AIRCRAFT MAINTENANCE PROGRAM

AIRCRAFT MAINTENANCE PROGRAM

C208B SERIES

MANUAL REFERENCE ALS/AMP/C208B EDITION 001 REV 000 ISSUED

26JUN15 Copy #

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P.O.BOX 41937 – 00100 NAIROBI, KENYA

Physical Address:

ALS Limited | ALS Building | Wilson Airport | P.O. Box 41937 - 00100 | Nairobi | Tel: +254 20 603 706

Fax: +254 20 607 185 Email: [email protected]|

Edition 001 ALS LIMITED SECTION 0

Revision 000 C208B AIRCRAFT MAINTENANCE

PROGRAMME Page 4

Issued 26Jun15 INTRODUCTION

SUBJECT: RECORD OF ‘A’ REVISIONS

Document Number:.……………………… Manual Holder:..……………………. Retain this record in the Manual. Upon receipt of revisions, insert revised pages in the Manual and enter

the revision number, date and initials (person inserting the pages), in the appropriate block on this page. Return acknowledgement form to the Librarian.

REV No.

Revision Date

Insertion Date

Inserted By

REV No

.

Revision Date

Insertion Date

Inserted By



PROGRAMME Page 5


SUBJECT: RECORD OF ‘B’ REVISIONS

Document Number:.……………………….… Manual Holder:..…………………………..………….

Retain this record in the Manual. Upon receipt of revisions, insert revised pages in the Manual and enter

the revision number, date and initials (person inserting the pages), in the appropriate block on this page. Return acknowledgement form to the Librarian. All personnel are expected to suggest revision requirements, when the need is apparent, to the Post-Holder Maintenance.

REV No.

Revision Date

Insertion Date

Inserted By

REV No

.

Revision Date

Insertion Date

Inserted By

Edition 001 ALS Section 0

Revision 000 AIRCRAFT MAINTENANCE PROGRAM Page 6

Issued 26Jun15 CESSNA 208 SERIES

SUBJECT: REVISION HIGHLIGHTS

Retain all previous highlight pages in this manual for reference. Remove all affected pages and insert attached pages. Enter revision no. and date inserted on Revision Record Sheet.

Section Sub-section Page Date Description




TABLE OF CONTENT PAGE NUMBER TITLE

1 Title Page 2 Operator statement of commitment 3 Approval Page

4-5 Amendment Record 6 List of Effective Pages

7-8 Table of Contents14 Manual Distribution List15 Operators information16 Abbreviation

SECTION 1 AMMENDMENTS TO THE MAINTENANCE PROGRAM PAGE NUMBER TITLE

1 Introduction Amendments to the ProgramTemporary Amendments

SECTION 2 APPLICABILITYPAGE NUMBER TITLE

1

Applicability Introduction Review

SECTION 3 RESPONSIBILITIES ,STANDARDS AND CERTIFICATION PAGE NUMBER TITLE

1 Operator ResponsibilitiesCertifying Persons ResponsibilitiesGeneral Inspection Standards

2 Airworthiness Life Limitations (scrap items)Airworthiness directivesKCAA Requirements

3

Instructions for Continued AirworthinessChanges / Repairs / ModificationsUnscheduled Maintenance InspectionsDuplicate InspectionsScheduled Maintenance Task cards

4-5 Definitions 5 Definitions continued

6

Mechanical Irregularities regarding crew observationsPerformance Flight TestOff The Aircraft MaintenanceInspection Irregularities FindingsCertification Release to ServiceCertificate of Airworthiness Renewal

7 Pilot MaintenanceAnnual check

8 Inspection – Certificate of airworthiness RenewalSECTION 4 AIRWOTHINESS LIMITATIONS

PAGE NUMBER TITLE1 Scope

Definition 2 Typical inspection Time limits

Inspection Time table 3 Severe Inspection limits 4 Replacements time limits

Replacement Schedule




SECTION 5 TIME LIMITS/MAINTENANCE CHECKS PAGE NUMBER TITLE

1 Scope Inspection Requirements Inspection Time limits

2

Inspection Time limits continuation Component Time limits Continuous Inspection Program Listing of Supplement Inspections

3 General inspection criteria 3-4 Inspection Interval requirements 5 AMTOSS Code

6-12 Inspection items time limits 12-15 Components time limits

15 Typical operation condition Operation Inspection interval Inspection Time limits

16 Definition and Procedure

SECTION 6 CONTINUOUS INSPECTION PROGRAM PAGE NUMBER TITLE

1 Purpose Construction Inspection Time limitations

2 Definitions and procedure Definitions and procedure continued

3 Inspection documents 4 Procedure for escalation of Check periods

SECTION 7 PRATT & WHITNEY ENGINE INSPECTION 1 PRATT & WHITNEY ENGINE INSPECTION PROGRAM PREAMBLE Maintenance Concept Line Maintenance Heavy Maintenance Turboprop Inspection General 2 Inspection Tolerances 5 Period Inspection Timetable

7

Unscheduled Inspection Procedures General • Overspeed• Inadvertent Cut-off and Relight During Taxi• Over-temperature• Over-torque

8

• Immersion in Water• Dropped Engine• Material Ingestion• Bird Strike/Soft Material Ingestion

9 • Propeller sudden stoppage10 • Propeller strike causing minor blade damage 10 • Propeller Electrical Leads Shorting11 • Propeller Lightning Strike




SECTION 8 ROTOR COMPONENT SERVICE LIFE

PAGE TITLE1 Rotor Component Service Life

Effectivity 2 Component Life Calculation Formula

Rotor Cycle Limit Time Table

3 Operating Times Between OverhaulsEffectivity Summary

4 Basic industry Time between OverhaulTBO Extension RecommendationsHot Section Inspection (HSI) Frequency

5 Compressor Turbine Blade Maintenance Requirements

SECTION 9 KCAA REQUIREMENTSPAGE TITLE

1 KCAA Requirements

SECTION 10 DEFECTS DEFERREDPAGE TITLE

1 Defects deferred in the field

SECTION 11 DEFERED DEFECTS PAGE

NUMBER TITLE

1 Deferred defects

11 • Heavy/Hard Landing

13

• Aircraft Flown Through Volcanic Ash or Smoke • Sustained Running at Oil Temperature Outside Limits • Loss of Oil/Oil Pressure or low oil pressure

15

• Oil pressure follows throttle• Contamination by Fire Extinguishing Agents• Halon

16 • Audible Rubbing, Binding or Scraping

17

• Audible Rubbing, Binding or Scraping continued • Propeller Wind-milling after In-flight Shutdown• Contamination of Oil with Non-metallic Foreign Material

18

• Starter-Generator Replacement• Starter-Generator Replacement continued• Chip Detector Circuit Completion and/or Debris in Oil Filter • Propeller sudden stoppage continued• Engine maintenance schedule chart

19-24 • Engine maintenance schedule chart continued

SECTION 12 ALS DAILY AND WEEKLY INSPECTIONS PAGE TITLE

1 Daily Inspection walk-around2 Daily Inspection walk-around continued




SECTION 13 SUPPLEMENTAL INSPECTION

PAGE TITLE1 Introduction

Function 2 Principal Structural elements 3 Classification for types of operation4 Reporting –Communication discrepancies5 Discrepancy report6 Inspection Methods

Applicability/LimitationsSECTION 13 SUPPLEMENTAL INSPECTIONS

PAGE TITLE7 Listing on Supplemental inspections

8-12 Supplemental Inspection to Task Matrix

SECTION 14 RELIABILITY PROGRAM INSPECTIONSPAGE TITLE

1 Reliability Program inspections

SECTION 15 UNSCHEDULED MAINTENANCE CHECKS PAGE TITLE

1

General Unscheduled Maintenance Checks Defined

• Hard / Overweight Landing • Overspeed • Severe air turbulence or severe manoeuvres• Lightning strike

2 • Foreign object damage• High drag/side loads due to ground handling

Unscheduled Inspection Check Timetable & Procedure

3

• Hard / Overweight Landings• Overspeed • Severe Air Turbulence or severe Manoeuvres • High drag/side loads due to ground handling

4 • Lightning Strike • Lightning Strike Continued • Foreign Object Damage

5 • High drag/side loads to ground handling • Lightning strike/static discharge incident reporting form Part 1

6 • Lightning strike/static discharge incident reporting form Part 2

3 Daily Inspection Pocket Edition Checklist 4 Weekly Inspection5 Weekly Inspection walk requirements5 Weekly Inspection checklist




SECTION 17 ALS MAINTENANCE TRACKING SYSTEM

PAGE TITLE1-2 ALS maintenance tracking system

SECTION 18 ANNEXURE

Annex 1 Ground run sheet Annex 2 Maintenance task cardAnnex 3 100 Hours inspection Annex 4 Static dischargeAnnex 5 Cable tension check record sheetAnnex 6 Cable travels check record sheetAnnex 7 FCU static override 200 hours inspectionAnnex 8 ITT calibration sheetAnnex 9 Torque calibration sheetAnnex 10 Main Landing Gear inspection sheetAnnex 11 Accessory Gearbox Scavenge Filter 1000 hour inspection Check SheetAnnex 12 Post SB 1581 Bleed off Valve 600 hour Inspection Check Sheet Annex 13 Brake burn in procedureAnnex 14 Daily Inspection ChecklistAnnex 15 Weekly inspection ChecklistAnnex 16 C OF A test flightAnnex 17 Engine & components removal and installation form

SECTION 16 CONTINUOUS INSPECTION PROGRAM TASK BASED CHECK SHEETSPAGE TITLE1-50 Continuous inspection program task based check sheets




MANUAL DISTRIBUTION

COPY Number

COPY HOLDER FORMAT

001 KCAA Hardcopy

002 Central Library Hardcopy

003 Chief Executive Officer CD/SERVER

004 Director of Maintenance ALS CD/SERVER

006 Technical Director CD/SERVER

009 Director of Quality Assurance CD/SERVER

011 Quality Control Manager CD/SERVER

012 Base Maintenance Manager CD/SERVER

101 Base Maintenance Nairobi CD/SERVER




1. OPERATOR’S INFORMATION

Register Name : ALS Limited

Registered Address : Wilson Airport Nairobi, Kenya

East Africa

Aircraft Applicability : Cessna 208B series

Aircraft Registration : 5Y-SXC

Aircraft Serial Number : 208B2372

Operator’s Maintenance

Program Reference : ALS/AMP/C208B

Edition. : 001

Revision : 000

Date : 26Jun15

2. AIRCRAFT PARTICULARS

Aircraft Type : Cessna 208B series

Aircraft Manufacturer : Cessna

Aircraft Model : C208B series


Engine Type : PT6A-114A

Engine Manufacturer : Pratt & Whitney

Propeller Type : MCAULEY Propeller Manufacturer : Hamilton Standard




ABBREVIATION KCAA Kenya Civil Aviation Authority SB Service Bulletin AD Airworthiness Directive CAWIS Continuing Airworthiness Web Information System C of A Certificate of Airworthiness C of R Certificate of Registration AOG Aircraft on Ground OEM Original Equipment Manufacturer SRM Structural Repair Manual AMO Approved Maintenance Organization FAA Federal Aviation Administration ATA Air Transport Association MPM Maintenance Procedures Manual WTR Without Type Rating Cat A Airframe Cat C Engine Cat X Electrical, Instrument, Autopilot and Compass Cat R Radio CRS Certificate of Release to Service AME Aircraft Maintenance Engineer MEL Minimum Equipment List INOP Inoperative FOD Foreign Object Damage HSI Hot Section Inspection CFR Code of federal regulations




MANUAL DISTRIBUTION

COPY Number

COPY HOLDER FORMAT

001 KCAA Hardcopy

002 Central Library Hardcopy

003 Chief Executive Officer CD/SERVER

004 Director of Maintenance ALS CD/SERVER

006 Technical Director CD/SERVER

009 Director of Quality Assurance CD/SERVER

011 Quality Control Manager CD/SERVER

012 Base Maintenance Manager CD/SERVER

101 Base Maintenance Nairobi CD/SERVER




1. OPERATOR’S INFORMATION

Register Name : ALS Limited

Registered Address : Wilson Airport Nairobi, Kenya

East Africa

Aircraft Applicability : Cessna 208B series

Aircraft Registration : 5Y-SXC


Operator’s Maintenance

Program Reference : ALS/AMP/C208B

Edition. : 001

Revision : 000

Date : 26Jun15

2. AIRCRAFT PARTICULARS

Aircraft Type : Cessna 208B series

Aircraft Manufacturer : Cessna

Aircraft Model : C208B series


Engine Type : PT6A-114A

Engine Manufacturer : Pratt & Whitney

Propeller Type : MCAULEY Propeller Manufacturer : Hamilton Standard




ABBREVIATION KCAA Kenya Civil Aviation Authority SB Service Bulletin AD Airworthiness Directive CAWIS Continuing Airworthiness Web Information System C of A Certificate of Airworthiness C of R Certificate of Registration AOG Aircraft on Ground OEM Original Equipment Manufacturer SRM Structural Repair Manual AMO Approved Maintenance Organization FAA Federal Aviation Administration ATA Air Transport Association MPM Maintenance Procedures Manual WTR Without Type Rating Cat A Airframe Cat C Engine Cat X Electrical, Instrument, Autopilot and Compass Cat R Radio CRS Certificate of Release to Service AME Aircraft Maintenance Engineer MEL Minimum Equipment List INOP Inoperative FOD Foreign Object Damage HSI Hot Section Inspection CFR Code of federal regulations

SECTION 1

AMMENDMENT TO THE

MAINTENANCE PROGRAM


Revision 000 C208B AMP Page 1


1.0. Any amendments introduced into this Program by ALS Ltd., after the approval, KCAA shall be notified for approval in the form of replacement pages bearing the amendment date and page affected being submitted. Each page amended will be indicated in the list of effective pages and details elaborated in the reserved part. Amendments shall be incorporated in the program immediately and in the Amendment Record at the front of this Program after approval from KCAA. All amendments to this Program are the responsibility of the Director of Maintenance. 1.1 AMENDMENTS TO THE PROGRAM Amendments to this Maintenance Program will be prepared by ALS Limited. Amendments are raised to reflect the embodiment of mandatory and non-mandatory modifications, inspections, maintenance tasks, manufacturer’s recommendations or requirements and the results of operational experience. Refer to MCM Section 3.2.5.4 and section 3.2.2.1 pg 2-3. Revisions to the Inspection Program must be approved by the Kenya Civil Aviation Authority and shall not be incorporated into the Company’s Maintenance Program prior to KCAA approval.

Every amendments issue will include a list of highlights indicating significant changes. Each revision should be confirmed in the Record Sheet of Revision. Revision bars are located Right and adjacent to the affected text.

The AMO will review these requirements including the effectiveness of the maintenance program for continued validity and airworthiness at least once annually. Refer MCM section 3.2.5 pg 2-3 KCAA “A” amendments must be incorporated in the program without delay and recorded on the amendment record in the front of this book. Following chapters of the AMP are reissued completely with every AMP revision:

List of Effective Items

The Director of Maintenance will review these requirements including the effectiveness of the maintenance program for continued validity and airworthiness as per current 1.2 Temporary Amendments The changes that arises will be in the form of a Temporary Revision printed in Yellow paper and inserted on the top of the amended page The temporary revision will remain within the maintenance program until such time that the revision has been approved by the KCAA. Temporary revisions that are more restrictive than those specified in the Approved AMP, KCAA requirements and The Manufacturer shall be incorporated into the AMP immediately. All temporary revisions will be submitted to the central library for distribution MCM section 3.2.3 pg 2 will be transmitted to all manual holders in the form of email attachments or in print on white paper, accompanied by a list of amendments on a compliance register. The completed list will then be filed appropriately in the Central Library by the librarian. Once the new revisions are placed in the AMP (The temp rev and the superseded page will be removed).

SECTION 2

APPLICABILITY



Issued 26Jun15 APPLICABILITY

2.1 Applicability This program is applicable to C208B series aircraft operated by ALS Limited.

2.2 Introduction This program is derived from:

Cessna 208B Maintenance Manual D2078MM rev. 28 ATA CHAPTER

REFERENCE Airworthiness Limitations 4-00-00 Typical Inspection Limits 4-10-00Severe Inspection Limits 4-10-01 Replacement time Limits 4-11-00 Time Limits/Maintenance Checks 5-00-00 Inspections 5-10-00 Inspection Time Limits 5-10-01 Component Time Limits 5-11-00 Supplemental Inspection Document 5-13-00 Listing of Supplement Inspections 5-14-00 Continuous Inspection Program 5-15-00 Inspection Documents 5-15-0A thru 5-15-ML Unscheduled Maintenance Checks 5-50-00

PWC PT6A Engine Maintenance Manual 3043512 rev. 30

PWC Service Bulletins

McCauley service bulletins

Requirements by the Kenya Civil Aviation Authority.

FAA & CAWIS Airworthiness Directives Note: please refer to the publication listing in the central library for current revisions of manuals & bulletins. All civil airplanes of Kenya registry must have a complete examination (Annual) each 12 calendar months. In addition, maintenance after every 100 hours 200hrs of operation also is required to be carried as required by the Civil Aviation Regulations and respective maintenance manuals. Non-compliance with Time Limited Tasks program and inspections, overhauls, repairs, component changes and modifications, which could affect the airworthiness of the aircraft, will invalidate the Certificate of Airworthiness and the Certificate of Release to Service insofar as it applies to a particular aircraft. Inspections will be carried out in accordance with the Task-Based Inspection Program, which is divided into Main operations referred to as Inspection 1 through 12 Inspections, which include all 12Month, 24Month, 48Month, 72Month, 144Months, 200Hrs/12Month,400Hr/12Month, 400Hr/24Month, 800Hr/12Month, 800Hr/24Month, 1600Hr/24Month, 1600Hr/60Month inspection requirements. There are out of phase inspection items due at other intervals that begin from Inspection 13 to Inspection 22, Inspection MA thru Inspection ML. 2.3 Review Review of this Program will be continuous as changes and/or revisions occur to the documents referred to above to ensure that the maintenance needs of the aircraft are being met such that continuing safe operation can be assured.MCM section 3.2.5 pg 2

A/C MODEL A/C REG A/C S/N ENGINE MODEL PROPELLER MODEL

C208B 5Y-SXC 208B2372 PT6A-114A McCauley 3GFR34C703-B

SECTION 3

RESPONSIBILITIES, STANDARDS

AND CERTIFICATION



Issued 26Jun15 RESPONSIBILITIES, STANDARDS AND CERTIFICATION

3.1 Operator Responsibilities The CRS shall be issued by ALS limited Approved Maintenance Organization. On completion of any of the program maintenance checks, a detailed, referenced entry is made in the relevant log books with an appropriate Certificate of Release to Service by certifying person. The issue of a Certificate of Release to Service is indicative that all mandatory modifications and inspections have been complied with. The Certificate of Release to Service is issued for the following categories:

Airframe category “A” Engine category “C” Radio category “R” Electrical category “X”

Compass Cat ‘X’ Task 1c/Annual compass swing at C of A renewal Instrument Cat ‘X’ Task 1C/Annual Pitot/static leak check at C of A renewal Autopilot Cat ‘X’ Task 2A/2C 800-hour or 24-months whichever occurs first.

3.2 Certifying Persons Responsibilities 1 Certifying Persons shall be Aircraft Maintenance Engineers with the appropriate license or approved authority, as per Regulation 27 (2)(a,b,c) of The Civil Aviation (AIRWORTHINESS) Regulations, 2013. 2 Certifying persons will use their engineering skills and judgment in determining the depth of inspection needed and other matters, which could affect the airworthiness of the aircraft. In order to claim any alleviation on subsequent inspections, the aircraft maintenance records shall record the extent of previous inspections upon which the alleviation is based. 3. Certifying persons shall be responsible for: a. Recording in the appropriate log book or worksheet, any defects, deficiencies or additional maintenance required as a result of implementation of this schedule. b. Any damage or defect affecting safety found during an inspection is rectified before the aircraft is released to service. c. Ensure that all work carried out on aircraft is done so in accordance with the standards and recommendations detailed in the Manufacturer’s Maintenance Manual, the Maintenance Control Manual and the Maintenance Procedures Manual. 4. Nothing in this schedule is to be construed as absolving maintenance engineers from maintaining aircraft under their care in a thoroughly serviceable condition and from ensuring that all mandatory requirements applicable to the aircraft and its equipment have been complied with. 3 .3 General Inspection Standards 1 The general inspection standards applied to individual task inspections shall meet the recommended standards and practices of the organization responsible for the type design as published in maintenance manuals. 2 In the absence of general inspection standards of the organization responsible for the type design, refer to KCAA recommended standards and practices, i .e. Airworthiness Notices shall be applied, as well as procedures laid out in the FAA AC43-13-2A. NOTE: Airworthiness Notices shall be assessed for applicability and where necessary included in this Maintenance program. Inspections shall be carried out without component removal or dismantling unless considered necessary or where required by this program.




3.4 Airworthiness Life Limitations (Retirement/Scrap Lives) Airworthiness life limitations shall be those published by Cessna 208 series Maintenance Manual, Pratt & Whitney Maintenance Manual, PWC SB 1703 as revised, the KCAA and the state of design Type Certificate or Supplementary Type Certificate Holder. 1 Life limited components shall be retired from service at the intervals specified by Cessna 208 series Maintenance Manual, Pratt & Whitney Maintenance Manual, PWC SB 1703 as revised, the KCAA and the state of design Type Certificate or Supplementary Type Certificate Holder Overhaul Manuals. 2 Component life limitations shall be monitored through a computerized maintenance tracking system to enable accomplishment of inspections and maintenance on an on-going basis. 3.5 Airworthiness Directives 1 All applicable Airworthiness Directives issued by the FAA, the CAWIS, the KCAA shall be complied with. 2 Compliance with Airworthiness Directives shall be recorded in the aircraft log book or an approved equivalent. 3 In cases where an AD is issued that varies from the organization responsible for the type design requirements/lives specified in the AD will take precedence. 4 In cases whereby the AD issued is beyond the AMO holder’s capability, contracted maintenance organizations either local or international will be used subject to KCAA approval. In certain cases the aircraft may be flown to such facilities. 5 Repetitive ADs and SBs shall be included as part of this program to prevent inadvertent non-compliance. 6 ADs and SBs are tracked by maintenance software and computer program by ALS Technical Records Office, for each specific aircraft registration, and are reviewed at each scheduled inspection. 7 New ADs and SB that are published while the aircraft is away from base are reviewed on arrival for compliance time limits. The Director of Maintenance will determine the period stated for incorporation there-of, and determine if compliance can be postponed to the next scheduled check. Should compliance be deemed with immediate effect, the Director of Maintenance will, through Operations Office, recall the aircraft from service for compliance, or make arrangements for compliance to be carried out in the field if the publication deems this possible. 3.6 KCAA Requirements All applicable mandatory KCAA Requirements (’B’ Notices) must be complied with. Compliance with KCARs shall be recorded in the relevant logbooks. KCARS AIRWORTHINESS 37 (1) 1. Overhaul, Additional Inspections and Test Periods 2. Overhaul, additional inspections and test periods shall be those recommended by the manufacturers responsible for the type design. 3. FAA, CAWIS and the KCAA may vary or mandate overhaul and test periods and additional inspections by the issue of an Airworthiness Directive or KCAA Requirements. 4. The overhaul, additional inspections and test periods shall be recorded in the appropriate logbook or an appropriate equivalent.




3.7 Instructions for Continuing Airworthiness Instructions for continuing airworthiness shall consist of in service data published by type design organizations in addition to this maintenance schedule in order to ensure the approved maintenance schedule remains valid for the aircraft maintained by ALS. 1. Instructions for continuing airworthiness (Service Bulletins, Service Letters, etc.) shall be formally, technically assessed by the Quality Control Manager. All mandatory Instructions for continuing airworthiness shall be complied with. Recommended and Optional shall be considered by the Director of Maintenance and adopted if required to ensure operational safety and reliability. 2. Repetitive Instructions for continuing airworthiness shall be included in this schedule to prevent inadvertent non-compliance. 3. In the event of any conflict between the requirements or instructions issued by a manufacturer and/or those issued by the Director General KCAA and this Schedule, the provisions of the former shall prevail. 3.8 Changes (Repairs/Modifications) 1.In case of proposed ‘changes’ to the airframe, engine, propeller, components and radio after original manufacture, KCAA shall be notified for approval by filling the modification application forms. 2. Approved ‘changes’ once carried out shall be recorded in the appropriate log book(s). 3. Any recurring inspection or maintenance task resulting from approved ‘changes’ shall be included in this schedule as soon as possible. 3.9 Unscheduled Maintenance inspections In case of unscheduled maintenance inspections necessitated by, Hard or Overweight landing, severe turbulence, Lightening strikes or Foreign Object Damage the manufacturer’s recommendations shall be followed as the Special Inspection Chapter. 3.10 Duplicate Inspections Whenever any part of either the main or associated system of the flying controls or engine controls is dismantled, adjusted, repaired or renewed, that part of the system which has been disturbed shall be subject to a duplicate inspection check, and shall be certified accordingly. These areas include, but are not limited to:

Installation, rigging and adjustments of engine and flight controls. Installation and repair of major structural components. Installation of aircraft engines and propellers. Calibration or rigging of components such as engines or propellers.

An initial inspection of items mentioned above must be by a type rated licenced engineer/licensed engineer with KCAA Dispensation ,and a second inspection carried out by another person who is also a type rated licenced engineer/licensed engineer with KCAA Dispensation. Certification shall be recorded in the appropriate worksheet, logbook or aircraft technical log. 3.11 Scheduled Maintenance Task Cards Task Cards shall be issued and the tasks certified for all scheduled maintenance checks. These Task Cards are printed from the latest revision of the Maintenance Manual and form part of the maintenance records required to be kept by ALS. 1. Task Cards have the date of currency of the tasks as well as the Chapter and revision number of the manual used printed across the top of the Task Cards. The page number is printed at the bottom right hand corner of the task card. Below the INSPECTION DOCUMENT NUMBER, there is provision for mechanic to write the date, aircraft registration number, serial number and the aircraft total time. REFER to Chapter 16 of this program for the task cards.




2. All maintenance carried out in connection with a particular check shall be certified on the worksheets and cross- referenced in the appropriate log book(s) entry giving general details of maintenance carried out. 3.12 Definitions Throughout this program, the following terminology and abbreviations pertaining to the inspection procedures which are in accordance with the Code of Federal Regulations Parts 143 and 91 issued by the FAA, have the following stated definitions: 1 Continuous Inspection A continuous inspection is a continuing airworthiness inspection of an airplane and its various components and systems at scheduled intervals IAW procedures prescribed by the Manufacturer as laid out in the Maintenance Manual. 2 Operation Inspection Operation Inspection consists of a thorough examination of the appliances, the airplane and components and systems with such disassembly as necessary. 3 Flight Time Flight time shall mean the total time from the moment of take off to the moment of landing. 4 Maintenance Means all work carried out in accordance with manufacturer’s recommendation and approved maintenance schedules and shall include cleaning, inspection, adjustment, rectification, repair, modification, testing, preservations, overhaul and the replacement of time limited parts excluding preventive maintenance 5. Preventive Maintenance Means simple or minor preservative operations and the replacement of small standard parts not involving complex, assembly operations. 6. Pilot in Command Pilot in command shall mean the pilot responsible for the operation and safety of the airplane during the time defined as flight time as well as time on ground from the moment the airplane first moves under its own power for the purpose of flight to the moment it comes to rest at the next point of landing. 7. Time in Service Time in Service, as used in computing maintenance and inspection time records is the time from the moment the airplane leaves the ground for purposes of flight until it touches the ground at the end of a flight. 8. Flight Cycle A flight cycle is defined as: engine start-up and increase to full power (as required during normal flight), one landing gear retraction and extension and a complete shutdown. 9. Corrosion Pitting or, a surface breakdown of material, due to chemical or electro-chemical attack by atmosphere, moisture or other agents. 10. Inspect (Insp.) An ‘Inspection’ is a visual check performed externally or internally in suitable lighting conditions from a distance considered necessary to detect unsatisfactory conditions/discrepancies using, where necessary, inspection aids such as mirrors, torches, a magnifying glass etc. Surface cleaning and




removal of detachable cowlings, panels, covers and fabric may be required to be able to satisfy the inspection requirements. 11. Operational Check (OPS/C) An ‘Operational Check’ is a test used to determine that a system or component or any function thereof is operating normally. 12. Functional Check (F/C) A ‘Functional Check’ is a detailed examination of a complete system, sub- system or component to determine if operating parameters are within limits of range of movement, rate of flow, temperature, pressure, revolutions per minute, degrees of travel, etc., as specified in the appropriate maintenance manual. Measured parameters should be recorded. 13. Check (CHK) A ‘Check’ is the verification of compliance with the type design organization’s recommendations. 14.Continuing Airworthiness Means all of the processes ensuring that, at any time in its operating life, the aircraft complies with the airworthiness requirements in force and is in a condition for safe operation. 15. Calendar Time The time from the date on the ORIGINAL AIRWORTHINESS CERTIFICATE as issued on FAA form 8100-2 or equivalent, used as a basis of all TBOs or of replacement of components. 16. Special Inspection Inspections of components or systems based on calendar time, hours or cycles, which do not coincide with scheduled inspections. 17. Unscheduled Maintenance Checks Inspections and checks for damage after operating the airplane in conditions that require unscheduled maintenance, i.e. lightning strikes, hard landing, polluted atmospheric conditions etc. 18. Public Transport The provisions of this maintenance schedule related to Commercial Air Transport are applicable to aircraft operated by licensed air carriers i.e. operators issued with an Air Operator’s Certificate (AOC). 19. Non- Commercial Air Transport The provisions of this maintenance schedule related to Non- Commercial Air Transport are applicable to aircraft operated for Private purposes or Public Transport or Aerial Work as defined in KCARS (as amended) and not used for Commercial Air Transport. • Public Transport Purposes a) Where payment is made for the carriage of passengers or cargo; or b) Where valuable consideration (hire and reward) is given for a person to fly the aircraft, then the flight is deemed to be Public Transport for continuing airworthiness purposes. The flight may be considered Private for all other purposes. Example: A private pilot, not being the owner/ group owner of the aircraft, paying for hire of an aircraft from an owner or flying club. • Private Purposes A flight for Private purposes means a private flight in accordance with KCARS




3.13 Mechanical irregularities regarding crew observations 3.13.1 Upon the rectification of any defect entered in the technical logbook the person authorized to perform maintenance to rectify the defect and sign a maintenance release in respect of that defect shall enter the release in the technical logbook in such a position as to be identifiable as to which defect it relates. 3.13. 2 In the event that unscheduled maintenance and/or defect rectification is required to be carried out away from main base, the authorized engineer authorized by the AMO to carry out the defect rectification will be required to issue a Certificate of Release to Service in the Technical Log in the manner described in the maintenance control manual and shall release the aircraft back to service in accordance with the release to service procedures contained in ALS Maintenance procedures manual. 3.13.3 ALS will ensure that where defect rectification is carried out in the field and defects cleared on the technical log sheet that a copy of the technical log sheet is left behind at the station where the defect rectification was carried out. 3.13.4 The technical log sheet will be left with the company representative where ALS has operations support staff and in areas where ALS has no operations support staff the technical log sheet with an entry cleared out of base will be left for that specific flight with a responsible agency, the Engineer that rectified the defect will the technical log sheet left behind are collected and forwarded to the respective recipients as a policy copies of all Technical Log Sector Record Pages, and any other pertinent maintenance-related information, is forwarded promptly to ALS maintenance division , to allow them to perform their planning and Maintenance Co-ordination functions. 3.14 Performance Test Flight. 3.14.1 At the end of every scheduled 200 hour inspection, ALS has introduced an acceptance flight form to be used by flight crews. The form has provision for informing the pilot of any major work that has been carried out during the maintenance, or should maintenance require a particular system to be functionally checked. 3.14.2 Should any major work be carried out on an aircraft, engine, in relation to major structural repair, engine change, flight control maintenance, a test flight shall be carried out in order to check aircraft performance. 3.14.3 For the annual Certificate of Airworthiness Renewal, or precertification flight testing, a performance flight shall be carried out on the aircraft, engine and systems, and figures recorded on an ALS performance record. 3.15 Off the Aircraft Maintenance Overhaul and Repair of Engine, Propeller, and Appliance, whether scheduled or unscheduled, may be independent from maintenance performed on the aircraft. However, the tasks shall be performed in accordance with the procedures approved by the authority, and in compliance with the current manufactures instructions and standards. 3.16 Inspection Irregularity Findings. Irregularity Findings relating to structural, mechanical, operational or function during routine maintenance shall be recorded and rectified as per the Maintenance Procedure Manual. 3.17 Certificate of Release to Service (C of R) On completion of any check required by this schedule including any additional or out of phase inspections resulting from the review of instructions for continued airworthiness a C of R shall be issued IAW the KCARS AMO 31(1)




1 The period of validity of the C of R shall not exceed the due date of the next annual check or Maintenance actions that could render the aircraft un-airworthy that fall due before the next maintenance check. 2 The signatories for the C of R shall be Aircraft Maintenance Engineers with the appropriate type-rating license valid in the country in which the aircraft is registered. 3 Wordings of the Certificate of Release given in KCARS AMO 31(5). "Certifies that the work specified was carried out in accordance with current regulations and in respect of that work the aircraft or aircraft component is considered ready for release to service." 3.18 Certificate of Airworthiness Renewal 1 A certificate of airworthiness or restricted certificate of airworthiness issued under KCARS Airworthiness Regulation Part 3 (12) is valid for twelve months from the date of issue unless-

(a) a shorter period is specified by the Authority; (b) the Authority amends, extends, suspends, revokes or otherwise terminates the certificate; (c) the aircraft owner or operator surrenders the certificate to the Authority;

2. A person shall not fly an aircraft unless there is in force in respect of that aircraft, a certificate of airworthiness, a restricted certificate of airworthiness or a special flight permit duly issued or rendered valid under the law of the state of registry and any conditions subject to which the certificate was issued or rendered valid are complied with. 3. A certificate of airworthiness or restricted certificate of airworthiness issued in respect of an aircraft shall cease to be in force if: (a) the aircraft or such of its equipment as is necessary for the airworthiness of the aircraft is maintained or if any part of the aircraft or such equipment is removed or is replaced, otherwise than in a manner and with material of a type approved by the Authority either generally or in relation to a class of aircraft or to the particular aircraft; (b) the aircraft or any of its equipment is not maintained as required by the maintenance schedule approved by the Authority in relation to that aircraft; (c) an inspection or modification classified as mandatory by the Authority applicable to the aircraft or of any such equipment as aforesaid, has not, been completed to the satisfaction of the Authority; or (d) the aircraft or any equipment of the aircraft sustains damage and the damage is ascertained during inspection which affects the airworthiness of the aircraft. NOTE: Attention is drawn to the necessity of ensuring that a certificate of release to service is issued at the completion of any maintenance activity. 3.19 Pilot Maintenance A licensed pilot who is the operator of an aircraft may carry out the following:

a) Pre-flight Inspections if an aircraft is to be operated. b) The pilot must include his/ her pilot's license number with his/ her signature in the appropriate technical log.

c) Defer items as per the approved Minimum Equipment List for the aircraft type.




3.20 Annual Check Under the supervision of an organization appropriately approved in accordance with KCARS AMO 31(1) with the appropriate type rating or the holder of a license with the appropriate type or group rating. 3.21 Inspection - Certificate of Airworthiness Renewal During the C of A renewal an Inspection comprising of all annual inspections required by KCAA, organization responsible for the type design as published in maintenance manuals, (see Appendix 1) and associated work shall be completed before making a recommendation for the renewal of the Certificate of Airworthiness.

SECTION 4 AIRWORTHINESS

LIMITATIONS



Issued 26Jun15 AIRWORTHINESS LIMITATIONS

4.1. SCOPE A. This chapter gives the mandatory replacement times and inspection intervals for components and structures that are life-limited. The section also gives the scheduled inspection requirements for structural and fatigue components that are considered a part of the certification process. 4.2. DEFINITION A. This chapter has three sections. (1) Typical Inspection Time Limits (AMM 4-10-00). This section gives the systems and components that must be inspected at specified intervals for typical operations. The intervals are the maximum time permitted between inspections. (2) Severe Inspection Time Limits (AMM 4-10-01). This section gives the systems and components that must be inspected at specified intervals for severe operations. The intervals are the maximum time permitted between inspections. (3) Replacement Time Limits (AMM 4-11-00). This section gives the life limited components which must be replaced at a specific time. B. Operational Inspection Times. (1) Aircraft operation is based on average flight length. (2) You must also find the number of hours and number of landings on the airplane, then find the average flight length based on the formulas found below. You must use whichever number is less.

Number of Flight _____ Hours ____ Number of Flights

= Average Flight Length

or Number of Flight _____ Hours ____

Number of Landings = Average Flight Length

(3) If the average flight length is less than or equal to thirty-five minutes, then ALS Limited shall use the inspection times found in section 4-10-01, Severe Inspection Time Limits. (4) For airplanes with an average flight length greater than thirty-five minutes, ALS will find the severity of the operating environment. If the airplane operates thirty percent or more of its flight time in severe environments, ALS will use the severe operation inspection times found in section 4-10-01, Severe Inspection Time Limits. Examples of severe environments would include floatplane operations, flight operations at low altitude (i.e., less than 5,000 ft. above ground level) such as pipeline patrol, sightseeing, training flights, traversing mountainous terrain or flying near coastal areas identified in section 51-12-00, Corrosion Severity Maps - Description and Operation. (5) For all other operating environments, inspections should be conducted using the typical operation inspection times in AMM 4-10-00, Typical Inspection Time Limits. For the time being ALS Limited uses the Typical Inspection Time Limits (6) After the operating environment is known, make an airplane logbook entry that states which inspection (Typical or Severe) is being used.




4.3 Typical Inspection Time Limits 4.3.1 General Inspection time intervals for the components that follow show the maximum intervals. Expanded inspection and maintenance check procedures are shown in the applicable sections in the maintenance manual. 4.4 Inspection Time Table (extracted from Cessna MM Rev 28 Chapter 4-10-00)

ITEM INSPECTIONFlight Controls (Chapter 27)

Flap Bell Crank (Part Numbers 2622281-2, -12)

NDI- Eddy Current (Ref: CAB02-1 Rev 2)

first 4000 landings, then every 500 landings thereafter

Flap Bell Crank (Part Number 2692001-2)

NDI- Eddy Current (Ref: CAB02-1 Rev 2)

first 4000 landings, then every 500 landings thereafter

NOTE: Total Landings include the accumulated landings of 2622281-2 prior to modification by SK208-123 to the 2692001-2 configuration

NOTE: These components also have replacement time limits. Refer to Chapter 4-11-00 ,Replacement time limits, of the Maintenance Manual for replacement criteria

Landing Gear (Chapter 32) Main Landing Gear Axles

(Part Numbers 2641011-1, -3, -4) NDI- Magnetic

Particle inspection first 5000 landings and every 1000 landings thereafter

Ref task 32-10-00-240(SID 32-10-01) NOTE: These components also have replacement time limits. Refer to Chapter 4-11-00 ,Replacement time limits, of the

Maintenance Manual for replacement criteria Fuselage(P/N 2610000-1,-2 & 2610001-1,-2) (Chapter 53)

Fuselage to Strut Attach Fitting and Lugs NDI- Eddy Current

First 5,000 hours (SID 53-20-07) and a).every 1200 hours thereafter for lugs with standard/nominal bolt size p/n S3461-74 b). every 500 hours thereafter for lugs with 1/64inch oversize bolt size p/n S3461-159 c). every 400 hours thereafter for lugs with 1/32inch oversize bolt size p/n S3461-160

Fuselage to Wing Carry-Thru Attach Fitting NDI- Eddy Current First 20,000 hours and every 5000 hours thereafter (SID 53-20-02)

Wing (Chapter 57) Wing ( Part Numbers 2622000-1, -2, -101, -102, -119, -120, -123, -124)

Centre Flap Track NDI- Eddy Current First 15,000 landings and every 3000 landings thereafter ( Supplemental Inspection Number 57-50-01)

Inboard Flap Track NDI- Eddy Current First 15,000 landings and every 3000 landings thereafter( Supplemental Inspection Number 57-50-01)

Outboard Flap Track NDI- Eddy Current First 15,000 landings and every 3000 landings thereafter( Supplemental Inspection Number 57-50-01)

Front Spar Lower Cap Inspection Inboard of WS 141.20 NDI- Eddy Current First 20,000 hours and every 5000 hours thereafter

( Supplemental Inspection Number 57-20-02) Rear Spar Lower Cap Inspection Inboard of WS 141.20 NDI- Eddy Current First 20,000 hours and every 5000 hours thereafter

( Supplemental Inspection Number 57-20-03) ITEM INSPECTION

Wing ( Part Numbers 2622000-1, -2, -101, -102, -119, -120, -123, -124)

Wing/Strut Attachment to Front Spar NDI- Eddy Current First 20,000 hours and every 5000 hours thereafter ( Supplemental Inspection Number 57-60-02)

Wing to Carry-Thru Front Spar Attachment Fittings NDI- Eddy Current First 20,000 hours and every 5000 hours thereafter

( Supplemental Inspection Number 57-20-01) Wing to Carry-Thru Rear Spar Attachment Fittings NDI- Eddy Current First 20,000 hours and every 5000 hours thereafter

( Supplemental Inspection Number 57-20-01) Wing Strut (Part Numbers 2621000-5, -6, -11, -12, -19,-20, -21, -22)

Wing Strut Attach Fitting NDI- Eddy Current First 10,000 hours and every 5000 hours thereafter (Supplemental Inspection Number 57-60-01)




4.5 Severe Inspection Time Limits 4.5.1 General All Cessna 208s maintained by ALS Limited do not operate in severe conditions of high humidity and salt laden atmosphere, so this section is not included in this schedule. All Aircraft listed on Section 2.5 is maintained on the Typical Time Limits Schedule.




4.6 Replacement time limits General The following life-limited components are to be replaced at the specified time. It is recommended that the components be scheduled for replacement during the airplane's inspection interval coinciding with, or occurring just before, the expiration of the specified time limit. Procedures for replacement of the components are described in the applicable chapters in the Maintenance Manual. 4.7 Replacement Schedule (extracted from Cessna MM Rev 28 Chapter 4-11-00)

ITEM REPLACE Flight Controls (Chapter 27)

Flap Bell Crank (Part Number 2622083-18) At every 2,250 landings Flap Bell Crank (Part Number DDA00028-4) At every 2,250 landings Flap Bell Crank (Part Numbers 2622281-2,-12) At every 7,000 landings Flap Bell Crank (Part Number 2692001-2) At every 7,000 landings

NOTE: Total Landings include the accumulated landings of 2622281-2 prior to modification by SK208-123 to the 2692001-2 configuration

Flap Bell Crank (Part Numbers 2622311-7,-16) At every 40,000 landings Flap Bell Crank Part Number 2622311-7 attaching parts: Bearings ( Part Number MS27641-5 or S3952-5) and Bolt ( Part Number AN5-77) At every 10,000 landings

Flap Bell Crank Part Number 2622311-16 attaching parts: Bearings ( Part Number KP5A-H) and Bolt ( Part Number AN5-77) At every 10,000 landings

Landing Gear (Chapter 32) Main Landing Gear

NOTE: Attaching hardware (bolts, bearings, bushings and trunnion pins related to the installation of the components below) is to be replaced whenever the associated component is replaced.

Main Landing Gear Centre Spring (Part Numbers 2641014-2,-3,-4,-5,-6,-7,-8,-9) At every 31,500 landings Main Landing Gear Trunnion Assembly (Part Numbers 2641012-2,-8,-9,-13,-14) At every 31,500 landings Main Landing Gear Spring (Part Numbers 2641013-1,-2,-3,-4,-5,-6,-7,-8) At every 31,500 landingsMain Landing Gear Attach Pin (Part Numbers 2641008-1,-2,-200) At every 31,500 landingsMain Landing Gear Axles (Part Numbers 2641011-1,-3,-4) At every 10,000 landings Main Landing Gear Axles (Part Numbers 2641011-5) At every 31,500 landings Main Landing Gear Axles Fittings (Part Numbers 2641010-1,-3,-7) At every 31,500 landings

Landing Gear (Chapter 32) Nose Landing Gear

NOTE: Attaching hardware is to be replaced whenever the associated components are replaced.The attaching hardware can be used again if a rental component is to be installed for no more than 100 landings. The attaching hardware can also be used again if the original gear is to be installed again. If a replacement gear is installed, all of the attachment hardware must be replaced Nose Gear Drag Link Spring (Part Numbers 2643062-1,-2,-3) At every 15,000 Landings NOTE: For nose gear drag link springs repaired per CAB96-24 or per the Maintenance Manual Chapter 32, Nose Landing Gear- Cleaning/Painting with damage repaired between 0.050 inch and 0.062 inch (1.270 mm and 1.575 mm), the life limit is an additional 12,000 Landings after repair, not to exceed 15,000 landings NOTE: For nose gear drag link springs repaired per CAB96-24 or per the Maintenance Manual Chapter 32, Nose Landing Gear- Cleaning/Painting with damage repaired between 0.063 inch and 0.075 inch (1.600 mm and 1.905 mm), the life limit is an additional 10,000 Landings after repair, not to exceed 15,000 landings Nose Gear Assembly (Part Numbers 2643045, 2643100 and 2643095 series Part Numbers) At every 40,000 Landings

NOTE: For an illustration of the nose gear assembly to be replaced, refer to the Maintenance Manual Chapter 32, Section 32-20-00, Nose Landing Gear- Maintenance Practices Support Assembly, Nose Gear Spring (Part Numbers 2643030, 2643055 and 2643099 Series Part Numbers) At every 40,000 Landings

NOTE: For an illustration of the nose gear spring support assembly to be replaced, refer to the Maintenance Manual Chapter 32, Section 32-20-00, Nose Landing Gear- Maintenance PracticesFork Assembly, Nose Gear Spring (Part Numbers 2643031-1, -7) At every 40,000 Landings NOTE: For an illustration of the nose gear spring fork assembly to be replaced, refer to the Maintenance Manual Chapter 32,Section 32-20-00, Nose Landing Gear- Maintenance Practices

Oxygen (Chapter 35)Oxygen cylinders (Part Numbers C166001-1101,-1201,-1102,-1103) Every 15 years

SECTION 5

TIME LIMITS/MAINTENANCE

CHECKS



Issued 26Jun15 TIME LIMITS/MAINTENANCE CHECKS

5.0 Scope This section gives the time limits and maintenance checks for the Model 208 and 208B airplanes. It is divided into several sections, each with a special purpose toward providing information necessary to establish inspection criteria. Refer to the Description section of the maintenance manual for detailed information concerning each of these sections. NOTE: Refer to Chapter 4 for those components that have a mandatory inspection and components replacement schedule. Chapter 4 of the maintenance manual is FAA approved and issued separately from the maintenance manual. Some inspection interval and life limit requirements of Chapter 4 possibly will not agree with the current Chapter 5 of the maintenance manual. When there is a conflict between the two chapters, Chapter 4 requirements must always be followed. Inspection Documents that begin with the letter M are those inspections found in Chapter 4. These were separated because there can be no grace period for these inspections. Description NOTE: Given below is a detailed description and the purpose of each section of this chapter Section 5-00-00-Time Limits/Maintenance Checks – General: This section gives a description and purpose of each section of this chapter. 5.1 Inspection Time Limits (Extracted from Section 5-10-01 of the maintenance Manual) This section supplies a list, in chart format, of all of the inspection and service requirements which must be done. Each page has the six columns that follow:

Revision Status gives the date that an item was added, deleted or revised. A blank entry in this column shows no change was made since the issue of this program

The ITEM CODE NUMBER column gives a seven-character, alphanumeric code that is related to each inspection. The item code number does not change. The alphanumeric code contains one letter and six numbers. The letter at the start of the code is A, B, C, or D. Refer to the list that follows for a description of the code:

The letter A shows that a visual inspection is necessary

The letter B shows that a functional check or an operational check is necessary

The letter C shows that a lubrication is necessary

The letter D shows that a clean, service, or replacement is necessary

The Task columns give a short description of the maintenance item and are supplied in chapter order. The Interval is an alphanumeric code character that shows the frequency of the item. The frequencies for each code are given in Chapter 5-10-00 of the Maintenance Manual. The CH SE SU is a reference to the applicable Inspection Document that currently has the inspection item. Applicable Zone refers to the physical location(s) in the airplane where the item is. Most functional and operational tests do not give a zone, but a code which shows the special conditions required to do the test. The codes and conditions are as follows:

ALL-This code and condition is applicable to the entire airplane. ENG-Airplane engine to be running




AUX- External source of electrical power. Airplane engine power sources shall not be used for these tests

NOTE: It is possible to do many of the tests in the AUX category with the airplane's battery power. However, it is not recommended because of the power drain on the battery.

BAT - These tests must be done with the component powered by the airplane’s battery or the batteries built into the individual component, like the ELT or other components with internal battery power.

LAB - Is when special equipment is used which requires that the component be removed from the airplane and taken to a place equipped to do the check or calibration.

FLT - The test is to be done during a flight. The primary purpose of the Inspection Time Limits section is to give a complete list of all inspection items in an order that lets the information given previously be easily found. This section is not to be used as a method to examine the airplane. The Inspection Time Limits Chart shows the recommended intervals at which items are to be examined for normal use in average environmental conditions. Airplanes operated in very humid areas (tropics), or in very cold, damp climates, etc., can need more frequent inspections for wear, corrosion, and lubrication. When the airplane is used in these bad conditions, complete periodic inspections that agree with this chart at more frequent intervals until you can use field experience to set your own inspection periods. The operator’s inspection intervals shall obey the inspection time limits shown in this program except as given below: Each inspection interval can have 10 more hours (if time controlled), or 30 more days (if date controlled) or can be done early any time before the regular interval as given below: If any inspection document is done late, the next inspection document in sequence keeps a due point from the time the late inspection document was initially scheduled. If any inspection document is done early, 10 hours or less ahead of schedule, the next inspection document due point can remain where initially set. 5.1.1 Component Time Limits (Extracted from Section 5-11-00 of the Maintenance Manual) This section gives a list of overhaul or replacement intervals for components in chapter order. These requirements are not given in the 5-10-01 Inspection Time Limits section. The component overhaul or replacement criteria must be used to find the correct action for the components in the list. These requirements must be worked into the continuous inspection program to supply a complete inspection program. 5.1.2 Continuous Inspection Program (Extracted from Section 5-15-00 of the Maintenance Manual) This section gives information about the continuous inspection programs. Each section of 5-15-XX is the Inspection Document that records the items to be examined for that given interval. The last two characters give the subject of the chapter/section/subject identification. 5.1.3 Listing of Supplemental Inspections (Extracted from Section 5-14-00 of the Maintenance Manual) This section has a matrix or cross-reference table for the Supplemental Inspection Documents to the Task Inspection Documents.




5.2 INSPECTIONS GENERAL GENERAL INSPECTION CRITERIA

1) When carrying out each of the specified inspections in this chapter, you must do a general examination of the adjustment areas while access is available. The general visual examinations can help find conditions which will need more maintenance procedures.

2) When you access an area, examine the wire bundles and make repairs as applicable.

Make sure the wire bundles are not attached to hydraulic tubes or lines. 3) Inspection items are given for specified components and systems. The technician must have good professionalism. He must make sure that all components and systems are in good condition and kept to the highest safety standards. 4) If a component or system is moved or changed (because of maintenance done) after a required operational or functional test is done, then a test must be done again before the system or component is returned to service. Refer to the appropriate maintenance manual for removal, installation, operational test, and functional tests of components and/or systems. 5) Refer to Chapter 12, Servicing for information about the lubricant, lubrication points and the method of lubrication for items or components that are lubricated. 6) Refer to Chapter 6, Airplane Zoning – Description and Operation, for airplane zone definition. 7) Refer to the Pilot’s Operating Handbook or Approved Airplane Flight Manual to do a preflight inspection. 8) Inspection Document intervals that begin with the Letter M are those inspections that match chapter 4. There is NO GRACE PERIOD for these inspections. 8) TKS is a fluid based anti-ice system. The system is not installed in any of ALS aircraft at present 5.3 INSPECTION INTERVAL REQUIREMENTS Inspection time intervals for the task-based inspections listed below show the intervals. Expanded inspection and maintenance check procedures are shown in the applicable sections throughout this Program .

Inspection Interval Inspection Document

Interval 0A gives a list of item(s), which are completed during the Annual inspection 5-15-0A Interval 1C item(s), which are completed every 12 calendar months. 5-15-01 Interval 2C item(s), which are completed every 24 calendar months. 5-15-02Interval 4C item(s), which are completed every 48 calendar months. 5-15-03 Interval 6C item(s), which are completed every 72 calendar months. 5-15-04 Interval 12C item(s), which are completed every 144 calendar months. 5-15-05 Interval 200hrs/1C item(s), which are completed every 200 Hours or 12 calendar months, whichever occurs first.

5-15-06

Interval 1A/1C item(s), which are completed every 400 Hours or 12 calendar months, whichever occurs first.

5-15-07


5-15-08


5-15-09

Interval 2A/2C item(s), which are completed every 800 Hours or 24 calendar months, whichever 5-15-10




occurs first. Interval 4A/2C item(s), which are completed every 1600 Hours or 24 calendar months, whichever occurs first.

5-15-11


5-15-12

Interval AD item(s), which are completed at the first 20,000 hours and every 5000 hours thereafter. 5-15-13 Interval AE item(s), which are completed at the first 5000 hours and every 2500 hours thereafter. 5-15-14 Interval AF item(s), which are completed at the first 7500 hours and every 2500 hours thereafter. 5-15-15 Interval AG item(s), which are completed at the first 12,500 hours and every 2500 hours thereafter. 5-15-16 Interval AH item(s), which are completed at the first 16,500 hours and every 5000 hours thereafter. 5-15-17 Interval AI item(s), which are completed at the first 17,500 hours and every 1000 hours thereafter. 5-15-18Interval AJ item(s), which are completed at the first 25,000 landings and every 5000 landings thereafter.

5-15-19

Required by KCAA (Emergency Locator Transmitters) interval item(s), which are completed every 12calendar months (No grace period).

5-15-20

Required by KCAA ( Pitot/static & altitude reporting systems) certification interval item(s), which are completed every 12 calendar months (No grace period).

5-15-21

Required by KCAA ( ATC Transponder Tests) certification interval item(s), which are completed every 12 calendar months (No grace period).

5-15-22

Interval AK item(s), which are completed every 100 flight hours for airplanes incorporating CAB-32-02 that operate in "Severe" corrosion environments. Refer to Chapter 51, Corrosion Severity Maps - Description and Operation.

5-15-23

Interval AL item(s), which are completed every 200 flight hours for airplanes incorporating CAB-32-02 that operate in "Mild" or "Moderate" corrosion environments. Refer to Chapter 51, Corrosion Severity Maps - Description and Operation.

5-15-24

Interval AM item(s), which are completed at the first 20,000 hours and every 6000 hours thereafter. 5-15-25 Interval MA item(s), which are completed at 10,000 hours and every 5000 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-MA

Interval MB item(s), which are completed at 5000 landings and every 1000 landings thereafter, up to 10,000 landings. Replace at 10,000 landings. (Chapter 4 requirement - No grace period)

5-15-MB

Interval MD item(s), which are completed at 15,000 landings and every 3000 landings thereafter. (Chapter 4 requirement - No grace period)

5-15-MD

Interval ME item(s), which are completed at 5000 hours and every 3600 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-ME

Interval MF item(s), which are completed at 20,000 hours and every 5000 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-MF

Interval MG item(s), which are completed at 5000 hours and every 1200 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-MG

Interval MH item(s), which are completed at 10,000 hours and every 2500 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-MH

Interval MI item(s), which are completed at 5000 hours and every 500 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-MI

Interval MJ item(s), which are completed at 5000 hours and every 400 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-MJ

Interval MK item(s), which are completed at 20,000 hours and every 4400 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-MK

Interval ML item(s), which are completed at 20,000 hours and every 3600 hours thereafter. (Chapter 4 requirement - No grace period)

5-15-ML

A. Touch-and-go landings are to be considered identical to full-stop landings and must therefore be included in the count of accumulated landings for all inspections and maintenance. Both full-stop landings and Touch-and-go landings must be tracked. 5.4 TASKS A. The inspection tasks have more data than that given in Inspection Time Limits. The Inspection tasks are identified with ATA (Chapter-Section-Subsection-Function) numbers. Each task has




different ATA number. The Chapter-Section-Subsection digits give the location of the inspection task in the maintenance manual. The last three digits give the function of the inspection task. Refer to the task example. B. An example task number is given in the task example. The numbers that follow the word Task give the chapter, section and subsection location of the inspection task. The first two digits of the function gives the Aircraft Maintenance and Task Oriented Support System (AMTOSS) code. Refer to Table 1 for a description of the function AMTOSS codes. The last digit gives the task sequence number. If the same chapter-section-subsection and function number is used for a different task, the sequence number increments by one or more. C. Table 1. Function AMTOSS Codes 10 CLEANING 64 Lubricating 11 Chemical 65 Fueling, Defueling 12 Abrasive 67 Disinfect, Sanitize 13 Ultrasonic 68 Drain Fluid 14 Mechanical 70 TESTING, CHECKING 15 Stripping 71 Operational 16 Miscellaneous Cleaning 72 Functional 17 Flushing 73 System 20 INSPECTION, CHECKS 74 Bite21 General Visual 75 Special 22 Detailed Dimensional 76 Electrical23 Penetrant 78 Pressure 24 Magnetic 79 Leak25 Eddy Current 80 MISCELLANEOUS 26 X-Ray 81 Fault Isolation 27 Ultrasonic 82 Adjusting, Aligning, Calibration, Rigging 28 Specific, Special 87 Bleeding 29 Bore scope 90 CHANGE, REMOVE, INSTALL 60 SERVICING, PRESERVING, LUBRICATING 96 Replace 61 Servicing




5.5 INSPECTION ITEMS TIME LIMITS ITEM CODE

NUMBER

TASK INTERVAL CH SE SU ZONE

A052001 Aircraft Records Check Task 5-20-00-280 Annual 05-15-0A ALL

A0502002 Annual/100 Hours Inspection Task 5-20-00-750

Annual 05-15-0A ALL

A110001 Interior and Exterior Placard and Decal Detailed Inspection Task 11-00-00-220

200Hours/12 Months 05-15-06

ALL

D121001 Brake System Servicing Task 12-10-01-610 200Hours/12 Months 05-15-06

121

D121003 Shimmy Damper Servicing Task 12-10-01-611 200Hours/12 Months 05-15-06

710

C122101 Landing Gear Lubrication Task 12-21-03-640 200Hours/12 Months 05-15-06

700

C122103 Hartzell Propeller Lubrication Task 12-21-04-640


110

C122105 Nose Landing Gear Brag link Support Servicing(Airplanes incorporating CAB-32-02 Only)Task 12-21-03-641

AK 05-15-24 701

C122106 Key Lock Lubrication Task 12-21-07-640 12 Months 05-15-01 801,802,803,804,921,922 923,924

B212401 Avionics Cooling Fan Operational Check Task 21-24-00-710

800Hours/12 Months

05-15-09 211 212

B215001 Compressor Drive Belt Functional Check Task 21-50-00-720

400Hours/24 Months

05-15-08 121 122

C221201 Autopilot Servos Lubrication Task 22-12-00-640

800Hours/12 Months

05-15-09 226 232

B221201 Garmin Autopilot (GFC 700) Functional Check Task 22-12-00-720

800Hours/24 Months

05-15-10 226 232

B236001 Static Discharge System Functional Check Task 23-60-00-720

800Hours/12 Months

05-15-09 343 375 376 571 671

B243201 Gill Flooded Lead-Acid Battery Functional Check (Capacity Check) Task 24-32-00-720

200Hours/12 Months

05-15-06 122

B243301 Concord Sealed Lead Acid Battery Functional Check (Capacity Check) Task 24-33-00-720


122

B243401 Marathon Ni-Cad Battery Functional Check (Capacity Check) Task 24-34-00-720

200Hours/12 Months

05-15-09 122

A243601 Standby Alternator Detailed Inspection Task 24-36-00-220

400Hours/12 Months

05-15-06 121

A245001 Power Distribution Boxes Detailed Inspection Task 24-50-00-220

800Hours/24 Months

05-15-07 121 122

A251000 Smoke Goggle General Visual Inspection Task 25-10-00-210

12 Months 05-15-10 801 802

A251001 Crew Seats Detailed Inspection Task 25-10-00-220

800Hours/24 Months

05-15-10 231 232

B251001 Inertia Reel Operational Check Task 25-10-00-710

400Hours/12 Months

05-15-07 221 232

A251003 Passenger Seats Detailed Inspection Task 25-21-00-220


231 232




A255101 Cargo Nets Detailed Inspection Task 25-51-00-220


251 252 255 256 257 258

B255201 Cargo Pod Drains Operational Check Task 25-52-00-710


901 902 903 904 905 906

A255201 Cargo Pod Zonal Inspection Task 25-52-00-210

72 Months 05-15-04 901 902 903 904 905 906

B256001 ARTEX C406-2 Emergency Locator Transmitter (ELT) Functional Check Task 25-60-00-720

12 calendar months

05-15-20 220 311 312 340

B256003 ARTEX ME406 Emergency Locator Transmitter (ELT) Functional Check Task 25-60-00-721

12 calendar months

05-15-20 220 311 312 340

B256005 ARTEX C406-N Emergency Locator Transmitter (ELT) Functional Check Task 25-60-00-722

12 calendar months

05-15-20 220 311 312 340

B256007 Dorne and Margolin, Pointer 3000-1, and Pointer 3000-11 Emergency Locator Transmitter (ELT) Functional Check Task 25-60-00-723

12 calendar months

05-15-20 220 311 312 340

A261001 Engine Fire Detection System General Visual Inspection Task 26-10-00-210

400Hours/12 Months

05-15-07 121 122

B262001 Portable Fire Extinguisher Functional Check (Weight Check) Task 26-20-00-720 12 Months

05-15-01 215 216 251 252

B262003 Portable Fire Extinguisher Restoration (Hydrostatic Test) Task 26-20-00-780

144Months 05-15-05 215 216 251 252

B262005 Portable Fire Extinguisher Restoration (Internal Inspection) Task 26-20-00-290 72 Months

05-15-04 215 216 251 252

C270001 Flight Controls Lubrication Task 27-00-00-640 200Hours/12 Months

05-15-06 215 216 226 373 374 503 525 603 625

C271001 Aileron Trim System Lubrication Task 27-10-02-640

400Hours/12Months

05-15-07 211 212 217 218 233 234 253 254 251 252 551 571 651 671

B271001 Spoiler System Functional Check Task 27-10-00-720

800Hours/24Months

05-15-10 211 212 217 218 233 234 253 254 251 252 503 525 603 625

B271003 Aileron System Functional Check Task 27-10-00-721

1600Hours/24Months

05-15-11 211 212 217 218 233 234 253 254 251 252 503 525 603 625

C271003 Aileron Trim Tab Actuator (2660044-1) Lubrication Task 27-10-02-641

800Hours/24Months

05-15-10 551 571 651 671

B271005 Aileron Trim Tab (Free Play) Functional Check Task 27-10-02-720

400Hours/ 12Months

05-15-07 551 571 651 671

C271005 Aileron Trim Tab Actuator (2661615-1, 2661615- 9, or 2661615-10) Lubrication Task 27-10-02-642

1600 Hours /60Months

05-15-12 551 571 651 671

B272001 Rudder System Functional Check (Standard Rudder Installation) Task 27-20-00-720

1600 Hours/24Months

05-15-11 211 212 213 214 217 218 233 234 253 254 257 258 311 312 320 341

C272001 Rudder Bar Bearings and Rudder Pedals Lubrication Task 27-20-00-640

1600 Hours/24Months

05-15-11 211 212 213 214

B272003 Rudder System Functional Check (Float Kit 12 Months 05-15-01 211 212 213 214 217 218 233




Installation) Task 27-20-00-721 234 253 254 257 258 311 312 320 341

B273001 Elevator System Functional Check Task 27-30-00-720

1600 Hours/24Months

05-15-11 211 212 213 214 217 218 233 234 253 254 257 258 311 312 320 373 374 375 376

C273001 Elevator Trim Tab Actuator (2660017-1) Lubrication Task 27-30-02-640

800Hours/ 24Months

05-15-10 371 372 375 376

C273003 Elevator Trim Tab Actuator (2661215-1 and 2661215-9) Lubrication Task 27-30-02-641

1600Hours/60Months

05-15-12 371 372 375 376

B273003 Elevator Trim Tab (Free Play) Functional Check Task 27-30-02-720

400Hours / 12 Months

05-15-07 371 372 375 376

B273101 Stall Warning System Operational Check Task 27-31-00-710

200Hours/12 Months

05-15-0A 211 212 503

C275001 Flap Tracks and Rollers Lubrication Task 27-50-00-640

200Hours/12 Months

05-15-0A 525 527 625 627

B275001

Flap System Functional Check Task 27-50-00-720

1600 Hours/24Months

05-15-11

'251 252 511 611 525 625

A275001 Flap Actuator Mount Bracket Detailed Inspection Task 27-50-00-220


05-15-09 231 232

A275003 Flap Bellcrank Detailed Inspection Task 27-50-00-221


05-15-09 251 252 511 611 525 625

B277001

Rudder Gust Lock Detailed Inspection (Airplanes 20800237 and On, Airplanes 208B0382andOnandAirplanesequipped withAeroTwinSTCSA3649NM)Task27- 70-01-221

1600 Hours/24Months 05-15-11

330

A281001 Fuel Filler Assembly Detailed Inspection Task 28-10-01-220

200Hours / 12Months

05-15-06 521 621

B281001 Fuel Vent Line Float Valve Operational Check Task 28-10-03-710

200Hours / 12Months

05-15-06 575 675

A281003 Fuel Storage System Detailed Inspection Task 28-10-01-221 48 Months 05-15-03

521 621

B282103 Firewall Fuel Shutoff Valve Control Operational Check Task 28-21-00-711 400Hours / 12

Months05-15-07

213 214 220

C282301 Wing Shutoff Valve Linkage Lubrication Task 28-23-00-640

400Hours / 12Months

05-15-07 231 232 511 611

B284101 Fuel Reservoir Warning System Operational Check Task 28-41-00-710

400Hours / 12Months

05-15-07 ENG

B284103 Fuel Quantity and Low Fuel Warning Systems Functional Check Task 28-41-00-720

800Hours / 24Months 05-15-10

AUX

B301001 Bleed Air Pressure Regulator Functional Check (without TKS and not incorporating CAB93-2) Task 30-10-00-720

400Hours / 12Months

05-15-07 122 AUX

B301003 Bleed Air Pressure Regulator Functional Check (without TKS and incorporating CAB93-2)Task 30-10-00-720

200Hours / 12Months

05-15-06 122 AUX

B304001 Windshield Anti-Ice System Operational Check Task 30-40-00-710

400Hours / 12Months

05-15-07 AUX




A321001 Main Landing Gear Detailed Inspection Task 32-10-00-220

12 Months 05-15-01 721 722

A321003 Center-Spring and Main Gear-Spring Interface Area Special Detailed (Corrosion Inspection and Repair) Task 32-10-00-221

48 Months 05-15-03 721 722

A321005 Main Landing Gear Axle (Part Numbers 2641011-1,-3,-4)Special Detailed Inspection (SID 32-10-01) Task 32-10-00-240

MB 05-15-MB 721 722

B322001 Shimmy Damper Functional Check Task 32-20-02-720

200Hours/12 Months

05-15-06 710

A322001 Nose Landing Gear Detailed Inspection Task 32-20-00-220

400Hours/ 24 Months 05-15-08

710

A322002

Drag Link Forward Support Seal General Visual Inspection. (Airplanes 20800553 andOnand208B5076andOn)Task32- 20-00-210

12 Months05-15-01

701

A322003

Drag Link Forward Support General Visual Inspection.(Airplanes20800553andOn and208B5076andOn)Task32-20-00-211

48 Months 05-15-03 701

A324001 Brakes Detailed Inspection Task 32-40-00-220 12 Months 05-15-01 721 722

B324001 Brakes Operational Check Task 32-40-00-710 800Hours/ 24Months

05-15-10 ENG

A324005 Main Landing Gear Wheels and Tires Detailed Inspection Task 32-40-00-222

12 Months 05-15-01 721 722

A324009 Nose Landing Gear Wheel and Tire Detailed Inspection Task 32-40-00-224

12 Months 05-15-01 710

B332001 Passenger/Cargo Compartment Lighting Operational Check Task 33-20-00-710

800Hours/24 Months

05-15-10 AUX

B341101 Pitot Tube Heaters Operational Check Task 34-11-00-710

200 Hours/ 12 months

05-15-06 AUX

B341103 Pitot/Static System Functional Check Task 34-11-00-720

12 months 05-15-21 AUX

B342101 Magnetic Compass Functional Check Task 34-21-00-720

12 months 05-15-01 ENG

B345001 Transponder Functional Check Task 34-50-00-720

12 months 05-15-22 AUX

B350101 Oxygen System Operational Check Task 35-01-00-710

12 months 05-15-01 231 232 251 252 255 256 311 312 801 802

A353001 Portable Oxygen Mask Detailed Inspection Task 35-30-00-220

200Hours/12 Months

05-15-06

256

A353003 Portable Oxygen Cylinder Detailed Inspec- tion Task 35-30-00-221

400Hours/12 Months

05-15-07

256

A520001 Crew Doors Detailed Inspection Task 52-00-00-220

800Hours/24 Months

05-15-10 801 802

A520003 Passenger/Cargo Doors and Door Frames Detailed Inspection Task 52-00-00-221

800Hours/24Months

05-15-10 255 256 257 258 803 804

A531001 External Fuselage Zonal Inspection Task 53-10-00-210 72 Months

05-15-04 ALL

A531003 Internal Cockpit Zonal Inspection Task 53-10-00-211 48 Months

05-15-03 211 212 213 214 215 216 217 218 231 232 233 234

A531004 Internal Cabin Zonal Inspection Task 53-10- 05-15-04 251 252 253 254 255 256 257




00-212 72 Months 258 311 312

A531005 Fuselage to Strut Attach Fitting Lugs (Nominal Standard Bolt Size) (Typical Inspection Compliance) Special Detailed Inspection (SID 53-20-07) Task 53-20-07-250

MH 05-15-MH 251 252 253 254

A531007 Internal Tail Cone Zonal Inspection Task 53-10-00-213

48 Months 05-15-03 311 312 320 330

A531008 Fuselage Engine Mount Fittings Special Detailed Inspection (SID 53-10-01) Task 53-10-00-250

AD 05-15-13 121 122 130

A531009 Seat Rails and Attachment Structure Detailed Inspection (SID 53-10-07) Task 53-25-00-220

AF 05-15-15 231 232 233 234 251 252 253 254 255 256 257 258

A531013 Empennage and Horizontal Stabilizer Zonal Inspection Task 53-10-00-214

72 Months 05-15-04 340 341 373 374

A532003 Cargo and Passenger Door Doublers Special Detailed Inspection (SID 53-20-01) Task 53-10-00-251

AF 05-15-15 255 256 257 258 803 804

A532004 Lower Forward Carry-Thru Bulkhead Special Detailed Inspection (SID 53-20-03) Task 53-10-00-253

AG 05-15-16 253 254

A532005 Main Landing Gear Fitting Special Detailed Inspection (SID 53-20-04) Task 53-10-00-254

AJ 05-15-19 253 254

A532006 Main Landing Gear Attach Fittings and Aft Carry-Thru Bulkhead (SID 53-20-05) Task 53-10-00-255

AG 05-15-16 253 254

A532007 Fuselage to Wing Attach Fitting Lugs Special Detailed Inspection (SID 53-20-02) Task 53-10-00-252

MF 05-15-MF 251 252 501 511 525 601 611 625

A532008 Firewall Brace and Doubler Assemblies Detailed Inspection (SID 53-20-11) Task 53-10-00-223

AD 05-15-13 121 122 130

A532009 Carry-Through Root Rib Detailed Inspection (SID 53-20-08) Task 53-10-00-220

AD 05-15-13 251 252 500 600

A532011 Crew Door Frames Detailed Inspection (SID 53-20-09) Task 53-10-00-221

AD 05-15-13 231 232 233 234 801 802

A532012 Passenger and Cargo Door Frames Detailed Inspection (SID 53-20-10) Task 53-10-00-222

AD 05-15-13 255 256 257 258 803 804

A532013 Bulkheads and Stiffeners Below the Seat Rail Attachments at FS 143.00 and FS 158.00 Detailed Inspection (SID 53-20-12) Task 53-25-00-221

AF 05-15-15 233 234

A532014 Stringers at Intersections with Forward and Aft Carry - Thru Bulkheads Detailed Inspection (SID 53-20-13) Task 53-10-00-224

AG 05-15-16 251 252

A532015 Fuselage Skin Doubler at Main Landing Gear Cutout Detailed Inspection (SID 53-20-14) Task 53-10-00-225

AE 05-15-14 253 254

A532016 Fuselage to Wing Carry-Thru Attach Fitting and Bulkhead Special Detailed Inspection (SID

AG 05-15-16 251 252




53-20-06) Task 53-10-00-256

A535001 Fuselage to Horizontal Stabilizer Attach Fittings Special Detailed Inspection (SID 53-50-01) Task 53-10-00-257

AD 05-15-13 320 373 374

A535002 Vertical Stabilizer Attach Points Special Detailed Inspection (Typical Inspection Compliance) (SID 53-50-02) Task 53-10-00-258

AD 05-15-13 311 312 320 341

A551003 Horizontal Stabilizer Forward and Aft Attach Points Special Detailed Inspection (SID 55-10-01) Task 55-10-00-250

AD 05-15-13 373 374

A553001 Vertical Stabilizer Spars Special Detailed Inspection (Typical Inspection Compliance) (SID 55-30-01) Task 55-30-00-250

AD 05-15-13 320 341

A553004 Horizontal Stabilizer Spars Special Detailed Inspection (Typical Inspection Compliance) (SID 55-10-02) Task 55-10-00-251

AD 05-15-13 373 374

A564002 Windshield and Attachment Structure Detailed Inspection (SID 56-30-01) Task 56-00-01-220

AD 05-15-13 240

A570008 Wing Strut Fittings Special Detailed Inspection (Typical Inspection Compliance) (SID 57-60-01) Task 57-10-01-250

MA 05-15-MA 531 631

A570010 Front Spar Lower Cap Inboard of WS 141.20 Special Detailed Inspection (SID 57-20-02) Task 57-10-00-252

MF 05-15-MF 501 521 601 621

A570011 Rear Spar Lower Cap Inboard of WS 141.20 Special Detailed Inspection (SID 57-20-03) Task 57-10-00-253

MF 05-15-MF 521 525 621 625

A570012 Wing Strut Attachment to Front Spar Special Detailed Inspection (Nominal/Standard Bolt Size) (Typical Inspection Compliance) (SID 57-60-02) Task 57-10-01-252

MF 05-15-MF

531 631

A570013 Wing to Carry - Thru Front Spar Attachment Fittings Special Detailed Inspection (SID 57-20-01) Task 57-10-00-250

MF 05-15-MF 251 252

A570014 Wing to Carry - Thru Rear Spar Attachment Fittings Special Detailed Inspection (SID 57-20-01) Task 57-10-00-251

MF 05-15-MF 251 252

A571001 Wing Zonal Inspection Task 57-10-00-210 48 Months 05-15-03 500 600

A575002 Center Flap Track and Inboard Flap Track Special Detailed Inspection (SID 57-50-01) Task 57-10-00-254

MD 05-15-MD 525 527 625 627

A575003 Outboard Flap Track Special Detailed Inspection (SID 57-50-01) Task 57-10-00-255

MD 05-15-MD 525 527 625 627

B611001 Hartzell Propeller Functional Check Task 61-10-00-720

400Hours/12 Months

05-15-07 110

B611101 McCauley Propeller Functional Check Task 61-11-00-720

400Hours/ 12 Months

05-15-07 110

A710001 Engine Compartment Zonal Inspection Task 24 Months 05-15-02 130




71-00-01-210

A712001 Engine Mounts and Firewall Detailed Inspection Task 71-20-00-220

1A/1C 05-15-07 130

A712003 Engine Truss and Ring Assembly Special Detailed Inspection (SID 71-20-01) Task 71-20-00-240

AM 05-15-25 130

A714101 Engine Wash Ring, Air Plenum, and Thermocouple (T1) Detailed Inspection Task 71-41-00-220

12 Months 05-15-01 130

A716001 Inertial Air Separator Detailed Inspection Task 71-60-00-220


05-15-07 130

B761001 Engine Controls Functional Check Task 76-10-00-720


05-15-07 130 211 212 ENG

B761003 Emergency Power Lever Annunciator Light (EPL) Operational Check Task 76-10-01-710

200Hours/ 12 Months 05-15-06

AUX

A781001 Primary and Secondary Exhaust Duct General Visual Inspection Task 78-10-00-211


05-15-10 130

A801001 Starter-Generator (Part Number 23081 Series only) Detailed Inspection Task 80-10-00-220


05-15-07 130

5.6 COMPONENT TIME LIMITS

All components not recorded here must be examined as given in other sections of this chapter and repaired, overhauled or replaced as required. Items shown here must be overhauled or replaced during the regular maintenance periods that are to be done nearest to the specified limit. The replacement life for each component recorded in this section applies to the part throughout its life on the original installation and on later installations. The life (number of hours or number of landings) must be recorded individually for these components and must stay with the component during removal. For example, if a component is removed for overhaul, it must be tagged with the life (number of hours or number of landings) to the date of removal and this tag must remain with the component throughout the overhaul process. (Overhaul of a component does not zero time the life of the component.) When received from overhaul and installed on an airplane, the life of the component must be recorded for continued accumulation toward the life-limit. Component Time Limits (extracted from Cessna MM rev. 28 chapter 5-11-00)




Component / Item Replace Time

Equipment and Furnishings (Chapter 25) Emergency Locator Transmitter(ELT) Battery Pack

Replace at replacement date. (refer to task 25-60-00-960) NOTE: Replace battery if transmitter has been in use for more than one cumulative hour or when 50 percent of the useful life of the battery has expired.

Flight Controls (Chapter 27) Flap Bell Crank Part Number 2622083-18 Replace 2250 landings. Flap Bell Crank Part Number DDA00028-4 Replace 2250 landings Flap Bell Crank Part Number 2622281-2 Replace 7000 landings Flap Bell Crank Part Number 262281-12 Replace 7000 landingsFlap Bell Crank Part Number 2692001-2 Replace 7000 landingsNOTE: Total landings includes the accumulated landings of 2622281-2 prior to modification by SK208-123 to the 2692001-2 configuration Flap Bell Crank Part Number 2622311-7 Replace 40,000 landings Flap Bell Crank Part Number 2622311-16 Replace 40,000 landings Flap Bell Crank (Part Number 2622311-7) attaching parts: Bearings (Part Number MS27641-5 or S3952-5) and Bolt (Part Number AN5-77)

Replace 10,000 landings.

Flap Bell Crank (Part Number 2622311-16) attaching parts: Bearings (Part Number KP5A-H) and Bolt (Part Number AN5-77)

Replace 10,000 landings

Elevator Forward Pushrod Part Number 2613440-1 Replace 9500 landings Elevator Forward Pushrod Part Numbers 2613414-1 Replace 9500 landings Elevator Forward Pushrod Part Numbers 2660034-1 Replace 9500 landings Elevator Forward Pushrod Part Number 2613440-3 Replace 40,000 landings Elevator Forward Pushrod Part Number 2613440-5 Replace 40,000 landings Elevator Forward Pushrod Part Number DDA05946-1 Replace 40,000 landings Elevator Aft Pushrod Part Number 2634009-1 Replace 40,000 landings

Components Time Limits-Continuation

Elevator Aft Pushrod Part Number 2634027-1 Replace 40,000 landings Elevator Aft Pushrod Part Number 2634027-3 Replace 40,000 landings Ice and Rain Protection (Chapter 30) TKS Metering Pumps Part Number 9514A1-1 Replace 5000 flight hours Landing Gear (Chapter 32) Main Landing Gear NOTE: Attaching hardware (bolts, bearings, bushings, and trunnion pins related to the installation of the components below) is to be replaced whenever the associated component is replaced. Main Landing Gear Center Spring (Part Numbers 2641014-2, -3, -4, -5, -6 -7, -8, -9)


Main Landing Gear Trunnion Assembly (Part Numbers 2641012-1, -2, -8, -9, -13 -14)


Main Landing Gear Spring (Part Numbers 2641013-1, -2, -3, -4, -5, -6, 7, -8)


Main Landing Gear Attach Pin (Part Numbers 2641008-1, -2, -200) Replace 31,500 landings Component / Item Replace Time

Main Landing Gear Axles (Part Numbers 2641011-1, -3, -4) Replace 10,000 landings. Main Landing Gear Axles (Part Number 2641011-5) Replace 31,500 landings. Main Landing Gear Axle Fittings (Part Numbers 2641010-1, -3, -7) Replace 31,500 landings Nose Landing Gear NOTE: Attaching hardware (bolts, bearings, bushings, and trunnion pins related to the installation of the components below) is to be replaced whenever the associated component is replaced. Nose Gear Drag Link Spring (Part Numbers 2643062-1, -2, -3) Replace 15,000 landings NOTE: For nose gear drag link springs repaired per CAB96-24 or per the Maintenance Manual Chapter 32, Nose Landing Gear- Cleaning/Painting with damage repaired between 0.050 inch and 0.062 inch (1.270 mm and 1.575 mm), the life limit is an additional 12,000 Landings after repair, not to exceed 15,000 landings




NOTE: For nose gear drag link springs repaired per CAB96-24 or per the Maintenance Manual Chapter 32, Nose Landing Gear- Cleaning/Painting with damage repaired between 0.063 inch and 0.075 inch (1.600 mm and 1.905 mm), the life limit is an additional 10,000 Landings after repair, not to exceed 15,000 landingsNose Gear Assembly (Part Numbers 2643045, 2643100 and 2643095 series Part Numbers) Replace 40,000 landings.

NOTE: For an illustration of the nose gear assembly to be replaced, refer to the Maintenance Manual Chapter 32, Section 32-20-00, Nose Landing Gear- Maintenance Practices Support Assembly, Nose Gear Spring(Part Numbers 2643030, 2643055 and 2643099 Series Part Numbers) Replace 40,000 landings

NOTE: For an illustration of the nose gear spring support assembly to be replaced, refer to the Maintenance Manual Chapter 32, Section 32-20-00, Nose Landing Gear- Maintenance Practices Fork Assembly,Nose Gear Spring (Part Numbers 2643031-1, -7) Replace 40,000 landings NOTE: For an illustration of the nose gear spring fork assembly to be replaced, refer to the Maintenance Manual Chapter 32,Section 32-20-00, Nose Landing Gear- Maintenance Practices Navigation (Chapter 34) Pitot and static hoses Replace 10 years Oxygen (Chapter 35) Oxygen cylinders (Part Numbers C166001-1101,-1201,-1102,-1103) Replace 15 years Scott 359 Series Oxygen Mask All Components Including Regulator Overhaul/Re

placement 5 years

Oxygen cylinder hydrostatic test intervals are determined by DOT-E 8162 or DOT-SP 8162.Refer to Table 1 below for Hydrostatic Test Intervals Table 1: Hydrostatic Test Intervals DOT Cylinder Marking

Last Retest Next Retest Subsequent Retest Intervals

E 8162 Before July 1,2006 3 years after last hydrostatic test 5 years E 8162 On or After July 1,2006 5 years after last hydrostatic test 5 years

SP 8162 On or After July 1,2006 5 years after last hydrostatic test 5 years 3AA N/A N/A 5 years

Vacuum (Chapter 37) Vacuum hoses Replace 10 yearsPropeller - Hartzell (Chapter 61) Overhaul 5 Yrs or 3000 hrs Governor (Woodward) Ref PW &C SB 1703 Overhaul Engine TBO + 500 Over-speed Governor (Woodward) Ref SB 33580 Overhaul Engine TBO + 500 Propeller McCauley (Chapter 61) Overhaul 4000 hrs/6 years Governor (Woodward) Ref PW &C SB 1703 Overhaul Engine TBO + 500 Over-speed Governor (Woodward) Ref SB 33580 Overhaul Engine TBO + 500 Power plant (Chapter 71) Fuel Hose: From firewall fuel filter to engine fuel heater Rubber base number S2495 (Purchased through Cessna)

Replace 5 yrs or 3600 hrs

Fuel Hose: From firewall fuel filter to engine fuel heater Teflon base number S2808 (Purchased through Cessna)

Replace 10 yrs or Engine TBO

Fuel Hose: From fuel control unit motive flow return to firewall fitting Rubber base number S2495 (Purchased through Cessna)

Replace 5 yrs or 3600 hrs

Fuel Hose: From fuel control unit motive flow return to firewall fitting Teflon base number S2808 (Purchased through Cessna)


Fuel Hose: From firewall fuel filter to engine fuel control unit inlet Teflon


Fuel Hose: From fuel control unit motive flow return to firewall fitting rubber Teflon


Oil Hose: Oil cooler supply from engine external scavenge pump to oil cooler inlet


Oil Hose: Oil cooler return outlet to engine oil tank Replace 10 yrs or Engine TBO




Oil Hose: Torque indicating pressure hose Replace 10 yrs or Engine TBO Oil Hose: Torque indicating vent hose Replace 10 yrs or Engine TBO Oil Hose: Engine oil pressure indicating hose from engine to firewall Replace 10 yrs or Engine TBO Engine (Chapter 72) Engine Gas Generator/Power Section O/H SB 1703 Latest Revision Starter-Generator (Chapter 80) Lear Siegler/Lucas Aerospace except Part Number 23081-023A Overhaul 1000 hoursLear Siegler/Lucas Aerospace part number 23081-023A Overhaul/

Replace 1200 hours

Starter-Generator (Aircraft Parts Corp. - APC "XL" ) Overhaul with genuine APC parts 200SGL119Q Overhaul 1600 hours Original equipment starter-generators APC 200SGL119Q-2 Overhaul 2000 hours Starter-Generator 200SGL153Q Overhaul 2000 hours Starter-Generator(Aircraft Parts Corp- APC part number 300SGL145Q)

Overhaul/ Replace 1000 hours

5.7 TYPICAL OPERATIONS CONDITIONS

At the of producing this initial issue of this Aircraft Maintenance Program, Astral Aviation had calculated the number of cycles and hours flown in the average flying day, and taking into account the flying environment, had by using the criteria laid out in 4-00-00 2B(1,2,3,4,5,6),determined that the aircraft that this program applies to, are maintained in accordance with TYPICAL OPERATIONS CONDITIONS. 5.8 THE OPERATOR’S INSPECTION INTERVALS

The operator’s inspection intervals shall obey the inspection time limits shown in this manual except as given below:

(a) Each inspection interval can have 10 more hours (if time controlled), or 30 more days (if date controlled) or can be done early any time before the regular interval as given below:

1. If any inspection document is done late, the next inspection document in sequence keeps a due point from the time the late inspection document was initially scheduled. 2 .If any inspection document is done early, 10 hours or less ahead of schedule, the inspection

document due point can remain where initially set. 3 .If any inspection document is done early, more than 10 hours ahead of schedule, the next inspection document due point must be rescheduled to set a new due point from the time

it was done early. 5.9 INSPECTION TIME LIMITATIONS 1. A calendar month starts on the first day of the month. You must complete the inspections on or

before the last day of the month for their related calendar month interval. 2.Any inspection time limits found in Chapter 5 and also required in Chapter 4 shall noted be

extended. 3. Any inspection required by KCAA in Chapter 4 shall noted be extended, without the approval

of the Authority in writing. 4. Inspection items that use flight hours with calendar limits can be extended up to a maximum of

30 flight hours or two calendar months beyond the time when the inspection is due. 5. Inspection items that use flight hour limits can be extended up to a maximum of 30 flight hours

beyond the due time. 6.The part of the allowable extension that is used does not need to be deducted from the

subsequent due point. 7.Any inspection program based upon the intervals of the items in this chapter, or more frequent

intervals, is acceptable and will be first be approved by the KCAA in the form of a revision of this Maintenance Program.

The primary purpose of the Inspection Time Limits Section is to give a complete list of all inspection items in an order that lets the information given

previously be easily found. This section is not to be used as a method to examine the airplane. The Inspection Time Limits Chart shows the recommended intervals at which items are to be

examined for normal use in average environmental conditions. Airplanes operated in very humid areas (tropics), or in very cold, damp climates, etc., can need more frequent inspections for wear,




corrosion, and lubrication. When the airplane is used in these bad conditions, complete periodic inspections that agree with this chart at more frequent intervals until the operator can use field experience to set his own inspection periods.

A. Any inspection time limit found in Chapter 5 and also required in Chapter 4 shall not be extended. Any inspection required by KCARS shall not be extended.

B. Inspection item time limits can be extended for maintenance scheduling purposes only as provided below

(1) Inspection items that use flight hours with calendar limits can be extended up to a maximum of 30 flight hours or two calendar months beyond the time when the inspection is due..

(2) Inspection items that use flight hour limits can be extended up to a maximum of 30 flight hours beyond the due time.

(3) Inspection items that use calendar limits can be extended up to two calendar months beyond the due date.

(4) The part of the allowable extension that is used does not need to be deducted from the subsequent due point.

C. Any inspection program based upon the intervals of the items in this chapter, or more frequent intervals, is acceptable.

5.10 DEFINITIONS AND PROCEDURES 1. On Condition is defined as follows: The necessary inspections and/or checks to make sure that

a failure of the component will not occur before the next scheduled inspection. 2. Condition is defined as follows: Inspect for, but not limited to, cleanliness, cracks,

deformation, corrosion, wear, and loose or missing fasteners. 3. MOVABLE PARTS: Inspect for lubrication, servicing, make sure the part is tight, binding,

more than normal wear, safetying, correct operation, correct adjustment, correct travel, cracked fittings, condition of the hinges, defective bearings, cleanliness, corrosion, deformation, sealing, and tension.

4. FLUID LINES AND HOSES: Inspect for leaks, cracks, bulging, collapsed, twisted lines/hoses, dents, kinks, chafing, proper radius, security, discoloration, bleaching, deterioration, and proper routing; rubber hoses for hardness or flexibility and metal lines for corrosion.

5. METAL PARTS: Make sure the installation is correct and tight, and that there are no cracks and/or metal distortion.

6. WIRING: Inspect for correct and tight installation, chafing, burning, arcing, defective insulation, loose or broken terminals, heat deterioration, and corroded terminals.

7. STRUCTURAL BOLTS: Inspect for correct torque. Obey the applicable torque values. Refer to Bolt Torque Data during installation or when visual inspection shows the need for a torque check.

NOTE: The torque values that are listed are not to be used for the measurement of tightness of installed parts while they are in service.

8. FILTERS, SCREENS, AND FLUIDS: Make sure the filters and screens are replaced at the required interval. Make sure you use clean fluids and that the filters or screens are kept clean. 9. Make sure the system checks (operation or function) that need electrical power are done with 28.5 Volts, +0.25 or -0.25 Volts, bus voltage. This will make sure all components operate at their operational voltage. During Issue of Certificate of release to service after scheduled maintenance, the checks as listed in the table below will be indicated:

SECTION 6

CONTINUOUS INSPECTION PROGRAM



Issued 26Jun15 CONTINOUS INSPECTION PROGRAM

6.1 Purpose and Use. 6.1.1 As the person who has control of the airworthiness of the airplane, the ALS Ltd shall use only approved personnel to do maintenance on the airplane. 6.1.2 The Cessna continuous inspection program will help the operator to do the intent of Regulation 56 of “The Civil Aviation (Air Operator Certification and Administration) Regulations 2013. 6.2 Construction To meet the requirements of regulation 21 of “The Civil Aviation ( Operation of Aircraft) Regulations 2013, Cessna has provided a Continuous Inspection Program which includes all of the inspections for the Model 208, 208 Cargo master, 208B, 208B Super Cargomster and 208B Passenger airplanes and is recommended by Cessna Aircraft Company. A continuous maintenance inspection program Schedule for ALS Ltd has been selected and forms this Package. The inspections are done at subsequent intervals that are related to hours, calendar months, and years or in accordance with (IAW) the Manufacturer’s Instructions. Intervals for some inspections are given by the manufacturer of the component that is examined. The applicable Manufacturer’s Manual gives the data necessary to find those intervals. Refer the MM Introduction-List of Publications. Inspections will be carried out in accordance with the Task-Based Inspection Program, which is divided into Main operations referred to as Inspection 1 through 12 Inspections, which include all 12Month, 24Month, 48Month, 72Month, 144Months, 200Hrs/12Month,400Hr/12Month, 400Hr/24Month, 800Hr/12Month, 800Hr/24Month, 1600Hr/24Month, 1600Hr/60Month inspection requirements. There are out of phase inspection items due at other intervals that begin from Inspection 13 to Inspection 22, Inspection MA thru Inspection ML. The Inspection Program is divided into inspections documents for each of the required inspection interval. (Refer to 6.7). 6.3 Inspection Time Limitations 6.3.1 Any inspection time limit found in Chapter 5 and also required in Chapter 4 shall not be extended. Inspection item time limits can be extended for maintenance scheduling purposes only as provided below. NOTE: The annual inspection is due on the last day of the calendar month in which it was previously completed twelve months before and cannot be extended. The 200-hour inspection can only be extended up to 10 hours while en route to reach a place where the inspection can be done.

Inspection items that use flight hours with calendar limits can be extended up to a maximum of 10 flight hours or 30 Days beyond the time when the inspection is due.

Inspection items that use flight hours limits can be extended up to a maximum of 10 flight hours beyond the due time

If any inspection document is done late, the next inspection document in sequence keeps a due point from the time the late inspection document was initially scheduled.

If any inspection document is done early, 10 hours or less ahead of schedule, the next inspection document due point can remain where initially set.

Any inspection program based upon the intervals of the items in the Cessna MM chapter 5, or more frequent intervals, is acceptable.




6.4 Maintenance Manual –Compact Disc-Read Only Memory (Cd-Rom) The maintenance manual on Compact Disc - Read Only Memory (CD-ROM) contains a search feature. With this, any item code can be found, quickly and entirely. Along with the item code, task information about the inspection and zone is given. A task number is supplied with the items which give special inspection instructions. When a task number is clicked on, the link will show the task information from the appropriate section of the manual. A print task function selection is available when that button is set with the cursor. The task text and any linked documents, such as illustrations, are printed together as one document. The end of each task is clearly shown with the message "End of Task". 6.5 Inspection Guidelines The Inspection Documents are to be used as a recommended inspection outline. 6.5.1 Detailed information of systems and components in the airplane will be found in various chapters of the Maintenance Manual and the applicable vendor publications. 6.5.2 It is recommended that you refer to the applicable portion of the Maintenance manual for service instructions and installation instructions and to the vendor’s data or publications specifications for torque values, clearances, settings, tolerances, and other requirements. 6.6 Definitions and procedures 6.6.1. On Condition is defined as follows: The necessary inspections and/or checks to make sure that a failure of the component will not occur before the next scheduled inspection. 6.6.2 Condition is defined as follows: Inspect for, but not limited to, cleanliness, cracks, deformation, corrosion, wear, and loose or missing fasteners. 6.6.3 Movable parts: Inspect for lubrication, servicing, make sure the part is tight, binding, more than normal wear, safetying, correct operation, correct adjustment, correct travel, cracked fittings, condition of the hinges, defective bearings, cleanliness, corrosion, deformation, sealing, and tension. 6.6.4 FLUID LINES AND HOSES: Inspect for leaks, cracks, bulging, collapsed, twisted lines/hoses, dents, kinks, chafing, proper radius, security, discoloration, bleaching, deterioration, and proper routing; rubber hoses for hardness or flexibility and metal lines for corrosion. 6.6.5 METAL PARTS: Make sure the installation is correct and tight, and that there are no cracks and/or metal distortion. 6.6.6 WIRING: Inspect for correct and tight installation, chafing, burning, arcing, defective insulation, loose or broken terminals, heat deterioration, and corroded terminals. 6.6.7. STRUCTURAL BOLTS: Inspect for correct torque. Obey the applicable torque values. Refer to Bolt Torque Data during installation or when visual inspection shows the need for a torque check. NOTE: The torque values that are listed are not to be used for the measurement of tightness of installed parts while they are in service. 6.6.8. FILTERS, SCREENS, AND FLUIDS: Make sure the filters and screens are replaced at the required interval. Make sure you use clean fluids and that the filters or screens are kept clean. Make sure the system checks (operation or function) that need electrical power are done with 28.5 Volts, +0.25 or -0.25 Volts, bus voltage. This will make sure all components operate at their operational voltage.




6.7 INSPECTION DOCUMENTS (Extracted from Cessna Maintenance Manual Rev 26 Introduction-Revision Summary)

05-15-0A INSPECTION DOCUMENT 0A

05-15-01 INSPECTION DOCUMENT 01






















05-15-MA INSPECTION DOCUMENT MA

05-15-MB INSPECTION DOCUMENT MB

05-15-MD INSPECTION DOCUMENT MD

05-15-ME INSPECTION DOCUMENT ME

05-15-MF INSPECTION DOCUMENT MF

05-15-MG INSPECTION DOCUMENT MG

05-15-MH INSPECTION DOCUMENT MH

05-15-MI INSPECTION DOCUMENT MI

05-15-MJ INSPECTION DOCUMENT MJ

05-15-MK INSPECTION DOCUMENT MK

05-15-ML INSPECTION DOCUMENT ML




6.9 PROCEDURE FOR ESCALATION OF CHECK PERIODS 6.9.1 Should ALS AMO wish to escalate any check period, the Quality Manager will apply to the KCAA for such escalation providing the reason for the application, all relevant supporting documentation and reliability history. 6.9.2 Should ALS AMO wish to make use of the 30 day tolerance described in 6.3, say for example due to spare parts not being available, the Quality Manager will notify the Director of Civil Aviation of such intention, stating the reason, and an expected time of arrival of the required parts. Refer to MCM part 3 section 3.4. Reference should be made to the MEL in such cases, which may assist with supporting the notification. Refer (MCM part 3 sec 3.3)

SECTION 7

PRATT AND WHITNEY ENGINE INSPECTION

PROGRAM



Issued 26Jun15 PRATT & WHITNEY ENGINE INSPECTION PROGRAM

CHAPTER 7 PRATT & WHITNEY ENGINE INSPECTION PROGRAM 7.1 Maintenance Concept The maintenance functions detailed in this schedule fall into two categories: Line Maintenance and Heavy Maintenance. 7.1.1 Repairs beyond the levels detailed in this manual are not recommended as maintenance functions and should be done by an approved overhaul facility. 7.2 Line Maintenance The scope of line maintenance consists of removal and installation of external components and engine accessories. All procedures in this manual are to be considered line maintenance in the absence of the words‘‘(Heavy Maintenance Only)’’ appearing with the procedure title in Maintenance Practices. 7.3 Heavy Maintenance Heavy maintenance details removal, installation and repair of components or parts normally considered beyond the capabilities of the average line maintenance facility. 7.4 ENGINE, TURBOPROP - INSPECTION 7.4.1 General The inspection criteria for the various sections of the engine are summarized in the time table following. Detailed inspection procedures are provided, where applicable, in the relevant INSPECTION/CHECK sections of subject chapters in this manual. 7.4.2 The inspection procedures detailed are considered a normal function of operating organizations and are intended as a guide for minimum inspection and maintenance requirements. 7.4.3 ROUTINE inspection coincides with the daily or pre-flight airframe inspection. 7.4.4 MINOR inspection is coincidental with a typical airframe zone inspection. 7.4.5 The intervals at which these inspections are performed may be altered by the aircraft manufacturer’s maintenance program and approved by the KCAA. 7.4.6 Engines maintained in compliance with the aircraft manufacturer’s approved maintenance program shall be inspected as required by Condition Monitoring. 7.4.7 Engines operating in sandy or dusty environments or in smog or salt-laden atmospheres should be subjected to additional inspections for corrosion and compressor erosion. 7.4.8 Hot section inspection frequencies are outlined in the applicable service bulletin and will be updated periodically as dictated by service experience and time-between-overhauls (TBO). If, in the light of experience, it becomes necessary to modify procedures, these will be included in subsequent revisions to this manual.




7.4.9 INSPECTION TOLERANCES 7.4.10 Unless otherwise stated, the tolerance for periodic inspections is ten percent (10%), or up to a maximum of 100 hours operating time, whichever is less. 7.4.11 the tolerance for scheduled inspections is ten percent (10%), or up to a maximum of 30 days calendar time, whichever is less. Subsequent intervals will be adjusted to re-establish the original schedule. When an inspection is done more than 10% early, subsequent inspections will be advanced as required to not exceed the maximum tolerance. 7.5 Engine Periodic Inspection Time Table These time tables have been extracted from Chapter 72-00-00 pg 604 of PWC PT6A-114 / 114A series Maintenance Manual P/N 3043512 Rev 30 Note: Refer revision status printout in the technical library for latest revisions of Manuals

Component Inspection Interval Engine Externals

Clamps, Brackets, Tubes/ Lines, Linkages

All accessible connections, clamps and brackets for attachment MINOR

Inspect accessible lock wire and safety cable for security and installation. MINOR

Wear, Chafing, cracks and corrosion. Visually inspect insulated air tubes for signs of swelling, cracking, bulging of rubber sheath material. Refer to repair section and SB1687. Replace as necessary.

MINOR

Fuel and oil lines for leaks ROUTINE Depending on operating conditions and environment, examine linkages at regular intervals. MINOR

Pay particular attention to rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings. MINOR

Disconnect rod ends and clean using solvent (PWC11-027) or (PWC11-031). MINOR

Examine the rod ball for corrosion, roughness in rotation, side play and radial play. MINOR

Lubricate with light grease (PWC04-001) after engine external wash. After lubrication reinstall rod ends and torque to specified value (Ref 76-10-00).

MINOR

Examine rod end for corrosion, roughness in rotation, side play and radial play. MINOR

Check free movement of linkage. MINOR NOTE: With the exception of rod end fittings, linkages generally will operate satisfactorily without lubrication. While lubrication will be effective in some instances, it must be realized that grease and oil attracts dirt and foreign matter. Depending on local conditions, ALS will take these facts into consideration before deciding to lubricate components or do otherwise. Mandatory lubrication of all engine control linkages is required after every engine wash.

Air Inlet Inspect air inlet screen for cleanliness MINOR Inspect inlet surface areas, with screen removed, inspect overall surface area and struts for corrosion MINOR

Gas Generator

Case

External surfaces, and fire seal mount ring brackets for cracks, distortion, and corrosion MINOR

Fire-seal Mount Rings Cracks and attachment of brackets and seals MINOR




Exhaust Duct Cracks and distortion MINOR Engines that exhibit inferior welds (Ref.72-50-05, MAINTENANCE PRACTICES) MINOR

Propeller Shaft Seal

Check for oil leaks

ROUTINE

Accessories

Attachment and linkages, air, oil and fuel lines MINOR Visually inspect insulated air tubes for signs of swelling, cracking, bulging of rubber sheath material. MINOR

Oil and fuel leaks as applicable ROUTINE

Starter-generator gear shaft splines for wear At starter-generator removal/replacement

Engine Internals

Hot Section Examine with boroscope in conjunction with periodic fuel nozzle leak and flow check 400 hours

Component Inspection Interval Systems

Oil System

Check oil level ROUTINE Check condition and locking of oil filler cap ROUTINE

Examine oil filter. MINOR Elements must be inspected and cleaned MINOR

Light traces of sediment only may be removed from the main filter screen .All other contamination requires replacement of filter element. Any foreign material found in main oil filter or on chip detector, should be identified before further inspection/operation If carbons like deposits are found, drain accessory gearbox oil into a clean container and examine debris. Varnish flakes are non metallic and are usually dark on one side and shiny, similar to bronze, on the other side. They are hard and will not form into paste when rubbed between fingers

Oil Filter Replace 1000 hours

Chip Detectors

Check magnetic chip detector(s) for continuity; open circuit must exist indicating no contamination at pole tips.

200 hours

If continuity exists, remove and inspect for contamination. Any foreign material found on the chip detector or in the main oil filter should be identified before further inspection/operation

200 hours

For aircraft equipped with a cockpit indicating system, use a suitable ohmmeter to check completely as stated

200 hours

Bridge chip detector(s) magnetic pins with suitable jumper, and using a suitable ohmmeter, check continuity between connector pins. If continuity does not exist, replace chip detector.

600 hours or 12 months, whichever comes first

Any foreign material found on either chip detector or in main oil filter should be identified before further inspection/operation. While the chip detector is removed, inspect with both poles bridged (Ref. Step 4).With poles unbridged, inspect for continuity. If continuity exists, replace the chip detector. For aircraft equipped with an airframe supplied indicating device, the integrity of the complete




indicating system can be checked by re-attaching the electrical connector to the removed chip detector and check for chip indication when magnetic poles are bridged. Closed circuit condition must exist

Accessory Gearbox

Checks scavenge pump housing for leaks. ROUTINE

Check AGB internal scavenge oil pump inlet screen

1000 hours for engines not operating in high humidity.

Use a mirror and a flashlight to inspect the scavenge oil pump inlet screen. 1000 hours

Fuel System

Check for water contamination ROUTINE Check fuel pump for installation and leaks MINOR Check fuel pump inlet screen for foreign matter or distortion, clean and reinstall, or install new screen. PWC 600 hours

Check fuel pump outlet filter for foreign matter or distortion PWC 600 hours

Install new filter 200 hours If Sundstrand fuel pump installed, check fuel pump coupling in-situ for fretting, and corrosion. 600 hours

Remove Sundstrand fuel pump and inspect the drive coupling and cover (accessory gearbox side) for signs of reddish-brown (iron oxide) stains. If stains are observed, return the fuel pump to an approved overhaul facility

1800 hours

Check drain valve(s) for installation and leaks MINOR Check FCU for installation, linkages and pneumatic lines. MINOR

Evidence of FCU bearing washout indicated by traces of blue dye effluent is caused by a mixture of bearing grease and fuel

MINOR

On new aircraft, check filter after each flight until no contamination is evident. Check after first flight or ground run whenever any component upstream of filter is replaced.

Fuel Control Unit

Check FCU for bearing wash-out, indicated by blue dye (grease and fuel mixed) at FCU vent. ROUTINE

For engines fitted with a manual override on the fuel control, check FCU Manual Override System for static operation (Ref. 71-00-00)

200 hours

Remove FCU for Drive body Inspection/ Driveshaft Bearing Replacement. 3000 hours

Flow divider/ dump valve Check valve for installation and leaks MINOR

Fuel Nozzles Leak test and function test fuel manifold adapter and nozzle assemblies 400 hours

Oil to Fuel Heater Check oil-to-fuel heater installation MINOR

Ignition System

Check ignition exciter for installation and condition MINOR

Check ignition cables for chafing, wear and installation MINOR Check spark igniters for cleanliness and erosion. Check function MINOR




Pneumatic System

Check P3 filter installation MINOR Clean filter dependent on condition service 200 HOURS Inspect pneumatic tubes and lines for cracks and damages especially at the end fittings and joints. 200 HOURS

Visually inspect the P3 filter for corrosion. If the filter shows presence of corrosion, discard the filter and replace with a new filter.

200 HOURS

Clean and inspect Post-SB3350 P3 filter drain valve housing assembly 200 HOURS

Replace disposable filter based on condition, service experience or environment 1000 HOURS




7.6.1 General Unscheduled inspection is done when the engine is subjected to unusual stress or operating conditions, or exceeds operating limitations or gives unsatisfactory performance. 7.6.2 If as a result of the inspection, engine removal is required, a written report stating cause of removal in detail (e.g. over-speed, over-temperature, etc.) must be sent with the engine to an approved overhaul/repair facility. 7.6.3. Refer to the applicable accessories manual for disposition of external components or, if applicable, send component along with the removed engine or module to an approved overhaul facility. 7.6.4 Several types of events call for rotating the propeller by hand as part of the inspection of the power section. On some engines, the power turbine may rub immediately after shutdown. This is not an indication of distress providing the rubbing/noise disappears after engine cool down. 7.7 Engine Overspeed 7.7.1 Check engine/aircraft indicating system. If satisfactory, do the following: 7.7.2 (a) Gas Generator Speed (Ng):

If observed gas generator speed (Ng) is more than 101.6% but less than 102.6% for less than 2 seconds No action required.

If observed gas generator speed (Ng) is more than 101.6% but less than 102.6% for more than 2 seconds: Return compressor turbine disk assembly for light overhaul (FPI and stretch check on CT Blades).

If observed gas generator speed (Ng) is more than 102.6% but less than 106%.Return engine for light overhaul (FPI and stretch check on CT Blades).

If observed gas generator speed (Ng) is more than 106% return the engine for light overhaul and discard compressor turbine disk and blades

Bleed Valve

Check the bleed valve (Ref. 75-30-00, Inspection/Check) For PT6A-114A engines only, incorporating SB1510 and not incorporating SB1581 or SB1588

Based on operators experience but not to exceed 600 hours.

Check the bleed valve (Ref. 75-30-00, Inspection/Check) For engines operating in dusty, industrial/smog, salt laden environments or under high cyclic conditions

Based on operators experience but not to exceed 600 hours.

Check the bleed valve (Ref. 75-30-00, Inspection/Check) For other engines NOT operating in conditions as above

Inspect in conjunction with a Hot Section inspection




7.7.3 (b) Power turbine speed (Np) If Np exceeded 110%, determine and rectify cause of over-speed. Send engine or power section to an approved overhaul facility: for light overhaul. (c) If Np exceeded 100% for more than 20 seconds, but did not exceed 110% Inspect PT blades and check for rubs. Remove and inspect RGB chip detector, oil strainer, and main oil filter If metallic debris is found, refer to FAULT ISOLATION. Turn the propeller by hand and listen for unusual noises coming from the reduction

gearbox or PT bearings. For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate the maximum speed attained the duration, and any inspection discrepancy.

Run at 80 % TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00, 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals.

7.7.4 Inadvertent Cut-off and Relight during Taxi NOTE: An inadvertent cut-off and relight happens when the operator moves the fuel condition lever from Low Idle to Cut-off and immediately back to Low Idle. This may result in a short-term sub-idle over-temperature. 7.7.5. WITH an engine monitor and have obtained a detailed recording of the over temperature event: Refer to Chap. 71-00-00, ADJUSTMENT/TEST, and Inadvertent Cut-off and Relight during Taxi figure. 7.7.6 WITHOUT an engine monitor: Return the compressor turbine blade and disk assembly to an overhaul shop facility for stretch check, fluorescent penetrent inspection and a metallurgical analysis (cut-up) of two blades. 7.8 Over-temperature

Check engine/aircraft indicating system. If satisfactory, refer to Chapter 71-00-00, ADJUSTMENT/TEST for required action.

When an over-temperature has occurred, and the maximum temperature reached and/or its duration cannot be established, or whenever an over-temperature is suspected to have occurred, send the engine to an overhaul facility for Light Overhaul. Indicate ‘‘Unknown Over-temperature’’.

NOTE: Two compressor turbine blades must be sent for metallurgical analysis (cut-up) to determine the extent of any damage to the engine 7.9 Over-torque

Check the engine/aircraft indicating system. If satisfactory, refer to Chapter71-00-00, ADJUSTMENT/TEST and do the following:

If the over-torque is in Area B:




Remove and inspect RGB chip detector, oil strainer and main oil filter (Ref. 72-10-00, 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

Turn the propeller by hand and listen for unusual noises coming from the reduction

gearbox or PT bearings. For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate torque observed and duration.

Run at 80 % TO power for ten minutes. Remove and inspect RGB chip-detector, oil

strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector

daily for one week (25 hours minimum). Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref.

79-20-02). If no metallic debris is found, return to standard inspection intervals.

If the over-torque is in Area C, send PSM to an approved overhaul facility for Light Overhaul. Indicate torque observed and duration.

When an over torque has occurred, and the maximum torque reached and/or its

duration cannot be established, or whenever an over torque is suspected to have occurred, send the PSM to an overhaul facility for Light Overhaul. Indicate ‘‘Unknown Over torque’’.

NOTE: Providing RBG chip detector, strainer and main oil filter element inspections are done and the results are found satisfactory, a ferry flight may be done under the authorization of the KCAA to bring the aircraft to a maintenance base capable of power section module change. 7.10 Immersion in Water Send engine to an approved overhaul facility for Light Overhaul. Indicate immersion in water. 7.11 Dropped Engine Send the engine or component to an approved overhaul facility for Light Overhaul. Indicate dropped engine or component, the type of surface the engine struck and from what height. 7.12 Material Ingestion (e.g., ice, stones, etc)

Check compressor first-stage blades for damage (Ref. 72-30-05, Inspection/Check).

Do engine performance/ground powers check (Ref. 71-00-00, ADJUSTMENT/TEST, and Engine Performance Check) or ground power check (Ref. 71-00-00, ADJUSTMENT/TEST, Ground Power Check).

7.13 Bird Strike/Soft Material Ingestion (e.g., rags, plastic bags, etc.).

Remains on compressor first-stage blades confirm if bird or soft material has passed through the engine and possibly contaminated the gas path and CT vane cooling air passages.




If contamination occurred, remove the power section and inspect hot section

components (Ref. In-service Inspection).

Evidence of possible contamination of the compressor turbine vane cooling passages necessitates an approved overhaul level inspection of the vane.

If the engine remains in service, do a performance recovery wash (Ref. POWER

PLANT - CLEANING, Internal Washing) and a performance (Ref. 71-00-00, ADJUSTMENT/TEST, Engine Performance Check) or ground power check as applicable (Ref. 71-00-00, ADJUSTMENT/TEST, Ground Power Check)

7.14 (a) Propeller sudden stoppage Occurs when propeller rotation stops due to contact (propeller strike) with a hard object (e.g. ground, ground service equipment, etc). 7.14 (b) The term propeller strike Is used when either a rotating propeller hits an object which causes a speed variation ( no stoppage) and blade damage or a stationary propeller is hit by a moving object which causes blade damage. 7.14.1 For Propeller sudden stoppage, propeller strike causing blade structural damage (e.g. bent blade, or blade tip missing or bent over 1 in.), propeller strike on a power line, or propeller strike at power above FLIGHT-IDLE (Ng above 82 %) do the following:

Send power section to an approved overhaul facility for Light Overhaul. Indicate propeller strike, sudden stoppage as applicable, propeller speed and power at

event, and extent of propeller damage. Inspect remainder of engine:

(a) Remove and inspect the main oil filter (Ref. 79-20-02). If metallic debris if found, refer to FAULT ISOLATION. (b) Inspect for cracks or distortion at all engine casings and housings, especially at or near the flanges. Remove the starter-generator and check all AGB pads and AGB mounted engine and airframe components. Look for shearing, cracks, distortion or mis-alignment, and loose/pulled fasteners. Similarly, inspect all engine mounts. (c) Inspect fire-seals for warping or buckling, and all external tubes for damage and/or fluid leaks. (d) Check all airframe/engine connections, including fuel inlet and oil cooler lines, air system, electrical, ignition and indicating systems, control linkages, and drains. (e) For propeller strike on a power line (power utility line - does not include guide/support wires, telephone or telecommunications lines), check for evidence of electrical discharge (localized burn marks) at the C-flange or at the compressor turbine. (f) Rotate the compressor by hand and listen for rubbing, scraping, interference of rotating components with stationary parts, or rapid/abrupt deceleration. Check for rear accessory case




mounted accessory drag. Check for compressor turbine tip rub (Ref. 72-50-02, Inspection/Check). (g) For casing or accessories damage, evidence of electrical discharge, unusual noises that could indicate damage to the gears, bearings, seals or rotors, slow compressor acceleration on start or abrupt deceleration on shutdown, send the complete engine to an approved overhaul facility for Light Overhaul. Indicate propeller strike/sudden stoppage as applicable, propeller speed and power at event, and extent of propeller damage. (h) After installation of a repaired/replacement power section on the serviceable gas generator, run at 80% TO power for ten minutes. Remove and inspect the main oil filter (Ref. 79-20-02). If no metallic debris is found, return the engine to service. (i) Inspect main oil filter after one week (25 hours minimum, 65 hours maximum). If no metallic debris is found, return to standard inspection schedule. 7.14.10 For Propeller strike causing minor blade damage (e.g. delamination, indentation, blade tip bent slightly, etc.) with engine at or below FLIGHT-IDLE power or while engine was shut down do the following:

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings. For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate what the propeller hit and at what speed and power, and extent of damage.

Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals.

7.15 Propeller Electrical Leads Shorting If signs of arcing between de-icer leads and the propeller spinner, bulkhead or hub assembly have been found, check propeller de-icing system (Ref. Aircraft Maintenance Manual) and rectify. 7.15.1 Inspect Engine:

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20- 02). If metallic debris is found, refer to FAULT ISOLATION.

Turn the propeller by hand and listen for unusual noises coming from the reduction

gearbox or PT bearings For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate propeller electrical leads short and any discrepancy noted. Otherwise, run engine at 80% TO power for ten minutes.




Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref.

79-20-02). If no metallic debris is found, return to standard inspection intervals. 7.16 Propeller Lightning Strike 7.16.1 If signs of arcing are found on the propeller blades, the propeller shaft and flange must be checked for magnetism. NOTE: Refer to the applicable accessories manual for disposition of external components. 7.16.2 Check for magnetism, using one of the following methods: Check propeller shaft, especially flange, using a magnetometer to make sure residual magnetism is within ± 3 gauss or 3 oersted of 2.38 A/cm. If reading is above limits, replace power section. 7.16.3 If the propeller shaft or flange are found magnetized:

Ship the power section to an approved overhaul facility for Light Overhaul. Indicate a lightning strike.

On the gas generator, check for evidence of electrical discharge (localized burn

marks) at the C- approved overhaul facility.

Inspect the main oil filter (Ref. 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

7.16.4 If the propeller shaft or flange are not magnetized:

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

Turn the propeller by hand and listen for unusual noises from the reduction gearbox or

PT bearings. For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate a lightning strike.

Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return the engine to service and check RGB chip detector daily for one week (25 hours minimum).


79-20-02). If no metallic debris is found, return to standard inspection intervals. 7.17 Heavy/Hard Landing NOTE: 1 A landing must be considered hard if the aircraft incurred any airframe or landing gear damage. NOTE: 2. If the heavy/hard landing involved a wind-milling (inoperative) engine, send the complete engine to an approved overhaul facility for Light Overhaul. Indicate heavy/hard landing of inoperative engine. Otherwise, proceed as follows:




Inspect for cracks or distortion at all engine casings and housings, especially at or near the flanges.

Remove the starter-generator and check all AGB pads and AGB mounted engine and

airframe components. Look for shearing, cracks, distortion or mis-alignment, and loose/pulled fasteners. Similarly, inspect all other accessories and engine mounts.

Inspect fire seals for warping or buckling, and all external tubes for damage and/or

fluid leaks.

Check all airframe/engine connections, including fuel inlet and oil cooler lines, air system, electrical, ignition and indicating systems, control linkages, and drains.

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00

and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

Rotate the compressor by hand and listen for rubbing, scraping, interference of rotating components with stationary parts, or rapid/abrupt deceleration. Check for rear accessory case mounted accessory drag. Check for compressor turbine tip rub (Ref. 72-50-02, Inspection/Check). Rotate the propeller by hand and listen for any interference of rotating components with stationary parts or any other unusual noises coming from the gearbox or turbines Examine PT disk assembly and exhaust area through exhaust ports for evidence of distress.

For casing or accessories damage, unusual noises that could indicate damage to the

gears, bearings, seals or rotors, slow propeller acceleration on start or abrupt deceleration of compressor or power section on shutdown, send the complete engine to an approved overhaul facility for Light Overhaul. Indicate heavy landing and discrepancies observed.

Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip

detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum). If no

metallic debris is found, return to standard inspection schedule.




7.18 Aircraft Flown Through Volcanic Ash or Smoke Wash compressor and turbine (Ref. 71-00-00, POWER PLANT - CLEANING,

Internal Washing).

Drain and refill oil system with new oil (Ref. SERVICING, Lubricating Oil System).

Clean or change main oil filter (Ref. 79-20-02, Cleaning).

Examine compressor (Ref. INSPECTION/CHECK, Borescope).

Return engine to service if no defects are found.

Drain and refill oil system with new oil (Ref. SERVICING, Lubricating Oil System) 50 ± 10 flight hours after original oil change done in step (2).

7.19 Sustained Running at Oil Temperature outside Limits

Check aircraft/engine indicating system and correct cause of high oil temperature.

Rotate the compressor rotor and check for indications of AGB or bearing distress.

Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings.

For any presence of unusual noise, send the complete engine to an approved overhaul

facility for Light Overhaul. Indicate the oil temperature that the engine was operated at, the engine power and the duration.

Drain and discard oil (Ref. SERVICING, Lubricating Oil System).

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00

and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

Fill oil system (Ref. SERVICING, Lubricating Oil System).

Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).


79-20-02). If no metallic debris is found, return to standard inspection intervals 7.20 Loss of Oil/Oil Pressure or Low Oil Pressure CAUTION: IF AIRCRAFT OIL SYSTEM CONTAMINATION IS SUSPECTED, REVERSE FLUSH ENGINE OIL SYSTEM, INCLUDING OIL-TO-FUEL HEATER. AIRCRAFT OIL COOLER MUST BE REJECTED.




NOTE: Low oil pressure is defined as oil pressure below limits (Ref. 71-00-00, ADJUSTMENT/TEST, Pre-Operational Check). 7.20.1 If the loss of oil is 6 qt. or more, resulting in fluctuation of oil pressure or torque indication or oil pressure dropped below nominal value (Ref. 71-00-00), but was above 60 psi:

Check oil pressure and torque indicating system. If correct, and the engine did not run above 27000 rpm (72 %) Ng with pressure below 85 psig (minimum time running is permitted to allow flight crew to follow the emergency procedure), remove main oil filter, strainer and chip detector and inspect for metallic debris. If metallic debris is found, refer to FAULT ISOLATION.

NOTE: Oil pressures below 85 psig are unsafe and require either the engine to be shut down or an emergency landing made as soon as possible, using minimum power to sustain flight.

Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings. If unusual noises are heard, send power section to an approved overhaul facility for Light Overhaul. Indicate unusual oil conditions.

NOTE: PT blades may rub, immediately after engine shutdown which is not an indication of distress, providing the rubbing/noise disappears after engine cool down.

Turn the compressor rotor. Listen for unusual noises coming from bearings, seals, gears, compressor and/or CT.

If unusual noises are heard, send gas generator to an approved overhaul facility for

Light Overhaul. Indicate unusual oil conditions.

Run the engine at 80% TO power for 10 minutes. (i)Remove main oil filter, strainer and chip detector and inspect for metallic debris. If metallic debris is found, refer to FAULT ISOLATION. (ii)If no metallic debris is found return engine to service. (iii)Inspect chip detector daily for one week and main oil filter after seven days or approx. 50 flight hours, whichever comes first. (iv)If no metallic debris is found, return to standard inspection intervals.

If the engine was kept running above 27000 rpm (72 %) Ng with oil pressure below 85 psig, check oil pressure indicating system, and if correct, remove the engine and send it to an overhaul facility for Light Overhaul. Indicate low oil pressure.

7.20.2 If the loss of oil is 6 qt. or more, and the engine oil pressure or torque-meter indication have fluctuated or oil pressure dropped below 60 psi:

Check oil pressure and torque indicating system. If correct, and the engine was kept running with oil pressure below 40 psig in excess of the time required to carry out the emergency engine shutdown procedure, ship the engine to an overhaul facility for Light Overhaul. Indicate unusual oil conditions.




In case the oil pressure drops below 40 psi, an engine shut down is required. In single engine installation or emergency, use minimum power to sustain flight and prepare for emergency landing.

Remove and ship propeller governor for overhaul. Indicate loss of oil.

7.21 Oil Pressure Follows Throttle NOTE: Under normal operating conditions, oil pressure indication is stable. Malfunction of the pressure relief valve or oil leakage can cause indication to increase as throttle is advanced, or drop when throttle is retarded.

Check external lines for breaks and leakage. Remove pressure relief valve and check for sticking, scoring, etc

Remove accessory gearbox. Check oil pump housing for cracks

Remove relief valve and housing. Examine housing for wear resulting from relief valve rotation. Replace housing if necessary.

7.22 Contamination by Fire Extinguishing Agents 7.22.1 Foam, powder or other chemical extinguishers: (a) If only engine externals are exposed, then wash (Ref. 71-00-00, CLEANING, Engine External Wash) using drinkable quality water only and monitor for corrosion. (b) In the event of internal contamination, return engine to an approved overhaul facility for Light Overhaul. Indicate the agent ingested by the engine. Depending on the agent, and at the option of the operator, an attempt may be made at cleaning the contaminating agent prior to shipping:

Do a dry motoring run (Ref. 71-00-00, ADJUSTMENT/TEST, Dry Motoring Run) to blow out any residual deposits.

Wash engine externally (Ref. 71-00-00, CLEANING) using drinkable quality water only.

Do an engine performance recovery wash (Ref. 71-00-00, CLEANING) followed by two dry motoring runs.

7.22.2 Halon: No engine maintenance required. 7.23. Audible Rubbing, Binding or Scraping NOTE: Any unusual (internal) engine noises (e.g. rubbing, scraping and/or squealing, etc.) require immediate investigation. (a)Rotate compressor rotor and listen for any interference of rotating components with stationary parts and/or check for rapid deceleration on shutdown.

Check for rear accessory case mounted accessory drag. Check for compressor turbine tip rub (Ref. 72-50-02, Inspection/Check). Indications of compressor rub or bearing or AGB distress. Send engine to an approved

overhaul facility for Light Overhaul.




(b) Rotate the propeller and listen for any interference of rotating components with stationary parts .If power turbine rotor rattles, or if there is rubbing or scraping, slow propeller acceleration on start or abrupt deceleration on shutdown:

Examine PT disk assembly and exhaust area through exhaust ports for evidence of distress.

If damage is found, inspect (Ref. 72-50-04, Inspection/Check). Slow or stiff propeller rotation. Send power section to an approved overhaul facility

for Light Overhaul. Indicate rubbing.

(c) If the suspected problem cannot be repeated or confirmed:

Remove and inspect RGB chip detector, oil strainer, and main oil filter(Ref.72-10-00 and 79-20-02). If metallic debris is found, refer to FAULTISOLATION.

Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02).If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals




7.23 Propeller Wind-milling after In-flight Shutdown 7.23.1 Investigate cause of shutdown. If suspected of being attributed to an engine or accessory problem, send engine or accessory to an approved overhaul facility for Light Overhaul. Indicate engine shutdown and the events and conditions at the time. 7.23.2 With shutdown not related to an engine problem (serviceable engine):

With stabilized wind milling Np not more than 20 rpm and less than 6 qt. of oil required to bring oil level to MAX on dipstick, no further action is necessary.

With an unknown (not recorded) Np or stabilized wind-milling Np greater than 20

rpm or if 6 qt. or more of oil is required to bring oil level to MAX on dipstick: (a) Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00, 79-20-02). If metallic debris is found, refer to FAULT ISOLATION. (b) Rotate the compressor rotor and check for indications of AGB or bearing distress.

7.24 Contamination of Oil with Non-metallic Foreign Material NOTE: 1. AGB/RGB internal protective coatings may be released within the engine and appear as flakes 1/64 inch to 3/8 inch in diameter, usually shiny, yellow, brown or green in color, and may or may not be transparent. NOTE: 2. Inspect chip detector, main oil filter and AGB scavenge pump screen after approximately 10 hours. If no debris is found, inspect at 50 hours. NOTE: 3. If no debris is found at 50 hours, refer to the standard periodic inspection interval for oil fitler and chip detector. NOTE: 4. If these flakes are found, immediately contact your local P&WC customer support representative. Send engine to an approved overhaul facility for Light Overhaul. Indicate oil contamination from released AGB/RGB internal protective coatings.

(a). Remove chip detector from reduction gearbox front housing (Ref. SERVICING,

Oil Change) and scrub scavenge oil strainer sleeve with a brush to remove any foreign material blocking the screen.

(b) Remove accessory gearbox drain plug(s).

(c) Flush oil system (Ref. SERVICING, Oil System Flushing).

(d). Reinstall chip detector and plug(s) and tighten. Refill engine oil tank.

NOTE: Do not lockwire chip detector and drain plug(s) at this time.

(e) Remove chip detector and inspect scavenge oil strainer sleeve for residual foreign material accumulated after system flush (Ref. NOTE 1).

(f).Repeat steps (b) thru (e), if required.




(g). Reinstall chip detector. Tighten all plugs and chip detector and lockwire. 7.25 Starter-Generator Replacement If there is an engine starting fault or an electrical generation defect, do the following inspections:

(a) Inspect the starter-generator drive splines: Inspect per Aircraft Maintenance Manual (AMM). If there is no inspection procedure in the AMM, clean the starter-generator splines and

inspect for evidence of electrical arcing damage (in the form of pitting) using a 10X magnifying glass.

NOTE: 1. If there is any evidence of electrical arching, return engine to an approved overhaul facility for Electrical Discharge Damage (EDD) repair. NOTE: 2. If there is NO evidence of electrical arching, inspect the main oil filter (Ref. Step (b).

If cause of pitting cannot be determined, metallurgical analysis may be required. Contact the Aircraft OEM.

(b) Inspect the main oil filter: Do a main oil filter patch check (Ref. Chapter 79-20-02). The results of the filter

patch analysis should be reviewed within the next 25 flight hours. If non allowable debris is found, follow the recommended maintenance actions (Ref. Chapter 79-20-02).

Regardless of the results of the patch analysis, repeat step (a) every 100 hours, for the next 700 flight hours.

If bearing material (AMS 6440/6444 or AMS 6490/6491, Ref. Chapter 79-20-02) is found, remove the engine/gas generator module and send to an approved overhaul facility for repair.

7.26 Chip Detector Circuit Completion and/or Debris in Oil Filter (1) Refer to FAULT ISOLATION 7.27 Engine maintenance schedule chart (compiled from P&WC MM Rev 30, SB1002 and SB1703 latest revisions) Fuel Pump outlet filter cartridge ** RENEW 100 HOURS Fuel Pump inlet screen ** INSPECT 100 HOURS EPL manual override static ops 71-00-00 CHECK 200 HOURS Fuel Nozzle Flow Check CHECK 400 HOURS Flow Divider TBO + 500 OVERHAUL 3600 HOURS Sunstrand coupling in situ fret & corrosion 73-10-02 INSPECT 600 HOURS

Sunstrand coupling & drive spline 73-10-02 INSPECT 1800 HOURS Pump Hamilton Sunstrand.Engine TBO OVERHAUL 3600 HOURS Pump Argotech Engine TBO + 500 hours RENEW 3600 HOURS Boroscope (Full inspection) (SIL PT6A-116R1) INSPECT 400 HOURS

P3 Filter ELECTROSONICCLEAN 200 HOURS

P3 Filter RENEW 1000 HOURS Bleed Valve Removal and Inspection 75-30-00 INSPECT 600 HOURS




Bleed Valve TBO + 500 OVERHAUL 3600 HOURS Fuel Control TBO + 500 OVERHAUL 3600 HOURS Fuel Heater TBO + 500 OVERHAUL 3600 HOURS Engine Hot Section Inspection +- 50 hours INSPECT 1800 HOURS Engine Gas Generator Overhaul OVERHAUL 3600 HOURS Engine Power Section OVERHAUL 3600 HOURS Ignition Exciter TBO + 500 OVERHAUL 3600 HOURS Compressor Turbine Disk RENEW 16000 CYCLESCT two blade metallurgical evaluation DESTRUCT TEST 1800 HOURS Compressor Turbine Disk Blades OHC STRETCH TEST 3000 HOURS Compressor Turbine Disk Blades NEW STRETCH TEST 5000 HOURS Compressor First Stage Hub REPLACE 19000 HOURS Engine Impeller REPLACE 19000 CYCLESPower Turbine Disk REPLACE 20000 CYCLESCompressor Second Stage Disk REPLACE 24000 CYCLESCompressor Third Stage Disk REPLACE 25000 CYCLESPropeller Dynamic Balance ** BALANCE 6 MONTH Propeller Primary Governor TBO + 500 OVERHAUL 3600 HOURS Propeller Overspeed Governor Hartzell TBO + 500 OVERHAUL 4600 HOURS

Propeller Overspeed Governor McCauley OVERHAUL 6500 HOURS Propeller - McCauley OVERHAUL 4000 HOURS Propeller - Hartzell OVERHAUL 3000 HOURS Chip detector pin bridge & continuity check CHECK 600 HOURS Chip detector pin bridge & continuity check CHECK 1 YEAR AGB scavenge pump inlet screen (72-60-00) INSPECT 1000 HOURS Compressor power recovery wash CLEAN 100 HOURS Compressor turbine wash CLEAN 100 HOURS

Oil Filter ELECTROSONIC CLEAN 200 HOURS

Oil Filter RENEW 1000 HOURS ** Items are additions to the Type Certificate holders’ recommendations.

7.28 General Considerations for TBO Extension Recommendations

1. A TBO extension recommendation from P&WC is based on both the ALS Ltd procedures and experience and on P&WC experience. P&WC experience is based on:

a. Engines that incorporate only P&WC parts originally supplied by P&WC or its authorized distributors or components repaired in accordance with P&WC approved repair process. b. Factory built engines or engines overhauled/repaired at a P&WC service center or a P&WC Designated Overhaul Facility (DOF). c. As P&WC experience grows, the TBO extension requirements and limitations may be adjusted accordingly.

2. An engine maintains its TBO extension recommendation on either program as long as it is operated within the limitations of the relevant aircraft operating manuals and is maintained in accordance with the appropriate P&WC Maintenance Manual and the terms of this S.B.




NOTE: P&WC recommendation is null and void in instances where engine abuse or non-compliance with this recommendation is reported. 3. If the engine was put in storage or was unused since its last overhaul (or since new if not previously overhauled), there must be documented evidence that the engine has been preserved per the engine Maintenance Manual. 4. Extension recommendations are only transferable between ALS Ltd under circumstances described in option A and B. 5. Recommendations for extension are subject to limitations including the maximum numbers of years between overhauls, being 12 years.

B. Assembly and Component Records: TBO extensions incorporate limitations on the life of certain components. The ALS Ltd and/or the Approved Maintenance Organization selected by the ALS Ltd must have a system to log the total accumulated time, i.e. Time Since New (TSN), and the Time Since Overhaul (TSO) of the following assemblies and components:

Engine times and cycles since new and since last overhaul; Accessories time since new or since last overhaul; Total cycles of life limited rotors (Ref. P&WC S.B. No. 1002); Total hours since new for the components that follow:

o The mainline ball bearings (bearings No. 1 and No. 4); o The power turbine blades; o The compressor turbine blades; o The first stage sun gears; and o The first stage planet gears.

NOTE: For non-serialized turbine blades, the total hours since new must be based on the oldest installed blade. For example, if a complete new set of blades is installed at overhaul and 18 blades are replaced at TSO = 1800 hrs, the total time on the entire blade set will still be considered 1800 hrs, even though the 18 newly installed blades have zero time. C. Configuration Records P&WC makes available product improvements through the issuance of Service Bulletins (S.B.). The ALS Ltd and/or the maintenance organization selected by the ALS Ltd must have a system to log S.B.s that are incorporated in each engine. In particular, the following are considered especially valuable for ALS Ltd on extended TBO:

P&WC S.B. No. 1427 PT Containment Ring (PT6A-114) P&WC S.B. No. 1430 Exhaust Duct and No. 3 Bearing Cover P&WC S.B. No. 1434 Combustion Chamber & Large Exit Duct P&WC S.B. No. 1446 External Scavenge Pump P&WC S.B. No. 1510 Third Stage Compressor Stator (See Note 2) P&WC S.B. No. 1669 Compressor Turbine Blades (PT6A-114A)

D. Option A - Fleet TBO Extension by Overhaul Sample Evaluation 1. P&WC may provide extension recommendations for the TBO of an ALS Ltd’s fleet of similarly operated and maintained engines. The condition of the engines examined at overhaul is one element of validating that the specific ALS Ltd is operating and maintaining the engines in a manner that warrants extending the TBO interval for the specific fleet. Other elements include but are not limited to:

a .Accuracy of maintenance records. b. Reported condition of hardware at previous maintenance intervals. c. Local regulatory endorsement of ALS Ltd adherence to OEM recommended operation and maintenance practices. This endorsement should be obtained on a yearly

basis. 2. The time limits applicable under this program are as follows: BO Limit: 8,000 hrs




Calendar Limit: Engines may operate at the extended TBO for a maximum period of 12 years since new or since overhaul as applicable, or as otherwise agreed in writing by P&WC. 3. To make sure that engine durability is maintained as the engines are operated into their subsequent extended overhaul intervals, the components listed in the page , that are used for engine reassembly at overhaul, must not have more than 12,000 hours since new. Also, all the service bulletins listed in C-(Configurations records) above and all applicable category 1, 2 and 3 service bulletins must be incorporated in the build of the sample engine and at the next overhaul of other engines in the fleet for which the TBO extension is applicable. 4. Normal TBO extension recommendations are 500 hours. For TBO extension up to 5,100 hours one representative sample engine per 500 hrs increment is required. For TBO extensions above 5,100 hours two representative sample engines per 500 hrs increment are required. 5. Requirements applicable to the sample(s):

a. The sample must have a Time since Overhaul (TSO) that is within 250 hours of the

current TBO period. Engines that have more hours than the current P&WC recommended TBO are also acceptable but the extension will be based on the currently recommended P&WC TBO.

b. The sample must have been operated by the current ALS Ltd for the majority of the TBO period (i.e. for more than 50% of the current TBO interval).

c. The sample engine must not have had a shop visit for major repairs (Overhaul Manual level) during the current TBO interval (i.e. only Maintenance Manual level tasks and repairs have been carried out).

d. The ALS Ltd must complete the fleet TBO Evaluation Sample Request and the fleet information form available in the PWC Website and submit them to their P&WC service center or Designated Overhaul Facility for forwarding to P&WC.

e. The sample engine must be sent to a P&WC service center or Designated Overhaul Facility (DOF) for the TBO evaluation. The evaluation consist of 2 stages, the first portion consists of a visual examination of the engines prior to cleaning to assess whether the hardware appears capable of 500 hours of further operation. Following satisfactory completion of this phase the second portion consist of detailed examination of the components to the requirements of the P&WC OHM. The P&WC DOF or P&WC Service Centre will forward the TBO Evaluation Sample Request Form, ALS Ltd’s Fleet Information Form and the TBO Evaluation Hardware Report to P&WC for review and request a TBO extension.

f. After one or two successful samples, depending on the TBO escalation threshold P&WC will issue a letter to the ALS Ltd stating that a TBO extension is recommended, subject to the approval of the Tanzania Civil Aviation’s Authority.

NOTE: 1. when shipping an engine to a P&WC service center or DOF as a sample, ALS Ltd should state that it is a sample and request a TBO extension evaluation report.

NOTE: 2. Forward all documents to [email protected] NOTE: 3. Refer to P&WC SIL PT6A-041 for further information.

6. ALS Ltd can make a request for a TBO contingency of up to 200 hours directly to the Tanzania Civil Aviation Authority, for the remaining engines in the fleet. This will permit continued operations beyond the current TBO interval, while the sample engine is evaluated and overhauled, provided that engine performance remains satisfactory and a boroscope inspection of the hot section is performed in accordance with the applicable P&WC Maintenance Manual.




7. Should a sample be rejected P&WC will not consider a TBO escalation unless ALS Ltd defines the actions taken to correct the observed conditions. 8. The extended TBO may apply to other eligible engines in the ALS Ltd’s fleet

covered by the same TBO P&WC S.B. No. 1703., or by P&WC P &WC S.B. No. 1403, 1803 or 12003.

9. Extended TBO intervals for engines which were added to the fleet from another ALS Ltd are subject to the pro-rating formula in Para. (13). This formula must be used again when a fleet TBO extension is granted (Ref. Para. (13), Example 2).

10. The TBO extension process can be repeated when the next engine reaches the new escalated TBO interval. 11. Certain circumstances may warrant a higher TBO increase increment. These will be reviewed on a case by case basis upon written request. 12.P&WC reserves the right to request additional information on the sample condition, or further TBO extension samples, and this request does not herein imply that P&WC will automatically recommend the extension. 13. TBO escalation recommendation is subject to the approval of the Tanzania Civil Aviation Authority.

E. Option B - Engine Specific Extension by Evaluation of Configuration, Condition and Operation At this time ALS Ltd will not be using the option B in order to secure specific engine extensions. Should this change at a future date, then the procedures thereto will be added to this Aircraft Maintenance Program as a revision, and will be submitted to Tanzania Civil Aviation Authority for Approval.

F. Transfer of Fleet TBO Extension Recommendations Fleet TBO extensions are valid only as long as the operator, the Approved Maintenance

Organization (A.M.O.) and the typical mission remain unchanged. The following conditions apply for P&WC to transfer the recommendation to a new AMO., a new operator, or a new application (typical mission):

NOTE: For changes limited to the selection by the operator of a new A M.O., the change will have no effect if the maintenance plan remains unchanged and the newly selected M.O. is already supporting operators who have approval for engines covered by this SB and to the same or higher TBO. a. For the transfer of an engine to a different fleet extended TBO, the operator can use a pro-rating formula. This formula is generally recognized by regulatory authorities, including Tanzania Civil Aviation Authority. The TBO applicable to an engine in these circumstances is the fleet TBO formerly applicable and the fleet TBO established for the new operator, Approved Maintenance Organization and mission for the same engine models. It is then weighted on the basis of the time remaining to overhaul under the original operation.

The formula for this purpose is: X = Y * a/b where X = time remaining to overhaul on new program (buyer’s TBO) Y = time remaining to overhaul on previous program (seller’s TBO) a =TBO interval on new program (buyer’s TBO) b = TBO interval on previous program (seller’s TBO) Example 1: An aircraft is transferred (by sale or lease) between two operators. The

previous operator’s engine TBO is 8,000 hours and the new operator’s engine TBO is 5,000 hours

and the engine has a time since overhaul (TSO) of 6,000 hours Time remaining to overhaul on the previous program: Y = 8,000 - 6,000 = 2,000 hours.




Time remaining to overhaul on the new program: X = Y * a/b X = 2,000 * 5,000/8,000 = 1,250 hours Therefore this engine may be operated to a onetime TBO interval of 7,250 hours. After overhaul, the engine TBO will revert to the new owners TBO, which is 5,000 hrs. in this example.

Example 2: An operator obtains a recommendation from P&WC for a TBO extension from 5,000 to 5,500 hours, but one of the engines was purchased from an operator with a TBO of 8,000 hours and is currently running to a TBO of 7,250 hours (Ref. Example 1). The new TBO interval will be calculated using the pro-rating formula and the TSO of the engine at entry to the new operator’s fleet (6,000 hours).

Time remaining to overhaul on the previous program: Y = 8,000 - 6,000 = 2,000 hours. Time remaining to overhaul on the new program: X = Y * a/b X = 2,000 * 5,500/8,000 = 1,375 hours Therefore this engine may be operated to a onetime TBO interval of 7,375 hours. After overhaul, the engine TBO will revert to the new owners TBO, which is 5,500 hrs. in this Example.

7.29 Pratt and Whitney Service Bulletins Compliance Categories Codes Pratt and Whitney issues Service bulletins that are rated in the following categories and group codes Category 1 P&WC recommend to do this service bulletin before the next flight. Category 2 P&WC recommend to do this service bulletin the first time the aircraft is at a

line station or maintenance base that can do the procedures. Category 3* P&WC recommend to do this service bulletin within....hours or....cycles. Category 4 P&WC recommend to do this service bulletin the first time the engine or

module is at a maintenance base that can do the procedures, regardless of the scheduled maintenance action or reason for engine removal.

Category 5 P&WC recommend to do this service bulletin when the engine is disassembled and access is available to the necessary sub-assemblies (i.e. module, accessories, components, or build groups). Do all spare sub-assemblies?

Category 6 P&WC recommend doing this service bulletin when the sub-assembly (i.e. module, accessories, components, or build groups) is disassembled and access is available to the necessary part. Do all spare sub-assemblies?

Category 7 You can do this service bulletin when the supply of superseded parts is fully used.

Category 8 This service bulletin is optional and can be done at the decision of the operator.

Category 9 Spare Parts Information Only. Old and new parts are directly interchangeable and operators can mix old and new parts.

Category CSU Operators who participate should include this service bulletin at the next maintenance or overhaul of the engine. For conditions which could result in an in-flight shutdown, significant loss of power/thrust or any other similar situation affecting flight safety.




Group / Code Compliance Statement A For conditions which could result in an in-flight shutdown, significant loss

of power/thrust or any other similar situation affecting flight safety. A1A Recommended - Urgent. P&WC recommends (Alert SBs) accomplishment

prior to next flight. An Airworthiness Directive has been requested. A1B Recommended - Most desirable. To be accomplished during next visit to a

facility where specified maintenance action(s)/modification(s) can be accomplished.

A1C Currently not used. A1D Recommend - Highly desirable. To be accomplished prior to part life expiry

or within....hours (or....cycles). A2 Recommend - Highly desirable. P&WC recommends accomplishment at

first shop visit of module/engine/power section/RGB/accessory regardless of extent of disassembly.

B For conditions which affect engine life (PERs) and operating costs: B3A Recommended - Desirable. P&WC recommends accomplishment when

disassembly of engine/power section/RGB/accessory is sufficient to afford access to the affected module/subassembly.

B3B Recommended - Desirable. P&WC recommends accomplishment when disassembly of engine/power section/RGB/accessory is sufficient to afford access to the affected part.

B4 Recommended - Incorporation applicable on attrition of prior configuration parts when supply of such items is depleted.

B5 Optional - At the discretion of an operator. P&WC recommends accomplishment based on operator's experience with prior configuration parts.

B6 Informational - For record purposes and/or to provide useful technical information or to support engine operation/maintenance/logistics.

SECTION 8

ROTOR COMPONENT SERVICE LIFE



Issued 26Jun15 ROTOR COMPONENT SERVICE LIFE.

Rotor component service life. 8.1.1 The information contained in this section is extracted from Pratt & Whitney Service Bulletin SB 1002 Revision 28, PWC MM Rev 30 chapter 72-00-00 & PWC SB 1703 Revision 6 8.1.2 The Table below will be updated in its entirety every time a new SB revision is issued, changes relating to components or time will be indicated by a black bar in the left hand margin on revision pages. Refer to latest revision of SB 1002 for latest requirements. 8.2 Effectively Applies to PT6A—114 / -114A series engines, 8.2.1 Description Engine rotating components listed in the timetable are subject to low-cycle fatigue due to cyclic operation of the engine. As a result, these parts must be replaced when their respective accumulated total cycle limit is reached. 8.2.2Techincal Records must record all flights, starts and accumulated total cycles (which must be calculated using the formula.) in the applicable logbook for each component. 8.2.3 The following is additional information for the Accumulated Total Cycle calculation: Start is defined as an engine start followed by one or more flights. 8.2.4 Aircraft operation often includes abbreviated engine cycles. The definition of an abbreviated cycle is: idle - takeoff - flight - landing - idle.

A normal or full cycle includes the foregoing plus an engine start and shutdown (i.e. abbreviated cycles are equivalent to the number of flights minus the number of starts).

The limits specified in the table below are in terms of full cycles. Accumulated abbreviated cycles are summated in terms of full cycles by means of a

formula and tabulated factors. A full cycle is defined as an engine start followed by one flight then shutdown. An abbreviated cycle is less severe than a full cycle. To benefit from this, an Abbreviated Cycle Factor (ACF) is listed in the table below, and used

in the formula which determines accumulated total cycles; Flight Count Factor is a multiplying factor that can be used to credit or debit life to the

components listed in the Life Service Tables to reflect the aircraft application of the engine. This factor can also be specific to an operator that diverges from the standards as missions.

8.2.5 When abbreviated cycles are not recorded, each flight is considered to have been preceded by one start, i.e., each flight is equivalent to a full cycle. 8.2.6 The same component (e.g. disk, Hub, Impeller, etc.) may be installed in different models, providing the part number is authorized to be installed in the specific engine models (Ref. applicable Service Bulletin). Operators transferring rotating components between engine models governed by different SBs must adhere to the lower of the LCF life limits published in the applicable SBs. 8.2.7 Turbine disk assemblies removed for repair must be suitably tagged, stating the total number of flights, engine starts and/or the calculated total cycles, per Paragraph 8.9.2. 8.2.8 Rotor components with lives greater than the limits shown in the table, or rotor components not supported with proper documentation are to be removed from service.




8.2.9 At repair and overhaul, component life is calculated in accordance with the following formula: Accumulated Total Cycles= No. Of Starts + No. of Flights - No. of Starts X Flight Count Factor

Abbreviated Cycle Factor 8.2.10. EXAMPLE: Part No. 3013111 (Hub 1st Stage) Abbreviated Cycle Factor 2 No. of Starts 9000 No. of Flights 9000 Flight Count Factor 1 Accumulated Total Cycles = 9000 + 9000 - 9000 X 1 2 = [9000 + 0] X 1 = 9000 8.3 Rotor Cycle Limit Time Table (derived from PWC SB1002R28)

Description Part Number

Model Abbr’d Cyc Fact

Flt Count Cycle Limit

Time

Hub Compressor (1st Stage)

3013111 -114 / -114A 2 1 19000

Disk Compressor (2nd Stage)

3011713 -114 / -114A 2 1 20000

Disk Compressor (3rd Stage)

3011713 -114 / -114A 2 1 25000

Impeller, Centrifugal

3013176 -114 2 1 19000 3027798 -114A 2 1 19000

Disk Compressor Turbine

3013411 -114 / -114A 5 1 16000

Disk Power Turbine

3026812 -114 / -114A 5 1 20000

** Items are additions to the Type Certificate holders’ recommendations




8.3.1. The above limits have been incorporated into the planning Winair programme. A complete description of how the system is managed and update refer to the MCM 8.4 Operating Times between Overhauls and Hot Section Inspection Frequency 8.4.1 The information contained in this section is extracted from Pratt & Whitney Service Bulletin SB 1703 Revision 6 8.4.2 The paragraphs below will be updated every time a new SB revision is issued, changes relating to components or time will be indicated by a black bar in the left hand margin on revision pages. Refer to latest revision of SB 1703 for latest requirements. 8.5 Effectivity Applies to PT6A-114 / -114A series engines. 8.6 Summary 8.6.1 This Table provides a recommended basic operating Time Between Overhaul (TBO) and specifies a recommended initial Hot Section Inspection (HSI) frequency. 8.6.2 P&WC turbine engines are required to undergo periodic inspection in accordance with a pre-established schedule in order to ensure serviceability. 8.6.3 The TBO and HSI intervals represent the two major scheduled periodic inspections, and are defined in this SB. 8.6.4 SB 1703 also provides TBO extension procedures for operators with an average utilization higher than 300 hours/year. 8.6.5 The technical content of this service bulletin has been reviewed by and is acceptable to Commissioner. 8.6.6 Description TBO recommendations take into consideration the average effect of the many variables affecting overhaul life, such as:

average flight duration; percentage of time at any given power level; climatic conditions and environment; maintenance practices; utilization; and engine modification standards.

8.6.7. Under extreme conditions of very low utilization, coupled with continuous operation in salt water atmosphere or heavy sand and dust environment, periodic inspections in accordance with the applicable maintenance instructions may indicate maintenance action prior to the recommended overhaul life. 8.6.8 The TBO interval may be extended with the approval of the KCAA. The minimum requirements for engine TBO extension or for fleet TBO extension are described in the Para. 3. Accomplishment Instructions. 8.6.9 The inspection intervals and overhaul periods provided in this table are the manufacturer’s recommendations. 8.6.10 KCAA normally requires operators to follow these recommendations unless alternative arrangements have been made between the operator and the manufacturer, and approved by the KCAA.




8.6.11 The rotor component life limitations of P&WC S.B. No.1002 override TBO considerations. 8.6.12 Engines that are within the basic recommended TBO and that have been maintained or stored per maintenance manual requirements have no related calendar time limits. 8.7 Basic Industry Time between Overhaul. (Extracted from PWC SB 1703R6) For all PT6A-114 and PT6A-114A engines is 3600 hours. 8.7.1 The basic TBO may be extended, subject to the approval of the KCAA 8.7.2 Engines that are within the basic recommended TBO and that have been maintained or stored per maintenance manual requirements have no related calendar time limits 8.7.3 The Hamilton Sundstrand fuel pump may be operated to the engine TBO (basic or extended, as applicable). 8.7.4 The engine accessories that follow may be operated to the engine TBO (basic or extended, as applicable) plus 500 hours.

FCU Fuel Heater Propeller Governor Ignition Exciter Compressor Bleed Valve Flow Divider Fuel Pump (Argo-Tech only)

8.7.5 Where accessories are removed for shop repair and subsequently reinstalled, operating time since new or overhaul must be recorded on the repair tag. 8.8 TBO Extension Recommendations Provisions for extensions are laid out in the latest revision of PWC SB 1703. 8.9. If the engine was put in storage or was unused for an extended period in the time since its last overhaul (or since new if not previously overhauled), there must be documented evidence that the engine has been preserved per the engine maintenance manual. 8.10 Hot Section Inspection (HSI) Frequency (extracted from PWC SB 1703R6) P&WC recommends doing the HSI within 50 EFH of the scheduled HSI interval. The HSI interval does not increase, as the TBO is extended. 8.10.1 The scheduled Hot Section Inspection interval is 1800 hours. (Extracted from PWC SB 1703R6)




8.10.2 Compressor Turbine Blade Maintenance Requirements (extracted from PWC SB 1703R6)

Component Part Number Frequency Inspection

CT Blades New condition

3045741-01 1800 hours *2 blade metallurgical analysis 3102401-01

3039901

CT Blades Overhaul condition

3045741-01 1800 hours *2 blade metallurgical analysis 3102401-01

3039901

CT Blades New condition

3045741-01 5000 hours Stretch Test 3102401-01

3039901

CT Blades Overhaul condition

3045741-01 3000 hours Stretch Test 3102401-01

3039901 *NOTE: This inspection must include Non Destructive Testing (NDT) and stretch measurement 8.10.3 Compressor Blades part number 3072791-01, installed in accordance with PWC SB 1669R6 are not required to undergo the maintenance requirements as laid out in the table 8.10.2

SECTION 9

KCAA REQUIREMENTS



Issued 26Jun15 KENYA CIVIL AVIATION AUTHORITY REQUIREMENTS

SECTION 9 KENYA CIVIL AVIATION AUTHORITY REQUIREMENTS Maintenance requirements required by the Kenya Civil Aviation Regulations 2013, as amended must be complied with at or before the required intervals. All KCAA requirements are listed below: Compass System SWING 1 YEAR Pitot System leak check & Calibration CHECK 1 YEAR Transponder functional CHECK 1 YEAR Radio Equipment CHECK 1 YEAR Weight and Balance REWEIGH 5 YEARS Fire Extinguisher Weight CHECK 1 YEAR

SECTION 10

DEFERRED DEFECTS



Issued 26Jun15 DEFERRED DEFECTS

10.1 Defects deferred in the field and maintenance (MCM Part 3 sec 1.4,2 & 9) The procedure for deferred defects is highlighted in the MCM Part 3 section 9.4.1 pg 32 – 33 and MCM Part 3 Sec 1.4.2

SECTION 11

SCHEDULED FINDINGS



Issued 26Jun15 SCHEDULED FINDINGS

SECTION 11 SCHEDULED FINDINGS (MCM Part 3 Section 15.2.5) 11.1.1 Introduction This involves those parts that have been deferred for future installation. These items have nothing to do with the airworthiness of the aircraft, and therefore not affected by the MEL, but form part of the Preventative Maintenance custom. 11.1.2 During Scheduled Maintenance at Base, or Line Maintenance in the field, there can be times when items are found to be worn, but still within maintenance manual limits, but through the good judgment and experience of maintenance staff, should be replaced before the item wears beyond limits, or become unserviceable while in the field. 11.1.3 Examples of these items are; torque link bushings, wheel bearing grease seals, nose gear lower Trunnion shims etc. If some item is noted as “wearing”, but not yet worn to limits, and is not available in the stores at that time, the item raised as scheduled finding and installed or replaced at a subsequent inspection in the future. 11.1.4 In order to keep track of these items and have a record of them, the scheduled finding will be raised and status placed as in progress (I/P) and will be cleared once the part(s) is received. 11.1.5 When the aircraft returns for maintenance, during his task of entering “carried over” items, these items under same scheduled work order is cleared. 11.1.6 Should the noted part not have been delivered to the stores at the time of the current inspection, the item is then able to be re-inspected by maintenance staff and noted for the next inspection.

SECTION 12

ALS DAILY AND WEEKLY INSPECTIONS



Issued 26Jun15 DAILY AND WEEKLY INSPECTIONS

12.0 Daily and weekly inspections 12.1 Daily Inspection.(MCM part 3 sec 12) The daily inspection is carried out by the maintenance engineer in the field and is intended to identify defects that may have occurred during the rotation of the day. 12.1.1 This inspection is in no way intended to preclude any part of the pre-flight inspection carried out by the flight crew. 12.1.2 The inspection is carried out on arrival or prior to departure. 12.1.3 The inspection is to be carried out visually, and requires no opening of access panels, other than the hinged engine cowls and the oil filler cap access panel. 12.1.4 Standing on the cockpit floor and hand on the cabin roof will provide sufficient height for visual inspection 12.1.5 The checklist is laid out in order to carry out a complete airframe inspection during a walk-around in clockwise direction in one circuit. 12.1.6 The checklist is read in a left to right reading order. 12.1.7 Fuselage Inspection Walk-around Check Perform a walk-around of the airframe in a clockwise direction beginning at the nose. Check the following for serviceability, damage, loose fasteners, security and leakage. Inlet cowl Oil cooler Nose gear assy Torque links NLG oleo Spring fairing Spring bushing

Windscreen Skin Door Windows Steps

Upper skin Fuel cap Bellcrank panel

Fairing boot Fairing Brake line

Tire Wheel rim Brake Pads Brake Disk Leading Edge Pitot Tube Lower skin Fuel Drains Lights Wing tip Nav / strobe Wing tip Aileron Trim Tab Static Wicks Flaps Lower skin Fuselage skin Windows Entry door up Steps Step Cables Fuselage skin Window Vertical Stab Leading edge VHF antenna HF antenna Horiz

Stabilizer Leading edge

Lower skin Elevator horn Elevator Trim Tab Static wicks Rudder skin Static wicks Beacon Light Tailcone Nav light Static wick Rudder Skin Elevator Trim tab Static Wicks Elevator horn Lower skin Leading edge Vertical stab VHF antenna Fuselage skin Window Cargo Door

upr Cargo Door lwr

Pull cable Windows Fuselage skin Flaps Lower skin Aileron Servo tab Static wicks Wing tip Nav strobe Leading edge Lower skin Lights Pitot tube Leading edge Lower skin Fuel drains Bellcrank

panel Fairing boot Fairing Brake line Tire Wheel rim Brake Pads Brake Disk Windows Door Steps Upper skin Fuel cap Windshield Fuselage skin Condenser gill END 12.2 Propeller Walk-around Inspection 12.2.1 Begin with one blade on and repeat the inspection for other blades. 12.2.3 Check for serviceability, damage, dents, nicks, tears, burns.




Propeller Walk-Around Check Spinner Spinner

screws Bulkhead Leading edge Forward Face Aft Face

Engine oil leak

Red Dye Leak Rotate Prop & listen for abnormal sounds or binding

12.3 Engine Walk-around Check 12.3.1 Engine Oil must be dipped within ten minutes of shutdown. If the level cannot be checked within ten minutes of shutdown, and level low on the dipstick, the engine must be motored and level rechecked prior to topping up. 12.3.2 Open both cowlings 12.3.3 Check for serviceability, leakage, loose connections. Engine Walk-around Open Cowl Accessory

Gearbox AGB drains Wiring Harness Control Linkages

Standby Alt Inertial Separator Oil Tubes Fuel Lines Ducts Starter Generator Aircon pump Close cowl Latch Catches Shim damper 12.4 Daily Inspection Checklist Pocket Edition: (Printed for the Field Engineer)

FUSELAGE INSPECTION WALK AROUND IN CLOCKWISE DIRECTION Inlet cowl Oil cooler Nose gear assy Torque links NLG oleo Spring fairing Spring bushing

Windscreen Skin Door Windows Steps

Upper skin Fuel cap Bellcrank panel

Fairing boot Fairing Brake line

Tire Wheel rim Brake Pads Brake Disk Leading Edge Pitot Tube Lower skin Fuel Drains Lights Wing tip Nav / strobe Wing tip Aileron Trim Tab Static Wicks Flaps Lower skin Fuselage skin Windows Entry door up Steps Step Cables Fuselage skin Window Vertical Stab Leading edge VHF antenna HF antenna Horiz

Stabilizer Leading edge

Lower skin Elevator horn Elevator Trim Tab Static wicks Rudder skin Static wicks Beacon Light Tailcone Nav light Static wick Rudder Skin Elevator Trim tab Static Wicks Elevator horn Lower skin Leading edge Vertical stab VHF antenna Fuselage skin Window Cargo Door

upr Cargo Door lwr

Pull cable Windows Fuselage skin Flaps Lower skin Aileron Servo tab Static wicks Wing tip Nav strobe Leading edge Lower skin Lights Pitot tube Leading edge Lower skin Fuel drains Bellcrank

panel Fairing boot Fairing Brake line Tire Wheel rim Brake Pads Brake Disk Windows Door Steps Upper skin Fuel cap Windshield Fuselage skin Condenser gill END




ALS 208B DAILY INSPECTION GUIDE 12.4 Daily Inspection Checklist Pocket Edition: (Printed for the Field Engineer) NB: Ensure each item inspected is ticked and append signature on the Right Side of each row FUSELAGE INSPECTION WALK AROUND IN CLOCKWISE DIRECTION

SIGNATURE Inlet cowl Oil cooler Nose gear assy Torque links NLG oleo Spring fairing

Spring bushing Windscreen Skin Door Windows Steps Upper skin Fuel cap Bellcrank panel Fairing boot Fairing Brake line

Tire Wheel rim Brake Pads Brake Disk Leading Edge Pitot Tube Tire pressure LH......psi RH.....psi Nose....psi Lower skin Fuel Drains Lights Wing tip Nav / strobe Wing tip

Aileron Trim Tab Static Wicks Flaps Lower skin Fuselage skin Windows Entry door up Steps Step Cables Fuselage skin Window

Vertical Stab Leading edge VHF antenna HF antenna Horiz Stabilizer Leading edge Lower skin Elevator horn Elevator Trim Tab Static wicks Rudder skin Static wicks Beacon Light Tailcone Nav light Static wick Rudder Skin

Elevator Trim tab Static Wicks Elevator horn Lower skin Leading edge Vertical stab VHF antenna Fuselage skin Window Cargo Door upper Cargo Door lower

Pull cable Windows Fuselage skin Flaps Lower skin Aileron Servo tab Static wicks Wing tip Nav strobe Leading edge Lower skin

Lights Pitot tube Leading edge Lower skin Fuel drains Bellcrank panel Fairing boot Fairing Brake line Tire Wheel rim Brake Pads Brake Disk Windows Door Steps Upper skin Fuel cap Windshield Fuselage skin Condenser gill Oil level ........................... END

Engine Walk-around SIGNATURE

Open Cowl Accessory Gearbox AGB drains Wiring Harness Control Linkages Standby Alt Inertial Separator Oil Tubes Fuel Lines Ducts

Starter Generator Aircon pump Close cowl Latch Catches Shim damper Propeller Walk-Around Check

SIGNATURE Spinner Spinner screws Bulkhead Leading edge Forward Face Aft Face

Engine oil leak Red Dye Leak Rotate Prop & listen for abnormal sounds or binding

FINDINGS RECTIFICATION

1.

2.

3.

4.

5. N/B FINDINGS SHOULD BE TRANSFERRED TO

WPACK AND ADDRESSED IMMEDIATELY

Aircraft Registration Engineer / Technician Date of inspection. Were any defects found during this inspection or during the weeks daily inspections yes no

Was maintenance base informed of the findings? Yes No




12.5 Weekly Inspection. The weekly inspection is carried out by the maintenance engineer in the field and is intended to identify defects that may have occurred during the week, in areas that are not covered during the daily inspection. This inspection is in no way intended to preclude any part of the pre-flight inspection carried out by the flight crew. The inspection is carried out on arrival or prior to departure. The inspection is to be carried out visually, and requires minimal opening of access panels, and the hinged engine cowls and the oil filler cap access panel. This inspection should be carried out in addition to the daily walk-around. 12.5.1 Inspection Requirements: Engine

Area Inspection Tick

Externals

All accessible connections, clamps and brackets for attachment Chafing, cracks and corrosion Rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings Examine the rod ball for corrosion, roughness in rotation, side play and radial play.

Examine rod end for corrosion, roughness in rotation, side play and radial play Check free movement of linkage

Air Inlet Inspect air inlet screen for cleanliness GG Case Surfaces, and fire-seal mount ring brackets for cracks, distortion, and

corrosion

Exhaust Duct Cracks and distortion Accessories Attachment and linkages, air, oil and fuel lines

Fuel System

Check fuel pump for installation and leaks Check drain valve(s) for installation and leaks Check FCU for installation, linkages and pneumatic lines Evidence of FCU bearing washout indicated by traces of blue dye

Ignition System Check ignition cables for chafing, wear and installation

12.5.2 Inspection Requirements: Airframe


Landing Gears

Wipe exposed oleo struts with rag moistened in hydraulic oil Check tire pressures Record tire pressures (Nose……………psi L/H main…………psi R/H main………..psi

Check brake hydraulic fluid level Gear rubber fairings

Interior

Passenger Seats for cleanliness and serviceability Crew Seats for cleanliness and serviceability Oxygen cylinder gauge pressure Cleanliness of cabin area Cleanliness of cockpit area First Aid Kit Seal Survival Equipment Seal

Lights Check operation of all exterior lighting

Wings Check operation of flaps, ensure smooth travels and no unusual noise Check operation of fuel cap latches

Keep Battery use to minimum during the light and flap ops checks. Low battery will result in hot starting! This checklist is to be signed on a weekly basis and filed in the outstation office.




12.6 Weekly Checklist Engines


Externals

All accessible connections, clamps and brackets for attachmentChafing, cracks and corrosion Rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings

Examine the rod ball for corrosion, roughness in rotation, side play and radial play.

Examine rod end for corrosion, roughness in rotation, side play and radial play

Check free movement of linkage Air Inlet Inspect air inlet screen for cleanliness

GG Case Surfaces, and fire-seal mount ring brackets for cracks, distortion, and corrosion


Fuel System


Ignition System

Check ignition cables for chafing, wear and installation

Airframe Area Inspection Tick

Landing Gears

Wipe exposed oleo struts with rag moistened in hydraulic oil Check tire pressures Check brake hydraulic fluid level Gear rubber fairings

Interior




Keep Battery use to minimum during the light and flap ops checks. Low battery will result in hot starting!

Aircraft Registration Engineer / Technician Date of inspection. Were any defects found during this inspection or during the weeks daily inspections yes no Was maintenance base informed of the findings? Yes No Findings:

a. …………………………………………………………………………….……………………

b. ………………………………………………………………………………….………………

c. ……………………………………………………………………………………………………………………………………………………………………………………………………

SECTION 13

SUPPLEMENTAL INSPECTIONS



Issued 26Jun15 SUPPLEMENTAL INSPECTION DOCUMENT

13.1 INTRODUCTION The Supplemental Structural Inspection Program for the Cessna Models 208 and 208B airplane is a result of the Models 208 and 208B airplane's current usage and state-of-the-art analysis, testing and inspection methods. Analysis methods include durability, fatigue, and damage tolerance assessments. The Supplemental Structural Inspection Program was made with the combined efforts of Cessna Aircraft Company and Model 208 and 208B operators. The inspection program is the current structural maintenance inspection, plus supplemental inspections for continued airworthiness of the airplane as years of service are collected. The primary function of the Supplemental Structural Inspection Program is to find fatigue damage which will increase with time. In addition to the supplemental inspections, a Corrosion Prevention and Control Program (CPCP) to prevent or control corrosion that can have an effect on the continued airworthiness of the airplane, was started. The Supplemental Structural Inspection Program is valid for airplanes with less than 50,000 hours. Beyond this the continued airworthiness of the airplane can no longer be assured. Retirement of the airframe is recommended when 50,000 flight hours have been accumulated. 13.2 Function The function of the Supplemental Structural Inspection Program is to find damage from fatigue, overload or corrosion through the use of the Nondestructive Inspections (NDI), and visual inspections. This Supplemental Inspection Document (SID) is only for primary and secondary airframe components. Engine, electrical items and primary and secondary systems are not included in this document. A list is included to show the requirements for the SID program for primary and secondary airframe components. The airplane maintenance agrees with Cessna's recommendations or the equivalent. If the SID is for a specific part or component, you must examine and evaluate the surrounding area of the parts and equipment. If problems are found outside these areas, report them to Cessna Aircraft Company on a reporting form. Changes can then be made to SID program, if necessary. The SID inspections are for all Cessna Models 208 and 208B airplanes. The inspection intervals are for unmodified airplanes, and represent the maximum approved inspection times. On airplanes that changed the airplane design, gross weight, or airplane performance, it can be necessary to do inspections more frequently. Examples of some Supplemental Type Certification (STC) installations, which will require modified inspection intervals, include vortex generators and non-standard engines. The owner or the maintenance organization should contact the STC holder(s) or modification originator to get new FAA approved inspection information.




PRINCIPAL STRUCTURAL ELEMENTS DESCRIPTION An airplane component is classified as a Principal Structural Element (PSE) if:

The component contributes significantly to carrying flight and ground loads. And, if the component fails, it can result in a catastrophic failure of the airframe.

The monitoring of these PSEs is the main focus of this Supplemental Structural Inspection Program. Table 1. Typical Examples of Principal Structural Elements (PSEs)

Wing and Empennage

Control surfaces, flaps and their mechanical systems and attachments (hinges, tracks and fittings) Primary fittings Principal splices Skin or reinforcement around cutouts or discontinuities Skin-stringer combinations Spar caps Spar webs

Fuselage

Circumferential frames and adjacent skin Door frames Pilot window posts Bulkheads Skin and single frame or stiffener element around a cutout Skin or skin splices, under circumferential loads Skin or skin splices, under fore-and-aft loads Window frames Door skins, frames and latches

Landing Gear and their Attachments Engine Support Structure and Mounts 13.5 CLASSIFICATION FOR TYPES OF OPERATION

I. To find the frequency of inspections, first find the total number of hours and the total number of landings on the airplane, then find an average flight length over the life of the airplane, whichever is less.

AVERAGE FLIGHT PATH

OR

Number of Flight _____ Hours ____

Number of Landings = Average Flight Length

II. If the average flight length is less than or equal to 35 minutes, then use the Severe Flight

Profile for inspections.

III. For airplanes with an average flight length greater than 35 minutes you must determine the severity of the operating environment. If the airplane operates thirty percent or more of its flight time in severe environments, you must use the severe operation inspection times found in section 4-10-01-Severe Operation Inspection and 5-14-00-Listing of Supplemental

Number of Flight _____ Hours ____ Number of Flights

= Average Flight Length




Inspections. Examples of severe environments would include flight operations at low altitude (i.e., less than 5,000 ft. above ground level) such as pipeline patrol, sight-seeing, training flights, traversing mountainous terrain or flying near coastal areas identified in section 51-11-00, Corrosion Severity Maps - Description and Operation.

IV. Airplanes operated in all other environmental conditions will use the typical operation

inspection times found in 4-10-00-Typical Inspection Time Limits and 5-14-00-Listing of Supplemental Inspections.

V. Make an airplane logbook entry that gives the applicable inspection schedule after it has been found.

13.6. REPORTING – COMMUNICATIONS DISCREPANCIES

For the SID to continue to stay applicable, it is necessary to have a free flow of information between the operator, the FAA and Cessna Aircraft Company. The important information about the inspection results, repairs and modifications done must be supplied to Cessna Aircraft Company to let the effect of the recommended inspection procedures and inspection intervals to be calculated. Also, the operator's inspections and reports can find items not included in the SID before. These items will be examined by Cessna Aircraft Company and will be added to the SID for all of the operators, if applicable. Cessna Propeller Aircraft Product Support has a system to collect the reports. The applicable forms are included in this document. Copies of these forms are also available from a Cessna Service Station or Cessna Field Service Engineer. Discrepancy Reporting Discrepancy reporting is very important to let the inspection start times and repeat times be adjusted as well as to add or remove PSEs. It can be possible to make the inspection methods, repairs, and modifications better for the PSEs from the reported data All cracks, multiple cut off fasteners, and corrosion found during the inspection must be reported to Cessna Aircraft Company within ten days. The PSE inspection results are to be reported on a form as shown on the pages that follow.




DISCREPANCY REPORT

Send all available data, which includes forms, repairs, photographs, sketches, etc., to:

Cessna Aircraft Company Attn: SID Program Technical Support Services Dept. 751 Wichita, KS 67277 USA 316-942-9006

NOTE: This system does not replace the normal channels to send information for items not included in the SID. Cessna Aircraft Company Follow-Up Action All SID reports will be examined to find if any of the steps are necessary:

I. Complete a check of the effect on the structural or operational condition. II. Complete a check of other high-time airplanes to find if a service bulletin shall be issued.

III. Find if a reinforcement is required. IV. Change the SID if required.




INSPECTION METHODS

Selection of inspection method A very important part of the SID program is to select and evaluate the state-of-the-art nondestructive inspection (NDI) methods applicable to each PSE, and to find a minimum detectable crack length. The selection of NDI method uses cracks direction, location, part thickness and access as criteria. The size of the inspection task, human factors (such as qualifications of the inspection), equipment used, and access will effect an inspection. Visual, radiographic, liquid penetrant, eddy current and magnetic particle methods are used. A complete description of each of these methods is given in the Model 208 Nondestructive Testing Manual.

13.8 APPLICABILITY/LIMITATIONS

a) This SID is applicable to the Models 208 and 208B airplanes.

b) STC Installations

I. The Cessna Models 208 and 208B airplanes can have modifications that were done by STCs by other organizations without Cessna Engineering approval. The inspection intervals given in this SID are for unchanged airplanes, and are the maximum approved inspection times

II. On airplanes that changed the airplane design, gross weight, or airplane performance, it can be necessary to do inspections more frequently.

Examples of common STCs not applicable in this SID document include vortex generators and non-standard engines. The owner and/or maintenance organization must contact the STC holder(s) or modification originator to get new FAA approved inspection requirements.

III. The SID inspection times use total airframe hours/landings in service. If a specific airframe component has been replaced, the component is examined for the total component hours/landings requirements. However, any attachment structure that was not replaced when the component was replaced must be examined and use the total airframe hour/landings requirements.

13.8 PSE Details

Details This section contains the important instructions selected by the rationale process described in Section 2-Principal Structural Elements. These items are considered important for continued airworthiness of the Cessna Models 208 and 208B airplane. Service Information Letters and Service Bulletins about the PSEs are available from Cessna Aircraft Company. A summary of the PSEs is presented in the 5-14-00-Listing of Supplemental Inspections. This can be used as a checklist by the operators. A summary of the inspections by flight hours is also given.




13.9 LISTING ON SUPPLEMENTAL INSPECTIONS 5-14-00 Supplemental Inspection Procedures Each of the Supplemental Inspections listed in this section are now incorporated into Task based inspections. This document provides a cross reference between the Supplemental Inspections. The Supplemental Inspection Number corresponds to the section of the Model 208 Nondestructive Testing Manual section number and is also referenced in the tasks. Each supplemental inspection is assigned an independent item code in Chapter 5 of the Maintenance Manual and Task number in the applicable ATA chapters. The item codes are in Chapter 5, Inspection Time Limits, of the Maintenance Manual and in the Inspection Documents. The item codes for the supplemental inspections below have not changed but for editorial reasons, the letter A was added. Inspections that are also necessary for Chapter 4, Airworthiness Limitations, are done at intervals that start with M to help you keep records. The intervals for these inspections are specified in Chapter 4 of the Maintenance Manual. It is necessary to complete the Chapter 4 inspections on or before the specified interval. Chapter 4 inspections do not have a grace period Note: The CPCPs were incorporated into the tasks and incorporated into the task-based program Supplemental Inspections to Task Matrix Supplemental Inspection Time-Table (extracted from Cessna Maintenance Manual Rev 28 Chapter 5-14-00) Task Inspection to SID

DETAILS FOUND IN TASK

SUPPLEMENTAL INSPECTION NUMBER

INSPECTION COMPLIANCE TITLE

INSPECTION DOCUMENT

ITEM CODE

Task 32-10-00-240

32-10-01 Main Landing Gear Axle Special Detailed Inspection

05-15-MB A321005

Task 53-10-00-250

53-10-01 Fuselage Engine Mount Fittings Special Detailed Inspection

05-15-13 A531008

Task 53-10-00-251

53-20-01 Cargo and Passenger Door Doublers Special Detailed Inspection

05-15-15 A532003

Task 53-20-07-250

53-20-07 Fuselage to Strut Attach Fitting Lugs (Nominal Standard Bolt Size) (Typical Inspection Compliance) Special Detailed Inspection

05-15-MH A531005

Task 53-20-07-251

53-20-07 Fuselage to Strut Attach Fitting Lugs (Nominal Standard Bolt Size) (Severe Inspection Compliance) Special Detailed Inspection (Part Number S3461-74)

05-15-MG A531006




Task 53-20-07-252

53-20-07 Fuselage to Strut Attach Fitting Lugs (Oversize 1/64 - Inch Bolt Size) (Severe Inspection Compliance) Special Detailed Inspection (Part Number S3461-159)

05-15-MI A531010

Task 53-20-07-253

53-20-07 Fuselage to Strut Attach Fitting Lugs (Oversize 1/32- Inch Bolt Size) (Severe Inspection Compliance) Special Detailed Inspection (Part Number S3461-160)

05-15-MJ A531011

Task 53-10-00-253

53-20-03 Lower Forward Carry-Thru Bulkhead Special Detailed Inspection

05-15-16 A532004

Task 53-10-00-254

53-20-04 Main Landing Gear Fitting Special Detailed Inspection

05-15-19 A532005

Task 53-10-00-255

53-20-05 Main Landing Gear Attach Fittings and Aft Carry-Thru Bulkhead

05-15-16 A532006

Task 53-10-00-252

53-20-02 Fuselage to Wing Attach Fitting Lugs Special Detailed Inspection

05-15-MF A532007

Task 53-10-00-223

53-20-11 Firewall Brace and Doubler Assemblies Detailed Inspection

05-15-13 A532008

Task 53-10-00-220

53-20-08 Carry-Through Root Rib Detailed Inspection

05-15-13 A532009

Task 53-10-00-221

53-20-09 Crew Door Frames Detailed Inspection

05-15-13 A532011

Task 53-10-00-222

53-20-10 Passenger and Cargo Door Frames Detailed Inspection

05-15-13 A532012

Task 53-25-00-220

53-10-07 Seat Rails and Attachment Structure Detailed Inspection

05-15-15 A531009

Task 53-25-00-221

53-20-12 Bulkheads and Stiffeners Below the Seat Rail Attachments at FS 143.00 and FS 158.00 Detailed Inspection

05-15-15 A532013

Task 53-10-00-224

53-20-13 Stringers at Intersections with Forward and Aft Carry - Thru Bulkheads Detailed Inspection

05-15-16 A532014

Task 53-10-00-225

53-20-14 Fuselage Skin Doubler at Main Landing Gear Cutout Detailed Inspection

05-15-14 A532015

Task 53-10-00-257

53-50-01 Fuselage to Horizontal Stabilizer Attach Fittings Special Detailed Inspection

05-15-13 A535001




Task 53-10-00-258

53-50-02 Vertical Stabilizer Attach Points Special Detailed Inspection (Typical Inspection Compliance)

05-15-13 A535002

Task 53-10-00-259

53-50-02 Vertical Stabilizer Attach Points Special Detailed Inspection (Severe Inspection Compliance)

05-15-17 A535003

Task 55-10-00-250

55-10-01 Horizontal Stabilizer Forward and Aft Attach Points Special Detailed Inspection

05-15-13 A551003

Task 55-10-00-251

55-10-02 Horizontal Stabilizer Spars Special Detailed Inspection (Typical Inspection Compliance)

05-15-13 A553004

Task 55-10-00-252

55-10-02 Horizontal Stabilizer Spars Special Detailed Inspection (Severe Inspection Compliance)

05-15-18 A551005

Task 53-10-00-256

53-20-06 Fuselage to Wing Carry-Thru Attach Fitting and Bulkhead Special Detailed Inspection

05-15-16 A532016

Task 55-30-00-250

55-30-01 Vertical Stabilizer Spars Special Detailed Inspection (Typical Inspection Compliance)

05-15-13 A553001

Task 55-30-00-251

55-30-01 Vertical Stabilizer Spars Special Detailed Inspection (Severe Inspection Compliance)

05-15-17 A553002

Task 56-00-01-220

56-30-01 Windshield and Attachment Structure Detailed Inspection

05-15-13 A564002

Task 57-10-00-250

57-20-01 Wing to Carry - Thru Front Spar Attachment Fittings Special Detailed Inspection

05-15-MF A570013

Task 57-10-00-251

57-20-01 Wing to Carry - Thru Rear Spar Attachment Fittings Special Detailed Inspection

05-15-MF A570014

Task 57-10-00-252

57-20-02 Front Spar Lower Cap Inboard of WS 141.20 Special Detailed Inspection

05-15-MF A570010

Task 57-10-00-253

57-20-03 Rear Spar Lower Cap Inboard of WS 141.20 Special Detailed Inspection

05-15-MF A570011

Task 57-10-00-254

57-50-01 Center Flap Track and Inboard Flap Track Special Detailed Inspection

05-15-MD A575002

Task 57-10-00-255

57-50-01 Outboard Flap Track Special Detailed Inspection

05-15-MD A575003

Task 57-10-01- 57-60-01 Wing Strut Fittings Special 05-15-MA A570008




250 Detailed Inspection (Typical Inspection Compliance)

Task 57-10-01-251

57-60-01 Wing Strut Fittings Special Detailed Inspection (Severe Inspection Compliance)

05-15-ME A570009

Task 57-10-01-252

57-60-02 Wing Strut Attachment to Front Spar Special Detailed Inspection (Typical Inspection Compliance)

05-15-MF A570012

Task 57-10-01-253

57-60-02 Wing Strut Attachment to Front Spar Special Detailed Inspection (Nominal/Standard Bolt Size) (Severe Inspection Compliance) (Part Number S3461-77)

05-15-MF A570015

Task 57-10-01-254

57-60-02 Wing Strut Attachment to Front Spar Special Detailed Inspection (1/64 Inch Oversize Bolt Size) (Severe Inspection Compliance) (Part Number S3461-163)

05-15-MK A570016

Task 57-10-01-255

57-60-02 Wing Strut Attachment to Front Spar Special Detailed Inspection (1/32 Inch Oversize Bolt Size) (Severe Inspection Compliance) (Part Number S3461-164)

05-15-ML A570017

Task 71-20-00-240

71-20-01 Engine Truss and Ring Assembly Special Detailed Inspection

05-15-13 A712003

SECTION 14

RELIABILITY PROGRAM INSPECTIONS



PROGRAMME Page 1

Issued 26Jun15

SECTION 14 ALS RELIABILITY PROGRAM INSPECTIONS. Through the Reliability Program, manufacturers and KCAA recommendations and experience from our operations that require new inspections to be incorporated, ALS will add these inspections into the maintenance programme tracking system.

SECTION 15

UNSCHEDULED MAINTENANCE CHECKS



PROGRAMME Page 1

Issued 26Jun15

SECTION 15 UNSCHEDULED MAINTENANCE CHECKS (Extracted from Section 5-50-00 of Cessna Maintenance Manual) This section has the inspections and checks which can be required because of special or unusual circumstances and do not have regular repeated intervals to be done. General During operation, the airplane may be subjected to:

Hard landings. Over-speed. Severe air turbulence or severe manoeuvres. Towing with a large fuel unbalance or high drag/side loads due to ground

handling. Lightning Strike.

When any of these conditions are reported by the flight crew, a visual inspection of the airframe and specific inspections of components and areas involved must be accomplished. The inspections are performed to determine and evaluate the extent of damage in local areas of visible damage, and to the structure and components adjacent to the area of damage. If foreign object damage is encountered (suspected or actual), a visual inspection of the airplane must be accomplished before airplane is returned to service. 15.1 Unscheduled Maintenance Checks Defined Hard/Overweight Landings A hard landing is any landing made at what is believed to be an excessive sink rate. Closely related to hard landings, is an overweight landing, which is defined as landing the airplane at any gross weight which exceeds maximum gross landing weight as specified in the KCAA Approved Pilot's Operating Handbook. NOTE: If the hard/overweight landing is combined with high drag/side loads, additional checks are required. Overspeed Any time an airplane has exceeded one or both of the following:

Airplane overspeed exceeding placard speed limits of flaps. Airplane overspeed exceeding design speeds.

Airplanes equipped with an airspeed exceedence device capable of recording an airspeed exceedence with accompanying time duration:

For a recorded airspeed above 175 knots in smooth air, with duration greater than 5 seconds; or any airspeed above 181 knots, perform the specified overspeed inspection.

Severe air turbulence or severe manoeuvres May be defined as atmospheric conditions producing violent buffeting of airplane. Severe manoeuvres can be defined as any manoeuvres exceeding Pilot's Operating Handbook and KCAA Approved Airplane Flight Manual limits. Lightning strike If flown through an electrically stressed region of the atmosphere where electrical discharges are transferred from cloud to cloud and from cloud to earth, the airplane may become a part of this discharge path.



PROGRAMME Page 2

Issued 26Jun15

During a lightning strike, the current enters the airplane at one point and exits at another, usually at opposite extremities. The wing tips, nose and tail sections are the areas where damage is most likely to occur. Burning and/or eroding of small surface areas of the skin and structure may be detected during inspection. In most cases, the damage is obvious. In some cases, however, hidden damage may result. The purpose of the lightning strike inspection is to locate any damage that may have occurred to the airplane before returning it to service. Foreign object damage Damage to the airplane engine may be caused by the ingestion of slush, by a bird strike or by any other foreign object while operating the airplane on the ground or in normal flight. Damage may also be caused by tools, bolts, nuts, washers, rivets, rags or pieces of safety-wire left in the engine inlet duct during maintenance operations. The purpose of the foreign object damage inspection is to locate any damage prior to repairing or returning the airplane to service. Safety precautions should be taken to prevent foreign objects from coming in contact with the airplane during towing and at all times when airplane is not in service. To prevent dirt and foreign objects damage, the engines should be provided with suitable covers. When there are wind and dust conditions, the covers should be installed as soon as practicable following engine shutdown and engine cooling. The aerodynamic cleanliness level (degree of surface smoothness), contributes to performance capabilities of the airplane. It is important that the high cleanliness level be maintained. Contour and waviness distortion of the aerodynamic surface may be developed in the course of normal operation or by improper handling during maintenance operations. Doors and access panels are susceptible to waviness through rough handling. Care should be exercised in the handling of these items. High drag/side loads due to ground handling. High drag/side load condition shall be defined to exist whenever the airplane skids or overruns from the prepared surface onto an unprepared surface, or landings short of prepared surface, or makes a landing which involves the blowing of tires or skids on a runway to the extent that the safety of the airplane was in question. This covers takeoff and landings or unusual taxi conditions. 15.2 Unscheduled Inspection Check Table (Extracted from Cessna MM Rev 28 chapter 5-50-00)



PROGRAMME Page 3

Issued 26Jun15

Hard/Overweight Landings

Area Inspections

Landing gear

Main gear struts - Inspect for security of attachment and permanent set. Main gear attachments and supporting structure - Inspect for security, loose or failed fasteners, and any evidence of structural damage Main gear spring - Inspect for gear spread or wing low Nose gear trunnion supports and attaching structure - Inspect for security, loose or failed fasteners, and any evidence of structural damage Nose gear attachments and supporting structure - Inspect for security, loose or failed fasteners, and any evidence of structural damage

Wings

Wing surface and lift strut - Inspect for skin buckles, loose or failed fasteners, and security of attach fittings and fuel leaks Trailing edge - Inspect for any deformation affecting normal flap operation.

Overspeed

Fuselage

Windshield and Windows - Inspect for buckling, dents, loose or failed fasteners, and any evidence of structural damage All hinged doors - Inspect hinges, hinge attach points, latches and attachments, and skins for deformation and evidence of structural damage

Cowling Skins-Inspect for buckling, cracks, loose or failed fasteners, and indications of structural damage.

Stabilizers Stabilizers - Inspect skins, hinges and attachments, movable surfaces, mass balance weights, and attaching structure for cracks, dents, buckling, loose or failed fasteners, and evidence of structural damage

Wings

Flaps - Inspect for skin buckling, cracks, loose or failed fasteners, attachments and structure for damage Fillets and fairings- Inspect for buckling, dents, cracks, and loose or failed fasteners

Severe air turbulence or severe manoeuvres

Stabilizers

Horizontal stabilizer hinge fittings, actuator fittings and stabilizer centre section - Inspect for security, loose or failed fasteners, and any evidence of structural damage Vertical stabilizer - Inspect for evidence of structural damage, skin buckles and security at primary attachments in tail-cone, loose or failed fasteners, damage to hinges and actuator fittings. Elevator and rudder balance weight supporting structure - Inspect for security, loose or failed fasteners, and evidence of structural damage.

Wing

Wing to body strut fittings and supporting structure - Inspect for security, loose or failed fasteners, and evidence of structural damage Trailing Edge - Inspect for any deformation affecting normal operation of flap and aileron

High drag/side loads due to ground handling check

Landing gear

Main gear and fairings - Inspect for loose or failed fasteners, buckling, security, cracks and evidence of structural damage Nose gear and fairing - Inspect for loose or failed fasteners, cracks, steering cables tension, security, buckling and evidence of structural damage

Wings Wing to fuselage attach fittings and attaching structure - Inspect for security, loose or failed fasteners and evidence of structural failure



PROGRAMME Page 4

Issued 26Jun15

Lightning strike check

Area Inspections As the following checks are performed, complete the lightning strike/Static Discharge Incident Reporting Form. The completed form must be mailed to: Cessna Contract Services P.O.BOX 7706, Wichita, KS 67277 Attn: Manager Contract Services

Communications Antennas - Inspect all antennas for evidence of burning or eroding. If damage is noted, perform functional check of affected system.

Navigation

Radar reflector, feed horn, motor box assembly and mounting structure-Inspect for damage. If damage is noted, perform a bench check of system. If superficial pitting or burning of mount structure only is noted, perform a functional check of radar system.Glide-slope antenna - Inspect for burning and pitting. If damage is noted, perform a functional check of glide-slope system. Compass - Compass should be considered serviceable if the corrected heading is within plus or minus 10 degrees of heading indicated by the remote compass system. If remote compass is not within tolerance, remove, repair or replace

Lightning strike check-Contd: Area Inspections

Fuselage Skin - Inspect surface of fuselage skin for evidence of damage. Tailcone - Inspect tail-cone and static dischargers for damage

Stabilizers Inspect surfaces of stabilizers for evidence of damage

Wings

Skins - Inspect for evidence of burning and eroding Wing tips - Inspect for evidence of burning and pitting Flight surfaces and hinging mechanisms - Inspect for burning and pitting Radome - Inspect for evidence of burning or eroding

Propeller Propeller- Remove from service and have inspected at an authorized repair station

Power plant Engine - Refer to engine manufacturer's overhaul manual for inspection procedures

Foreign object damage check

Landing gear Fairings - Inspect for dents, cracks, misalignment, and indication of structural damage

Fuselage Skin - Inspect forward and belly areas for dents, punctures, cracks, and any evidence of damage

Cowling Skins - Inspect for dents, punctures, loose or failed fasteners, cracks or indications of structural damage

Stabilizers Leading edge skins - Inspect for dents, cracks, scratches, and any evidence of structural damage Surface de-ice boots - Inspect for cuts, punctures, or tears

Windows Windshield - Inspect for chipping, scratches, and cracks

Wings Leading edge skins - Inspect for dents, cracks, punctures, and evidence of possible structural damage Radome - Inspect for dents, cracks, punctures, scratches, etc

Surface de-ice boots - Inspect for cuts, punctures, or tears. Engine Air inlet section - Inspect for dents, cracks, scratches, punctures, blood and

feathers Propeller Inspect for nicked, bent, broken, cracked, or rubbing blades



PROGRAMME Page 5

Issued 26Jun15

High drag/side loads due to ground handling. Landi

ng gear. Main gear and fairings - Inspect for loose or failed fasteners, buckling, security, cracks, and evidence of structural damage. Nose gear and fairing - Inspect for loose or failed fasteners, cracks, steering cables tension, security, buckling, and evidence of structural damage

Wings Wing to fuselage attach fittings and attaching structure - Inspect for security, loose or failed fasteners, and evidence of structural failure.



PROGRAMME Page 6

Issued 26Jun15

SECTION 16

CONTINUOUS INSPECTION PROGRAM

TASK BASED CHECK SHEETS


Revision 000 C208B AIRCRAFT MAINTENANCE PROGRAMME Page 1

Issued 26Jun15 CONTINUOUS INSPECTION PROGRAMME













Print Date: Thu Jul 02 16:02:53 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-03(Rev 28)

© 2015 Cessna Aircraft CompanyRetain printed data for historical reference only. For future maintenance, use only current data. Page 1

INSPECTION DOCUMENT 03

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Inspection Document 03 gives a list of item(s), which are completed every 48 calendar months.

B. Inspection items are given in the sequence of the zone in which the inspection is completed. Adescription of the inspection, as well as the Item Code Number are supplied for cross-reference tosection 5-10-01. Frequently, tasks give more information about each inspection. These tasks arefound in the individual chapters of this manual.

C. The right portion of each page gives space for the mechanic's and inspector's initials and remarks.You can use copies of these pages as a checklist while you complete the tasks in this InspectionDocument.

2. General Inspection Criteria

A. As you complete each of the inspection tasks in this Inspection Document, examine the adjacentarea while access is available to find conditions that need more maintenance.

B. If it is necessary to replace a component or to make a change to a system while you complete atask, do the task again before the system or component is returned to service.

C. Inspection Kits are available for some Inspection Documents. They supply consumable materialsused to complete the inspection item(s) given for the interval. Refer to the Model 208 IllustratedParts Catalog, Introduction, Service Kit List to find applicable part numbers.

ITEM CODENUMBER

TASK ZONE MECH IN-SP

REMARKS

A281003 Fuel Storage SystemDetailed Inspection Task 28-10-01-221

521 621

A321003 Center-Spring and Main Gear-Spring Interface AreaSpecial Detailed (Corrosion Inspection and Repair) Task32-10-00-221

721 722

A322003 Drag Link Forward Support General Visual Inspection.(Airplanes 20800553 and On and 208B5076 and On)Task 32-20-00-211

701

A531003 Internal Cockpit Zonal Inspection Task 53-10-00-211 211 212213 214215 216217 218231 232233 234



ITEM CODENUMBER


REMARKS

A531007 Internal Tail Cone Zonal Inspection Task 53-10-00-213 311 312320 330

A571001 Wing Zonal Inspection Task 57-10-00-210 500 600

*** End of Inspection Document 03 Inspection Items ***




Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

A255201 Cargo Pod Zonal Inspection Task 25-52-00-210 901 902903 904905 906

B262005 Portable Fire Extinguisher Restoration (Internal Inspec-tion) Task 26-20-00-290

215 216251 252

A531001 External Fuselage Zonal Inspection Task 53-10-00-210 ALL

A531004 Internal Cabin Zonal Inspection Task 53-10-00-212 251 252253 254255 256257 258311 312



ITEM CODENUMBER


REMARKS

A531013 Empennage and Horizontal Stabilizer Zonal InspectionTask 53-10-00-214

340 341373 374





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

B262003 Portable Fire Extinguisher Restoration (Hydrostatic Test)Task 26-20-00-780

215 216251 252





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 06 gives a list of item(s), which are completed every 200 Hours or 12 calendarmonths, whichever occurs first.







ITEM CODENUMBER


REMARKS

A110001 Interior and Exterior Placard and Decal Detailed Inspec-tion Task 11-00-00-220

ALL

D121001 Brake System Servicing Task 12-10-01-610 121

D121003 Shimmy Damper Servicing Task 12-10-01-611 710

C122101 Landing Gear Lubrication Task 12-21-03-640 700

C122103 Hartzell Propeller Lubrication Task 12-21-04-640 110

B236001 Static Discharge System Functional Check Task 23-60-00-720

343 375376 571671



ITEM CODENUMBER


REMARKS

B243401 Marathon Ni-Cad Battery Functional Check (CapacityCheck) Task 24-34-00-720

122

A255101 Cargo Nets Detailed Inspection Task 25-51-00-220 251 252255 256257 258

C270001 Flight Controls Lubrication Task 27-00-00-640 215 216226 373374 503525 603625

B273101 Stall Warning System Operational Check Task 27-31-00-710

211 212503

C275001 Flap Tracks and Rollers Lubrication Task 27-50-00-640 525 527625 627

B281001 Fuel Vent Line Float Valve Operational Check Task 28-10-03-710

575 675

A281001 Fuel Filler Assembly Detailed Inspection Task 28-10-01-220

521 621

B301003 Bleed Air Pressure Regulator Functional Check (withoutTKS and not incorporating CAB93-2) Task 30-10-00-720

122 AUX

B322001 Shimmy Damper Functional Check Task 32-20-02-720 710

B341101 Pitot Tube Heaters Operational Check Task 34-11-00-710

AUX

A353001 Portable Oxygen Mask Detailed Inspection Task 35-30-00-220

256

B761003 Emergency Power Lever Annunciator Light (EPL) Oper-ational Check Task 76-10-01-710

AUX


Print Date: Fri Jul 03 07:19:13 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-07(Rev 28)



Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

A243601 Standby Alternator Detailed Inspection Task 24-36-00-220

121

B251001 Inertia Reel Operational Check Task 25-10-00-710 221 232

B255201 Cargo Pod Drains Operational Check Task 25-52-00-710 901 902903 904905 906

A261001 Engine Fire Detection System General Visual InspectionTask 26-10-00-210

121 122



ITEM CODENUMBER


REMARKS

C271001 Aileron Trim System Lubrication Task 27-10-02-640 211 212217 218233 234253 254251 252551 571651 671

B271005 Aileron Trim Tab (Free Play) Functional Check Task 27-10-02-720

551 571651 671

B273003 Elevator Trim Tab (Free Play) Functional Check Task 27-30-02-720

371 372375 376

D282101 Firewall Mounted Fuel Filter Servicing Task 28-21-00-610

130

B282103 Firewall Fuel Shutoff Valve Control Operational CheckTask 28-21-00-711

213 214220

C282301 Wing Shutoff Valve Linkage Lubrication Task 28-23-00-640

231 232511 611

B284101 Fuel Reservoir Warning System Operational Check Task28-41-00-710

ENG

B301001 Bleed Air Pressure Regulator Functional Check (withoutTKS and incorporating CAB93-2) Task 30-10-00-720

122 AUX

B301101 TKS Anti-Ice System Functional Check Task 30-11-00-720

AUX

B301105 TKS System Pressure and Flow Functional Check Task30-11-00-722

AUX

B304001 Windshield Anti-Ice System Operational Check Task 30-40-00-710

AUX

A353003 Portable Oxygen Cylinder Detailed Inspection Task 35-30-00-221

256



ITEM CODENUMBER


REMARKS

B611001 Hartzell Propeller Functional Check Task 61-10-00-720 110

B611101 McCauley Propeller Functional Check Task 61-11-00-720

110

A712001 Engine Mounts and Firewall Detailed Inspection Task 71-20-00-220

130

A716001 Inertial Air Separator Detailed Inspection Task 71-60-00-220

130

B761001 Engine Controls Functional Check Task 76-10-00-720 130 211212 ENG

A801001 Starter-Generator (Part Number 23081 Series only) De-tailed Inspection Task 80-10-00-220

130





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

B215001 Compressor Drive Belt Functional Check Task 21-50-00-720

121 122

A322001 Nose Landing Gear Detailed Inspection Task 32-20-00-220

710





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

B212401 Avionics Cooling Fan Operational Check Task 21-24-00-710

211 212

B221201 Garmin Autopilot (GFC 700) Functional Check Task 22-12-00-720

226 232

B221203 Garmin Autopilot (GFC 700) Slip Clutch Override Oper-ational Check Task 22-12-00-710

226 232

B243201 Gill Flooded Lead-Acid Battery Functional Check (Ca-pacity Check) Task 24-32-00-720

122

B243301 Concord Sealed Lead Acid Battery Functional Check(Capacity Check) Task 24-33-00-720

122



ITEM CODENUMBER


REMARKS

A275001 Flap Actuator Mount Bracket Detailed Inspection Task27-50-00-220

231 232

A275003 Flap Bellcrank Detailed Inspection Task 27-50-00-221 251 252511 611525 625





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

C221201 Autopilot Servos Lubrication Task 22-12-00-640 226 232

A245001 Power Distribution Boxes Detailed Inspection Task 24-50-00-220

121 122

A251001 Crew Seats Detailed Inspection Task 25-10-00-220 231 232

A251003 Passenger Seats Detailed Inspection Task 25-21-00-220 231 232



ITEM CODENUMBER


REMARKS

B271001 Spoiler System Functional Check Task 27-10-00-720 211 212217 218233 234253 254251 252503 525603 625

C271003 Aileron Trim Tab Actuator (2660044-1) Lubrication Task27-10-02-641

551 571651 671

C273001 Elevator Trim Tab Actuator (2660017-1) LubricationTask 27-30-02-640

371 372375 376

B284103 Fuel Quantity and Low Fuel Warning Systems FunctionalCheck Task 28-41-00-720

AUX

B313103 Flight Data Recorder Underwater Locator Beacon Func-tional Check Task 31-31-00-721

312

B324001 Brakes Operational Check Task 32-40-00-710 ENG

B332001 Passenger/Cargo Compartment Lighting OperationalCheck Task 33-20-00-710

AUX

A520001 Crew Doors Detailed Inspection Task 52-00-00-220 801 802

A520003 Passenger/Cargo Doors and Door Frames Detailed In-spection Task 52-00-00-221

255 256257 258803 804

A781001 Primary and Secondary Exhaust Duct General Visual In-spection Task 78-10-00-211

130





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 11 gives a list of item(s), which are completed every 1600 Hours or 24calendar months, whichever occurs first.







ITEM CODENUMBER


REMARKS

B271003 Aileron System Functional Check Task 27-10-00-721 211 212217 218233 234253 254251 252503 525603 625

C272001 Rudder Bar Bearings and Rudder Pedals LubricationTask 27-20-00-640

211 212213 214



ITEM CODENUMBER


REMARKS

B272001 Rudder System Functional Check (Standard Rudder In-stallation) Task 27-20-00-720

211 212213 214217 218233 234253 254257 258311 312320 341

B273001 Elevator System Functional Check Task 27-30-00-720 211 212213 214217 218233 234253 254257 258311 312320 373374 375376

B275001 Flap System Functional Check Task 27-50-00-720 '251 252511 611525 625

B277001 Rudder Gust Lock Detailed Inspection (Airplanes20800237 and On, Airplanes 208B0382 and On and Air-planes equipped with Aero Twin STC SA3649NM) Task27-70-01-221

330





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 12 gives a list of item(s), which are completed every 1600 Hours or 60calendar months, whichever occurs first.







ITEM CODENUMBER


REMARKS

C271005 Aileron Trim Tab Actuator (2661615-1, 2661615- 9, or2661615-10) Lubrication Task 27-10-02-642

551 571651 671

C273003 Elevator Trim Tab Actuator (2661215-1 and 2661215-9)Lubrication Task 27-30-02-641

371 372375 376





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 13 gives a list of item(s), which are completed at the first 20,000 hours andevery 5000 hours thereafter.



D. Item Code A712003 was removed from this Inspection Document in Revision 28.





ITEM CODENUMBER


REMARKS

A531008 Fuselage Engine Mount Fittings Special Detailed Inspec-tion (SID 53-10-01) Task 53-10-00-250

121 122130

A532008 Firewall Brace and Doubler Assemblies Detailed Inspec-tion (SID 53-20-11) Task 53-10-00-223

121 122130

A532009 Carry-Through Root Rib Detailed Inspection (SID 53-20-08) Task 53-10-00-220

251 252500 600

A532011 Crew Door Frames Detailed Inspection (SID 53-20-09)Task 53-10-00-221

231 232233 234801 802



ITEM CODENUMBER


REMARKS

A532012 Passenger and Cargo Door Frames Detailed Inspection(SID 53-20-10) Task 53-10-00-222

255 256257 258803 804

A535001 Fuselage to Horizontal Stabilizer Attach Fittings SpecialDetailed Inspection (SID 53-50-01) Task 53-10-00-257

320 373374

A535002 Vertical Stabilizer Attach Points Special Detailed In-spection (Typical Inspection Compliance) (SID 53-50-02)Task 53-10-00-258

311 312320 341

A551003 Horizontal Stabilizer Forward and Aft Attach Points Spe-cial Detailed Inspection (SID 55-10-01) Task 55-10-00-250

373 374

A553001 Vertical Stabilizer Spars Special Detailed Inspection(Typical Inspection Compliance) (SID 55-30-01) Task55-30-00-250

320 341

A553004 Horizontal Stabilizer Spars Special Detailed Inspection(Typical Inspection Compliance) (SID 55-10-02) Task55-10-00-251

373 374

A564002 Windshield and Attachment Structure Detailed Inspec-tion (SID 56-30-01) Task 56-00-01-220

240





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 14 gives a list of item(s), which are completed at the first 5000 hours andevery 2500 hours thereafter.







ITEM CODENUMBER


REMARKS

A532015 Fuselage Skin Doubler at Main Landing Gear Cutout De-tailed Inspection (SID 53-20-14) Task 53-10-00-225

253 254





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 15 gives a list of item(s), which are completed at the first 7500 hours andevery 2500 hours thereafter.







ITEM CODENUMBER


REMARKS

A531009 Seat Rails and Attachment Structure Detailed Inspection(SID 53-10-07) Task 53-25-00-220

231 232233 234251 252253 254255 256257 258

A532003 Cargo and Passenger Door Doublers Special DetailedInspection (SID 53-20-01) Task 53-10-00-251

255 256257 258803 804

A532013 Bulkheads and Stiffeners Below the Seat Rail Attach-ments at FS 143.00 and FS 158.00 Detailed Inspection(SID 53-20-12) Task 53-25-00-221

233 234





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

A532004 Lower Forward Carry-Thru Bulkhead Special Detailed In-spection (SID 53-20-03) Task 53-10-00-253

253 254

A532006 Main Landing Gear Attach Fittings and Aft Carry-ThruBulkhead (SID 53-20-05) Task 53-10-00-255

253 254

A532014 Stringers at Intersections with Forward and Aft Carry -Thru Bulkheads Detailed Inspection (SID 53-20-13) Task53-10-00-224

251 252

A532016 Fuselage to Wing Carry-Thru Attach Fitting and Bulk-head Special Detailed Inspection (SID 53-20-06) Task53-10-00-256

251 252





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

A535003 Vertical Stabilizer Attach Points Special Detailed In-spection (Severe Inspection Compliance) (SID 53-50-02)Task 53-10-00-259

311 312320 341

A553002 Vertical Stabilizer Spars Special Detailed Inspection (Se-vere Inspection Compliance) (SID 55-30-01) Task 55-30-00-251

320 341





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

A551005 Horizontal Stabilizer Spars Special Detailed Inspection(Severe Inspection Compliance) (SID 55-10-02) Task55-10-00-252

373 374





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 19 gives a list of item(s), which are completed at the first 25,000 landings andevery 5000 landings thereafter.







ITEM CODENUMBER


REMARKS

A532005 Main Landing Gear Fitting Special Detailed Inspection(SID 53-20-04) Task 53-10-00-254

253 254





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 20 gives a list of required 14CFR 91.207 interval item(s), which are completedevery 12 calendar months (No grace period).







ITEM CODENUMBER


REMARKS

B256001 ARTEX C406-2 Emergency Locator Transmitter (ELT)Functional Check Task 25-60-00-720

220 311312 340

B256003 ARTEX ME406 Emergency Locator Transmitter (ELT)Functional Check Task 25-60-00-721

220 311312 340

B256005 ARTEX C406-N Emergency Locator Transmitter (ELT)Functional Check Task 25-60-00-722

220 311312 340

B256007 Dorne and Margolin, Pointer 3000-1, and Pointer 3000-11 Emergency Locator Transmitter (ELT) FunctionalCheck Task 25-60-00-723

220 311312 340





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 20 gives a list of required 14 CFR 91.411 interval item(s), which are completedevery 24 calendar months (No grace period).







ITEM CODENUMBER


REMARKS

B341103 Pitot/Static System Functional Check Task 34-11-00-720 AUX





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 20 gives a list of required 14 CFR 91.413 interval item(s), which are completedevery 24 calendar months (No grace period).







ITEM CODENUMBER


REMARKS

B345001 Transponder Functional Check Task 34-50-00-720 AUX





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 23 gives a list of item(s), which are completed every 100 flight hours forairplanes incorporating CAB-32-02 that operate in "Severe" corrosion environments. Refer toChapter 51, Corrosion Severity Maps - Description and Operation.







ITEM CODENUMBER


RE-MARKS

C122104 Nose Landing Gear Drag Link Support Servicing (Air-planes Incorporating CAB-32-02 Only) Task 12-21-03-641

701





Date: _______________



Total Time: _______________

1. Description

A. Inspection Document 24 gives a list of item(s), which are completed every 200 flight hours forairplanes incorporating CAB-32-02 that operate in "Mild" or "Moderate" corrosion environments.Refer to Chapter 51, Corrosion Severity Maps - Description and Operation.







ITEM CODENUMBER


RE-MARKS

C122105 Nose Landing Gear Drag Link Support Servicing (Air-planes Incorporating CAB-32-02 Only) Task 12-21-03-641

701





Date: _______________



Total Time: _______________

1. Description








ITEM CODENUMBER


REMARKS

A712003 Engine Truss and Ring Assembly Special Detailed In-spection (SID 71-20-01) Task 71-20-00-240

130


Print Date: Fri Jul 03 07:24:49 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MA(Rev 24)


INSPECTION DOCUMENT MA

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MA gives a list of item(s), which are completed at 10,000 hours and every5000 hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A570008 Wing Strut Fittings Special Detailed Inspection (TypicalInspection Compliance) (SID 57-60-01) Task 57-10-01-250

531 631

*** End of Inspection Document MA Inspection Items ***

Print Date: Fri Jul 03 07:24:39 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MB(Rev 26)


INSPECTION DOCUMENT MB

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MB gives a list of item(s), which are completed at 5000 landings and every1000 landings thereafter, up to 10,000 landings. Replace at 10,000 landings (Chapter 4 requirement- No grace period).







ITEM CODENUMBER


REMARKS

A321005 Main Landing Gear Axle (Part Numbers 2641011-1, -3,-4) Special Detailed Inspection (SID 32-10-01) Task 32-10-00-240

721 722

*** End of Inspection Document MB Inspection Items ***

Print Date: Fri Jul 03 07:25:06 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MD(Rev 24)


INSPECTION DOCUMENT MD

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MD gives a list of item(s), which are completed at 15,000 landings and every3000 landings thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A575002 Center Flap Track and Inboard Flap Track Special De-tailed Inspection (SID 57-50-01) Task 57-10-00-254

525 527625 627

A575003 Outboard Flap Track Special Detailed Inspection (SID57-50-01) Task 57-10-00-255

525 527625 627

*** End of Inspection Document MD Inspection Items ***

Print Date: Fri Jul 03 07:25:18 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-ME(Rev 24)


INSPECTION DOCUMENT ME

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document ME gives a list of item(s), which are completed at 5000 hours and every 3600hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A570009 Wing Strut Fittings Special Detailed Inspection (SevereInspection Compliance) (SID 57-60-01) Task 57-10-01-251

531 631

*** End of Inspection Document ME Inspection Items ***

Print Date: Fri Jul 03 07:25:30 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MF(Rev 24)


INSPECTION DOCUMENT MF

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MF gives a list of item(s), which are completed at 20,000 hours and every5000 hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A532007 Fuselage to Wing Attach Fitting Lugs Special DetailedInspection (SID 53-20-02) Task 53-10-00-252

251 252501 511525 601611 625

A570010 Front Spar Lower Cap Inboard of WS 141.20 Special De-tailed Inspection (SID 57-20-02) Task 57-10-00-252

501 521601 621

A570011 Rear Spar Lower Cap Inboard of WS 141.20 Special De-tailed Inspection (SID 57-20-03) Task 57-10-00-253

521 525621 625

A570012 Wing Strut Attachment to Front Spar Special Detailed In-spection (Nominal/Standard Bolt Size) (Typical Inspec-tion Compliance) (SID 57-60-02) Task 57-10-01-252

531 631

Print Date: Fri Jul 03 07:25:30 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MF(Rev 24)


ITEM CODENUMBER


REMARKS

A570013 Wing to Carry - Thru Front Spar Attachment Fittings Spe-cial Detailed Inspection (SID 57-20-01) Task 57-10-00-250

251 252

A570014 Wing to Carry - Thru Rear Spar Attachment Fittings Spe-cial Detailed Inspection (SID 57-20-01) Task 57-10-00-251

251 252

A570015 Wing Strut Attachment to Front Spar Special Detailed In-spection (Nominal/Standard Bolt Size) (Severe Inspec-tion Compliance) (SID 57-60-02) Task 57-10-01-253

531 631

*** End of Inspection Document MF Inspection Items ***

Print Date: Fri Jul 03 07:25:43 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MG(Rev 24)


INSPECTION DOCUMENT MG

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MG gives a list of item(s), which are completed at 5000 hours and every 1200hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A531006 Fuselage to Strut Attach Fitting Lugs (Nominal StandardBolt Size) (Severe Inspection Compliance) Special De-tailed Inspection (SID 53-20-07) Task 53-20-07-251

251 252253 254

*** End of Inspection Document MG Inspection Items ***

Print Date: Fri Jul 03 07:25:55 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MH(Rev 24)


INSPECTION DOCUMENT MH

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MH gives a list of item(s), which are completed at 10,000 hours and every2500 hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A531005 Fuselage to Strut Attach Fitting Lugs (Nominal StandardBolt Size) (Typical Inspection Compliance) Special De-tailed Inspection (SID 53-20-07) Task 53-20-07-250

251 252253 254

*** End of Inspection Document MH Inspection Items ***

Print Date: Fri Jul 03 07:26:07 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MI(Rev 24)


INSPECTION DOCUMENT MI

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MI gives a list of item(s), which are completed at 5000 hours and every 500hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A531010 Fuselage to Strut Attach Fitting Lugs (Oversize 1/64 -Inch Bolt Size) (Severe Inspection Compliance) SpecialDetailed Inspection (SID 53-20-07) Task 53-20-07-252

251 252253 254

*** End of Inspection Document MI Inspection Items ***

Print Date: Fri Jul 03 07:26:20 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MJ(Rev 24)


INSPECTION DOCUMENT MJ

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MJ gives a list of item(s), which are completed at 5000 hours and every 400hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A531011 Fuselage to Strut Attach Fitting Lugs (Oversize 1/32-Inch Bolt Size) (Severe Inspection Compliance) SpecialDetailed Inspection (SID 53-20-07) Task 53-20-07-253

251 252253 254

*** End of Inspection Document MJ Inspection Items ***

Print Date: Fri Jul 03 07:26:32 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-MK(Rev 24)


INSPECTION DOCUMENT MK

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document MK gives a list of item(s), which are completed at 20,000 hours and every4400 hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A570016 Wing Strut Attachment to Front Spar Special Detailed In-spection (1/64 Inch Oversize Bolt Size) (Severe Inspec-tion Compliance) (SID 57-60-02) Task 57-10-01-254

531 631

*** End of Inspection Document MK Inspection Items ***

Print Date: Fri Jul 03 07:26:46 EAT 2015 MODEL 208 MAINTENANCE MANUAL (Rev 28)5-15-ML(Rev 24)


INSPECTION DOCUMENT ML

Date: _______________



Total Time: _______________

1. Description

A. Inspection Document ML gives a list of item(s), which are completed at 20,000 hours and every3600 hours thereafter (Chapter 4 requirement - No grace period).







ITEM CODENUMBER


REMARKS

A570017 Wing Strut Attachment to Front Spar Special Detailed In-spection (1/32 Inch Oversize Bolt Size) (Severe Inspec-tion Compliance) (SID 57-60-02) Task 57-10-01-255

531 631

*** End of Inspection Document ML Inspection Items ***

SECTION 17

ALS MAINTENANCE TRACKING SYSTEM



PROGRAMME Page 1

Issued 26Jun15

SECTION 17 ALS MAINTENANCE TRACKING SYSTEMS. Explanation of ALS Maintenance Tracking System. The tracking system used by Maintenance to control and identify the requirements of the life limited components, inspections, lubrication schedules is Winair maintenance programme. The components of the system are derived from:

Manufacturers Maintenance Manual Time Limits and Maintenance Checks Manufacturers Maintenance Manual Overhaul and Replacement Schedules Manufacturers Maintenance Manual Scheduled Inspection Programs Local Authority Airworthiness Directives Local Authority Airworthiness Information Circulars Federal Aviation Administration and Canadian Airworthiness Directives Manufacturers Service Bulletins Manufacturers Service Information Letters Also it might be derived from the ALS Reliability Committee Recommendations

Whenever a revision or amendment is required, the procedure as laid down in the MCM part 3 will be followed. The Master Tracking Program is set out, controlled and manipulated on computers using Winair maintenance programme. Each individual aircraft maintained by ALS is loaded onto the maintenance Winair System (refer to Winair 5.5 role based work instructions manual pg 7-14), by going through maintenance history written in the aircraft airframe, engine and propeller logbooks. Item-by item the information is entered into the Winair maintenance templates, the data relating to date, times or cycles when the inspections / overhauls / servicing / bulletins were carried out and this forms part of the aircraft record. Preparing and creation of work package The work order will be created by the technical records using the procedure laid down in the MCM Part 3 Section 15 (Also refer to Winair 5.5 role based work instructions manual pg 18-22) Update of the inspection Updates are made on the system using the hours and cycles at last inspection and adding the hours and cycles flown since that time (refer to Winair 5.5 role based work instructions manual pg 18-19) The update is the tab (refer to Winair 5.5 role based work instructions manual pg 17 on how to make log entries) where the hours flown landings and starts flown since the last inspection are added to the current hours and cycles and automatically calculates them for:

TT AF (total time airframe) TCAF (total cycles airframe) TTSN (engine total time since new) TTSO (engine total time since overhaul) TCSN (engine total cycles since new) TCSO (engine total cycles since overhaul) TTSHSI (engine total time since hot section inspection) TT prop (propeller total time since new) TSO prop (propeller total time since overhaul)

Logbook Entries The logbook entries are made by directly transferring the tech log entry hours and cycles to the logbooks. (MPM Sec2.17.7 and MCM Part 1.5.2) Maintenance forecast Maintenance forecast shall be made according to the instructions laid down and will help the maintenance planning and engineering personnel in planning for upcoming or future maintenance to be carried out on specified aircrafts .( Winair 5.5 role based work instructions manual pg 22)



PROGRAMME Page 2

Issued 26Jun15

Storage of Tracking Once the respective templates for inspections have been updated after job completion, they are then saved and these inspections are retained automatically in the respective workorders in the Winair system. This maintenance software and information therein is saved and backed up on the server. The workorder that is automatically generated by the system ensures complete history of the aircraft tracking status task by task. It’s also a back-up for the printed inspection workorder for the particular jobs. All these jobs and access to the software is protected by the passwords which when used they keep track of the time, log in ID and changes made in the system.

SECTION 18

APPENDICES



PROGRAMME Page 1

Issued 26Jun15 APPENDICES

SECTION 18.0 ANNEXURE

SAMPLE OF FORMS USED

ANNEXURE NO.

FORM NUMBER FORM TITILE

1 ALS/C208AMP/01 Ground run sheet

2 ALS/C208AMP/02 Maintenance task card

3 ALS/C208AMP/03 100 Hours inspection

4 ALS/C208AMP/04 Static discharge

5 ALS/C208AMP/05 Cable tension check record sheet

6 ALS/C208AMP/06 Cable travels check record sheet

7 ALS/C208AMP/07 FCU static override 200 hours inspection

8 ALS/C208AMP/08 ITT calibration sheet

9 ALS/C208AMP/09 Torque calibration sheet

10 ALS/C208AMP/10 Main Landing Gear inspection sheet

11 ALS/C208AMP/11 Accessory Gearbox Scavenge Filter 1000 hour inspection

Check Sheet

12 ALS/C208AMP/12 Post SB 1581 Bleed off Valve 600 hour Inspection Check Sheet

13 ALS/C208AMP/13 Brake burn in procedure

14 ALS/C208AMP/14 Daily Inspection Checklist

15 ALS/C208AMP/15 Weekly inspection Checklist

16 ALS/C208AMP/16 C OF A test flight

17 ALS/C208AMP/17 Engine & components removal and installation form



PROGRAMME Page 2


ANNEXURE 1 GROUND RUN SHEET

RUN PARAMETERS -114A PRE / POST (indicate which)

W/O #: ........................ QNH: ................. FUEL BALANCE LH............ RH................

REG : ……………… OAT: ................. ALT: ........................

DATE: ………………….. INSP: ................. SIGN: ........................

ENG: .................. SIGN: ........................

EPL WITNESS WIRE IN TACT / REPLACED

START TEMP * If above 830°C make report

SOURCE (GPU BATT)

GENERATOR CHECKS

STANDBY ALT CHECKS

PROPELLER FEATHERING

PROPELLER UNFEATHERING

SURFACE DEICE OPS

OVERSPEED GOVERNOR SETTING 1765 to 1805 NP 800 ft lbs MAX TORQ

VACUUM PRESSURE

ENGINE BLEED CLOSING Ng GRAPH lower GRAPH upper

ACTUAL GRAPH ETM

VARIANCE LIMITS

($) Max Limit

TORQUE ±1% 1865

PROPELLER SPEED ±0.2% 1900 rpm,100% Np max (report if exceeded)

INTER TURBINE TEMP ±5 805

GAS GENERATOR SPEED ±0.2% *101.0% max 5 secs (report if exceeded)

FUEL FLOW ±2.5% * Note that

exceedance of operating limits

will lead to engine unscheduled inspections

(ref:72-00-00)

OIL PRESSURE 85 to 105 psi ($) Variance Limits should be

documented and rectified whenever a difference exceeding the given tolerances is noted between the Analog and ETM.

OIL TEMP 10 to 99 degs C

REVERSE TORQUE * 1865 lbs

REVERSE Ng *101.0% max 1 min

ACCELERATION CHECK GRAPH min time GRAPH max time Computed Ng

GROUND HEATER OPERATION

CABIN HEATER OPERATION

HIGH IDLE Ng 64 to 66% * Note that there is an ITT limit

of 685° at idle. Increase Ng to keep below this limit.

LOW IDLE Ng 52 to 55%

*company limit

Notes / Snags ..............………………………………………………………………………………………………………

……………....................………………………………………………………………………………….

……………....................………………………………………………………………………………….

Form Number: ALS/ C208AMP /01



PROGRAMME Page 3


ANNEXURE 2 GROUND RUN SHEET CONT’




PROGRAMME Page 4


ANNEXURE 2 MAINTENANCE TASK CARD (SAMPLE)




PROGRAMME Page 5


ANNEXURE 3 ALS PWC -114A 100 HOUR INSPECTION CHECK SHEET Refer to pwc mm P/N 3043512 Rev 30 Chapter 72-00-00 table 601

AREA INSPECTION SIGN INSPECTOR

A. Tubing, wiring, Control Linkages, Hose Assemblies

All accessible Connections, clamps and brackets for attachment

Wear, chafing, cracks and corrosion

Fuel and oil lines for leaks

Pay particular attention to rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings.

Clean rod ends using dry rag (AWKs requirement due dusty ops environment)

Lubricate with light grease (PWC04-001) after engine external wash.

Examine rod end for corrosion, roughness in rotation, side play and radial play.

Check free movement of linkage

B. Air Inlet Screen Cleanliness (Ref. 72-20-00)

C. Gas Generator Case

External surfaces, and fireseal mount ring brackets for cracks, distortion, and corrosion (Ref. 72-30-04)

D. Fireseal Mount Rings

Cracks and attachment of brackets and seals. (Ref. 72-30-01/-02)

E. Exhaust Duct Cracks and distortion (Ref. 72-50-05)

F. Propeller Shaft Seal

Check for oil leaks (Ref. 72-10-00)

G. Accessories

Attachment and linkages, air, oil and fuel lines (Ref. 73-10-07/-08)

Oil and fuel leaks as applicable




PROGRAMME Page 6


ANNEXURE 4 STATIC DISCHARGE OPS TEST AIRCRAFT REGISTRATION ………………. W/O………………………………DATE…………………………………..

1. Visually examine the static dischargers for lightning damage and erosion of the airplane skin at the

attach points. If the static discharger shows signs of a lightning strike, replace the static discharger and examine the entire aircraft for lightning strike damage. Refer to Chapter 5, Unscheduled Maintenance Checks.

2. Visually examine between the tips of the static dischargers and the base assemblies for erosion. Visually examine the static dischargers for condition and security. Replace the damaged or the missing static dischargers. Make sure that all static dischargers are tight.

3. Use an ohmmeter (bonding meter) to do a check of the resistance between the base assemblies and a good airplane ground. Make sure that the resistance between the base assembly and the metal surface is 0.5 ohms or less. Make sure there is a good ground before you do the next step. USE PRECAUTION WHEN YOU USE A HIGH VOLTAGE MEGOHMMETER TO PREVENT AN ELECTRICAL SHOCK.

4. Use a megohmmeter set to 500 volts to do a check of the resistance between the base assemblies and the static dischargers. Make sure that the resistance between the base assembly AND THE STATIC DISCHARGER IS 1 TO 100 MEGOHMS. If the resistance between the base assembly and the static discharger is not in tolerance, replace the static discharger.

INSPECTION CARRIED OUT BY NAME: SIGNATURE:

Remarks: .......................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................................... Form Number: ALS/ C208AMP /04

RESISTANCE RESISTANCE RESISTANCE

1 B1 C1

2 B2 C2

3 B3 C3

4 B4 C4

RESISTANCE RESISTANCE RESISTANCE

1 E1 F1

2 E2 F2

3 E3 F3

4 E4 F4



PROGRAMME Page 7


ANNEXURE 5 CABLE TENSION INSPECTIONS ALS 208B CABLE TENSION CHECK RECORD

REG……………………. DATE……………. W/O#…………..

Aileron Cables: UP DOWN

Control Column 25 to 35 ............... ............... lbs

Carry Thru 35 to 45 ............... ............... lbs

Direct 35 to 45 ............... ............... lbs

Fuselage Loop 35 to 45 ............... ............... lbs

Trim Tab 3 ............... ............... lbs

A/P Bridal 7 to 17 ............... ............... lbs

Elevator Cables:

UP DOWN

Control 55 to 65 ............... ............... lbs

Trim Tab 15 to 25 ............... ............... lbs

Rudder Cables:

LEFT RIGHT

Control 25 to 35 ............... ............... lbs

Tensions checked and recorded by:

Name:………………………………………………………….

Sign:……………………………………………………………..

Tensions checked and recorded by:

Name:………………………………………………………….

Sign:……………………………………………………………..




PROGRAMME Page 8


ANNEXURE 6 CABLE TRAVELS CHECK SHEET (All readings in degrees) A/c Reg:............................ w/o:............................ Date:...................................

RUDDER RUDDER

Left 23-27 Left

Right 23-27 Right

ELEVATOR ELEVATOR

Left up 23-27 Left up

Left down 19-21 Left down

Right up 23-27 Right up

Right down 19-21 Right down

ELEVATOR TRIMS ELEVATOR TRIMS


Left down 13 Left down

Right up 13 Right up

Right down 13 Right down

AILERONS AILERONS


Left down 16-17 Left down


Right down 16-17 Right down

AILERONS TRIM TAB AILERONS TRIM TAB

Right up 13-17 left up

Right down 13-17 left down

FLAPS FLAPS L R

Flaps 0 Flaps 0

Flaps 10 Flaps 10

Flaps 20 Flaps 20

Flaps 30 Flaps 30

SPOILERS SPOILERS Left up 35-45 Left up

Left down -5-0 Left down


Right down -5-0 Right down

Travels checked and recorded by: Name:……………………………

Sign:………………………………

Travels checked and recorded by:

Name:………………………………




PROGRAMME Page 9


ANNEXURE 7 FCU STATIC OVERRIDE 200 HOURS INSPECTION Aircraft:.................................. W/O...................................... Date:................................................... DESCRIPTION PROCEDURE MECHANIC SIGN As part of the periodic inspection (Ref. 72-00-00, INSPECTION, Periodic Inspection), check the static operation of the manual override system, with the engine shutdown Manual Override System Static Check

Set cockpit Manual Override Control lever - OFF. Make sure the Manual Override lever on the FCU is in the OFF position (hard against its internal stop).

Set cockpit Manual Override Control lever to the maximum forward position. Make sure the cockpit Manual Override Control lever does not bind and the Manual Override Lever on the FCU contacts the stop at the MAXIMUM FLOW position

NOTE Some resistance to movement of the cockpit Manual Override Control lever is normal.

If either stop is not reached, check/adjust the airframe rigging (Ref. Aircraft Maintenance Manual).

Manual Override System Operational Check

CAUTION other : than the following check, use of the manual override system is restricted for emergencies only. CAUTION when : using the manual override system, the engine response may be more rapid than when using the power lever. a rapid increase in manual override lever position towards maximum is to be avoided, as this can cause engine surge, engine over-temperature, ng over-speed or over-torque

Do the Manual Override System static check

Set Manual Override Control lever - OFF

Fuel Condition lever - GROUND-IDLE

Power Control lever - GROUND-IDLE

Slowly advance Manual Override Control lever observing ITT, torque and Ng at all times. Keep Ng maximum increase under 4% per second.

NOTE Some movement of the Manual Override Control lever, resulting in no increase in engine power, is normal.

Slowly increase Ng until a 15% increase above ground-idle speed is obtained. This indicates proper functioning of the Manual Override System

Slowly reduce the Manual Override Control lever to OFF, keeping Ng decrease less than 4% Ng per second.




PROGRAMME Page 10


ANNEXURE 8 ITT CALIBRATION SHEET

ALS INTER TURBINE TEMPERATURE INDICATOR ADJUSTMENT AND TEST

C208B

Aircraft:……………………………… W/O:…………………………….. Date:…………………………………

Notes for maintenance staff

NOTE: Let the junctions in the ice bath become stable for 5 minutes before any test.

NOTE: Make sure that the ITT harness and the TT5 trim harness are disconnected from the system

A large terminal is designated for the alumel connector

NOTE: Let the junctions in the ice bath become stable for 5 minutes before any test. Follow procedure refer C208 MM Rev 28 chapter 77-21-00

TEST POINT Â°C APPLIED VOLTAGE

IN MILLIVOLTS

TOLERANCE

TEMPERATURE Â°C

ACTUAL GAUGE

READING

100 4.095 +20 to -20

300 12.207 +20 to -20

660 27.445 +7.5 to -7.5

805 33.480 +2.5 to -2.5

900 37.325 +5.0 to -5.0

1090 44.729 +2.5 to -2.5

1100 45.108 +5.0 to -5.0

If the ITT indication does not agree with the applied millivolt input, do the following:

a) Examine the connectors and wiring between the thermocouple harness connector and the ITT indicator.

Make sure that the wiring is clean, there is proper contact, and there is correct alumel/chromel pin

arrangement

b) Examine the interconnect ITT indicator.

If the ITT indicator agrees with the millivolt input, but the indication during the engine operation is incorrect, refer

to the Pratt & Whitney Maintenance Manual for ITT Thermocouple and Thermocouple Harness Inspection

Procedure

Instrument reader name

Name:…………………………………

Sign:…………………………………

Tester reader

Name:…………………………………

Sign:……………………………………

Inspector Name:…………………………………

Sign:……………………………………




PROGRAMME Page 11


ANNEXURE 9: TORQUE CALIBRATION SHEET

(connected at the engine input ports) Compiled from 208B MM Rev 28 Chapter 77‐11‐00

REG……………………. DATE……………. W/O…………...

Instruction and Caution engineers to sign each item Sign Sign

CAUTION: Improper connection will damage the indicator. Connect pressure source and gage (or deadweight tester) to pressure port

(marked P) of the indicator.

Leave reference port (marked V) of the indicator open to atmosphere.

Apply pressures in increasing direction. Check indicator reading tolerance after tapping indicator to overcome friction

Repeat with decreasing pressure, except at the 2500 ft‐Ib point

Failure of indicator to comply with above shall result in rejection of unit.

For this test, deadweight tester is at the same level as the engine ports. 20" higher than the indicator in the cockpit

INPUT PRESSURE PSI REQUIRED INDICATOR READING FT‐LBS

GAUGE READING INCREASING

GAUGE READING DECREASING

12.82 to 15.58 500.00 to 550.00

28.39 to 29.41 1000.00 to 1035.00

41.81 to 43.37 1500.00 to 1528.00

46.52 to 47.64 1658.00 to 1678.00

55.37 to 56.49 1970.00 to 1990.00

69.8 to 72.16 2500.00 to 2540.00

Deadweight tester operator name............................ Signature..........................

Instrument readers name......................................... Signature..........................

Certifying Inspector name........................................ Signature..........................




PROGRAMME Page 12


ANNEXURE 10 MAIN LANDING GEAR INSPECTION SHEET



PROGRAMME Page 13


ANNEXURE 10 MAIN LANDING GEAR INSPECTION SHEET CONT’




PROGRAMME Page 14






PROGRAMME Page 15






PROGRAMME Page 16






PROGRAMME Page 17


ANNEXURE 11 ACCESSORY GEAR BOX SCAVENGE FILTER 1000 HOURS INSPECTION CHECKSHEET

ALS AGB SCAVENGE FILTER 1000 HR INSPECTION CHECK SHEET ‐114A Registration ___________________ W/O ____________________ Date---------------------------

AREA To be carried out every 1000 hours due not operating in

a humid or tropical environment

SIGN INSPECTOR

Check the AGB internal scavenge oil pump inlet screen

Remove oil drain plug located on the AGB housing. For engine

equipped with an AGB chip detector, remove the chip detector

Collect drained oil in a clean container and check for debris

Use a mirror and suitable light source ( or borescope) and inspect the

scavenge oil pump inlet screen for carbon or debris

Any foreign material found blocking the screen or contained in the oil

should be identified. Look especially for paint flakes approximately 1/8 inch

to ½ inch diameter

If carbon or debris is present, clean the inlet screen

Install the drain plug on the AGB housing. For engine equipped with an

AGB detector, install the chip detector

Replenish the drained oil (if not contaminated by foreign material) in

oil tank





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ANNEXURE 12 POST SB 1581 BLEED VALVE 600 HOURS INSPECTION ALS POST SB 1581 BLEED VALVE 600 HOUR INSPECTION CHECK SHEET-114A Registration ________________________ W/O ___________________ Date-------------------------------

AREA Check the bleed valve (Ref. 75-30-00

Inspection/Check as follows: SIGN INSPECTOR

BLEED VALVE COMPONENTS INSPECTION Visually inspect bleed valve externally for signs of damage or

corrosion. Stone or file small nicks and burrs.

CAUTION: KEEP FINGERS CLEAR OF PISTON TRAVEL. THE PISTON MAY MOVE QUICKLY WHEN SHOP AIR IS APPLIED

Block the final metering plug orifice with one finger and carefully blow shop air at low pressure into the P3 passage at the base of the bleed valve

Under control, hold the piston as it starts to move Move the piston in and out to make sure the piston moves freely NOTE: It is normal to feel the return spring force pulling the piston

towards the open position

Check for corrosion or contaminants on the inner surface of the piston or guide pin.

As there is no field repair possible for this type of bleed valve, return the entire bleed valve to an authorized accessories overhaul shop for: Severe corrosion or damage. The piston sticking anywhere during its travel Leakage exceeds the specified limits

Required closing point cannot be achieved on ground runs

KEY to Figure: 1. Final metering Plug 2. Piston 3. Self-Locking Screw 4. Locking Plate 5. Adjustment Stem 6. Orifice Retainer 7. Valve Housing 8. Blanking Plug




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ANNEXURE 12 POST SB 1581 BLEED VALVE 600 HOURS INSPECTION CONT’




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ANNEXURE 13 BRAKE BURN IN PROCEDURE ALS

BRAKE BURN IN PROCEDURE

A/C Reg:..........................

Date:..............................

W/O:..............................

a) This form to be submitted to the operation department by Quality manager or maintenance manager as a

request for this procedure to be carried out b) The CRS will be issued to the operations department accompanied with this form completed and signed

Extracted from C208B maintenance manual chapter 32-40-00

(A) Airplanes 20800001 thru 20800135 and 208B0001 thru 208B0102

Perform six consecutive light braking applications from 20 to 35 knots. Allow brake discs to cool

substantially between stops.

Caution: Do not set the parking brakes while they are hot. This will help to prevent irregular friction

surface mix transfer that can result in brake clatter, noise and vibration.

(B) Airplanes 20800136 and On, 208B0103 and On, and All Spares

NOTE: The brake pads are of a metallic composition and require the following break-in

procedure.

Perform two consecutive full stop braking applications from 30 to 35 knots.

Caution: Do not allow brake discs to cool substantially between stops. Use caution in performing this

procedure, as higher speeds with successive stops could cause the brakes to overheat, resulting in warped discs

and/or pressure plates.

Aircraft status: Serviceable Unserviceable Name of pilot Licence No. signature Date To be filled by certifying inspector Were there any brake related defects arising during the procedure If yes, record it in the remarks below and open a new task card for the defect.

YES

NO.

(Tick in boxes above)

Remarks -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------




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ANNEXURE 14 DAILY INSPECTION CHECKLISTS Daily Inspection Checklist Pocket Edition: (Printed for the Line station/field Engineer) NB: Ensure each item inspected is ticked and append signature on the Right Side of each row FUSELAGE INSPECTION WALK AROUND IN CLOCKWISE DIRECTION

SIGNATURE

Inlet cowl Oil cooler Nose gear assy Torque links NLG oleo Spring fairing Spring bushing Windscreen Skin Door Windows Steps

Upper skin Fuel cap Bellcrank panel Fairing boot Fairing Brake line Tire Wheel rim Brake Pads Brake Disk Leading Edge Pitot Tube

Tire pressure LH......psi RH.....psi Nose....psi Lower skin Fuel Drains Lights Wing tip Nav / strobe Wing tip

Aileron Trim Tab Static Wicks Flaps Lower skin Fuselage skin Windows Entry door up Steps Step Cables Fuselage skin Window

Vertical Stab Leading edge VHF antenna HF antenna Horiz Stabilizer Leading edgeLower skin Elevator horn Elevator Trim Tab Static wicks Rudder skin Static wicks Beacon Light Tailcone Nav light Static wick Rudder Skin

Elevator Trim tab Static Wicks Elevator horn Lower skin Leading edge Vertical stab VHF antenna Fuselage skin Window Cargo Door

upper Cargo Door

lower

Pull cable Windows Fuselage skin Flaps Lower skin Aileron Servo tab Static wicks Wing tip Nav strobe Leading edge Lower skin

Lights Pitot tube Leading edge Lower skin Fuel drains Bellcrank panel Fairing boot Fairing Brake line Tire Wheel rim Brake Pads Brake Disk Windows Door Steps Upper skin Fuel cap Windshield Fuselage skin Condenser gill END

Engine Walk-around SIGNATURE

Open Cowl Accessory Gearbox AGB drains Wiring Harness Control Linkages Standby Alt Inertial Separator Oil Tubes Fuel Lines Ducts

Starter Generator Aircon pump Close cowl Latch Catches Shim damper Propeller Walk-Around Check

SIGNATURE Spinner Spinner screws Bulkhead Leading edge Forward Face Aft Face

Engine oil leak Red Dye Leak Rotate Prop & listen for abnormal sounds or binding Oil level on dipstick

NB: 1.A tick(√) denotes satisfactory compliance of Maintenance Manual requirements. 2.A wrong (X)denotes non compliance of Maintenance Manual requirements. Transfer discrepancy to defect sheet.

Form number: ALS/ C208AMP /14

FINDINGS RECTIFICATION 1.

2.

3.

4.

5.

N/B FINDINGS SHOULD BE TRANSFERRED TO WPACK AND ADDRESSED IMMEDIATELY

Aircraft Registration

Engineer / Technician

Date of inspection.

Are there any defects found during this inspection? Yes no

Was the findings communicated to the base? Yes No



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ANNEXURE 15 WEEKLY INSPECTION CHECKLIST Engine Area Inspection TICK SIGN

Externals

All accessible connections, clamps and brackets for attachment Chafing, cracks and corrosion Rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings Examine the rod ball for corrosion, roughness in rotation, side play and radial play. Examine rod end for corrosion, roughness in rotation, side play and radial play Check free movement of linkage

Air Inlet Inspect air inlet screen for cleanliness GG Case Surfaces, and fire-seal mount ring brackets for cracks, distortion, and corrosion


Fuel System


Ignition System Check ignition cables for chafing, wear and installation 12.5.6 Inspection Requirements: Airframe Area Inspection TICK SIGN

Landing Gears

Wipe exposed oleo struts with rag moistened in hydraulic oil Check tire pressures Record tire pressures (Nose……………psi L/H main…………psi R/H main………..psi

Check brake hydraulic fluid levelGear rubber fairings

Interior




Keep Battery use to minimum during the light and flap ops checks. Low battery will result in hot starting! DEFECT RECTIFICATION 1. 2. 3. 4. N/B FINDINGS SHOULD BE TRANSFERRED TO WPACK AND ADDRESSED IMMEDIATELY


Aircraft Registration

Engineer / Technician

Date of inspection.

Were any defects found during this inspection or during the weekly inspections Yes No

Was maintenance base informed of the findings? Yes No



PROGRAMME Page 23


ANNEXURE 16 C OF A TEST FLIGHT FORM

Operator

Maintenance Organization

Aeroplane Type

Registration

Aerodrome

Temperature

Q.F.E.

Date of Flight Test

Pilot

Observer

Any Weather significant

to the tests (i.e. cloud base,

Tops, turbulence)

PRE-FLIGHT. (Delete As Necessary)

Flight Authority Issued and Signed Yes/No

Check that the Following are on board

Flight Manual / Owner’s Manual / Pilots Handbook Yes/No

Pilot’s Notes Yes/No

Cabin Fire Extinguisher (If Applicable) Yes/No


ALS LIMITED

AIRWORTHINESS FLIGHT TEST REPORT CESSNA 208 CARAVAN I/



PROGRAMME Page 24


LOADING.

Take-off weight (actual) (Kg/lb). Actual C of G position

The weight and C of G must remain within the Flight Manual limitations at all times.

PRE-FLIGHT INFORMATION

Total airframe hours Engine type Serial Number Hours run since new Hours run since overhaul

GROUND TESTS

Check all flying controls and trimmers for Full travel, freedom of movement and Correct functioning. Carry out pre-flight checks of stall Protection system Check engine and propeller controls for Full travel, freedom of movement and Correct functioning including reverse and Reverse lockout.

- Start ITT - Ng low idle - High idle - Acceleration low idle to take-off power - Unfeathering at low idle - Bleed air heating - Max reverse - Note time from idle - Note engine readings when ITT peaks.

TAXING Parking brake (including lock and release) Brake (including freedom from binding And normal ability to hold aircraft at high Engine power). Taxing (including nose wheel steering/ Differential braking).

TAKE-OFF.

Flap 20 VR 75 KIAS climb 95 KIAS Carry out normal take-off Note any unusual characteristics



PROGRAMME Page 25


ENROUTE CLIMB PERFORMANCE. Carry out an en route climb for 5 minutes clear off cloud and turbulence, with

- Flaps up, - Propeller lever fully forward (1,900 rpm) - Engine at maximum continuous power (see graph on page V-24 & II-7) - Inertial separator-Normal - KIAS see page V-24 - Altimeter set to 1013mb (29.92 in Hg)

Record the altitude, IAS and OAT every half minute and after about three minutes the engine instrument

readings.

Time (Minutes)

Altitude (Ft)

IAS (Knots)

OAT (C)

Fuel Gone (Lb/Kg)

0

½

Trimmer settings:

1

Rudder:

1½

Aileron:

2

Elevator:

2½

3

3½

Weather conditions

4

4½

5

Torque ITT Propeller

Rpm NP Gas Generator Rpm NG Fuel Flow

Oil Temp Oil Press

Lb/ft C Rpm % Lb/hr C psi




PROGRAMME Page 26


CRUISE. Recommended FL 100

With a typical high cruise power, trim the aircraft accurately in level flight and record the following: Indicated Altitude IAS OAT Trimmer Settings: Rudder. Aileron Elevator Torque

ITT Np rpm Ng rpm Fuel flow

Oil Temp Oil Press

Lb/ft C % Lb/hr C psi

Flying Control Break-out load Centering

Backlash Weight Response

Rudder Aileron Elevator

Trimmers Friction

Backlash Response

Rudder Aileron Elevator

Left Right

MAXIMUM SPEED CHECK.

Only to be done in smooth conditions


Kt.

FUEL SYSTEM. - System functioning on each tank - Fuel selectors - Fuel Gauges

VNE Red Line – 175 KIAS Altitude Indicated Airspeed



PROGRAMME Page 27


Check the following:

STALLS.

For each stall, the aircraft is to be trimmed in the prescribed configuration with power lever at Flight Idle

and propeller Lever fully forward at a speed 1.5 times the scheduled stalling speed. From this trimmed condition the rate of speed reduction should be controlled smoothly at as close as possible to 1 Knot per second. This will probably result in a gentle rate of descent and do not attempt to fly a constant altitude approach to the stall.

Stall the aircraft with flaps up, 0 and Power Lever Flight Idle.

Aircraft Weight Lb/kg

Trim Speed KIAS

Elevator trim

Stall Warn. KIAS Stall Speed KIAS Behavior at Stall

Sched. Achieved

Stall the aircraft with flaps at 10 and Power Lever Flight Idle.


Trim Speed KIAS

Elevator trim


Sched. Achieved

Stall the aircraft with flaps at 20 (take-off) and Power Lever Flight Idle.


Trim Speed KIAS

Elevator trim


Sched. Achieved

Stall the aircraft with flaps at LAND (30) and Power Lever Flight Idle. Aircr

aft Weight Lb/kg

Trim Speed KIAS

Elevator trim


Sched. Achieved


Control force and aircraft response to Small movements Engine and propeller for any Abnormal behaviors



PROGRAMME Page 28


APPROACH AND LANDING.

Carry out a normal approach and landing with full flap using the scheduled approach speed. Record any unusual characteristics.

NOTE: If the correct speed is used at the threshold, the stall warning should not operate. After landing, select reverse thrust on the engine and check for normal operation.

AFTER LANDING

Check all placards for presence, accuracy and legibility. Climb Performance Evaluation: Plot the altitude and IOAT recorded during the climb against time. Determine the mean achieved rate of

climb and evaluate the scheduled gross rate of climb from the Flight Manual Supplement.

Mean altitude during climb

Ft.

Mean Ind. OAT during climb C.

Mean aircraft weight during climb

Lb.

Scheduled rate of climb

Ft/min

Achieved rate of climb

Ft/min

Rate of climb differential

Ft/min

CESSNA - 208 Registration: -

Constructor’s No: - I CERTIFY That I have carried out all the tests specified in this Airworthiness Flight Test schedule. The following deficiencies and unsatisfactory features were revealed by the flight tests and noted at other

times during the flight(s) and I CONSIDER that those annoted ‘R’ and/or ‘FT’ should be dealt with as follows:

(a) Those annoted ‘R’ must be rectified prior to the renewal of the Certificate of Airworthiness or flight for hire or reward, whichever occurs first?

(b) Those annoted ‘FT’ must be re-assessed in flight before the defect can be considered rectified. Form Number: ALS/ C208AMP /16



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NO FLIGHT DEFECTS R/FT


Flight Defects transcribed to…………………………………...……………for certification and clearance.

Pilot………………………………………………….………License No………….…………………….…

Date………………………………………………………….Signed…………..……………………………



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Airplane model Registration #. Serial # Date of flight.

Communications Radio

Equipment

Type Auth. Ground Sta.

Freq. A/C Position & Distance from Sta.

Alt. +

Time (Z)

Reported signal

TX RX

VHF com 1

VHF com 2

HF com. * See UK ‘Air Pilot’ or ‘General Aviation Flight Guide’ or contact CAA ‘Local Area Office’.

+ To be acceptable, a VHF Communication test must establish a minimum range of 20 nm from a height of 2000 ft above the ground station. At greater heights, the range so established must be correspondingly greater. Navigation Aids.

Type

Ground Station.

Freq.

A/C Position

Actual Radial

Audio Ident

Flag Ind. of reliable signal.

Pointer Indicator.

VOR (1) Yes/no Radial from/to

VOR (2) Yes/no Radial from/to

LOC (1) Yes/no Satis/unsatis

LOC (2) Yes/no Satis/unsatis

G/S (1) Yes/no Satis/unsatis

G/S (2) Yes/no Satis/unsatis

MARKER (LO setting if

fitted)

TYPE.

BEACON

GROUND STATION.

AUDIO

LIGHT

OUTER SATIS/UNSATIS SATIS/UNSATIS MIDDLE SATIS/UNSATIS SATIS/UNSATIS

TYPE. GROUND STATION.

FREQ.

AIRPLANE POSITION

HEADING

ACTUAL BEARING

INDICATED BEARING

ADF (1)

ADF (2)

DME.

TYPE.

GROUND STATION.

FREQ.

AIRPLANE POSITION

RANGE. ACTUAL INDICATED

AREA NAV.

TYPE.

POSITION

ACTUAL INDICATED ERROR


AIRWORTHINESS FLIGHT TEST SCHEDULE NO. 3, ISSUE 1 RADIO FLIGHT TEST REPORT



PROGRAMME Page 31


MISCELLANEOUS

TRANSPONDER

TYPE GROUND STATION

CODE RANGE ALT. REPORTED SIGNAL

ENCODING ALTIMETER

TYPE INDICATED ALTITUDE (1013 mb) REPORTED ALTITUDE

INTER-COM TYPE OPERATION

RADIO FLIGHT TEST DEFECTS: I certify that the radio station designated overleaf has, in every respect, been found to perform

satisfactorily in flight, with the exception of the items listed above, which have been transcribed

Pilot Signature

Radio License No




PROGRAMME Page 32


ANNEXURE 17: ENGINE INSTALLATION/REMOVAL

ALS LTD

C208 MAINTENANCE TASK CARD

A/C REG: A/C TT: DATE:

A/C S/No. A/C TC: W/O.

TASK DESCRIPTION Engine Installation/Removal #

NOTES Carry out "Engine Installation/Removal " Task Card.

NO. PROCEDURE

1 Install/Remove Engine S/No…………..…… IAW MM Chap 71-00-00.

NO TASK COMPLETION DATE:

HOURS MECH INSP

Duplicate Insp Req? Y □ N □ Sign:

P/NO ON S/NO ON

P/NO OFF S/NO OFF

CERTIFICATE OF RELEASE TO SERVICE

"The undersigned certifies that the work specified was carried out in accordance with current regulations and in

respect of that work the aircraft component is considered ready for release to service."

Cat 'A' Signed………………………………Authority ……………………………...Date ………………………………..

Cat 'C' Signed……………………………...Authority ……………………………...Date ………………………………..

Cat 'X' Signed………………………………Authority ………………………………Date ………………………………..

Page 1 of 2



PROGRAMME Page 33



REMARKS HOURS MECH INSP

1 Check condition of packing case for shock load

2 Check appropriate Log books are enclosed

3 Check Engine external condition. Ref PWC 70-00-00

a. Power Section for general condition

b. Gas Section for general condition

c. Exhaust Section for general condition

COMPONENTS ENGINE: (Components installed on Engine at Receive)

DESCRIPTION P/No. S/No.

Power Section

1 Governor - Propeller

Gas Section

1 Pump-Fuel

2 Fuel Control Unit

3 Heater-Oil to Fuel

4 Exciter-Ignition

5 Valve-Compressor Bleed

6 Flow divider & Dump gate

COMPONENTS ENGINE: (Components added to Engine at installation)

1 Starter Generator

2 Prop O'speed Governor

3 Engine Tacho generator

4 Prop Tacho generator

5 Oil Pressure Transmitter

Remarks:




Cat 'C' Signed……………………………...Authority ……………………………...Date…………………………..

Page 2 of 2 Form Number: ALS/ C208AMP /17



PROGRAMME Page 34


ANNEXURE 18: PROPELLER INSTALLATION/REMOVAL

ALS LTD

C208B MAINTENANCE TASK CARD

A/C REG: A/C TT: DATE:

A/C S/No. A/C TC: W/O.

TASK DESCRIPTION Propeller Assembly Installation/Removal

NOTES Reason for Installation/Removal l

1 Remove and Refit Propeller Assy SN …...… IAW with Chap 61-10-00 of the Maintenance Manual


HOURS MECH INSP

Duplicate Insp:

P/NO ON P/NO OFF

S/NO ON S/NO OFF

TSO TSO

CALENDAR START CALENDAR START




Cat 'A' Signed………………………………Authority ……………………………...Date ………………………………..

Cat 'C' Signed……………………………...Authority ……………………………...Date ………………………………..

Cat 'X' Signed………………………………Authority ………………………………Date ………………………………..


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