27. EXHIBIT XXVII - Cessna 206 AIP.pdf

Cessna 206 Series Aircraft AAOC Approved Inspection Program

Alliance Aviation Operation Center

Cessna 206 Approved Inspection Program

(AIP)

Alliance Aviation Operations Center

2300 Horizon Drive

Fort Worth, Texas 76177

Exhibit ????

APPROVAL LETTER:

AAOC APPROVED

INSPECTION PROGRAM

206 Cessna Series Aircraft (A4CE)

AIP MANUAL REVISION CONTROL

Revision

Number

Revision

Date

Inserted

Date Remarks Initials

0 7/1/2018

1 11/7/2018

2 12/21/2022

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TABLE OF CONTENTS

Table of Contents Page Cessna 206 Approved Inspection Program (AIP)

APPROVAL LETTER:

AIP MANUAL REVISION CONTROL

LIST OF EFFECTIVE PAGES

TABLE OF CONTENTS

SECTION 1: ADMINISTRATION

1. General

2. Duties and Responsibilities

3. AIP Control and Distribution

4. Revisions to the AIP

5. Adding Aircraft to the AIP

6. Life Limited Components/Parts

7. Scheduled Inspections/Unscheduled Maintenance

8. Instructions for Performing Inspections and Returning Aircraft to Service

9. Removing Aircraft from the AIP

SECTION 2: INSPECTION REQUIREMENTS

1. Required Inspections

2. Modification Inspections

3. Summary

SECTION 3: AIRCRAFT ZONING

D. Description

APPENDIX A

SECTION 1: COMPONENT TIME LIMITS

1. General

2. Cessna-Supplied Replacement Time Limits

3. Supplier-Supplied Replacement Time Limits

SECTION 2: INSPECTION PROGRAM

1. General

2. Procedure

3. General Inspection Terms and Guidelines

INSPECTION OPERATION 1

INSPECTION OPERATION 2

INSPECTION OPERATION 3

INSPECTION OPERATION 4

INSPECTION OPERATION 5

INSPECTION OPERATION 6

INSPECTION OPERATION 7

INSPECTION OPERATION 8

INSPECTION OPERATION 9

INSPECTION OPERATION 10

INSPECTION OPERATION 11

APPENDIX B

AIRWORTHINESS DIRECTIVES

APPENDIX C

INSTRUCTIONS FOR CONTINUED AIRWORHINESS (ICA)

SECTION 1: ADMINISTRATION

1. General

AAOC has developed this Federal Aviation Administration (FAA) Approved Inspection Program (AIP) in accordance with 14 CFR Part 91.409. This program will be used by the Director of Maintenance (DOM), Contracted Maintenance Organizations, Maintenance Technicians, and others designated by the DOM for performing scheduled periodic and special inspections, and inspections as required by adverse operational conditions. This inspection program provides for a continuous aircraft inspection regiment along with other tasks to ensure continued airworthiness to a degree of safety that is equivalent to or higher than the aircraft manufacturer’s recommended inspection program. All inspections under this program will be updated when completed by the DOM and tracked on a computerized tracking program.

This inspection program utilizes the manufacturer’s recommendations in the following manuals/directives.

All AOC 206 single engine piston powered Cessna aircraft will be inspected utilizing this AIP. The AAOC will maintain current subscriptions with the manufacturers to ensure manual/directive/information currency.

• Cessna Model 206H, T206H and U206G Maintenance Manual (Current Revision)

• Lycoming Operators Manual (Current Revision)

• Lycoming Engine Overhaul Manual (Current Revision)

• Continental Operators Manual (Current Revision)

• Continental Overhaul Manual (Current Revision)

• Hartzell Propeller Manuals (Current Revision)

• McCauley Propeller Owner/Operator Manual (Current Revision)

• Recurring FAA Airworthiness Directives

• Aircraft & Engine Specifications or Type Certificate Data Sheets.

• Instructions for Continued Airworthiness.

• Fleet Campaign Alerts / Technical Guidance (Current Revision)

All work is to be performed in accordance with the manufacturer’s maintenance manuals/instructions or other data approved or acceptable by the administrator, and 14 CFR part 43. The elements of this program satisfy the requirements of applicable paragraphs of the Federal Aviation Regulations 14 CFR parts 43 and

91.

2. Duties and Responsibilities

The Director of Maintenance (DOM) Christopher L. Cooper, is responsible for administering the AIP as detailed in subsequent paragraphs and sections.

Contracted Maintenance Technicians and Non-Certified Repair Organizations must reference applicable sections of the AIP prior to performing any inspection and assure compliance with all applicable sections prior to approving the aircraft for return to service.

Contracted FAA Certified Repair Stations must reference applicable sections of the AIP prior to performing any inspection and assure compliance with all applicable sections prior to approving the aircraft for return to service. They shall also utilize the repair station’s work order and quality control system in accordance with the repair station’s procedures and quality control manuals.

3. AIP Control and Distribution The Director of Maintenance (DOM) is responsible for the control and distribution of the AIP. The Original

AIP will be kept in the DOM’s office. Additional copies of the AIP will be available electronically for each aircraft, for the purpose of utilization at each aircraft inspection event, and a hard copy kept in the AAOC

Library as a reference for all authorized company personnel.

4. Revisions to the AIP

The Director of Maintenance (DOM) is responsible for an annual review of the AIP.

The Director of Maintenance (DOM) is responsible for all AIP revisions which shall be revised when:

a) The aircraft manufacturer’s recommended inspection program is revised and the changes are deemed necessary for integration.

b) Airworthiness Authority’s Regulatory requirements deem it necessary.

c) Operational requirements deem it necessary.

d) The DOM deems it necessary.

Once a revision is deemed necessary, the current AIP will be amended with all changes identified in red text. The revised AIP will then be reviewed by the DOM prior to submission to the FAA for approval.

5. Adding Aircraft to the AIP

Any aircraft, engine or propeller to be added to the AIP must follow a current inspection plan as referenced in 14 CFR part 91.409. This includes compliance with the FAA approved airworthiness limitations and recommended overhaul requirements for components. Applicable FAA Airworthiness Directives must be complied with. The aircraft, engine and propeller shall conform to their original type design or properly altered condition.

In addition, all the inspection requirements listed in SECTION 2 and APPENDIX A shall be complied with.

If logbook research indicates that any of these inspections have been previously accomplished in accordance with another FAA AIP, and are current, that inspection may be accepted and will not need to be performed until it becomes due by the current AIP requirements. These additional inspection requirements do not require initial compliance for newly certificated aircraft until due per the appropriate monthly or hourly intervals from the new certification date.

Aircraft, Engine and Propeller records will be researched for the current status of all applicable inspection requirements, the results of which will be entered into a computerized tracking program, if not already accomplished. Any deficiencies shall be corrected prior to the aircraft being accepted into the AIP.

When an aircraft is approved to be maintained using this AIP, the following statement will be entered in the aircraft records: “This aircraft is now being maintained in accordance with Alliance Aviation

Operation Center Cessna 206 Approved Inspection Program”.

6. Life Limited Components/Parts

The Director of Maintenance (DOM) shall ensure that all life limited components/parts are replaced on time as required by the AIP. A computerized tracking program will be used to track life limited parts and will be updated as components/parts are replaced and whenever a change to the life limits warrants an update.

The tracking program will be referenced and updated during each scheduled periodic inspection.

Replacement of life limited components/parts will be documented in accordance with 14 CFR part 43.9,

43.10 and 91.417. No airworthiness limitations will be exceeded.

7. Scheduled Inspections/Unscheduled Maintenance

The Director of Maintenance (DOM) shall ensure all scheduled inspections are performed on time as required by the AIP. A computerized tracking program will be used to track and aid in scheduling inspections, Airworthiness Directives (ADs), Instructions for Continued Airworthiness (ICAs) and Service

Bulletins (SBs). The tracking program will be monitored by the Fleet Management Department and updated as inspections are completed. Unscheduled maintenance and Conditional inspections must be accomplished utilizing the most current manufacturer maintenance/service manuals/directives, where instructions have not been incorporated into this AIP.

8. Instructions for Performing Inspections and Returning Aircraft to

Service

In accordance with 14 CFR parts 43.11, 145.213 and 91.417, following the completion of an inspection performed under this AIP, the Director of Maintenance (DOM) shall ensure an appropriately rated person makes a maintenance record entry returning an aircraft to service. The entry shall contain the following at a minimum:

• Type of inspection performed.

• Total Time in Service (TIS), Total Landings and Date.

• Referenced manuals and directives used to perform inspections.

• Return to service statement as stated: “I certify this aircraft has been inspected in accordance with Alliance Aviation Operation Center’s Cessna 206 Approved

Inspection Program as required by FAR 91.409(f)(4), and is approved for return to service and found to be in airworthy condition”.

• Name, certificate number, kind of certificate, signature of the person approving the aircraft for return to service, and Certified Repair Station (CRS) number if applicable.

Technicians and inspection personnel must reference the most current manufacturer’s maintenance manuals and other associated publications when performing any maintenance on company aircraft.

All maintenance record entries will become part of the aircraft permanent records. The Fleet Management

Department shall ensure that a computerized tracking system is updated and all documents supporting airworthiness determinations are properly completed and added to the aircraft permanent records.

Discrepancies corrected during the inspection shall also be documented with a maintenance record entry.

There is no specific form used to document open discrepancies.

9. Removing Aircraft from the AIP

Aircraft removed from the AAOC AIP will be inducted into an inspection program in accordance with 14

CFR FAR 91.409, as elected by the new operator. When an aircraft is removed from the AIP, the following statement will be entered in the aircraft records: “This aircraft has been removed from the Alliance

Aviation Operation Center’s Cessna 206 Approved Inspection Program”.

SECTION 2: INSPECTION REQUIREMENTS

1. Required Inspections

Refer to Appendixes’ listed below for a comprehensive listing of all required inspections.

Appendix A: Component Time Limits and Inspection Program

Appendix B: Applicable Airworthiness Directives

Appendix C: Instructions for Continued Airworthiness (ICA), Technical Guidance Documents (TG) and

Fleet Campaign Alerts (FCA).

Note: The DOM shall ensure all mandatory and Alert Service Bulletins (ASBs) are reviewed to determine applicability and compliance.

2. Modification Inspections

Modifications and additional equipment installations applied to the aircraft under the authority of a

Supplement Type Certificate (STC) or FAA Field Approval will have that component or system inspected in accordance with the Instructions for Continued Airworthiness (ICAs) issued by the manufacturer of the equipment, the holder of the STC, or the agency/individual applying the field approval, as applicable.

These inspections shall be entered and tracked in a computerized tracking program, and are referenced in

Appendix C. The current revision will be provided as necessary for compliance, or as requested.

3. Summary

All inspections must be conducted under the condition and time limits stated herein. The instructions for inspection methods, techniques, practices and standards detailed and/or referenced in the manufacturer’s manual must be followed for accomplishment of all inspections listed in this AIP.

It is the responsibility of the maintenance technician and inspection personnel to review all inspection requirements for applicability for the particular aircraft authorized under this AIP prior to approving the aircraft for return to service.

SECTION 3: AIRCRAFT ZONING

AIRPLANE ZONING - DESCRIPTION AND OPERATION

A. The Model 206/T206 is divided into numbered zones to provide a method for locating components and/or placards throughout the airplane. The zones are identified by a three digit number as shown in the example below. The first digit in the sequence denotes the major zone (300 series for aft of cabin, 500 series for left wing, etc.). The second digit in the sequence further divides the zone into submajor zones (Zone 510 for inboard portion of the left wing and Zone 520 for outboard portion of the left wing, etc.). The third digit further divides the submajor zones into subdivisions (if no subdivision is needed, this digit is typically assigned as 0 (zero).

B. Major Zones.

A. 100 - Forward side of firewall and forward.

B. 200 - Aft side of firewall to end of cabin.

C. 300 - Aft of cabin to end of airplane.

D. 500 - Left wing.

E. 600 - Right wing.

F. 700 - Landing gear.

2. Description

For a breakdown of airplane zones, refer to Figure 1.

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APPENDIX A

SECTION 1: COMPONENT TIME LIMITS

This section gives a list of items which must be overhauled or replaced at specific time limits. Cessna-supplied replacement time limits show those items which Cessna has found necessary to overhaul or replace at specific time limits. Supplier-supplied replacement time limits show component time limits which have been given by an outside supplier for their products. If necessary, based on service use and inspection results, these components can be overhauled or replaced before their time limit is reached.

2. Cessna-Supplied Replacement Time Limits

A. Electrical Power (Cessna 206H Maintenance Manual Chapter 24)

(1) For airplanes equipped with the NAV III, Garmin G1000 Avionics System only:

(a) Avionics Switch - Replace every 2 years of operation. (see operation 6)

B. Equipment/Furnishings (Cessna 206H Maintenance Manual Chapter 25).

(1) Restraint System(s) - Replace every 10 years. (see operation 11)

C. Flight Controls (Cessna 206H Maintenance Manual Chapter 27).

D. Lights (Cessna 206H Maintenance Manual Chapter 33)

D. Position Light Assembly - Replace every 10,000 hours.

E. Beacon/Landing Light Switch – Replace every 4 years. (see operation 8)

E. Oxygen (Cessna 206H Maintenance Manual Chapter 35).

F. Oxymizer Cannula – Replace after 7 years. (see operation 10)

G. Passenger Mask - Replace after 7 years. (see operation 10)

H. Pilot Microphone Mask - Replace after 7 years. (see operation 10)

I. Oxygen bottle (cylinder) hydrostatic test and discard. (see operation 9 for hydrostatic)

NOTE: DOT Ratings are used to find the correct hydrostatic test and service life intervals.

NOTE: US DOT Exemption E 8162 was superseded by US DOT Special Permit SP 8162 dated May 11, 2007. DOT-SP 8162 applies to all cylinders manufactured after September 30, 2007 and DOT-E 8162 cylinders hydrostatic tested after July 1, 2006. Reference AVOX Service Information Letters SIL- 35-114 and SIL-35-116.

NOTE: DOT-SP 8162 applies to DOT3FC1850 cylinders.

(a) Hydrostatic test, refer to Table 1 for the correct Hydrostatic Test Interval and related Task.

Table 1. Oxygen Bottle Hydrostatic Test Intervals

DOT RATING HYDROSTATIC TEST INTERVAL

DOT3AA 5 years (NOTE 1)

DOT-SP 8162 5 years

NOTE: The DOT3AA text requirement is 5 years. If the hydrostatic test is overdue, you can complete the test at the next inspection phase interval.

(b) Discard, refer to Table 2 for the correct Service Life Interval and related Task.

Table 2. Oxygen Bottle Service Life Intervals

DOT RATING SERVICE LIFE INTERVAL

DOT3AA N/A

DOT-SP 8162 15 years

F. Vacuum (Cessna 206H Maintenance Manual Chapter 37).

J. C294502-0201 Gyro Filter - Replace every 2 years. (see operation 6)

K. Standby Dry Vacuum Pump - Replace every 10 years. (see operation 11)

G. Propeller (Cessna 206H Maintenance Manual Chapter 61).

H. Powerplant (Cessna 206H Maintenance Manual Chapter 71).

L. Airframe/Engine Flexible Fluid-Carrying Teflon Hoses - Replace every 20 years.

M. Airframe/Engine Rubber Hoses - Replace every 10 years. (see operation 11)

N. Engine Starter - Replace at every engine TBO.

O. Engine Shock Mounts - Replace at every engine TBO or on condition of the part shows the need for replacement.

P. Air Filter’s (206) - Replace every 500 hours or on condition of the part shows the need for replacement.

3. Supplier-Supplied Replacement Time Limits

Q. Equipment/Furnishings (Cessna 206H Maintenance Manual Chapter 25).

(1) ELT Battery - Refer to 14 CFR 91.207 for battery replacement time limits.

(2) Remote Mounted CO Detector - Replace 5 years. (See operation 9)

R. Fuel (Cessna 206H Maintenance Manual Chapter 28).

(1) Electric Fuel Pump – Replace at 10 Years if not overhauled.

(2) Lycoming IO-540-AC1A5 – Replace Engine Driven Fuel Pump Every 1000 Hours

(see Technical Guidance –TG-20-003).

S. Vacuum (Cessna 206H Maintenance Manual Chapter 37).

(1) 1H5-25 Vacuum Manifold - Refer to Airborne Air & Fuel Product

Reference Memo No. 39 or the latest revision for replacement time limits.

(see operation 5)

(2) Regulator Valve Filter - Replace at 100 hours. (see operation 2 & 4)

(3) Dry Vacuum Pump and Coupling - Replace every 500 hours.

(4) Aero Accessories Vacuum Manifolds Models AA1H25 and AA1H5-25A -

Refer to Tempest Service Bulletin SB-007 or the latest revision for replacement time limits. (see operation 5)

T. Propeller (Cessna 206H Maintenance Manual Chapter 61).

(1) Propeller - Refer to the latest propeller manual revision or applicable service bulletin for the overhaul time limits.

(2) Propeller Governor – Engine TBO or Any governor damaged by a propeller blade strike, propeller or engine lightning strike, engine detonation, oil contamination, or sudden engine stop. All such parts must be repaired or overhauled.

U. Powerplant (Cessna 206H Maintenance Manual Chapter 71).

(1) IO-540-AC1A5 and IO-540-AJ1A Engines - Refer to Lycoming SB480 revision for oil change time limits.

(2) IO520-F, TSIO520-C and TSIO520-M Engines – Refer to Continental

Maintenance Manual for oil change time limits.

V. Ignition (Cessna 206H Maintenance Manual Chapter 74).

(1) Slick Magnetos – Replace every 500 hours.

SECTION 2: INSPECTION PROGRAM

NOTE: The inspection charts contained within the Inspection Program are not intended to be all inclusive, for no such charts can replace the good judgment of a certified airframe and powerplant mechanic in performance of his duties. As the one primarily responsible for the airworthiness of the airplane, only qualified personnel/facilities will be selected to maintain the airplane.

This program is divided into four primary operations (Operations 1 through 4).

Operation 1 - 4 are complied with at 50-hour intervals. (i.e. OP 1 @ 50 hours, OP 2

@ 100 hours, OP 3 @ 150 hours, OP 4 @ 200 hours) Operations 1 through 4 must be completed within a calendar year from the last operation 5. Any operation 1 through 4 not accomplished within the previous calendar year from the last

Operation 5, must be performed during the operation 5. All remaining operations, (operations 6 through 11), must be complied with at the stated intervals.

Example 1: Aircraft 1 flew 50 hours in a calendar year requiring completion of

Operations 1 and 5. At the Operation 5 the remaining operations 2, 3, and 4 are also due. Then the next operation in sequence would be an operation 1.

Example 2: Aircraft 2 flew 250 hours in a calendar year. Operations 1-4 and an addition operation 1 were completed, only requiring completion of Operation 5 at the end of the calendar year. Operation 2 would be the next operation in sequence to be completed.

Operation 1 - Consists of all 50-hour interval inspections items to include items contained in the wing area.

Operation 2 - Consists of all 50-hour interval inspections items to include items contained in the engine compartment area.

Operation 3 - Consists of all 50-hour interval inspections items to include items contained in the fuselage area.

Operation 4 - Consists of all 50-hour interval inspections items to include items contained in the landing gear.

Operation 5 1 Year.

Operation 6 - Every 2 years.

Operation 7 - Every 3 years.

Operation 8 - Every 4 years.

Operation 9 - Every 5 years.

Operation 10 - Every 7 years.

Operation 11 - Every 10 years.

2. Procedure

A. A COMPLETE AIRPLANE INSPECTION consists of operations 1 through 4 and operation 5, completed in the previous 12 months, plus those Inspection Items contained in other operations which are due at the specified time.

B. The Component Time Limits section should be verified at each inspection interval to ensure proper overhaul and replacement requirements are accomplished at the specified times.

C. The inspection operations have been developed based on normal usage under average and severe environmental conditions. The operator's inspection intervals must not deviate from the inspection time limits shown in this AIP except as given below:

(1) Each interval can be exceeded by no greater than 10% or can be performed early at any time prior to the regular interval as provided below:

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

(b) In the event of early compliance of any operation scheduled, the next operation due point must be rescheduled to establish a new due point from the time of early accomplishment.

(2) The specified time/date of each AD and time specified for each Life Limited Part may be performed early but shall never exceed the stated compliance time/date.

3. General Inspection Terms and Guidelines

NOTE: When inspection criteria is required, this criteria is spelled out in the text. If more detailed instructions are required for an inspection, these instructions will be referenced out to appropriate locations (supplier publications and/or the maintenance manual).

A. Definitions of terms used through the inspection programs are as follows:

(1) ON CONDITION is defined as the necessary inspections and/or checks to determine that a malfunction or failure of the component will not occur prior to the next scheduled inspection.

(2) CONDITION is defined as inspection for (but not limited to) cleanliness, cracks, deformation, corrosion, wear, and loose or missing fasteners.

(3) SECURITY: Inspect for looseness of fasteners and fastener securing devices such as safety wire, cotter pins and self-locking nuts.

B. During Inspections, use the following general guidelines:

(1) MOVABLE PARTS: Inspect for lubrication, servicing, security of attachment, binding, excessive wear, safety wiring, proper operation, proper adjustment, correct travel, cracked fittings, security of hinges, defective bearings, cleanliness, corrosion, deformation, sealing, and tension.

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

(3) METAL PARTS: Inspect for security of attachment, cracks, metal distortion, and heat deterioration.

(4) WIRING: Inspect for security, chafing, burning, arcing, defective insulation, loose or broken terminals, heat deterioration, and corroded terminals.

(5) STRUCTURAL FASTENERS: Inspect for correct torque in accordance with applicable torque values.

(6) FILTERS, SCREENS, and FLUIDS: Inspect for cleanliness and the need for replacement at specified intervals.

(7) A system check (operation or function) that requires electrical power, must be performed using appropriate aircraft Voltage, +0.25 or -1.00 Volts, bus voltage.

This will make sure that all components are operating at their operational voltage.

C. Airplane file.

(1) Miscellaneous data, information, and licenses are a part of the airplane file.

Check that the following documents are up-to-date and in accordance with current Federal Aviation Regulations. Most of the items listed are required by the Airworthiness Authority.

(a) To be displayed in the airplane at all times:

1. Standard Airworthiness Certificate (FAA Form 8100-2).

2. Aircraft Registration Certificate (FAA Form 8050-3).

(b) To be carried in the airplane at all times:

1. Weight and Balance Data Sheets.

2. Equipment List.

3. Pilot’s Operating Handbook and FAA Approved Airplane Flight

Manual.

(c) To be made available upon request:

1. Airplane, Engine and Propeller Logbooks.

D. Corrosion Guideline and definitions.

(1) Level 1 Corrosion - Level 1 Corrosion is one or more of the items that follow:

Corrosion damage occurring between successive inspections, that is local and can be reworked or blended out within the allowable limit. Local corrosion damage that exceeds the allowable limit but can be attributed to an event not typical of the operator's usage or other airplanes in the same fleet (e.g., mercury spill).

(2) Level 2 Corrosion - Level 2 corrosion occurs between two successive corrosion inspection tasks that requires a single rework or blend-out that exceeds the allowable limit. A finding of Level 2 corrosion requires repair, reinforcement or complete or partial replacement of the applicable structure.

(3) Level 3 Corrosion - Level 3 corrosion occurs during the first or subsequent accomplishments of a corrosion inspection task that the operator determines to be an urgent airworthiness concern.

NOTE:

If Level 3 corrosion is determined at the implementation threshold or any repeat inspection, it should be reported. Any corrosion that is more than the maximum acceptable to the design approval holder or the FAA (or applicable regulatory authority) must be reported in accordance with current regulations. This determination should be conducted jointly with the design approval holder.

(4) Light Corrosion - Light corrosion is corrosion damage so slight that removal and blend out over multiple repeat intervals (RI) may be accomplished before material loss exceeds the allowable limit.

(5) Local Corrosion - Generally, local corrosion is corrosion of a skin or web

(wing, fuselage, empennage or strut) that does not exceed one frame, stringer or stiffener bay. Local corrosion is typically limited to a single frame, chord, stringer or stiffener or the corrosion of more than one frame, chord, stringer or stiffener where no corrosion exists on two adjacent members on each side of the corroded member.

(6) Aircraft wash every 50 hours if located in severe area and every 100 hours or

1 year if located in moderate or mild. (See corrosion severity legend and

Aviation Operation Handbook 9.15)

(7) Aircraft wax every 6 months if located in severe area and 1 year if located in moderate or mild. (See corrosion severity legend and Aviation Operation

Handbook 9.15)

INSPECTION OPERATION 1

Date:

Registration Number:

Serial Number:

Total Time:

1. Description

A. Operation 1 gives a list of item(s) which has all 50-hour interval inspection items and those items contained in the wings. Items from other areas are included to meet their required time interval.

B. Inspection items are given in the order of the zone in which the inspection is to be completed.

Frequently, the tasks define more specifically the scope and extent of each required inspection.

C. The right portion of each page gives space for the mechanics and inspector's initials and remarks. A copy of these pages can be used as a checklist when these inspections are completed.

2. General Inspection Criteria

A. During each of the specified inspection tasks in this section, more general inspections of the adjacent areas must be done while access is available. These general inspections are used to find apparent conditions which can need more maintenance

B. If a component or system is changed after a required task has been completed, then that specified task must be done again to make sure it is correct before the system or component is returned to service.

C. Do a preflight inspection after these inspections are completed to make sure all the required items are correctly serviced. Refer to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.

D. A Corrosion Prevention and Control Program is a comprehensive approach to controlling corrosion such that the load carrying capability of an airplane structure is not degraded below a level necessary to maintain Airworthiness. It contains the corrosion program inspections, a definition of corrosion levels, implementation thresholds, a repeat interval for task accomplishment in each area or zone and specific procedures that if corrosion damage exceeds level 1.

TASK ZONE MECH INSP REMARKS

GENERAL

01 - Aircraft/Engine Monitoring System - Download or replace card for review, and archive recorded data. (reference TG-13-0002).

02 - Research Chapter 4 / Airworthiness Limitations to ensure life-limited components are within limitations.

All

03 - Verify ADs have been incorporated and are properly documented in the corresponding logbook (Appendix B).

All

04 - Interior Placards, Exterior Placards, Decals, Markings and Identification Plates - Inspect for security of installation and legibility.

All

05 - Aircraft Corrosion Inspection - General visual inspection of aircraft. See Appendix A for Corrosion Severity Map See Appendix C Item 36. (All Corrosion Discrepancies must be sent to FM Planner for Review).

All

06 - Aircraft Wash- See Appendix C for Zone determination and applicability All

POWERPLANT & PROPELLER

01 - Spinner - Complete a check of its general condition and that it is correctly attached.

02 - Propeller Blades - Inspect for cracks, dents, nicks, scratches, erosion, corrosion, or other damage.

03 - Propeller Mounting - Check for security of installation.

04 - Alternate Induction Air System - Check for obstructions, operation, and security.

05 - Exhaust System - Inspect for cracks and security. Special check in area of heat exchanger.

06 - Exhaust System (turbocharged engine) - Inspect couplings, seals, clamps, and expansion joints for cracks. Special check in area of heat exchanger.

07 - Perform inspection on the multi-segment V- Band coupling clamps.

08 - Engine Oil - Drain oil sump and oil cooler.

Check for metal particles or foreign material in filter, on sump drain plug, and on engine suction screen.

Replace filter and refill with recommended grade aviation oil. Refer to installed engine maintenance manual for procedures. See also Lycoming MSB 480F or latest revision (as applicable). (Reference

TG-21-006)

FUSELAGE / INTERIOR

01 - Communication Antennas and Cables - Inspect for security of attachment, connection, and condition.

02 - Windows and Windshield - Inspect general condition. Check latches, hinges, and seals for condition, operation, and security of attachment.

03 - Ventilation System - Inspect clamps, hoses, and valves for condition and security.

04 - Heater Components, Inlets, and Outlets - Inspect all lines, ducts, clamps, seals, and gaskets for condition, restriction, and security.

05 - Seats - Examine the seats to make sure they are serviceable and installed correctly. Make sure the seat stops and adjustment mechanism operate correctly. Examine the seat recline control and attaching hardware to make sure the hardware and lock are not damaged and are correctly installed.

Lubricate the threads of the Seat Crank Handle Assembly with MIL-PRF-81322 general purpose grease.

06 - Restraint System, front and rear - Check belts for thinning, fraying, cutting, broken stitches, or ultra-violet deterioration. Check system hardware for security of installation.

07 - Instruments - Check general condition and markings for legibility. 220

08 - Fuel Selector Valve - Check controls for detent in each position, security of attachment, and for proper placarding.

09 - Fuel Selector - Using quick drain, ensure no contamination exists. 224

11 - Portable Hand Fire Extinguisher - Inspect for proper operating pressure, condition, security of installation, and servicing date.

12 - Emergency Locator Transmitter - Examine for security of attachment and check operation by verifying transmitter output. Check cumulative time and useful life of batteries in accordance with 14 CFR Part 91.207.

13 - Navigation, Beacon, Strobe, and Landing Lights - Check operation, condition of lens, and security of attachment.

TAIL / STABILIZERS / FLIGHT CONTROLS

01 - Rudder Control - Check freedom of movement and proper operation through full travel.

02 - Elevator Control - Check freedom of movement and proper operation through full travel.

03 - Elevator Trim Tab and Hinges - Check condition, security, and operation.

WINGS / FLIGHT CONTROLS

01 - Aileron Controls - Check freedom of movement and proper operation through full travel.

02 - Ailerons and Cables - Check operation and security of stops. Check cables for tension, routing, fraying, corrosion, and turnbuckle safety.

Check travel if cable tension requires adjustment or if stops are damaged. Check fairleads and rub strips for condition.

03 - Flaps - Check tracks, rollers, and control rods for security of attachment. Check rod end bearings for corrosion. Check operation.

04 - Flap Structure, Linkage, Bellcranks, Pulleys, and Pulley Brackets - Check for condition, operation and security.

05 - Flaps and Cables - Check cables for proper tension, routing, fraying, corrosion, and turnbuckle safety. Check travel if cable tension requires adjustment.

06 - Fuel System - Inspect plumbing and components for mounting and security.

07 - Fuel Tank Vent Lines and Vent Valves - Check vents for obstruction and proper positioning.

Check valves for operation.

08 - Integral Fuel Bays - Check for evidence of leakage and condition of fuel caps/seals, adapters, and placards. Using quick drains, ensure no contamination exists. Check quick drains for proper shut off.

09 - Fuel Reservoir - Using quick drain, ensure no contamination exists.

10 - Fuel Strainer, Drain Valve, and Controls - Checkfreedom of movement, security, and proper operation. Disassemble, flush, and clean screen and bowl.

11 - Pitot Tube and Stall Warning Vane - Check for condition and obstructions and verify operation of anti-ice heat.

12 - Wing Struts and Strut Fairings - Check for dents, cracks, loose screws and rivets, and condition of paint.

13 - Wing Surfaces and Tips - Inspect for skin damage, loose rivets, and condition of paint.

14 - Wing Access Plates - Check for damage and security on installation.

15 - Wing Spar and Wing Strut Fittings - Check for evidence of wear. Check attach bolts for indications of looseness and retorque as required.

16 - Wing Structure - Inspect spars, ribs, skins, and stringers for cracks, wrinkles, loose rivets, corrosion, or other damage.

17 - Wing structure internal. Make sure you inspect these areas: 1. Main spar upper and lower carry-thru fittings. 2. Main spar upper and lower caps. 3. Main spar web.

18 - Flap Track Brackets - Inspect LH/RH flap track attach brackets and surrounding area for cracks, corrosion, loose rivets, and overall condition.

(Reference FCA QC-041)

19 - Aileron Structure, Control Rods, Hinges, Balance Weights, Bell Cranks, Linkage, Bolts, Pulleys, and Pulley Brackets - Check condition, operation, and security of attachment.

20 - Ailerons and Hinges - Check condition, security, and operation.

21 - Flap Motor, Actuator, and Limit Switches - Check wiring and terminals for condition and security. Check actuator for condition and security.

Clean and lubricate jack screw actuator threads.

LANDING GEAR

01 - Tires - Check tread wear and general condition. Check for proper inflation.

02 - Wheels, Brake Discs, and Linings - Inspect for wear, cracks, warps, dents, or other damage.

Check wheel through-bolts and nuts for looseness.

*** End of Inspection Operation 1 Inspection Items ***

INSPECTION OPERATION 2

A. Operation 2 gives a list of item(s) which has all 50-hour interval inspection items and those items contained in the engine compartment. Items from other areas are included to meet their required time interval.

B. Inspection items are given in the order of the zone in which the inspection is to be completed.

Frequently, the tasks define more specifically the scope and extent of each required inspection

C. The right portion of each page gives space for the mechanics and inspector's initials and remarks.

A copy of these pages can be used as a checklist when these inspections are completed.

find apparent conditions which can need more maintenance.

B. If a component or system is changed after a required task has been completed, then that specified task must be done again to make sure it is correct before the system or component is returned to service.

C. Do a preflight inspection after these inspections are completed to make sure all the required items are correctly serviced. Refer to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.

D. A Corrosion Prevention and Control Program is a comprehensive approach to controlling corrosion such that the load carrying capability of an airplane structure is not degraded below a level necessary to maintain Airworthiness. It contains the corrosion program inspections, a definition of corrosion levels, implementation thresholds, a repeat interval for task

01 - Aircraft/Engine Monitoring System - Download or replace card for review, and archive recorded data.

(reference TG-13-0002)

All

02 - Research Chapter 4 / Airworthiness Limitations to ensure life-limited components are within limitations. All

03 - Verify ADs have been incorporated and are properly documented in the corresponding logbook (Appendix B). All

04 - Interior Placards, Exterior Placards, Decals, Markings and Identification Plates - Inspect for security of installation and legibility.

All

05 - Aircraft Corrosion Inspection - General visual inspection of aircraft. See Appendix A for Corrosion Severity Map See Appendix C Item 36 (All Corrosion Discrepancies must be sent to FM Planner for Review).

06 - Aircraft Wash- See Appendix A for Zone determination and applicability All

07 - Aircraft Wax- See Appendix A for Zone determination and applicability All

POWERPLANT & PROPELLER

01 - Spinner - Complete a check of its general condition and that it is correctly attached. Make sure it has a minimum clearance of

0.14 inch (3.56 mm) to the propeller blades.

02 - Spinner and Spinner Bulkhead - Remove spinner, wash, and inspect for cracks and fractures. 110

03 - Propeller Blades - Inspect for cracks, dents, nicks, scratches, erosion, corrosion, or other damage. 110

04 - Propeller Hub - Check general condition. 110

05 - Propeller Mounting/Bolts - Check for security of installation. Inspect mounting bolts and safety wire for signs of looseness. Retorque mounting bolts as required.

06 - Propeller Heat Slip Rings, Brushes, and Boots - Inspect for condition and security. Perform operational check.

07 - Propeller Governor and Control - Inspect for oil and grease leaks. If leakage is evident, refer to Propeller Service Manual.

08 - Propeller Governor and Control - Examine the security and operation of the controls. The maximum linear freeplay is 0.050 inch.

09 - Cold and Hot Air Hoses - Check condition, routing, and security. 120

10 - Alternator and Mounting Bracket - Check condition and security. Check alternator belts for condition and proper adjustment. Check belt tension.

11 - Alternator Electrical Connections - Check condition and security. Check for cracks on the shank of terminals connecting to alternator BAT and GND connection posts.

Make sure the terminals are not bent or under mechanical stress caused by the routing of the attached wire. Make sure the field wire connector on alternators is secure and firmly latched.

12 - Main Battery - Examine the general condition and security. Complete a check of the level of electrolyte (if applicable).

13 - Main Battery Box and Cables - Clean and remove any corrosion. Examine the cables for routing, support, and security of the connections.

14 - External Power Receptacle and Power Cables - Inspect for condition and security. 120

15 - Auxiliary (Electric) Fuel Pump - Check pump and fittings for condition, operation, security. 120

16 - Vacuum Pumps - Check for condition and security.

Check vacuum system breather line for obstructions, condition, and security (If installed).

17 - Vacuum System Hoses - Inspect for hardness, deterioration, looseness, or collapsed hoses (if installed). 120

18 - Gyro Filter - Inspect for damage, deterioration and contamination. Clean or replace if required (if installed). 120

19 - Regulator Valve and Filter - Inspect valve assembly for security of installation. Visually inspect filter for damage, deterioration and contamination. Clean or replace if required (If installed). Replacement of filter every 100 hours

20 - Firewall Structure - Inspect for wrinkles, damage, cracks, sheared rivets, etc. 120

21 - Remove the engine compressor inlet duct. Examine the compressor for blade condition on the impeller and oil deposits in the turbocharger. Make sure the compressor turns freely (if applicable).

22 - Engine Shock Mounts, Engine Mount Structure, and Ground Straps - Check condition, security, and alignment. 120

23 - Fuel line (Stainless steel tube assembly) and support clamp inspection and installation. 120

24 - Engine - Inspect for evidence of oil and fuel leaks.

Wash engine and check for security of accessories. 120

25 - Turbocharger (if applicable) - Inspect turbocharger mounting brackets, ducting, linkage, and attaching parts for general condition, leakage or damage, and security of attachment. Check waste gate, actuator, controller, oil and vent lines, over-boost relief valve, and compressor housing for leakage, apparent damage, security of attachment, and evidence of wear. Check waste gate return spring for condition and security.

26 - Turbocharger (if applicable) - Examine the turbocharger for burned areas, bulges, or cracks. Use a flashlight and mirror in the tailpipe to examine the turbine for coking, carbonization, oil deposits, and turbine impellers for damage.

27 - Cowling and Cowl Flaps - Inspect for cracks, dents, other damage and security of cowl fasteners. Check cowl flaps for condition, security, and operation. Check cowl flap controls for freedom of movement through full travel.

28 - Alternate Induction Air System - Check for obstructions, operation, and security. 120

29 - Engine, Induction System – Remove the duct that is between the filter box and the induction air elbow. Make sure the duct support wire is correctly placed, there are no loose, or broken cords and the fabric is not torn.

Install an operable duct and make sure there is 0.25 inch (6.35 mm) of wire and cord under the clamps that attach the duct to the filter box and elbow. Make sure the clamps, tubes, and duct are correctly installed and make sure there are no leaks.

30 - Induction Airbox, Valves, Doors, and Controls – Remove air filter and inspect hinges, doors, seals, and attaching parts for wear and security. Check operation.

31 - Induction Air Filter - Remove and clean. Inspect for damage and service. 120

32 - Crankcase, Oil Sump, and Accessory Section - Inspect for cracks and evidence of oil leakage. Check bolts and nuts for looseness and retorque as necessary.

Check crankcase breather lines for obstructions, security, and general condition.

33 - Hoses, Metal Lines, Clamps, and Fittings - Inspect for signs of oil and fuel leaks, abrasions, chafing, condition, security, proper routing and support and for evidence of deterioration.

34 - Engine Baffles and Seals - Check condition and security of attachment. 120

35 - Engine Cylinders, Rocker Box Covers, and Pushrod Housings - Check for fin damage, cracks, oil leakage, security of attachment, and general condition.

36 - Cylinder Compression - Complete a differential compression test and provide results. (Reference TG-14- 0004)

37 - Engine-Driven Fuel Pump - Check for evidence of leakage, security of attachment, and general condition. 120

38 - Fuel Injection System - Check system for security and condition. Clean fuel inlet screen, check and clean injection nozzles and screens (if evidence of contamination is found), and lubricate air throttle shaft.

39 - Magnetos - Examine the external condition and for correct installation. Examine the condition of the electrical leads. Complete a check of the engine timing (external timing).

40 - Ignition System (Switch, Harness and Insulators) - Check for proper routing, deterioration, damage, security and condition of terminals.

41 - Spark Plugs - Remove, clean, analyze, test, gap, and rotate top plugs to bottom and bottom plugs to top.

42 - Engine Controls and Linkage - Examine the general condition and freedom of movement through the full range. Complete a check for the proper travel, security of attachment, and for evidence of wear. Complete a check of the friction lock and vernier adjustment for proper operation. Complete a check that the throttle, fuel mixture, and propeller governor arms operate through their full arc of travel. The maximum linear free play is

0.050 inch.

43 - Exhaust System - Inspect couplings, seals, clamps, and expansion joints for cracks and security. Special check in area of heat exchanger.

44 - Perform inspection on the multi-segment V-Band coupling clamps. 120

45 - Engine Oil - Drain oil sump and oil cooler. Check for metal particles or foreign material in filter, on sump drain plug, and on engine suction screen. Replace filter and refill with recommended grade aviation oil. Refer to installed engine maintenance manual for procedures.

See also Lycoming MSB 480F or latest revision (as applicable). (Reference TG-21-006)

46 - Oil Cooler - Check for obstructions, leaks, and security of attachment. 120

47 - Starter and Electrical Connections - Check security and condition of starter, electrical connection and cable. 120

48 - Bendix Drive Starter Assembly - Clean and lubricate starter drive assembly. 120

49 - N400 Alternator (if installed) - Inspect and service.

Refer to Appendix C Item 2 (National Airparts N400 General Information Manual).

50 - Idle and Mixture Adjustment - Check idle speed and idle mixture (lean rise). Adjust if necessary. 120

51 - Engine support structure. Make sure you inspect these areas: 1. Tunnel structure side walls. 2. Shock mount support brackets.

FUSELAGE / INTERIOR

01 - MVP Installation (if installed) - Check all parts installed in conjunction with the MVP. Refer to Appendix C Item 4 (Electronics International MVP-50).

02 - KLN-94 Installation (if installed) - Inspect for damage, wear, and chafing. Refer to Appendix C Item 28 (Honeywell KLN-94 Maintenance Manual).

05 - Camera Mount (if installed) - Inspect electronics and camera mount support assembly. Refer to Appendix C Item 27 (Soloy Aviation Service Instruction).

06 - Gyrocam Dovetail Mount Gimbal (if installed) - Inspect for loose or missing hardware and for damage.

Refer to Appendix C Item 05 (Lockheed Martin Gyrocam

ICA).

07 - Wescam Dovetail (if installed) - Inspect for loose or missing hardware and for damage. Refer to Appendix C Item 06 (Wescam DT-1 Dovetail Set ICA).

08 - Paravian Camera Mount (if installed) - Inspect electronics support module installation brackets and beams for cracks and installation security. Refer to Appendix C Item 07 (Integrated Surveillance and Defense

ICA).

09 - Split Forward Cargo Door Window (if installed) - Inspect per Inspection check list 2-I. Refer to Appendix C Item 31 (Airworthiness Resources Corporation)

10 - Gyrocam Desiccant (if installed) - Check Gyrocam desiccant assembly is serviceable. Refer to Appendix C Item 08 (Gyrocam DNV Manual ICA).

TAIL / STABILIZERS / FLIGHT CONTROLS

01 - Rudder Control - Check freedom of movement and proper operation through full travel.

02 - Elevator Control - Check freedom of movement and proper operation through full travel.

WINGS / FLIGHT CONTROLS

01 - Aileron Controls - Check freedom of movement and proper operation through full travel.

02 - Flap Track Brackets - Inspect LH/RH flap track attach brackets and surrounding area for cracks, corrosion, loose rivets, and overall condition. (Reference FCA QC- 041)

LANDING GEAR

01 - Tires - Check tread wear and general condition.

Check for proper inflation.

02 - Wheels, Brake Discs, and Linings - Inspect for wear, cracks, warps, dents, or other damage. Check wheel through-bolts and nuts for looseness.

*** End of Inspection Operation 2 Inspection Items ***

INSPECTION OPERATION 3

A. Operation 3 gives a list of item(s) which has all 50-hour interval inspection items and those items contained in the fuselage. Items from other areas are included to meet their required time interval.

B. Inspection items are given in the order of the zone in which the inspection is to be completed.

Frequently, the tasks define more specifically the scope and extent of each required inspection.

C. The right portion of each page gives space for the mechanics and inspector's initials and remarks.

find apparent conditions which can need more maintenance.

B. If a…