MAINTENANCE PROGRAM CESSNA T206H - SOLOY

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MAINTENANCE PROGRAM CESSNA T206H - SOLOY

HIGHLIGHT REV 01

CHAPTER PAGE REVISION DETAILS

Chapter 1 General Page 1-4 Added Dba HeliSGI and Air Bali in Chapter 1.6 General Information Company Organization

Page 1-5 Update the latest revision RR 250-B17F publication on Chapter 1.8 Manufacturer’s Technical Publications.

Form Inspection Sheets Revised taskcard for 150 hours, 300 hours and 1750 hours Engine Inspection

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CESSNA T206H - SOLOY

LIST OF EFFECTIVE PAGES

Revision No. : 01 Page LEP - 1

Date of Issued : July 2019

LIST OF EFFECTIVE PAGES

Chapter Description Page Rev No. Effective Date

Table of Content TOC – 1 Reissued 10 July 2018

1. GENERAL 1 – 1 Reissued 10 July 2018

1 – 2 Reissued 10 July 2018 1 – 3 Reissued 10 July 2018

1 – 4 01 July 2019

1 – 5 01 July 2019

1 – 6 Reissued 10 July 2018 1 – 7 Reissued 10 July 2018

2. MAINTENANCE PROGRAM 2 – 1 Reissued 10 July 2018 2 – 2 Reissued 10 July 2018 2 – 3 Reissued 10 July 2018 2 – 4 Reissued 10 July 2018 2 – 5 Reissued 10 July 2018 2 – 6 Reissued 10 July 2018 2 – 7 Reissued 10 July 2018 2 – 8 Reissued 10 July 2018 2 – 9 Reissued 10 July 2018 2 – 10 Reissued 10 July 2018 2 – 11 Reissued 10 July 2018 2 – 12 Reissued 10 July 2018

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CESSNA T206H - SOLOY

LIST OF EFFECTIVE PAGES

Revision No. : Reissued Page LEP - 2

Date of Issued : 10 July 2018

Chapter Description Page Rev No. Effective Date

3 AIRWORTHINESS LIMITATIONS 3 – 1 Reissued 10 July 2018 3 – 2 Reissued 10 July 2018 3 – 3 Reissued 10 July 2018 3 – 4 Reissued 10 July 2018 3 – 5 Reissued 10 July 2018 3 – 6 Reissued 10 July 2018 3 – 7 Reissued 10 July 2018

FORMS INSPECTION SHEETS Rev No. Effective Date

1. Deleted 2. Deleted 3. Deleted 4. Deleted

5. Airframe – Daily Check Reissued 10 July 2018

6. Airframe – 100 Hour or 1 Years Reissued 10 July 2018 7. Airframe/Supplement Inspection A Check –

50 Hours Reissued 10 July 2018

8. Airframe/Supplement Inspection B Check –

9. Airframe/Supplement Inspection C check –

10. Airframe/Supplement Inspection D check –

11. Airframe/ Supplement Inspection E check –

400 Hours or 1 Year Reissued 10 July 2018

12. Deleted (Inspection F check)

13. Airframe/ Supplement Inspection G check –

600 Hours or 1 Year Reissued 10 July 2018

14. Airframe/ Supplement Inspection H check –

15. Airframe/ Supplement Inspection I check – 2

Years Reissued 10 July 2018

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CESSNA T206H - SOLOY

LIST OF EFFECTIVE PAGES

Revision No. : 01 Page LEP - 3

16. Airframe/ Supplement Inspection J check –

5 Years of MFG, 12 Month then after Reissued 10 July 2018 17. Deleted (Inspection K check)

18. Airframe/ Supplement Inspection L check –

2 Years Reissued 10 July 2018

19. Airframe/ Supplement Inspection M check –

20. Deleted (Inspection N check)

21. Airframe/ Supplement Inspection O check –

1000 Hours or 1 year Reissued 10 July 2018

22. Airframe/ Supplement Inspection P check –

12 Months Reissued 10 July 2018

23. Airframe/ Supplement Inspection Q check –

6 years Reissued 10 July 2018

24. Airframe/ Supplement Inspection R check –

25. Airframe/ Supplement Inspection S check –

26. Airframe/ Supplement Inspection T check –

1 year Reissued 10 July 2018

27. Airframe/ Supplement Inspection U check –

1000 H or 3 years Reissued 10 July 2018

28. Airframe/ Supplement Inspection W check – 600 H and as defined by Manufacturer thereafter

Reissued 10 July 2018 29. Rolls Royce 250-B17F Engine Inspection –

150 Hours Inspection 01 July 2019

30. Deleted

31. Rolls Royce 250-B17F Engine Inspection –

32. Deleted

33. Rolls Royce 250-B17F1 Engine Inspection –

600 Hours Inspection Reissued 10 July 2018

1500 Hours Inspection Reissued 10 July 2018

36. HC-B3TF-7A Propeller 400 Hours / 12

Months Inspection Reissued 10 July 2018

37. Corrosion Prevention and Control Program

Inspections - Y check – 12 Months Reissued 10 July 2018

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CESSNA T206H - SOLOY

LIST OF EFFECTIVE PAGES

Revision No. : Reissued Page LEP - 4

38. Corrosion Prevention and Control Program

Inspections - Z check – 24 Months Reissued 10 July 2018 39. Corrosion Prevention and Control Program

Inspections - AA check – 36 Months Reissued 10 July 2018 40. Corrosion Prevention and Control Program

Inspections - AB check – 48 Months Reissued 10 July 2018 41. Corrosion Prevention and Control Program

Inspections - AC check – 60 Months Reissued 10 July 2018 42. Supplemental Inspection Document – AD

check – 1000 Hours or 3 Years Reissued 10 July 2018 43. Supplemental Inspection Document – AE

check – 2000 Hours or 5 Years Reissued 10 July 2018 44. Supplemental Inspection Document – AF

check –2500 Hours or 5 Years Initial, 1000 Hours or 3 Years thereafter.

Reissued 10 July 2018 45. Supplemental Inspection Document – AG

check – 3000 Hours or 5 Years Initial, 1000 Hours or 5 Years thereafter

Reissued 10 July 2018 46. Supplemental Inspection Document – AH

Reissued 10 July 2018 47. Supplemental Inspection Document – AI

Reissued 10 July 2018 48. Supplemental Inspection Document – AO

check – 3 Years Initial, 3 Years thereafter Reissued 10 July 2018 49. Supplemental Inspection Document – AP

check – 5 Years Initial, 5 Years thereafter Reissued 10 July 2018 50. Supplemental Inspection Document – AQ

check – 10 Years Initial, 3 Years thereafter Reissued 10 July 2018 51. Supplemental Inspection Document – AR

check – 10 Years Initial, 5 Years thereafter Reissued 10 July 2018 52. Supplemental Inspection Document – AT

Reissued 10 July 2018 53. Supplemental Inspection Document – AU

check – 100 Hours Initial, 600 Hours or 12 months thereafter

Reissued 10 July 2018

54. Weight and Balance Reissued 10 July 2018

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CESSNA T206H - SOLOY

TABLE OF CONTENT

Revision No. : Reissued Page TOC - 1

TABLE OF CONTENT

CHAPTER DESCRIPTION PAGE

1 GENERAL

1.1. PREFACE 1 – 1

1.2 INTRODUCTION 1 – 2

1.3. MANUAL CONTROL SYSTEM 1 – 2

1.3.1. Policy 1 – 2

1.3.2 Page Control System 1 – 2

1.4. MANUAL DISTRIBUTION 1 – 3

1.5. MANUAL REVISION AND PROCEDURE 1 – 4

1.6. GENERAL INFORMATION 1 – 4

1.7. AFFECTED AIRCRAFT 1 – 5

1.8. MANUFACTURER’S TECHNICAL PUBLICATION 1 – 5

1.9. GENERAL INSPECTION TERMS AND GUIDELINES 1 – 6

2 MAINTENANCE PROGRAM

2.1. SCHEDULE MAINTENANCE CHECK 2 – 1

2.2. SCHEDULE INSPECTION CHECLIST LEGEND 2 – 1

2.3. AIRFRAME INSPECTIONS 2 – 1

2.4. SOLOY/CESSNA 206 WITH RR 250-B17F/2 SUPPLEMENT INSPECTION

2 – 2

2.5. SCHEDULE INSPECTION NOTES 2 – 2

2.6. INSPECTION TOLERANCE 2 – 3

2.7. ENGINE INSPECTION 2 – 3

2.8. PROPELLER INSPECTIONS 2 – 4

2.9. SPECIAL INSPECTION / UNSCHEDULE MAINTENANCE CHECK DEFINED AND AREAS OF INSPECTION

2.9.1 SUPPLEMENTAL INSPECTION DOCUMENT (SID) AND CORROSION PREVENTION AND CONTROL PROGRAM (CPCP)

2 – 4 2 – 9

2.10. CASR REQUIREMENTS 2 – 10

2.10.1. Airplane Weight and Balance Control 2 – 10

2.10.2. Compass Compensating Interval 2 – 10

2.10.3. ATC Transponders 2 – 10

2.10.4. Altimeters and Static Pressure Test 2 – 10

2.10.5. VOR Equipment Check for IFR Operations 2 – 11

2.10.6. Emergency Locator Transmitter 2 – 11

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CESSNA T206H - SOLOY

TABLE OF CONTENT

CHAPTER DESCRIPTION PAGE

2.11.1. General 2 – 11

2.11.2. Required Inspection Item List 2 – 11

2.11.3. Persons Authorized to Perform RII 2 – 12

3 AIRWORTHINESS LIMITATIONS

3.1. GENERAL 3 – 1

3.2. DEFINITIONS 3 – 1

3.3. MAINTENANCE INSPECTION TIME INTERVAL 3 – 1

3.4. ENGINE AND ENGINE COMPONENT LIMITATIONS 3 – 3

3.4.1. Engine Time between Overhaul 3 – 3

3.4.2. Life Limits of the Compressor Rotor Assembly 3 – 4 3.4.3. Life Limits of the Gas Generator Turbine Rotor (N1) Assembly 3 – 5 3.4.4. Life Limits of the Power Turbine Rotor (N2) Assembly 3 – 6 3.4.5. Life Limits of the Propeller Reduction Gearbox Assembly 3 – 6 3.4.6. On-Condition Accessories and Components 3 – 6

FORM INSPECTION SHEET 1. Deleted

2. Deleted 3. Deleted 4. Deleted

5. Airframe/Supplement Inspection – Daily Inspection 6. Airframe Inspection – 100 Hours or 1 Years

7. Airframe/Supplement Inspection A check – 50 Hours 8. Airframe/Supplement Inspection B check – 100 Hours 9. Airframe/Supplement Inspection C check – 200 Hours 10. Airframe/Supplement Inspection D check – 300 Hours

11. Airframe/Supplement Inspection E check – 400 Hours or 1 Year 12. Deleted

13. Airframe/Supplement Inspection G check – 600 Hours or 1 Year 14. Airframe/Supplement Inspection H check – 1000 Hours

15. Airframe/Supplement Inspection I check – 2 Years

16. Airframe/Supplement Inspection J check – 5 Years of MFG, 12 Month thereafter

17. Deleted

18. Airframe/Supplement Inspection L check – 2 Years 19. Airframe/Supplement Inspection M check – 1750 Hours 20. Deleted

21. Airframe/Supplement Inspection O check – 1000 Hours or 1 Year

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CESSNA T206H - SOLOY

TABLE OF CONTENT

FORM INSPECTION SHEET

22. Airframe/Supplement Inspection P check – 12 Months 23. Airframe/Supplement Inspection Q check – 6 Years 24. Airframe/Supplement Inspection R check – 12 Years 25. Airframe/Supplement Inspection S check – 3 Years 26. Airframe/Supplement Inspection T check – 1 Years

27. Airframe/Supplement Inspection U check – 1000 Hours or 3 Years 28. Airframe/Supplement Inspection W check – 600 Hours and as defined by

Manufacturer thereafter

29. Rolls Royce 250-B17 Engine Inspection – 150 Hours Inspection 30. Deleted

31. Rolls Royce 250-B17 Engine Inspection – 300 Hours Inspection 32. Deleted

33. Rolls Royce 250-B17 Engine Inspection – 600 Hours Inspection 34. Rolls Royce 250-B17 Engine Inspection – 1500 Hours Inspection 35. Rolls Royce 250-B17 Engine Inspection – 1750 Hours Inspection 36. HC-B3TF-7A Propeller 400 Hours / 12 Months Inspection

37. Corrosion Prevention and Control Program Inspections – Y check – 12 Months

38. Corrosion Prevention and Control Program Inspections – Z check – 24 Months

39. Corrosion Prevention and Control Program Inspections – AA check – 36 Months

40. Corrosion Prevention and Control Program Inspections – AB check – 48 Months

41. Corrosion Prevention and Control Program Inspections – AC check – 60 Months

42. Supplemental Inspection Document – AD check – 1000 Hours or 3 Years 43. Supplemental Inspection Document – AE check – 2000 Hours or 5 Years 44. Supplemental Inspection Document – AF check – 2500 Hours or 5 Years

Initial, 1000 Hours or 3 Years thereafter

45. Supplemental Inspection Document – AG check – 3000 Hours or 5 Years Initial, 1000 Hours or 5 Years thereafter

46. Supplemental Inspection Document – AH check – 3000 Hours or 5 Years Initial, 3000 Hours or 5 Years thereafter

47. Supplemental Inspection Document – AI check – 10000 Hours or 20 Years Initial, 3000 Hours or 5 Years thereafter

48. Supplemental Inspection Document – AO check – 3 Years Initial, 3 Years thereafter

49. Supplemental Inspection Document – AP check – 5 Years Initial, 5 Years thereafter

50. Supplemental Inspection Document – AQ check – 10 Years Initial, 3 Years thereafter

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CESSNA T206H - SOLOY

TABLE OF CONTENT

51. Supplemental Inspection Document – AR check – 10 Years Initial, 5 Years thereafter

52. Supplemental Inspection Document – AT check – 6000 Hours or 10 Years Initial, 1000 Hours or 5 Years thereafter

53. Supplemental Inspection Document – AU check – 100 Hours Initial, 600 Hours or 12 months thereafter

54. Weight and Balance

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CESSNA T206H - SOLOY

CHAPTER 1 – GENERAL

Revision No. : Reissued Page 1 - 1

1.1. PREFACE

PT. SGI is engaged in the carriage of air charter under the terms and conditions of CASR Part 135. Air Operator Certificate Number: AOC/135-004 issued by Indonesian Directorate General of Civil Aviation. The Maintenance program (MP) for Cessna T206H - Soloy has been prepared in accordance with Civil Aviation Safety Regulations, Parts 135.367 and is not contrary to any applicable Regulation, or the Company’s Operations Specifications or operating certificate.

The Maintenance Program has been compiled for the use and guidance of all personnel responsible for performing maintenance and/or overhaul on aircraft. Each manual is controlled and assigned to specific individual’s aircraft type as necessary.

This manual is to be used in conjunction with other manuals, manufactures’ maintenance and overhaul manuals and in accordance with applicable Aviation Regulations. The Maintenance Program will provide direction for use with aircraft, engine, and component maintenance and overhaul manuals. It also provides guidelines on how to fulfil requirements outlined in CASR’s, AD’s, SB’s, etc. and the proper completion of the forms related to and distribution of the necessary reports in conjunction with the CASR’s. If any material described in this Manual is in conflict with the CASR, the CASR will take priority.

Manufacturer’s manuals are also included and are considered part of the Company manual.

All maintenance employees are required to adhere to the instructions contained in this manual and follow the procedures outlined. In the event procedures in the manufacturers’

publications differ from this manual, the manufacturer’s manual prevails.

All personnel are encouraged to submit suggestions and recommendations to improve utilization and technical quality of the manual.

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CESSNA T206H - SOLOY

CHAPTER 1 – GENERAL

1.2 INTRODUCTION

The purpose of this Maintenance Program (MP) is to provide guide regarding the schedule, un-schedule maintenance, proper procedures and practices to be followed in conducting maintenance of Cessna T206H - Soloy under the Air Operator Certificate issued by Directorate General of Civil Aviation in compliance with Civil Aviation Safety Regulation (CASR) Part 135 and related Parts.

Copies of this Maintenance Program (MP) will be distributed to all out base utilizing Cessna T206H – Soloy aircraft. Maintenance Manager will determine the distribution of the manual.

It will be their responsibility of Maintenance Manager and Chief Inspector to assure that all mechanic, supervisors and inspectors are formally trained, kept current and familiar with the contents of this manual.

This Maintenance Program (MP) will be subjected to revision as necessary. It will be the responsibility of the person to whom this manual is issued to maintain it and insert all amendments and revisions. Such amendments and revisions will be issued by whom this manual is issued in the form of new revised pages.

1.3. MANUAL CONTROL SYSTEM 1.3.1. Policy

a. The manuals are not transferable. Holder shall retain the manuals originally issued regardless of change of station or location.

b. Upon termination of employment, the manuals shall be returned to Chief Inspector.

c. Text within a section (subject matter) should not be taken out of context. The reader should read the entire section for a complete understanding of the policies and procedures regarding a specific subject. If question arise, contact the Chief Inspector for clarification. A written response shall be made to clarify the matter in question.

1.3.2 Page Control System a. Record of Revision

Designed to quickly identify the current revision status of the manual.

b. List of Effective Pages

Designed to provide a summary listing of all applicable pages and the revision date for the entire manual

c. Page Format

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CESSNA T206H - SOLOY

CHAPTER 1 – GENERAL

1. Top of the Page

MAINTENANCE PROGRAM CESSNA T206H - SOLOY

CHAPTER 1 G E N E R A L

no. of chapter Section Logo manual’s name 2. Bottom of the Page

Revision No : 0 Page : 1 - 2

Date : September 2012

Date of issued Revision no. Page No.

(Chapter 1 Page 2) 1.4. Manual Distribution

This Maintenance Program shall be distributed to all personnel involved and responsible for aircraft maintenance activities.

Manual Distribution List

This list of distribution is maintained in the Technical Department and this Cessna T206H - Soloy Maintenance Program will be distributed to:

Control

No. AAIP Holder

1 Maintenance Manager 2 President Director 3 Indonesian DGCA 4 Chief Inspector 5 Technical Support

6, 7, 8… Any out base utilizing PT. SGI Cessna T206H aircraft

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CESSNA T206H - SOLOY

CHAPTER 1 – GENERAL

Revision No. : 01 Page 1 - 4

1.5 MANUAL REVISION AND PROCEDURE A. Manual Revision

All amendments, revisions, and / or alterations to the Maintenance Program must have an approval from DGCA. The changes shall be recorded through incorporation in a Record of Revision.

Changes shall not be introduced through written notation on the documents but through the removal of expired pages and insertion of revised pages. The bottom of each page shall indicate the issue and revision status (dates and number).

B. Procedures

1. Revision shall be numbered consecutively. The revised pages shall replace the earlier issued pages with the same part page number. Revision index shall be up dated; the revision status in the bottom left hand corner must have been adjusted.

The removed pages must be deleted / destroyed. The changes on the revised pages with respect to the preceding ones shall be indicated with one vertical line.

2. In case a new issue to be published, the respective issue number shall be one higher than the preceding manual. The revision number of all pages shall become zero. The preceding issued manual shall now be deleted / destroyed.

3. Whenever revisions are made, either by the company or the manufacturer, Chief Inspector shall route them to the holders of the manuals. The responsibility for inserting revisions is the direct responsibility of the manual holder.

4. On occasion, minor revisions to pages will be necessary to correct spelling, add or delete a word, or number. These corrections may be made in pen and ink. Such changes will be annotated in pen above the word, or number or as directed on Revision Transmittal Sheet and a single line drawn through the word or number changed or deleted. Pen and ink changes will be included in the next regular revision of the manual.

1.6. GENERAL INFORMATION

1. Company Organization

PT. SGI is authorized by the Indonesia Directorate General of Civil Aviation (DGCA) under the Civil Aviation Safety Regulations (CASRs) as a Commercial Operator. The company office is in Denpasar, Bali, mailing address is as follows:

PT. SAYAP GARUDA INDAH Dba : HeliSGI and Air Bali

Address : Dewa Ruci Building No.2 Jl. Bypass Ngurah Rai – Kuta Bali Indonesia, 80361

Phone : +62-361 767466/766582 Fax : +62-361 766581

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CESSNA T206H - SOLOY

CHAPTER 1 – GENERAL

Revision No. : 01 Page 1 - 5

Aircraft General Specification:

a. Aircraft

Model : Cessna T206H - Soloy Manufacturer : Cessna Aircraft Company

b. Engine

Model : Rolls Royce 250-B17F/2 Manufacturer : Rolls Royce

c. Propeller

Model : HC-B3TF-7A

Manufacturer : Hartzell

1.7. AFFECTED AIRCRAFT

This Maintenance Program is applicable to the following aircraft:

No. Make/Model Serial Number Reg. Mark

1. CESSNA T206H - SOLOY T20608081 PK-ZGY

1.8. MANUFACTURER’S TECHNICAL PUBLICATIONS

This Maintenance Program (MP) is the basic document, which provides and specifies all scheduled and unscheduled inspection program for the Cessna T206H Aircraft and the related components in order to meet the minimum standard of airworthiness, which is required by the Civil Aviation Safety Regulations (CASRs).

The following are references publication regarding each inspection item which contained in this Maintenance Program:

1. Soloy/Cessna 206H with Rolls-Royce 250-B17F/2, Maintenance Manual Supplement (S/MMS) Rev 02 – October 2013,

2. Soloy Service Bulletins (S/SB), 3. Soloy Service Instructions (S/SI),

4. Cessna Model 206/T206 Maintenance Manual (C/MM) Rev 20 – Sept 2016, 5. Cessna Service Bulletins (C/SB),

6. Cessna Service Instructions (C/SI),

7. Rolls-Royce 250-B17F series Operation and Maintenance Manual (RR/OMM) Rev 25 – May 2019,

8. Hartzell Manual 139 (HM139) Rev 16 – October 2017, 9. Other documents concerning to this Maintenance Program

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CESSNA T206H - SOLOY

CHAPTER 1 – GENERAL

1.9. GENERAL INSPECTION TERMS AND GUIDELINES

This paragraph remains unchanged from the Cessna T206H model Maintenance Manual with the addition of the following:

A. Special Inspections

Special inspections are required when certain engine or propeller operating parameters have been exceeded, when an abnormal condition exists or when deemed necessary.

Refer to the Rolls-Royce 250-B17F series Operation and Maintenance Manual, Chapter 72, and Hartzell Propeller Owners Manual 139, Chapter 5 Inspection and Check.

B. Engine Run-Up

Before conducting each Annual/100 Hour inspection, start, run-up, and shut down the engine in accordance with the instructions in the Pilots Operating Handbook Supplement.

Duration of the run need not exceed 5 minutes. Verify the proper operation of all engine warning systems. During the run-up, check all instruments for a satisfactory reading and observe the propeller, propeller gearbox, and engine for abnormal conditions making note of any discrepancies as follows:

(1) Engine oil temperature and pressure

(2) Engine temperature (T.O.T.) and torque indicator function (3) Smooth operation of all engine controls

(4) Any unusual vibration, noise or leakage

(5) Ensure the T.O.T. stays between 740°C and 810°C during startup. Also ensure the propeller un-feathers.

(6) Ammeter (7) Vacuum gauge

(8) Fuel flow and temperature indication

After the inspection has been completed, an engine run-up should again be performed to determine that any discrepancies or abnormalities have been corrected and to leak check areas opened for inspection or replacement.

C. MOVEABLE PARTS for : lubrication, servicing, security of attachment, bidding, excessive wear, safeying, proper operation, proper adjustment, correct travel, cracked fittings, security of hinges, defective bearings, clean lines, corrosion, deformation, sealing and tension.

D. FLUID LINES AND HOSES for: leaks, cracks, dents, kinks, chaffing, proper radius, security, corrosion, deterioration obstruction and foreign matter.

E. METAL PARTS for: Security, chaffing burning, defective insulation, loose or broken terminals, heat deterioration and corroded terminal.

F. BOLTS AND CRITICAL AREAS for: correct torque in accordance with torque values went installed or when visual inspection indicates the need for torque check.

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CESSNA T206H - SOLOY

CHAPTER 1 – GENERAL

G. FILTERS, SCREENS AND FLUID for: Cleanliness, contamination and / or replacement at specified intervals.

H. MAGNETIC PARTICLE INSPECTION

(1) There are no periodic inspection requirements for magnetic particle inspection on Soloy provided components.

I. FLUORESCENT PENETRANT INSPECTION

(1) There are no periodic inspection requirements for fluorescent penetrant inspection on Soloy provided components.

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CESSNA 206H - SOLOY

CHAPTER 2 – MAINTENANCE PROGRAM

2.1. SCHEDULED MAINTENANCE CHECK

The primary purpose of this chapter is to provide inspection time intervals.

The intervals shown are recommended intervals at which items are to be inspected based on normal usage under average environmental conditions. Airplanes operated in extremely humid areas (tropics), or in exceptionally cold, damp climates, etc., may need more frequent inspections for wear, corrosion, and lubrication. Under these adverse conditions, perform periodic inspections in compliance with this chart at more frequent intervals until the operator can set his own inspection periods based on field experience without exceeding the maximum intervals listed in this section.

2.2. SCHEDULED INSPECTION CHECKLIST LEGEND

• ITEM... Inspection item number grouped in sections.

• REQ... Provides a short description of the inspection and/or servicing procedure.

• REFF ... Refers to the appropriate manual for further information.

• ENG... This column is used to be signed by engineer in charge once each item has been completed.

• INS... This column is used to be signed by RII Inspector when Required Inspection Item Required.

2.3. AIRFRAME INSPECTIONS

The schedule maintenance program for the Cessna 206H is made up of all systems, power plant and structural maintenance tasks, which are detailed in the following:

a. Daily Inspection

All items require for servicing and inspection on daily.

b. Pre-flight / Post Flight Inspection

Inspection that must be made before flight (Preflight) and after the final flight of the day (post flight)

c. 50 Hours Inspection

All items airframe require for servicing and inspection every 50 hours.

d. 100 Hours Inspection

e. 200 Hours INSPECTION

f. Annual Inspection ( if the aircraft is flow less than 200 hours annually)

All items require for servicing and inspection on one year, including 100 hours inspection and special inspection that have a one year interval as applicable.

An Annual/100 Hour inspection would include all items listed in a 50 hour and 100 hour inspection checklist. A complete airplane inspection includes all inspection items. Once the inspection is completed, before the approval, run the aircraft engine to determine satisfactory performance in accordance with the manufacturer's recommendations.

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CESSNA 206H - SOLOY

CHAPTER 2 – MAINTENANCE PROGRAM

2.4. SOLOY/CESSNA 206 WITH ROLLS ROYCE 250-B17F/2 SUPPLEMENT INSPECTION The legend for the alpha code is listed below:

Interval Letter Interval

A Shall be carried out every 50 Hours B Shall be carried out every 100 Hours C Shall be carried out every 200 Hours D Shall be carried out every 300 Hours

E Shall be carried out every 400 Hours or 1 year, whichever come first

F Shall be carried out every 500 Hours

G Shall be carried out every 600 Hours or 1 year, whichever come first

H Shall be carried out every 1000 Hours

I Shall be carried out every 2 Years (covered by CASR

requirements)

J Shall be carried out 5 years from date of manufacture and every 12 month thereafter

K Shall be carried out every 50 Hours or 4 months, which ever come first

L Shall be carried out every 2 Years, or any time components are added or removed which have potential to affect the magnetic accuracy and/or variation of the compass calibration, or anytime the accuracy of the compass is in question. (covered by CASR requirements)

M Shall be carried out every 1750 Hours N Shall be carried out every 2000 Hours

O Shall be carried out every 1000 Hours or 1 year, whichever come first

P Shall be carried out every 12 Months (cover by CASR

requirements)

Q Shall be carried out every 6 Years R Shall be carried out every 12 Years S Shall be carried out every 3 Years T Shall be carried out every 1 Year

U Shall be carried out every 1000 Hours or 3 Years, whichever occurs first.

2.5. SCHEDULED INSPECTION NOTES

A. If a chip detector warning light is observed in the cockpit, determine which chip detector caused the light to illuminate. Remove and visually inspect the applicable chip detector for metal accumulation. Refer to the Rolls-Royce 250-B17F series Operation and

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CESSNA 206H - SOLOY

CHAPTER 2 – MAINTENANCE PROGRAM

Maintenance Manual, Chapter 72 for complete engine magnetic plug inspection requirements.

B. At every Annual/100 Hour engine inspection, prior to installing the cleaned magnetic plugs, test the system as follows: Reconnect the magnetic plugs to the electrical connectors and energize the aircraft electrical system. Check one plug at a time by touching the plug probe to a well grounded area of bare metal on the engine. Check that the OIL CHIPS light illuminates on the annunciator light panel.

C. The recommended oil change interval is 300 hours or 6 months, whichever occurs first.

The calendar limit can be extended to 12 months if an approved high thermal stability oil (Third Generation) is used. With an approved HTS (Third Generation Oil), and an external scavenge oil filter system is installed, the oil change interval can be increased to 600 hours or 12 months, whichever occurs first.

D. Change scavenge oil filter element at each oil change. Remove and inspect oil filter.

Note any accumulation of metal chips, debris or carbon particles. Conduct further inspection of the lube system and/or gear train/bearings if metal chips or debris are found. Filter element is non-cleanable. Refer to the Rolls-Royce 250-B17F series Operation and Maintenance Manual, Chapter 72 for complete inspection requirements.

2.6. INSPECTION TOLERANCE

a. The airplane can only exceed its inspection point up to ten hours if the airplane is enroute to a facility to have the inspection completed.

b. In the event of late compliance of any operation scheduled, the next operation in sequence retains a due point from the time the late operation was originally scheduled (reschedule if late).

c. In the event of early compliance of any operation scheduled, that occurs 10 hours or less ahead of schedule, the next phase due point may remain where originally set.

d. In the event of early compliance on any operation scheduled, that occurs more than 10 hours ahead of schedule, the next phase due point must be rescheduled to establish a new due point from the time of early accomplishment.

e. In accordance with OPSPEC Sub Part D76, PT. SGI is authorized to issue the Short Term Escalation (STE). STE is only one times issued. No more times issuing of STE for same subject on same aircraft. If the STE’s subject still need extension when STEvoid, Chief Inspector is responsible to provide and submit the STE to DGCA for approval.

Master of STE application shall be retained in Chief Inspector, and copy distribution to Maintenance Controller, Aircraft ATL and DGCA PMI

2.7. ENGINE INSPECTIONS

The schedule maintenance program for the Rolls Royce 250-B17F/2 are made up of all systems, power plant and structural maintenance tasks, which are detailed in the following:

A. 150 Hours Inspection B. 300 Hours Inspection C. 600 Hours Inspection D. 1500 Hour Inspection D. 1750 Hour Inspection

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CESSNA 206H - SOLOY

CHAPTER 2 – MAINTENANCE PROGRAM

2.8. PROPELLER INSPECTION

The following are periodic inspections applicable for Hartzell HC-B3TF-7A propeller:

A. 400 Hours Inspection

Perform detailed inspection procedures at 400 hour intervals not to exceed twelve (12) calendar months

2.9. SPECIAL INSPECTION / UNSCHEDULED MAINTENANCE CHECKS DEFINED AND AREAS OF INSPECTION

The following are Unscheduled Maintenance events applicable for Cessna T206H, Rolls Royce 250-817F2 and Hartzell HC-B3TF-7A include, but are not limited to:

A. Hard Landing Limits

(1) Make a visual inspection of the installed engine for external damage from airframe components after any hard landing.

(2) Engines, fuel controls, and governors that have sustained landing forces exceeding 10g shall be sent to an overhaul facility. Refer to the applicable airframe manual for airframe conditions that indicate that the 10g landing force limit has been exceeded B. Gearbox-Compressor Mounting Insert Inspection

(1) Inspect the inserts for looseness anytime the compressor is removed from the gearbox. (Refer to Insert Inspection, PARA 4.E., 72-60-00.)

C. Vibration Inspection

(a) If engine vibration is suspected, or any of the vibration symptoms listed in the 100 hour inspection (Table 602) are encountered, inspect the compressor and return it to repair/overhaul if any of the following conditions are encountered:

1. Remove the top half of the compressor case and check all blades and vanes for possible foreign object damage and/or for bent or distorted vanes. Blade and vane condition must be within the limits given in Blade and Vane Inspection, PARA 4.B., 72-30-00.

2. Remove the compressor assembly from the engine.

3. Check the scroll outlet ports (turning vanes) for evidence of damage. Damage is indicative of impeller vane tip or shroud failure.

D. Sudden Stoppage Inspection

The following inspections must be satisfactorily completed whenever the propeller strikes a moving or stationary object.

NOTE: Sudden stoppage is the momentary or complete interruption in the rotation of the aircraft propeller and engine drive system when the aircraft propeller comes in contact with the ground, water, trees or other obstacles.

The shock felt by the drive system requires that the engine be inspected and/or overhauled by a designated overhaul facility as a result of possible damage.

If the aircraft propeller strikes an object causing damage to the propeller which can be corrected by light grinding or filing and normal blending of the blades (nicks, gouges,

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scratches, etc.) in accordance with applicable propeller service instructions, complete the following inspection:

(a) Inspect the engine inlet for foreign objects.

(b) Inspect the compressor for foreign object damage.

(c) Inspect all magnetic plugs for metal accumulation. (Refer to Magnetic Plug, PARA 11.I., 72--00--00, Engine Servicing.)

(d) Rotate the propeller by hand and check for unusual noise.

(e) Motor the engine and check for unusual noise.

(f) Operate the engine for 30 minutes on the ground then check the magnetic plugs for metal accumulation.

(g) Check balance the propeller.

If the aircraft propeller strikes an object causing damage to the propeller blades requiring blade replacement and overhaul of the propeller assembly, remove the engine and send it to a designated overhaul facility for inspection.

(h) Refer to the appropriate propeller Service Instructions and Overhaul Manual.

(i) Refer to the Special Inspections required after propeller strike and/or crash in the engine Overhaul Manual.

E. Compressor Inlet Air Blockage

Replace the compressor assembly if the engine has been operated with inlet air restricted due to foreign objects or materials which have become lodged in the compressor inlet. Tag the replaced compressor to show that the cause of removal was inlet air blockage and send to an Rolls--Royce approved repair facility for complete overhaul. Conditions which constitute blockage are:

(a) Power loss encountered following a restriction at the compressor inlet area while the engine is in operation. Blockage in flight can usually be verified by inspection after landing (blockage still exists). However, some blockage may be followed by ingestion before inspection can take place. Objects or materials which were large enough to have stopped at the inlet guide vanes before ingestion, or which causes a noticeable rise in TOT, can be considered to have caused compressor inlet blockage.

(b) Foreign objects or materials found in the inlet during inspection of the aircraft when not in operation. If it can be determined that the blockage was not there during the last operation of the engine, remove the foreign object or material and leave the compressor in service.

F. Engine Submerged in Water

If the engine has been submerged in water, proceed as follows:

(a) Tag the engine indicating that it encountered submersion in water.

(b) Return the entire engine to an overhaul facility as soon as possible for replacement of all compressor and turbine wheels.

G. Lightning Strike Inspection

Aircraft lightning strikes occur when the airframe can serve as a least--resistance bridge for the electrical bolt as it travels through the air. Consequently, aircraft extremities

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(propeller, blades, nose, landing gear, wing tips, vertical and horizontal tail surfaces, etc.) typically act as points of entry or exit.

However since the exact electrical path through the aircraft may not be readily traceable following a strike, the following guidelines are recommended:

(a) In the event of a lightning strike in the immediate vicinity of the engine(s) (as evidenced by charring, burn marks or pitting associated with electrical arcing on the engine cowl, compartment or inlet) remove the engine(s) prior to further flight and send them to an Rolls--Royce approved repair facility for detailed teardown and inspection.

(b) Where the aircraft is known or suspected of having been involved in a lightning strike and entry/exit points either cannot be determined or appear remote to the engine(s), perform the following:

1. Inspect the engine compartment for evidence of lightning strike damage.

2. Manually rotate N1 and N2 systems and check for binding and abnormal noise.

3. Remove, inspect, and clean the engine oil filter. (Refer to Oil Filter Replacement, para 1.C., Power and Accessory Gearbox Maintenance Practices, 72--60--00.) 4. Remove, inspect, and clean the magnetic plugs. (Refer to Magnetic Plug

Inspection, para 11.I., Engine Servicing, 72--00--00.)

5. Operate the engine for 30 minutes on the ground in accordance with Engine Check Run, para 1.A., 72--00--00, Engine/Adjustment Test and recheck the magnetic plugs for metal accumulation. (Refer to para 11.I, 72--00--00, Engine-- Servicing.)

a. On twin engine aircraft, operate each engine individually.

b. Listen for abnormal noise on coastdown and abnormally short coastdown time.

H. Hot Start Inspection

When the engine starting temperature limits of Table 6, 72--00--00, are exceeded and turbine inspection is the recommended maintenance action, proceed as follows:

(a) Remove the outer combustion case and combustion liner. (Refer to Replacing the Combustion Liner, PARA 1.A., 72--40--00.)

(b) Inspect the nozzle in accordance with Items 1 and 2 of Table 201, 72--50--00.

(c) Inspect the turbine wheels. (Refer to, PARA 6.A., 72--50--00.)

(d) Inspect the combustion liner in accordance with Table 201, 72--40--00.

(e) Reassemble the engine. (Refer to Replacing the Combustion Liner, PARA 1.A., 72-- 40--00.)

I. Erosion Inspection

If the aircraft is frequently subjected to sand or dust ingestion or operated in a corrosive environment (salt laden or other chemically laden atmosphere such as pesticides, herbicides, sulfur, industrial pollutants,etc.), inspect the compressor blades and vanes for erosion or corrosion damage. Engines operated in a corrosive environment should be subject to daily fresh water compressor rinses. (Refer to Blade Damage, Vane Damage, Case and Vane Abradable Seal Coating Inspection, PARA 5.B., 5.C., 5.D., and 5.E., 72-- 30--00.)

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NOTE: If the aircraft is subjected to sand, dust, or other small particle ingestion, periodic compressor erosion inspection is recommended. The frequency of the inspection should be based on the degree of ingestion and condition of the compressor at the last inspection. The need for more frequent compressor rinse may also be indicated.

NOTE: See TP CSL--2004 for instructions on suggested contamination removal using water only and for maps of operating areas with salt laden air.

NOTE: 10X power magnification is recommended for corrosion pit inspection.

J. Snow Ingestion Inspection

Inspect the engine for snow, ice, or water damage as follows:

(a) Obtain access to the compressor inlet but do not disassemble any engine parts.

(b) Replace the compressor assembly if any mechanical damage, distortion, or bending is detected on the compressor front support struts or the first--stage rotor blades.

K. On Condition Inspection Power and Accessory Gearbox

Any time the gearbox housing is separated from the cover, all gears shall be magnetic particle inspected if the log book indicates that more than 3500 hours have elapsed since the gears were new or last magnafluxed. (Refer to M250--B17F Series Overhaul Manual, Publ. No. GTP 5243--3, for inspection criteria.)

NOTE: Record compliance with this inspection in the appropriate section of the log book. Include date and hours.

L. Rotating Balance of Engine and Propeller Assembly

To prevent operation with excessive vibration, it is recommended that an installation running balance be accomplished under the following conditions:

(a) After any engine assembly, engine module, or propeller change.

(b) After propeller overhaul, propeller blade replacement, or extensive blade blending for nicks or dents.

(c) At periodic maintenance inspection intervals such as every other 100 hour inspection.

The frequency of inspection should be dictated by the particular aircraft and the operational environment of that aircraft. It is Rolls--Royce’s suggestion that 600 hours be the maximum time interval for a propeller balance check.

(d) Any time vibration is reported by the flight crew.

Balance the propeller using typical Fixed Base Operator (FBO) equipment such as:

Chadwick--Helmuth “Vibrex” balance system or Spectral Dynamics “Trim Balance Analyzer”. Accomplish the balance in accordance with the instructions provided with the particular equipment.

The maximum unbalance limit when measured at the propeller reduction gearbox is 3.0 mils or 0.2 inches/second (ips) average. This average is usually found near 1300 rpm propeller speed.

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M. Propeller Overspeed / Overtorque

An overspeed has occurred when the propeller RPM has exceeded the maximum RPM stated in the applicable Aircraft Type Certificate Data Sheet. An overtorque condition occurs when the engine load exceeds the limits established by the engine, propeller, or airframe manufacturer. The duration of time at overspeed/overtorque for a single event determines the corrective action that must be taken to make sure no damage to the propeller has occurred.

The criteria for determining the required action after an overspeed are based on many factors. The additional centrifugal forces that occur during overspeed are not the only concern. Some applications have sharp increases in vibratory stresses at RPMs above the maximum rated for the airframe/engine/propeller combination.

(1) When a propeller installed on a turbine engine has an overspeed event, refer to the Turbine Engine Overspeed Limits to determine the corrective action to be taken.

(2) When a propeller installed on a turbine engine has an overtorque event, refer to the Turbine Engine Overtorque Limits to determine the corrective action to be taken.

(3) Make an entry in the propeller log book to document the overspeed/overtorque event.

N. Propeller Lightning Strike

In the event of a propeller lightning strike, an inspection is required before further flight. It may be permissible to operate a propeller for an additional ten (10) hours of operation if the propeller is not severely damaged and meets the requirements in Procedure for Temporary Operation in this section. Regardless of the outcome of the initial inspection, the propeller must eventually be removed from the aircraft, disassembled, evaluated, and/ or repaired by an appropriately licensed propeller repair facility.

O. Propeller Foreign Object Strike A foreign object strike is defined as:

1. Any incident, whether or not the engine is operating, that requires repair to the propeller other than minor dressing of the blades. Examples of foreign object strike include situations where an aircraft is stationary and the landing gear collapses, causing one or more blades to be significantly damaged, or where a hangar door (or other object) strikes the propeller blade. These cases should be handled as foreign object strikes because of potentially severe side loading on the propeller hub, clamps, blades and retention bearings.

2. Any incident during engine operation in which the propeller impacts a solid object that causes a drop in revolutions per minute (RPM) and also requires structural repair of the propeller (incidents requiring only paint touch-up are not included). This is not restricted to propeller strikes against the ground.

3. A sudden RPM drop while impacting water, tail grass, or similar yielding medium, where propeller blade damage is not normally incurred.

P. Propeller Fire Damage or Overheat Damage

On rare occasions propellers may be exposed to fire or heat damage, such as an engine or hangar fire. In the event of such an incident, an inspection by an appropriately licensed propeller repair facility is required before further flight.

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Q. Propeller Long Term Storage

Parts shipped from the Hartzell factory are not shipped or packaged in a container that is designed for long term storage.

Long term storage procedures may be obtained by contacting a Hartzell distributor, or the Hartzeil factory via the Product Support number listed in the Introduction chapter of this manual. Storage information is also detailed in Hartzell Manual 202A (61-01-02).

2.9.1. Supplemental Inspection Document (SID) and Corrosion Prevention and Control Program (CPCP) Inspection Requirements

(1). Two types of inspection requirements are available based on operating usage and two additional types of inspections are available based on operating environment.

(a). Operating Usage

1. Severe Usage Environment

· If the average flight length is less than 30 minutes, then you must use the SEVERE inspection time limits

· If the airplane has been engaged in operations at low altitudes such as pipeline patrol, fish or game spotting, aerial applications, police patrol, sightseeing, livestock management, etc. more than 30% of its life you must use the SEVERE inspection time limits

2. Typical Usage Environment

· If no requirement of the Severe Usage Environment applies, the TYPICAL usage environment applies and should be used.

(b). Operating Environment

1. Severe Corrosion Environment

· If the airplane is operating more than 30% of the time in a zone shown as severe on the corrosion severity maps in located in Chapter 51, Corrosion – Description and Operation, then the SEVERE CORROSION environment time limits apply.

2. Mild or Moderate Corrosion Environment

· If the airplane is not classified as operating in a Severe Corrosion Environment, then the MILD/MODERATE CORROSION environment time limits apply.

(2). After the operating usage and the operating environment are determined, make a logbook entry that states which inspection schedules (TYPICAL or SEVERE operating usage and MILD/MODERATE or SEVERE operating environment) are being used.

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2.10. CASR REQUIREMENTS

2.10.1. Airplane Weight and Balance Control

Re-weighing of the aircraft should be accomplished when:

1. Every 3 (Three) years.

2. After Paint stripping and repainting.

3. After any modification which significantly affecting empty weight.

4. If there is any complaint from the pilot flying the aircraft regarding the aircraft stability.

5. Empty weight of the aircraft has been change more than 0.5% of the maximum take-off weight or empty center of gravity (C.G. location) has been change more than 0.5% of Mean Aerodynamic Chord (M.A.C.).

6. Specially required by the Directorate General of Civil Aviation (DGCA).

Accomplishment of the Weight and Balance must be supervised by a person appointed and authorized by PT. SGI. After accomplishment of the weight and balance, the maintenance release in the Aircraft Technical Log should be signed and the weight and balance report should be issued.

2.10.2. Compass Compensating Interval

The calibration / checking of the Aircraft compass has to be carried out every 2 (two) years or after any of the following condition(s):

a. After lightning strike

b. After replacement of any compass.

c. Any complaint of the pilot flying the aircraft about the aircraft accuracy of the compass installed on the aircraft.

Accomplishment of the Compass Swing must be supervised by a person appointed and authorized by PT. SGI.

2.10.3. ATC Transponders

The ATC Transponder is designated for ramp use as is capable of exacting functional, the inspection of Aircraft Transponder (XPDR) and Distance Measuring Equipment system. This inspection must be carried out at interval 24 calendar months as require by CASR 43, Appendix F and CASR 91.413.

2.10.4. Altimeters and Static Pressure Test

The altimeter measures the difference between the ambient static pressure and the ground pressure as displayed on the scale. The sealed housing admits static pressure the variations of which distort the membranes of an aneroid chamber. The setting control of ground barometric pressure actuates mechanism, which drives the pointer, dial and scale; swing the altitude according to the pressure altitude correspondence low. The maintenance and functional test as prescribed in the CASR Part 43 and CASR 91. 411 has been tested and inspected within the preceding 24 calendar months.

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2.10.5. VOR Equipment Check for IFR Operations

This inspection must be carried out when the Aircraft is operated under Instrument Flight Rule (IFR). VOR equipment inspection is required by CASR 91.171, which states that VOR equipment should be checked within the preceding 1 calendar month or 30 days. This Inspection may be performed by Pilot. After accomplishment of this Inspection and discrepancies rectification, the maintenance release in the Aircraft Technical Log and the appropriate form should be signed

2.10.6. Emergency Locator Transmitter

ELT inspection is required by CASR Part 91.207 which stated in part that ELT must be inspected within 12 calendar months after the last Inspection.

2.11. REQUIRED INSPECTION ITEM 2.11.1. General

Required Inspection Items are those items that could result in a failure, malfunction or defect, endangering the safe operation of the aircraft if not performed properly or improper parts or materials are used.

It is PT. SGI’s policy to maintain the aircraft to CASR Part 135 standards, therefore the Required Inspection Items, (RII), procedures must be followed, specifically, it is required that a person who performs work on RII items is prohibited from also performing the inspection of that work.

It shall be the responsibility of the Chief Inspector function to ensure that this procedure is strictly followed and that this fact is verifiable in the permanent aircraft record. This procedure requires that the Chief Inspector functions monitor all maintenance actions against the list of RII's that follows.

When an RII is to be performed, Chief Inspector guides the work to assure that THE PERSON INSPECTING THE WORK IS OTHER THAN THE PERSON PERFORMING THE WORK and that the signatures and stamps of both persons involved in an RII action are recorded on the appropriate document.

2.11.2. Required Inspection Item List The following items will require RII:

ATA Chapter Description

8 Deleted 26 Deleted

27 Flight Control System Major repair, rigging and/or adjustment, removal and/or installation of flight control including related components, for example: cable, pulleys, linkage, hinges

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28 Deleted 29 Deleted 34 Deleted 52 Deleted 53 Deleted 54 Deleted 55 Deleted 57 Deleted

61 Propeller Removal and/or installation propeller

72 Engine Removal and/or installation engine. Major repair as defined in Engine Maintenance Manual.

73 Deleted

76 Engine control Removal and/or installation engine control Rigging, adjustment of engine control

79 Deleted

2.11.3. Persons Authorized to Perform RII

The person authorized to inspect and approve the RII must be an experience engineers, have been conduct RII training and have AME licence for the category of system requiring inspection and/or authorized by Chief Inspector.

Note: Personnel authorized to conduct RII are controlled by the Chief Inspector.

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CHAPTER 3 – AIRWORTHINESS LIMITATIONS

3.1. GENERAL

This chapter gives a list of items which must be overhauled or replaced at specific time limits.

Cessna-Supplied Replacement Time Limits shows those items which Cessna has found necessary to overhaul or replace at specific time limits. Supplier-Supplied Replacement Time Limits shows component time limits which have been given by an outside supplier for their products. If necessary, based on service use and inspection results, these components can be overhauled or replaced before their time limit is reached.

3.2. DEFINITIONS

The terms as used within this section are defined as follows:

(1) Overhaul - Overhaul the item or replace it.

(2) Replacement - Replace the item with a new item or a serviceable item that is within its service life and time limits or has been rebuilt.

(3) TBO - Time Between Overhauls (4) HMI - Heavy Maintenance Inspection

3.3. MAINTENANCE INSPECTION TIME INTERVALS

ATA NOMENCLATURE PMP

Recommended Maintenance / TBO/

Replacement Interval

Remark

20 Deleted. N/A after Soloy Conversion

Deleted. N/A after Soloy Conversion

24 Deleted. N/A after Soloy Conversion

Deleted. N/A after Soloy Conversion

25

Restraint Assembly Pilot, Copilot, and Passenger Seats

PN : Various

HT 10 YR Replace

First Aid kit OC 12 Month Inspection

Life vest OC 12 Month Inspection

25 ELT battery HT Vendor

Recommendation Replace

26 Fire Extinguisher OC 12 Month

144 Month

Weighing

Hydrostatic Test

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Remark

27 Trim Tab actuator OC 200 Hours Inspection

28 Deleted

Engine Airframe Fuel Filter HT 300 Hours Replace 33 Deleted

35 Deleted

Oxygen bottle – Composite HT 24 Years Replace

37 Gyro filter OC 100 Hours Inspection

Deleted Deleted

Vacuum relief / Regulator Valve

Filter (if Installed) OC 100 Hours Inspection

61 Propeller (P/N HCB3TF-7A) HT 3000 Hours / 60

months Overhaul Propeller Shaft (P/N 23005735) HT 2000 Hours Replace Propeller Drive Flange (P/N

23031231) HT 2000 Hours Replace

Woodward Combined Governor

PN 23068275 HT 2000 Hours Overhaul

Woodward Propeller Overspeed Governor

PN 23032241

HT 3000 Hours Overhaul

72 Deleted

Engine-Driven Vacuum Pump OC

Initial at 600 Hours, every 100 Hours

thereafter

Inspection

Deleted

Bleed Valve PN 23073207 HT 1500 Hours Overhaul

73

Fuel Pump Goodrich P/N 23070459,

ALT P/N 23074705 (Rolls Royce PN)

HT 3500 Hours Overhaul

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Remark

Fuel Control (P/N 23070604) HT 2500 Hours Overhaul Fuel Nozzle (P/N 23077068) HT 2500 Hours Overhaul Honeywell Fuel Control (P/N

M250-10824) HT 2500 Hours Overhaul

75 Deleted

76 Engine Control Cable HT 3500 Hours or 10

Years Replace

Engine isolator Mounts HT 10 Years Replace

Engine Compartment Flexible

Fluid Carrying Hoses HT 15 Years Replace

80 Starter Generator Brushes OC 300 Hours Inspection Starter Generator

P/N 200SGL129Q HT 1200 Hours Overhaul

3.4. ENGINE AND ENGINE COMPONENT LIFE LIMITS 3.4.1. Engine Time between Overhaul

The Model 250 engine was designed to permit modular overhaul. The major components of the engine are the compressor, gearbox, propeller reduction gearbox and turbine. A premature removal of any of these components should not cause removal of the other components unless secondary damage has occurred.

A. Engine TBO

For operators who do not wish to utilize the modular overhaul concept, the recommended time between overhaul excluding the TBO for Individual accessories, is 3500 hours with a 1750 hour turbine heavy maintenance inspection. However, it is possible that the allowable cycle life limit of certain rotating parts may be exceeded before the recommended TBO is reached.

B. Modular TBO

For operators who wish to utilize modular overhaul, Rolls--Royce recommends time between overhauls. However, it is possible that the allowable cycle life limit of certain parts may be exceeded before the recommended TBO.

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The following are Modular Overhaul Components Recommended Time Between Overhauls:

NOMENCLATURE Recommended

TBO

Recommended Heavy Maintenance Inspection (HMI) by

Authorized Overhaul Facilities

Gearbox PN 23033382 On condition None

Compressor PN 23073499 3500 (1) None

Turbine PN 23088159 3500 (1) 1750 (1)

Propeller Reduction Gearbox, P/N 23050802 (250--B17F/1, --B17F/2)

On condition None

Propeller Reduction Gearbox, P/N 23033880

(250--B17F)

2000 (2) None

(1) Refer to life limits on certain rotating parts. It is the responsibility of the operator to assure that the life limits are never exceeded.

(2) Refer to certain life limits on certain rotating parts of the aerobatic propeller reduction gearbox (250-B17F).

3.4.2. Life Limits of the Compressor Rotor Assembly

Nomenclature Part Number Description

Max Operating

Hours

Maximum Cycles

Impeller 23034785 Original 4575 9150

Impeller 23039065 New forging 7500 15000

Wheel, 1^st 23032621 Original 7500 15000

Wheel, 1^st 23079008 Machined 7500 15000

Wheel, 2^nd 23032622 Original 7500 15000

Wheel, 2^nd 23035252 High taper 7500 15000

Wheel, 2^nd 23079007 Machined 7500 15000

Wheel, 3^rd 23032623 Original 7500 15000

Wheel, 3^rd 23079006 Machined 7500 15000

Wheel, 4^th 23032624 Original 7500 15000

Wheel, 4^th 23035254 High taper 7500 15000

Wheel, 4^th 23078987 Machined 7500 15000