# b

THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com Refer to applicable government agency regulations and requi rements and make sure that the work described in this publication is performed in compliance with manufac turer’s recommendations and/or acceptable industry standards. This document is proprietary to Bombardi er Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior wr itten consent of Bombardier Inc. and/or its affiliates. © 2009, Bombardier Inc. All rights reserved. Challenger*, Global Express*, Learjet* , are Trademarks of Bombardier Inc. SB 40-71-04 Page 1 of 32 Basic Issue: Dec 7/09 

### 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 Logistics or push 4 then push 1 for Technical Publications. December 7, 2009 

### LEARJET 40 SB 40-71-04 Recommended

If you cannot complete the instructio ns 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 APPROVED IN WHITE

POWERPLANT - REPLACEMENT OF THE LEFT ENGINE FUEL AND HYDRAULIC TUBING AND INSTALLATION OF TUBI NG SUPPORT CHANNEL 1. Planning Information A. Effectivity (1) Learjet 45-2001 thru 45-2126. NOTE: You must do Learjet Service Bulletin No. 40-71-02, “Modification of the Left and Right Engine Wire Routing and Clamping” before or at the same time you complete these instructions. The effectivity of Learjet Servic e Bulletin 40-71-02 will tell you if it is applicable to your aircraft. B. Reason (1) The left engine hydraulic/fuel lines can contact ea ch other and structure. If not corrected, chafing of these lines could result in loss of hydraulic fluid and fuel. Completing this service bulletin will provide better support and clamping to maintain the proper clearance of the hydraulic/fuel lines routed between the engine firewall, engine driv en hydraulic pump and the engine driven motive flow fuel pump.THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 2 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin C. Description (1) This service bulletin provides in structions to replace the left engine hydraulic lines and fuel lines and install a support channel to provide better clamping and maintain proper clearance between the hydraulic and fuel lines. D. Compliance (1) Recommended - Bombardier Learjet Inc. recommend s that you complete these instructions in less than 300 flight hours or 12 months from the initial distribution date of this publication, whichever occurs first. E. Approval (1) The Federal Aviation Administration (FAA) has ap proved the technical content in this publication that has an affect on the airplane type design. NOTE: This Service Bulletin (Basic Issue) is approved as an alternate method of compliance with AD 2009-11-13, Paragraphs g, h, i and j, by the Manager, Wichita Aircraft Certification Office, ACE-115W, by letter number L115W-09-1145. (2) The European Aviation Safety Agency (EASA) has accepted the technical content in this publication that has an affect 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 personnel capabilities may caus e the labor ho urs 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 ti tle page of this document for contact information.) ‐ 801 KIT TASK 2.5 Labor hours to gain access. 18.5 Labor hours to do the aircraft modification. 1.5 Labor hours to do a functional test/operational check. 1.5 Labor hours to return the aircraft to airworthy status. 24.0 Total Labor HoursTHIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 3 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin G. Expense Coverage (1) Labor Coverage - Labor coverage applies to all aircraft affected by this publication. NOTE: For labor coverage to apply, you must complete these instructions at a Bombardier Business Aviation Service Fa cility or at a Bombardier Learjet Authorized Service Facility. You must complete these instructions within 24 months from the Basic Issue distribution date of this p ublication, December 7, 2009. (2) Material Coverage (a) Aircraft in the new aircraft warranty period , material covera ge is provided.NOTE: For material coverage to apply, you must place an order for this kit from Bombardier Learjet within 12 months from the Basi c Issue distribution date of this publication, December 7, 2009. (b) Aircraft out of the new warranty period , no material coverage is provided. (3) Smart Parts Plus Coverage (a) On aircraft in the new aircraft warranty peri od at the time of serv ice bulletin distribution , Smart Parts Plus does not pay for the kit necessary to do this service bulletin at any time. (b) On aircraft out of the new aircra ft warranty period at the time of service bulletin distribution , Smart Parts Plus pays for the kit necessary to do this service bulletin for up to 12 months from the Basic Issue distribution date of this service bulletin. H. Material Required

NOTE: The above price can change. For ordering and shipping information, please call Bombardier Aerospace, Learjet Inc. Business Aircraft Customer Service, Parts Logist ics. (Refer to the title page of this document for contact information.) (1) Other materials/parts that may be necessary if the fuel supply manifold assembly shows signs of galling during the repl acement of the main fuel supply line.

PART NUMBER QTY NOMENCLATURE PRICING 4571430001

‐ 801 1 Service Bulletin Kit $14, 739.95

PART NUMBER NOMENCLATURE QTY NOTES 4573100000V3

‐ 1 (* See note) Manifold Assembly 1 Required if existing manifold is galled. MS29513

‐ 118 (* See note) O

‐ Ring 1 Part of the manifold installation. MS29512

‐ 04 (* See note) O

‐ Ring 1 Part of the manifold installation.THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 4 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

NOTE: * Before ordering these parts required to replace the fuel manifold assembly, makesure the inspection of the manifold assembly threads reveals damage caused by galling. 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) Special tools and equipment necessary to complete these instructions.

J. Weight and Balance (1) Change in basic weight and moment.

K. References (1) Learjet Maintenance Manual, Chapters 6, 12, 20, 24, 28, 29, 71 and 80. (2) Airplane Flight Manual. L. Other Publications Affected (1) Learjet Illustrated Parts Catalog, Chapter 28 and 29. 2. Accomplishment Instructions A. Gain Access (1) Depressurize the main hydraulic system. (Refer to Chapter 12 of the Maintenance Manual .) (2) Push and release the L Engine Fire switch to close the firewall shutoff valves. N385

‐ 9028 Liquid ‐ Moly NV Thread Compound or Equivalent 1 Obtain Locally

Dapco 2200 Primerless Firewall Sealant As Required Obtain Locally

00116 LPS 2 Penetrating Oil or Equivalent As Required LPS Laboratories Inc. Tucker, GA 30025 EC

‐ 1252 Torque Putty As Required 3M Co. Minneapolis, MN

NOMENCLATURE QTY USAGE NOTES 7/32” Wrench (7 to 8 inches in length) 1 Used to remove and install fasteners located on the firewall fuel supply tube assembly flange Obtain Locally

CHANGE IN BASIC WEIGHT CHANGE IN BASIC MOMENT Plus (+) 1.02 pounds Plus (+) 506.3 inch

‐ pounds PART NUMBER NOMENCLATURE QTY NOTESTHIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 5 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (3) Disconnect external electrical power and the main and emergency batteries from the aircraft. (Refer to Chapter 24 of the Maintenance Manual .) (4) Remove the left lower engine cowling (450CL) fr om the aircraf t. (Refer to Chapter 71 of the Maintenance Manual .) (5) Remove the left upper engine cowling (450AL) from the aircraft. (Refer to Chapter 71 of the Maintenance Manual .) (6) Remove the left lower forward pylon panel (340DL). (Refer to Chapter 6 of the Maintenance Manual .) (7) Remove the left upper forward pylon panel (340AL). (Refer to Chapter 6 of the Maintenance Manual .) (8) Remove the left alternator (G3) from the aircraft. (Refer to Chapter 24 of the Maintenance Manual .) (9) Remove the left starter/generator (G1) from the aircraft. (Refer to Chapter 24 of the Maintenance Manual .) B. Modification of Aircraft CAUTION: TO PREVENT DAMAGE TO AIRCRA FT AND INJURY TO PERSONNEL MAKE SURE TO DEPRESSURIZE THE AIRCRAFT HYDRAULIC SYSTEM, AND COMPLY WITH ALL THE SAFETY PRECAUTION S OUTLINED IN CHAPTERS 28 AND 29 OF THE AIRCRAFT MAINTENANCE MANUAL. (1) Spray the fuel supply manifold assembly fitting with penetrating oil.NOTE: The penetrating oil is used to help aid in the loosening of the fuel supply tube assembly from the fuel supply manifold assembly. (2) Inspect the fuel supp ly manifold assembly for galling as follows: (See Figure 1 , Detail B.) (a) Disconnect the nacelle fuel supply tube assembly fitting from the fuel supply manifold assembly. (b) Inspect the fuel supply manifold assembly threads for any signs of galling. NOTE: If galling is presen t on the threads of the fuel su pply manifold assembly, place an order for a new manifold assembly as soon as possible. Have the new fuel supply manifold assembly shipped next day air to avoid additional airc raft down time due to parts delay. (Refer to Paragraph 1.H.(1).) (3) Remove all nacelle/firewall flexible fuel and hy draulic hoses and tube assemblies listed in Paragraph 3.B. Parts Removed List. (See Figure 1 , Details A and C.) NOTE: Retain large hardware (nuts and washers) that secures the fuel and hydraulic tubes to the engine firewall. Discard all clamps and associated attaching hardware. New clamps and attaching hardware are supplied in the service bulletin kit for all new fuel and hydraulic tubes required to complete these instructions. When disconnecting the fuel and hydraulic tubes and flexible ho ses, make sure to place a container under the affected tubes and flexible hoses to catch any residual fluid. (4) After the removal of the firewall fuel supply tube assembly, clean the old residual firewall sealant from the engine firewall.THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 6 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (5) Replace the existing rivets on the lower engine inlet bulkhead flange. (See Figure 1 , View D-D and Detail M.) NOTE: The new rivets are installed double flushed with the head of the rivets installed on the inboard side of the lower engine inlet bulkhead flange. These rivets are required to be shaved after installation on the engine inlet bulkhead flange. (6) Apply alodine and epoxy primer to all ba re metal at the rivet location. (Refer to Chapter 20 of the Maintenance Manual .) (7) Install the forward and aft nacelle bracket assemblies as follows: (See Figure 1 , Views E-E and FF.) (a) Remove the bolt and washer from the engine flange at the location where the aft nacelle bracket assembly is to be insta lled. Discard the bolt and washer. NOTE: The engine flange bolt location is the fourth (4th) bolt from the bottom engine flange centerline, moving clockwise when looking aft at the engine flange. (b) Install the aft nacelle bracket assembly onto the engine flange using new bolt and washer. (c) Temporarily install the channel assembly onto the forward and aft nacelle bracket assemblies to determine the proper location of the forward nacelle bracket assembly. (d) Temporarily position the forward nacelle brac ket assembly onto the lo wer engine inlet bulkhead assembly. (See Figure 1 , View E-E.) NOTE: It is acceptable to use double back tape to temporarily position the forward nacelle bracket onto the lower engine inlet bulkhead assembly for location of the forward nacelle bracket assembly. CAUTION: WHEN DRILLING THROUGH TH E LOWER ENGINE INLET BULKHEAD ASSEMBLY, MAKE SURE TO USE A DRILL STOP TO PREVENT DAMAGE TO THE THRUST REVERSER HYDRAU LIC LINES LOCATED BEHIND THE LOWER ENGINE BULKHEAD ASSEMBLY. (e) When proper location of the forward nacelle bracket assembly is determined, remove the channel assembly and drill three #40 pilot holes (0.098 in [2.5 4 mm]) through the lower engine inlet bulkhead assembly using the forward nacelle bracket as a template. (f) Enlarge the holes in the forward nacelle br acket assembly and lowe r engine inlet bulkhead assembly to #30 holes (0.129 in [3.27 mm]). (g) Remove the forward nacelle bracket assembly from the lower engine inlet bulkhead assembly. (h) Deburr and apply alodine to the holes in the forward nacelle bracket assembly and lower engine inlet bulkhead assembly. (Refer to Chapter 20 of the Maintenance Manual .)(i) Identify the lower engine inlet bulkhead assembly using an indelible marker. (Refer to Paragraph 3.C.) NOTE: The lower engine inlet bu lkhead assembly part number may not be visible. Identify the bulkhead assembly just bel ow the drilled holes location. (j) Install the forward nacelle bracket assembly onto the lower engine inlet bulkhead assembly. (8) Remove the existing support bracket and attaching hardware from the lower engine inlet bulkhead assembly. (See Figure 1 , Detail A.) (9) Install the new support bracket with attaching hardware onto the lower engine inlet bulkhead assembly. (See Figure 1 , Detail G.)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 7 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (10) Install the firewall hydraulic and fuel tubes assemblies as follows: (See Figure 1 , View H-H.) NOTE: Do not torque the clamps or the fuel and hy draulic line fittings until installation is complete, lines should be left loose for clearance adjustment, if needed. (a) Loosely install the firewall fuel supply tu be assembly in place with securing hardware. (b) Loosely install all attaching hardware to support the firewall fuel supply tube assembly flange to the firewall. NOTE: Loosely install hardware such that fire wall sealant can be injected between flange and firewall at a later time. (c) Inspect for a minimum clearance between th e firewall fuel supply tube assembly and the engine firewall cutout of 0.125 in [3.17 mm]. NOTE: The clearance measurement is taken by moving the tube assembly up and down on the engine firewall and checking for clearance between tube assembly and the engine firewall cutout. (d) On aircraft that fail the minimum clearance requirements between the firewall fuel supply tube assembly and engine firewall cutout , do the steps that follow: 1) Trim the engine firewall cutout to meet minimum clearance requirements of 0.125 in [3.17 mm]. 2) Deburr and apply alodine and epoxy primer to the engine firewall cutout. (Refer to Chapter 20 of the Maintenance Manual .) 3) Proceed to Paragraph 2.B.(10)(f) to loosely install the firewall motive flow tube assembly onto the pylon firewall. (e) On aircraft that pass the minimum clearance requirements between the firewall fuel supply tube assembly and engine firewall cutout , proceed to Paragraph 2.B(10)(f) to loosely install the firewall motive fl ow tube assembly onto the pylon firewall. NOTE: Do not tighten/torque any fuel tube a ssemblies until all of the required clearances have been met. (f) Loosely install the firewall fuel motive flow tube assembly onto the pylon firewall and secure in place using retained hardware. (g) Loosely install the firewall hydraulic case dr ain tube assembly onto the pylon firewall and secure in place using retained hardware. (h) Loosely install the firewall hydraulic pressure tube assembly onto the pylon firewall and secure in place using retained hardware. (i) Loosely install the firewall hydraulic suction tu be assembly onto the pylon firewall and secure in place using retained hardware. (11) Install the channel assembly onto the fo rward and aft nacelle bracket assemblies. (See Figure 1 , View H-H.) (12) Loosely install all clamps that secure the firewall tube assemblies to the channel assembly. (See Figure 1 , View H-H.)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 8 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (13) Install the nacelle hydrau lic flexible hoses and tube assemblies as follows: (See Figure 1 , Detail G.) NOTE: Do not torque the clamps or the hydraulic line fittings until inst allation is complete, lines should be left loose for clearance adjustment, if needed. (a) Loosely install the nacelle hydraulic suction tu be assembly onto the firewall hydraulic suction tube assembly. (b) Loosely install a new clamp and spacer and at taching hardware to secure the nacelle hydraulic suction tube assembly to the lower engine inlet bulkhead assembly. (c) Loosely install a new clamp and attaching hardware to secure the nacelle hydraulic suction tube assembly to the support bracket. (d) Loosely install the flexible hydraulic suction ho se assembly onto the nacelle hydraulic suction tube assembly. (e) Loosely install the opposite end of the flexib le hydraulic suction hose assembly onto the engine driven hydraulic pump. (f) Loosely install the nacelle hydraulic case drai n tube assembly onto the firewall hydraulic case drain tube assembly. NOTE: When installing the nace lle hydraulic case drain tube assembly, make sure toroute the tube assembly between the thrust reverser hydraulic pressure and suction lines. (g) Loosely install a new clamp and spacer and at taching hardware to secure the nacelle hydraulic case drain tube assembly to the lower inlet bu lkhead assembly. (h) Loosely install the flexible hydraulic case drain hose assembly onto the nacelle hydraulic case drain tube assembly. (i) Loosely install the opposite end of the flexible hydraulic case drain hose assembly onto the engine driven hydraulic pump.(j) Loosely install the nacelle hydraulic pressure tube assembly onto the firewall hydraulic pressure tube assembly. (k) Loosely install new clamps and attaching hardware to secure the nacelle hydraulic pressure tube assembly and hydraulic case drain tube assembly to the support bracket. (l) Loosely install the flexible hydraulic pressure hose assembly onto the nacelle hydraulic pressure tube assembly. (m) Loosely install the opposite end of the flexible hydraulic pressure hose assembly onto the engine driven hydraulic pump bleed fitting tee. (14) Install the hydraulic case drain support assembly. (See Figure 1 , Detail G.)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 9 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (15) Inspect the lower nacelle hydraulic tube and hose assemblies for minimum clearances. NOTE: Minimum clearance unless otherwise note d is 0.125 in [3.17 mm] between all unsupported sections of tubing /hoses and adjacent components/structure, or a minimum clearance of 0.06 in [1.52 mm] between a ll supported sections of tubing/hoses and adjacent components/structure. An unsupported section of tube/hose is defined as the porti on of tube/hose that extends beyond 4.00 in [9.16 cm] on either side of the support clamp. A supported section of tube/hose is defined as the port ion of tube/hose that extends within 4.00 in [9.16 cm] on either side of the support clamp. The flexible hydraulic suction hose asse mbly has a minimum clearance requirement of 0.05 in [1.27 mm] between the suction hose assembly and the lower engine inlet bulkhead assembly. (a) On aircraft that fail the minimum hydrau lic tube and hose clearance requirements , adjust the tubing, flexible hoses and clamps to achieve the minimum clearance requirements. After minimum clearance requirements have been met, proceed to Paragraph 2.B.(16) to torque all hydraulic flexible hoses, nacelle hydraulic tube assemblies and associated clamps. (b) On aircraft that pass the minimum hydraulic tube and hose clearance requirements , proceed to Paragraph 2.B.(16) to torque all hydraulic fl exible hoses, nacelle hy draulic tube assemblies and associated clamps. (16) Torque all hydraulic flexible hoses, nacelle hydraulic tube assemblies and associated clamps as follows: NOTE: Care should be taken to maintain the minimum clearance requirements and not to preload the nacelle hydraulic tubing while torquing. (a) Torque the nacelle hydraulic suction tube asse mbly at the connection point of the firewall hydraulic suction tube assembly. (Refer to Chapter 20 of the Maintenance Manual .) (b) Torque the nacelle hydraulic suction tube asse mbly at the connection point of the flexible hydraulic suction hose assembly. (Refer to Chapter 20 of the Maintenance Manual .) (c) Torque the flexible hydraulic suction hose assembly at the connection point of the engine driven hydraulic pump. (Refer to Chapter 20 of the Maintenance Manual .) (d) Torque the nacelle hydraulic case drain tube a ssembly at the connection point of the firewall hydraulic case drain tube assembly. (Refer to Chapter 20 of the Maintenance Manual .) (e) Torque the nacelle hydraulic case drain tube assembly at the connection point of the flexible hydraulic case drain hose assembly. (Refer to Chapter 20 of the Maintenance Manual .) (f) Torque the flexible hydraulic case drain hose assembly at the connection point of the engine driven hydraulic pump. (Refer to Chapter 20 of the Maintenance Manual .) (g) Torque the nacelle hydraulic pressure tube assembly at the connection point of the firewall hydraulic pressure tube assembly. (Refer to Chapter 20 of the Maintenance Manual .) (h) Torque the nacelle hydraulic pressure tube as sembly at the connection point of the flexible hydraulic pressure hose assembly. (Refer to Chapter 20 of the Maintenance Manual .)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 10 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (i) Torque the flexible hydraulic pressure hose assembly at the connection point of the engine driven hydraulic pump bleed fitting. (Refer to Chapter 20 of the Maintenance Manual .) (j) Torque all associated support clamps on th e flexible hydraulic hoses and hydraulic tube assemblies. (Refer to Chapter 20 of the Maintenance Manual .) NOTE: At this point, all hydrau lic flexible hoses and hydraulic nacelle tubes must be properly installed with all fittings and sup port clamps torqued, and minimum clearances maintained. (17) On aircraft 45-2001 thru 45-2094 replace the exis ting spacer and attachment screw on the thrust reverser hydraulic return and pressure tube assemblies , as follows: (See Figure 1 , Detail M.) (a) If not already done, remove the starter/generator inlet duct from the engine nacelle. NOTE: The thrust reverser hydraulic return and pressure tube assemblies are located on the forward side of the engine inlet bulkhead assembly. The tube assemblies can be reached through the starter/generator inlet duct opening. (b) Remove the existing spacer and attachment screw from the clamp location used to secure the thrust reverser hydraulic return tube assembly to the engine inlet bulkhead assembly.(c) Install the new spacer and screw into the retained clamp to secure the thrust reverser hydraulic return tube assembly to the engine inlet bulkhead assembly. (d) Remove the existing spacer and attachment screw from the clamp location used to secure the thrust reverser hydraulic pressure tube assembly to the engine inlet bulkhead assembly.(e) Install the new spacer and screw into the retained clamp to secure the thrust reverser hydraulic pressure tube assembly to the engine inlet bulkhead assembly. (f) Make sure that a minimum clearance of 0.125 in [3.17 mm] exists between the thrust reverser hydraulic pressure tube assembly and support bracket attachment screw. (18) Install the starter/generator (G1) on the aircraft. (Refer to Chapter 24 of the Maintenance Manual .) (19) Install the alternator (G3) on the aircraft. (Refer to Chapter 24 of the Maintenance Manual .) (20) Install the nacelle fuel tubes and flexible hose assemblies as follows: NOTE: Minimum clearance unless otherwise note d is 0.125 in [3.17 mm] between all unsupported sections of tubing /hoses and adjacent components/structure, or a minimum clearance of 0.06 in [1.52 mm] between a ll supported sections of tubing/hoses and adjacent components/structure. An unsupported section of tube/hose is defined as the porti on of tube/hose that extends beyond 4.00 in [9.16 cm] on either side of the support clamp. A supported section of tube/hose is defined as the port ion of tube/hose that extends within 4.00 in [9.16 cm] on either side of the support clamp. (a) On aircraft where the inspection of the fuel su pply manifold assembly threads revealed galling , do the steps that follow: (See Figure 1 , View J-J.) 1) Disconnect the damper assembly tubing fr om the fuel supply manifold assembly. 2) Remove the union from the fuel supply manifold assembly. 3) Remove the O-ring from the union and discard. 4) Remove and discard the fuel supply manifold assembly from the airc raft. Retain attaching hardware for the installation of ne w fuel supply manifold assembly. 5) Install a new O-ring onto the new fuel supply manifold assembly. 6) Install the new fuel supply manifold assembly on the engine driven fuel pump using retained attaching hardware.THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 11 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin 7) Install the union and a new O-ring into the fuel supply manifold assembly. 8) Connect the damper assembly tube to the union in the new fuel supply manifold assembly. 9) Proceed to Paragraph 2.B.(20)(c) to positi on the five (5) MS21919WCH16 clamps on the nacelle fuel supply tube asse mbly prior to installation. (b) On aircraft where the inspection of the fuel supply manifold assembly threads did not reveal galling , the fuel supply manifold does not require replacement. NOTE: Before connecting the nace lle fuel supply tube assembly on the aircraft, apply anti-seize compound (Liquid-Moly) to th e threads of the fuel supply manifold assembly and the male threads of the firewall fuel supply tube assembly. (c) Position the five (5) MS21919WCH16 clamps on t he nacelle fuel supply tube assembly prior to installation. (See Figure 1 , Detail L for clamp position and orientation.) NOTE: The MS21219WCH16 clamps used to support the nacelle motive flow assembly must be in position on the nacelle fuel su pply tube assembly prior to installation. (d) Loosely install the nacelle fuel supply tube as sembly onto the firewall fuel supply tube assembly and the fuel supply manifold assembly. NOTE: It is permissible to loosen the atta ching hardware on the fuel supply manifold assembly to ease in the installation of the nacelle fuel supply tube assembly. (e) Loosely install the nacelle fuel supply tube assembly onto the lower engine inlet bulkhead assembly using the required clamps, spacers and hardware. (See Figure 1 , Detail L.) (f) Loosely install the nacelle fuel motive flow tube assembly onto the firewall fuel motive flow tube assembly. (g) Loosely install the opposite end of the nacelle fuel motive flow tube assembly onto the lower engine inlet bulkhead assembly using the required clamps and hardware. (See Figure 1 , Detail L.) (h) Loosely install the flexible fuel motive flow hose assembly onto the nacelle fuel motive flow tube assembly. (See Figure 1 , Detail L.) (i) Loosely install the opposite end of the flexible fuel motive flow hose assembly onto the motive flow pump. (21) Inspect the lower nacelle fuel tubes and flexible hoses for minimum clearances. NOTE: Minimum clearance unless otherwise note d is 0.125 in [3.17 mm] between all unsupported sections of tubing /hoses and adjacent components/structure, or a minimum clearance of 0.06 in [1.52 mm] between a ll supported sections of tubing/hoses and adjacent components/structure. An unsupported section of tube/hose is defined as the porti on of tube/hose that extends beyond 4.00 in [9.16 cm] on either side of the support clamp. A supported section of tube/hose is defined as the port ion of tube/hose that extends within 4.00 in [9.16 cm] on either side of the support clamp.THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 12 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (a) On aircraft that fail the minimum fuel tube and hose clearance requirements , loosen and adjust the tubing, flexible hoses and clamps to maintain the minimum clearance requirements. After minimum clearance requirements have been met, proceed to Paragraph 2.B.(22) to adjust the inboard area of the nacelle fuel supply tube assembly and the lower engine inlet bulkhead flange. (b) On aircraft that pass the minimum fuel tube and hose clearance requirements , proceed to Paragraph 2.B.(22) to adjust the inboard area of the nacelle fuel supply tube assembly and the lower engine inlet bulkhead flange. (22) Adjust the inboard area of the nacelle fuel su pply tube assembly and the lower engine inlet bulkhead flange to a minimum clearance of 0.05 in [1.27 mm] between the flange and the tube assembly as follows: NOTE: The flange of the firewall fuel supply tube assembly is slotted for adjustment to maintain the 0.05 in [1.27 mm] clearance between the nacelle fuel supply tube assembly and lower engine inlet flange.(a) Place a 0.05 in [1.27 mm] shim or feeler gauge between the nacelle fuel supply tube assembly, and the lower engine inlet bulkhead flange to maintain the required 0.05 in [1.27 mm] clearance. (23) Fay seal the firewall fuel supply tube assembly flange as follows: (a) Loosely install all screws attaching the flange of the firewall fuel supply tube assembly to the engine firewall as necessary to inject Dapco 2200 Primerless Firewall Sealant. (b) Loosen the clamps and attaching hardware on the firewall fuel supply tube assembly as required to fay seal the flange of th e tube assembly to the engine firewall. (c) Fay seal the flange of the firewall fuel supply tube assembly with Dapco 2200 Primerless Firewall Sealant. NOTE: The fuel supply tube assembly flange is fay sealed by using a sealer gun to inject the firewall sealant between the tube flange and firewall assembly. (24) Torque all fasteners in th e firewall fuel supply tube assembly flange. (Refer to Chapter 20 of the Maintenance Manual .) NOTE: While torquing the fasteners on the tube assembly flange, make sure to maintain the required clearance of 0.05 in [1.27mm] between the nacelle fuel supply tube assembly and the lower engine inlet flange. Contact between the firewall fuel supply tube assembly and the fire extinguisher discharge tube assembly lower support clamp is permissible. (25) Torque the attaching hardware that secures the firewall fuel and hydraulic tube assemblies to the engine firewall. (Refer to Chapter 20 of the Maintenance Manual .) (26) Torque all fuel flexible hoses and nacelle fuel tube assemblies and associated clamps as follows:NOTE: Care should be taken to maintain minimum clearance requirements, and not to preload the nacelle fuel tubing while torquing. (a) Torque the nacelle fuel supply tube assembly at the connection point of the firewall fuel supply tube assembly. (Refer to Chapter 20 of the Maintenance Manual .) (b) Torque the nacelle fuel supply tube assembly at the connection point of the fuel supply manifold. (Refer to Chapter 20 of the Maintenance Manual .)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 13 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (c) If loosened to aid in the alignment of the nace lle fuel supply tube assembly, torque the attaching hardware on the fuel manifold assembly. (Refer to Chapter 20 of the Maintenance Manual .) (d) Torque the nacelle motive flow tube assembly at the connection point of the firewall motive flow fuel tube assembly. (Refer to Chapter 20. of the Maintenance Manual .) (e) Torque the nacelle motive flow tube assembly at the connection point of the flexible motive flow hose assembly. (Refer to Chapter 20 of the Maintenance Manual .) (f) Torque the flexible motive flow hose assembly at the connection point of the engine driven motive flow fuel pump. (Refer to Chapter 20 of the Maintenance Manual .) (g) Torque all associated support clamps on t he flexible fuel hoses and fuel tube assemblies. (Refer to Chapter 20 of the Maintenance Manual .) (27) Connect the flexible fuel and hydraulic hose a ssemblies located in the engine pylon to the engine firewall. (Refer to Chapter 20 of the Maintenance Manual .) (28) Torque all fuel and hydraulic tube and hose a ssembly clamps on the support channel. (Refer to Chapter 20 of the Maintenance Manual .) (29) Remove the 0.05 in [1.27 mm] shim or feeler gauge from the aircraft. (30) Check the electrical bond of the hydraulic tube assemblies. (Refer to Chapter 20 of the Wiring Manual .) (31) Check the electrical bond of the fuel tube assemblies. (Refer to Chapter 20 of the Wiring Manual .) NOTE: The resistance of the fuel tube assemblies should not exceed 1.0 ohm. (32) Route and clamp the starter/generator wiring harnesses (G1-E, G1-B) and the left alternator wiring harness (G3P2) on the left engine. (See Figure 1 , Detail Q.) NOTE: Minimum clearance requirements between the starter/generator electrical harness,and hydraulic and fuel tube assemblies that have been installed by this service bulletin, is 0.125 in [1.27 mm ] unless otherwise specified. (33) Clamp the alternator wire harness (G3P1) onto the firewall hydraulic suction tube assembly. (See Figure 1 , Detail R.) NOTE: Minimum clearance requirements betwe en the alternator electrical harness and hydraulic and fuel tube assemblies that have been installed by this service bulletin, is 0.125 in [1.27 mm] unless otherwise specified. (34) Connect the main and emergency batteries to the aircraft. (Refer to Chapter 24 of the Maintenance Manual .) (35) Push and release the L Engine Fire switch to open the firewall shutoff valves. (36) If necessary, service the aircraft hydraulic system. (Refer to Chapter 12 of the Maintenance Manual .) (37) If not already done, install the starter/generator inlet duct on the aircraft. C. Functional Test/Operational Check (1) Bleed the aircraft hydr aulic system. (Refer to Chapter 29 of the Maintenance Manual .) (2) Do the Functional Test of the Engi ne Driven Hydraulic Pump. (Refer to Chapter 29 of the Maintenance Manual .) (3) Do an Automatic Engine Start (Left Engine Only). (Refer to Chapter 80 of the Maintenance Manual .) (4) Advance the left engine throttle lever to the Takeoff detent for one (1) minute. (Refer to the Airplane Flight Manual.)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 14 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin (5) Check all replaced hydraulic flexible hoses and tube assemblies for leakage. (6) Check all replaced flexible fuel hoses and tube assemblies for leakage. (7) Shut down the left engine. (Refer to the Airplane Flight Manual.) D. Return Aircraft to Airworthy Status (1) Install the left upper forward pylon panel (340AL). (Refer to Chapter 6 of the Maintenance Manual .) (2) Install the left lower forward pylon panel (340DL). (Refer to Chapter 6 of the Maintenance Manual .) (3) Install the left upper engine cowling (450AL) on the aircraft. (Refer to Chapter 71 of the Maintenance Manual .) (4) Install the left lower engine cowling (450CL) on the airc raft. (Refer to Chapter 71 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. NOTE: Complete the aircraft records in accordance with the regulatory requirements of your aircraft certification authority. 3. Material Information A. Parts Required (1) The 4571430001-801 kit contains the parts that follow: PART NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER 7629100003

‐ 001 1 Flex Hose Assembly, Hydraulic Case Drain AE720134

‐ 1

7629100002

‐ 001 1 Flex Hose Assembly, Hydraulic Suction AE720133

‐ 1

7629100001

‐ 001 1 Flex Hose Assembly, Hydraulic Pressure AE720132

‐ 1

7628200001

‐ 001 1 Flex Hose Assembly, Fuel Motive Flow AE713701

‐ 2

4571408529

‐ 001 1 Channel Assembly 4571408519

‐ 001 1 Nacelle Bracket Assembly (Aft) 4571408518

‐ 001 1 Nacelle Bracket Assembly (Forward) 4529101097

‐ 001 1 Tube Assembly, Hydraulic Case Drain, FirewallTHIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 15 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

4529101096

‐ 001 1 Tube Assembly, Hydraulic Suction, Firewall 4529101095

‐ 001 1 Tube Assembly, Hydraulic Pressure, Firewall 4529101094

‐ 001 1 Tube Assembly, Hydraulic Case Drain, Nacelle 4529101093

‐ 001 1 Tube Assembly, Hydraulic Pressure, Nacelle 4529101092

‐ 005 1 Tube Assembly, Hydraulic Suction, Nacelle 4529101027

‐ 001 1 Support Assembly, Case Drain 4529101026

‐ 001 1 Bracket Assembly, Support 4528200013

‐ 009 1 Tube Assembly, Fuel Supply, Nacelle 4528200010

‐ 009 1 Tube Assembly, Motive Flow, Nacelle 4528200009

‐ 001 1 Tube Assembly, Motive Flow, Firewall 4528200007

‐ 005 1 Tube Assembly, Fuel Supply, Firewall NAS1097AD3

‐ 3 2 Rivet NAS1097AD3

‐ 4 2 Rivet NAS1802

‐ 3

‐ 8 15 Screw NAS1802

‐ 3

‐ 10 2 Screw NAS1802

‐ 3

‐ 12 2 Screw NAS1802

‐ 3

‐ 14 1 Screw NAS1802

‐ 3

‐ 24 2 Screw PART NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBERTHIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 16 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

NOTE: Some hardware comes in pre-packaged quantities. When that occurs, the quantity in the kit will be more than the qu antity in the parts list. NAS1802

‐ 08

‐ 7 5 Screw NAS1149C0316R 20 Washer NAS1149CN816R 10 Washer NAS43DD3

‐ 16FC 4 Spacer NAS43DD3

‐ 32FC 1 Spacer NAS43HT3

‐ 48 1 Spacer NAS43HT3

‐ 25 1 Spacer NAS620C10L 4 Washer M85052/3

‐ 8 4 Clamp M85052/3

‐ 6 2 Clamp M85052/3

‐ 4 4 Clamp MS21919WCH5 1 Clamp MS21919WCH15 1 Clamp MS21919WCH16 6 Clamp MS21919WCH8 4 Clamp MS21279

‐ 07 1 Bolt MS21042

‐ 08 5 Nut MS21042

‐ 3 9 Nut MS27039C1

‐ 12 1 Screw MS27039C1

‐ 18 1 Screw CR3213

‐ 4

‐ 02 3 Rivet PART NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBERTHIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 17 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin
B. Parts Removed List

PART NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY 4529101088

‐ 001 1 Tube Assembly ‐ Hydraulic Suction, Nacelle Destroy All

4529101089

‐ 001 1 Tube Assembly ‐ Hydraulic Pressure, Nacelle Destroy All

4529101090

‐ 001 1 Tube Assembly ‐ Hydraulic Case Drain, Nacelle Destroy 45

‐ 2001 thru 45

‐ 2094

4529101090

‐ 005 1 Tube Assembly ‐ Hydraulic Case Drain, Nacelle Destroy 45

‐ 2095 and 45

‐ 2126

4529101066

‐ 003 1 Bracket ‐ Support, Nacelle Destroy All

4528200005

‐ 001 1 Tube Assembly ‐ Fuel Supply, Firewall Destroy All

4528200011

‐ 001 1 Tube Assembly ‐ Motive Flow, Firewall Destroy All

4529101067

‐ 001 1 Tube Assembly ‐ Hydraulic Pressure, Firewall Destroy All

4529101071

‐ 001 1 Tube Assembly ‐ Hydraulic Suction, Firewall Destroy All

4529101075

‐ 005 1 Tube Assembly ‐ Hydraulic Case Drain, Firewall Destroy All

4528200044

‐ 001 1 Tube Assembly ‐ Motive Flow, Nacelle Destroy 45

‐ 2001 thru 45

‐ 2026

4573100000V13

‐ 001 1 Tube Assembly ‐ Motive Flow, Nacelle Destroy 45

‐ 2027 thru 45

‐ 2126

4573100005

‐ 013 1 Tube Assembly ‐ Fuel Supply, Nacelle Destroy 45

‐ 2001 thru 45

‐ 2026

4573100000V12

‐ 001 1 Tube Assembly ‐ Fuel Supply, Nacelle Destroy 45

‐ 2027 thru 45

‐ 2126THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 18 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

C. Identification Table A7967

‐ 2 1 Hose Assembly ‐ Hydraulic Pressure Destroy When Installed

AS623

‐ 06H0073 1 Hose Assembly ‐ Hydraulic Pressure Destroy When Installed

A7968

‐ 1 1 Hose Assembly ‐ Hydraulic Suction Destroy When Installed

AE1010563H0081 1 Hose Assembly ‐ Hydraulic Suction Destroy When Installed

A7969

‐ 1 1 Hose Assembly ‐ Case Drain Destroy When Installed

AE3663169E0067 1 Hose Assembly ‐ Case Drain Destroy When Installed

A7970

‐ 1 1 Hose Assembly ‐ Motive Flow Destroy When Installed

AE713701

‐ 1 1 Hose Assembly ‐ Motive Flow Destroy When Installed

NAS43HT3

‐ 25 1 Spacer Destroy 45

‐ 2001 thru 45

‐ 2094 NAS43HT3

‐ 31 1 Spacer Destroy 45

‐ 2001 thru 45

‐ 2094 MS27039C1

‐ 12 1 Screw Destroy 45

‐ 2001 thru 45

‐ 2094 MS27039C1

‐ 14 1 Screw Destroy 45

‐ 2001 thru 45

‐ 2094 MS27039C1

‐ 17 1 Screw Destroy 45

‐ 2001 thru 45

‐ 2094

PART NUMBER NOMENCLATURE IDENTIFY TO SPARES REPLACEMENT EFFECTIVITY
4571600052

‐ 005 Lower Engine Inlet Bulkhead Assembly 4571430001

‐ 803 No Spares Available All PART NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITYTHIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 19 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 1 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 20 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 2 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 21 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 3 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 22 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 4 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 23 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 5 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 24 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 6 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 25 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 7 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 26 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 8 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 27 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Replacement of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 9 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 28 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Installation of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 10 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 29 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Installation of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 11 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 30 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Installation of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 12 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 31 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Installation of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 13 of 14)THIS PUBLICATION IS AVAILABLE AT: www.cic.bombardier.com SB 40-71-04 Page 32 of 32 Basic Issue: Dec 7/09 

### LEARJET 40 Service Bulletin

Installation of the Left Engine Fuel and Hydraulic Tubing Figure 1 (Sheet 14 of 14)