b

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

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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 modify and install protective shielding to the main

landing gear squat switches and to separate the main landing gear transducer wiring.
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Service Bulletin

D. Compliance

(1) Recommended - Bombardier Learjet Inc. recommends that you complete these instructions in less

than 600 flight hours or less than 24 months from the initial distribution date of this publication,

whichever comes first.

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

NOTE: These labor hours are an estimate and are for planning purposes only. Facility and personnel 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 Logistics for parts availability and

shipping times as necessary. (Refer to the title page of this document for contact information.)

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 Bombardier Business Aviation Service Facility or at a Bombardier Learjet Authorized Service 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 functional 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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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, ordering and shipping information, please call Bombardier Aerospace, 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 necessary to complete these instructions.

NOTE: For ordering and shipping information, please contact Bombardier Aerospace, Learjet

Inc., Business Aircraft Customer Service, Parts 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 maintenance 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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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 attachment tab in the Adobe Acrobat Reader software.

(1) Service Bulletin Compliance 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 Parts 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 NOMENCLATURE

DISPOSITION 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 Maintenance 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 installation.

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 MAINTENANCE MANUAL.

(a) Remove and discard the butterfly clamping and attaching hardware located on the flexible

brake lines.

(b) Remove the existing rigid hydraulic tube assemblies from the main landing gear strut assembly 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 existing 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 NOMENCLATURE

DISPOSITION 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 antiskid 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 previous 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 landing 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 completed in later procedures outlined in this service

bulletin.

(g) Take note of how the main landing gear squat switch wiring is routed at the squat switch location.

NOTE: The main landing gear squat switch wiring 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 squat switch wiring cannot be adjusted and clamped

to fit within the edge of the bracket, do the steps that follow:
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1) Trim the heat shrink tubing on the main landing 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 tubing 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 wire harness in position and heat shrink the tubing 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-skid 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 wiring 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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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 exterior 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 over 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 tubing onto each of the anti-skid wheel transducer

electrical wire harnesses.

12) Cut convoluted 6032040001-814 tubing 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 harnesses. 

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 electrical connector and install them one at

time. If this is not done, the anti-skid wheel transducer electrical wire harnesses can be installed in the wrong positions. 

16) Solder the anti-skid wheel transducer electrical 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 harnesses 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 harnesses 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 electrical connectors (P1055/J1055, LH; P1056/J1056,

RH). Retain the protective wraps for later installation.

4) Disconnect electrical connectors (P1055/J1055, 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 exterior heat shrink sleeve from the J1056 connector end back to the fire sleeve jacket to separate 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 tubing 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 harnesses 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 and ground terminal lugs (J1055, LH; J1056, RH).

(Refer to Chapter 32 of the Wiring Manual.)

15) Route the anti-skid wheel transducer electrical wire harnesses and connect electrical connectors (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 landing 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 and squat switch electrical wire harnesses. 

(c) Secure the lower portion of the anti-skid wheel transducer and squat switch electrical wire harnesses 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 protect the electrical wire harnesses.

(d) Secure the upper portion of the anti-skid wheel transducer and squat switch electrical wire harnesses 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 protect the electrical wire harnesses.

(5) Make sure all electrical wire harnesses disconnected 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 harnesses do not extend below the brake assemblies.

(10) Do the Operational Check of the Anti-Skid System. (Refer to Chapter 32 of the Maintenance Manual.)

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 PERSONAL INJURY OR DAMAGE TO THE AIRCRAFT. 

(11) Slowly retract the main landing gear and check for clearance between the landing light lens,

hydraulic lines and electrical wire harnesses with the new shielding.

NOTE: Apply hydraulic pressure to the gear incrementally starting at 0.00 PSI and increase

cart pressure slowly to cycle the landing gear.
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(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 aircraft 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 which 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°
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 1 of 7)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 2 of 7)
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Recommended

Page 15 of 19

Basic Issue: Jul 23/12

LEARJET 60

Service Bulletin

Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 3 of 7)
THIS PUBLICATION IS AVAILABLE AT:

www.cic.bombardier.com

SB 60-32-33

Recommended

Page 16 of 19

Basic Issue: Jul 23/12

LEARJET 60

Service Bulletin

Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 4 of 7)
THIS PUBLICATION IS AVAILABLE AT:

www.cic.bombardier.com

SB 60-32-33

Recommended

Page 17 of 19

Basic Issue: Jul 23/12

LEARJET 60

Service Bulletin

Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 5 of 7)
THIS PUBLICATION IS AVAILABLE AT:

www.cic.bombardier.com

SB 60-32-33

Recommended

Page 18 of 19

Basic Issue: Jul 23/12

LEARJET 60

Service Bulletin

Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 6 of 7)
THIS PUBLICATION IS AVAILABLE AT:

www.cic.bombardier.com

SB 60-32-33

Recommended

Page 19 of 19

Basic Issue: Jul 23/12

LEARJET 60

Service Bulletin

Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 7 of 7)