Volume 5. Challenger 605. Maintenance and Inspection Program

Transcription

1 Ace Aviation Services, Corp. General Maintenance Manual Volume 5 Challenger 605 Maintenance and Inspection Program

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3 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: Highlights Volume 2: Challenger 605 Maintenance and Inspection Program Revision: 2 Chapter: Highlights of Changes Date: 06/29/2018 Page: 1 of 4 A. GENERAL 1. The scope of this revision is to: a. LEP; i. Inserted omitted cover pages where applicable. b. Chapter 01, Section 02 Definitions; i. Revised Calendar items definition. c. Chapter 01, Section 03 - Program Summary; i. 0.0, A. Updated manufacturer TLMC revision status. ii. 0.0, B. Updated manufacturer MPD revision status. iii. 0.0, C Updated manufacturer M/M revision status. d. Chapter 02, PART ; i. Pg 1: Corrected spelling error. ii. Pg 5: inserted missing column lines e. Chapter 02, PART ; i. Corrected service bulletin reference for task f. Chapter 02, PART : i. Reformatted Cover page. ii. Deleted task requirement. iii. Added omitted 5 to task iv. Revised repeat interval on task to v. Revised the repeat interval on task to vi. Deleted the second repeat interval for;

4 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: Highlights Volume 2: Challenger 605 Maintenance and Inspection Program Revision: 2 Chapter: Highlights of Changes Date: 06/29/2018 Page: 2 of

5 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: Highlights Volume 2: Challenger 605 Maintenance and Inspection Program Revision: 2 Chapter: Highlights of Changes Date: 06/29/2018 Page: 3 of 4 g. Chapter 02, PART ; i. Pg 5: Reformatted column width. ii. Pg 10: Separated combined paragraph and inserted omitted task interval for P/N /-114/-115/-116. iii. Pg 11: Moved task under proper column. h. Chapter 02, PART ; i. Deleted GTCP APU for tasks and ii. Added task , Operational Test of the Cabin Power Shut-Off Switch. iii. Added note to task , Whichever interval occurs first. iv. Task , corrected number and from single channel to dual. v. Pg 16 Space formatting only. vi. Tasks and revised to 24 M for concurrence with FAR Added note Mfg TLMC 36 M. vii. Task corrected ATA prefix from 5 to 35. i. Chapter 02, PART ; i. Pg 1 Space formatting only. j. Chapter 02, PART ; i. Pg 1 Moved task to proper column. ii. Pg 2 Moved task to proper column. iii. Pg 3 Formatting and alignment only of table. k. Chapter 02, PART ; i. Task 53-ZL revised interval to 48M. l. Chapter 02, PART ;

6 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: Highlights Volume 2: Challenger 605 Maintenance and Inspection Program Revision: 2 Chapter: Highlights of Changes Date: 06/29/2018 Page: 4 of 4 i. Task inserted omitted 00. m. Chapter 03, Airworthiness Limitations; i. 1. B Revised where inspections for parts are found. ii. Added omitted components to table. n. Chapter 3, ; i. Page T02P04 inserted omitted 15,000 in table. ii. Page 2 Revised P/N for Stage 4 turbine disk. iii. Page 2 Inserted omitted P/N for Cone Turbine Drive. iv. Added asterisk to affected disks with note below table. o. Chapter 4, CL605-1 TLL; i. Pg 2 formatting change. ii. Pg 3 correctly identified AD R3. p. Chapter 5, ACE Form-CL605-01; i. Reformatted for larger signature blocks. ii. X. 1. Added seatbelt extensions.

7 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ROR Volume 5: Challenger 605 Maintenance and Inspection Program Revision: 2 Section: Record of Revision Date: 06/29/2018 Page: 1 of 1 REISSUE... 09/22/2017 Revision /05/2018 Revision /29/2018

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11 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ToC Volume 5: Challenger 605 Maintenance and Inspection Program Revision: REISSUE Section: Table of Contents Date: 09/22/2017 Page: 1 of 2 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 Chapter 2: Airframe Manufacturers Times Limitations & Maintenance Checks SECTION: PART : Introduction PART : Introduction and Rules : Life Limits (Structures) : Life Limits (Systems) : RVSM Qualified Aircraft : Time Limits by Aircraft Effectivity : Tasks by Aircraft Effectivity Custom Installations : Tasks by Aircraft Effectivity Repairs : Airworthiness Limitation Items : Certification Maintenance Requirements PART : Introduction : Avionics, Systems and Powerplant Program : Avionics, Systems and Powerplant Program Tasks and Intervals : Honeywell APU (CL) Program

12 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: ToC Volume 5: Challenger 605 Maintenance and Inspection Program Revision: REISSUE Section: Table of Contents Date: 09/22/2017 Page: 2 of 2 Chapter 2: Airframe Manufacturers Times Limitations & Maintenance Checks SECTION: PART 3 (Continued) : Structural Program : Structural Program Tasks and Intervals : Zonal Inspection Program : Zonal Inspection Program Tasks and Intervals : L/HIRF Inspection Program : L/HIRF Inspection Program Tasks and Intervals UNSCHEDULED MAINTENANCE CHECKS / -51: Unscheduled Airframe Maintenance Checks : Unscheduled Engine Maintenance Checks Chapter 3: Engine Manufacturers Life Limits GE CF 34-3B SECTION: : Airworthiness Limitations : Life Limits of Engine Rotating Parts : Fan Rotor Life Limits : Compressor Rotor Life Limits : High Pressure Turbine Rotor Life Limits : Low Pressure Turbine Rotor Life Limits Chapter 4: Ace Aviation Services, Corp. Time Limitations Listings SECTION: 605-1: N699ST Chapter 5: Forms ACE Form -CL Service Check ACE Form-CL Day Check

13 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:01 Volume 5: Challenger 605 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 5: Challenger 605 Maintenance and Inspection Program Revision: 2 Chapter 01: Introduction Date: 06/29/2018 Section 02: Definitions Page: 1 of 1 These are definitions of subject matter contained in this appendix. Approved by Transport Canada APU Hours: APU Cycles: Also means FAA approved through Bi Lateral agreement. 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. Calendar Items: Hour(s): Landings: Cycles: Operator 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 Means: Ace Aviation Services, Corp.

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17 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 5: Challenger 605 Maintenance and Inspection Program Revision: 2 Chapter 01: Introduction Date: 06/29/2018 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. Bombardier Challenger 605 Time Limits and Maintenance Checks (TLMC), Revision 19 dated May 29/ Section is applicable to the Commonwealth of Independent States only and not U.S. Certificated aircraft and is excluded from this MIP. B. Bombardier Challenger 605 Maintenance Planning Document (MPD), Revision 19 dated May 29/2018. C. Bombardier Challenger 605 Maintenance Manual (Part 2), Revision 48 dated May 29/2018 D. Bombardier Challenger 605 Supplemental Time Limits and Maintenance Checks (STLMC) as applicable to individual aircraft serial number/s. E. General Electric CF34SJ Service Manual SEI-780-REV 57, 02/01/ Introduction A. This Maintenance Inspection Program volume is used in conjunction with the General Maintenance Manual, Volume 1 for the maintenance schedule for Bombardier Challenger 605 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 his responsibility. 1.2 Authority A. The Director of Maintenance has the authority to make changes to the Maintenance Inspection Program.

18 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 5: Challenger 605 Maintenance and Inspection Program Revision: 1 Chapter 01: Introduction Date: 3/5/2018 Section 03: Program Summary Page: 2 of Basis, Implementation and Revision for Maintenance Inspection Program A. AIRFRAME / AVIONICS / POWERPLANT SYSTEMS - Ace Aviation Services, Corp. has adopted the Bombardier Challenger 605 Maintenance Inspection Program, with noted exceptions, from the manufacturer as described in Bombardier Challenger 605 Time Limits and Maintenance Checks. All exceptions in the program will be highlighted by NOTE: Ace Aviation Services, Corp (explanation of exception). Chapter 5 Airworthiness Limitations and Maintenance Management Review Board Reports (MRB) are inclusive to this volume in chapter 2. Elections and interpretations are listed below. 1. References within chapter 2 of this volume to other ATA chapters means Bombardier Challenger 605 Maintenance Manual (Part Two) as revised. 2. References within chapter 2 of this volume to NDT Manual mean Bombardier Challenger 605 Nondestructive Testing Manual, as revised. 3. References to SRM means, Bombardier Challenger 605 Structural Repair Manual as revised. 4. At the current time, no Ace Aviation Services, Corp aircraft listed on Ops Spec D085 are on the Equalized Maintenance Program as described in the MPD Section Ace Aviation Services, Corp. utilizes the Maintenance Planning Document as a basis for planning Airworthiness Limitations and Maintenance Management Review Board tasks from the regulatory approved Time Limitations and Maintenance Checks. a. The MPD is used as a template to plan the accomplishment of the tasks at specific intervals using the Contracted Computer Maintenance Tracking Program as described in the General Maintenance Manual Volume 1 Sub- Section ) The Director of Maintenance may at will, to maximize aircraft availability, separate tasks from packages or merge tasks into packages as described in the MPD. 2) At no time, will any task interval be set in the Contracted Computerized Maintenance Tracking Program that exceeds limits described in the TLMC. b. The Manufacturers Flexible Maintenance Program in the MPD Section 4, 4.1 is to be used for the Challenger 605 in accordance with the General Maintenance Manual Volume 1 Sub-Section 5.3.

19 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 5: Challenger 605 Maintenance and Inspection Program Revision: 1 Chapter 01: Introduction Date: 3/5/2018 Section 03: Program Summary Page: 3 of Basis, Implementation and Revision for Maintenance Inspection Program (Continued) 6. When a Chapter 5 Task No. 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 Chapter 5 Task No. will be tracked on Status Report and noted as N/A by S/N. The requirements interval will be suspended. 7. When a Chapter 5 Task No. 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 Chapter 5 Task No. will be tracked on Status Report and noted as N/A by S/B incorporation or not incorporated. The requirements interval will be suspended. 8. When there are multiple part numbers that are eligible by a single Chapter 5 Task No. 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. 9. When revisions to the Manufacturers program in the TLMC, through CASS those revisions will be reviewed for implementation against the program/s in chapter 2 of this volume for revision, incorporation or deletion as appropriate. 10. Reference the GMM, Volume 1 sub-section for revision FAA approval procedures. 11. STC s installed by Bombardier Completion Centers are eligible for the Flexible Maintenance Program unless otherwise stated in the ICA or are and Airworthy Limitation item. 12. Bombardier, the manufacture, will from time issue Supplemental Time Limits and Maintenance Checks to individual aircraft or series of serial number aircraft. Normally these STLMC items are based on repairs that have been developed by Bombardier engineering as damage tolerant inspections from those repairs. a. The Director of Maintenance is to ensure any STLMC issued is incorporated into this Maintenance and Inspection Program by incorporating them into the Ace Aviation Services, Corp Time Limits Listing (TLL). B. ENGINE - Ace Aviation Services, Corp. has adopted: 1. The Bombardier Challenger 605 Maintenance Inspection Program, with noted exceptions, from the manufacturer as described in Bombardier Challenger 605 Time Limits and Maintenance Checks for the powerplant while on wing.

20 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 5: Challenger 605 Maintenance and Inspection Program Revision: 1 Chapter 01: Introduction Date: 3/5/2018 Section 03: Program Summary Page: 4 of Basis, Implementation and Revision for Maintenance Inspection Program (Continued) a. The Bombardier Challenger 605 Maintenance Inspection Program per the MRB incorporates the Task Oriented (On Condition) Maintenance Program (for CF34A1 and CF34-3B Engines per SEI-780 Chapter paragraph 7. b. Unscheduled engine maintenance is found in Bombardier Challenger 605 Time Limits and Maintenance Checks chapter The General Electric CF34SJ Service Manual SEI-780 for engine Life Limitations. 3. All exceptions in the program will be highlighted by NOTE: Ace Aviation Services, Corp (explanation of exception) Airworthiness Limitations are inclusive to this volume in chapter 2. Elections and interpretations are listed below. 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 either Manufacturers programs referenced in B1 and B2 occur, through CASS those revisions will be reviewed for implementation against the program/s in chapters 2 and 3 of this volume for revision, incorporation or deletion as appropriate. 6. Reference the GMM sub-section for revision FAA approval procedures. C. Un-Scheduled Maintenance Ace Aviation Services, Corp. has adopted: 1. The Bombardier Challenger 605 Unscheduled Maintenance, with noted exceptions, from the manufacturer as described in Bombardier Challenger 605 Maintenance Manual (Part 2) Chapter 05 for the airframe and the powerplant while on wing. a. All exceptions in the program will be highlighted by NOTE: Ace Aviation Services, Corp (explanation of exception) D. CASS - Through judicious use of the Continuing 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.

21 Ace Aviation Services, Corporation Manual: General Maintenance Manual Reference: 01:03 Volume 5: Challenger 605 Maintenance and Inspection Program Revision: 1 Chapter 01: Introduction Date: 3/5/2018 Section 03: Program Summary Page: 5 of Basis, Implementation and Revision for Maintenance Inspection Program (Continued) E. 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. 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 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. F. RVSM - Reduced Vertical Separation Minimum tasks are incorporated into our Maintenance Inspection Program. 1. Unless otherwise specified, RVSM tasks are incorporated in the TLMC per chapter G. CPCP - Corrosion Prevention and Control Program items are incorporated into the Maintenance Inspection Program thru the Airframe and Powerplant Manufacturers Inspection Programs. H. AD s - Airworthiness Directives are incorporated into the Maintenance Inspection Program for scheduling and compliance tracking. I. S/B s - Service Bulletins, when approved by the Director of Maintenance, are incorporated into the CCMTP for scheduling and compliance tracking. J. CFR s US regulatory, Code of Federal Regulations, items for equipment are incorporated into the Maintenance Inspection Program. K. ECTM Engine Condition Trend Monitoring (ECTM) program, while optional under the Bombardier TLCM is to be performed every 30 days not to exceed 50 flight cycles. L. 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 5: Challenger 605 Maintenance and Inspection Program Revision: REISSUE Chapter 01: Introduction Date: 9/22/2017 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 5: Challenger 605 Maintenance and Inspection Program Revision: REISSUE Chapter 01: Introduction Date: 9/22/2017 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 5: Challenger 605 Maintenance and Inspection Program Revision: REISSUE Chapter 01: Introduction Date: 9/22/2017 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-103 [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 5: Challenger 605 Maintenance and Inspection Program Revision: REISSUE Chapter 01: Introduction Date: 9/22/2017 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 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction INTRODUCTION 1. Scope The Time Limits/Maintenance Checks (TLMC) manual (called Chapter 5 in this manual) shows tasks that are Airworthiness Limitations (life limited components, airworthiness limitation items and certification maintenance requirements) and Maintenance Review Board tasks (MRB) for the Bombardier Challenger 605, Model CL 600 2B16, Aircraft Serial No and subsequent. These tasks are required to make sure of the continued airworthiness of the aircraft. The Airworthiness Limitations section and the MRB section are approved by Transport Canada. The MRB Report and the Airworthiness Limitations form the basis of the Manufacturer s recommended inspection/maintenance program. The MRB Report contains the initial minimum maintenance/inspection requirements in compliance with Instructions for Continued Airworthiness. It does not include the Mandatory Airworthiness Inspection tasks that follow: Life Limited Components Airworthiness Limitation Items (ALI) Certification Maintenance Requirements (CMR). 2. Manual Organization NOTE: Ace Aviation Services, Corp. ancillary manual organization is omitted and is covered in GMM Volume 2. The TLMC manual is divided into the sections that follow: PART 1, General PART 2, Airworthiness Limitations PART 3, Maintenance Review Board (MRB) Report For extension tolerances to the inspection intervals, refer to the Maintenance Planning Document (MPD). Revision: REISSUE PART 1 Page Sep 22/2017

28 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction 3. Complementary Information The manual has references to the publications that follow: CL 605 Aircraft Maintenance Manual (AMM) CL 605 Structural Repair Manual CL 605 Component Maintenance Manual CL 605 Non Destructive Test Manual CL 605 Service Bulletins. Aircraft stations and zones data can be found in the AMM, Chapter 6. Engine inspection procedures can be found in the General Electric publication that follows: SEI 780 CF34 Turbofan Engine Maintenance Manual The CF 34 3B engine is operated under the Task Oriented Maintenance Program thus having no mandatory scheduled Overhaul or Hot Section Inspection maintenance. This program consists of installed engine repetitive visual borescope inspections of the external and internal components, specific maintenance checks and an optional but highly recommended Trend Monitoring program. 4. Program Glossary and Definitions Accidental Damage Physical deterioration of an item caused by contact or impact with an object or influence which is not a part of the aircraft, or by human error during manufacturing, operation of the aircraft, or maintenance practices. Age Exploration A systematic evaluation of an item based on analysis of collected information from in service experience. It verifies the item s resistance to a deterioration process with respect to increasing age. Airworthiness Limitations Section A section of the Instructions for Continued Airworthiness that contains each mandatory replacement time, inspection interval, and related inspection procedure for structural items (ALIs) and for systems items (CMRs). This section also includes mandatory replacement times, inspection intervals and related inspection procedures resulting from custom installations and/or repairs on Principal Structural Elements (PSEs). The information contained in the Airworthiness Limitations section may be changed to reflect service and/or test experience of new analysis methods but only with the approval of Transport Canada. Airworthiness Limitations Items A required periodic task, established as a result of fatigue analysis or damage tolerance analysis carried out on each PSE as part of certification of the airplane as an operating limitation of the type certificate. Revision: REISSUE PART 1 Page Sep 22/2017

29 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction Certification Maintenance Requirements Items derived from the Airworthiness Limitation Section of the Instructions for Continued Airworthiness which specify mandatory periodic tasks, established during the design certification of the airplane as an operating limitation of the type certificate. CMRs are a subset of the tasks identified during the type certification process. CMRs usually result from a formal, numerical analysis conducted to show compliance with catastrophic and hazardous failure conditions. Corrosion The gradual deterioration of a metal or alloy as a result of chemical interaction with its environment. Corrosion Level 1 Corrosion damage that does not require structural reinforcement or replacement; or Corrosion occurring between successive inspections exceeds allowable limits, but is local and can be attributed to an event not typical of operator usage of other aircraft in the same fleet (e.g. Mercury spill). Damage Tolerant A qualification standard for aircraft structure. An item is judged to be damage tolerant if it can sustain damage and the remaining structure can withstand reasonable loads without structural failure or excessive structural deformation until the damage is detected. Direct Adverse Effect on Operating Safety Direct To be direct, the functional failure or resulting secondary damage must achieve its effect by itself, not in combination with other functional failures (no redundancy exists and it is a primary dispatch item) Adverse Effect on Safety This implies that the consequences are extremely serious or possibly catastrophic and might cause the loss of aircraft or injury to occupants. Operating This is defined as the time interval during which passengers and crew are on board for the purpose of flight. Discard The removal from service of an item at a specified time limit. Economic Effects Failure effects which do not prevent aircraft operation, but are economically undesirable due to added labor and material cost for aircraft or shop repair. Engine Hours Accumulated time interval between wheels off to wheels on. Environmental Deterioration Physical deterioration of the strength or resistance to failure of an item as a result of chemical interaction with its climate or environment. Failure The inability of an item to perform within previously specified limits. Failure Cause Why the functional failure occurs. Failure Effect That which is the result of a functional failure. Revision: REISSUE PART 1 Page Sep 22/2017

30 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction Fatigue Damage The initiation of a crack or cracks due to cyclic loads and subsequent propagation. Fleet Leader Concept The concentration of sample inspections on the pieces of equipment which have the highest operating ages to identify the first evidence of changes in their condition with increasing age. Flight Hours Accumulated time interval between wheels off to wheels on Function The normal characteristic actions of an item. Functional Test A quantitative test to determine if one or more functions of an item performs within specified limits. Functional Failure How an item failed to perform its function. Hidden Function A function which is normally active and whose cessation will not be evident to the operating crew during performances of normal duties. A function which is normally inactive and whose readiness to perform, prior to it being needed, will not be evident to the operating crew during performance of normal duties. Inherent Level of Reliability and Safety That level which is built into the unit and, therefore, inherent in its design. This is the highest level of reliability and safety that can be expected from a unit, system, or aircraft if it receives effective maintenance. To achieve higher levels of reliability generally requires modification or redesign. Inspection An examination of an item against a specific standard. Inspection Detailed An intensive visual examination of a specific structural area, system installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate by the inspector. Inspection aids such as mirrors, hand lens, borescope, etc., surface cleaning and elaborate access procedures may be required. Inspection General Visual -A visual examination of an interior or exterior area, installation or assembly, to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance, unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. A General Visual Inspection cannot be a candidate for transfer to Zonal Working Group if originated from route 5 or 8. Revision: REISSUE PART 1 Page Sep 22/2017

31 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction Inspection Special Detailed An intensive examination of a specific item(s), installation, or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. Item Any level of hardware assembly (i.e.: system, sub system, module, accessory, component, unit, part etc.). Landing A sequence covering the approach and touchdown phases. Each touch and go operation is considered a landing. Life Limited Items An item which must be removed from service and discarded before a specified time is achieved. Lubrication and Servicing Any act of lubricating or servicing for the purpose of maintaining inherent design capabilities. Maintenance Significant Item Items identified by the manufacturer whose failure: could affect safety (on ground or in flight), and/or is undetectable during operations, and/or could have significant operational impact, and/or could have significant economic impact. Multiple Site Fatigue Damage The presence of a number of adjacent small cracks that might coalesce to form a single long crack. Operating Crew Normal Duties Operating Crew Qualified cockpit and cabin attendant personnel who are on duty. Normal Duties Those duties associated with the routine operation of the aircraft, on a daily basis, to include the following: Procedures and checks performed during aircraft operation Recognition of abnormalities or failures by the operating crew through the use of normal physical senses (e.g. odor, noise, vibration, temperature, visual observation of damage or failure, changes in physical input force requirements, etc.). Operational Effects Failure effects which interfere with the completion of the aircraft mission. These failures cause delays, cancellations, ground or flight interruptions, high drag coefficients, altitude restrictions, etc. Operational Test An operational test is a task to determine that an item is fulfilling its intended purpose. This test does not require quantitative tolerances. This is a failure finding task. Revision: REISSUE PART 1 Page Sep 22/2017

32 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction Other Structure Structure which is judged not to be a Structural Significant Item. "Other Structure" is defined both externally and internally within zonal boundaries. Principal Structural Element (PSE) Elements of Primary Structure which contribute significantly to carrying flight, ground, pressurization or control loads, and whose failure could result in catastrophic failure of the airplane. PSEs are a subset of SSIs (every PSE is an SSI or contained within an SSI). Residual Strength The strength of a damaged structure. Restoration That work necessary to return an item to a specific standard. Restoration may vary from cleaning or replacement of single parts up to a complete overhaul. Safe Life Limit A term applied to items which must be modified or removed from service at or before the specified life limit, determined by the likely occurrence of age related failure. Safe Life Structure Structure which is not practical to design or qualify as damage tolerant. Its reliability is protected by discard limits which remove items from service before fatigue cracking is expected. Scheduled Maintenance Check Any of the maintenance opportunities which are prepackaged and are accomplished on a regular basis. Structural Assembly One or more structural elements which together provide a basic structural function. Structural Detail The lowest structural level in an aircraft structure. A discrete region or area of a structural element, or a boundary intersection of two or more elements. Structural Element Two or more structural details which together form an identified manufacturer s assembly part. Structural Function The mode of action of aircraft structure. It includes acceptance and transfer of specific loads in items (details/elements/assemblies) and provides consistently adequate aircraft response and flight characteristics. Structural Significant Item Any detail, element or assembly which contributes significantly to carrying flight, ground, pressure or control loads and whose failure could affect the structural integrity necessary for the safety of the aircraft. Tasks Maintenance An action or set of actions required to achieve a desired outcome which restores an item to or maintains an item in serviceable condition, including inspection and determination of condition. Threshold The initial accomplishment of a specific maintenance task expressed in flight cycle, flight hours, and/or calendar time. Revision: REISSUE PART 1 Page Sep 22/2017

33 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction Visual Check - A visual check is an observation to determine that an item is fulfilling its intended purpose. Does not require quantitative tolerances. This is a failure finding task. 5. Abbreviations AC Advisory Circular ACO Aircraft Certification Office AD Accidental Damage AEG Aircraft Evaluation Group ALI Airworthiness Limitation Item AMA Airworthiness Manual Advisory AMM Aircraft Maintenance Manual AMTOSS Aircraft Maintenance Task Oriented Support System APU Auxiliary Power Unit ATA Air Transport Association of America ATC Air Traffic Control BBAD Bombardier Business Aircraft Division BL Buttock Line CIC Corrosion Inhibiting Compound CMM Component Maintenance Manual CMR Certification Maintenance Requirement CPCP Corrosion Prevention and Control Program CRES Corrosion Resistant Steel DI Detailed Inspection DME Distance Measuring Equipment DOT Department of Transport DTR Damage Tolerance Rating ED Environmental Deterioration FAA Federal Aviation Administration FAR Federal Aviation Regulation FC Flight Cycles FD Fatigue Damage FMS Flight Management System FOD Foreign Object Damage FS Fuselage Station GVI General Visual Inspection H Hours ISC Industry Steering Committee IWG Industry Working Group JAA Joint Aviation Authorities JAR Joint Aviation Requirements L Landings Revision: REISSUE PART 1 Page Sep 22/2017

34 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction LBL Left Buttock Line LEP List of Effective Pages LRU Line Replaceable Unit M Months MEL Minimum Equipment List MMEL Master Minimum Equipment List MLG Main Landing Gear MPD Maintenance Planning Document MPE Maintenance Planning Engineering MPP Maintenance Program Proposal MPS Material Process Specification MRB Maintenance Review Board MSG 3 Maintenance Steering Group 3rd Task Force MSI Maintenance Significant Item MTBF Mean Time Between Failure MTBUR Mean Time Between Unscheduled Removal NDI Non Destructive Inspection NDT Non Destructive Test NLG Nose Landing Gear P/N Part Number PPH Policy and Procedures Handbook PROP Propulsion PSE Principal Structural Element R Repeat RBL Right Buttock Line REF Reference REO Repair Engineering Order REV Revision SB Service Bulletin SDI Special Detailed Inspection SID Supplemental Inspection Document SIP Structural Inspection Program SRM Structural Repair Manual SSA System Safety Analysis SSI Structural Significant Item STR Stringer SWG Structure Working Group SYS System T Threshold TBD To Be Determined TC Transport Canada TR Temporary Revision TSOP Technical Support Operating Procedure Revision: REISSUE PART 1 Page Sep 22/2017

35 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction VS Vertical Stabilizer WG Working Group WL Water Line WS Wing Stations ZIN Zonal Identification Number ZL Zonal ZWG Zonal Working Group Revision: REISSUE PART 1 Page Sep 22/2017

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37 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction and Rules 1. General 2. Scope The airworthiness Limitations section is approved by Transport Canada (TC). It shows the mandatory maintenance required by the Airworthiness Manual, chapter , Appendix H. The rules applicable to airworthiness limitations are shown in paragraph 4. The rules applicable to CMRs are shown in paragraph 5. All airworthiness limitation maintenance tasks are identified with a * or a ** (two stars). The tasks included in this section are as follows: A. Life Limits Structures (Section ) These tasks are discard tasks which make sure that structural items are discarded before critical failure occurs. B. Life Limits Systems (Section ) These tasks are discard tasks which make sure that items are discarded before critical failure occurs. The life limits of individual engine components are given in GE Maintenance Manual SEI 780, Chapter (Life Limits of Engine Rotating Parts). C. RVSM Qualified Aircraft (Section ) These tasks are required in order to ensure continued airworthiness of aircraft qualified to operate in Reduced Vertical Separation Minimum (RVSM) airspace. D. Time Limits Structural Service Bulletin Incorporation (Section ) This shows tasks related to structural components required to maintain continued airworthiness. E. Time Limits by Aircraft Effectivity (Section ) This shows discard tasks (retirement lives) for structural components on specific aircraft. F. Tasks by Aircraft Effectivity ( ) These are maintenance tasks due to structural and/or systems changes and custom installations done on individual aircraft or groups of aircraft at aircraft completion (finishing) centers. Revision: REISSUE PART 2 Page Sep 22/2017

38 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction and Rules These tasks must be controlled by the operator. Operators receive only those pages which show tasks applicable to their aircraft. This section is not available on microfiche or CD ROM. G. Airworthiness Limitation Tasks by Aircraft Effectivity (Repairs) (Section ) These are maintenance tasks due to structural repairs done on aircraft or groups of aircraft. New repairs show interim approval of the Repair Engineering Order (REO). Each interim approval will then be superseded by a final approval which shows the threshold (T) and repeat (R) inspection intervals. A List of Effective Pages (LEP) is given at the front of the section. It is revised and included with each new or revised repair. These tasks must be controlled by the operator. Operators receive only those pages which show tasks applicable to their aircraft. This section is not available on microfiche or CD ROM. H. Airworthiness Limitation Tasks by Chapter 5 Task Number (Section ) These are maintenance tasks due to durability and damage tolerance analysis. The tasks are the mandatory structural inspections for the basic aircraft. 1. The first (left) column contains the engineering source document and the revision level for the specific Principal Structural Elements (PSE). 2. The second column contains the paragraph number of the source document shown in the first column. 3. The third column contains the Chapter 5 task number. It is made up of 4 parts XX XX XX YZZ and a *. The description of the parts is as follows: XX XX XX is the ATA number. Y is given the number 1 to show a mandatory, nonescalatable (see Rule 4.A.) airworthiness limitation task. ZZ is the unit sequence identifier. The unit sequence identifier starts at 01 for each variation to the full ATA number sequence shown in the chapter 5 task number. 4. The fourth column contains the task title. This title includes the inspection level and a brief description of the area or items to be inspected. 5. The fifth column contains the inspection intervals threshold (T) and repeat (R) which are the maximum allowable values as approved by Transport Canada. The repeat interval is defined from the last time that particular task was done. The inspection intervals in this column are in landings (L). I. CMR Tasks by Chapter 5 Task Number (Section ) Revision: REISSUE PART 2 Page Sep 22/2017

39 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction and Rules These are maintenance tasks due to aircraft system safety analysis. The tasks are the mandatory systems tasks for the basic aircraft. 1. The first (left) column contains the engineering source document and the revision level for the specific CMR. 2. The second column shows the Chapter 5 task number and is made up of 4 parts XX XX XX YZZ and either a * or ** (two stars). The description of the parts is as follows: XX XX XX is the ATA number. Y is given the number 1 to show a mandatory CMR task. ZZ is the unit sequence identifier. The unit sequence identifier begins at 01 for each variation to the full ATA number sequence shown in the Chapter 5 task number. 3. The third column contains the task title. The title shows the type of task and a brief description of the system. 4. The fourth column contains the task intervals. The task interval is defined from the last time that particular task was done. The task intervals in this column are hours (H), months (M) or landings (L). 5. The fifth column contains exceptional short term extension (see rule 5.A.) that can be used to cover an uncontrollable or unexpected situation. The time intervals are hours (H), months (M) or landings (L). If there is no data in this column for a given task, then there is no allowable extension. 6. The seventh column shows the paragraph number of the source document shown in the 3. Records and Reports Follow the procedures in Ace Aviation Services, Corp. GMM Section 7.0, Maintenance Record Keeping 4. Rules Applicable to Airworthiness Limitations (Section ) A. The Canadair Challenger 605, Model CL 600 2B16 is Type Approved as Damage Tolerant and, as a result, some maintenance tasks are mandatory. These tasks are identified with a * and cannot be deleted from the program. The check intervals cannot be increased without the approval of the Airworthiness Branch of Transport Canada or other applicable foreign airworthiness authorities. B. The Inspection Program in section has been substantiated up to landings (Aircraft Initial Design Goal). Operation beyond landings requires additional substantiation and operators wishing to do so should contact Bombardier for the development of a Supplemental Structural Integrity Document. Revision: REISSUE PART 2 Page Sep 22/2017

40 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction and Rules C. Mandatory tasks from the damage tolerance evaluation are divided into the two time intervals that follow: (1) Threshold (T) tasks are done once only at or before the aircraft time value shown. This time period is measured from the zero time of the aircraft. (2) Repeat (R) tasks are done at or before the interval shown. This interval is measured from when the threshold or last repeat check was done. (3) Repeat (R1) tasks, where specified, are done once only at or before the interval shown. This interval is measured from when the threshold check was done. (4) Repeat (R2) tasks, where specified, are done subsequently after the first Repeat (R1) tasks which in these cases are done once only. D. Any task with a repeat (R) interval only, must be incorporated into the aircraft inspection program at or before this interval (R), unless required earlier to comply with the inspection frequency defined in an airworthiness directive. 5. Rules Applicable to Certification Maintenance Requirements (section ) A. The allowable extension in the sixth column is an exceptional short term increase of a CMR interval that can be used when an uncontrollable or unexpected situation prevents the accomplishment of the task at its prescribed interval. Local regulatory authorities must be notified as soon as practical if any short term extension has been used. Repeated use of extensions cannot be used as a substitute to the task s original due date for good management practices. CMR tasks with a NOTE A in the sixth column Allowable Extension have an Allowable Task Tolerance, the value of which is indicated above the NOTE A. This gives the start and end of the envelope for the published interval in column 5. In accordance with the definition of the Allowable Task Tolerance : If a CMR task is accomplished within +/ Allowable Task Tolerance envelope, the next due time shall be calculated from the time at which the CMR task was initially due, not from the point of completion of the task (as explained in example A and B). If a task was accomplished early, before the start of the Allowable Task Tolerance envelope, the next due point envelope starts earlier by the same amount. The length of the envelope remains unchanged (as explained in example C). A task cannot be accomplished later than the maximum Allowable Task Tolerance limit. Local regulatory authorities must approve, prior to use, any desired extension beyond the maximum Allowable Task Tolerance unless first approved in accordance with local regulatory authorities. Example A (Refer to Figure 1) Revision: REISSUE PART 2 Page Sep 22/2017

41 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction and Rules Inspections accomplished late, but within the Allowable Task Tolerance envelope, must have that late period subtracted from the interval at which the inspection was accomplished, in order to keep the original schedule. Using a 600 hour interval as an example, an inspection due at 1200 hours is accomplished at 1220 hours (within the Allowable Task Tolerance ), the next inspection window will be centered at: time accomplished (1220H) late period (20H) + TLMC interval (600H) = next inspection window center (1800H) Example B (Refer to Figure 1) Inspections accomplished early, but within the Allowable Task Tolerance envelope, must have that early period added to the interval at which the inspection was accomplished, in order to keep the original schedule. Using a 600 hour interval as an example, an inspection due at 1200 hours is accomplished at 1180 hours (within the Allowable Task Tolerance ), the next inspection window will be centered at: time accomplished (1180H) + early period (20H) + TLMC interval (600H) = next inspection window center (1800H) Example C (Refer to Figure 1) Inspections accomplished earlier than the minimum values of the Allowable Task Tolerance envelope will require a new schedule. Using a 600 hour interval as an example, an inspection due at 1200 hours is accomplished at 1100 hours (not within the Allowable Task Tolerance ), the next inspection window will be centered at: time accomplished (1100H) + minimum Allowable Task Tolerance (40H) + TLMC interval (600H) = next inspection window center (1740H) Revision: REISSUE PART 2 Page Sep 22/2017

42 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction and Rules B. * shows that the task is mandatory and cannot be changed, escalated (increased) or deleted without the approval of the certification airworthiness authority. Revision: REISSUE PART 2 Page Sep 22/2017

43 Chapter 2: Section: Airframe Manufacturers Time Limitations & Maintenance Checks Introduction and Rules C. ** (two stars) shows that the task interval can be adjusted to agree with an operator s approved escalation practices or an approved reliability program, but the task can not be changed or deleted without prior approval of the airworthiness authority. D. Task ** was issued as Temporary Revision (TR) dated Mar 22/2007. In that TR, the Repeat (R1, R2 and R3) were explained as follows: Repeat Sequence After Threshold Threshold (T) task is done once only at or before the aircraft time value shown. This time period is measured from the zero time of the aircraft. Repeat (R1) task is done once only at or before the (R1) interval (aircraft time value). R1 = T+1600 Hours Repeat (R2) task is done once only at or before the (R2) interval (aircraft time value). R2 = R Hours Repeat (R3) task is done subsequent to the second Repeat (R2) (aircraft time value). R3 = R Hours Interval 1600 Hours (T) 1600 Hours (R1) 1600 Hours (R2) 1000 Hours (R3) Interval Example: (T) completed at 1600 H; (R1) at 3200 H; (R2) at 4800 H; R3 at 5800 H, 6800 H, 7800 H etc. or (R3) at 5600 H, 6600 H, 7600 H etc. Phase In Example: An aircraft has 3950 hours at the issue date (Mar 22/2007) of Temporary Revision The task is to be done at or before 5550 hours. An aircraft has 4050 hours at the issue date (Mar 22/2007) of Temporary Revision The task is to be done at or before 5050 hours. NOTE: The 1000 H interval is the maximum repeat. For planning purposes, the aircraft can use 800 H to coincide with the 800 H inspection package. Revision: REISSUE PART 2 Page Sep 22/2017

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45 CL-605 TIME LIMITS/MAINTENANCE CHECKS LIFE LIMITS (STRUCTURES) 1. The structural life limits of the Safe Life items shown on the pages that follow are taken from the Structural Airworthiness Control Document. Discard is mandatory at the expiration of the specified structural life limit for the item. These life limit values may be superseded by the life limits contained in section , for specific serialized components. NOTES: 1. Individual Main and Nose Landing Gear component utilization must be recorded from the time of initial installation. 2. If no dash number is specified, the life limit is applicable to all the dash numbers of the part numbers listed. 3. For aircraft under the Commonwealth of Independent States (CIS) (Russia) operations, the life limits in section must be superseded by those in section The non serialized pin/bolts must be discarded on removal from aircraft and at intervals not exceeding the discard time presented in this section. PART 2 Page 1 Revision: Jun 29/2018

46 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 2 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX * Discard of the Aileron Antifloat Spring, Part No L Rev / 6. COMPONENT RAS604DX * Discard of the Horizontal Stabilizer Trim Actuator L (HSTA), Part No /5/7 (Vendor Part Rev. B6 COMPONENT No /2/3). RAS604DX * Discard of the Horizontal Stabilizer Trim Actuator L (HSTA) Trunnion Support; Part No. Rev. C3 COMPONENT 601R / 3. RAS604DX * Discard of the Horizontal Stabilizer Trim Actuator 7800 L (HSTA) Upper and Lower Attachment Pins; Upper Rev. C3 COMPONENT Pin Part No / 7 or 601R / 3 and Lower Pin Part No / 7 or 601R / 3. RAS604DX * Discard of the Main Landing Gear (MLG) Fitting, L Part No / 2 (NHA / 104/- Rev. B9 COMPONENT 105/-106). RAS604DX * Discard of the Main Landing Gear (MLG) Pintle L Pin, Part No Rev. -- COMPONENT RAS604DX * Discard of the MLG Shock Strut Upper Pin, Part L No Rev. -- COMPONENT RAS604DX * Discard of the MLG Shock Strut Lower Pin, Part L No Rev. -- COMPONENT RAS604DX * Discard of the MLG Shock Strut Piston, Part No L /-3 (NHA /-103). Rev. -- COMPONENT

47 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 3 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX * Discard of the MLG Shock Strut Cylinder, Part No / 3 (NHA / 103). Rev. -- RAS604DX * Discard of the Main Landing Gear (MLG) Trailing Arm, Part No (NHA ). Rev. -- RAS604DX * Discard of the MLG Main Fitting/Trailing Arm Pivot Pin, Part No Rev. -- RAS604DX * Discard of the Main Landing Gear (MLG) Axle, Part No Rev. -- RAS604DX * Discard of the NLG Main Fitting, Part No or (NHA or ). Rev. -- RAS604DX * Discard of the NLG Pivot (Trunion) Pin (Main Fitting to Aircraft), Part No Rev. -- RAS604DX * Discard of the NLG Shock Strut Sliding Tube, Part No Rev. -- RAS604DX * Discard of the NLG Drag Brace Lower Link, Part No (NHA ). Rev. -- RAS604DX * Discard of the NLG Drag Brace Upper Link, Part No / 3 (NHA ). Rev. A-3 RAS * Discard of the NLG Drag Brace Hinge Pin, Part No Rev L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT

48 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 4 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX * Discard of the NLG Attachment Pin (Main Fitting to Drag Brace), Part No Rev. -- RAS604DX * Discard of the NLG Drag Brace Upper Pivot Pin, Part No Rev. -- RAS604DX * Discard of the NLG Axle Fitting, Part No (NHA ). Rev. -- RAS604DX * Discard of the NLG Pin, Sliding Tube to End Fitting, Part No Rev.-- RAS604DX * Discard of the Main Landing Gear (MLG) Stay Side Pin, Rev. -- Part No / 3 (NHA / 3). RAS604DX * Discard of the Main Landing Gear (MLG) Side Stay Actuator Eye Bolt (Rod End), Part No. Rev (NHA ) L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT L COMPONENT RAS604DX * Discard of the Main Landing Gear (MLG) Side Stay Actuator Cylinder, Part No (NHA ). Rev. -- RAS604DX * Discard of the Main Landing Gear (MLG) Side Stay Actuator Piston, Part No / 8. Rev. A-3 RAS604DX * Rev. C-2 Discard of the Main Landing Gear (MLG) Side Brace Fitting Shaft, Part No. 601R / 3 and Part No. 601R L COMPONENT L COMPONENT L COMPONENT

49 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 5 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX * Discard of the Inboard Flap Vane Beam, Part No. Rev /25/27/29. RAS604DX 990 Rev. B * Discard of the Inboard Flap Fasteners Hinge Box Wing Forward Fitting L COMPONENT 7800 L COMPONENT See NOTE NOTE: For aircraft Post SB A (Part B) that have replaced all 16 fasteners, the 7800 L interval starts at the incorporation date of the Service Bulletin.

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51 CL-605 TIME LIMITS/MAINTENANCE CHECKS LIFE LIMITS (SYSTEMS) 1. The systems life limits shown on page 2 are taken from the design compliance reports. Discard is mandatory at the expiry of the specified system life limit for the item. NOTE: The life limit items are in flight hours unless otherwise stated. Revision: 2 PART 2 Page Jun 29/2018

52 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 2 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RBR * Discard of the Discharge Cartridges of the 120 M Engine Fire Extinguisher Containers, Part No. Rev. C COMPONENT RBR * Discard of the Discharge Cartridges of the 120 M Auxiliary Power Unit (APU) Fire Extinguisher Rev. C COMPONENT Containers, Part No RBR * Discard of the Horizontal Stabilizer Trim Rev. F 8 Add 5 Actuator (HSTA), Part No /5/ H RBR * Discard of the Hydraulic Accumulator L Assembly, Part No. 601R Rev. F6 Add 4 COMPONENT ( ) NOTE: This task is only applicable to accumulators identified with "TNAE" after the serial number. RBR Rev. F9 Add * Discard of the Hydraulic Accumulator Assembly, Part No. 601R ( ) NOTE: This task is only applicable to accumulators identified with "TNAE" after the serial number. RBR * Discard of the Modulating and Shut Off Valve, Rev. F 10, Add Part No (Post SB ). 6 RBR Rev. G * Discard of the Thrust Reverser Ballscrew Actuator, Part No / L COMPONENT H H COMPONENT Without overhaul

53 CL-605 TIME LIMITS/MAINTENANCE CHECKS RVSM QUALIFIED AIRCRAFT 1. For all RVSM approved operators, in order to ensure continued airworthiness of aircraft qualified to operate in Reduced Vertical Separation Minimum (RVSM) airspace, the tasks shown on page 2 are required at the intervals shown.. Revision: REISSUE PART 2 Page Sep 22/2017

54 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 2 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RAZ 604DX * Discard of the Pitot Static Probes (RVSM Qualified A/C 9600 H Rev. -- COMPONENT RAZ 604DX * Functional Test of the Air Data Computer (ADC), (RVSM Qualified A/C) Rev. 5 Add.4 24 M COMPONENT 1 M

55 CL-605 TIME LIMITS/MAINTENANCE CHECKS PART 2 SECTION TIME LIMITS BY AIRCRAFT EFFECTIVITY PART 2 Cover Revision: REISSSUE Sep 22/2017

56 TIME LIMITS BY AIRCRAFT EFFECTIVITY 1. Introduction Section is customized to the requirements of individual aircraft, where applicable. It tabulates life limits by aircraft effectivity to ensure that specific serialized components are removed from service at the required interval(s). Repairs or modifications following interim approval of the Repair Engineering Order (REO) can affect the life of a component. Where such repairs or modifications affect the life limit of a component, that changed life limit will be shown in this section. The components listed are those which have been installed on the aircraft. Removal from service of the life limited parts must be controlled by the operator. Operators receive only those pages applicable to their aircraft. This section is not available on microfiche or CD ROM 2. Organization Section should be arranged as follows: Introduction List of Effective Pages (if applicable) Individualized life limits as shown on respective aircraft List of Effective Pages. NOTE: The list of effective pages will be revised with each new or revised repair. Page1 PART 2 Revision: REISSUE Sep 22/2017

57 CL-605 TIME LIMITS/MAINTENANCE CHECKS PART 2 SECTION TASKS BY AIRCRAFT EFFECTIVITY CUSTOM INSTALLATIONS PART 2 Cover Revision: REISSUE Sep 22/2017

58 TASKS BY AIRCRAFT EFFECTIVITY CUSTOM INSTALLATIONS 1. Introduction Section is customized to the requirements of individual aircraft, where applicable. It contains Airworthiness Limitation checks by aircraft effectivity, to impose additional maintenance requirements as a result of structural modifications or installations carried out on those aircraft. These tasks must be controlled by the operator. NOTE: Operators receive only those pages applicable to their aircraft. This section is not available on microfiche or CD ROM. 2. Organization Section should be arranged as follows: Introduction List of Effective pages (if applicable) Individualized inspection tasks as shown on respective aircraft List of Effective Pages The list of effective pages will be revised with each new or revised repair. PART Page 1 Revision: REISSUE Sep 22/2017

59 CL-605 TIME LIMITS/MAINTENANCE CHECKS PART 2 SECTION TASKS BY AIRCRAFT EFFECTIVITY REPAIRS PART 2 Cover Revision: REISSUE Sep 22/2017

60 TASKS BY AIRCRAFT EFFECTIVITY REPAIRS 1. Introduction Section is customized to the requirements of individual aircraft, where applicable. it contains Airworthiness Limitation checks by aircraft effectivity, to impose additional maintenance requirements as a result of structural repairs carried out on those aircraft. New repairs will be release showing interim approval of the Repair Engineering Order (REO). Each interim approval will then be superseded by a final approval showing threshold and repeat inspection intervals in the usual manner, and identifying the applicable inspection procedure(s). These tasks must be controlled by the operator. NOTE: Operators receive only those pages applicable to their aircraft. This section is not available on microfiche or CD ROM. 2. Organization Section should be arranged as follows: Introduction List of Effective pages (if applicable) Individualized inspection tasks as shown on respective aircraft List of Effective Pages The list of effective pages will be revised with each new or revised repair. PART Page 1 Revision: REISSUE Sep 22/2017

61 PART 2 SECTION AIRWORTHINESS LIMITATION ITEMS Tasks by Chapter 5 Task Number PART 2 Cover Revision: Jun 29/2018

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63 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 1 Sep 22/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval

64 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 2 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Passenger Door Hinge. T 5315 L R 1391 L RAS Rev. G * Detailed Inspection of the Passenger Door Flap Cutout. R 4255 L

65 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 3 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Detailed Inspection of the Fuselage Skin at the NLG Cutout FS235. R 7800 L RAS Rev. G * Detailed Inspection of the Forward Pressure Bulkhead Web FS202. T 6900 L R 4540 L RAS Rev. G * Detailed Inspection of the Frame FS220. R 1545 L RAS Rev. G * Detailed Inspection of the Window Lower Sill FS235, FS249 and FS T 2262 L R 1545 L RAS * Detailed Inspection of the Window Lower Sill FS209. T 2262 L R 1933 L Rev. G RAS * Detailed Inspection of the Window Upper Sill FS234, Rev. G BL2.5. RAS * Detailed Inspection of the Forward Pressure Bulkhead Rev. G Vertical Stiffener BL22. RAS * Detailed Inspection of the Forward Pressure Bulkhead Rev. G Vertical Member WL79.5 and WL93, BL22. RAS * Special Detailed Inspection of the Fuselage Frame Rev. G FS235 Upper Cap Angle, BL8. RAS604DX 990 Rev. B * Detailed Inspection of the Floor Connection Clips FS T 3747 L R 755 L T 5545 L R 897 L R 3509 L R 4808 L R 1559 L

66 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 4 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Forward Pressure Bulkhead Web WL79.5 to WL91.7. R 7800 L RAS Rev. G RAS Rev. G * * Detailed Inspection of the NLG Beam, Web below Drag Beam FS210 to FS215, Upper Cap FS210 and Lower Cap FS224. Detailed Inspection of the NLG Drag Strut FS213, and the NLG Beam Vertical Stiffener Clip FS215. R 2752 L R 3791 L RAS Rev. G * Special Detailed Inspection of the Pilots Floor Web Adjacent to the Pressure Bulkhead FS203, BL16. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Lower Sill and Fuselage Skin FS220. R 7800 L RAS Rev. G * Special Detailed Inspection of the End Post of the Side Window FS280. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Structure around the Cabin Windows R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Fuselage skin around the Overwing Emergency Exit. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Cutouts for the Cabin Windows. T 4637 L R 3798 L

67 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 5 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * Special Detailed Inspection of the Structure around the Passenger Door. R 7471 L RAS604DX 990 Rev * Special Detailed Inspection of the Keel Longeron Links FS R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Passenger Door Frames FS310 and FS349. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Corner of the Pressure Skin FS409 to FS559, WL73. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Wing to Fuselage Attachment Frame FS424, WL73. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Wing to Fuselage Attachment Frame FS513, BL16. R 7800 L RAS Rev. G * Special Detailed Inspection of the Longitudinal Floor Beams FS513. R 5073 L RAS Rev. G * Detailed Inspection of the Longitudinal Floor Beams FS484, BL18. R 2607 L RAS604DX 990 Rev * Detailed Inspection of the Wing to Fuselage Attachment Lugs, FS424, FS473 and FS513. R 7800 L

68 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 6 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev. B * Detailed Inspection of the Longeron Assembly Under Floor, FS513, BL45. R 2033 L RAS604DX 990 Rev * Special Detailed Inspection of the Wing to Fuselage Attachment Frame FS513. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Keel Longeron. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Frame to Longeron Cleats FS439, FS461, FS484, FS499, FS529 and FS544. T 6695 L R 3370 L RAS Rev. G * Detailed Inspection of the Tension Clip, Bulb Angle, Beams and the Aft Skin Panel of the Forward Auxiliary Tank. R 1920 L RAS Rev. G * Special Detailed Inspection of the Access Doors on the Forward Auxiliary Tank T 6300 L R 3215 L RAS Rev. G * Detailed Inspection of the Forward Pressure Skin Panel and the Forward Attachment Angles of the Forward Auxiliary Tank. R 3970 L RAS Rev. G * Special Detailed Inspection of the Forward Pressure Skin Panel of the Forward Auxiliary Tank. R 4500 L

69 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 7 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * Detailed Inspection of the Stops, Fittings and Attachments of the Overwing Emergency Exit. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Skin and the Stringer Splice Stringer 0.0, FS559. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Skin Circumferential Splice at FS between Stringers 1L and 1R. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Structure around the Overwing Emergency Exit. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Skin Splice Stringer0.0, FS439. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Fuselage Skin at Light Frames FS202 to FS621. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Skin Splice Stringer 8L, FS424 to FS439. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Tie Beam, Pressure Floor to Wing FS460. T 7639 L R 921 L RAS604DX 990 Rev * Detailed Inspection of the Stringer Splice Stringer 13, FS513. R 7800 L

70 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 8 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * Special Detailed Inspection of the Pressure Box of the Forward Keel Beam FS R 7800 L RAS604DX 990 Rev * Detailed Inspection of the TCAS Antenna Installation and Surrounding Structure. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Longitudinal Splice at the TCAS Antenna Location R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Passenger Door Light Cutout at FS between Stringers 14L and 15L, and the Emergency Exit Door Light Cutouts at FS401.50, FS and FS between Stringers 13R and 14R. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the GPS Antenna. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Wing to Fuselage Pins. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Fuselage Skin around the Lower Beacon Light Harness. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Potable Water Fill Adaptor Cutout. R 7800 L

71 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 9 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * Detailed Inspection of the Drain Mast Cutout. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Area around the Cutouts that Follow: 1) VHF1 Antenna Penetration, FS349 to FS364 2) Upper Beacon Light Penetration, FS424 to FS439. 3) LDS Antenna Installation, FS513 to FS529 4) VHF3 Antenna Penetration, FS544 to FS559. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Area around the Cutouts that follow: 1) TCAS Omni Antenna Penetration, FS310 to FS333 2) ATC Antenna Installation, FS257.5 and FS ) XM Radio Antenna Penetration, FS473 to FS484. 4) Angle of Attack Vane Installation, FS280 to FS295. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Area around the Cutouts that follow: 1) ADF Antenna 2) VHF2 Antenna R L R L RAS604DX 990 Rev * Detailed Inspection of the Fuselage Skin around the DME1 Antenna Harness. R 7800 L

72 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 10 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * Detailed Inspection of the DME2 Installation R 2473 L RAS604DX 990 Rev * Special Detailed Inspection of the Pressure Bulkhead at FS R 3095 L RAS604DX 990 Rev * Detailed Inspection of the Overwing Emergency Exit Door. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Area around the Cutouts that Follow: 1) Second Radio Altimeter Antenna (if installed) at FS633.5, BL3R 2) ELT Antenna Installation at FS723.15, BL12.57 R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Skin Stringer 0, FS439. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Fuselage Skin at the Splice of Stringer 3, FS473. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Keel Longeron Bolts. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Overwing Floor Intercostals FS421 to FS529. R 4211 L

73 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 11 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * Special Detailed Inspection of the Area at the Cutouts that Follow: 1) VHF1 Antenna 2) Upper Beacon Light at FS ) VHF3 Antenna R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Baggage Door Sills. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Fuselage Frame at FS589. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Fuselage Skin at the Corners of the Baggage Door. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Iridium Satcom Antenna Installation, FS338.00, Stringer 0 to 1R. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Vertical Posts of the Pressure Bulkhead at FS R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Keel Longeron Bolts FS R 7800 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Dual Patch Iridium Antenna Cutout R 7800 L

74 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 12 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev. B * Special Detailed Inspection of the Upper Latch Pins of the Passenger Door R 4420 L RAS Rev. G * Detailed Inspection of the Bulb Angle Stiffener, Forward Pressure Skin Panel and Forward Attachment Angles of the Aft Auxiliary Tank. R 1549 L RAS Rev. G * Detailed Inspection of the Beams and the Fuel Skin Panels of the Aft Auxiliary Tank. R 1220 L RAS Rev. G * Special Detailed Inspection of the Access Doors on the Aft Auxiliary Tank. T 6375 L R 3215 L RAS Rev. G * Special Detailed Inspection of the Forward Pressure Skin Panel of the Aft Auxiliary Fuel Tank. R 5905 L RAS Rev. G * Detailed Inspection of the Frame Assembly Pressure Bulkhead FS621. T 6695 L R 3370 L RAS Rev. G * Detailed Inspection of the Rear Pressure Bulkhead Web Feed Through Holes and Cutouts. T 1954 L R 1548 L RAS604DX 990 Rev * Detailed Inspection of the Stringer Splice FS718, Stringer 1L and 1R. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Fuselage Frame VS55.625%, Stringer 5. R 4178 L

75 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 13 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * Special Detailed Inspection of the Skin, Drag Angle and Circumferential Splice at FS755. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Fuselage Frame at the Front Spar Attachment of the Vertical Stabilizer FS755. R 7800 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Vertical Stiffeners of the Rear Pressure Bulkhead R 2400 L RAS Rev. G * Special Detailed Inspection of the Floor Beam Attachment to the Pressure Bulkhead FS621. R 2000 L RAS Rev. G * Special Detailed Inspection of the Transverse Beam, Aft of the Pressure Bulkhead FS621, BL27. R 3698 L RAS Rev. G * Special Detailed Inspection of the Upper Cap of the Pylon Spar FS R 2460 L RAS Rev. G * Special Detailed Inspection of the Upper Cap of the Pylon Spar at the Fuselage Frame Attachment FS R 7800 L RAS Rev. G * Special Detailed Inspection of the Upper Cap of the Engine Support Beam FS R 1942 L RAS Rev. C * Special Detailed Inspection of the Splice Angle of the Outer Flange Cap FS R 7800L

76 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 14 Jun 29/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. B * Detailed Inspection of the Intercostals and Clips FS621 to FS625.3, Pressure Bulkhead Vertical Stiffeners FS621, and the Stiffening Angles on the Engine Support Beam FS R 690 L RAS604DX 990 Rev * Detailed Inspection of the Fuselage Frame Web FS755, BL5.5 and WL131. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Drag Angle VS67.5%. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Splices and Stringers (L&R) between Frames VS55.625% and VS67.5%. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Fuselage Skin and Vertical Stabilizer along the Drag Angle. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Fuselage Skin at Frame Splice FS672.2, Stringer 6. R 7800 L RAS604DX 990 Rev * Special Detailed Inspection of the Longitudinal Splice FS672.2, Stringer 6. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Structure Adjacent to the Overboard Lavatory Services. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Structure Adjacent to the Auxiliary Fuel Tank Cutout. R 7800 L

77 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 15 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev * General Visual Inspection of the Primary Radio Altimeter Antenna Installation. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Marker Beacon Antenna Installation. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Area around the VOR/ILS Antenna Installation. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Stringer Splice at the Rear Pressure Bulkhead FS621 R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Floorbeam Fittings at FS621. R 4457 L RAS604DX 990 Rev * Detailed Inspection of the Rear Pressure Bulkhead Frame Cap, Skin and Skin Doubler at FS621. R 7800 L RAS604DX 990 Rev * Detailed Inspection of the Cap Angle of the Fuselage Frame FS755. R 7800 L RAS604DX 990 Rev * General Visual Inspection of the Fuselage Stringer Splice FS625.3, Stringers 0.0 and 1. R 7800 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Rear Pressure Bulkhead Web FS Fwd Face R 4360 L RAS604DX 990 Rev. B * Detailed Inspection of the Engine Support Beam R 1100 L

78 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 16 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev. B * Detailed Inspection of the Air to Ground (ATG) Antenna Cutout R 6797 L RAS604DX 990 Rev. B * Detailed Inspection of the Fuselage Skin Around the LDS Antenna between FS and FS755.00, and Stringers 26R and 26L, (Post SB ) or (Post SB ) R 7800 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Splice Strap and Skin at Stringer 20L and 20R between FS and FS R 2817 L RAS604DX 990 Rev. B * Detailed Inspection of the Fuselage Structure for Hydraulic System No. 3 Accumulator at FS574.00, (Post SB ) R 229 L RAS604DX 990 Rev. C * Detailed Inspection of the Splice Angle of the Outer Flange Cap FS R 7800L

79 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 1 Page 17 3/5/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Detailed Inspection of the Pylon Upper Skin FS682. R 3233 L RAS Rev. G * Detailed Inspection of the Upper Splice of the Pylon Canted Rib FS R 7800 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Aft Engine Mount Upper Cap from FS to FS R 1677 L

80 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 18 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev. A * Detailed Inspection of the Horizontal Stabilizer Bathtub Fitting. R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Upper Cap and Skin of the Rear Spar of the Horizontal Stabilizer Rib 1. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Centerline Rib Upper Cap of the Horizontal Stabilizer FS886. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Rear Spar Upper Cap Splice at BL0.0 of the Horizontal Stabilizer R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Pivot Fitting Lugs of the Horizontal Stabilizer on the Horizontal Stabilizer Side. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Upper Cap Splice of the Front Spar of the Horizontal Stabilizer BL6. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Upper Skin Panel at Stringer 1 of the Horizontal Stabilizer BL6. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Horizontal Stabilizer Rear Spar Web Splice BL0. R 7800 L RAS Rev. G * Special Detailed Inspection of the PCU Fittings and the Hinge Fittings of the Elevator. T 3600 L R 3600 L RAS Rev. G * Detailed Inspection of the Elevator Skins and Front Spar. R 7800 L

81 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 19 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Detailed Inspection of the Elevator Hinge Bolts. T 4800 L R 4800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Horizontal Stabilizer Pivot Fitting Lugs on the Vertical Stabilizer Side. R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Stringer Extension Fitting at VS31.875%. R L R2 981 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Pivot Lugs of the Pitch Trim Actuator on the Vertical Stabilizer Side. R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Vertical Stabilizer Front Spar to the Fuselage Attachment Fittings. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Vertical Stabilizer Stringer Splice VS55.625% at Rib 3 and VS31.875% at Rib 2. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Skin Cutout at the Access Holes between Ribs 1 and 3, VS31.875% and VS43.75% of the Vertical Stabilizer. R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Rear Spar Caps of the Vertical Stabilizer. R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Front Spar Caps at Rib 1 and Splice Straps LH/RH of the Vertical Stabilizer. R 7800 L

82 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 20 Jun 29/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS604DX 990 Rev. A * General Visual Inspection of the Rear Spar Web of the Vertical Stabilizer Rib 7. R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Mid Spar Caps of the Vertical Stabilizer. R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Vertical Stabilizer Front Spar to Frame Attachment Fittings at FS755.00, WL R 7800 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Skin Cutout at the Access Hole between Ribs 4 and 5, VS % and VS31.875% of the Vertical Stabilizer. R L RAS604DX 990 Rev. A * Detailed Inspection of the Pitch Trim Actuator Pivot Lugs Support Plates on the Vertical Stabilizer Side. R 7800 L RAS604DX 990 Rev. A * Detailed Inspection of the Hinges and PCU Bolts of the Rudder. R 7800 L RAS604DX 990 Rev. B * General Visual Inspection of the External Skins and Front Spar of the Rudder. R 1600 L RAS604DX 990 Rev. A * Special Detailed Inspection of the Vertical Stabilizer to Rudder Hinge Fittings and PCU Attachment Lugs. R 7800 L

83 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 21 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Detailed Inspection of the Windshield and Side Window Lower T Plates. T 3747 L R 755 L RAS Rev. G * Detailed Inspection of the Side Window 4 Bushing Holes. T 300 L R 300 L RAS Rev. G * Detailed Inspection of the Windshield and Side Window Bushing Holes. T 600 L R 600 L RAS Rev. G * Special Detailed Inspection of the Bolts at the Windshield and Side Window T Plates. T 1200 L R 1200 L NOTE: It is acceptable to replace the bolts with new bolts in lieu of this inspection. RAS Rev. G * Special Detailed Inspection of the Attachment Bolts for the Windshield and Side Window. T 4800 L R 4800 L NOTE: It is acceptable to replace the bolts with new bolts in lieu of this inspection.

84 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 22 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Detailed Inspection of the Lower Wing Plank Centerline Splice, Stringers 15 and 16. T 6407 L R 878 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank Centerline Splice, WS242 and WS264. R 3199 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Lower Wing Plank Skin Splice Stringers 15 and 16. T 3900 L R 1966 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank WS45,WS199 and WS220. R 1295 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank Front Spar Splice WS R 3021 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank Front Spar WS45. R 4701 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank WS45, Stringer 10. T 3064 L R 1416 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank Fuel Drain Hole WS45, Stringer 17. T 4644 L R 2442 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Lower Wing Plank at the Rear Spar WS45 and WS47. R 1771 L

85 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 23 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank WS45, Stringers 14 and 15. T 3250 L R 1368 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank WS65, WS94, WS106.4 and WS R 627 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank WS65, Stringer 17. T 2778 L R 1307 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank at the Rear Spar WS59 to WS65. T 5297 L R 5297 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank Near the MLG Trunnion WS65, and the Auxiliary Spar Access Hole. R 7800 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank WS85.5, Stringers 14 to 17. T 2651 L R 883 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank at the Rear Spar WS T 3951 L R 1372 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank WS148, Stringers 8 to 10 and Stringer 15. T 1719 L R 1719 L

86 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 24 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank WS148, Stringer 19. R 1334 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank at the Aft Edge WS163 to WS R 2039 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Lower Wing Plank WS163, Stringer 15. T 2565 L R 1200 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank at the Rear Spar WS178 and WS189. R 2039 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank at the Rear Spar WS166. R 2039 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank at the Rear Spar WS217 and WS222. R 6320 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank around the Access Hole WS220, Stringer 10. T 2240 L R 1809 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank at the Rear Spar WS219. R 6320 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank WS238 and WS242. T 5740 L R 1591 L

87 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 25 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Detailed Inspection of the Lower Wing Plank at the Rear Spar WS242 and WS260. R 3199 L RAS Rev. G * Special Detailed Inspection of the Lower Wing Plank around the Access Hole WS112, Stringer 10. T 6158 L R 1044 L RAS Rev. G * Detailed Inspection of the Wing Upper Surface. T 4800 L R 600 L RAS Rev. G * Detailed Inspection of the Internal Structure of the Wing Box. T 4800 L R 4800 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank at the Butt Strap at the Front and Rear Spar WS R 7800 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank WS88.0. T 1938 L R 792 L RAS Rev. G * Detailed Inspection of the Lower Wing Plank WS T 2965 L R 952 L RAS DX Rev * Detailed Inspection of the Wing to Fuselage Attachment Lugs FS424.0, FS473.0 and FS R 7800 L RAS Rev. G * Detailed Inspection of the External Surfaces of the Wing Tip. T 4800 L R 1200 L

88 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 26 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Outboard Flap Front Spar. R 5233 L RAS Rev. G * Special Detailed Inspection of the Vane Tangs (End Support) of the Outboard Flap. R 3092 L RAS Rev. G * Special Detailed Inspection of the Forward Lugs of the Outboard Flap. R 4150 L RAS Rev. G * Special Detailed Inspection of the Forward Upper Lugs of the Outboard Flap Arm WS220. R 1340 L RAS Rev. G * Special Detailed Inspection of the Vane Mid Support Fittings of the Outboard Flap. R 2200 L RAS Rev. G * Detailed Inspection of the Vane Support Fitting of the Outboard Flap. R 1700 L RAS Rev. G * Special Detailed Inspection of the Forward Lugs of the Inboard Flap. R 3500 L RAS Rev. G * Special Detailed Inspection of the Inboard Flap Hinge Boxes. T 5300 L R 4250 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Inboard Flap Front Spar. R 7800 L RAS Rev. G * Special Detailed Inspection of the Wing/Rib Backup Fitting of the Inboard Flaps WS T 7240 L R 6783 L

89 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 27 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Detailed Inspection of the Inboard Flap Vane Support Attachment Brackets. T 7200 L R 1800 L RAS Rev. G * Special Detailed Inspection of the Carriages of the Inboard Flap Vane. R 7800 L RAS Rev. G * Special Detailed Inspection of the Inboard Flap Arms. R 1675 L RAS Rev. G * Special Detailed Inspection of the Intermediate Support of the Outboard Flap Vane. R 3725 L RAS Rev. G * Special Detailed Inspection of the Support Struts of the Outboard Flap Vane. R 7102 L RAS Rev. G * Special Detailed Inspection of the End Ramps of the Outboard Flap Vane. R 7800 L RAS Rev. G * Special Detailed Inspection of the Flap Hinge Bolts. R 7800 L RAS604DX 990 Rev. B * Special Detailed Inspection of the Forward Lugs of the Inboard Flap Hinge Box R 6647 L RAS Rev. G * Special Detailed Inspection of the Outboard Flap Wing/Hinge Forward Box Fittings. R 1400 L RAS Rev. B * Special Detailed Inspection of the Hinge Box Forward Lugs of the Outboard Flap. R 3610 L

90 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 28 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Hinge Box Supports of the Outboard Flap. R 3050 L RAS Rev. G * Detailed Inspection of the Aileron. T 1867 L R 1867 L RAS Rev. G * Detailed Inspection of the Aileron Upper and Lower Skins and Front Spar. R 2400 L RAS Rev. G * Detailed Inspection of the Hinge Bolts of the Aileron. T 4800 L R 4800 L RAS Rev. G * Special Detailed Inspection of the Flight Spoiler. T 1200 L R 1200 L RAS Rev. G * Detailed Inspection of the Upper and Lower Skins of the Flight Spoiler. R 7800 L RAS Rev. G * Detailed Inspection of the Hinge Bolts of the Flight Spoiler. T 4800 L R 4800 L

91 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 29 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Engine Nacelle Joint. R 7800 L RAS Rev. G * Special Detailed Inspection of the Support Fitting of the Nose Cowl Actuator. T 4400 L R 2400 L RAS Rev. G * Special Detailed Inspection of the Track Support Assembly and Flange of the Service Pylon. R 2400 L RAS Rev. G * Special Detailed Inspection of the Yoke of the Forward Engine Mount. R 7800 L RAS Rev. G * Special Detailed Inspection of the Thrust Fitting of the Aft Engine Mount. R 4126 L RAS Rev. G * Special Detailed Inspection of the Link and Bolts of the Forward Engine Mount. R 7800 L

92 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 30 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval RAS Rev. G * Special Detailed Inspection of the Aft Lug of the Main Track of the Thrust Reverser. R 3133 L RAS Rev. G * Special Detailed Inspection of the Main Tracks Lower Flange of the Thrust Reverser. R 7800 L RAS Rev. G * Special Detailed Inspection of the Main Upper and Lower Pylon Track. R 7800 L RAS Rev. G * Special Detailed Inspection of the Attachment Fitting of the Main Track of the Thrust Reverser. R 2800 L RAS Rev. G * Detailed Inspection of the Support Bed for the Upper and Lower Pylon Track on the Service Pylon. R 7800 L

93 PART 2 SECTION CERTIFICATION MAINTENANCE REQUIREMENTS Tasks by Chapter 5 Task Number Cover Revision: REISSUE Sep 22/2017 PART

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95 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 1 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev.E ** (two stars) Functional Test of the Outflow Valves H 40 H RBR Rev.B ** (two stars) Operational Test of the Cabin Pressure Acquisition Module H 40 H NOTE A NOTE: See Section ; Rules Applicable to Certification Maintenance Requirements (Section ).

96 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 2 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev.NC ** (two stars) Operational Test of the Yaw Damper Linear Actuators (SVL 4000 Relays) H 40 H

97 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 3 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev.F * Functional Test of the Generator Control Unit (GCU) Overvoltage Protection Circuits H 40H RBR Rev.F , * Operational Test of the Air Driven Generator (ADG). NOTE: Whichever interval occurs first H or 24M S See NOTE 40 H

98 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 4 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev.A * Operational Test of the Roll Disconnect System. 800 H 40 H RBR Rev. E ** (two stars) Functional Test of the Aileron Power Control Units (PCUs). 800 H 40 H RBR Rev.E ** (two stars) Detailed Inspection of the Aileron Flutter Damper. 800 H 40 H RBR Rev.E RBR Rev. NC 3 RBR Rev.A ** (two stars) ** (two stars) ** (two stars) Functional Test of the Rudder Backlash. 800 H 40 H Operational Test of the PCU Load Limiters H 40 H Functional Test of the Pitch Feel Simulator H 40 H RBR Rev.A * Operational Test of the Elevator Disconnect System. 800 H 40 H RBR Rev.E * Functional Test of the Elevator Backlash. 800 H 40 H RBR Rev.A * Functional Test of the Elevator Flutter Dampers H 40 H RBR Rev.A ** (two stars) Detailed Inspection of the Elevator Flutter Dampers. 800 H 40 H

99 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 5 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension MBR Rev. C ** (two stars) Functional Test for the Flap and Sideslip Compensation Monitor of the Stall Protection System 4800 H 40 H * Functional Test of the Angle of Attack (AOA) Transducer Linearity RSI C 1830 Rev. NC RBR Rev. E N/A Part Number Part Number H COMPONENT 100 H COMPONENT N/A N/A RBR Rev. C * Restoration of the Angle of Attack (AOA) Transducer, Part No H COMPONENT 40 H RBR Rev. E ** (two stars) Functional Test for the Stall Protection System (SPS) Stick Pusher Capstan Shaft, Part No (Vendor Part No ) 1600 H 40 H RBR Rev. C 3 Add ** (two stars) Operational Test (BITE) of the Horizontal Stabilizer Trim Control System (HSTCS) 400 H 40 H PHASE IN: For aircraft with more than 400 hours since task was done, this task must be accomplished at or before the next 400 hour inspection but no later than May 01, 2013, whichever occurs first.

100 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 6 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBS Rev. E 25 Add * Restoration (Overhaul) of the Horizontal Stabilizer Trim Actuator, Part No and Subs (Vendor Part No and Subs) PHASE IN: As follows or as mandated per AD: a) 500 H from January 31/2014 with a calendar cap of November 2015 for the units exceeding either 9600 H or 8420 L, whichever comes first, or b) No PHASE IN for all other HSTAs H COMPONENT or 8420 L COMPONENT whichever occurs first N/A NOTE: Remove HSTA from aircraft and send to vendor for the following: 1. Vendor to perform restoration and replace the parts that follow: Primary Housing P/N (included in P/N ) and Subs, Secondary Housing P/N (included in P/N ) and Subs, Secondary Spur Gear (CH2) P/N and Subs, Primary Pinion (CH1) P/N and Subs, and Secondary Pinion (CH2) P/N and Subs 2. Vendor to perform the following tasks: Functional Check of the Torque Limiters, Detailed Inspection of the Secondary Load Path Indicator, and Special Detailed Inspection of the Primary Spur Gear.

101 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 7 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval NOTE: When this task is performed, credit can be taken for task **, task * and MRB and their time reset to zero. Repeat interval for task ** is 120 M. Repeat interval for task * is 5000 H. Allowable Extension N/A RBS Rev. E 25 Add ** (two stars) Special Detailed Inspection of the Horizontal Stabilizer Trim Actuator (HSTA), Part No and Subs (Vendor Part No and Subs) 120 M COMPONENT N/A NOTE: Remove HSTA from aircraft and send to vendor for the following:

102 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 8 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension 1. Corrosion/oxidation and wear inspection of the following items: Primary Spur Gear (P/N ), ACME Screw (P/N ), Gearing (Primary P/N , Secondary P/N ), Gimbals (P/N / 057/ 056/ 055) and Gimbal Pins (Primary P/N / 068, Secondary P/N / 066), Secondary Spur Gear (P/N ), Attachment Shaft (P/N ), Nuts (Primary P/N , Secondary P/N ), Secondary Housing (P/N ), Primary Housing (P/N ), Stop Adjustable Extension (P/N ), Bearing (Thrust Roller P/N K81107TN and Needle P/N HK3516). 2. Visual inspection and replacement of seals, plastics, polymers, silicon, and lubricants. When this task is performed, credit can be taken for task * and MRB and their time reset to zero. Repeat interval for task * is 5000 H.

103 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 9 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension When task * (Restoration) is performed, or when P/N / 5 (Vendor P/N / 2) is upgraded to P/N (Vendor P/N ) as mandated by the AD CF , credit can be taken for task ** and its time reset to zero. Repeat interval for task ** is 120 M. RBR Rev. C 4 Add * Detailed Inspection of the Horizontal Stabilizer Trim Actuator (HSTA) Secondary Load Path Indicator, Part No and Subs (Vendor Part No and Subs) H COMPONENT N/A NOTE: When task *, VSB , or MRB are performed, credit can be taken for task * and its time reset to zero. Repeat interval for task * is 5000 H. RBR Rev. NC * Functional Test of the Flap Control Unit (All Drivers On Circuit) H 40 H

104 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 10 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev. F ** (two stars) Restoration of the Outboard Flap Actuator P/N / 114/ 115/ 116 where the component flight cycles are known 9600 L COMPONENT 50 L P/N / 114/ 115/ 116 for replaced actuators where the total component flight cycles are unknown. The 2000 landing interval to be calculated from the date of TR (May 12/2010). 2000L COMPONENT 50L PHASE IN: For actuators that have exceeded 9600 landings, replace the actuator within 300 hours of the date on TR or by Dec 31/2010, whichever occurs first. NOTE: During restoration, the following components must be replaced: Worm Gear, P/N Helical Gear, P/N or Retaining Key, P/N NAS558 P404 2 Torque Shunt Washer, P/N Thrust Bearing, P/N NTA1828 Thrust Washer, P/N TRA1828

105 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: 2 Page 11 Jun 29/2018 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RAP Rev. J ** (two stars) Functional Test of the Tail Tank Restrictor H 50 H RBR Rev. E * Operational Test of the Auxiliary Power Unit (APU) Fuel Feed Shutoff Valve and Negative G Shutoff Valve for Internal Leaks H 40 H RBR Rev. B * Operational Test of the Dump Valve. NOTE: See Section ; Rules Applicable to Certification Maintenance Requirements (Section ). 400 H 40 H NOTE A

106 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 12 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev. A Add ** (two stars) Detailed Inspection of the Wing Anti Ice Duct Piccolo Tube H 40 H NOTE A NOTE: Consideration should be given to accomplishing this task in conjunction with task which requires the removal of the wing leading edge. NOTE: See Section ; Rules Applicable to Certification Maintenance Requirements (Section ). RBR Rev. E ** (two stars) Functional Test of the Low Temperature Ground Wing Anti Ice (LTGWAIS) Overheat Circuit (Post SB ) H 40 H RBR Rev. E * Operational Test of the Cowl Anti Ice Failure Indication (Post SB ). 600 H 40 H

107 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 13 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev. A Add * Functional Test of the Leading Edge Thermal Switches 6400 H 40 H NOTE A NOTE: Consideration should be given to accomplishing this task in conjunction with task which requires the removal of the wing leading edge. NOTE: See Section ; Rules Applicable to Certification Maintenance Requirements (Section ).

108 CL 605 TIME LIMITS/MAINTENANCE CHECKS PART Revision: REISSUE Page 14 Sep 22/2017 Source Document Ref. No. Chapter 5 Task No. Task Title Task Interval Allowable Extension RBR Rev. E ** (two stars) Functional Test of the Engine Throttle Control Gearbox Part No / 007 See NOTE 40 H NOTE: Threshold (T) interval is 1600 H. First Repeat (R1) interval is 1600 H. Next Repeat (R2) is 1600 H. Subsequent Repeat intervals (R3) are 1000 H. RBR Rev. F2 Add 2 Part No H COMPONENT N/A

109 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Introduction INTRODUCTION 1. Scope and Purpose This report outlines the initial minimum scheduled maintenance/inspection requirements to be used in the development of an approved continuous airworthiness maintenance program for the airframe, engines (on wing engine only, model CF34 3B), systems, and components of the Bombardier Challenger CL 600 2B16 (CL 605). These MRB requirements are a basis from which each operator develops its own continuous airworthiness maintenance program. The responsible regulatory inspector shall ascertain that all of the applicable scheduled maintenance/inspection requirements in this report are included in the operator s initial continuous airworthiness maintenance program. This MRB Report was developed in accordance with Advisory Circular A, Maintenance Review Board Procedures." These tasks originate from analysis performed in accordance with Maintenance Program Development MSG 3 Revision 2 and are approved by the respective Working Groups and the Industry Steering Committee. The MSG 3 analysis considered the optional equipment that follows: Dual Global Positioning System (GPS) Flight Data Recorder (FDR) Ground Proximity Warning System (GPWS) Lightning Sensor System Second Radio Altimeter Split Scan Radar Third Data Concentrator Unit (DCU) Third Flight Management System (FMS) Third Inertial Reference System (IRS) Third VHF Unit Traffic Alert Collision Avoidance System (TCAS) Automatic Flight Information System (AFIS). 2. General Program Rules The purpose of the following general program rules is to provide standard guidelines common to the avionics, systems, powerplant, structures and zonal maintenance programs. Revision: REISSUE PART 3 Page Sep 22/2017

110 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Introduction A. Performance of the required tasks will be in accordance with the Instructions for Continued Airworthiness (Maintenance Manual, NDT Manual etc.) for the CL 605 aircraft. B. It is the responsibility of each operator to adjust their own maintenance program in accordance with their national requirements, and to comply with existing rules with respect to reporting to their airworthiness authority and to the manufacturer, events having effects on the continued airworthiness of the aircraft. C. An operator may elect to follow this approved maintenance program or to develop variations with approval of the operator s regulatory authority. This scheduled maintenance program has been developed through careful evaluation of airworthiness and economic aspects. Before seeking local regulatory authority approval of changes to the tasks and intervals prescribed, an operator should carefully consider the potential effect of each change on safety and reliability. When in doubt about the effect of any change, the operator should seek the advice of Bombardier Aerospace. D. Maintenance requirements of supplemental installations made by agencies other than the manufacturer must be established by the operator and/or that agency, with the appropriate regulatory authority. E. Unless otherwise stated component hours commence at the time of installation. F. Inspection intervals are given in either Flight Hours (H), Months (M), Landings (L), Engine Hours (Eng H) and also Component Hours (e.g. APU H). G. The MRB Report for the CL 605 aircraft is based on an average airplane utilization of 500 flight hours, 300 flight cycles (landings) within 12 months (calendar) time. Operators whose airplane utilization differs significantly from these parameters will need to reevaluate the intervals in this report with their local Regulatory Authority. H. Revisions to the MRB Report, which introduce new tasks or change existing tasks, must be evaluated for incorporation into an operator s maintenance program. Incorporation (where required) should be at the next suitable point in that program within the frequency designated for these tasks. However, operational penalties such as withdrawing the aircraft from service specifically to perform a new or reduced interval MRB Report task may be avoided by following the guidelines listed in paragraphs 1. and 2. below: 1. Where a new task is introduced to the MRB Report, the task should be introduced to the operator s program (where required) at any convenient point, but within 6 months of the date of receipt of the MRB Report revision by the operator. Initial task accomplishment should be within the interval designated for the task from the date of introduction to the operator s program. 2. Where a task interval is revised from a given value to a lower value, the revised task should be introduced into the operator s program within 6 months of the date of receipt of the MRB Report revision by the operator. It should be completed within Revision: REISSUE PART 3 Page Sep 22/2017

111 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Introduction the new task repeat interval or 6 months from the date of introduction to the maintenance program by the operator whichever is greater, the exception is if this rescheduling was to postpone the task beyond the pre revision task accomplishment deadline. The guidelines contained in this Rule do not apply to the Airworthiness Limitation Items. Intervals for tasks resulting from Airworthiness Directives or Service Bulletins are defined solely by the instructions contained in those documents and are not subject to this Rule. I. An operator may desire to perform scheduled maintenance tasks on a continuous or manufacturer s recommended maintenance program system; e.g. scheduled maintenance tasks would be phased into a number of individual packages. J. Note: Not Applicable to Ace Aviation Services, Corp. K. Definition of Month: Equivalent to Calendar Month, ie., all calendar controlled intervals are to be mm/yyyy; meaning anytime within the month it falls due, unless an item is certified as having a due date in dd/mm/yyyy. 3. Program Notes The purpose of the following general program notes is to provide a single source of information that may be referenced repeatedly throughout the Tasks and Intervals Tables in the avionics, systems, powerplant, structures and zonal maintenance programs. Note 2: Note 3: Note 7: Note 10: Note 11: Not to exceed Vendor recommendation. Task and interval may be part of the operator s National Regulatory Requirements. When a task has 2 intervals, one being NOTE 3, the most restrictive interval applies. When a National Regulatory Requirement does not exist, the MRB Report interval shall be followed. Functional Testing (Hydrostatic) and discard of the fire extinguisher containers will be accomplished in accordance with the operator s national requirements. The life limits and calculation of cycles of individual APU components are published in Allied Signal Component Maintenance Manual (CMM) GTCP36 100(E), Functional Testing (Hydrostatic) schedules and maximum Life Limit (Discard) of the oxygen cylinder shall be in accordance with Table 1 below (based on part numbers and DOT/Canadian markings). Restoration (Overhaul) schedule of the oxygen cylinder regulator shall be in accordance with Table 1 below or maximum of six (6) years from the date noted in the latest certification document, as applicable. Revision: REISSUE PART 3 Page Sep 22/2017

112 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Introduction Table 1 Hydrostatic Test, Regulator Overhaul, and Maximum Cylinder Life Limit Intervals P/N US DOT Cylinder Marking Hydrostatic Test Interval Transport Canada Cylinder Marking Oxygen Cylinder Regulator Overhaul Interval Maximum Cylinder Life Limit 895-xxxxx E 8162 SU Years 5 Years 15 Years xxx SP 8162 SU Years 5 Years 15 Years xxx SP 8162 SU Years 5 Years 15 Years xx DOT-3HT Years 6 Years 24 Years GSD1402 DOT-3HT Years 6 Years 24 Years Note 14: Discard at the manufacturer s expiration date. Note 15: Note 16: Note 17: Initial interval is calculated from the date of manufacture of the item. The intent of this MRBR task is also covered under a CMR or a Life Limit. Refer to TLMC section or An operator will have complied with the CMR or Life Limit and MRBR requirement by completing the task with the most restrictive interval. The ABSC Wheels Recommended Inspection Schedule found in this program note is copied from ABSC General Service Letter GS SL 36 Revision No. 7. Tire Change (Refer to CMM for Main Wheels and for Nose Wheels.) In case of discrepancy between this table and the wheel manufacturer s publication, the later takes precedent. Special Detailed Inspection Additional Periodic Inspection ABSC GS-SL-36 Section II paragraph D No. of Perform Inspection at Tire Landings Change # or at the Next Tire Change after noted No. of Landings X X Restoration Overhaul ABSC GS-SL-36 Section II Paragraph E Perform Inspection at Tire Change # or at the Next Tire Change after noted No. of Landings Revision: REISSUE PART 3 Page Sep 22/2017

113 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Introduction Special Detailed Inspection Additional Periodic Inspection ABSC GS-SL-36 Section II paragraph D No. of Perform Inspection at Tire Landings Change # or at the Next Tire Change after noted No. of Landings X X X X X X X X X X X X X X X X X Tire Change Restoration Overhaul ABSC GS-SL-36 Section II Paragraph E Perform Inspection at Tire Change # or at the Next Tire Change after noted No. of Landings Note 18: The task due time is calculated from the date noted in the certification documentation. Revision: REISSUE PART 3 Page Sep 22/2017

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115 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program Avionics, Systems and Powerplant Program 1. General This section provides the basic scheduled inspection tasks and frequencies applicable to the CL-605 Avionics, Systems and Powerplant. For definitions/terms used in this section, refer to Section , Program Glossary and Definitions. Maintenance Significant Items (MSI) and task references provided in this section are presented in sequence by the Airline Transport Association (ATA) assigned subject numbers. The following is a list of ATA Specification 100 assigned numbers and titles applicable to this section. They are provided for information and reference only. 21 Air Conditioning & Pressurization 45 Central Maintenance System 22 Auto Flight 49 Airborne Auxiliary Power 23 Communications 51 Structures (Drains/Pressure Relief Doors) 24 Electrical Power 52 Doors (Systems) 25 Equipment & Furnishings 54 Strut Doors (Systems) 26 Fire Protection 57 Wings (Drains/Pressure Relief Doors) 27 Flight Controls 71 Powerplant 28 Fuel 72 Engine 29 Hydraulic Power 73 Engine & Fuel Control 30 Ice and Rain Protection 74 Engine Ignition 31 Instruments 75 Engine Air 32 Landing Gear 76 Engine Controls 33 Lights 77 Engine Indicating 34 Navigation 78 Engine Exhaust 35 Oxygen 79 Engine Oil 36 Pneumatic 80 Engine Starting 38 Water/Waste MSG-3 (Rev. 2) logic was used to develop an on-wing scheduled maintenance program. With the exception of life-limited parts, this process does not normally include detailed off-wing shop maintenance procedures. Offwing detailed procedures are controlled by individual operators and are derived from the operator s reliability program or are in accordance with the manufacturer s Instructions for Continued Airworthiness (ICA) which are required by the Regulations. PART 3 Revision: REISSUE Page Sep 22/2017

116 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program 2. Program Rules The purpose of the following program rules is to provide standard guidelines common to the avionics, systems and powerplant maintenance programs. A. MSG-3 logic considers a hidden function in combination with an additional failure. For protective systems the additional failure is considered to be the system/component failure resulting in an abnormal condition that required the use of the protective system. B. MSG-3 logic was used to develop an on-wing scheduled maintenance program. With the exception of life-limited parts, this process does not include off-wing in-shop maintenance tasks. C. Operators are responsible for maintaining accurate records of all the inspection intervals described in section , paragraph 2.G. Operators must also monitor life-limited part status to ensure that life limits are not exceeded. D. Engine trend monitoring (if elected) procedures require the collection, at an interval not greater than 50 flight cycles, of certain engine parameters and ambient conditions, recorded during a high-power setting. From these parameters, a takeoff performance margin is calculated, given in degrees of interturbine temperature (ITT). The results of these performance checks are recorded and a performance trend is established. E. Servicing requirements specified in this MRB report were developed under MSG-3 and do not represent the total servicing for the aircraft. Consequently, operators should refer to section 3 of the Maintenance Planning Document (MPD) for additional servicing recommendations. F. Operators must perform a Detailed Inspection of the Forward Engine Mounts AMM and Aft Engine Mounts AMM when they do an unscheduled Removal and Installation of the Engine AMM PART 3 Revision: REISSUE Page Sep 22/2017

117 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program 3. List of Maintenance Significant Items (MSIs) The following table lists all the MSIs identified by BBA that were subjected to MSG-3 analysis. The table also describes which Working Group approved the analysis and whether a task was generated. MSI Title Working Group Task No Task Air Conditioning Distribution Systems X Pressurization Control Systems X Air Conditioning Cooling Systems X Temperature Control Systems X Automatic Flight Control System (AFCS) Avionics X Integrated Avionics Processing System Avionics X (IAPS) VHF Communication Avionics X HF Communication Avionics X Selective Calling System (SELCAL) Avionics X Audio Integrating System Avionics X Static Dischargers Avionics X Cockpit Voice Recorder (CVR) Avionics X Radio Tuning Unit (RTU) Avionics X AC Generation Avionics X DC Generation Avionics X Pilot s and Copilot s Seat Systems X Emergency Locator Transmitter (ELT) Systems X Insulation Systems X Fire Detection System Systems X Extinguishing System Systems X Ailerons Systems X Rudder Systems X Elevators Systems X Stall Protection System (SPS) Systems X Horizontal Stabilizer Systems X Horizontal Stabilizer Control System Systems X PART 3 Revision: REISSUE Page Sep 22/2017

118 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program MSI Title Working Group Task No Task Flaps Systems X Spoilers Systems X Fuel Storage Powerplant X Fuel Transfer Powerplant X Fuel Distribution Powerplant X Fuel Jettison System Powerplant X Fuel Indication & Warning Powerplant X Hydraulic System No.1 and No.2 Systems X Hydraulic System No.3 Systems X Hydraulic Indicating Systems X Airfoil Anti Icing System Systems X Anti Icing System Air Intake Systems X Pitot and Static Anti Icing System Systems X Windows and Windshields Systems X Ice Detection System Systems X C locks Avionics X Digital Flight Data Recorder (DFDR) Avionics X Engine Indication and Crew Alerting System Avionics X (EICAS) Landing Gear System Systems X Wheels and Brakes Systems X Antiskid System Systems X Steering System Systems X Position Indicating and Warning System Systems X Flight Compartment Lighting Avionics X Exterior Lighting Avionics X Emergency Lighting Avionics X System, Pitot Static and Temperature Avionics X Sensing Standby Pneumatic Instruments Avionics X Air Data System Avionics X PART 3 Revision: REISSUE Page Sep 22/2017

119 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program MSI Title Working Group Task No Task Standby Attitude and Direction Avionics X Electronic Flight Instrument System (EFIS) Avionics X Weather Radar System Avionics X Ground Proximity Warning System (GPWS) Avionics X Traffic Alert Collision Avoidance System Avionics X (TCAS) Radio Altimeter Avionics X Inertial Reference System (IRS) Avionics X VHF Navigation Avionics X Automatic Direction Finder (ADF) Avionics X Distance Measuring Equipment (DME) Avionics X Mode S Transponder Avionics X Global Positioning System (GPS) Avionics X Flight Management System (FMS) Avionics X Airborne Flight Information System (AFIS) Avionics X Oxygen System Avionics X Oxygen System (1 Bottle Configuration) Avionics X Bleed Air Distribution Systems X Bleed Air Indicating Systems X Central Maintenance System Avionics X APU Enclosure Assembly Powerplant X APU Mount System Powerplant X APU Inlet Duct Powerplant X APU Drains Powerplant X APU Compressor Inlet Section Powerplant X Compressor Section Powerplant X Combustor Section Powerplant X Turbine Section Powerplant X Gearbox Section Powerplant X Engine Fuel and Control Powerplant X Ignition and Starting System Powerplant X Pneumatic System Powerplant X Engine Controls Powerplant X Indicating Powerplant X Exhaust Powerplant X APU Oil System Powerplant X PART 3 Revision: REISSUE Page Sep 22/2017

120 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program MSI Title Working Group Task No Task Passenger Door Systems X Emergency Exit Systems X Cargo Compartment Door Systems X Service Doors Systems X Door Warning Systems X Core Cowl Doors Powerplant X Core Cowl Fixed Side Panels Powerplant X Exhaust Nozzle Fairing Assembly Powerplant X Forward Core Cowl Assembly Powerplan t X Engine Mounts Forward Powerplant X Engine Mounts Aft Powerplant X Fire Seals Powerplant X Electrical Harness Powerplant X Nose Cowl Assembly Powerplant X Air Inlet System (Fan Section) Powerplant X Compressor Section Powerplant X Combustion Section Powerplant X Turbine Section Powerplant X Accessory Drive Section Powerplant X Fuel Distribution Powerplant X Fuel Controlling Powerplant X Fuel Indicating Powerplant X Ignition System Powerplant X Compressor Control Powerplant X Throttle Controls, Engine mounted Powerplant X Throttle Controls, Airframe mounted Powerplant X Engine Indicating Powerplant X Exhaust Nozzle Assembly Powerplant X Thrust Reverser Control Powerplant X Oil System Powerplant X Starting Powerplant X PART 3 Revision: REISSUE Page Sep 22/2017

121 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program 4. Tasks and Intervals Table Format (RVSM Qualified A/C) Detailed information is given below concerning the format of the table listing the inspection requirements provided on subsequent pages. MSG 3 Task No. Route Chapter 5 Task No. Task Title Task Interval A. Column The first (left) column lists all MSG-3 tasks from avionics, systems and powerplant analysis which were used to make the chapter 5 task shown in column 2. XXXXXX-2YY are tasks assigned from CL-605 MSG-3 Analysis, where - XXXXXX is the MSI number - Y is 2 to show that the task is a MRB item Y is 6 for any non-production equipment and furnishings tasks - ZZ is the unit sequence identifier. The format for structures tasks and zonal tasks are defined in sections and , respectively. B. Column 2 The second column identifies either the MSG-3 Route or the relevant paragraph of the appropriate SSA reliability report. MSG-3 analysis allocates tasks against the following routes depending on the consequence of failure: - Route 5: Evident Safety Effects - Route 6: Evident Operational Effects - Route 7: Evident Economic Effects - Route 8: Hidden Safety Effects - Route 9: Hidden Non-Safety Effects. Where there are several consequences of failure, the route identifications will be separated by an oblique line, i.e. (6/8). PART 3 Revision: REISSUE Page Sep 22/2017

122 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Avionics, Systems and Powerplant Program C. Column 3 The third column lists the corresponding Chapter 5 task number and is of the form XX-XX-XX- YZZ. The components are as follows: - XX-XX-XX is the ATA breakdown number - Y has the number 1 if the task originated through system safety analysis Y has the number 2 if the task originated from MSG-3 analysis Y has the number 6 for any non-production equipment and furnishings tasks. - ZZ is the unit sequence identifier and begins at 01" for each variation to the full ATA number sequence contained in the Chapter 5 task number. D. Column 4 The fourth column contains the task title. This title includes the inspection level and a brief description of the area or items to be inspected. E. Column 5 The fifth column contains the inspection intervals. The inspection interval is defined from the last time that particular task was carried out. The inspection intervals in this column are in months (M), in landings (L), in flight hours (H), engine hours (Eng H) or component Hours (e.g. APU H). PART 3 Revision: REISSUE Page Sep 22/2017

123 CL-605 TIME LIMITS/MAINTENANCE CHECKS PART 3 SECTION AVIONICS, SYSTEMS AND POWERPLANT PROGRAM Tasks and Intervals Cover Revision: 2 Jun 29/2018 PART

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125 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 1 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Operational Test of the Pressure Bulkhead Check Valves. 800 H Operational Test of the Low Speed Detector for the Avionics Exhaust Fan. 800 H Restoration (Cleaning) of the Outflow Valve Poppet Area H Discard of the Primary Outflow Valve Air Filter H Operational Test of the Pressurization Control System (Manual Mode). 600H Operational Test of the EMER DEPRESS Switch/Light H ** Functional Test of the Outflow Valves H (two stars) NOTE Operational Test of the Ram Air Shutoff Valve H

126 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 2 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Operational Test of the SVL 4000 Rudder Actuator Brake H Lubrication of the Elevator Servo. 48 M

127 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 3 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Static Dischargers Functional Test (Bonding Check) of the Static Discharger 48 M Base Functional Test (Bonding Check) of the Nose Radome Lightning Strips. 48 M Discard of the Cockpit Voice Recorder (CVR) Underwater NOTE14 9 Locating Device (ULD) Battery Operational Test of the Cockpit Voice Recorder (CVR) 1200 H System. NOTE Operational Test of the Cockpit Voice Recorder (CVR) 36 M Underwater Locating Device (ULD). NOTE 3

128 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 4 Jun 29/2018 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Discard of the IDG Charge (Oil In) Filter Element H Discard of the IDG Scavenge (Oil Out) Filter Element H Discard of the APU Generator/Adaptor Filter Element. GTCP APU 2500 APU H Detailed Inspection of the Auxiliary Power Unit (APU) Generator/ Adaptor Dry Cavity. GTCP APU 750 APU H Operational Test of the Cabin Power Shut-Off Switch 24 M Functional Test of the Air Driven Generator (ADG) Heater NOTE: Whichever interval occurs first. NOTE: Whichever interval occurs first H or24m See NOTE * Operational Test of the Air Driven Generator (ADG) H or24m NOTE: Whichever interval occurs first. NOTE16 See NOTE Operational Test of the Transformer Rectifier Unit (TRU) 600 H Fan Functional Test (Capacity Check) of the Main Battery. 6 M NOTE 18

129 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 5 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test (Capacity Check) of the APU Battery. 6 M NOTE Operational Test of the DC Essential Bus. 800 H Operational Test of the Left and Right Battery Busses H Operational Test of the DC Emergency Bus. 800 H

130 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 6 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval / Operational Test of the Inertial Reel Control and Inertia 36 M Reel General Visual Inspection of the Pilot s/copilot s Seat 36 M Restraints / Operational Test of the Emergency Locator Transmitter (ELT) 24 M System. NOTE Discard of the Emergency Locator Transmitter Unit (ELT) NOTE 14 Battery Detailed Inspection of the Emergency Locator Transmitter 24 M (ELT) Battery. NOTE 3

131 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 7 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Visual Check of the Main Landing Gear (MLG) Sensing Element H Functional Test of the Main Landing Gear (MLG) Sensing 3200 H Element Functional Test of the Engine Fire Extinguisher Containers. 60 M NOTE 7 NOTE Functional Test (Hydrostatic) of the Portable Fire Extinguisher 144 M Container. NOTE * Discard the Discharge Cartridges of the Engine Fire Extinguisher Containers NOTE 2 NOTE Functional Test of the Engine Fire Shutoff Relay Circuitry H Functional Test (Weight Check) of the Portable 24 M Fire Extinguisher Container * Discard the Discharge Cartridges of the Auxiliary Power Unit (APU) Fire Extinguisher Container (Part No ) NOTE 2 NOTE 16

132 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 8 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Auxiliary Power Unit (APU) 60 M Fire Extinguisher Container. NOTE 7 NOTE Functional Test of the BOTTLE 1 and BOTTLE 2 ARMED 4800 H PUSH TO DISCH Switch/Lights Detailed Inspection of the Engine Fire Extinguisher Bottle Pressure Gauge. 24 M Detailed Inspection of the Fire Extinguishing System Lines. 48 M Functional Test of the Auxiliary Power Unit (APU) Fire Extinguishing System H Detailed Inspection of the Auxiliary Power Unit (APU) Fire Extinguisher Bottle Pressure Gauge. 24 M

133 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 9 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Aileron, Rudder, Elevator and 48 M Spoiler Control Cables in the Lower Forward Fuselage Detailed Inspection of the Aileron, Rudder, Elevator and Spoiler Control Cables in the Main Avionics Compartment. 48 M Detailed Inspection of the Aileron and Spoiler Control Cables 48 M in the Main Landing Gear (MLG) Wheel Well Detailed Inspection of the Aileron, Rudder, Elevator and Spoiler Control Cables in the Mid Lower Fuselage Detailed Inspection of the Rudder and Elevator Control Cables in the Lower Mid Fuselage Compartment Detailed Inspection of the Rudder and Elevator Control Cables in the Aft Equipment Compartment. 24 M Detailed Inspection of the Elevator Control Cables in the Vertical Stabilizer Detailed Inspection of the Rudder and Elevator Control Cables 48 M in the Fuselage/Stabilizer Section.

134 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 10 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Aileron Control Cables in the Outboard Wing Box. 48 M Detailed Inspection of the Aileron Control Cables in the Inboard Trailing Edge. 36 M Detailed Inspection of the Aileron Control Cables in the Outboard Trailing Edge. 36 M Detailed Inspection of the Aileron Control Cables in the Control Column. 48 M * Operational Test of the Roll Disconnect System. 800 H NOTE Operational Test of the Aileron Antifloat Mechanism. 800 H ** Detailed Inspection of the Aileron Flutter Dampers. 800 H (two stars) NOTE Functional Test of the Aileron Flutter Dampers H General Visual Inspection of the Single Rudder Control Path H Functional Test of the Load Limiter (in Vertical Stabilizer) Travels H General Visual Inspection of the Rudder Balance Spring H

135 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 11 Jun 29/2018 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval General Visual Inspection of the Elevator Power Control Unit (PCU) Centering Spring H Operational Test of the Elevator Jam Tolerant Mechanism H Operational Test of the Load Limiter (Vertical Stabilizer) H ** Functional Test of the Pitch Feel Simulator H (two stars) NOTE * Operational Test of the Elevator Disconnect System. 800 H NOTE General Visual Inspection of the Elevator Balance Springs H * Functional Test of the Elevator Flutter Dampers H NOTE ** Detailed Inspection of the Elevator Flutter Dampers. 800 H (two stars) NOTE Operational Test for the Single Channel of the Stall Protection Computer. 800 H Operational Test for the Dual Channel of the Stall Protection Computer. 800 H

136 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 12 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval , Detailed Inspection of the Horizontal Stabilizer Trim Actuator 48 M Assembly Lubrication of the Horizontal Stabilizer Pitch Trim Actuator. 48 M Operational Test of the Pitch Trim Switch. 800 H Operational Test of the Horizontal Stabilizer Trim System. 800 H , ** Operational Test (BITE) of the Horizontal Stabilizer Trim 800 H (two stars) Control System (HSTCS). NOTE Functional Test of the Asymmetry/Overspeed Detector and 800 H Brake Unit Detailed Inspection of the Flexible Drive Shaft Assembly H Lubrication of the Ball Nut of the Flap Actuators. 12 M Lubrication of the Flap Vane Actuator Rods. 12 M Lubrication of the Bent Up Trailing Edge (BUTE) Door 12 M Hinge Visual Check of the Inboard and Outboard Flap Actuators. 800 H Functional Test of the Inboard and Outboard Flap Actuators H

137 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 13 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Lubrication of the Flight Spoiler Flexshaft and Control Cable Ends. 400 H

138 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 14 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval General Visual Inspection of the Fuel Access Panels. 600 H General Visual Inspection of the Fuel Drain Valves. 600 H General Visual Inspection of the Water Drain Valves. 600 H General Visual Inspection of the Fuel Tank Exterior. 600 H General Visual Inspection of the Saddle Tank Drain. 600 H General Visual Inspection of the Gravity Filler Cap. 600 H Functional Test of the Vent Line Shrouds Functional Test of the Motive Flow Line Shrouds Functional Test of the Fuel Feed Line Shrouds Functional Test of the Forward and Aft Auxiliary Tanks Interspace and Fuel Transfer Line Shrouds Visual Check of the Vent and Distribution Shroud Drains for Blockage and Leakage 600 H Functional Test of the Rotor Burst Protection Pressure Switch H Operational Test of the Tail Tank Transfer Shutoff Valve H

139 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 15 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Operational Test of the Tail Tank Secondary Transfer Pump H Discard of the Fuel Feed Line Filter of the Auxiliary Power Unit (APU). GTCP APU 1000 APU H Operational Test of the Collector Tank Check Valve Operational Test of the Engine Firewall Fuel Shutoff Valve. 400 H Operational Test of the Engine Firewall Fuel Shutoff Valve for Leaks. 800 ENG H * Operational Test of the Dump Valve. 400 H 8 NOTE 16

140 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 16 Jun 29/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Visual Check of the Filter Differential Pressure Indicator. 600 H Operational Test of the Hydraulic Firewall Shutoff Valve. Part Numbers B / 453/ 454/ 454A Part Number B and Subs 600 H 1600 H

141 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 17 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Sensor Detection Circuit H ** Functional Test of the Low Temperature Ground Wing 2400 H (two stars) Anti Ice (LTGWAIS) Overheat Circuit (Post SB NOTE ) Functional Test of the Windshield Rain Repellent Layer. 600 H NOTE: This task applies to Sully Glass Faceply Windshields, Part No XX and Sierracin Glass Faceply Windshields, Part No and Subs Operational Test of the Ice Detection System. 800 H

142 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 18 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Discard of the Digital Flight Data Recorder (FDR) Underwater Locating Device (ULD) Battery. NOTE Operational Test of the Digital Flight Data Recorder (FDR) 36 M Underwater Locating Device (ULD). NOTE Functional Test of the Flight Data Recorder (FDR) Dedicated Sensors (Post SB ) Functional Test of the Flight Data Recorder (FDR) Force Sensors (Post SB ). NOTE: The 96 month task interval starts at the incorporation date of SB Operational Test of the Audio Warning Control Panel 600 H Operational Test of the Electronic Flight Instrument System (EFIS) H / Operational Test of the Basic Reversionary Control Panel. 24 M

143 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 19 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Landing Gear Emergency Extension System. 800 H Functional Test of the Main Landing Gear (MLG) Shock Strut Assembly H Functional Test of the Nose Landing Gear (NLG) Shock Strut Assembly H Lubrication of the Main Landing Gear (MLG). 400 H Lubrication of the Nose Landing Gear (NLG). 400 H Lubrication of the Main Landing Gear (MLG) Doors. 400 H Lubrication of the Nose Landing Gear (NLG) Doors. 400 H Detailed Inspection of the Landing Gear Emergency Extension Cable in the NLG Wheel Well. 48 M Detailed Inspection of the Landing Gear Emergency Extension Cable in the Forward Avionics Compartment. 48 M Detailed Inspection of the Landing Gear Emergency Extension Cable in the Main Avionics Compartment. 48 M

144 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 20 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Landing Gear Emergency Extension Cable in the Mid Lower Fuselage Compartment Detailed Inspection of the Landing Gear Emergency Extension Cable in the MLG Wheel Well. 48 M General Visual Inspection of the Main Landing Gear (MLG) Assembly. 600 H General Visual Inspection of the Nose Landing Gear (NLG) Assembly. 600 H Detailed Inspection of the Main Landing Gear (MLG) Assembly Detailed Inspection of the Nose Landing Gear (NLG) Assembly Restoration (Overhaul) of the Main Landing Gear (MLG) T 192 M Assembly. R

145 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 21 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Restoration (Overhaul) of the Nose Landing Gear (NLG) T 192 M Assembly. R , Functional Test of the Brake Accumulators. 800 H Special Detailed Inspection of the Main Landing Gear Wheels. NOTE Special Detailed Inspection of the Nose Landing Gear Wheels. NOTE Lubrication of the Main Landing Gear (MLG) Brake Control Valve Assembly. 800 H Detailed Inspection of the Brake Wear Pins. 600 H Detailed Inspection of the Main Landing Gear Wheels. Every Tire Change Restoration (Overhaul) of the Main Landing Gear Wheels. NOTE Detailed Inspection of the Nose Landing Gear Wheels. Every Tire Change Restoration (Overhaul) of the Nose Landing Gear Wheels. NOTE Operational Test of the Nosewheel Steering Selector and Arming Valve. 400 H

146 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 22 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Operational Test of the Nosewheel Steering Electronic Control Module (ECM), Part No Vendor Part No / H

147 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 23 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Emergency Lights Power Supply. 12 M NOTE Operational Test of the Emergency Lights. 12 M

148 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 24 Jun 29/2018 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Pitot Static System. NOTE: Mfg TLMC 36 M 24 M Detailed Inspection of the Pitot Static Probes. NOTE: Mfg TLMC 36 M 24 M Servicing of the Visual Drains. 24 M NOTE Functional Test of the Integrated Standby Instrument. 48 M

149 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 25 Jun 29/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional (Hydrostatic) Test of the Oxygen Cylinder Assembly. NOTE NOTE 11 NOTE Operational Test of the Passenger Oxygen System (Effectivity: 36 M , 5306, 5310, 5316, 5331 and Subs) Operational Test of the Crew Oxygen Mask. 36 M / Restoration of the Crew Oxygen Mask Regulator Assembly. 72 M NOTE Discard of the Oxygen Cylinder NOTE 11 NOTE General Visual Inspection of the Oxygen Indication System. 24 M / Restoration of the Oxygen Cylinder Regulator. NOTE 11

150 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 26 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Passenger Door Latch Mechanism H Lubrication of the Passenger Door (External). 400 H Lubrication of the Passenger Door (Internal) H Operational Test of the Latch Mechanism of the Overwing Emergency Exit Door. 36 M Functional Test of the EXIT PULL Sign. 36 M /8/ Lubrication of the Emergency Exit Door. 24 M Operational Test of the ADG Door Operating Mechanism H

151 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 27 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Core Blow Out Doors H General Visual Inspection of the Drains Mast and Channels. 600 H Operational Test of the Drains Mast and Channels. 600 H Detailed Inspection of the Thrust Reverser Slider Blocks H General Visual Inspection of the Engine Fire Seals H Lubrication of the Ballscrew Actuators Support Bushings. 800 H Detailed Inspection of the Ballscrew Actuator Support Fittings H

152 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 28 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval General Visual Inspection of the Fan Blades. 600 Eng H General Visual Inspection of the Fan Spinner. 600 Eng H Detailed Inspection of the Engine Master Chip Detector 100 Eng H Indicator General Visual Inspection of the Engine Fan Case Forward 3200 Eng H Mounts General Visual Inspection of the Fan Shroud Core Material. 600 Eng H General Visual Inspection of the Exterior of the Engine Fan Case and Blade Containment Case Eng H Special Detailed Inspection (Borescope) of the Compressor Blades Eng H Special Detailed Inspection (Borescope) of the Variable and Stationary Vanes Eng H Lubrication of the Variable Geometry Linkage Rod End 6 Bearings. 800 Eng H

153 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 29 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Special Detailed Inspection (Borescope) of the Combustor Liner Eng H Special Detailed Inspection (Borescope) of the Stage 1 Nozzle Eng H General Visual Inspection of the Thermal Blanket. 600 Eng H General Visual Inspection of the Rear Main Mount Eng H Special Detailed Inspection (Borescope) of the High Pressure Turbine Stage 1 and 2 Rotor Blades Eng H Visual Check of the Exhaust Centerbody Eng H

154 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 30 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Discard of the Fuel Filter Element Eng H Visual Check of the Engine Fuel Filter Mechanical Actual Bypass Indicator Eng H Detailed Inspection of the Engine Fuel Manifold Eng H Special Detailed Inspection (Borescope) of the Fuel Injectors Eng H Detailed Inspection of the Main Fuel Control Eng H

155 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 31 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Ceramic on the High Voltage Igniters 1200 Eng H

156 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 32 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Functional Test of the Gearbox Assembly Eng H General Visual Inspection of the Engine Throttle Push/Pull Control Assembly H

157 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 33 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Exhaust Nozzle Assembly H Lubrication of the Thrust Reverser Ballscrew Actuators. 800 H Lubrication of the Thrust Reverser Flexshafts H Detailed Inspection of the Flexshaft Drive H Functional Test of the Auto Throttle Retarder System, Throttle Locks and Bellcrank H

158 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 34 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Visual Check of the Oil Filter Impending Bypass Indicator. 600 Eng H Discard of the Oil Filter Element Eng H Functional Test of the Oil Filter Impending Bypass Sensor Eng H Functional Test of the Engine Master Chip Detector Eng H Visual Check of the C Sump Drain Outlet. 600 Eng H Detailed Inspection of the C Sump Scavenge Screens (Pre GE SB ) Eng H

159 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 35 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval / Detailed Inspection of the Drain Plug Magnetic Chip Detector. 600 H / Discard of the Air Turbine Starter (ATS) Oil. 600 H

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161 1. General ACE AVIATION SERVICES, CORP. CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE REVIEW BOARD REPORT HONEYWELL APU (CL) PROGRAM This section provides the basic scheduled maintenance inspection tasks and frequencies applicable to the CL 604 Honeywell APU (CL). MSG 3 (Rev ) logic was used to develop this on wing scheduled maintenance program. This process does not normally include detailed off wing shop maintenance procedures. Off wing detailed procedures are controlled by individual operators and are derived from the operator s reliability program or are in accordance with the manufacturer s Instructions for Continued Airworthiness (ICA) which are required by the Regulations. 2. List of Maintenance Significant Items (MSIs) Refer to section PART Page 1 Revision: REISSUE Sep 22/2017

162 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE REVIEW BOARD REPORT PART Revision: 2 Page 2 Jun 29/2018 MSG 3 Task No. Route Chapter 5 Task No. Task Title Task Interval Operational Test of the Auxiliary Power Unit (APU) Enclosure Drains Detailed Inspection of the Auxiliary Power Unit (APU) Enclosure Assembly General Visual Inspection of the Auxiliary Power Unit (APU) Inlet Duct Screens General Visual Inspection of the Auxiliary Power Unit (APU) Lower Rubber Boot General Visual Inspection of the Auxiliary Power Unit (APU) Upper and Lower Inlet Duct Operational Test of the Auxiliary Power Unit (APU) Drains Discard of the Auxiliary Power Unit (APU) Compressor Rotor Detailed Inspection of the Auxiliary Power Unit (APU) Compressor Housing Shroud Discard of the Auxiliary Power Unit (APU) Turbine Rotor APU H 750 APU H 2250 APU H 2250 APU H 3000 APU H 3000 APU H APU H At next component access opportunity APU H

163 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE REVIEW BOARD REPORT PART Revision: REISSUE Page 3 Sep 22/2017 MSG 3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Auxiliary Power Unit (APU) Containment Ring and Turbine Housing General Visual Inspection of the Auxiliary Power Unit (APU) Fuel System Components. At next component access opportunity 750 APU H General Visual Inspection of the Auxiliary Power Unit (APU) Fuel Filter Differential Pressure Indicator. 750 APU H Detailed Inspection of the Auxiliary Power Unit (APU) Igniter Plug APU H Operational Test of the Auxiliary Power Unit (APU) External Remote Switch APU H Restoration (Overhaul) of the Auxiliary Power Unit (APU) Starter Motor APU H / / Detailed Inspection of the Auxiliary Power Unit (APU) Exhaust Systems Detailed Inspection of the Auxiliary Power Unit (APU) Exhaust Nozzle APU H At next APU removal / Detailed Inspection of the Auxiliary Power Unit (APU) Exhaust Shield and Visor Assembly APU H

164 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE REVIEW BOARD REPORT PART Revision: REISSUE Page 4 Sep 22/2017 MSG 3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Auxiliary Power Unit (APU) Magnetic Chip Detector. 750 APU H Discard of the Auxiliary Power Unit (APU) Oil Filter Element APU H Discard of the Auxiliary Power Unit (APU) Oil APU H

165 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program Structural Program 1. General This section provides the basic scheduled inspection tasks and frequencies applicable to the aircraft structure. According to the analysis procedure, for each Structural Significant Item (SSI), various inspection levels have been considered with the aim of selecting the lowest inspection level compatible with the type of damage and the expected damage growth. Therefore the various inspection levels, General Visual Inspection (GVI), Detailed Inspection or Special Detailed Inspection can be selected for one SSI. Refer to the definitions in Section When a General Visual Inspection level has been selected for an SSI, these inspection requirements are considered adequately covered by the Zonal Program inspections provided the inspection interval does not exceed that of the SSI inspection task. These inspection requirements are therefore transferred to the Zonal Program to avoid duplication of inspection tasks to those given by the zonal program as described in Section of this document. Should the inspection interval of a GVI task generated from analysis of an SSI be lower than that of the corresponding zonal program inspection, the task does not qualify for transfer to the Zonal Program and must be retained as a specific structure inspection. The structure inspection tasks selected for fatigue are derived from damage tolerance evaluation according to the criteria defined by Federal Aviation Regulation FAR , Amendment 45, with the aim of ensuring timely damage detection. The following types of damage have been considered for establishment of this program: Fatigue Damage (FD) Environmental Deterioration (ED) Accidental Damage (AD) For fatigue, the damage initiation and subsequent crack growth is primarily dependent upon the ground air ground loading variation occurring once per flight. Therefore, flight cycles are used as the unit for inspection threshold and repeat intervals. For environmental deterioration, as corrosion is mainly age dependent, inspection threshold and repeat intervals are based on calendar time. For environmental deterioration likely to occur on a random basis (e.g. stress corrosion, corrosion due to fluid spillage, or resulting from accidental damage), inspections shall be applied at each repeat interval without a separate threshold. For other kinds of environmental deterioration, for which the development is expected to have systematic characteristics related with the increasing age of the aircraft, the inspection shall be applied at a separately determined threshold followed by the repeat interval. PART 3 Revision: REISSUE Page Sep 22/2017

166 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program For accidental damage, it is considered that major damage such as that caused by bird impact, or ground handling equipment, will be detected by routine inspections. Minor damage which could have an impact on fatigue and/or corrosion damage is considered during analysis. There is no separate inspection task resulting from accidental damage analysis. This section also includes MSG 3 tasks that were absorbed by other tasks. These tasks are either duplications, or a combination of adjacent or complementary tasks. They are also not covered by any tasks cards. 2. Program Rules The purpose of the following program rules is to provide standard guidelines to the structures maintenance program. A. All aircraft must be inspected in accordance with the requirements of this section and with the requirements of the Zonal Program. B. The threshold is the time when the first inspection is due. It is indicated with a T" in the Task Interval column. C. For repeat inspection, the interval commences at the time of the last inspection performed. It is indicated with a R" in the Task Interval column. D. Normal cleaning procedures are to be used prior to Detailed Inspections and specified cleaning procedures prior to Special Detailed Inspections. Sealant and corrosion protection finishes should be removed only when specified. E. Operators shall report all structural findings to the manufacturer. F. For information concerning SSI inspections refer to Bombardier supporting publications such as CL 605 Maintenance Planning Document, Maintenance Manual, Non Destructive Test Manual, Structural Repair Manual, etc. G. No repeat inspection interval shall be escalated until at least three aircraft in the model fleet have been inspected within the initially defined interval listed in this document. H. Airworthiness Limitation Instructions: Additional structural tasks for Principal Structural Elements (PSE) and Safe life structure are listed in the Structural Airworthiness Control Document, Bombardier Engineering Report RAS 604DX 990", titled CL 605 Airworthiness Limitation Instructions (ALI). ALI tasks refer to mandatory fixed intervals resulting from fatigue and damage tolerance analysis performed by Bombardier Structural Engineering in coordination with Transport Canada Engineering. The operator must consider both report (MRB/ALI) requirements when developing and maintaining their maintenance programs and shall not change the requirements without the approval of their regulatory authority (Engineering/Certification discipline s). PART 3 Revision: REISSUE Page Sep 22/2017

167 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program 3. List of Structural Significant Items (SSIs) This section contains a list of all the SSIs sorted in ATA sequence by SSI number. Each SSI is covered by at least one MSG 3 task. SSI No. SSI Description Main Landing Gear Main Landing Gear Door Hinges and Fasteners Nose Landing Gear Wheels Passenger Door External Ski Passenger Door Fittings and Attachments Passenger Door Internal Structure Overwing Emergency Exit Door External Skin Overwing Emergency Exit Door Latch Fittings and Door Stops Overwing Emergency Exit Door Internal Structur Cargo Compartment Door External Skin Cargo Compartment Door Stop Fittings Cargo Compartment Door Internal Structure Frames FS169.0 and FS Forward Pressure Bulkhead FS Frames below WL110.0 (Window Structure) FS210.0, FS220.0, FS235.0, FS250.0 and FS Flight Compartment Roof Internal Structure Internal Skin and Stringers below WL110.0 (Window Structure) Pilot Bulkhead and Frame FS Floor Structure from FS169.0 to FS280.0 Beams, Cross members and Panels External Skin from FS169.0 to FS280.0, including Pressurized Access Panels Forward Jacking Point FS Windshield and Side Window Surround Structure and Retaining Plates NLG Wheel Well Structure including Webs and Trunnion Fittings NLG Internal Box Structure including Web and Diagonal Beam FS169.0 to FS Sills, Frames and Skin around Passenger Door Cutout Fittings and Hinge on Fuselage for Passenger Door. PART 3 Revision: REISSUE Page Sep 22/2017

168 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program SSI No. SSI Description Floor Support Structure from FS280.0 to FS409.0 (including Floor Beams, Struts, Floor sills and Seat Rails) Internal Skin Panels, Frames and Stringers in Upper Fuselage from Floor to Top Centerline, FS280.0 to FS439.0, LH and RH Internal Skin Panels, Frames and Stringers in Lower Fuselage from Floor to Bottom Centerline, FS280.0 to FS409.0, LH and RH External Top Skins Panels, FS280.0 to FS439.0 and STR8 LH to STR8 RH External Side and Lower Skin Panels from FS280.0 to FS439.0 and from STR8 LH to STR8 RH Internal Forward Keel Beam, FS364.0 to FS Forward Keel Beam Pressure Box, FS394.0 to FS409.0 and Keel Beam Lugs and Links, FS394.0 to FS Aft Keel Beam, FS513.0 to FS Internal Skin Panels, Frames and Stringers in Upper Fuselage, FS409.0 to FS559.0, above WL External Upper Skin Panels, FS439.0 to FS559.0, STR 17L to 17R (Floor Level) Frame FS409.0 Forward Face below Floor Level (including Bulkhead Web and Floor Support Posts) Frame FS409.0 Aft Face below Floor Level (including Bulkhead Web and Frame Cap Members) Sills, Frames and Skin around Emergency Exit Door Cutout Emergency Exit Door Fittings Emergency Exit Door Fittings Skin Assembly at Window Surround Sill Structure, FS409.0 to FS559.0, BL36 to BL47, LH and RH Frame FS424.0 Wing to Fuselage Attachment Lugs Frame FS Wing to Fuselage Attachment Lugs Frame FS513.0 below Floor level Frame FS513.0 Wing Attachment Links Floor Wing Tie Beam at FS Pressure Floor Skin Panel, FS409.0 to FS559.0 and BL36L to BL36R (Top Surface) Pressure Floor Skin Panel, FS409.0 to FS559.0 and BL36L to BL36R (Lower Surface) Pressure Floor Support Beams, FS409.0 to FS559.0, BL0, BL9, BL18.6, BL27and BL35.4 PART 3 Revision: REISSUE Page Sep 22/2017

169 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program SSI No. SSI Description Underfloor Longeron Assembly, FS409.0 to FS MLG Uplock Structure, FS513.0 to FS559.0 and below WL73 LH and RH Forward Auxiliary Tank External Forward Auxiliary Tank Internal Frame FS559.0 Aft Face Below Floor Level (including Bulkhead Web and Floor Support Posts) Frame FS559.0 Forward Side below Floor Level (including Bulkhead Web and Frame Cap Members) Rear Pressure Bulkhead FS621.0 Aft Side (including Web, Stiffeners and Lower Transverse Beams) Drag Angles between FS718.0 to FS820.0, L and R Rear Pressure Bhd FS621.0 Forward Side above Floor Level (WL73.5) Floor Support Structure FS559.0 to FS Engine Support Beam Structure Internal Lower Fuselage Structure FS559.0 to FS621.0 (including Frames, Stringers and Skin Panels but not Rear Press. Bhd) Forward Side of Rear Pressure Bhd FS621.0 below Floor Level (WL73.5) Cargo Compartment Door Cutout Internal Surround Structure External Skin around Cargo Compartment Door Cutout Cargo Compartment Door Stop Fittings on Fuselage Internal Upper Structure above Floor FS559.0 to FS621.0 (including Frames, Stringers and Skin Panels) Internal Structure FS621.0 to FS755.0 (including Frames Stringers and Skin Panels) Frame FS755.0 Forward Side (including Frame Cap, Web and Stiffeners) External Skin around APU Exhaust External Upper Skin Panel FS559.0 to FS755.0 and STR6L to STR6R External Side Skin Panels FS559.0 to FS755.0 and STR6 to STR20, L and R External Lower Skin Panels FS559.0 to FS Aft Auxiliary Tank External Aft Auxiliary Tank Internal External Skin Panels of Fuselage/Stabilizer Section FS755.0 to VS67.5% Fuselage Frame VS67.5% Aft Side PART 3 Revision: REISSUE Page Sep 22/2017

170 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program SSI No. SSI Description Internal Structure FS755.0 aft side to VS67.5% fwd side (including Frames, Stringers and Skin Panels) Tail Tank Internal Structure Tail Tank External Skins and Floor Structure Tail Tank Forward Bulkhead Forward Face Tail Tank Aft Bulkhead Aft Face Forward Engine Mount Assembly Pylon Box External Skins Pylon Canted Ribs and Drag Braces Aft Engine Mount Structure Fittings, Trim Actuator Support, Bathtub and Pivot, and Upper and Lower Skin Splices Front Spar Assembly and Splice Horizontal Stabilizer Rear Spar, Splice and Hinge Fittings Horizontal Stabilizer Upper Skin External Horizontal Stabilizer Lower Skin External Horizontal Stabilizer, Internal Structure including Fittings and Skin Splices Horizontal Stabilizer Trim Actuator and Pivot and Actuator Attach Bolts Elevator Front Spar and Hinge Fittings Elevator Structure (excluding Front Spar and Fittings) Elevator Hinge Bolts Vertical Stabilizer Front Spar to Fuselage Attachment Fittings and Splice Straps Vertical Stabilizer Forward Side of Front Spar from Fuselage to Tip Vertical Stabilizer Aft Side of Rear Spar from Fuselage to Tip and Rudder Hinge Fittings on Vertical Stabilizer Vertical Stabilizer External Skins Vertical Stabilizer Top Canted Rib, Horizontal Stabilizer Pivot Fittings on Vertical Stabilizer and Horizontal Stabilizer Trim Actuator Pivot Structure Vertical Stabilizer Internal Structure Rudder Structure (excluding Front Spar and Fittings) Rudder Front Spar and Attachment Fittings Rudder Hinge Bolts Windshield and Side Window PART 3 Revision: REISSUE Page Sep 22/2017

171 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program SSI No. SSI Description Center Wing Front Spar Forward Side LWS50 to RWS Center Wing Front Spar Aft Side LBL45 to RBL Center Wing Rear Spar Forward Side LBL45 to RBL Center Wing Rear Spar Aft Side LWS48 to RWS Center Wing Upper Plank External Surface LBL47 to RBL Center Wing Lower Plank External Surface LBL45 to RBL Center Wing Upper Plank, Lower Plank and Ribs Internal LBL45 to RBL Wing Front Spar Forward Side WS50 to WS Wing Front Spar Aft Side BL45 to Canted WS Wing Rear Spar Forward Side BL45 to WS Wing Rear Spar Aft Side WS48 to WS Center Wing Upper Plank, Lower Plank and Ribs Internal BL45 to Canted WS Dry Bay Internal Structure Canted WS314.5 to WS Upper Wing Plank External BL47 to WS Lower Wing Plank External BL45 to WS Wing Skin Upper and Lower External Canted WS314.5 to WS Auxiliary Spar Assembly Internal Wing Planks, Skins and Batt Ribs between Rear Spar and Auxiliary Spar WS48 to WS MLG Trunnion Fitting MLG Mounting Fittings on Rib WS MLG Side Brace Attach Fitting Front Spar Bayonet Fitting External Rear Spar Bayonet Fitting External Wing to Fuselage Attach Fitting FS Wing to Fuselage Attach Fitting FS Wing to Fuselage Attach Fitting FS Flap Box Attach Fittings Inboard Flap Flap Box Attach Fittings Outboard Flap Aileron Hinge Fittings Ground Spoiler Hinge Fittings PART 3 Revision: REISSUE Page Sep 22/2017

172 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program SSI No. SSI Description Flight Spoiler Hinge Fittings Wing to Fuselage Attachment Bolts Winglets Skins, Spars, Attach Fittings and Ribs Inboard Flap Structure (excluding Hinge and Vanes) Inboard Flap Hinge Arms Inboard Flap Vane Actuator Sliding Beams and Carriages Inboard Flap Vane External Outboard Flap Structure (excluding Hinge and Vane) Outboard Flap Hinge Arms Outboard Flap Vane External Inboard Flap Hinge Boxes Outboard Flap Hinge Boxes Inboard Flaps Hinge Bolts Outboard Flaps Hinge Bolts Aileron Structure Aileron Hinge Bolts Ground Spoiler External Hinge Ribs, Spar and Skins Flight Spoiler External Hinge Fittings, Spar and Skins Ground Spoiler Hinge Bolts Flight Spoiler Hinge Bolts Powerplant Core Cowl Door Hinge Fittings Powerplant Nacelle Service Pylon Engine Mount Forward Engine Mount Aft Powerplant Nose Inlet Cowl Exhaust Thrust Reverser PART 3 Revision: REISSUE Page Sep 22/2017

173 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Structural Program 4. Tasks and Intervals Table Format Detailed information is given below concerning the format of the table listing the inspection requirements provided on subsequent pages. MSG 3 Task No. Route Chapter 5 Task No. Task Title Task Interval A. Column The first (left) column lists all MSG 3 tasks from structures analysis which were used to make the Chapter 5 task shown in column 2. These task numbers are of the form XXXXXXX 2YY for structures tasks, where XXXXXXX is the SSI number, 2" indicates a MRB item and YY is the unit sequence identifier. The format for avionics, systems, powerplant tasks and zonal tasks are defined in sections and , respectively. B. Column 2 The second column identifies the type of damage analysis used to generate the MSG 3 task(s) listed in column 1. This column also identifies whenever the corresponding AMTOSS/NDT No. procedure includes application of corrosion inhibiting compound (CIC) by listing CPCP". C. Column 3 The third column lists the corresponding Chapter 5 task number and is of the form XX XX XX YZZ, where XX XX XX is the ATA breakdown number, Y is designated as 2" to indicate a MRB item, and ZZ is the unit sequence identifier. The unit sequence identifier begins at 01" for each variation to the full ATA number sequence contained in the Chapter 5 task number. D. Column 4 The fourth column contains the task title. This title includes the inspection level and a brief description of the area or items to be inspected. E. Column 5 The fifth column contains the inspection intervals (T Threshold, R Repeat). The inspection intervals in this column are in months (M), in landings (L) or in flight hours (H). PART 3 Revision: REISSUE Page Sep 22/2017

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175 CL-605 TIME LIMITS/MAINTENANCE CHECKS PART 3 SECTION STRUCTURE PROGRAM Tasks and Intervals PART Cover Revision: REISSUE Sep 22, 2017

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177 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 1 Jun 29/2018 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED CPCP Special Detailed Inspection of the Main Landing Gear Side Brace Fitting Shaft, Part No. 601R only. T 48 M R 48 M ED Detailed Inspection of the Hinge and Fasteners of the Main Landing Gear Door. T R 48 M

178 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision:2 REISSUE Page 2 Jun 29/2018 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Fittings and Attachments of the Passenger Door ED CPCP Detailed Inspection of the Internal Structure of the Passenger Door. T R T R 48 M 48 M ED CPCP Detailed Inspection of the Internal Structure of the Overwing Emergency Exit Door. T R 48 M AD/ED Detailed Inspection of the Door Frame Machined Fittings, Stops and Hooks of the Overwing Emergency Exit Door. T R 48 M 48 M ED Detailed Inspection of the Stop Fittings of the Cargo Compartment Door ED CPCP Detailed Inspection of the Internal Structure of the Cargo Compartment Door. T R T R 48 M

179 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 3 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Internal Fuselage, Frames and Forward Bulkhead FS to FS T R 48 M ED Detailed Inspection of the Internal Fuselage (Skins and Structure) FS to FS Below the Floor. T R 48 M ED Detailed Inspection of the Internal Fuselage, Skin and Structure FS to FS Above the Floor. T R 192 M 48 M ED Detailed Inspection of the Beams, Crossmembers and Panels of the Floor Structure FS169 to FS280. T R 48 M ED Detailed Inspection of the Forward Jacking Point FS278. T R 48 M ED Detailed Inspection of the NLG Wheel Well Structure ED Detailed Inspection of the NLG Internal Box Structure FS169 to FS235. T R T R 48 M 48 M 48 M 48 M ED CPCP Detailed Inspection of the Aft Side of the Pilot Bulkhead and Frame FS Above WL73.50 (Floor Level). T R 240 M

180 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 4 Jun 29/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval AD/ED CPCP Detailed Inspection of the Sills, Frames and External Skin around the Passenger Door Cutout. T R 48 M AD/ED CPCP Detailed Inspection of the Fittings and the Hinge on the Fuselage for the Passenger Door. T R 48 M 48 M AD/ED CPCP Detailed Inspection of the Floor Support Structure FS280 to FS409, as Visible with the Floor Panels Installed. T R 48 M AD/ED CPCP Detailed Inspection of the Floor Support Structure FS280 to FS409. T R ED CPCP Detailed Inspection of the Internal Fuselage (Skins and Structure) FS to FS Above the Floor. T R 240 M ED CPCP Detailed Inspection of the Lower Internal Skin and Fuselage Structure FS280 to FS409, as Visible with the Floor Panels Installed. T R 48 M ED CPCP Detailed Inspection of the Internal Mid Fuselage (Skin and Structure, FS Bulkhead Forward Face and the External Surfaces of the Forward Auxiliary Fuel Tank) FS to FS Below the Floor. T R ED CPCP Detailed Inspection of the Internal Forward Keel Beam FS364 to FS ED Detailed Inspection of the Forward Keel Beam Pressure Box and Keel Beam Lugs and Links FS394 to FS409. T R T R

181 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 5 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval AD/ED CPCP Detailed Inspection of the Aft Keel Beam FS513 to FS559. T R 48 M 48 M ED Detailed Inspection of the Aft Face of the Frame below the Floor FS409. T R ED Detailed Inspection of the Sills, Frames and External Skin around the Emergency Exit Door Cutout. T R ED Detailed Inspection of the Fittings of the Emergency Exit Door. T R 48 M ED CPCP Detailed Inspection of the Floor Sill Area Over the Wing Box FS409 to FS559. T R 48 M ED Detailed Inspection of the Wing to Fuselage Attachment Lug FS424. T R ED Detailed Inspection of the Wing to Fuselage Attachment Lug FS T R ED Detailed Inspection of the Frame below the Floor FS513. T R ED Detailed Inspection of Wing to Fuselage Attachment Link FS513. T R 48 M ED Detailed Inspection of the Wing to Floor Tie Beam FS460. T R

182 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED CPCP Detailed Inspection of the Upper Surface of the Pressure Floor Skin Panel FS409 to FS559 and BL36L to BL36R ED Detailed Inspection of the Lower Surface of the Pressure Floor Skin Panel FS409 to FS559 and BL36L to BL36R. T R T R 48 M 48 M ED CPCP Detailed Inspection of the Pressure Floor Support Beams FS409 to FS559, BL0.0, BL9, BL18.6, BL27 and BL35.4. T R ED Detailed Inspection of the Underfloor Longeron Assembly FS409 to FS559. T R ED Detailed Inspection of the MLG Uplock Structure FS513 to FS559 below WL73 (LH and RH). T R ED Detailed Inspection of the Internal Surfaces of the Forward Auxiliary Tank. T R PART ED CPCP Lubrication of the Wing to Fuselage Attachment Links FS ED CPCP Detailed Inspection of the Aft Face of the Pressure Bulkhead below the Floor FS559 T R T R 48 M 48 M 48 M Revision: REISSUE Page 6 Sep 22/ ED Detailed Inspection of the Forward Face of the Pressure Bulkhead below the Floor FS ED Detailed Inspection of the Aft Face of the Rear Pressure Bulkhead FS621. T R T R 48 M 48 M

183 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Stabilizer Drag Angles FS700 to FS820, and Stringer 2L and 2R ED CPCP Detailed Inspection of the Forward Face of the Rear Pressure Bulkhead above the Floor FS621. T R T R 240 M AD/ED CPCP Detailed Inspection of the Profile Plates of the Floor Support Structure FS559 to FS621. T R AD/ED CPCP Detailed Inspection of the Profile Plates of the Floor Support Structure FS621. T R 48 M 48 M ED Detailed Inspection of the Engine Support Beam Structure T R PART AD/ED CPCP Detailed Inspection of the Internal Aft Fuselage (Skin and Structure, FS Bulkhead Forward Face and the External Surfaces of the Aft Auxiliary Fuel Tank) FS to FS Below the Floor ED CPCP Detailed Inspection of the Track Supports near, and the Sills and Frames around, the Cargo Compartment Door Cutout T R T R 48 M ED Detailed Inspection of the Fittings of the Cargo Compartment Door. T R 48 M Revision: REISSUE Page 7 Sep 22/ ED Detailed Inspection of the Internal Skin and Fuselage Structure FS621 to FS755. T R 48 M 48 M

184 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Forward Face of the Frame FS AD/ED Detailed Inspection of the External Skin around the APU Exhaust Cutout. T R T R 48 M 48 M 48 M ED Detailed Inspection of the External Side Skin Panels of the Fuselage FS559 to FS755 and Stringer 6L to 20L and 6R to 20R Covered by Pylon. T R ED Detailed Inspection of the Internal Skin and Structure of the Aft Auxiliary Tank. T R ED Special Detailed Inspection of the Skin and Fuselage Structure FS to FS T R ED Detailed Inspection of the Aft Face of the Frame VS67.5%. T R 48 M PART ED Detailed Inspection of the Internal Skin and Fuselage Structure FS755 to VS67.5% ED Detailed Inspection of the Internal Skin and Structure of the Tail Tank. T R T R 48 M Revision: REISSUE Page 8 Sep 22/ ED Detailed Inspection of the Floor Structure of the Tail Tank T R ED Detailed Inspection of the Forward Face of the Fuel Tail Tank Forward Bulkhead. T R

185 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Aft Face of the Tail Tank Aft Bulkhead. T R PART Revision; REISSUE Page 9 Sep 22/2017

186 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Forward Engine Mount Spar Assembly. T R ED Detailed Inspection of the Internal Structure of the Pylon T R ED Detailed Inspection of the Aft Engine Mount Support Structure T R PART Revision: REISSUE Page 10 Sep 22/2017

187 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED CPCP Detailed Inspection of the Upper Face of the Top Canted Rib and the Rib Fittings of the Vertical Stabilizer and the Attachment Fittings and Skin Splices of the Horizontal Stabilizer T R 48 M ED Detailed Inspection of the Front Spar of the Horizontal Stabilizer. T R ED Detailed Inspection of the Horizontal Stabilizer (Internal Skins, Structure, Rear Spar and Hinge Fittings) and the Elevator (Forward Face of the Front Spar, Hinge Fittings and Bolts) T R ED Detailed Inspection of the Inner Pivot Pin of the Horizontal Stabilizer. T R 48 M 48 M PART Revision: REISSUE Page 11 Sep 22/ ED Detailed Inspection of the External Surfaces of the Elevator T R 48 M ED Detailed Inspection of the Vertical Stabilizer (Forward Side of the Front Spar, Attachment Fittings and the Splice Strap) ED Detailed Inspection of the Internal Structure of the Vertical Stabilizer ED Detailed Inspection of the External Surfaces of the Rudder T R 48 M T R T R

188 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Rudder (Forward Face of the Front Spar and Hinge Bolts) and the Vertical Stabilizer (Aft Face of the Rear Spar and Rudder Hinge Fittings). T R PART Revision: REISSUE Page 12 Sep 22/2017

189 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the External Center Wing (Front Spar and the Bayonet Fitting) LWS50.00 to RWS T R ED Detailed Inspection of the Internal Center Wing (Spars, Rib and Wing Plank Surfaces) LWS45.00 to RWS T R 48 M ED CPCP Detailed Inspection of the External Center Wing (Rear Spar and Upper Wing Plank, MLG Side Brace Fitting and Rear Spar Bayonet Fitting) LWS48.00 to RWS T R ED CPCP Detailed Inspection of the Forward Face of the Front Spar of the Wing WS50 to WS353. T R 48 M ED Detailed Inspection of the Internal Wing (Front Spar, Rear Spar, Wing Planks, Structure and the MLG Mounting Fittings) WS45.00 to Canted WS T R 48 M PART AD/ED Detailed Inspection of the Aft Face of the Rear Spar of the Wing WS48 to WS353 T R 48 M 48 M ED Detailed Inspection of the Internal Skin and the Wing Structure Canted WS314.5 to WS353 T R 48 M Revision: REISSUE Page 13 Sep 22/ AD/ED Detailed Inspection of the Internal Wing (Auxiliary Spar, Planks, Skins,Structure and the MLG Trunnion Fitting) WS48.00 to WS T R 48 M 48 M

190 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Wing to Fuselage Attachment Fittings and Bolts FS424.00, FS and FS T R ED Detailed Inspection of the Attachment Fittings of the Flap Hinge Box of the Inboard Flap WS76.5 and WS T R ED Detailed Inspection of the Attachment Fittings of the Flap Hinge Box of the Outboard Flap WS178, WS220 and WS264 T R ED Detailed Inspection of the Aileron (External Surfaces, Wing to Aileron Hinge Fittings, Hinge Bolts and Anti Float Torsion Bar). T R ED Detailed Inspection of the Hinge Fittings for the Ground Spoiler. T R PART ED Detailed Inspection of the Hinge Fittings for the Flight Spoiler. T R ED Detailed Inspection of the Skin, Spars, Attachment Fittings, and Internal Structure of the Winglet T R Revision: REISSUE Page 14 Sep 22/ AD/ED Detailed Inspection of the Inboard Flap and Inboard Flap Vane (External Surfaces). ED Detailed Inspection of the Inboard Flap (External Skins, Attachment Lugs and Hinge Arms). T R T R 48 M 48 M

191 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Vane Actuator Sliding Beams and Carriages of the Inboard Flap. T 7000 L R 1800 L AD/ED Detailed Inspection of the Outboard Flap (External Surfaces) and the Outboard Flap Vane (External Surfaces and Support Fittings) T R 48 M 48 M ED Detailed Inspection of the Outboard Flap (External Skins, Attachment Lugs and Hinge Arms). T R ED Detailed Inspection of the Flap Hinge Boxes of the Inboard Flap. T R 48 M ED Detailed Inspection of the Flap Hinge Boxes of the Outboard Flap T R 48 M PART ED Detailed Inspection of the Attachment Bolts for the Flap Hinge Boxes and the Flap Hinge Arms of the Inboard Flap ED Detailed Inspection of the Attachment Bolts f or the Flap Hinge Boxes and the Flap Hinge Arms of the Outboard Flap. T R T R 7800 L 7800 L 7800 L 7800 L Revision: REISSUE Page 15 Sep 22/ ED Detailed Inspection of the Vane Support Straps of the Outboard Flap. T R 7800 L 3700 L ED Detailed Inspection of the Front Spar of the Outboard Flap R 5200 L

192 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the External Surfaces and Forward Face of the Front Spar of the Ground Spoiler ED Special Detailed Inspection of the Bonded Skins of the Ground Spoiler ED Detailed Inspection of the External Surfaces and Forward Face of the Front Spar of the Flight Spoiler ED Special Detailed Inspection of the Bonded Skins of the Flight Spoiler T R T R T R T R 48 M 48 M 48 M 48 M 48 M 48 M 48 M 48 M ED Detailed Inspection of the Hinge Bolts of the Ground Spoiler. T R ED Detailed Inspection of the Hinge Bolts of the Flight Spoiler T R PART Revision: REISSUE Page 16 Sep 22/2017

193 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Hinge Fittings of the Core Cowl Door. T R ED Detailed Inspection of the Service Pylon Casting and Support Rails ED Detailed Inspection of the Forward Engine Mount Yoke and Link Assembly. T R T R ED Detailed Inspection of the Aft Engine Mount Assembly T R ED Detailed Inspection of the Attachment Ring of the Nose Inlet Cowl. T R 7800 L 7800 L PART Revision: REISSUE Page 17 Sep 22/2017

194 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ED Detailed Inspection of the Main Pylon Tracks of the Thrust Reverser ED Detailed Inspection of the Thrust Reverser Main Tracks T R T R ED Detailed Inspection of the Attachment Fittings for the Thrust Reverser Main Tracks ED Detailed Inspection of the Support Fittings of the Thrust Reverser Ballscrew Actuators. T R T R PART Revision: REISSUE Page 18 Sep 22/2017

195 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Zonal Inspection Program Zonal Inspection Program 1. General This section provides the GVI requirements for each aircraft zone to check system and powerplant installations and structure for security and general condition. The inspections are specified by quoting the relevant zone number, zone description, access requirement and intervals. There are zones which will require more than one inspection at different intervals, because the depth at which the zone is to be examined may necessitate differing levels of accessibility. 2. Program Rules The purpose of the following program rules is to provide standard guidelines to the zonal maintenance program. A. Zones which contain systems/components/installations are assigned a zonal GVI task to be performed at specified intervals. Zones which contain no systems installations or which received adequate coverage from other maintenance or structural inspection tasks will not require the additional zonal inspection task. Detailed and Special Detailed Inspection tasks shall not be contained in the Zonal Inspection Program. B. In addition to a GVI, the zonal inspection shall include, if required, a physical check of the general condition and security of attachment of the accessible systems and structures items contained in the defined zone (components, wiring, plumbing, ducting, tubing, fittings, brackets, pulleys, bearings, fasteners, electrical bonding, etc.). This includes a check for evidence of degradation such as chafing of tubing, paint deterioration, loose duct supports, wiring damage, cable and pulley wear, fluid leaks, inadequate drainage, cracks, etc. and corrosion, or damage which could lead to corrosion. It also includes a check of the general condition of any fairings, panels or other items which are removed/opened to gain access to a particular zone. C. When necessary, seats, carpets, ceiling and wall trim panels including insulation are to be removed to access and complete an adequate GVI. PART 3 Revision: REISSUE Page Sep 22/2017

196 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Zonal Inspection Program 3. List of Zonal Identification Numbers (ZIN s) This section contains a list of all the ZIN items sorted in ATA zone sequence by ZIN number. Each ZIN is covered by at least one MSG 3 task. Zone ID No. Description Nose Landing Gear Assembly LH/RH Main Landing Gear Assembly LH/RH/AFT Nose Landing Gear Doors LH/RH Main Landing Gear Doors External Passenger Door Internal Passenger Door External RH Overwing Emergency Exit Door External RH Overwing Emergency Exit Door Internal RH Overwing Emergency Exit Door External Cargo Compartment Door Internal Cargo Compartment Door External Nose Radome Internal Nose Radome External Lower Nose Compartment Internal LH Lower Nose Compartment Internal RH Lower Nose Compartment Nose Wheel Well External Forward Avionics and Flight Controls Compartment Internal LH/RH Forward Avionics and Flight Controls Compartment External Main Avionics Compartment Internal Main Avionics Compartment External Lower Mid Fuselage Exterior Face of Lower Mid Fuselage Pressure Floor Main Landing Gear Wheel Well Internal Lower Mid Fuselage between Pressure Floor and Cabin Floor External Lower Mid Compartment and Aft Wing to Fuselage Fairing Internal Lower Mid Fuselage Compartment External Forward Equipment Compartment Internal Forward Equipment Compartment PART 3 Revision: REISSUE Page Sep 22/2017

197 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Zonal Inspection Program Zone ID No. Description External Flight Compartment Internal Flight Compartment External Passenger Compartment Internal Passenger Compartment External Cargo Compartment Internal Cargo Compartment External Aft Equipment Compartment Internal Aft Equipment Compartment External Fuselage/Stabilizer Section Internal Fuselage/Stabilizer Section External Tail Cone Internal Tail Cone External LH/RH Pylon Internal LH/RH Pylon Leading Edge Internal LH/RH Pylon Mid Section Internal LH/RH Pylon Trailing Edge External Vertical Stabilizer Assembly Internal Ram Air Intake and Dorsal fairing Internal Leading Edge of the Vertical Stabilizer Internal Vertical Stabilizer Internal Vertical Stabilizer Tip External LH/RH Horizontal Stabilizer Internal LH/RH Horizontal Stabilizer Leading Edges Internal LH/RH Horizontal Stabilizer External LH/RH Side of the Center Wing Internal LH/RH Side of the Center Wing External LH/RH Inboard Leading Edge Internal LH/RH Inboard Leading Edge External LH/RH Outboard Leading Edge Internal LH/RH Outboard Leading Edge External LH/RH Inboard Wing PART 3 Revision: REISSUE Page Sep 22/2017

198 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Zonal Inspection Program Zone ID No. Description Internal LH/RH Inboard Wing External LH/RH Outboard Wing Internal LH/RH Outboard Wing Internal LH/RH Outboard Wing External LH/RH Winglet Internal LH/RH Winglet External LH/RH Inboard Wing Trailing Edge Internal LH/RH Inboard Wing Trailing Edge External LH/RH Outboard Wing Trailing Edge Internal LH/RH Aileron Shroud External LH/RH Engine Nacelle Inside the LH/RH Engine Nose Inlet & Access Cowl Inside the LH/RH Engine Translating Cowl Inside the LH/RH Engine Core Cowl Inside the LH/RH Engine Thrust Reverser Torque Box Inside the LH/RH Engine Tailpipe Fairing 4. Tasks and Intervals Table Format Detailed information is given below concerning the format of the table listing the inspection requirements provided on subsequent pages. MSG 3 Task No. Route Chapter 5 Task No. Task Title Task Interval A. Column 1 The first (left) column lists all MSG 3 tasks from Avionics, Systems, Powerplant, Structures and/or Zonal analysis which were used to make the Chapter 5 task shown in column 2. These task numbers are of the form XXXXXXXXXX YY for zonal tasks where XXXXXXXXXX is the ZIN number and YY is the unit sequence identifier. The format for avionics, systems, powerplant tasks and structures tasks are defined in section and , respectively. PART 3 Revision: REISSUE Page Sep 22/2017

199 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 Zonal Inspection Program B. Column 2 The second column identifies from which working group an MSG 3 task was transferred (when applicable). C. Column 3 The third column lists the corresponding Chapter 5 task number and is of the form XX YY 00 WZZ, where XX is the ATA Chapter number, YY is designated as ZL" to indicate the task is zonal task, W is designated as 2" to indicate a MRB item, and ZZ is the unit sequence identifier. The unit sequence identifier begins at 01" for each variation to the full ATA number sequence contained in the Chapter 5 task number. D. Column 4 The fourth column contains the task title. This title includes the inspection level and a brief description of the area or items to be inspected. E. Column 5 The fifth column contains the inspection intervals. The inspection interval is defined from the last time that particular task was carried out. The inspection intervals in this column are in months (M), flight hours (H) or in landings (L). PART 3 Revision: REISSUE Page Sep 22/2017

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201 CL-605 TIME LIMITS/MAINTENANCE CHECKS PART 3 SECTION ZONAL INSPECTION PROGRAM Tasks and Intervals PART Cover Revision: REISSUE Sep 22, 2017

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203 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 1 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Nose Landing Gear Door LH. 48 M ZL General Visual Inspection of the Nose Landing Gear Door RH ZL General Visual Inspection of the Aft Nose Landing Gear Door ZL General Visual Inspection of the Main Landing Gear Door LH ZL General Visual Inspection of the Main Landing Gear Door RH. 48 M 48 M 48 M 48 M

204 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 2 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Stru 52 ZL General Visual Inspection of the Passenger Door External. 48 M ZL General Visual Inspection of the Passenger Door Internal. 48 M Stru 52 ZL General Visual Inspection of the Overwing Emergency Exit Door External ZL General Visual Inspection of the Overwing Emergency Exit Door Internal. 48 M Stru 52 ZL General Visual Inspection of the Cargo Compartment Door External. 48 M ZL General Visual Inspection of the Cargo Compartment Door Internal. 48 M

205 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 3 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Nose Radome External. 48 M ZL General Visual Inspection of the Nose Radome Internal. 48 M Stru 53 ZL General Visual Inspection of the Nose Compartment Lower External Stru 53 ZL General Visual Inspection of the Nose Compartment Lower Internal LH Stru 53 ZL General Visual Inspection of the Nose Compartment Lower Internal RH. 48 M ZL General Visual Inspection of the NLG Wheel Well 48 M Stru 53 ZL General Visual Inspection of the Forward Avionics and Flight Controls Compartment External Prop Stru 53 ZL General Visual Inspection of the Forward Avionics and Flight Controls Compartment Internal LH 48 M Stru 53 ZL General Visual Inspection of the Forward Avionics and Flight Controls Compartment Internal RH. 48 M Stru 53 ZL General Visual Inspection of the Main Avionics Compartment External. 48 M ZL General Visual Inspection of the Main Avionics Compartment Internal. 48 M

206 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 4 Jun 29/2018 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Mid Fuselage Lower External ZL General Visual Inspection of the Lower Surface of the Pressure Floor from FS409 to FS ZL General Visual Inspection of the Main Landing Gear Wheel Well. 48 M 48 M Prop 53 ZL General Visual Inspection of the Mid Fuselage between the Pressure Floor and the Cabin Floor Lower Internal Stru Stru 53 ZL General Visual Inspection of the Aft Compartment and Aft Wing to Fuselage Fairing External ZL General Visual Inspection of the Mid Fuselage Compartment Lower Internal (FS589.0 to FS621.0). 24 M Stru 53 ZL General Visual Inspection of the Forward Equipment Compartment External Stru 53 ZL General Visual Inspection of the Forward Equipment Compartment Internal. 48 M Stru 53 ZL General Visual Inspection of the Flight Compartment External. 24 M

207 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 5 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Prop Prop 53 ZL General Visual Inspection of the Flight Compartment Internal without Removal of the Headliner and the Glareshield. 48 M Stru Stru Stru Stru 53 ZL General Visual Inspection of the Passenger Compartment External ZL General Visual Inspection of the Passenger Compartment Internal. 192 M Stru Stru Stru 53 ZL General Visual Inspection of the Cargo Compartment External ZL General Visual Inspection of the Cargo Compartment Internal without Removal of the Headliner Prop 53 ZL General Visual Inspection of the Cargo Compartment Internal with the Headliner Removed 192 M Stru Stru 53 ZL General Visual Inspection of the Aft Equipment Compartment External 48 M Stru

208 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 6 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Aft Equipment Compartment Internal. 12 M Stru 53 ZL General Visual Inspection of the Fuselage/Stabilizer Section External ZL General Visual Inspection of the Fuselage/Stabilizer Section Internal. 48 M Stru 53 ZL General Visual Inspection of the Tail Cone External. 48 M Stru 53 ZL General Visual Inspection of the Tail Cone Internal. 48 M Prop 53 ZL General Visual Inspection of the Mid Fuselage Compartment Lower Internal (FS559.0 to FS621.0).

209 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 7 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Stru 54 ZL General Visual Inspection of the Pylon External LH. 48 M Stru 54 ZL General Visual Inspection of the Pylon External RH. 48 M ZL General Visual Inspection of the Pylon Leading Edge Internal LH ZL General Visual Inspection of the Pylon Leading Edge Internal RH. 48 M 48 M ZL General Visual Inspection of the Pylon Mid Section Internal LH 48 M ZL General Visual Inspection of the Pylon Mid Section Internal RH. 48 M ZL General Visual Inspection of the Pylon Trailing Edge Internal LH ZL General Visual Inspection of the Pylon Trailing Edge Internal RH.

210 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 8 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Stru 55 ZL General Visual Inspection of the Vertical Stabilizer Assembly External. 48 M Stru 55 ZL General Visual Inspection of the Ram Air Intake and Dorsal Fairing Internal ZL General Visual Inspection of the Leading Edge of the Vertical Stabilizer Internal Stru 55 ZL General Visual Inspection of the Vertical Stabilizer Internal ZL General Visual Inspection of the Tip of the Vertical Stabilizer Internal Stru Stru 55 ZL General Visual Inspection of the Horizontal Stabilizer External LH ZL General Visual Inspection of the Horizontal Stabilizer External RH ZL General Visual Inspection of the Leading Edge of the Horizontal Stabilizer Internal LH ZL General Visual Inspection of the Leading Edge of the Horizontal Stabilizer Internal RH.

211 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 9 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Horizontal Stabilizer Internal LH ZL General Visual Inspection of the Horizontal Stabilizer Internal LH.

212 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 10 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval STRU 57 ZL General Visual Inspection of the Wing Center Section External LH. STRU 57 ZL General Visual Inspection of the Wing Center Section External RH. STRU 57 ZL General Visual Inspection of the Front Spar of the Wing Center Section External. 48 M 48 M ZL General Visual Inspection of the Wing Center Section Internal LH ZL General Visual Inspection of the Wing Center Section Internal RH ZL General Visual Inspection of the Inboard Leading Edge of the Wing External LH ZL General Visual Inspection of the Inboard Leading Edge of the Wing External RH. 48 M 48 M ZL General Visual Inspection of the Inboard Leading Edge of the Wing Internal LH ZL General Visual Inspection of the Inboard Leading Edge of the Wing Internal RH ZL General Visual Inspection of the Outboard Leading Edge of the Wing External LH. 48 M

213 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 11 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Outboard Leading Edge of the Wing External RH. 48 M ZL General Visual Inspection of the Outboard Leading Edge of the Wing Internal LH ZL General Visual Inspection of the Outboard Leading Edge of the Wing Internal RH STRU STRU 57 ZL General Visual Inspection of the Wing from WS47 to WS148 External LH. 48 M STRU STRU 57 ZL General Visual Inspection of the Wing from WS47 to WS148 External RH. 48 M ZL General Visual Inspection of the Wing from WS45 to WS148 Internal LH ZL General Visual Inspection of the Wing from WS45 to WS148 Internal RH STRU STRU STRU 57 ZL General Visual Inspection of the Wing from WS148 to WS353 External LH. 48 M

214 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 12 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval STRU STRU STRU 57 ZL General Visual Inspection of the Wing from WS148 to WS353 External RH. 48 M ZL General Visual Inspection of the Wing from WS148 to WS353 Internal LH ZL General Visual Inspection of the Wing from WS148 to WS353 Internal RH ZL General Visual Inspection of the Winglet External LH. 48 M ZL General Visual Inspection of the Winglet External RH. 48 M ZL General Visual Inspection of the Inboard Trailing Edge of the Wing External LH ZL General Visual Inspection of the Inboard Trailing Edge of the Wing External RH. 48 M 48 M ZL General Visual Inspection of the Wing Trailing Edge Internal LH. 36 M ZL General Visual Inspection of the Wing Trailing Edge Internal RH ZL General Visual Inspection of the Outboard Trailing Edge of the Wing External LH. 36 M 48 M

215 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 13 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Outboard Trailing Edge of the Wing External RH ZL General Visual Inspection of the Aileron Shroud Internal LH ZL General Visual Inspection of the Aileron Shroud Internal RH. 48 M

216 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 14 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval ZL General Visual Inspection of the Nacelle External LH 48 M ZL General Visual Inspection of the Nacelle External RH. 48 M Prop Prop Stru Prop 71 ZL General Visual Inspection of the Nose Inlet Access Cowl Inside LH. 36 M Prop Prop Stru Prop 71 ZL General Visual Inspection of the Nose Inlet Access Cowl Inside RH. 36 M ZL General Visual Inspection of the Translating Cowl Internal LH. 48 M ZL General Visual Inspection of the Translating Cowl Internal RH. 48 M

217 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 15 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Sys Sys Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop 71 ZL General Visual Inspection of the Core Cowl Internal LH. 36 M

218 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 16 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Sys Sys Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop Prop 71 ZL General Visual Inspection of the Core Cowl Internal RH. 36 M

219 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 17 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Prop Prop 78 ZL General Visual Inspection of the Torque Box of the Thrust Reverser Internal LH. 48 M Prop Prop 78 ZL General Visual Inspection of the Torque Box of the Thrust Reverser Internal RH. 48 M Prop 78 ZL General Visual Inspection of the Torque Box of the Thrust Reverser Internal RH. 48 M Prop 78 ZL General Visual Inspection of the Exhaust Nozzle Fairing Assembly RH. 48 M

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221 Chapter 2: Section: 1. General CL 605 TLMC Maintenance Management Review Board Part 3 L/HIRF Inspection Program L/HIRF INSPECTION PROGRAM This section provides the basic scheduled inspection task and frequencies applicable to the CL 605 lightning/high intensity radiated field (L/HIRF) protection. The intent of the Challenger 605 L/HIRF protection maintenance program is to ensure the availability of L/HIRF protection for each line replaceable unit (LRU) and wiring disconnect within a specified system. The L/HIRF maintenance program will involve on aircraft inspection of L/HIRF protection termination at LRUs and wiring disconnects for unserviceability resulting from accidental or environmental damage. Wiring runs are considered to be covered within the scope of the normal Zonal Inspection Program. 2. Program Rules The purpose of the following program rules is to provide standard guidelines for the L/HIRF maintenance program. A. During the performance of detailed inspection of L/HIRF protective devices, no connector or equipment is to be removed that would necessitate subsequent functional testing. B. For all wiring and termination points installed within heat shrink or other conduits, the defined detailed inspection will apply only to the heat shrink or conduit for integrity C. The L/HIRF maintenance program addresses only on aircraft inspections of L/HIRF protective devices. However, specified LRUs may also incorporate, inside the equipment, additional protective devices. These internal devices will be subject to off aircraft inspection and testing, on an opportunity basis, as per instructions contained within the LRU manufacturer s component maintenance manual. 3. List of L/HIRF Significant Items The following is a list of the L/HIRF significant items. L/HIRF ANALYSIS TITLE Pressure Indicating and Warning System Automatic Flight Control System (AFCS) and Yaw Damper (Y/D) Integrated Avionics Processor System (IAPS) Auto Throttle System PART 3 Revision: REISSUE Page Sep 22/2017

222 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 L/HIRF Inspection Program L/HIRF ANALYSIS TITLE VHF Communication High Frequency (HF) Communication System Audio Integrating System Radio Tuning System Electrical Stall Protection System Horizontal Stabilizer Trim Actuating System Flap Control System Fuel Quantity Indicating System Windshield and Side Window Anti Ice Engine Indicating and Crew Alert System (EICAS) Anti Skid System Nose Wheel Steering Landing Gear Control and Indication Air Data System Weather Radar Ground Proximity Warning (GWPS) and Terrain Awareness Warning System (TAWS) Traffic Collision Avoidance System (TCAS) Radio Altimeter System Inertial Reference System VHF Navigation System Global Positioning System Flight Management System Auxiliary Power Unit Electronic Control Unit Electronic Control Unit (N1 Amplifier) Engine Indicating PART 3 Revision: REISSUE Page Sep 22/2017

223 Chapter 2: Section: CL 605 TLMC Maintenance Management Review Board Part 3 L/HIRF Inspection Program 4. Tasks and Intervals Table Format The table in section provides a list of the L/HIRF program tasks. Data about the table is shown below. MSG 3 Task No. Route Chapter 5 Task No. Task Title Task Interval A. Column 1 Column number 1 lists all L/HIRF task numbers. The task numbers are of the form XXXXXXXX YZZ for L/HIRF tasks. XXXXXXXX is the system ATA number. YZZ is the task sequence identifier that starts at 201 for all different ATA numbers. The format for avionics, systems and powerplant tasks, structures tasks and zonal tasks are defined in sections , and respectively. B. Column 2 Not applicable for L/HIRF tasks. C. Column 3 Column number 3 shows the Chapter 5 task number that corresponds to the L/HIRF task number in column 1. Chapter 5 task numbers are XX XX XX YZZ where: XX XX XX is the ATA Chapter number Y is 2 if the source data was MSG 3 analysis ZZ is the task sequence identifier that starts at 01 for all different ATA numbers. D. Column 4 Column number 4 shows the title of the task. This title includes the inspection level and a brief description of the area or items to be inspected. E. Column 5 Column number 5 shows the intervals for the task. The interval is measured from the last time that the task was done. The task interval is measured in months (M). PART 3 Revision: REISSUE Page Sep 22/2017

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225 CL-605 TIME LIMITS/MAINTENANCE CHECKS PART 3 SECTION L/HIRF INSPECTION PROGRAM Tasks and Intervals PART Cover Revision: REISSUE SEP 22, 2017

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227 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: 2 Page 1 Jun MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection in the Flight Compartment Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection in the Fuselage/Stabilizer Internal 48 M Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection of the Vertical Stabilizer Internal

228 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 2 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection in the Aft Equipment Compartment 48 M Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection in the Fuselage between FS and FS621.00, below WL73.5 Internal Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection on the Avionics Racks

229 CL 605 TIME LIMITS/MAINTENANCE CHECKS MAINTENANCE MANAGEMENT REVIEW BOARD REPORT PART Revision: REISSUE Page 3 Sep 22/2017 MSG-3 Task No. Route Chapter 5 Task No. Task Title Task Interval Special Detailed Inspection (Borescope) of the Lightning/High Intensity Radiated Field (L/HIRF) Protection on the #2 VHF Antenna Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection in the Avionics Compartments Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection on the Upper FS621 Bulkhead 48 M Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection on the Wing Disconnects External Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection on the Wing Disconnects Internal Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection in the Main Wheel Wells Detailed Inspection of the Lightning/High Intensity Radiated Field (L/HIRF) Protection in the Nose Wheel Well and Landing Gear Assembly 48 M 48 M

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231 Chapter 2: Section: Airframe Manufacturers Unscheduled Maintenance Checks Airframe A. General Unscheduled airframe maintenance tasks are listed in Table 1 below. Procedures for determining and compliance of the task are found in the Bombardier Aircraft Maintenance Manual (Part Two) Chapter 5, as revised. TABLE 1 AIRFRAME UNSCHEDULED MAINTENANCE TASKS Subject / Type / Task No. / Description AIRCRAFT PARKED IN STRONG WIND OR WINDGUSTS Inspection/Check TASK Inspection After the Aircraft is Parked in Strong Windsor Windgusts HARD/OVERWEIGHT LANDINGS Inspection/Check TASK General Visual Inspection for Hard/Overweight Landing Damage EXTREME TURBULENCE/MANEUVER Inspection/Check TASK General Visual Inspection for Extreme Turbulence/Maneuver Damage LIGHTNING STRIKE Inspection/Check TASK General Visual Inspection for Lightning Strike Damage OVERSPEED CONDITION Inspection/Check TASK General Visual Inspection of the Flaps and the Landing Gear for Overspeed Damage DEFLATED TIRE, BURST TIRE OR FUSIBLE PLUG RELEASE Inspection/Check TASK General Visual Inspection for Tire Burst Damage TASK General Visual Inspection after a Tire Deflates AMM Ch 5 Reference Revision: REISSUE Page /-51 Sep 22/2017

232 Chapter 2: Section: Airframe Manufacturers Unscheduled Maintenance Checks Airframe TABLE 1 (Continued) AIRFRAME UNSCHEDULED MAINTENANCE TASKS Subject / Type / Task No. / Description WING LEADING EDGE OVERHEAT Inspection/Check TASK General Visual Inspection of Aircraft for Wing Leading Edge Overheat Damage AIR DRIVEN GENERATOR (ADG) IN FLIGHT DEPLOYMENT Inspection/Check TASK General Visual Inspection of Air Driven Generator (ADG) after In Flight Deployment CABIN OVERPRESSURIZATION Inspection/Check TASK Detailed Inspection of Cabin Overpressurization Damage ENGINE DRIVEN PUMP (EDP) OPERATED DRY AFTER LOSS OF HYDRAULIC FLUID Inspection/Check TASK General Visual Inspection of the Engine Driven Pump (EDP) after Dry Operation due to Hydraulic Fluid loss HYDRAULIC SYSTEM OVERHEAT Inspection/Check TASK Inspection of Hydraulic Fluid After System Overheat SYMMETRY AND ALIGNMENT Inspection/Check TASK Detailed Dimensional Inspection of Aircraft for Symmetry and Alignment PITOT STATIC VISUAL DRAINS Inspection/Check TASK General Visual Inspection of the Pitot Static Visual Drains after Adverse Weather Operations HIGH ENERGY STOP/REJET TAKEOFF (RTO) Inspection/Check TASK General Visual Inspection for High Energy Stop/Reject Takeoff (RTO) Damage AMM Ch 5 Reference Revision: REISSUE Page /-51 Sep 22/2017

233 Chapter 2: Section: Airframe Manufacturers Unscheduled Maintenance Checks Airframe TABLE 1 (Continued) AIRFRAME UNSCHEDULED MAINTENANCE TASKS Subject / Type / Task No. / Description HYDRAULIC HARRISSON H FITTINGS Inspection/Check TASK General Visual Inspection of Hydraulic Harrisson H Fitting HYDRAULIC PUMP SHOCK MOUNT CONTAMINATION CHECK Inspection/Check TASK General Visual Inspection of Hydraulic Pump Shock Mount Contamination Check ELECTRICAL MOTOR DRIVEN PUMP (EMPD) AFTER DRY OPERATION DUE TO HYDRAULIC FLUID LOSS Inspection/Check TASK General Visual Inspection of the Electrical Motor Driven Pump (EMPD) after Dry Operation due to Hydraulic Fluid Loss LAVATORY SPILL OR LEAK Inspection/Check TASK Detailed Inspection After Lavatory Spill or Leak BIRD STRIKE CONDITION Inspection/Check TASK Visual Inspection After a Bird Strike RAPID CONTROL REVERSAL Inspection/Check TASK Inspection After Rapid Control Reversal RUNWAY DE ICING PRODUCT CONTAMINATION Inspection/Check TASK Inspection of Aircraft after Contamination with Organic Salt Based Runway De Icing Products FIRE EXTINGUISHING FOAM CONTAMINATION Inspection/Check TASK General Visual Inspection after Extinguishing Foam Contamination AMM Ch 5 Reference Revision: REISSUE Page /-51 Sep 22/2017

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235 Chapter 2: Section: Airframe Manufacturers Unscheduled Maintenance Checks Engine CF34-3B A. General Unscheduled engine maintenance tasks are listed in Table 1 below. Procedures for determining and compliance of the task are found in the Bombardier Aircraft Maintenance Manual (Part Two) Chapter 5, as revised. Subject / Type / Task No. / Description TABLE 1 ENGINE UNSCHEDULED MAINTENANCE TASKS Detailed Inspection of the Engine Master Chip Detector Indicator TASK AMM Ch 5 Reference Refer to CF34 3B (SEI 780) Engine Maintenance Manual for Inspections of Engines Involved in Accidents or Incidents for information of the following Engine Checks: Inspection of Engines (In Flight G Loading) that have Operated Above the Limits Inspection of Engines that have Operated Above the Temperature Limits Inspection of Engines that Show Hot Section Distress (Burnouts) Inspection of Engines that have Operated in Over Speed Condition Inspection of Engines After a VG System Malfunction or Compressor Limits Inspection of Engines After the Aircraft has been Hit by Lightning Inspection of Engines that have been in Salt Water or Exposed to Fire Extinguishing Material Inspection of Engines for Metal Contamination of the Oil System, as Shown by Debris on the Master Magnetic Chip Detector or on the Oil Filter NOTE: Refer to (TASK ) for one time reset of the indicator to prevent unnecessary inspections and troubleshooting. Inspection of Engines that have been Hit by Birds Inspection of Engines after a Foreign Object Damage (FOD) Event Inspection of Engine with Low or No Oil Pressure Revision: REISSUE Page Sep 22/2017

236 Chapter 2: Section: Airframe Manufacturers Unscheduled Maintenance Checks Engine CF34-3B TABLE 1 (Continued) AIRFRAME UNSCHEDULED MAINTENANCE TASKS Subject / Type / Task No. / Description AMM Ch 5 Reference Inspection of Engines that have Experienced Flames Exiting the Tailpipe Inspection of Engines After Ingestion of Volcanic Ash Inspection of Engines that have Operated in an Incorrectly Assembled Condition Revision: REISSUE Page Sep 22/2017

237 GE CF34-3B ENGINE AIRWORTHINESS LIMITATIONS 1. General A. The Airworthiness Limitations Section is FAA-approved and specifies the maintenance required under paragraph and of the Federal Aviation Regulations, unless an alternative program has been FAA-approved. B. The rotating parts listed below have been identified by the Federal Aviation Administration (FAA) as Life Limited Parts (LLP). Life Limitations for these parts are listed in Sections , , , Mandatory inspections for these parts are listed in Chapter 2 Part Fan Disk Forward Fan Shaft Fan Drive Shaft Stage 1 Compressor Rotor Disk Stage 1 Compressor Rotor Blisk Compressor Forward Shaft Stage 2 Compressor Rotor Disk Stages 3 through 8 Compressor Rotor Spool Stage 9 Compressor Rotor Disk Stages 10 thru 14 Compressor Rotor Spool Compressor Rotor Rear Shaft Compressor Discharge Rotating Seal High-Pressure Turbine Rotor Shaft Rotating Air Balance-Piston Seal Stage 1 Front Cooling Plate Stage 1 Front High-Pressure Turbine Rotor Forward Cooling Plate Stage 1 Aft Cooling Plate Stage 1 High-Pressure Turbine Rotor Rear Cooling Plate Inner Torque Coupling Outer Torque Coupling Stage 2 Front Cooling Plate Stage 2 Forward Cooling Plate Stage 2 Turbine Disk Stage 2 Rear Cooling Plate Stage 2 High-Pressure Turbine Rotor Aft Cooling Plate Turbine Rear Shaft Stage 3 Turbine Disk Stage 3-4 Turbine Seal Stage 4 Turbine Disk Stages 4-5 Turbine Seal Turbine Driver Cone Stage 5 Turbine Disk Stages 5-6 Turbine Seal Stage 6 Turbine Disk Page 1 Airworthiness Limitations Revision: 2 09/22/2017

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239 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Life Limits of Engine Rotating Parts 1. General A. The FAA has approved service life-limits cycles (Airworthiness Limitations) for rotating parts installed in the GE Aircraft Engines CF34-3A1 and CF34-3B turbofan engines. B. Rotating parts of all turbine engines have some type of service limits. Critical rotating parts are those parts whose sudden failure could threaten the structural integrity of the engine. These parts, when subjected to large repeated and/or alternating stresses, can fail through fatigue. The material properties of a part are depleted by fatigue as a function of the number of stress cycles the part experiences. Stress cycles of turbine engine rotating parts result from the transients of the engine speed and temperatures occurring during normal engine operation. Therefore, the life limit cycles provide the operator the means of tracking the useful service life of a part so that the part can be removed from service before possible fatigue failure. These life-limits are usually expressed in the terms of cycles, and can be related almost directly to the number of stress cycles that occur during engine operation. It is for this reason that the limits are in terms of cycles. The maximum life limits for all rotating parts are given in the sections that follow. A life limit is given for each part number and each CF34 engine model for which the part can be used. An accurate record of cycles must be kept for each part serial number. This history must include the total number of cycles operated, and the number of cycles remaining. It is recommended that a record be kept of the aircraft application in which the parts are installed and the number of cycles operated in each aircraft application/engine model mix. For parts used in only one engine model and within only one aircraft application (for example only the Biz Jet application), the life limits for that engine model/aircraft are applicable. For parts used in only one engine model and within multiple aircraft application (for example Commercial Regional Jet and Biz Jet applications), the life limits for each engine model/aircraft application are applicable to determine part life limits. C. Life limits of the critical rotating parts are established through analysis and testing. Accumulated cycles are compared to the life limits to determine if the affected hardware is still serviceable. No component must be permitted to remain in service beyond its life-limit cycles. Refer to paragraph 2.A. for the definitions of a cycle. 2. Requirements CAUTION: CERTAIN ROTATING PARTS ARE LIFE-LIMITED BASED ON THE SPECIFIC MODEL OR APPLICATION FOR WHICH THE PART IS INTENDED. IN SOME CASES, DIFFERENT LIFE LIMITS HAVE BEEN ESTABLISHED FOR IDENTICAL GE LIFE-LIMITED PARTS FOR DIFFERENT MODEL OR APPLICATIONS (FOR EXAMPLE, CF34-3A1 VS CF34-3B, OR BOMBARDIER CL604 BUSINESS JET VS BOMBARDIER CRJ200 REGIONAL JET APPLICATION). ACCORDINGLY, THE FOLLOWING PRECAUTIONS AND GUIDELINES MUST BE OBSERVED. * USED LIFE-LIMITED PARTS MUST NOT BE REUSED UNLESS THE HISTORY OF THAT PART IS KNOWN. THIS CHAPTER CONTAINS INFORMATION FOR DETERMINING EQUIVALENT ACCUMULATED CYCLES VS MODEL OR APPLICATION. * IF THE MODELS AND/OR APPLICATIONS IN WHICH THE PART HAS OPERATED AND THE TOTAL NUMBER OF CYCLES ACCUMULATED ARE KNOWN, BUT THE NUMBER OF CYCLES OPERATED IN EACH MODEL OR APPLICATION ARE NOT KNOWN, THE LOWEST LIFE LIMIT FOR A GIVEN PART MUST BE APPLIED (REFER TO METHOD I, PARAGRAPH 2.B.). Page Revision: Reissue 09/22/2017

240 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Life Limits of Engine Rotating Parts IT IS THE RESPONSIBILITY OF THE OPERATOR TO MAINTAIN ACCURATE RECORDS OF PART OPERATION. * There are currently six CF34-1/-3 engine models (CF34-1A/-3A/-3A1/-3A2/-3B/- 3B1) in service with five aircraft applications. All six of these engine models can be used in business jet applications. * The CF34-1A/-3A/-3A2 engine models are used in the Bombardier CL601 Challenger Biz Jet. Life limits for these engine models can be found in SEI-580, Chapters through * The CF34-3A1 engine model is used in the Bombardier CL601 (601R Variant) Challenger Biz Jet. The CF34-3B engine model is used in the Bombardier CL604 Challenger Biz Jet. Life limits for these engine models can be found in SEI-780, Chapter through * The CF34-3A1 and CF34-3B1 engine models are also used in airline Commercial Regional Jet applications. These engine models utilize the Bombardier CRJ100 and CRJ200 Regional Jets. Life limits for these engine models can be found in SEI-756, Chapter through * The CF34-3A1 and CF34-3B1 engine models are also used in the Bombardier CRJ100 and CRJ200 Corporate Jetliner, Special Edition, and Challenger 800 aircraft identified by Service Bulletin (AL) on the engine nameplate. Life limits for these engine models can be found in SEI-756, Chapter through A. Definitions. (1) A cycle is defined as a flight consisting of an acceleration to takeoff power, takeoff, and landing. Use (or non-use) of thrust reverser does not change the cycle count. (2) Engine starts and shutdowns for operational checks, ground maintenance, and taxiing do not count against life-limit cycles, unless the engine is operated at takeoff fan speed. In that case, it counts as 1 cycle. * Other operational procedures that affect the life-limit cycles of rotating parts are counted as follows: An air start is considered 1 cycle on rotating parts. * A touch-and-go landing counts as 1 cycle for each rotating part. * A go-around counts as 2 cycles for each rotating part if APR power is set using the throttle during the go-around (if APR power is not set, the go around counts as 1 cycle for each rotating part). * Whenever the throttle is used to set APR power, 2 cycles are added to the cycle count for each rotating part, per the above definition of a cycle. B. Calculating Cycle Count For Common CF34 Engine Parts That Are Transferred Between Different CF34 Engine Models or Applications. (1) The different CF34 engine models have a number of life-limited parts that are common (have the same part number). Some of these common parts also have the same life limits when transferred between the different engine models or applications. However, because the engine model or applications experience different operating environments, the life limits of some of the common parts may differ when used in different CF34 models or applications. Refer to Table 601 for engine model/ aircraft application life limits. (2) When a common life-limited part is transferred from one CF34 engine model or application to another (for example, CF34-3A1 vs. CF34-3B, or Bombardier CL604 Business Jet vs. Bombardier CRJ200 Commercial Regional Jet application), it will be necessary to calculate the remaining part cyclic life in the engine model or application in which the part will be operated. Page Revision: Reissue 09/22/2017

241 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Life Limits of Engine Rotating Parts To determine this, it is necessary to take into account the engine models or applications in which the part had previously operated, if the cyclic life of the part differs between engine models or applications. All applicable information should be entered into the CF34 common life-limited parts tracking form, refer to Figure 601. The completed tracking form must be returned with the applicable common parts when those parts are transferred between different CF34 model series. (3) The operator must get from GEAE, or from a GE authorized CF34 overhaul facility, the life limits for each CF34 model or applications applicable to the components service history. CF34-1A/-3A/ -3A2 Challenger 601 Biz Jet SEI thru CF34-3A1 Challenger 601-3R Biz SEI thru Jet CF34-3B Challenger 604 and Challenger 605 Biz Jet SEI thru CF34-3A1/-3B1 CRJ100/200 Regional Jet SEI thru CF34-3A1/-3B1 Corporate Jetliner/ Special Edition/ Challenger 800 SEI thru (4) Two methods are available to establish the total life limit for life-limited parts that are used in more than one CF34 engine model or applications: CAUTION: METHOD I MUST BE APPLIED, UNLESS THE NUMBER OF CYCLES OPERATED IN EACH ENGINE MODEL OR APPLICATION IS KNOWN AND DOCUMENTED. WHEN A PART LIFE LIMIT IS CHANGED, ACCUMULATED CYCLES MUST BE CALCULATED AGAIN TO REFLECT THE CHANGE ON THE PART TOTAL ACCUMULATED CYCLES. IT IS THE RESPONSIBILITY OF THE OPERATOR TO MAINTAIN ACCURATE RECORDS OF PART OPERATION. (a) Method I. The life limit of a part used in more than one CF34 engine model or application is the lowest limit published for all models or applications in which the part has been used. This method requires maintaining only records the total number of cycles on the part (in any CF34 model or application) and the engine models or applications in which the part has been used. Refer to Table 601 for engine model/aircraft application life limits. (b) Method II. If the number of cycles accumulated on one or more CF34 models or applications is accurately known and documented, the total life limit for a part used in more than one CF34 model or application can be calculated by pro-rating the life consumed. Refer to Table 601 for engine model/aircraft application life limits. Calculate the fraction of life used for a part installed in a given CF34 model or application, and then calculate the remaining cycles since new (CSN) for the part installed in a different CF34 model or application (refer to Figure 602). * * * FOR ALL Page Revision: Reissue 09/22/2017

242 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Life Limits of Engine Rotating Parts PART NAME PART NUMBER SERIAL NUMBER Note: TO DETREMINE APPROPRIATE LIFE LIMITS FOR THE CF34 ENGINE MODEL AND AIRCRAFT APPLICATION, REFER TO TABLE 601 (ENGINE MODEL/AIRCRAFT APPLICATION LIFE LIMITS) CONTINUE TO USE THIS FORM UNTIL ALL ENGINE APPLICATIONS HAVE BEEN LOGGED AND THE PART REACHES ITS MANDATORY LIMIT. TO MAKE SURE THAT INDIVIDUAL PART CYCLE HISTORY IS MAINTAINED, IT IS RECOMMENDED THAT A COPY OF THE CF34 COMMON LIFE LIMITED PARTS TRACKING FORM BE MAINTAINED WITH THE ENGINE RECORD BOOK. 1 CF34MODEL/AIRCRAFT APPLICATION IN WHICH PART WAS PREVIOUSLY INSTALLED 2 MAINTENANCE MANUAL NUMBER AND LIFE LIMIT SECTION APPLICABLE TO THE CF34 MODEL ON LINE 1 3 PART LIFE LIMIT (CYCLES) INDICATED IN THE MAINTENANCE MANUAL ON LINE 2 4 ENGINE SERIAL NUMBER (ESN) 5 DATE OF PREVIOUS INSTALLATION 6 OVERHAUL SHOP LOCATION OF PREVIOUS INSTALLATION 7 DATE OF REMOVAL 8 OVERHAUL SHOP LOCATION OF REMOVAL 9 TIME AT PREVIOUS INSTALLATION (HOURS) 10 TIME AT REMOVAL (HOURS) 11 TIME ACCUMULATED ON ENGINE MODEL ON LINE 1: SUBTRACT LINE 9 FROM LINE CYCLES AT PREVIOUS INSTALLATION 13 CYCLES AT REMOVAL 14 CYCLES ACCUMULATED ON ENGINE APPLICATION ON LINE 1: SUBTRACT LINE 12 FROM LINE FRACTION OF LIFE USED ON ENGINE APPLICATION IN LINE 1: DIVIDE LINE 14 BY LINE CUMULATIVE FRACTION OF LIFE USED ON ALL PREVIOUS ENGINE APPLICATIONS: ADD CURRENT AN PREVIOUS ENTRIES ON LINE CF34 MODEL/AIRCRAFT APPLICATION IN WHICH PART WILL BE INSTALLED 18 MAINTENANCE MANUAL NUMBER AND SECTION APPLICABLE TO THE CF34 MODEL ON LINE PART LIFE LIMIT (CYCLES) INDICATED IN THE MAINTENANCE MANUAL ON LINE DATE OF RE-INSTALLATION 21 TIME AT INSTALLATION (HOURS): LINE CYCLES AT INSTALLATION FOR CF34 MODEL OR APPLICATION ON LINE 17: MULTIPLY LINE 16 BY LINE REMAINING CYCLES FOR CF34 MODEL OR APPLICATION ON LINE 17: SUBTRACT LINE 16 FROM 1.0 AND MULTIPLY THE RESULT BY LINE 19 THIS FORM CAN BE REPRODUCED FOR LOCAL USE. PART TRANSFER #1 PART TRANSFER #2 PART TRANSFER #3 Figure 601 CF34 Common Life Limited Parts Tracking Form * * * FOR ALL Page Revision: Reissue 09/22/2017

243 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Life Limits of Engine Rotating Parts 1 Calculate the fraction of life used for a part installed in initial CF34 model or application as follows: Cycles accumulated on Fraction of Life used = CF34 model or application 1 LCF Limit for CF34 model or application 1 2 Use this fraction, and calculate the remaining CSN on the part if installed in another different CF34 model or application (model or application 2) as follows: Cycles remaining for CF34 model or application 2 = Fraction of life used (from above) X LCF Limit for CF34 model or application 2 3 Example 1: Consider a part with a usage history on two previous models or applications, to be installed in a third engine model or application. a Calculate the fraction of the life used as follows: CF34-3A1 Biz Jet CF34-3A1 CRJ100 Regional Jet 601R Part Manual Limit (cycles) Part Usage (cycles) Fraction of life used 15,000 6,000 6,000/15,000 = ,000 1,000 1,000/18,000 = 0.56 CF34-3B1 20,000 b Calculate the total Fraction of Life used in previous CF34-3A1 models in a CL601R Biz Jet and CRJ Regional Jet aircraft applications: Total Fraction of Life used = = c Calculate the remaining cycles for the CF34-3B1 model in a Special Edition aircraft application: Remaining cycles = ( ) X 20,000 = 10,800 4 Example 2: Consider a part with LCF Limits in two different cf34 models or applications as follows Figure 602 (Sheet 1) Total Life Limits Calculation Method II Page Revision: Reissue 09/22/2017

244 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Life Limits of Engine Rotating Parts a Calculate the fraction of the Life used as follows: CF34-3A1 CRJ100 Regional Jet CF34-3A1 Biz Jet 601R Part Manual Limit (cycles) Part Usage (cycles) Fraction of life used 12,000 6,000 6,000/12,000 = ,000 b Calculate the total fraction of Life used in the previous CF34-3A1 model in the CRJ100 Regional Jet application: Total Fraction of Life Used = 0.5 c Calculate the remaining cycles for the CF34-3A1 model in a 601R Biz Jet application: Remaining cycles = (1 0.5) X 27,000 = 13,500 cycles 5 Example 3: Assume in Example 2, above the Manual Life Limit of Model or Application 1 is increased from 12,000 to 15,000 cycles while the part is installed in model or application 2. The remaining life in model or application 2 must be calculated again as follows: a Recalculate the fraction of life used in model or application1: CF34-3A1 CRJ100 Regional Jet CF34-3B1 Biz Jet 601R Part Manual Limit (cycles) Part Usage (cycles) Fraction of life used 15,000 6,000 6,000/15,000 = ,000 b Calculate the total fraction of Life used in the previous CF34-3A1 model in the CRJ100 Regional Jet application: Total Fraction of Life Used = 0.4 Page Revision: Reissue 09/22/2017

245 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Life Limits of Engine Rotating Parts c Recalculate the remaining cycles for the CF34-3B1 model in the CRJ200 Regional Jet application: Remaining cycles = (1 0.4) X 27,000 = 16,200 cycles Figure 602 (Sheet 2) Total Life Limits Calculation Method II CAUTION: LIFE-LIMITED PARTS DEFINED BY THIS SECTION MUST NOT BE OPERATED BEYOND THE ESTABLISHED LIMITS. C. Affected Components. The CF34-3A1/-3B engine parts that are life-limited by this section are: * Fan rotor components (refer to ) * Compressor rotor components ( ) * High-pressure turbine rotor components ( ) * Low-pressure turbine rotor components ( ). D. Recording Cycles. (1) The operator is responsible for maintaining an accurate record of the cycles experienced during engine operation. The operator must also monitor the status of the parts to ensure that none of the parts listed in paragraph C exceed the established lifelimit cycles. Monitoring should also include making any adjustment to remaining part life when life-limit cycles change. (2) The CF34 Turbofan Engine Service Record book provides the forms for recording the engine cycle history. (3) The operator and/or the Service or Overhaul Facility is responsible for making appropriate engine logbook entries to reflect the changes in components. (4) The Engine Services Record Books, tracking forms, or logbooks referred to in this section are not the only acceptable method(s) for keeping a record of part history. Alternate record keeping methods may be used. Operators should contact their FAA office or applicable regulatory agency to ensure that their method for record keeping is acceptable. Page Revision: Reissue 09/22/2017

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247 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Fan Rotor Life Limits 1. General A. This section contains the FAA-approved life limits for the fan rotor component. B. The life limit is determined by the total number of flight cycles (refer to , TIME LIMITS for the definitions and the calculations of cycles). C. The operator is responsible to make sure that the cycle-limited components are not operated beyond their established cycle limits. 2. Life Limits of Fan Rotor Components. CAUTION: IF YOU TRANSFER A LIFE-LIMITED PART FROM ONE CF34 MODEL TO ANOTHER CF34 MODEL, REFER TO , TIME LIMITS, PARAGRAPH 2.B., FOR CALCULATING CYCLE COUNT FOR COMMON CF34 ENGINE PARTS THAT ARE TRANSFERRED BETWEEN DIFFERENT CF34 ENGINE MODELS. *** FOR CF34-3A1 NOTE: NOT APPLICABLE TO ACE AVIATION CORP. *** FOR CF34=3B 3. LIFE LIMITSOF FAN ROTOR COMPONENTS. (Refer to Figure 601) Figure 601, Index Number Part Name Part Number Life Limit Cycles 1 Disk, Fan 6078T57G02 6, T57G03 6, T57G04 30, T57G05 30, T57G06 30, T01G04 22, T01G05 22,700 2 Shaft, Forward Fan 6078T51P01 20, T51P02 20, T51P03 20,000 3 Shaft, Fan Drive 6036T78P02 20,000 *** FOR ALL Page Revision: Reissue 09/22/2017

248 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Fan Rotor Life Limits Figure 601 Fan Rotor Life Limited Components Page Revision: Re-Issue 02/28/2017

249 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Compressor Rotor Life Limits 1. General A. This section contains the FAA-approved life limits for the compressor rotor components. B. The life limit is determined by the total number of flight cycles (refer to , TIME LIMITS for the definitions and the calculations of cycles). C. The operator is responsible to make sure that the cycle-limited components are not operated beyond their established cycle limits. 2. Life Limits of Compressor Rotor Components. CAUTION: IF YOU TRANSFER A LIFE-LIMITED PART FROM ONE CF34 MODEL TO ANOTHER CF34 MODEL, REFER TO , TIME LIMITS, PARAGRAPH 2.B., FOR CALCULATING CYCLE COUNT FOR COMMON CF34 ENGINE PARTS THAT ARE TRANSFERRED BETWEEN DIFFERENT CF34 ENGINE MODELS. *** FOR CF34-3A1 NOTE: NOT APPLICABLE TO ACE AVIATION CORP. *** FOR CF34=3B 3. Life Limits of Compressor Rotor Components. (Refer to Figure 602) Figure 601, Index Number Part Name Part Number Life Limit Cycles 1 Blisk, Stage 1 Compressor Rotor 5087T84P01 20, T84P02 20, T84P03 20,000 2 Shaft, Compressor Forward 5037T01P03 30, T01P04 30,000 3 Disk, Stage 2 Compressor Rotor 6036T91P01 15, T91P02 15,000 4 Spool, Stage 3 8 Compressor Rotor 6078T56P03 (1) 20, T56P04 (1) 20, T56P05 15,000 Page Revision: Reissue 09/22/2017

250 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Compressor Rotor Life Limits 5 Spool, Stage Compressor Rotor 5087T46P T46P02 15,000 15,000 6 Seal, Compressor Discharge Rotating 4019T38P01 30,000 7 Shaft, Compressor Rotor Rear 6087T03P03 15,000 NOTE: 8 Disk, Stage 9 Compressor Rotor 6087T01P02 15, T01P03 15,000 (1) Subject to inspection by Airworthiness Directive and AMOC dated February 14, Page Revision: Reissue 09/22/2017

251 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Compressor Rotor Life Limits *** FOR CF34-3B Figure 602 COMPRESSOR Rotor Life Limited Components Page Revision: Reissue 09/22/2017

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253 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks High Pressure Turbine Rotor Life Limits 1. General A. This section contains the FAA-approved life limits for the high - pressure turbine rotor (HPT) components. B. The life limit is determined by the total number of flight cycles (refer to , TIME LIMITS for the definitions and the calculations of cycles). C. The operator is responsible to make sure that the cycle-limited components are not operated beyond their established cycle limits. 2. Life Limits of High Pressure Turbine Rotor Components. CAUTION: IF YOU TRANSFER A LIFE-LIMITED PART FROM ONE CF34 MODEL TO ANOTHER CF34 MODEL, REFER TO , TIME LIMITS, PARAGRAPH 2.B., FOR CALCULATING CYCLE COUNT FOR COMMON CF34 ENGINE PARTS THAT ARE TRANSFERRED BETWEEN DIFFERENT CF34 ENGINE MODELS. *** FOR CF34-3A1 NOTE: NOT APPLICABLE TO ACE AVIATION CORP. 3. *** FOR CF34-3A1 MODIFIED TO SB NOTE: NOT APPLICABLE TO ACE AVIATION CORP. 4. Life Limits of High-Pressure Turbine Rotor Components. ***FOR CF34=3B (Refer to Figure 602) Figure 601, Index Number Part Name Part Number Life Limit Cycles 1 Seal, Balance Piston Air 5079T63P02 15,000 2 Shaft, HPT Rotor 5079T62P02 20,000 3 Plate, Stage 1 Front Cooling 5079T65P04 20, T65P06 20,000 4 Disk, Stage 1 Turbine 5079T52P08 15, T52P09 15,000 Page Revision: Reissue 09/22/2017

254 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks High Pressure Turbine Rotor Life Limits 5 Plate, Stage 1 Aft Cooling 5123T02P01 14,000 6 Plate, Stage 2 Rear Cooling 5079T56P02 20,000 7 Disk, Stage 2 Turbine 5079T73P02 15, T73P04 15,000 8 Plate, Stage 2 Front Cooling 5079T55P04 15,000 9 Coupling, Outer Torque 5079T64P05 20,000 Page Revision: Reissue 09/22/2017

255 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks High Pressure Turbine Rotor Life Limits *** FOR CF34-3B Figure 602 High-Pressure Turbine Rotor Life Limited Components Page Revision: Reissue 09/22/2017

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257 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Low Pressure Turbine Rotor Life Limits 1. General A. This section contains the FAA-approved life limits for the low - pressure turbine rotor (LPT) components. B. The life limit is determined by the total number of flight cycles (refer to , TIME LIMITS for the definitions and the calculations of cycles). C. The operator is responsible to make sure that the cycle-limited components are not operated beyond their established cycle limits. 2. Life Limits of Low Pressure Turbine Rotor Components. CAUTION: IF YOU TRANSFER A LIFE-LIMITED PART FROM ONE CF34 MODEL TO ANOTHER CF34 MODEL, REFER TO , TIME LIMITS, PARAGRAPH 2.B., FOR CALCULATING CYCLE COUNT FOR COMMON CF34 ENGINE PARTS THAT ARE TRANSFERRED BETWEEN DIFFERENT CF34 ENGINE MODELS. *** FOR CF34-3A1 NOTE: NOT APPLICABLE TO ACE AVIATION CORP. 3. Life Limits of High-Pressure Turbine Rotor Components. ***FOR CF34=3B (Refer to Figure 601) Part Name Part Life Figure 601, Index Number Limit Number Cycles 1 Shaft, Rear Turbine 6030T72P02 15,000 2 Disk, Stage 3 Turbine 6078T91P01 15, T91P02 15,000 3 Seal, Stage 3 and 4 Turbine 5023T59P02 15, T59P06 15,000 4 Disk, Stage 4 Turbine *6078T02P03 15, T02P04 15,000 Page Revision: 2 06/29/2018

258 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Low Pressure Turbine Rotor Life Limits 5 Disk, Stage 6 Turbine *6078T89P01 15, T89P03 15,000 6 Seal, Stage 5 and 6 Turbine 5023T64P02 15, T64P04 15,000 7 Disk, Stage 5 Turbine *6078T92P01 15, T92P02 15,000 8 Cone, Turbine Drive 5023T67P03 15,000 9 Seal, Stage 4 and 5 Turbine 5023T67P01 15, T67P02 Stage 4 turbine disks PN 6078T02P03, Stage 5 turbine disks PN 6078T92P01, and stage 6 turbine disks PN 6078T89P01, with the part and serial number referenced in SB (Latest Revision), were subjected to an internal repair of the bolt flanges (scalloped). These disks must be removed and scrapped at the next exposure, but not later than 17,000-cycles for the stage 4 turbine disk PN 6078T02P03, 15,000-cycles for the stage 5 turbine disk PN 6078T92P01, and 15,000 cycles for the stage 6 turbine disk PN 6078T89P01. Page Revision: 2 06/29/2018

259 GE CF34-3B ENGINE Chapter 3: Section: Engine Manufacturers Time Limitations & Maintenance Checks Low Pressure Turbine Rotor Life Limits *** FOR ALL Figure 601 Low-Pressure Turbine Rotor Life Limited Components Page Revision: 2 06/29/2018

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261 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 1 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International A. Airframe Make: Bombardier Model: CL-604 Source Source Document Part No. Section(s) Bombardier Time Limits and Maintenance Checks CH 605 TLMC Parts 1, 2 and 3 Comments: None B. Engine Make: General Electric Company Model: CF34-3B Source Source Document Part No. Section(s) Bombardier Time Limits and Maintenance Checks CH 605 TLMC Parts 2 and 3 Comments: None C. Auxiliary Power Unit Make: Honeywell Model: (CL) Source Source Document Part No. Section(s) Bombardier Time Limits and Maintenance Checks CH 605 TLMC Part 3 Comments: None D. Reduced Vertical Separation Minimum Source Source Document Part No. Section(s) Bombardier Time Limits and Maintenance Checks CH 605 TLMC Part 3 Note 1: Aircraft equipment checks only. Reference GMM Volume 1 sub-section 4.29 for generic policies and procedures (Training, Tool Calibration, etc.) Note 2: Reference 14 CFR Section for Height Monitoring

262 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 2 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International E. US Regulatory Tasks Source ATA Task Interval 14 CFR Weighing of Aircraft 36 Months 14 CFR Aircraft Registration renewal 36 Months 14 CFR (2), (c), 25 Emergency Locator Transmitter battery (2) useful life as established by the transmitter manufacturer under its approval Notes 1 & 2 14 CFR (2), (d) 25 Emergency Locator Transmitter Inspection 12 Months 47 CFR (f) ELT Registration 36 Months 14 CFR Altimeter system and altitude reporting equipment tests and inspections. 24 Months 14 CFR ATC transponder tests and inspections 24 Months 14 CFR 91, Appendix G 34 Height Monitoring Verification Initial 6 Months Thereafter 24 1,000 Note 3 Months or Hours Note 1: As stamped on battery Note 2: Batteries used in the Emergency Locator Transmitters must be replaced (or recharged, if the batteries are rechargeable) When the transmitter has been in use for more than 1 cumulative hour. [14 CFR (2), (c), (1)] Note 3: Whichever comes last

263 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 3 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International F. Airworthiness Directives (AD) - Repetitive AD Source ATA Task Interval R3 38 k) Inspections: Lavatory Paper and Linen Waste Receptacle Enclosure Access Doors and Disposal Doors - inspect for proper operation, fit, sealing, and latching for the containment of possible trash fires. Comments: None 1,000 Hours G. Ace Aviation Services (Ace) Generated Tasks Ace Aviation Services Ace Aviation Services Source ATA Task Interval Ace Aviation Services 05 Challenger 605 Service Check Note 1 05 Challenger Day Check 1 Month 08 Passenger Baggage Scale Check for Reasonable Accuracy Check scale with a known 50 Lb. weight - 1. Reading to be within ½ Lb. 2. Scale must be able to be zeroed. 3. Install date placard when complete 12 Months Note 1: Service Checks are performed after aircraft returns to home base or before aircraft departs from home base as practical. Note 2: Service Check compliance is updated in commercial maintenance tracking system. Scheduling is monitored by the Director of Maintenance.

264 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 4 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International H. Supplemental Time Limitations / Maintenance Checks Source ATA Task Interval Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM General Visual Inspection of the Cabin Placards - Internal 24 Operational Test of the Ground Fault Interrupters (GFI) 25 Operational Check of the Passenger Seat Inertia Reels (Including Divans) 25 General Visual Inspection of the Passenger Seat Restraints 25 Detailed Inspection of the Passenger Seats (Including Divans and Jumpseat) for Attachment and Locking 25 General Visual Inspection of the Galley Waste Container 25 General Visual Inspection of the Lavatory Waste Container 25 Detailed Inspection of the Emergency Exit Life Line 12 Months 12 Months 12 Months 24 Months 24 Months 12 Months 12 Months 24 Months 25 Detailed Inspection of the Life Vests 12 Months 25 Restoration of the Life Vests 60 Months 25 Detailed Inspection of the Life Rafts 12 Months 25 Restoration of the Life Rafts 36 Months

265 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 5 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International H. Supplemental Time Limitations / Maintenance Checks (continued) Source ATA Task Interval Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Visual Inspection of the First Aid Kit Seal 12 Months 25 Restoration of the Flashlights 12 Months 25 Detailed Inspection of the Smoke Goggles 24 Months 25 Detailed Inspection of the Smoke Hoods 12 Months 25 Discard the Smoke Hoods 126 Months 26 Restoration of the Lavatory Smoke Detector 60 Months 26 Restoration of the Baggage Compartment Smoke Detector 26 Functional Test of the Portable Fire Extinguisher (Weight Test) 60 Months 12 Months 26 Restoration of the Portable Fire Extinguisher 72 Months 26 Functional Test of the Portable Fire Extinguisher (Hydrostatic Test) 144 Months 33 Operational Test of the Ordinance Signs 12 Months 33 Operational Test of the Interior Emergency Lights 12 Months

266 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 6 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International H. Supplemental Time Limitations / Maintenance Checks (continued) Source ATA Task Interval Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Functional Test of the Self-Illuminated Exit Sign 35 Functional (Hydrostatic) Test of the Oxygen Cylinder Assembly (PN: ) 35 Discard of the Oxygen Cylinder Assembly (PN: ) 35 Operational Test of the Passenger Oxygen System 35 Functional Test of the Passenger Oxygen System 35 Operational Test of the Crew Oxygen System Modifications Masks 35 Restoration of the Crew Oxygen System Modifications Masks 35 General Visual Inspection of the Portable Oxygen Cylinder, Regulator, and Mask 35 Functional (Hydrostatic) Test of the Portable Oxygen Cylinder and Regulator 35 Detailed Inspection of the Protective Breathing Equipment (PBE) 35 Discard the Protective Breathing Equipment (PBE) 24 Months 36 Months 180 Months 24 Months 36 Months 12 Months 72 Months 12 Months 36 Months 12 Months 120 Months 38 Sanitization of the Potable Water System 6 Months

267 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 7 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International H. Supplemental Time Limitations / Maintenance Checks (continued) Source ATA Task Interval Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Bombardier Doc. TE SM, SMM Detailed Inspection of the Air Pressure Regulator 6 Months 38 Functional Test of the Air Pressure Regulator 6 Months 38 General Visual Inspection of the Water Distribution Lines 12 Months 38 General Visual Inspection of the Water Tank 12 Months 38 Restoration of the Bleed Air Filter 6 Months 38 Restoration of the Water Filter Assembly (Replace Filter Cartridge) 38 Functional Test of the Water Heater Pressure Relief Valve 38 Restoration of the Water Filter Assembly (Replace Gasket Set) 38 Operational Test of the Floor Mat Activated Solenoid Valve 38 General Visual Inspection of the Waste Disposal System 6 Months 36 Months 48 Months 6 Months 1200 Hours 38 Cleaning of the Toilet Assembly 1200 Hours 44 Operational Test of the Passenger Notification System 400 Hours

268 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 8 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International H. Supplemental Time Limitations / Maintenance Checks (continued) Source ATA Task Interval TLMC TASK TLMC TASK * Special Detailed Inspection of the Pressure Floor FS409 to FS559, FS513 RBL to RBL * Detailed Inspection of the Pressure Floor Skin and Floor Angles FS439 to FS461.5 and FS484 to FS539, RBL to RBL Landings Landings Landings Landings Landings TLMC TASK TLMC TASK TLMC TASK * Detailed Inspection of the Floor Beams RBL27.00, FS to FS and LBL9.00, FS to FS * Detailed Inspection of the Fuel Tank Water Drain Holes, 5.00 FWD * Special Detailed Inspection of the Wing Fuel Access Holes REO , Access 510CB REO , Access 540AB REO , Access 510/610AB, 640BB REO , Access 550CB Landings Landings Landings Landings Landings Landings Landings Landings Landings Landings Landings Landings TLMC TASK TLMC TASK TLMC TASK Comments: 57 * Detailed Inspection of the Lower Wing Plank, Wing Center Front Spar Web Assembly, Splice, Lower Cap and Lower Spar Splice Angle (AFT Web-Bonded Doubler Installation); LBL29.42 and RBL * Special Detailed Inspection of the Wing Center Front Spar-Web and Doubler between LBL22.50 and RBL * Special Detailed Inspection of the Wing Center Front Spar Lower Cap Flanges Web; LBL29.42 and RBL29.42 * Airworthiness Limitation SMM: Bombardier Supplemental Maintenance Manual TE SMM Landings Landings Landings Landings Landings Landings

269 Ace Aviation Services Corporation General Maintenance Manual - Volume 5 Chapter 4 Time Limitation List Revised: 06/29/2018 Registration No.: N699ST Revision: 2 Serial No.: 5743 Page 9 of 9 TLL No.: Computerized Maintenance Tracking Program: CAMP Systems International I. Instructions for Continued Airworthiness Scheduled Maintenance and Inspection Tasks None Source ATA Task Interval

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271 GMM Volume 5 / Chapter 5 SERVICE CHECK Model: CL 605 Registration: TAT: S/N: TAL: APU Time: Hours: Date: A. INSTRUCTIONS 1. A Service Check is required to be accomplished whenever a flight has occurred, is returning to or departing from home base as practical. Or; a. If the aircraft has not flown in 7 days, step Y will be required to be performed. Step Y. may be extended 3 days at the discretion of the Director of Maintenance. b. If the aircraft has not flown in 30 days, step Z is to be performed. Step Z may be extended 7 days at the discretion of the Director of Maintenance. 2. A qualified mechanic may perform and complete the Service Check. Each line item is to be initialed by the person completing the task 3. For line items not requiring inspection, such as equipment not installed or not applicable to model aircraft inspected, enter, N/A for, Not Applicable in the initial block and place initial of person determining not applicable status to the right of the initial block. 4. A Service Check notation, including date, full signature and certificate number of person authorized to certify Airworthiness shall be entered within the Aircraft Maintenance Flight Log. ACE Form-CL Revision: 2 06/29/2018 Page 1 of 11

272 EXTERNAL SERVICE CHECK: ACE AVIATION SERVICES, CORP. GMM Volume 5 / Chapter 5 SERVICE CHECK ACE Form-CL Revision: 2 06/29/2018 Page 2 of 11

273 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic A. PREPARATION 1. Check Aircraft Maintenance Flight Log / Flight Canister for: Open discrepancies. If the aircraft has not flown in 7 or 30 days and step V. or W. need compliance. Open deferrals that may require attention. 3. Remove all covers and plugs as applicable to perform this check. B. LEFT UPPER FUSELAGE (FORWARD) 1. Oxygen blowout plug... Intact Passenger door emergency light Condition 2. Alternate static port.. Clear 3. Free movement/ AOA vane.. condition 4. Standby pitot probe Clear 5. Ice detector probe.. Clear 6. Pitot Static Probe... Clear 7. Radome. Check, secured 8. External Lights..Check 9. Windshields, windows.. Check 10. Nose landing lights Check C. NOSE AND GEAR WARNING Hydraulically operated nose doors open and shut rapidly. Stay clear when doors are operated. 1. Area Security. Verified 2. Wheel Chocks.. As required 3. Tires and wheels.. Condition 155 PSI +5%, - 0% Reference MM Record Tire Pressure on step Y. If service needed, write up on AMFL as a discrepancy item. 4. Oleo Extension (3.5 inches minimum). Check 5. Steering actuator.. Check 6. Rear door... Check 7. Down lock safety pin Check, installed 8. ADG safety pin..check, installed 9. Brake accumulator gauges (2).. Check. Ensure Record Pressure on step Y. pressure between If service needed, write up on AMFL as a 700 and 800psi. discrepancy item. 10. Circuit breakers (JB6) Closed 11. Fluid Leaks Check ACE Form-CL Revision: 2 06/29/2018 Page 3 of 11

274 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic D. RIGHT UPPER FUSELAGE (Forward) 1. External AC power service door.. Secured 2. ADG door Secured 3. Oxygen service door Secured 4. Pitot static probe.. Clear 5. Ice detector probe. Clear 6. TAT probe Clear 7. Aux AOA probe... Clear 8. Free movement/ AOA Vane... condition 9. Alternate static port.. Clear 10. Refuel/defuel adapter door Secured 11. Wing inspection lights.. Condition 12. Refuel/defuel panel door... Secured 13. Overwing emergency lights (3) Condition 14. Overwing emergency exit. Secured E. RIGHT LOWER FUSELAGE (Forward) 1. Antennae; ATC, ADF, TCAS, VHF 2 & DME 1 (if installed) Check F. RIGHT MAIN GEAR (Front) 1. Area security. Verified 2. Wheel chocks As required 3. Tires and wheels Condition 184 PSI +5% - 0% Reference M/M Record Tire Pressure on step Y. If service needed, write up on AMFL as discrepancy item. 4. Breaks and Wear pins (pin must protrude) Check 5. Gear door.. Secured 6. Fluid leaks. Check 7. No. 3 hydraulic accumulator gauge.. Check. Nominal Record Pressure on step Y. If service needed, write up on AMFL as a discrepancy item. pressure is 1,450 to 1,550 psi at 50 F. 8. Downlock safety pin. Installed G. RIGHT WING 1. Filler caps (2).Secured 2. Landing and taxi lights.. Condition ACE Form-CL Revision: 2 06/29/2018 Page 4 of 11

275 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic G. RIGHT WING (Continued) 3. Leading edge. Condition 4. Leading edge sealant Condition 5. Engine intake Clear 6. Ram air inlet. Clear 7. Upper wing surface Condition 8. Lower wing surface... Condition 9. Wing anti-ice louvers Clear 10. Fuel and water drains Check 11. Fuel vent valve.. Check 12. Navigation and strobe lights. Condition 13. Winglet.. Condition 14. Static dischargers (7). Condition 15. Fluid leaks. Check 16. Flight control surfaces.. Clear, Ensure proper clearance from GSE or other obstructions. Ensure surfaces clear of any contaminates 17. Trailing edge. Condition 18. Aileron.. Condition 19. Flaps.. Condition 20. Flight spoilers Condition 21. Ground spoilers. Condition 22. NACA vent Clear H. RIGHT MAIN GEAR (Aft) 1. Area security. Verified 2. Fluid leaks. Check 3. Tires and wheels Condition 4. Oleo extension (2 inches minimum) Check 5. Breaks and Wear pins (pin must protrude). Check I. RIGHT FUSELAGE (Aft) 1. Engine anti-ice blowout plug Check/flush 2. Fluid leaks. Check 2. Engine cowls. Condition /secured 3. Thrust reverser.. Stowed 4. Engine drains. Clear 5. Engine fuel vent ports Clear 6. Engine exhaust/jetpipe.. Condition / clear 7. Engine pylon.. Condition ACE Form-CL Revision: 2 06/29/2018 Page 5 of 11

276 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic I. RIGHT FUSELAGE (Aft) (Continued) WARNING APU EXHAUST DANGER AREA (15 feet) 8. APU exhaust. Condition / clear 9. External DC power door Secured J. EMPENNAGE 1. Flight control surfaces.. Clear, Ensure proper clearance from GSE or other obstructions. Ensure surfaces clear of any contaminates. 2. Fluid leaks. Check 3. Horizontal stabilizer.. Check 4. Vertical stabilizer.. Check 5. Elevators Check 6. Rudder... Check 7. Static dischargers (12)... Check 8. Navigation and strobe lights..condition 9. Tail vent Clear 10. Antennae; VOR/LOC (both sides of fin) and HF. Check 11. Dump mast Condition / clear K. AFT EQUIPMENT BAY 1. Rear fuse service lights..on 2. APU enclosure.. Check 3. Engine firex bottles (2)..Normal pressure 4. APU firex bottle Normal pressure 5. No. 1 & 2 hydraulic systems Check If service needed, write up on AMFL as a discrepancy item. No. 1 & 2 hydraulic accumulator gauges... Check. Nominal 6. Record Pressure on step BB. pressure is 1,450 If service needed, write up on AMFL as a to 1,550 psi at discrepancy item 50 F. 7. Circuit breakers (JB5) Closed 8. Engine oil refill system Add Engine Oil as required. Also note amount oil added to AMFL for oil consumption tracking Check Oil added quantity: Left Qts Right Qts ACE Form-CL Revision: 2 06/29/2018 Page 6 of 11

277 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic K. AFT EQUIPMENT BAY (Continued) 9. Area security and condition.. Check 10. Rear fuse service lights. Off 11. Bay door Secure/closed L. LEFT LOWER FUSELAGE (Aft) 1. Antennas; Marker beacon, Radio altimeter (2), and DME (2).. Check 2. Fluid leaks. Check M. LEFT UPPER FUSELAGE (Aft) 1. Engine anti-ice blowout plug Check/flush 2. Fluid leaks. Check 3. Engine cowls. Condition / secured 4. Thrust reverser.. Stowed 5. Engine drains. Clear 6. Engine fuel vent ports Clear 7. Engine exhaust/jetpipe.. Condition / clear 8. External ground air door Secured N. CARGO BAY 1. Cargo bay door Secured O. LEFT MAIN GEAR (Aft) 1. Area security. Verified 2. Fluid leaks. Check 3. Tires and wheels Condition 4. Oleo extension (2 inches minimum) Check 5. Breaks and Wear pins (pin must protrude) Check P. LEFT WING 1. Filler caps (2).Secured 2. Landing and taxi lights.. Condition 3. Leading edge. Condition 4. Leading edge sealant Condition 5. Engine intake Clear 6. Ram air inlet. Clear 7. Upper wing surface Condition 8. Lower wing surface... Condition 9. Wing anti-ice louvers Clear 10. Fuel and water drains Check 11. Fuel vent valve.. Check 12. Navigation and strobe lights. Condition 13. Winglet.. Condition ACE Form-CL Revision: 2 06/29/2018 Page 7 of 11

278 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic P. LEFT WING (Continued) 14. Static dischargers (7). Condition 15. Fluid leaks. Check 16. Flight control surfaces.. Clear, Ensure proper clearance from GSE or other obstructions. Ensure surfaces clear of any contaminates. 17. Trailing edge. Condition 18. Aileron.. Condition 19. Flaps.. Condition 20. Flight spoilers Condition 21. Ground spoilers. Condition 22. NACA vent Clear Q. LEFT MAIN GEAR (Front) 1. Area security. Verified 2. Wheel chocks As required 3. Tires and wheels Condition 4. Breaks and Wear pins (pin must protrude).. Check 5. Gear door.. Secured 6. Fluid leaks. Check 7. Downlock safety pin. Installed R. LEFT UPPER FUSELAGE (Forward) 1. Wing inspection lights. Condition 2. Antennae; VHF 1, ATC 1, and TCAS (if installed).. Check S. ENTERING AIRPLANE 1. Boarding lights. Check 2. Stairs. Check T. COCKPIT 1. Scan cockpit for general visual inspection and safe to apply power, ensure circuit breakers are set as desired.. Check 2. Overhead panel - BATT MASTER switch select -... to ON: Apply external AC power or start APU 3. Oxygen system pressure Check: O2 pressure & qty sufficient. OXY LO PRESS caution message out. If service needed, write up on AMFL as a discrepancy item. 4. HYDRAULIC PANEL select Hydraulic synoptic page. Check: Fluid If service needed, write up on AMFL as a quantities discrepancy item. ACE Form-CL Revision: 2 06/29/2018 Page 8 of 11

279 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic T. COCKPIT 5. Turn on the following lights and ensure operation:. NAV Lights Anti/Collision Wing-Inspection Check Nose Recog / Taxi U. GALLEY 1. Lighting... Check 2. General visual inspection of galley for condition and cleanliness Check V. CABIN 1. Lighting... Check 2. General visual inspection of cabin for condition and cleanliness Check W. LAVATORY / CARGO COMPARTMENT 1. Lighting... Check 2. General visual inspection of lavatory and cargo compartment for condition and cleanliness.. Check X. CABIN AND FLIGHT COMPARTMENT EMERGENCY EQUIPMENT Verify condition and security of: Crash axe Fire extinguishers Life vests 1. Oxygen masks Check Flashlights PBE s Seatbelt extensions ACE Form-CL Revision: 2 06/29/2018 Page 9 of 11

280 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Item Inspection Description Mechanic Y. 7-DAY CHECK (Performed only if aircraft not flown in last 7 days) Perform complete AFM check list for engine start. Run 2. engines at ground idle for minimum of 10 minutes. Perform normal AFM shutdown. A qualified pilot may perform the run. Perform 3. Check engine oil level post shut down... Check Z. 30-DAY CHECK (Performed only if aircraft not flown in last 30 days) 1. Perform complete AFM check list for engine start through takeoff. Perform take off power check for both engines a minimum of five minutes. Perform normal AFM shutdown. A qualified pilot may perform the run Perform 2. VOR bearing check Perform AA. 1. FAA CRS Performing VOR Check: CLOSE OUT ALL STEPS Re-install all covers and plugs removed to perform this check, unless the aircraft is departing. If aircraft is departing, ensure Check covers and plugs stowed. ACE Form-CL Revision: 2 06/29/2018 Page 10 of 11

281 GMM Volume 5 / Chapter 5 SERVICE CHECK Reg. No.: N Date: Part IV: RECORDED INFORMATION BB. PRESSURES Oxygen: As Checked After Service (Note 1) # 1 Nose Tire: #1 Brake Accumulator: # 2 Nose Tire: #2 Brake Accumulator: #1 Main Tire: As Checked # 1 Hydraulic Accumulator: # 2 Main Tire: # 2 Hydraulic Accumulator: # 3 Main Tire: # 3 Hydraulic Accumulator: # 4 Main Tire: If no Service required, place, N/A in After Service Block. Note 1: If service needed, write up on AMFL as a discrepancy item. After Service (Note 1) ACE Form-CL Revision: 2 06/29/2018 Page 11 of 11

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283 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Model: CL-605 S/N: Date: TAT: TAL: Auxiliary Power Unit (APU) Meter Reads: A. Instructions 1. A 30 Day Check shall be performed at least once each thirty (30) day period Time In Service. The Director of Maintenance or designee may extend the 30 Day Check 7 days. Any time extended however is to be bought back, thus preserving the 30 day integrity. 2. A properly certificated and approved mechanic may perform and complete a 30 Day Check. Each line item is to be initialed by the person completing the task 3. For line items not requiring inspection, such as equipment not installed or not applicable to model aircraft inspected, enter, N/A for, Not Applicable in the initial block and place initial of person determining not applicable status to the right of the initial block. 4. A 30 Day Check notation, including Date, full signature and certificate number of person certifying Airworthiness shall be entered within the Aircraft Maintenance Flight Log. 5. Completion of a 30 Day Check satisfies the requirement for a Service Check. However, if the 7 Day or 30 Day requirement of the Service Check are due, then that portion of the Service Check must be accomplished. Part I: EXTERIOR Item Inspection Description Mechanic B. Forward Fuselage Area Left Right 1. Remove all covers and engine plugs. 2. Check Radar Dome for condition, evidence of damage, latches secure; Open forward Avionics Bay Doors inspect forward battery for 3. condition, security, and connections secure. Check CB 6, Circuit breakers in. Close and secure Avionics Bay Door Latches. 4. Check Windshield and Side Window for damage, discoloration and cleanliness 5. Check Pitot Head for damage, security and obstruction. Check Angle of Attack (AOA) Vane for damage, condition, 6. security, and full free movement. Note: Stow AOA Vane in horizontal position. 7. Check Static Port for damage, obstruction, surrounding skin damage or aberration. Revision: 1 3/5/2018 ACE Form-CL Page 1 of 16

284 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part I: EXTERIOR Item Inspection Description Mechanic B. Forward Fuselage Area (Continued) Left Right 8. Check Entrance Door (Exit) Emergency Light for damage condition. (L/H) 9. Check Entrance Door for condition and operation. Check seal for condition. 10. Check Oxygen System Pressure is psi; close and secure Oxygen panel. (R/H) 11. Check Oxygen System Blow-Out Plug Green and intact. 12. Check Ice Detector Light for condition and operation. Check Fuselage for condition, damage, cleanliness, access panels 13. closed/secured, evidence of fluid leakage. Check Cabin Windows for condition and cleanliness. C. Nose Landing Gear (NLG) / Bay Area 1. No.3 Hydraulic System; check doors open. 2. Check Bay Doors for condition, security Check NLG Door and Wheel Well Bay for condition, damage, security of installation and evidence of hydraulic fluid leakage; 3. check retraction actuating cylinder for security and leakage. Note: NLG Bay Doors must be opened to access the bay area. Check Rear Landing Gear Doors and Steering Actuator for 4. condition, security and leakage. Check Brake Accumulators (2 ea) at 700 to 800 PSI. 5. Record Pressure on step Q. If service needed, write up on AMFL as a discrepancy item. 6. Check NLG Uplock Pins for condition and security. 7. Check Nose Gear Door Cannon Plug for condition and connected. 8. Check Downlock Pin removed. 9. Check Weight on Wheels Switch, and electrical harness for condition and security. 10. Check Proximity Switches intact. 11. Air Driven Generator (ADG) pin installed (with, Remove Before Fly streamer). Revision: 1 3/5/2018 ACE Form-CL Page 2 of 16

285 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part I: EXTERIOR Item Inspection Description Mechanic C. Nose Landing Gear (NLG) / Bay Area (Continued) Left Right 12. Check NLG Oelo Strut for condition, cleanliness and extension Limit: 3.5 inches minimum 13. Check NLG Wheels for condition, damage and security. 14. Check NLG Tires for tread wear, condition, damage and tire inflation of 155 PSI +5%, - 0% Reference MM Record Tire Pressure on step Q. If service needed, write up on AMFL as a discrepancy item. 15. Check NLG Locking Pin in place. Close NLG bay doors. D. Wing Area 1. Check Taxi and Landing Light for condition and security. 2. Check Leading Edge for condition and Anti-Ice Exhaust Outlets for condition and obstructions. 3. Check Winglet Exterior for damage and condition, access panels closed and secured. 4. Check Main Fuel Tank Filler Cap for security and legible placarding. 5. Check Main Fuel Tank for evidence of leakage. 6. Check Navigation and Anti-Collision Light for damage and condition. 7. Check Static Dischargers for damage and condition, including missing elements. 8. Check Aileron for condition, leakage of fluid from flutter dampers; manually check for free play and there is no movement. 9. Check Flight Spoiler for condition, fluid leakage and there is no movement 10. Check Ground Spoiler for condition, fluid leakage and there is no movement 11. Check Flaps, Hinges, and Vanes for condition and movement. 12. Check Main Fuel Tank Drain for condition, obstruction, evidence of leakage, drain condensate. 13. Check Auxiliary Fuel Tank Vent Valve Exhaust for condition and obstruction. 14. Check NACA Scoops for condition. Revision: 1 3/5/2018 ACE Form-CL Page 3 of 16

286 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part I: EXTERIOR Item Inspection Description Mechanic E. Main Landing Gear (MLG) / Bay Area Left Right Check MLG Door and Wheel Bay Area for condition, damage, security installation and evidence of hydraulic fluid leakage; a) Check Well Bins for damage/security; 1. b) Check Hydraulic Actuating Cylinder for security and leakage; Check Down Lock is flush; c) Check Overheat Detectors (Sensing Loop) for condition and security; d) Check Uplock for condition and security. 2. Check MLG Oleo Strut for condition, cleanliness, and extension. Limit: 2 inches minimum. Check Main Tires for tread wear, condition, damage and tire inflation Aircraft on ground: 184 PSI +5% - 0% Aircraft on jacks: 177 PSI +5% - 0% Reference M/M Record Tire Pressure on step Q. If service needed, write up on AMFL as a discrepancy item. Check main Wheels for condition, damage, security and evidence of hydraulic fluid leakage; Check wheel Brakes Wear Index Pins are protruding with brakes set. Brake lines for leaks, damage and security. 6. Check MLG Weight on Wheel (WOW) Switches/Sensors and harness for condition and security. 7. Check MLG Locking Pins in place. 8. Check No. 3 Hydraulic Accumulator gauge pressure. Nominal pressure is 1,450 to 1,550 psi at 50 F. Record Pressure on step Q. If service needed, write up on AMFL as a discrepancy item. Revision: 1 3/5/2018 ACE Form-CL Page 4 of 16

287 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part I: EXTERIOR Item Inspection Description Mechanic F. Mid Rear Fuselage Area Left Right 1. Check Cabin Windows for condition and cleanliness. Open Baggage Compartment Door, check for condition; check interior for condition, damage, liners secure; check seal; close and 2. secure compartment door; ensure external handle correctly stowed. (L/H) Check ACU Exhaust Plugs removed; check for damage, condition 3. and obstruction. Check Fuel Vent Shroud Drains for condition, evidence of 4. leakage. Open access panel and check APU Fault Panel clear of all flag 5. indicators; reset as necessary. (L/H) Check Ground Air Supply Inlet (Pneumatic) for condition; ensure 6. check valve undamaged and in closed position; close and secure access panel. (L/H) 7. Check all Service Doors, Access Panels are closed/secured. 8. Check APU Witness Drains for excessive leakage. 9. Check Lower Fuselage Antennas for condition and security. 10. Check Ram Air Intake for condition and obstruction. 11. Check APU Inlet for condition and obstruction. 12. Check APU Exhaust for condition and obstruction. (R/H) 13. Check 28 VDC Ground Power Unit (GPU) Receptacle for condition; check access cover for security. (R/H) 14. Check Hydraulic System Service Door is closed/secured Check Fuselage Exterior for damage, condition, access panels closed/secured, evidence of fluid leakage. Check Over-Wing Emergency Exit Lights (3 each) for condition and security. (R/H) Check Over-Wing Emergency Exit is closed/secured; window cleaned. (R/H) Revision: 1 3/5/2018 ACE Form-CL Page 5 of 16

288 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part I: EXTERIOR Item Inspection Description Mechanic G. Aft Equipment Bay 1. Open Equipment Bay Door, check door and seal for condition. Check Interior of Bay for general condition and cleanliness. 2. Check Service Light for condition and operation. 3. Check APU Enclosure for condition and fluid leaks. 4. Check APU Service Door is secure. 5. Check Outflow Valves (2 each) are clear. Check Engine Fire Extinguisher Bottles (2 each) proper pressure and that squibs are secure. 6. F PSIG F PSIG Check Pneumatic Ducting condition. 8. Check Battery for condition, security, and connections secure. 9. Check Battery Direct Bus-Circuit Breakers are in. 10. Check left/right ACU for condition, security, leakage. 11. Check No.1 and No. 2 Hydraulic Reservoir Fluid Level, Accumulators (2 each) have 1450 to 1550, no fluid leakage and Indicators for condition. Record Pressure on step Q. If service needed, write up on AMFL as a discrepancy item. Check Remote Engine Oil Reservoir for condition, leakage. 12. Add Engine Oil as required. Also note amount oil added to AMFL for oil consumption tracking Oil added quantity: Qts Qts Left Right Revision: 1 3/5/2018 ACE Form-CL Page 6 of 16

289 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part I: EXTERIOR Item Inspection Description Mechanic G. Aft Equipment Bay (Continued) Check APU Fire Extinguisher Bottle for proper pressure. 13. F PSIG , , Close, secure equipment bay door. H. Pylon Left Right 1. Check Pylon for evidence of leakage, damage, general condition. 2. Open cowlings perform a General Visual Inspection (GVI) of Engine Components and Accessories. Inspect for excess leakage of fuel, oil, and hydraulic systems. 3. Check Anti-Ice Over-Pressure Relief Valve for condition. 4. Check Engine Intake Area for condition, obstructions, FOD. Check Fan Turbine Blades for condition. 5. Check Engine Drain Lines for condition and evidence of leakage. 6. Check Engine Exhaust Area and Shrouds for damage, general condition and security. 7. Check Pylon Light for condition. 8. Check Engine Upper and Lower Cowlings for condition, damage, and latches secure; check access panels closed and secured. Revision: 1 3/5/2018 ACE Form-CL Page 7 of 16

290 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part I: EXTERIOR Item Inspection Description Mechanic I. Empennage Left Right 1. Check Horizontal Stabilizer for position, condition, damage access panels closed/secured, and evidence of fluid leakage. 2. Check Horizontal Stabilizer Static Dischargers for damage or missing elements. 3. Check Elevator for damage, general condition. Check Flutter Damper for leakage. Check Static Dischargers for damage or missing elements. 4. Check Vertical Stabilizer for damage, condition, access panels closed/secure and evidence of fluid leakage. 5. Check Vertical Stabilizer Static Dischargers for damage or missing elements. 6. Check Rudder for condition, evidence of leakage; Static Dischargers for damage or missing elements. 7. Check condition and security of Antennas. Check Tail Cone, Navigation Lights for damage, condition Static 8. Dischargers for damage or missing elements. J. Exterior Lighting Check operation of Exterior Lighting systems: a. Taxi Lights. b. Anti-Collision Beacons c. Navigation Lights. 1. d. Landing / Recognition Lights. e. Wing Ice Inspection Lights. f. Emergency Door Egress Lights. g. Exterior Service Lights. h. Logo Lights (Left & Right) Revision: 1 3/5/2018 ACE Form-CL Page 8 of 16

291 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part II: INTERIOR Item Inspection Description Mechanic K. Interior Lighting Check operation of Flight Compartment Lighting systems: a. Map Lights. b. Instrument panel lights. c. Instrument / indicator lights. 1. d. Light dimming switches / devices. e. Crew warning / advisory panel lights. f. Panel overlays. g. Cockpit service lights. Check operation of Passenger Compartment Lighting systems: a) Seat lights. b) Overhead lights. c) Reading lights. 2. d) Lavatory lights. e) Warning lights f) Galley lights g) Emergency exit lighting. h) Baggage compartment lights. L. Cockpit and 135 Requirements Check for current and legible; a) Aircraft Registration, 1. b) Certificate of Airworthiness, c) FCC Radio License. Manuals - Check, that the following are on board and in good condition: a) Flight Manual, 2. b) Weight & Balance Manual, c) Quick Reference Check List, d) Pilots manual Check Cockpit Headliner, Side Panels, Floor Covering for; a) General condition and security, 3. b) Legibility of placards; Check Pedestal Controls for condition. Part II: INTERIOR Revision: 1 3/5/2018 ACE Form-CL Page 9 of 16

292 Reg. No.: Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Date: Item Inspection Description Mechanic L. Cockpit and 135 Requirements (Continued) Check Cockpit Instrument and Control Panel Indicators/MFD s for broken or cracked glass, sticking indicators. 4. With power on the aircraft, check cockpit EFIS and Instrument Lighting and Annunciator Panels for operation. Check cockpit Electrical Control and Circuit Breaker (CB) 5. Panels for condition, legibility of marking, applicable circuit breakers are in. Check Microphones, Headsets, Speakers, PA, & Intercom for condition and operation. 6. Check communications and navigation Control Heads/Panels for condition, legibility and security of installation. Check Flight Crewmember, Observer Seat(s), shoulder harness 7. and Safety Belts for condition and operation and TSO tag for legibility and attachment. M. Passenger Compartment 1. Check Forward Closet for condition, all loose objects secured Check Buffet/Galley Compartment Doors, Drawers closed, secured, and Trash Containers empty. Check Buffet/Galley Equipment for condition, security and cleanliness; check Electrical Panel circuit breakers are In. Check Passenger Seats, Chairs, Lounges reclining and swivel mechanism operation. Check Passenger Seat Belts and shoulder harnesses for condition, cleanliness and operation and TSO tag for legibility and attachment. Place all Seats, Chairs to the full upright position, center seats or chairs facing aft or forward. Check Passenger Compartment Electrical Control and annunciator control panel, circuit breakers are In as required. Check all Cabin Windows and Shades for condition and cleanliness. With power on the aircraft; a) Check all Passenger Service Units, Vents, and Call System for condition and operation. b) Check Passenger Entertainment Center and associated equipment for condition and operation. Part II: INTERIOR Revision: 1 3/5/2018 ACE Form-CL Page 10 of 16

293 Reg. No.: Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Date: Item Inspection Description Mechanic M. Passenger Compartment (Continued) 10. Check Lavatory Area for condition, security, and cleanliness. 11. Check Lavatory for operation, and Trash Containers empty. 12. Check Aft Closet for condition, all loose objects secured. Check Aft Baggage Compartment for condition, cleanliness and 13. all loose objects secured. Fly-Away Kit (If Installed) - Check a) Condition of Container, b) If Kit has been opened; 14. i. Condition of Contents, ii. Quantity of Contents, iii. Presence of Documents Check Exterior Baggage Door operation from inside the 15. compartment. N. Emergency Equipment Check operation of all No Smoking, Fasten Seat Belt Signs within 1. passenger compartment. 2. Check operation of Aft Baggage Smoke Detector system Check Crew Member and Passenger Life Vests for; a) Proper Location by Passenger Briefing Card, b) Currency c) Life Vest Envelope sealed. d) Record Due Date & Serial Numbers in Part III of this Task Card. Check Cockpit Portable Fire Extinguisher secure in mounting, pressure in the green and weight check placard for presence, legibility and inspection current. Check Passenger Cabin Fire Extinguisher secure in mounting, pressure in the green and weight check placard for presence, legibility and inspection current. Check both First Aid Kit secure in mounting and sealed. Note: If seal broken, First Aid Kit shall be checked for contents and re-sealed. Check Cockpit/Cabin Portable Oxygen Walk Around Bottle, Regulator and Masks secure in mounting, bottle pressure is 1800 psi. Revision: 1 3/5/2018 ACE Form-CL Page 11 of 16

294 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part II: INTERIOR Item Inspection Description Mechanic N. Emergency Equipment (Continued) 8. Check Life Rafts (2 each) with at least one ELT provided are current, securely stowed. 9. Check Passenger Safety Information Cards available to each passenger. 10. Check opening, closing, and securing Over Wing Emergency Exit window. 11. Check Crewmember Oxygen Quick Donning Masks for condition and stowage. 12. Check Flight Crewmember Smoke Masks or Glasses for condition and security of stowage. 13. Check Crewmember Flashlights (3 each) for condition and security of stowage. 14. Check Emergency Locator Transmitter (ELT) for condition, security. CAUTION: DO NOT PULL GREEN TAB Check Emergency Defibrillator (if installed) for; a) Location, 15. b) Two sets of batteries, c) Batteries current, d) One set of paddles and paddles are current. Perform Unit Self-Test. AED/CPR Responder Pack (if installed) for; 16. a) Nylon Bag for condition b) Pack contents for condition c) Expiration dates of consumables Note: Replace any that expire within 30 days Reference Part III, Figure 1. Revision: 1 3/5/2018 ACE Form-CL Page 12 of 16

295 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part II: INTERIOR Item Inspection Description Mechanic O. Placards and Markings Check all required Exterior Placards and Markings for condition and legibility for items such as (but not limited to); a) Entrance Door, b) Exits, c) Baggage Compartment Doors, d) Door And e) Window Emergency Exits/Door And Window Procedural 1. Text, f) Right Wing Non-Skid Escape Path, g) Fuel, h) Oil, i) Other Fluid, j) Oxygen, k) Nitrogen Servicing Placards 2. (Reference Maintenance Manual). Check all required Interior Placards and Markings for condition and legibility for items such as (but not limited to); a) Cockpit/Cabin Compartment Emergency Equipment location (Portable Fire Extinguisher, Portable Oxygen/Regulator/Mask, Crash Axe, First Aid Kit), b) Emergency Exit Signs, c) No Smoking/Fasten Seat Belt signs, d) Floatation/Survival Equipment location, e) Lavatory No Smoking Signs, f) Prohibition of Placing Smoking Materials in Trash Container, Opening Exit(S) Markings, g) Lavatory Return To Seat, h) Storage Compartments Maximum Weight, i) Centering of Chairs, j) Seat Backs in Upright Position, k) Door and Window Exit Markings/Text. Revision: 1 3/5/2018 ACE Form-CL Page 13 of 16

296 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Part III: RECORDED INFORMATION P. LIFE VESTS Note: Replace any Life Vest with 45 days or less remaining to expiration. No. DUE DATE S/N No. DUE DATE S/N Lav 6 Pilot 7 Co-Pilot Q. PRESSURES As Checked After Service O2: # 1 Nose Tire: #1 Brake Accumulator: # 2 Nose Tire: #2 Brake Accumulator: #1 Main Tire: As Checked # 1 Hydraulic Accumulator: # 2 Main Tire: # 2 Hydraulic Accumulator: # 3 Main Tire: # 3 Hydraulic Accumulator: # 4 Main Tire: If no Service required, place, N/A in After Service Block. After Service If service needed for any of the above, write up on AMFL as a discrepancy item. Revision: 1 3/5/2018 ACE Form-CL Page 14 of 16

297 Ace Aviation Services Corporation GMM Volume 5 / Chapter 5 Challenger CL-605 Series 30 Day Check Reg. No.: Date: Figure 1 AED/CPR Responder Pack (P/N AMP1014) Contents 2 ea CPR Responder Masks 4 ea Gloves, Nitrile (Latex Free) Pairs 1 ea Shears 1 ea Razor, Medical Prep 1 ea Towel, Dry Absorbent 2 ea Towelettes, Antimicrobiological Hand 1 ea Towelette, Equipment Cleaning 1 ea Bag, Biohazard Revision: 1 3/5/2018 ACE Form-CL Page 15 of 16