45 (Model 45, 45-001 thru 45-2000) MAINTENANCE MANUAL

BOMBARDIER P.O. BOX 7707, MID-CONTINENT AIRPORT, WICHITA, KANSAS 67277-7707

Part Number:MM-104 JUNE 6, 1997 Publication Number: LR45MM Revision No. 53, dated Jan 10, 2011 TECHNICAL PUBLICATIONS USER COMMENT SHEET BOMBARDIER

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LEARJET 45 MAINTENANCE MANUAL

MAINTENANCE MANUAL REVISION HIGHLIGHTS Learjet 45, Revision No. 53, Dated Jan 10, 2011 These highlights describe the more significant changes made by this revision. (C/S/S) Brief Description CHAPTER 04 4-00-00-001 Updated the FAA approval. 4-1 0-00-001 Revised IRN T3040000. Revised IRN T2620001. Revised IRN S3510014. 4-10-01-001 Revised IRN T5510004. 4-11-00-001 Inc. TR4-33. Revised IRN T3220013. Revised IRN T3220046. Revised IRN T3220105. CHAPTER 05 5-11-01-001 Moved IRN T3411000 to 5-12-01. Moved IRN T5600001 to 5-12-01. 5-11-02-001 Moved IRN T5321011 to 5-12-02. Moved IRN T5360000 to 5-12-02. 5-11-04-001 Moved IRN T2710000 to 5-12-04. Deleted IRN T2711000 and combined with T2710000. 5-11-06-001 Moved IRN T5210001 to 5-12-06. Moved IRN T5210002 to 5-12-06. 5-12-01-001 Revised IRN T3040000. Revised IRN S3510014. Moved IRN T2400001 to 5-13-01. Added IRN T3411000. Moved IRN T351 0000 to 5-13-01. Moved IRN T521 0000 to 5-13-01 . Moved IRN T5240000 to 5-13-01 . Revised IRN T5321089. Moved IRN T5323031 to 5-13-01 . Added IRN T5600001. Moved IRN T7600001 to 5-13-01. 5-12-02-001 Moved IRN T5240003 to 5-13-02. Moved IRN T2140000 to 5-13-02. Moved IRN T2141000 to 5-13-02. Added IRN T5321011. Added IRN T5360000. 5-12-03-001 Moved IRN T2150058 to 5-13-02. Moved IRN T2150059 to 5-13-02. 5-12-04-001 Added IRN T2710000. 5-12-06-001 Added IRN T5210001. Added IRN T5210002. Moved IRN T5210003 to 5-13-06. Moved IRN T5210005 to 5-13-06.

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(C/S/S) Bri ef Description 5-13-01-001 Added IRN T2400001 . Moved IRN T2910003 to 5- 14-01. Added IRN T3510000. Added IRN T5210000. Added IRN T5240000. Added IRN T5323031. Added IRN T7600001 . Added IRN T2620001 . 5-13-02-001 Added IRN T2140000. Added IRN T2141000. Moved IRN T2431000 to 5-14-02. Added IRN T5240003. Added IRN T2150058. 5-13-03-001 Moved IRN T7830000 to 5-14-03. 5-13-06-001 Added IRN T5210003. Added IRN T5210005. 5-1 4-01-001 Added IRN T2910003. 5-14-02-001 Added IRN T2431000. 5-14-03-001 Added IRN T7830000. 5-15-00-001 Revised IRN 05323099. 5-16-00-001 Revised IRN N5710017. Revised IRN T5510004. 5-19-00-001 Revised IRN N3510013. 5- 19-01-001 Inc. TRS-81. Revised IRN T3220013. Revised IRN T3220046. Revised IRN T3220105. 5-60-00-001 Revised or added IRN numbers. CHAPTER 09 9-10-00-201 Updated the maintenance practices of Towing. CHAPTER10 10-12-00-201 Updated the maintenance practices of Storage. CHAPTER 11 11-31-00-001 Inc. TR11-4. Updated the description and operation of the Passenger Compartment Placards. CHAPTER12 12-10-02-301 Updated the servicing of the Nose Gear Shock Strut. 12-10-03-301 Updated the servicing of the Main Gear Shock Strut. 12-24-00-301 Updated the servicing of the External Cleaning. CHAPTER 20 20-10-00-201 Updated the maintenance practices of Sealants. 20-13-00-201 Updated the maintenance practices of Solvent Cleaning. 20-30-00-201 Updated the maintenance practices of the Flared Tubing. 20-3 1-01-201 Updated the maintenance practices of the Wiggins and Hydroflow Connectors. 20-31 -02-201 Updated the maintenance practices of the V-Band Couplings. 20-36-00-201 Added the maintenance practices of the Bleed Air Duct Insulation. 20-50-00-20 1 Updated the maintenance practices of the Exterior Paint. Page 2 Jan 10/11 LEARJET 45 MAINTENANCE MANUAL

(C/S/S) Brief Description 20-73-00-201 Updated the maintenance practices of the Conductive Coating. CHAPTER 21 21 -20-07-201 Updated the maintenance practices of the Gasper Air Check Valves. 21 -20-16-201 Updated the maintenance practices of the Door and Thermistor Assembly. 21-20-17-201 Updated the maintenance practices of the Actuator and PC Board Assembly. 21-30-01-201 Updated the maintenance practices of the Primary Outflow Valve. 21-30-05-201 Updated the maintenance practices of the Emergency Depressurization Switch. 21 -30-06-20 1 Updated the maintenance practices of the Jet Ejector Pump. 21-30-07-201 Updated the maintenance practi ces of the Cabin Pressurization Control System Check Valve. 21-31-00-201 Updated the maintenance practices of the Emergency Pressuri zation System. 21-50-05-201 Updated the maintenance practices of the Environmental Control Unit Bypass Shutoff Valve. 21-60-00-201 Updated the maintenance practices of the Temperature Control System. 21-60-02-201 Updated the maintenance practices of the Cockpit Temperature Sensor. 21-60-03-201 Updated the maintenance practices of the Cabin Temperature Sensor/Fan. 21 -60-06-201 Updated the maintenance practices of the Cabin Duct Temperature Sensor. 21-60-07-201 Updated the maintenance practices of the Cockpit Duct Temperature Sensor CHAPTER 23 23-11-03-201 Updated the maintenance practices of the Communication Strap Board. 23-50-01-201 Updated the maintenance practices of the Audio Control Unit. 23-50-03-201 Updated the maintenance practices of the Cockpit Speaker. 23-82-00-001 Updated the description and operation of the Clearance Delivery System. 23-82-00-201 Updated the maintenance practi ces of the Clearance Delivery System. 23-82-01-201 Updated the maintenance practices of the Clearance Delivery Unit. CHAPTER 24 24-00-00-201 Updated the maintenance practices of the Electrical Power. 24-20-01-201 Updated the maintenance practices of the Alternator. 24-31-06-201 Updated the maintenance practices of the Lead-Acid Battery. 24-60-03-201 Updated the maintenance practices of the Aft Power Distribution Panel. CHAPTER 25 25-10-01-201 Updated the maintenance practices of the Flig ht Compartment Overhead Panel. 25-10-25-201 Updated the maintenance practices of the Flight Compartment Floor Covering. 25-10 -35-201 Updated the maintenance practices of the Aft Glareshield. CHAPTER 26 26-21-00-201 Updated the maintenance practices of the Engine Fire Extinguishing System. 26-21 -01-201 Updated the maintenance practices of the Engine Fire Extinguishing Container. 26-22-00-201 Updated the maintenance practices of the Fire Extinguishing Sys- tern. CHAPTER 27 27-10-07-201 Updated the maintenance practi ces of the Aileron Control Quadrant Assembly. 27-30-01-201 Updated the maintenance practices of the Elevator. 27-30-06-201 Updated the maintenance practices of the Elevator Forward Disconnect Assembly. 27-31-00-201 Updated the maintenance practices of the Warning.

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(C/S/S) Brief Description 27-31-01-201 Updated the maintenance practices of the Angle-of-Attack Transmitter. 27-31-04-201 Updated the maintenance practices of the Angle-of-Attack Vane. 27-40-02-201 Updated the maintenance practices of the Horizontal Stabilizer Actuator. 27-60-02-201 Updated the maintenance practices of the Spoileron Computer. 27-60-04-201 Updated the maintenance practices of the Spoiler Actuator. 27-60-10-201 Updated the maintenance practices of the Spoileron Controller Resistor Box. CHAPTER 28 28-20-00-201 Updated the maintenance practices of the Fuel Distribution System. 28-20-01-201 Updated the maintenance practices of the Main Ejector Pump. 28-20-02-201 Updated the maintenance practices of the Standby Pump. 28-20-03-201 Updated the maintenance practices of the Supply Line Check Valve. 28-20-05-201 Updated the maintenance practices of the Motive Flow Check Valve. 28-20-09-201 Updated the maintenance practices of the Refuel Check Valve. 28-20-1 0-201 Updated the maintenance practices of the Refuel Shutoff Valve. 28-20-11-201 Updated the maintenance practices of the Pilot Valve. 28-20-12-201 Updated the maintenance practices of the Precheck Valve. 28-40-05-201 Updated the maintenance practices of the Fuel Probe. CHAPTER 29 29-10-00-201 Updated the maintenance practices of the Main Hydraulic System. 29-10-02-201 Updated the maintenance practices of the Hydraulic Reservoir. 29-1 0-04-201 Updated the maintenance practices of the Hydraulic Accumulator. 29-10-06-201 Updated the maintenance practices of the Reservoir Pressurization Control Module. 29-10-07-201 Updated the maintenance practices of the Thermal Shutoff Valve. 29-20-00-201 Updated the maintenance practices of the Auxiliary Hydraulic System. 29-20-02-201 Updated the maintenance practices of the Auxiliary Hydraulic Filter Manifold. 29-30-03-201 Updated the maintenance practices of the Hydraulic Pressure Switch. CHAPTER 30 30-10-00-201 Updated the maintenance practices of the Airfoil Anti-Ice System. 30-10-01-201 Updated the maintenance practices of the Anti-Ice Pressure Regulating and Shutoff Valve. 30-1 0-05-201 Updated the maintenance practices of the Horizontal Stabilizer Overheat Sensor. 30-20-00-201 Updated the maintenance practices of the Nacelle Anti-Ice System. 30-40-00-201 Updated the maintenance practices of the Windshield Anti-Ice System. 30-40-01-201 Updated the maintenance practices of the Windshield Anti-Ice System Controller. CHAPTER 31 31-11-04-201 Updated the maintenance practices of the Forward Quadrant Switch Panel. 31-21-00-201 Updated the maintenance practices of the Clocks. 31-41-01-201 Updated the maintenance practices of the Integrated Avionics Computer. 31-51-00-201 Updated the maintenance practices of the Engine Indicating And Crew Alerting System (EICAS)/Crew Warning System (CWS). 31-60-01-201 Updated the maintenance practices of the EFIS Display Unit. CHAPTER 32 32-10-01-201 Updated the maintenance practices of the Main Gear Shock Strut.

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(C/S/S) Brief Description 32-20-01 -201 Updated the maintenance practices of the Nose Gear Shock Strut. 32-30-02-201 Updated the maintenance practices of the Landing Gear Control Switch. 32-40-02-201 Updated the maintenance practices of the Main Gear Wheel and Tire. 32-41-01-201 Updated the maintenance practices of the Brake Assembly. 32-41-04-201 Updated the maintenance practices of the Brake Shuttle Module. 32-41-10-201 Updated the maintenance practices of the Wheel Speed Transducer. 32-42-00-201 Updated the maintenance practices of the Emergency/Parking Brake System. 32-42-01-201 Updated the maintenance practices of the Emergency/Parking Brake Control Valve. 32-42-02-201 Updated the maintenance practices of the Emergency/Parking Brake Accumulator. 32-42-05-201 Updated the maintenance practices of the Emergency/Parking Brake Cables 32-42-08-201 Updated the maintenance practices of the Emergency/Parking Brake Control Handle. 32-42-09-201 Updated the maintenance practices of the Emergency/Parking Brake Check Valve. 32-50-03-201 Updated the maintenance practices of the Nose Wheel Steering Gearbox. 32-50-04-201 Updated the maintenance practices of the Nose Wheel Steering Transducer. 32-50-06-201 Updated the maintenance practices of the Nose Wheel Steering Filter Box. 32-50-09-201 Updated the maintenance practices of the Nose Wheel Steering Weight on Wheel (WOW) Switch. 32-50-10-201 Updated the maintenance practices of the Nose Wheel Steering Rotating Disc. 32-60-09-201 Updated the maintenance practices of the Squat Switch. CHAPTER 33 33-40-01-201 Updated the maintenance practices of the Anti-Collision Lights. 33-40-03-201 Updated the maintenance practices of the Landing/Recognition Lights. 33-50-01-201 Updated the maintenance practices of the Emergency Activation Module. CHAPTER 34 34-11-01-201 Updated the maintenance practices of the Pi tot-Static Probe. 34-14-00-201 Updated the maintenance practices of the Radio Altimeter System. 34-14-01-201 Updated the maintenance practices of the Radio Altimeter Transceiver. 34-14-02-201 Updated the maintenance practices of the Radio Altimeter Antenna. 34-17-00-201 Updated the maintenance practices of the Air Data System. 34-17-01 -201 Added the maintenance practices of the Micro Air Data Computer. 34-21-01-201 Updated the maintenance practices of the Magnetic Compass. 34-26-02-201 Updated the maintenance practices of the Flux Valves. 34-30-02-201 Updated the maintenance practices of the Glideslope Antenna. 34-43-02-201 Updated the maintenance practices of the TCAS Antenna. 34-5 1-05-201 Updated the maintenance practices of the VHF Navigation Strap Board. 34-55-01-201 Updated the maintenance practices of the DME Antenna. 34-57-01-201 Updated the maintenance practices of the ADF Antenna. CHAPTER 35 35-20-06-201 Updated the maintenance practices of the Altitude Compensation Regulator. CHAPTER 38 38-30-01 -201 Updated the maintenance practices of the Toilet Assembly.

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(C/S/S) Brief Description CHAPTER 49 49-10-01-501 Updated the maintenance practices of the Auxiliary Power Unit (APU). 49-80-01-201 Updated the maintenance practices of the Auxiliary Power Unit Exhaust Duct. CHAPTER 52 52-10-01-201 Updated the maintenance practices of the Passenger/Crew Door. 52-11-01-201 Updated the maintenance practices of the Passenger/Crew Door Seal. 52-70-00-201 Updated the maintenance practices of the Door Warning System. 52-70-01-201 Updated the maintenance practices of the Passenger/Crew Door Warning System. 52-80-01-201 Updated the maintenance practices of the Main Gear Doors. CHAPTER 53 53-20-02-201 Updated the maintenance practices of the Aft Pedestal. 53-20-04-201 Updated the maintenance practices of the Forward Pedestal. CHAPTER 55 55-10-00-201 Updated the maintenance practices of the Horizontal Stabilizer. 55-10-02-201 Updated the maintenance practices of the Horizontal Stabilizer Gap Fairings. CHAPTER 56 56-10-01-201 Updated the maintenance practices of the Windshield. CHAPTER 57 57-10-00-201 Updated the maintenance practices of the Wings. 57-20-01-201 Updated the maintenance practices of the Wing Fuel Tank Access Panels. 57-60-02-201 Updated the maintenance practices of the Aileron Hinge Fitting Bearing. CHAPTER 76 76-10-02-201 Updated the maintenance practices of the Thrust Lever Control Module. CHAPTER 78 78-32-40-501 Updated the adjustment test of the Throttle Retard Actuator Assembly.

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Record of Revisions

Revision Issue Insertion Revision Issue Insertion By By Number Date Date Number Date Date

Orig. Jun 6/97 19 Aug 20/00

1 Aug 22/97 20 Nov 10/00

2 Nov 21/97 21 Dec 8/00

3 Apr 10/98 22 Jan 12/01

4 Apr 20/98 23 Mar 16/01

5 Ju l 31/98 24 Apr 13/01

6 Nov 13/98 25 Jun 15/01

7 Dec 11/98 26 Aug 17/01

8 Mar 19/99 27 Oct 12/01

9 Jun 25/99 28 Dec 7/01

10 Sep 24/99 29 Apr 12/02

11 Oct 15/99 30 Aug 16/02

12 Dec 17/99 31 Dec 6/02

13 Jan 21/00 32 Jun 13/03

14 Mar 17/00 33 Feb 13/04

15 Apr 14/00 34 Aug 13/04

16 May 25/00 35 Feb 14/05

17 Jun 16/00 36 Aug 29/05

18 Jul 21/00 37 Nov 28/05

Page 1 Record of Revisions Jan 10/ 11

MM-104 LEARJET 45 MAINTENANCE MANUAL

Record of Revisions

Revision Issue Insertion Revision Issue Insertion By By Number Date Date Number Date Date

38 Apr 24/06

39 Aug 28/06

40 Dec 25/06

41 Apr 30/07

42 Aug 27/07

43 Dec 24/07

44 Apr 28/08

45 Aug 25/08

46 Dec 22/08

47 Mar 30/09

48 Jul 27/09

49 Nov 23/09

50 Mar 29/10

51 Jun 28/10

52 Sep 20/10

53 Jan 10/1 1

Page 2 Record of Revisions Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MANUAL

Chapter Chapter Section Section Subject Page Date Subject Page Date

Cover Letter • Title Page User Comment Sheet Safety Advisory Nov 10/00 • Record of Revisions 1 Jan 10/11 • Record of Revisions 2 Jan 10/11 • lntroduction-LOEP 1 Jan 10/1 1 • Introduction 1 Jan 10/11 • Introduction 2 Jan 10/1 1 • Introduction 3 Jan 10/11 • Introduction 4 Jan 10/1 1 • Introduction 5 Jan 10/11 • Introduction 6 Jan 10/1 1

Insert latest revised pages; destroy superseded or deleted pages.

• Asterisk indicates pages revised, added, or deleted by current revision. The portion of the text affected by the current revision is indicated by a vertical line the outer margin of the page.

Page 1 lntroduction-LOEP Jan 10/11 MM·104 LEARJET 45 MAINTENANCE MANUAL

INTRODUCTION

1. Coverage

A. This Maintenance Manual has been prepared by the Technical Publications Department of Learjet Inc. It contains information necessary to enable a trained mechanic to service, trouble shoot, functionally test, and repair systems and equipment in the Learjet. It also includes information necessary for the mechanic to perform maintenance or make minor repair to units in the aircraft normally requiring such action on the flight line or in the maintenance hangar. It covers the standard aircraft configuration as defined by Learjet Engineering. Maintenance information for optional equipment can be found in the Customized Completion Manual (CCM).

NOTE: Wiring schematics within the description and operation sections of this manual are for general information purposes only. Troubleshooting shall be performed using the standard Wiring Manual, and the Customized Avionics and Optional Electrical Wiring Manual.

B. This Maintenance Manual does not reflect part numbers and should not be used for ordering replace­ ment parts. Spares and replacement parts should be ordered using the current Learjet Illustrated Parts Catalog.

C. All technical data provided by Learjet Field Support Engineering is based on information traceable to the applicable DER or otherwise cognizant engineer. Verbal information provided in person or by tele­ phone is considered advisory and does not carry any status relative to FAA approval. Written informa­ tion provided by FAX, Memo, or E-mail is used when required to address "Minor" as defined by 14 CFR, part 1 and part 43, appendix A conditions supplemental to the applicable maintenance manual or structural repair manual and constitutes "data acceptable to the administrator". Engineering repair drawings with a cover letter stating DER approval and specific aircraft applicability are use for major repairs and are "FAA Approved Data". All written data is limited to the aircraft applicability defined within the document. Learjet is not responsible or liable for quality of repair work performed nor condi­ tions which are not identified to Learjet.

2. Temporary Revisions

A. Temporary revisions are used to provide additional information and changes as they become avail­ able. Temporary revisions provide, with the least possible delay, new information which assists in maintaining safe and efficient flighUground operations.

B. Temporary revisions are incorporated at the next regularly scheduled revision and become a perma­ nent part of the Maintenance Manual.

C. Upon receipt of a Temporary Revision, it should be filed in the applicable chapter in accordance with filing instructions that appear on the title page.

D. Temporary Revisions should be removed from this Maintenance Manual only when removal instruc­ tions are noted on the Record of Temporary Revisions, a revision summary sheet, or a superseding Temporary Revision.

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3. Serialization

A. Serial numbers are placed in the effectivity block in the lower left corner of each page and denote that the maintenance data on that individual page relates to the listed serial number on that page.

4. Warnings, Cautions, and Notes

A. The use of WARNINGS, CAUTIONS, and NOTES in this manual serve the following purposes: (1) Warnings call attention to use of materials, processes, methods, procedures, or limits which must be followed precisely to avoid injury to persons. (2) Cautions call attention to methods and procedures which must be followed to avoid damage to equ ipment. (3) Notes call attention to methods which make the job easier.

5. Using the Maintenance Manual

A. This Maintenance Manual is divided into four major sections, each of which is separated into chapters. Each chapter contains its own effectivity page and table of contents.

B. Page Numbering System (1) Page numbers used in this Maintenance Manual consist of three-element numbers separated by dashes, under which the page number and date are printed. (2) Whenever the chapter/system element number is followed by zeros in the section/subsystem and subjecUunit positions (26-00-00) the information is applicable to the entire system. (3) Whenever the section/subsystem element number is followed by zeros in the subjecUunit position (26-20-00) the information is applicable to the subsystems within the system. (4) The subjecUunit element number is used to identify information applicable to units within. The sub­ jecUunit element number progresses from the number -01 in accordance with the number of sub­ system units covered. (5) All system/subsystem/unit data is separated into specific types of information. Blocks of page numbers are used to identify the type of information. (a) Pages 1 thru 99 - Description and Operation (b) Pages 101 thru 199- Troubleshooting (c) Pages 201 thru 299 - Maintenance Practices (6) Some units may not require all the information listed in these three blocks of numbers, in which case those blocks of numbers are omitted. (7) Some units may require many types of maintenances practices, in which case page block 201 through 299 is omitted and the maintenance practices are broken out as follows: (a) Pages 301 thru 399 - Servicing (b) Pages 401 thru 499- Removal/Installation (c) Pages 501 thru 599 - AdjustmenUTest (d) Pages 601 thru 699- Inspection/Check (e) Pages 701 thru 799 - Cleaning/Painting (f) Pages 801 thru 899 - Repairs (8) Illustrations use the same figure number as the page block in which they appear. As an example, Figure 202 will be the second illustration appearing in the maintenance practices section.

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(9) Maintenance Manual Chapters and revision status is as follows:

CHAPTER REVISION CHAPTER TITLE STATUS Major Section 1 - Aircraft General I Introduction Rev No. 53, Jan 10/1 1 I 4 Airworthiness Limitations Rev No. 53, Jan 10/11 I 5 Time Limits/Maintenance Checks Rev No. 53, Jan 10/11 6 Dimensions and Areas Rev No. 42, Aug 27/07 7 Lifting and Shoring Rev No. 52, Sep 20/1 0 8 Leveling and Weighing Rev No. 37, Nov 28/05 I 9 Towing and Taxiing Rev No. 53, Jan 10/11 I 10 Parking and Mooring Rev No. 53, Jan 10/11 I 11 Placards and Markings Rev No. 53, Jan 10/11 I 12 Servicing Rev No. 53, Jan 10/11 Major Section 2 - Aircraft Systems I 20 Standard Practices Rev No. 53, Jan 10/ 11 I 21 Air Conditioning Rev No. 53, Jan 10/1 1 22 Auto Flight Rev No. 52, Sep 20/10 23 Communications Rev No. 53, Jan 10/1 1 24 Electrical Power Rev No. 53, Jan 10/1 1 25 Equipment and Furnishings Rev No. 53, Jan 10/11 26 Fire Protection Rev No. 53, Jan 10/11 27 Flight Controls Rev No. 53, Jan 10/1 1 28 Fuel Rev No. 53, Jan 10/11 29 Hydraulic Power Rev No. 53, Jan 10/11 30 Ice and Rain Protection Rev No. 53, Jan 10/11 31 Indicating and Recording Rev No. 53, Jan 10/11 32 Landing Gear Rev No. 53, Jan 10/11 33 Lights Rev No. 53, Jan 10/11 34 Navigation Rev No. 53, Jan 10/11 35 Oxygen Rev No. 53, Jan 10/11 36 Pneumatic Rev No. 51, Jun 28/10 I 38 Water and Waste Rev No. 53, Jan 10/11 I 49 Airborne Aux Power Rev No. 53, Jan 10/11

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CHAPTER REVISION CHAPTER TITLE STATUS Major Section 3 - Structures I 52 Doors Rev No. 53, Jan 10/11 I 53 Rev No. 53, Jan 10/11 54 Nacelles/Pylons Rev No. 48, Jul 27/09 I 55 Stabilizers Rev No. 53, Jan 10/11 I 56 Windows Rev No. 53, Jan 10/ 11 I 57 Wings Rev No. 53, Jan 10/11 Major Section 4 - PowerPiant 71 Power Plant Rev No. 52, Sep 20/10 73 Engine and Fuel Control Rev No. 43, Dec 24/07 74 Ignition Rev No. 4 7, Mar 30/09 I 76 Engine Controls Rev No. 53, Jan 10/11 77 Engine Indicating Rev No. 52, Sep 20/10 I 78 Exhaust Rev No. 53, Jan 10/11 79 Oil Rev No. 46, Dec 22/08 80 Starting Rev No. 33 , Feb 13/04

6. Revision Bars

A. Changes to data in an existing section will be identified by a revision bar in the outer margin of the page.

7. Supplementary Publications

A. The following list of publications provide servicing , overhau l, and parts information on various compo­ nents on the aircraft. You may want to obtain these documents from the companies listed below to sup­ plement the maintenance manual. Since a wide variety of radio equipment is available, and because manufacturers normally supply parts and servicing manuals with their equipment, radio publications have not been included.

B. Chapter 20 (Standard Practices) (1) Aeroquip Rynglok Fitting System Installation Gu ide, Bulletin AB7; Aeroquip Corporation, Engi­ neered Systems Group, Aerospace Division, 300 S. East Avenue, Jackson, MI. 49203-1972.

C. Chapter 24 (Electrical Power) (1) Component Maintenance Manual with Illustrated Parts List, Publication No. 24-39-57; Rear DC Power Distribution Panel, P/N: 660GC02Y05, PIN: 660GC02Y07, PIN : 700GC02Y05, P/N: 700GC02Y07; E.C.E., 129 Boulevard Davout, Paris 75020, France. (2} Maintenance Manual 23700 DC Generators and Starter- Generators; TRW Aeronautical Systems, Lucas Aerospace, 30 Van Nostram Avenue, Englewood, NJ 07631 -4396.

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D. Chapter 26 (Fire Protection) (1) Component Maintenance Manual with Illustrated Parts List, Publication No. 26-20-10; Discharge Indicator Assembly, P/N: 18600, P/N: 18601; Pacific Scientific, HTL!Kin-Tech Division, 1800 High­ land Ave, Duarte, CA 91010. (2) Supplement to Component Maintenance Manual, Publication No. 26-20-200; Fire Extinguisher, P/ N: 30402102-4; Pacific Scientific, HTUKin-Tech Division, 1800 Highland Ave, Duarte, CA 91010. (3) Component Maintenance Manual with Illustrated Parts List, Publication No. 26-20-02; Fire Extin­ guisher P/N 50-1200; Safecraft, Inc., 2708 Teagarden St., San Leandro, CA 94577.

E. Chapter 27 (Flight Controls) (1) Component Maintenance Manual with Illustrated Parts List, Publication No. 27-50-02; Flap Control Unit, P/N: C144486-3-003; Microtecnica SPA, 147 via Madama Cristina, Torino 10126, . (2) Component Maintenance Manual with Illustrated Parts List, Publication No. 27-50-03; Flap Posi­ tion Indicator, P/N: C145159-1; Microtecnica SPA, 147 via Madama Cristina, Torino 10126, Italy. (3) Component Maintenance Manual with Illustrated Parts List, Publication No. 27-50-05; Flap Actua­ tors, PIN: C144487-1, PIN: C144488-1; Microtecnica SPA, 147 via Madama Cristina, Torino 10126, Italy. (4) Component Maintenance Manual with Illustrated Parts List, Publication No. 27-50-06; Flap Power Unit, P/N: C144483-1; Microtecnica SPA, 147 via Madama Cristina, Torino 10126, Italy.

F. Chapter 29 (Hydraulic Power) (1) Maintenance Manual, Publication No. 2496; Main Filter Manifold Assembly, P/N: 2247HOOO; Nor­ malair-Garrett Ltd., Customer Support Group, Bournemouth Inti. Airport, Christchurch, Dorset BH236NW, England. (2) Component Maintenance Manual with Illustrated Parts List, Publication No. 2499, 32-20-04; Auxil­ iary Filter Manifold Assembly, P/N: 2248H000-004; Normalair-Garrett Ltd., Customer Support Group, Bournemouth Inti. Airport, Christchurch, Dorset BH236NW, England. (3) Component Maintenance Manual with Illustrated Parts List, Publication No. 29-12-01; Reservoir Pressurization Control Module, P/N: ZVM11-1; Circle Seal Controls Inc., 2301 Wardlow Dr., Corona, CA 91720. (4) Component Maintenance Manual with Illustrated Parts List, Publication No. 29-10-60; Pump Motor Package, Hydraulic Assembly, Model No. PMP05VC-75-01 -02, P/N: 66157-01, -02; Parker-Han­ nifin Corporation, ABEX NWL Aerospace, 2220 Palmer Ave., Kalamazoo, Ml 49001.

G. Chapter 30 (Ice and Rain Protection) (1) Component Maintenance Manual with Illustrated Parts List, Publication No. 30-81-23; Ice Detec­ tor, P/N: 0871 HN2; Rosemount Aerospace Inc., 12001 Technology Dr., Eden Prairie, NM 55344- 3695.

H. Chapter 32 (Landing Gear) (1) BF Goodrich Aerospace Component Maintenance Manual with Illustrated Parts List, Publication No. 32-48-71; Main Brake Assembly, P/N: 2-1579-1, P/N: 2-1579-2; BF Goodrich Co., 101 Waco St., Troy, OH 45373-3835. (2) BF Goodrich Aerospace Component Maintenance Manual with Illustrated Parts List, Publication No. 32-48-72; Main Wheel Assembly, P/N: 3-1545-1; BF Goodrich Co., 10 1 Waco St., Troy, OH 45373-3835.

EFFECTIVITY: ALL INTRO Page 5 I Jan 10/11 MM·104 LEARJET 45 MAINTENANCE MANUAL

(3) Component Maintenance Manual with Illustrated Parts List, Publication No. CMM-001 ; Nose Land­ ing Gear Strut Assembly, PIN: 2342100-24; Learjet Inc., P.O. Box 7707, Mid-Continent Airport, Wichita, KS 67277-7707. (4) Component Maintenance Manual with Illustrated Parts List, Publication No. CMM-002; Main Land­ ing Gear Strut Assembly, P/N: 6632101000; Learjet Inc., P.O. Box 7707, Mid-Continent Airport, Wichita, KS 67277-7707. (5) Component Maintenance Manual with Illustrated Parts List, Publication No. CMM-003; Main Land­ ing Gear Actuator, P/N: 200-0300; Learjet Inc., P.O. Box 7707, Mid-Continent Airport, Wichita, KS 67277-7707. (6) Maintenance Manual, Publication No. 2494, 32-30-01; Landing Gear Control Valve Manifold, P/N: 2245H000-002; Normalair-Garrett ltd., Customer Support Group, Bournemouth Inti. Airport, Christchurch, Dorset BH236NW, England. (7) Maintenance Manual, Publication No. 2587; Uplock, Nose Landing Gear, P/N:2269H000-003; Nor­ malair-Garrett Ltd., Customer Support Group, Bournemouth Inti . Airport, Christchurch, Dorset BH236NW, England. (8) Component Maintenance Manual with Illustrated Parts List, Publication No. AP-494, 32-46-14; Nose Wheel Assembly, P/N:9544207-4; Aircraft Braking Systems Corp., 1204 Massillon Rd ., Akron, OH 44306-4186. (9) Nondestructive Testing Manual with Procedures, Publication No. AP-763, 32-42-05; Eddy Current Inspection; Aircraft Braking Systems Corp., 1204 Massillon Rd., Akron, OH 44306-4186. (10) Goodyear Service Bulletin GY SB 98-32-007, dated November 17, 1998, Goodyear Tire and Rub­ ber Company, Aviation Products Division, 1144 East Market Street, Akron, OH 44316-0001.

I. Chapter 34 (Navigation) (1) Installation and Operating Instructions for Standby Altimeter 2D540 (50B700), Publication No. 060894, Avionix Corp., 8 Romanelli Ave., South Hackensack, NJ 07606. (2) PRIMUS 440/66/880 Digital Weather Radar System, Publication No. A09-3944-01, ATA 34-42-12; Honeywell Aerospace Electronic Systems, P.O. Box 21111, Phoenix, AZ, 85036-1111.

J. Chapter 35 (Oxygen) (1) Component Maintenance Manual with Illustrated Parts List- 898 Series and 804882 Series Cylin­ der and Regulator Assembly, 35-21-99, Scott Aviation, 225 Erie Street, Lancaster, NY 14086- 9502.

K. Chapter 49 (Airborne Auxiliary Power) (1) Gas Turbine Engine Component Maintenance Manual, ATA Publication No. 49-31-79; P/N: 3883900-1; Honeywell Inc., 111 S. 34th St., P.O. Box 52181, Phoenix, AZ 85072-2181 . (2) Maintenance Manual 23700 DC Generators and Starter- Generators; TRW Aeronautical Systems, Lucas Aerospace, 30 Van Nostram Avenue, Englewood, NJ 07631-4396.

L. Chapter 71 (Power Plant) ( 1) Aircraft Engine Light Maintenance Manual, Publication No. 72-03-06; P/N: 3060020-7, Honeywell Inc., 111 S. 34th St., P.O. Box 52181, Phoenix, AZ 85072-2181.

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Record of Temporary Revisions

Revision Insertion Inserter's Removal Remover's Status Date Location Number Date Initials Date Initials

4-1 Inactive Apr 13/99 4-10-01 Jun 25/99 Rev. 9

4-2 Inactive Jan 2/01 4-10-01 Mar 16/01 Rev. 23

4-3 Inactive May 16/03 4-10-01 Jun 13/03 Rev 32

4-4 Inactive Jul10/03 4-1 1-00 Feb 13/04 Rev 33

4-5 Inactive Sep 8/03 4-10-01 Dec 15/03 TR 4-7

4-6 Inactive Sep 8/03 4-11 -00 Feb 13/04 Rev33

4-7 Inactive Dec 15/03 4-10-01 Feb 13/04 Rev 33

4-8 Inactive Feb 14/05 4-10-01 Aug 29/05 Rev 36

4-9 Inactive Feb 14/05 4-10-01 Aug 29/05 Rev 36

4-10 Inactive Nov 18/05 4-11-00 Feb 15/06 TR 4-16

4-1 1 Inactive Nov 18/05 4-10-01 Dec 15/05 TR 4-15

4-12 Inactive Nov 28/05 4-10-01 Apr 24/06 Rev 38

4-13 Inactive Nov 28/05 4-11-00 Apr 24/06 Rev 38

Page 1 I 4-RTR Jan 10/11 MM- 104 LEARJET 45 MAINTENANCE MANUAL

Record of Temporary Revisions

Revision Insertion Inserter's Removal Remover's Status Date Location Number Date Initials Date Initials

4-14 Inactive Nov 28/05 4-1 1-00 Apr 24/06 Rev 38

4-15 Inactive Dec 15/05 4-10-01 Apr 24/06 Rev 38

4-16 Inactive Feb 15/06 4-1 1-01 Apr 24/06 Rev 38

4-17 Inactive May 31/07 4-10-01 Aug 27107 Rev42

4-1 8 Inactive May 31 /07 4-11-00 Aug 27107 Rev42

4-19 Never Released

4-20 Inactive Sept 25/07 4-10-01 Dec 24/07 Rev43

4-21 Never Released

4-22 Not yet released

4-23 Never Released

4-24 Never Released

4-25 Inactive May 1/08 04-10-01 Aug 25/08 Rev 45

4-26 Inactive May 1/08 04-11-00 Aug 25/08 Rev45

Page 2 I 4-RTR Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MANUAL

Record of Temporary Revisions

Revision Insertion Inserter's Removal Remover's Status Date Location Number Date Initials Date Initials

4-27 Inactive Dec 23/08 4-10-01 Jul27/09 Rev48

4-28 Inactive Nov 14/08 4-10-01 Dec 22/08 Rev46

4-29 Never Released

4-30 Never Released

4-31 Inactive Jan 25/1 0 4-10-01 Mar 29/10 Rev 50

4-32 Inactive Mar 30/10 4-11-00 Jun 28/10 Rev 51

4-33 lnaclive Nov 29/10 4-11-00 Jan 10/11 I Rev 53

Page 3 4-RTR Jan 10/1 1 MM-104 LEARJET 45 MAINTENANCE MANUAL

Chapter Chapter Section Section Subject Page Date Subject Page Date

* 4-RTR 1 Jan 10/11 • 4-10-01 32 Jan 10/11 * 4-RTR 2 Jan 10/11 • 4-10-01 33 Jan 10/11 * 4-RTR 3 Jan 10/11 • 4-10-01 34 Jan 10/11 * 4-LOEP Jan 10/11 • 4-10-01 35 Jan 10/11 * 4-CONTENTS Jan 10/11 • 4-10-01 36 Jan 10/11 • 4-00-00 1 Jan 10/1 1 • 4-11-00 1 Jan 10/11 • 4-00-00 2 Jan 10/1 1 • 4-11-00 2 Jan 10/1 1 • 4-00-00 3 Jan 10/11 • 4-11-00 3 Jan 10/1 1 • 4-10-00 1 Jan 10/1 1 • 4-11-00 4 Jan 10/11 • 4-10-00 2 Jan 10/11 4-12-00 1 Aug 29/05 • 4-10-00 3 Jan 10/11 • 4-10-00 4 Jan 10/11 • 4-10-00 5 Jan 10/11 • 4-10-01 1 Jan 10/11 • 4-10-01 2 Jan 10/11 • 4-10-01 3 Jan 10/11 • 4-10-01 4 Jan 10/11 • 4-10-01 5 Jan 10/11 • 4-10-01 6 Jan 10/11 • 4-10-01 7 Jan 10/11 • 4-10-01 8 Jan 10/11 • 4-10-01 9 Jan 10/11 • 4-10-01 10 Jan 10/11 • 4-10-01 11 Jan 10/11 • 4-10-01 12 Jan 10/11 • 4-10-01 13 Jan 10/11 • 4-10-01 14 Jan 10/11 • 4-10-01 15 Jan 10/11 • 4-10-01 16 Jan 10/11 * 4-10-01 17 Jan 10/11 • 4-10-01 18 Jan 10/11 • 4-10-01 19 Jan 10/11 • 4-10-01 20 Jan 10/11 • 4-10-01 21 Jan 10/11 • 4-10-01 22 Jan 10/11 • 4-10-01 23 Jan 10/11 • 4-10-01 24 Jan 10/11 • 4-10-01 25 Jan 10/1 1 • 4-10-01 26 Jan 10/11 • 4-10-01 27 Jan 10/11 • 4-10-01 28 Jan 10/11 • 4-10-01 29 Jan 10/11 • 4-10-01 30 Jan 10/11 • 4-10-01 31 Jan 10/11

Insert latest revised pages; destroy superseded or deleted pages.

• Asterisk indicates pages revised, added, or deleted by the current revision. The portion of the text affected by the current revision is indicated by a vertical line in the outer margin of the page.

Page 1 4-LOEP Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MANUAL

Chapter Section Subject Subject Page

AIRWORTHINESS LIMITATIONS

Description 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 00 0 0 0 0 0 0 0 0 0 0 0 0 0 00 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 00 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 00 0 0 0 04-00-00

Definition 000 000 0 0 00 0 0 0 oo o o 00 0 00 00 0000 00 oooo o 0 0 00 Oo 00 Oo O o o 0 000 00 0000 00 0000 o o oo 000 oo o o 00 00000 00 0000 00 ooo oo oo 000 0 0 0 ooo o oo 00 00 00 0 00 04-00-00

CERTIFICATION MAINTENANCE REQUIREMENTS - COMPONENT AND SYSTEM CHECKS

Time Compliance 000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000000 04-10-00

Certification Maintenance Requirements 0 000 00 00 0000 0 00000000 000 00000000 00 000 00 00 0 0 00 00 0 00 000000 00 00 0 0 0 04-10-00

CERTIFICATION MAINTENANCE REQUIREMENTS- STRUCTURE CHECKS

Time Compliance oooooooooooooooooooooooooooooooooooooo oooooooooo OOOooooOOooooo ooooooooooooooooooooooooooooooooooooooooo oo 04-10-01

Certification Maintenance Requirements - Structure Checks oooo oo oooooooooooooooooooooo 0000 04-1 0-01

AIRWORTHINESS LIMITATIONS - REPLACEMENT REQUIREMENTS

Time Compliance 0 00 00 0 0 00 0 0000 00 0 0 0000 00 0000 00 000 00 0 000 00 00 00 000000 0 000 000 0000 00 00 0000 000 00 00 00 00000 00 0000 0 00 000 0 00 0 0 00 00 04-11-00

Replacement Requirements .. oooooooooOOOOooooooo•oooooo • • oo.oooooooooo • •oo •oo ••o ooo . ... oooooooooooo •• oo.OOOO 04-11-00

Replacement Items . oo 00 00 00 00 00 ...... 00 00 00 00 00 00 00 00 00 00 00 00 0 0 oo• 0000 0000 00000 00 00 0000 oo• 00 00 00 00 0 000 0 00 oo • · 00 00 04-11-00

MAINTENANCE REQUIREMENTS BY AIRCRAFT EFFECTIVITY

Time Compliance oooooooooooooooooooooooooooo••oooooooooooooo • •oooo • •ooooooo oo ooooo •• oo.oooooooooooooooo•• •oo• oooooooooooo 04-12-00

Maintenance Requirements by Effectivity 00 oooooo· 00 oooooooo•oooooooo· .. oooooooo• oo • oooo· 00 0000 0000 .... 04-12-00

Page 1 I 4-CONTENTS Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MANUAL

AIRWORTHINESS LIMITATIONS

1. Description (See Figure 1.)

A. The Airworthiness Limitations section is FAA approved and specifies maintenance required under Parts 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. This chapter outlines the maintenance requirements for aircraft components, systems, and structures determined to be life limited and/or require monitoring through scheduled maintenance.

2. Definition

A. This chapter contains four sections as outlined below: (1) Certification Maintenance Requirements - Component and System Checks - Certification Mainte­ nance Requirements (4-1 0-00) lists aircraft components and systems which require monitoring through scheduled maintenance. (2) Certification Maintenance Requirements - Structure Checks (4-1 0-01) lists aircraft structural items which require monitoring through scheduled maintenance. (3) Airworthiness Limitations- Replacement Requirements (4-11-00) describes and lists life limited aircraft components or structures which are to be replaced at a specific time. (4) Maintenance Requirements by Aircraft Effectivity (4-12-00) lists structural and/or system changes, custom installations, and repairs done on aircraft or groups of aircraft and contains only those pages applicable to operators aircraft. These tasks must be controlled by the operator. Items listed in this section are not contained in Chapter 5.

B. Inspection tolerances (1) The following specifies the allowable inspection tolerances for component and system checks and structure checks: (a) Items marked by one asterisk(") in Sections 4-10-00 and 4-10-01 indicates that the inspection task interval cannot be changed, increased, or deleted without the approval of the certification airworthiness authority. The inspection tolerances indicated in Chapter 5, Section 5-1 0-00 are not applicable to these tasks. (b) Items marked by two asterisks(**) in Sections 4-10-00 and 4-10-01 indicates that the inspec­ tion task can be adjusted to agree with the inspection tolerances indicated in Chapter 5, Sec­ tion 5-10-00, but the task cannot be changed or deleted without prior approval of the airworthiness authority.

NOTE: The inspection tolerances are not permitted to be accumulative tolerances. For example, if an operator performs a 300 Hour certification check requirement at 325 hours, the next check must still be performed at 600 hours.

(2) The following specifies the allowable tolerances for replacement items: (a) Replacement items that are designated with one asterisk(*) in Section 4-11-00 are mandatory replacement items by FAA certification basis and cannot be changed, increased, or deleted without the approval of the certification airworthiness authority. The inspection tolerances listed in Chapter 5, Section 5-10-00 are not applicable to those items with one asterisk (*).

EFFECTIVITY: ALL Page 1 I 04-00-00 Jan 10/11 MM· 104 LEARJET 45 MAINTENANCE MANUAL

(b) Replacement items that are designated with two asterisks (**) in Section 4-11-00 are part of the manufacturer's recommended maintenance program and can be adjusted according to the tolerances listed in Chapter 5, Section 5-10-00. Vendor recommendations, service experience, and engineering assessment are all factors considered in these recommendations.

EFFECTIVITY: ALL Page 2 I 04-00-00 Jan 10/11 MM·104 LEARJET 45 MAINTENANCE MANUAL

APPROVED BY L ~ 2/J} z;:_k.,..._~

~ Margaret Kline, Manager Aircraft Certification Office Federal Aviation Administration Wichita, Kansas

OA TE OF APPROVAL ___:f.....;/i-/-f~:-p+-,/..:...J..:..{' ;_/(_j ___

FAA Approval Figure 1

EFFECTIVITY: ALL Page 3 04-00-00 Jan 10/11 MM·104 LEARJET 45 MAINTENANCE MANUAL

CERTIFICATION MAINTENANCE REQUIREMENTS - COMPONENT AND SYSTEM CHECKS

1. Time Compliance

A. Certification Maintenance Requirements (1) For the application of Certification Maintenance Requirements, the following definitions apply: (a) Flight Cycle - A complete sequence covering taxi, takeoff, climb, cruise, descent, approach, touchdown, and taxi, including any number of touch-and-go operations. (b) Landing - A sequence covering the approach and touchdown phases. Each touch-and-go operation is considered a landing. (c) Flight Hours - Flight hours are the accumulated time calculated from takeoff to final touch­ down.

ZONEI MAINTENANCE REQUIREMENTS -COMPONENT IRN INTERVAL ACCESS AND SYSTEM CHECKS

100 NOSE

03510005 120 •• Oxygen Cylinder Low Pressure Relief Valve - Perform 5,195 Hours. Functional Test.

N3510013 120 •• Oxygen Cylinder and Remote Oxygen Fill Valves - 1, 500 Hours. Perform Periodic Check. (Effective on Aircraft 45-005 thru 45-244 modified Q.er SB 45-12-1 and Aircraft 45-245 and Subsequent.!

200 FORWARD FUSELAGE

02130002 220 •• Pressurization Control System - Perform Functional 1 ,200 Hours. Test.

A2210033 220 •• Autopilot System - Perform Autopilot Disconnect Tone 900 Hours. Test.

A2300000- 220 •• Engine Indicating and Crew Alerting System (EICAS)- 1 ,000 Hours. 4A Perform Radio Management Units (RMU) Backup Engine Page Check.

A2300000- 220 •• Engine Indicating and Crew Alerting System (EICAS) - 2,300 Hours. 48 Perform Radio Management Units (RMU ) Power Supply Check.

R2431003 220 •• Battery Warning System - Perform Functional Test. 2,400 Hours. (Refer to 24-31-00.) (Effective on Aircraft with Ni-Cad batteries installed.!

82450000 220 .. Generator Fail Indication - Perform Operational Check. 300 Hours.

EFFECTIVITY: NOTED Page 1 I 04-10-00 Jan 10/11 MM·104 LEARJET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUIREMENTS - COMPONENT IRN INTERVAL ACCESS AND SYSTEM CHECKS

H2450001 220 •• Auxiliary Power Supplies - Perform Functional Test. 600 Hours.

82450002 220 •• Electrical System Control - Perform Operational Check. 1,200 Hours.

H2450023 200 ** EMER BATT LOW and GEN AMPS HIGH Indication- 600 Hours. Perform Operational Check.

J2620000 220 •• Engine Fire Extinguishing System Fire Switch - Perform 5,000 Hours. Functional Test. I T2620001 220 •• Firewall Shutoff Valves - Perform Operational Check. 2,500 Hours. A2711001 220 •• Aileron Trim Tab Control System - Perform Operational 600 Hours. Check.

A2712000 220 •• Roll Disconnect - Perform Operational Check. 600 Hours.

A2721001 220 •• Rudder Trim System - Perform Operational Check. 600 Hours.

D2740003 220 •• Horizontal Stabilizer Actuator Secondary Trim - Perform 600 Hours. Functional Test.

D2740004 220 •• Horizontal Stabilizer Actuator Primary Trim - Perform 600 Hours. Functional Test.

F2840003 220 .. Fuel Quantity Signal Conditioner - Perform Functional 1,200 Hours. Test to Veri fy Weight-on-Wheels (WOW) inputs. (Effective on Aircraft 45-005 thru 45-194 modified ger SB 45-28-5 and Aircraft 45-195 and Subseg.uent.1

H3010000 220 •• Wing/Stab Anti-Ice Switch - Perform Operational Check. 600 Hours.

A3030000 220 •• PitoUStatic Heat System - Perform Operational Check. 3,000 Hours.

T3040000 220 •• Windshield Anti-ice- Perform Functional Test of the 600 Hours. I Windshield Anti-ice System Controller 83100000- 220 •• Integrated Avionics Computer- Perform Symbol 1,000 Hours. 4A Generation Reversion Check.

83100000- 220 •• Engine Indicating and Crew Alerting System (EICAS} - 1,200 Hours. 48 Perform Data Acquisition Units (DAU) Reversion Check.

A3400000- 220 •• Air Data Computers - Perform Reversion Check. 3,000 Hours. 4A

A3400000- 220 "* Attitude Heading Reference System (AHRS)- Perform 1,000 Hours. 48 Power Supply Check.

EFFECTIVITY: NOTED Page 2 04-10-00 Jan 10/11 MM -104 LEARJET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUIREMENTS- COMPONENT IRN INTERVAL ACCESS AND SYSTEM CHECKS

A3400000- 220 **Attitude Heading Reference System (AHRS)- Perform 1 ,000 Hours. 4C AHRS Reversion Check.

K3500021 200 ** Oxygen System Low Pressure Supply Hoses - Perform 6,000 Flight Operational Check. Ensure that hoses are free of Hours. obstructions. (Effective on Aircraft 45-033, 45-035, 45- 195, and 45-207.1

03510002 230 ** Oxygen System - Perform Operational Check. 300 Hours.

03510003 220,230 ** Cabin Low Pressure Oxygen Distribution Flex Hoses - 600 Hours. Perform Functional Test.

S3510014 220 •• Oxygen System Altitude Compensating Regulator- 600 Hours. Perform Functional Test. (Refer to 35-20-06.) (Effective on Aircraft 45-005 thru 45-169 modified b'f. $845-35-1 extended duration OX'iiJ.en S'f.Stem installed and 45-170 and Subseguent.)

03510018 230 **Oxygen Cylinder Lower Pressure Relief Valve- Perform 5,195 Hours. functional test. (Effective on aircraft eguiQ.Q.ed with increased caQ.acit'i. OX'f.Q.en S'f.Siem.)

N3510019 230 ** Oxygen Cylinder and Remote Oxygen Fill Valves - 1 ,500 Flight Perform periodic check. (Effective on Aircraft 45-005 thru Hours. 45-244 modified Q.er SB 45-12-1 and Aircraft 45-245 and Subseguent, and on aircraft eguiQ.Q.ed with increased caQ.acit'i. OX'f.gen S'f.Stem./

A3610000 220 ** Bleed Air System - Perform Functional Test. 600 Hours.

A3610001 220 ** Pylon Overheat Thermostat and Electrical System - 600 Hours. Perform Functional Test.

H4900011 200 ** APU Generator - Perform overvoltage protection check. 1 ,200 Hours.

05600002 220 ** Windshield - Perform Rain Removal Coating 300 Hours. Effectiveness Test.

300 AFT FUSELAGE/

L2150056 300 ** Auxiliary Heat System- Perform Functional Test. 600 Hours. (Effective on Aircraft 45-250 and subseguent eguiQ.Q.ed with Keith Products vaQ.or air C'f.Cie air conditioning S'f.Stem using refrigerant R-134./

EFFECTIVITY: NOTED Page 3 04-10-00 Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUI REMENTS- COMPONENT IRN INTERVAL ACCESS AND SYSTEM CHECKS

L2150057 300 ** Auxiliary Heat System - Perform Auxiliary Heater 1,200 Hours. Electrical and Temperature Switch Test. (Effective on Aircraft 45-250 and subsequent eg_uiQ.Q.ed with Keith Products vaaor air C'f.Cie air conditioning S"t_stem using refrigerant R-134.1

A2731002 220/320 •• Elevator Disconnect System - Perform Operational 600 Hours. Check.

82731001 320 •• Pitch Trim - Perform Operational Check of Elevator 300 Hours. Override Actuator.

H2840001 320 • Dual Fuel Flow Convertor (DFFC) (P/N 10540806F07) - 300 Flight Hours Perform Acceptance Test and Low Temperature or 12 Months, Screening. whichever is greater. NOTE: Removal and replacement of DFFC is required for these tests. After removal, return DFFC to Learjet with a Parts Return Claim Form so unit can be exchanged with serviceable unit and returned to vendor for testing.

400 POWERPLANTS, NACELLES, AND TH RUST REVERSERS

A3020000 430/440 •• Nacelle Anti-ice System - Perform Functional Test. 1,200 Hours.

F7720002 410/420 •• Engine Temperature Indicating System - Perform ITT 600 Hours. Margin Check. (Effective on Aircraft 45-080 thru 45-169 not modified aer SB 45-22-4.1

D7830078 400 •• Thrust Reverser System Throttle Retard Actuator - 2,400 Hours. Perform Operational Check.

500/600 LEFT/RIGHT WING

A2760001 540/640 •• Spoiler Actuator Check Valve - Perform Operational 600 Hours. Check.

A2760002 540/640 •• Spoiler System - Perform Spoiler Authority with Flaps 600 Hours. Check.

700 LANDING GEAR AND RELATED SYSTEMS

02460001 720/730 •• Power Distribution System - Perform Squat Switch 1, 200 Hours. Check.

EFFECTIVITY: NOTED Page4 I 04-10-00 Jan 10/ 11 MM· 104 LEARJET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUIREMENTS- COMPONENT IRN INTERVAL ACCESS AND SYSTEM CHECKS

03220005 720/730 •• Main Inboard Gear Door Uplock Release Mechanism - 300 Hours. Using gear freefall handle, release inboard gear doors and perform visual inspection. Verify that doors have released by activating gear freefall handle.

A3230001 710/720/ •• Landing Gear - Perform Emergency Gear Extension 600 Hours. 730 Functional Test.

H3240004 720/730 •• Emergency/Parking Brake Switch - Verify that 300 Hours. "Emergency/Parking Brake" message illuminates on EICAS when parking brake is set and throttles are moved above MCR detent.

A3240005 720/730 ** Brake Hydraulic Fuses- Perform Functional Test. 1,200 Hours.

A3240006 720/730 •• Brake Shuttle Module- Perform Functional Test. 1,200 Hours.

A3240007 720/730 ** Brake Shuttle Valves- Perform Functional Test. 2,400 Hours.

N3240008 720/730 ** Emergency/Parking Brake Accumulator - Perform 300 Hours. functional test.

A3240009 720/730 ** Brake Pressure Transducers- Perform Functional Test. 4,800 Hours.

B3261000 Replaced by IRN 02460001

EFFECTIVITY: ALL Page 5 I 04-10-00 Jan 10/11 MM·104 LEARJET 45 MAINTENANCE MANUAL

CERTIFI CATION MAINTENANCE REQUIREMENTS - STRUCTURE CHECKS

1. Time Compliance

A. Certification Maintenance Requirements - Structure Checks (1) For the application of Certifi cation Maintenance Requirements, the following definitions apply: (a) Flight Cycle - A complete sequence covering taxi, takeoff, climb, cruise, descent approach, touchdown, and taxi, including any number of touch-and-go operations. (b) Landing - A sequence covering the approach and touchdown phases. Each touch-and-go operation is considered a landing. (c) Flight Hours - Flight hours are the accumulated time calculated from takeoff to final touch­ down.

ZONE/ MAINTENANCE REQU IREMENTS -STRUCTURE IRN INTERVAL ACCESS CHECKS

200 FORWARD FUSELAGE

K2700007 230 • Aileron Control System Primary Cables- Remove from 4,800 Flight Hours aircraft and perform detailed visual inspection. from installation, 4,800 Flight Hours thereafter.

K2700008 230 • Elevator Control System Primary Cables - Remove 4,800 Flight Hours from aircraft and perform detailed visual inspection. from installation, 4,800 Flight Hours thereafter.

K2700009 230 • Rudder Control System Primary Cables - Remove 4,800 Flight Hours from aircraft and perform detailed visual inspection. from installation, 4,800 Flight Hours thereafter.

E5310001 230CL, • Longeron, Internal (between FS 384 and FS 433)- 10,000 Flight 230DL, Perform visual inspection . Hours Initial, 230EL, 10,000 Flight 230CR, Hours Repeat. 230DR, 230ER

E5310002 220AL, * Flight Deck Longeron - Perform visual inspection (FS 10,000 Flight 220BL, 149- FS 196). Inspect flight deck longeron stiffeners, Hours Initial, 220DL, webs, and cutouts. 10,000 Flight 220AR, Hours Repeat. 220BR, 220DR

EFFECTIVITY: ALL Page 1 I 04-10-01 Jan 10/ 11 MM· 104 LEARJ ET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUIREMENTS- STRUCTURE IRN INTERVAL ACCESS CHECKS

P5310003 270 • Aft Pressure Bulkhead Support Post (FS 457)- 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5310004 270 • Aft Pressure Bulkhead Frame Periphery- Perform 10,000 Flight Eddy Current Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5310006 120AR, • Forward Pressure Bulkhead - Perform Eddy Current 10,000 Flight 130AL Inspection. Hours Initial, 10,000 Flight Hours Repeat.

A5310007 270 • Aft Pressure Bulkhead Bottom Shear Diaphragm - 10,000 Flight Perform Detailed Visual inspection. Inspect bulkhead Hours Initial, post attachment fastener holes and control cable slot. 10,000 Flight Hours Repeat.

E5310017 270 • Aft Pressure Bulkhead Bottom Crossmember (FS 457) 10,000 Flight - Perform Detailed Visual inspection. Inspect tee- Hours Initial, section at FS 457 flange at attachment to pressure floor. 10,000 Flight Hours Repeat.

E5310018 270 • Aft Pressure Bulkhead Panel Facing Sheets (FS 457) - 10,000 Flight Perform visual inspection. Inspect both front and aft of Hours Initial, facing sheets. 10,000 Flight Hours Repeat.

P5310027 270 • Aft Pressure Bulkhead Top Mounting Structure - 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

L5311002 210 • Nose Landing Gear Actuator Attachment on Forward 10,000 Landings Pressure Bulkhead - Perform Eddy Current Inspection. Initial, 10,000 Landings Repeat.

P5320001 230 • Fuselage Pressure Floor Step (FS 433 - FS 457) - 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

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M5323021 250DL, • Externallongeron, fastener locations, and area around 10,000 Flight 250ER wing attachments - Perform visual inspection. Inspect Hours Initial, longeron between FS 398 and FS 486, stringer 13LHS 10,000 Flight & RHS. Hours Repeat.

A5323023 250DL, • Drag Link Attachment Lug- Perform visual inspection. 10,000 Flight 250ER Hours Initial, 5,000 Flight Hours Repeat.

E5323025 220 • Forward/Aft Wheelbox Joint (FS 150)- Perform visual 10,000 Flight inspection. Inspect splice strap aft of forward pressure Hours Initial, bulkhead at intersection of attachment angle and flight 10,000 Flight deck longeron. Hours Repeat.

N5323026 230 • Upper and Lower Passenger/Crew Door Skin Cutout 4,800 Flight Hours Corners (FS 224- FS 256)- Perform Eddy Current Initial, 2,400 Flight Inspection. Inspect skin at corners of passenger/crew Hours Repeat. door cutout.

P5323027 230 • Fuselage Frame at F.S. 412 - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5323028 250 *Fuselage to Wing Attach Fittings- Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5323029 230 • Machined Frames Systems Cutouts (FS 398, FS 10,000 Flight 412, FS 432, FS 466) - Perform Eddy Current Hours Initial, 5,000 Inspection . Flight Hours Repeat.

H5323032 230 • Exterior Cabin Window Coamings (Unpainted) - 2,400 Flight Hours/ Perform Eddy Current Inspection. 24 Months Initial, 2,400 Flight Hours/ 24 Months Repeat.

P5323033 230 • Fuselage Skin at Emergency Door Egress Light and 10,000 Flight Wing Inspection Light - Perform Eddy Current Hours Initial, Inspection. 10,000 Flight Hours Repeat.

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M5323034 220 • Upper and Lower Coupe Rail and Center PosV 10,000 Flight Windshield Retainer Attachment - Perform Eddy Hours Initial, Current inspection. 10,000 Flight Hours Repeat.

P5323037 220 • Windshield Coupe Rail Tie Rod Bracket - Perform 10,000 Flight Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5323038 220 *Windshield Centerpostto Upper Coupe Rail Joint 10,000 Flight Attachment - Perform Eddy Current Inspection. Hours Initial, 7,600 Flight Hours Repeat.

05323039 230 • Machined Fuselage Frame at FS 466- Perform 10,000 Flight detailed visual inspection of the lower frame section Hours Initial, 5,000 between stringer 13 left and right, paying particular Flight Hours attention to the BL 10 splices. Confirm any crack Repeat. indications with eddy current procedures. (Effective on Aircraft 45-034 onl'f:)

P5323047 220/230 • Pressure Cabin Fuselage Crown Skin - Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 2,400 Flight Hours Repeat.

05323048 220/230 • Fuselage (Pressure Cabin)- Perform Eddy Current 10,000 Flight Inspection. Inspect pressure cabin skin (longitudinal Hours Initial, 6,625 skin cracking). Flight Hours Repeat.

P5323049 220 *Fuselage Skin at Upper and Lower Coupe Rail Run-out 10,000 Flight Joints- Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

E5323050 220 • Aft PosUWindshield Retainer Attachment - Perform 10,000 Flight Eddy Current Inspection. Inspect windshield aft post at Hours Initial, 6,797 windshield retainer fastener holes. Flight Hours Repeat.

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05323051 220/230 * Longitudinal Joints inside Pressure Cabin (FS 220 - 10,000 Flight FS 457) and skin within one stringer bay of joint - Hours Initial, 6,625 Perform NDI inspection. Inspect skin fastener holes Flight Hours along joints at stringer 10 LH and RH , stringer 2 RH , Repeat. and stringer 18 RH.

E5323053 220 *Frame Attachments to Upper and Lower Coupe Rails 10,000 Flight (FS 171 to FS 204)- Perform visual inspection. Inspect Hours Initial, the following: 10,000 Flight a. Frame attachments to lower coupe rails at FS 171, Hours Repeat. FS 182, FS 196, and FS 204. b. Frame attachments to upper coupe rails at FS 196 and FS 204. c. Gussets at fastener holes.

E5323054 220 * Tie-Rod Assembly (FS 162) (Aluminum ends) - 4,800 Flight Hours Perform visual inspection. Inspect tie-rod ends, tie-rod Initial, 4,800 Flight tubes, and tie-rod bolts. Hours Repeat.

E5323055 220 *Tie-Rod Assembly (FS 162) (Titanium ends) - Perform 9,600 Flight Hours visual inspection. Inspect tie-rod ends, tie-rod tubes, Initial, 9,600 Flight and tie-rod bolts. Hours Repeat.

F5323056 220 * Tie-Rod Fork Ends (Aluminum)- Perform Fluorescent 4,800 Flight Hours Penetrant Inspection. (Effective on Aircraft 45-001 thru Initial, 4,800 Flight 45-058.l Hours Repeat.

P5323057 220/230 * Pressure Cabin Skin at Fuselage Station 451 - 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 2,400 Flight Hours Repeat.

P5323058 220/230 * Fuselage Skin at F.S. 504 - Perform Eddy Current 10,000 Flight Inspection . Hours Initial, 5,000 Flight Hours Repeat.

05323059 220 *Stringer to Frame Joints (FS 162 to FS 213) - Perform 10,000 Flight Eddy Current Inspection. Inspect skin, stringers, and Hours Initial, frames at joints. 10,000 Flight Hours Repeat.

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ZONE/ MAINTENANCE REQUIREMENTS -STRUCTURE IRN INTERVAL ACCESS CHECKS

P5323069 220 * Circumferential Skin Joint at Forward Pressure 10,000 Flight Bulkhead - Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

E5323073 220 * Fuselage Bottom Skin Panel - Perform visual 10,000 Flight inspection. Inspect corner radius at junction of external Hours Initial, longeron and mid spar frame (FS 435). 10,000 Flight Hours Repeat.

E5323074 220 * Auxiliary Skin Panel - Perform visual inspection. 10,000 Flight Inspect corner radius at junction of keelbeam and rear Hours Initial, spar frame (FS 466). 10,000 Flight Hours Repeat.

F5323081 220 * Tie-Rod Fork Ends (Titanium, P/N R24889) - Perform 9600 Flight Hours Fluorescent Penetrant Inspection. (Effective on Aircraft Initial, 9600 Flight 45-059 and Subseg.uent and Q.rior Aircraft with titanium Hours Repeat. rod assembl'i. installed.l

H5323092 230 * Exterior Cabin Window Coamings (Painted) - Perform 4800 Flight Hours/ Eddy Current Inspection. 96 Month Initial, 4800 Flight Hours/ 96 Month Repeat.

P5323164 220 • Fuselage Skin and Doubler around ECS Duct Cutout - 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5323165 220 * Windshield Center Post to Lower Coupe Rail Joint 10,000 Flight Attachment - Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

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R5323166 200 • Skin Cut-outs/Penetrations (Pressure Cabin) - Perform 10,000 Flight Detailed Visual Inspection. Inspect skin and doublers at Hours/12 years or skin penetrations and cut-outs especially antennas, less. electrical components, and access panels. (Refer to 5- 10-00.)

NOTE: Removal of antennas, electrical components and access panels is necessary for completion of this inspection.

On Aircraft that have exceeded 12 years from C of A, perform inspection within 12 months from date of revision.

E5350000 240 • Bottom Keelbeam End Pads (FS 384 - FS 486) - 10,000 Flight Perform visual inspection. Inspect end pads around bolt Hours Initial, holes and in radii at FS 433. 10,000 Flight Hours Repeat.

N5600003 220/230 • Windshields - Perform ultrasonic inspection of the 4,800 Flight Hours structural plies. (Effective on Aircraft with Sierracin from installation, windshields installed.) 4,800 Flight Hours thereafter.

L5600010 220/230 • Cabin Windows (including the emergency exit window) 4,800 Flight Hours - Perform detailed visual inspection. Initial, 4,800 Flight Hours Repeat.

N5600012 220/230 • Windshields - Perform bolt hole inspection. (Effective 4,800 Flight Hours on Aircraft with GKN windshields installed.l from installation, 4,800 Flight Hours thereafter.

300 AFT FUSELAGE/EMPENNAGE

K2700010 310 • Elevator Control System Primary Cables - Remove 4,800 Flight Hours from aircraft and perform detailed visual inspection. from installation, 4,800 Flight Hours thereafter.

K2700012 310 • Rudder Control System Primary Cables - Remove 4,800 Flight Hours from aircraft and perform detailed visual inspection. from installation, 4,800 Flight Hours thereafter.

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N2740002 330AC, • Horizontal Stabilizer Actuator (6627401000-007) · 600 Hours. 330AR, Perform Inspection. 330BC, 330CC, NOTE: Remove Horizontal Stabilizer Actuator from 330CL, aircraft. Send actuator to Learjet on a parts 330XL, return claim form so unit can be exchanged with 330WR, serviceable unit and returned to vendor for 330YL, overhaul. 330XR Refer to Replacement Schedule section 4-11- 00 for life limited components (IRN #'s N2740023 and N2740024).

N2740025 330AC, • Horizontal Stabilizer Actuator (6627401000-007)­ 2,400 Flight Hours 330AR, Perform Detailed Structural Inspection. Initial, 2,400 Flight 330BC, Hours Repeat. 330CC, NOTE: Remove Horizontal Stabilizer Actuator from 330CL, aircraft. Send actuator to Learjet on a parts 330XL, return claim form so unit can be exchanged with 330WR, serviceable unit and returned to vendor for 330YL, overhaul and structural inspection. 330XR Refer to Replacement Schedule section 4-11· 00 for life limited components (IRN #'s N2740023 and N2740024).

P2740032 330AR, • Horizontal Stabilizer Actuator (6627401000-009)­ 1200 Hours. 330BC, Perform Inspection. (Refer to 27-40-00.) 330CL, 330XL, NOTE: Remove Horizontal Stabilizer Actuator from 330WR, aircraft. Send actuator to Learjet on a parts 330YL, return claim form so unit can be exchanged with 330XR serviceable unit and returned to vendor for overhaul.

Interval is calculated from time since new or from the Time Since Overhaul (TSO) hours.

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P2740033 330AR, • Horizontal Stabilizer Actuator (6627401000-009)- 2,400 Flight Hours 330BC, Perform Detailed Structural Inspection. Initial, 2,400 Flight 330CL, Hours Repeat. 330XL, NOTE: Remove Horizontal Stabilizer Actuator from 330WR, aircraft. Send actuator to Learjet on a parts 330YL, return claim form so unit can be exchanged with 330XR serviceable unit and returned to vendor for overhaul and structural inspection.

Interval is calculated from time since new or from the Time Since Structural Inspection (TSSI) hours.

03010006 310QR, _. Anti-Ice Manifold - Perform Baroscope Inspection. 1200 Hours. 310HL

A5310005 360 • Fuselage Fuel Cell Canted Bulkhead (FS 495)- 10,000 Flig ht Perform visual inspection, paying particular attention to Hours Initial, 5,000 main crossmember. Inspect flanges and attachments for Flight Hours cracking. Repeat.

P5323024 310AC, • Fuselage Skin Cut-outs Above Fuel Cell - Perform 10,000 Flight 310BC, Eddy Current Inspection. Hours Initial, 5,000 310AL, Flight Hours 310BL, Repeat. 310AR, 310BR

E5323068 310 • Stringer 1 RH between FS 533 and FS 543 - Perform 10,000 Flight visual inspection. Inspect stringer 1 flange and skin Hours Initial, along stringer 1 between FS 533 and FS 543. 10,000 Flight Hours Repeat.

F5331021 320CL, • Forward Canted Bulkhead (FS 630) - Perform visual 10,000 Flight 320BR inspection. Inspect at front spar upper attachment Hours Initial, 5,000 fasteners. Flight Hours Repeat.

F5331022 320DL, • Mid Canted Bulkhead (FS 657) - Perform visual 10,000 Flight 320CR inspection at mid spar upper attachment fasteners. Hours Initial, 10,000 Flight Hours Repeat.

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F5331023 320BL, • Aft Canted Bulkhead (FS 682) • Perform visual 10,000 Flight 320EL, inspection. Inspect at rear spar attachment fasteners. Hours Initial, 320DR 10,000 Flight Hours Repeat.

F5331024 320 • Vertical Stabilizer Front Spar Root Bu lkhead 10,000 Flight Attachment (FS 630)- Perform visual inspection. Hours Initial, Inspect front spar root bulkhead attachment at fastener 10,000 Flight holes. Hours Repeat.

F5331025 320 • Vertical Stabilizer Mid Spar Root Bulkhead Attachment 10,000 Flight (FS 657)- Perform visual inspection. Inspect mid spar Hours Initial, root bulkhead attachment at fastener holes. 10,000 Flight Hours Repeat.

F5331026 320 • Vertical Stabilizer Rear Spar Root Bulkhead 10,000 Flight Attachment (FS 682)- Perform visual inspection. Hours Initial, Inspect rear spar root bulkhead attachment at fastener 10,000 Flight holes. Hours Repeat.

H5450012 310HL, • Frames 39/40 (FS 512/518) at Engine Beam 10,000 Flight 310JL, Attachment- Perform Eddy Current Inspection. Inspect Hours Initial, 5,000 310QR, outer flange and frame web at engine beam attachment. Flight Hours 310RR Repeat.

E5450029 310HL, * Aft Engine Beam - Perform visual inspection. Inspect 10,000 Flight 310RR, upper capping plate, around fastener holes in the Hours Initial, 5,000 340FL, capping plate, and channel flange. Flight Hours 340GL, Repeat. 340HL, 340FR, 340GR, 340HR

P5450030 310HL, * Aft Engine Beam End Fitting - Perform Eddy Current 10,000 Flig ht 310RR, Inspection. Hours Initial, 5,000 340FL, Flight Hours 340GL, Repeat. 340HL, 340FR, 340GR, 340HR

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G5510000 330AC, • Horizontal Stabilizer Actuator Attachment Fitting - 5,000 Flight Hours 330BC, Perform Eddy Current Inspection. Initial, 5,000 Flight 330CL, Hours Repeat. 330XL, 330WR, 330AR. 330XR, 330YL I T5510004-4A 330 • Rudder Top Hinge Fitting - Perform visual inspection .. 10,000 Flight Inspect lug (FS 721 ). Hours Initial, 10,000 Flight Hours Repeat. I T5510004-48 330 • Rudder Mid Hinge Fitting - Perform visual inspection. 10,000 Flight Inspect lug (FS 721). Hours Initial, 10,000 Flight Hours Repeat. I T551 0004-4C 330 • Rudder Lower Hinge Fitting - Perform visual 10,000 Flight inspection. Inspect lug (FS 709). Hours Initial, 10,000 Flight Hours Repeat.

N5510005 330CC • Horizontal Stabilizer Rear Spar Cap - Perform Eddy 4,800 Flight Hours Current Inspection. Inspect rear spar cap and web at Initial, 2,400 Flight center splice. Hours Repeat.

NOTE: On aircraft that have exceeded 4,800 hours total time, perform inspection within 600 hours.

P5510006 320CL, • Vertical Stabilizer Front Spar and Mid Spar- Perform 10,000 Flight 320BR Radiographic Inspection. Hours Initial, 10,000 Flight Hours Repeat.

05510007 320EL, • Vertical Stabilizer Skin and Lower Aft Spar Cap- 10,000 Flight 320DR Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5510008 330FL, • Horizontal Stabilizer Primary and Secondary Attach 10,000 Flight 330ER Bolts- Perform Magnetic Particle Inspection. Hours Initial, 10,000 Flight Hours Repeat.

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P5510009 330 * Horizontal Stabilizer Mid Spar Upper Cap B.L. 0.0 to 10,000 Flight B.L. 4.0 - Perform X-ray Inspection. Hours Initial, 2,500 Flight Hours Repeat.

M5510010 330 * Horizontal Stabilizer Aft Root Rib - Perform Eddy 4,800 Flight Hours Current Inspection. Inspect aft root rib internal between Initial, 1,200 Flight mid spar and aft spar and upper and lower skins Hours Repeat. external at attachment fasteners.

NOTE: On aircraft that have exceeded 4,800 hours total time, perform inspection within 600 hours.

P5510011 330 * Hori zontal Stabilizer Mid Spar and Rear Spar Upper 10,000 Flight Flange at Root Rib -Perform Radiographic Inspection . Hours Initial, 9,720 Flight Hours Repeat.

A5510014 330 • Vertical Stabilizer Pivot Fitting Bottom Plate - Perform 10,000 Flight Detailed Visual Inspection. Inspect aft portion of bottom Hours Initial, plate through lightening hole in top plate, forward 10,000 Flight portion of bottom plate through top plate cutouts, and Hours Repeat. bottom of outside exposed surface of pivot fitting.

N5510015 330WR, • Vertical Stabilizer Pivot Fitting Top Plate - Perform 5,000 Flight Hours 330XL, Eddy Current Inspection. Initial, 2,451 Flight 330CC, Hours Repeat. 330XR, 330YL, 330DL

N5510016 330BL, * Vertical Stabilizer Pivot Fitting Tower Section Forward 5,000 Flight Hours 330BR, Radius - Perform Eddy Current Inspection. Inspect pivot Initial, 2,451 Flight 330CC, fitting at tower section radius, pivot fitting and top plate Hours Repeat. 330XL, around adjacent fasteners, and pivot fitting sides at 330WR, tower section radius. 330YL, 330XR, 330DL

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P5510017 330BL, • Vertical Stabilizer Pivot Fitting Tower Section - Perform 10,000 Flight 330BR, Eddy Current Inspection. Hours Initial, 4,641 330CC, Flight Hours 330XL, Repeat. 330WR, 330YL, 330XR, 330DL

P5510018 330 • Vertical Stabilizer Pivot Fitting Lugs - Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5510019 330 • Elevator Hinges on Horizontal Stabilizer- Perform 10,000 Flight Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5510020 330 • Horizontal Mid Spar Upper Cap - Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

A5510021 330 • Horizontal Mid Spar from Canted Rib #2 to Canted Rib 10,000 Flight #3 - Perform Detailed Visual Inspection. Hours Initial, 10,000 Flight Hours Repeat.

G5510023 330AC, • Horizontal Stabilizer Actuator Vertical Tail Attachment- 5,000 Flight Hours 330BC, Perform Eddy Current Inspection. Initial, 5,000 Flight 330CL, Hours Repeat. 330XL, 330WR, 330AR, 330XR, 330YL

P5510024 330XL, • Elevator Control Horn - Perform Eddy Current 10,000 Flight 330WR, Inspection. Hours Initial, 330CC 10,000 Flig ht Hours Repeat.

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H5510033 330CL, • Horizontal Stabilizer Actuator Attach Bolts - Perform 5,000 Flight Hours 330BR, Liquid Penetrant Inspection. Initial, 5,000 Flight 330XL, Hours Repeat. 330WR, 330YL, 330XR

N5510069 330 * Horizontal Stabilizer Mid Spar Flange Root Rib 4,800 Flight Hours Attachment- Perform Eddy Current Inspection. Initial, 2.400 Flight Hours Repeat.

P5510070 330WL, * Horizontal Stabilizer Front Spar - Perform 10,000 Flight 330VR Radiographic Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5510073 330FL, * Horizontal Stabilizer Rear Spar Upper Cap - Perform 10,000 Flight 330ER Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

E5510074 330WL, * Horizontal Stabilizer Rear Spar from Canted Rib #2 to 10,000 Flight 330VR Canted Rib #3- Perform visual inspection. Inspect rear Hours Initial, spar cap and fasteners. 10,000 Flight Hours Repeat.

E5510075 330WL, • Horizontal Stabilizer Outboard Spars and Skins 10,000 Flight 330VR Outboard of Canted Rib #3 - Perform visual inspection. Hours Initial, Inspect spar caps and fasteners. 10,000 Flight Hours Repeat.

E5510076 330WL, * Horizontal Stabilizer Front Spar from Canted Rib #2 to 10,000 Flight 330VR Canted Rib #3- Perform visual inspection. Inspect front Hours Initial, spar cap and fasteners. 10,000 Flight Hours Repeat.

N5510082 330 • Horizontal Stabilizer Rear Spar Flange Root Rib 4,800 Flight Hours Attachment - Perform Eddy Current Inspection. Initial, 2,400 Flight Hours Repeat NOTE: On aircraft that have exceeded 4,800 hours total time, perform inspection within 600 hours.

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05510091 330ER, *Horizontal Stabilizer Hinge Primary and Secondary 600 Hours 330FL Pivot Pin Installation and Attaching Hardware- Perform Detailed Visual Inspection.

P5510092 330AC, • Horizontal Stabilizer Upper Spar Splice Doubler - 10,000 Flight 330BC, Perform Eddy Current Inspection. Hours Initial, 2,500 330CC Flight Hours Repeat.

P5520001 330 * Elevator Hinge Attach Bolt- Perform Magnetic Particle 10,000 Flight Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5520002 330ML, • Elevator Hinge Pin - Perform Liquid Penetrant 10,000 Flight 330PL, Inspection. Hours Initial, 330LR, 10,000 Flight 330NR Hours Repeat.

E5520003 330 * Elevator Front Spar - Perform visual inspection. 10,000 Flight Inspect spar cap at fastener holes. Hours Initial, 10,000 Flight Hours Repeat.

E5520004 330CC • Elevator Rib #1 Cap - Perform visual inspection of rib 10,000 Flight #1 cap cross section and rib cap flanges at torque tube. Hours Initial, 10,000 Flight Hours Repeat.

P5520021 330UL, * Elevator Hinge Fittings - Perform Eddy Current 10,000 Flight 330VL, Inspection. (Effective on Aircraft 45-015 and Hours Initial, 330JL, subsequent. I 10,000 Flight 330TR, Hours Repeat. 330UR, 330HR

P5520022 330 * Elevator Hinge Primary and Secondary Attach Bolts - 10,000 Flight Perform Liquid Penetrant Inspection. Hours Initial, 10,000 Flight Hours Repeat.

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05530011 330 *Vertical Stabilizer Skin and Upper Aft Spar Cap - 9,600 Flight Hours Perform Eddy Current Inspection. Initial, 2,400 Flight Hours Repeat.

A5540000 330 * Rudder Root Rib Cap (FS 698)- Perform visual 10,000 Flight inspection. Inspect around fastener holes and lightening Hours Initial, holes. 10,000 Flight Hours Repeat.

P5540001 330QL, * Rudder Spar- Perform Detailed Visual Inspection. 10,000 Flight 330RL, Inspect spar caps and fasteners. (Refer to 5-10-00.) Hours Initial, 330SL, 10,000 Flight 330TL, Hours Repeat. 330PR, 330QR, 330RR, 330SR

P5540002 330 • Rudder Attach Bolts - Perform Liquid Penetrant 9,600 Flight Hours Inspection. Initial, 9,600 Flight Hours Repeat.

400 POWERPLANTS, NACELLES, AND THRUST REVERSERS

P5450011 450/460 * Drag Strut Attachment Fittings - Perform Eddy Current 10,000 Flight 340CL, Inspection. Hours Initial, 5,000 340CR Flight Hours Repeat.

M5450015 450/460 * Forward Engine Beam, Spar Cap and Web- Perform 10,000 Flight NDI Inspection. Hours Initial, 4,800 Flight Hours Repeat.

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ZONE/ MAINTENA NCE REQUIREMENTS - STRUCTURE IRN INTERVAL ACCESS CHECKS

P5450016 340AR, • Forward Engine Beam End Fitting - Perform Eddy 10,000 Flight 340BR, Current Inspection. Hours Initial, 4,800 340CR, Flight Hours 340DR, Repeat. 340ER, 340FR, 340AL, 340BL, 340CL, 340DL, 340EL, 340FL

P5450017 450/460 • Forward Engine Beam to Frame Attach Bolts - Perform 10,000 Flight Liquid Penetrant Inspection. Hours Initial, 5,000 Flight Hours Repeat.

M5450018 400 * Forward Engine Mount Attach Bolts - Perform 10,000 Flight Fluorescent Liquid Penetrant Inspection. Hours Initial, 4,800 Flight Hours Repeat.

F5450019 450/460 * Aft Engine Beam Attachment to Frames - Perform 10,000 Flight visual inspection . Inspect aft engine beam attachment to Hours Initial, 5,000 frames. Flight Hours Repeat.

P5450020 450/460 • Aft Engine Beam to Frame Attachment Bolt - Perform 10,000 Flight Liquid Penetrant Inspection . Hours Initial, 5,000 Flight Hours Repeat.

P5450021 450/460 • Engine Aft Isolator Mount Fittings - Perform Liquid 10,000 Flight Penetrant Inspection. Hours Initial, 5,000 Flight Hours Repeat.

A5450022 450/460 • Aft Engine Mount to End Fitting Attach Bolt - Perform 10,000 Flight Magnetic Particle Inspection. Hours Initial, 5,000 Flight Hours Repeat.

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ZONE/ MAINTENANCE REQUIREMENTS - STRUCTURE IRN INTERVAL ACCESS CHECKS

P5450023 450/460 • Engine to Aft Engine Mount Attach Bolts- Perform 10,000 Flight Liquid Penetrant Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5450024 450/460 * Fuselage Frames at FS 543.55 and 546.15 to Aft 10,000 Flight Engine Beam Attachment- Perform Eddy Current Hours Initial, 5,000 Inspection. Flight Hours Repeat.

P5450025 450/460 * Forward Engine Beam and Frames at Attach Holes - 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 5,000 Flight Hours Repeat.

A5450026 450/460 • Engine Drag Strut- Perform Eddy Current Inspection. 10,000 Flight Hours Initial, 5,000 Flight Hours Repeat.

P7120001 450/460 • Forward Engine Mount - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 4,800 Flight Hours Repeat.

500/600 LEFT/RIGHT WING

K2700014 540/640 * Aileron Control System Primary Cables - Remove from 4,800 Flight Hours aircraft and perform detailed visual inspection. from installation, 4,800 Flight Hours thereafter.

R2750056 540/640 • Flap Actuator Joint (PIN 145673-1) - Perform Detailed See Note, Visual Inspection. Apply Corrosion Preventive 12 Months Repeat. Compound (CPC) to joint.

NOTE: For Aircraft 45-340 thru 45-396 and Aircraft that have not complied with SBA 45-27-30, perform inspection in 3 months. For Aircraft with more than 6 months from compliance of SBA 45-27- 30, perform inspection in 3 months. For Aircraft with less than 6 months from compliance with SBA 45-27-30, perform inspection in 6 months.

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S2750057 540/640 * Flap Actuator Ballnut Sleeve 6 Months Initial, (Flap Actuator Assembly Learjet P/N 6627503000-009, 6 Months Repeat. 6627503000-011 ' 6627503000-021' 6627503000-023, 6627503000-025 and 6627503000-027, Flap Actuator Assembly Microtecnica P/N C144487-1, C144488-1, C144487-2, C144488-2, C144487-3 and C144488-3)- Perform Fluorescent Penetrant Inspection. (Refer to NDI Manual (NDI-104), Part 8, 27- 50-0 1 or 27-50-02).

NOTE: On Aircraft modified per SB 45-27-41, "Flight Controls - Modification of the Flap Actuator Ballscrew Assembly Sleeves", inspect modification half sleeve surrounding original sleeve. On Aircraft not modified per SB 45-27-41 , "Flight Controls - Modification of the Flap Actuator Ballscrew Assembly Sleeves", inspect original sleeve.

P5710001 250DL, * Wing Drag Link Attach Fitting - Perform Magnetic 10,000 Flight 250CL, Particle Inspection. Hours In itial, 4,640 250ER, Flight Hours 250DR, Repeat. 510BL, 610BR

N5710002 520GL, * Wing Box Mid Spar Lower Cap, Outboard of Joint at 9,600 Flight Hours 620GR WS 137 between Rib #7 and 8 - Perform Directed Initial, 3,580 Flight Visual Inspection. Inspect mid spar lower cap and lower Hours Repeat. skin panels. (Effective on Aircraft not modified per SB 45-11-5. "Increase Maximum Zero Fuel Weight (16,500 pounds).")

N5710004 250CC, * Wing Center Section Rear Spar- Perform Eddy 10,000 Flight 250FL, Current Inspection. Inspect rear spar lower cap from Hours Initial, 250GR, centerline toWS 33 . (Effective on Aircraft not modified 5,000 Flight 510BC per SB 45-11 -5. "Increase Maximum Zero Fuel Weight Hours Repeat. (16. 500 pounds).")

E5710005 510/610 * Wing Center Section Spar Upper Caps - Perform 10,000 Flight visual inspection. Inspect front, mid, and rear spar upper Hours Initial, caps from centerline to skin termination at WS 33. 10,000 Flight Hours Repeat. EFFECTIVITY: NOTED 04-10-01 Page 19 I Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MANUAL

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N5710006 510AC, • Wing Center Section Forward and Aft Ribs at WS 6 10,000 Flight 510AL, and Forward Ribs at WS 17 - Perform Eddy Current Hours Initial , 5,000 610AR, Inspection. (Effective on Aircraft not modified e.er SB 45- Flight Hours 510BC 11-5, "Increase Maximum Zero Fuel Weight (16,500 Repeat. eounds1."1

P5710007 510/610 • Wing to Fuselage Attach Fittings and Links - Perform 10,000 Flight Eddy Current Inspection. Hours Initial, 5,000 Flight Hours Repeat.

N5710008 520EL, * Wing Box Mid Spar Lower Cap- Perform Ultrasonic 9,600 Flight Hours 520FL, Inspection. Inspect mid spar lower cap and lower skin Initial, 2,500 Flight 620ER, panels between WS 99 and WS 137. (Effective on Hours Repeat. 620GR Aircraft not modified eer SB 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 eounds1. "1

N5710009 520FL, *Wing Box Mid Spar Lower Cap Joint at WS 137- 9,600 Flight Hours 520GL, Perform X-ray Inspection. Inspect mid spar center/outer Initial, 4,517 Flight 620FR, joint. (Effective on Aircraft not modified eer SB 45-11-5, Hours Repeat. 620GR "Increase Maximum Zero Fuel Weight U6,500 eounds1. "1

N5710010 510/610 ·Wing Box Rear Spar Lower Cap Inboard of Joint at 9,600 Flight Hours WS 81 -Perform Ultrasonic Inspection. Inspect rear Initial, 960 Flight spar lower cap between skin termination at WS 48 and Hours Repeat. closing rib at WS 60. (Effective on Aircraft not modified eer SB 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 eounds1. "1

N5710011 510AZ, * Wing Box Rear Spar Lower Cap Joint at WS 81 - 10,000 Flight 520CL, Perform X-ray Inspection. Inspect center and outer rear Hours Initial, 520DL, spars, lower splice plate, and lower skin between WS 60 2,500 Flight 610AZ, and WS 90. (Effective on AircratJ. not modifi~d eer SB Hours Repeat. 620CR, 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 620DR eounds)."1

N5710012 520DL, * Wing Box Rear Spar Lower Cap Outboard of Joint at 9,600 Flight Hours 620DR WS 81 to Rib #6- Perform Detailed Visual Inspection. Initial, 3,443 Flight Inspect outer rear spar lower cap and aft lower skin Hours Repeat. panel outboard of rear splice at WS 90 . (Effective on Aircraft not modified eer SB 45-11-5, "lncr~ase Maximum Zero Fuel Weight (16,500 eounds1. "1

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N5710013 510/610 • Wing Box Rear Spar Lower Cap Skin Termination at 10,000 Flight MS 48- Perform Eddy Current Inspection. Inspect rear Hours Initial, spar lower cap between WS 33 and WS 48. (Effective 1 ,077 Flight on Aircraft not modified eer SB 45-11-5, "Increase Hours Repeat. Maximum Zero Fuel Weight (16,500 eounds/.'2

N5710014 500/600 * Wing Box Rear Spar Flap Track Cut-outs - Perform 10,000 Flight Eddy Current Inspection. Inspect flap track cut-outs at Hours Initial, 5,000 WS 65, WS 126, and WS 184 on rear spar. (Effective on Flight Hours Aircraft not modified eer SB 45-11-5, "Increase Repeat. Maximum Zero Fuel Weight (16,500 eounds)."l

P5710015 540DZ, * Wing Box Rear Spar at Aileron Hinge - Perform Eddy 10,000 Flight 540EZ, Current Inspection. Hours Initial, 5,000 540FZ, Flight Hours 540GZ, Repeat. 640DZ, 640EZ, 640FZ, 640GZ

N5710016 520AL * Wing Box Basic Skin/Stringer, Lower Skin - Perform 10,000 Flight thru Visual Inspection. Inspect outboard wing forward and aft Hours Initial, 5,000 520ML, lower skin panels and stringers. (Effective on Aircraft Flight Hours and not modified eer SB 45-11-5, "Increase Maximum Zero Repeat. 620AR Fuel Weight (16,500 eounds)."1 thru 620MR

N5710017 520AL * Wing Box Basic Skin/Stringer at Stringer Run-Out, 10,000 Flight thru Lower Skin - Perform Visual Inspection. Inspect stringer Hours Initial, 520ML, run-outs in forward and aft lower skin panels. (Effective 10,000 Flight and on Aircraft not modified eer SB 45-11-5, "Increase Hours Repeat. 620AR Maximum Zero Fuel Weight (16,500 eounds). "1 thru 620MR

P5710018 510/610 * Wing Lower Skin at Mid Spar Span Wise Joint - 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

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E5710019 510/610 * Wing Box, Upper Skin, Skin/Stringer and Spar Caps - 10,000 Flight Perform visual inspection. Inspect upper wing spar Hours Initial, caps, skin panel, and stringers of outer wing. 10,000 Flight Hours Repeat.

E5710020 510/610 * Wing Box Ribs - Perform visual inspection. Inspect all 10,000 Flight wing box ribs except closing rib between front and mid Hours Initial, spars and closing rib between mid and rear spar. 10,000 Flight Hours Repeat.

N5710021 520AL, * Center Section Mid Spar Lower Cap - Perform Eddy 10,000 Flight 520BL, Current Inspection. Inspect mid spar from centerline Hours Initial, 2,500 520CL, splice plate to skin termination at MS 33. (Effective on Flight Hours 620AR, Airg_ratt. nQ( mQt;/jfi~tJ. Q.~r S.B 4Q.-11-Q., "lnr;.r~s;J.~~ Repeat. 620BR Maximum Zero Fuel Weight (16,500 Q.ounds/."1

N5710022 520AL, * Center Section Mid Spar Centerline Joint - Perform 10,000 Flight 520BL, Eddy Current Inspection. Inspect center mid spar Hours Initial, 2,500 520CL, (centerline toWS 17), lower splice plate, and center mid Flight Hours 620AR, spar joint fi tting lower cap. (Effective on Aircraft not Repeat. 620BR modified Q.er SB 45-11-5, "Increase Maximum Zero Fuel Weight (.16,500 Q.ounds). "1

N5710023 250BC, * Center Section Front Spar Lower Cap- Perform Eddy 10,000 Flight 250BL, Current Inspection . Inspect center wing front spar lower Hours Initial, 2,500 250CR, cap between skin terminations (WS 31 left to WS 31 Flight Hours 510AC, right). (Effective on Aircraft not modified Q.er SB 45-11-5, Repeat. 520AL, "Increase Maximum Zero Fuel Weight (16,500 520BL, Q.Ounds). "1 620AR, 620BR

P5710024 510/610 * Wing Rear Spar Side Stay Fitting Support Structure - 10,000 Flight Perform Eddy Current Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5710025 510/610 * Wing Front Spar Lower Cap From WS 33.0 toWS 60.0 10,000 Flight -Perform Radiographic Inspection. Hours Initial, 2,500 Flight Hours Repeat.

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N5710026 520AL, • Wing Box Mid Spar Lower Cap - Perform Ultrasonic 10,000 Flight thru Inspection. Inspect mid spar lower cap outboard of root Hours Initial, 2,278 520DL, rib at WS 33 toWS 99. (Effective on Aircraft not Flight Hours and modified Q.er SB 45-11-5, "Increase Maximum Zero Fuel Repeat. 620AR Weight (16,500 Q.ounds). ") thru 620DR

N5710028 510/610 • Wing Box Mid Spar Lower Cap, Skin Termination at 10,000 Flight WS 33- Perform Bolt Hole Eddy Current Inspection. Hours Initial, 4,800 Inspect mid spar lower cap underneath root rib (WS 33) Flight Hours at point of skin termination. (Effective on Aircraft not Repeat. modified Q.er SB 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 Q.OUnds). ")

P5710029 510/610 • Wing Mid Spar Vertical Web - Perform Eddy Current 10,000 Flight Inspection . Hours Initial, 10,000 Flight Hours Repeat.

P5710030 510/610 • Wing Rear Spar Vertical Web - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 10,000 Flight Hours Repeat.

N57 10031 520AL • Wing Box Skin Access Cover Holes - Perform Eddy 10,000 Flight thru Current Inspection. Inspect access holes in forward and Hours Initial, 5,000 520ML, aft lower skin panels. (Effective on Aircraft not modified Flight Hours 620AR Q.er SB 45-11-5, "Increase Maximum Zero Fuel Weight Repeat. thru (16,500 Q.Ounds). ") 620MR

P5710032 520AL, • Wing Rib Upper Aft Flange Fillet Radius at WS 33.0 - 10,000 Flight 620AR Perform Ultrasonic Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5710033 510/610 • Wing Access Hole in Closing Rib between Mid and 10,000 Flight Rear Spar- Perform Eddy Current Inspection. Hours In itial, 5,000 Flight Hours Repeat.

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P5710034 550CL, • Wing Box Joint to Winglet - Perform Eddy Current 10,000 Flight 650CR Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5710035 520/620 * Wing Lower Skin at Drain Hole - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 5,000 Flight Hours Repeat.

N5710037 520BL * Wing Box Front Spar Lower Cap - Perform Visual 10,000 Flight thru Inspection. Inspect front spar lower cap and lower Hours Initial, 2,500 520ML, forward skin outboard of Mid-Spar Station (MS) 55. Flight Hours and (Etf.~JI.liV~ QQ Air!t,GJ.tJ. QQ( illQQi[i~Q. Q.~[ S,/2. 4~-11-~, Repeat. 620BR "Increase Maximum Zero Fuel Weight (16,500 thru pounds!."! 620MR

P5710039 550/650 • Winglet Skin - Perform Eddy Current Inspection. 10,000 Flight Hours Initial, 5,000 Flight Hours Repeat.

P5710083 550/650 • Flap Box Basic Structure - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 5,000 Flight Hours Repeat.

N5710121 520HL '* Wing Box Mid Spar, Outboard of Rib #8 - Perform 10,000 Flight thru Visual Inspection at WS 156 and outboard to WS 260. Hours Initial, 5,000 520ML, (Effective on Aircraft not modified per SB 45-11-5, Flight Hours and "Increase Maximum Zero Fuel Weight (16,500 Repeat. 620HR pounds). ") thru 620MR

N5710122 520FL • Wing Box Rear Spar, Outboard of Rib #6 - Perform 10,000 Flight thru Visual Inspection at WS 118 and outboard to WS 260. Hours Initial, 5,000 520ML, (Effective on Aircraft not modified per SB 45-11-5, Flight Hours and "Increase Maximum Zero Fuel Weight (16,500 Repeat. 620FR pounds).") thru 620MR

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N5710123 520/620 * Wing Box Mid Spar Lower Cap- Perform Eddy Current 9,600 Flight Hours Inspection at trunnion fitting. (Effective on Aircraft not Initial, 2,666 Flight modified e.er SB 45-11-5, "Increase Maximum Zero Fuel Hours Repeat. Weight (16,500 e.ounds/."1

L5710124 520/620 * Aileron Drive Support - Perform ultrasoinc inspection. 4,800 Flight Hours Initial, 4,800 Flight Hours Repeat.

N5710137 520BL, * Mid Spar at Rib #2 near WS 48 - Perform Bolt Hole 10,000 Flight 620BR Eddy Current Inspection. (Effective on Aircraft not Hours Initial, 4,800 modified e.er SB 45-11-5, "Increase Maximum Zero Fuel Flight Hours Weight (16,500 e.ounds).") Repeat.

N5710138 520CL, * Mid Spar at Rib #3 near WS 60 - Perform Bolt Hole 10,000 Flight 620CR Eddy Current Inspection. (Effective on Aircraft not Hours Initial, 4,800 modified e.er SB 45-11-5, "Increase Maximum Zero Fuel Flight Hours Weight U6,500 e.ounds). ") Repeat.

N5710139 510AZ, *Forward Flange Fasteners at Rear Spar between WS 9,600 Flight Hours 610AZ 52 and WS 60 - Perform Bolt Hole Eddy Current Initial, 3,600 Flig ht Inspection. (Effective on Aircraft not modified e.er SB 45- Hours Repeat. 11-5, "Increase Maximum Zero Fuel Weight (16,500 e.ounds). "1

N5710147 520GL, • Wing Box Mid Spar Lower Cap, Outboard of Joint at 6,500 Flight Hours 620GR WS 137 between Rib #7 and 8 - Perform Detailed Visual Initial, 2,400 Flight Inspection. Inspect mid spar lower cap and lower skin Hours Repeat. panels. (Effective on Aircraft modified e.er SB 45-11-5, "Increase Maximum Zero Fuel Weight U6,500 e.ounds). ")

N5710148 250CC, • Wing Center Section Rear Spar- Perform Eddy 9,500 Flight Hours 250FL, Current Inspection. Inspect rear spar lower cap from Initial, 4,500 Flight 250GR, centerline to WS 33. (Effective on aircraft modified e.er Hours Repeat. 510BC SB 45-11 -5, "Increase Maximum Zero Fuel Weight U6,500 e.ounds). ")

N5710149 510AC, * Wing Center Section Forward and Aft Ribs at WS 6 10,000 Flight 510AL, and Forward Ribs at WS 17 - Perform Eddy Current Hours Initial, 3,400 610AR, Inspection. (Effective on aircraft modified e.er SB 45-11- Flight Hours 510BC 5, "Increase Maximum Zero Fuel Weight (16,500 Repeat. e.ounds). "1

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N5710150 520EL, • Wing Box Mid Spar Lower Cap- Perform Ultrasonic 6,500 Flight Hours 520GL, Inspection. Inspect mid spar lower cap and lower skin Initial, 2,500 Flight 620ER, panels between WS 99 and WS 137. (Effective on Hours Repeat. 620GR aircraft modified Q.er sa 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 Q.Ounds/. "1

N5710151 520FL, • Wing Box Mid Spar Lower Cap Joint at WS 137- 6,500 Flight Hours 520GL, Perform X-ray Inspection. Inspect mid spar center/outer Initial, 3,000 Flight 620FR, joint. (Effective on aircraft modified Q.er sa 45-11-5, Hours Repeat. 620GR "Increase Maximum Zero Fuel Weight (16,500 Q.Ounds/. "1

N5710152 500/600 • Wing Box Rear Spar Lower Cap Inboard of Joint at 6,500 Flight Hours WS 81 - Perform Ultrasonic Inspection. Inspect rear Initial, 600 Flight spar lower cap between skin termination at WS 48 and Hours Repeat. closing rib at WS 60. (Effective on aircraft modified Q.er Sa 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 Q.Ounds/."1

N57 10153 510AZ, • Wing Box Rear Spar Lower Cap Joint at WS 81 - 10,000 Flight 520CL, Perform X-ray Inspection. Inspect center and outer rear Hours Initial, 3,400 520DL, spars, lower splice plate, and lower skin between WS 60 Flight Hours 610AZ, and WS 90. (Effective on aircraft modified Q.er sa 45-11- Repeat. 620CR, 5, "Increase Maximum Zero Fuel Weight (16,500 620DR Q.Ounds/. "1

N5710154 520DL, • Wing Box Rear Spar Lower Cap Outboard of Joint at 6,500 Flight Hours 620DR WS 81 to Rib #6- Perform Detailed Visual Inspection. Initial, 2,300 Flight Inspect outer rear spar lower cap and aft lower skin Hours Repeat. panel outboard of rear splice at WS 90. (Effective on aircraft modified Q.er sa 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 Q.Ounds). "1

N5710155 510/610 • Wing Box Rear Spar Lower Cap Skin Termination at 6,900 Flight Hours MS 48 -Perform Eddy Current Inspection. Inspect rear Initial, 700 Flight spar lower cap between WS 33 and WS 48. (Effective Hours Repeat. on aircraft modified Q.er sa 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 Q.Ounds/. "1

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05710156 520AL * Wing Box Basic Skin/Stringer, Lower Skin - Perform 7,400 Flight Hours thru Visual Inspection. Inspect outboard wing forward and aft Initial, 5,000 Flight 520ML, lower skin panels and stringers. (Effective on aircraft Hours Repeat. and modified Q.er SB 45-11-5, "Increase Maximum Zero Fuel 620AR Weight (16,500 Q.Ounds). ") thru 620MR

N5710157 520AL * Wing Box Basic Skin/Stringer Run-Out, Lower Skin - 10,000 Flight thru Perform Visual Inspection. Inspect Stringer run-outs in Hours Initial, 6,800 520ML, forward and aft lower skin panels. (Effective on aircraft Flight Hours and modified Q.er SB 45-11-5, "Increase Maximum Zero Fuel Repeat. 620AR Weight (16,500 Q.Ounds).") thru 620MR

N571 0158 250BC, * Center Section Front Spar Lower Cap - Perform Eddy 10,000 Flight 250BL, Current Inspection. Inspect center wing front spar lower Hours Initial, 1,800 250CR, cap between skin terminations (WS 31 left to WS 31 Flight Hours 510AC, right). (Effective on aircraft modified Q.er SB 45-11-5, Repeat. 520AL, "Increase Maximum Zero Fuel Weight (16, 500 520BL, Q.Ounds). ") 620AR, 620BR

N5710159 520AL, * Wing Box Mid Spar Lower Cap- Perform Ultrasonic 7,700 Flight Hours 520BL, Inspection. Inspect mid spar lower cap outboard of root Initial, 2,200 Flight 520CL, rib at WS 33 toWS 99. (Effective on aircraft modified Hours Repeat. 520DL, Q.er SB 45-11-5, "Increase Maximum Zero Fuel Weight 620AR, (16,500 Q.Ounds). ") 620BR, 620CR, 620DR

N5710160 520AL, * Wing Box Mid Spar Lower Cap, Skin Termination at 6,800 Flight Hours 620AR WS 33- Perform Bolt Hole Eddy Current Inspection. Initial, 3,300 Flight Inspect mid spar lower cap underneath root rib (WS 33) Hours Repeat. at point of skin termination. (Effective on aircraft modified Q.er SB 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 Q.Ounds). ")

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N571 0161 520AL * Wing Box Skin Access Cover Holes - Perform Eddy 10,000 Flight thru Current Inspection. Inspect access holes in forward and Hours Initial, 3,900 520ML, aft lower skin panels. (Effective on aircraft modified Q.er Flight Hours and SB 45-11-5, "Increase Maximum Zero Fuel Weig_ht Repeat. 620AR (16,500 Q.Ounds). ") thru 620MR

05710162 520BL * Wing Box Front Spar Lower Cap - Perform Visual 8,000 Flight Hours thru Inspection. Inspect front spar lower cap and lower Initial, 2,500 Flight 520ML, forward skin outboard of Mid-Spar Station (MS) 55. Hours Repeat. and (Effective on aircraft modified Q.er SB 45-11-5, "Increase 620BR Maximum Zero Fuel Weig_ht (16,500 Q.ounds/."1 thru 620MR

N5710163 520AL, • Center Section Mid Spar Centerline Joint - Perform 7,000 Flight Hours 520BL, NDI Inspection. Inspect center mid spar (centerline to Initial, 1,700 Flight 620AR, WS 17), lower splice plate, and center mid spar joint Hours Repeat. 620BR fitting lower cap. (Effective on aircraft modified Q.er SB 45-11 -5, "Increase Maximum Zero Fuel Weight (16,500 Q.Ounds). "1

N5710164 520AL, * Center Section Mid Spar Lower Cap - Perform Eddy 10,000 Flight 520BL, Current Inspection. Inspect mid spar from centerline Hours Initial, 1, 700 520CL, splice plate to skin termination at MS 33. (Effective on Flight Hours 620AR, aircraft modified Q.er SB 45-11-5, "Increase Maximum Repeat. 620BR, Zero Fuel Weig_ht (16,500 Q.Ounds). "1 open inboard MLG doors

N5710165 remove * Wing Box Rear Spar Flap Track Cut-outs - Perform 9,300 Flight Hours flaps Eddy Current Inspection. Inspect flap track cut-outs at Initial, 3,400 Flight WS 65, WS 126, and WS 184 on rear spar. (Effective on Hours Repeat. aircraft modified Q.er SB 45-11 -5, "Increase Maximum Zero Fuel Weight (16,500 eounds1. "1

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05710166 520HL • Wing Box Mid Spar, Outboard of Rib #8 - Perform 8,200 Flight Hours thru Visual Inspection at WS 156 and outboard toWS 260. Initial, 4,100 Flight 520ML, (Effective on aircraft modified Q.er SB 45-11-5, "Increase Hours Repeat. and Maximum Zero Fuel Weight (16,500 Q.Oundsl."l 620HR thru 620MR

05710167 520FL • Wing Box Rear Spar, Outboard of Rib #6 - Perform 10,000 Flight thru Visual Inspection at WS 118 and outboard to WS 260. Hours Initial, 4,100 520ML, (Effective on aircraft modified Q.er SB 45-11-5, "Increase Flight Hours and Maximum Zero Fuel Weight (16,500 Q.Oundsl."l Repeat. 620FR thru 620MR

N5710168 520/620 • Wing Box Mid Spar Lower Cap - Perform Eddy Current 6,500 Flight Hours Inspection at trunnion fitting. (Effective on aircraft Initial, 1,800 Flight modified Q.er SB 45-11-5, "Increase Maximum Zero Fuel Hours Repeat. Weight (16,500 g_ounds). "1

N5710169 520BL, • Mid Spar at Rib #2 near WS 48 - Perform Bolt Hole 7,700 Flight Hours 620BR Eddy Current Inspection. (Effective on aircraft modified Initial, 3200 Flight Q.er SB 45-11-5, "Increase Maximum Zero Fuel Weight Hours Repeat. (16,500 g_oundsl. "I

N5710170 520CL, • Mid Spar at Rib #3 near WS 60 - Perform Bolt Hole 7,700 Flight Hours 620CR Eddy Current Inspection. (Effective on aircraft modified Initial, 3,200 Flight Q.er SB 45-11-5, "Increase Maximum Zero Fuel Weight Hours Repeat. (16,500 g_oundsl."1

N5710171 510AZ, *Forward Flange Fasteners at Rear Spar between WS 6,500 Flight Hours 610AZ 52 and WS 60 - Perform Bolt Hole Eddy Current Initial. 2,400 Flight Inspection. (Effective on aircraft modified g_er SB 45-11- Hours Repeat. 5, "Increase Maximum Zero Fuel Weight (16,500 g_ounds). "I

N5710172 520/620 • Wing Box Mid Spar Lower Cap - Perform Ultrasonic 9,600 Flight Hours Inspection at trunnion fitting. (Effective on aircraft not Initial, 2,666 Flight modified g_er SB 45-11-5, "Increase Maximum Zero Fuel Hours Repeat. Weight (16,500 g_ounds). "I

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N571 0173 520/620 • Wing Box Mid Spar Lower Cap- Perform Ultrasonic 6,500 Flight Hours Inspection at trunnion fitting. (Effective on aircraft Initial , 1,800 Flight modified Qer SB 45-11-5, "Increase Maximum Zero Fuel Hours Repeat. Weight (,16,500 QOunds/. "1

N5710174 510/610 • Wing Box Rear Spar Lower Cap Termination at MS 48 10,000 Flight - Perform Ultrasonic Inspection. Inspect rear spar lower Hours Initial, 1,077 cap between WS 33 and WS 48. (Effective on aircraft Flight Hours not modified Qer SB 45-11-5, "Increase Maximum Zero Repeat. Fuel Weight (,16,500 Qounds/. "1

N5710175 510/610 • Wing Box Rear Spar Lower Cap Skin Termination at 6,900 Flight Hours MS 48 - Perform Ultrasonic Inspection. Inspect rear Initial, 700 Flight spar lower cap between WS 33 and WS 48. (Effective Hours Repeat. on aircraft modified Qer SB 45-11-5, "Increase Maximum Zero Fuel Weight (16,500 Qounds/. "1

N5710176 520AL, • Wing Mid Spar (Center Section) Lower Cap and 10,000 Flight 520BL, Center Joint Fitting- Perform Ultrasonic Inspection. Hours Initial, 2,500 520CL, (Effective on aircraft not modified 12er SB 45-11-5, Flight Hours 620AR, ulncrease Maximum Zero Fuel W~ight (1§.,500 Repeat. 620BR Qounds/.1

N5710177 520AL, • Wing Mid Spar (Center Section) Lower Cap and 7,000 Flight Hours 520BL, Center Joint Fitting- Perform Ultrasonic Inspection. Initial, 1,700 Flight 520CL, (Effective on aircraft modified Qer SB 45-11-5, "Increase Hours Repeat. 620AR, Maximum Zero Fuel Weight (1§.,500 Qound§./. "1 620BR

P5710181 250DL, • Wing Drag Link Tube - Perform Magnetic Particle 10,000 Flight 250CL, Inspection. Hours Initial, 4,640 250ER, Flight Hours 250DR, Repeat. 510BL, 610BR

P5710182 250DL, • Wing Drag Link Attach Bolts - Perform Liquid 10,000 Flight 250CL, Penetrant Inspection. Hours Initial, 4,640 250ER, Flight Hours 250DR, Repeat. 510BL, 610BR

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P5710183 250DL, • Wing Drag Link Attach Clevis - Perform Magnetic 10,000 Flight 250CL, Particle Inspection. Hours Initial, 4,640 250ER, Flight Hours 250DR, Repeat. 510BL, 610BR

P5710184 510/610 • Wing Attach Bolts - Perform Fluorescent Penetrant 10,000 Flight Inspection . Hours Initial, 5,000 Flight Hours Repeat.

P5710185 510/610 • Wing Attach Links - Perform Magnetic Particle 10,000 Flight Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5710186 510/610 • Wing Attach Fittings at Mid Spar and Rear Spar - 10,000 Flight Perform Magnetic Particle Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5750002 540BL, • Flap Front Spar Cutouts - Perform Eddy Current 10,000 Flight 540CL, Inspection. Hours Initial, 2,500 540JL, Flight Hours 640BR, Repeat. 640CR, 640JR, 640KR

P5750003 540/640 • Flap Nose Roller Ribs - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5750004 540/640 • Flap Actuator Support Ribs - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 10,000 Flight Hours Repeat.

N5750005 540/640 • Flap Main Track Hinge Fittings, Track, and Flap Box 10,000 Flight Sides - Perform visual inspection. Inspect main track Hou rs Initial, 2,500 hinge fittings on track and flap box sides. Flight Hours Repeat.

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P5750048 540/640 • Flap Tracks - Perform Magnetic Particle Inspection. 10,000 Flight Hours Initial, 10,000 Flight Hours Repeat.

P5750049 540BL, • Flap Nose Roller Tracks- Perform Magnetic Particle 10,000 Flight 540CL, Inspection with flaps removed . Hours Initial, 540JL, 10,000 Flight 540KL Hours Repeat.

E5750051 540BL, • Flap Main Track Rollers - Perform visual inspection 10,000 Flight 540CL, with flaps removed. Hours Initial, 600 540JL, Flight Hours 540KL Repeat.

E5750052 540BL, • Flap Nose Rollers - Perform visual inspection with 7,200 Flight Hours 540CL, flaps removed. Initial, 600 Flight 540JL, Hours Repeat. 540KL

P5750053 540BL, • Flap Track Support Ribs- Perform Eddy Current 10,000 Flight 540CL, Inspection. Hours Initial , 540JL, 10,000 Flight 540KL Hours Repeat.

P5750068 540/640 • Flap Front Spar Rib Support Structure - Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 5,000 Flight Hours Repeat.

P5760000 540/640 * Aileron Actuator Hinge Fitting - Perform Eddy Current 10,000 Flight Inspection. Hours Initial, 10,000 Flight Hours Repeat.

P5760001 540/640 • Aileron Skin - Perform Eddy Current Inspection. 10,000 Flight Hours Initial, 10,000 Flight Hours Repeat.

P5760002 540/640 • Aileron Balance Tab Hinge Fittings - Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 2,500 Flight Hours Repeat.

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P5760003 540/640 • Aileron Trim and Balance Tab Front Spars - Perform 10,000 Flight Radiographic Inspection. Hours Initial, 5,000 Flight Hours Repeat.

A5760004 540/640 *Aileron Bolts - Perform Magnetic Particle Inspection. 10,000 Flight Hours Initial, 2,500 Flight Hours Repeat.

P5760005 540/640 * Aileron Hinge Lugs and Fittings - Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

E5760006 540/640 * Aileron Basic Structure - Perform visual inspection . 10,000 Flight Hours Initial, 10,000 Flight Hours Repeat.

P5760014 540/640 • Aileron Hinge Support Structure - Perform Eddy 10,000 Flight Current Inspection. Hours Initial, 10,000 Flight Hours Repeat.

700 LANDING GEAR AND RELATED SYSTEMS

P3220007 720/730 • Main Landing Gear Axles - Perform Main Landing Initial, See Note, Gear Axle Beam Assembly (P/N 200-203-001) 48 Months Repeat. Boroscope Inspection.

NOTE: On aircraft over 5 years from C of A date, initial inspection is due within 18 months from October 31, 2008. On aircraft with 3 to 5 years from C of A date, initial inspection is due within 24 months from October 31, 2008. On aircraft with less than 3 years from C of A date, initial inspection is due within 30 months from October 31, 2008. Repeat inspections are 48 months from initial inspection.

EFFECTIVITY: ALL 04-10-01 Page 33 I Jan 10/ 11 MM-104 LEARJET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUIREMENTS - STRUCTURE IRN INTERVAL ACC ESS CHECKS

L3220020 720/730 * Main Landing Gear Trunnion Fittings on Mid and Rear 10,000 Landings Spar - Perform Eddy Current Inspection. Initial, 5,000 Landings Repeat.

M3220024 720/730 • Main Landing Gear Side-Stay Actuator Pins - Perform 12 Months Initial, Magnetic Particle Inspection. 24 Months Repeat

L3220118 720/730 * Main Landing Gear Shock Strut Cylinder (P/N 200- 3,300 Landing 0201 -105, 200-0201-106)- Perform Ultrasonic Initial, 600 Inspection of the Lower Service Port and Forging Landings Repeat. Parting Line.

J3220120 720/730 * Main Landing Gear Trunnion Shear Pin Bushing - 600 Landings. Perform Visual Inspecti on for Bushing Migration. (Effective on Aircraft 45-005 thru 45-208, 45-210 ihru 45-222, 45-224, 45-225, 45-229, and 45-230 not modified Q.er SB 45-57-l.l

M3220135 720/730 * Main Landing Gear Side-Stay Actuator Pins - Perform 12 Months Initial, Detailed Visual Inspection. (Refer to 5-1 0-00.) 24 Months Repeat

M3220136 720/730 * Main Landing Gear Shock Strut Cylinder (P/N 200- 4,800 Landings 0201-101 , 200-0201 -102, 200-0201-103, 200-0201- Initial, 600 104 , 200-0201-107, 200-0201 -108)- Perform Ultrasonic Landings Repeat. Inspection of the Lower Service Port and Forging Parting Line.

P3220146 720/730 • Main Landing Gear Trunnion Shock Strut Cylinder (P/ 4,800 Landings N 200-0201 -109 and 200-0201-110)- Perform Initial, 600 Ultrasonic Inspection of the Forging Parting Line. Landings Repeat.

L5311004 710 * Nose Landing Gear Trunnion Fittings - Perform visual 10,000 Landings inspection of the trunnion fittings and attachment bolts. Initial, 10,000 Landings Repeat.

L5311005 710 • Nose Landing Gear Trunnion Fittings and Support 10,000 Landings Structure - Perform Eddy Current Inspection of the Initial, 10,000 trunnion support structure at the forward pressure Landings Repeat. bulkhead flange.

EFFECTIVITY: NOTED 04-10-01 Page 34 I Jan 10/ 11 MM·104 LEARJ ET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUIREM ENTS - STRU CTURE IRN INTERVAL ACC ESS CHECKS

A5323022 710AL, * Nose Landing Gear Aft Wheelbox Closing Structure 10,000 Flight 710AR (FS 150 to FS 162) - Perform Visual Inspection. Inspect Hours Initial, the following: 10,000 Flight a. Panel Hours Repeat. b. Channel Stiffeners c. Support Angle d. Angle Stiffener e. Zee Stiffener.

800 DOORS, GENERAL INSPECTION, AND SERVICING TASKS

A5210009 820AR • Emergency Exit Door Retainers -Perform visual 10,000 Flight inspection. Inspect door stop fittings on emergency exit Hours Initial, door frames in flange radii (FS 374 and 394). 10,000 Flight Hours Repeat.

N5210010 810 • Lower Passenger Door Tension Bolts, Bolt Retainers, 9,600 Flight Hours Tension Fittings, and Door Attachments - Perform visual Initial, 3,408 Flight inspection. Hours Repeat.

N5210011 810 • Upper and Lower Passenger Door Latch Pins - 9,600 Flight Hours Perform visual inspection. Inspect bolts and door end rib Initial, 3,850 Flight structure at lock pins. Hours Repeat.

A5210012 810 • Lower Passenger Door Hinge - Perform visual 10,000 Flight inspection. Inspect piano hinge lugs and fasteners. Hours Initial, 10,000 Flight Hours Repeat.

E5210013 810 • Upper and Lower Passenger Door Latch Arms and 10,000 Flight Door Attachments - Perform visual inspection. Hours Initial, 7,068 Flight Hours Repeat.

A5210014 810 * Upper Passenger Door Tension Fittings- Perform 10,000 Flight visual inspection. Inspect the following: Hours Initial, a.Tension studs at retaining flanges 10,000 Flight b. Radii around flange periphery. Hours Repeat.

D5210015 820AR • Emergency Exit Door- Perform visual inspection . Pay 10,000 Flight particular attention to flanges and fastener holes of door Hours Initial, 8,000 stop fittings. Flight Hours Repeat.

EFFECTIVITY: ALL 04-10-01 Page 35 I Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MANUAL

ZONE/ MAINTENANCE REQUIREMENTS· STRUCTURE IRN INTERVAL ACCESS CHECKS

F5210016 810AL • Upper Passenger Door Hinge - Perform visual 10,000 Flight inspection. Inspect upper surface of hinge fi ngers at Hours Initial, base of lug. 10,000 Flight Hours Repeat.

N5210017 810AL • Upper Passenger Door Tension Bolts, Bolt Retainers, 9,600 Flight Hours Tension Fittings, and Door Attachments - Perform visual Initial, 3,408 Flight inspection. Hours Repeat.

N5314000 820 • Emergency Exit Door Skin Cutout Corners and 4,800 Flight Hours Doublers (FS 370- FS 398)- Perform Eddy Current Initial, 2,400 Flight Inspection. Hours Repeat.

EFFECTIVITY: ALL 04-10-01 Page 36 I Jan 10/ 11 MM· 104 ..

LEARJET 45 MAINTENANCE MANUAL

AIRWORTHINESS LIMITATIONS · REPLACEMENT REQUIREMENTS

1. Time Compliance

A. Replacement Requirements (1) For the application of Airworthiness Limitations, the following defi nitions apply: (a) Flight Cycle - A complete sequence covering taxi, takeoff, climb, cruise, descent, approach, touchdown, and taxi, including any number of touch-and-go operations. (b) Landing - A sequence covering the approach and touchdown phases. Each touch-and-go operation is considered a landing. (c) Flying Hours - Flying hours are the accumulated time calculated on a takeoff to touchdown basis.

B. Replacement Items

ZONE/ IRN AC- REPLACEMENT REQUIREMENTS INTERVA L CESS

200 FORWARD FUSELAGE

R2710041 230AC, • Aileron Spindle (PIN 4527102103-001) 10 Years. 230BC, 230CC, 250CC, 540AL, 640AR

300 AFT FUSELAGE/EMPENNAGE

N2740023 330AC, • Horizontal Stabilizer Actuator ACME Screw (P/N 600 Flight Hours. 330BC, 2A94568008). (.Effective on aircraft eguig_g_ed with 330CC, 6627401000-007 Horizontal Stabilizer Actuators.) 330CL, 330BR

N2740024 330AC, • Horizontal Stabilizer Actuator ACME Nut (P/N 600 Flight Hours. 330BC, 2A94567005). (.Effective on aircraft eguig_g_ed with 330CC, 6627401000-007 Horizontal Stabilizer Actuators.) 330CL, 330BR

400 POWERPLANTS, NACELLES, AND THRUST REVERSERS

F2420000 410 .. Alternator - Perform Bearing Replacement. 1200 Hours.

EFFECTIVI TY: NOTED Page 1 I 04-11-00 Jan 10/11 MM-104 LEARJET 45 • MAINTENANCE MANUAL

ZONE/ IRN AC- REPLACEMENT REQUIREMENTS INTERVAL CESS

500/600 LEFT AND RIGHT WING

02750055 540/640 * Flap Actuator Joint (P/N 145673-1) - Replace. 24 Months.

700 LANDING GEAR AND RELATED ITEMS

03220009 710 *Nose Landing Gear Strut Assembly (P/N 2342100). 20,000 Landings.

03220010 710 * Nose Landing Gear Actuator Assembly (P/N 20,000 Landings. 6632201000).

03220011 710 * Nose Landing Gear Actuator Upper Pin (P/N 20,000 Landings. 4532302043).

N3220012 710 *Main Landing Gear Strut Assembly (P/N 6632101000, 10,000 Landings. 200-0200).

T3220013 710 * Main Landing Gear Side Brace Actuator Assembly (P/N 17,000 Landings. 200-0300-003, -004) excluding the End Cap (PIN 200- 0303).

NOTE: The replacement of the MLG Side Brace Actuator Assembly includes the replacement of the MLG Actuator Piston (P/N 200-0301 ), MLG Actuator Cylinder (PIN 200-0302), and MLG Actuator Housing (PIN 200-0304 ).

Refer to IRN T3220105 for the replacement interval of the End Cap.

M3220014 710 • Main Landing Gear Actuator Upper Pin (P/N 200-0325). 60 Months.

N3220023 720/730 • Main Landing Gear Trunnion Pins (P/N 200-02 12 and 10,000 Landings. 200-0213).

03220028 710 • Nose Landing Gear Trunnion Pins (P/N 2342108). 20,000 Landings.

03220029 710 * Nose Landing Gear Trunnion Axle (P/N 2342110). 20,000 Landings.

N3220035 720/730 * Main Landing Gear Shock Strut Piston (P/N 200-0202). 10,000 Landings.

N3220036 720/730 • Main Landing Gear Axle Beam (P/N 200-0203). 10,000 Landings.

N3220037 720/730 * Main Landing Gear Shock Strut Link (P/N 200-0204). 10,000 Landings.

M3220038 720/730 * Main Landing Gear Actuator Lower Pin (P/N 200-0217). 60 Months.

EFFECTIVITY: ALL Page 2 04-11-00 Jan 10/11 MM-104 LEARJET 45 MAINTENANCE MAN UAL

ZONE/ IRN AC- REPLACEMENT REQUIREMENTS INTERVAL CESS

N3220041 720/730 • Main Landing Gear Forward Trunnion Shear Pins (PIN 1,800 Landings. 4532103015 and 4532103132).

N3220042 720/730 • Main Landing Gear Aft Trunnion Upper Shear Pin (P/N 1,800 Landings. 4532103025, 453203133).

N3220043 720/730 • Main Landing Gear Aft Trunnion Lower Shear Pin (PIN 1, 800 Landings. 4532103026, 4532103134 ).

T3220046 710 • Main Landing Gear Side Brace Actuator Assembly (P/N 2,500 Landings. 200-0300-001, -002) excluding the End Cap (P/N 200- 0303).

NOTE: Refer to IRN T3220105 for the replacement interval of the End Cap.

N3220101 720/730 • Main Landing Gear Link Pin (P/N 200-0214). 10,000 Landings.

N3220102 720/730 • Main Landing Gear Piston Pin (P/N 200-0215). 10,000 Landings.

N3220103 720/730 • Main Landing Gear Actuator Piston (P/N 200-0301 ). 17,000 Landings.

N3220104 720/730 • Main Landing Gear Actuator Cylinder (P/N 200-0302). 17,000 Landings.

T3220105 720/730 • Main Landing Gear Actuator End Cap (PIN 200-0303). 2,387 Landings.

NOTE: On Aircraft with End Caps that have over 2,387 landings since C of A or last replacement, replace End Caps within 25 landings from the date of this revision.

N3220106 720/730 • Main Landing Gear Actuator Housing (PIN 200-0304 ). 17,000 Landings.

N3220116 720/730 *Main Landing Gear Shock Strut Cylinder (P/N 200-0201- 10,000 Landings. 109 and -110).

N3220126 720/730 * Main Landing Gear Side-Stay Actuator Fitting (P/N 20,000 Landings. 4532103041).

03220128 720/730 • Main Landing Gear Shock Strut Cylinder (P/N 200-0201- 6,600 Landings. 105, -106, -1 07, and -108).

03220137 720/730 • Main Landing Gear Shock Strut Cylinder (P/N 200-0201 - 10,000 Landings. 101,-102, -103, and -104 ).

N3220139 720/730 • Main Landing Gear Forward Trunnion Shear Pin (P/N 5,000 Landings. 4532103201).

EFFECTIVITY: ALL Page 3 04-11-00 Jan 10/11 MM·104 LEARJET 45 r MAINTENANCE MANUAL

ZONE/ IRN AC- REPLACEMENT REQUIREMENTS INTERVAL CESS

N3220140 720/730 • Main Landing Gear Aft Trunnion Upper Shear Pin (P/N 5,000 Landings. 45321 03202).

N3220141 720/730 • Main Landing Gear Aft Trunnion Lower Shear Pin (P/N 5,000 Landings. 4532103203 ).

L3231024 720/730 Main Landing Gear Inboard Door Actuator (P/N 7469-1) 2,400 Hours. Cap Screws - Replace. (.Effective on Aircraft 45-005 thru 45-276 modified eer SB 45-32-19, "Main Landing Gear Door Actuator lmerovement!Saddle Installation" and 45- 277 and subsequent.)

EFFECTIVITY: NOTED Page 4 I 04-11-00 Jan 10/ 11 MM-104 LEARJET 45 MAINTENANCE MANUAL 1

MAINTENANCE REQUIREMENTS BY AIRCRAFT EFFECTIVITY

1. Time Compliance

A. Maintenance Requirements by Effectivity (1) For the application of Airworthiness Limitations, the following definitions apply: (a) Flight Cycle - A complete sequence covering taxi, takeoff, climb, cruise, descent approach, touchdown, and taxi, including any number of touch-and-go operations. (b) Landing - A sequence covering the approach and touchdown phases. Each touch-and-go operation is considered a landing. (c) Flight Hours - Flight hours are the accumulated time calculated from takeoff to final touch­ down.

EFFECTIVITY: ALL Page 1 4-12-00 Aug 29/05 I MM·104 LEARJET 45 MAINTENANCE MANUAL

MAINTENANCE REQUIREMENTS BY AIRCRAFT EFFECTIVITY

1. Time Compliance

A. Maintenance Requirements by Effectivity {1) For the application of Airworthiness limitations, the following definitions apply: (a) Flight Cycle - A complete sequence covering taxi, takeoff. climb, cruise, descent approach, touchdown. and taxi, including any number of touch-and-go operations. (b) Landing - A sequence covering the approach and touchdown phases. Each touch-and-go operation is considered a landing. (c) Flight Hours - Flight hours are the accumulated time calculated from takeoff to final touch­ down.

EFFECTIVITY: ALL Page 1 4-12-00 Aug 29/05 I MM·104 '{