b

THIS PUBLICATION IS AVAILABLE AT:

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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.

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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.

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WINGS - INSTALLATION OF THE MAIN LANDING GEAR ANTI-SKID VALVE SHIELDING

IMPROVEMENTS

1. Planning Information

A. Effectivity

(1) Learjet 60-001 thru 60-413.

B. Reason

(1) To improve the protective shielding of the anti-skid system components located in the main landing

gear wheel well. 

C. Description

(1) This service bulletin provides instructions to modify and install protective shielding to the anti-skid

system in the main landing gear wheel well.
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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 TASK

2.0 Labor hours to gain access.

16.0 Labor hours to do the aircraft modification.

4.0 Labor hours to do a functional test/operational check.

2.5 Labor hours to return the aircraft to airworthy status.

24.5 Total Labor Hours
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(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: * This part is required for aircraft that have convex (round) landing light lamps

installed. The convex (round) landing light will not clear the new shielding installed by

this modification.

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) Refer to Chapter 29 of the Maintenance Manual, Safety Practices, Chapter 7 of the Maintenance

Manual, Jacking the Aircraft and Chapter 12 of the Maintenance Manual, Service the Hydraulic

Reservoir.

PART NUMBER QTY NOMENCLATURE PRICING

6032040001-801 1 Service Bulletin Kit $17,960.00

PART 

NUMBER NOMENCLATURE QTY SUPPLIER

A/KQ4681 or Q4681

(* See Note)

Landing Light Lamp 

(Flat)

As 

Required

Amglo Kemlite Inc.

Largo, FL 33733

MS35206-233

(* See Note) Screw As Required Obtain Locally

PART NUMBER NOMENCLATURE SUPPLIER USAGE

N/A 0.1660 inch Reamer Obtain Locally Open Drilled Holes
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J. Weight and Balance

(1) Change in basic weight and moment for aircraft that do the landing light change.

(2) Change in basic weight and moment for aircraft that do not do the landing light change.

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 33.

L. Other Publications Affected

(1) Learjet Illustrated Parts Catalog, Chapter 57.

2. Material Information

A. Parts Required

(1) The 6032040001-801 kit contains the parts that follow:

CHANGE IN BASIC WEIGHT CHANGE IN BASIC MOMENT

Plus (+) 2.00 pounds Plus (+) 779.10 inch-pounds

CHANGE IN BASIC WEIGHT CHANGE IN BASIC MOMENT

Plus (+) 1.78 pounds Plus (+) 692.70 inch-pounds

PART NUMBER QTY NOMENCLATURE ALTERNATE

PART NUMBER

AN525-832R7 8 Screw

AN525-832R9 20 Screw

MS20470AD3-6 8 Rivet

MS21042-08 26 Nut

MS21042-3 4 Nut

MS21266-2N 2 Grommet

MS21919WDG4 6 Clamp

MS27039-1-23 8 Screw

NAS1149F0316P 4 Washer

NAS1149F0332P 22 Washer

NAS1149FN832P 2 Washer

NAS1801-3-8 16 Screw

NAS1801-08-10 2 Screw
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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

S-151-1 4 Bracket Assembly

5418401-033 2 Strap

6029109002-005 1 Shield, Anti-Skid, LH 6029109002-003

6029109002-006 1 Shield, Anti-Skid, RH 6029109002-004

6029109003-001 1 Bracket Assembly, Upper Inboard, LH

6029109003-002 1 Bracket Assembly, Upper inboard, RH

6029109004-005 4 Bracket Assembly, Upper Outboard

6029109006-001 2 Bracket Assembly, Lower inboard

6032040001-811 2 Cover, Electrical, Forward

6032040001-812 1 Cover, Electrical, Aft, LH

6032040001-813 1 Cover, Electrical, Aft, RH

6032040001-816 1 Rayrim Edge Protection (No. 7, 15 in [38.1 cm].)

PART 

NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACEDBY

2448000-42 6 Strap Destroy When Installed Not Replaced

5418401-22 6 Strap Destroy When Installed Not Replaced

5418401-033 2 Strap Destroy 60-313 and 

Subsequent 5418401-033

MS21919WDG14 2 Clamp Destroy When Installed Not Replaced

HL70-6 4 Hi-Lok Collar Destroy All MS21042-3

GE-4580 2 Landing Light (Convex) Destroy When Installed

A/KQ4681

or

Q4681

2484021-16 2 Landing Light Cover Destroy When Installed Not Replaced

2484108-801 2 Landing Light Cover Destroy When Installed Not Replaced

51-0723-1 2 Grille Assembly Destroy When Installed Not Replaced

PART NUMBER QTY NOMENCLATURE ALTERNATE

PART NUMBER
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C. Identification Table

NOTE: * There is no direct spares replacement available. For spares replacement, order part

number shown prior to the modification, and match drill hole pattern to current aircraft

configuration.

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 main landing gear door from the door actuator. Retain attaching hardware

for installation.

NAS43DD1-16 8 Spacer Destroy When Installed Not Replaced

AN515-6R20 8 Screw Destroy When Installed MS35206-233

PART 

NUMBER NOMENCLATURE IDENTIFY TO SPARESREPLACEMENT EFFECTIVITY

12225-0065-085 Forward Stiffener, LH 6032040001-802 (* See Note) When Installed

12225-0065-086 Forward Stiffener, RH 6032040001-803 (* See Note) When Installed

12225-0065-089 Forward Stiffener, LH 6032040001-804 (* See Note) When Installed

12225-0065-090 Forward Stiffener, RH 6032040001-805 (* See Note) When Installed

12225-0065-027 Aft Stiffener, LH 6032040001-806 (* See Note) All

12225-0065-028 Aft Stiffener, RH 6032040001-807 (* See Note) All

6032040001-811 Forward Electrical Cover 6032040001-808 (* See Note) All

6032040001-812 Aft Electrical Cover, LH 6032040001-809 (* See Note) All

6032040001-813 Aft Electrical Cover, RH 6032040001-810 (* See Note) All

PART 

NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACEDBY
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B. Modification of Aircraft

NOTE: The instructions that follow are for both the left and right main landing gear.

(1) Install the outboard bracket assemblies on the aircraft (Wing Spar No. 5) as follows: (See Figure 1,

Detail A and View B-B.)

(a) Remove and discard the existing screws and washers that attach the upper and lower shuttle

valves to the aircraft.

NOTE: Do not disconnect the hydraulic lines from the upper and lower shuttle valves.

(b) If necessary, open pilot holes in the outboard bracket assemblies to a No. 10 (0.194 in) [4.92

mm] drill size.

(c) Secure the outboard bracket assemblies to the upper and lower shuttle valves using new

screws and washers. 

(2) Install the anti-skid shield as follows:

(a) Attach grommet to the anti-skid shield. (See Figure 1, Detail A.)

(b) If necessary, open pilot holes in the anti-skid shield to 0.219 in [5.56 mm] diameter.

(c) Temporarily install the anti-skid shield to the outboard bracket assemblies.

(d) Trim the edge of the anti-skid shield as necessary to clear anti-skid valve and adjacent tubing.

NOTE: Make sure to maintain minimum clearance of 1/4 inch (0.25 in) [6.35 mm] with

adjacent tubing.

(e) Deburr and apply alodine and epoxy primer to bare metal surfaces. (Refer to Chapter 20 of the

Maintenance Manual.)

(f) Install the anti-skid shield to the outboard bracket assemblies with fasteners.

(3) Locate and install the forward electrical cover on the forward stiffener as follows: (See Figure 1,

Detail A and View E-E.)

(a) Remove the existing clamps and screws that secure the electrical wire harnesses to the forward stiffener.

(b) Position the new electrical cover on the forward stiffener. (See Figure 1, View E-E.)

(c) Use a marker to transfer the hole pattern for the aft outboard fasteners that secures the forward electrical cover.

(d) Remove the cover and drill two 0.166 in [4.21 mm] dia. holes at the marked location. (See Figure 1, View E-E and Detail F.)

(e) Temporarily install the forward electrical cover to the forward stiffener at the aft hole locations.

(f) Match drill a third hole location at the forward outboard location perpendicular to the hole

located on the opposite side of the stiffener.

NOTE: Make sure to maintain minimum edge distance of 0.30 in [7.62 mm] when locating

and drilling the holes through the cover and forward stiffener.

(g) Remove the forward electrical cover from the aircraft.

(h) Locate and drill two 0.177 in [4.49 mm] dia. holes in the forward electrical cover for electrical

wire harness clamp installation. (See Figure 1, Detail G.)

(i) Deburr all drilled hole locations. (Refer to Chapter 20 of the Maintenance Manual.)

(j) Apply alodine and epoxy primer to all drilled holes. (Refer to Chapter 20 of the Maintenance

Manual.)

(k) Identify the forward stiffener. (See Paragraph 2.C.)

(l) Install clamps and attaching hardware to secure the electrical wire harness to the forward electrical cover. 
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(m) Install the forward electrical cover to the aircraft at the three mounting locations using supplied

hardware. 

(4) Install the upper inboard bracket assembly as follows: (See Figure 1, Detail C.)

(a) Temporarily install the upper inboard bracket assembly to the shield assembly with the provided hardware.

(b) Make sure the upper bracket assembly is positioned along the forward side of the forward stiffener. 

(c) On aircraft that have an existing hole location in the stiffener for mounting the upper inboard

bracket, do as follows:

1) Make sure the hole location provides for minimum edge distance of 0.30 in [7.62 mm] with

the upper inboard bracket.

2) If minimum edged distance cannot be obtained, proceed to Step 3.B.(4)(d).

3) If minimum edged distance can be obtained, use a marker to mark a hole location to

secure the upper inboard bracket assembly to the stiffener.

NOTE: Make sure to maintain a minimum edge distance of 0.30 in [7.62 mm]. (See

Figure 1, Detail C.)

4) Drill a 0.166 in [4.21 mm] hole through the upper inboard bracket assembly, the electrical

cover, and the stiffener at the marked location.

(d) On aircraft that do not have an existing hole location in the stiffener for mounting the upper

inboard bracket or where the hole location does not provide for minimum edge distance, do as

follows:

1) Use a marker to mark a new hole location to secure the upper inboard bracket assembly

to the stiffener.

NOTE: Make sure to maintain a minimum edge distance of 0.30 in [7.62 mm]. (See

Figure 1, Detail C.)

2) Drill a 0.166 in [4.21 mm] hole through the upper inboard bracket assembly, the electrical

cover, and the stiffener at the marked location.

(e) Remove the upper inboard bracket assembly and forward electrical cover from the aircraft.

(f) Deburr drilled hole locations. (Refer to Chapter 20 of the Maintenance Manual.)

(g) Apply alodine and epoxy primer to drilled holes. (Refer to Chapter 20 of the Maintenance Manual.)

(h) Identify the forward electrical cover. (See Paragraph 2.C.)

(i) Install the forward electrical cover and upper inboard bracket assembly using provided hardware. 

(5) Install clamps that support electrical wire harness as it routes inboard along the forward stiffener

using provided hardware. 

(6) Install the lower inboard bracket assembly as follows: (See Figure 1, Detail A and View D-D.)

(a) Temporarily position the lower inboard bracket assembly to the shield assembly and locate the

Hi-Loc fasteners where the inboard bracket assembly is to be installed (two places on the

lower wing spar). 

(b) Remove the Hi-Loc fastener collars from the wing spar where the inboard bracket assembly is

to be installed.

(c) If necessary, use a No. 2 drill size, to enlarge the holes in the lower inboard bracket assembly

to 0.221 in [5.61 mm].

(d) Deburr all drilled hole locations. (Refer to Chapter 20 of the Maintenance Manual.)

(e) Apply alodine and epoxy primer to drilled holes. (Refer to Chapter 20 of the Maintenance Manual.)

(f) Install the shield to the lower inboard bracket assembly as follows: 
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1) With the shield assembly loosely installed, visually check the lower inboard bracket

mounting hole location for alignment with the anti-skid shield.

2) If holes do not align, mark a new hole location on the anti-skid shield.

3) Slot or relocate the lower inboard hole in the anti-skid shield as necessary to attach the

anti-skid shield to the lower inboard bracket. Hole to be 7/32 (0.219) in [5.56 mm] diameter. Slot to be a maximum width of 0.50 in [12.70 mm].

4) Deburr all drilled and/or slotted holes and apply alodine and epoxy primer to all bare metal

surfaces. (Refer to Chapter 20 of the Maintenance Manual.)

5) Install the anti-skid shield to the lower bracket support.

(7) Modify the aft stiffener for new electrical wire harness support as follows: (See Figure 1, Detail A

and View G-G.)

(a) Remove the existing three outboard straps that support the electrical wire harness inside the

aft stiffener. Discard existing attaching hardware and straps. 

(b) On aircraft 60-001 thru 60-312, do the steps that follow: 

1) Remove the existing inboard clamp and attaching hardware that support the electrical wire

harnesses as they route inboard along the aft stiffener. Discard clamp and attaching hardware.

2) As necessary, remove electrical wire harnesses away from the aft stiffener to allow for

installation of the S-151-1 brackets.

3) Install the S-151-1 bracket assemblies on the aft stiffener. (See Figure 1 View K-K.) 

4) Identify the aft stiffener. (See Paragraph 2.C.)

(c) On aircraft 60-313 thru 60-413, remove and discard the existing inboard strap and attaching

hardware. 

(8) Locate and install the aft electrical cover and strap on the aft stiffener as follows: (See Figure 1

Detail A and View G-G.)

(a) Install rayrim edge protection on the strap. 

(b) Position the anti-skid wheel and squat switch electrical wire harnesses back inside the aft stiffener. 

(c) Secure wire harnesses in the aft stiffener using strap and supplied hardware. 

(d) Position the new aft electrical cover on the aft stiffener.

NOTE: When locating the right aft electrical cover, make sure the louver faces aft.

(e) Use a marker to transfer the (six) (6) hole pattern of the stiffener onto the aft electrical cover.

(f) Remove the aft electrical cover from the aircraft.

(g) Drill six (6) 0.166 in [4.21 mm] dia. holes at the marked locations on the aft electrical cover.

(h) Deburr all drilled hole locations. (Refer to Chapter 20 of the Maintenance Manual.)

(i) Apply alodine and epoxy primer to all drilled holes. (Refer to Chapter 20 of the Maintenance

Manual.)

(j) Install rayrim edge protection to the edge of the aft electrical cover. 

NOTE: Make sure to install the rayrim edge protection to the louvered portion of the right

aft electrical cover.

(k) As necessary for fit, remove the tie wraps from the area of the electrical wire harnesses covered by the new aft electrical cover.
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(l) Make sure the holes in the stiffener are large enough for the shank on the AN525-832R9

screws used to install the cover to pass through the stiffener.

1) If the holes in the stiffener are large enough to install all screws, proceed to Step

3.B.(8)(m).

2) If the holes are not large enough, use a 0.166 in [4.216 mm] reamer to open the holes in

the stiffener.

NOTE: Make sure that the nutplate is not damaged when hole is opened with reamer.

3) Apply alodine and epoxy primer to all bare metal. (Refer to Chapter 20 of the Maintenance

Manual.)

(m) Install the new aft electrical cover on the aircraft.

(n) Identify the aft electrical cover. (See Paragraph 2.C.)

(9) On aircraft with a convex (round) shape landing light lamp (P/N GE-4580) and/or a protective landing light lens cover installed, do as follows:

NOTE: During main landing gear retraction, the convex (round) shape landing light assembly

and/or protective lens cover will not clear the new shielding provided by this modification.

(a) Remove the protective landing light lens cover, attaching screws, spacers and nuts. Discard

attaching screws, spacers and lens cover. Retain the nuts for installation. (Refer to Chapter 33

of the Maintenance Manual.)

(b) Remove and discard the convex (round) landing light lamp. (Refer to Paragraph 1.H.(1) for

landing light lamp parts required.) (Refer to Chapter 33 of the Maintenance Manual.)

(c) Install the new flat landing light lamp with MS35206-233 screws and retained nuts. (Refer to

Paragraph 1.H.(1) for landing light lamp parts required.) (Refer to Chapter 33 of the Maintenance Manual.)

(10) Make sure all electrical wire harnesses affected by this modification have been secured and supported.

(11) Make sure all hardware used to install the shield assembly, brackets and straps have been tightened to the proper torque values. (Refer to Chapter 20 of the Maintenance Manual.)

C. Functional Test/Operational Check

(1) Use retained attaching hardware to connect the inner main landing gear door to the door actuator.

(2) Disconnect the outer main landing gear door push rod from the main landing gear strut assembly.

Retain attaching hardware for installation.

(3) Connect the batteries to the aircraft. (Refer to Chapter 24 of the Maintenance Manual.)

(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.)

NOTE: Apply hydraulic pressure to the gear incrementally starting at zero (0) PSI and

increase cart pressure slowly to cycle the landing gear.

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. 
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(6) Slowly retract and extend the main landing gear and check for clearance between the landing light

lens, hydraulic lines and electrical wire harnesses with the new shielding. (Refer to Chapter 32 of

the Maintenance Manual.)

(7) Use retained attaching hardware to connect the outer main landing gear door push rod to the main

landing gear strut assembly.

D. Return Aircraft to Airworthy Status

(1) With the landing gear fully extended and locked, 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.)

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 8)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 2 of 8)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 3 of 8)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 4 of 8)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 5 of 8)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 6 of 8)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 7 of 8)
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Installation of the Main Landing Gear Shielding Improvements

Figure 1 (Sheet 8 of 8)