Volume 3. Learjet 45. Maintenance and Inspection Program

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

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3 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 and c. Chapter 2, ; i. IRN revised to revision Y, clarified effectivity to P/N of valve installed. d. Chapter 2, ; i. Revised IRN s Q , Q , Q , and Q from two asterisks to one. e. Chapter 2, ; i. Reformatted Zone/Access column all pages. ii. Revised IRN to revision AA. Revised interval to manufacturer s instructions. Defined Manufacturer used and interval. iii. Incorporated Temporary Revision by adding IRN AA Added inspection for the Horizontal Stabilizer Primary and Secondary Bolts and Bushings iv. Revised IRN to revision AA. Removed note regarding original C of A and compliance date. v. Revised IRN 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, ; i. Reformatted Zone / Access Column. ii. Incorporated Temporary Revision by adding IRN Z , Replace Door Handle. iii. Revised IRN to revision AA, added clarification to note. iv. Added IRN AA Replace Spoiler Swivel. g. Chapter 2, ;

4 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

5 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 /16/2018 Revision /06/2018

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9 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: : Airworthiness Limitations LR : Certification Maintenance Requirements - Component and System Checks - LR : Certification Maintenance Requirements - Structure Checks - LR : Airworthiness Limitations - Replacement Requirements LR : Time Limits and Maintenance Checks LR : Inspections Maintenance Practices LR : Phase A1 Inspection LR : Phase A2 Inspection LR : Phase A3 Inspection LR : Phase A4 Inspection LR 45

10 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: : Phase A5 Inspection LR : Phase A6 Inspection LR : Phase B1 Inspection LR : Phase B2 Inspection LR : Phase B3 Inspection LR : Phase B4 Inspection LR : Phase B5 Inspection LR : Phase B6 Inspection LR : Phase C1 Inspection LR : Phase C2 Inspection LR : Phase C3 Inspection LR : Phase C4 Inspection LR : Phase C5 Inspection LR : Phase C6 Inspection LR : Phase D1 Inspection LR : Phase D2 Inspection LR : Phase D3 Inspection LR : Phase D4 Inspection LR : Phase D5 Inspection LR : Phase D6 Inspection LR 45

11 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: : 4800 Hour Checks LR : 9600 Hour Checks LR : Major Landing Gear Inspections LR : Special Inspections LR : RVSM Inspections LR 45 05/10-30: RVSM Inspections LR 60/60XR : Reference Data LR 45 Chapter 3: Engine Manufacturers Times Limitations & Maintenance Checks SECTION: Airworthiness Limitations: - TFE : Time Limits of Engine Critical Components TFE : Part History Reports TFE : Scheduled Maintenance Checks TFE : Overhaul TFE : Unscheduled Maintenance Checks TFE : Engine - Inspection / Check TFE731-20

12 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 Day Check

13 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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15 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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17 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; , 47, , , , , 91 Appendix G, (b)(1), 0.0 MANUFACTURERS REVISIONS INCORPORATED IN THIS INSPECTION PROGRAM A. Learjet 45 Maintenance Manual MM-104 Revision 70 dated Apr 20/ Temporary Revision dated Apr 30/ Temporary Revision dated Apr 30/18. B. Honeywell TFE Light Maintenance Manual P/N Revision 12 dated May 31, 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 D 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.

18 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 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 as noted in A. 5. Currently there are no chapter Maintenance Requirements by Aircraft Effectivity and 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 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 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.

19 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 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 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 TFE Inspection Program, with noted exceptions, from the manufacturer as described in Honeywell MM Part No 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 TFE MM as revised 2. Pages 801 thru 809 of the Honeywell TFE MM ENGINE - INSPECTION / CHECK are included in this MIP as Engine Inspection / Check Pages 1 thru 8. Ace Aviation Services, Corp. has elected to set the times for the Routine Periodic Inspections found in 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 TO 1300 HOUR INSPECTION: To be performed at 1250 hours not to exceed 1300 hours. e TO 1650 HOUR INSPECTION: To be performed at 1600 hours not to exceed 1650 hours. 3. Refer to TFE LMM MM C. for inspection requirements of Major Periodic Inspection (MPI). a. 2. C. (2) Specifies the allowable exceedance of 100 hours of operation for MPI

20 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 Basis, Implementation and Revision for Maintenance Inspection Program (Continued) 4. Refer to TFE LMM MM 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 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 , Statement of Compliance with Airworthiness Standards, Damage Tolerance Assessments are also incorporated into our Maintenance Inspection Program.

21 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 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 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. F 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 B, (3). K. This Maintenance Inspection Program is an FAA Approved document as indicated on the List of Effective pages.

22 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 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.

23 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 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.

24 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: 8 of How to read Time Limitation List A. Aircraft and Powerplant Manufactures Sections Source Source Document Part No. Section(s) [A] Learjet [B] Maintenance Manual [C] MM-104 [D] Chapter 4 & 5 Comments: [E] [A] Source: Time Limitation Document source (Type Certificate Holder, Supplemental Type Certificate Holder, Production Authority Holder, Regulation, etc.) [B] Source Document: Name of type source document (Maintenance Manual, Time Limitation and Maintenance Checks, Maintenance Planning Document, Maintenance Manual Supplement, etc.) [C] Part No.: Part number of the source document [D] Section(s): Applicable sections of the source document where task and interval derived from [E] Comments: Comments and notes necessary for clarity B. Other Sources than Aircraft and Powerplant Manufactures Comments: Source ATA Task Interval [A] [B] [C] [D] [E] [A] Source: [B] ATA: [C] Task.: [D] Interval: Time Limitation Document source (Type Certificate Holder, Supplemental Type Certificate Holder, Production Authority Holder, Regulation, etc.). Modified Aircraft Transportation Association Code for task listed. Reference GMM section for ATA Codes adopted by Ace Aviation Services. Task description sufficiently detailed with scope of task. Task interval and repeat interval if different than threshold interval. [E] Comments: Comments and notes necessary for clarity

25 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: 9 of 9 b) Interfaces Operations Specifications D089 D085 Time Limitations Aircraft Listing General Maintenance Manual Sub-Section 4.16: Sub-Section : Sub-Section 4.29: Sub-Section 5.3: Section 7.0: Section 9.0: Section 10.0: Airworthiness Directives Service Bulletins and Change Kits RVSM Extension of Maintenance Inspection Program Maintenance Record Keeping Training CASS

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27 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 and 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 ( ) lists aircraft components and systems which require monitoring through scheduled maintenance. (2) Certification Maintenance Requirements - Structure Checks ( ) lists aircraft structural items which require monitoring through scheduled maintenance. (3) Airworthiness Limitations - Replacement Requirements ( ) describes and lists life limited aircraft components or structures which are to be replaced at a specific time. (4) Maintenance Requirements by Aircraft Effectivity ( ) 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 and 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 are not applicable to these tasks. (b) Items marked by two asterisks (**) in Sections and indicates that the inspection task can be adjusted to agree with the inspection tolerances indicated in Chapter 5, Section , 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 Revision: Reissue 09/22/2017

28 Airworthiness Limitations (2) The following specifies the allowable tolerances for replacement items: (a) Replacement items that are designated with one asterisk (*) in Section 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 are not applicable to those items with one asterisk (*). (b) Replacement items that are designated with two asterisks (**) in Section are part of the manufacturer s recommended maintenance program and can be adjusted according to the tolerances listed in Chapter 5, Section Vendor recommendations, service experience, and engineering assessment are all factors considered in these recommendations. Page Revision: Reissue 09/22/2017

29 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 Q ** Oxygen Cylinder Low Pressure Relief Valve - Perform Functional Test. N ** Oxygen Cylinder and Remote Oxygen Fill Valves - Perform Periodic Check. (Effective on Aircraft thru modified per SB and Aircraft and Subsequent.) 200 FORWARD FUSELAGE INTERVAL 5,195 Hours. 1,500 Hours. O ** Pressurization Control System - Perform Functional Test. 1,200 Hours A ** Autopilot System - Perform Autopilot Disconnect Tone Test. A A A B 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. R ** 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. W ** Generator Fail Indication - Perform Operational Check. 600 Hours. H ** Auxiliary Power Supplies - Perform Functional Test. 600 Hours. B ** Electrical System Control - Perform Operational Check. 1,200 Hours. Page Revision: Reissue 09/22/2017

30 Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS H ** EMER BATT LOW and GEN AMPS HIGH Indication - Perform Operational Check. J ** Engine Fire Extinguishing System Fire Switch - Perform Functional Test. INTERVAL 600 Hours. 5,000 Hours T ** Firewall Shutoff Valves - Perform Operational Check. 2,500 Hours. A ** Aileron Trim Tab Control System - Perform Operational Check. 600 Hours. V ** Roll Disconnect Switches - Perform Operational Check. 600 Hours. A ** Rudder Trim System - Perform Operational Check. 600 Hours. D ** Horizontal Stabilizer Actuator Secondary Trim - Perform Functional Test. D ** Horizontal Stabilizer Actuator Primary Trim - Perform Functional Test. F ** Fuel Quantity Signal Conditioner - Perform Functional Test to Verify Weight-on-Wheels (WOW) inputs. (Effective on Aircraft thru modified per SB and Aircraft and Subsequent.) 600 Hours. 600 Hours. 1,200 Hours. H ** Wing/Stab Anti-Ice Switch - Perform Operational Check. 600 Hours. A ** Pitot/Static Heat System - Perform Operational Check. 3,000 Hours. T ** Windshield Anti-ice - Perform Functional Test of the Windshield Anti-ice System. B A B B A A A B A C 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 Revision: 1 04/16/2018

31 Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS K ** Oxygen System Low Pressure Supply Hoses - Perform Operational Check. Ensure that hoses are free of obstructions. (Effective on Aircraft , , , and ) INTERVAL 6,000 Flight Hours. W ** Oxygen System - Perform Operational Check. 600 Hours. O ,230 ** Cabin Low Pressure Oxygen Distribution Flex Hoses - Perform Functional Test. S ** Oxygen System Altitude Compensating Regulator - Perform Functional Test. (Effective on Aircraft thru modified by SB extended duration oxygen system installed and and Subsequent.) Q ** Oxygen Cylinder Lower Pressure Relief Valve - Perform functional test. (Effective on aircraft equipped with increased capacity oxygen system.) N ** 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. A ** Bleed Air System - Perform Functional Test. 600 Hours. A ** Pylon Overheat Thermostat and Electrical System - Perform Functional Test. 600 Hours. H ** APU Generator - Perform overvoltage protection check. 1,200 Hours. W ** Windshield - Perform Rain Removal Coating Effectiveness Test. 300 AFT FUSELAGE/EMPENNAGE L ** Auxiliary Heat System - Perform Functional Test. (Effective on Aircraft and subsequent equipped with Keith Products vapor air cycle air conditioning system using refrigerant R-134.) L ** Auxiliary Heat System - Perform Auxiliary Heater Electrical and Temperature Switch Test. (Effective on Aircraft and subsequent equipped with Keith Products vapor air cycle air conditioning system using refrigerant R-134.) A /320 ** Elevator Disconnect System - Perform Operational Check. 12 Months. 600 Hours. 1,200 Hours. 600 Hours. Page Revision: Reissue 09/22/2017

32 Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS W ** Pitch Trim - Perform Operational Check of Elevator Override Actuator. H * 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. A /440 ** Nacelle Anti-ice System- Perform Functional Test. 1,200 Hours. F Deleted. D ** Thrust Reverser System Throttle Retard Actuator - Perform Operational Check. 500/600 LEFT/RIGHT WING A /640 ** Spoiler Actuator Check Valve - Perform Operational Check. A /640 ** Spoiler System - Perform Spoiler Authority with Flaps Check. 700 LANDING GEAR AND RELATED SYSTEMS Q /730 ** Power Distribution System - Perform Squat Switch Check. O A /720/ 730 Deleted. ** Landing Gear - Perform Emergency Gear Extension Functional Test. V /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. A /730 ** Brake Hydraulic Fuses - Perform Functional Test. 1,200 Hours. Page Revision: Reissue 09/22/2017

33 Certification Maintenance Requirements Component and System Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS COMPONENT AND SYSTEM CHECKS INTERVAL A /730 ** Brake Shuttle Module - Perform Functional Test. 1,200 Hours. A /730 ** Brake Shuttle Valves - Perform Functional Test. 2,400 Hours. V /730 ** Emergency/Parking Brake Control System Perform Functional Test. 600 Hours. A /730 ** Brake Pressure Transducers - Perform Functional Test. 4,800 Hours. B Replaced by IRN Q Page Revision: Reissue 09/22/2017

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35 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 K * Aileron Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. K * Elevator Control System Primary Cables - Remove from aircraft and perform detailed visual inspection K * Rudder Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. E E CL, 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 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 Revision: Reissue 09/22/2017

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

37 Certification Maintenance Requirements Structure Checks IRN M A 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 E * 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. N * Upper and Lower Passenger/Crew Door Skin Cutout Corners (FS FS 256) - Perform Eddy Current Inspection. Inspect skin at corners of passenger/crew door cutout. P * Fuselage Frame at F.S Perform Eddy Current Inspection. T * Fuselage to Wing Attach Fittings - Perform Eddy Current Inspection. P * Machined Spar Frames Systems Cutouts (FS 398, FS 412, FS 432, FS 466) - Perform Eddy Current Inspection. H * Exterior Cabin Window Coamings (Unpainted) - Perform Eddy Current Inspection. P * 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 Revision: Reissue 09/22/201

38 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS M * Upper and Lower Coupe Rail and Center Post/ Windshield Retainer Attachment - Perform Eddy Current inspection. P * Windshield Coupe Rail Tie Rod Bracket - Perform Eddy Current Inspection. P * Windshield Centerpost to Upper Coupe Rail Joint Attachment - Perform Eddy Current Inspection. D * Machined Fuselage Frame at FS 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 only.) P /230 * Pressure Cabin Fuselage Crown Skin - Perform Eddy Current Inspection. Q /230 * Fuselage (Pressure Cabin) - Perform Eddy Current Inspection. Inspect pressure cabin skin (longitudinal skin cracking). P * Fuselage Skin at Upper and Lower Coupe Rail Runout Joints - Perform Eddy Current Inspection. E * 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 Revision: Reissue 09/22/2017

39 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS Q /230 * Longitudinal Joints inside Pressure Cabin (FS 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. E * 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. E * Tie-Rod Assembly (FS 162) (Aluminum ends) - Perform visual inspection. Inspect tie-rod ends, tie-rod tubes, and tie-rod bolts. E * Tie-Rod Assembly (FS 162) (Titanium ends) - Perform visual inspection. Inspect tie-rod ends, tie-rod tubes, and tie-rod bolts. F * Tie-Rod Fork Ends (Aluminum) - Perform Fluorescent Penetrant Inspection. (Effective on Aircraft thru ) P /230 * Pressure Cabin Skin at Fuselage Station Perform Eddy Current Inspection. P /230 * Fuselage Skin at F.S Perform Eddy Current Inspection. Q * 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 Revision: Reissue 09/22/2017

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

41 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS T * 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 ) 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, V * LH and RH Lower Coupe Rail Radius/Windscreen Retainer Attach (P/N s thru ) - Perform Eddy Current Inspection (Effective on Aircraft that have complied with SB , Windows - Windshield Coupe Rail Inspection. ) Z * Skin Cut-Out for Iridium Antennas FS to FS Perform Eddy Current Inspection. (Effective on Aircraft , , , , , , , and only) E * Bottom Keelbeam End Pads (FS FS 486) - Perform visual inspection. Inspect end pads around bolt holes and in radii at FS 433. N /230 * Windshields - Perform ultrasonic inspection of the structural plies. (Effective on Aircraft with Sierracin windshields installed.) L /230 * Cabin Windows (including the emergency exit window) - Perform detailed visual inspection. N /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 Revision: 1 04/16/2018

42 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS K * Elevator Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. K * Rudder Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. T AC, 330AR, 330BC, 330CC, 330CL, 330XL, 330WR, 330YL, 330XR * Horizontal Stabilizer Actuator ( ) - 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 for life-limited components (IRN # s N and N ). 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, N AC, 330AR, 330BC, 330CC, 330CL, 330XL, 330WR, 330YL, 330XR * Horizontal Stabilizer Actuator ( ) - 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 for life limited components (IRN # s N and N ). 2,400 Flight Hours Initial, 2,400 Flight Page Revision: Reissue 09/22/2017

43 Certification Maintenance Requirements Structure Checks IRN P ZONE/ ACCESS 330AR, 330BC, 330CL, 330XL, 330WR, 330YL, 330XR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Horizontal Stabilizer Actuator ( ) - Perform Inspection. (Refer to ) 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. P AR, 330BC, 330CL, 330XL, 330WR, 330YL, 330XR * Horizontal Stabilizer Actuator ( ) - 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 Q QR, 310HL Interval is calculated from time since new or from the Time Since Structural Inspection (TSSI) hours. ** Anti-Ice Manifold - Perform Boroscope Inspection Hours. A * 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 P AC, 310BC, 310AL, 310BL, 310AR, 310BR * Fuselage Skin Cut-outs Above Fuel Cell - Perform Eddy Current Inspection. E * Stringer 1 RH between FS 533 and FS Perform visual inspection. Inspect stringer 1 flange and skin along stringer 1 between FS 533 and FS ,000 Flight Hours Repeat. Page Revision: Reissue 09/22/2017

44 Certification Maintenance Requirements Structure Checks IRN F 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 F F DL, 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. F * Vertical Stabilizer Front Spar Root Bulkhead Attachment (FS 630) - Perform visual inspection. Inspect front spar root bulkhead attachment at fastener holes. F * Vertical Stabilizer Mid Spar Root Bulkhead Attachment (FS 657) - Perform visual inspection. Inspect mid spar root bulkhead attachment at fastener holes. F * Vertical Stabilizer Rear Spar Root Bulkhead Attachment (FS 682) - Perform visual inspection. Inspect rear spar root bulkhead attachment at fastener holes. H E HL, 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 Revision: Reissue 09/22/2017

45 Certification Maintenance Requirements Structure Checks IRN P 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 G AC, 330BC, 330CL, 330XL, 330WR, 330AR. 330XR, 330YL * Horizontal Stabilizer Actuator Attachment Fitting - Perform Eddy Current Inspection. 5,000 Flight 5,000 Flight T A 330 * Rudder Top Hinge Fitting - Perform visual inspection. Inspect lug (FS 721). T B 330 * Rudder Mid Hinge Fitting - Perform visual inspection. Inspect lug (FS 721). T C 330 * Rudder Lower Hinge Fitting - Perform visual inspection. Inspect lug (FS 709). N CC * Horizontal Stabilizer Rear Spar Cap - Perform Eddy Current Inspection. Inspect rear spar cap and web at center splice. P CL, 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 Revision: Reissue 09/22/2017

46 Certification Maintenance Requirements Structure Checks IRN Q P 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. P * Horizontal Stabilizer Mid Spar Upper Cap B.L. 0.0 to B.L Perform X-ray Inspection. M * 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. P * Horizontal Stabilizer Mid Spar and Rear Spar Upper Flange at Root Rib - Perform Radiographic Inspection. A * 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. N WR, 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 Revision: Reissue 09/22/2017

47 Certification Maintenance Requirements Structure Checks IRN N P 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. P * Vertical Stabilizer Pivot Fitting Lugs - Perform Eddy Current Inspection. P * Elevator Hinges on Horizontal Stabilizer - Perform Eddy Current Inspection. P * Horizontal Mid Spar Upper Cap - Perform Eddy Current Inspection. A * 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 Revision: Reissue 09/22/2017

48 Certification Maintenance Requirements Structure Checks IRN G P H 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. N * Horizontal Stabilizer Mid Spar Flange Root Rib Attachment - Perform Eddy Current Inspection. P * Horizontal Stabilizer Front Spar - Perform Radiographic Inspection. P E FL, 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 Revision: Reissue 09/22/2017

49 Certification Maintenance Requirements Structure Checks IRN E E 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. N * Horizontal Stabilizer Rear Spar Flange Root Rib Attachment - Perform Eddy Current Inspection. W P ER, 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. P * Elevator Hinge Attach Bolt - Perform Magnetic Particle Inspection. P ML, 330PL, 330LR, 330NR * Elevator Hinge Pin - Perform Liquid Penetrant Inspection. (Effective on Aircraft thru ) E * 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 Revision: Reissue 09/22/2017

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

51 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS 400 POWERPLANTS, NACELLES, AND THRUST REVERSERS Z /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 ) (Effective on Aircraft thru , , and thru not modified by SB P / CL, 340CR * Drag Strut Attachment Fittings - Perform Eddy Current Inspection. M /460 * Forward Engine Beam, Spar Cap and Web - Perform Eddy Current Inspection. P AR, 340BR, 340CR, 340DR, 340ER, 340FR, 340AL, 340BL, 340CL, 340DL, 340EL, 340FL * Forward Engine Beam End Fitting - Perform Eddy Current Inspection. P /460 * Forward Engine Beam to Frame Attach Bolts - Perform Liquid Penetrant Inspection. M * 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 Revision: 1 04/16/2018

52 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS F /460 * Aft Engine Beam Attachment to Frames - Perform visual inspection. Inspect aft engine beam attachment to frames. P /460 * Aft Engine Beam to Frame Attachment Bolt - Perform Liquid Penetrant Inspection. P /460 * Engine Aft Isolator Mount Fittings - Perform Liquid Penetrant Inspection. A /460 * Aft Engine Mount to End Fitting Attach Bolt - Perform Magnetic Particle Inspection. P /460 * Engine to Aft Engine Mount Attach Bolts - Perform Liquid Penetrant Inspection. P /460 * Fuselage Frames at FS and 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 P /460 * Forward Engine Beam and Frames at Attach Holes - Perform Eddy Current Inspection. 5,000 Flight A /460 * Engine Drag Strut - Perform Eddy Current Inspection. 5,000 Flight P /460 * Forward Engine Mount - Perform Eddy Current Inspection. 500/600 LEFT/RIGHT WING 4,800 Flight Page Revision: Reissue 09/22/2017

53 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS K /640 * Aileron Control System Primary Cables - Remove from aircraft and perform detailed visual inspection. W /640 * Flap Actuator Joint (P/N ) - Perform Detailed Visual Inspection. Apply Corrosion Preventive Compound (CPC) to joint. S /640 * Flap Actuator Ballnut Sleeve (Flap Actuator Assembly Learjet P/N , , , , and , Flap Actuator Assembly Microtecnica P/N C , C , C , C , C and C ) - 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 , Flight Controls - Modification of the Flap Actuator Ballscrew Assembly Sleeves, inspect modification half sleeve surrounding original sleeve. On aircraft not modified per SB , Flight Controls - Modification of the Flap Actuator Ballscrew Assembly Sleeves, inspect original sleeve. P DL, 250CL, 250ER, 250DR, 510BL, 610BR * Wing Drag Link Attach Fitting - Perform Magnetic Particle Inspection. 4,640 Flight N GL, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 9,600 Flight 3,580 Flight Page Revision: Reissue 09/22/2017

54 Certification Maintenance Requirements Structure Checks IRN N 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) E /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. N AC, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) P /610 * Wing to Fuselage Attach Fittings and Links - Perform Eddy Current Inspection. N N EL, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Mid Spar Lower Cap Joint at WS Perform X-ray Inspection. Inspect mid spar center/outer joint. (Effective on Aircraft not modified by SB , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , 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 Revision: Reissue 09/22/2017

55 Certification Maintenance Requirements Structure Checks IRN N N 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 , 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) P N DZ, 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 , 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 Revision: Reissue 09/22/2017

56 Certification Maintenance Requirements Structure Checks IRN N 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) P /610 * Wing Lower Skin at Mid Spar Span Wise Joint - Perform Eddy Current Inspection. E /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. E /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. N N N AL, 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 , 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 , 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 2,500 Flight 2,500 Flight 2,500 Flight Hours Repeat. Page Revision: Reissue 09/22/2017

57 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS P /610 * Wing Rear Spar Side Stay Fitting Support Structure - Perform Eddy Current Inspection. P /610 * Wing Front Spar Lower Cap From WS 33.0 to WS Perform Radiographic Inspection. N AL, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) P /610 * Wing Mid Spar Vertical Web - Perform Eddy Current Inspection. P /610 * Wing Rear Spar Vertical Web - Perform Eddy Current Inspection. N AL 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 , 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 Revision: 1 04/16/2018

58 Certification Maintenance Requirements Structure Checks IRN P ZONE/ ACCESS 520AL, 620AR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Rib Upper Aft Flange Fillet Radius at WS Perform Ultrasonic Inspection. P /610 * Wing Access Hole in Closing Rib between Mid and Rear Spar - Perform Eddy Current Inspection. P CL, 650CR * Wing Box Joint to Winglet - Perform Eddy Current Inspection. P /620 * Wing Lower Skin at Drain Hole - Perform Eddy Current Inspection. N BL 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) P /650 * Flap Box Basic Structure - Perform Eddy Current Inspection. N HL 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 , 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 Revision: Reissue 09/22/2017

59 Certification Maintenance Requirements Structure Checks IRN N 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /620 * Wing Box Mid Spar Lower Cap - Perform Eddy Current Inspection at trunnion fitting. (Effective on Aircraft not modified by SB , Increase Maximum Zero Fuel Weight (16,500 pounds). ) L /620 * Aileron Drive Support - Perform Ultrasonic Inspection. 4,800 Flight Hours N N N U N BL, 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 , 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 , 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 , 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 , 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 , 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 Revision: Reissue 09/22/2017

60 Certification Maintenance Requirements Structure Checks IRN N N N 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 , 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) * Wing Box Mid Spar Lower Cap Joint at WS Perform X- ray Inspection. Inspect mid spar center/outer joint. (Effective on aircraft modified by SB , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N U AZ, 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 , 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , 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 Revision: 1 04/16/2018

61 Certification Maintenance Requirements Structure Checks IRN Q 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 7,400 Flight 5,000 Flight N AL 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 6,800 Flight N BC, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 1,800 Flight N AL, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 7,700 Flight 2,200 Flight N AL, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 6,800 Flight 3,300 Flight Page Revision: Reissue 09/22/2017

62 Certification Maintenance Requirements Structure Checks IRN N 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) INTERVAL 3,900 Flight Q BL 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 8,000 Flight Hours Initial, 2,500 Flight N AL, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 7,000 Flight 1,700 Flight N AL, 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 1,700 Flight N 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) 9,300 Flight Hours Initial, 3,400 Flight Page Revision: Reissue 09/22/2017

63 Certification Maintenance Requirements Structure Checks IRN Q Q 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 , 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /620 * Wing Box Mid Spar Lower Cap - Perform Eddy Current Inspection at trunnion fitting. (Effective on aircraft modified by SB , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N N N BL, 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 , 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 , 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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /620 * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection at trunnion fitting. (Effective on aircraft not modified by SB , 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 Revision: Reissue 09/22/2017

64 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS N /620 * Wing Box Mid Spar Lower Cap - Perform Ultrasonic Inspection at trunnion fitting. (Effective on aircraft modified by SB , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N /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 , Increase Maximum Zero Fuel Weight (16,500 pounds). ) N N P P AL, 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 , 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 , 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 Revision: Reissue 09/22/2017

65 Certification Maintenance Requirements Structure Checks IRN P ZONE/ ACCESS 250DL, 250CL, 250ER, 250DR, 510BL, 610BR MAINTENANCE REQUIREMENTS STRUCTURE CHECKS * Wing Drag Link Attach Clevis - Perform Magnetic Particle Inspection. P /610 * Wing Attach Bolts - Perform Fluorescent Penetrant Inspection. P /610 * Wing Attach Links - Perform Magnetic Particle Inspection. P /610 * Wing Attach Fittings at Mid Spar and Rear Spar - Perform Magnetic Particle Inspection. P BL, 540CL, 540JL, 540KL, 640BR, 640CR, 640JR, 640KR * Flap Front Spar Cutouts - Perform Eddy Current Inspection. P /640 * Flap Nose Roller Ribs - Perform Eddy Current Inspection. P /640 * Flap Actuator Support Ribs - Perform Eddy Current Inspection. N /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 Revision: Reissue 09/22/2017

66 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS INTERVAL P /640 * Flap Tracks - Perform Magnetic Particle Inspection. Hours Repeat P E E P BL, 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. P /640 * Flap Front Spar Rib Support Structure - Perform Eddy Current Inspection. P /640 * Aileron Actuator Hinge Fitting - Perform Eddy Current Inspection. 600 Flight Hours Repeat. 7,200 Flight 600 Flight Hours Repeat. 5,000 Flight P /640 * Aileron Skin - Perform Eddy Current Inspection. P /640 * Aileron Balance Tab Hinge Fittings - Perform Eddy Current Inspection. 2,500 Flight Page Revision: Reissue 09/22/2017

67 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS P /640 * Aileron Trim and Balance Tab Front Spars - Perform Radiographic Inspection. INTERVAL 5,000 Flight A /640 * Aileron Bolts - Perform Magnetic Particle Inspection. 2,500 Flight P /640 * Aileron Hinge Lugs and Fittings - Perform Eddy Current Inspection. E /640 * Aileron Basic Structure - Perform visual inspection. P /640 * Aileron Hinge Support Structure - Perform Eddy Current Inspection. 700 LANDING GEAR AND RELATED SYSTEMS T /730 * Main Landing Gear Axles - Perform Main Landing Gear Axle Beam Assembly (P/N ) Boroscope Inspection. L /730 * Main Landing Gear Trunnion Fittings on Mid and Rear Spar - Perform Eddy Current Inspection. T /730 * Main Landing Gear Side-Stay Actuator Pins - Perform Magnetic Particle Inspection. L /730 * Main Landing Gear Shock Strut Cylinder (P/N , ) - 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 Revision: Reissue 09/22/2017

68 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS J /730 * Main Landing Gear Trunnion Shear Pin Bushing - Perform Visual Inspection for Bushing Migration. (Effective on Aircraft thru , thru , , , , and not modified by SB ) T /730 * Main Landing Gear Side-Stay Actuator Pins - Perform Detailed Visual Inspection. (Refer to ) M /730 * Main Landing Gear Shock Strut Cylinder (P/N , , , , , ) - Perform Ultrasonic Inspection of the Lower Service Port and Forging Parting Line. P /730 * Main Landing Gear Trunnion Shock Strut Cylinder (P/ N and ) - Perform Ultrasonic Inspection of the Forging Parting Line. T /730 * Main Landing Gear Trunnion Shear Pins - Perform visual Inspection for pin migration. (Effective on Aircraft thru not modified by SB ) L * Nose Landing Gear Trunnion Fittings - Perform visual inspection of the trunnion fittings and attachment bolts. L * Nose Landing Gear Trunnion Fittings and Support Structure - Perform Eddy Current Inspection of the trunnion support structure at the forward pressure bulkhead flange. A AL, 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 Revision: Reissue 09/22/2017

69 Certification Maintenance Requirements Structure Checks IRN ZONE/ ACCESS MAINTENANCE REQUIREMENTS STRUCTURE CHECKS A AR * Emergency Exit Door Retainers - Perform visual inspection. Inspect door stop fittings on emergency exit door frames in flange radii (FS 374 and 394). N * Lower Passenger Door Tension Bolts, Bolt Retainers, Tension Fittings, and Door Attachments - Perform visual inspection. N * Upper and Lower Passenger Door Latch Pins - Perform visual inspection. Inspect bolts and door end rib structure at lock pins. A * Lower Passenger Door Hinge - Perform visual inspection. Inspect piano hinge lugs and fasteners. E * Upper and Lower Passenger Door Latch Arms and Door Attachments - Perform visual inspection. A * Upper Passenger Door Tension Fittings - Perform visual inspection. Inspect the following: a. Tension studs at retaining flanges b. Radii around flange periphery. D AR * Emergency Exit Door - Perform visual inspection. Pay particular attention to flanges and fastener holes of door stop fittings. F AL * Upper Passenger Door Hinge - Perform visual inspection. Inspect upper surface of hinge fingers at base of lug. N AL * 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 N * Emergency Exit Door Skin Cutout Corners and Doublers (FS FS 398) - Perform Eddy Current Inspection. 4,800 Flight 2,400 Flight Page Revision: Reissue 09/22/2017

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71 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 R ZONE/ ACCESS 200 FORWARD FUSELAGE 230AC, 230BC, 230CC, 250CC, 540AL, 640AR REPLACEMENT REQUIREMENTS * Aileron Spindle (P/N ) 10 Years. U * LH & RH Coupe Rails (P/N V , V ). N N AFT FUSELAGE/EMPENNAGE 330AC, 330BC, 330CC, 330CL, 330BR 330AC, 330BC, 330CC, 330CL, 330BR * Horizontal Stabilizer Actuator ACME Screw (P/N 2A ). (Effective on aircraft equipped with Horizontal Stabilizer Actuators.) * Horizontal Stabilizer Actuator ACME Nut (P/N 2A ). (Effective on aircraft equipped with Horizontal Stabilizer Actuators.) INTERVAL 600 Hours/36 Months, whichever occurs first 600 Flight Hours. 600 Flight Hours. Page Revision: Reissue 09/22/2017

72 Airworthiness Limitations Replacement Requirements IRN ZONE/ ACCESS REPLACEMENT REQUIREMENTS 400 POWERPLANTS, NACELLES, AND THRUST REVERSERS INTERVAL F ** Alternator - Perform Bearing Replacement Hours. V /420 * Aft Engine Mount Bolt (P/N ) NOTE: Do not Replace with same P/N bolt. Use P/N /600 LEFT AND RIGHT WING Next Engine Removal after July 2, W /640 * Flap Actuator Joint (P/N ) - Replace. 24 Months. 700 LANDING GEAR AND RELATED ITEMS O * Nose Landing Gear Strut Assembly (P/N ). 20,000 Landings. O * Nose Landing Gear Actuator Assembly (P/N ). O * Nose Landing Gear Actuator Upper Pin (P/N ). N /730 * Main Landing Gear Strut Assembly (P/N , ). T /730 * Main Landing Gear Side Brace Actuator Assembly (P/N , -004) excluding the End Cap (P/N ). NOTE: The replacement of the MLG Side Brace Actuator Assembly includes the replacement of the MLG Actuator Piston (P/N ), MLG Actuator Cylinder (P/N ), and MLG Actuator Housing (P/N ). Refer to IRN T for the replacement interval of the End Cap. 20,000 Landings 20,000 Landings. 10,000 Landings. 17,000 Landings. T /730 * Main Landing Gear Actuator Upper Pin (P/N ). 96 Months. N /730 * Main Landing Gear Trunnion Pins (P/N and ). 10,000 Landings. O * Nose Landing Gear Trunnion Pins (P/N ). 20,000 Landings. O * Nose Landing Gear Trunnion Axle (P/N ). 20,000 Landings. Page Revision: Reissue 09/22/2017

73 Airworthiness Limitations Replacement Requirements IRN ZONE/ ACCESS REPLACEMENT REQUIREMENTS INTERVAL N /730 * Main Landing Gear Shock Strut Piston (P/N ).. 10,000 Landings N /730 * Main Landing Gear Axle Beam (P/N ). 10,000 Landings. N /730 * Main Landing Gear Shock Strut Link (P/N ). 10,000 Landings. T /730 * Main Landing Gear Actuator Lower Pin (P/N ). 96 Months. N /730 * Main Landing Gear Forward Trunnion Shear Pins (P/N and ). N /730 * Main Landing Gear Aft Trunnion Upper Shear Pin (P/N , ). N /730 * Main Landing Gear Aft Trunnion Lower Shear Pin (P/N , ). T /730 * Main Landing Gear Side Brace Actuator Assembly (P/N , -002) excluding the End Cap (P/N ). NOTE: Refer to IRN T for the replacement interval of the End Cap. 1,800 Landings. 1,800 Landings. 1,800 Landings. 2,500 Landings. N /730 * Main Landing Gear Link Pin (P/N ). 10,000 Landings. N /730 * Main Landing Gear Piston Pin (P/N ). 10,000 Landings. N /730 * Main Landing Gear Actuator Piston (P/N ). 17,000 Landings. N /730 * Main Landing Gear Actuator Cylinder (P/N ). 17,000 Landings. T /730 * Main Landing Gear Actuator End Cap (P/N ). 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, ,387 Landings. N /730 * Main Landing Gear Actuator Housing (P/N ). 17,000 Landings. N /730 * Main Landing Gear Shock Strut Cylinder (P/N and -110). N /730 * Main Landing Gear Side-Stay Actuator Fitting (P/N ). 10,000 Landings. 20,000 Landings. Q /730 * Main Landing Gear Shock Strut Cylinder (P/N , -106, -107, and -108). 6,600 Landings. Page Revision: Reissue 09/22/2017

74 Airworthiness Limitations Replacement Requirements IRN ZONE/ ACCESS REPLACEMENT REQUIREMENTS Q /730 * Main Landing Gear Shock Strut Cylinder (P/N , -102, -103, and -104 ). N /730 * Main Landing Gear Forward Trunnion Shear Pin (P/N ). N /730 * Main Landing Gear Aft Trunnion Upper Shear Pin (P/N ). N /730 * Main Landing Gear Aft Trunnion Lower Shear Pin (P/N ). W /730 * Main Landing Gear Side Brace Actuator Assembly (P/N , -006). L /730 * Main Landing Gear Inboard Door Actuator (P/N ) Cap Screws - Replace. (Effective on Aircraft thru modified per SB , Main Landing Gear Door Actuator Improvement/Saddle Installation and and subsequent.) INTERVAL 10,000 Landings. 5,000 Landings 5,000 Landings. 5,000 Landings. 17,000 Landings. 2,400 Hours. Page Revision: Reissue 09/22/2017

75 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 (f)(3). All scheduled inspections, special inspection requirements, and unscheduled maintenance checks are described in the following sections: (1) Phase Inspections - Sections thru 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 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 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 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 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 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 is a list of the inspections required to maintain reduced vertical separation minimums (RVSM) certification. (8) Unscheduled Maintenance Checks - Section 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 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 Revision: Reissue 09/22/2017

76 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 Revision: Reissue 09/22/2017

77 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 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 Revision: Reissue 09/22/2017

78 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 Revision: Reissue 09/22/2017

79 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 Revision: Reissue 09/22/2017

80 Time Limits and Maintenance Checks Page Revision: Reissue 09/22/2017

81 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 Revision: Reissue 09/22/2017

82 Time Limits and Maintenance Checks Page Revision: Reissue 09/22/2017

83 Time Limits and Maintenance Checks Page Revision: Reissue 09/22/2017

84 Time Limits and Maintenance Checks Page Revision: Reissue 09/22/2017

85 Time Limits and Maintenance Checks Page Revision: Reissue 09/22/2017

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