Volume 3. Learjet 45. Maintenance and Inspection Program

Ace Aviation Services, Corp. General Maintenance Manual Volume 3 Learjet 45 Maintenance and Inspection Program

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Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: Highlights Volume 3: Learjet 45 Maintenance and Inspection Program Revision: 2 Chapter: Highlights of Changes Date: 07/06/2018 Page: 1of 2 A. GENERAL 1. The scope of this revision is to: a. Correct LEP formatting. b. Chapter 1, Section 3.0 Program Summary; i. 0.0 Revise paragraph A to airframe manufacturers maintenance manual revision level 70 and temporary revisions 5-113 and 5-120. c. Chapter 2, 05-12-02; i. IRN 3610061 revised to revision Y, clarified effectivity to P/N of valve installed. d. Chapter 2, 05-14-04; i. Revised IRN s Q5710156, Q5710162, Q5710166, and Q5710167 from two asterisks to one. e. Chapter 2, 05-19-00; i. Reformatted Zone/Access column all pages. ii. Revised IRN 2560000 to revision AA. Revised interval to manufacturer s instructions. Defined Manufacturer used and interval. iii. Incorporated Temporary Revision 5-120 by adding IRN AA5510034 Added inspection for the Horizontal Stabilizer Primary and Secondary Bolts and Bushings iv. Revised IRN 3220018 to revision AA. Removed note regarding original C of A and compliance date. v. Revised IRN 3220111 to revision AA. Removed note regarding original C of A and compliance date. Added note to contact Learjet CR&O or FSR. f. Chapter 2, 05-19-01; i. Reformatted Zone / Access Column. ii. Incorporated Temporary Revision 5-113 by adding IRN Z5210053, Replace Door Handle. iii. Revised IRN 4900039 to revision AA, added clarification to note. iv. Added IRN AA2760021 Replace Spoiler Swivel. g. Chapter 2, 05-60-00;

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: Highlights Volume 3: Learjet 45 Maintenance and Inspection Program Revision: 2 Chapter: Highlights of Changes Date: 07/06/2018 Page: 2of 2 i. Revised IRN s as referenced c. thru e. h. Chapter 4, Ace TLL 45-1 i. Reformatted header layout only

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ROR Volume 3: Learjet 45 Maintenance and Inspection Program Revision: 2 Record of Revision Date: 07/06/2018 Page: 1 of 1 REISSUE... 09/22/2017 Revision 1... 04/16/2018 Revision 2... 07/06/2018

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Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ToC Volume 3: Learjet 45 Maintenance and Inspection Program Revision: REISSUE Table of Contents Date: 09/22/2017 Page: 1 of 4 Highlights of Changes Record of Revisions List of Effective Pages Table of Contents Chapter 1: Introduction Section 01 Section 02: Section 03: Abbreviations Definitions Program Summary Airframe Manufacturers Times Limitations & Maintenance Checks SECTION: 04-00-00: Airworthiness Limitations LR 45 04-10-00: Certification Maintenance Requirements - Component and System Checks - LR 45 04-10-01: Certification Maintenance Requirements - Structure Checks - LR 45 04-11-00: Airworthiness Limitations - Replacement Requirements LR45 05-10-00: Time Limits and Maintenance Checks LR 45 05-10-00: Inspections Maintenance Practices LR45 05-11-01: Phase A1 Inspection LR 45 05-11-02: Phase A2 Inspection LR 45 05-11-03: Phase A3 Inspection LR 45 05-11-04: Phase A4 Inspection LR 45

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ToC Volume 3: Learjet 45 Maintenance and Inspection Program Revision: REISSUE Table of Contents Date: 09/22/2017 Page: 2 of 4 Airframe Manufacturers Times Limitations & Maintenance Checks SECTION: 05-11-05: Phase A5 Inspection LR 45 05-11-06: Phase A6 Inspection LR 45 05-12-01: Phase B1 Inspection LR 45 05-12-02: Phase B2 Inspection LR 45 05-12-03: Phase B3 Inspection LR 45 05-12-04: Phase B4 Inspection LR 45 05-12-05: Phase B5 Inspection LR 45 05-12-06: Phase B6 Inspection LR 45 05-13-01: Phase C1 Inspection LR 45 05-13-02: Phase C2 Inspection LR 45 05-13-03: Phase C3 Inspection LR 45 05-13-04: Phase C4 Inspection LR 45 05-13-05: Phase C5 Inspection LR 45 05-13-06: Phase C6 Inspection LR 45 05-14-01: Phase D1 Inspection LR 45 05-14-02: Phase D2 Inspection LR 45 05-14-03: Phase D3 Inspection LR 45 05-14-04: Phase D4 Inspection LR 45 05-14-05: Phase D5 Inspection LR 45 05-14-06: Phase D6 Inspection LR 45

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ToC Volume 3: Learjet 45 Maintenance and Inspection Program Revision: REISSUE Table of Contents Date: 09/22/2017 Page: 3 of 4 Airframe Manufacturers Times Limitations & Maintenance Checks SECTION: 05-15-00: 4800 Hour Checks LR 45 05-16-00: 9600 Hour Checks LR 45 05-17-00: Major Landing Gear Inspections LR 45 05-19-01: Special Inspections LR 45 05-19-02: RVSM Inspections LR 45 05/10-30: RVSM Inspections LR 60/60XR 05-60-00: Reference Data LR 45 Chapter 3: Engine Manufacturers Times Limitations & Maintenance Checks SECTION: Airworthiness Limitations: - TFE731-20 05-10-00: Time Limits of Engine Critical Components TFE731-20 05-10-01: Part History Reports TFE731-20 05-20-00: Scheduled Maintenance Checks TFE731-20 05-20-01: Overhaul TFE731-20 05-50-00: Unscheduled Maintenance Checks TFE731-20 72-00-00: Engine - Inspection / Check TFE731-20

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ToC Volume 3: Learjet 45 Maintenance and Inspection Program Revision: REISSUE Table of Contents Date: 09/22/2017 Page: 4 of 4 Chapter 4: Ace Aviation Services, Corp. Time Limitations Listings SECTION: 45-1 N170LS 45-2 N777QL Chapter 5: Forms ACE Form -LR45-01, Learjet 45 Service Check ACE Form-LR45-02, Learjet 45 30-Day Check

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:01 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: REISSUE Chapter 01: Introduction Date: 09/22/2017 Section 01: Abbreviations Page: 1 of 1 These are abbreviations used within Chapter 1, Program Summary ACE: AD: ATA: AWL: CASS: CCMTP: CFR: CMR: Doc.: ELT: ECTM: FAA: GMM ICA: IRN: LR: MIP: MM: NDT: PW: RVSM: SRM: STC: TLL: TLMC: Ace Aviation Services, Corporation Airworthiness Directive Aircraft Transportation Association [(now Airlines for America (A4A)] Airworthiness Limitation Continuous Airworthiness Surveillance System Contracted Computer Maintenance Tracking Code of Federal Regulations Certification Maintenance Requirement Document Emergency Locator Beacon Engine Condition Trend Monitoring Federal Aviation Administration General Maintenance Manual Instructions for Continued Airworthiness Inspection Reference Number Learjet Maintenance Inspection Program Maintenance Manual Non-Destructive Testing Pratt & Whitney Reduced Vertical Separation Minimum Structural Repair Manual Supplemental Type Certificate Time Limitation List Time Limits and Maintenance Checks

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Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:02 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: 1 Chapter 01: Introduction Date: 04/16/2018 Section 02: Definitions Page: 1 of 1 These are definitions of subject matter contained in this appendix. APU Hours: APU Cycles: Monthly / 30 Day Calendar Items: Hour(s): Landings: Cycles: APU Hours are those hours accumulated on the APU while operating as indicated by APU meter. APU Cycles are to quantity of APU starts as indicated by APU meter. Unless superseded by Manufacturers calendric definition, calendar items are due within the month they expire in. Calendar items may be tracked as date to date for early warning purposes, however they do not expire until the end of that month. Calendar items may have their expiration date adjusted to the end of that month. This adjustment is not an extension. Hours are flight hours unless otherwise indicated. Landings are flight landings unless otherwise indicated. Touch and go is considered a landing. ACE has determined that there are no punitive cycle counts within the Pratt & Whitney 305 Engine Program. There are partial cycle counts, however, due to ACE s operation, tracking partial cycle counts is not beneficial to the burden created so therefore; Engine Cycles are an engine start followed by one or more flights. A flight is defined as a lift-off to touch down, irrespective of engine starts and stops. Each flight is considered to have been preceded by one engine start, ie. number of starts is equal to the number of flights

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Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: 2 Chapter 01: Introduction Date: 07/06/2018 Section 03: Program Summary Page: 1 of 9 Resources: 14 CFR Parts; 135.185 43.16, 47, 91.207, 91.403, 91.411, 91.413, 91 Appendix G, 91.513 (b)(1), 0.0 MANUFACTURERS REVISIONS INCORPORATED IN THIS INSPECTION PROGRAM A. Learjet 45 Maintenance Manual MM-104 Revision 70 dated Apr 20/2018. 1. Temporary Revision 5-113 dated Apr 30/18. 2. Temporary Revision 5-120 dated Apr 30/18. B. Honeywell TFE731-20 Light Maintenance Manual P/N 72-03-06 Revision 12 dated May 31, 2013. 1.0 Introduction A. This Maintenance Inspection Program volume is used in conjunction with the General Maintenance Manual, Volume 1 for the maintenance schedule for Learjet 45 as listed on Operations Specifications D085. 1.1 Responsibility A. The Director of Maintenance is responsible for the Maintenance Inspection Program (MIP). B. The Director of Maintenance may delegate part or all duties relative to this matter, however this does not alleviate Director of Maintenance from overall responsibility. 1.2 Authority A. The Director of Maintenance has the authority to make changes to the Maintenance Inspection Program. 1.3 Basis, Implementation and Revision for Maintenance Inspection Program A. AIRFRAME - Ace Aviation Services, Corp. has adopted the Learjet 45 Maintenance Inspection Program, with noted exceptions, from the manufacturer as described in Learjet Maintenance Manual Part Number MM-104. All exceptions in the program will be highlighted by NOTE: Ace Aviation Services, Corp (explanation of exception) Chapters 4 and 5 are inclusive to this volume in chapter 2. Elections and interpretations are listed below. 1. References within chapters 4 and 5 of this volume to other ATA chapters means Learjet Maintenance Manual Part Number MM-104 as revised. 2. References to NDI-104 means, Learjet Non-Destructive Inspection Manual NDI 104 as revised.

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: Reissue Chapter 01: Introduction Date: 09/22/2017 Section 03: Program Summary Page: 2 of 9 1.3 Basis, Implementation and Revision for Maintenance Inspection Program (Continued) 3. References to SRM-104 means, Learjet Structural Repair Manual SRM-104 as revised. 4. At the current time, no Ace Aviation Services, Corp aircraft listed on Ops Spec D085 are on the Learjet Evolved Maintenance Program per Service Bulletin 45-5-1 as noted in 05-00-00 1. A. 5. Currently there are no chapter 04-12-00 Maintenance Requirements by Aircraft Effectivity and 04-12-00 is omitted from this MIP. 6. Ace Aviation Services, Corp. utilizes the Phase Inspection Program as noted in Sample Inspection Program #1 as noted in 05-10-00 5. A. (1). a. If through CASS it is determined to utilize one of the other available programs, a revision declaring that program will be made to 5. A. (3). 7. GENERAL INSPECTION CHECKS as defined in 05-10-00 2. E. are an integral part of Ace Aviation Services CAMP and are not required at each inspection for review. 8. When an IRN Code task specifies effectivity by aircraft serial number on an inspection form and the aircraft is not effected, N/A by S/N will be entered in the MECH sign off block. 9. When an IRN Code task specifies effectivity by aircraft serial number on an individual line item and the aircraft is not effected, that item is still tracked in the CCMTP. The IRN Code will be tracked on Status Report and noted as N/A by S/N. The requirements interval will be suspended. 10. When an IRN Code task specifies effectivity by Service Bulletin (Pre or Post), on an inspection form and the aircraft is not effected, N/A by S/B will be entered in the MECH sign off block. 11. When an IRN Code task specifies effectivity by Service Bulletin (Pre or Post), on an individual line item and the aircraft is not effected, that item is still tracked in the CCMTP. The IRN Code will be tracked on Status Report and noted as N/A by S/B incorporation or not incorporated. The requirements interval will be suspended. 12. When there are multiple part numbers that are eligible by a single IRN Code that have an Airworthiness Limitation or are a Manufacturers Replacement Recommendation, the part number/s installed will be identified on the CCMTP Status Report along with the corresponding time limit for that part number.

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: Reissue Chapter 01: Introduction Date: 09/22/2017 Section 03: Program Summary Page: 3 of 9 1.3 Basis, Implementation and Revision for Maintenance Inspection Program (Continued) 12. When revisions to the Manufacturers program in chapters 4 and 5 occur, through CASS those revisions will be reviewed for implementation against the program/s in chapters 4 and 5 of this volume for revision, incorporation or deletion as appropriate. 13. Reference the GMM, Volume 1 sub-section 5.2.3 for revision FAA approval procedures. 14. STC s installed by Learjet Completion Centers are eligible for inspection tolerances unless otherwise stated in the ICA or are and Airworthy Limitation item. B. ENGINE - Ace Aviation Services, Corp. has adopted the Honeywell TFE731-20 Inspection Program, with noted exceptions, from the manufacturer as described in Honeywell MM Part No. 72-03-06. All exceptions in the program will be highlighted by NOTE: Ace Aviation Services, Corp (explanation of exception) Airworthiness Limitations and Chapter 5 are inclusive to this volume in chapter 2. Elections and interpretations are listed below. 1. References within the chapters, Airworthiness Limitations and 5, of this volume to other ATA chapters means Honeywell TFE731-20 MM 72-03-06 as revised 2. Pages 801 thru 809 of the Honeywell TFE731-20 MM 72-03-06 ENGINE - INSPECTION / CHECK are included in this MIP as 72-00-00 Engine Inspection / Check Pages 1 thru 8. Ace Aviation Services, Corp. has elected to set the times for the Routine Periodic Inspections found in 72-00-00 as follows: a. 150 TO 250 HOUR INSPECTION: To be performed at 200 hours not to exceed 250 hours. b. 300 TO 440 HOUR INSPECTION : To be performed at 390 hours not to exceed 440 hours. c. 500 TO 650 HOUR & 500 TO 850 HOUR INSPECTION: To be performed together at 600 hours not to exceed 650 hours. d. 1000 TO 1300 HOUR INSPECTION: To be performed at 1250 hours not to exceed 1300 hours. e. 1500 TO 1650 HOUR INSPECTION: To be performed at 1600 hours not to exceed 1650 hours. 3. Refer to TFE731-20 LMM MM 72-03-06 2. C. for inspection requirements of Major Periodic Inspection (MPI). a. 2. C. (2) Specifies the allowable exceedance of 100 hours of operation for MPI

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: Reissue Chapter 01: Introduction Date: 09/22/2017 Section 03: Program Summary Page: 4 of 9 1.3 Basis, Implementation and Revision for Maintenance Inspection Program (Continued) 4. Refer to TFE731-20 LMM MM 72-03-06 2. D. for inspection requirements of Compressor Zone Inspection (CZI). a. 2. D. (2) Specifies the allowable exceedance of 200 hours of operation for MPI 5. When a task specifies effectivity by Service Bulletin (Pre or Post), on an individual line item and the engine is not effected, that item is still tracked in the CCMTP. The item will be tracked on Status Report and noted as N/A by S/B incorporation or not incorporated. The requirements interval will be suspended. 4. When there are multiple part numbers that are eligible for installation that have an Airworthiness Limitation, the part number/s installed will be identified on the CCMTP Status Report along with the corresponding time limit for that part number. 5. When revisions to the Manufacturers program in chapters Airworthiness Limitations and 5 occur, through CASS those revisions will be reviewed for implementation against the program/s in chapters 4 and 5 of this volume for revision, incorporation or deletion as appropriate. 6. Reference the GMM sub-section 5.2.3 for revision FAA approval procedures. C. CASS - Through judicious use of the Continuous Analysis and Surveillance System (CASS), Ace Aviation Services, Corporation, may adjust Manufacturers task intervals, generate internal inspections or maintenance tasks, to better maintain our fleet types. When approved by the Director of Maintenance these adjustments or additional tasks are incorporated into our MIP. 1. Adjustments to Manufacturers task intervals will always be in a reduction, usually due to reliability issues. Ace Aviation Services, Corp. will not increase any Manufacturers time interval. D. ICA s - Instructions for Continued Airworthiness (ICA) items generated from Supplemental Type Certificates, Major Alterations or Repairs, FAA 8110-3, Statement of Compliance with Airworthiness Standards, Damage Tolerance Assessments are also incorporated into our Maintenance Inspection Program.

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: Reissue Chapter 01: Introduction Date: 09/22/2017 Section 03: Program Summary Page: 5 of 9 1.3 Basis, Implementation and Revision for Maintenance Inspection Program (Continued) 1. When grace periods for ICA s are permitted per the controlling document, these may be used at the discretion of the Director of Maintenance. However, whether the ICA allows it or not, all extended time within the allowable time period will be bought back. Reference the GMM, Volume 1 Sub-Section 5.3, Extension of Maintenance Inspection Program Items, for policies and procedures for Escalation of Maintenance Inspection Time Periods. E. RVSM - Reduced Vertical Separation Minimum tasks are incorporated into our Maintenance Inspection Program. 1. Unless otherwise specified, RVSM tasks are incorporated in the Learjet 45 MM 104 Chapter 05-19-02. F. CPCP - Corrosion Prevention and Control Program items are incorporated into the Maintenance Inspection Program thru the Airframe and Powerplant Manufacturers Inspection Programs. G. AD s - Airworthiness Directives are incorporated into the Maintenance Inspection Program for scheduling and compliance tracking. H. S/B s - Service Bulletins, when approved by the Director of Maintenance, are incorporated into the CCMTP for scheduling and compliance tracking. I. CFR s US regulatory, Code of Federal Regulations, items for equipment are incorporated into the Maintenance Inspection Program. J. ECTM Engine Condition Trend Monitoring (ECTM) program Tasks. Certain engine warranty programs i.e. Honeywell Maintenance Service Plan (MSP) or Jet Support Services, Inc. (JSSI) require Engine Health Monitoring to keep the plan in warranty. When required by these plans, the ECTM task will be incorporated into Ace Aviation Services, Corp MIP for the particular effected engines to track this requirement. 1. Honeywell Service Information Letter S.I.L. NO. F731-88 as revised describes the ETCM program. a. ETCM is not considered part of the Engine Manufacturers Maintenance Inspection Program and will be listed in the Time Limitations List for each effected aircraft. b. ETCM data is to be collected every 30 hours not to exceed 50 hours per 72-00-00 B, (3). K. This Maintenance Inspection Program is an FAA Approved document as indicated on the List of Effective pages.

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: Reissue Chapter 01: Introduction Date: 09/22/2017 Section 03: Program Summary Page: 6 of 9 1.3.1 Ace Aviation Services, Corp. Time Limitations List (TLL) A. Ace Aviation Services, Corp. TLL is the results the audits/research of 1.3, C through J for those time items not part of the Airframe or Engine Manufacturers program. The TLL for each aircraft is found in chapter 4 of this volume. 1.4 Maintenance Inspection Task Listing A. Ace Aviation Services, Corp. utilizes Contracted Computer Maintenance Tracking Programs (CCMTP) available from a variety of commercial sources. Each program is aircraft specific by U.S. aircraft registration number. B. Each aircraft Time Limits List (TLL) will identify the CCMTP being utilized for that particular aircraft. C. Regardless of the brand type, all CCMTP s will be able to list all Maintenance Inspection Program tasks required by this MIP on a Status Report. 1. Each listed task on a Status Report shall be able to; a. Be sorted by ATA code. b. Be readily identified back to the approving document through either one of or a combination of; (i) Task description, A. Minor variances and abbreviations to task description may be acceptable. (ii) Unique identifier number assigned by the controlling document or through the Time Limitation Listing (TLL) in appendices of this MIP. A. CCMTP s will at time utilize the identifying number within their own unique number system or; B. The number will be referenced in a portion of the Status Report listing as a Reference. c. Show last compliance. d. Show interval/s. e. Show next due. f. Show time remaining g. List part number and serial number (if applicable) if a time controlled component.

Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 3: Learjet 45 Maintenance and Inspection Program Revision: Reissue Chapter 01: Introduction Date: 09/22/2017 Section 03: Program Summary Page: 7 of 9 1.5 Short Term Escalation, Ops Spec D076 A. Ace Aviation Services, Corp. through Operations Specification D076 may escalate MIP tasks as applicable to the Short Term Escalation policies and procedures in the GMM, Volume 1 Sub-Section 5.3, Extension of Maintenance Inspection Program Items.

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Airworthiness Limitations AIRWORTHINESS LIMITATIONS 1. Description (See Figure 1.) NOTE: Figure 1 is the FAA ACO approval page and is found in the LR45 MM-104. 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 Maintenance Requirements (4-10-00) lists aircraft components and systems which require monitoring through scheduled maintenance. (2) Certification Maintenance Requirements - Structure Checks (4-10-01) 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 5-10-00 are not applicable to these tasks. (b) Items marked by two asterisks (**) in Sections 4-10-00 and 4-10-01 indicates that the inspection task can be adjusted to agree with the inspection tolerances indicated in Chapter 5, Section 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. Page 1 04-00-00 Revision: Reissue 09/22/2017

Airworthiness Limitations (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 (*). (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. Page 2 04-00-00 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Component and System Checks 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 touchdown. IRN ZONE/ ACCES S 100 NOSE MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS Q3510005 120 ** Oxygen Cylinder Low Pressure Relief Valve - Perform Functional Test. N3510013 120 ** Oxygen Cylinder and Remote Oxygen Fill Valves - Perform Periodic Check. (Effective on Aircraft 45-005 thru 45-244 modified per SB 45-12-1 and Aircraft 45-245 and Subsequent.) 200 FORWARD FUSELAGE INTERVAL 5,195 Hours. 1,500 Hours. O2130002 220 ** Pressurization Control System - Perform Functional Test. 1,200 Hours A2210033 220 ** Autopilot System - Perform Autopilot Disconnect Tone Test. A2300000-4A A2300000-4B 220 ** Engine Indicating and Crew Alerting System (EICAS) - Perform Radio Management Units (RMU) Backup Engine Page Check. 220 ** Engine Indicating and Crew Alerting System (EICAS) - Perform Radio Management Units (RMU) Power Supply Check. R2431003 220 ** Battery Warning System - Perform Functional Test. (Effective on Aircraft with Ni-Cad batteries installed.) 900 Hours 1,000 Hours. 2,300 Hours. 2,400 Hours. W2450000 220 ** Generator Fail Indication - Perform Operational Check. 600 Hours. H2450001 220 ** Auxiliary Power Supplies - Perform Functional Test. 600 Hours. B2450002 220 ** Electrical System Control - Perform Operational Check. 1,200 Hours. Page 1 04-10-00 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS H2450023 200 ** EMER BATT LOW and GEN AMPS HIGH Indication - Perform Operational Check. J2620000 220 ** Engine Fire Extinguishing System Fire Switch - Perform Functional Test. INTERVAL 600 Hours. 5,000 Hours T2620001 220 ** Firewall Shutoff Valves - Perform Operational Check. 2,500 Hours. A2711001 220 ** Aileron Trim Tab Control System - Perform Operational Check. 600 Hours. V2712000 220 ** Roll Disconnect Switches - Perform Operational Check. 600 Hours. A2721001 220 ** Rudder Trim System - Perform Operational Check. 600 Hours. D2740003 220 ** Horizontal Stabilizer Actuator Secondary Trim - Perform Functional Test. D2740004 220 ** Horizontal Stabilizer Actuator Primary Trim - Perform Functional Test. F2840003 220 ** Fuel Quantity Signal Conditioner - Perform Functional Test to Verify Weight-on-Wheels (WOW) inputs. (Effective on Aircraft 45-005 thru 45-194 modified per SB 45-28-5 and Aircraft 45-195 and Subsequent.) 600 Hours. 600 Hours. 1,200 Hours. H3010000 220 ** Wing/Stab Anti-Ice Switch - Perform Operational Check. 600 Hours. A3030000 220 ** Pitot/Static Heat System - Perform Operational Check. 3,000 Hours. T3040000 220 ** Windshield Anti-ice - Perform Functional Test of the Windshield Anti-ice System. B3100000-4A B3100000-4B A3400000-4A A3400000-4B A3400000-4C 220 ** Integrated Avionics Computer - Perform Symbol Generation Reversion Check. 220 ** Engine Indicating and Crew Alerting System (EICAS) - Perform Data Acquisition Units (DAU) Reversion Check. 600 Hours. 1,000 Hours. 1,200 Hours. 220 ** Air Data Computers - Perform Reversion Check. 3,000 Hours. 220 ** Attitude Heading Reference System (AHRS) - Perform Power Supply Check. 220 ** Attitude Heading Reference System (AHRS) - Perform AHRS Reversion Check. 1,000 Hours. 1,000 Hours. Page 2 04-10-00 Revision: 1 04/16/2018

Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS K3500021 200 ** Oxygen System Low Pressure Supply Hoses - Perform Operational Check. Ensure that hoses are free of obstructions. (Effective on Aircraft 45-033, 45-035, 45-195, and 45-207.) INTERVAL 6,000 Flight Hours. W3510002 230 ** Oxygen System - Perform Operational Check. 600 Hours. O3510003 220,230 ** Cabin Low Pressure Oxygen Distribution Flex Hoses - Perform Functional Test. S3510014 220 ** Oxygen System Altitude Compensating Regulator - Perform Functional Test. (Effective on Aircraft 45-005 thru 45-169 modified by SB45-35-1 extended duration oxygen system installed and 45-170 and Subsequent.) Q3510018 230 ** Oxygen Cylinder Lower Pressure Relief Valve - Perform functional test. (Effective on aircraft equipped with increased capacity oxygen system.) N3510019 230 ** Oxygen Cylinder and Remote Oxygen Fill Valves - Perform periodic check. (Effective on aircraft equipped with increased capacity oxygen system.) 600 Hours. 600 Hours. 5,195 Hours. 1,500 Flight Hours. A3610000 220 ** Bleed Air System - Perform Functional Test. 600 Hours. A3610001 220 ** Pylon Overheat Thermostat and Electrical System - Perform Functional Test. 600 Hours. H4900011 200 ** APU Generator - Perform overvoltage protection check. 1,200 Hours. W5600002 220 ** Windshield - Perform Rain Removal Coating Effectiveness Test. 300 AFT FUSELAGE/EMPENNAGE L2150056 300 ** Auxiliary Heat System - Perform Functional Test. (Effective on Aircraft 45-250 and subsequent equipped with Keith Products vapor air cycle air conditioning system using refrigerant R-134.) L2150057 300 ** Auxiliary Heat System - Perform Auxiliary Heater Electrical and Temperature Switch Test. (Effective on Aircraft 45-250 and subsequent equipped with Keith Products vapor air cycle air conditioning system using refrigerant R-134.) A2731002 220/320 ** Elevator Disconnect System - Perform Operational Check. 12 Months. 600 Hours. 1,200 Hours. 600 Hours. Page 3 04-10-00 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS W2731001 320 ** Pitch Trim - Perform Operational Check of Elevator Override Actuator. H2840001 320 * Dual Fuel Flow Convertor (DFFC) (P/N 10540B06F07) - Perform Acceptance Test and Low Temperature Screening. 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 THRUST REVERSERS INTERVAL 600 Hours. 300 Flight Hours or 12 Months, whichever is greater. A3020000 430/440 ** Nacelle Anti-ice System- Perform Functional Test. 1,200 Hours. F7720002 Deleted. D7830078 400 ** Thrust Reverser System Throttle Retard Actuator - Perform Operational Check. 500/600 LEFT/RIGHT WING A2760001 540/640 ** Spoiler Actuator Check Valve - Perform Operational Check. A2760002 540/640 ** Spoiler System - Perform Spoiler Authority with Flaps Check. 700 LANDING GEAR AND RELATED SYSTEMS Q2460001 720/730 ** Power Distribution System - Perform Squat Switch Check. O3220005 A3230001 710/720/ 730 Deleted. ** Landing Gear - Perform Emergency Gear Extension Functional Test. V3240004 720/730 ** Emergency/Parking Brake Switch - Verify that "Emergency/Parking Brake" message illuminates on EICAS when parking brake is set and throttles are moved above MCR detent. 2,400 Hours. 600 Hours. 600 Hours. 1,200 Hours. 600 Hours. 600 Hours. A3240005 720/730 ** Brake Hydraulic Fuses - Perform Functional Test. 1,200 Hours. Page 4 04-10-00 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS INTERVAL A3240006 720/730 ** Brake Shuttle Module - Perform Functional Test. 1,200 Hours. A3240007 720/730 ** Brake Shuttle Valves - Perform Functional Test. 2,400 Hours. V3240008 720/730 ** Emergency/Parking Brake Control System Perform Functional Test. 600 Hours. A3240009 720/730 ** Brake Pressure Transducers - Perform Functional Test. 4,800 Hours. B3261000 Replaced by IRN Q2460001 Page 5 04-10-00 Revision: Reissue 09/22/2017

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Certification Maintenance Requirements Structure Checks 1. Time Compliance CERTIFICATION MAINTENANCE REQUIREMENTS STRUCTURE CHECKS 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 touchdown. IRN ZONE/ ACCESS 200 FORWARD FUSELAGE MAINTENANCE REQUIREMENTS STRUCTURE CHECKS K2700007 230 * Aileron Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. K2700008 230 * Elevator Control System Primary Cables - Remove from aircraft and perform detailed visual inspection K2700009 230 * Rudder Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. E5310001 E5310002 230CL, 230DL, 230EL, 230CR, 230DR, 230ER 220AL, 220BL, 220DL, 220AR, 220BR, 220DR * Longeron, Internal (between FS 384 and FS 433) - Perform visual inspection. * Flight Deck Longeron - Perform visual inspection (FS 149 - FS 196). Inspect flight deck longeron stiffeners, webs, and cutouts. INTERVAL 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. Page 1 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS P5310003 270 * Aft Pressure Bulkhead Support Post (FS 457) - Perform Eddy Current Inspection. P5310004 270 * Aft Pressure Bulkhead Frame Periphery - Perform Eddy Current Inspection. P5310006 120AR, 130AL * Forward Pressure Bulkhead - Perform Eddy Current Inspection. A5310007 270 * Aft Pressure Bulkhead Bottom Shear Diaphragm - Perform Detailed Visual Inspection. Inspect bulkhead post attachment fastener holes and control cable slot. E5310017 270 * Aft Pressure Bulkhead Bottom Crossmember (FS 457) - Perform Detailed Visual Inspection. Inspect tee-section at FS 457 flange at attachment to pressure floor. E5310018 270 * Aft Pressure Bulkhead Panel Facing Sheets (FS 457) - Perform visual inspection. Inspect both front and aft of facing sheets. T5310027 270BC * Aft Pressure Bulkhead Top Mounting Structure - Perform Eddy Current Inspection. L5311002 210 * Nose Landing Gear Actuator Attachment on Forward Pressure Bulkhead - Perform Eddy Current Inspection. P5320001 230 * Fuselage Pressure Floor Step (FS 433 - FS 457) - Perform Eddy Current Inspection. INTERVAL 5,000 Flight Hours Repeat. 10,000 Landings Initial, 10,000 Landings Repeat. Page 2 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN M5323021 A5323023 ZONE/ ACCESS 250DL, 250ER 250DL, 250ER MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * External longeron, fastener locations, and area around wing attachments - Perform visual inspection. Inspect longeron between FS 398 and FS 486, stringer 13LHS & RHS. INTERVAL * Drag Link Attachment Lug - Perform visual inspection. 5,000 Flight E5323025 220 * Forward/Aft Wheelbox Joint (FS 150) - Perform visual inspection. Inspect splice strap aft of forward pressure bulkhead at intersection of attachment angle and flight deck longeron. N5323026 230 * Upper and Lower Passenger/Crew Door Skin Cutout Corners (FS 224 - FS 256) - Perform Eddy Current Inspection. Inspect skin at corners of passenger/crew door cutout. P5323027 230 * Fuselage Frame at F.S. 412 - Perform Eddy Current Inspection. T5323028 250 * Fuselage to Wing Attach Fittings - Perform Eddy Current Inspection. P5323029 230 * Machined Spar Frames Systems Cutouts (FS 398, FS 412, FS 432, FS 466) - Perform Eddy Current Inspection. H5323032 230 * Exterior Cabin Window Coamings (Unpainted) - Perform Eddy Current Inspection. P5323033 230 * Fuselage Skin at Emergency Door Egress Light and Wing Inspection Light - Perform Eddy Current Inspection. 4,800 Flight Hours Initial, 2,400 Flight 5,000 Flight 5,000 Flight 5,000 Flight 2,400 Flight Hours/ 24 Months Initial, 2,400 Flight Hours/ 24 Months Repeat. Page 3 04-10-01 Revision: Reissue 09/22/201

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS M5323034 220 * Upper and Lower Coupe Rail and Center Post/ Windshield Retainer Attachment - Perform Eddy Current inspection. P5323037 220 * Windshield Coupe Rail Tie Rod Bracket - Perform Eddy Current Inspection. P5323038 220 * Windshield Centerpost to Upper Coupe Rail Joint Attachment - Perform Eddy Current Inspection. D5323039 230 * Machined Fuselage Frame at FS 466 - Perform detailed visual inspection of the lower frame section between stringer 13 left and right, paying particular attention to the BL 10 splices. Confirm any crack indications with eddy current procedures. (Effective on Aircraft 45-034 only.) P5323047 220/230 * Pressure Cabin Fuselage Crown Skin - Perform Eddy Current Inspection. Q5323048 220/230 * Fuselage (Pressure Cabin) - Perform Eddy Current Inspection. Inspect pressure cabin skin (longitudinal skin cracking). P5323049 220 * Fuselage Skin at Upper and Lower Coupe Rail Runout Joints - Perform Eddy Current Inspection. E5323050 220 * Aft Post/Windshield Retainer Attachment - Perform Eddy Current Inspection. Inspect windshield aft post at windshield retainer fastener holes. INTERVAL 7,600 Flight Hours Repeat. 5,000 Flight Hours Repeat. 2,400 Flight Hours Repeat. 6,625 Flight Hours Repeat. 6,797 Flight Hours Repeat. Page 4 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS Q5323051 220/230 * Longitudinal Joints inside Pressure Cabin (FS 220 - FS 457) and skin within one stringer bay of joint - Perform Eddy Current inspection. Inspect skin fastener holes along joints at stringer 10 LH and RH, stringer 2 RH, and stringer 18 RH. E5323053 220 * Frame Attachments to Upper and Lower Coupe Rails (FS 171 to FS 204) - Perform visual inspection. Inspect the following: a. Frame attachments to lower coupe rails at FS 171, 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) - Perform visual inspection. Inspect tie-rod ends, tie-rod tubes, and tie-rod bolts. E5323055 220 * Tie-Rod Assembly (FS 162) (Titanium ends) - Perform visual inspection. Inspect tie-rod ends, tie-rod tubes, and tie-rod bolts. F5323056 220 * Tie-Rod Fork Ends (Aluminum) - Perform Fluorescent Penetrant Inspection. (Effective on Aircraft 45-001 thru45-058.) P5323057 220/230 * Pressure Cabin Skin at Fuselage Station 451 - Perform Eddy Current Inspection. P5323058 220/230 * Fuselage Skin at F.S. 504 - Perform Eddy Current Inspection. Q5323059 220 * Stringer to Frame Joints (FS 162 to FS 213) - Perform Eddy Current Inspection. Inspect skin, stringers, and frames at joints. INTERVAL 6,625 Flight Hours Repeat. 4,800 Flight 4,800 Flight 9,600 Flight 9,600 Flight Hours Repeat 4,800 Flight 4,800 Flight 2,400 Flight 5,000 Flight Page 5 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS P5323069 220 * Circumferential Skin Joint at Forward Pressure Bulkhead - Perform Eddy Current Inspection. E5323073 220 * Fuselage Bottom Skin Panel - Perform visual inspection. Inspect corner radius at junction of external longeron and mid spar frame (FS 435). E5323074 220 * Auxiliary Skin Panel - Perform visual inspection. Inspect corner radius at junction of keelbeam and rear spar frame (FS 466). F5323081 220 * Tie-Rod Fork Ends (Titanium, P/N R24889) - Perform Fluorescent Penetrant Inspection. (Effective on Aircraft 45-059 and Subsequent and prior Aircraft with titanium rod assembly installed.) H5323092 230 * Fuselage Skin and Doubler around ECS Duct Cutout - Perform Eddy Current Inspection. P5323164 220 * Fuselage Skin and Doubler around ECS Duct Cutout - Perform Eddy Current Inspection. P5323165 220 * Windshield Center Post to Lower Coupe Rail Joint Attachment - Perform Eddy Current Inspection. INTERVAL 9600 Flight 9600 Flight Page 6 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS T5323166 200 * External Skin Cut-outs/Penetrations (Pressure Cabin) - Perform Detailed Visual Inspection. Inspect skin and doublers at antennas, electrical components, and access panels (excluding pitot/static probes, AOA stall vanes, and wing inspection light). (Refer to 5-10-00.) INTERVAL Hours/12 years or less. 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 September 20, 2010. V5323168 220 * LH and RH Lower Coupe Rail Radius/Windscreen Retainer Attach (P/N s 4553130001-802 thru 4553130001-809) - Perform Eddy Current Inspection (Effective on Aircraft that have complied with SB 45-56- 3, Windows - Windshield Coupe Rail Inspection. ) Z5323172 200 * Skin Cut-Out for Iridium Antennas FS283.88 to FS308.39 - Perform Eddy Current Inspection. (Effective on Aircraft 45-435, 45-445, 45-447, 45-448, 45-449, 45-450, 45-451, 45-452 and 45-454 only) E5350000 240 * Bottom Keelbeam End Pads (FS 384 - FS 486) - Perform visual inspection. Inspect end pads around bolt holes and in radii at FS 433. N5600003 220/230 * Windshields - Perform ultrasonic inspection of the structural plies. (Effective on Aircraft with Sierracin windshields installed.) L5600010 220/230 * Cabin Windows (including the emergency exit window) - Perform detailed visual inspection. N5600012 220/230 * Windshields - Perform bolt hole inspection. (Effective on Aircraft with GKN windshields installed.) 300 AFT FUSELAGE/EMPENNAGE 5,000 Flight 5,000 Flight Hours Repeat 9,600 Flight 4,800 Flight 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. 4,800 Flight 4,800 Flight 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. Page 7 04-10-01 Revision: 1 04/16/2018

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS K2700010 310 * Elevator Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. K2700012 310 * Rudder Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. T2740002 330AC, 330AR, 330BC, 330CC, 330CL, 330XL, 330WR, 330YL, 330XR * Horizontal Stabilizer Actuator (6627401000-007) - Perform Inspection. NOTE: Remove Horizontal Stabilizer Actuator from aircraft. Send actuator to Learjet on a parts return claim form so unit can be exchanged with serviceable unit and returned to vendor for overhaul. Refer to Replacement Schedule section 5-19- 01 for life-limited components (IRN # s N2740023 and N2740024). INTERVAL 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. 600 Flight Hours or 24 Months, whichever occurs first. The 24 Month interval is calculated from September 6, 2011. N2740025 330AC, 330AR, 330BC, 330CC, 330CL, 330XL, 330WR, 330YL, 330XR * Horizontal Stabilizer Actuator (6627401000-007) - Perform Detailed Structural Inspection. NOTE: Remove Horizontal Stabilizer Actuator from aircraft. Send actuator to Learjet on a parts return claim form so unit can be exchanged with serviceable unit and returned to vendor for overhaul and structural inspection. Refer to Replacement Schedule section 4-11- 00 for life limited components (IRN # s N2740023 and N2740024). 2,400 Flight Hours Initial, 2,400 Flight Page 8 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN P2740032 ZONE/ ACCESS 330AR, 330BC, 330CL, 330XL, 330WR, 330YL, 330XR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Horizontal Stabilizer Actuator (6627401000-009) - Perform Inspection. (Refer to 27-40-00.) NOTE: Remove Horizontal Stabilizer Actuator from aircraft. Send actuator to Learjet on a parts return claim form so unit can be exchanged with serviceable unit and returned to vendor for overhaul. INTERVAL 1200 Hours. Interval is calculated from time since new or from the Time Since Overhaul (TSO) hours. P2740033 330AR, 330BC, 330CL, 330XL, 330WR, 330YL, 330XR * Horizontal Stabilizer Actuator (6627401000-009) - Perform Detailed Structural Inspection. NOTE: Remove Horizontal Stabilizer Actuator from aircraft. Send actuator to Learjet on a parts return claim form so unit can be exchanged with serviceable unit and returned to vendor for overhaul and structural inspection. 2,400 Flight 2,400 Flight Q3010006 310QR, 310HL Interval is calculated from time since new or from the Time Since Structural Inspection (TSSI) hours. ** Anti-Ice Manifold - Perform Boroscope Inspection. 1200 Hours. A5310005 360 * Fuselage Fuel Cell Canted Bulkhead (FS 495) - Perform visual inspection, paying particular attention to main crossmember. Inspect flanges and attachments for cracking. 5,000 Flight P5323024 310AC, 310BC, 310AL, 310BL, 310AR, 310BR * Fuselage Skin Cut-outs Above Fuel Cell - Perform Eddy Current Inspection. E5323068 310 * Stringer 1 RH between FS 533 and FS 543 - Perform visual inspection. Inspect stringer 1 flange and skin along stringer 1 between FS 533 and FS 543. 5,000 Flight Hours Repeat. Page 9 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN F5331021 ZONE/ ACCESS 320CL, 320BR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Forward Canted Bulkhead (FS 630) - Perform visual inspection. Inspect at front spar upper attachment fasteners. INTERVAL 5,000 Flight F5331022 F5331023 320DL, 320CR 320BL, 320EL, 320DR * Mid Canted Bulkhead (FS 657) - Perform visual inspection at mid spar upper attachment fasteners. * Aft Canted Bulkhead (FS 682) - Perform visual inspection. Inspect at rear spar attachment fasteners. F5331024 320 * Vertical Stabilizer Front Spar Root Bulkhead Attachment (FS 630) - Perform visual inspection. Inspect front spar root bulkhead attachment at fastener holes. F5331025 320 * Vertical Stabilizer Mid Spar Root Bulkhead Attachment (FS 657) - Perform visual inspection. Inspect mid spar root bulkhead attachment at fastener holes. F5331026 320 * Vertical Stabilizer Rear Spar Root Bulkhead Attachment (FS 682) - Perform visual inspection. Inspect rear spar root bulkhead attachment at fastener holes. H5450012 E5450029 310HL, 310JL, 310QR, 310RR 310HL, 310RR, 340FL, 340GL, 340HL, 340FR, 340GR, 340HR * Frames 39/40 (FS 512/518) at Engine Beam Attachment - Perform Eddy Current Inspection. Inspect outer flange and frame web at engine beam attachment. * Aft Engine Beam - Perform visual inspection. Inspect upper capping plate, around fastener holes in the capping plate, and channel flange. 5,000 Flight 5,000 Flight Page 10 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN P5450030 ZONE/ ACCESS 310HL, 310RR, 340FL, 340GL, 340HL, 340FR, 340GR, 340HR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Aft Engine Beam End Fitting - Perform Eddy Current Inspection. INTERVAL 5,000 Flight G5510000 330AC, 330BC, 330CL, 330XL, 330WR, 330AR. 330XR, 330YL * Horizontal Stabilizer Actuator Attachment Fitting - Perform Eddy Current Inspection. 5,000 Flight 5,000 Flight T5510004-4A 330 * Rudder Top Hinge Fitting - Perform visual inspection. Inspect lug (FS 721). T5510004-4B 330 * Rudder Mid Hinge Fitting - Perform visual inspection. Inspect lug (FS 721). T5510004-4C 330 * Rudder Lower Hinge Fitting - Perform visual inspection. Inspect lug (FS 709). N5510005 330CC * Horizontal Stabilizer Rear Spar Cap - Perform Eddy Current Inspection. Inspect rear spar cap and web at center splice. P5510006 320CL, 320BR NOTE: On aircraft that have exceeded 4,800 hours total time, perform inspection within 600 hours. * Vertical Stabilizer Front Spar and Mid Spar- Perform Radiographic Inspection. 4,800 Flight Hours Initial, 2,400 Flight Page 11 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN Q5510007 P5510008 ZONE/ ACCESS 320EL, 320DR 330FL, 330ER MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Vertical Stabilizer Skin and Lower Aft Spar Cap - Perform Eddy Current Inspection. * Horizontal Stabilizer Primary and Secondary Attach Bolts - Perform Magnetic Particle Inspection. P5510009 330 * Horizontal Stabilizer Mid Spar Upper Cap B.L. 0.0 to B.L. 4.0 - Perform X-ray Inspection. M5510010 330 * Horizontal Stabilizer Aft Root Rib - Perform Eddy Current Inspection. Inspect aft root rib internal between mid spar and aft spar and upper and lower skins external at attachment fasteners. NOTE: On aircraft that have exceeded 4,800 hours total time, perform inspection within 600 hours. P5510011 330 * Horizontal Stabilizer Mid Spar and Rear Spar Upper Flange at Root Rib - Perform Radiographic Inspection. A5510014 330 * Vertical Stabilizer Pivot Fitting Bottom Plate - Perform Detailed Visual Inspection. Inspect aft portion of bottom plate through lightening hole in top plate, forward portion of bottom plate through top plate cutouts, and bottom of outside exposed surface of pivot fitting. N5510015 330WR, 330XL, 330CC, 330XR, 330YL, 330DL * Vertical Stabilizer Pivot Fitting Top Plate - Perform Eddy Current Inspection. INTERVAL 2,500 Flight 4,800 Flight 1,200 Flight 9,720 Flight 5,000 Flight Hours Initial, 2,451 Flight Page 12 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN N5510016 P5510017 ZONE/ ACCESS 330BL, 330BR, 330CC, 330XL, 330WR, 330YL, 330XR, 330DL 330BL, 330BR, 330CC, 330XL, 330WR, 330YL, 330XR, 330DL MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Vertical Stabilizer Pivot Fitting Tower Section Forward Radius - Perform Eddy Current Inspection. Inspect pivot fitting at tower section radius, pivot fitting and top plate around adjacent fasteners, and pivot fitting sides at tower section radius. * Vertical Stabilizer Pivot Fitting Tower Section - Perform Eddy Current Inspection. P5510018 330 * Vertical Stabilizer Pivot Fitting Lugs - Perform Eddy Current Inspection. P5510019 330 * Elevator Hinges on Horizontal Stabilizer - Perform Eddy Current Inspection. P5510020 330 * Horizontal Mid Spar Upper Cap - Perform Eddy Current Inspection. A5510021 330 * Horizontal Mid Spar from Canted Rib #2 to Canted Rib #3 - Perform Detailed Visual Inspection. INTERVAL 5,000 Flight 2,451 Flight 4,641 Flight Page 13 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN G5510023 P5510024 H5510033 ZONE/ ACCESS 330AC, 330BC, 330CL, 330XL, 330WR, 330AR, 330XR, 330YL 330XL, 330WR, 330CC 330CL, 330BR, 330XL, 330WR, 330YL, 330XR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Horizontal Stabilizer Actuator Vertical Tail Attachment - Perform Eddy Current Inspection. * Elevator Control Horn - Perform Eddy Current Inspection. * Horizontal Stabilizer Actuator Attach Bolts - Perform Liquid Penetrant Inspection. N5510069 330 * Horizontal Stabilizer Mid Spar Flange Root Rib Attachment - Perform Eddy Current Inspection. P5510070 330 * Horizontal Stabilizer Front Spar - Perform Radiographic Inspection. P5510073 E5510074 330FL, 330ER 330WL, 330VR * Horizontal Stabilizer Rear Spar Upper Cap - Perform Eddy Current Inspection. * Horizontal Stabilizer Rear Spar from Canted Rib #2 to Canted Rib #3 - Perform visual inspection. Inspect rear spar cap and fasteners. INTERVAL 5,000 Flight 5,000 Flight 5,000 Flight Hours Initial, 5,000 Flight Hours Repeat. 4,800 Flight Hours Initial, 2,400 Flight Hours Repeat. Page 14 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN E5510075 E5510076 ZONE/ ACCESS 330WL, 330VR 330WL, 330VR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Horizontal Stabilizer Outboard Spars and Skins Outboard of Canted Rib #3 - Perform visual inspection. Inspect spar caps and fasteners. * Horizontal Stabilizer Front Spar from Canted Rib #2 to Canted Rib #3 - Perform visual inspection. Inspect front spar cap and fasteners. N5510082 330 * Horizontal Stabilizer Rear Spar Flange Root Rib Attachment - Perform Eddy Current Inspection. W5510091 P5510092 330ER, 330FL 330AC, 330BC, 330CC NOTE: On aircraft that have exceeded 4,800 hours total time, perform inspection within 600 hours. * Horizontal Stabilizer Hinge Primary and Secondary Pivot Pin Installation and Attaching Hardware - Perform Detailed Visual Inspection. * Horizontal Stabilizer Upper Spar Splice Doubler - Perform Eddy Current Inspection. P5520001 330 * Elevator Hinge Attach Bolt - Perform Magnetic Particle Inspection. P5520002 330ML, 330PL, 330LR, 330NR * Elevator Hinge Pin - Perform Liquid Penetrant Inspection. (Effective on Aircraft 45-001 thru 45-014.) E5520003 330 * Elevator Front Spar - Perform visual inspection. Inspect spar cap at fastener holes. INTERVAL 4,800 Flight Hours Initial, 2,400 Flight Hours Repeat 625 Hours 2,500 Flight Page 15 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS E5520004 330CC * Elevator Rib #1 Cap - Perform visual inspection of rib #1 cap cross section and rib cap flanges at torque tube. P5520021 330UL, 330VL, 330JL, 330TR, 330UR, 330HR * Elevator Hinge Fittings - Perform Eddy Current Inspection. (Effective on Aircraft 45-015 and subsequent.) P5520022 330 * Elevator Hinge Primary and Secondary Attach Bolts - Perform Liquid Penetrant Inspection. Q5530011 330 * Vertical Stabilizer Skin and Upper Aft Spar Cap - Perform Eddy Current Inspection. A5540000 330 * Rudder Root Rib Cap (FS 698) - Perform visual inspection. Inspect around fastener holes and lightening holes. P5540001 330QL, 330RL, 330SL, 330TL, 330PR, 330QR, 330RR, 330SR * Rudder Spar - Perform Detailed Visual Inspection. Inspect spar caps and fasteners. (Refer to 5-10-00.) P5540002 330 * Rudder Attach Bolts - Perform Liquid Penetrant Inspection. INTERVAL 9,600 Flight 2,400 Flight 9,600 Flight 9,600 Flight Page 16 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS 400 POWERPLANTS, NACELLES, AND THRUST REVERSERS Z3020005 430/440 * Engine inlet anti-ice tube assembly from the aft inlet bulkhead connection point forward to spray ring connection, perform detailed visual/borescope inspection of the welds inside and outside of the tube at both forward and aft ends. (Refer to 30-20-00) (Effective on Aircraft 45-001 thru 45-367, 45-369, and 45-447 thru 45-455 not modified by SB 45-72-3 P5450011 450/460 340CL, 340CR * Drag Strut Attachment Fittings - Perform Eddy Current Inspection. M5450015 450/460 * Forward Engine Beam, Spar Cap and Web - Perform Eddy Current Inspection. P5450016 340AR, 340BR, 340CR, 340DR, 340ER, 340FR, 340AL, 340BL, 340CL, 340DL, 340EL, 340FL * Forward Engine Beam End Fitting - Perform Eddy Current Inspection. P5450017 450/460 * Forward Engine Beam to Frame Attach Bolts - Perform Liquid Penetrant Inspection. M5450018 400 * Forward Engine Mount Attach Bolts - Perform Fluorescent Liquid Penetrant Inspection. INTERVAL 250 Hours. 5,000 Flight 4,800 Flight 4,800 Flight Hours Repeat. 5,000 Flight 4,800 Flight Page 17 04-10-01 Revision: 1 04/16/2018

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS F5450019 450/460 * Aft Engine Beam Attachment to Frames - Perform visual inspection. Inspect aft engine beam attachment to frames. P5450020 450/460 * Aft Engine Beam to Frame Attachment Bolt - Perform Liquid Penetrant Inspection. P5450021 450/460 * Engine Aft Isolator Mount Fittings - Perform Liquid Penetrant Inspection. A5450022 450/460 * Aft Engine Mount to End Fitting Attach Bolt - Perform Magnetic Particle Inspection. P5450023 450/460 * Engine to Aft Engine Mount Attach Bolts - Perform Liquid Penetrant Inspection. P5450024 450/460 * Fuselage Frames at FS 543.55 and 546.15 to Aft Engine Beam Attachment - Perform Eddy Current Inspection. INTERVAL 5,000 Flight 5,000 Flight 5,000 Flight 5,000 Flight 5,000 Flight 5,000 Flight P5450025 450/460 * Forward Engine Beam and Frames at Attach Holes - Perform Eddy Current Inspection. 5,000 Flight A5450026 450/460 * Engine Drag Strut - Perform Eddy Current Inspection. 5,000 Flight P7120001 450/460 * Forward Engine Mount - Perform Eddy Current Inspection. 500/600 LEFT/RIGHT WING 4,800 Flight Page 18 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS K2700014 540/640 * Aileron Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. W2750056 540/640 * Flap Actuator Joint (P/N 145673-1) - Perform Detailed Visual Inspection. Apply Corrosion Preventive Compound (CPC) to joint. S2750057 540/640 * Flap Actuator Ballnut Sleeve (Flap Actuator Assembly Learjet P/N 6627503000-009, 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. INTERVAL 4,800 Flight Hours from installation, 4,800 Flight Hours thereafter. 12 Months. 6 Months Initial, 6 Months Repeat. 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, 250CL, 250ER, 250DR, 510BL, 610BR * Wing Drag Link Attach Fitting - Perform Magnetic Particle Inspection. 4,640 Flight N5710002 520GL, 620GR * Wing Box Mid Spar Lower Cap, Outboard of Joint at WS 137 between Rib #7 and 8 - Perform Directed Visual Inspection. Inspect mid spar lower cap and lower skin panels. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 9,600 Flight 3,580 Flight Page 19 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN N5710004 ZONE/ ACCESS 250CC, 250FL, 250GR, 510BC MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Center Section Rear Spar - Perform Eddy Current Inspection. Inspect rear spar lower cap from centerline to WS 33. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) E5710005 510/610 * Wing Center Section Spar Upper Caps - Perform visual inspection. Inspect front, mid, and rear spar upper caps from centerline to skin termination at WS 33. N5710006 510AC, 510AL, 610AR, 510BC * Wing Center Section Forward and Aft Ribs at WS 6 and Forward Ribs at WS 17 - Perform Eddy Current Inspection. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) P5710007 510/610 * Wing to Fuselage Attach Fittings and Links - Perform Eddy Current Inspection. N5710008 N5710009 520EL, 520FL, 620ER, 620GR 520FL, 520GL, 620FR, 620GR * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection. Inspect mid spar lower cap and lower skin panels between WS 99 and WS 137. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Mid Spar Lower Cap Joint at WS 137 - Perform X-ray Inspection. Inspect mid spar center/outer joint. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710010 510/610 * Wing Box Rear Spar Lower Cap Inboard of Joint at WS 81 - Perform Ultrasonic Inspection. Inspect rear spar lower cap between skin termination at WS 48 and closing rib at WS 60. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 5,000 Flight 5,000 Flight 5,000 Flight 9,600 Flight 2,500 Flight 9,600 Flight Hours Initial, 4,517 Flight 9,600 Flight Hours Initial, 960 Flight Page 20 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN N5710011 N5710012 ZONE/ ACCESS 510AZ, 520CL, 520DL, 610AZ, 620CR, 620DR 520DL, 620DR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Box Rear Spar Lower Cap Joint at WS 81 - Perform X-ray Inspection. Inspect center and outer rear spars, lower splice plate, and lower skin between WS 60 and WS 90. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Rear Spar Lower Cap Outboard of Joint at WS 81 to Rib #6 - Perform Detailed Visual Inspection. Inspect outer rear spar lower cap and aft lower skin panel outboard of rear splice at WS 90. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710013 510/610 * Wing Box Rear Spar Lower Cap Skin Termination at MS 48 - Perform Eddy Current Inspection. Inspect rear spar lower cap between WS 33 and WS 48. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710014 500/600 * Wing Box Rear Spar Flap Track Cut-outs Perform Eddy Current Inspection. Inspect flap track cut-outs at WS 65, WS 126, and WS 184 on rear spar. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) P5710015 N5710016 540DZ, 540EZ, 540FZ, 540GZ, 640DZ, 640EZ, 640FZ, 640GZ 520AL thru 520ML, and 620AR thru 620MR * Wing Box Rear Spar at Aileron Hinge - Perform Eddy Current Inspection. * Wing Box Basic Skin/Stringer, Lower Skin - Perform Visual Inspection. Inspect outboard wing forward and aft lower skin panels and stringers. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 2,500 Flight 9,600 Flight 3,443 Flight 1,077 Flight 5,000 Flight 5,000 Flight 5,000 Flight Page 21 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN N5710017 ZONE/ ACCESS 520AL thru 520ML, and 620AR thru 620MR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Box Basic Skin/Stringer at Stringer Run-Out, Lower Skin - Perform Visual Inspection. Inspect stringer run-outs in forward and aft lower skin panels. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) P5710018 510/610 * Wing Lower Skin at Mid Spar Span Wise Joint - Perform Eddy Current Inspection. E5710019 510/610 * Wing Box, Upper Skin, Skin/Stringer and Spar Caps - Perform visual inspection. Inspect upper wing spar caps, skin panel, and stringers of outer wing. E5710020 510/610 * Wing Box Ribs - Perform visual inspection. Inspect all wing box ribs except closing rib between front and mid spars and closing rib between mid and rear spar. N5710021 N5710022 N5710023 520AL, 520BL, 520CL, 620AR, 620BR 520AL, 520BL, 520CL, 620AR, 620BR 250BC, 250BL, 250CR, 510AC, 520AL, 520BL, 620AR, 620BR * Center Section Mid Spar Lower Cap - Perform Eddy Current Inspection. Inspect mid spar from centerline splice plate to skin termination at MS 33. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Center Section Mid Spar Centerline Joint Perform Eddy Current Inspection. Inspect center mid spar (centerline to WS 17), lower splice plate, and center mid spar joint fitting lower cap. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Center Section Front Spar Lower Cap - Perform Eddy Current Inspection. Inspect center wing front spar lower cap between skin terminations (WS 31 left to WS 31 right). (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 2,500 Flight 2,500 Flight 2,500 Flight Hours Repeat. Page 22 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS P5710024 510/610 * Wing Rear Spar Side Stay Fitting Support Structure - Perform Eddy Current Inspection. P5710025 510/610 * Wing Front Spar Lower Cap From WS 33.0 to WS 60.0 - Perform Radiographic Inspection. N5710026 520AL, thru 520DL, and 620AR thru 620DR * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection. Inspect mid spar lower cap outboard of root rib at WS 33 to WS 99. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710028 510/610 * Wing Box Mid Spar Lower Cap, Skin Termination at WS 33 - Perform Bolt Hole Eddy Current Inspection. Inspect mid spar lower cap underneath root rib (WS 33) at point of skin termination. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) P5710029 510/610 * Wing Mid Spar Vertical Web - Perform Eddy Current Inspection. P5710030 510/610 * Wing Rear Spar Vertical Web - Perform Eddy Current Inspection. N5710031 520AL thru 520ML, 620AR thru 620MR * Wing Box Skin Access Cover Holes - Perform Eddy Current Inspection. Inspect access holes in forward and aft lower skin panels. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 5,000 Flight 2,500 Flight 2,278 Flight 4,800 Flight 5,000 Flight Hours Repeat. Page 23 04-10-01 Revision: 1 04/16/2018

Certification Maintenance Requirements Structure Checks IRN P5710032 ZONE/ ACCESS 520AL, 620AR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Rib Upper Aft Flange Fillet Radius at WS 33.0 - Perform Ultrasonic Inspection. P5710033 510/610 * Wing Access Hole in Closing Rib between Mid and Rear Spar - Perform Eddy Current Inspection. P5710034 550CL, 650CR * Wing Box Joint to Winglet - Perform Eddy Current Inspection. P5710035 520/620 * Wing Lower Skin at Drain Hole - Perform Eddy Current Inspection. N5710037 520BL thru 520ML, and 620BR thru 620MR * Wing Box Front Spar Lower Cap - Perform Visual Inspection. Inspect front spar lower cap and lower forward skin outboard of Mid-Spar Station (MS) 55. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) P5710083 550/650 * Flap Box Basic Structure - Perform Eddy Current Inspection. N5710121 520HL thru 520ML, and 620HR thru 620MR * Wing Box Mid Spar, Outboard of Rib #8 - Perform Visual Inspection at WS 156 and outboard to WS 260. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 5,000 Flight 5,000 Flight 5,000 Flight 5,000 Flight 2,500 Flight Hours Repeat. 5,000 Flight 5,000 Flight Page 24 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN N5710122 ZONE/ ACCESS 520FL thru 520ML, and 620FR thru 620MR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Box Rear Spar, Outboard of Rib #6 Perform Visual Inspection at WS 118 and outboard to WS 260. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710123 520/620 * Wing Box Mid Spar Lower Cap - Perform Eddy Current Inspection at trunnion fitting. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) L5710124 520/620 * Aileron Drive Support - Perform Ultrasonic Inspection. 4,800 Flight Hours N5710137 N5710138 N5710139 U5710147 N5710148 520BL, 620BR 520CL, 620CR 510AZ, 610AZ 520GL, 620GR 250CC, 250FL, 250GR, 510BC * Mid Spar at Rib #2 near WS 48 - Perform Bolt Hole Eddy Current Inspection. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Mid Spar at Rib #3 near WS 60 - Perform Bolt Hole Eddy Current Inspection. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Forward Flange Fasteners at Rear Spar between WS 52 and WS 60 - Perform Bolt Hole Eddy Current Inspection. (Effective on Aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Mid Spar Lower Cap, Outboard of Joint at WS 137 between Rib #7 and 8 - Perform Detailed Visual Inspection. Inspect mid spar lower cap and lower skin panels. (Effective on Aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Center Section Rear Spar - Perform Eddy Current Inspection. Inspect rear spar lower cap from centerline to WS 33. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). INTERVAL 5,000 Flight 9,600 Flight 2,666 Flight Initial, 4,800 Flight Hours Repeat. 4,800 Flight 4,800 Flight 9,600 Flight Hours Initial, 3,600 Flight 6,500 Flight 2,400 Flight 9,500 Flight Hours Initial, 4,500 Flight Page 25 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN N5710149 N5710150 N5710151 ZONE/ ACCESS 510AC, 510AL, 610AR, 510BC 520EL, 520GL, 620ER, 620GR 520FL, 520GL, 620FR, 620GR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Center Section Forward and Aft Ribs at WS 6 and Forward Ribs at WS 17 - Perform Eddy Current Inspection. (Effective on aircraft modified by SB 45-11- 5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection. Inspect mid spar lower cap and lower skin panels between WS 99 and WS 137. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Mid Spar Lower Cap Joint at WS 137 - Perform X- ray Inspection. Inspect mid spar center/outer joint. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710152 500/600 * Wing Box Rear Spar Lower Cap Inboard of Joint at WS 81 - Perform Ultrasonic Inspection. Inspect rear spar lower cap between skin termination at WS 48 and closing rib at WS 60. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710153 U5710154 10AZ, 520CL, 520DL, 610AZ, 620CR, 620DR 520DL, 620DR * Wing Box Rear Spar Lower Cap Joint at WS 81 - Perform X-ray Inspection. Inspect center and outer rear spars, lower splice plate, and lower skin between WS 60 and WS 90. (Effective on aircraft modified by SB 45-11- 5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Rear Spar Lower Cap Outboard of Joint at WS 81 to Rib #6 - Perform Detailed Visual Inspection. Inspect outer rear spar lower cap and aft lower skin panel outboard of rear splice at WS 90. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710155 510/610 * Wing Box Rear Spar Lower Cap Skin Termination at MS 48 - Perform Eddy Current Inspection. Inspect rear spar lower cap between WS 33 and WS 48. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 3,400 Flight 6,500 Flight 2,500 Flight 6,500 Flight Hours Initial, 3,000 Flight 6,500 Flight 600 Flight Hours Repeat. 3,400 Flight 6,500 Flight 2,300 Flight 6,900 Flight Hours Initial, 700 Flight Page 26 04-10-01 Revision: 1 04/16/2018

Certification Maintenance Requirements Structure Checks IRN Q5710156 ZONE/ ACCESS 520AL thru 520ML, and 620AR thru 620MR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Box Basic Skin/Stringer, Lower Skin Perform Visual Inspection. Inspect outboard wing forward and aft lower skin panels and stringers. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 7,400 Flight 5,000 Flight N5710157 520AL thru 520ML, and 620AR thru 620MR * Wing Box Basic Skin/Stringer Run-Out, Lower Skin - Perform Visual Inspection. Inspect Stringer run-outs in forward and aft lower skin panels. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 6,800 Flight N5710158 250BC, 250BL, 250CR, 510AC, 520AL, 520BL, 620AR, 620BR * Center Section Front Spar Lower Cap - Perform Eddy Current Inspection. Inspect center wing front spar lower cap between skin terminations (WS 31 left to WS 31 right). (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 1,800 Flight N5710159 520AL, 520BL, 520CL, 520DL, 620AR, 620BR, 620CR, 620DR * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection. Inspect mid spar lower cap outboard of root rib at WS 33 to WS 99. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 7,700 Flight 2,200 Flight N5710160 520AL, 620AR * Wing Box Mid Spar Lower Cap, Skin Termination at WS 33 - Perform Bolt Hole Eddy Current Inspection. Inspect mid spar lower cap underneath root rib (WS 33) at point of skin termination. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 6,800 Flight 3,300 Flight Page 27 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN N5710161 ZONE/ ACCESS 520AL thru 520ML, and 620AR thru 620MR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Box Skin Access Cover Holes - Perform Eddy Current Inspection. Inspect access holes in forward and aft lower skin panels. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 3,900 Flight Q5710162 520BL thru 520ML, and 620BR thru 620MR * Wing Box Front Spar Lower Cap - Perform Visual Inspection. Inspect front spar lower cap and lower forward skin outboard of Mid-Spar Station (MS) 55. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 8,000 Flight Hours Initial, 2,500 Flight N5710163 520AL, 520BL, 520CL, 620AR, 620BR * Center Section Mid Spar Centerline Joint Perform Eddy Current Inspection. Inspect center mid spar (centerline to WS 17), lower splice plate, and center mid spar joint fitting lower cap. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 7,000 Flight 1,700 Flight N5710164 520AL, 520BL, 520CL, 620AR, 620BR, open inboard MLG doors * Center Section Mid Spar Lower Cap - Perform Eddy Current Inspection. Inspect mid spar from centerline splice plate to skin termination at MS 33. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 1,700 Flight N5710165 remove flaps * Wing Box Rear Spar Flap Track Cut-outs - Perform Eddy Current Inspection. Inspect flap track cut-outs at WS 65, WS 126, and WS 184 on rear spar. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) 9,300 Flight Hours Initial, 3,400 Flight Page 28 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN Q5710166 Q5710167 ZONE/ ACCESS 520HL thru 520ML, and 620HR thru 620MR 520FL thru 520ML, and 620FR thru 620MR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Box Mid Spar, Outboard of Rib #8 - Perform Visual Inspection at WS 156 and outboard to WS 260. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Rear Spar, Outboard of Rib #6 - Perform Visual Inspection at WS 118 and outboard to WS 260. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710168 520/620 * Wing Box Mid Spar Lower Cap - Perform Eddy Current Inspection at trunnion fitting. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710169 N5710170 N5710171 520BL, 620BR 520CL, 620CR 510AZ, 610AZ * Mid Spar at Rib #2 near WS 48 - Perform Bolt Hole Eddy Current Inspection. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Mid Spar at Rib #3 near WS 60 - Perform Bolt Hole Eddy Current Inspection. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Forward Flange Fasteners at Rear Spar between WS 52 and WS 60 - Perform Bolt Hole Eddy Current Inspection. (Effective on aircraft modified by SB 45-11- 5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710172 520/620 * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection at trunnion fitting. (Effective on aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 8,200 Flight 4,100 Flight 4,100 Flight 6,500 Flight 1,800 Flight 7,700 Flight 3200 Flight 7,700 Flight 3,200 Flight 6,500 Flight 2,400 Flight 9,600 Flight 2,666 Flight Page 29 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS N5710173 520/620 * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection at trunnion fitting. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710174 510/610 * Wing Box Rear Spar Lower Cap Skin Termination at MS 48 - Perform Ultrasonic Inspection. Inspect rear spar lower cap between WS 33 and WS 48. (Effective on aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710175 510/610 * Wing Box Rear Spar Lower Cap Skin Termination at MS 48 - Perform Ultrasonic Inspection. Inspect rear spar lower cap between WS 33 and WS 48. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) N5710176 N5710177 P5710181 P5710182 520AL, 520BL, 520CL, 620AR, 620BR 520AL, 520BL, 520CL, 620AR, 620BR 250DL, 250CL, 250ER, 250DR, 510BL, 610BR 250DL, 250CL, 250ER, 250DR, 510BL, 610BR * Wing Mid Spar (Center Section) Lower Cap and Center Joint Fitting - Perform Ultrasonic Inspection. (Effective on aircraft not modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Mid Spar (Center Section) Lower Cap and Center Joint Fitting - Perform Ultrasonic Inspection. (Effective on aircraft modified by SB 45-11-5, Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Drag Link Tube - Perform Magnetic Particle Inspection. * Wing Drag Link Attach Bolts - Perform Liquid Penetrant Inspection. INTERVAL 6,500 Flight Hours Initial, 1,800 Flight 1,077 Flight 6,900 Flight 700 Flight Hours Repeat. 2,500 Flight 7,000 Flight 1,700 Flight 4,640 Flight 4,640 Flight Page 30 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN P5710183 ZONE/ ACCESS 250DL, 250CL, 250ER, 250DR, 510BL, 610BR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Drag Link Attach Clevis - Perform Magnetic Particle Inspection. P5710184 510/610 * Wing Attach Bolts - Perform Fluorescent Penetrant Inspection. P5710185 510/610 * Wing Attach Links - Perform Magnetic Particle Inspection. P5710186 510/610 * Wing Attach Fittings at Mid Spar and Rear Spar - Perform Magnetic Particle Inspection. P5750002 540BL, 540CL, 540JL, 540KL, 640BR, 640CR, 640JR, 640KR * Flap Front Spar Cutouts - Perform Eddy Current Inspection. P5750003 540/640 * Flap Nose Roller Ribs - Perform Eddy Current Inspection. P5750004 540/640 * Flap Actuator Support Ribs - Perform Eddy Current Inspection. N5750005 540/640 * Flap Main Track Hinge Fittings, Track, and Flap Box Sides - Perform visual inspection. Inspect main track hinge fittings on track and flap box sides. INTERVAL 4,640 Flight 5,000 Flight 5,000 Flight 5,000 Flight 2,500 Flight 5,000 Flight 2,500 Flight Page 31 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS INTERVAL P5750048 540/640 * Flap Tracks - Perform Magnetic Particle Inspection. Hours Repeat P5750049 E5750051 E5750052 P5750053 540BL, 540CL, 540JL, 540KL 540BL, 540CL, 540JL, 540KL 540BL, 540CL, 540JL, 540KL 540BL, 540CL, 540JL, 540KL * Flap Nose Roller Tracks - Perform Magnetic Particle Inspection with flaps removed. * Flap Main Track Rollers - Perform visual inspection with flaps removed. * Flap Nose Rollers - Perform visual inspection with flaps removed. * Flap Track Support Ribs - Perform Eddy Current Inspection. P5750068 540/640 * Flap Front Spar Rib Support Structure - Perform Eddy Current Inspection. P5760000 540/640 * Aileron Actuator Hinge Fitting - Perform Eddy Current Inspection. 600 Flight Hours Repeat. 7,200 Flight 600 Flight Hours Repeat. 5,000 Flight P5760001 540/640 * Aileron Skin - Perform Eddy Current Inspection. P5760002 540/640 * Aileron Balance Tab Hinge Fittings - Perform Eddy Current Inspection. 2,500 Flight Page 32 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS P5760003 540/640 * Aileron Trim and Balance Tab Front Spars - Perform Radiographic Inspection. INTERVAL 5,000 Flight A5760004 540/640 * Aileron Bolts - Perform Magnetic Particle Inspection. 2,500 Flight P5760005 540/640 * Aileron Hinge Lugs and Fittings - Perform Eddy Current Inspection. E5760006 540/640 * Aileron Basic Structure - Perform visual inspection. P5760014 540/640 * Aileron Hinge Support Structure - Perform Eddy Current Inspection. 700 LANDING GEAR AND RELATED SYSTEMS T3220007 720/730 * Main Landing Gear Axles - Perform Main Landing Gear Axle Beam Assembly (P/N 200-203-001) Boroscope Inspection. L3220020 720/730 * Main Landing Gear Trunnion Fittings on Mid and Rear Spar - Perform Eddy Current Inspection. T3220024 720/730 * Main Landing Gear Side-Stay Actuator Pins - Perform Magnetic Particle Inspection. L3220118 720/730 * Main Landing Gear Shock Strut Cylinder (P/N 200-0201-105, 200-0201-106) - Perform Ultrasonic Inspection of the Lower Service Port and Forging Parting Line. 48 Months. 10,000 Landings Initial, 5,000 Landings Repeat. 48 Months 3,300 Landing Initial, 600 Landings Repeat. Page 33 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS J3220120 720/730 * Main Landing Gear Trunnion Shear Pin Bushing - Perform Visual Inspection for Bushing Migration. (Effective on Aircraft 45-005 thru 45-208, 45-210 thru 45-222, 45-224, 45-225, 45-229, and 45-230 not modified by SB 45-57-7.) T3220135 720/730 * Main Landing Gear Side-Stay Actuator Pins - Perform Detailed Visual Inspection. (Refer to 5-10-00.) M3220136 720/730 * Main Landing Gear Shock Strut Cylinder (P/N 200-0201-101, 200-0201-102, 200-0201-103, 200-0201- 104, 200-0201-107, 200-0201-108) - Perform Ultrasonic Inspection of the Lower Service Port and Forging Parting Line. P3220146 720/730 * Main Landing Gear Trunnion Shock Strut Cylinder (P/ N 200-0201-109 and 200-0201-110) - Perform Ultrasonic Inspection of the Forging Parting Line. T3220147 720/730 * Main Landing Gear Trunnion Shear Pins - Perform visual Inspection for pin migration. (Effective on Aircraft 45-005 thru 45-425 not modified by SB 45-57-11.) L5311004 710 * Nose Landing Gear Trunnion Fittings - Perform visual inspection of the trunnion fittings and attachment bolts. L5311005 710 * Nose Landing Gear Trunnion Fittings and Support Structure - Perform Eddy Current Inspection of the trunnion support structure at the forward pressure bulkhead flange. A5323022 710AL, 710AR * Nose Landing Gear Aft Wheelbox Closing Structure (FS 150 to FS 162) - Perform Visual Inspection. Inspect the following: a. Panel b. Channel Stiffeners c. Support Angle d. Angle Stiffener e. Zee Stiffener. 800 DOORS, GENERAL INSPECTION, AND SERVICING TASKS INTERVAL 600 Landings. 48 Months 4,800 Landings Initial, 600 Landings Repeat. 4,800 Landings Initial, 600 Landings Repeat. 600 Landings. 10,000 Landings Initial, 10,000 Landings Repeat. 10,000 Landings Initial, 10,000 Landings Repeat. Page 34 04-10-01 Revision: Reissue 09/22/2017

Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS A5210009 820AR * Emergency Exit Door Retainers - Perform visual inspection. Inspect door stop fittings on emergency exit door frames in flange radii (FS 374 and 394). N5210010 810 * Lower Passenger Door Tension Bolts, Bolt Retainers, Tension Fittings, and Door Attachments - Perform visual inspection. N5210011 810 * Upper and Lower Passenger Door Latch Pins - Perform visual inspection. Inspect bolts and door end rib structure at lock pins. A5210012 810 * Lower Passenger Door Hinge - Perform visual inspection. Inspect piano hinge lugs and fasteners. E5210013 810 * Upper and Lower Passenger Door Latch Arms and Door Attachments - Perform visual inspection. A5210014 810 * Upper Passenger Door Tension Fittings - Perform visual inspection. Inspect the following: a. Tension studs at retaining flanges b. Radii around flange periphery. D5210015 820AR * Emergency Exit Door - Perform visual inspection. Pay particular attention to flanges and fastener holes of door stop fittings. F5210016 810AL * Upper Passenger Door Hinge - Perform visual inspection. Inspect upper surface of hinge fingers at base of lug. N5210017 810AL * Upper Passenger Door Tension Bolts, Bolt Retainers, Tension Fittings, and Door Attachments - Perform visual inspection. INTERVAL 9,600 Flight 3,408 Flight 9,600 Flight 3,850 Flight 7,068 Flight 8,000 Flight 9,600 Flight 3,408 Flight N5314000 820 * Emergency Exit Door Skin Cutout Corners and Doublers (FS 370 - FS 398) - Perform Eddy Current Inspection. 4,800 Flight 2,400 Flight Page 35 04-10-01 Revision: Reissue 09/22/2017

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Airworthiness Limitations Replacement Requirements 1. Time Compliance AIRWORTHINESS LIMITATIONS REPLACEMENT REQUIREMENTS A. Replacement Requirements (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 touchdown. B. Replacement Items IRN R2710041 ZONE/ ACCESS 200 FORWARD FUSELAGE 230AC, 230BC, 230CC, 250CC, 540AL, 640AR REPLACEMENT REQUIREMENTS * Aileron Spindle (P/N 4527102103-001) 10 Years. U5323167 220 * LH & RH Coupe Rails (P/N 4553002003V7000-001, 4553002003V7001-002). N2740023 N2740024 300 AFT FUSELAGE/EMPENNAGE 330AC, 330BC, 330CC, 330CL, 330BR 330AC, 330BC, 330CC, 330CL, 330BR * Horizontal Stabilizer Actuator ACME Screw (P/N 2A94568008). (Effective on aircraft equipped with 6627401000-007 Horizontal Stabilizer Actuators.) * Horizontal Stabilizer Actuator ACME Nut (P/N 2A94567005). (Effective on aircraft equipped with 6627401000-007 Horizontal Stabilizer Actuators.) INTERVAL 600 Hours/36 Months, whichever occurs first 600 Flight Hours. 600 Flight Hours. Page 1 04-11-00 Revision: Reissue 09/22/2017

Airworthiness Limitations Replacement Requirements IRN ZONE/ ACCESS REPLACEMENT REQUIREMENTS 400 POWERPLANTS, NACELLES, AND THRUST REVERSERS INTERVAL F2420000 410 ** Alternator - Perform Bearing Replacement. 1200 Hours. V7120074 410/420 * Aft Engine Mount Bolt (P/N 4571408525-001) NOTE: Do not Replace with same P/N bolt. Use P/N 4571408525-003. 500/600 LEFT AND RIGHT WING Next Engine Removal after July 2, 2013. W2750055 540/640 * Flap Actuator Joint (P/N 145673-1) - Replace. 24 Months. 700 LANDING GEAR AND RELATED ITEMS O3220009 710 * Nose Landing Gear Strut Assembly (P/N 2342100). 20,000 Landings. O3220010 710 * Nose Landing Gear Actuator Assembly (P/N 6632201000). O3220011 710 * Nose Landing Gear Actuator Upper Pin (P/N 4532302043). N3220012 720/730 * Main Landing Gear Strut Assembly (P/N 6632101000, 200-0200). T3220013 720/730 * Main Landing Gear Side Brace Actuator Assembly (P/N 200-0300-003, -004) excluding the End Cap (P/N 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 (P/N 200-0302), and MLG Actuator Housing (P/N 200-0304). Refer to IRN T3220105 for the replacement interval of the End Cap. 20,000 Landings 20,000 Landings. 10,000 Landings. 17,000 Landings. T3220014 720/730 * Main Landing Gear Actuator Upper Pin (P/N 200-0325). 96 Months. N3220023 720/730 * Main Landing Gear Trunnion Pins (P/N 200-0212 and 200-0213). 10,000 Landings. O3220028 710 * Nose Landing Gear Trunnion Pins (P/N 2342108). 20,000 Landings. O3220029 710 * Nose Landing Gear Trunnion Axle (P/N 2342110). 20,000 Landings. Page 2 04-11-00 Revision: Reissue 09/22/2017

Airworthiness Limitations Replacement Requirements IRN ZONE/ ACCESS REPLACEMENT REQUIREMENTS INTERVAL 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. T3220038 720/730 * Main Landing Gear Actuator Lower Pin (P/N 200-0217). 96 Months. N3220041 720/730 * Main Landing Gear Forward Trunnion Shear Pins (P/N 4532103015 and 4532103132). N3220042 720/730 * Main Landing Gear Aft Trunnion Upper Shear Pin (P/N 4532103025, 4532103133). N3220043 720/730 * Main Landing Gear Aft Trunnion Lower Shear Pin (P/N 4532103026, 4532103134). T3220046 720/730 * Main Landing Gear Side Brace Actuator Assembly (P/N 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. 1,800 Landings. 1,800 Landings. 1,800 Landings. 2,500 Landings. 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 (P/N 200-0303). 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 November 29, 2010. 2,387 Landings. N3220106 720/730 * Main Landing Gear Actuator Housing (P/N 200-0304). 17,000 Landings. N3220116 720/730 * Main Landing Gear Shock Strut Cylinder (P/N 200-0201- 109 and -110). N3220126 720/730 * Main Landing Gear Side-Stay Actuator Fitting (P/N 4532103041). 10,000 Landings. 20,000 Landings. Q3220128 720/730 * Main Landing Gear Shock Strut Cylinder (P/N 200-0201- 105, -106, -107, and -108). 6,600 Landings. Page 3 04-11-00 Revision: Reissue 09/22/2017

Airworthiness Limitations Replacement Requirements IRN ZONE/ ACCESS REPLACEMENT REQUIREMENTS Q3220137 720/730 * Main Landing Gear Shock Strut Cylinder (P/N 200-0201- 101, -102, -103, and -104 ). N3220139 720/730 * Main Landing Gear Forward Trunnion Shear Pin (P/N 4532103201). N3220140 720/730 * Main Landing Gear Aft Trunnion Upper Shear Pin (P/N 4532103202). N3220141 720/730 * Main Landing Gear Aft Trunnion Lower Shear Pin (P/N 4532103203). W3220149 720/730 * Main Landing Gear Side Brace Actuator Assembly (P/N 200-0300-005, -006). L3231024 720/730 * Main Landing Gear Inboard Door Actuator (P/N 7469-1) Cap Screws - Replace. (Effective on Aircraft 45-005 thru 45-276 modified per SB 45-32-19, Main Landing Gear Door Actuator Improvement/Saddle Installation and 45-277 and subsequent.) INTERVAL 10,000 Landings. 5,000 Landings 5,000 Landings. 5,000 Landings. 17,000 Landings. 2,400 Hours. Page 4 04-11-00 Revision: Reissue 09/22/2017

Time Limits and Maintenance Checks 1. Description A. This chapter contains the minimum maintenance requirements for continued airworthiness recommended by the aircraft manufacturer. All inspections and maintenance requirements defined herein are in accordance with FAR 91.409 (f)(3). All scheduled inspections, special inspection requirements, and unscheduled maintenance checks are described in the following sections: (1) Phase Inspections - Sections 5-11-01 thru 5-14-06 contain inspections which are required to maintain the aircraft in an airworthy condition and range from a period of 300 hours or 12 months to 2,400 hours or 96 months. (Refer to Phase Inspections, this section.) (2) 4800 Hour Inspection - Section 5-15-00 contains those scheduled inspections which are required to maintain the aircraft in an airworthy condition and are performed every 4800 hours. (3) 9600 Hour Inspection - Section 5-16-00 contains those scheduled inspections which are required to maintain the aircraft in an airworthy condition and are performed every 9600 hours. (4) Major Landing Gear Inspection - Section 5-17-00 is a list of inspection checks for Zone 700 Landing Gear and Related Systems which are performed every 10,000 landings. (5) Special Inspections - Section 5-19-00 is a list of inspection checks which do not correspond with the regularly scheduled inspections within the approved Learjet Manufacturer s Inspection Program or that have special requirements attached to the inspection item. (6) Replacement Schedule - Section 5-19-01 is a list of items that shall be replaced at the indicated intervals. Replacement requirements of the manufacturer and vendors are also included. (7) RVSM Inspections - Section 5-19-02 is a list of the inspections required to maintain reduced vertical separation minimums (RVSM) certification. (8) Unscheduled Maintenance Checks - Section 5-50-00 is a list of maintenance checks covering abnormal aircraft operation including hard or overweight landings, severe turbulence and/or maneuvers, engine change, high energy stop (landing and rejected takeoff), thrust reverser slam-stow, overspeed recovery with landing gear extended, lightning strike, high ground wind gust inspection, nacelle heat fail message, and elevator disconnect due to elevator jam. (9) Reference Data - Section 5-60-00 contains a listing of the Inspection Reference Numbers (IRN). The IRNs are listed in numerical order with the interval, phase, phase number, and section where the inspection is located. B. Chapter 4 items have been incorporated into Chapter 5 at the nearest lower inspection interval from the maximum interval from the maximum interval listed in Chapter 4 and are designated with one asterisk (*) or two asterisks (**), denoting an Airworthiness Limitation. (1) The following specifies the allowable inspection tolerances for components and system checks: (a) Items marked by one asterisk (*) in Chapter 5 indicate that the corresponding Chapter 4 inspection task cannot be changed, increased, or deleted without the approval of the certification airworthiness authority. The inspection tolerances indicated in this chapter are not applicable to these tasks. Page 1 05-10-00 Revision: Reissue 09/22/2017

Time Limits and Maintenance Checks (b) Items marked by two asterisks (**) in Chapter 5 indicate that the corresponding Chapter 4 inspection task can be adjusted to agree with the inspection tolerances indicated in this chapter, but the task cannot be changed or deleted without the prior approval of the certification 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. Scheduled Inspections A. The Learjet Inspection Program is based on 24 Phase Inspections, accomplished one at a time, in groups or collectively, as scheduled by the aircraft operator, and in accordance with Allowable Inspection Tolerances (refer to Allowable Inspection Tolerances, this section). Each Phase Inspection is contained within one of four hourly or calendar driven inspection intervals, the 300 Hour or 12 Month A-Phases, 600 Hour or 24 Month B-Phases, 1,200 Hour or 48 Month C-Phases, and 2,400 Hour or 96 Month D-Phases. Each of the primary inspection intervals (A, B, C, and D) contains six stand-alone Phase Inspections. The Learjet Inspection Program also contains other inspections and individual stand-alone inspection checks, which must be accomplished at the specified intervals. All periodic inspections, inspection checks, and maintenance requirements are designed to preserve aircraft reliability and ensure the continued airworthiness and safe operation of the aircraft. B. The following is a list of all scheduled inspections contained in the Learjet Inspection Program and the overall interval for each inspection. (1) Phases A1, A2, A3, A4, A5, and A6 - Each A-Phase Due Every 300 Hours or 12 Months. (2) Phases B1, B2, B3, B4, B5, and B6 - Each B-Phase Due Every 600 Hours or 24 Months. (3) Phases C1, C2, C3, C4, C5, and C6 - Each C-Phase Due Every 1,200 Hours or 48 Months. (4) Phases D1, D2, D3, D4, D5, and D6 - Each D-Phase Due Every 2,400 Hours or 96 Months. (5) 4,800 Hour Checks - Due every 4,800 Hours. (6) 9,600 Hour Checks - Due every 9,600 Hours. (7) Major Landing Gear Inspection - Due every 10,000 Landings. C. New inspection requirements become effective on the revision date of the change. All single and double asterisked items are calculated from the Certificate of Airworthiness date, last inspection date or replacement date, which includes all new and revised inspections. Unless otherwise noted, compliance of a new inspection requirement will be accomplished no later than the next scheduled interval following receipt of the revision. Unless otherwise noted, an inspection in progress at the time a new revision becomes effective may be completed, utilizing the inspection criteria in effect when the inspection was initiated. Page 2 05-10-00 Revision: Reissue 09/22/2017

Time Limits and Maintenance Checks D. A signoff in either the MECH or INSP block can constitute task completion on the work forms. A signoff in both blocks is optional and is left to the discretion of the inspector responsible for return to service. E. General Inspection Checks - NOTE: Ace Aviation Services, Corp s. Aircraft are on a Continuous Airworthy Maintenance Program and this paragraph does not apply. Reference GMM Volume 1. 3. Time Compliance NOTE: The following inspections must be performed at the following times, dates, landings, or cycles: A. 300 Hour A-Phases (1) At or before 300 total aircraft hours or 24 months from the original Certificate of Airworthiness date, whichever occurs first, perform each A-Phase inspection (Phase A1 thru A6), either individually, in groups, or collectively, as scheduled by the aircraft operator in accordance with Allowable Inspection Tolerances. (Refer to Allowable Inspection Tolerances, this section.) Perform each subsequent A-Phase inspection every 300 hours or 12months, whichever occurs first, from the completion date of the previous inspection. NOTE: Inspections may only be accomplished early to reschedule or adjust future inspection due times. B. 600 Hour B-Phases (1) At or before 600 total aircraft hours or 36 months from the original Certificate of Airworthiness date, whichever occurs first, perform each B-Phase inspection (Phase B1 thru B6), either individually, in groups, or collectively, as scheduled by the aircraft operator in accordance with Allowable Inspection Tolerances. (Refer to Allowable Inspection Tolerances, this section.) Perform each subsequent B-Phase inspection every 600 hours or 24months, whichever occurs first, from the completion date of the previous inspection. NOTE: Inspections may only be accomplished early to reschedule or adjust future inspection due times. C. 1,200 Hour C-Phases (1) At or before 1,200 total aircraft hours or 48 months from the original Certificate of Airworthiness date, whichever occurs first, perform each C-Phase inspection (Phase C1 thru C6), either individually, in groups, or collectively, as scheduled by the aircraft operator in accordance with Allowable Inspection Tolerances. (Refer to Allowable Inspection Tolerances, this section.) Perform each subsequent C-Phase inspection every 1,200 hours or 48 months, whichever occurs first, from the completion date of the previous inspection. NOTE: Inspections may only be accomplished early to reschedule or adjust future inspection due times. Page 3 05-10-00 Revision: Reissue 09/22/2017

Time Limits and Maintenance Checks D. 2,400 Hour D-Phases (1) At or before 2,400 total aircraft hours or 96 months from the original Certificate of Airworthiness date, whichever occurs first, perform each D-Phase inspection (Phase D1 thru D6), either individually, in groups, or collectively, as scheduled by the aircraft operator in accordance with Allowable Inspection Tolerances. (Refer to Allowable Inspection Tolerances, this section.) Perform each subsequent D-Phase inspection every 2,400 hours or 96 months, whichever occurs first, from the completion date of the previous inspection. NOTE: Inspections may only be accomplished early to reschedule or adjust future inspection due times. E. 4,800 Hour Inspection (1) At 4,800 total aircraft hours, perform a 4,800 Hour Inspection. From this point forward, perform a 4,800 Hour Inspection every 4,800 hours in accordance with Allowable Inspection Tolerances. (Refer to Phase Inspections and Allowable Inspection Tolerances, this section.) F. 9,600 Hour Inspection (1) At 9,600 total aircraft hours, perform a 9,600 Hour Inspection. From this point forward, perform a 9,600 Hour Inspection every 9,600 hours in accordance with Allowable Inspection Tolerances. (Refer to Phase Inspections and Allowable Inspection Tolerances, this section.) G. Major Landing Gear Inspection (1) At 10,000 total aircraft landings, perform a Major Landing Gear Inspection. From this point forward, perform a complete Major Landing Gear Inspection every 10,000 landings, in accordance with Allowable Inspection Tolerances. (Refer to Allowable Inspection Tolerances, this section.) 4. Allowable Inspection Tolerances A. The following specifies the Allowable Inspection Tolerances for Learjet scheduled inspections: (1) Inspections controlled by calendar time may be accomplished within a period beginning two weeks before, and ending no later than two weeks after the inspection due date. (See Figure 1.) (2) Inspections controlled by flight hours may be accomplished within a period beginning 25 flight hours before, and ending no later than 25 flight hours after the inspection due time. (See Figure 1 (3) Inspections controlled by landings or cycles may be accomplished within a period beginning 25 landings or cycles before, and ending no later than 25 landings or cycles after the inspection due time. (4) A signed and dated record must be prepared and maintained as each inspection task is completed. When the last task of an inspection has been completed, the inspection as a whole (e.g. Phase A1) is to be signed off in the appropriate Log Book/Maintenance Record at the time that inspection was completed. (5) After completion of an inspection, the next due time shall be at the scheduled time, date, or cycle as calculated from the DUE TIME of the last completed inspection, not from the point of completion. Page 4 05-10-00 Revision: Reissue 09/22/2017

Time Limits and Maintenance Checks (6) Any inspection accomplished early, before the beginning of its inspection window, must adjust the next scheduled due for time that inspection from the point of early completion. NOTE: Inspections may only be accomplished early to re-schedule or adjust future inspection due times. (7) In the event of early accomplishment of an inspection task, before the start time, date, or cycle of the inspection envelope, the next due-point for that task will be calculated from the point of the early accomplishment of that task. (8) Inspection tolerances are not cumulative. Any inspection exceeding its scheduled due time must calculate due time for the next inspection from the due time of the last inspection completed, not from the point of completion. B. Each inspection defined in this section stands on its own and does not specify other inspection intervals. At each inspection, a review should be made for any other inspection or maintenance task due in the near future. Page 5 05-10-00 Revision: Reissue 09/22/2017

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Time Limits and Maintenance Checks 5. Phase Inspections A. Each individual Phase Inspection is basically a zonal inspection of a specific aircraft area or related systems. Other factors considered when determining task placement within a Phase Inspection were convenience, access requirements, and maintenance equipment required. Each Phase Inspection and the following information should be carefully reviewed prior to proceeding with any Phase Inspection contained within this chapter. Several suggested methods of utilizing the Phase Inspections have been included in this section to aid operators in designing a program best suited to their own specific operational requirements. These are suggestions only. Provided no inspection tolerance is exceeded, there is no prescribed method of utilizing the Phase Inspections. (1) Sample Inspection Program #1 (See Figure 2.)- A, B, C, and D Phases performed together at their (a) This example is for operators wishing to remain on a standard 300 Hour, 600 Hour, 1,200 Hour, and 2,400 Hour inspection schedule. The Phase Inspections are utilized by performing all A-Phase inspections together at 300 hour or12 month intervals, all B-Phases at 600 hour or 24 month intervals, all C-Phases at 1,200 hour or 48 month intervals, and all D-Phases at 2,400 hour or 96 month intervals. This would be the most frequently used method for low utilization operators, operators utilizing outside maintenance facilities for their required inspections, and operators able to absorb longer downtimes for scheduled inspections. (2) Sample Inspection Program #2 (See Figure 3.)- A-Phases at 50 hour intervals, combined with C, and D Phases (a) This example performs single A-Phases at 50-hour intervals, combined with B, C, and D performed, as required, in accordance with allowable inspection tolerances. This method would be best suited to high utilization operators with complete in-house maintenance capabilities, and requiring minimum downtimes for scheduled inspections. (3) Sample Inspection Program #3 (See Figure 4.)- A-Phases at 100 hour intervals, with standard B, C and D intervals. (a) This example utilizes the 300-hour A-Phases two at a time, at 100 hour intervals, while performing all B-Phases together every 600 hours, C-Phases together every 1,200 hours and all D-Phases together every 2,400 hours. This method would be best suited for average utilization operators with some limited in-house maintenance capabilities, but still requiring an outside maintenance facility to accomplish more detailed inspections. (4) Sample Inspection #4 (See Figure 5.)- A-Phases at 150 hour intervals, combined with B, C, and D Phases. (a) This example performs multiple A-Phases at 150 hour intervals, combined with single or combined B, C, and D Phases performed, as required, in accordance with allowable inspection tolerances. This method would be best suited for average utilization operators with complete in-house maintenance capabilities, and able to absorb longer downtimes for scheduled inspections. (5) Inspection Program Planning and Documentation (See Figure 6.) (a) After careful consideration by the operator, a form recording the sequence the operator will utilize with each Phase Inspection should be prepared (a blank form is provided, see Figure 6). A copy of the completed Phase Inspection form should be placed in the aircraft s airframe maintenance log for future reference. Page 7 05-10-00 Revision: Reissue 09/22/2017

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