating the anti-skid wheel  transducer electrical wire harnesses,
make sure to start at the end attached to the transducers.
8) On the right anti-skid wheel transducer electrical wire harness , carefully remove the exte-
rior heat shrink sleeve from the anti-skid wiring as necessary to separate MT20, (RH
Outbd) and MT22 (RH Inbd) transducer wiring for approximately 40.0 inches [101.6 cm] to
extend past the anti-skid brake hose bracket.
NOTE: When separating the anti-skid wheel  transducer electrical wire harnesses,
make sure to start at the end attached to the transducers.
9) Install M23053/5-106-9 heat shrink tubing ov er each anti-skid wheel transducer electrical
wire harness (MT19, LH Outbd; MT21, LH Inbd; MT20, RH Outbd; MT22, RH Inbd).
NOTE: Make sure to install the heat shrink tubing up to the point where the electrical
wire harnesses are no longer separated.
10) As necessary, cut the installed heat shrink  tubing at the transducer end of the electrical
wire harnesses to expose the wire harnesses electrical shield.
11) Use a heat gun to shrink the heat shrink tu bing onto each of the anti-skid wheel transducer
electrical wire harnesses.
12) Cut convoluted 6032040001-814 tubi ng to 18.0 inches [45.7 cm] long.
13) Install the convoluted tubing over anti-skid wheel transducer electrical wire harnesses
(MT19, LH Outbd; MT21, LH Inbd; MT20, RH Outbd; MT22, RH Inbd).
NOTE: Make sure to slide the convoluted tubing up to the point where the electrical
wire harnesses are no longer separated.
14) Install the retained fire sleeve over both the anti-skid wheel transducer electrical wire har-
nesses. 
15) Install the anti-skid transducer electrical wire harness in the main landing gear strut
assembly. 
NOTE: Before installation of the anti-skid electrical wire harnesses, make sure to
identify the wire harnesses by electric al connector and install them one at
time. If this is not done, the anti-skid wheel transducer electrical wire har-
nesses can be installed in the wrong positions. 
16) Solder the anti-skid wheel transducer elec trical wiring to the connectors with SN60PB40A
rosin core solder. (Refer to Chapter 32 of the Wiring Manual.)
17) Install the anti-skid wheel transducers (MT19, LH Outbd; MT21, LH Inbd; MT20, RH
Outbd; MT22, RH Inbd) in the main landing gear strut assembly. (Refer to Chapter 32 of
the Maintenance Manual.)
NOTE: Do not do the functional test of the anti-skid system at this time.
18) Install the main landing gear brake assemblies on the main landing gear strut. (Refer to
Chapter 32 of the Maintenance Manual.)
19) Make sure the grommet and fire sleeve are seated into the bottom of the axle of the main
landing gear strut assembly.

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20) Apply RTV 106 sealant to both ends of the fire sleeve.
NOTE: Make sure the anti-skid wire harne sses do not extend below the brake
assemblies.
21) Install the main landing gear wheel and tire assemblies on the main landing gear strut.
(Refer to Chapter 32 of the Maintenance Manual.)
22) Secure the convoluted tubing to the flexible hydraulic lines with tie wraps.
(b) On aircraft 60-109 thru 60-413, do the steps that follow:
1) Remove the large clamps that secure the anti-skid wheel transducer electrical wire har-
nesses to the main landing gear strut assembly. Discard the large clamps and hardware.
2) As necessary, remove tie wraps located between the electrical connector and fire sleeve
to separate the anti-skid wheel transducer electrical wire harnesses from the flexible
hydraulic lines.
3) Remove the protective wraps from electric al connectors (P1055/J1055, LH; P1056/J1056,
RH). Retain the protective wraps for later installation.
4) Disconnect electrical connectors (P1055/J 1055, LH; P1056/J1056, RH). (Refer to Chapter
32 of the Wiring Manual.)
5) De-pin the anti-skid wheel transducer wiring and ground wires at terminal backshell from
connectors J1055 and J1056. (Refer to Chapter 32 of the Wiring Manual.)
NOTE: Make sure to remove ground terminal lug from backshell to allow heat shrink
tubing to be placed over wire harnesses.
6) On the left anti-skid wheel transducer electrical wire harnesses, carefully strip the exterior
heat shrink sleeve from the J1055 connector end back to the fire sleeve jacket to separate
the MT19 (LH Outbd) wire harness from the MT21 (LH Inbd) wire harness. (See  Figure 1,
View E-E.)
7) On the right anti-skid wheel transducer electrical wire harnesses , carefully strip the exte-
rior heat shrink sleeve from the J1056 connector end back to the fire sleeve jacket to sep-
arate the MT20 (RH Outbd) wire harness from the MT22 (RH Inbd) wire harness. (See
Figure 1, View E-E.)
8) Install approximately 7.0 feet [2.1 m] of heat shrink tubing over the inboard and outboard
anti-skid wheel transducer electrical wire harnesses up to the fire sleeve.
9) As necessary, trim excess heat shrink at electrical connectors (J1055, LH; J1056, RH).
10) Use a heat gun to shrink the heat shrink tu bing onto each of the anti-skid wheel transducer
electrical wire harnesses.
11) Cut convoluted tubing to 18.0 inches [45.7 cm] long.
12) Install the convoluted tubing over both the inboard and outboard anti-skid wheel electrical
wire harnesses. Position the convoluted tubing next to the fire sleeve. 
NOTE: Make sure the anti-skid wire harne sses do not extend below the brake
assemblies.
13) Secure the convoluted tubing to the flexible hydraulic lines with tie wraps. 
14) Install and re-pin electrical connectors an d ground terminal lugs (J1055, LH; J1056, RH).
(Refer to Chapter 32 of the Wiring Manual.)
15) Route the anti-skid wheel transducer electr ical wire harnesses and connect electrical con-
nectors (P1055/J1055, LH; P1056/J1056, RH).
16) Install the retained protective wraps on the electrical connectors (P1055/J1055, LH;
P1056/J1056, RH) using tie wraps.

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(4) Route and secure the anti-skid wheel and squat switch electrical wire harnesses to the main land-
ing gear strut assembly as follows: (See Figure 1, View D-D and G-G.)
(a) Use double sided tape or Class I adhesive to install shim on the main landing gear strut. (Refer
to Chapter 20 of the Maintenance Manual.) (See Figure 1, View D-D and G-G.)
NOTE: Heavily scuff the side of shim to be bonded.
(b) Route the anti-skid wheel transducer an d squat switch electrical wire harnesses. 
(c) Secure the lower portion of the anti-skid wheel transducer and squat switch electrical wire har-
nesses to the main landing gear shock strut assembly using new clamps. 
NOTE: Make sure the cushion is installed on the clamp and is properly centered to pro-
tect the electrical wire harnesses.
(d) Secure the upper portion of the anti-skid wheel transducer and squat switch electrical wire har-
nesses to the main landing gear shock strut assembly using new clamps. 
NOTE: Make sure the cushion is installed on the clamp and is properly centered to pro-
tect the electrical wire harnesses.
(5) Make sure all electrical wire harnesses disconnect ed for this modification have been secured and
supported.
(6) Make sure all hydraulic connections removed for this modification have been torqued.
(7) Make sure all hardware loosened or installed by this modification have been properly tightened.
(Refer to Chapter 20 of the Maintenance Manual.)
C. Functional Test/Operational Check
(1) Connect the batteries to the aircraft. (Refer to Chapter 24 of the Maintenance Manual.)
(2) Do the Adjustment of the Squat Switches. (Refer to Chapter 32 of the Maintenance Manual.)
(3) Connect the inboard gear door to the door actuator with retained hardware.
(4) Connect external hydraulic power source to the aircraft. (Refer to Chapter 29 of the Maintenance
Manual.)
(5) Pressurize the aircraft hydraulic system. (Refer to Chapter 29 of the Maintenance Manual.)
(6) Bleed the Brake System. (Refer to Chapter 32 of the Maintenance Manual.)
(7) Push the brake pedals and check all hydraulic connections removed by this modification for leaks.
(8) Release the brake pedals. Make sure the brake assemblies release correctly.
(9) Examine the anti-skid wheel transducer electrical  wire harnesses. Make sure electrical wire har-
nesses do not extend below the brake assemblies.
(10) Do the Operational Check of the Anti-Skid System. (Refer to Chapter 32 of the Maintenance Man-
ual.)
WARNING: USE EXTREME CARE WHEN LANDING GEAR IS RETRACTED AND EXTENDED.
MAKE SURE TO OBSERVE FROM AN ADEQUATE DISTANCE AND KEEP ALL
BODILY PARTS OUT OF THE WAY OF ALL LANDING GEAR AND LANDING
GEAR DOORS. FAILURE TO KEEP SAFE DISTANCE CAN RESULT IN PER-
SONAL INJURY OR DAMAGE TO THE AIRCRAFT. 
(11) Slowly retract the main landing gear and chec k for clearance between the landing light lens,
hydraulic lines and electrical wire harnesses with the new shielding.
NOTE: Apply hydraulic pressure to the gear in crementally starting at 0.00 PSI and increase
cart pressure slowly to cycle the landing gear.

### Page 12

THIS PUBLICATION IS AVAILABLE AT:
www.cic.bombardier.com
SB 60-32-33
Recommended
Page 12 of 19
Basic Issue: Jul 23/12
LEARJET 60
Service Bulletin
(12) Make sure of correct landing gear operation and indication in the cockpit. 
D. Return Aircraft to Airworthy Status
(1) Remove aircraft from jacks. (Refer to Chapter 7 of the Maintenance Manual.)
(2) Unless already done, connect the batteries to the aircraft. (Refer to Chapter 24 of the Maintenance
Manual.)
(3) If not already done, service the ai rcraft hydraulic system. (Refer to Chapter 12 of the Maintenance
Manual.)
E. Compliance Response Form
(1) Complete the compliance response form.
(2) Send the compliance response form to Learjet Inc. as soon as possible.
F. Aircraft Maintenance Records
(1) Complete the Aircraft Maintenance Records in  accordance with the regulatory requirements of
your aircraft certification authority.
G. General Information
(1) The table below lists standard tolerances wh ich shall apply to dimensions defined within the
instructions or illustrations of this document that do not have specified tolerances.
UNLESS OTHERWISE SPECIFIED
ALL TOLERANCES ARE AS FOLLOWS:
DECIMALS ANGLES
  0.0 ± 0.1 [0.0 mm ± 2.54 mm]
0.00 ± 0.03 [0.00 mm ± 0.76 mm]
0.000 ± 0.010 [0.000 mm ± 0.254 mm] 
MACHINED FORMED
± 0°30’ ± 2 °

### Page 13 (OCR)

LEARJET 60
Service Bulletin
D
OUTBOARD
BRAKE PRESSURE  INBOARD
TUBE ASSEMBLY  BRAKE PRESSURE
6032409005\  TUBE ASSEMBLY
(REF)  6032409004
(REF)
LEARJET 60
MAIN LANDING GEAR
(LEFT SIDE SHOWN)
→→D
(VIEW LOOKING FORWARD)
View A-A
K60-603233-001-01
Installation of the Main Landing Gear Shielding Improvements
Figure 1 (Sheet 1 of 7)
Basic Issue: Jul 23/12  THIS PUBLICATION IS AVAILABLE AT:  SB 60-32-33
www.cic.bombardier.com  Recommended
Page 13 of 19

### Page 14 (OCR)

LEARJET 60
Service Bulletin
OUTBOARD
BRAKE PRESSURE
TUBE ASSEMBLY
6032409005-005 (LH)
6032409005-006 (RH)
(1 REQUIRED EACH SIDE)
INBOARD
BRAKE PRESSURE
TUBE ASSEMBLY
6032409004-001 (LH)
CLAMP  6032409004-002 (RH)
MS21919WDG7  (1 REQUIRED EACH SIDE)
(2 REQUIRED)
SCREW
NAS1801-3-8
NUT
MS21042-3 NUT
(1 EACH REQUIRED)
9.8 in
[24.9 mm]  ANTI-SKID
BRAKE HOSE
BRACKET
6032409003-001 (LH)
6032409003-002 (RH)
FWD D  (1 REQUIRED EACH SIDE)
View B-B
EXISTING
CLAMP
(REF)
View C-C
K60-603233-001-02
Installation of the Main Landing Gear Shielding Improvements
Figure 1 (Sheet 2 of 7)
Basic Issue: Jul 23/12  THIS PUBLICATION IS AVAILABLE AT:  SB 60-32-33
www.cic.bombardier.com  Recommended
Page 14 of 19

### Page 15 (OCR)

LEARJET 60
Service Bulletin
CLAMP
AN735D64
SCREW
MS35207-268  18.2 in
NUT  [46.2 cm]
MS21042-3
(1 EACH REQUIRED, 2 PLACES)
(LOCATE SCREWS ON
AFT SIDE OF STRUT  13.2 in
[33.5 cm]
CLAMP
AN735D64
SCREW
MS35207-270
NUT
6.3 in
MS21042-3  [16.0 cm]
(1 EACH REQUIRED)
(LOCATE SCREWS ON
AFT SIDE OF STRUT
STRIKER PLATE
ASSEMBLY
(REF)
TORQUE ARM
STRUT EXTENDED
AIR MODE
A FWD  E-
(VIEW LOOKING INBOARD,
LH SHOWN, RH TYPICAL
NOTE  UNLESS OTHERWISE INDICATED)
the last sheet of the figure.  Notes information is found on  View D-D  K60-603233-001-03
Installation of the Main Landing Gear Shielding Improvements
Figure 1 (Sheet 3 of 7)
Basic Issue: Jul 23/12  THIS PUBLICATION IS AVAILABLE AT:  SB 60-32-33
www.cic.bombardier.com  Recommended
Page 15 of 19

### Page 16 (OCR)

LEARJET 60
Service Bulletin
CONVOLUTED
TUBING
6032040001-814
(2 REQUIRED)
ROUTE TO MT21,
HEAT SHRINK  LH INBD WHEEL
TUBING  ROUTE TO MT 19,
M23053/5-106-9  LH OUTBD WHEEL
(2 REQUIRED)  ROUTE TO MT22,
RH INBD WHEEL
ROUTE TO MT20,
RH OUTBD WHEEL
FIRESLEEVE
(REF)
NOTE  (VIEW LOOKING FORWARD)
Notes information is found on  the last sheet of the figure.  View E-E  K60-603233-001-04
Installation of the Main Landing Gear Shielding Improvements
Figure 1 (Sheet 4 of 7)
Basic Issue: Jul 23/12  THIS PUBLICATION IS AVAILABLE AT:  SB 60-32-33
www.cic.bombardier.com  Recommended
Page 16 of 19

### Page 17 (OCR)

LEARJET 60
Service Bulletin
SCREW  TORQUE ARM  CONVOLUTED
NAS1801-3-27  (REF)  TUBING
WASHER  6032040001-815
(UNDER SCREW HEAD)  (REF)
NAS1149F0332P  (TRIM AS REQUIRED)
WASHER
(UNDER NUT)  SCREW
NAS1149F0332P  NAS1801-3-29
NUT  CLAMP
MS21042-3  AN742D12
(1 EACH REQUIRED,  WASHER
2 PLACES)  (UNDER SCREW HEAD)
NAS1149F0332P
LH MAIN LG SQUAT  WASHER
SWITCH BRACKET  1.5 in  (UNDER NUT)
(1 REQUIRED)  6032600009-001  HEAT SHRINK  [3.8 cm]  NAS1149F0332P  NUT
TUBING  MS21042-3
S11
M23053/5-109-9  (1 EACH
(AS REQUIRED)  (REF)  REQUIRED)
(LH SQUAT SWITCH INSTALLATION)
SCREW
NAS1801-3-29  CONVOLUTED
CLAMP  TUBING
AN742D12  6032040001-815
WASHER  (REF)
(UNDER SCREW HEAD)  (TRIM AS REQUIRED)
NAS1149F0332P.
WASHER  TORQUE ARM
(UNDER NUT)  (REF)
NAS1149F0332P
NUT  SCREW
MS21042-3  1.5 in  NAS1801-3-27
(1 EACH  [3.8 cm]  WASHER
REQUIRED)  (UNDER SCREW HEAD)
NAS1149F0332P
S12  WASHER
(REF)  (UNDER NUT)
NAS1149F0332P
RH MAIN LG SQUAT  HEAT SHRINK
NUT
SWITCH BRACKET  TUBING
MS21042-3
6032600010-001  (1 REQUIRED)  (AS REQUIRED)  M23053/5-109-9  (1 EACH REQUIRED,  2 PLACES)
(RH SQUAT SWITCH INSTALLATION)
NOTE
Notes information is found on
the last sheet of the figure.  View F-F  K60-603233-001-05
Installation of the Main Landing Gear Shielding Improvements
Figure 1 (Sheet 5 of 7)
Basic Issue: Jul 23/12  THIS PUBLICATION IS AVAILABLE AT:  SB 60-32-33
www.cic.bombardier.com  Recommended
Page 17 of 19

### Page 18 (OCR)

LEARJET 60
Service Bulletin
MAIN LANDING
GEAR LIGHT
INBOARD  WIRE BUNDLE
WHEEL SPEED  (REF)
TRANSDUCER  SQUAT SWITCH
WIRE BUNDLE  WIRE BUNDLE
(REF)  (REF)
• SHIM
6032600011-001
(1 REQUIRED)
HYDRAULIC
AND
PNEUMATIC
PLUMBING
INSTALLATION
(REF)  OUTBOARD
WHEEL SPEED
TRANSDUCER
WIRE BUNDLE
(REF)
TRIM CONVOLUTED TUBING,
AS NECESSARY, TO ROUTE
TUBING AND HARNESS AS SHOWN.
View G-G
NOTE
Notes information is found on
the last sheet of the figure.  K60-603233-001-06
Installation of the Main Landing Gear Shielding Improvements
Figure 1 (Sheet 6 of 7)
Basic Issue: Jul 23/12  THIS PUBLICATION IS AVAILABLE AT:  SB 60-32-33
www.cic.bombardier.com  Recommended
Page 18 of 19

### Page 19 (OCR)

LEARJET 60
Service Bulletin
NOTES  portion of the cushion and discard the metal clamp.  run ho and data De near dan profect the wing. Trim of the wedg
Tie wrap the firesleeve to the brake hose for support as shown.
Distance between tie wraps should not exceed 2.80 in [7.11 cm].
Keep the convoluted tubing open at the bottom with approximately 0.40 in [10.16 mm]
clearance with the firesleeve to allow moisture to drain from the tubing.
Secure the convoluted tubing that was installed over the wheel speed transducer to the
corresponding hydraulic brake flex line. Use tie wraps as shown. Spacing between
tiewraps should not exceed 2.80 in [7.11 cm].
Approximate dimensions.
> Squat switch wiring must not hang below bracket.
• Shim should be centered between the brake lines and placed against the brake hose
anti skid bracket as shown. Heavily scuff the surface of the shim to be bonded. Use
double sided tape (3M VHB type preferred) or Class I adhesive to bond shim to the
main landing gear strut. (Refer to Chapter 20 of the Maintenance Manual.)
K60-603233-001-07
Installation of the Main Landing Gear Shielding Improvements
Figure 1 (Sheet 7 of 7)
Basic Issue: Jul 23/12  THIS PUBLICATION IS AVAILABLE AT:  SB 60-32-33
www.cic.bombardier.com  Recommended
Page 19 of 19

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