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b

THIS SERVICE BULLETIN IS AVAILABLE AT:

www.cic.bombardier.com

Basic Issue: Feb 13/07

Refer to applicable government agency regulations and requirements and make sure that the work described 

in this Service Bulletin 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. 

© 2007, Bombardier Inc. All rights reserved. Challenger*, Global Express*, Learjet*, are Trademarks of Bombardier Inc.

LEARJET 45

RECOMMENDED

SB 45-71-5

SERVICE BULLETIN

If you cannot do all steps in this service bulletin 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.

POWER PLANT - MODIFICATION OF THE LEFT AND RIGHT ENGINE WIRE ROUTING AND

CLAMPING

1. Planning Information

A. Effectivity

(1) Learjet 45-005 thru 45-319, and 45-321.

B. Reason

(1) The purpose of this modification is to improve the routing and clamping of the left and right engine

alternator wire harnesses and the starter/generator wire bundles to prevent chafing. An inspection

to reveal possible chafing between the left engine hydraulic and fuel tubes is also necessary.

NOTE: Aircraft that have previously installed the left engine hydraulic pump case drain tube

part number 4529101090-005 tube per Learjet Service Bulletin A45-29-15 are not

required to replace the tube as instructed in this service bulletin. 

CONTACT INFORMATION DISTRIBUTION 

DATE

Business Aircraft

Learjet Inc.

MS 53

P.O. Box 7707

Wichita, Kansas 67277-7707

(316) 946-2421

February 13, 2007
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LEARJET 45

SERVICE BULLETIN

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Basic Issue: Feb 13/07

C. Description

(1) This service bulletin provides instructions to change the routing and clamping configuration of the

engine and alternator wire harnesses, and the starter/generator wire bundles. Instructions are also

provided to inspect specific hydraulic tubes located within the left engine nacelle for chafing

between the adjacent fuel tubes, to replace tubes damaged beyond acceptable limits, and to

secure the hydraulic tubes with additional clamps.

D. Compliance

(1) Recommended - Bombardier Learjet Inc. recommends that you do this service bulletin in less than

300 flight hours from the initial distribution date of this service bulletin.

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.

G. Expense Coverage

(1) Labor Coverage

(a) Aircraft in the new aircraft warranty period, labor coverage is provided.

NOTE: For labor coverage to apply, you must do this service bulletin at a Bombardier

Business Aviation Service Facility or at a Bombardier Learjet Authorized Service

Facility. You must do this service bulletin within 24 months from the release date

of this service bulletin, basic issue, February 13, 2007.

(b) Aircraft out of the new aircraft warranty period, no labor coverage is provided.

-801 

KIT

-802 

KIT TASK

1.0 1.0 Labor hours to gain access.

3.5 4.0 Labor hours to do the aircraft modification.

1.5 1.5 Labor hours to do a functional test/operational check.

1.0 1.0 Labor hours to return the aircraft to airworthy status.

7.0 7.5 Total Labor Hours
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SERVICE BULLETIN

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Basic Issue: Feb 13/07

(2) Material Coverage

(a) Aircraft in the new aircraft warranty period, material coverage is provided.

NOTE: For material coverage to apply, this service bulletin kit must be placed on order

from Bombardier within 12 months from the basic issue distribution date of this

service bulletin, February 13, 2007.

(b) Aircraft out of the new aircraft warranty period, no material coverage is provided.

(3) Smart Parts 

(a) For those aircraft in the new aircraft warranty period at the time of service bulletin distribution,

Smart Parts Plus does not pay for the kits at any time.

(b) For those aircraft out of the new aircraft warranty period at the time of service bulletin distribution, Smart Parts Plus pays for the kits for up to 12 months from the service bulletin distribution

date.

H. Material Required to do this Service Bulletin

NOTE: The above price can change. 

To place an order for these kits, please call Bombardier Aerospace Parts Logistics Business Aircraft Customer Service at 1-888-222-1428 in North America or 1-316-946-2377

outside North America for information.

Refer to paragraph 3.A. to know which kit is necessary.

(1) Other materials/parts necessary to do this service bulletin.

NOTE: To place an order for these materials, please call Bombardier Aerospace Parts Logistics Business Aircraft Customer Service at 1-888-222-1428 in North America or 1-316-

946-2377 outside North America for information.

PART NUMBER QTY NOMENCLATURE PRICING

4571530001-801 1 Service Bulletin Kit $108.00

4571530001-802 1 Service Bulletin Kit $80.45

PART NUMBER NAME QTY MANUFACTURER

361 Tape-Fiberglass 1 Roll 3-M Company, St. Paul, MN

MIL-T-43435E 

or equivalent

String Tie As Required Commercially Available

Red GLPT Insulating Varnish As Required Commercially Available
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LEARJET 45

SERVICE BULLETIN

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Basic Issue: Feb 13/07

(2) Other materials/parts that may be necessary to do this service bulletin based on inspection results.

NOTE: * Required on aircraft that have not installed the 4529101090-005 left engine 

hydraulic pump case drain tube per Learjet Service Bulletin A45-29-15. 

To place an order for these parts, please call Bombardier Aerospace Parts Logistics

Business Aircraft Customer Service at 1-888-222-1428 in North America or 1-316-

946-2377 outside North America for information.

I. Tooling

(1) None.

J. Weight and Balance

(1) Change in basic weight and moment.

K. References

(1) Learjet Maintenance Manual, Chapters 12, 20, 24, 28, 29, 71 and 80.

PART NUMBER QTY NOMENCLATURE EFFECTIVITY

4529101067-001 1 Tube-Hydraulic

(Pressure)

45-005 thru 45-267

4529101071-001 1 Tube-Hydraulic

(Pump Supply)

45-005 thru 45-267

4529101075-001 1 Tube-Hydraulic

(Pump Case Drain)

45-006 thru 45-076

4529101075-005 1 Tube-Hydraulic

(Pump Case Drain)

45-005, 45-077 thru 

45-267

4529101090-005 1 Tube-Hydraulic

(Pump Case Drain)

All

* See Note Below

4573100000V13-001 1 Tube-Fuel

(Motive Flow)

45-005 thru 45-267

4573100000V12-001 1 Tube-Fuel (Supply) 45-005 thru 45-267

CHANGE IN BASIC WEIGHT CHANGE IN BASIC MOMENT

Plus (+) 1.17 pounds Plus (+) 608.4 inch-pounds
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LEARJET 45

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Basic Issue: Feb 13/07

2. Accomplishment Instructions

A. Gain Access

(1) Disconnect the external electrical power and the main and emergency batteries from aircraft.

(Refer to Learjet Maintenance Manual, Chapter 24.)

(2) On aircraft 45-005 thru 45-274, remove the left and right engine upper and lower engine cowling.

(Refer to Learjet Maintenance Manual, Chapter 71.)

(3) On aircraft 45-275 thru 45-319 and 45-321, remove the left engine lower cowling. (Refer to Learjet

Maintenance Manual, Chapter 71.)

B. Modification of Aircraft

(1) On aircraft 45-005 thru 45-274, disconnect the left engine starter/generator wire bundles and

remove the clamping as follows; 

(a) Disconnect starter/generator wire bundles (G1-B "+" and G1-E "-") from the starter/generator. 

(b) Disconnect engine wire harnesses (G1 and G1P1) from the starter/generator. 

(c) Disconnect alternator wire harness (G3P2) from the alternator.

(d) Remove the existing clamping configuration of the starter/generator wire bundles at nacelle

station 180.00. (See Figure 1, View C-C.)

(2) On aircraft that have not installed the 4529101090-005 left engine hydraulic pump case drain tube

per Learjet Service Bulletin No. A45-29-15, replace the 4529101090-001 left engine hydraulic

pump case drain tube with a new 4529101090-005 tube. (See Figure 1, View L-L.) 

(3) On aircraft 45-005 thru 45-267, inspect the remaining hydraulic tubing on the left engine for clearance as follows;

(a) Inspect the hydraulic tubing for clearance and chafing in the area shown. (See Figure 1, View

K-K and Detail M.) (Refer to Learjet Maintenance Manual, Chapter 20 for damage tolerance

on tubing.)

CAUTION: REVIEW THE SAFETY PRACTICES WHEN YOU WORK WITH OR AROUND

THE AIRCRAFT HYDRAULIC SYSTEM. (REFER TO LEARJET MAINTENANCE MANUAL, CHAPTER 29.)

(b) On aircraft where chafing on the hydraulic tubes is beyond acceptable limits, do as follows;

1) Depressurize the hydraulic system. (Refer to Learjet Maintenance Manual, Chapter 12.)

2) Replace the chafed tubing.

(c) Install additional clamping to the hydraulic tubing. (See Figure 1, Detail M.)

(d) Inspect the adjacent fuel tubing for interference with the hydraulic tubing.

CAUTION: REVIEW THE SAFETY PRACTICES WHEN YOU WORK WITH OR AROUND

THE AIRCRAFT FUEL SYSTEM. (REFER TO LEARJET MAINTENANCE MANUAL, CHAPTER 28.)

(e) On aircraft where interference between the fuel tubing and hydraulic tubing is found, replace

the fuel tubing as noted and shown. (See Figure 1, View K-K.)

(4) On aircraft 45-268 thru 45-319 and 45-321, inspect the remaining left engine hydraulic tubing for

clearance with adjacent tubing, structure, and other components.
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Basic Issue: Feb 13/07

(5) On aircraft 45-005 thru 45-274, change the routing and clamping of the left engine starter/generator wire bundles as follows;

(a) Route the starter/generator wire bundles and the engine wire harness (G1 and G1P1)

between the engine and the hydraulic pump. (See Figure 1, Detail B.)

NOTE: The starter/generator wire bundles should be next to the engine and inboard of

the thrust reverser hydraulic plumbing coming through nacelle station 180.00.

(b) On aircraft 45-005 thru 45-049, make sure the length of the starter/generator wire bundles is

sufficient to be routed and clamped as shown. See Figure 1, View A-A, Detail D, Detail E, View

F-F and View G-G.)

(c) On aircraft 45-005 thru 45-049 where the length of the starter/generator wire bundles is sufficient, and aircraft 45-050 thru 45-274, route and clamp the starter/generator wire bundles as

shown. (See Figure 1, View A-A, Detail D, Detail E, View F-F and View G-G.)

(d) On aircraft 45-005 thru 45-049 where the length of the starter/generator wire bundles is not

sufficient, replace clamps MS21919WH12 with MS21919WCH11 at existing clamp locations

that secure the positive (+) starter/generator bundle (G1-B).

(e) Route and clamp the starter/generator wire bundles at nacelle station 186.00 as shown. (See

Figure 1, View H-H and View J-J.)

(f) Individually wrap the starter/generator wire bundles with MIL-I-22129 or equivalent spiral wrap

as shown. (See Figure 1, Detail B and View C-C.)

NOTE: Make sure that the minimum clearance requirements are maintained between the

spiral wrapped starter/generator wire bundles and adjacent tubing and components. (Refer to Learjet Maintenance Manual, Chapter 20 for clearance requirements.)

(g) Connect the starter/generator wire bundles (G1-B "+" and G1-E "-") to the starter/generator.

(h) Starting immediately forward of nacelle station 186.00, apply MIL-I-22129 or equivalent spiral

wrap to engine wire harnesses (G1 and G1P1), and alternator wire harness (G3P2) as shown.

(See Figure 1, View H-H and View J-J.)

NOTE: At the location where alternator wire harness (G3P2) begins to route toward the

alternator, discontinue spiral wrapping the engine wire harnesses (G1 and G1P1).

Continue the spiral wrap on alternator wire harness (G3P2) up to the alternator.

(i) Connect the engine wire harnesses (G1 and G1P1) to the starter/generator.

(j) Use MIL-T-43435E or equivalent string tie to secure the spiral wrap to the harnesses.

(6) On aircraft 45-005 thru 45-274, change the routing and clamping of the left engine alternator wire

harnesses (G3P1 and G3P2) as follows;

(a) Route alternator wire harness (G3P2) along the starter/generator wire bundles and secure to

starter/generator wire bundles as shown. (See Figure 1, View C-C, View H-H and View J-J.)

(b) Connect alternator wire harness (G3P2) to the alternator.

(c) Disconnect alternator wire harness (G3P1) from the alternator. 

(d) Route the alternator wire harness (G3P1) as shown. (See Figure 1, View K-K.)
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Basic Issue: Feb 13/07

(e) Wrap alternator wire harness (G3P1) with fiberglass tape at bracket assemblies as shown.

(See Figure 1, View K-K.)

(f) Install new clamping configuration on alternator wire harness (G3P1) as shown. (See Figure 1,

View K-K.)

(g) Connect alternator wire harness (G3P1) to the alternator.

(h) Apply MIL-I-22129 spiral wrap or equivalent around alternator wire harness (G3P1) as necessary. (See Figure 1, View K-K.)

NOTE: Make sure that the minimum clearance requirements are maintained between the

spiral wrapped alternator wire harnesses and adjacent tubing and components.

(Refer to Learjet Maintenance Manual, Chapter 20 for clearance requirements.)

(i) Use MIL-T-43435E or equivalent string tie to secure the spiral wrap to the harnesses.

(7) On aircraft 45-005 thru 45-274, change the routing and clamping configuration of the right engine

starter/generator wire bundles and alternator wire harnesses as follows;

(a) Disconnect alternator wire harnesses (G3P1 and G3P2) from the alternator.

(b) Remove the clamps and attaching hardware that support alternator wire harnesses (G3P1 and

G3P2) to nacelle station 180.00. (See Figure 2, View C-C.)

(c) Disconnect the engine wire harness (G1 and G1P1) from the starter/generator. 

(d) On aircraft 45-005 thru 45-048, install the new clamping configuration as shown. (See Figure

2, View D-D, View E-E, View G-G, and View H-H.)

(e) On aircraft 45-049 thru 45-273, install the new clamping configuration as shown, (See Figure

2, View D-D, View E-E, View F-F, View G-G, View H-H and View J-J.)

(f) Route alternator wire harnesses (G3P1 and G3P2) and engine wire harnesses (G1 and G1P1)

as shown. (See Figure 2, Detail B and View C-C.)

NOTE: Wire harnesses must be routed between the engine and the hydraulic pump.

(g) Apply MIL-I-22129 spiral wrap or equivalent to the alternator wire harnesses (G3P1 and

G3P2) and engine wire harnesses (G1 and G1P1) as shown. (See Figure 2, Detail B and View

C-C.)

NOTE: Make sure that the minimum clearance requirements are maintained between the

spiral wrapped alternator and engine wire harnesses and adjacent tubing and

components. (Refer to Learjet Maintenance Manual, Chapter 20 for clearance

requirements.)

(h) Install new clamping configuration on alternator wire harness (G3P1) as shown. (See Figure 2,

View C-C.)

(i) Use MIL-T-43435E or equivalent string tie to secure the spiral wrap to the harnesses.

(j) Route alternator wire harness (G3P2) along alternator wire harness (G3P1) and tie together

with MIL-T-43435E string tie or equivalent. Apply insulating varnish to secure string ties. (See

Figure 2, View C-C.)

(k) Connect alternator wire harnesses (G3P1 and G3P2) to the alternator.
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Basic Issue: Feb 13/07

(l) Connect engine wire harnesses (G1 and G1P1) to the starter/generator. 

NOTE: It is permissible to fold and tie engine wire harness (G1P1) as necessary to take

up excessive length.

(8) On aircraft 45-005 thru 45-274, do an inspection of the clearances between the wire harnesses

and the hydraulic and fuel tubing on the left and right engines. (Refer to Learjet Maintenance Manual, Chapter 20.)

(9) On aircraft 45-275 thru 45-319 and 45-321, do an inspection of the clearances between the wire

harnesses and the hydraulic and fuel tubing on the left engine. (Refer to Learjet Maintenance Manual, Chapter 20.)

(10) On aircraft that replaced hydraulic tubes due to chafing, service the hydraulic system reservoir.

(Refer to Learjet Maintenance Manual, Chapter 12.)

C. Functional Test/Operational Check

(1) Connect the main and emergency batteries to the aircraft. (Refer to Learjet Maintenance Manual,

Chapter 24.)

(2) Connect external electrical power.

(3) Do the Automatic Engine Start for the left and right engines. (Refer to Learjet Maintenance Manual, Chapter 80.)

(4) Do the Generator Voltage Adjustment and Current Test. (Refer to Learjet Maintenance Manual,

Chapter 24.)

(5) On aircraft that replaced hydraulic or fuel tubes, check new tubes for leaks around fittings.

D. Return Aircraft to Airworthy Status

(1) Install the left and right engine upper and lower engine cowling. (Refer to Learjet Maintenance

Manual, Chapter 71.)

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.

NOTE: To complete the aircraft maintenance records, refer to FAR/CFR 43.9.

3. Material Information

A. Parts Required

(1) The 4571530001-801 Kit is for the left engine and contains the parts that follow.

PART NUMBER QTY NOMENCLATURE

MS9592-014 1 Bracket

MS9592-387 1 Bracket

MS21919WCH4 2 Clamp
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Basic Issue: Feb 13/07

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.

MS21919WCH5 2 Clamp

MS21919WCH10 1 Clamp

MS21919WCH11 5 Clamp

MS85052/3-6 1 Clamp

MS85052/3-8 1 Clamp

NAS1802-3-7 1 Screw

NAS1802-3-8 4 Screw

MS21042-3 4 Nut

NAS1149C0316R 1 Washer

SWT1/2Natural 15 ft. Spiral Wrap (MIL-I-22129)

PART NUMBER QTY NOMENCLATURE
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Basic Issue: Feb 13/07

(2) The 4571530001-802 Kit is for the right engine and contains the parts that follow.

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

PART NUMBER QTY NOMENCLATURE

MS9592-010 3 Bracket

MS9592-022 1 Bracket

AN743-C12 1 Bracket

MS21919WCH5 1 Clamp

MS21919WCH9 3 Clamp

MS21919WCH11 4 Clamp

NAS1802-3-8 3 Screw

MS21042-3 3 Nut

SWT1/2Natural 15 ft. Spiral Wrap (MIL-I-22129)

PART NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY

AN743-12 1 Bracket Destroy 45-006, 45-008 thru 45-023 

(RH Engine)

MS9592-010 2 Bracket Destroy 45-005 thru 45-274

(Both Engines)

MS9592-010 1 Bracket Destroy 45-005 thru 45-049

(LH Engine)

MS21919WH4 2 Clamp Destroy 45-005 thru 45-274

(RH Engine)

MS21919WH5 1 Clamp Destroy 45-005, 45-007, 45-024 thru 

45-048 (RH Engine) 

MS21919WH5 2 Clamp Destroy 45-005 thru 45-274

(RH Engine)

MS21919WH7 2 Clamp Destroy 45-049 thru 45-274 

(RH Engine)

MS21919WH8 1 Clamp Destroy 45-005, 45-007, 45-024 thru 

45-048 (RH Engine) 

MS21919WH8 2 Clamp Destroy 45-049 thru 45-274 

(RH Engine)
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SERVICE BULLETIN

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MS21919WH10 1 Clamp Destroy 45-005 thru 45-274

(LH Engine)

MS21919WH12 4 Clamp Destroy 45-005 thru 45-274 

(RH Engine)

MS21919WH12 5 Clamp Destroy 45-005 thru 45-274 

(LH Engine)

NAS1802-3-8 2 Screw Destroy 45-005 thru 45-274 

(RH Engine)

NAS1802-3-9 2 Screw Destroy 45-005 thru 45-274

(LH Engine)

NAS43DD3-64FC 1 Spacer Destroy 45-005 thru 45-274

(LH Engine)

MS21042-3 1 Nut Destroy 45-005 thru 45-274

(LH Engine)

4529101067-001 1 Tube-Hydraulic

(Pressure)

Destroy 45-005 thru 45-267

* See Note Below

(LH Engine)

4529101071-001 1 Tube-Hydraulic

(Pump Supply)

Destroy 45-005 thru 45-267

* See Note Below

(LH Engine)

4529101075-001 1 Tube-Hydraulic

(Pump Case Drain)

Destroy 45-006 thru 45-076

* See Note Below

(LH Engine)

4529101075-005 1 Tube-Hydraulic

(Pump Case Drain)

Destroy 45-005, 45-077 thru 45-267

* See Note Below

(LH Engine)

4529101090-001 1 Tube-Hydraulic

(Pump Case Drain)

Destroy All

* * * See Note Below

(LH Engine)

4528200044-001 1 Tube-Fuel

(Motive Flow) 

Destroy 45-005 thru 45-267

* * See Note Below

(LH Engine)

4573100005V1-005 1 Tube-Fuel (Supply) Destroy When Installed

* * See Note Below

(LH Engine)

PART NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY
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Basic Issue: Feb 13/07

NOTE: * On aircraft 45-005 thru 45-267, replace hydraulic tubes as necessary that have

 chafing beyond acceptable limits.

* * On aircraft 45-005 thru 45-267, replace fuel tubes as necessary to correct or prevent

 an interference condition with the adjacent hydraulic tubes.

* * * Aircraft that have not installed the 4529101090-005 left engine hydraulic pump case

 drain tube per Learjet Service Bulletin No. A45-29-15.

4573100005-009 1 Tube-Fuel (Supply) Destroy When Installed

* * See Note Below

(LH Engine)

4573100000V5-001 1 Tube-Fuel (Supply) Destroy When Installed

* * See Note Below

(LH Engine)

4573100000V8-001 1 Tube-Fuel (Supply) Destroy When Installed

* * See Note Below

(LH Engine)

4573100005-013 1 Tube-Fuel (Supply) Destroy When Installed

* * See Note Below

(LH Engine)

PART NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY
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Basic Issue: Feb 13/07

Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 1 of 9)
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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 2 of 9)
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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 3 of 9)
SB 45-71-5

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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 4 of 9)
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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 5 of 9)
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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 6 of 9)
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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 7 of 9)
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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 8 of 9)
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Left Engine Wire Harness Routing and Clamping

Figure 1 (Sheet 9 of 9)
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Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 1 of 9)
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Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 2 of 9)
SB 45-71-5

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Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 3 of 9)
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Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 4 of 9)
SB 45-71-5

Page 26 of 30

LEARJET 45

SERVICE BULLETIN

THIS SERVICE BULLETIN IS AVAILABLE AT:

www.cic.bombardier.com

Basic Issue: Feb 13/07

Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 5 of 9)
SB 45-71-5

Page 27 of 30

LEARJET 45

SERVICE BULLETIN

THIS SERVICE BULLETIN IS AVAILABLE AT:

www.cic.bombardier.com

Basic Issue: Feb 13/07

Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 6 of 9)
SB 45-71-5

Page 28 of 30

LEARJET 45

SERVICE BULLETIN

THIS SERVICE BULLETIN IS AVAILABLE AT:

www.cic.bombardier.com

Basic Issue: Feb 13/07

Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 7 of 9)
SB 45-71-5

Page 29 of 30

LEARJET 45

SERVICE BULLETIN

THIS SERVICE BULLETIN IS AVAILABLE AT:

www.cic.bombardier.com

Basic Issue: Feb 13/07

Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 8 of 9)
SB 45-71-5

Page 30 of 30

LEARJET 45

SERVICE BULLETIN

THIS SERVICE BULLETIN IS AVAILABLE AT:

www.cic.bombardier.com

Basic Issue: Feb 13/07

Right Engine Wire Harness Routing and Clamping

Figure 2 (Sheet 9 of 9)
SERVICE BULLETIN COMPLIANCE RESPONSE 

It is necessary that Bombardier Learjet record aircraft having complied with this 

Service Bulletin. Please fill in the Service Bulletin 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 Service 

Bulletin, 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

Mailing Information: 

Bombardier Learjet 

Maintenance Engineering 

(MS #78) (FAX 316 946-2305) 

fracas_usa@aero.bombardier.com 

Customer Support 

Learjet, Inc.

Service Bulletin Information Aircraft Information 

Service Bulletin No. 45-71-5 Model 

Rev No. Basic Date February 13, 2007 Serial No. 

Service Facility Information Flight Hours 

Facility Incorporating Bulletin Landings 

Compliance Information 

The above referenced Service Bulletin was complied with on the referenced serial number aircraft at the listed aircraft flight 

hours/landings: 

Actual hours to accomplish Service Bulletin: Access _______ SB _______ Test(s) _______ Restore _______ 

Signature Title Date 

Comments

SERVICE BULLETIN EVALUATION SHEET

YOUR COMMENTS WILL HELP US IMPROVE OUR 

SERVICE BULLETINS 

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SERVICE BULLETIN 45-71-5 REVISION: Basic DATED: February 13, 2007 

TITLE: Modification of the Left and Right Engine Wire Routing and Clamping 

LEARJET CONTACT INFORMATION TELEPHONE: (316) 946-2421 FACSIMILE: (316) 946-2002 

HOW EASY IS THE BULLETIN TO UNDERSTAND? POOR FAIR GOOD VERY 

GOOD

EXCELLENT

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KNOW ABOUT THE JOB? 

 

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WAY TO DO THE JOB? 

 

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(S), FIGURE (S) AND/OR KIT DRAWING (S)? 

 

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Actual hours to accomplish Service Bulletin: Access _______ Modify _______ Test(s) _______ Restore _______ 

PLEASE SUPPLY THE FOLLOWING 

DATA: 

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OPERATOR: TELEPHONE:

AIRCRAFT: FACSIMILE:

UPON COMPLETION OF THE EVALUATION FORM, PLEASE FAX TO (316) 946-2002 OR FOLD AND RETURN TO 

ADDRESS ON THE REVERSE SIDE.