Revision Transmittal

May 16, 2014

TO: Cessna Distributors and Caravan Authorized Service Facilities

SUBJECT: Caravan Service Bulletin CAB11-5 Revision 1: Time Limits/Maintenance Checks - New 208/208B

Task-Based Inspection Program

REASON FOR REVISION

To add airplanes to the serial effectivity.

Due to denial by the FAA of Cessna's petition for exemption from CFR 14 Part 91.409(a) and (b), Cessna

wishes to clarify the instructions regarding the task-based inspection program.

To change the compliance from Mandatory to Optional.

Miscellaneous changes as necessary.

REQUIRED ACTION

Please replace any copy of CAB11-5 with the attached copy of CAB11-5 Revision 1 which is printed in

its entirety.

NOTE: Compliance with CAB11-5 Revision 1 is required for airplanes that were able to comply with the

Original Issue.

LOG OF EFFECTIVE PAGES

Page No. Date

1 May 16, 2014

2 May 16, 2014

3 May 16, 2014

**** ***

Page 1 of 1

To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and

prevailing government regulations. Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the

requirements of this publication.

Cessna Aircraft Company, Customer Service, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 517-5800, Facsimile (316) 517-7271

www.cessnasupport.com

COPYRIGHT © 2014

Caravan

Service Bulletin

May 16, 2014 CAB11-5

Revision 1

TITLE

TIME LIMITS/MAINTENANCE CHECKS - NEW 208/208B TASK-BASED INSPECTION PROGRAM

EFFECTIVITY

Model Serial Numbers

208 20800001 and On

208B 208B0001 and On

PURPOSE

The purpose of this Service Bulletin is to clarify the instructions provided in CAB11-5 Original Issue to

incorporate the new, task-based inspection program on the Model 208/208B presented in Revision 24 to the

maintenance manual. The task-based inspection program replaced the inspection program from Revision 23

of the maintenance manual and the phase card inspections. The maintenance manual has since revised to

Revision 27.

U.S. registered airplanes operating under CFR 14 Part 91 that have not obtained approval for the task-based

maintenance program as a progressive inspection under 91.409 paragraph d or that have not obtained an

exemption from CFR 14 Part 91.409(a) and (b) must be inspected as required by 91.409(a) and (b).

The task-based inspection program was incorporated on the Model 208/208B in order to make maintenance

procedures and inspections more efficient for operators who obtain approval for the task-based inspection

program as an approved aircraft inspection program AAIP under part 135 of the U.S. aviation regulations or for

operators who adopt the task-based program as a manufacturer’s recommended program as authorized by their

local regulatory authorities. Cessna has reviewed all item codes for efficiency, applicability, and effectiveness.

• Many item codes were incorporated into one task.

• Item codes that were found to be not applicable or not effective were eliminated.

• Many item code intervals were extended within the new tasks.

• The scheduled maintenance checks in Chapter 5-20-01 were removed from the maintenance manual.

• Chapter 5-10-00 has incorporated inspection documents to replace the progressive care program and the

inspection operations.

• Inspection time limits in Chapter 5-10-01 have tasks incorporated.

• Phase cards will no longer be sold, revised, or supported by Cessna Aircraft Company.

• The supplemental inspection documents (SIDS) were incorporated into the tasks. Refer to Chapter

5-14-00 for the conversion matrix.

Original Issue: July 8, 2011 Page 1 of 3

To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and

prevailing government regulations. Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the

requirements of this publication.

Cessna Aircraft Company, Customer Service, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 517-5800, Facsimile (316) 517-7271

www.cessnasupport.com

COPYRIGHT © 2011
• The CPCPs were incorporated into the tasks and incorporated into the task-based program.

COMPLIANCE

Optional: Conversion to the manufacturer’s recommended 208/208B Task-Based Inspection Program may be

accomplished at the owner's discretion with prior approval from your local regulatory authority.

NOTE: Compliance with CAB11-5 Revision 1 is required for airplanes that were able to comply with the

Original Issue.

NOTE: Cessna no longer supports the previous inspection programs. There will be no updates to the phase

cards or the maintenance program they supported.

NOTE: If you wish to continue the phase card program, you may apply to your local regulatory authority to

have the continued use of the phase cards approved for your airplanes.

NOTE: For United States operators who operate per Part 91 of Title 14, Code of Federal Regulations, the

manufacturer's recommended task-based inspection program provided in the maintenance manual

does not relieve the requirements for an annual and/or 100 hour inspection per Part 91.409(a) and

(b). It is the person with the Inspection Authorization's (or equivalent) responsibility to select the

necessary inspections to create a checklist to make sure that the scope and detail of an annual

and/or 100 hour is performed in accordance with Part 43 Appendix D of Title 14, Code of Federal

Regulations. Otherwise, the individual owner/operator may refer to Part 11 to petition the FAA for an

exemption from Part 91.409(a) and (b) in order to use the manufacturer's recommended task-based

inspection program as written.

APPROVAL

FAA approval has been obtained on technical data in this publication that affects airplane type design.

REFERENCE

Model 208 Maintenance Manual

NOTE: Make sure all publications used are complete and current. Refer to cessnasupport.com.

ACCOMPLISHMENT INSTRUCTIONS

1. Attached are the necessary documents from Revision 23, [Chapter 5-10-00 Inspections, Chapter 5-10-01

Inspection Time Limits, Chapter 5-12-00 Progressive Care Program, Chapter 5-13-00 Supplemental

Inspection Document, Chapter 5-14-00 Listing of Supplemental Inspections, Chapter 5-20-01 Scheduled

Inspection Checks, Chapter 5-30-00 Corrosion Prevention and Control Program, Chapter 5-30-01

Corrosion Prevention and Control Inspections (Airplanes without TKS Anti-Ice System), Chapter 5-30-02

Corrosion Prevention and Control Inspections (Airplanes with TKS Anti-Ice System), and Chapter

5-30-05 Corrosion Prevention and Control Program - Appendix] which are valid until you change to the

new task-based inspection program.

NOTE: Be sure to keep this Service Bulletin with the attached documents.

2. Revision 08 or later of the Phase cards was no longer valid after December 31, 2013. At that time, the

only Cessna-provided scheduled maintenance plan will be the task-based inspection program provided

in the maintenance manual Revision 24 or later.

3. For operators who will apply for an AAIP-type inspection, this Service Bulletin is to be completed at your

next annual inspection, at the end of your current phase card cycle (Phase 4, 8, or 12), at the end of

your Progressive Care cycle (Operation 4), or if your total aircraft time is under 100 hours. Complete

Inspection Document 5-15-0A. Using the completion dates and hours of Inspection Document 5-15-0A,

calculate the due times for Inspection Documents 1 through 22. 5-15 M Series Inspection Documents

match the current 5-12 M Series Inspection Operations and the due times remain the same.

CAB11-5 Revision 1

Page 2 May 16, 2014
• All Chapter 4 inspection and replacement item due times will not change and will remain at the

current due times.

• All Chapter 5-11-00 inspection and replacement item due times will not change and will remain at

the current due times.

• Altimeter, Pitot/Static Airspeed Test, and Static Port Vertical Speed (Rate of Climb) Test and

Inspections required in accordance with FAR 91.411 due times will not change and will remain at

the current due times.

• Portable Hand Fire Extinguisher Inspection due times will not change and will remain at the current

due times.

• Cockpit and/or Cabin Mounted Halon-Type Fire Extinguishers Inspection due times will not change

and will remain at the current due times.

• Cockpit and/or Cabin Mounted Halon-Type Fire Extinguishers Hydrostatic Test Inspection due times

will not change and will remain at the current due times.

• Oxygen Cylinder (DOT-E 8162) Hydrostatic Test Inspection due times will not change and will

remain at the current due times.

• Oxygen Cylinder (DOT-SP 8162) Hydrostatic Test Inspection due times will not change and will

remain at the current due times.

• Emergency Locator Transmitter Inspections required in accordance with FAR 91.207 due times will

not change and will remain at the current due times.

• Emergency Locator Transmitter Battery Inspections required in accordance with FAR 91.207 due

times will not change and will remain at the current due times.

• Battery capacity checks due times will not change and will remain at the current due times. After the

capacity check has been completed, the new inspection interval can be used.

4. Any questions about the new inspection program can be directed to Customer Service at 1-316-517-5800.

5. Record that this Service Bulletin has been completed. This will indicate the date of conversion.

A. Complete a Maintenance Transaction Record (or equivalent) that shows compliance with this

Service Bulletin and completion of Inspection Document 5-15-0A.

B. Put a copy of the completed Maintenance Transaction Record (or equivalent) in the airplane logbook.

C. Send a copy of the completed Maintenance Transaction Record to: CESCOM (phone 316-462-2267)

at: CESCOM C/O, Camp Systems International, 8200 East 34th Street North, Building 1600 Suite

1607, Wichita, KS 67226, Fax: 316-462-2443.

*******

CAB11-5 Revision 1

May 16, 2014 Page 3

AFS-12-419-E 

 Exemption No. 10981

UNITED STATES OF AMERICA 

DEPARTMENT OF TRANSPORTATION 

FEDERAL AVIATION ADMINISTRATION 

WASHINGTON, DC 20591 

 

In the matter of the petition of 

 

CESSNA AIRCRAFT COMPANY Regulatory Docket No. FAA-2012- 0604

 

for an exemption from § 91.409(a) and (b) 

of Title 14, Code of Federal Regulations 

 

 

DENIAL OF EXEMPTION 

 By letters dated May 30, 2012 and July 9, 2012, Mr. Gerald P. Snook, Manager, 

Maintenance Engineering, Cessna Aircraft Company (Cessna), One Citation Lane, Wichita, 

Kansas 67209, petitioned the Federal Aviation Administration (FAA) on behalf of Cessna for 

an exemption from § 91.409(a) and (b) of Title 14, Code of Federal Regulations (14 CFR). 

The proposed exemption, if granted, would allow operators to select a manufacturer 

recommended program that is task based and integrated into the 208/208B published aircraft 

maintenance manual, revision 24 or later. 

The petitioner requests relief from the following regulations:

Section 91.409(a), prescribes in pertinent part that, except as provided in paragraph (c) 

of the section

1

 no person may operate an aircraft unless, within the preceding 12 

calendar months, it has had an annual inspection in accordance with part 43 and has 

been approved for return to service. Section 91.409(b), prescribes, in pertinent part, that

 

1

 Section 91 .409(c) provides tor exceptions to this requirement, including when an aircraft is inspected under 

another type of inspection program. Relevant to this petition for exemption is an inspection program described 

in § 91 .409(t)(3)- a current inspection program recommended by the airplane's manufacturer. Under 

§ 91.409(e), however, that program is available to "large airplanes (to which part 125 is not applicable), turbojet 

multiengine airplanes, turbopropeller-powered multiengine airplanes, and turbine-powered rotorcraft." Cessna 

Model CE208 airplanes do not fit that description. 
2

no person may operate an aircraft carrying any person (other than a crewmember) for hire,

and no person may give flight instruction for hire in an aircraft which that person 

provides, unless within the preceding 100 hours of time in service the aircraft has

received an annual or 100-hour inspection and been approved for return to service in

accordance with part 43.

Cessna petitioned for this exemption so operators of its Model CE208 aircraft could use a 

task-based inspection program it developed in lieu of the annual and 100-hour inspections 

required by § 91.409(a) and (b). Cessna's program would qualify as a current inspection 

program recommended by the manufacturer under the provisions of§ 91.409(f)(3), but the 

Model CE208 aircraft do not meet the criteria of the large airplanes authorized by 

§ 91.409(e) to use that program.

The petitioner supports its request with the following information:

Cessna seeks relief that would enable use of a current inspection program recommended by 

Cessna the manufacturer, in lieu of the annual inspection requirements of 

§ 91.409(a)(b) for the company’s model CE-208 aircraft. Cessna developed a task-based 

manufacturer-recommended inspection program for the CE-208 and 208B aircraft. This 

program is published in the CE-208 aircraft maintenance manual, revision 24 or later. 

The petitioner states the 208/208B inspection document task-based inspection program was 

developed from the 208/208B phasecard inspection program that was accepted by the FAA as 

“a manufacturer’s approved inspection program” on October 24, 1990. This exemption would 

allow operators to select a manufacturer-recommended program that is task based and 

integrated into the 208/208B published instructions for continued airworthiness. 

The petitioner states field data was used to identify the interval that an item needed to be 

inspected so there would be minimum wear and tear to the airframe. The minimum wear and 

tear and risk of inducing damage occurs when the best inspection intervals are used. By using 

the task-based inspection document program, a manufacturer-recommended program with 

each inspection task interval based on field input, customers are assured their airplanes are 

being inspected at the optimum time by all maintenance providers. The CE-208 operators, 

passengers, and cargo will benefit because this program would expand qualified maintenance 

repair and overhaul support of the CE-208, enabling maintenance providers to inspect the 

airplane as efficiently as possible while maintaining the highest level of safety. The public 

would benefit from this exemption because the airplane’s availability would be increased, and 

the aircraft will be inspected to a higher level of safety. 

Although requesting relief from both§ 91.409(a) (annual inspections) and§ 91.409(b) (100-

hour inspections), the petitioner addresses only annual inspections in its supporting 

information. The petitioner states that the regulation requires an annual inspection developed 

by an inspection authorization (IA) holder that follows 14 CFR part 43, Appendix D. Each IA 

holder controls the level of detail at which the airplane is inspected. Conversely, use of the 
3

inspection document program to maintain the airplane would benefit the public by providing a 

standard set of inspection task instructions for all technicians to follow that were developed 

with the latest FAA guidance. When the technicians follow the inspection document program, 

variations would be at a minimum. This would provide the customers with a consistent level 

of safety for all units. 

The petitioner states the Model 208/208B airplane is delivered worldwide, and the 208 

airplane maintenance manual is used worldwide. Therefore, the petitioner requests to exercise 

the privileges of this exemption outside the United States to provide operators with the 

benefits on increased safety and operational availability. 

A summary of the petition was published in the Federal Register on October 9, 2012 (77 FR 

61469). No comments were received. 

The FAA’s analysis is as follows: 

The FAA finds that Cessna's task-based inspection program is not compatible with the 

agency's requirements for annual and 100-hour inspections currently applicable to the Model 

CE208/208B airplanes. Use of the task-based program in lieu of the inspections required by 

§ 91.409(a) and (b) would result in some items not being inspected at the currently required 

intervals of annually or 100 hours. While the task-based inspections may be suitable for some 

airplanes under their specific operating conditions, they may not be suitable for others. 

Cessna Model CE208/208B airplanes are small, single engine turbopropeller-powered 

airplanes weighing less than 12,500 pounds. These airplanes can be equipped to operate in 

remote environments in several different configurations, including water operations with 

amphibious floats. The FAA believes that these airplanes when operated under these or other 

extreme conditions should be inspected within the periods specified in§ 91.409(a) (annually 

for all operations) and§ 91.409 (b) (100 hours when operated for hire). 

The FAA finds that a general exemption that would permit all operators of Model 

CE208/208B airplanes to use the proposed task-based inspection program in lieu of the 

currently required annual and 100-hour inspections would not provide a level of safety at least 

equal to that provided by the rule from which the petitioner seeks exemption. As explained 

above, this is because of the variable conditions under which these airplanes operate. The 

scope of the operating conditions for these airplanes is unknown and potentially unlimited. It 

is not the FAA's practice to grant this type of broad exemption that would apply to an 

undefined and open- ended number of aircraft.
4

Because an equivalent level of safety cannot be assured with the requested exemption, a grant 

would not be in the public interest. 

The FAA would entertain requests from individual operators who could provide the specific 

circumstances applicable to their operations and demonstrate how an equivalent level of safety 

would be assured. 

The FAA’s Decision:

In consideration of the foregoing, I find that a grant of exemption would not be in the public 

interest. Therefore, pursuant to the authority contained in 49 U.S.C. §§ 106(f), 40113 

and 44701 delegated to me by the Administrator, the petition of Cessna Aircraft Company for 

an exemption from 14 CFR § 91.409 is hereby denied. 

Issued in Washington, D.C, on April 15, 2014. 

/s/ 

John S. Duncan 

Director, Flight Standards Service 

 
CHAPTER

TIME LIMITS/

5

MAINTENANCE

CHECKS
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES

CHAPTER-SECTION-SUBJECT PAGE DATE

05-Title

05-List of Effective Pages

05-Record of Temporary Revisions

05-Table of Contents

5-00-00 Pages 1-4 Apr 1/2010

5-10-00 Pages 1-3 Jul 1/2010

5-10-01 Pages 1-43 Jul 1/2010

5-11-00 Pages 1-3 Jul 1/2010

5-11-01 Page 1 Jun 3/2002

5-12-00 Pages 1-3 Apr 1/2010

5-12-01 Pages 1-14 Apr 1/2010

5-12-02 Pages 1-11 Apr 1/2010

5-12-03 Pages 1-15 Apr 1/2010

5-12-04 Pages 1-17 Apr 1/2010

5-12-05 Page 1 Sep 4/2001

5-12-06 Pages 1-2 May 5/2003

5-12-07 Pages 1-2 Apr 1/2010

5-12-08 Page 1 Jan 2/2006

5-12-09 Pages 1-2 Apr 1/2010

5-12-10 Page 1 Apr 1/2010

5-12-11 Page 1 Jul 1/2010

5-12-12 Page 1 Dec 1/2006

5-12-13 Page 1 Sep 4/2001

5-12-14 Page 1 Sep 4/2001

5-12-15 Page 1 Sep 4/2001

5-12-16 Page 1 Sep 4/2001

5-12-17 Page 1 Sep 4/2001

5-12-18 Page 1 Apr 1/2010

5-12-19 Page 1 Nov 3/2003

5-12-23 Page 1 Nov 3/2003

5-12-29 Page 1 Apr 1/2010

5-12-30 Page 1 Apr 1/2010

5-12-31 Pages 1-2 Mar 1/2008

5-12-32 Page 1 Nov 3/2003

5-12-33 Page 1 Nov 3/2003

5-12-34 Page 1 Nov 3/2003

5-12-35 Page 1 Nov 3/2003

5-12-36 Page 1 Nov 3/2003

5-12-37 Page 1 Nov 3/2003

5-12-38 Page 1 Mar 1/2008

5-12-39 Page 1 Mar 1/2008

5-12-40 Page 1 Apr 1/2010

5-12-41 Page 1 Jul 1/2010

5-12-MA Page 1 Jun 1/2010

05 - LIST OF EFFECTIVE PAGES Page 1 of 2

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

5-12-MB Page 1 Jun 1/2010

5-12-MC Page 1 Jun 1/2010

5-12-MD Page 1 Jun 1/2010

5-12-ME Page 1 Jun 1/2010

5-12-MF Pages 1-2 Jun 1/2010

5-12-MG Page 1 Jun 1/2010

5-12-MI Page 1 Jun 1/2010

5-12-MJ Page 1 Jun 1/2010

5-12-MK Page 1 Jun 1/2010

5-12-ML Page 1 Jun 1/2010

5-12-MH Page 1 Jun 1/2010

5-13-00 Pages 1-8 Apr 1/2010

5-14-00 Pages 1-4 Apr 1/2010

5-14-01 Page 1 Nov 3/2003

5-14-02 Page 1 Nov 3/2003

5-14-03 Page 1 Nov 3/2003

5-14-04 Page 1 Mar 1/2008

5-14-05 Page 1 Nov 3/2003

5-14-06 Page 1 Nov 3/2003

5-14-07 Page 1 Aug 2/2004

5-14-08 Page 1 Nov 3/2003

5-14-09 Page 1 Nov 3/2003

5-14-10 Page 1 Nov 3/2003

5-14-11 Page 1 Nov 3/2003

5-14-12 Page 1 Nov 3/2003

5-14-13 Page 1 Nov 3/2003

5-14-14 Page 1 Nov 3/2003

5-14-15 Page 1 Nov 3/2003

5-14-16 Page 1 Apr 1/2010

5-14-17 Page 1 Nov 3/2003

5-14-18 Page 1 Nov 3/2003

5-14-19 Page 1 Nov 3/2003

5-14-20 Page 1 Nov 3/2003

5-14-21 Page 1 Nov 3/2003

5-14-22 Page 1 Nov 3/2003

5-14-23 Page 1 Nov 3/2003

5-14-24 Page 1 Nov 3/2003

5-14-25 Page 1 Nov 3/2003

5-14-26 Page 1 Apr 1/2010

5-14-27 Page 1 Nov 3/2003

5-14-28 Page 1 Aug 2/2004

5-14-29 Page 1 Mar 1/2008

5-14-30 Page 1 Nov 3/2003

5-20-01 Pages 1-18 Apr 1/2010

5-30-00 Pages 1-7 Dec 1/2006

5-30-01 Pages 1-38 Apr 1/2010

5-30-02 Pages 1-38 Mar 1/2008

5-30-05 Pages 1-14 Mar 1/2008

5-50-00 Pages 1-6 Apr 1/2010

05 - LIST OF EFFECTIVE PAGES Page 2 of 2

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MAINTENANCE MANUAL

RECORD OF TEMPORARY REVISIONS

Temporary Revision

Number Page Number Issue Date By Date Removed By
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

CONTENTS

TIME LIMITS/MAINTENANCE CHECKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-00-00 Page 1

Scope. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-00-00 Page 1

Inspection Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-00-00 Page 1

Inspection Program Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-00-00 Page 2

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-00-00 Page 2

INSPECTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10-00 Page 1

General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10-00 Page 1

Inspection Interval Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10-00 Page 1

INSPECTION TIME LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10-01 Page 1

Inspection Items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-10-01 Page 1

COMPONENT TIME LIMITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11-00 Page 1

Component Time Limit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11-00 Page 1

Schedule. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11-00 Page 1

COMPONENT TIME LIMITS - RUSSIAN CERTIFIED AIRPLANES . . . . . . . . . . . . . . . . . . . 5-11-01 Page 1

Component Time Limit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11-01 Page 1

Schedule. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11-01 Page 1

PROGRESSIVE CARE PROGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-00 Page 1

Progressive Care Program. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-00 Page 1

Construction. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-00 Page 1

Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-00 Page 2

Inspection Guidelines. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-00 Page 2

INSPECTION OPERATION 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-01 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-01 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-01 Page 1

INSPECTION OPERATION 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-02 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-02 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-02 Page 1

INSPECTION OPERATION 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-03 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-03 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-03 Page 1

INSPECTION OPERATION 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-04 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-04 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-04 Page 1

INSPECTION OPERATION 5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-05 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-05 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-05 Page 1

INSPECTION OPERATION 6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-06 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-06 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-06 Page 1

INSPECTION OPERATION 7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-07 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-07 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-07 Page 1

INSPECTION OPERATION 8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-08 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-08 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-08 Page 1

INSPECTION OPERATION 9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-09 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-09 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-09 Page 1

05 - CONTENTS Page 1 of 7

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-10 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-10 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-10 Page 1

INSPECTION OPERATION 11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-11 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-11 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-11 Page 1

INSPECTION OPERATION 12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-12 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-12 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-12 Page 1

INSPECTION OPERATION 13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-13 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-13 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-13 Page 1

INSPECTION OPERATION 14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-14 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-14 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-14 Page 1

INSPECTION OPERATION 15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-15 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-15 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-15 Page 1

INSPECTION OPERATION 16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-16 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-16 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-16 Page 1

INSPECTION OPERATION 17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-17 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-17 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-17 Page 1

INSPECTION OPERATION 18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-18 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-18 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-18 Page 1

INSPECTION OPERATION 19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-19 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-19 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-19 Page 1

INSPECTION OPERATION 23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-23 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-23 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-23 Page 1

INSPECTION OPERATION 29 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-29 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-29 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-29 Page 1

INSPECTION OPERATION 30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-30 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-30 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-30 Page 1

INSPECTION OPERATION 31 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-31 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-31 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-31 Page 1

INSPECTION OPERATION 32 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-32 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-32 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-32 Page 1

INSPECTION OPERATION 33 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-33 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-33 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-33 Page 1

05 - CONTENTS Page 2 of 7

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 34 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-34 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-34 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-34 Page 1

INSPECTION OPERATION 35 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-35 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-35 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-35 Page 1

INSPECTION OPERATION 36 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-36 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-36 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-36 Page 1

INSPECTION OPERATION 37 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-37 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-37 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-37 Page 1

INSPECTION OPERATION 38 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-38 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-38 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-38 Page 1

INSPECTION OPERATION 39 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-39 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-39 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-39 Page 1

INSPECTION OPERATION 40 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-40 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-40 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-40 Page 1

INSPECTION OPERATION 41 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-41 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-41 Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-41 Page 1

INSPECTION OPERATION MA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MA Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MA Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MA Page 1

INSPECTION OPERATION MB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MB Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MB Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MB Page 1

INSPECTION OPERATION MC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MC Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MC Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MC Page 1

INSPECTION OPERATION MD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MD Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MD Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MD Page 1

INSPECTION OPERATION ME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ME Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ME Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ME Page 1

INSPECTION OPERATION MF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MF Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MF Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MF Page 1

INSPECTION OPERATION MG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MG Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MG Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MG Page 1

INSPECTION OPERATION MI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MI Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MI Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MI Page 1

05 - CONTENTS Page 3 of 7

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MJ. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MJ Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MJ Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MJ Page 1

INSPECTION OPERATION MK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MK Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MK Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MK Page 1

INSPECTION OPERATION ML . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ML Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ML Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ML Page 1

INSPECTION OPERATION MH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MH Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MH Page 1

General Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MH Page 1

SUPPLEMENTAL INSPECTION DOCUMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 1

Supplemental Inspection Document . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 1

Principal Structural Elements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 1

Durability - Fatigue And Damage Tolerance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 2

Reporting - Communications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 5

Inspection Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 5

Applicability/Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 5

PSE Details . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 6

LISTING OF SUPPLEMENTAL INSPECTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-00 Page 1

Supplemental Inspection Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-00 Page 1

Supplemental Inspections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-00 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 32-10-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-01 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-01 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-01 Page 1

Main Landing Gear Axle Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-01 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-10-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-02 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-02 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-02 Page 1

Fuselage Engine Mount Fittings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-02 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-03 Page 1

Title........................................................................ 5-14-03 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-03 Page 1

Cargo and Passenger Door Doublers Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-03 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-07 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-04 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-04 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-04 Page 1

Fuselage to Strut Attach Fitting Lugs Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-04 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-03 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-05 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-05 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-05 Page 1

Lower Forward Carry-Thru Bulkhead Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-05 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-04 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-06 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-06 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-06 Page 1

Main Landing Gear Fitting Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-06 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-05 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-07 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-07 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-07 Page 1

Main Landing Gear Attach Fittings and Aft Carry-Thru Bulkhead Inspection. . . . . . . 5-14-07 Page 1

05 - CONTENTS Page 4 of 7

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-08 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-08 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-08 Page 1

Fuselage to Wing Attach Fitting Lugs Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-08 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-09 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-09 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-09 Page 1

Firewall Brace and Doubler Assemblies Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-09 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-08 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Page 1

Carry-Thru Root Rib Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-09 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-11 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-11 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-11 Page 1

Crew Door Frames Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-11 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-12 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-12 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-12 Page 1

Passenger and Cargo Door Frames Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-12 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-10-07 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-13 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-13 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-13 Page 1

Seat Rails and Attachment Structure Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-13 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-14 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-14 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-14 Page 1

Bulkheads and Stiffeners Below the Seat Rail Attachments Inspection . . . . . . . . . . . 5-14-14 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-15 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-15 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-15 Page 1

Stringers at Intersections with Forward and Aft Carry-Thru Bulkheads Inspection . 5-14-15 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-16 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-16 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-16 Page 1

Fuselage Skin Doubler at Main Landing Gear Cutout Inspection. . . . . . . . . . . . . . . . . 5-14-16 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-50-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-17 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-17 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-17 Page 1

Fuselage to Horizontal Stabilizer Attach Fittings Inspection . . . . . . . . . . . . . . . . . . . . . 5-14-17 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-50-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-18 Page 1

Title.. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . 5-14-18 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-18 Page 1

Vertical Stabilizer Attach Points Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-18 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 55-10-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-19 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-19 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-19 Page 1

Horizontal Stabilizer Forward and Aft Attach Points Inspection . . . . . . . . . . . . . . . . . . 5-14-19 Page 1

05 - CONTENTS Page 5 of 7

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 55-10-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-20 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-20 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-20 Page 1

Horizontal Stabilizer Forward Spar Cap Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-20 Page 1

Horizontal Stabilizer Aft Spar Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-20 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 53-20-06 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-21 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-21 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-21 Page 1

Fuselage to Wing Carry-Thru Attach Fitting and Bulkhead Inspection . . . . . . . . . . . . 5-14-21 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 55-30-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-22 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-22 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-22 Page 1

Vertical Stabilizer Spars Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-22 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 56-30-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-23 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-23 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-23 Page 1

Windshield and Attachment Structure Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-23 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 57-20-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-24 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-24 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-24 Page 1

Wing to Carry-Thru Spar Attachment Fittings Inspection . . . . . . . . . . . . . . . . . . . . . . . . 5-14-24 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 57-20-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-25 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-25 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-25 Page 1

Front Spar Lower Cap Inboard of WS 141.20 Inspection . . . . . . . . . . . . . . . . . . . . . . . . 5-14-25 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 57-20-03 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-26 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-26 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-26 Page 1

Rear Spar Lower Cap Inboard of WS 141.20 Inspection . . . . . . . . . . . . . . . . . . . . . . . . 5-14-26 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 57-50-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-27 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-27 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-27 Page 1

Flap Tracks Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-27 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 57-60-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-28 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-28 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-28 Page 1

Wing Strut Fittings Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-28 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 57-60-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-29 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-29 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-29 Page 1

Wing Strut Attachment to Front Spar Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-29 Page 1

SUPPLEMENTAL INSPECTION NUMBER: 71-20-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-30 Page 1

Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-30 Page 1

Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-30 Page 1

Engine Truss and Ring Assembly Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-30 Page 1

SCHEDULED INSPECTION CHECKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-20-01 Page 1

Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-20-01 Page 1

05 - CONTENTS Page 6 of 7

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CORROSION PREVENTION AND CONTROL PROGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 1

Introduction. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 1

Corrosion Prevention and Control Program Objective. . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 1

Corrosion Prevention and Control Program Function . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 1

References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 2

Control Prevention and Control Program Application . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 2

Baseline Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 3

Baseline Program Implementation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 4

Reporting System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 5

Periodic Review . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 7

Corrosion Related Airworthiness Directives. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-00 Page 7

CORROSION PREVENTION AND CONTROL INSPECTIONS (AIRPLANES WITHOUT

TKS ANTI-ICE SYSTEM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-01 Page 1

Corrosion Prevention and Control Program Inspections. . . . . . . . . . . . . . . . . . . . . . . . . 5-30-01 Page 1

CORROSION PREVENTION AND CONTROL INSPECTIONS (AIRPLANES WITH TKS

ANTI-ICE SYSTEM). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-02 Page 1

Corrosion Prevention and Control Program Inspections. . . . . . . . . . . . . . . . . . . . . . . . . 5-30-02 Page 1

CORROSION PREVENTION AND CONTROL PROGRAM - APPENDIX . . . . . . . . . . . . . . 5-30-05 Page 1

Appendix A - Development Of The Baseline Program . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 1

Appendix B - Procedures For Recording Inspection Results. . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 1

Appendix C - Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 1

Application Of The Corrosion Program Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 3

Determination of the Corrosion Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 8

Typical Actions That Follow the Determination of the Corrosion Level. . . . . . . . . . . . 5-30-05 Page 12

Factors Influencing Corrosion Occurrences. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 14

Reporting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 14

Program Implementation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-30-05 Page 14

UNSCHEDULED MAINTENANCE CHECKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-50-00 Page 1

General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-50-00 Page 1

Unscheduled Maintenance Checks Defined and Areas to be Inspected . . . . . . . . . . 5-50-00 Page 1

05 - CONTENTS Page 7 of 7

© Cessna Aircraft Company Jul 1/2010
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MODEL 208

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TIME LIMITS/MAINTENANCE CHECKS

1. Scope

A. This chapter 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 for detailed information concerning

each of these sections.

NOTE: In accordance with Title 14 of the Code of Federal Regulations (CFR) 23.1529, Chapter

4 (Airworthiness Limitations) of this manual is published as a separate document. Refer

to Chapter 4 for those components that have a mandatory inspection and components

replacement schedule.

NOTE: For EASA-certified airplanes, the Chapter 4 Airworthiness Limitations section is applicable

to airplanes with less than 50,000 flight hours. Flight beyond 50,000 flight hours is

prohibited until new or revised FAA-approved Airworthiness Limitations are obtained.

NOTE: The time limits and maintenance checks recorded in this chapter are the minimum

requirements for airplanes operated under normal conditions. For airplanes that operate

in areas of bad conditions can be found, such as, high salt coastal environments, areas

of high heat and humidity, areas where industrial or other airborne pollutants are present,

extreme cold, unimproved surfaces, etc., the time limits shall be changed as necessary.

NOTE: It is recommended that all Cessna Model 208 owners participate in CESCOM

(Computerized Maintenance Records System). This is a comprehensive system which

gives an easy procedure to monitor and schedule inspections, Service Bulletins, Service

Kits, Airworthiness Directives, and scheduled and unscheduled maintenance activities.

For additional information on CESCOM, refer to Section 8 in the Pilot’s Operating

Handbook, or the CESCOM Instruction Manual supplied with your airplane

B. Chapter 4 of this 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. When there is a conflict between the two chapters, Chapter 4 requirements must always

be followed. Chapter 5 requirements will be made to agree with Chapter 4 at the next revision to the

manual.

C. Inspection operations that begin with the letter M are those inspections found in Chapter 4. These

were added because there can be no grace period for these inspections.

2. Inspection Requirements

A. Three basic types of inspections are available as defined below:

(1) As required by Title 14 of the Code of Federal Regulations Part 91.409 (a), all civil airplanes

of U.S. registry must have a complete examination (ANNUAL) each 12 calendar months. In

addition to the required ANNUAL inspection, airplanes operated commercially (for hire) must

also have an inspection each 100 hours of operation as required by Title 14 of the Code of

Federal Regulations Part 91.409 (b).

(2) Instead of the above requirements, an airplane can be examined with a progressive inspection

program that agrees with Title 14 of the Code of Federal Regulations Part 91.409 (d), which lets

the work to be divided into smaller operations that can be done in a shorter time period. The

CESSNA PROGRESSIVE CARE PROGRAM has been made to give a modern progressive

inspection schedule that is satisfactory with the requirements of both the 100-HOUR and

ANNUAL inspections as applicable to Cessna airplanes.

(3) If an airplane is being operated under a CFR Part 135 Certificate, the operator can choose to

use an Approved Aircraft Inspection Program.

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3. Inspection Program Selection

A. The recommendation that follows is to help select the inspection program which is best for the

operation of the airplane:

(1) If the airplane is flown less than 400 hours annually, the conditions that follow apply:

(a) If flown for hire.

1 An airplane operating in this category must have a COMPLETE AIRPLANE

INSPECTION (ANNUAL) each 12 calendar months. Another inspection is required

each 100 hours of operation (100-HOUR). A COMPLETE AIRPLANE INSPECTION

has all of the 100-Hour, 200-Hour and 400-Hour items, and those operations which

are due at the specified time. The Component Time Limits shall also be examined

at each inspection interval to make sure the correct overhaul and replacement

requirements are done at the specified times.

(b) If not flown for hire.

1 An airplane that operates in this category must have a COMPLETE AIRPLANE

INSPECTION each 12 calendar months of operation (ANNUAL). A COMPLETE

AIRPLANE INSPECTION has all of the 100-Hour, 200-Hour and 400-Hour items,

and those operations which are due at the specified time. It is recommended that

between annual inspections, all items be examined at the intervals specified in the

Inspection Time Limits. The Component Time Limits shall be examined at each

inspection interval to make sure the correct overhaul and replacement requirements

are done at the specified times.

(2) If the airplane is flown more than 400 hours annually, the conditions that follow applies:

(a) Whether flown for hire or not, it is recommended that airplanes that operate in this

category be put on the CESSNA PROGRESSIVE CARE PROGRAM. However, if not

put on the CESSNA PROGRESSIVE CARE PROGRAM, the inspection requirements

for airplanes in this category are the same as those given by Paragraph 3.A.(1)(a)1 or

(b)1. The CESSNA PROGRESSIVE CARE PROGRAM can be used as a total concept

program which makes sure that the inspection intervals are not more than the inspection

charts. Manuals and forms which are required to do the CESSNA PROGRESSIVE CARE

PROGRAM inspections are available from the Cessna Supply Division.

(3) If the airplane is operated under Title 14 of the Code of Federal Regulations Part 135, and flown

an average of 400 hours annually, the manufacturer’s approved inspection program that follows

can be used. However, the program must be used as published and the latest revision must be

incorporated.

(a) Caravan PhaseCard Inspection Program D5127 or D5859 with the latest revision found by

the Cessna Revision Status Checklist issued quarterly by Cessna Aircraft Company.

4. Description

NOTE: Given below is a detailed description and the purpose of each section of this chapter.

A. Section 5-00-00, Time Limits/Maintenance Checks - General. This section gives a description and

purpose of each section of this chapter.

B. Section 5-10-01, Inspection Time Limits.

(1) 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:

(a) 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 reissue of this manual.

(b) Inspection Item Code Number is a six-digit number permanently assigned to a scheduled

maintenance item. A given inspection item code number will never change and will not be

used again if the scheduled maintenance item is deleted.

(c) Inspection Requirements give a short description of the maintenance item and are supplied

in chapter order.

(d) An Inspection Interval is an alpha code character that shows the frequency of the item.

The frequencies for each code are given at the beginning of Chapter 5-10-00.

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(e) Applicable Operation(s) shows the applicable inspection operation that currently has the

inspection item.

(f) 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.

(2) 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.

(3) 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. 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 scheduled operation is done late, the next operation in sequence keeps a due

point from the time the late operation was initially scheduled.

2 If any scheduled operation is done early, 10 hours or less ahead of schedule, the next

phase due point can remain where initially set.

3 If any scheduled operation is done early, more than 10 hours ahead of schedule, the

next phase due point must be rescheduled to set a new due point from the time it was

done early.

C. Section 5-11-00, Component Time Limits. 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.

D. Section 5-12-00, Progressive Care Program. This section shows the progressive inspection program

which is Cessna Aircraft Company's recommended inspection program. The program is divided into

four primary operations which gives all inspection requirements up through the 400-hour interval

inspection items. The operations that remain give the inspections which are at intervals other than

the four primary operations. Refer to the Progressive Care Program section for a more information

about the Progressive Care Program.

E. Section 5-13-00, Supplemental Inspection Document. This section gives the structural maintenance

inspections needed for continued airworthiness of the airplane. The Supplemental Inspections are

found in Chapter 5 in the applicable Operations. The details of each inspection begins at section

5-14-01.

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F. Section 5-20-01, Scheduled Maintenance Checks. This section gives a more information about the

inspection items given in the Inspection Time Limits section. It gives more information about what

and how to examine an inspection item. Specific functional and operational checks that are required

only because of inspection requirements are also given in this section. More information about an

inspection item, and functional and operational checks that are not often used are in the appropriate

chapter of this manual. The information in this section is arranged in chapter order.

G. Section 5-30-00, Corrosion Prevention and Control Program (CPCP). This section gives information

about structural components that must be examined to prevent and control corrosion. The section also

gives the necessary information to set the initial and repeat intervals for the CPCP. The inspections

are found in Chapter 5 in the applicable Operations.

H. Section 5-50-00, Unscheduled Maintenance Checks. 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.

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MAINTENANCE MANUAL

INSPECTIONS

1. General

A. General inspection criteria.

(1) When you do each of the specified inspections in this chapter, you must do a general examination

of the adjacent areas while access is available. These 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 inspection program must

have professionalism and good judgment used by all inspection personnel. The technician 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 you must do the test again before the system or

component is returned to service. Refer to the appropriate chapter in this Maintenance Manual

for removal, installation, operational tests, 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) After you complete the applicable inspections, refer to the Pilot's Operating Handbook and FAA

Approved Airplane Flight Manual to do a preflight inspection.

(8) You should perform operations 5 and on concurrently with one of the operations 1 through 4, or

as close to one of those due points as possible.

(9) Inspection operations that begin with the letter M are those inspections that match Chapter 4.

These were added because there is no grace period for these inspections.

(10) TKS is a fluid based anti-ice system.

2. Inspection Interval Requirements

INTERVAL OPERATION INTERVAL DETAILS

A 1, 2, 3, 4 Every 100 Hours.

B 1,3 or 2,4 Every 200 Hours.

C 1 or 2 or 3 or 4 Every 400 Hours.

D 5 Every 500 Hours or 1 year, whichever occurs first.

E 6 Every 800 Hours or 1 year, whichever occurs first.

F 7 Every 1000 Hours or 1 year, whichever occurs first.

G 8 Every 2000 Hours or 2 years, whichever occurs first.

H 9 Every 1 year.

I 10 Every 2 years.

J 11 Every 3 years.

K 12 Every 4 years.

L 13 Every 6 years.

M 14 Every 12 years.

N 15 Every 1200 hours or 1 year, whichever occurs first.

O 16 Every 100 hours and every external engine wash or engine compartment

wash.

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INTERVAL OPERATION INTERVAL DETAILS

P 17 Every 500 Hours.

Q 18 Every 1600 hours or 5 years, whichever occurs first.

R 19 Every 1000 hours.

S 20 At 13,000 hours and every 4000 hours thereafter. (Not Used)

T 21 At 10,000 hours and every 5000 hours thereafter. (Not Used)

U 22 At 5000 landings and every 1000 landings thereafter. (Not Used)

V 23 Every 400 hours or 6 calendar months, whichever occurs first.

W 24 At 4000 landings and every 500 landings thereafter. (Not Used)

X 25 At 15,000 landings and every 3000 landings thereafter. (Not Used)

Y 26 At 5000 hours and every 3600 hours thereafter. (Not Used)

Z 27 At 12 years if the airplane is operated in a mild or moderate corrosion

environment.

(Not Used)

AA 28 At 6 years if the airplane is operated in a severe corrosion environment.

(Not Used)

AB 29 Every two years if the airplane is operated in a mild corrosion environment.

Refer to Chapter 51, Corrosion Severity Maps - Description and Operation

for definition of corrosion severity zones.

AC 30 Every one year if the airplane is operated in a moderate or severe

corrosion environment. Refer to Chapter 51, Corrosion Severity Maps -

Description and Operation for definition of corrosion severity zones.

AD 31 At the first 20,000 hours and every 5000 hours thereafter.

AE 32 At the first 5000 hours and every 2500 hours thereafter.

AF 33 At the first 7500 hours and every 2500 hours thereafter.

AG 34 At the first 12,500 hours and every 2500 hours thereafter.

AH 35 At the first 16,500 hours and every 5000 hours thereafter.

AI 36 At the first 17,500 hours and every 1000 hours thereafter.

AJ 37 At the first 25,000 landings and every 5000 landings thereafter.

AK 38 Every 1200 hours.

AL 39 At each starter generator removal.

AM 40 Every 1000 Hours or 3 years, whichever occurs first.

AN 41 Every 5 years.

MA MA At 10,000 hours and every 5000 hours thereafter.

MB MB At 5000 landings and every 1000 landings thereafter, up to 10,000

landings. Replace at 10,000 landings.

MC MC At 4000 landings and every 500 landings thereafter.

MD MD At 15,000 landings and every 3000 landings thereafter.

ME ME At 5000 hours and every 3600 hours thereafter.

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INTERVAL OPERATION INTERVAL DETAILS

MF MF At 20,000 hours and every 5000 hours thereafter.

MG MG At 5000 hours and every 1200 hours thereafter.

MH MH At 10,000 hours and every 2500 hours thereafter.

MI MI At 5000 hours and every 500 hours thereafter.

MJ MJ At 5000 hours and every 400 hours thereafter.

MK MK At 20,000 hours and every 4400 hours thereafter.

ML ML At 20,000 hours and every 3600 hours thereafter.

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MAINTENANCE MANUAL

INSPECTION TIME LIMITS

1. Inspection Items

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Jan 3/05

112001 Interior Placards, Exterior Placards,

Decals, Markings and Identification

Plate - Inspect for security of

installation and legibility. Refer to

Chapter 11, Placards and Markings -

Inspection/Check.

A 1, 2, 3, 4 ALL

Deleted

Jan 3/05

113001

Revised

Mar 1/01

211001 Ram Air - Inspect clamps, hoses, valve,

inlet screens, and ventilation system for

condition and security of installation.

C 3 501, 601,

511, 611

Revised

Mar 1/01

212001 Ventilating Blower (if installed) - Inspect

for security of installation. Inspect

wiring for evidence of damage and

security of installation.

C 3 511, 611

212002 Ventilating Blower (if installed) - Inspect

blower fan/wheel for blade damage.

G 8 511, 611

Revised

Mar 1/01

212003 Ventilation Outlets (Cabin Overhead)

- Inspect for security of installation,

condition and operation.

C 4 231, 232,

251, 252,

255, 256

212004 Instrument Panel Ventilation Air

Outlets and Controls - Inspect doors,

cables and controls for condition and

operation.

C 4 220, 224

212005 Avionics Cooling Fan - Turn Battery

and Avionics Power switch No. 2 ON

and check for cooling fan operation.

A 1, 2, 3, 4 BAT

213001 Pressure Regulating Valve and

Plumbing - Inspect valve and plumbing

for security of installation, condition

and evidence of damage.

C 1 122

Revised

Mar 1/01

213002 Pressure Relief Valve - Inspect for

condition and security of installation.

C 1 151

Revised

Mar 1/01

214001 Heater Components - Check lines,

connectors, clamps, seals, gaskets,

and distribution ducts for condition,

restrictions, and security of installation.

C 1 122

214002 Heater System Plumbing - Inspect

P3 line, flow control valve and

heat regulating line for security of

installation, condition and evidence of

damage.

C 1 122

214003 Cabin Heater and Windshield Defroster

- Perform operational check.

A 1, 2, 3, 4 ENG

5-10-01 Page 1

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

214005 Cabin Heat Firewall Shutoff Control

and Valves - Inspect for general

condition, evidence of damage and

security of installation. Inspect linkage,

temperature probe, safety switch and

associated wiring for condition and

security of installation.

C 1 152, 226

Revised

Mar 1/01

215001 Vapor Cycle Cooling System - Inspect

evaporator and condenser air inlets for

obstruction and debris. Inspect system

for evidence of damage, indication of

leaks and mountings for security of

installation.

C 4 251, 311

Added

Mar 3/97

215002 Compressor Belt (Vapor Cycle Cooling

System) - Inspect for wear, alignment

and tension.

C 4 130

Revised

Dec 3/01

221001 Autopilot Actuator (Aileron) - Inspect

bridle cables for fraying, chafing,

cleanliness, turnbuckle safetying, and

proper routing. Inspect chain for proper

safetying at all points and chains

for proper alignment with actuator

sprockets. Inspect pulleys, drive

sprockets, drive chain, and guard

pins for condition, wear, corrosion,

and security of installation. Inspect

electrical components for operation,

condition, and security of installation.

B 1, 3 234

Revised

Mar 1/01

221002 Autopilot Aileron Actuator - Inspect for

condition, security of installation, and

evidence of overheating.

C 4 234

Revised

Mar 1/01

221003 Autopilot Elevator Actuator - Inspect for

condition, security of installation, and

evidence of overheating.

C 3 312

Revised

Mar 1/01

221004 Autopilot Actuator (Elevator) - Inspect

bridal cables for fraying, chafing,

cleanliness, turnbuckle safetying, and

proper routing. Inspect chain for proper

safetying at all points and chains

for proper alignment with actuators

sprockets. Inspect pulleys, drive

sprockets, drive chain, and guard

pins for condition, wear, corrosion,

and security of installation. Inspect

electrical components for operation,

condition, and security of installation.

B 2, 4 312

221005 400B Autopilot (AF-550A) and 400B

IFCS (IF-550A) - Check bridal Cable

tensions.

E 6 234, 312

5-10-01 Page 2

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

221006 King Flight Control System (KFC-250)

- Check bridal cable tensions.

F 7 234, 312

221007 King Flight Control System (KFC-250)

- Check actuator clutch torque setting.

F 7 234, 312

221008 King Flight Control System (KFC-150)

- Check bridal cable tensions.

F 7 234, 312

221009 King Flight Control System (KFC-150) -

Check actuator clutch torque settings.

F 7 234, 312

221010 King Flight Control System (KFC-250)

- Check cable tensions.

F 7 312

Revised

Mar 1/01

221011 King Yaw Damper Actuator Slip Clutch

Adjustment (if installed) - Check yaw

damper slip clutch torque setting.

F 7 312

221012 King Yaw Damper Cable Tension

Setting (if installed) - Verify yaw bridal

cable tension.

F 7 312

Revised

Mar 1/01

221013 400B Autopilot (AF-550A) and 400B

IFCS (IF-550A) - Check for security

of installation and switches for proper

operation.

E 6 223

Revised

Mar 1/01

221014 King Flight Control System (KFC-150)

- Check for security of installation and

switches for proper operation.

C 4 223

Revised

Mar 1/01

221015 King Flight Control System (KFC-250)

- Check for security of installation and

switches for proper operation.

C 4 223

Revised

Mar 1/10

221016 Flux Detector or Magnetometer -

Inspect for security of installation.

Inspect electrical connections and wire

routing for condition and security of

installation. Check for non-magnetic

screws in the access cover and in the

mounting brackets.

C 3 623

Revised

Mar 1/01

221017 Autopilot Computer Amplifier, Mount,

Mounting Knob and Electrical

Components (Model 208 Only) -

Inspect for security of installation.

C 4 216

221019 Autopilot Mode Controller, Mode

Annunciator, Slaving Accessory and

Compensator Unit, Autopilot Control

Wheel Switch Cap and Power Lever

Go-Around Button (Model 208 & 208B)

(if installed) - Check for security of

installation and switches for proper

operation.

C 4 220, 222,

223, 226

5-10-01 Page 3

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Added

Nov 3/03

221020 King Flight Control System (KFC-225)

- Check for security of installation and

switches for proper operation.

C 4 223

Added

Nov 3/03

221021 King Flight Control System (KFC-225)

- Check bridal cable tensions. Refer

to Chapter 27, Aileron - Adjustment/

Test, Elevator - Adjustment/Test and

Yaw Damper - Adjustment/Test.

F 7 234, 312

Added

Nov 3/03

221022 King Flight Control System (KFC-225)

- Check actuator clutch torque

setting. Refer to Chapter 27,

Aileron - Adjustment/Test, Elevator -

Adjustment/Test and Yaw Damper -

Adjustment/Test.

F 7 234, 312

Added

May 1/08

221023 Garmin Autopilot (GFC 700) Switches

- Examine the Autopilot Control

Wheel Switch Cap and Power

Lever Go-Around Button for correct

installation and operation.

C 4 223

Added

May 1/08

221024 Garmin Autopilot (GFC 700) System

Inspection - Examine the clutch torque

settings and complete a GFC 700

Visual Inspection in accordance with

the Garmin G1000 Caravan Line

Maintenance Manual.

F 7 226, 233,

234, 312

Added

May 1/08

221025 Garmin Roll, Pitch, Yaw, and Pitch

Trim Servos (GSA 80/81) - Clean and

apply grease to the output gear in

accordance with the Garmin G1000

Caravan Line Maintenance Manual.

AM 40 226, 234,

312

Revised

May 1/08

230001 Instrument Panel Mounted Avionics

Units (including Audio Panel, VHF

Nav/Com(s), ADF, Transponder,

DME, Compass System, RMI, Radar

Altimeter, Weather Radar, and

Garmin G1000 system ) - Inspect for

deterioration, cracks, and security of

instrument panel mounts. Inspect

for security of electrical connections,

condition, and security of wire routing.

C 4 223

Revised

Mar 1/01

230002 Avionic Operating Controls - Inspect

for security of installation and proper

operation of controls and switches

and ensure that all digital segments

illuminate properly.

C 4 223

230003 Remote Mounted Avionics (Fuselage)

- Inspect for security of units and

electrical connectors, condition and

security of wire routing. Also check for

evidence of damage and cleanliness.

C 4 311, 312

5-10-01 Page 4

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

230004 Remote Mounted Avionics

(Empennage) - Inspect for security

of units and electrical connectors,

condition and security of wire routing.

Also, check for evidence of damage

and cleanliness.

C 3 216

Revised

Mar 1/01

230005 Microphones, Headsets, and Jacks

- Inspect for cleanliness, security of

installation and evidence of damage.

C 4 222, 224,

226

Added

Nov 3/03

231001 Control Wheel Pushbutton Switches

- Clean the transponder identification

switch, microphone switch, and

the interphone switch on the pilot's

and copilot's control wheel. Refer

to Chapter 23, Communication -

Maintenance Practices.

A 1, 2, 3, 4 227, 228

Revised

May 5/03

236001 Static Wicks (Wings and Empennage)

- Inspect for condition and security of

installation.

B 1, 3 343, 375,

376, 575,

527, 571,

625, 627,

671

Revised

May 5/03

236002 Static Dischargers - Perform highresistance check.H 9 343, 375,

376, 575,

527, 571,

625, 627,

671

240001 General Airplane and System Wiring

- Inspect for chafing, broken or loose

terminals, general condition, broken or

inadequate clamps, and sharp bends in

wiring.

C 4 ALL

Revised

Mar 1/01

240002 Instrument Panel and Control Pedestal

- Inspect wiring, mounting and

terminals for condition and security of

installation.

C 4 220, 221,

222, 223,

224, 225,

226

Revised

Mar 1/01

242001 Standby Alternator - Inspect for

condition and security of installation,

belt tension and condition. Check

terminal boots for condition and

electrical leads for damage and

security of installation.

B 1, 3 121

Revised

Mar 1/01

242002 Standby Alternator Drive - Inspect for

security of installation, leakage, and

condition.

B 1, 3 121

242003 Standby Alternator Drive Drain (if

applicable) - Inspect for security of

installation and condition.

B 1, 3 130

5-10-01 Page 5

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

242004 Standby Alternator Power Distribution

Box - Inspect relay and associated

electrical components for condition and

security of installation.

C 1 121

242005 Standby Electrical System (Engine

Running) - Perform functional test.

Refer to Section 9 of the Pilot's

Operating Handbook.

A 1, 2, 3, 4 ENG

Revised

Mar 1/01

243001 Battery Cable Disconnect and Cables

- Inspect for condition, corrosion and

security of installation. Inspect battery

terminal receptacles for overheating or

burning.

A 1, 2, 3, 4 122

243002 Electrical System Power Distribution

Box, Contactors, Ground Power

Monitor, Circuit Breakers, Limiters and

Cables - Inspect cables for routing,

support and security of connections.

Check condition and security of all

components.

C 1 121

243003 Alternator and Generator Control Units

- Inspect security of mounting. Inspect

wiring for condition and routing.

C 4 215

243004 Volt/Ammeter and Selector Switch -

Inspect for security of installation.

C 4 220

Revised

Mar 1/01

243005 Volt/Ammeter (Engine Running) -

Perform operational check of each

position.

A 1, 2, 3, 4 ENG

243006 NI-CAD Battery (if installed) - Perform

capacity check. Check terminals for

overheating or burning.

A 1, 2, 3, 4 LAB

Revised

Mar 1/01

243007 Battery Tray - Inspect for condition,

corrosion and security of installation.

Inspect latching mechanism for proper

operation.

A 1, 2, 3, 4 122

Revised

Mar 1/01

243008 NI-CAD Battery Temperature Probe

Connector - Inspect connector and

associated wiring for condition and

security of installation. Disconnect plug

from battery and check annunciators.

Verify BATTERY HOT and BATTERY

OVERHEAT annunciator lights

illuminate with power ON.

B 1, 3 122

Revised

Mar 1/01

243009 Gill Flooded Lead Acid Battery (if

installed) - Check general condition

and security of installation. Check

level of electrolyte. Check terminals

for overheating or burning.

A 1, 2, 3, 4 122

5-10-01 Page 6

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

243010 Gill Lead Acid Only Battery Box -

Inspect for corrosion, condition and

security of installation.

A 1, 2, 3, 4 122

Revised

Mar 1/01

243011 Battery Vent Tubes - Inspect for

condition, obstructions and security of

installation.

A 1, 2, 3, 4 122

243012 Engine Electrical Cables and

Connectors - Inspect cables for routing,

support, security of connections and

connector hardware.

C 1 121, 122

243013 Tailcone Wire Bundles - Inspect for

proper position of drip loop to prevent

moisture from entering connector.

C 3 311, 312,

320, 330

Revised

Mar 1/01

243014 Concord Sealed Lead Acid Battery (if

installed) - Check general condition

and security of installation. Check

terminals for overheating or burning.

Perform checks in accordance with

servicing placard on the side of battery.

A 1, 2, 3, 4 122

Revised

Mar 1/01

244001 External Power Receptacle and Cables

- Inspect for condition and security of

installation.

C 1 121

244002 External Power - Perform operational

check of the BUS and STARTER

functions.

A 1, 2, 3, 4 ENG

Revised

Mar 1/01

245001 Side Consoles, Circuit Breaker Panels,

Terminal Blocks and Junction Boxes

- Inspect wiring and terminals for

condition and security of installation.

C 4 215

Revised

Mar 1/01

245002 Switches - Check operation, terminals,

wiring and mounting for condition,

security of installation and interference.

C 4 215

251001 Pilot's and Copilot's Inertia Reels,

Seat Belts and Shoulder Harnesses

- Inspect for security of installation,

frayed edges and evidence of damage

and proper operation.

C 4 231, 232

Revised

Mar 1/01

251002 Pilot's and Copilot's Seats - Inspect

seat brackets, guides, stops, seat

structure and seat cushions for

condition and security of installation;

and controls for condition, security

of installation and proper operation.

Service seat adjusting screws,

bearings and locking mechanisms.

A 1, 2, 3, 4 231, 232

5-10-01 Page 7

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

251003 Warning Horns Installation - Inspect

stall warning, fuel selector warning

horns, airspeed warning, radar

altimeter and fire detection warning

horns for security of installation and

evidence of damage. Inspect grill

cover for condition and security of

installation.

C 4 231, 232

Revised

Mar 1/01

251004 Relief Tube (if installed) - Inspect

for condition, security of installation,

cleanliness and corrosion.

C 4 233, 234,

256, 258

Added

Apr 1/96

251005 Pilot's and Copilot's Seat Back Stop

Bolts - Inspect for loose or missing

nuts.

A 1, 2, 3, 4 231, 232

Revised

Mar 1/01

252001 Seat Tracks - Inspect seat tracks and

stops for condition and security of

installation. Inspect seat track stops for

proper location, security of installation.

B 2, 4 251, 252,

255, 256

Revised

Mar 1/01

252002 Interior Furnishings - Inspect for

condition and security of installation.

Inspect electrical components in

accordance with electrical power

inspection.

C 4 251, 252,

255, 256

Revised

Mar 1/01

252003 Floor Covering - Inspect for condition,

security of installation and cleanliness.

C 4 231, 232,

251, 252,

255, 256

Revised

Mar 1/01

255001 Cargo Tie-Down Straps and Fittings

(if installed) - Inspect for condition,

security of installation and proper

installations.

C 4 251, 252,

255, 256

255003 Cargo Pod (if installed) - Inspect

structure for condition and security of

installation. Check condition of sealant

at fuselage and evidence of internal

leakage.

C 4 901, 902,

903, 904,

905, 906,

907, 908

Revised

Mar 1/01

255004 Cargo Pod Drain Tubes (if installed)

- Inspect cargo pod drain tubes for

obstruction, condition and security of

installation.

C 4 901, 902,

903, 904

255005 Cargo Pod Doors (if installed) - Inspect

door structure for condition, cracked

or debonded laminate. Check rubber

door seals for condition and proper

attachment.

C 4 921, 922,

923, 924

Revised

Mar 1/01

255006 Cargo Pod Door Hinges and Latches

(if installed) - Inspect for evidence of

damage, wear, security of installation,

and loose or failed fasteners.

C 4 921, 922,

923, 924

5-10-01 Page 8

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

255007 Cargo Pod Fuel Reservoir Remote

Drain (if installed) - Check drain for

proper operation and evidence of

leakage from drain tube outlet.

A 1, 2, 3, 4 244

255008 Cargo Pod Doors (if installed) - Check

legibility of weight limitations placards.

C 4 921, 922,

923, 924

255009 Cargo Nets and Barrier (if installed)

- Check for condition, security

of attachment and operation of

adjustment devices.

C 4 251, 252

Revised

Jun 3/02

256001 Emergency Locator Installation -

Inspect for security of installation,

position of function switch and

condition of electrical components.

Inspect structure for corrosion.

A 1, 2, 3, 4 312

Revised

Jun 3/02

256002 Emergency Locator Transmitter -

Perform operational test. Check

cumulative time and useful life of

batteries in accordance with FAR

91.207.

A 1, 2, 3, 4 BAT

Revised

Mar 1/01

261001 Fire Detection Control Unit - Inspect for

condition and security of installation.

C 4 121, 122

Revised

Mar 1/01

261002 Heat Detection Loop - Inspect the three

loop sections for condition, security of

installation and evidence of damage,

paying special attention to the loop

connection fittings.

A 1, 2, 3, 4 121, 122

Revised

Mar 1/01

262001 Engine Fire Detection - Perform engine

fire detection test.

A 1, 2, 3, 4 BAT

Revised

Mar 1/01

262002 Portable Hand Fire Extinguisher -

Inspect for proper operating pressure,

condition, and security of installation.

Check servicing date.

A 1, 2, 3, 4 231, 232

Revised

Mar 1/01

262003 Cockpit or Cabin Mounted Halon-Type

Fire Extinguishers - Empty, inspect for

damage and recharge.

L 13 LAB

Revised

Mar 1/01

262004 Cockpit and Cabin Mounted HalonType Fire Extinguishers - Perform

hydrostatic test at 12-year intervals,

based on initial servicing or date of last

hydrostatic test.

M 14 LAB

5-10-01 Page 9

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

271001 Aileron - Inspect the aileron skins

for cracks and loose rivets; aileron

hinges for condition, cracks, and

security of installation; hinge bolts,

hinge bearings, hinge attach fittings,

and bonding jumpers for evidence of

damage or wear, failed fasteners, and

security of installation. Inspect the

aileron hinge bolts for proper safetying

of nuts with cotter pins. Inspect

balance weights for looseness and

their supporting structure for damage.

A 1, 2, 3, 4 571, 671

Revised

Mar 1/01

271002A Aileron Wing Cables (Fuselage) -

Inspect wing cables for fraying, chafing,

cleanliness, turnbuckle safetying,

and proper routing. Inspect pulleys

and guard pins for condition, wear,

corrosion, and security of installation.

Inspect cable for deterioration.

C 4 240, 243

Revised

Mar 1/01

271002B Aileron Wing Cables (Wing) - Inspect

wing cables for fraying, chafing,

cleanliness, turnbuckle safetying,

and proper routing. Inspect pulleys

and guard pins for condition, wear,

corrosion, and security of installation.

Inspect cable for deterioration.

C 3 525, 551,

625, 651

Revised

Sep 2/02

271003 Aileron Bell Cranks (Above Headliner)

- Inspect bell cranks for security of

installation, cleanliness, corrosion,

evidence of damage to cable guard

and cable attach points. Inspect attach

bolts for security of installation and

proper safetying of nuts.

C 4 251, 252

Revised

Sep 2/02

271004 Aileron/Spoiler Bell Crank and

Pushrods (Both Wings) - Inspect

aileron bell crank and pushrods for

condition, security of installation,

corrosion, evidence of damage to

quadrant arm, stop bolts, and support

bracket. Inspect aileron bell crank bolt

and stop bolts for proper safetying.

Inspect pushrod attach bolts for

security of installation and proper

safetying. Refer to Chapter 20, Torque

Data - Maintenance Practices.

C 3 551, 651

Revised

Mar 1/01

271005 Fuselage and Control Column Aileron

Cables - Inspect cables for fraying,

chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect

pulleys and guard pins for condition,

wear, corrosion, and security of

installation.

C 4 215, 216,

231, 232

5-10-01 Page 10

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

271006 Control Wheel - Inspect control wheel

for condition and security of installation.

Operate control wheel and check for

freedom of movement.

B 2, 4 215, 216

271008 Aileron - Check aileron for correct travel

and cable tension.

E 6 571, 671

Revised

Mar 1/01

271009 Aileron Friction Band - Perform aileron

friction band check.

E 6 227

Revised

Mar 1/01

271010 Aileron Control System - Check

pushrod joints for security of

installation, and tightness of fasteners

where applicable. Refer to Chapter 20,

Torque Data - Maintenance Practices.

C 3 551, 651

Revised

Mar 1/01

271011 Aileron Slot Lip Spoiler Pushrods

- Lubricate. Refer to Chapter 12,

Lubricants - Description and Operation.

C 3 551, 651

271012 Spoiler System - Check rigging and

travel.

E 6 551, 651

Revised

Mar 1/01

271013 Spoiler - Inspect spoiler skins for cracks

and loose rivets; hinges for condition,

cracks, and security of installation;

pushrods, pushrod bolts, bearings,

and bonding jumpers for evidence of

damage or wear, failed fasteners, and

security of installation. Inspect bolts

on both ends of pushrods for proper

safetying of nuts with cotter pins.

B 1, 3 521, 621

Revised

Mar 1/01

271014 Aileron Trim Tab - Inspect the trim

tab skins for cracks, loose rivets, and

security of installation; and trim tab

hinge for cracks, security of installation,

and evidence of damage. Inspect

hinge pin for proper installation at hinge

pin retainer. Inspect horn and pushrod

for evidence of damage and security of

installation. Inspect pushrod bolts for

condition and proper safetying of nuts

with cotter pins.

A 1, 2, 3, 4 671

Revised

Mar 1/01

271015 Aileron Trim Tab Actuator - Inspect

actuator for security of installation and

evidence of damage and wear. Inspect

structure for evidence of damage,

cracks, and security of installation.

If torque putty is broken, retorque

mounting bolts. Inspect actuator rods

for evidence of bending. Inspect

pushrod bolts at actuator for proper

safetying of nut with cotter pin. Inspect

pushrod ends for bearing looseness

and excessive wear.

C 3 651

5-10-01 Page 11

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

271016 Aileron Trim Tab Actuator - Inspect for

free play in actuator. Refer to Chapter

27, Aileron Trim System - Maintenance

Practices.

B 1, 3 651

Revised

Mar 1/01

271017 Aileron Trim Tab Actuator Pushrods

- Inspect for free play in actuator,

condition and evidence of damage.

Inspect attaching hardware for wear

and security of installation.

B 1, 3 651

Revised

Mar 1/01

271018A Aileron Trim Tab Cables (Fuselage)

- Inspect cables for fraying, chafing,

cleanliness, turnbuckle safetying, and

proper routing. Inspect chains for

proper safetying at all points and chains

for proper alignment on sprockets.

Inspect pulleys and guard pins for

condition, wear, corrosion, and security

of installation.

C 4 625

Revised

Mar 1/01

271018B Aileron Trim Tab Cables (Wing) -

Inspect cables for fraying, chafing,

cleanliness, turnbuckle safetying, and

proper routing. Inspect chains for

proper safetying at all points and chains

for proper alignment on sprockets.

Inspect pulleys and guard pins for

condition, wear, corrosion, and security

of installation.

C 3 625, 651

Revised

Dec 1/06

271019 Aileron Trim Tab Cables - Lubricate

aileron trim cables and the cable

housing openings where the cables

enter the housing. Refer to Chapter

12, Flight Controls - Servicing.

K 12 625, 651

Revised

Mar 1/01

271020 Aileron Trim Tab Cable Stop Blocks

(Right Wing) - Inspect for condition and

security of installation.

C 3 671

Revised

Mar 1/01

271021 Aileron Trim Tab Control and Indicator

- Inspect control and indicator for

condition and security of installation.

Operate trim tab control and check

aileron trim tab for freedom of

movement. Inspect guide block for

condition and security of installation.

B 2, 4 226

271022 Aileron Trim Tab - Check aileron

trim tab travel and cable tension as

applicable.

E 6 671

271024 Aileron Trim Control Wheel Bearings -

Check for wear.

E 6 226

5-10-01 Page 12

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

271025 Aileron Trim Tab Actuator Part Number

2660044-1 - Disassemble, inspect and

lubricate.

E 6 651

Revised

Mar 1/10

271026 Aileron Trim Tab Actuator Part Number

2661615-1, -9 - Disassemble, inspect

and lubricate. Refer to Chapter 27,

Aileron Trim - Maintenance Practices.

Q 18 651

Revised

Mar 1/01

271027 Aileron Trim Tab Control Bearings

and Sprocket - Lubricate. Refer to

Chapter 12, Lubricants - Description

and Operation.

G 8 226

Added

May 5/03

271028 Control Tube and Control Column

Bearings - Lubricate. Refer to Chapter

12, Flight Controls - Servicing.

E 6 215, 216

Revised

Mar 1/01

272001 Rudder - Inspect rudder skins for

cracks and loose rivets, rudder

hinges for condition, cracks, and

security of installation; hinge bolts,

hinge bearings, hinge attach fitting,

and bonding jumper for evidence of

damage or wear, failed fasteners, and

security of installation. Inspect rudder

hinge bolts for proper safetying of

nuts with cotter pins. Inspect balance

weight for looseness and supporting

structure for damage.

A 1, 2, 3, 4 343

Revised

May 5/03

272002 Rudder Bell Crank - Inspect bell crank

stop bolts for corrosion, evidence of

damage, and security of installation.

Inspect cables attached to bell crank for

proper cotter pin safetying.

C 3 330

Revised

Mar 1/01

272003A Rudder Cables (Empennage) - Inspect

cables for deterioration. Inspect

cables for fraying, chafing, cleanliness,

turnbuckles safetying, and proper

routing. Inspect pulleys and guard

pins for condition, wear, corrosion, and

security of installation.

C 3 311, 320

Revised

Mar 1/01

272003B Rudder Cables (Fuselage) - Inspect

cables for deterioration. Inspect

cables for fraying, chafing, cleanliness,

turnbuckles safetying, and proper

routing. Inspect pulleys and guard

pins for condition, wear, corrosion, and

security of installation.

C 4 233, 253,

257

272004 Rudder Pedals and Rudder Pedal

Linkage - Inspect for condition and

security. Operate rudder controls and

check for freedom of movement.

B 2, 4 211, 212

5-10-01 Page 13

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

272005 Rudder Pedal Linkage - Lubricate.

Refer to Chapter 12, Lubricants -

Description and Operation.

E 6 211, 212

272006 Rudder - Check travel and cable

tension.

E 6 320, 343

Revised

Mar 1/01

272007 Rudder Gust Lock (Airplanes

20800030 thru 20800236 and

208B0001 thru 208B0381) (if installed)

- Inspect for condition, security of

installation, and positive locking action.

B 2, 4 320

Revised

Mar 1/01

272008 Rudder Control System - Check

connections for security of installation,

and tightness of fasteners where

applicable. Refer to Chapter 20,

Torque Data - Maintenance Practices.

C 3 211, 212,

320

Revised

Mar 1/01

272009 Rudder Trim Flex Shaft - Inspect for

deterioration and condition of coupling

and roll pins and safe wire.

C 4 226

Revised

Mar 1/01

272010 Rudder Trim Wheel and Indicator -

Inspect trim wheel and indicator for

condition and security of installation.

Operate trim wheel and check rudder

trim for freedom of movement.

B 2, 4 226

Revised

Mar 1/01

272011 Rudder Gust Lock (Airplanes

20800237 and On and 208B0382

and On) - Inspect in accordance

with AERO TWIN STC airworthiness

requirements.

B 2, 4 320

Revised

May 5/03

273001 Elevator - Inspect elevator skins for

cracks and loose rivets; elevator

hinges for condition, cracks, and

security; and hinge bolts, hinge

bearings, torque tube, horn, attach

fittings, and bonding jumpers for

evidence of damage or wear, failed

fasteners, and security. Inspect

elevator hinge bolts for proper

safetying of nuts with cotter pins.

Inspect balance weights for looseness

and supporting structure for damage.

Inspect outboard tips for cracks in rib

flange.

A 1, 2, 3, 4 375, 376

5-10-01 Page 14

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

May 5/03

273002 Elevator Bell Crank (Aft) - Inspect bell

crank, bearings, pushrod, stop bolts,

and brackets for corrosion, evidence of

damage, failed fasteners, and security

of installation; proper safetying of bell

crank; and pushrod bolts for proper

safetying of nuts with cotter pins.

Refer to Chapter 20, Torque Data -

Maintenance Practices.

C 3 320, 330

Revised

May 5/03

273003 Elevator Bell Crank (Forward) - Inspect

bell crank, bearings, pushrod, stop

bolts, and brackets for corrosion,

evidence of damage, failed fasteners,

and security of installation; proper

safetying of bell crank; and pushrod

bolts for proper safetying of nuts with

cotter pins. Refer to Chapter 20,

Torque Data - Maintenance Practices.

C 4 213, 214

Revised

Mar 1/01

273004 Elevator Cables (Tailcone) - Inspect

cables for fraying, chafing, cleanliness,

turnbuckle safetying, and proper

routing. Inspect pulleys and guard

pins for condition, wear, corrosion, and

security of installation.

C 4 213, 217,

233, 253,

257

Revised

Mar 1/01

273005 Elevator Cables (Fuselage) - Inspect

cables for fraying, chafing, cleanliness,

turnbuckle safetying, and proper

routing. Inspect pulleys and guard

pins for condition, wear, corrosion, and

security of installation.

C 3 311

Revised

Mar 1/01

273006 Control Column - Inspect control

column for evidence of damage, failed

fasteners, and security of installation.

Operate control column and check for

freedom of movement.

B 2, 4 223, 224

Revised

May 5/03

273007 Elevator - Check elevator travel and

cable tension.

E 6 375, 376

Revised

Mar 1/01

273008 Elevator Friction Band - Perform

elevator friction band checks.

E 6 227

Revised

Mar 1/01

273009 Elevator Control System - Check

pushrod joints for security of

installation, and tightness of fasteners

where applicable. Refer to Chapter 20,

Torque Data - Maintenance Practices.

C 3 320, 330

Revised

May 5/03

273010 Elevator Trim Tabs - Inspect elevator

trim tabs.

A 1, 2, 3, 4 375, 376

5-10-01 Page 15

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

May 5/03

273011 Elevator Trim Tab Actuators - Inspect

actuator for security of installation and

evidence of damage; and mounting

structure for evidence of damage,

cracks and security of installation at the

rear spar of the horizontal stabilizer.

C 4 373, 374

Revised

May 5/03

273012 Elevator Trim Tab Actuators - Inspect

for free play in actuator. Refer

to Chapter 27, Elevator Trim -

Maintenance Practices.

B 1, 3 373, 374

Revised

May 5/03

273013 Elevator Trim Tab Actuator Pushrods -

Inspect for condition and evidence of

damage. Inspect attaching hardware

for wear and security of installation.

B 2, 4 375, 376

Revised

Mar 1/01

273014 Elevator Trim Tab Cables (Fuselage)

- Inspect cables for fraying, chafing,

cleanliness, turnbuckle safetying, and

proper routing. Inspect chains for

proper safetying at all points and chains

for proper alignment on sprockets.

Inspect pulleys and guard pins for

condition, wear, corrosion, and security

of installation.

C 3 233, 253,

257

Revised

Mar 1/01

273015 Elevator Trim Tab Cables (Tailcone)

- Inspect cables for fraying, chafing,

cleanliness, turnbuckle safetying, and

proper routing. Inspect chains for

proper safetying at all points and chains

for proper alignment on sprockets.

Inspect pulleys and guard pins for

condition, wear, corrosion, and security

of installation.

C 4 311, 320

Revised

Mar 1/01

273016 Elevator Trim Tab Cable Stop Blocks

- Inspect for condition and security of

installation.

C 3 311, 312

Revised

Mar 1/01

273017 Elevator Trim Tab Control and Indicator

- Inspect control and indicator for

condition and security of installation.

Operate trim tab control and check for

freedom of movement.

B 2, 4 226

273018 Elevator Trim Control Wheel Bearing -

Check for wear.

E 6 226

Revised

May 5/03

273019 Elevator Trim Tab - Check elevator trim

tab travel and cable tension.

E 6 375, 376

5-10-01 Page 16

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

273020 Electric Elevator Trim Actuator -

Inspect actuator motor for condition,

security of installation, and evidence of

overheating. Inspect chain for tension

and proper alignment, actuator for

condition, wear, corrosion, and security

of installation.

C 4 226

273021 Electric Elevator Trim - Operate electric

trim, and check trim tab travel time and

cable tension.

E 6 226

Revised

Mar 1/00

273022 Electric Trim Clutch Torque Check

- Rotate sprocket housing slowly

clockwise or counterclockwise and

check torque. Refer to appropriate

Sperry Installation/Maintenance

Manual for torque settings.

E 6 226

273023 Stall Warning System - Inspect for

condition and security of installation.

C 3 503

273024 Stall Warning Heater Thermostat -

Inspect for condition and security of

installation.

C 3 503

Revised

Mar 1/01

273025 Stall Warning Horn - Perform an

operational check.

A 1, 2, 3, 4 ENG

Revised

Mar 1/01

273026 Stall Warning Heater - Perform an

operational check.

A 1, 2, 3, 4 ENG

Revised

May 5/03

273028 Elevator Trim Tab Actuator Part

Number 2660017-1 - Disassemble,

inspect and lubricate. Refer to Chapter

12, Lubricants - Description and

Operation.

E 6 373, 374

Revised

Mar 1/10

273029 Elevator Trim Tab Actuator Part

Number 2661215-1, -9 - Disassemble,

inspect and lubricate. Refer to

Chapter 27, Elevator Trim System -

Maintenance Practices.

Q 18 373, 374

Added

May 5/03

273030 Elevator Bell Crank (Forward) -

Lubricate forward elevator bell crank

components. Refer to Chapter 12,

Flight Controls - Servicing.

E 6 213, 214

Added

May 5/03

273031 Elevator Bell Crank (Aft) - Lubricate

the aft elevator bell crank components.

Refer to Chapter 12, Flight Controls -

Servicing.

E 6 320, 330

Revised

Mar 1/01

275001 Flaps - Inspect flaps for loose rivets,

cracks, condition, and security of

installation.

A 1, 2, 3, 4 527, 627

5-10-01 Page 17

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

275002 Primary Flap System - Operate flaps

with flap control lever, located in control

pedestal, through full range of travel

and observe flaps for erratic motion,

binding, and interference.

A 1, 2, 3, 4 226

Revised

Mar 1/01

275003 Standby Flap System - Perform

standby flap motor operational check.

Refer to Chapter 27, Flap System -

Maintenance Practices.

A 1, 2, 3, 4 243

275004 Flap Tracks - Inspect flap tracks and

rollers for corrosion, frozen bearings,

flat spots, wear, deformation, and

cracks.

C 3 525, 625

275005 Flap Control System - Inspect flap

control lever and pointer for security

of installation, travel, and evidence of

damage. Inspect flap control and flap

follow-up cables for deterioration and

security of installation.

C 4 226

Revised

Jan 2/06

275006 Flap Bell Cranks, Control Rods,

Pulleys, and Cables - Inspect bell

cranks, pulleys and cables for condition

and security of installation. Inspect flap

bell cranks for corrosion and cracks,

primarily in the welds. Inspect all

control rods (interconnect, connecting,

pushrod, and wing-to-wing) for bent

rods, chafing, seized or worn rod end

bearings, loose rod end locknuts, and

verify rod end thread engagement

reaches at least to the rod end

inspection hole. Check rod end and

bell crank bearings for corrosion; clean

and lubricate. Refer to Chapter 12,

Lubricants - Description and Operation.

C 3 252

Revised

Mar 1/01

275007 Flap Actuator Assembly and Fuselage

Seal Assemblies - Inspect condition

and security of motors, drivescrew,

and transmission. Clean drivescrew

threads and lubricate with #10 weight

non-detergent oil. Inspect flap actuator

assembly support structure for cracks

and security of installation. Inspect

fuselage seal assemblies for condition

and security of installation.

C 3 252

Revised

Mar 1/01

275008 Flap Switch Actuator - Inspect flap

switch actuator switches, support

structure, and associated linkage for

condition and security of installation.

C 4 252

5-10-01 Page 18

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

275009 Flaps - Perform an operational check.

Refer to Chapter 27, Flap Rigging

Guide - Adjustment/Test.

E 6 226, 243

Revised

Nov 3/03

275010 Flap bell crank Part Numbers

2622281-2, -12 and 2692001-2 -

Inspect in accordance with the latest

revision of CAB02-1. Refer to Chapter

4, Typical Inspection Time Limits or

Chapter 4, Severe Inspection Time

Limits.

MC MC 252

281001 Fuel Tank Area - Inspect for fuel stain,

discoloration, and evidence of fuel

leaks.

A 1, 2, 3, 4 521, 621

Revised

Mar 1/01

281002 Fuel Reservoir Tank - Check plumbing

and external components to reservoir

tank for condition, security of

installation, and evidence of leakage.

C 4 244

281003 Fuel Tank Filler Cap(s) and Flapper

Valve(s) - Inspect for damage or broken

components and check lock position of

filler cap.

A 1, 2, 3, 4 521, 621

281004 Drain Valves - Check operation and

inspect for leakage.

A 1, 2, 3, 4 521, 621

Revised

Mar 1/01

281005 Fuel Reservoir and Fuel Tanks - Check

auxiliary fuel pump, ejector pump,

swing check valves, and fuel shutoff

valve screens for damage and security

of installation.

C 4 244

Added

Mar 1/08

281006 Fuel Quantity System Check (CAN bus

system) - Do a fuel quantity system

check. Refer to Chapter 28, Fuel Tanks

- Adjustment/Test.

H 9 222

Revised

Oct 15/99

282001 Fuel Selector Valves and Linkages

(Wing Area) - Inspect shutoff valves,

controls and linkage for condition,

security and evidence of damage.

Inspect all fuel selector valve arms for

proper contact with the off stop pins.

Rerig if necessary.

A 1, 2, 3, 4 511, 611

282002 Fuel Selector Linkages (Cabin Area)

- Inspect linkage and controls for

condition, security and evidence of

damage.

C 4 243

282003 Fuel Shutoff Valve - Inspect linkage

and valve for evidence of damage and

operation. Inspect valve for leakage.

C 4 203

282004 Fuel Shutoff Control - Operational

check.

A 1, 2, 3, 4 226

5-10-01 Page 19

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

282005 Fuel Line Connector Covers and

Drains - Inspect covers and drain lines

for condition and security of installation.

C 4 233, 234

Revised

Mar 1/01

282006 Firewall Mounted Fuel Filter with

Bypass Flag (Red Warning Button) -

Clean, inspect for leaks, security of

installation and condition.

A 1, 2, 3, 4 151

Revised

Mar 1/01

282007 EPA Can - Inspect for leakage, security

of installation and condition. Drain

completely.

A 1, 2, 3, 4 151

282008 Fuel Float Vent Line - Inspect for

evidence of damage, cleanliness, and

obstruction.

C 4 575, 675

Revised

Mar 1/01

282009 Vent System Float Valve(s) - Perform

functional test. Refer to Chapter

28, Fuel Vent System - Maintenance

Practices.

E 6 521, 621

Revised

Mar 1/01

284001 Reservoir Fuel Low Annunciator

(Engine Running) - Position both fuel

selectors to OFF. Verify Reservoir Low

warning light illuminates as the fuel

level in the reservoir tank drops below

full, then place both fuel tank selectors

to ON.

A 1, 2, 3, 4 ENG

284002 Fuel Selectors OFF Warning System -

Perform operational check of warning

system.

A 1, 2, 3, 4 ENG

284003 Fuel Selector OFF Warning System -

Inspect relays, switches, connectors

and electrical wiring for condition and

security of installation.

C 4 243

Revised

Mar 1/08

284004 Fuel Quantity Indication Calibration

(Float system) - Do a fuel quantity

indication calibration. Refer to Chapter

28, Fuel Quantity Indicating System -

Maintenance Practices.

H 9 221

284005 Low Fuel Warning - Inspect for

damaged electrical components.

Perform functional test of wing and

reservoir low fuel warning systems.

H 9 244

Revised

Mar 1/08

301001 Surface De-ice Regulator and De-ice

Control Valves (without TKS) -

Examine for condition and correct

installation.

C 3 122, 251

Revised

Mar 1/08

301002 De-ice Boot Plumbing (without TKS)

- Examine for condition and correct

installation.

C 3 373, 374,

501, 503,

601, 602

5-10-01 Page 20

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/08

301003 Surface De-ice System (without TKS) -

Examine the electrical components for

condition and correct installation.

C 3 231

(208),

251

(208B)

Revised

Mar 1/08

301004 De-ice Boots (without TKS) - Examine

for abrasions, cuts, nicks, correct

installation, and cleanliness.

B 1, 3 340, 371,

372, 501,

503, 601,

602

Revised

Mar 1/08

301005 Wing De-ice System (Engine Running)

(without TKS) - Do a check of the wing

de-ice system.

A 1, 2, 3, 4 ENG

Revised

Mar 1/08

301006 Bleed Air Pressure Regulator

(Airplanes 20800222 and On

and 208B0317 and On, and

Airplanes 20800001 thru 20800221

and 208B0001 thru 208B0316

Incorporating SK208-112) (without

TKS) - Do a discharge pressure

check. Refer to Chapter 36, Pneumatic

Distribution - Maintenance Practices.

B 1, 3 122

Revised

Mar 1/08

301007 Bleed Air Pressure Regulator

(Airplanes 20800001 thru 20800221

and 208B0001 thru 208B0316 Not

Incorporating SK208-112) (without

TKS) - Do a discharge pressure

check. Refer to Chapter 36, Pneumatic

Distribution - Maintenance Practices.

A 1, 2, 3, 4 122

Revised

Mar 1/10

301101 100 Hour Operational Check (with

TKS) - Visually check for wear and

security of installation at the propeller

boots, propeller nozzle, propeller

feed tubes, and propeller slinger.

Check operation of pumps, pump CAS

annunciator (G1000), press test TKS

annunciator (non-G1000), fluid flow of

slinger and leading edge panels.

A 1, 2, 3, 4 110, 220,

221, 240,

340, 373,

374, 527,

531, 571,

627, 631,

671, 903,

904

Revised

Mar 1/10

301102 Annual Operational Check (with TKS) -

Do the 100-Hour operational check. Do

a check of the tank quantity indicator,

tank fluid level CAS annunciator,

pump fluid delivery rate, high-pressure

warning switch and CAS annunciator,

low-pressure warning switch and CAS

annunciator.

H 9 110, 130,

151, 152,

213, 214,

217, 218,

220, 233,

234, 253,

254, 257,

258, 311,

312, 320,

340, 373,

374, 527,

531, 571,

627, 631,

671, 903,

904

5-10-01 Page 21

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/08

304001 Windshield Anti-ice System (without

TKS) - Examine for condition, correct

installation and electrical wiring of

heated panel. Do a check of the

condition of storage bag.

C 4 240

Revised

Mar 1/08

304002 Windshield Anti-ice System (without

TKS) - Do a check of the condition and

mounting of controller and relay.

C 4 215

Revised

Mar 1/08

304003 Windshield Anti-ice System (without

TKS) - Do an operational check of the

AUTO and MANUAL systems. Make

sure that the WINDSHIELD ANTI-ICE

annunciator light comes on.

B 2, 4 AUX

Revised

Mar 1/08

306001 Propeller Anti-ice Slip Rings, Boots,

and Wiring (without TKS) - Examine

for condition and correct installation.

Examine brushes for proper tracking.

B 1, 3 110

Revised

Mar 1/08

306002 Propeller Anti-ice Brushes (without

TKS) - Examine each brush for

wear, signs of damage, cleanliness,

correct installation and correct rigging.

Examine electrical wires for condition

and correct installation.

A 1, 2, 3, 4 110

Revised

Mar 1/08

306003 Propeller Anti-ice System (Engine

Running) (without TKS) - Do a check

of the propeller anti-ice system.

A 1, 2, 3, 4 ENG

Revised

Mar 1/08

306004 Propeller Anti-ice Varistor (without

TKS) - Examine the firewall-mounted

varistor for condition and correct

installation. Examine the electrical

connections for condition and correct

installation.

C 1 151

Revised

Mar 1/01

308001 Ice Detector Light - Inspect for

condition and security of installation.

C 4 231

Revised

Mar 1/01

321001 Main Landing Gear System - Inspect

for condition and security of installation.

Check free play between the center

spring and gear legs.

C 2 721, 722

Revised

Mar 1/01

321002 Main Gear Fairings - Inspect for

condition and security of installation.

Check for interference between fairing

and brake lines.

C 2 721, 722

Deleted

Sep 2/02

321003

5-10-01 Page 22

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Added

Jun 3/02

321004 Inspect main landing gear spring

and center spring. Refer to

Chapter 32, Main Landing Gear -

Cleaning/Painting. Remove main

landing gear fairings. Inspect for

corrosion. If corrosion is found, remove

corrosion. Inspect paint and touch-up

paint as required. Inspect fillet seal

around main gear spring at center

spring. Repair seal if damaged.

V 23 721, 722

Revised

Nov 3/03

321005 Main Landing Gear Axle Part Numbers

2641011-1, -3 and -4 - Perform a

Magnetic Particle Inspection. Refer

to Chapter 4, Typical Inspection

Time Limits and Severe Inspection

Time Limits. Also, refer to 5-14-01,

Supplemental Inspection Number

32-10-01.

MB MB 721, 722

Deleted

Jan 2/06

321006

Deleted

Jan 2/06

321007

Revised

Jan 2/06

321008 Main Gear Spring and Center Spring.

Remove the main landing gear fairings.

Disassemble the outer spring from the

center spring. If corrosion is present,

the gear puller may be required to

disassemble the springs. Refer to

Chapter 32, Main Landing Gear -

Maintenance Practices. Remove

the corrosion and shot peen. If

corrosion cannot be removed within

the defined repair limits, install new

gear components. Reassemble the

gear with wet corrosion resistant

epoxy primer. Apply touch-up paint

as required, and add fillet seal. Refer

to Chapter 32, Main Landing Gear -

Cleaning/Painting. Failure to adhere

to the scheduled requirements could

result in gear failure if corrosion is not

detected and repaired.

AB 29 721, 722

5-10-01 Page 23

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Jan 2/06

321009 Main Gear Spring and Center Spring.

Remove the main landing gear

fairings. Disassemble the main gear

spring from the center spring. If

corrosion is present, the gear puller

may be required to disassemble the

springs. Refer to Chapter 32, Main

Landing Gear - Maintenance Practices.

Remove the corrosion and shot peen.

If corrosion cannot be removed within

the defined repair limits, install new

gear components. Reassemble the

gear with wet corrosion resistant

epoxy primer. Apply touch-up paint

as required, and add fillet seal. Refer

to Chapter 32, Main Landing Gear -

Cleaning/Painting. Failure to adhere

to the scheduled requirements could

result in gear failure if corrosion is not

detected and repaired.

AC 30 721, 722

322001 Nose Gear Shock Strut - Inspect

for evidence of leakage. Inspect

strut barrel for corrosion, pitting and

cleanliness.

C 2 701

Revised

Mar 1/01

322002 Nose Gear Torque Links and Shock

Strut - Inspect for condition, wear

at attach points and security of

installation, then service. Refer to

Chapter 12, Lubricants - Description

and Operation.

A 1, 2, 3, 4 701

Revised

Mar 1/01

322003 Nose Gear Fairings - Inspect for

condition and security of installation.

C 2 701

Revised

Mar 1/01

322004 Nose Gear Fork - Inspect for condition

and security of installation.

C 2 701

Revised

Mar 1/01

322005 Nose Gear Spring Yoke - Inspect

bearing for corrosion and freedom of

rotation. Lubricate bearing. Refer to

Chapter 12, Lubricants - Description

and Operation. Reinstall bolt and

torque and safety wire. Refer to

Chapter 32, Nose Landing Gear -

Maintenance Practices.

A 1, 2, 3, 4 701

Added

Mar 1/08

322006 Nose Gear Drag Link Spring Supports

- Examine for cracks, wear, loose bolts,

elongated holes, and corrosion.

A 1, 2, 3, 4 701

Revised

Mar 1/01

324001 Main Landing Gear Wheels and

Tires - Check for wear, pressure and

condition. Rotate tires as necessary

to achieve uniform tire wear. Refer to

Chapter 12, Tires - Servicing.

A 1, 2, 3, 4 721, 722

5-10-01 Page 24

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

324002A Landing Gear Wheel Bearings

(Airplanes 20800001 thru 20800201

and 208B0001 thru 208B0255 Not

Incorporating CAB 91-30) - Inspect

for condition and repack. Refer to

Chapter 12, Lubricants - Description

and Operation.

A 1, 2, 3, 4 701, 721,

722

Revised

Mar 1/01

324002B Landing Gear Wheel Bearings

(Airplanes 20800202 and On

and 208B0256 and On, and

Airplanes 20800001 thru 20800201

and 208B0001 thru 208B0255

Incorporating CAB 91-30) - Inspect

for condition and repack. Refer to

Chapter 12, Lubricants - Description

and Operation.

B 2, 4 701, 721,

722

Revised

Mar 1/01

324003 Nose Landing Gear Wheel and Tire

- Check for wear, pressure and

condition. Refer to Chapter 12, Tires -

Servicing.

A 1, 2, 3, 4 701

324004 Brake Assemblies - Inspect for wear of

linings, disc warpage and evidence of

leakage.

A 1, 2, 3, 4 721, 722

Revised

Mar 1/01

324005 Brake System Reservoir - Inspect for

security of installation, condition and

leaks. Check fluid level. Refer to

Chapter 12, Hydraulic Fluid - Servicing.

A 1, 2, 3, 4 151

Revised

Mar 1/01

324006 Parking Brake Control - Service

parking brake control using Silicone

lubrication.

E 6 220

Revised

Mar 1/01

324007 Parking Brake Control and Valve -

Inspect for condition, leakage, security

of installation, as well as freedom and

correct operation.

C 4 203

Revised

Mar 1/01

324008 Brake System Plumbing - Inspect for

leaks. Inspect hoses for bulges and

deterioration. Check rigid lines for

security of installation, proper routing

and chafing.

C 2 721, 722

Revised

Mar 1/01

325001 Nose Landing Gear Shimmy Damper

- Inspect for condition and security of

installation.

A 1, 2, 3, 4 701

Revised

Mar 1/01

325002 Nose Landing Gear Shimmy Damper

- Check for need to service. Refer to

Chapter 32, Landing Gear - General.

A 1, 2, 3, 4 701

Revised

Mar 1/01

325003 Nose Wheel Steering Linkage - Check

condition, security of installation and

travel.

C 2 701

5-10-01 Page 25

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

325004 Nose Wheel Steering Linkage Bolts -

Inspect for condition and security of

installation.

C 2 701

Revised

Jan 2/06

325005 Nose Landing Gear Shimmy Damper

Pivots - Lubricate nose landing gear

shimmy damper pivots. Refer to

Chapter 12, Lubricants - Description

and Operation. Airplanes 2080001

thru 2080393 and 208B0001 thru

208B1039

C 2 701

Revised

Mar 1/01

325006 Nose Landing Gear Steering Stop Bolt

or Block - Inspect for condition, security

of installation with bolt head down.

A 1, 2, 3, 4 701

Revised

May 5/03

325007 Nose Gear Steering Bell Crank -

Inspect for condition, and security of

installation.

C 2 701

Revised

Mar 1/01

325008 Nose Wheel Steering Rod End -

Inspect for condition and security of

installation.

C 2 701

Added

Mar 1/01

325009 Nose Landing Gear Spring and

Fuselage Support Chafing Inspection

- Inspect nose landing gear spring

and areas common to fuselage

support for gouging and chafing. If

gouging is equal to or less than 0.005

inch, touch up paint as required. If

gouging is between 0.005 and 0.050

inch, blend damaged area for a

smooth transition between gouge and

immediate surrounding area at a ratio

of 20:1 lengthwise, and 5:1 across the

circumference and shot peen blended

area. If gouging is between 0.050 and

0.075 inch, perform a magnetic particle

inspection. If gouging is deeper than

0.075 inch, replace spring prior to next

flight.

H 9 701

Revised

Mar 1/01

327001 Jack Pad Installation - Check for

condition and security of installation.

C 2 213, 214,

721, 722

Revised

Mar 1/01

330001 Flight Compartment Lights - Inspect

electrical components for condition and

security of installation.

C 4 231, 232

330002 Instrument Panel Lights - Perform

operational check.

A 1, 2, 3, 4 220, 221,

222, 223,

224

Revised

Mar 1/01

332001 Passenger and Cargo Compartment

Lights - Inspect electrical components

for condition, operation, and security of

installation.

C 4 251, 252,

255, 256

5-10-01 Page 26

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

332002 Interior Lighting - Check operation

of cabin, passenger reading, no

smoking/seatbelt, and control wheel

map lighting.

A 1, 2, 3, 4 231, 232,

251, 252,

255, 256

332003 Courtesy/Cargo Light Timer - Perform

operational check.

B 2, 4 BAT

Revised

Mar 1/01

334001 Exterior Lights - Inspect electrical

components for condition and security

of installation.

C 3 330, 501,

503, 575,

601, 603,

675

Revised

Mar 1/01

334002 Landing/Taxi Lights - Inspect for

condition and security of installation.

C 3 503, 603

334003 Exterior Lighting - Perform operational

check.

C 3 215

340001 Navigation Antenna(s) - Inspect for

condition, security of installation and

evidence of damage.

C 3 222

341001 Static System - Inspect plumbing for

security of installation and evidence of

damage.

C 3 503, 603

Revised

May 1/08

341002 Altimeter and Static System - Examine

in accordance with 14 CFR Part

91.411. (For airplanes equipped with

the Garmin G1000, also refer to the

Garmin G1000 Line Maintenance

Manual for specific instructions to

do the checks that follow: Altimeter,

Pitot/Static Airspeed Test, and Static

Port Vertical Speed (Rate of Climb)

Test).

I 10 223

341003 Alternate Static Source - Inspect for

evidence of damage and security of

installation.

C 4 215, 216

341005 Pitot Tube(s) - Visually check tube(s)

and static ports for obstructions.

Inspect mast(s) for bending and

evidence of damage. Ensure sealant at

mast-to-wing joint is in good condition.

A 1, 2, 3, 4 503, 603

Revised

Mar 1/01

341006 Pitot Tube(s) Heater - Place the

PITOT/STATIC heat switch to ON for

approximately 30 seconds, then to

OFF. Verify tube(s) heats.

A 1, 2, 3, 4 BAT

341007 Static System Drain Valves - Visually

inspect for leaks, and presence

of water in drain fittings. Drain

accumulated moisture. Inspect

condition and security of installation.

A 1, 2, 3, 4 215, 216

5-10-01 Page 27

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Dec 1/06

341008 Overspeed Pressure Switch and Icing

Low Airspeed Awareness System (110

KIAS) (if installed) - Complete the

operational tests. Refer to Chapter

34, Pitot Static System - Maintenance

Practices.

I 10 BAT

Revised

Dec 1/06

341009 Overspeed Pressure Switch and Icing

Low Airspeed Awareness System (110

KIAS) Switch (if installed) - Examine for

condition and correct installation.

C 4 222

Revised

Jan 2/06

342001 Transponder Control - Operate

individual controls and perform

operational test of transponder system

in accordance with 14 CFR Part

91.413.

I 10 BAT

Deleted

Jan 2/06

344101

Deleted

Jan 2/06

344102

Deleted

Jan 2/06

344103

Revised

Mar 1/01

350001 Oxygen System - Inspect system and

component mounting for condition and

security of installation.

C 3 251, 252,

255, 256

Revised

Mar 1/01

350002 Oxygen System - Inspect regulator,

shutoff valve and remote filling system

for operation, condition and security of

installation.

C 3 311, 312

350003 Oxygen Control System - Inspect

control handle and pressure regulator

for condition and operation.

C 4 243

Revised

Jul 1/10

350004 Oxygen Cylinder (DOT-E 8162) -

Perform hydrostatic test.

J 11 LAB

Added

Jul 1/10

350005 Oxygen Cylinder (DOT-SP 8162) -

Perform hydrostatic test.

AN 41 LAB

Revised

Mar 1/01

351001 Oxygen Masks and Hose Assemblies

- Inspect for condition and clean.

Inspect hose connection for security

of installation and hose for condition.

Perform operational check of pilot's

mask microphone.

A 1, 2, 3, 4 231, 232

351002 Oxygen Masks - Perform operational

test on the oxygen masks. Inspect flow

indicator for freedom of movement.

A 1, 2, 3, 4 231, 232

351003 Smoke Goggles (if installed) - Check

for condition of goggles and security of

storage bag to barrier.

C 4 231, 232

5-10-01 Page 28

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Added

Oct 15/99

351501 Scott 359 Series Oxygen Mask

- Inspect mask for cracks, tears,

obscured vision, dirt, buckles that

are mechanically sound and secure,

exhalation valve sticking, leakage and

microphone operation.

H 9 231, 232

Revised

Mar 1/01

371001 Vacuum System Ejector - Inspect for

condition and security of installation.

C 1 151

371002 Vacuum System Hoses - Inspect for

hardness, deterioration, looseness or

collapsed hoses.

C 4 201, 202

Revised

Mar 1/01

371003 Vacuum Relief Valve Filter - Replace

urethane filter element. Filter may

be replaced more often if conditions

require. Refer to Chapter 12, Vacuum

System Central Air Filter - Servicing.

C 4 201

Revised

Mar 1/01

371004 Vacuum System Central Air Filter

- Inspect for damage, deterioration

and contamination. Replace filter, if

required. Refer to Chapter 12, Vacuum

System Central Air Filter - Servicing.

C 4 201

Revised

Mar 1/01

371005 Vacuum System Relief Valve - Inspect

for condition and security of installation.

C 4 201

371006 Low Vacuum Warning Switch - Inspect

for condition and security of installation.

C 4 222

371007 Suction Gauge (Engine Running) -

Verify operation.

A 1, 2, 3, 4 ENG

520105 Crew Doors Latch Pin Receptacle -

Inspect for damage, cracks and wear.

C 4 801, 802

520106 Crew Doors Hinges, Latch Pin and

Stop Assembly - Service.

C 4 801, 802

Revised

Mar 1/01

521001 Pilot and Copilot Crew Doors - Inspect

for condition, security of installation and

operation.

C 4 801, 802

521002 Crew Doors Seal - Inspect for proper

installation, cuts, abrasions and

excessive wear. Clean.

C 4 801, 802

521003 Crew Doors Latch Pin - Inspect for

damage, cracks, wear and rigging.

C 4 801, 802

521004 Crew Doors Latch Pin Guide - Inspect

for damage, cracks and wear.

C 4 801, 802

5-10-01 Page 29

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

521007 Passenger Doors - Inspect for

condition, security of installation and

operation. Inspect hinges, latches,

steps, cables and latch pins for

damage, cracks, wear, alignment,

fraying and adjustment.

C 4 804

Revised

Mar 1/01

521008 Crew Door Entrance Steps - Inspect

for condition, security of installation and

folding operation. Clean.

C 4 801, 802

521009 Crew Door Locks - Check proper

operation of locking mechanisms

including the external key lock

operation.

C 4 801, 802

521010 Passenger Doors Seals - Inspect for

proper installation, cuts, abrasions and

excessive wear. Clean.

C 4 804

Revised

Mar 1/01

523001 Cargo Upper and Lower Doors -

Inspect for condition, security of

installation and operation. Inspect

hinges, latches and latch pins for

damage, cracks, wear, alignment and

adjustment.

C 4 803

523002 Cargo Upper and Lower Door Seals

- Inspect for proper installation, cuts,

abrasions and excessive wear. Clean

and service.

C 4 803

Deleted

Jan 2/06

523003

527001 Door Warning Annunciator Light -

Open upper cargo door and verify that

light illuminates, then close door. Open

upper passenger door (if applicable)

and verify that light illuminates.

C 4 BAT

Revised

Mar 1/08

530001 Corrosion Prevention and Corrosion

Program Inspections - Use the age of

the airplane for the initial inspection.

The initial and repeat intervals are

found in Chapter 5, 5-30-01 or 5-30-02,

Corrosion Prevention and Corrosion

Program Inspections, Table 1.

A 1, 2, 3, 4 ALL

Revised

Mar 1/01

531001 Fuselage Structure - Inspect skin

structure and fasteners for condition

and security of installation.

C 4 211, 212,

215, 216,

231, 232,

251, 252,

255, 256,

257, 258,

311, 312

Revised

Mar 1/01

531002 Control Pedestal - Inspect for condition

and security of installation.

C 4 226

5-10-01 Page 30

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

531003 Control Quadrant - Inspect for condition

and security of installation.

C 4 226

531004 Tailcone Drain Opening - Inspect for

obstruction and remove any foreign

material from opening to prevent

blockage.

A 1, 2, 3, 4 311, 312

Revised

Aug 2/04

531005 Fuselage to Strut Attach Fitting Lugs

(NDI - Eddy Current) - Inspect. Refer

to Chapter 4, Typical Inspection

Time Limits. Also, refer to 5-14-04,

Supplemental Inspection Number

53-20-07.

MH MH 253, 254

Revised

Mar 1/08

531006 Fuselage to Strut Attach Fitting

Lugs (Nominal/Standard Bolt Size)

Part Number S3461-74 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Severe Inspection Time Limits.

Also, refer to 5-14-04, Supplemental

Inspection Number 53-20-07.

MG MG 253, 254

Revised

Dec 1/06

531007 Fuselage to Wing Carry-Thru Attach

Fitting (NDI - Eddy Current) - Inspect.

Refer to Chapter 4, Typical Inspection

Time Limits or Severe Inspection

Time Limits. Also, refer to 5-14-08,

Supplemental Inspection Number

53-20-02.

MF MF 251, 252

Added

Nov 3/03

531008 Fuselage Engine Mount Fittings

- Inspect. Refer to 5-14-02,

Supplemental Inspection Number

53-10-01.

AD 31 152, 151

Added

Nov 3/03

531009 Seat Rails and Attachment Structure

Inspection - Perform. Refer to 5-14-13,

Supplemental Inspection Number 53-

10-07.

AF 33 251, 252,

255, 256

Added

Mar 1/08

531010 Fuselage to Strut Attach Fitting Lugs

(1/64 Inch Oversize Bolt Size) Part

Number S3461-159 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Severe Inspection Time Limits.

Also, refer to 5-14-04, Supplemental

Inspection Number 53-20-07.

MI MI 253, 254

Added

Mar 1/08

531011 Fuselage to Strut Attach Fitting Lugs

(1/32 Inch Oversize Bolt Size) Part

Number S3461-160 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Severe Inspection Time Limits.

Also, refer to 5-14-04, Supplemental

Inspection Number 53-20-07.

MJ MJ 253, 254

5-10-01 Page 31

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

532001 Center Section Drain Holes - Inspect

for obstruction and remove any

foreign material from holes to prevent

blockage.

C 4 233, 234,

253, 254,

257, 258

532002 Bilge Area - Clean and protect. E 6 233, 234,

253, 254,

257, 258

Added

Nov 3/03

532003 Cargo and Passenger Door Doublers

- Inspect. Refer to 5-14-03,

Supplemental Inspection Number

53-20-01.

AF 33 255, 256

Added

Nov 3/03

532004 Lower Forward Carry-Thru Bulkhead

- Inspect. Refer to 5-14-05,

Supplemental Inspection Number

53-20-03.

AG 34 233, 234

Added

Nov 3/03

532005 Main Landing Gear Fitting - Inspect.

Refer to 5-14-06, Supplemental

Inspection Number 53-20-04.

AJ 37 721, 722

Added

Nov 3/03

532006 Main Landing Gear Attach Fittings and

Aft Carry-Thru Bulkhead - Inspect.

Refer to 5-14-07, Supplemental

Inspection Number 53-20-05.

AG 34 721, 722

Added

Nov 3/03

532007 Fuselage to Wing Attach Fitting

Lugs - Inspect. Refer to 5-14-08,

Supplemental Inspection Number

53-20-02.

AD 31 233, 234

Added

Nov 3/03

532008 Firewall Brace and Doubler

Assemblies - Inspect. Refer to

5-14-09, Supplemental Inspection

Number 53-20-11.

AD 31 152, 151

Added

Nov 3/03

532009 Carry-Thru Root Rib - Inspect. Refer

to 5-14-10, Supplemental Inspection

Number 53-20-08.

AD 31 233, 234

Added

Nov 3/03

532011 Crew Door Frames - Inspect. Refer

to 5-14-11, Supplemental Inspection

Number 53-20-09.

AD 31 801, 802

Added

Nov 3/03

532012 Passenger and Cargo Door Frames

- Inspect. Refer to 5-14-12,

Supplemental Inspection Number

53-20-10.

AD 31 255, 256

Added

Nov 3/03

532013 Bulkheads and Stiffeners Below the

Seat Rail Attachments at FS 143.00

and FS 158.00 - Inspect. Refer to

5-14-14, Supplemental Inspection

Number 53-20-12.

AF 33 251, 252,

255, 256

5-10-01 Page 32

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Added

Nov 3/03

532014 Stringers at Intersections with Forward

and Aft Carry-Thru Bulkheads

- Inspect. Refer to 5-14-15,

Supplemental Inspection Number

53-20-13.

AG 34 233, 234

Added

Nov 3/03

532015 Fuselage Skin Doubler at Main Landing

Gear Cutout - Inspect. Refer to 5-14-

16, Supplemental Inspection Number

53-20-14.

AE 32 721, 722

Added

Nov 3/03

532016 Fuselage to Wing Carry-Thru Attach

Fitting and Bulkhead - Inspect. Refer

to 5-14-21, Supplemental Inspection

Number 53-20-06.

AG 34 511, 611

Added

Nov 3/03

535001 Fuselage to Horizontal Stabilizer

Attach Fittings - Inspect. Refer to

5-14-17, Supplemental Inspection

Number 53-50-01.

AD 31 340, 341,

373, 374,

375, 376

Added

Nov 3/03

535002 Vertical Stabilizer Attach Points

- Inspect. Refer to 5-14-18,

Supplemental Inspection Number

53-50-02 for the Typical Inspection

Compliance.

AD 31 340, 341,

373, 374,

375, 376

Added

Nov 3/03

535003 Vertical Stabilizer Attach Points

- Inspect. Refer to 5-14-18,

Supplemental Inspection Number

53-50-02 for the Severe Inspection

Compliance.

AH 35 340, 341,

373, 374,

375, 376

Revised

May 5/03

551001 Vertical and Horizontal Stabilizers -

Inspect structure and attach points for

condition and security of installation.

Check for missing or damaged Vortex

generators.

B 1, 3 340, 341,

373, 374,

375, 376

Revised

May 5/03

551002 Stabilizer Abrasion Boots (if installed)

- Check for nicks, cuts, tears, security

of attachment and evidence of other

damage.

C 3 340, 371,

372

Added

Nov 3/03

551003 Horizontal Stabilizer Forward and Aft

Attach Points - Inspect. Refer to 5-14-

19, Supplemental Inspection Number

55-10-01.

AD 31 340, 341,

373, 374,

375, 376

Added

Nov 3/03

551004 Horizontal Stabilizer Spars - Inspect.

Refer to 5-14-20, Supplemental

Inspection Number 55-10-02 for the

Typical Inspection Compliance.

AD 31 340, 341,

373, 374,

375, 376

Added

Nov 3/03

551005 Horizontal Stabilizer Spars - Inspect.

Refer to 5-14-20, Supplemental

Inspection Number 55-10-02 for the

Severe Inspection Compliance.

AI 36 340, 341,

373, 374,

375, 376

5-10-01 Page 33

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Added

Nov 3/03

553001 Vertical Stabilizer Spars - Inspect.

Refer to 5-14-22, Supplemental

Inspection Number 55-30-01 for the

Typical Inspection Compliance.

AD 31 340, 341,

373, 374,

375, 376

Added

Nov 3/03

553002 Vertical Stabilizer Spars - Inspect.

Refer to 5-14-22, Supplemental

Inspection Number 55-30-01 for the

Severe Inspection Compliance.

AH 35 340, 341,

373, 374,

375, 376

Added

Mar 1/08

554001 Rudder Spar (Airplanes Incorporating

CAB06-9) - Inspect in accordance with

the latest revision of CAB06-9.

AK 38 343

Revised

Mar 1/01

561001 Windows and Windshield - Inspect for

condition and security of installation.

Check pilot's foul weather window for

proper latching and sealing.

C 4 240, 251,

252, 255,

256, 801,

802

Added

Nov 3/03

564002 Windshield and Attachment Structure

- Inspect. Refer to 5-14-23,

Supplemental Inspection Number

56-30-01.

AD 31 240, 251,

252, 255,

256, 801,

802

Revised

Mar 1/01

570001 Wings - Inspect for loose fasteners,

corrosion, cracks, wrinkles, dents and

attach points for condition and security

of installation.

B 1, 3 500's,

600's

Revised

Mar 1/01

570002 Wing Spar Fittings - Inspect bolts for

condition and security of installation.

B 1, 3 511, 611

Revised

Mar 1/01

570003 Wing Strut - Inspect for evidence of

damage, condition and security of

installation.

B 1, 3 531, 631

Revised

Mar 1/01

570004 Wing Strut Fittings - Inspect bolts for

condition and security of installation.

B 1, 3 531, 631

570005 Drain Openings and Vent Holes

in Bottom of Wing - Inspect for

obstructions.

B 1, 3 501, 503,

527, 571,

601, 603,

527, 571

570006 Wing Access Plates - Inspect for

security of installation and evidence of

damage.

A 1, 2, 3, 4 501, 503,

601, 603

Deleted

Sep 2/02

570007

Revised

Jan 2/06

570008 Wing Strut Attach Fittings (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Typical Inspection Time Limits.

Also, refer to 5-14-28, Supplemental

Inspection Number 57-60-01.

MA MA 531, 631

5-10-01 Page 34

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Jan 2/06

570009 Wing Strut Attach Fitting (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Severe Inspection Time Limits.

Also, refer to 5-14-28, Supplemental

Inspection Number 57-60-01.

ME ME 531, 631

Added

Nov 3/03

570010 Front Spar Lower Cap Inspection

Inboard of WS 141.20 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Typical Inspection Time Limits

or Severe Inspection Time Limits.

Also, refer to 5-14-25, Supplemental

Inspection Number 57-20-02.

MF MF 521, 621

Added

Nov 3/03

570011 Rear Spar Lower Cap Inspection

Inboard of WS 141.20 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Typical Inspection Time Limits

or Severe Inspection Time Limits.

Also, refer to 5-14-26, Supplemental

Inspection Number 57-20-03.

MF MF 525, 625

Revised

Mar 1/08

570012 Wing Strut Attachment to Front Spar

(NDI - Eddy Current) - Inspect. Refer

to Chapter 4, Typical Inspection

Time Limits. Also, refer to 5-14-29,

Supplemental Inspection Number

57-60-02.

MF MF 521, 621

Added

Nov 3/03

570013 Wing to Carry-Thru Front Spar

Attachment Fitting (NDI - Eddy Current)

- Inspect. Refer to Chapter 4, Typical

Inspection Time Limits or Severe

Inspection Time Limits. Also, refer

to 5-14-24, Supplemental Inspection

Number 57-20-01.

MF MF 511, 611

Added

Nov 3/03

570014 Wing to Carry-Thru Rear Spar

Attachment Fitting (NDI - Eddy Current)

- Inspect. Refer to Chapter 4, Typical

Inspection Time Limits or Severe

Inspection Time Limits. Also, refer

to 5-14-24, Supplemental Inspection

Number 57-20-01.

MF MF 511, 611

Added

Mar 1/08

570015 Wing Strut Attachment to Front

Spar (Nominal/Standard Bolt Size)

Part Number S3461-77 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Severe Inspection Time Limits.

Also, refer to 5-14-29, Supplemental

Inspection Number 57-60-02.

MF MF 521, 621

5-10-01 Page 35

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Added

Mar 1/08

570016 Wing Strut Attachment to Front Spar

(1/64 Inch Oversize Bolt Size) Part

Number S3461-163 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Severe Inspection Time Limits.

Also, refer to 5-14-29, Supplemental

Inspection Number 57-60-02.

MK MK 521, 621

Added

Mar 1/08

570017 Wing Strut Attachment to Front Spar

(1/32 Inch Oversize Bolt Size) Part

Number S3461-164 (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Severe Inspection Time Limits.

Also, refer to 5-14-29, Supplemental

Inspection Number 57-60-02.

ML ML 521, 621

Deleted

May 5/03

575001

Revised

Jan 2/06

575002 Center Flap Track and Inboard Flap

Track (NDI - Eddy Current) - Inspect.

Refer to Chapter 4, Typical Inspection

Time Limits or Severe Inspection

Time Limits. Also, refer to 5-14-27,

Supplemental Inspection Number

57-50-01.

MD MD 527, 627

Revised

Jan 2/06

575003 Outboard Flap Track (NDI - Eddy

Current) - Inspect. Refer to Chapter

4, Typical Inspection Time Limits

or Severe Inspection Time Limits.

Also, refer to 5-14-27, Supplemental

Inspection Number 57-50-01.

MD MD 527, 627

Revised

Jun 3/02

611001 Propeller Spinner (Hartzell and

McCauley) - Remove, wash, inspect

for cracks, fractures, condition and

security of installation.

A 1, 2, 3, 4 110

Revised

Mar 1/01

611002 Hartzell Spinner Bulkhead - Inspect

for cracks, condition and security of

installation.

A 1, 2, 3, 4 110

Revised

Mar 1/01

611003 Hartzell Propeller Blades - Wash,

check for nicks, gouges, scratches,

leading edge looseness, depressions,

delaminating, cracks, condition and

security of installation. Inspect clamps

for security of installation.

A 1, 2, 3, 4 110

611004 Hartzell Propeller Blades - Check

alignment and freedom of movement.

A 1, 2, 3, 4 110

611005 Hartzell Propeller Hub (Exposed Area)

- Inspect for cracks, wear, condition,

and security of components to hub.

A 1, 2, 3, 4 110

611006 Hartzell Propeller - Inspect for oil and

grease leaks.

A 1, 2, 3, 4 110

5-10-01 Page 36

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

611007 Hartzell Propeller Mounting - Visually

check for security of installation.

A 1, 2, 3, 4 110

Revised

Mar 1/01

611008 Hartzell Propeller Blade Clamps -

Lubricate and check for security of

installation. Refer to Chapter 12,

Lubricants - Description and Operation,

and Chapter 61, Propeller (Hartzell) -

Description and Operation.

A 1, 2, 3, 4 110

Revised

Mar 1/01

612001 Hartzell Beta System Feedback Ring

- Inspect ring for condition, warpage

and security of installation. Inspect

carbon brush for wear and evidence of

damage. Inspect linkage for condition

and security of installation. Refer

to Chapter 61, Propeller (Hartzell) -

Maintenance Practices.

B 1, 3 110

Revised

Mar 1/01

612002 Propeller Governor and Overspeed

Governor - Inspect for oil leaks,

condition and security of installation.

A 1, 2, 3, 4 121

Revised

Mar 1/01

612003 Overspeed Governor - Inspect

electrical connection wiring for

evidence of damage and security of

installation.

C 1 121

Revised

Mar 1/01

612004 Propeller Governor (Engine Running) -

Perform an operational check.

A 1, 2, 3, 4 ENG

Deleted

Jun 3/02

621001

Revised

Mar 1/01

621002 McCauley Spinner Bulkhead - Inspect

for cracks, condition and security of

installation.

A 1, 2, 3, 4 110

621003 McCauley Propeller Blades - Wash,

check for nicks, gouges, scratches

corrosion and cracks.

A 1, 2, 3, 4 110

621005 McCauley Propeller Hub (Exposed

Area) - Inspect for cracks, wear,

condition, and security of components

to hub.

A 1, 2, 3, 4 110

621006 McCauley Propeller - Inspect for oil

leaks.

A 1, 2, 3, 4 110

621007 McCauley Propeller Mounting - Visually

check for security of installation.

A 1, 2, 3, 4 110

5-10-01 Page 37

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

622001 McCauley Beta System Feedback Ring

- Inspect ring for condition, warpage

and security of installation. Inspect

carbon brush for wear and evidence of

damage. Inspect linkage for condition

and security of installation. Refer to

Chapter 61, Propeller (McCauley) -

Maintenance Practices.

B 1, 3 110

Revised

Mar 1/01

622002 Propeller Governor and Overspeed

Governor - Inspect for oil leaks,

condition and security of installation.

A 1, 2, 3, 4 121

Revised

Mar 1/01

622003 Overspeed Governor - Inspect

electrical connection wiring for

evidence of damage and security of

installation.

C 1 121

Revised

Mar 1/01

622004 Propeller Governor (Engine Running) -

Perform operational check.

A 1, 2, 3, 4 ENG

Revised

Mar 1/01

711001 Cowling - Inspect the structure, rub

strips and fasteners for condition and

security of installation.

C 1 121, 122

712001 Engine Tubular Mounts - Inspect for

condition, corrosion, and security of

installation.

C 1 121, 122

Revised

Mar 1/01

712002 Engine Shock Mounts and Ground

Straps - Inspect for condition, security

of installation, and deterioration of

elastomers.

C 1 121, 122

Added

Nov 3/03

712003 Engine Truss and Ring Assembly

- Inspect. Refer to 5-14-30,

Supplemental Inspection Number

71-20-01.

AD 31 121, 122

713001 Firewall Structure - Inspect for

condition and evidence of damage.

C 1 151, 152

716001 Induction System and Inertial

Separator - Inspect for general

condition, security, and freedom of

operation. Inspect door pivot point

bearings for excessive wear. Check

separator linkage for proper operation.

Check for loose rivets.

A 1, 2, 3, 4 121

716002 Inertial Separator - Unlock control and

pull into bypass. Check for freedom of

movement and for full opening of the

bypass door in the air duct.

A 1, 2, 3, 4 121

716003 Induction Air Plenum - Remove access

door. Inspect for cracks, security of

installation and condition.

B 1, 3 121

5-10-01 Page 38

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

716004 Compressor Wash Ring - Inspect for

security of installation and condition.

C 1 121, 122

Revised

Mar 1/01

716005 Inertial Separator - Perform rivet

inspection. Refer to Chapter

71, Inertial Separator Forward

and Aft Vane Rivet Inspection -

Inspection/Check.

A 1, 2, 3, 4 121

717001 Engine Combustion Section Fuel

Drains - Inspect for security of

installation, line routing, deterioration

of hoses and evidence of damage.

C 1 130

717002 Drain Openings and Vent Holes in

Bottom of Engine Cowling - Inspect for

obstructions.

A 1, 2, 3, 4 130

Revised

Mar 1/01

720001 Engine Compartment - Inspect

for general condition, security of

installation, leakage, and damage.

B 1, 3 121, 122

Revised

Mar 1/01

720002 Engine Air Inlet Screen - Inspect for

cleanliness and security of installation.

B 1, 3 121, 122

720003 Engine Gas Generator Case - Inspect

for cracks, distortion, and corrosion.

B 1, 3 121, 122

Revised

Mar 1/01

720004 Engine Fire Seals - Inspect for security

of installation and general condition.

B 1, 3 151, 152

Revised

Mar 1/01

720005 Engine Propeller Shaft Seal - Inspect

for leaks and security of installation.

A 1, 2, 3, 4 110

Revised

Mar 1/01

720006 Accessory Gearbox Breather Line -

Inspect for security of installation and

condition.

B 1, 3 122

Revised

Mar 1/01

720007 Engine Accessories - Inspect for

security of installation, general

condition and leakage.

B 1, 3 121, 122

Revised

Mar 1/01

723001 P3 Filter - Inspect P3 filter for general

condition and clean.

A 1, 2, 3, 4 122

Revised

Mar 1/01

723002 P3 Filter - Replace P3 filter. R 19 122

731001 Fuel Lines - Inspect fuel supply and

fuel motive flow lines for deterioration,

chafing, fuel leaks, and security of

installation.

A 1, 2, 3, 4 121, 122

731002 Pneumatic Lines - Inspect P3/Py

lines for condition and security of

installation. Inspect connections for

proper safetying.

C 1 122

731003 Pneumatic Lines - Inspect P3/Py line

heaters for operation and evidence of

damage.

C 1 122

5-10-01 Page 39

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

731004 Engine Fuel Pump - Inspect for security

of installation and fuel leaks. Inspect

overboard drain line for security of

installation and condition.

A 1, 2, 3, 4 122

Revised

Mar 1/01

731005 Engine Fuel Pump - Perform fuel pump

inspection. Refer to Chapter 73, Fuel

Pump - Inspection/Check.

C 1 122

731006 Fuel Manifold - Inspect for security of

installation and evidence of fuel leaks.

A 1, 2, 3, 4 121, 122

Revised

Mar 1/01

731008 Fuel Pump Inlet Filter - Inspect and

clean fuel pump inlet filter.

P 17 122

Revised

Mar 1/01

731009 Fuel Pump Outlet Filter - Replace fuel

pump outlet filter.

P 17 122

731010 Flow Divider - Inspect for security of

installation and evidence of fuel leaks.

A 1, 2, 3, 4 121, 122

Revised

Mar 1/01

731011 Fuel Discharge Nozzles - Perform flow

check and clean.

C 2 122

732001 Fuel Control - Inspect for security of

installation and fuel leaks.

A 1, 2, 3, 4 122

732002 Fuel Control - Check for FCU bearing

washout indicated by blue dye (grease

and fuel mixed) at FCU overboard vent.

A 1, 2, 3, 4 122

733001 Fuel Flow Transducer - Inspect for

security of installation, fuel leaks, and

evidence of damage.

A 1, 2, 3, 4 122

733002 Fuel Totalizer Signal Conditioner

(if installed) - Inspect for security

of installation wiring connector for

security, and evidence of damage.

A 1, 2, 3, 4 122

741001 Ignition Exciter Box - Inspect for

security of installation and condition.

C 1 122

Revised

Mar 1/01

741002 Ignition Cables - Inspect for chafing,

wear, routing, and security of

installation.

C 1 121, 122

741003 Igniters - Inspect for wear, corrosion,

and condition of insulator. Clean

insulator at lead attachment, but do not

clean igniter end.

A 1, 2, 3, 4 121, 122

Revised

Mar 1/01

741004 Ignition Exciter Box Wiring Harness

- Inspect for security of installation,

condition and proper routing.

C 1 122

741005 Igniters - Perform operational check

by placing ignition switch in the ON

position (battery switch on). Verify

IGNITION ON annunciator illuminates.

A 1, 2, 3, 4 121, 122

5-10-01 Page 40

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

761001 Engine Controls - Check for freedom

of operation. Inspect for security of

installation, wear, corrosion, routing,

evidence of damage, and deterioration.

Check rubber seals for deterioration.

A 1, 2, 3, 4 122

761002 Control Linkages and Attach Brackets

- Inspect for security of installation,

wear, corrosion, general condition, and

freedom of movement.

A 1, 2, 3, 4 122

Revised

Mar 1/01

761003 Power Lever Reverse Speed Pickup

(Engine Running) - Check power lever

reverse speed pickup.

A 1, 2, 3, 4 ENG

761004 Inertial Separator Control - Inspect

handle and shaft for condition and

evidence of damage.

C 4 222

Revised

Mar 1/01

761005 Engine Control Rod Ends - Disconnect

and inspect engine control rods for

corrosion, roughness in rotation and

radial play. Lubricate rod ends. Refer

to Chapter 12, Lubricants - Description

and Operation.

O 16 122

Revised

Mar 1/01

761006 Engine Idle Check (Engine Running) -

Perform engine idle check.

A 1, 2, 3, 4 ENG

762001 Emergency Power Lever Annunciator

Light - Perform operational test.

A 1, 2, 3, 4 BAT

771001 Np Tach Generator - Inspect for

security of installation and general

condition. Inspect weep holes for oil

leakage.

C 1 121, 122

Revised

Mar 1/01

771002 Np Tach Generator Wiring - Inspect

for chafing, routing and security of

installation.

C 1 121, 122

771003 Ng Tach Generator - Inspect for

security of installation and general

condition. Inspect weep holes for oil

leakage.

C 1 121, 122

Revised

Mar 1/01

771004 Ng Tach Generator Wiring - Inspect

for chafing, routing and security of

installation.

C 1 121, 122

771005 T5 Terminal Block and External Wiring

- Inspect for security of installation and

condition.

C 1 122

771006 Trim Thermocouple - Inspect for

security of installation and condition.

C 1 122

773001 Electric Torque Transmitter (if installed)

- Inspect for security of installation,

condition, and leakage.

C 1 122

5-10-01 Page 41

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

773002 Torque Indication System - Inspect

plumbing for evidence of damage,

leakage, condition and security of

installation.

C 1 121, 122

773003 Electric Torque Transmitter Wiring

- Inspect for security of installation,

routing and condition.

C 1 121, 122

781001 Engine Exhaust System - Inspect

primary and secondary ducts

for cracks, distortion, security of

installation, and evidence of damage.

A 1, 2, 3, 4 130

Revised

Mar 1/01

781002 Engine Exhaust System - Perform

primary and secondary exhaust duct

inspection and alignment. Refer to

Chapter 78, Primary and Secondary

Exhaust Duct - Maintenance Practices.

B 1, 3 130

Revised

Mar 1/01

790001 Engine Oil (Airplanes Flown Less Than

50 Hours Per Month) - Change oil.

Refer to Chapter 12, Engine Oil System

- Servicing.

C 1 121, 122

Revised

Mar 1/01

790002 Engine Oil (Airplanes Flown More

Than 50 Hours Per Month) - Change

oil. Refer to Chapter 12, Engine Oil

System - Servicing.

N 15 121, 122

Revised

Mar 1/01

790003 Oil Filler Cap and Dipstick - Inspect for

condition and security of installation.

A 1, 2, 3, 4 122

790004 Oil Filter - Remove, clean and

inspect for damage. Filter may be

electrosonically cleaned if desired.

A 1, 2, 3, 4 121

Revised

Mar 1/01

790005 Oil Filter - Replace oil filter. R 19 121

Revised

Mar 1/01

792001 Oil Cooler - Inspect for security of

installation, evidence of damage and

condition. Inspect baffling and seals for

condition and security of installation.

C 1 122

793001 Chip Detectors with Annunciator Light -

Inspect.

B 1, 3 121, 122,

221

793002 Chip Detectors without Annunciator

Light - Inspect.

A 1, 2, 3, 4 121, 122

Revised

Mar 1/01

793003 Oil Pressure Switch and Fitting (Aft

Side of Firewall) - Inspect for security

of installation, condition and leakage.

B 2, 4 201

Revised

Mar 1/01

793004 Oil Pressure Indicator Plumbing

(Engine to Firewall) - Inspect for

security of installation, condition,

leakage and evidence of damage.

A 1, 2, 3, 4 151

5-10-01 Page 42

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

REVISION

STATUS

ITEM CODE

NUMBER

TASK INTERVAL OPERATION ZONE

Revised

Mar 1/01

793005 Oil Temperature Bulb - Inspect for

security of installation, condition and

leakage.

C 1 122

Revised

Mar 1/01

793006 Oil Temperature Bulb Wiring - Inspect

for security of installation, condition and

evidence of damage.

C 1 122

793007 Engine Oil Temperature and Pressure

Indicator - Inspect for security of

installation.

C 4 221

801001 Starter-Generator - Inspect security of

installation, terminal block, boot, and

electrical connections for cleanliness,

evidence of heat or arcing, and

evidence of damage.

B 1, 3 121

801002 Starter-Generator Brush Holders -

Inspect for proper spring tension

(30-39 ounces) and freedom. Refer

to Lear Siegler/Lucas Aerospace

Overhaul Manual for proper procedure.

NOTE: Does Not apply to Lucas

Aerospace Starter Generator Part

Number 23081-023A or APC Starter

Generator.

D 5 121

801003 Starter-Generator Brushes - Inspect for

cracks, wear, cleanliness, and brush

length. NOTE: Does Not apply to

Lucas Aerospace Starter Generator

Part Number 23081-023A or APC

Starter Generator.

D 5 121

801004 Starter-Generator Electrical Cables

and Connectors - Inspect cables

for routing, support, security of

connections and connector hardware.

B 1, 3 122

Added

Mar 1/08

801005 Starter-Generator Splines - Clean the

splines. Use a 10X magnifying glass

and examine for indications of electrical

arcing damage. Refer to the Pratt

and Whitney Canada publications for

additional checks. (Cessna SNL07-16)

AL 39 121

5-10-01 Page 43

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

COMPONENT TIME LIMITS

1. Component Time Limit

A. 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. Also, those

items that are underlined are recorded in Chapter 4, Airworthiness Limitations.

B. 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.

2. Schedule

A. Equipment and Furnishings (Chapter 25)

(1) Emergency Locator Transmitter (ELT) Battery Pack - Replace at replacement date.

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.

B. Flight Controls (Chapter 27)

(1) Flap Bell Crank (Part Number 2622083-18) - Replace at every 2250 landings.

(2) Flap Bell Crank (Part Number DDA00028-4) - Replace at every 2250 landings.

(3) Flap Bell Crank (Part Numbers 2622281-2, -12) - Replace at every 7000 landings.

(4) Flap Bell Crank (Part Number 2692001-2) - Replace at every 7000 landings.

NOTE: Total landings includes the accumulated landings of 2622281-2 prior to modification

by SK208-123 to the 2692001-2 configuration.

(5) Flap Bell Crank (Part Numbers 2622311-7, -16) - Replace at every 40,000 landings.

(6) Flap Bell Crank (Part Number 2622311-7) attaching parts: Bearings (Part Number MS27641-5

or S3952-5) and Bolt (Part Number AN5-77) - Replace at every 10,000 landings.

(7) Flap Bell Crank (Part Number 2622311-16) attaching parts: Bearings (Part Number KP5A-H)

and Bolt (Part Number AN5-77) - Replace at every 10,000 landings.

(8) Elevator Forward Pushrod Part Numbers 2613440-1, 2613414-1, and 2660034-1 - Replace at

9500 landings.

(9) Elevator Forward Pushrod Part Numbers 2613440-3, 2613440-5, DDA05946-1 - Replace at

40,000 landings.

(10) Elevator Aft Pushrod Part Numbers 2634009-1, 2634027-1, and 2634027-3 - Replace at 40,000

landings.

C. Ice and Rain Protection (Chapter 30)

(1) TKS Metering Pumps Part Number 9514A-1- Replace every 5000 flight hours.

D. Landing Gear (Chapter 32)

(1) 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.

(a) Main Landing Gear Center Spring (Part Numbers 2641014-2, -3, -4, -5, -6 -7, -8, -9) -

Replace at every 31,500 landings.

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MODEL 208

MAINTENANCE MANUAL

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

Replace at every 31,500 landings.

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

every 31,500 landings.

(d) Main Landing Gear Attach Pin (Part Numbers 2641008-1, -2, -200) - Replace at every

31,500 landings.

(e) Main Landing Gear Axles (Part Numbers 2641011-1, -3, -4) - Replace at every 10,000

landings.

(f) Main Landing Gear Axles (Part Numbers 2641011-5) - Replace at every 31,500 landings.

(g) Main Landing Gear Axle Fittings (Part Numbers 2641010-1, -3, -7) - Replace at every

31,500 landings.

(2) Nose Landing Gear

NOTE: Attaching hardware (bolts, bearings, bushings, and axle components related to the

installation of the components below) is to be replaced whenever the associated

component is replaced.

(a) Nose Gear Drag Link Spring (Part Numbers 2643062-1, -2, -3) - Replace at every 15,000

landings.

NOTE: For nose gear drag link springs repaired per CAB96-24 or per 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 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.

(b) Nose Gear Assembly (Part Numbers 2643045, 2643100 and 2643095 Series Part

Numbers) - Replace at every 40,000 landings.

NOTE: For an illustration of the nose gear assembly to be replaced, refer to Chapter

32, section 32-20-00, Nose Landing Gear - Maintenance Practices.

(c) Support Assembly, Nose Gear Spring (Part Numbers 2643030, 2643055 and 2643099

Series Part Numbers) - Replace at every 40,000 landings.

NOTE: For an illustration of the nose gear spring support assembly to be replaced, refer

to Chapter 32, section 32-20-00, Nose Landing Gear - Maintenance Practices.

(d) Fork Assembly, Nose Gear Spring (Part Numbers 2643031-1, -7) - Replace at every 40,000

landings.

NOTE: For an illustration of the nose gear spring fork assembly to be replaced, refer to

Chapter 32, section 32-20-00, Nose Landing Gear - Maintenance Practices.

E. Navigation (Chapter 34)

(1) Pitot and static hoses - Replace after 10 years in service.

F. Oxygen (Chapter 35)

(1) The airplane may be equipped with a two-port oxygen system incorporating a 50.67 cubic-footcapacity oxygen cylinder (Part Numbers C166001-1101 and C166001-1201) or a ten port oxygen

system incorporating a 116.95 cubic-foot-capacity oxygen cylinder (Part Numbers C166001-

1102 and C166001-1103). Both cylinders have a life limit of 15 years.

(2) Scott 359 Series Oxygen Mask All Components Including Regulator - Overhaul/Replacement 5

years.

5-11-00 Page 2

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

G. Vacuum (Chapter 37)

(1) Vacuum hoses - Replace after 10 years in service.

H. Propeller - Hartzell (Chapter 61)

(1) Governor (Woodward) - Overhaul, Refer to Pratt & Whitney Service Bulletin number 1703.

(2) Overspeed Governor (Woodward) - Overhaul, at engine overhaul plus 500 hours.

I. Propeller McCauley (Chapter 61A)

(1) Governor (Woodward) - Overhaul, Refer to Pratt & Whitney Service Bulletin number 1703.

(2) Overspeed Governor (Woodward) - Overhaul, Refer to Service Bulletin 33580.

J. Power plant (Chapter 71)

(1) Refer to Pratt & Whitney Maintenance Manual listed in the List of Publications in the front of this

publication and Pratt & Whitney Service Bulletin No. PT6A-72-1703, Rev. No. 1 or later.

NOTE: Engine components, such as standby alternator, etc., should be inspected for

condition at time of engine overhaul, as it may be cost effective to overhaul or

replace marginal components at that time. A determination is to be made during

engine overhaul such that if components have less hours in service than the engine,

or have not accumulated sufficient hours for economic reasons, these components

may not require overhaul or replacement concurrent with engine overhaul. It is

recommended that the overhaul or replacement interval for these components not

exceed the engine overhaul interval.

NOTE: Inspect the engine compartment for structural damage when engine is removed for

overhaul, and make the necessary repairs.

NOTE: Inspect the engine exhaust as it may be cost effective to replace marginal components

at engine overhaul.

NOTE: Inspect electrical harnesses for damage which would be cost effective to replace at

engine overhaul.

(2) Fuel Hose: From firewall fuel filter to engine fuel heater. From fuel control unit motive flow return

to firewall fitting - Replace rubber hoses, base number S2495 (Purchased through Cessna),

every 5 years or 3600 hours, whichever occurs first. Replace Teflon hoses, base number S2808

(Purchased through Cessna), every 10 years or at engine TBO, whichever occurs first.

(3) Oil Hose: Oil cooler supply from engine external scavenge pump to oil cooler inlet. From oil

cooler return outlet to engine oil tank. Torque indicating pressure hose. Engine oil pressure

indicating hose from engine to firewall. Torque indicating vent hose - Replace Teflon engine

compartment flexible fluid-carrying hoses, base number S2808/AE3663 (Purchased through

Cessna), every 10 years or at engine TBO, whichever occurs first.

K. Starter-Generator (Chapter 80)

(1) Starter-Generator (Lear Siegler/Lucas Aerospace)

(a) Except part number 23081-023A, - Overhaul every 1000 hours.

(b) Part number 23081-023A - Overhaul/replace every 1200 hours.

(2) Starter-Generator (Aircraft Parts Corp. - APC "XL")

(a) Overhaul with genuine APC parts (SNL02-1) - Overhaul every 1600 hours.

(b) Original equipment starter-generators APC 200SGL119Q-2 - Overhaul every 2000 hours.

(c) Starter-generators 200SGL119Q-2RX units overhauled by Cessna/APC - Overhaul every

2000 hours.

(3) Starter/Generator (Aircraft Parts Corp. - APC part number 300SGL145Q) - Overhaul/ replace

every 1000 hours.

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COMPONENT TIME LIMITS - RUSSIAN CERTIFIED AIRPLANES

1. Component Time Limit

A. All components not listed herein should be inspected as detailed elsewhere in this chapter and

repaired, overhauled or replaced as required. Items shown here should be overhauled or replaced

during regular maintenance periods falling due nearest to the specified limit.

B. Replacement life of each component listed 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 remain 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 to

allow continued accumulation toward the life limit.

2. Schedule

A. Flight Controls (Chapter 27)

(1) Flap bellcrank Part Number 2622083-18 -- Replace at 1500 landings.

(2) Flap bellcrank Part Number DDA00028-4 -- Replace at 1500 landings.

(3) Flap bellcrank Part Number 2622281-2 -- Replace at 5000 landings.

(4) Flap bellcrank Part Number 2622281-12 -- Replace at 5000 landings.

(5) Flap bellcrank Part Number 2692001-2 -- Replace at 5000 landings.

NOTE: Total landings include the accumulated landings of 2622281-2 prior to modification

by SK208-123 to the 2692001-2 configuration.

B. Landing Gear (Chapter 32)

(1) Main landing gear axle Part Numbers 2641011-1, -3 and -4 -- Replace at 10,000 landings

(2) Main landing gear assembly Part Numbers 2641000 and 2641027 (all assembly dash numbers)

-- Replace at 20,000 landings.

(3) Nose landing gear drag link spring Part Numbers 2643062-1 and -2 -- Replace at 15,000

landings.

(4) Nose landing gear assembly Part Numbers 2643000-1, -2, -3, -4 and -5 -- Replace at 20,000

landings.

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PROGRESSIVE CARE PROGRAM

1. Progressive Care Program

A. Purpose and Use.

(1) The Cessna Inspection Charts and Progressive Care Program will help the owner or operator to

do the intent of 14 CFR Part 91.409(a), (b) and (d). Use the Inspection Charts as a guide, and not

as a complete inspection program. The good judgement of a certified airframe and powerplant

mechanic is necessary. As the person who has control of the airworthiness of the airplane, the

owner or operator must use only qualified personnel to do maintenance on the airplane.

2. Construction

A. The information that follows is the recommended progressive inspection for Model 208, 208

Cargomaster, 208B, 208B Super Cargomaster and 208B passenger airplanes.

B. The program is divided into four main operations (operations 1 thru 4) which includes all 100 hour, 200

hour and 400 hour inspection requirements. The remaining operations include all of the inspection

requirements due at other intervals.

C. The inspection program is divided into operations to do the progressive inspection.

Operation 1 - Covers items in the engine, wing, empennage and fuselage areas.

Operation 2 - Covers items in the engine, wing and landing gear areas.

Operation 3 - Covers items in the engine, wing, empennage and fuselage areas.

Operation 4 - Covers items in the engine, wing, empennage and fuselage areas.

Operation 5 - Every 500 hours or 1 year, whichever occurs first.

Operation 6 - Every 800 hours or 1 year, whichever occurs first.

Operation 7 - Every 1000 hours or 1 year, whichever occurs first.

Operation 8 - Every 2000 hours or 2 years, whichever occurs first.

Operation 9 - Every 1 year.

Operation 10 - Every 2 years.

Operation 11 - Every 3 years.

Operation 12 - Every 4 years.

Operation 13 - Every 6 years.

Operation 14 - Every 12 years.

Operation 15 - Every 1200 hours or 1 year, whichever occurs first.

Operation 16 - Every 100 hours and every external engine wash or engine compartment wash.

Operation 17 - Every 500 hours.

Operation 18 - Every 1600 hours or 5 years.

Operation 19 - Every 1000 hours.

Operation 20 - (Not Used)

Operation 21 - (Not Used)

Operation 22 - (Not Used)

Operation 23 - Every 400 hours or 6 calendar months, whichever occurs first.

Operation 24 - (Not Used)

Operation 25 - (Not Used)

Operation 26 - (Not Used)

Operation 27 - (Not Used)

Operation 28 - (Not Used)

Operation 29 - Every 2 years if the airplane is operated in a mild corrosion environment.

Operation 30 - Every one year if the airplane is operated in a moderate or severe corrosion

environment.

Operation 31 - At the first 20,000 hours and every 5000 hours thereafter.

Operation 32 - At the first 5000 hours and every 2500 hours thereafter.

Operation 33 - At the first 7500 hours and every 2500 hours thereafter.

Operation 34 - At the first 12,500 hours and every 2500 hours thereafter.

Operation 35 - At the first 16,500 hours and every 5000 hours thereafter.

Operation 36 - At the first 17,500 hours and every 1000 hours thereafter.

Operation 37 - At the first 25,000 landings and every 5000 landings thereafter.

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Operation 38 - Every 1200 hours.

Operation 39 - At each starter generator removal.

Operation 40 - Every 1000 hours or 3 years, whichever occurs first.

Operation MA - At 10,000 hours and every 5000 hours thereafter.

Operation MB - At 5000 landings and every 1000 landings thereafter, up to 10,000 landings.

Replace at 10,000 landings.

Operation MC - At 4000 landings and every 500 landings thereafter.

Operation MD - At 15,000 landings and every 3000 landings thereafter.

Operation ME - At 5000 hours and every 3600 hours thereafter.

Operation MF - At 20,000 hours and every 5000 hours thereafter.

Operation MG - At 5000 hours and every 1200 hours thereafter.

Operation MH - At 10,000 hours and every 2500 hours thereafter.

Operation MI - At 5000 hours and every 500 hours thereafter.

Operation MJ - At 5000 hours and every 400 hours thereafter.

Operation MK - At 20,000 hours and every 4400 hours thereafter.

Operation ML - At 20,000 hours and every 3600 hours thereafter.

3. Procedure

A. The Inspection Time Limits Charts show the recommended intervals at which items are to be inspected

based on normal usage in average environmental conditions. Airplanes operated in very humid areas

(tropics), or in very cold, damp climates, etc., may need more frequent inspections for wear, corrosion,

and lubrication. With these different conditions, do periodic inspections with this chart at more frequent

intervals until the operator can set their own inspection periods because of field experience. The

operator’s inspection intervals must not be different from the inspection time limits shown in this

manual except as given below:

(1) Each inspection interval can use 10 hours more (if time controlled), or 30 days (if date controlled)

more than the interval. You can also do the inspection any time before the regular interval.

(a) In the event that any operation scheduled is done late, the next operation in sequence

keeps a due point from the time the late operation was originally scheduled.

(b) In the event that any operation scheduled is done 10 hours or less ahead of schedule, the

next phase due point can stay where it was originally set.

(c) In the event that any operation scheduled is done more than 10 hours ahead of

schedule, the next operation due point must have a new due point from the time of early

accomplishment.

B. A COMPLETE AIRPLANE INSPECTION includes all 100, 200, and 400 HOUR items plus those

Inspection Items that are in other operations which are due at the specified time.

C. Check the Component Time Limits at each inspection interval to make sure the correct overhaul and

replacement requirements are done at the specified times.

4. Inspection Guidelines.

A. The Inspection Charts are to be used as a recommended inspection outline. Detailed information of

systems and components in the airplane will be found in various chapters of this Maintenance Manual

and the applicable vendor publications. It is recommended that you refer to the applicable portion of

this 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.

B. 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.

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(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.

C. Airplane file.

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

documents listed in this section are up-to-date and obey the current 14 CFR. If other documents

and data are needed for other nations, owners of exported airplanes should talk with their aviation

officials to get their individual requirements.

(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).

3 Aircraft Radio Station License (Federal Communication Commission Form 556 if

transmitter is installed).

4 Radio Telephone Station License (Federal Communication Commission Form 409 if

Flitefone Radio Telephone is installed).

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

1 Weight and Balance Data Sheets and associated papers (all copies of the Repair and

Alteration Form, FAA Form 337, are applicable).

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.

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MAINTENANCE MANUAL

INSPECTION OPERATION 1

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 1 consists of all 100 hour interval inspection items and those 200 or 400 hour interval

inspection items contained in the engine, wing, empennage and fuselage areas. 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. A

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

306001 Propeller Anti-ice Slip Rings, Boots, and Wiring

(without TKS) - Examine for condition and correct

installation. Examine brushes for proper tracking.

110

306002 Propeller Anti-ice Brushes (without TKS) - Examine

each brush for wear, signs of damage, cleanliness,

correct installation and correct rigging. Examine

electrical wires for condition and correct installation.

110

611001 Propeller Spinner (Hartzell and McCauley) -

Remove, wash, inspect for cracks, fractures,

condition and security of installation.

110

611002 Hartzell Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

611003 Hartzell Propeller Blades - Wash, check for nicks,

gouges, scratches, leading edge looseness,

depressions, delaminating, cracks, condition and

security of installation. Inspect clamps for security

of installation.

110

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ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

611004 Hartzell Propeller Blades - Check alignment and

freedom of movement.

110

611005 Hartzell Propeller Hub (Exposed Area) - Inspect for

cracks, wear, condition, and security of components

to hub.

110

611006 Hartzell Propeller - Inspect for oil and grease leaks. 110

611007 Hartzell Propeller Mounting - Visually check for

security of installation.

110

611008 Hartzell Propeller Blade Clamps - Lubricate and

check for security of installation. Refer to Chapter

12, Lubricants - Description and Operation, and

Chapter 61, Propeller (Hartzell) - Description and

Operation.

110

612001 Hartzell Beta System Feedback Ring - Inspect ring

for condition, warpage and security of installation.

Inspect carbon brush for wear and evidence of

damage. Inspect linkage for condition and security

of installation. Refer to Chapter 61, Propeller

(Hartzell) - Maintenance Practices.

110

621002 McCauley Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

621003 McCauley Propeller Blades - Wash, check for nicks,

gouges, scratches corrosion and cracks.

110

621005 McCauley Propeller Hub (Exposed Area) - Inspect

for cracks, wear, condition, and security of

components to hub.

110

621006 McCauley Propeller - Inspect for oil leaks. 110

621007 McCauley Propeller Mounting - Visually check for

security of installation.

110

622001 McCauley Beta System Feedback Ring - Inspect ring

for condition, warpage and security of installation.

Inspect carbon brush for wear and evidence of

damage. Inspect linkage for condition and security

of installation. Refer to Chapter 61, Propeller

(McCauley) - Maintenance Practices.

110

720005 Engine Propeller Shaft Seal - Inspect for leaks and

security of installation.

110

301101 100 Hour Operational Check (with TKS) - Visually

check for wear and security of installation at the

propeller boots, propeller nozzle, propeller feed

tubes, and propeller slinger. Check operation of

pumps, pump CAS annunciator (G1000), press test

TKS annunciator (non-G1000), fluid flow of slinger

and leading edge panels.

110, 220,

221, 240,

340, 373,

374, 527,

531, 571,

627, 631,

671, 903,

904

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ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

242001 Standby Alternator - Inspect for condition and

security of installation, belt tension and condition.

Check terminal boots for condition and electrical

leads for damage and security of installation.

121

242002 Standby Alternator Drive - Inspect for security of

installation, leakage, and condition.

121

242004 Standby Alternator Power Distribution Box - Inspect

relay and associated electrical components for

condition and security of installation.

121

243002 Electrical System Power Distribution Box,

Contactors, Ground Power Monitor, Circuit

Breakers, Limiters and Cables - Inspect cables for

routing, support and security of connections. Check

condition and security of all components.

121

244001 External Power Receptacle and Cables - Inspect for

condition and security of installation.

121

612002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

612003 Overspeed Governor - Inspect electrical connection

wiring for evidence of damage and security of

installation.

121

622002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

622003 Overspeed Governor - Inspect electrical connection

wiring for evidence of damage and security of

installation.

121

716001 Induction System and Inertial Separator - Inspect

for general condition, security, and freedom of

operation. Inspect door pivot point bearings for

excessive wear. Check separator linkage for proper

operation. Check for loose rivets.

121

716002 Inertial Separator - Unlock control and pull into

bypass. Check for freedom of movement and for full

opening of the bypass door in the air duct.

121

716003 Induction Air Plenum - Remove access door. Inspect

for cracks, security of installation and condition.

121

716005 Inertial Separator - Perform rivet inspection. Refer to

Chapter 71, Inertial Separator Forward and Aft Vane

Rivet Inspection - Inspection/Check.

121

790004 Oil Filter - Remove, clean and inspect for damage.

Filter may be electrosonically cleaned if desired.

121

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ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

801001 Starter-Generator - Inspect security of installation,

terminal block, boot, and electrical connections

for cleanliness, evidence of heat or arcing, and

evidence of damage.

121

243012 Engine Electrical Cables and Connectors - Inspect

cables for routing, support, security of connections

and connector hardware.

121, 122

261002 Heat Detection Loop - Inspect the three loop

sections for condition, security of installation and

evidence of damage, paying special attention to the

loop connection fittings.

121, 122

711001 Cowling - Inspect the structure, rub strips and

fasteners for condition and security of installation.

121, 122

712001 Engine Tubular Mounts - Inspect for condition,

corrosion, and security of installation.

121, 122

712002 Engine Shock Mounts and Ground Straps -

Inspect for condition, security of installation, and

deterioration of elastomers.

121, 122

716004 Compressor Wash Ring - Inspect for security of

installation and condition.

121, 122

720001 Engine Compartment - Inspect for general condition,

security of installation, leakage, and damage.

121, 122

720002 Engine Air Inlet Screen - Inspect for cleanliness and

security of installation.

121, 122

720003 Engine Gas Generator Case - Inspect for cracks,

distortion, and corrosion.

121, 122

720007 Engine Accessories - Inspect for security of

installation, general condition and leakage.

121, 122

731001 Fuel Lines - Inspect fuel supply and fuel motive

flow lines for deterioration, chafing, fuel leaks, and

security of installation.

121, 122

731006 Fuel Manifold - Inspect for security of installation and

evidence of fuel leaks.

121, 122

731010 Flow Divider - Inspect for security of installation and

evidence of fuel leaks.

121, 122

741002 Ignition Cables - Inspect for chafing, wear, routing,

and security of installation.

121, 122

741003 Igniters - Inspect for wear, corrosion, and condition

of insulator. Clean insulator at lead attachment, but

do not clean igniter end.

121, 122

741005 Igniters - Perform operational check by placing

ignition switch in the ON position (battery switch on).

Verify IGNITION ON annunciator illuminates.

121, 122

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ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

771001 Np Tach Generator - Inspect for security of

installation and general condition. Inspect weep

holes for oil leakage.

121, 122

771002 Np Tach Generator Wiring - Inspect for chafing,

routing and security of installation.

121, 122

771003 Ng Tach Generator - Inspect for security of

installation and general condition. Inspect weep

holes for oil leakage.

121, 122

771004 Ng Tach Generator Wiring - Inspect for chafing,

routing and security of installation.

121, 122

773002 Torque Indication System - Inspect plumbing for

evidence of damage, leakage, condition and security

of installation.

121, 122

773003 Electric Torque Transmitter Wiring - Inspect for

security of installation, routing and condition.

121, 122

790001 Engine Oil (Airplanes Flown Less Than 50 Hours Per

Month) - Change oil. Refer to Chapter 12, Engine Oil

System - Servicing.

121, 122

793002 Chip Detectors without Annunciator Light - Inspect. 121, 122

793001 Chip Detectors with Annunciator Light - Inspect. 121, 122,

221

213001 Pressure Regulating Valve and Plumbing - Inspect

valve and plumbing for security of installation,

condition and evidence of damage.

122

214001 Heater Components - Check lines, connectors,

clamps, seals, gaskets, and distribution ducts for

condition, restrictions, and security of installation.

122

214002 Heater System Plumbing - Inspect P3 line, flow

control valve and heat regulating line for security of

installation, condition and evidence of damage.

122

243001 Battery Cable Disconnect and Cables - Inspect

for condition, corrosion and security of installation.

Inspect battery terminal receptacles for overheating

or burning.

122

243007 Battery Tray - Inspect for condition, corrosion and

security of installation. Inspect latching mechanism

for proper operation.

122

243008 NI-CAD Battery Temperature Probe Connector

- Inspect connector and associated wiring for

condition and security of installation. Disconnect

plug from battery and check annunciators. Verify

BATTERY HOT and BATTERY OVERHEAT

annunciator lights illuminate with power ON.

122

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ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

243009 Gill Flooded Lead Acid Battery (if installed) - Check

general condition and security of installation. Check

level of electrolyte. Check terminals for overheating

or burning.

122

243010 Gill Lead Acid Only Battery Box - Inspect for

corrosion, condition and security of installation.

122

243011 Battery Vent Tubes - Inspect for condition,

obstructions and security of installation.

122

243014 Concord Sealed Lead Acid Battery (if installed) -

Check general condition and security of installation.

Check terminals for overheating or burning. Perform

checks in accordance with servicing placard on the

side of battery.

122

301006 Bleed Air Pressure Regulator (Airplanes 20800222

and On and 208B0317 and On, and Airplanes

20800001 thru 20800221 and 208B0001 thru

208B0316 Incorporating SK208-112) (without TKS)

- Do a discharge pressure check. Refer to Chapter

36, Pneumatic Distribution - Maintenance Practices.

122

301007 Bleed Air Pressure Regulator (Airplanes 20800001

thru 20800221 and 208B0001 thru 208B0316 Not

Incorporating SK208-112) (without TKS) - Do a

discharge pressure check. Refer to Chapter 36,

Pneumatic Distribution - Maintenance Practices.

122

720006 Accessory Gearbox Breather Line - Inspect for

security of installation and condition.

122

723001 P3 Filter - Inspect P3 filter for general condition and

clean.

122

731002 Pneumatic Lines - Inspect P3/Py lines for condition

and security of installation. Inspect connections for

proper safetying.

122

731003 Pneumatic Lines - Inspect P3/Py line heaters for

operation and evidence of damage.

122

731004 Engine Fuel Pump - Inspect for security of

installation and fuel leaks. Inspect overboard drain

line for security of installation and condition.

122

731005 Engine Fuel Pump - Perform fuel pump inspection.

Refer to Chapter 73, Fuel Pump - Inspection/Check.

122

732001 Fuel Control - Inspect for security of installation and

fuel leaks.

122

732002 Fuel Control - Check for FCU bearing washout

indicated by blue dye (grease and fuel mixed) at

FCU overboard vent.

122

733001 Fuel Flow Transducer - Inspect for security of

installation, fuel leaks, and evidence of damage.

122

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ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

733002 Fuel Totalizer Signal Conditioner (if installed) -

Inspect for security of installation wiring connector

for security, and evidence of damage.

122

741001 Ignition Exciter Box - Inspect for security of

installation and condition.

122

741004 Ignition Exciter Box Wiring Harness - Inspect for

security of installation, condition and proper routing.

122

761001 Engine Controls - Check for freedom of operation.

Inspect for security of installation, wear, corrosion,

routing, evidence of damage, and deterioration.

Check rubber seals for deterioration.

122

761002 Control Linkages and Attach Brackets - Inspect

for security of installation, wear, corrosion, general

condition, and freedom of movement.

122

771005 T5 Terminal Block and External Wiring - Inspect for

security of installation and condition.

122

771006 Trim Thermocouple - Inspect for security of

installation and condition.

122

773001 Electric Torque Transmitter (if installed) - Inspect for

security of installation, condition, and leakage.

122

790003 Oil Filler Cap and Dipstick - Inspect for condition and

security of installation.

122

792001 Oil Cooler - Inspect for security of installation,

evidence of damage and condition. Inspect baffling

and seals for condition and security of installation.

122

793005 Oil Temperature Bulb - Inspect for security of

installation, condition and leakage.

122

793006 Oil Temperature Bulb Wiring - Inspect for security of

installation, condition and evidence of damage.

122

801004 Starter-Generator Electrical Cables and Connectors

- Inspect cables for routing, support, security of

connections and connector hardware.

122

242003 Standby Alternator Drive Drain (if applicable) -

Inspect for security of installation and condition.

130

717001 Engine Combustion Section Fuel Drains - Inspect for

security of installation, line routing, deterioration of

hoses and evidence of damage.

130

717002 Drain Openings and Vent Holes in Bottom of Engine

Cowling - Inspect for obstructions.

130

781001 Engine Exhaust System - Inspect primary and

secondary ducts for cracks, distortion, security of

installation, and evidence of damage.

130

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ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

781002 Engine Exhaust System - Perform primary and

secondary exhaust duct inspection and alignment.

Refer to Chapter 78, Primary and Secondary

Exhaust Duct - Maintenance Practices.

130

213002 Pressure Relief Valve - Inspect for condition and

security of installation.

151

282006 Firewall Mounted Fuel Filter with Bypass Flag (Red

Warning Button) - Clean, inspect for leaks, security

of installation and condition.

151

282007 EPA Can - Inspect for leakage, security of installation

and condition. Drain completely.

151

306004 Propeller Anti-ice Varistor (without TKS) - Examine

the firewall-mounted varistor for condition and

correct installation. Examine the electrical

connections for condition and correct installation.

151

324005 Brake System Reservoir - Inspect for security of

installation, condition and leaks. Check fluid level.

Refer to Chapter 12, Hydraulic Fluid - Servicing.

151

371001 Vacuum System Ejector - Inspect for condition and

security of installation.

151

793004 Oil Pressure Indicator Plumbing (Engine to Firewall)

- Inspect for security of installation, condition,

leakage and evidence of damage.

151

713001 Firewall Structure - Inspect for condition and

evidence of damage.

151, 152

720004 Engine Fire Seals - Inspect for security of installation

and general condition.

151, 152

214005 Cabin Heat Firewall Shutoff Control and Valves -

Inspect for general condition, evidence of damage

and security of installation. Inspect linkage,

temperature probe, safety switch and associated

wiring for condition and security of installation.

152, 226

341007 Static System Drain Valves - Visually inspect for

leaks, and presence of water in drain fittings.

Drain accumulated moisture. Inspect condition and

security of installation.

215, 216

330002 Instrument Panel Lights - Perform operational check. 220, 221,

222, 223,

224

275002 Primary Flap System - Operate flaps with flap control

lever, located in control pedestal, through full range

of travel and observe flaps for erratic motion, binding,

and interference.

226

282004 Fuel Shutoff Control - Operational check. 226

5-12-01 Page 8

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

231001 Control Wheel Pushbutton Switches - Clean the

transponder identification switch, microphone

switch, and the interphone switch on the pilot's

and copilot's control wheel. Refer to Chapter 23,

Communication - Maintenance Practices.

227, 228

251002 Pilot's and Copilot's Seats - Inspect seat brackets,

guides, stops, seat structure and seat cushions for

condition and security of installation; and controls

for condition, security of installation and proper

operation. Service seat adjusting screws, bearings

and locking mechanisms.

231, 232

251005 Pilot's and Copilot's Seat Back Stop Bolts - Inspect

for loose or missing nuts.

231, 232

262002 Portable Hand Fire Extinguisher - Inspect for proper

operating pressure, condition, and security of

installation. Check servicing date.

231, 232

351001 Oxygen Masks and Hose Assemblies - Inspect

for condition and clean. Inspect hose connection

for security of installation and hose for condition.

Perform operational check of pilot's mask

microphone.

231, 232

351002 Oxygen Masks - Perform operational test on the

oxygen masks. Inspect flow indicator for freedom of

movement.

231, 232

332002 Interior Lighting - Check operation of cabin,

passenger reading, no smoking/seatbelt, and control

wheel map lighting.

231, 232,

251, 252,

255, 256

221001 Autopilot Actuator (Aileron) - Inspect bridle cables

for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect chain

for proper safetying at all points and chains for

proper alignment with actuator sprockets. Inspect

pulleys, drive sprockets, drive chain, and guard

pins for condition, wear, corrosion, and security

of installation. Inspect electrical components for

operation, condition, and security of installation.

234

275003 Standby Flap System - Perform standby flap motor

operational check. Refer to Chapter 27, Flap System

- Maintenance Practices.

243

255007 Cargo Pod Fuel Reservoir Remote Drain (if installed)

- Check drain for proper operation and evidence of

leakage from drain tube outlet.

244

531004 Tailcone Drain Opening - Inspect for obstruction and

remove any foreign material from opening to prevent

blockage.

311, 312

5-12-01 Page 9

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

256001 Emergency Locator Installation - Inspect for security

of installation, position of function switch and

condition of electrical components. Inspect structure

for corrosion.

312

551001 Vertical and Horizontal Stabilizers - Inspect structure

and attach points for condition and security of

installation. Check for missing or damaged Vortex

generators.

340, 341,

373, 374,

375, 376

301004 De-ice Boots (without TKS) - Examine for abrasions,

cuts, nicks, correct installation, and cleanliness.

340, 371,

372, 501,

503, 601,

602

272001 Rudder - Inspect rudder skins for cracks and loose

rivets, rudder hinges for condition, cracks, and

security of installation; hinge bolts, hinge bearings,

hinge attach fitting, and bonding jumper for evidence

of damage or wear, failed fasteners, and security of

installation. Inspect rudder hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weight for looseness and supporting structure for

damage.

343

236001 Static Wicks (Wings and Empennage) - Inspect for

condition and security of installation.

343, 375,

376, 575,

527, 571,

625, 627,

671

273012 Elevator Trim Tab Actuators - Inspect for free play

in actuator. Refer to Chapter 27, Elevator Trim -

Maintenance Practices.

373, 374

273001 Elevator - Inspect elevator skins for cracks and

loose rivets; elevator hinges for condition, cracks,

and security; and hinge bolts, hinge bearings, torque

tube, horn, attach fittings, and bonding jumpers for

evidence of damage or wear, failed fasteners, and

security. Inspect elevator hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weights for looseness and supporting structure for

damage. Inspect outboard tips for cracks in rib

flange.

375, 376

273010 Elevator Trim Tabs - Inspect elevator trim tabs. 375, 376

570001 Wings - Inspect for loose fasteners, corrosion,

cracks, wrinkles, dents and attach points for

condition and security of installation.

500's,

600's

570005 Drain Openings and Vent Holes in Bottom of Wing -

Inspect for obstructions.

501, 503,

527, 571,

601, 603,

527, 571

570006 Wing Access Plates - Inspect for security of

installation and evidence of damage.

501, 503,

601, 603

5-12-01 Page 10

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

341005 Pitot Tube(s) - Visually check tube(s) and static ports

for obstructions. Inspect mast(s) for bending and

evidence of damage. Ensure sealant at mast-towing joint is in good condition.

503, 603

282001 Fuel Selector Valves and Linkages (Wing Area)

- Inspect shutoff valves, controls and linkage for

condition, security and evidence of damage. Inspect

all fuel selector valve arms for proper contact with

the off stop pins. Rerig if necessary.

511, 611

570002 Wing Spar Fittings - Inspect bolts for condition and

security of installation.

511, 611

271013 Spoiler - Inspect spoiler skins for cracks and loose

rivets; hinges for condition, cracks, and security of

installation; pushrods, pushrod bolts, bearings, and

bonding jumpers for evidence of damage or wear,

failed fasteners, and security of installation. Inspect

bolts on both ends of pushrods for proper safetying

of nuts with cotter pins.

521, 621

281001 Fuel Tank Area - Inspect for fuel stain, discoloration,

and evidence of fuel leaks.

521, 621

281003 Fuel Tank Filler Cap(s) and Flapper Valve(s) -

Inspect for damage or broken components and

check lock position of filler cap.

521, 621

281004 Drain Valves - Check operation and inspect for

leakage.

521, 621

275001 Flaps - Inspect flaps for loose rivets, cracks,

condition, and security of installation.

527, 627

570003 Wing Strut - Inspect for evidence of damage,

condition and security of installation.

531, 631

570004 Wing Strut Fittings - Inspect bolts for condition and

security of installation.

531, 631

271001 Aileron - Inspect the aileron skins for cracks and

loose rivets; aileron hinges for condition, cracks,

and security of installation; hinge bolts, hinge

bearings, hinge attach fittings, and bonding jumpers

for evidence of damage or wear, failed fasteners,

and security of installation. Inspect the aileron hinge

bolts for proper safetying of nuts with cotter pins.

Inspect balance weights for looseness and their

supporting structure for damage.

571, 671

271016 Aileron Trim Tab Actuator - Inspect for free play in

actuator. Refer to Chapter 27, Aileron Trim System

- Maintenance Practices.

651

271017 Aileron Trim Tab Actuator Pushrods - Inspect for free

play in actuator, condition and evidence of damage.

Inspect attaching hardware for wear and security of

installation.

651

5-12-01 Page 11

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

271014 Aileron Trim Tab - Inspect the trim tab skins for

cracks, loose rivets, and security of installation; and

trim tab hinge for cracks, security of installation, and

evidence of damage. Inspect hinge pin for proper

installation at hinge pin retainer. Inspect horn and

pushrod for evidence of damage and security of

installation. Inspect pushrod bolts for condition and

proper safetying of nuts with cotter pins.

671

322002 Nose Gear Torque Links and Shock Strut - Inspect

for condition, wear at attach points and security

of installation, then service. Refer to Chapter 12,

Lubricants - Description and Operation.

701

322005 Nose Gear Spring Yoke - Inspect bearing for

corrosion and freedom of rotation. Lubricate

bearing. Refer to Chapter 12, Lubricants -

Description and Operation. Reinstall bolt and torque

and safety wire. Refer to Chapter 32, Nose Landing

Gear - Maintenance Practices.

701

322006 Nose Gear Drag Link Spring Supports - Examine

for cracks, wear, loose bolts, elongated holes, and

corrosion.

701

324003 Nose Landing Gear Wheel and Tire - Check for wear,

pressure and condition. Refer to Chapter 12, Tires -

Servicing.

701

325001 Nose Landing Gear Shimmy Damper - Inspect for

condition and security of installation.

701

325002 Nose Landing Gear Shimmy Damper - Check for

need to service. Refer to Chapter 32, Landing Gear

- General.

701

325006 Nose Landing Gear Steering Stop Bolt or Block -

Inspect for condition, security of installation with bolt

head down.

701

324002A Landing Gear Wheel Bearings (Airplanes 20800001

thru 20800201 and 208B0001 thru 208B0255 Not

Incorporating CAB 91-30) - Inspect for condition

and repack. Refer to Chapter 12, Lubricants -

Description and Operation.

701, 721,

722

324001 Main Landing Gear Wheels and Tires - Check

for wear, pressure and condition. Rotate tires as

necessary to achieve uniform tire wear. Refer to

Chapter 12, Tires - Servicing.

721, 722

324004 Brake Assemblies - Inspect for wear of linings, disc

warpage and evidence of leakage.

721, 722

112001 Interior Placards, Exterior Placards, Decals,

Markings and Identification Plate - Inspect for

security of installation and legibility. Refer to Chapter

11, Placards and Markings - Inspection/Check.

ALL

5-12-01 Page 12

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

530001 Corrosion Prevention and Corrosion Program

Inspections - Use the age of the airplane for the

initial inspection. The initial and repeat intervals are

found in Chapter 5, 5-30-01 or 5-30-02, Corrosion

Prevention and Corrosion Program Inspections,

Table 1.

ALL

212005 Avionics Cooling Fan - Turn Battery and Avionics

Power switch No. 2 ON and check for cooling fan

operation.

BAT

256002 Emergency Locator Transmitter - Perform

operational test. Check cumulative time and useful

life of batteries in accordance with FAR 91.207.

BAT

262001 Engine Fire Detection - Perform engine fire detection

test.

BAT

341006 Pitot Tube(s) Heater - Place the PITOT/STATIC heat

switch to ON for approximately 30 seconds, then to

OFF. Verify tube(s) heats.

BAT

762001 Emergency Power Lever Annunciator Light -

Perform operational test.

BAT

214003 Cabin Heater and Windshield Defroster - Perform

operational check.

ENG

242005 Standby Electrical System (Engine Running) -

Perform functional test. Refer to Section 9 of the

Pilot's Operating Handbook.

ENG

243005 Volt/Ammeter (Engine Running) - Perform

operational check of each position.

ENG

244002 External Power - Perform operational check of the

BUS and STARTER functions.

ENG

273025 Stall Warning Horn - Perform an operational check. ENG

273026 Stall Warning Heater - Perform an operational check. ENG

284001 Reservoir Fuel Low Annunciator (Engine Running) -

Position both fuel selectors to OFF. Verify Reservoir

Low warning light illuminates as the fuel level in the

reservoir tank drops below full, then place both fuel

tank selectors to ON.

ENG

284002 Fuel Selectors OFF Warning System - Perform

operational check of warning system.

ENG

301005 Wing De-ice System (Engine Running) (without

TKS) - Do a check of the wing de-ice system.

ENG

306003 Propeller Anti-ice System (Engine Running) (without

TKS) - Do a check of the propeller anti-ice system.

ENG

371007 Suction Gauge (Engine Running) - Verify operation. ENG

612004 Propeller Governor (Engine Running) - Perform an

operational check.

ENG

5-12-01 Page 13

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

622004 Propeller Governor (Engine Running) - Perform

operational check.

ENG

761003 Power Lever Reverse Speed Pickup (Engine

Running) - Check power lever reverse speed pickup.

ENG

761006 Engine Idle Check (Engine Running) - Perform

engine idle check.

ENG

243006 NI-CAD Battery (if installed) - Perform capacity

check. Check terminals for overheating or burning.

LAB

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

5-12-01 Page 14

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 2

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 2 consists of all 100 hour interval inspection items and those 200 or 400 hour interval

inspection items contained in the engine, wing and landing gear areas. 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. A

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

306002 Propeller Anti-ice Brushes (without TKS) - Examine

each brush for wear, signs of damage, cleanliness,

correct installation and correct rigging. Examine

electrical wires for condition and correct installation.

110

611001 Propeller Spinner (Hartzell and McCauley) -

Remove, wash, inspect for cracks, fractures,

condition and security of installation.

110

611002 Hartzell Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

611003 Hartzell Propeller Blades - Wash, check for nicks,

gouges, scratches, leading edge looseness,

depressions, delaminating, cracks, condition and

security of installation. Inspect clamps for security

of installation.

110

611004 Hartzell Propeller Blades - Check alignment and

freedom of movement.

110

5-12-02 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

611005 Hartzell Propeller Hub (Exposed Area) - Inspect for

cracks, wear, condition, and security of components

to hub.

110

611006 Hartzell Propeller - Inspect for oil and grease leaks. 110

611007 Hartzell Propeller Mounting - Visually check for

security of installation.

110

611008 Hartzell Propeller Blade Clamps - Lubricate and

check for security of installation. Refer to Chapter

12, Lubricants - Description and Operation, and

Chapter 61, Propeller (Hartzell) - Description and

Operation.

110

621002 McCauley Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

621003 McCauley Propeller Blades - Wash, check for nicks,

gouges, scratches corrosion and cracks.

110

621005 McCauley Propeller Hub (Exposed Area) - Inspect

for cracks, wear, condition, and security of

components to hub.

110

621006 McCauley Propeller - Inspect for oil leaks. 110

621007 McCauley Propeller Mounting - Visually check for

security of installation.

110

720005 Engine Propeller Shaft Seal - Inspect for leaks and

security of installation.

110

301101 100 Hour Operational Check (with TKS) - Visually

check for wear and security of installation at the

propeller boots, propeller nozzle, propeller feed

tubes, and propeller slinger. Check operation of

pumps, pump CAS annunciator (G1000), press test

TKS annunciator (non-G1000), fluid flow of slinger

and leading edge panels.

110, 220,

221, 240,

340, 373,

374, 527,

531, 571,

627, 631,

671, 903,

904

612002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

622002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

716001 Induction System and Inertial Separator - Inspect

for general condition, security, and freedom of

operation. Inspect door pivot point bearings for

excessive wear. Check separator linkage for proper

operation. Check for loose rivets.

121

716002 Inertial Separator - Unlock control and pull into

bypass. Check for freedom of movement and for full

opening of the bypass door in the air duct.

121

5-12-02 Page 2

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

716005 Inertial Separator - Perform rivet inspection. Refer to

Chapter 71, Inertial Separator Forward and Aft Vane

Rivet Inspection - Inspection/Check.

121

790004 Oil Filter - Remove, clean and inspect for damage.

Filter may be electrosonically cleaned if desired.

121

261002 Heat Detection Loop - Inspect the three loop

sections for condition, security of installation and

evidence of damage, paying special attention to the

loop connection fittings.

121, 122

731001 Fuel Lines - Inspect fuel supply and fuel motive

flow lines for deterioration, chafing, fuel leaks, and

security of installation.

121, 122

731006 Fuel Manifold - Inspect for security of installation and

evidence of fuel leaks.

121, 122

731010 Flow Divider - Inspect for security of installation and

evidence of fuel leaks.

121, 122

741003 Igniters - Inspect for wear, corrosion, and condition

of insulator. Clean insulator at lead attachment, but

do not clean igniter end.

121, 122

741005 Igniters - Perform operational check by placing

ignition switch in the ON position (battery switch on).

Verify IGNITION ON annunciator illuminates.

121, 122

793002 Chip Detectors without Annunciator Light - Inspect. 121, 122

243001 Battery Cable Disconnect and Cables - Inspect

for condition, corrosion and security of installation.

Inspect battery terminal receptacles for overheating

or burning.

122

243007 Battery Tray - Inspect for condition, corrosion and

security of installation. Inspect latching mechanism

for proper operation.

122

243009 Gill Flooded Lead Acid Battery (if installed) - Check

general condition and security of installation. Check

level of electrolyte. Check terminals for overheating

or burning.

122

243010 Gill Lead Acid Only Battery Box - Inspect for

corrosion, condition and security of installation.

122

243011 Battery Vent Tubes - Inspect for condition,

obstructions and security of installation.

122

243014 Concord Sealed Lead Acid Battery (if installed) -

Check general condition and security of installation.

Check terminals for overheating or burning. Perform

checks in accordance with servicing placard on the

side of battery.

122

5-12-02 Page 3

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

301007 Bleed Air Pressure Regulator (Airplanes 20800001

thru 20800221 and 208B0001 thru 208B0316 Not

Incorporating SK208-112) (without TKS) - Do a

discharge pressure check. Refer to Chapter 36,

Pneumatic Distribution - Maintenance Practices.

122

723001 P3 Filter - Inspect P3 filter for general condition and

clean.

122

731004 Engine Fuel Pump - Inspect for security of

installation and fuel leaks. Inspect overboard drain

line for security of installation and condition.

122

731011 Fuel Discharge Nozzles - Perform flow check and

clean.

122

732001 Fuel Control - Inspect for security of installation and

fuel leaks.

122

732002 Fuel Control - Check for FCU bearing washout

indicated by blue dye (grease and fuel mixed) at

FCU overboard vent.

122

733001 Fuel Flow Transducer - Inspect for security of

installation, fuel leaks, and evidence of damage.

122

733002 Fuel Totalizer Signal Conditioner (if installed) -

Inspect for security of installation wiring connector

for security, and evidence of damage.

122

761001 Engine Controls - Check for freedom of operation.

Inspect for security of installation, wear, corrosion,

routing, evidence of damage, and deterioration.

Check rubber seals for deterioration.

122

761002 Control Linkages and Attach Brackets - Inspect

for security of installation, wear, corrosion, general

condition, and freedom of movement.

122

790003 Oil Filler Cap and Dipstick - Inspect for condition and

security of installation.

122

717002 Drain Openings and Vent Holes in Bottom of Engine

Cowling - Inspect for obstructions.

130

781001 Engine Exhaust System - Inspect primary and

secondary ducts for cracks, distortion, security of

installation, and evidence of damage.

130

282006 Firewall Mounted Fuel Filter with Bypass Flag (Red

Warning Button) - Clean, inspect for leaks, security

of installation and condition.

151

282007 EPA Can - Inspect for leakage, security of installation

and condition. Drain completely.

151

324005 Brake System Reservoir - Inspect for security of

installation, condition and leaks. Check fluid level.

Refer to Chapter 12, Hydraulic Fluid - Servicing.

151

5-12-02 Page 4

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

793004 Oil Pressure Indicator Plumbing (Engine to Firewall)

- Inspect for security of installation, condition,

leakage and evidence of damage.

151

793003 Oil Pressure Switch and Fitting (Aft Side of Firewall)

- Inspect for security of installation, condition and

leakage.

201

272004 Rudder Pedals and Rudder Pedal Linkage - Inspect

for condition and security. Operate rudder controls

and check for freedom of movement.

211, 212

327001 Jack Pad Installation - Check for condition and

security of installation.

213, 214,

721, 722

271006 Control Wheel - Inspect control wheel for condition

and security of installation. Operate control wheel

and check for freedom of movement.

215, 216

341007 Static System Drain Valves - Visually inspect for

leaks, and presence of water in drain fittings.

Drain accumulated moisture. Inspect condition and

security of installation.

215, 216

330002 Instrument Panel Lights - Perform operational check. 220, 221,

222, 223,

224

273006 Control Column - Inspect control column for

evidence of damage, failed fasteners, and security

of installation. Operate control column and check

for freedom of movement.

223, 224

271021 Aileron Trim Tab Control and Indicator - Inspect

control and indicator for condition and security of

installation. Operate trim tab control and check

aileron trim tab for freedom of movement. Inspect

guide block for condition and security of installation.

226

272010 Rudder Trim Wheel and Indicator - Inspect trim

wheel and indicator for condition and security of

installation. Operate trim wheel and check rudder

trim for freedom of movement.

226

273017 Elevator Trim Tab Control and Indicator - Inspect

control and indicator for condition and security of

installation. Operate trim tab control and check for

freedom of movement.

226

275002 Primary Flap System - Operate flaps with flap control

lever, located in control pedestal, through full range

of travel and observe flaps for erratic motion, binding,

and interference.

226

282004 Fuel Shutoff Control - Operational check. 226

5-12-02 Page 5

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

231001 Control Wheel Pushbutton Switches - Clean the

transponder identification switch, microphone

switch, and the interphone switch on the pilot's

and copilot's control wheel. Refer to Chapter 23,

Communication - Maintenance Practices.

227, 228

251002 Pilot's and Copilot's Seats - Inspect seat brackets,

guides, stops, seat structure and seat cushions for

condition and security of installation; and controls

for condition, security of installation and proper

operation. Service seat adjusting screws, bearings

and locking mechanisms.

231, 232

251005 Pilot's and Copilot's Seat Back Stop Bolts - Inspect

for loose or missing nuts.

231, 232

262002 Portable Hand Fire Extinguisher - Inspect for proper

operating pressure, condition, and security of

installation. Check servicing date.

231, 232

351001 Oxygen Masks and Hose Assemblies - Inspect

for condition and clean. Inspect hose connection

for security of installation and hose for condition.

Perform operational check of pilot's mask

microphone.

231, 232

351002 Oxygen Masks - Perform operational test on the

oxygen masks. Inspect flow indicator for freedom of

movement.

231, 232

332002 Interior Lighting - Check operation of cabin,

passenger reading, no smoking/seatbelt, and control

wheel map lighting.

231, 232,

251, 252,

255, 256

275003 Standby Flap System - Perform standby flap motor

operational check. Refer to Chapter 27, Flap System

- Maintenance Practices.

243

255007 Cargo Pod Fuel Reservoir Remote Drain (if installed)

- Check drain for proper operation and evidence of

leakage from drain tube outlet.

244

252001 Seat Tracks - Inspect seat tracks and stops for

condition and security of installation. Inspect

seat track stops for proper location, security of

installation.

251, 252,

255, 256

531004 Tailcone Drain Opening - Inspect for obstruction and

remove any foreign material from opening to prevent

blockage.

311, 312

5-12-02 Page 6

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

221004 Autopilot Actuator (Elevator) - Inspect bridal

cables for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect chain

for proper safetying at all points and chains for

proper alignment with actuators sprockets. Inspect

pulleys, drive sprockets, drive chain, and guard

pins for condition, wear, corrosion, and security

of installation. Inspect electrical components for

operation, condition, and security of installation.

312

256001 Emergency Locator Installation - Inspect for security

of installation, position of function switch and

condition of electrical components. Inspect structure

for corrosion.

312

272007 Rudder Gust Lock (Airplanes 20800030 thru

20800236 and 208B0001 thru 208B0381) (if

installed) - Inspect for condition, security of

installation, and positive locking action.

320

272011 Rudder Gust Lock (Airplanes 20800237 and On and

208B0382 and On) - Inspect in accordance with

AERO TWIN STC airworthiness requirements.

320

272001 Rudder - Inspect rudder skins for cracks and loose

rivets, rudder hinges for condition, cracks, and

security of installation; hinge bolts, hinge bearings,

hinge attach fitting, and bonding jumper for evidence

of damage or wear, failed fasteners, and security of

installation. Inspect rudder hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weight for looseness and supporting structure for

damage.

343

273001 Elevator - Inspect elevator skins for cracks and

loose rivets; elevator hinges for condition, cracks,

and security; and hinge bolts, hinge bearings, torque

tube, horn, attach fittings, and bonding jumpers for

evidence of damage or wear, failed fasteners, and

security. Inspect elevator hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weights for looseness and supporting structure for

damage. Inspect outboard tips for cracks in rib

flange.

375, 376

273010 Elevator Trim Tabs - Inspect elevator trim tabs. 375, 376

273013 Elevator Trim Tab Actuator Pushrods - Inspect

for condition and evidence of damage. Inspect

attaching hardware for wear and security of

installation.

375, 376

570006 Wing Access Plates - Inspect for security of

installation and evidence of damage.

501, 503,

601, 603

5-12-02 Page 7

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

341005 Pitot Tube(s) - Visually check tube(s) and static ports

for obstructions. Inspect mast(s) for bending and

evidence of damage. Ensure sealant at mast-towing joint is in good condition.

503, 603

282001 Fuel Selector Valves and Linkages (Wing Area)

- Inspect shutoff valves, controls and linkage for

condition, security and evidence of damage. Inspect

all fuel selector valve arms for proper contact with

the off stop pins. Rerig if necessary.

511, 611

281001 Fuel Tank Area - Inspect for fuel stain, discoloration,

and evidence of fuel leaks.

521, 621

281003 Fuel Tank Filler Cap(s) and Flapper Valve(s) -

Inspect for damage or broken components and

check lock position of filler cap.

521, 621

281004 Drain Valves - Check operation and inspect for

leakage.

521, 621

275001 Flaps - Inspect flaps for loose rivets, cracks,

condition, and security of installation.

527, 627

271001 Aileron - Inspect the aileron skins for cracks and

loose rivets; aileron hinges for condition, cracks,

and security of installation; hinge bolts, hinge

bearings, hinge attach fittings, and bonding jumpers

for evidence of damage or wear, failed fasteners,

and security of installation. Inspect the aileron hinge

bolts for proper safetying of nuts with cotter pins.

Inspect balance weights for looseness and their

supporting structure for damage.

571, 671

271014 Aileron Trim Tab - Inspect the trim tab skins for

cracks, loose rivets, and security of installation; and

trim tab hinge for cracks, security of installation, and

evidence of damage. Inspect hinge pin for proper

installation at hinge pin retainer. Inspect horn and

pushrod for evidence of damage and security of

installation. Inspect pushrod bolts for condition and

proper safetying of nuts with cotter pins.

671

322001 Nose Gear Shock Strut - Inspect for evidence of

leakage. Inspect strut barrel for corrosion, pitting

and cleanliness.

701

322002 Nose Gear Torque Links and Shock Strut - Inspect

for condition, wear at attach points and security

of installation, then service. Refer to Chapter 12,

Lubricants - Description and Operation.

701

322003 Nose Gear Fairings - Inspect for condition and

security of installation.

701

322004 Nose Gear Fork - Inspect for condition and security

of installation.

701

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

322005 Nose Gear Spring Yoke - Inspect bearing for

corrosion and freedom of rotation. Lubricate

bearing. Refer to Chapter 12, Lubricants -

Description and Operation. Reinstall bolt and torque

and safety wire. Refer to Chapter 32, Nose Landing

Gear - Maintenance Practices.

701

322006 Nose Gear Drag Link Spring Supports - Examine

for cracks, wear, loose bolts, elongated holes, and

corrosion.

701

324003 Nose Landing Gear Wheel and Tire - Check for wear,

pressure and condition. Refer to Chapter 12, Tires -

Servicing.

701

325001 Nose Landing Gear Shimmy Damper - Inspect for

condition and security of installation.

701

325002 Nose Landing Gear Shimmy Damper - Check for

need to service. Refer to Chapter 32, Landing Gear

- General.

701

325003 Nose Wheel Steering Linkage - Check condition,

security of installation and travel.

701

325004 Nose Wheel Steering Linkage Bolts - Inspect for

condition and security of installation.

701

325005 Nose Landing Gear Shimmy Damper Pivots -

Lubricate nose landing gear shimmy damper pivots.

Refer to Chapter 12, Lubricants - Description and

Operation. Airplanes 2080001 thru 2080393 and

208B0001 thru 208B1039

701

325006 Nose Landing Gear Steering Stop Bolt or Block -

Inspect for condition, security of installation with bolt

head down.

701

325007 Nose Gear Steering Bell Crank - Inspect for

condition, and security of installation.

701

325008 Nose Wheel Steering Rod End - Inspect for condition

and security of installation.

701

324002A Landing Gear Wheel Bearings (Airplanes 20800001

thru 20800201 and 208B0001 thru 208B0255 Not

Incorporating CAB 91-30) - Inspect for condition

and repack. Refer to Chapter 12, Lubricants -

Description and Operation.

701, 721,

722

324002B Landing Gear Wheel Bearings (Airplanes 20800202

and On and 208B0256 and On, and Airplanes

20800001 thru 20800201 and 208B0001 thru

208B0255 Incorporating CAB 91-30) - Inspect

for condition and repack. Refer to Chapter 12,

Lubricants - Description and Operation.

701, 721,

722

321001 Main Landing Gear System - Inspect for condition

and security of installation. Check free play between

the center spring and gear legs.

721, 722

5-12-02 Page 9

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

321002 Main Gear Fairings - Inspect for condition and

security of installation. Check for interference

between fairing and brake lines.

721, 722

324001 Main Landing Gear Wheels and Tires - Check

for wear, pressure and condition. Rotate tires as

necessary to achieve uniform tire wear. Refer to

Chapter 12, Tires - Servicing.

721, 722

324004 Brake Assemblies - Inspect for wear of linings, disc

warpage and evidence of leakage.

721, 722

324008 Brake System Plumbing - Inspect for leaks. Inspect

hoses for bulges and deterioration. Check rigid

lines for security of installation, proper routing and

chafing.

721, 722

112001 Interior Placards, Exterior Placards, Decals,

Markings and Identification Plate - Inspect for

security of installation and legibility. Refer to Chapter

11, Placards and Markings - Inspection/Check.

ALL

530001 Corrosion Prevention and Corrosion Program

Inspections - Use the age of the airplane for the

initial inspection. The initial and repeat intervals are

found in Chapter 5, 5-30-01 or 5-30-02, Corrosion

Prevention and Corrosion Program Inspections,

Table 1.

ALL

304003 Windshield Anti-ice System (without TKS) - Do

an operational check of the AUTO and MANUAL

systems. Make sure that the WINDSHIELD

ANTI-ICE annunciator light comes on.

AUX

212005 Avionics Cooling Fan - Turn Battery and Avionics

Power switch No. 2 ON and check for cooling fan

operation.

BAT

256002 Emergency Locator Transmitter - Perform

operational test. Check cumulative time and useful

life of batteries in accordance with FAR 91.207.

BAT

262001 Engine Fire Detection - Perform engine fire detection

test.

BAT

332003 Courtesy/Cargo Light Timer - Perform operational

check.

BAT

341006 Pitot Tube(s) Heater - Place the PITOT/STATIC heat

switch to ON for approximately 30 seconds, then to

OFF. Verify tube(s) heats.

BAT

762001 Emergency Power Lever Annunciator Light -

Perform operational test.

BAT

214003 Cabin Heater and Windshield Defroster - Perform

operational check.

ENG

5-12-02 Page 10

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

242005 Standby Electrical System (Engine Running) -

Perform functional test. Refer to Section 9 of the

Pilot's Operating Handbook.

ENG

243005 Volt/Ammeter (Engine Running) - Perform

operational check of each position.

ENG

244002 External Power - Perform operational check of the

BUS and STARTER functions.

ENG

273025 Stall Warning Horn - Perform an operational check. ENG

273026 Stall Warning Heater - Perform an operational check. ENG

284001 Reservoir Fuel Low Annunciator (Engine Running) -

Position both fuel selectors to OFF. Verify Reservoir

Low warning light illuminates as the fuel level in the

reservoir tank drops below full, then place both fuel

tank selectors to ON.

ENG

284002 Fuel Selectors OFF Warning System - Perform

operational check of warning system.

ENG

301005 Wing De-ice System (Engine Running) (without

TKS) - Do a check of the wing de-ice system.

ENG

306003 Propeller Anti-ice System (Engine Running) (without

TKS) - Do a check of the propeller anti-ice system.

ENG

371007 Suction Gauge (Engine Running) - Verify operation. ENG

612004 Propeller Governor (Engine Running) - Perform an

operational check.

ENG

622004 Propeller Governor (Engine Running) - Perform

operational check.

ENG

761003 Power Lever Reverse Speed Pickup (Engine

Running) - Check power lever reverse speed pickup.

ENG

761006 Engine Idle Check (Engine Running) - Perform

engine idle check.

ENG

243006 NI-CAD Battery (if installed) - Perform capacity

check. Check terminals for overheating or burning.

LAB

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

5-12-02 Page 11

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 3

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 3 consists of all 100 hour interval inspection items and those 200 or 400 hour interval

inspection items contained in the engine, wing, empennage and fuselage areas. 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. A

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

306001 Propeller Anti-ice Slip Rings, Boots, and Wiring

(without TKS) - Examine for condition and correct

installation. Examine brushes for proper tracking.

110

306002 Propeller Anti-ice Brushes (without TKS) - Examine

each brush for wear, signs of damage, cleanliness,

correct installation and correct rigging. Examine

electrical wires for condition and correct installation.

110

611001 Propeller Spinner (Hartzell and McCauley) -

Remove, wash, inspect for cracks, fractures,

condition and security of installation.

110

611002 Hartzell Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

611003 Hartzell Propeller Blades - Wash, check for nicks,

gouges, scratches, leading edge looseness,

depressions, delaminating, cracks, condition and

security of installation. Inspect clamps for security

of installation.

110

5-12-03 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

611004 Hartzell Propeller Blades - Check alignment and

freedom of movement.

110

611005 Hartzell Propeller Hub (Exposed Area) - Inspect for

cracks, wear, condition, and security of components

to hub.

110

611006 Hartzell Propeller - Inspect for oil and grease leaks. 110

611007 Hartzell Propeller Mounting - Visually check for

security of installation.

110

611008 Hartzell Propeller Blade Clamps - Lubricate and

check for security of installation. Refer to Chapter

12, Lubricants - Description and Operation, and

Chapter 61, Propeller (Hartzell) - Description and

Operation.

110

612001 Hartzell Beta System Feedback Ring - Inspect ring

for condition, warpage and security of installation.

Inspect carbon brush for wear and evidence of

damage. Inspect linkage for condition and security

of installation. Refer to Chapter 61, Propeller

(Hartzell) - Maintenance Practices.

110

621002 McCauley Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

621003 McCauley Propeller Blades - Wash, check for nicks,

gouges, scratches corrosion and cracks.

110

621005 McCauley Propeller Hub (Exposed Area) - Inspect

for cracks, wear, condition, and security of

components to hub.

110

621006 McCauley Propeller - Inspect for oil leaks. 110

621007 McCauley Propeller Mounting - Visually check for

security of installation.

110

622001 McCauley Beta System Feedback Ring - Inspect ring

for condition, warpage and security of installation.

Inspect carbon brush for wear and evidence of

damage. Inspect linkage for condition and security

of installation. Refer to Chapter 61, Propeller

(McCauley) - Maintenance Practices.

110

720005 Engine Propeller Shaft Seal - Inspect for leaks and

security of installation.

110

301101 100 Hour Operational Check (with TKS) - Visually

check for wear and security of installation at the

propeller boots, propeller nozzle, propeller feed

tubes, and propeller slinger. Check operation of

pumps, pump CAS annunciator (G1000), press test

TKS annunciator (non-G1000), fluid flow of slinger

and leading edge panels.

110, 220,

221, 240,

340, 373,

374, 527,

531, 571,

627, 631,

671, 903,

904

5-12-03 Page 2

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

242001 Standby Alternator - Inspect for condition and

security of installation, belt tension and condition.

Check terminal boots for condition and electrical

leads for damage and security of installation.

121

242002 Standby Alternator Drive - Inspect for security of

installation, leakage, and condition.

121

612002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

622002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

716001 Induction System and Inertial Separator - Inspect

for general condition, security, and freedom of

operation. Inspect door pivot point bearings for

excessive wear. Check separator linkage for proper

operation. Check for loose rivets.

121

716002 Inertial Separator - Unlock control and pull into

bypass. Check for freedom of movement and for full

opening of the bypass door in the air duct.

121

716003 Induction Air Plenum - Remove access door. Inspect

for cracks, security of installation and condition.

121

716005 Inertial Separator - Perform rivet inspection. Refer to

Chapter 71, Inertial Separator Forward and Aft Vane

Rivet Inspection - Inspection/Check.

121

790004 Oil Filter - Remove, clean and inspect for damage.

Filter may be electrosonically cleaned if desired.

121

801001 Starter-Generator - Inspect security of installation,

terminal block, boot, and electrical connections

for cleanliness, evidence of heat or arcing, and

evidence of damage.

121

261002 Heat Detection Loop - Inspect the three loop

sections for condition, security of installation and

evidence of damage, paying special attention to the

loop connection fittings.

121, 122

720001 Engine Compartment - Inspect for general condition,

security of installation, leakage, and damage.

121, 122

720002 Engine Air Inlet Screen - Inspect for cleanliness and

security of installation.

121, 122

720003 Engine Gas Generator Case - Inspect for cracks,

distortion, and corrosion.

121, 122

720007 Engine Accessories - Inspect for security of

installation, general condition and leakage.

121, 122

731001 Fuel Lines - Inspect fuel supply and fuel motive

flow lines for deterioration, chafing, fuel leaks, and

security of installation.

121, 122

5-12-03 Page 3

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

731006 Fuel Manifold - Inspect for security of installation and

evidence of fuel leaks.

121, 122

731010 Flow Divider - Inspect for security of installation and

evidence of fuel leaks.

121, 122

741003 Igniters - Inspect for wear, corrosion, and condition

of insulator. Clean insulator at lead attachment, but

do not clean igniter end.

121, 122

741005 Igniters - Perform operational check by placing

ignition switch in the ON position (battery switch on).

Verify IGNITION ON annunciator illuminates.

121, 122

793002 Chip Detectors without Annunciator Light - Inspect. 121, 122

793001 Chip Detectors with Annunciator Light - Inspect. 121, 122,

221

243001 Battery Cable Disconnect and Cables - Inspect

for condition, corrosion and security of installation.

Inspect battery terminal receptacles for overheating

or burning.

122

243007 Battery Tray - Inspect for condition, corrosion and

security of installation. Inspect latching mechanism

for proper operation.

122

243008 NI-CAD Battery Temperature Probe Connector

- Inspect connector and associated wiring for

condition and security of installation. Disconnect

plug from battery and check annunciators. Verify

BATTERY HOT and BATTERY OVERHEAT

annunciator lights illuminate with power ON.

122

243009 Gill Flooded Lead Acid Battery (if installed) - Check

general condition and security of installation. Check

level of electrolyte. Check terminals for overheating

or burning.

122

243010 Gill Lead Acid Only Battery Box - Inspect for

corrosion, condition and security of installation.

122

243011 Battery Vent Tubes - Inspect for condition,

obstructions and security of installation.

122

243014 Concord Sealed Lead Acid Battery (if installed) -

Check general condition and security of installation.

Check terminals for overheating or burning. Perform

checks in accordance with servicing placard on the

side of battery.

122

301006 Bleed Air Pressure Regulator (Airplanes 20800222

and On and 208B0317 and On, and Airplanes

20800001 thru 20800221 and 208B0001 thru

208B0316 Incorporating SK208-112) (without TKS)

- Do a discharge pressure check. Refer to Chapter

36, Pneumatic Distribution - Maintenance Practices.

122

5-12-03 Page 4

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

301007 Bleed Air Pressure Regulator (Airplanes 20800001

thru 20800221 and 208B0001 thru 208B0316 Not

Incorporating SK208-112) (without TKS) - Do a

discharge pressure check. Refer to Chapter 36,

Pneumatic Distribution - Maintenance Practices.

122

720006 Accessory Gearbox Breather Line - Inspect for

security of installation and condition.

122

723001 P3 Filter - Inspect P3 filter for general condition and

clean.

122

731004 Engine Fuel Pump - Inspect for security of

installation and fuel leaks. Inspect overboard drain

line for security of installation and condition.

122

732001 Fuel Control - Inspect for security of installation and

fuel leaks.

122

732002 Fuel Control - Check for FCU bearing washout

indicated by blue dye (grease and fuel mixed) at

FCU overboard vent.

122

733001 Fuel Flow Transducer - Inspect for security of

installation, fuel leaks, and evidence of damage.

122

733002 Fuel Totalizer Signal Conditioner (if installed) -

Inspect for security of installation wiring connector

for security, and evidence of damage.

122

761001 Engine Controls - Check for freedom of operation.

Inspect for security of installation, wear, corrosion,

routing, evidence of damage, and deterioration.

Check rubber seals for deterioration.

122

761002 Control Linkages and Attach Brackets - Inspect

for security of installation, wear, corrosion, general

condition, and freedom of movement.

122

790003 Oil Filler Cap and Dipstick - Inspect for condition and

security of installation.

122

801004 Starter-Generator Electrical Cables and Connectors

- Inspect cables for routing, support, security of

connections and connector hardware.

122

301001 Surface De-ice Regulator and De-ice Control Valves

(without TKS) - Examine for condition and correct

installation.

122, 251

242003 Standby Alternator Drive Drain (if applicable) -

Inspect for security of installation and condition.

130

717002 Drain Openings and Vent Holes in Bottom of Engine

Cowling - Inspect for obstructions.

130

781001 Engine Exhaust System - Inspect primary and

secondary ducts for cracks, distortion, security of

installation, and evidence of damage.

130

5-12-03 Page 5

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

781002 Engine Exhaust System - Perform primary and

secondary exhaust duct inspection and alignment.

Refer to Chapter 78, Primary and Secondary

Exhaust Duct - Maintenance Practices.

130

282006 Firewall Mounted Fuel Filter with Bypass Flag (Red

Warning Button) - Clean, inspect for leaks, security

of installation and condition.

151

282007 EPA Can - Inspect for leakage, security of installation

and condition. Drain completely.

151

324005 Brake System Reservoir - Inspect for security of

installation, condition and leaks. Check fluid level.

Refer to Chapter 12, Hydraulic Fluid - Servicing.

151

793004 Oil Pressure Indicator Plumbing (Engine to Firewall)

- Inspect for security of installation, condition,

leakage and evidence of damage.

151

720004 Engine Fire Seals - Inspect for security of installation

and general condition.

151, 152

272008 Rudder Control System - Check connections for

security of installation, and tightness of fasteners

where applicable. Refer to Chapter 20, Torque Data

- Maintenance Practices.

211, 212,

320

334003 Exterior Lighting - Perform operational check. 215

341007 Static System Drain Valves - Visually inspect for

leaks, and presence of water in drain fittings.

Drain accumulated moisture. Inspect condition and

security of installation.

215, 216

230004 Remote Mounted Avionics (Empennage) - Inspect

for security of units and electrical connectors,

condition and security of wire routing. Also, check

for evidence of damage and cleanliness.

216

330002 Instrument Panel Lights - Perform operational check. 220, 221,

222, 223,

224

340001 Navigation Antenna(s) - Inspect for condition,

security of installation and evidence of damage.

222

275002 Primary Flap System - Operate flaps with flap control

lever, located in control pedestal, through full range

of travel and observe flaps for erratic motion, binding,

and interference.

226

282004 Fuel Shutoff Control - Operational check. 226

231001 Control Wheel Pushbutton Switches - Clean the

transponder identification switch, microphone

switch, and the interphone switch on the pilot's

and copilot's control wheel. Refer to Chapter 23,

Communication - Maintenance Practices.

227, 228

5-12-03 Page 6

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

301003 Surface De-ice System (without TKS) - Examine

the electrical components for condition and correct

installation.

231

(208),

251

(208B)

251002 Pilot's and Copilot's Seats - Inspect seat brackets,

guides, stops, seat structure and seat cushions for

condition and security of installation; and controls

for condition, security of installation and proper

operation. Service seat adjusting screws, bearings

and locking mechanisms.

231, 232

251005 Pilot's and Copilot's Seat Back Stop Bolts - Inspect

for loose or missing nuts.

231, 232

262002 Portable Hand Fire Extinguisher - Inspect for proper

operating pressure, condition, and security of

installation. Check servicing date.

231, 232

351001 Oxygen Masks and Hose Assemblies - Inspect

for condition and clean. Inspect hose connection

for security of installation and hose for condition.

Perform operational check of pilot's mask

microphone.

231, 232

351002 Oxygen Masks - Perform operational test on the

oxygen masks. Inspect flow indicator for freedom of

movement.

231, 232

332002 Interior Lighting - Check operation of cabin,

passenger reading, no smoking/seatbelt, and control

wheel map lighting.

231, 232,

251, 252,

255, 256

273014 Elevator Trim Tab Cables (Fuselage) - Inspect

cables for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect chains for

proper safetying at all points and chains for proper

alignment on sprockets. Inspect pulleys and guard

pins for condition, wear, corrosion, and security of

installation.

233, 253,

257

221001 Autopilot Actuator (Aileron) - Inspect bridle cables

for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect chain

for proper safetying at all points and chains for

proper alignment with actuator sprockets. Inspect

pulleys, drive sprockets, drive chain, and guard

pins for condition, wear, corrosion, and security

of installation. Inspect electrical components for

operation, condition, and security of installation.

234

275003 Standby Flap System - Perform standby flap motor

operational check. Refer to Chapter 27, Flap System

- Maintenance Practices.

243

255007 Cargo Pod Fuel Reservoir Remote Drain (if installed)

- Check drain for proper operation and evidence of

leakage from drain tube outlet.

244

5-12-03 Page 7

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

350001 Oxygen System - Inspect system and component

mounting for condition and security of installation.

251, 252,

255, 256

275006 Flap Bell Cranks, Control Rods, Pulleys, and Cables

- Inspect bell cranks, pulleys and cables for condition

and security of installation. Inspect flap bell cranks

for corrosion and cracks, primarily in the welds.

Inspect all control rods (interconnect, connecting,

pushrod, and wing-to-wing) for bent rods, chafing,

seized or worn rod end bearings, loose rod end

locknuts, and verify rod end thread engagement

reaches at least to the rod end inspection hole.

Check rod end and bell crank bearings for corrosion;

clean and lubricate. Refer to Chapter 12, Lubricants

- Description and Operation.

252

275007 Flap Actuator Assembly and Fuselage Seal

Assemblies - Inspect condition and security of

motors, drivescrew, and transmission. Clean

drivescrew threads and lubricate with #10 weight

non-detergent oil. Inspect flap actuator assembly

support structure for cracks and security of

installation. Inspect fuselage seal assemblies for

condition and security of installation.

252

273005 Elevator Cables (Fuselage) - Inspect cables for

fraying, chafing, cleanliness, turnbuckle safetying,

and proper routing. Inspect pulleys and guard

pins for condition, wear, corrosion, and security of

installation.

311

273016 Elevator Trim Tab Cable Stop Blocks - Inspect for

condition and security of installation.

311, 312

350002 Oxygen System - Inspect regulator, shutoff valve and

remote filling system for operation, condition and

security of installation.

311, 312

531004 Tailcone Drain Opening - Inspect for obstruction and

remove any foreign material from opening to prevent

blockage.

311, 312

243013 Tailcone Wire Bundles - Inspect for proper position

of drip loop to prevent moisture from entering

connector.

311, 312,

320, 330

272003A Rudder Cables (Empennage) - Inspect cables for

deterioration. Inspect cables for fraying, chafing,

cleanliness, turnbuckles safetying, and proper

routing. Inspect pulleys and guard pins for condition,

wear, corrosion, and security of installation.

311, 320

221003 Autopilot Elevator Actuator - Inspect for condition,

security of installation, and evidence of overheating.

312

256001 Emergency Locator Installation - Inspect for security

of installation, position of function switch and

condition of electrical components. Inspect structure

for corrosion.

312

5-12-03 Page 8

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

273002 Elevator Bell Crank (Aft) - Inspect bell crank,

bearings, pushrod, stop bolts, and brackets for

corrosion, evidence of damage, failed fasteners,

and security of installation; proper safetying of bell

crank; and pushrod bolts for proper safetying of nuts

with cotter pins. Refer to Chapter 20, Torque Data

- Maintenance Practices.

320, 330

273009 Elevator Control System - Check pushrod joints for

security of installation, and tightness of fasteners

where applicable. Refer to Chapter 20, Torque Data

- Maintenance Practices.

320, 330

272002 Rudder Bell Crank - Inspect bell crank stop bolts

for corrosion, evidence of damage, and security of

installation. Inspect cables attached to bell crank for

proper cotter pin safetying.

330

334001 Exterior Lights - Inspect electrical components for

condition and security of installation.

330, 501,

503, 575,

601, 603,

675

551001 Vertical and Horizontal Stabilizers - Inspect structure

and attach points for condition and security of

installation. Check for missing or damaged Vortex

generators.

340, 341,

373, 374,

375, 376

551002 Stabilizer Abrasion Boots (if installed) - Check

for nicks, cuts, tears, security of attachment and

evidence of other damage.

340, 371,

372

301004 De-ice Boots (without TKS) - Examine for abrasions,

cuts, nicks, correct installation, and cleanliness.

340, 371,

372, 501,

503, 601,

602

272001 Rudder - Inspect rudder skins for cracks and loose

rivets, rudder hinges for condition, cracks, and

security of installation; hinge bolts, hinge bearings,

hinge attach fitting, and bonding jumper for evidence

of damage or wear, failed fasteners, and security of

installation. Inspect rudder hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weight for looseness and supporting structure for

damage.

343

236001 Static Wicks (Wings and Empennage) - Inspect for

condition and security of installation.

343, 375,

376, 575,

527, 571,

625, 627,

671

273012 Elevator Trim Tab Actuators - Inspect for free play

in actuator. Refer to Chapter 27, Elevator Trim -

Maintenance Practices.

373, 374

5-12-03 Page 9

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MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

301002 De-ice Boot Plumbing (without TKS) - Examine for

condition and correct installation.

373, 374,

501, 503,

601, 602

273001 Elevator - Inspect elevator skins for cracks and

loose rivets; elevator hinges for condition, cracks,

and security; and hinge bolts, hinge bearings, torque

tube, horn, attach fittings, and bonding jumpers for

evidence of damage or wear, failed fasteners, and

security. Inspect elevator hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weights for looseness and supporting structure for

damage. Inspect outboard tips for cracks in rib

flange.

375, 376

273010 Elevator Trim Tabs - Inspect elevator trim tabs. 375, 376

570001 Wings - Inspect for loose fasteners, corrosion,

cracks, wrinkles, dents and attach points for

condition and security of installation.

500's,

600's

570005 Drain Openings and Vent Holes in Bottom of Wing -

Inspect for obstructions.

501, 503,

527, 571,

601, 603,

527, 571

570006 Wing Access Plates - Inspect for security of

installation and evidence of damage.

501, 503,

601, 603

211001 Ram Air - Inspect clamps, hoses, valve, inlet

screens, and ventilation system for condition and

security of installation.

501, 601,

511, 611

273023 Stall Warning System - Inspect for condition and

security of installation.

503

273024 Stall Warning Heater Thermostat - Inspect for

condition and security of installation.

503

334002 Landing/Taxi Lights - Inspect for condition and

security of installation.

503, 603

341001 Static System - Inspect plumbing for security of

installation and evidence of damage.

503, 603

341005 Pitot Tube(s) - Visually check tube(s) and static ports

for obstructions. Inspect mast(s) for bending and

evidence of damage. Ensure sealant at mast-towing joint is in good condition.

503, 603

212001 Ventilating Blower (if installed) - Inspect for security

of installation. Inspect wiring for evidence of damage

and security of installation.

511, 611

282001 Fuel Selector Valves and Linkages (Wing Area)

- Inspect shutoff valves, controls and linkage for

condition, security and evidence of damage. Inspect

all fuel selector valve arms for proper contact with

the off stop pins. Rerig if necessary.

511, 611

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© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

570002 Wing Spar Fittings - Inspect bolts for condition and

security of installation.

511, 611

271013 Spoiler - Inspect spoiler skins for cracks and loose

rivets; hinges for condition, cracks, and security of

installation; pushrods, pushrod bolts, bearings, and

bonding jumpers for evidence of damage or wear,

failed fasteners, and security of installation. Inspect

bolts on both ends of pushrods for proper safetying

of nuts with cotter pins.

521, 621

281001 Fuel Tank Area - Inspect for fuel stain, discoloration,

and evidence of fuel leaks.

521, 621

281003 Fuel Tank Filler Cap(s) and Flapper Valve(s) -

Inspect for damage or broken components and

check lock position of filler cap.

521, 621

281004 Drain Valves - Check operation and inspect for

leakage.

521, 621

271002B Aileron Wing Cables (Wing) - Inspect wing cables for

fraying, chafing, cleanliness, turnbuckle safetying,

and proper routing. Inspect pulleys and guard

pins for condition, wear, corrosion, and security of

installation. Inspect cable for deterioration.

525, 551,

625, 651

275004 Flap Tracks - Inspect flap tracks and rollers

for corrosion, frozen bearings, flat spots, wear,

deformation, and cracks.

525, 625

275001 Flaps - Inspect flaps for loose rivets, cracks,

condition, and security of installation.

527, 627

570003 Wing Strut - Inspect for evidence of damage,

condition and security of installation.

531, 631

570004 Wing Strut Fittings - Inspect bolts for condition and

security of installation.

531, 631

271004 Aileron/Spoiler Bell Crank and Pushrods (Both

Wings) - Inspect aileron bell crank and pushrods

for condition, security of installation, corrosion,

evidence of damage to quadrant arm, stop bolts,

and support bracket. Inspect aileron bell crank

bolt and stop bolts for proper safetying. Inspect

pushrod attach bolts for security of installation and

proper safetying. Refer to Chapter 20, Torque Data

- Maintenance Practices.

551, 651

271010 Aileron Control System - Check pushrod joints for

security of installation, and tightness of fasteners

where applicable. Refer to Chapter 20, Torque Data

- Maintenance Practices.

551, 651

271011 Aileron Slot Lip Spoiler Pushrods - Lubricate.

Refer to Chapter 12, Lubricants - Description and

Operation.

551, 651

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© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

271001 Aileron - Inspect the aileron skins for cracks and

loose rivets; aileron hinges for condition, cracks,

and security of installation; hinge bolts, hinge

bearings, hinge attach fittings, and bonding jumpers

for evidence of damage or wear, failed fasteners,

and security of installation. Inspect the aileron hinge

bolts for proper safetying of nuts with cotter pins.

Inspect balance weights for looseness and their

supporting structure for damage.

571, 671

221016 Flux Detector or Magnetometer - Inspect for security

of installation. Inspect electrical connections and

wire routing for condition and security of installation.

Check for non-magnetic screws in the access cover

and in the mounting brackets.

623

271018B Aileron Trim Tab Cables (Wing) - Inspect cables for

fraying, chafing, cleanliness, turnbuckle safetying,

and proper routing. Inspect chains for proper

safetying at all points and chains for proper

alignment on sprockets. Inspect pulleys and guard

pins for condition, wear, corrosion, and security of

installation.

625, 651

271015 Aileron Trim Tab Actuator - Inspect actuator for

security of installation and evidence of damage and

wear. Inspect structure for evidence of damage,

cracks, and security of installation. If torque putty is

broken, retorque mounting bolts. Inspect actuator

rods for evidence of bending. Inspect pushrod bolts

at actuator for proper safetying of nut with cotter pin.

Inspect pushrod ends for bearing looseness and

excessive wear.

651

271016 Aileron Trim Tab Actuator - Inspect for free play in

actuator. Refer to Chapter 27, Aileron Trim System

- Maintenance Practices.

651

271017 Aileron Trim Tab Actuator Pushrods - Inspect for free

play in actuator, condition and evidence of damage.

Inspect attaching hardware for wear and security of

installation.

651

271014 Aileron Trim Tab - Inspect the trim tab skins for

cracks, loose rivets, and security of installation; and

trim tab hinge for cracks, security of installation, and

evidence of damage. Inspect hinge pin for proper

installation at hinge pin retainer. Inspect horn and

pushrod for evidence of damage and security of

installation. Inspect pushrod bolts for condition and

proper safetying of nuts with cotter pins.

671

271020 Aileron Trim Tab Cable Stop Blocks (Right Wing) -

Inspect for condition and security of installation.

671

5-12-03 Page 12

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

322002 Nose Gear Torque Links and Shock Strut - Inspect

for condition, wear at attach points and security

of installation, then service. Refer to Chapter 12,

Lubricants - Description and Operation.

701

322005 Nose Gear Spring Yoke - Inspect bearing for

corrosion and freedom of rotation. Lubricate

bearing. Refer to Chapter 12, Lubricants -

Description and Operation. Reinstall bolt and torque

and safety wire. Refer to Chapter 32, Nose Landing

Gear - Maintenance Practices.

701

322006 Nose Gear Drag Link Spring Supports - Examine

for cracks, wear, loose bolts, elongated holes, and

corrosion.

701

324003 Nose Landing Gear Wheel and Tire - Check for wear,

pressure and condition. Refer to Chapter 12, Tires -

Servicing.

701

325001 Nose Landing Gear Shimmy Damper - Inspect for

condition and security of installation.

701

325002 Nose Landing Gear Shimmy Damper - Check for

need to service. Refer to Chapter 32, Landing Gear

- General.

701

325006 Nose Landing Gear Steering Stop Bolt or Block -

Inspect for condition, security of installation with bolt

head down.

701

324002A Landing Gear Wheel Bearings (Airplanes 20800001

thru 20800201 and 208B0001 thru 208B0255 Not

Incorporating CAB 91-30) - Inspect for condition

and repack. Refer to Chapter 12, Lubricants -

Description and Operation.

701, 721,

722

324001 Main Landing Gear Wheels and Tires - Check

for wear, pressure and condition. Rotate tires as

necessary to achieve uniform tire wear. Refer to

Chapter 12, Tires - Servicing.

721, 722

324004 Brake Assemblies - Inspect for wear of linings, disc

warpage and evidence of leakage.

721, 722

112001 Interior Placards, Exterior Placards, Decals,

Markings and Identification Plate - Inspect for

security of installation and legibility. Refer to Chapter

11, Placards and Markings - Inspection/Check.

ALL

530001 Corrosion Prevention and Corrosion Program

Inspections - Use the age of the airplane for the

initial inspection. The initial and repeat intervals are

found in Chapter 5, 5-30-01 or 5-30-02, Corrosion

Prevention and Corrosion Program Inspections,

Table 1.

ALL

212005 Avionics Cooling Fan - Turn Battery and Avionics

Power switch No. 2 ON and check for cooling fan

operation.

BAT

5-12-03 Page 13

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

256002 Emergency Locator Transmitter - Perform

operational test. Check cumulative time and useful

life of batteries in accordance with FAR 91.207.

BAT

262001 Engine Fire Detection - Perform engine fire detection

test.

BAT

341006 Pitot Tube(s) Heater - Place the PITOT/STATIC heat

switch to ON for approximately 30 seconds, then to

OFF. Verify tube(s) heats.

BAT

762001 Emergency Power Lever Annunciator Light -

Perform operational test.

BAT

214003 Cabin Heater and Windshield Defroster - Perform

operational check.

ENG

242005 Standby Electrical System (Engine Running) -

Perform functional test. Refer to Section 9 of the

Pilot's Operating Handbook.

ENG

243005 Volt/Ammeter (Engine Running) - Perform

operational check of each position.

ENG

244002 External Power - Perform operational check of the

BUS and STARTER functions.

ENG

273025 Stall Warning Horn - Perform an operational check. ENG

273026 Stall Warning Heater - Perform an operational check. ENG

284001 Reservoir Fuel Low Annunciator (Engine Running) -

Position both fuel selectors to OFF. Verify Reservoir

Low warning light illuminates as the fuel level in the

reservoir tank drops below full, then place both fuel

tank selectors to ON.

ENG

284002 Fuel Selectors OFF Warning System - Perform

operational check of warning system.

ENG

301005 Wing De-ice System (Engine Running) (without

TKS) - Do a check of the wing de-ice system.

ENG

306003 Propeller Anti-ice System (Engine Running) (without

TKS) - Do a check of the propeller anti-ice system.

ENG

371007 Suction Gauge (Engine Running) - Verify operation. ENG

612004 Propeller Governor (Engine Running) - Perform an

operational check.

ENG

622004 Propeller Governor (Engine Running) - Perform

operational check.

ENG

761003 Power Lever Reverse Speed Pickup (Engine

Running) - Check power lever reverse speed pickup.

ENG

5-12-03 Page 14

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

761006 Engine Idle Check (Engine Running) - Perform

engine idle check.

ENG

243006 NI-CAD Battery (if installed) - Perform capacity

check. Check terminals for overheating or burning.

LAB

*** End of Operation 3 Inspection Items ***

5-12-03 Page 15

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 4

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 4 consists of all 100 hour interval inspection items and those 200 or 400 hour interval

inspection items contained in the engine, wing, empennage, gear and fuselage areas. 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. A

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

306002 Propeller Anti-ice Brushes (without TKS) - Examine

each brush for wear, signs of damage, cleanliness,

correct installation and correct rigging. Examine

electrical wires for condition and correct installation.

110

611001 Propeller Spinner (Hartzell and McCauley) -

Remove, wash, inspect for cracks, fractures,

condition and security of installation.

110

611002 Hartzell Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

611003 Hartzell Propeller Blades - Wash, check for nicks,

gouges, scratches, leading edge looseness,

depressions, delaminating, cracks, condition and

security of installation. Inspect clamps for security

of installation.

110

611004 Hartzell Propeller Blades - Check alignment and

freedom of movement.

110

5-12-04 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

611005 Hartzell Propeller Hub (Exposed Area) - Inspect for

cracks, wear, condition, and security of components

to hub.

110

611006 Hartzell Propeller - Inspect for oil and grease leaks. 110

611007 Hartzell Propeller Mounting - Visually check for

security of installation.

110

611008 Hartzell Propeller Blade Clamps - Lubricate and

check for security of installation. Refer to Chapter

12, Lubricants - Description and Operation, and

Chapter 61, Propeller (Hartzell) - Description and

Operation.

110

621002 McCauley Spinner Bulkhead - Inspect for cracks,

condition and security of installation.

110

621003 McCauley Propeller Blades - Wash, check for nicks,

gouges, scratches corrosion and cracks.

110

621005 McCauley Propeller Hub (Exposed Area) - Inspect

for cracks, wear, condition, and security of

components to hub.

110

621006 McCauley Propeller - Inspect for oil leaks. 110

621007 McCauley Propeller Mounting - Visually check for

security of installation.

110

720005 Engine Propeller Shaft Seal - Inspect for leaks and

security of installation.

110

301101 100 Hour Operational Check (with TKS) - Visually

check for wear and security of installation at the

propeller boots, propeller nozzle, propeller feed

tubes, and propeller slinger. Check operation of

pumps, pump CAS annunciator (G1000), press test

TKS annunciator (non-G1000), fluid flow of slinger

and leading edge panels.

110, 220,

221, 240,

340, 373,

374, 527,

531, 571,

627, 631,

671, 903,

904

612002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

622002 Propeller Governor and Overspeed Governor -

Inspect for oil leaks, condition and security of

installation.

121

716001 Induction System and Inertial Separator - Inspect

for general condition, security, and freedom of

operation. Inspect door pivot point bearings for

excessive wear. Check separator linkage for proper

operation. Check for loose rivets.

121

716002 Inertial Separator - Unlock control and pull into

bypass. Check for freedom of movement and for full

opening of the bypass door in the air duct.

121

5-12-04 Page 2

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

716005 Inertial Separator - Perform rivet inspection. Refer to

Chapter 71, Inertial Separator Forward and Aft Vane

Rivet Inspection - Inspection/Check.

121

790004 Oil Filter - Remove, clean and inspect for damage.

Filter may be electrosonically cleaned if desired.

121

261001 Fire Detection Control Unit - Inspect for condition and

security of installation.

121, 122

261002 Heat Detection Loop - Inspect the three loop

sections for condition, security of installation and

evidence of damage, paying special attention to the

loop connection fittings.

121, 122

731001 Fuel Lines - Inspect fuel supply and fuel motive

flow lines for deterioration, chafing, fuel leaks, and

security of installation.

121, 122

731006 Fuel Manifold - Inspect for security of installation and

evidence of fuel leaks.

121, 122

731010 Flow Divider - Inspect for security of installation and

evidence of fuel leaks.

121, 122

741003 Igniters - Inspect for wear, corrosion, and condition

of insulator. Clean insulator at lead attachment, but

do not clean igniter end.

121, 122

741005 Igniters - Perform operational check by placing

ignition switch in the ON position (battery switch on).

Verify IGNITION ON annunciator illuminates.

121, 122

793002 Chip Detectors without Annunciator Light - Inspect. 121, 122

243001 Battery Cable Disconnect and Cables - Inspect

for condition, corrosion and security of installation.

Inspect battery terminal receptacles for overheating

or burning.

122

243007 Battery Tray - Inspect for condition, corrosion and

security of installation. Inspect latching mechanism

for proper operation.

122

243009 Gill Flooded Lead Acid Battery (if installed) - Check

general condition and security of installation. Check

level of electrolyte. Check terminals for overheating

or burning.

122

243010 Gill Lead Acid Only Battery Box - Inspect for

corrosion, condition and security of installation.

122

243011 Battery Vent Tubes - Inspect for condition,

obstructions and security of installation.

122

243014 Concord Sealed Lead Acid Battery (if installed) -

Check general condition and security of installation.

Check terminals for overheating or burning. Perform

checks in accordance with servicing placard on the

side of battery.

122

5-12-04 Page 3

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

301007 Bleed Air Pressure Regulator (Airplanes 20800001

thru 20800221 and 208B0001 thru 208B0316 Not

Incorporating SK208-112) (without TKS) - Do a

discharge pressure check. Refer to Chapter 36,

Pneumatic Distribution - Maintenance Practices.

122

723001 P3 Filter - Inspect P3 filter for general condition and

clean.

122

731004 Engine Fuel Pump - Inspect for security of

installation and fuel leaks. Inspect overboard drain

line for security of installation and condition.

122

732001 Fuel Control - Inspect for security of installation and

fuel leaks.

122

732002 Fuel Control - Check for FCU bearing washout

indicated by blue dye (grease and fuel mixed) at

FCU overboard vent.

122

733001 Fuel Flow Transducer - Inspect for security of

installation, fuel leaks, and evidence of damage.

122

733002 Fuel Totalizer Signal Conditioner (if installed) -

Inspect for security of installation wiring connector

for security, and evidence of damage.

122

761001 Engine Controls - Check for freedom of operation.

Inspect for security of installation, wear, corrosion,

routing, evidence of damage, and deterioration.

Check rubber seals for deterioration.

122

761002 Control Linkages and Attach Brackets - Inspect

for security of installation, wear, corrosion, general

condition, and freedom of movement.

122

790003 Oil Filler Cap and Dipstick - Inspect for condition and

security of installation.

122

215002 Compressor Belt (Vapor Cycle Cooling System) -

Inspect for wear, alignment and tension.

130

717002 Drain Openings and Vent Holes in Bottom of Engine

Cowling - Inspect for obstructions.

130

781001 Engine Exhaust System - Inspect primary and

secondary ducts for cracks, distortion, security of

installation, and evidence of damage.

130

282006 Firewall Mounted Fuel Filter with Bypass Flag (Red

Warning Button) - Clean, inspect for leaks, security

of installation and condition.

151

282007 EPA Can - Inspect for leakage, security of installation

and condition. Drain completely.

151

324005 Brake System Reservoir - Inspect for security of

installation, condition and leaks. Check fluid level.

Refer to Chapter 12, Hydraulic Fluid - Servicing.

151

5-12-04 Page 4

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

793004 Oil Pressure Indicator Plumbing (Engine to Firewall)

- Inspect for security of installation, condition,

leakage and evidence of damage.

151

371003 Vacuum Relief Valve Filter - Replace urethane

filter element. Filter may be replaced more often if

conditions require. Refer to Chapter 12, Vacuum

System Central Air Filter - Servicing.

201

371004 Vacuum System Central Air Filter - Inspect for

damage, deterioration and contamination. Replace

filter, if required. Refer to Chapter 12, Vacuum

System Central Air Filter - Servicing.

201

371005 Vacuum System Relief Valve - Inspect for condition

and security of installation.

201

793003 Oil Pressure Switch and Fitting (Aft Side of Firewall)

- Inspect for security of installation, condition and

leakage.

201

371002 Vacuum System Hoses - Inspect for hardness,

deterioration, looseness or collapsed hoses.

201, 202

282003 Fuel Shutoff Valve - Inspect linkage and valve for

evidence of damage and operation. Inspect valve

for leakage.

203

324007 Parking Brake Control and Valve - Inspect for

condition, leakage, security of installation, as well

as freedom and correct operation.

203

272004 Rudder Pedals and Rudder Pedal Linkage - Inspect

for condition and security. Operate rudder controls

and check for freedom of movement.

211, 212

531001 Fuselage Structure - Inspect skin structure and

fasteners for condition and security of installation.

211, 212,

215, 216,

231, 232,

251, 252,

255, 256,

257, 258,

311, 312

273003 Elevator Bell Crank (Forward) - Inspect bell crank,

bearings, pushrod, stop bolts, and brackets for

corrosion, evidence of damage, failed fasteners,

and security of installation; proper safetying of bell

crank; and pushrod bolts for proper safetying of nuts

with cotter pins. Refer to Chapter 20, Torque Data

- Maintenance Practices.

213, 214

273004 Elevator Cables (Tailcone) - Inspect cables for

fraying, chafing, cleanliness, turnbuckle safetying,

and proper routing. Inspect pulleys and guard

pins for condition, wear, corrosion, and security of

installation.

213, 217,

233, 253,

257

5-12-04 Page 5

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

243003 Alternator and Generator Control Units - Inspect

security of mounting. Inspect wiring for condition

and routing.

215

245001 Side Consoles, Circuit Breaker Panels, Terminal

Blocks and Junction Boxes - Inspect wiring and

terminals for condition and security of installation.

215

245002 Switches - Check operation, terminals, wiring and

mounting for condition, security of installation and

interference.

215

304002 Windshield Anti-ice System (without TKS) - Do a

check of the condition and mounting of controller and

relay.

215

271006 Control Wheel - Inspect control wheel for condition

and security of installation. Operate control wheel

and check for freedom of movement.

215, 216

341003 Alternate Static Source - Inspect for evidence of

damage and security of installation.

215, 216

341007 Static System Drain Valves - Visually inspect for

leaks, and presence of water in drain fittings.

Drain accumulated moisture. Inspect condition and

security of installation.

215, 216

271005 Fuselage and Control Column Aileron Cables -

Inspect cables for fraying, chafing, cleanliness,

turnbuckle safetying, and proper routing. Inspect

pulleys and guard pins for condition, wear, corrosion,

and security of installation.

215, 216,

231, 232

221017 Autopilot Computer Amplifier, Mount, Mounting

Knob and Electrical Components (Model 208 Only)

- Inspect for security of installation.

216

243004 Volt/Ammeter and Selector Switch - Inspect for

security of installation.

220

330002 Instrument Panel Lights - Perform operational check. 220, 221,

222, 223,

224

240002 Instrument Panel and Control Pedestal - Inspect

wiring, mounting and terminals for condition and

security of installation.

220, 221,

222, 223,

224, 225,

226

221019 Autopilot Mode Controller, Mode Annunciator,

Slaving Accessory and Compensator Unit, Autopilot

Control Wheel Switch Cap and Power Lever

Go-Around Button (Model 208 & 208B) (if installed)

- Check for security of installation and switches for

proper operation.

220, 222,

223, 226

212004 Instrument Panel Ventilation Air Outlets and Controls

- Inspect doors, cables and controls for condition and

operation.

220, 224

5-12-04 Page 6

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

793007 Engine Oil Temperature and Pressure Indicator -

Inspect for security of installation.

221

341009 Overspeed Pressure Switch and Icing Low Airspeed

Awareness System (110 KIAS) Switch (if installed) -

Examine for condition and correct installation.

222

371006 Low Vacuum Warning Switch - Inspect for condition

and security of installation.

222

761004 Inertial Separator Control - Inspect handle and shaft

for condition and evidence of damage.

222

230005 Microphones, Headsets, and Jacks - Inspect for

cleanliness, security of installation and evidence of

damage.

222, 224,

226

221014 King Flight Control System (KFC-150) - Check

for security of installation and switches for proper

operation.

223

221015 King Flight Control System (KFC-250) - Check

for security of installation and switches for proper

operation.

223

221020 King Flight Control System (KFC-225) - Check

for security of installation and switches for proper

operation.

223

221023 Garmin Autopilot (GFC 700) Switches - Examine

the Autopilot Control Wheel Switch Cap and Power

Lever Go-Around Button for correct installation and

operation.

223

230001 Instrument Panel Mounted Avionics Units (including

Audio Panel, VHF Nav/Com(s), ADF, Transponder,

DME, Compass System, RMI, Radar Altimeter,

Weather Radar, and Garmin G1000 system ) -

Inspect for deterioration, cracks, and security of

instrument panel mounts. Inspect for security of

electrical connections, condition, and security of

wire routing.

223

230002 Avionic Operating Controls - Inspect for security

of installation and proper operation of controls

and switches and ensure that all digital segments

illuminate properly.

223

273006 Control Column - Inspect control column for

evidence of damage, failed fasteners, and security

of installation. Operate control column and check

for freedom of movement.

223, 224

271021 Aileron Trim Tab Control and Indicator - Inspect

control and indicator for condition and security of

installation. Operate trim tab control and check

aileron trim tab for freedom of movement. Inspect

guide block for condition and security of installation.

226

5-12-04 Page 7

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

272009 Rudder Trim Flex Shaft - Inspect for deterioration

and condition of coupling and roll pins and safe wire.

226

272010 Rudder Trim Wheel and Indicator - Inspect trim

wheel and indicator for condition and security of

installation. Operate trim wheel and check rudder

trim for freedom of movement.

226

273017 Elevator Trim Tab Control and Indicator - Inspect

control and indicator for condition and security of

installation. Operate trim tab control and check for

freedom of movement.

226

273020 Electric Elevator Trim Actuator - Inspect actuator

motor for condition, security of installation, and

evidence of overheating. Inspect chain for tension

and proper alignment, actuator for condition, wear,

corrosion, and security of installation.

226

275002 Primary Flap System - Operate flaps with flap control

lever, located in control pedestal, through full range

of travel and observe flaps for erratic motion, binding,

and interference.

226

275005 Flap Control System - Inspect flap control lever

and pointer for security of installation, travel, and

evidence of damage. Inspect flap control and flap

follow-up cables for deterioration and security of

installation.

226

282004 Fuel Shutoff Control - Operational check. 226

531002 Control Pedestal - Inspect for condition and security

of installation.

226

531003 Control Quadrant - Inspect for condition and security

of installation.

226

231001 Control Wheel Pushbutton Switches - Clean the

transponder identification switch, microphone

switch, and the interphone switch on the pilot's

and copilot's control wheel. Refer to Chapter 23,

Communication - Maintenance Practices.

227, 228

308001 Ice Detector Light - Inspect for condition and security

of installation.

231

251001 Pilot's and Copilot's Inertia Reels, Seat Belts

and Shoulder Harnesses - Inspect for security of

installation, frayed edges and evidence of damage

and proper operation.

231, 232

251002 Pilot's and Copilot's Seats - Inspect seat brackets,

guides, stops, seat structure and seat cushions for

condition and security of installation; and controls

for condition, security of installation and proper

operation. Service seat adjusting screws, bearings

and locking mechanisms.

231, 232

5-12-04 Page 8

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

251003 Warning Horns Installation - Inspect stall warning,

fuel selector warning horns, airspeed warning,

radar altimeter and fire detection warning horns for

security of installation and evidence of damage.

Inspect grill cover for condition and security of

installation.

231, 232

251005 Pilot's and Copilot's Seat Back Stop Bolts - Inspect

for loose or missing nuts.

231, 232

262002 Portable Hand Fire Extinguisher - Inspect for proper

operating pressure, condition, and security of

installation. Check servicing date.

231, 232

330001 Flight Compartment Lights - Inspect electrical

components for condition and security of installation.

231, 232

351001 Oxygen Masks and Hose Assemblies - Inspect

for condition and clean. Inspect hose connection

for security of installation and hose for condition.

Perform operational check of pilot's mask

microphone.

231, 232

351002 Oxygen Masks - Perform operational test on the

oxygen masks. Inspect flow indicator for freedom of

movement.

231, 232

351003 Smoke Goggles (if installed) - Check for condition of

goggles and security of storage bag to barrier.

231, 232

212003 Ventilation Outlets (Cabin Overhead) - Inspect for

security of installation, condition and operation.

231, 232,

251, 252,

255, 256

252003 Floor Covering - Inspect for condition, security of

installation and cleanliness.

231, 232,

251, 252,

255, 256

332002 Interior Lighting - Check operation of cabin,

passenger reading, no smoking/seatbelt, and control

wheel map lighting.

231, 232,

251, 252,

255, 256

282005 Fuel Line Connector Covers and Drains - Inspect

covers and drain lines for condition and security of

installation.

233, 234

532001 Center Section Drain Holes - Inspect for obstruction

and remove any foreign material from holes to

prevent blockage.

233, 234,

253, 254,

257, 258

251004 Relief Tube (if installed) - Inspect for condition,

security of installation, cleanliness and corrosion.

233, 234,

256, 258

272003B Rudder Cables (Fuselage) - Inspect cables for

deterioration. Inspect cables for fraying, chafing,

cleanliness, turnbuckles safetying, and proper

routing. Inspect pulleys and guard pins for condition,

wear, corrosion, and security of installation.

233, 253,

257

5-12-04 Page 9

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

221002 Autopilot Aileron Actuator - Inspect for condition,

security of installation, and evidence of overheating.

234

304001 Windshield Anti-ice System (without TKS) - Examine

for condition, correct installation and electrical wiring

of heated panel. Do a check of the condition of

storage bag.

240

271002A Aileron Wing Cables (Fuselage) - Inspect wing

cables for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect pulleys

and guard pins for condition, wear, corrosion,

and security of installation. Inspect cable for

deterioration.

240, 243

561001 Windows and Windshield - Inspect for condition and

security of installation. Check pilot's foul weather

window for proper latching and sealing.

240, 251,

252, 255,

256, 801,

802

275003 Standby Flap System - Perform standby flap motor

operational check. Refer to Chapter 27, Flap System

- Maintenance Practices.

243

282002 Fuel Selector Linkages (Cabin Area) - Inspect

linkage and controls for condition, security and

evidence of damage.

243

284003 Fuel Selector OFF Warning System - Inspect

relays, switches, connectors and electrical wiring for

condition and security of installation.

243

350003 Oxygen Control System - Inspect control handle and

pressure regulator for condition and operation.

243

255007 Cargo Pod Fuel Reservoir Remote Drain (if installed)

- Check drain for proper operation and evidence of

leakage from drain tube outlet.

244

281002 Fuel Reservoir Tank - Check plumbing and external

components to reservoir tank for condition, security

of installation, and evidence of leakage.

244

281005 Fuel Reservoir and Fuel Tanks - Check auxiliary fuel

pump, ejector pump, swing check valves, and fuel

shutoff valve screens for damage and security of

installation.

244

255009 Cargo Nets and Barrier (if installed) - Check for

condition, security of attachment and operation of

adjustment devices.

251, 252

271003 Aileron Bell Cranks (Above Headliner) - Inspect

bell cranks for security of installation, cleanliness,

corrosion, evidence of damage to cable guard and

cable attach points. Inspect attach bolts for security

of installation and proper safetying of nuts.

251, 252

5-12-04 Page 10

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

252001 Seat Tracks - Inspect seat tracks and stops for

condition and security of installation. Inspect

seat track stops for proper location, security of

installation.

251, 252,

255, 256

252002 Interior Furnishings - Inspect for condition

and security of installation. Inspect electrical

components in accordance with electrical power

inspection.

251, 252,

255, 256

255001 Cargo Tie-Down Straps and Fittings (if installed)

- Inspect for condition, security of installation and

proper installations.

251, 252,

255, 256

332001 Passenger and Cargo Compartment Lights - Inspect

electrical components for condition, operation, and

security of installation.

251, 252,

255, 256

215001 Vapor Cycle Cooling System - Inspect evaporator

and condenser air inlets for obstruction and debris.

Inspect system for evidence of damage, indication of

leaks and mountings for security of installation.

251, 311

275008 Flap Switch Actuator - Inspect flap switch actuator

switches, support structure, and associated linkage

for condition and security of installation.

252

230003 Remote Mounted Avionics (Fuselage) - Inspect for

security of units and electrical connectors, condition

and security of wire routing. Also check for evidence

of damage and cleanliness.

311, 312

531004 Tailcone Drain Opening - Inspect for obstruction and

remove any foreign material from opening to prevent

blockage.

311, 312

273015 Elevator Trim Tab Cables (Tailcone) - Inspect

cables for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect chains for

proper safetying at all points and chains for proper

alignment on sprockets. Inspect pulleys and guard

pins for condition, wear, corrosion, and security of

installation.

311, 320

221004 Autopilot Actuator (Elevator) - Inspect bridal

cables for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect chain

for proper safetying at all points and chains for

proper alignment with actuators sprockets. Inspect

pulleys, drive sprockets, drive chain, and guard

pins for condition, wear, corrosion, and security

of installation. Inspect electrical components for

operation, condition, and security of installation.

312

256001 Emergency Locator Installation - Inspect for security

of installation, position of function switch and

condition of electrical components. Inspect structure

for corrosion.

312

5-12-04 Page 11

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

272007 Rudder Gust Lock (Airplanes 20800030 thru

20800236 and 208B0001 thru 208B0381) (if

installed) - Inspect for condition, security of

installation, and positive locking action.

320

272011 Rudder Gust Lock (Airplanes 20800237 and On and

208B0382 and On) - Inspect in accordance with

AERO TWIN STC airworthiness requirements.

320

272001 Rudder - Inspect rudder skins for cracks and loose

rivets, rudder hinges for condition, cracks, and

security of installation; hinge bolts, hinge bearings,

hinge attach fitting, and bonding jumper for evidence

of damage or wear, failed fasteners, and security of

installation. Inspect rudder hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weight for looseness and supporting structure for

damage.

343

273011 Elevator Trim Tab Actuators - Inspect actuator for

security of installation and evidence of damage; and

mounting structure for evidence of damage, cracks

and security of installation at the rear spar of the

horizontal stabilizer.

373, 374

273001 Elevator - Inspect elevator skins for cracks and

loose rivets; elevator hinges for condition, cracks,

and security; and hinge bolts, hinge bearings, torque

tube, horn, attach fittings, and bonding jumpers for

evidence of damage or wear, failed fasteners, and

security. Inspect elevator hinge bolts for proper

safetying of nuts with cotter pins. Inspect balance

weights for looseness and supporting structure for

damage. Inspect outboard tips for cracks in rib

flange.

375, 376

273010 Elevator Trim Tabs - Inspect elevator trim tabs. 375, 376

273013 Elevator Trim Tab Actuator Pushrods - Inspect

for condition and evidence of damage. Inspect

attaching hardware for wear and security of

installation.

375, 376

570006 Wing Access Plates - Inspect for security of

installation and evidence of damage.

501, 503,

601, 603

341005 Pitot Tube(s) - Visually check tube(s) and static ports

for obstructions. Inspect mast(s) for bending and

evidence of damage. Ensure sealant at mast-towing joint is in good condition.

503, 603

282001 Fuel Selector Valves and Linkages (Wing Area)

- Inspect shutoff valves, controls and linkage for

condition, security and evidence of damage. Inspect

all fuel selector valve arms for proper contact with

the off stop pins. Rerig if necessary.

511, 611

281001 Fuel Tank Area - Inspect for fuel stain, discoloration,

and evidence of fuel leaks.

521, 621

5-12-04 Page 12

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

281003 Fuel Tank Filler Cap(s) and Flapper Valve(s) -

Inspect for damage or broken components and

check lock position of filler cap.

521, 621

281004 Drain Valves - Check operation and inspect for

leakage.

521, 621

275001 Flaps - Inspect flaps for loose rivets, cracks,

condition, and security of installation.

527, 627

271001 Aileron - Inspect the aileron skins for cracks and

loose rivets; aileron hinges for condition, cracks,

and security of installation; hinge bolts, hinge

bearings, hinge attach fittings, and bonding jumpers

for evidence of damage or wear, failed fasteners,

and security of installation. Inspect the aileron hinge

bolts for proper safetying of nuts with cotter pins.

Inspect balance weights for looseness and their

supporting structure for damage.

571, 671

282008 Fuel Float Vent Line - Inspect for evidence of

damage, cleanliness, and obstruction.

575, 675

271018A Aileron Trim Tab Cables (Fuselage) - Inspect

cables for fraying, chafing, cleanliness, turnbuckle

safetying, and proper routing. Inspect chains for

proper safetying at all points and chains for proper

alignment on sprockets. Inspect pulleys and guard

pins for condition, wear, corrosion, and security of

installation.

625

271014 Aileron Trim Tab - Inspect the trim tab skins for

cracks, loose rivets, and security of installation; and

trim tab hinge for cracks, security of installation, and

evidence of damage. Inspect hinge pin for proper

installation at hinge pin retainer. Inspect horn and

pushrod for evidence of damage and security of

installation. Inspect pushrod bolts for condition and

proper safetying of nuts with cotter pins.

671

322002 Nose Gear Torque Links and Shock Strut - Inspect

for condition, wear at attach points and security

of installation, then service. Refer to Chapter 12,

Lubricants - Description and Operation.

701

322005 Nose Gear Spring Yoke - Inspect bearing for

corrosion and freedom of rotation. Lubricate

bearing. Refer to Chapter 12, Lubricants -

Description and Operation. Reinstall bolt and torque

and safety wire. Refer to Chapter 32, Nose Landing

Gear - Maintenance Practices.

701

322006 Nose Gear Drag Link Spring Supports - Examine

for cracks, wear, loose bolts, elongated holes, and

corrosion.

701

324003 Nose Landing Gear Wheel and Tire - Check for wear,

pressure and condition. Refer to Chapter 12, Tires -

Servicing.

701

5-12-04 Page 13

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

325001 Nose Landing Gear Shimmy Damper - Inspect for

condition and security of installation.

701

325002 Nose Landing Gear Shimmy Damper - Check for

need to service. Refer to Chapter 32, Landing Gear

- General.

701

325006 Nose Landing Gear Steering Stop Bolt or Block -

Inspect for condition, security of installation with bolt

head down.

701

324002A Landing Gear Wheel Bearings (Airplanes 20800001

thru 20800201 and 208B0001 thru 208B0255 Not

Incorporating CAB 91-30) - Inspect for condition

and repack. Refer to Chapter 12, Lubricants -

Description and Operation.

701, 721,

722

324002B Landing Gear Wheel Bearings (Airplanes 20800202

and On and 208B0256 and On, and Airplanes

20800001 thru 20800201 and 208B0001 thru

208B0255 Incorporating CAB 91-30) - Inspect

for condition and repack. Refer to Chapter 12,

Lubricants - Description and Operation.

701, 721,

722

324001 Main Landing Gear Wheels and Tires - Check

for wear, pressure and condition. Rotate tires as

necessary to achieve uniform tire wear. Refer to

Chapter 12, Tires - Servicing.

721, 722

324004 Brake Assemblies - Inspect for wear of linings, disc

warpage and evidence of leakage.

721, 722

520105 Crew Doors Latch Pin Receptacle - Inspect for

damage, cracks and wear.

801, 802

520106 Crew Doors Hinges, Latch Pin and Stop Assembly -

Service.

801, 802

521001 Pilot and Copilot Crew Doors - Inspect for condition,

security of installation and operation.

801, 802

521002 Crew Doors Seal - Inspect for proper installation,

cuts, abrasions and excessive wear. Clean.

801, 802

521003 Crew Doors Latch Pin - Inspect for damage, cracks,

wear and rigging.

801, 802

521004 Crew Doors Latch Pin Guide - Inspect for damage,

cracks and wear.

801, 802

521008 Crew Door Entrance Steps - Inspect for condition,

security of installation and folding operation. Clean.

801, 802

521009 Crew Door Locks - Check proper operation of

locking mechanisms including the external key lock

operation.

801, 802

523001 Cargo Upper and Lower Doors - Inspect for

condition, security of installation and operation.

Inspect hinges, latches and latch pins for damage,

cracks, wear, alignment and adjustment.

803

5-12-04 Page 14

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

523002 Cargo Upper and Lower Door Seals - Inspect for

proper installation, cuts, abrasions and excessive

wear. Clean and service.

803

521007 Passenger Doors - Inspect for condition, security of

installation and operation. Inspect hinges, latches,

steps, cables and latch pins for damage, cracks,

wear, alignment, fraying and adjustment.

804

521010 Passenger Doors Seals - Inspect for proper

installation, cuts, abrasions and excessive wear.

Clean.

804

255004 Cargo Pod Drain Tubes (if installed) - Inspect

cargo pod drain tubes for obstruction, condition and

security of installation.

901, 902,

903, 904

255003 Cargo Pod (if installed) - Inspect structure for

condition and security of installation. Check

condition of sealant at fuselage and evidence of

internal leakage.

901, 902,

903, 904,

905, 906,

907, 908

255005 Cargo Pod Doors (if installed) - Inspect door

structure for condition, cracked or debonded

laminate. Check rubber door seals for condition and

proper attachment.

921, 922,

923, 924

255006 Cargo Pod Door Hinges and Latches (if installed) -

Inspect for evidence of damage, wear, security of

installation, and loose or failed fasteners.

921, 922,

923, 924

255008 Cargo Pod Doors (if installed) - Check legibility of

weight limitations placards.

921, 922,

923, 924

112001 Interior Placards, Exterior Placards, Decals,

Markings and Identification Plate - Inspect for

security of installation and legibility. Refer to Chapter

11, Placards and Markings - Inspection/Check.

ALL

240001 General Airplane and System Wiring - Inspect

for chafing, broken or loose terminals, general

condition, broken or inadequate clamps, and sharp

bends in wiring.

ALL

530001 Corrosion Prevention and Corrosion Program

Inspections - Use the age of the airplane for the

initial inspection. The initial and repeat intervals are

found in Chapter 5, 5-30-01 or 5-30-02, Corrosion

Prevention and Corrosion Program Inspections,

Table 1.

ALL

304003 Windshield Anti-ice System (without TKS) - Do

an operational check of the AUTO and MANUAL

systems. Make sure that the WINDSHIELD

ANTI-ICE annunciator light comes on.

AUX

212005 Avionics Cooling Fan - Turn Battery and Avionics

Power switch No. 2 ON and check for cooling fan

operation.

BAT

5-12-04 Page 15

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

256002 Emergency Locator Transmitter - Perform

operational test. Check cumulative time and useful

life of batteries in accordance with FAR 91.207.

BAT

262001 Engine Fire Detection - Perform engine fire detection

test.

BAT

332003 Courtesy/Cargo Light Timer - Perform operational

check.

BAT

341006 Pitot Tube(s) Heater - Place the PITOT/STATIC heat

switch to ON for approximately 30 seconds, then to

OFF. Verify tube(s) heats.

BAT

527001 Door Warning Annunciator Light - Open upper cargo

door and verify that light illuminates, then close door.

Open upper passenger door (if applicable) and verify

that light illuminates.

BAT

762001 Emergency Power Lever Annunciator Light -

Perform operational test.

BAT

214003 Cabin Heater and Windshield Defroster - Perform

operational check.

ENG

242005 Standby Electrical System (Engine Running) -

Perform functional test. Refer to Section 9 of the

Pilot's Operating Handbook.

ENG

243005 Volt/Ammeter (Engine Running) - Perform

operational check of each position.

ENG

244002 External Power - Perform operational check of the

BUS and STARTER functions.

ENG

273025 Stall Warning Horn - Perform an operational check. ENG

273026 Stall Warning Heater - Perform an operational check. ENG

284001 Reservoir Fuel Low Annunciator (Engine Running) -

Position both fuel selectors to OFF. Verify Reservoir

Low warning light illuminates as the fuel level in the

reservoir tank drops below full, then place both fuel

tank selectors to ON.

ENG

284002 Fuel Selectors OFF Warning System - Perform

operational check of warning system.

ENG

301005 Wing De-ice System (Engine Running) (without

TKS) - Do a check of the wing de-ice system.

ENG

306003 Propeller Anti-ice System (Engine Running) (without

TKS) - Do a check of the propeller anti-ice system.

ENG

371007 Suction Gauge (Engine Running) - Verify operation. ENG

612004 Propeller Governor (Engine Running) - Perform an

operational check.

ENG

622004 Propeller Governor (Engine Running) - Perform

operational check.

ENG

5-12-04 Page 16

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

761003 Power Lever Reverse Speed Pickup (Engine

Running) - Check power lever reverse speed pickup.

ENG

761006 Engine Idle Check (Engine Running) - Perform

engine idle check.

ENG

243006 NI-CAD Battery (if installed) - Perform capacity

check. Check terminals for overheating or burning.

LAB

*** End of Operation 4 Inspection Items ***

5-12-04 Page 17

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 5

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 5 consists of items to be inspected every 500 hours or 1 year whichever occurs first.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component to service.

C. Conduct a preflight inspection upon completion of this operation to ensure all required items are

properly serviced. Refer to the Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

801002 Starter-Generator Brush Holders - Inspect for proper

spring tension (30-39 ounces) and freedom. Refer to

Lear Siegler/Lucas Aerospace Overhaul Manual for

proper procedure. NOTE: Does Not apply to Lucas

Aerospace Starter Generator Part Number 23081-

023A or APC Starter Generator.

121

801003 Starter-Generator Brushes - Inspect for cracks,

wear, cleanliness, and brush length. NOTE: Does

Not apply to Lucas Aerospace Starter Generator

Part Number 23081-023A or APC Starter Generator.

121

*** End of Operation 5 Inspection Items ***

5-12-05 Page 1

© Cessna Aircraft Company Sep 4/2001
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 6

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 6 consists of items to be inspected every 800 hours or 1 year whichever occurs first.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component to service.

C. Conduct a preflight inspection upon completion of this operation to ensure all required items are

properly serviced. Refer to the Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

272005 Rudder Pedal Linkage - Lubricate. Refer to Chapter

12, Lubricants - Description and Operation.

211, 212

273030 Elevator Bell Crank (Forward) - Lubricate forward

elevator bell crank components. Refer to Chapter

12, Flight Controls - Servicing.

213, 214

271028 Control Tube and Control Column Bearings -

Lubricate. Refer to Chapter 12, Flight Controls -

Servicing.

215, 216

324006 Parking Brake Control - Service parking brake

control using Silicone lubrication.

220

221013 400B Autopilot (AF-550A) and 400B IFCS (IF-550A)

- Check for security of installation and switches for

proper operation.

223

271024 Aileron Trim Control Wheel Bearings - Check for

wear.

226

273018 Elevator Trim Control Wheel Bearing - Check for

wear.

226

273021 Electric Elevator Trim - Operate electric trim, and

check trim tab travel time and cable tension.

226

5-12-06 Page 1

© Cessna Aircraft Company May 5/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

273022 Electric Trim Clutch Torque Check - Rotate sprocket

housing slowly clockwise or counterclockwise

and check torque. Refer to appropriate Sperry

Installation/Maintenance Manual for torque settings.

226

275009 Flaps - Perform an operational check. Refer to

Chapter 27, Flap Rigging Guide - Adjustment/Test.

226, 243

271009 Aileron Friction Band - Perform aileron friction band

check.

227

273008 Elevator Friction Band - Perform elevator friction

band checks.

227

532002 Bilge Area - Clean and protect. 233, 234,

253, 254,

257, 258

221005 400B Autopilot (AF-550A) and 400B IFCS (IF-550A)

- Check bridal Cable tensions.

234, 312

273031 Elevator Bell Crank (Aft) - Lubricate the aft elevator

bell crank components. Refer to Chapter 12, Flight

Controls - Servicing.

320, 330

272006 Rudder - Check travel and cable tension. 320, 343

273028 Elevator Trim Tab Actuator Part Number 2660017-

1 - Disassemble, inspect and lubricate. Refer to

Chapter 12, Lubricants - Description and Operation.

373, 374

273007 Elevator - Check elevator travel and cable tension. 375, 376

273019 Elevator Trim Tab - Check elevator trim tab travel and

cable tension.

375, 376

282009 Vent System Float Valve(s) - Perform functional

test. Refer to Chapter 28, Fuel Vent System -

Maintenance Practices.

521, 621

271012 Spoiler System - Check rigging and travel. 551, 651

271008 Aileron - Check aileron for correct travel and cable

tension.

571, 671

271025 Aileron Trim Tab Actuator Part Number 2660044-1 -

Disassemble, inspect and lubricate.

651

271022 Aileron Trim Tab - Check aileron trim tab travel and

cable tension as applicable.

671

*** End of Operation 6 Inspection Items ***

5-12-06 Page 2

© Cessna Aircraft Company May 5/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 7

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 7 consists of items to be inspected every 1000 hours or 1 year whichever occurs first.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

221024 Garmin Autopilot (GFC 700) System Inspection -

Examine the clutch torque settings and complete a

GFC 700 Visual Inspection in accordance with the

Garmin G1000 Caravan Line Maintenance Manual.

226, 233,

234, 312

221006 King Flight Control System (KFC-250) - Check bridal

cable tensions.

234, 312

221007 King Flight Control System (KFC-250) - Check

actuator clutch torque setting.

234, 312

221008 King Flight Control System (KFC-150) - Check bridal

cable tensions.

234, 312

221009 King Flight Control System (KFC-150) - Check

actuator clutch torque settings.

234, 312

221021 King Flight Control System (KFC-225) - Check

bridal cable tensions. Refer to Chapter 27, Aileron

- Adjustment/Test, Elevator - Adjustment/Test and

Yaw Damper - Adjustment/Test.

234, 312

5-12-07 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

221022 King Flight Control System (KFC-225) - Check

actuator clutch torque setting. Refer to Chapter 27,

Aileron - Adjustment/Test, Elevator - Adjustment/

Test and Yaw Damper - Adjustment/Test.

234, 312

221010 King Flight Control System (KFC-250) - Check cable

tensions.

312

221011 King Yaw Damper Actuator Slip Clutch Adjustment

(if installed) - Check yaw damper slip clutch torque

setting.

312

221012 King Yaw Damper Cable Tension Setting (if installed)

- Verify yaw bridal cable tension.

312

*** End of Operation 7 Inspection Items ***

5-12-07 Page 2

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 8

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 8 consists of items to be inspected every 2000 hours or 2 years whichever occurs first.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

D. Item Code(s) were removed from this document during this revision.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

271027 Aileron Trim Tab Control Bearings and Sprocket

- Lubricate. Refer to Chapter 12, Lubricants -

Description and Operation.

226

212002 Ventilating Blower (if installed) - Inspect blower fan/

wheel for blade damage.

511, 611

*** End of Operation 8 Inspection Items ***

5-12-08 Page 1

© Cessna Aircraft Company Jan 2/2006
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 9

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 9 consists of items to be inspected every 1 year.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

301102 Annual Operational Check (with TKS) - Do the

100-Hour operational check. Do a check of the tank

quantity indicator, tank fluid level CAS annunciator,

pump fluid delivery rate, high-pressure warning

switch and CAS annunciator, low-pressure warning

switch and CAS annunciator.

110, 130,

151, 152,

213, 214,

217, 218,

220, 233,

234, 253,

254, 257,

258, 311,

312, 320,

340, 373,

374, 527,

531, 571,

627, 631,

671, 903,

904

284004 Fuel Quantity Indication Calibration (Float system)

- Do a fuel quantity indication calibration. Refer

to Chapter 28, Fuel Quantity Indicating System -

Maintenance Practices.

221

281006 Fuel Quantity System Check (CAN bus system) - Do

a fuel quantity system check. Refer to Chapter 28,

Fuel Tanks - Adjustment/Test.

222

5-12-09 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

351501 Scott 359 Series Oxygen Mask - Inspect mask for

cracks, tears, obscured vision, dirt, buckles that are

mechanically sound and secure, exhalation valve

sticking, leakage and microphone operation.

231, 232

284005 Low Fuel Warning - Inspect for damaged electrical

components. Perform functional test of wing and

reservoir low fuel warning systems.

244

236002 Static Dischargers - Perform high-resistance check. 343, 375,

376, 575,

527, 571,

625, 627,

671

325009 Nose Landing Gear Spring and Fuselage Support

Chafing Inspection - Inspect nose landing gear

spring and areas common to fuselage support for

gouging and chafing. If gouging is equal to or less

than 0.005 inch, touch up paint as required. If

gouging is between 0.005 and 0.050 inch, blend

damaged area for a smooth transition between

gouge and immediate surrounding area at a ratio of

20:1 lengthwise, and 5:1 across the circumference

and shot peen blended area. If gouging is between

0.050 and 0.075 inch, perform a magnetic particle

inspection. If gouging is deeper than 0.075 inch,

replace spring prior to next flight.

701

*** End of Operation 9 Inspection Items ***

5-12-09 Page 2

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 10

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 10 consists of items to be inspected every 2 years.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

341002 Altimeter and Static System - Examine in

accordance with 14 CFR Part 91.411. (For airplanes

equipped with the Garmin G1000, also refer to

the Garmin G1000 Line Maintenance Manual for

specific instructions to do the checks that follow:

Altimeter, Pitot/Static Airspeed Test, and Static Port

Vertical Speed (Rate of Climb) Test).

223

341008 Overspeed Pressure Switch and Icing Low Airspeed

Awareness System (110 KIAS) (if installed) -

Complete the operational tests. Refer to Chapter

34, Pitot Static System - Maintenance Practices.

BAT

342001 Transponder Control - Operate individual controls

and perform operational test of transponder system

in accordance with 14 CFR Part 91.413.

BAT

*** End of Operation 10 Inspection Items ***

5-12-10 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 11

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 11 consists of items to be inspected every 3 years.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

350004 Oxygen Cylinder (DOT-E-8162) - Perform

hydrostatic test.

LAB

*** End of Operation 11 Inspection Items ***

5-12-11 Page 1

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 12

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 12 consists of items to be inspected every 4 years.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

271019 Aileron Trim Tab Cables - Lubricate aileron trim

cables and the cable housing openings where the

cables enter the housing. Refer to Chapter 12,

Flight Controls - Servicing.

625, 651

*** End of Operation 12 Inspection Items ***

5-12-12 Page 1

© Cessna Aircraft Company Dec 1/2006
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 13

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 13 consists of items to be inspected every 6 years.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component to service.

C. Conduct a preflight inspection upon completion of this operation to ensure all required items are

properly serviced. Refer to the Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

262003 Cockpit or Cabin Mounted Halon-Type Fire

Extinguishers - Empty, inspect for damage and

recharge.

LAB

*** End of Operation 13 Inspection Items ***

5-12-13 Page 1

© Cessna Aircraft Company Sep 4/2001
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 14

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 14 consists of items to be inspected every 12 years.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component to service.

C. Conduct a preflight inspection upon completion of this operation to ensure all required items are

properly serviced. Refer to the Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

262004 Cockpit and Cabin Mounted Halon-Type Fire

Extinguishers - Perform hydrostatic test at 12-year

intervals, based on initial servicing or date of last

hydrostatic test.

LAB

*** End of Operation 14 Inspection Items ***

5-12-14 Page 1

© Cessna Aircraft Company Sep 4/2001
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 15

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 15 consists of items to be inspected every 1200 hours or 1 year whichever occurs first.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component to service.

C. Conduct a preflight inspection upon completion of this operation to ensure all required items are

properly serviced. Refer to the Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

790002 Engine Oil (Airplanes Flown More Than 50 Hours

Per Month) - Change oil. Refer to Chapter 12,

Engine Oil System - Servicing.

121, 122

*** End of Operation 15 Inspection Items ***

5-12-15 Page 1

© Cessna Aircraft Company Sep 4/2001
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 16

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 16 consists of items to be inspected every 100 hours or at every external engine wash or

engine compartment wash.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component to service.

C. Conduct a preflight inspection upon completion of this operation to ensure all required items are

properly serviced. Refer to the Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

761005 Engine Control Rod Ends - Disconnect and inspect

engine control rods for corrosion, roughness in

rotation and radial play. Lubricate rod ends. Refer to

Chapter 12, Lubricants - Description and Operation.

122

*** End of Operation 16 Inspection Items ***

5-12-16 Page 1

© Cessna Aircraft Company Sep 4/2001
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 17

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 17 consists of items to be inspected every 500 hours.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component to service.

C. Conduct a preflight inspection upon completion of this operation to ensure all required items are

properly serviced. Refer to the Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

731008 Fuel Pump Inlet Filter - Inspect and clean fuel pump

inlet filter.

122

731009 Fuel Pump Outlet Filter - Replace fuel pump outlet

filter.

122

*** End of Operation 17 Inspection Items ***

5-12-17 Page 1

© Cessna Aircraft Company Sep 4/2001
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 18

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 18 consists of items to be inspected every 1600 hours or 5 years whichever occurs first.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

273029 Elevator Trim Tab Actuator Part Number 2661215-

1, -9 - Disassemble, inspect and lubricate. Refer

to Chapter 27, Elevator Trim System - Maintenance

Practices.

373, 374

271026 Aileron Trim Tab Actuator Part Number 2661615-1,

-9 - Disassemble, inspect and lubricate. Refer to

Chapter 27, Aileron Trim - Maintenance Practices.

651

*** End of Operation 18 Inspection Items ***

5-12-18 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 19

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 19 consists of items to be inspected every 1000 hours.

B. Inspection items are listed in order of the zone in which the inspection is to be performed. A descriptive

statement of the inspection requirement and the Item Code Number for cross reference to section

5-10-01 is provided. In many instances, tasks define more specifically the scope and extent of each

required operation. These tasks are printed in the individual chapters of this manual.

C. The right portion of each page provides room for the mechanic's and inspector's initials and remarks.

These pages may be reproduced as a checklist for use when performing this operation.

2. General Inspection Criteria

A. During accomplishment of each of the specific inspection tasks within this operation, additional general

inspections of the surrounding areas should be performed while access is available. These general

inspections are intended to detect obvious conditions which may warrant further action.

B. If a component or system is disturbed (due to maintenance being performed) after completion of an

initially required task, then that specific task must be re-confirmed after completion of any maintenance

before returning the system or component 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

790005 Oil Filter - Replace oil filter. 121

723002 P3 Filter - Replace P3 filter. 122

*** End of Operation 19 Inspection Items ***

5-12-19 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 23

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 23 has items to be inspected every 400 hours or 6 calendar months, whichever occurs first.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

321004 Inspect main landing gear spring and center

spring. Refer to Chapter 32, Main Landing Gear

- Cleaning/Painting. Remove main landing gear

fairings. Inspect for corrosion. If corrosion is found,

remove corrosion. Inspect paint and touch-up paint

as required. Inspect fillet seal around main gear

spring at center spring. Repair seal if damaged.

721, 722

*** End of Operation 23 Inspection Items ***

5-12-23 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 29

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 29 consists of items to be inspected every two years if the airplane is operated in a mild

corrosion environment and does not have the TKS anti-ice system installed. Refer to Chapter 51,

Corrosion Severity Maps - Description and Operation for definition of corrosion severity zones. NOTE:

The Repeat Interval (RI) can be adjusted according to the inspection findings. Refer to Section 5-30-

05, Appendix C, Typical Actions That Follow the Determination of the Corrosion Level, for actions

required between future successive inspections.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

321008 Main Gear Spring and Center Spring. Remove the

main landing gear fairings. Disassemble the outer

spring from the center spring. If corrosion is present,

the gear puller may be required to disassemble the

springs. Refer to Chapter 32, Main Landing Gear -

Maintenance Practices. Remove the corrosion and

shot peen. If corrosion cannot be removed within the

defined repair limits, install new gear components.

Reassemble the gear with wet corrosion resistant

epoxy primer. Apply touch-up paint as required, and

add fillet seal. Refer to Chapter 32, Main Landing

Gear - Cleaning/Painting. Failure to adhere to the

scheduled requirements could result in gear failure

if corrosion is not detected and repaired.

721, 722

*** End of Operation 29 Inspection Items ***

5-12-29 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 30

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 30 consists of items to be inspected every one year if the airplane is operated in a moderate

or severe corrosion environment, or if the airplane has the TKS anti-ice system installed. Refer to

Chapter 51, Corrosion Severity Maps - Description and Operation for definition of corrosion severity

zones. NOTE: The Repeat Interval (RI) can be adjusted according to the inspection findings. Refer to

Section 5-30-05, Appendix C, Typical Actions That Follow the Determination of the Corrosion Level,

for actions required between future successive inspections.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

321009 Main Gear Spring and Center Spring. Remove the

main landing gear fairings. Disassemble the main

gear spring from the center spring. If corrosion

is present, the gear puller may be required to

disassemble the springs. Refer to Chapter 32, Main

Landing Gear - Maintenance Practices. Remove

the corrosion and shot peen. If corrosion cannot be

removed within the defined repair limits, install new

gear components. Reassemble the gear with wet

corrosion resistant epoxy primer. Apply touch-up

paint as required, and add fillet seal. Refer to

Chapter 32, Main Landing Gear - Cleaning/Painting.

Failure to adhere to the scheduled requirements

could result in gear failure if corrosion is not detected

and repaired.

721, 722

*** End of Operation 30 Inspection Items ***

5-12-30 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 31

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 31 consists of items to be inspected at 20,000 hours and every 5000 hours thereafter. Refer

to the Model 208 Nondestructive Testing Manual.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

712003 Engine Truss and Ring Assembly - Inspect. Refer

to 5-14-30, Supplemental Inspection Number 71-20-

01.

121, 122

531008 Fuselage Engine Mount Fittings - Inspect. Refer

to 5-14-02, Supplemental Inspection Number 53-10-

01.

152, 151

532008 Firewall Brace and Doubler Assemblies - Inspect.

Refer to 5-14-09, Supplemental Inspection Number

53-20-11.

152, 151

532007 Fuselage to Wing Attach Fitting Lugs - Inspect.

Refer to 5-14-08, Supplemental Inspection Number

53-20-02.

233, 234

532009 Carry-Thru Root Rib - Inspect. Refer to 5-14-10,

Supplemental Inspection Number 53-20-08.

233, 234

564002 Windshield and Attachment Structure - Inspect.

Refer to 5-14-23, Supplemental Inspection Number

56-30-01.

240, 251,

252, 255,

256, 801,

802

5-12-31 Page 1

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

532012 Passenger and Cargo Door Frames - Inspect. Refer

to 5-14-12, Supplemental Inspection Number 53-20-

10.

255, 256

535001 Fuselage to Horizontal Stabilizer Attach Fittings -

Inspect. Refer to 5-14-17, Supplemental Inspection

Number 53-50-01.

340, 341,

373, 374,

375, 376

535002 Vertical Stabilizer Attach Points - Inspect. Refer to

5-14-18, Supplemental Inspection Number 53-50-02

for the Typical Inspection Compliance.

340, 341,

373, 374,

375, 376

551003 Horizontal Stabilizer Forward and Aft Attach Points -

Inspect. Refer to 5-14-19, Supplemental Inspection

Number 55-10-01.

340, 341,

373, 374,

375, 376

551004 Horizontal Stabilizer Spars - Inspect. Refer to 5-14-

20, Supplemental Inspection Number 55-10-02 for

the Typical Inspection Compliance.

340, 341,

373, 374,

375, 376

553001 Vertical Stabilizer Spars - Inspect. Refer to 5-14-22,

Supplemental Inspection Number 55-30-01 for the

Typical Inspection Compliance.

340, 341,

373, 374,

375, 376

532011 Crew Door Frames - Inspect. Refer to 5-14-11,

Supplemental Inspection Number 53-20-09.

801, 802

*** End of Operation 31 Inspection Items ***

5-12-31 Page 2

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 32

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 32 consists of items to be inspected at 5000 hours and every 2500 hours thereafter.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

532015 Fuselage Skin Doubler at Main Landing Gear Cutout

- Inspect. Refer to 5-14-16, Supplemental Inspection

Number 53-20-14.

721, 722

*** End of Operation 32 Inspection Items ***

5-12-32 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 33

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 33 consists of items to be inspected at 7500 hours and every 2500 hours thereafter.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

531009 Seat Rails and Attachment Structure Inspection -

Perform. Refer to 5-14-13, Supplemental Inspection

Number 53-10-07.

251, 252,

255, 256

532013 Bulkheads and Stiffeners Below the Seat Rail

Attachments at FS 143.00 and FS 158.00 - Inspect.

Refer to 5-14-14, Supplemental Inspection Number

53-20-12.

251, 252,

255, 256

532003 Cargo and Passenger Door Doublers - Inspect.

Refer to 5-14-03, Supplemental Inspection Number

53-20-01.

255, 256

*** End of Operation 33 Inspection Items ***

5-12-33 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 34

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 34 consists of items to be inspected at 12,500 hours and every 2500 hours thereafter.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

532004 Lower Forward Carry-Thru Bulkhead - Inspect.

Refer to 5-14-05, Supplemental Inspection Number

53-20-03.

233, 234

532014 Stringers at Intersections with Forward and Aft

Carry-Thru Bulkheads - Inspect. Refer to 5-14-15,

Supplemental Inspection Number 53-20-13.

233, 234

532016 Fuselage to Wing Carry-Thru Attach Fitting and

Bulkhead - Inspect. Refer to 5-14-21, Supplemental

Inspection Number 53-20-06.

511, 611

532006 Main Landing Gear Attach Fittings and Aft

Carry-Thru Bulkhead - Inspect. Refer to 5-14-07,

Supplemental Inspection Number 53-20-05.

721, 722

*** End of Operation 34 Inspection Items ***

5-12-34 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 35

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 35 consists of items to be inspected at 16,500 hours and every 5000 hours thereafter.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

535003 Vertical Stabilizer Attach Points - Inspect. Refer to

5-14-18, Supplemental Inspection Number 53-50-02

for the Severe Inspection Compliance.

340, 341,

373, 374,

375, 376

553002 Vertical Stabilizer Spars - Inspect. Refer to 5-14-22,

Supplemental Inspection Number 55-30-01 for the

Severe Inspection Compliance.

340, 341,

373, 374,

375, 376

*** End of Operation 35 Inspection Items ***

5-12-35 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 36

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 36 consists of items to be inspected at 17,500 hours and every 1000 hours thereafter.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

551005 Horizontal Stabilizer Spars - Inspect. Refer to 5-14-

20, Supplemental Inspection Number 55-10-02 for

the Severe Inspection Compliance.

340, 341,

373, 374,

375, 376

*** End of Operation 36 Inspection Items ***

5-12-36 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 37

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 37 consists of items to be inspected at 25,000 landings and every 5000 landings thereafter.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

532005 Main Landing Gear Fitting - Inspect. Refer to 5-14-

06, Supplemental Inspection Number 53-20-04.

721, 722

*** End of Operation 37 Inspection Items ***

5-12-37 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 38

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 38 consists of items to be inspected every 1200 hours.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

554001 Rudder Spar (Airplanes Incorporating CAB06-9)

- Inspect in accordance with the latest revision of

CAB06-9.

343

*** End of Operation 38 Inspection Items ***

5-12-38 Page 1

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 39

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 39 consists of items to be inspected each starter-generator removal.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

801005 Starter-Generator Splines - Clean the splines. Use

a 10X magnifying glass and examine for indications

of electrical arcing damage. Refer to the Pratt and

Whitney Canada publications for additional checks.

(Cessna SNL07-16)

121

*** End of Operation 39 Inspection Items ***

5-12-39 Page 1

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 40

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 40 consists of items to be inspected every 1000 hours or 3 years whichever occurs first.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

221025 Garmin Roll, Pitch, Yaw, and Pitch Trim Servos (GSA

80/81) - Clean and apply grease to the output gear

in accordance with the Garmin G1000 Caravan Line

Maintenance Manual.

226, 234,

312

*** End of Operation 40 Inspection Items ***

5-12-40 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION 41

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation 41 consists of items to be inspected every 5 years.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

350005 Oxygen Cylinder (DOT-SP-8162) - Perform

hydrostatic test.

LAB

*** End of Operation 41 Inspection Items ***

5-12-41 Page 1

© Cessna Aircraft Company Jul 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MA

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MA consists of items to be inspected at 10,000 hours and every 5000 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

570008 Wing Strut Attach Fittings (NDI - Eddy Current)

- Inspect. Refer to Chapter 4, Typical Inspection

Time Limits. Also, refer to 5-14-28, Supplemental

Inspection Number 57-60-01.

531, 631

*** End of Operation MA Inspection Items ***

5-12-MA Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MB

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MB has items to be examined at 5000 landings and every 1000 landings thereafter, up

to 10,000 landings. The items must be replaced at 10,000 landings. This inspection is a Chapter 4

requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

321005 Main Landing Gear Axle Part Numbers 2641011-1,

-3 and -4 - Perform a Magnetic Particle Inspection.

Refer to Chapter 4, Typical Inspection Time Limits

and Severe Inspection Time Limits. Also, refer to 5-

14-01, Supplemental Inspection Number 32-10-01.

721, 722

*** End of Operation MB Inspection Items ***

5-12-MB Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MC

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MC consists of items to be inspected at 4000 landings and every 500 landings thereafter.

This inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

275010 Flap bell crank Part Numbers 2622281-2, -12

and 2692001-2 - Inspect in accordance with the

latest revision of CAB02-1. Refer to Chapter 4,

Typical Inspection Time Limits or Chapter 4, Severe

Inspection Time Limits.

252

*** End of Operation MC Inspection Items ***

5-12-MC Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MD

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MD consists of items to be inspected at 15,000 landings and every 3000 landings thereafter.

This inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

575002 Center Flap Track and Inboard Flap Track (NDI

- Eddy Current) - Inspect. Refer to Chapter 4,

Typical Inspection Time Limits or Severe Inspection

Time Limits. Also, refer to 5-14-27, Supplemental

Inspection Number 57-50-01.

527, 627

575003 Outboard Flap Track (NDI - Eddy Current) - Inspect.

Refer to Chapter 4, Typical Inspection Time Limits or

Severe Inspection Time Limits. Also, refer to 5-14-

27, Supplemental Inspection Number 57-50-01.

527, 627

*** End of Operation MD Inspection Items ***

5-12-MD Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION ME

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation ME consists of items to be inspected at 5000 hours and every 3600 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

570009 Wing Strut Attach Fitting (NDI - Eddy Current) -

Inspect. Refer to Chapter 4, Severe Inspection

Time Limits. Also, refer to 5-14-28, Supplemental

Inspection Number 57-60-01.

531, 631

*** End of Operation ME Inspection Items ***

5-12-ME Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MF

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MF consists of items to be inspected at 20,000 hours and every 5000 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

531007 Fuselage to Wing Carry-Thru Attach Fitting (NDI

- Eddy Current) - Inspect. Refer to Chapter 4,

Typical Inspection Time Limits or Severe Inspection

Time Limits. Also, refer to 5-14-08, Supplemental

Inspection Number 53-20-02.

251, 252

570013 Wing to Carry-Thru Front Spar Attachment Fitting

(NDI - Eddy Current) - Inspect. Refer to Chapter 4,

Typical Inspection Time Limits or Severe Inspection

Time Limits. Also, refer to 5-14-24, Supplemental

Inspection Number 57-20-01.

511, 611

570014 Wing to Carry-Thru Rear Spar Attachment Fitting

(NDI - Eddy Current) - Inspect. Refer to Chapter 4,

Typical Inspection Time Limits or Severe Inspection

Time Limits. Also, refer to 5-14-24, Supplemental

Inspection Number 57-20-01.

511, 611

570010 Front Spar Lower Cap Inspection Inboard of WS

141.20 (NDI - Eddy Current) - Inspect. Refer to

Chapter 4, Typical Inspection Time Limits or Severe

Inspection Time Limits. Also, refer to 5-14-25,

Supplemental Inspection Number 57-20-02.

521, 621

5-12-MF Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

570012 Wing Strut Attachment to Front Spar (NDI - Eddy

Current) - Inspect. Refer to Chapter 4, Typical

Inspection Time Limits. Also, refer to 5-14-29,

Supplemental Inspection Number 57-60-02.

521, 621

570015 Wing Strut Attachment to Front Spar (Nominal/

Standard Bolt Size) Part Number S3461-77 (NDI -

Eddy Current) - Inspect. Refer to Chapter 4, Severe

Inspection Time Limits. Also, refer to 5-14-29,

Supplemental Inspection Number 57-60-02.

521, 621

570011 Rear Spar Lower Cap Inspection Inboard of WS

141.20 (NDI - Eddy Current) - Inspect. Refer to

Chapter 4, Typical Inspection Time Limits or Severe

Inspection Time Limits. Also, refer to 5-14-26,

Supplemental Inspection Number 57-20-03.

525, 625

*** End of Operation MF Inspection Items ***

5-12-MF Page 2

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MG

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MG consists of items to be inspected at 5000 hours and every 1200 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

531006 Fuselage to Strut Attach Fitting Lugs (Nominal/

Standard Bolt Size) Part Number S3461-74 (NDI -

Eddy Current) - Inspect. Refer to Chapter 4, Severe

Inspection Time Limits. Also, refer to 5-14-04,

Supplemental Inspection Number 53-20-07.

253, 254

*** End of Operation MG Inspection Items ***

5-12-MG Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MI

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MI consists of items to be inspected at 5000 hours and every 500 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

531010 Fuselage to Strut Attach Fitting Lugs (1/64 Inch

Oversize Bolt Size) Part Number S3461-159 (NDI -

Eddy Current) - Inspect. Refer to Chapter 4, Severe

Inspection Time Limits. Also, refer to 5-14-04,

Supplemental Inspection Number 53-20-07.

253, 254

*** End of Operation MI Inspection Items ***

5-12-MI Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MJ

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MJ consists of items to be inspected at 5000 hours and every 400 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

531011 Fuselage to Strut Attach Fitting Lugs (1/32 Inch

Oversize Bolt Size) Part Number S3461-160 (NDI -

Eddy Current) - Inspect. Refer to Chapter 4, Severe

Inspection Time Limits. Also, refer to 5-14-04,

Supplemental Inspection Number 53-20-07.

253, 254

*** End of Operation MJ Inspection Items ***

5-12-MJ Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MK

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MK consists of items to be inspected at 20,000 hours and every 4400 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

570016 Wing Strut Attachment to Front Spar (1/64 Inch

Oversize Bolt Size) Part Number S3461-163 (NDI -

Eddy Current) - Inspect. Refer to Chapter 4, Severe

Inspection Time Limits. Also, refer to 5-14-29,

Supplemental Inspection Number 57-60-02.

521, 621

*** End of Operation MK Inspection Items ***

5-12-MK Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION ML

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation ML consists of items to be inspected at 20,000 hours and every 3600 hours thereafter. This

inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

570017 Wing Strut Attachment to Front Spar (1/32 Inch

Oversize Bolt Size) Part Number S3461-164 (NDI -

Eddy Current) - Inspect. Refer to Chapter 4, Severe

Inspection Time Limits. Also, refer to 5-14-29,

Supplemental Inspection Number 57-60-02.

521, 621

*** End of Operation ML Inspection Items ***

5-12-ML Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

INSPECTION OPERATION MH

Date: _______________

Registration Number: _______________

Serial Number: _______________

Total Time: _______________

1. Description

A. Operation MH consists of items to be inspected at 10,000 hours and every 2500 hours thereafter.

This inspection is a Chapter 4 requirement, and the interval CANNOT be extended.

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

general description of the inspection required and the Item Code Number for cross-reference to section

5-10-01 is shown. Frequently, tasks give more information about each required inspection. These

tasks are printed 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. A

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

2. General Inspection Criteria

A. While each of the specified inspection tasks in this section are done, 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 Approved Airplane Flight Manual.

ITEM CODE

NUMBER

TASK ZONE MECH INSP REMARKS

531005 Fuselage to Strut Attach Fitting Lugs (NDI - Eddy

Current) - Inspect. Refer to Chapter 4, Typical

Inspection Time Limits. Also, refer to 5-14-04,

Supplemental Inspection Number 53-20-07.

253, 254

*** End of Operation MH Inspection Items ***

5-12-MH Page 1

© Cessna Aircraft Company Jun 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION DOCUMENT

1. Supplemental Inspection Document

A. Introduction

(1) 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. A practical state-of-the-art inspection program is found for each

Principal Structural Element (PSE). The FAA has defined a PSE in AC25.571:

(a) A PSE is an element that contributes significantly to carrying flight, ground or pressurization

loads, and whose integrity is essential in maintaining the overall structural integrity of the

airplane.

(2) 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, we started a Corrosion Prevention

and Control Program (CPCP) to prevent or control corrosion that can have an effect on the

continued airworthiness of the airplane.

(3) 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.

B. Function

(1) 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) A list is included to show the requirements for the SID program for primary and secondary

airframe components.

1 The airplane maintenance agrees with Cessna's recommendations or the equivalent.

2 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.

3 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.

2. Principal Structural Elements

A. Principal Structural Elements Description

(1) An airplane component is classified as a Principal Structural Element (PSE) if:

(a) The component contributes significantly to carrying flight and ground loads.

(b) And, if the component fails, it can result in a catastrophic failure of the airframe.

(2) The monitoring of these PSEs is the main focus of this Supplemental Structural Inspection

Program.

(3) Typical examples of PSEs, as listed in FAA Advisory Circular 25.571, are listed in Table 1.

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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

Door skins, frames and latches

Window frames

Landing Gear and their Attachments

Engine Support Structure and Mounts

B. Selection Criteria

(1) The factors used to find the PSEs in this document include:

(a) Service Experience

1 Two sources of information were used to find the service discrepancies.

a Cessna Service Bulletins and Service Information Letters issued to repair

common service discrepancies were examined.

b FAA Service Difficulty Records were examined.

2 The data collected was also used to find a component's susceptibility to corrosion or

accidental damage as well as its inspectability.

(b) Fatigue And Damage Tolerance Analysis

1 Fatigue and damage tolerance analyses were conducted for the critical areas of the

PSEs. Details of these analyses are presented in Section 3, Durability - Fatigue And

Damage Tolerance.

(c) Testing

1 Test results from previous static tests and fatigue cyclic tests were reviewed to identify

the critical areas of the PSEs.

3. Durability - Fatigue And Damage Tolerance

A. Airplane Usage

(1) Airplane usage data for the SID program is from the analysis of the in-service use of the airplane.

Operational data for the SID is from operator surveys and from CESCOM (Computerized

Maintenance Program). This information was used to make the fatigue loads spectra.

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(2) Usage results from inspection of typical flight lengths, takeoff gross weights, payloads and fuel.

One flight profile was made to represent each usage. Different usages are mixed to make a

fatigue loads spectrum.

(3) The flight profile has the applicable facts of the flight. The profile gives the gross weight, payload,

fuel, altitude, speed, distance, etc., necessary to find the pertinent flight and ground parameters

to develop the fatigue loads. The flight is then divided into operational segments, where each

segment represents the average values of the parameters (speed, payload, fuel, etc.) that are

used to calculate the fatigue loads spectrum.

B. Stress Spectrum

(1) A fatigue loads spectrum, which is the gross area stress, was made for each PSE to be analyzed.

This analysis is based on the usage-flight profile.

(2) The spectrum represents the loading environments, they are:

(a) Flight loads (gust and maneuver)

(b) Landing impact

(c) Balancing tail loads

(d) Thrust loads

(e) Ground loads (taxi, turning, landing, braking, pivoting, etc.),

(f) Ground-air-ground cycles

(3) The spectrum is representative of a flight-by-flight, cycle-by-cycle random loading sequence that

gives a reflection of the applicable and important airplane response characteristics.

(4) After an examination of the airplane usage data and the ways in which the surveyed airplanes

were flown, two sets of stress profiles were developed, one for each flight profile.

(a) The first flight profile represents a typical usage with an average flight length of

approximately one hour.

(b) The second flight profile represents severe usage, which includes flight lengths of less than

35 minutes, flights at low altitudes or operations in high humidity climates.

C. Classification for Types of Operation

(1) 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.

(2) If the average flight length is less than or equal to 35 minutes, then use the Severe Flight Profile

for inspections.

(3) 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 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.

(4) 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.

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(5) Make an airplane logbook entry that gives the applicable inspection schedule after it has been

found.

D. Damage Tolerance and Fatigue Assessments

(1) The damage tolerance and fatigue analysis gives the information used to set the inspection

frequency requirements for each PSE. The analysis includes the possible fatigue failure locations

and types of damage. Required inspections are set using analytical results, available test data

and service experience. The analysis includes standard fatigue analyses, the crack growth time

history and the strength that remains. Linear elastic fracture mechanics are used for the damage

tolerance analysis, while fatigue analyses use the "Palmgren-Miner" linear cumulative damage

theory.

(2) In the analysis, the possible structural condition areas related to the airplanes as they are used

more frequently, are carefully examined. Examples include:

(a) Large areas of structure working at the same stress level, which can start widespread

fatigue damage.

(b) A number of small (less than detection size) adjacent cracks suddenly connected into a

long crack (as in a line of rivet holes).

(c) A load supplied from adjacent damaged parts that can cause faster damage to nearby

parts (the "domino" effect).

(d) Failure of multiple load path structure at the same time (crack arrest structure).

(3) Initial inspections of a selected area of structure are set by both crack growth and fatigue analysis

results, as well as test results.

(a) The structures which were found to be fail-safe, use the fatigue life to set the initial

inspections.

(b) The locations with long fatigue life, the maximum initial inspection has a limit of 20,000

flight hours.

(c) Structure which was found to be fail-safe includes the Models 208 and 208B wing, fuselage

and empennage.

(4) For locations that were identified as very important by tests, the initial inspection time was set

by crack growth. The crack growth for each PSE is calculated from the initial crack size co to

the crack length at instability/failure, ccrit, because of limit load. The crack's growth during time

is shown by crack length versus time in flight hours. All inspections that were done again and

again were derived from crack growth.

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4. Reporting - Communications

A. Discrepancies

(1) 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.

(2) 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.

(3) 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.

B. Discrepancy Reporting

(1) 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.

(2) 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.

C. Send the Discrepancy Form

(1) 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

Fax: 316-942-9006

NOTE: This system does not replace the normal channels to send information for items not

included in the SID.

D. Cessna Aircraft Company Follow-Up Action

(1) All SID reports will be examined to find if any of the steps are necessary:

(a) Complete a check of the effect on the structural or operational condition.

(b) Complete a check of other high-time airplanes to find if a service bulletin shall be issued.

(c) Find if a reinforcement is required.

(d) Change the SID if required.

5. Inspection Methods

A. Selection of inspection method.

(1) 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, cdet, for each NDI method.

(2) The selection of NDI method uses crack direction, location, ccrit, 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.

6. Applicability/Limitations

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

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B. STC Installations

(1) 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.

(2) On airplanes that changed the airplane design, gross weight, or airplane performance, it can be

necessary to do inspections more frequently.

(a) 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.

(3) 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.

7. PSE Details

A. Details

(1) 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.

(2) 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.

B. Repairs, Alterations and Modifications (RAM)

(1) Repairs, Alterations and Modifications (RAM) made to PSEs can have an effect on the inspection

times and methods necessary for the SID. The flowchart in Figure 1 can be used to find if

a new damage tolerance assessment and FAA approved supplemental inspection criteria are

necessary.

(2) For repairs that are not included in the recommendations of this SID document or the Model

208 Structural Repair Manual, contact Cessna Propeller Aircraft Product Support for assistance;

(316) 517-5800 or Fax (316) 942-9006.

(a) All repairs supplied by Cessna Aircraft Company since January 2003 meet the damage

tolerance assessment requirements.

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MODEL 208

MAINTENANCE MANUAL

LISTING OF SUPPLEMENTAL INSPECTIONS

1. Supplemental Inspection Procedures

A. Each of the supplemental inspections listed in this section have the instructions to do each

Nondestructive Testing procedure needed. The Supplemental Inspection Number corresponds to

the section of the Model 208 Nondestructive Testing Manual section number.

B. Procedure

(1) Each supplemental inspection is assigned an independent item code in Chapter 5.

(2) The item codes are in Chapter 5, Inspection Time Limits. They are found in section 5-10-01.

(3) The item code contains the subject and a reference to the actual supplemental inspection. These

inspections are found in sections that begin with 5-14-XX.

(4) Each 5-14-XX section has the details of the inspection and, if needed, a reference to the

Nondestructive Testing procedure for that inspection.

(5) Every supplemental inspection will reference the Model 208 Nondestructive Testing Manual and

which part of the manual to go to. For example, in the Nondestructive Testing Manual, Part 6 is

the Eddy Current information.

(6) The supplemental inspection numbers in the list below agree with the same number in the

Nondestructive Testing Manual, if applicable.

(7) Inspection operations that begin with the letter M are those inspections that match Chapter 4.

These were added because there is no grace period for these inspections.

2. Supplemental Inspections

DETAILS

FOUND

IN

SECTION

5-14-XX

SUPPLEMENTAL

INSPECTION

NUMBER

INSPECTION

COMPLIANCE TITLE

INITIAL REPEAT INSPECTION OPERATION

ITEM

CODE

5-14-01 32-10-01 Main Landing Gear Axle

(2641011-1, -3 and -4)

5000

Landings

1000

Landings

up to

10,000

Landings

MB 321005

5-14-02 53-10-01 Fuselage Engine Mount

Fittings

20,000

Hours

5000 Hours 31 531008

5-14-03 53-20-01 Cargo and Passenger

Door Doublers

7500 Hours 2500 Hours 33 532003

Fuselage to Strut Attach

Fitting Lugs

Typical

10,000

Hours

Typical

2500 Hours

MH 531005

(Nominal/Standard Bolt

Size - Part Number

S3461-74)

Severe

5000 Hours

Severe

1200 Hours

MG 531006

1/64 Inch Oversize Bolt

Size - Part Number

S3461-159)

Severe

5000 Hours

Severe 500

Hours

MI 531010

5-14-04 53-20-07

(1/32 Inch Oversize

Bolt Size - Part Number

S3461-160)

Severe

5000 Hours

Severe 400

Hours

MJ 531011

5-14-05 53-20-03 Lower Forward

Carry-Thru Bulkhead

12,500

Hours

2500 Hours 34 532004

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DETAILS

FOUND

IN

SECTION

5-14-XX

SUPPLEMENTAL

INSPECTION

NUMBER

INSPECTION

COMPLIANCE TITLE

INITIAL REPEAT INSPECTION OPERATION

ITEM

CODE

5-14-06 53-20-04 Main Landing Gear

Fitting

25,000

Landings

5000

Landings

37 532005

5-14-07 53-20-05 Main Landing Gear

Attach Fittings and Aft

Carry-Thru Bulkhead

12,500

Hours

2500 Hours 34 532006

5-14-08 53-20-02 Fuselage to Wing Attach

Fitting Lugs

20,000

Hours

5000 Hours MF 532007

5-14-09 53-20-11 Firewall Brace and

Doubler Assemblies

20,000

Hours

5000 Hours 31 532008

5-14-10 53-20-08 Carry-Thru Root Rib 20,000

Hours

5000 Hours 31 532009

5-14-11 53-20-09 Crew Door Frames 20,000

Hours

5000 Hours 31 532011

5-14-12 53-20-10 Passenger and Cargo

Door Frames

20,000

Hours

5000 Hours 31 532012

5-14-13 53-10-07 Seat Rails and

Attachment Structure

7500 Hours 2500 Hours 33 531009

5-14-14 53-20-12 Bulkheads and Stiffeners

Below the Seat Rail

Attachments at FS

143.00 and FS 158.00

7500 Hours 2500 Hours 33 532013

5-14-15 53-20-13 Stringers at Intersections

with Forward and Aft

Carry-Thru Bulkheads

12,500

Hours

2500 Hours 34 532014

5-14-16 53-20-14 Fuselage Skin Doubler

at Main Landing Gear

Cutout

5000 Hours 2500 Hours 32 532015

5-14-17 53-50-01 Fuselage to Horizontal

Stabilizer Attach Fittings

20,000

Hours

5000 Hours 31 535001

5-14-18 Typical

20,000

Hours

Typical

5000 Hours

53-50-02 Vertical Stabilizer Attach 31 535002

Points

Severe

16,500

Hours

Severe

5000 Hours

35 535003

5-14-19 55-10-01 Horizontal Stabilizer

Forward and Aft Attach

Points

20,000

Hours

5000 Hours 31 551003

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MODEL 208

MAINTENANCE MANUAL

DETAILS

FOUND

IN

SECTION

5-14-XX

SUPPLEMENTAL

INSPECTION

NUMBER

INSPECTION

COMPLIANCE TITLE

INITIAL REPEAT INSPECTION OPERATION

ITEM

CODE

5-14-20 Typical

20,000

Hours

Typical

5000 Hours

55-10-02 Horizontal Stabilizer 31 553004

Spars

Severe

17,500

Hours

Severe

1000 Hours

36 551005

5-14-21 53-20-06 Fuselage to Wing

Carry-Thru Attach Fitting

and Bulkhead

12,500

Hours

2500 Hours 34 532016

5-14-22 Typical

20,000

Hours

Typical

5000 Hours

55-30-01 Vertical Stabilizer Spars 31 553001

Severe

16,500

Hours

Severe

5000 Hours

35 553002

5-14-23 56-30-01 Windshield and

Attachment Structure

20,000

Hours

5000 Hours 31 564002

Wing to Carry-Thru Front

Spar Attachment Fittings

20,000

Hours

5-14-24 57-20-01 5000 Hours MF 570013

Wing to Carry-Thru Rear

Spar Attachment Fittings

20,000

Hours

5000 Hours MF 570014

5-14-25 57-20-02 Front Spar Lower Cap

Inboard of WS 141.20

20,000

Hours

5000 Hours MF 570010

5-14-26 57-20-03 Rear Spar Lower Cap

Inboard of WS 141.20

20,000

Hours

5000 Hours MF 570011

Flap Tracks (Center and

Inboard)

15,000

Landings

3000

Landings

5-14-27 57-50-01 MD 575002

Flap Track (Outboard) 15,000

Landings

3000

Landings

MD 575003

5-14-28 Typical

10,000

Hours

Typical

5000 Hours

57-60-01 Wing Strut Fittings MA 570008

Severe

5000 Hours

Severe

3600 Hours

ME 570009

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MAINTENANCE MANUAL

DETAILS

FOUND

IN

SECTION

5-14-XX

SUPPLEMENTAL

INSPECTION

NUMBER

INSPECTION

COMPLIANCE TITLE

INITIAL REPEAT INSPECTION OPERATION

ITEM

CODE

Wing Strut Attachment to

Front Spar

Typical

20,000

Hours

Typical

5000 Hours

MF 570012

(Nominal/Standard Bolt

Size - Part Number

S3461-77)

Severe

20,000

Hours

Severe

5000 Hours

MF 570015

(1/64 Inch Oversize

Bolt Size - Part Number

S3461-163)

Severe

20,000

Hours

Severe

4400 Hours

MK 570016

5-14-29 57-60-02

(1/32 Inch Oversize

Bolt Size - Part Number

S3461-164)

Severe

20,000

Hours

Severe

3600 Hours

ML 570017

5-14-30 71-20-01 Engine Truss and Ring

Assembly

20,000

Hours

5000 Hours 31 712003

NOTE: If the number of landings is not know use the data that follows to calculate the necessary

inspection intervals:

• For airplanes that use the severe scheduled inspections, use three landings for each flight

hour to calculate the inspection intervals.

• For airplane that use the typical scheduled inspection, use two landings for each flight hour

to calculate the inspection intervals.

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MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 32-10-01

1. Title

Main Landing Gear Axle (2641011-1, -3 and -4)

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 5000 Landings 1000 Landings up to 10,000

Landings

3. Main Landing Gear Axle Inspection

A. Examine the Main Landing Gear Axle.

(1) Examine the main landing gear axle for fatigue and cracks in the main landing gear axle radius.

Refer to the Model 208 Nondestructive Testing Manual, Part 8, Magnetic Particle Inspection.

B. Replace at 10,000 landings.

5-14-01 Page 1

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MODEL 208

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SUPPLEMENTAL INSPECTION NUMBER: 53-10-01

1. Title

Fuselage Engine Mount Fittings

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Fuselage Engine Mount Fittings

A. Examine the Fuselage Engine Mount Fittings.

(1) Remove the engine cowling to get access to the firewall engine mount assemblies. Refer to

Chapter 71, Engine Cowling and Nose Cap - Maintenance Practices.

(2) Examine the Firewall Engine Mount Assemblies at FS 100.00.

(a) Do a Nondestructive Testing (NDT) inspection of the four truss assembly attachment points.

Refer to the Model 208 Nondestructive Testing Manual Part 6.

(b) Do a visual inspection of the gusset for cracks around the engine truss assembly

attachment points.

(c) Do a visual inspection of the flange rings for cracks.

(d) Do an NDT inspection of the upper engine mount attachment. Refer to the Model 208

Nondestructive Testing Manual Part 6.

(3) If no cracks are found, install the engine cowling on the airplane. Refer to Chapter 71, Engine

Cowling and Nose Cap - Maintenance Practices.

(4) If cracks are found, repair the damaged part(s) or replace the parts. Refer to Chapter 71, Engine

Cowling and Nose Cap - Maintenance Practices or the Model 208 Structural Repair Manual.

(a) Install the engine cowling on the airplane. Refer to Chapter 71, Engine Cowling and Nose

Cap - Maintenance Practices.

5-14-02 Page 1

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MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-01

1. Title

Cargo and Passenger Door Doublers

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 7500 Hours 2500 Hours

3. Cargo and Passenger Door Doublers Inspection

A. Examine the Cargo and Passenger Door Doublers.

(1) Remove the upholstery. Refer to Chapter 52, Passenger Doors - Maintenance Practices.

(2) Do an eddy current inspection of the upper passenger frame doublers and corners for cracks.

Refer to the Model 208 Nondestructive Testing Manual Part 6.

(3) Do an eddy current inspection of the upper cargo frame doublers and corners for cracks. Refer

to the Model 208 Nondestructive Testing Manual Part 6.

(4) If no cracks are found, install the upholstery. Refer to Chapter 52, Passenger Doors -

Maintenance Practices.

(5) If cracks are found, repair or replace the damaged part(s). Refer to Chapter 52, Passenger Doors

- Maintenance Practices, Passenger Doors - Maintenance Practices,Cargo Doors - Maintenance

Practices or the Model 208 Structural Repair Manual.

(a) Install the upholstery. Refer to Chapter 52, Passenger Doors - Maintenance Practices.

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MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-07

1. Title

Fuselage to Strut Attach Fitting Lugs

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 10,000 Hours 2500 Hours

SEVERE 5000 Hours See Note 1

NOTE 1: For nominal/standard bolt size, Part Number S3461-74: 1200 Hours; for 1/64 inch oversize bolt size,

Part Number S3461-159: 500 Hours; for 1/32 inch oversize bolt size, Part Number S3461-160: 400

Hours.

3. Fuselage to Strut Attach Fitting Lugs Inspection

NOTE: Models 208/208A have the fuselage to strut attach fitting lugs installed between FS 166.00 and

FS 168.00.

NOTE: Model 208B has the fuselage to strut attach fitting lugs installed between FS 186.00 and FS

188.00.

A. Examine the Fuselage to Strut Attach Fitting Lugs.

(1) Remove the struts. Refer to Chapter 57, Wings - Removal/Installation.

(2) Do an eddy current inspection for cracks in the fuselage attach fittings. Refer to the Model 208

Nondestructive Testing Manual Part 6.

(3) If no cracks are found, install the struts. Refer to Chapter 57, Wings - Removal/Installation.

(4) If cracks are found, replace the strut attach fitting lug. Refer to Chapter 57, Wings - Removal/

Installation.

(a) Install the struts. Refer to Chapter 57, Wings - Removal/Installation.

5-14-04 Page 1

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MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-03

1. Title

Lower Forward Carry-Thru Bulkhead

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 12,500 Hours 2500 Hours

3. Lower Forward Carry-Thru Bulkhead Inspection

NOTE: The lower forward carry-thru bulkhead on Models 208/208A are installed at FS 166.00 and FS

168.00.

NOTE: The lower forward carry-thru bulkhead on Model 208B are installed at FS 186.00 and FS 188.00.

A. Examine the Lower Forward Carry-Thru Bulkhead.

(1) Remove the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance Practices.

(2) Remove the upholstery and floorboard panels below the passenger seat locations. Refer to

Chapter 53, Floorboards and Access Plates - Maintenance Practices.

(3) Examine the lower forward carry-thru bulkhead.

(a) Do a visual inspection of the bulkhead and frames for cracks.

1 Do a visual inspection of the corners of the frames around the strut attach fittings.

(b) Remove the bolts one at a time in the strut attach fitting and eddy current inspect each

hole. Refer to the Model 208 Nondestructive Testing Manual Part 6.

(c) Remove the bolts one at a time in the wing attach fitting and eddy current inspect each

hole.

(4) If no cracks are found:

(a) Install the floorboards and upholstery. Refer to Chapter 53, Floorboards and Access Plates

- Maintenance Practices.

(b) Install the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance

Practices.

(5) If cracks are found in the bulkhead, repair the bulkhead. Refer to the Model 208 Structural Repair

Manual.

(a) If cracks are found in the attach fitting(s), replace the attach fitting(s).

(b) Install the floorboards and upholstery. Refer to Chapter 53, Floorboards and Access Plates

- Maintenance Practices.

(c) Install the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance

Practices.

5-14-05 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-04

1. Title

Main Landing Gear Fitting

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 25,000 Landings 5000 Landings

3. Main Landing Gear Fitting Inspection

A. Examine the Main Landing Gear Fitting.

(1) Remove the fuselage to main landing gear fairing to get access to the main landing gear fitting.

Refer to Chapter 32, Main Landing Gear - Maintenance Practices.

(2) Lift the airplane with jacks. Refer to Chapter 7, Jacking - Maintenance Practices.

(3) Eddy current inspect the main landing gear fitting attachment holes. Refer to the Model 208

Nondestructive Testing Manual Part 6.

(4) If no cracks are found, lower the airplane with jacks. Refer to Chapter 7, Jacking - Maintenance

Practices.

(a) Install the fuselage to main landing gear fairing. Refer to Chapter 32, Main Landing Gear

- Maintenance Practices.

(5) If cracks are found, replace the main landing gear fitting. Refer to Chapter 32, Main Landing

Gear - Maintenance Practices.

(a) Lower the airplane with jacks. Refer to Chapter 7, Jacking - Maintenance Practices.

(b) Install the fuselage to main landing gear fairing. Refer to Chapter 32, Main Landing Gear

- Maintenance Practices.

5-14-06 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-05

1. Title

Main Landing Gear Attach Fittings and Aft Carry-Thru Bulkhead

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 12,500 Hours 2500 Hours

3. Main Landing Gear Attach Fittings and Aft Carry-Thru Bulkhead Inspection

NOTE: The main landing gear attach fittings and aft carry-thru bulkhead on Models 208/208A are

installed at FS 194.40 and FS 208.00.

NOTE: The main landing gear attach fittings and aft carry-thru bulkheads on Airplanes Model 208B are

installed at FS 214.40 and FS 228.00.

A. Examine the Main Landing Attach Gear Fittings and Aft Carry-Thru Bulkhead.

(1) Remove the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance Practices.

(2) Remove the upholstery and floorboard panels below the passenger seat locations. Refer to

Chapter 53, Floorboards and Access Plates - Maintenance Practices.

(3) Do an inspection of the frames for cracks.

(a) Do a visual inspection of the corners around the attach fittings for cracks.

1 Examine the corners of the frames around the strut attach fittings.

(b) Remove the bolts one at a time in the left main gear attach fitting, forward and aft, and

eddy current inspect each hole.

(c) One at a time, remove the bolts in the right main gear attach fitting, forward and aft, and

eddy current inspect each hole. Refer to the Model 208 Nondestructive Testing Manual

Part 6.

(4) If no cracks are found:

(a) Install the floorboards and upholstery. Refer to Chapter 53, Floorboards and Access Plates

- Maintenance Practices.

(b) Install the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance

Practices.

(5) If cracks are found in the lower aft carry-thru bulkhead, repair the bulkhead. Refer to the Model

208 Structural Repair Manual.

(a) If cracks are found in the attach fitting(s), replace the attach fitting(s).

(b) Install the floorboards and upholstery. Refer to Chapter 53, Floorboards and Access Plates

- Maintenance Practices.

(c) Install the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance

Practices.

5-14-07 Page 1

© Cessna Aircraft Company Aug 2/2004
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-02

1. Title

Fuselage to Wing Attach Fitting Lugs

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Fuselage to Wing Attach Fitting Lugs Inspection

A. Examine the Fuselage to Wing Attach Fitting Lugs.

(1) Remove the wing. Refer to Chapter 57, Wings - Removal/Installation.

(2) Do an eddy current inspection of the bolt holes in the attach fittings lugs. Refer to the Model 208

Nondestructive Testing Manual, Part 6.

(3) If no cracks are found, install the wing. Refer to Chapter 57, Wings - Removal/Installation.

(4) If cracks are found, replace the fittings.

(a) Install the wing. Refer to Chapter 57, Wings - Removal/Installation.

5-14-08 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-11

1. Title

Firewall Brace and Doubler Assemblies

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Firewall Brace and Doubler Assemblies Inspection

A. Examine the Firewall Brace and Doubler Assemblies.

(1) Remove the engine cowling to get access to the firewall engine mount assemblies. Refer to

Chapter 71, Engine Cowling and Nose Cap - Maintenance Practices.

(2) Do a visual inspection of the doubler and supports for cracks on the forward and the aft sides of

the firewall.

(3) Do a visual inspection of the firewall brace and the adjacent web for cracks that come from the

fastener holes on the forward and the aft sides of the firewall.

(4) If no cracks are found, install the engine cowling on the airplane. Refer to Chapter 71, Engine

Cowling and Nose Cap - Maintenance Practices.

(5) If cracks are found, repair or replace the part(s). Refer to Chapter 71, Main Landing Gear -

Maintenance Practices.

(a) Install the engine cowling the airplane. Refer to Chapter 71, Engine Cowling and Nose

Cap - Maintenance Practices.

5-14-09 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-08

1. Title

Carry-Thru Root Rib

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Carry-Thru Root Rib Inspection

A. Examine the Carry-Thru Root Rib.

(1) Remove the wing from the airplane. Refer to Chapter 57, Wings - Removal/Installation.

(2) Do a visual inspection of the root rib for cracks.

(3) If no cracks are found, install the wing on the airplane. Refer to Chapter 57, Wings - Removal/

Installation.

(4) If cracks are found, repair or replace the root rib. Refer to Chapter 57, Wings - Removal/

Installation or the Model 208 Structural Repair Manual.

(a) Install the wing on the airplane. Refer to Chapter 57, Wings - Removal/Installation.

5-14-10 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-09

1. Title

Crew Door Frames

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Crew Door Frames Inspection

A. Examine the Crew Door Frames.

(1) Open the doors or remove the doors. Refer to Chapter 52, Crew Doors - Maintenance Practices.

(2) Do a visual inspection of the crew door frames for cracks. Refer to Chapter 52, Crew Doors -

Maintenance Practices.

(a) Examine the corners and around the jamb assembly.

(b) Replace the jamb assembly if it is damaged. Refer to Chapter 52, Crew Doors -

Maintenance Practices.

(3) If cracks are found, repair or replace the damaged part(s). Refer to Chapter 52, Crew Doors -

Maintenance Practices.

(4) Close the doors or replace the doors. Refer to Chapter 52, Crew Doors - Maintenance Practices.

5-14-11 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-10

1. Title

Passenger and Cargo Door Frames

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Passenger and Cargo Door Frames Inspection

A. Examine the Passenger and Cargo Door Frames.

(1) Open the cargo doors.

(2) Do a visual inspection of the passenger door frames for cracks. Refer to Chapter 52, Passenger

Doors - Maintenance Practices.

(a) Examine the corners and around the jamb assembly.

(b) Replace the jamb assembly if it is damaged.

(3) Do a visual inspection of the cargo door frames for cracks. Refer to Chapter 52, Cargo Doors -

Maintenance Practices.

(a) Examine the corners and around the jamb assembly.

(b) Replace the jamb assembly if it is damaged. Refer to Chapter 52, Passenger Doors -

Maintenance Practices.

(4) If cracks are found, repair or replace the part(s). Refer to Chapter 52, Passenger Doors -

Maintenance Practicesor Cargo Doors - Maintenance Practices.

(5) Close the cargo doors.

5-14-12 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-10-07

1. Title

Seat Rails and Attachment Structure

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 7500 Hours 2500 Hours

3. Seat Rails and Attachment Structure Inspection

A. Examine the Pilot and Copilot's Seat Rails and Attachment Structure.

(1) Remove the pilot and the copilot's seats. Refer to Chapter 25, Flight Compartment - Maintenance

Practices.

(2) Do a visual inspection of the pilot and copilot's seat rails for cracks or holes that are stretched

more than 0.21 inch.

(a) If there are no cracks or holes that are stretched more than 0.21 inch, continue to step

3.A.(3).

(b) If any of the seat rails have cracks or holes that are stretched more than 0.21 inch, replace

the seat rails. Refer to Service Kit SK208-138 and Chapter 32, Flight Compartment -

Maintenance Practices.

(3) Do a visual inspection of the structure beneath the pilot and copilot's seat rails for cracks.

(a) If there are no cracks in the structure beneath the pilot or copilot's seat rails, install the

seats. Refer to Chapter 25, Flight Compartment - Maintenance Practices.

(b) If the structure beneath the pilot and copilot's seats has cracks, repair the structure. Refer

to Service Kit SK208-138 and the Model 208 Structural Repair Manual.

1 Install the pilot and copilot's seats. Refer to Chapter 25, Flight Compartment -

Maintenance Practices.

B. Inspect the Passenger Seat Rails and Attachment Structure.

(1) Remove the passenger seats and floor covering. Refer to Chapter 25, Passenger Seats -

Maintenance Practices.

(2) Do a visual inspection of the passenger seat rails for cracks.

(a) If there are no cracks in the passenger seat rails, continue to step 3.B.(3).

(b) If any of the seat rails have cracks, replace the seat rails. Refer to Chapter 25, Passenger

Seats - Maintenance Practices.

(3) Do a visual inspection of the structure beneath the passenger seat rails for cracks.

(a) If there are no cracks in the structure beneath the passenger seat rails, install the seats.

Refer to Chapter 25, Passenger Seats - Maintenance Practices.

(b) If the structure beneath the passenger seats has cracks, repair the structure. Refer to the

Model 208 Structural Repair Manual.

1 Install the passenger seats. Refer to Chapter 25, Flight Compartment - Maintenance

Practices.

5-14-13 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-12

1. Title

Bulkheads and Stiffeners Below the Seat Rail Attachments at FS 143.00 and FS 158.00

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 7500 Hours 2500 Hours

3. Bulkheads and Stiffeners Below the Seat Rail Attachments Inspection

A. Examine the Bulkheads and Stiffeners Below the Seat Rail Attachments.

(1) Remove the pilot and the copilot's seats. Refer to Chapter 25, Flight Compartment - Maintenance

Practices.

(2) Remove the upholstery and floorboard panels below the pilot and the copilot's seat locations.

Refer to Chapter 53, Floorboards and Access Plates - Maintenance Practices.

(3) Examine the bulkheads and stiffeners for cracks at FS 143.00 and FS 158.00.

(a) Do a visual inspection of the bulkheads and stiffeners for cracks.

(b) Do a visual inspection of the bulkhead structure near the lightening holes for cracks.

(c) Do a visual inspection of the bulkhead structure near the intersections with the longitudinal

bulkheads for cracks.

(4) Examine the longitudinal bulkheads and stiffeners for cracks at FS 143.00 and FS 158.00.

(a) Do a visual inspection of the longitudinal bulkheads and stiffeners for cracks.

(b) Do a visual inspection of the bulkhead structure near the lightening holes for cracks.

(c) Do a visual inspection of the bulkhead structure near the intersections with the longitudinal

bulkheads for cracks.

(5) If there are no cracks, install the upholstery and floorboard panels below the pilot and the copilot's

seat locations. Refer to Chapter 53, Floorboards and Access Plates - Maintenance Practices.

(6) If there are cracks in the bulkheads, replace the bulkheads. Refer to Chapter 25, Flight

Compartment - Maintenance Practices.

(a) Install the pilot and the copilot's seats. Refer to Chapter 25, Flight Compartment -

Maintenance Practices.

(7) Install the upholstery and floorboard panels below the pilot and the copilot's seat locations. Refer

to Chapter 53, Floorboards and Access Plates - Maintenance Practices.

5-14-14 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-13

1. Title

Stringers at Intersections with Forward and Aft Carry-Thru Bulkheads

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 12,500 Hours 2500 Hours

3. Stringers at Intersections with Forward and Aft Carry-Thru Bulkheads Inspection

NOTE: Models 208/208A have the stringers installed between FS 168.00 and FS 195.00.

NOTE: Model 208B has the stringers installed between FS 188.00 and FS 215.00.

A. Examine the stringers.

(1) Remove the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance Practices.

(2) Remove the upholstery and floorboard panels below the passenger seat locations. Refer to

Chapter 53, Floorboards and Access Plates - Maintenance Practices.

(3) Do a visual inspection of the stringers for cracks.

(a) Do a visual inspection of the corners around the attach fittings for cracks.

1 Do a visual inspection of the intersections with the forward and aft carry-thru

bulkheads.

(4) If no cracks are found, install the floorboards and upholstery. Refer to Chapter 53, Floorboards

and Access Plates - Maintenance Practices.

(a) Install the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance

Practices.

(5) If cracks are found in the stringer(s), repair or replace the stringer(s). Refer to the Model 208

Structural Repair Manual.

(a) Install the floorboards and upholstery. Refer to Chapter 53, Floorboards and Access Plates

- Maintenance Practices.

(b) Install the passenger seats. Refer to Chapter 25, Passenger Seats - Maintenance

Practices.

5-14-15 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-14

1. Title

Fuselage Skin Doubler at Main Landing Gear Cutout

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 5000 Hours 2500 Hours

3. Fuselage Skin Doubler at Main Landing Gear Cutout Inspection

A. Examine the Fuselage Skin Doubler at the Main Landing Gear Cutout.

(1) Remove the main landing gear fairing. Refer to Chapter 32, Main Landing Gear - Maintenance

Practices.

(2) Do a visual inspection for cracks and gouges in the doubler.

(a) Do a visual inspection of the area where the main landing gear fairing attaches.

(3) If no cracks or gouges are found, install the main landing gear fairing. Refer to Chapter 32, Main

Landing Gear - Maintenance Practices.

(4) If cracks or gouges are found, repair cracks or gouges with the instructions given in Service

Bulletin CAB03-6.

(a) Install the main landing gear fairing. Refer to Chapter 32, Main Landing Gear - Maintenance

Practices.

5-14-16 Page 1

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-50-01

1. Title

Fuselage to Horizontal Stabilizer Attach Fittings

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Fuselage to Horizontal Stabilizer Attach Fittings Inspection

A. Examine the Fuselage to Horizontal Stabilizer Attach Fittings.

(1) Remove the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer - Removal/

Installation.

(2) Examine the horizontal stabilizer forward attach fitting.

(a) Do a visual inspection for cracks in the forward side of the horizontal stabilizer forward

attach fitting.

(b) Do a Nondestructive Testing Inspection (NDI) for cracks at the horizontal stabilizer forward

attach fitting holes. Refer to the Model 208 Nondestructive Testing Manual Part 6.

(3) Examine the horizontal stabilizer aft attach fitting.

(a) Do a visual inspection for cracks in the fuselage side of the horizontal stabilizer aft attach

fitting.

(b) Do an NDI inspection for cracks at the horizontal stabilizer aft attach fitting holes. Refer to

the Model 208 Nondestructive Testing Manual Part 6.

(4) If no cracks are found, install the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer

- Removal/Installation.

(5) If cracks are found, replace the damaged parts. Refer to Chapter 55, Horizontal Stabilizer -

Removal/Installation.

(a) Install the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer - Removal/

Installation.

5-14-17 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-50-02

1. Title

Vertical Stabilizer Attach Points

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours

Vertical Stabilizer Forward and Aft

Attach Point

5000 Hours

Vertical Stabilizer Forward and Aft

Attach Point

SEVERE 16,500 Hours

Vertical Stabilizer Forward Attach

Point

5000 Hours

Vertical Stabilizer Forward Attach

Point

3. Vertical Stabilizer Attach Points Inspection

A. Examine the Vertical Stabilizer Attach Points.

(1) Remove the vertical stabilizer. Refer to Chapter 55, Vertical Stabilizer - Removal/Installation.

(2) Examine the vertical stabilizer forward attach point.

(a) Do a visual inspection for cracks in the fuselage side of the vertical stabilizer forward attach

point.

(b) Do a Nondestructive Inspection (NDI) for cracks at the vertical stabilizer forward attach

point holes. Refer to the Model 208 Nondestructive Testing Manual Part 6.

(3) Examine the vertical stabilizer aft attach point.

(a) Do a visual inspection for cracks in the fuselage side of the vertical stabilizer aft attach

point.

(b) Do an NDI for cracks at the vertical stabilizer aft attach point holes. Refer to the Model 208

Nondestructive Testing Manual Part 6.

(4) If no cracks are found, install the vertical stabilizer. Refer to Chapter 55, Vertical Stabilizer -

Removal/Installation.

(5) If cracks are found, replace the damaged parts or contact Cessna Propeller Aircraft Product

Support for repair procedures. Refer to Chapter 55, Vertical Stabilizer - Removal/Installation.

(a) Install the vertical stabilizer. Refer to Chapter 55, Vertical Stabilizer - Removal/Installation.

5-14-18 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 55-10-01

1. Title

Horizontal Stabilizer Forward and Aft Attach Points

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Horizontal Stabilizer Forward and Aft Attach Points Inspection

A. Examine the Horizontal Stabilizer Forward and Aft Attach Fittings.

(1) Remove the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer - Removal/

Installation.

(2) Examine the horizontal stabilizer forward spar attach fittings.

(a) Do a visual inspection for cracks in the horizontal stabilizer forward spar attach fitting.

(b) Do a Nondestructive Testing Inspection (NDI) for cracks in the horizontal stabilizer forward

spar attach fitting. Refer to the Model 208 Nondestructive Testing Manual Part 6.

(3) Examine the horizontal stabilizer aft spar attach fitting.

(a) Do a visual inspection for cracks in the horizontal stabilizer aft spar attach fitting.

(b) Do an NDI for cracks in the horizontal stabilizer aft spar attach fitting. Refer to the Model

208 Nondestructive Testing Manual Part 6.

(4) If no cracks are found, install the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer

- Removal/Installation.

(5) If cracks are found, replace the horizontal stabilizer attach fitting. Refer to Chapter 55, Horizontal

Stabilizer - Removal/Installation.

(a) Install the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer - Removal/

Installation.

5-14-19 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 55-10-02

1. Title

Horizontal Stabilizer Spars

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

SEVERE 17,500 Hours 1000 Hours

3. Horizontal Stabilizer Forward Spar Cap Inspection

A. Examine the Horizontal Stabilizer Forward Spar Cap.

(1) Remove the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer - Removal/

Installation.

(2) Examine the horizontal stabilizer forward spar upper cap.

(a) Do a visual inspection for cracks in the horizontal stabilizer forward spar upper cap.

(b) Do a Nondestructive Testing Inspection (NDI) for cracks in the horizontal stabilizer forward

spar upper cap between SS 0.00 and SS 9.90. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(3) Examine the horizontal stabilizer forward spar lower cap.

(a) Do a visual inspection for cracks in the horizontal stabilizer forward spar lower cap.

(b) Do an NDI inspection for cracks in the horizontal stabilizer forward spar lower cap between

SS 0.00 and SS 9.90. Refer to the Model 208 Nondestructive Testing Manual Part 6.

(4) If cracks are found, contact Cessna Propeller Aircraft Product Support for repair procedures.

4. Horizontal Stabilizer Aft Spar Inspection

A. Examine the Horizontal Stabilizer Aft Spar Cap.

(1) Examine the horizontal stabilizer aft spar upper cap.

(a) Do a visual inspection for cracks in the horizontal stabilizer aft spar upper cap.

(b) Do a Nondestructive Testing Inspection (NDI) for cracks in the horizontal stabilizer aft spar

upper cap between SS 0.00 and SS 10.60. Refer to the Model 208 Nondestructive Testing

Manual Part 6.

(2) Examine the horizontal stabilizer aft spar lower cap.

(a) Do a visual inspection for cracks in the horizontal stabilizer aft spar lower cap.

(b) Do an NDI for cracks in the horizontal stabilizer aft spar lower cap between SS 0.00 and

SS 10.60. Refer to the Model 208 Nondestructive Testing Manual Part 6.

(3) If no cracks are found, install the horizontal stabilizer. Refer to Chapter 55, Horizontal Stabilizer

- Removal/Installation.

(4) If cracks are found, contact Cessna Propeller Aircraft Product Support for repair procedures.

5-14-20 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-06

1. Title

Fuselage to Wing Carry-Thru Attach Fitting and Bulkhead

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 12,500 Hours 2500 Hours

3. Fuselage to Wing Carry-Thru Attach Fitting and Bulkhead Inspection

A. Examine the fuselage to wing carry-thru attach fitting and bulkhead.

(1) Remove the upholstery and floorboard panels to get access to the fuselage to wing carry-thru

bulkhead. Refer to Chapter 53, Floorboards and Access Plates - Maintenance Practices.

(2) Do a visual inspection of the frames for cracks.

(a) Examine the corners of the frames around the attach fittings.

(3) Do an eddy current inspection on the shown holes. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(4) If no cracks are found, install the floorboards and upholstery. Refer to Chapter 53, Floorboards

and Access Plates - Maintenance Practices.

(5) If cracks are found in the fuselage to wing carry-thru bulkhead, repair the bulkhead. Refer to the

Model 208 Structural Repair Manual.

(6) If cracks are found in the wing carry-thru attach fitting, replace the attach fitting.

5-14-21 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 55-30-01

1. Title

Vertical Stabilizer Spars

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours

Vertical Stabilizer Forward and Aft

Spar, Caps and Attach Holes

5000 Hours

Vertical Stabilizer Forward and Aft

Spar, Caps and Attach Holes

SEVERE 16,500 Hours

Vertical Stabilizer Forward Spar,

Cap and Attach Holes at WL

134.38

5000 Hours

Vertical Stabilizer Forward Spar,

Cap and Attach Holes at WL

134.38

3. Vertical Stabilizer Spars Inspection

A. Examine the Vertical Stabilizer Spars.

(1) Remove the vertical stabilizer. Refer to Chapter 55, Vertical Stabilizer - Removal/Installation.

(2) Examine the vertical stabilizer forward spar, cap, and attach holes.

(a) Do a visual inspection for cracks in the vertical stabilizer forward spar cap.

(b) Do a Nondestructive Testing Inspection (NDI) for cracks at the vertical stabilizer forward

spar attach holes at WL 126.03. Refer to the Model 208 Nondestructive Testing Manual

Part 6.

(c) Do an NDI for cracks at the vertical stabilizer forward spar attach holes at WL 134.28. Refer

to the Model 208 Nondestructive Testing Manual Part 6.

(d) Do an NDI for cracks in the vertical stabilizer forward spar from WL 134.38 to WL 138.00.

Refer to the Model 208 Nondestructive Testing Manual Part 6.

(3) Examine the vertical stabilizer aft spar, cap and attach holes.

(a) Do a visual inspection for cracks in the vertical stabilizer aft spar cap.

(b) Do an NDI for cracks at the vertical stabilizer aft spar attach holes at WL 116.40. Refer to

the Model 208 Nondestructive Testing Manual Part 6.

(c) Do an NDI for cracks at the vertical stabilizer aft spar attach holes at WL 126.12. Refer to

the Model 208 Nondestructive Testing Manual Part 6.

(d) Do an NDI for cracks in the vertical stabilizer aft spar from WL 126.12 to WL 129.00. Refer

to the Model 208 Nondestructive Testing Manual Part 6.

(4) If no cracks are found, install the vertical stabilizer. Refer to Chapter 55, Vertical Stabilizer -

Removal/Installation.

(5) If cracks are found, contact Cessna Propeller Aircraft Product Support for repair procedures.

Refer to Chapter 55, Vertical Stabilizer - Removal/Installation.

(a) Install the vertical stabilizer. Refer to Chapter 55, Vertical Stabilizer - Removal/Installation

5-14-22 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 56-30-01

1. Title

Windshield and Attachment Structure

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Windshield and Attachment Structure Inspection

A. Examine the Windshield and Attachment Structure.

(1) Use the optical prism procedure to examine for cracks in the windshield that start at the fastener

hole(s) and extend to the adjacent fastener holes into the window area that the operator views

out of or the edge of the window. Refer to the Model 208 Nondestructive Testing Manual Part 9.

(2) Do a visual inspection of the windshield retainer for cracks.

(3) Do a visual inspection for cracks in the skin around the windshield.

(4) Do a visual inspection of the door post for cracks out of the fastener holes.

(5) If cracks are found, replace or repair the damaged part(s). Refer to Chapter 56, Flight

Compartment Windows - Removal/Installation or the Model 208 Structural Repair Manual.

5-14-23 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 57-20-01

1. Title

Wing to Carry-Thru Spar Attachment Fitting

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Wing to Carry-Thru Spar Attachment Fittings Inspection

A. Examine the Wing to Carry-Thru Front and Rear Spar Attachment Fittings.

(1) Remove the wing. Refer to Chapter 57, Wings - Removal/Installation.

(2) Examine the front wing-to-carry-thru spar attach fitting. Refer to the Model 208 Nondestructive

Testing Manual.

(a) Do an eddy current inspection for cracks in the front wing-to-carry-thru spar attach fitting

lug. Refer to the Model 208 Nondestructive Testing Manual Part 6.

(b) Do an eddy current inspection for cracks in the front wing-to-carry-thru spar attach fitting

holes.

(3) Examine the rear wing-to-carry-thru spar attach fitting. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(a) Do an eddy current inspection for cracks in the rear wing-to-carry-thru spar attach fitting

lug.

(b) Do an eddy current inspection for cracks in the rear wing-to-carry-thru spar attach fitting

holes.

(4) If no cracks are found, install the wing. Refer to Chapter 57, Wings - Removal/Installation.

(5) If cracks are found, replace the wing-to-carry-thru spar attach fitting. Refer to Chapter 57, Wings

- Removal/Installation.

(a) Install the wing. Refer to Chapter 57, Wings - Removal/Installation.

5-14-24 Page 1

© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 57-20-02

1. Title

Front Spar Lower Cap Inboard of WS 141.20

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Front Spar Lower Cap Inboard of WS 141.20 Inspection

A. Examine the wing Front Spar Lower Cap Inboard of WS 141.20.

(1) Remove the access panels on the bottom of the wing to gain access to the front spar. Refer to

Chapter 6, Access Plates and Panels Identification - Description and Operation.

(2) Examine the wing front spar lower cap inboard of WS 141.20.

(a) Do a visual inspection for cracks in the wing front spar lower cap inboard of WS 141.20.

(b) Do a Nondestructive Testing Inspection (NDI) for cracks in the wing front spar lower cap

between the wing attach fittings and WS 141.20. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(3) If no cracks are found, install the access panels on the bottom of the wing. Refer to Chapter 6,

Access Plates and Panels Identification - Description and Operation.

(4) If cracks are found, contact Cessna Propeller Aircraft Product Support for repair procedures.

(a) Install the access panels on the bottom of the wing. Refer to Chapter 6, Access Plates and

Panels Identification - Description and Operation.

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© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 57-20-03

1. Title

Rear Spar Lower Cap Inboard of WS 141.20

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Rear Spar Lower Cap Inboard of WS 141.20 Inspection

A. Examine the Wing Rear Spar Lower Cap Inboard of WS 141.20.

(1) Remove the access panels on the bottom of the wing to get access to the rear spar. Refer to

Chapter 6, Access Plates and Panels Identification - Description and Operation.

(2) Examine the wing rear spar lower cap inboard of WS 141.20.

(a) Do a visual inspection for cracks in the wing rear spar lower cap inboard of WS 141.20.

(b) Do a Nondestructive Testing Inspection (NDI) for cracks in the wing rear spar lower cap

between the wing attach fitting and WS 141.20. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(3) If no cracks are found, install the access panels on the bottom of the wing. Refer to Chapter 6,

Access Plates and Panels Identification - Description and Operation.

(a) Install the flaps. Refer to Chapter 57 Flaps - Maintenance Practices.

(4) If cracks are found, contact Cessna Propeller Aircraft Product Support for repair procedures;

Telephone (316) 517-5800 or Fax (316) 517-7271.

(a) Install the access panels on the bottom of the wing. Refer to Chapter 6, Access Plates and

Panels Identification - Description and Operation.

(b) Install the flaps. Refer to Chapter 57 Flaps - Maintenance Practices.

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© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 57-50-01

1. Title

Flap Tracks

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 15,000 Landings 3000 Landings

3. Flap Tracks Inspection

A. Examine the Flap Tracks.

(1) Remove the flap. Refer to Chapter 57, Flaps - Maintenance Practices.

(2) Examine the inboard, center and outboard flap tracks. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(a) Do a Nondestructive Testing Inspection (NDI) for cracks in the inboard flap track at WS

53.00.

(b) Do an NDI for cracks in the center flap track at WS 126.50.

(c) Do an NDI for cracks in the outboard flap track at WS 214.30.

(3) If no cracks are found, install the flap. Refer to Chapter 57, Flaps - Maintenance Practices.

(4) If cracks are found, replace the flap track(s). Refer to Chapter 57, Flaps - Maintenance Practices.

(a) Install the flap. Refer to Chapter 57, Flaps - Maintenance Practices.

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© Cessna Aircraft Company Nov 3/2003
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 57-60-01

1. Title

Wing Strut Fittings

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 10,000 Hours 5000 Hours

SEVERE 5000 Hours 3600 Hours

3. Wing Strut Fittings Inspection

A. Examine the Wing Strut Attach Fittings.

(1) Remove the wing strut-to-wing fairing. Refer to Chapter 57, Wings - Removal/Installation.

(2) Remove the wing strut. Refer to Chapter 57, Wings - Removal/Installation.

(3) Examine the wing strut upper attach fitting and holes. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(a) Do an eddy current inspection for cracks in the wing strut upper attach fitting holes.

(b) Do an eddy current inspection for cracks in the wing strut upper attach fitting extrusion radii.

(c) Do an eddy current inspection for cracks in the wing strut upper attach fitting lugs.

(4) Examine the wing strut lower attach fitting and holes. Refer to the Model 208 Nondestructive

Testing Manual Part 6.

(a) Do an eddy current inspection for cracks in the wing strut lower attach fitting holes.

(b) Do an eddy current inspection for cracks in the wing strut lower attach fitting extrusion radii.

(c) Do an eddy current inspection for cracks in the wing strut lower attach fitting lugs.

(5) If no cracks are found, install the wing strut. Refer to Chapter 57, Wings - Removal/Installation.

(a) Install the wing strut-to-wing fairing. Refer to Chapter 57, Wings - Removal/Installation.

(6) If cracks are found, replace the damaged parts. Refer to Chapter 57, Wings - Removal/

Installation.

(a) Install the wing strut. Refer to Chapter 57, Wings - Removal/Installation.

(b) Install the wing strut-to-wing fairing. Refer to Chapter 57, Wings - Removal/Installation.

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 57-60-02

1. Title

Wing Strut Attachment to Front Spar

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

SEVERE 20,000 Hours See Note 1

NOTE 1: For nominal/standard bolt size, Part Number S3461-77: 5000 Hours; for 1/64 inch oversize bolt size,

Part Number S3461-163: 4400 Hours; for 1/32 inch oversize bolt size, Part Number S3461-164: 3600

Hours.

3. Wing Strut Attachment to Front Spar Inspection

A. Examine the Wing Strut Attachment to Front Spar.

(1) Remove the wing strut-to-wing fairing. Refer to Chapter 57, Wings - Removal/Installation.

(2) Remove the wing strut. Refer to Chapter 57, Wings - Removal/Installation.

(3) Examine the forward spar wing strut attach fitting. Refer to the Model 208 Nondestructive Testing

Manual Part 6.

(a) Do an eddy current inspection for cracks in the forward spar wing strut attach fitting.

(b) Do an eddy current inspection for cracks in the forward spar wing strut attach fitting lug.

(4) If no cracks are found, install the wing strut. Refer to Chapter 57, Wings - Removal/Installation.

(a) Install the wing strut-to-wing fairing. Refer to Chapter 57, Wings - Removal/Installation.

(5) If cracks are found, replace the forward spar wing strut attach fitting. Refer to Chapter 57, Wings

- Removal/Installation.

(a) Install the wing strut. Refer to Chapter 57, Wings - Removal/Installation.

(b) Install the wing strut-to-wing fairing. Refer to Chapter 57, Wings - Removal/Installation.

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 71-20-01

1. Title

Engine Truss and Ring Assembly

2. Inspection Compliance

INITIAL REPEAT

TYPICAL 20,000 Hours 5000 Hours

3. Engine Truss and Ring Assembly Inspection

A. Examine the Engine Truss and Ring Assembly.

(1) Remove the engine cowling. Refer to Chapter 71, Engine Cowling and Nose Cap - Maintenance

Practices.

(2) Examine the engine truss and ring assemblies. Refer to the Model 208 Nondestructive Testing

Manual Part 8.

(a) Do a Nondestructive Inspection (NDI) for cracks in the engine mount ring assembly.

(b) Do an NDI for cracks in the engine mount assembly at the engine mount ring assembly.

(c) Do an NDI for cracks in the engine mount assembly at the firewall attachments.

(3) If no cracks are found, install the engine cowling. Refer to Chapter 71, Engine Cowling and

Nose Cap - Maintenance Practices.

(4) If cracks are found, replace the damaged parts. Refer to Chapter 71, Engine Cowling and Nose

Cap - Maintenance Practices.

(a) Install the engine cowling. Refer to Chapter 71, Engine Cowling and Nose Cap -

Maintenance Practices.

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

SCHEDULED INSPECTION CHECKS

1. Description

A. Air Conditioning (Chapter 21).

(1) Cabin Heater and Windshield Defroster Operational Check.

(a) Pull out the Ground Heat Control and check for airflow then place the control in the flight

position.

(b) Turn on bleed air heat switch and rotate the temperature control fully clockwise.

(c) Operate the forward and aft cabin valve and defrost valve, and check for proper airflow.

(d) Pull out the firewall shutoff control and make sure that the airflow stops.

(e) Return the firewall valve to open make sure that the airflow returns.

(f) Turn heater system off with the temperature control knob and make sure that the airflow

stops completely.

(g) Turn off the bleed air switch.

B. Autoflight (Chapter 22).

(1) King Yaw Damper Actuator Slip Clutch Adjustment.

(a) Make sure that the yaw damper slip clutch torque setting is 50 inch-pounds, +5 or -5 inchpounds.

(2) King Yaw Damper Cable Tension Setting.

(a) Make sure that the yaw bridal cable tension is 20 pounds, +5 or -5 pounds.

(3) 400B Autopilot.

(a) Control Unit, Accessory Unit, Autopilot Roll Trim Indicator, Mode Selector Unit, Flight

Director Indicator (FDI), Horizontal Situation Indicator (HSI), Control Wheel Mounted

Autopilot Electric Trim Disconnect Pushbutton (AP/TRM/DISC), Control Wheel mounted

Pitch Synchronization (Pitch Synch) Switch, Throttle Control mounted Go-Around (GA)

Switch, Mode Selector White Light and Green Light Dimming Controls, Annunciation

Panel Light and Aileron Trim Knob.

(b) Make sure the bridal cable tension for the aileron and elevator is 10 to 15 pounds.

(c) Elevator Trim Cable tension: Raise or lower supports to point that when 5 pounds of

pressure is applied to the chain, the chain will produce 0.40 inch total vertical travel.

(d) Check actuator clutch torque setting: Aileron and Elevator setting is 25 inch-pounds, +5 or

-5 inch-pounds; Elevator trim setting is 30 inch-pounds, +5 or -5 inch-pounds.

(4) King Flight Control System (KFC-150).

(a) Autopilot and Flight Director Indicator, Remote Mode Annunciator Autopilot Control Wheel

Switch Assembly, Autopilot Disconnect/Trim Interrupt (AP Dis/Trim Inner) Switch, Control

Wheel Steering (CWS) Button, Manual Electric Trim Control Switches.

(b) Bridal Cable Tensions: Aileron cable tension setting is 20 pounds, +5 or -5 pounds for the

208 and is 12 pounds, +2 or -2 pounds for the 208B. Elevator cable tension setting is 20

pounds, +5 or -5 pounds for both the 208 and 208B.

(c) Actuator clutch torque settings: Aileron actuator clutch torque setting is 33 inch-pounds, +3

or -3 inch-pounds, for 208 and is 38 inch-pounds, +4 or -4 inch-pounds, for 208B. Elevator

actuator clutch torque setting is 43 inch-pounds, +4 or -4 inch-pounds for both the 208 and

208B.

(5) King Flight Control System (KFC-250).

(a) Mode Controller, Mode Annunciator, Slaving Accessory and Compensation Unit, Autopilot

Control Wheel Switch Cap consisting of Autopilot Control Wheel Switch Assembly,

Disconnect Interrupt (A/P Disc/Trim Inner) Switches, Electrical Trim Control Switches and

Power Lever Go Around Button.

(b) Actuator Clutch Torque Setting: Aileron actuator clutch torque setting is 47 inch-pounds,

+5 or -5 inch-pounds; Elevator actuator clutch torque setting is 60 inch-pounds +5 or -5

inch-pounds.

(c) Bridal Cable Tensions: Aileron and Elevator setting is 20 pounds, +5 or -5 inch-pounds.

(d) Aileron cable tension setting is 20 pounds, +5 or -5 pounds.

(e) Elevator cable tension setting is 20 pounds, +5 or -5 pounds.

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MODEL 208

MAINTENANCE MANUAL

C. Electrical Power (Chapter 24).

(1) Standby Alternator Excitation.

(a) With engine running, Standby Power switch OFF, both Avionics Switches OFF, trip the

Generator Switch OFF and turn OFF the Battery switch.

(b) Turn Standby Power Switch ON and make sure that the alternator is functioning properly.

(c) Turn Battery Switch ON and reset the generator.

(d) Make sure that the Generator Off annunciator light goes out.

(2) Avionics Standby Power Diode Check.

(a) Set the switches and circuit breakers as shown in Table 1 Step 1.

1 Make sure that the left flood light and PFD 1 are on.

(b) Set the switches and circuit breakers as shown in Table 1 Step 2.

1 Make sure that the left flood light is off and PFD 1 is on.

NOTE: If the left flood light does not go off, the diode (DI001) does not operate

correctly or is installed backwards..

(c) Set the switches and circuit breakers as shown in Table 1 Step 3.

1 Make sure that the left flood light and PFD 1 are on.

(d) If the result of the check is different from the expected results listed above, make sure that

the installation and operation of the diode is correct.

Table 1. Avionics Switches and Circuit Breaker Settings.

AVIONICS SWITCHES CIRCUIT BREAKERS

BUS 1 PWR BUS 2 PWR

STEP

1 2 AVIONICS STBY

PWR STBY

PWR

(BUS 2)

TOP MID BOTTOM TOP MID BOTTOM

1 ON OFF OFF Closed Open Open Open Closed Open Open

2 ON OFF ON Closed Open Open Open Open Open Open

3 OFF OFF On Closed Open Open Open Closed Open Open

D. Equipment and Furnishings (Chapter 25).

(1) Hourmeter operational check.

(a) Hold the vane in the ON position and have an observer make sure the hourmeter operates.

E. Fire Detection (Chapter 26).

(1) Engine Fire Detection Test.

(a) Press the test button and make sure the wailing siren and ENGINE FIRE light comes on.

F. Flight Controls (Chapter 27).

(1) Aileron Friction Band Check.

(a) The desired friction band without an autopilot installed is 6 pounds or less for the Aileron;

the desired friction band with an autopilot installed is 8 pounds or less for the Aileron.

(2) Rudder Gust Lock.

(a) Move the fuel condition lever to LOW IDLE to check for positive automatic disengagement.

(3) Elevator Friction Band Check.

(a) (Cessna 400B and 400B IFCS equipped airplanes). The desired friction band without an

autopilot installed is 15 pounds or less for the elevator; the desired friction band with an

autopilot installed is 20 pounds.

(b) (KFC 150 and KFC 250 Flight Control System and KAP 150 Autopilot equipped airplanes).

The desired friction band without an autopilot installed is 15 pounds or less for the elevator;

the desired friction band with an autopilot installed is 20 pounds.

(4) Elevator Trim Tabs.

(a) Examine the trim tab skins for cracks, loose rivets, and security; and trim tab hinge for

security, cracks, and evidence of damage.

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(b) Inspect hinge pin for proper installation at hinge pin retainer.

(c) Inspect horn(s) and pushrod(s) for evidence of damage and security.

(d) Inspect horn(s) and pushrod bolts for condition and proper safetying of nuts with cotter

pins.

(5) Elevator Trim Tab Actuators.

(a) Check that the bolts are secure (torque putty not broken).

(b) Looking through the actuator access holes in the horizontal stabilizer, examine the chain

guard for security. Check that the guard attach screws are tight.

(c) Examine the actuator rods and bearings for condition and security. Examine the pushrod

bolts for presence of safety wire on nuts and cotter pins. Examine the actuator chain for

condition.

(d) Make sure the chain to cable attach link is tight.

(6) Stall Warning System.

(a) Horn - Hold the lift detector up (left wing) and listen for audible tone with power on.

(b) Heater - Turn ON STALL HEAT switch for 30 seconds, then OFF. Make sure that the vane

heats and also that the face of the detector heats.

G. Fuel (Chapter 28).

(1) Fuel Boost Pump Operational Test.

(a) Place the Fuel Boost Pump Switch in the Normal position (power on).

1 The AUX FUEL PUMP ON Annunciator and the FUEL PRESSURE LOW annunciator

should continue to cycle on and off.

(b) Put the Fuel Boost Pump Switch in the ON position.

1 Verify the AUX FUEL PUMP ON annunciator stays on and the FUEL PRESSURE

LOW annunciator goes off.

2 Make sure that the Fuel Flow gauge indicates no fuel flow.

(2) Fuel Shutoff Control.

(a) Check the fuel shutoff control for freedom of movement and for positive shutoff of fuel at

the firewall.

(b) With the control pulled OFF, open the drain valve on the firewall fuel filter and make sure

no fuel drains.

(3) Fuel Filter Inspection.

(a) If indications of flakes or particles of paint (wing internal primer) are noted when inspecting

fuel filter, refer to Chapter 28, Fuel Tanks - Maintenance Practices.

H. Ice and Rain Protection (Chapter 30).

(1) Propeller De-ice System - (engine running) (without TKS).

(a) Turn the propeller de-ice system to ON, Make sure that the ammeter needle indicates in

the green arc. Every 90 seconds the system should cycle from ON to OFF and then ON

again.

(b) Place the control switch in the MANUAL position and make sure that the de-ice system is

operating by looking at the ammeter gauge.

(2) Wing De-ice System - (engine running) (without TKS).

(a) With Ng speed at 65%, move the wing De-ice Switch. Observe that all three cycles occur

and a de-ice annunciator light illuminates during each cycle.

(b) Hold the switch in the MANUAL position. Make sure all the boots inflate and the DE-ICE

PRESSURE annunciator light comes on.

(3) 100 Hour Operational Check without G1000 (with TKS).

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

WARNING: For health and environmental data, review the applicable

Material Safety Data Sheet (MSDS).

WARNING: Before you disconnect components of the TKS anti-ice

system, slowly loosen the coupling that is connected to

the component because it is possible that high pressure

is still in the system.

WARNING: Immediately remove (clean) or contain all the TKS fluid that

is spilled. TKS fluid on the floor will cause a slip hazard.

WARNING: Discard all unwanted TKS fluid and/or dirty cloths

correctly. TKS fluid is a hazardous waste and must be

discarded in accordance with approved procedures.

CAUTION: Use only approved TKS fluids. Approved fluids, in accordance

with specification DDT 406B, are normally 80% to 85% monoethylene glycol, 5% isopropyl alcohol, and 10% to 20% deionized water. Fluid density is approximately 9.2 lbs/gal.

CAUTION: Use only clean, filtered fluid in the TKS system. Contamination

will cause fluid blockage and/or damage to the porous panel.

(a) Remove the engine cowlings.

1 Do a visual inspection for correct installation and condition of the TKS components.

a Examine the propeller boots and propeller feed tubes for damage.

b Examine the TKS supply hoses and propeller hose assembly for correct

installation and signs of fluid leaks.

c Examine the propeller nozzle for correct installation. Make sure that the nozzle

will direct a stream of fluid into the propeller slinger when the system is operated

in the HIGH mode.

d Install the engine cowlings.

(b) Apply power to the airplane.

(c) Push the annunciator test switch.

1 Make sure the three elements of the TKS annunciator come on.

(d) If necessary, fill the TKS tank until the fluid shows in the sight glass.

(e) Make sure that the WARN annunciator operates correctly.

1 Set the PRIMARY switch to the HIGH position.

a Make sure that the WARN annunciator goes off as the pressure increases.

2 Make sure that the CAUT annunciator does not come on.

NOTE: If the CAUT annunciator comes on, the replacement of the system fliters

is usually necessary.

3 Monitor the system quantity gage to make sure that a low fluid level does not exist.

4 Set the PRIMARY switch to the OFF position.

5 Set the BACKUP switch to the ON position.

a Make sure that the WARN annunciator goes off as the pressure increases.

(f) Make sure that the ANTI-ICE ON annunciator operates correctly.

1 Set the PRIMARY switch to the NORM position.

a Make sure that the ANTI-ICE ON annunciator comes on.

2 Set the PRIMARY switch to the OFF position.

a Make sure that the ANTI-ICE ON annunciator goes off.

3 Set the PRIMARY switch to the HIGH position.

a Make sure that the ANTI-ICE ON annunciator comes on.

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MODEL 208

MAINTENANCE MANUAL

4 Set the PRIMARY switch to the OFF position.

a Make sure that the ANTI-ICE ON annunciator goes off.

(g) Make sure that the windshield anti-ice system operates correctly.

1 Set the momentary MAX FLOW switch to the WINDSHIELD position.

2 Make sure that the windshield pump operates for at least four seconds after the

release of the switch.

3 Make sure that the anti-ice fluid comes out of the spray bar.

4 Make sure that no holes in the spray bar are blocked.

(h) Make sure that the airframe anti-ice system operates correctly.

1 Set the PRIMARY switch to the HIGH position.

2 Make sure that anti-ice fluid comes out evenly over the porous panels.

NOTE: At high temperatures (temperature 70°F or higher) a “waterline” can be

seen at the top of some panels because of the pressure is not sufficient to

remove the trapped air. This condition is permitted unless the performance

of the panel in icing conditions shows that this is other than a temporary

occurrence.

3 Set the PRIMARY switch to the OFF position.

(i) Make sure that the airframe maximum flow anti-ice system operates correctly.

1 Set the PRIMARY switch to the NORM or HIGH position.

2 Set the momentary MAX FLOW switch to the AIRFRAME position.

a Make sure that both pumps operate at the same time and supply anti-ice fluid

to the system.

3 After waiting for approximately two minutes, make sure that the system returned to

mode set on the PRIMARY switch.

4 Set the PRIMARY switch to the OFF position.

(4) 100 Hour Operational Check with G1000 (with TKS).

WARNING: For health and environmental data, review the applicable

Material Safety Data Sheet (MSDS).

WARNING: Before you disconnect components of the TKS anti-ice

system, slowly loosen the coupling that is connected to

the component because it is possible that high pressure

is still in the system.

WARNING: Immediately remove (clean) or contain all the TKS fluid that

is spilled. TKS fluid on the floor will cause a slip hazard.

WARNING: Discard all unwanted TKS fluid and/or dirty cloths

correctly. TKS fluid is a hazardous waste and must be

discarded in accordance with approved procedures.

CAUTION: Use only approved TKS fluids. Approved fluids, in accordance

with specification DDT 406B, are normally 80% to 85% monoethylene glycol, 5% isopropyl alcohol, and 10% to 20% deionized water. Fluid density is approximately 9.2 lbs/gal.

CAUTION: Use only clean, filtered fluid in the TKS system. Contamination

will cause fluid blockage and/or damage to the porous panel.

(a) Remove the engine cowlings.

1 Do a visual inspection for correct installation and condition of the TKS components.

a Examine the propeller boots and propeller feed tubes for damage.

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b Examine the TKS supply hoses and propeller hose assembly for correct

installation and signs of fluid leaks.

c Examine the propeller nozzle for correct installation. Make sure that the nozzle

will direct a stream of fluid into the propeller slinger when the system is operated

in the HIGH mode.

d Install the engine cowlings.

(b) Apply power to the airplane.

(c) If necessary, fill the TKS tank until the fluid shows in the sight glass.

(d) Make sure that the A-ICE PRESS LOW red CAS message operates correctly.

1 Set the PRIMARY switch to the HIGH position.

a Make sure that the A-ICE PRESS LOW red CAS message goes off on the

applicable EICAS display as the pressure increases.

2 Make sure that the A-ICE PRESS HIGH amber CAS message does not show on the

applicable EICAS display.

NOTE: If the A-ICE PRESS HIGH amber message comes on, the replacement of

the system filters is usually necessary.

3 Monitor the MFD to make sure that a low fluid level does not exist.

4 Set the PRIMARY switch to the OFF position.

5 Set the BACKUP switch to the ON position.

a Make sure that the A-ICE PRESS LOW red CAS message goes off on the

applicable EICAS display as the pressure increases.

(e) Make sure that the A-ICE NORM white CAS messages operate correctly.

1 Set the PRIMARY switch to the NORM position.

a Make sure that the A-ICE NORM white CAS message shows on the applicable

EICAS display.

2 Set the PRIMARY switch to the OFF position.

a Make sure that the A-ICE NORM white CAS message goes off on the applicable

EICAS display.

(f) Make sure that the A-ICE HIGH white CAS messages operate correctly.

1 Set the PRIMARY switch to the HIGH position.

a Make sure that the A-ICE HIGH white CAS message shows on the applicable

EICAS display.

2 Set the PRIMARY switch to the OFF position.

a Make sure that the A-ICE HIGH white CAS message goes off on the applicable

EICAS display.

(g) Make sure that the windshield anti-ice system operates correctly.

1 Set the momentary MAX FLOW switch to the WINDSHIELD position.

2 Make sure that the windshield pump operates for at least four seconds after the

release of the switch.

3 Make sure that the anti-ice fluid comes out of the spray bar.

4 Make sure that no holes in the spray bar are blocked.

(h) Make sure that the airframe anti-ice system operates correctly.

1 Set the PRIMARY switch to the HIGH position.

2 Make sure that anti-ice fluid comes out evenly over the porous panels.

NOTE: At high temperatures (temperature 70°F or higher) a “waterline” can be

seen at the top of some panels because of the pressure is not sufficient to

remove the trapped air. This condition is permitted unless the performance

of the panel in icing conditions shows that this is other than a temporary

occurrence.

3 Set the PRIMARY switch to the OFF position.

(i) Make sure that the airframe maximum flow anti-ice system operates correctly.

1 Set the PRIMARY switch to the NORM or HIGH position.

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2 Set the momentary MAX FLOW switch to the AIRFRAME position.

a Make sure that both pumps operate at the same time and supply anti-ice fluid

to the system.

3 After waiting for approximately two minutes, make sure that the system returned to

mode set on the PRIMARY switch.

4 Set the PRIMARY switch to the OFF position.

(5) Annual Operational Check without G1000 (with TKS).

WARNING: For health and environmental data, review the applicable

Material Safety Data Sheet (MSDS).

WARNING: Before you disconnect components of the TKS anti-ice

system, slowly loosen the coupling that is connected to

the component because it is possible that high pressure

is still in the system.

WARNING: Immediately remove (clean) or contain all the TKS fluid that

is spilled. TKS fluid on the floor will cause a slip hazard.

WARNING: Discard all unwanted TKS fluid and/or dirty cloths

correctly. TKS fluid is a hazardous waste and must be

discarded in accordance with approved procedures.

CAUTION: Use only approved TKS fluids. Approved fluids, in accordance

with specification DDT 406B, are normally 80% to 85% monoethylene glycol, 5% isopropyl alcohol, and 10% to 20% deionized water. Fluid density is approximately 9.2 lbs/gal.

CAUTION: Use only clean, filtered fluid in the TKS system. Contamination

will cause fluid blockage and/or damage to the porous panel.

(a) If not already completed, do the 100 Hour Operational Check (with TKS).

(b) Remove the necessary access panels. Refer to Chapter 6, Access Plates and Panels

Identification - Description and Operation.

(c) Do a visual inspection for correct installation and condition of the TKS components, supply

lines, and wiring.

(d) Make sure the CAUT annunciator operates correctly.

1 Make sure the TKS tank is empty.

a Make sure that the gage shows 0 gallons of fluid.

2 Put 1.0 gallon of fluid in the tank.

3 Set the PRIMARY switch in the HIGH position.

a Make sure that the CAUT annunciator comes on.

4 Add 2.0 gallons of fluid in the tank.

5 Set the PRIMARY switch in the HIGH position.

a Make sure that the CAUT annunciator does not come on.

(e) Do a check of the pump fluid delivery rate.

1 Fill the TKS tank to the minimum dispatch level. Refer to Chapter 12, TKS Anti-Ice

System - Servicing.

NOTE: The minimum dispatch level is when the bottom of the ball in the sight

glass is just above the line on the sight glass.

2 Disconnect and cap the nylon tube from the filter assembly outlet.

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3 Use TKS nylon tube fittings as necessary and connect a tube to the filter assembly

outlet so it will reach into an empty bucket.

NOTE: The fluid will flow into the bucket during the system operation.

4 Set the PRIMARY switch to the HIGH position.

5 Operate the system for a timed period not more than 30 minutes.

6 Set the PRIMARY switch to the OFF position.

7 Measure the amount of fluid necessary to fill the tank again to the minimum dispatch

level or the amount of fluid collected in the bucket.

a Empty the bucket in accordance with approved procedures.

8 Calculate the fluid delivery rate.

NOTE: The permitted limit is 33.22 ounces/minute, -0.00 or +0.34 ounces/minute.

9 Fill the TKS tank again to the minimum dispatch level. Refer to Chapter 12, TKS

Anti-Ice System - Servicing.

10 Set the BACKUP switch to the ON position.

11 Operate the system for a timed period not more than 30 minutes.

12 Set the BACKUP switch to the OFF position.

13 Measure the amount of fluid necessary to fill the tank again to the minimum dispatch

level or the amount of fluid collected in the bucket.

14 Calculate the fluid delivery rate.

NOTE: The permitted limit is 33.22 ounces/minute, -0.00 or +0.34 ounces/minute.

15 If no additional checks that include the filter assembly outlet are necessary, do the

steps that follow:

a Disconnect the tube from the filter assembly outlet.

CAUTION: Do not use the seals again after you loosen or

disconnect a tube coupling. Replace the 3/16-inch

and 5/16-inch sealing ring and/or 1/2-inch O-ring,

as applicable, when you assemble a tube coupling.

Examine the seal for damage and make sure that it

is in the correct position in the coupling as shown in

Figure 1. This will help to prevent fluid leakage from

the coupling.

b Remove the cap and install new seals in the couplings as shown in Figure 1.

c Connect the nylon tube to the filter assembly outlet.

d Complete a leak check of any fittings that were disconnected.

16 Empty the bucket in accordance with approved procedures.

(f) Do a check of the high pressure warning switch.

1 Disconnect and cap the nylon tube from the filter assembly outlet.

2 Use TKS nylon tube fittings as necessary and connect a tube to the filter assembly

outlet so it will reach into a bucket.

3 Put a cap on the end of the tube.

4 Operate the system in the HIGH mode.

5 Monitor that the CAUT annunciator comes on in less than 30 seconds and stop the

system operation.

NOTE: Normally the CAUT annunciator will come on in 10 to 15 seconds.

a If the CAUT annunciator does not come on in 30 seconds, stop the system

operation.

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b Remove the cap to release the pressure from the system.

c Repair the CAUT annunciator circuit as necessary.

6 If no additional checks that include the filter assembly outlet are necessary, do the

steps that follow:

a Disconnect the tube from the filter assembly outlet.

CAUTION: Do not use the seals again after you loosen or

disconnect a tube coupling. Replace the 3/16-inch

and 5/16-inch sealing ring and/or 1/2-inch O-ring,

as applicable, when you assemble a tube coupling.

Examine the seal for damage and make sure that it

is in the correct position in the coupling as shown in

Figure 1. This will help to prevent fluid leakage from

the coupling.

b Remove the cap and install new seals in the couplings as shown in Figure 1.

c Connect the nylon tube to the filter assembly outlet.

7 Empty the bucket in accordance with approved procedures.

(g) Do a check of the low pressure warning switch.

1 Disconnect and cap the nylon tube from the filter assembly outlet.

2 Use TKS nylon tube fittings as necessary and connect a tube to the filter assembly

outlet so it will reach into a bucket.

NOTE: The fluid will flow into the bucket during the system operation.

3 Remove the tail cone access panel. Refer to Chapter 6, Access Plates and Panels

Identification - Description and Operation.

4 Disconnect the tail bracket electrical connection to the proportioning unit.

a Connect a jumper from pin 3 of the tail bracket electrical connection to pin 3 of

the proportioning unit electrical connection.

b Connect a jumper from pin 2 of the tail bracket electrical connection to pin 2 of

the proportioning unit electrical connection.

5 Operate the system in the HIGH mode.

a Make sure that after 15 seconds the WARN light comes on.

6 Disconnect the jumper from pin 2 of the tail bracket electrical connection to pin 2 of

the proportioning unit electrical connection.

7 Connect a jumper from pin 1 of the tail bracket electrical connection to pin 1 of the

proportioning unit electrical connection.

8 Operate the system in the HIGH mode.

a Make sure that after 15 seconds the WARN light comes on.

9 Disconnect the jumper wires from pins 1 and 3 of the bracket electrical connection to

pins 1 and 3 of the proportioning unit electrical connection.

10 Connect the tail bracket electrical connection to the proportioning unit.

11 Install the tail cone access panel. Refer to Chapter 6, Access Plates and Panels

Identification - Description and Operation.

12 Disconnect the tube from the filter assembly outlet.

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CAUTION: Do not use the seals again after you loosen or disconnect

a tube coupling. Replace the 3/16-inch and 5/16-inch

sealing ring and/or 1/2-inch O-ring, as applicable, when

you assemble a tube coupling. Examine the seal for

damage and make sure that it is in the correct position

in the coupling as shown in Figure 1. This will help to

prevent fluid leakage from the coupling.

13 Remove the cap and install new seals in the couplings as shown in Figure 1.

14 Connect the nylon tube to the filter assembly outlet.

15 Empty the bucket in accordance with approved procedures.

(h) Do a check of the windshield pump fluid delivery rate.

1 Get access to the windshield pump.

a Remove the bulkhead aft of the TKS equipment/tanks assembly found in the

cargo pod.

2 Disconnect and cap the 3/16-inch nylon tube from the pump outlet.

3 Use TKS nylon tube fittings as necessary and connect a tube to the pump outlet so

it will reach into a bucket.

NOTE: The fluid will flow into the bucket during the system operation.

4 Set the momentary MAX FLOW switch to WINDSHIELD position.

5 Collect the fluid over a timed period of 5 seconds.

6 Make sure that there is more than 0.84 ounces of fluid.

7 Disconnect the tube from the pump outlet.

CAUTION: Do not use the seals again after you loosen or disconnect

a tube coupling. Replace the 3/16-inch and 5/16-inch

sealing ring and/or 1/2-inch O-ring, as applicable, when

you assemble a tube coupling. Examine the seal for

damage and make sure that it is in the correct position

in the coupling as shown in Figure 1. This will help to

prevent fluid leakage from the coupling.

8 Remove the cap and install new seals in the couplings as shown in Figure 1.

9 Connect the 3/16-inch nylon tube to the pump outlet.

10 Empty the bucket in accordance with approved procedures.

(6) Annual Operational Check with G1000 (with TKS).

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WARNING: For health and environmental data, review the applicable

Material Safety Data Sheet (MSDS).

WARNING: Before you disconnect components of the TKS anti-ice

system, slowly loosen the coupling that is connected to

the component because it is possible that high pressure

is still in the system.

WARNING: Immediately remove (clean) or contain all the TKS fluid that

is spilled. TKS fluid on the floor will cause a slip hazard.

WARNING: Discard all unwanted TKS fluid and/or dirty cloths

correctly. TKS fluid is a hazardous waste and must be

discarded in accordance with approved procedures.

CAUTION: Use only approved TKS fluids. Approved fluids, in accordance

with specification DDT 406B, are normally 80% to 85% monoethylene glycol, 5% isopropyl alcohol, and 10% to 20% deionized water. Fluid density is approximately 9.2 lbs/gal.

CAUTION: Use only clean, filtered fluid in the TKS system. Contamination

will cause fluid blockage and/or damage to the porous panel.

(a) If not already completed, do the 100 Hour Operational Check (with TKS).

(b) Remove the necessary access panels. Refer to Chapter 6, Access Plates and Panels

Identification - Description and Operation.

(c) Do a visual inspection for correct installation and condition of the TKS components, supply

lines, and wiring.

(d) Make sure the A-ICE FLUID LO amber CAS message operates correctly.

1 Make sure the TKS tank is empty.

a Make sure that the gage shows 0 gallons of fluid.

2 Put 1.0 gallon of fluid in the tank.

3 Set the PRIMARY switch in the HIGH position.

a Make sure that the A-ICE FLUID LO amber CAS message shows on the

applicable EICAS display..

4 Add 2.0 gallons of fluid in the tank.

5 Set the PRIMARY switch in the HIGH position.

a Make sure that the A-ICE FLUID LO amber CAS message does not come on.

(e) Do a check of the pump fluid delivery rate.

1 Fill the TKS tank to the minimum dispatch level. Refer to Chapter 12, TKS Anti-Ice

System - Servicing.

NOTE: The minimum dispatch level is when the bottom of the ball in the sight

glass is just above the line on the sight glass.

2 Disconnect and cap the nylon tube from the filter assembly outlet.

3 Use TKS nylon tube fittings as necessary and connect a tube to the filter assembly

outlet so it will reach into an empty bucket.

NOTE: The fluid will flow into the bucket during the system operation.

4 Set the PRIMARY switch to the HIGH position.

5 Operate the system for a timed period not more than 30 minutes.

6 Set the PRIMARY switch to the OFF position.

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7 Measure the amount of fluid necessary to fill the tank again to the minimum dispatch

level or the amount of fluid collected in the bucket.

a Empty the bucket in accordance with approved procedures.

8 Calculate the fluid delivery rate.

NOTE: The permitted limit is 33.22 ounces/minute, -0.00 or +0.34 ounces/minute.

9 Fill the TKS tank to the minimum dispatch level. Refer to Chapter 12, TKS Anti-Ice

System - Servicing.

10 Set the BACKUP switch to the ON position.

11 Operate the system for a timed period not more than 30 minutes.

12 Set the BACKUP switch to the OFF position.

13 Measure the amount of fluid necessary to fill the tank again to the minimum dispatch

level or the amount of fluid collected in the bucket.

14 Calculate the fluid delivery rate.

NOTE: The permitted limit is 33.22 ounces/minute, -0.00 or +0.34 ounces/minute.

15 If no additional checks that include the filter assembly outlet are necessary, do the

steps that follow:

a Disconnect the tube from the filter assembly outlet.

CAUTION: Do not use the seals again after you loosen or

disconnect a tube coupling. Replace the 3/16-inch

and 5/16-inch sealing ring and/or 1/2-inch O-ring,

as applicable, when you assemble a tube coupling.

Examine the seal for damage and make sure that it

is in the correct position in the coupling as shown in

Figure 1. This will help to prevent fluid leakage from

the coupling.

b Remove the cap and install new seals in the couplings as shown in Figure 1.

c Connect the nylon tube to the filter assembly outlet.

16 Empty the bucket in accordance with approved procedures.

(f) Do a check of the high pressure warning switch.

1 Disconnect and cap the nylon tube from the filter assembly outlet.

2 Use TKS nylon tube fittings as necessary and connect a tube to the filter assembly

outlet so it will reach into a bucket.

3 Put a cap on the end of the tube.

4 Operate the system in the HIGH mode.

5 Monitor that the A-ICE PRESS HI amber CAS message shows on the applicable

EICAS display in less than 30 seconds and stop the system operation.

NOTE: Normally the A-ICE PRESS HI amber CAS message will show on the

applicable EICAS display in 10 to 15 seconds.

a If the A-ICE PRESS HI amber CAS message does not show on the applicable

EICAS display in 30 seconds, stop the system operation.

b Remove the cap to release the pressure from the system.

c Repair the A-ICE PRESS HI amber CAS message circuit as necessary.

6 If no additional checks that include the filter assembly outlet are necessary, do the

steps that follow:

a Disconnect the tube from the filter assembly outlet.

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CAUTION: Do not use the seals again after you loosen or

disconnect a tube coupling. Replace the 3/16-inch

and 5/16-inch sealing ring and/or 1/2-inch O-ring,

as applicable, when you assemble a tube coupling.

Examine the seal for damage and make sure that it

is in the correct position in the coupling as shown in

Figure 1. This will help to prevent fluid leakage from

the coupling.

b Remove the cap and install new seals in the couplings as shown in Figure 1.

c Connect the nylon tube to the filter assembly outlet.

7 Empty the bucket in accordance with approved procedures.

(g) Do a check of the low pressure warning switch.

1 Disconnect and cap the nylon tube from the filter assembly outlet.

2 Use TKS nylon tube fittings as necessary and connect a tube to the filter assembly

outlet so it will reach into a bucket.

NOTE: The fluid will flow into the bucket during the system operation.

3 Remove the tail cone access panel. Refer to Chapter 6, Access Plates and Panels

Identification - Description and Operation.

4 Disconnect the tail bracket electrical connection to the proportioning unit.

a Connect a jumper from pin 3 of the tail bracket electrical connection to pin 3 of

the proportioning unit electrical connection.

b Connect a jumper from pin 2 of the tail bracket electrical connection to pin 2 of

the proportioning unit electrical connection.

5 Operate the system in the HIGH mode.

a Make sure that A-ICE PRESS LO red CAS message shows on the applicable

EICAS display in 15 seconds.

6 Disconnect the jumper from pin 2 of the tail bracket electrical connection to pin 2 of

the proportioning unit electrical connection.

7 Connect a jumper from pin 1 of the tail bracket electrical connection to pin 1 of the

proportioning unit electrical connection.

8 Operate the system in the HIGH mode.

a Make sure that A-ICE PRESS LO red CAS message shows on the applicable

EICAS display in 15 seconds.

9 Disconnect the jumper wires from pins 1 and 3 of the bracket electrical connection to

pins 1 and 3 of the proportioning unit electrical connection.

10 Connect the tail bracket electrical connection to the proportioning unit.

11 Install the tail cone access panel. Refer to Chapter 6, Access Plates and Panels

Identification - Description and Operation.

12 Disconnect the tube from the filter assembly outlet.

CAUTION: Do not use the seals again after you loosen or disconnect

a tube coupling. Replace the 3/16-inch and 5/16-inch

sealing ring and/or 1/2-inch O-ring, as applicable, when

you assemble a tube coupling. Examine the seal for

damage and make sure that it is in the correct position

in the coupling as shown in Figure 1. This will help to

prevent fluid leakage from the coupling.

13 Remove the cap and install new seals in the couplings as shown in Figure 1.

14 Connect the nylon tube to the filter assembly outlet.

15 Empty the bucket in accordance with approved procedures.

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(h) Do a check of the windshield pump fluid delivery rate.

1 Get access to the windshield pump.

a Remove the bulkhead aft of the TKS equipment/tanks assembly found in the

cargo pod.

2 Disconnect and cap the 3/16-inch nylon tube from the pump outlet.

3 Use TKS nylon tube fittings as necessary and connect a tube to the filter assembly

outlet so it will reach into a bucket.

NOTE: The fluid will flow into the bucket during the system operation.

4 Set the momentary MAX FLOW switch to WINDSHIELD position.

5 Collect the fluid over a timed period of 5 seconds.

6 Make sure that there is more than 0.84 ounces of fluid.

7 Disconnect the tube from the pump outlet.

CAUTION: Do not use the seals again after you loosen or disconnect

a tube coupling. Replace the 3/16-inch and 5/16-inch

sealing ring and/or 1/2-inch O-ring, as applicable, when

you assemble a tube coupling. Examine the seal for

damage and make sure that it is in the correct position

in the coupling as shown in Figure 1. This will help to

prevent fluid leakage from the coupling.

8 Remove the cap and install new seals in the couplings as shown in Figure 1.

9 Connect the 3/16-inch nylon tube to the pump outlet.

10 Empty the bucket in accordance with approved procedures.

I. Landing Gear (Chapter 32).

(1) Main landing gear spring free play check. Refer to Figure 2.

(a) Jack the airplane, refer to Chapter 7.

(b) Remove the wheel from the axle.

(c) Install a magnetic base dial indicator on the uppermost point of the center spring outboard

of the trunnion fitting.

(d) Position dial indicator so that tip is 2.0 inches from outboard end of the center spring.

(e) Zero the dial indicator. While observing the dial indicator, lift the end of the axle by hand

until dial indicator pointer does not increase any more.

(f) Make sure that the total dial indicator reading does not change by more than 0.0140 inch.

1 If reading is acceptable, restore airplane.

(g) If indicator reading exceeds 0.0140 inch, disassemble main gear spring from center spring.

(h) Using a micrometer, make sure that the difference between the outer diameter of the main

gear spring and the inner diameter of the center spring does not exceed 0.0133 inch.

(i) If tolerance is exceeded, replace defective parts.

(j) Restore airplane.

J. Lights (Chapter 33).

(1) Instrument Panel Lights Operational Check.

(a) Turn all eight rheostats full clockwise. Check that all flight panel lights, internal instrument

and radio lights, flood lights, magnetic compass light, O.A.T. light, fuel selector panel lights,

and audio panel lights are ON full bright.

(b) Check controllability of light intensity.

(2) Light Timer Operational Check.

(a) Turn on the courtesy/cargo lights and note the time. In approximately 30 minutes the timer

should turn these lights out.

(3) Exterior Lighting Operational Check.

(a) Check operation of the navigation/strobe lights, landing/taxi, flashing beacon, ice detection,

and wing courtesy lights.

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(b) Make sure that the wing courtesy and cargo lights can be operated by either the instrument

panel switch or cargo/passenger compartment switches. Check operation of all switches.

K. Vacuum (Chapter 37).

(1) Suction Gauge (engine running)

(a) Make sure the suction gage operation is in the green arc at 60% Ng. Perform operational

check of the LOW VAC annunciator light by reducing engine power to idle (52-54% Ng).

Light should illuminate if vacuum drops below 3 inches Hg (cycling the de-ice boots should

drop the vacuum suction.

L. Fuselage (Chapter 53).

(1) Bilge Area

(a) (Model 208 Cargomaster: Station 168 thru 211; Model 208B: Station 168 thru 356) - Clean

bilge area and brush coat or spray with LPS-3 metal protector.

M. Hartzell Propeller (Chapter 61).

(1) Propeller Governor (operational check with engine running)

(a) With the prop control at MAX RPM, advance the power lever until the prop RPM stabilizes

at 1900 RPM, +10 or -10 RPM.

(b) Reduce the power to idle and place the prop control at minimum RPM.

(c) Advance the power lever until prop RPM stabilizes at 1600 RPM, +0, or -50 RPM.

(d) Reduce the power to idle and return the prop control to maximum RPM.

(2) Propeller Blades.

(a) Check red marks on blade and hub to make sure of the correct alignment.

(b) Move the counterweights back and forth to determine freedom of blade movement on the

hub of pilot tube. If the blades appear tight, remove the pitch change mechanism and

check each blade individually.

(c) If blades are tight, remove the propeller assembly and return to the nearest Hartzell

Propeller Overhaul Facility.

N. McCauley Propeller (Chapter 61A).

(1) Propeller Governor (operational check with engine running)

(a) With prop control at MAX RPM, advance power lever until prop RPM stabilizes at 1900

RPM, +10 or -10 RPM.

(b) Reduce power to idle and place prop control at minimum RPM.

(c) Advance power lever until prop RPM stabilizes at 1600 RPM, +0 or -50 RPM.

(d) Reduce power to idle and return prop control to maximum RPM.

O. Engine Controls (Chapter 76).

(1) Engine Idle Check (engine running)

(a) With the power lever at idle, the bleed air heat ON, cabin heat full hot, 40 amp generator

load, and condition lever at low idle, check the Ng speed. It should be 52 to 54 Ng. Move

the condition lever to high idle and check Ng to be 64 to 66 Ng.

(2) Power Lever Reverse Speed Pickup (engine running)

(a) With the prop lever at max forward and the condition lever at low idle, move the power

lever slowly rearward over the gate.

(b) Make sure the propeller RPM rises as the prop blade angle decreases toward 0 degrees

and then decreases 0 to 15 RPM before Ng starts to increase from the idle setting.

(3) Emergency Power Lever Annunciator Light Operational Test.

CAUTION: Use of the emergency power control lever (EPL) is indicated

by breakage of the frangible/shear wire. Upon use of the epl,

appropriate engine maintenance actions must be performed. Refer

to the Pratt & Whitney Maintenance Manual, Chapter 71-00.

(a) The following airplanes incorporate frangible/shear wire, which is installed from the

Emergency Power Lever (EPL) to the pedestal cover:

• Airplanes 20800351 and On.

• Airplanes 208B0920 and On.

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• Airplanes 20800001 thru 20800350 Incorporating SK208-142.

• Airplanes 208B0001 thru 208B0919 Incorporating SK208-142.

(b) If the frangible/shear wire on the EPL, on applicable airplanes, is broken or missing,

maintenance personnel must determine if engine limitations have been exceeded. If these

limitations have been exceeded, make sure the appropriate engine maintenance actions

are performed. Refer to the Pratt & Whitney Maintenance Manual, Chapter 71-00.

(c) Remove the frangible/shear wire from the EPL, if installed.

(d) Move the emergency power lever from normal to idle noting control position when the light

comes ON.

(e) The light should come ON with the control in the idle position.

(f) Place the control in the normal position when complete.

(g) Perform the required maintenance checks found in the Pratt & Whitney Maintenance

Manual, Chapter 71-00.

(h) Install MS20995CY15 or C489003 frangible/shear wire from the EPL to the pedestal cover.

Refer to Emergency Power Lever Frangible/Shear Wire Removal/Installation in Chapter

76, Quadrant Assembly and Controls - Maintenance Practices.

P. Oil (Chapter 79).

(1) Chip Detectors With Annunciator Light

(a) Visually inspect for condition and leakage.

(b) Perform system check of CHIP DETECTOR annunciator light circuitry by placing a jumper

wire across the two electrical pins in each plug.

(2) Chip Detectors Without Annunciator Light

(a) Remove the chip detector from the engine, bridge the magnetic poles with a suitable

metallic jumper and then check for continuity.

Q. Starting (Chapter 80).

(1) Starter-Generator Brush Holders

(a) Inspect for proper spring tension (30 to 39 ounces) and freedom. Refer to Lear Siegler/

Lucas Aerospace Overhaul Manual for proper procedure. Does Not apply to alternate

Lucas Aerospace 23081-23A or APC Starter Generator.

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CORROSION PREVENTION AND CONTROL PROGRAM

1. Introduction

A. As the airplane ages, corrosion occurs more often, while, at the same time, other types of damage

such as fatigue cracks occur. Corrosion can cause damage to the airplane’s structural integrity, and if

it is not controlled, the airframe will carry less load than what is necessary for continued airworthiness.

(1) To help to prevent this, we started a Corrosion Prevention and Control Program (CPCP) for the

Models 208 and 208B. A CPCP is a system to control the corrosion in the airplane’s primary

structure. It is not the function of the CPCP to stop all of the corrosion conditions, but to control

the corrosion to a level that the airplane's continued airworthiness is not put in risk.

B. The initial and repeat inspection intervals are based on Model 208/208B service experience. It is

recommended that you record the results of the inspection. After the second CPCP inspection, it

is possible to shorten or lengthen the Repeat Interval (RI). Proposed changes to the RI should be

submitted with supporting data to the regulatory authority.

2. Corrosion Prevention and Control Program Objective

A. The objective of the CPCP is to help to prevent or control the corrosion so that it does not cause a

risk to the continued airworthiness of the Models 208 and 208B airplanes.

3. Corrosion Prevention and Control Program Function

A. The function of this document is to give the minimum procedures necessary to control the corrosion

so that the continued airworthiness is not put in risk. The CPCP consists of a Corrosion Program

Inspection number, the area where the inspection will be done, specified corrosion levels and

compliance times (Implementation Thresholds and Repeat Intervals). The CPCP also includes

procedures to let Cessna Aircraft Company and the regulatory authorities know of the findings and

the data associated with Level 2 and Level 3 corrosion. This includes the actions that were done to

decrease possible corrosion in the future to Level 1.

B. Maintenance or inspection programs need to include a good quality CPCP. The level of corrosion

identified on the Principal Structural Elements (PSEs) and other structure listed in the Baseline

Program will help make sure the CPCP provides good corrosion protection.

NOTE: A good quality program is one that will control the corrosion of all of the structure at Level

1 or better.

C. Corrosion Program Levels.

NOTE: In this manual the corrosion inspection task are referred to as the corrosion program

inspection.

(1) Level 1 Corrosion.

(a) Corrosion damage occurring between successive inspection tasks, that is local and can

be reworked or blended out with the allowable limit.

(b) 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).

(c) Operator experience has demonstrated only light corrosion between each successive

corrosion task inspection; the latest corrosion inspection task results in rework or blend

out that exceeds the allowable limit.

(2) Level 2 Corrosion.

(a) 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.

(a) 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.

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MAINTENANCE MANUAL

4. References

A. This is a list of references for the Corrosion Prevention and Control Program.

(1) FAA Advisory Circular AC120-CPCP, Development and Implementation of Corrosion Prevention

and Control Program

(2) FAA Advisory Circular AC43-4A, Corrosion Control for Aircraft

(3) Cessna Model 208 Illustrated Parts Catalog

(4) Cessna Model 208 Maintenance Manual

(5) Cessna Model 208 Structural Repair Manual, Chapter 51-11-00, Corrosion Repair

(6) Cessna Model 208 Nondestructive Testing Manual

5. Control Prevention and Control Program Application

A. The Models 208 and 208B Corrosion Prevention and Control Program gives the information required

for each corrosion inspection. Maintenance personnel must fully know about corrosion control. The

regulatory agency will give approval and monitor the CPCP for each airplane.

(1) The CPCP procedures apply to all Models 208 and 208B airplanes that are at or have more than

the Baseline Program Implementation Threshold for each location on the airplane. Refer to the

Glossary and the Baseline Program.

(a) Cessna Aircraft Company recommends that the CPCP be done first on older airplanes and

areas that need greater changes to the maintenance procedures to meet the necessary

corrosion prevention and control requirements.

(2) Maintenance programs must include corrosion prevention and control procedures that limit

corrosion to Level 1 or better on all Principal Structural Elements (PSEs) and other structure

specified in the Baseline Program. If the current maintenance program includes corrosion

control procedures in an inspection area and there is a report to show that corrosion is always

controlled to Level 1 or better, the current inspection program can be used.

(a) The Baseline Program is not always sufficient if the airplane is operated in high humidity

environments, has a corrosive cargo leakage or has had an unsatisfactory maintenance or

repair. When this occurs, make adjustments to the Baseline Program until the corrosion is

controlled to Level 1 or better.

(3) The CPCP consists of the corrosion inspection applied at a specified interval, and, at times, a

corrosion inspection interval can be listed in a Service Bulletin. For the CPCP to be applied,

remove all systems, equipment and interior furnishings that prevent sufficient inspection of the

structure. A nondestructive test (NDI) or a visual inspection can be necessary after some items

are removed if there is an indication of hidden corrosion such as skin deformation, corrosion

under splices or corrosion under fittings. Refer to the Baseline Program.

(4) The corrosion rate can change between different airplanes. This can be a result of different

environments the airplane operates in, flight missions, payloads, maintenance practices (for

example more than one owner), variation in rate of protective finish or coating wear.

(a) Some airplanes that operate under equivalent environments and maintenance practices

can be able to extend the Implementation Threshold (IT) or Repeat Interval (RI) if a

sufficient number of inspections do not show indications of corrosion in that area. Refer

to the Glossary.

(5) Later design and/or production changes done as a result of corrosion conditions can delay

the start of corrosion. Operators that have done corrosion-related service bulletins or the

improved maintenance manual procedures listed in the Corrosion Program Inspection can use

that specified implementation threshold or repeat inspection interval. Unless the instructions

tell you differently, the requirements given in this document apply to all of the Models 208 and

208B airplanes.

(6) Another system has been added to report all Level 2 and Level 3 corrosion conditions identified

during the second and each subsequent CPCP inspection. This information will be reviewed by

Cessna Aircraft Company to make sure the Baseline Program is sufficient and to change it as

necessary.

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

6. Baseline Program

A. The Baseline Program is part of the Models 208 and 208B Corrosion Prevention and Control Program

(CPCP). It is divided into Basic Task, Implementation Threshold (IT) and Repeat Interval (RI). In this

manual the Basic Tasks are referred to as the Corrosion Program Inspection. This program is to

be used on all airplanes without an approved CPCP. Those who currently have a CPCP that does

not control corrosion to Level 1 or better must make adjustments to the areas given in the Baseline

Program.

B. Typical Airplane Zone Corrosion Program Inspection Procedures.

(1) Remove all the equipment and airplane interior (for example the insulation, upper upholstery

panel, lower upholstery panel) as necessary to do the corrosion inspection.

(2) Clean the areas given in the corrosion inspection before you inspect them.

(3) Do a visual inspection of all of the Principal Structural Elements (PSEs) and other structure given

in the corrosion inspection for corrosion, cracking, and deformation.

(a) Carefully examine the areas that show that corrosion has occurred before.

NOTE: Areas that need a careful inspection are given in the corrosion inspection.

(b) Nondestructive testing inspections or visual inspections can be needed after some

disassembly if the inspection shows a bulge in the skin, corrosion under the splices or

corrosion under fittings.

(4) Remove all of the corrosion, examine the damage, and repair or replace the damaged structure.

(a) Apply a protective finish where it is required. Refer to Chapter 20, Interior and Exterior

Finish - Cleaning/Painting or Chapter 51, Corrosion - Description and Operation.

(b) Clean or replace the ferrous metal fasteners with oxidation.

(5) Remove blockages of foreign object debris so that the holes and clearances between parts can

drain.

(6) For bare metal on any surface of the airplane, apply fuel and corrosion resistant primer MILPRF-23377.

(a) Apply a polyurethane topcoat paint to the exterior painted surface. Refer to the

manufacturer's procedures.

(7) Cessna Aircraft Company recommends that you apply a corrosion preventive compound once

every two years to areas with a high possibility for severe corrosion identified in the corrosion

inspection.

(a) On the Model 208, apply LPS-3 Heavy-Duty Rust Inhibitor, or equivalent, in the bilge area

below the floorboards between FS 168.00 and FS 211.00. Refer to Chapter 51, Corrosion

- Description and Operation.

(b) On the Model 208B, apply LPS-3 Heavy-Duty Rust Inhibitor, or equivalent, in the bilge area

below the floorboards between FS 168.00 and FS 356.00. Refer to Chapter 51, Corrosion

- Description and Operation

(8) Apply compounds that will replace water and prevent corrosion. Refer to Chapter 51, Corrosion

- Description and Operation.

(a) Apply one layer of LPS-3 Heavy-Duty Rust Inhibitor, or equivalent, that will soak into the

fayed surfaces to replace water and prevent corrosion.

Table 1. Areas and Items Not to Apply Compounds to Replace Water and Prevent Corrosion

AREA or ITEM

Oxygen System Lines and Components

Cables, Pulleys, and Trim Tab Pushrod

Plastics, Elastomers

Lubricated and Teflon Surfaces (Greased Joints, Sealed Bearings, and Grommets)

Adjacent to Tears and Holes in Insulation (Not Waterproof)

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MODEL 208

MAINTENANCE MANUAL

Table 1. Areas and Items Not to Apply Compounds to Replace Water and Prevent Corrosion (continued)

Areas with Electrical Arc Potential, Wiring

Interior Upholstery Panels (Changes the Flammability Properties)

Cargo Pod (Changes the Flammability Properties)

Pitot Tubes

Fuel Cap

Tie Down Lugs

Chrome Items (handles, locks)

Standard Polished Spinner

Stall Warning Detector

(9) Install the dry insulation blankets.

(10) Install the equipment and airplane interior (for example the upper upholstery panel and lower

upholstery panel) that was removed to do the corrosion inspection.

7. Baseline Program Implementation

A. The Baseline Program is divided into specific inspection areas and zone locations. Both of these

items have an Implementation Threshold (IT) and Repeat Interval (RI) to do the corrosion program

inspection. The inspection areas and zone locations apply to all 208/208B airplanes for which the

given airplane calendar age is equal to or greater than the IT. For the structural parts that have been

replaced, the IT can be calculated from the time of the installation of the new part. Refer to Table 2

and Table 3.

B. Calculate the Implementation Threshold (IT).

NOTE: The corrosion inspections apply to airplanes with a calendar year age that is equal to or

greater than the IT.

(1) To calculate the IT on a new structural part, start at the time the structural part was replaced.

(2) Start the Baseline Program during scheduled maintenance when the maintenance check

intervals are equal to or greater than the IT.

NOTE: The Baseline Program must be started before the airplane gets to the point of IT + RI

for any corrosion inspection.

NOTE: For airplanes near or greater than IT + RI, Cessna Aircraft Company recommends that

you apply the Baseline Program immediately after the regulatory authority approves

the schedule.

NOTE: Early implementation of the Baseline Program is highly recommended.

Table 2. Corrosion Prevention and Control Program Example

INTERVAL

(YEARS)

CORROSION

INSPECTION

NUMBER IT RI

ZONE ACCESS MAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION

INSPECTION

DESCRIPTIONS

C32.701.01E

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CESSNA AIRCRAFT COMPANY

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MAINTENANCE MANUAL

Table 3. Corrosion Program Inspection Legend

ITEM DESCRIPTION

CORROSION INSPECTION NUMBER The Corrosion Inspection Number identifies the area

on the airplane where you will do the inspection.

Each Corrosion Inspection Number consists of an ATA

code, airplane zone, and the item number.

EXAMPLE: C32.701.01E

C The first letter identifies this as a Corrosion

Prevention and Control Program inspection.

32 This is the ATA code (Chapter 32).

701 This is the airplane zone between 100 and 999.

01 This is the sequence number between 1 and 99.

E This letter identifies this as an external inspection. An

I would identify it as an internal inspection.

INTERVAL -

IMPLEMENTATION THRESHOLD (IT) The specified Implementation Threshold for an

airplane is the date that you must do the initial

corrosion inspection in an area and zone. Use the

age of the airplane to find the IT.

REPEAT INTERVAL (RI) The Repeat Interval is the time interval between the

successive corrosion inspections for an area and

zone.

ZONE This is the airplane zone number in which the

inspection will be done. Refer to Chapter 6, Airplane

Zoning - Description and Operation.

ACCESS This is the list of access plates or panels that you

need to remove to do a corrosion inspection. Refer

to Chapter 6, Access Plates and Panels Identification

- Description and Operation.

MAINTENANCE MANUAL REFERENCE SECTION This gives the location of the removal and installation

procedures in the maintenance manual.

CORROSION INSPECTION DESCRIPTION This describes the inspection to be done.

8. Reporting System

A. Corrosion Prevention and Control Program Reporting System (Refer to Figure 1).

(1) The Corrosion Prevention and Control Program (CPCP) includes a system to report to Cessna

Aircraft Company data that will show that the Baseline Program is sufficient and, if necessary,

make changes.

(2) At the start of the second Corrosion Program Inspection of each area, report all Level 2 and

Level 3 Corrosion results that are listed in the Baseline Program to Cessna Aircraft Company.

Send the Control Prevention and Control Program Damage Reporting Form to:

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© Cessna Aircraft Company Dec 1/2006

CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Cessna Aircraft Company

Technical Support Services

Department 751

P.O. Box 7706

Wichita, Kansas USA 67277

9. Periodic Review

A. Use the Service Difficulty Reporting System to report all Level 2 and Level 3 Corrosion results to the

FAA and to Cessna Aircraft Company. All corrosion reports received by Cessna Aircraft Company will

be reviewed to determine if the Baseline Program is adequate.

10. Corrosion Related Airworthiness Directives

A. Safety-related corrosion conditions transmitted by a service bulletin can be mandated by an

Airworthiness Directive (AD). The service bulletins and ADs will be listed in this section. There are

no corrosion-related ADs for the Models 208 and 208B.

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MODEL 208

MAINTENANCE MANUAL

CORROSION PREVENTION AND CONTROL INSPECTIONS (AIRPLANES

WITHOUT TKS ANTI-ICE SYSTEM)

1. Corrosion Prevention and Control Program Inspections

A. Corrosion Prevention and Control Program Inspection.

(1) Complete the corrosion program inspection for the corrosion prevention and control program.

(2) The initial and repeat inspection intervals are based on Model 208/208B service experience. It is

recommended that you record the results of the inspection. After the second CPCP inspection,

it is possible to shorten or lengthen the Repeat Interval (RI). Proposed changes to the RI should

be submitted with supporting data to the regulatory authority.

Table 1. Corrosion Prevention and Control Program

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C27.320.1I 5 2 320 330A

320A

27-00-00

27-30-01

Elevator control system installation.

Make sure you examine these areas:

01.01 Elevator Bell Crank and Bell

Crank Bearing.

01.02 Elevator Bell Crank Push Rod,

Push Rod Bearing and Bolt.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATION:

FS 388.68 to FS 427.88 Model 208

FS 436.68 to FS 475.88 Model 208B

C27.373.01I

C27.374.01I

3 1 373

374

373AL

374AR

27-00-00

27-30-02

27-30-03

Elevator trim tab actuator installation.

Make sure you examine these areas:

01.01 Elevator Trim Tab Actuator and

Actuator Internal Screw.

01.02 Sprocket, Attach Bolt, Spacer

and Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

sprocket and bearings.

STATION: SS 67.80 Models 208 and

208B

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MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C27.373.02I

C27.374.02I

5 2 373

374

373AL

374AR

27-00-00

27-30-02

27-30-03

Elevator trim tab actuator control

system. Make sure you examine this

area:

02.01 Elevator Trim Tab Push Rod,

Push Rod Bearing, Bolt and Bushing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATION: SS 67.80 Models 208 and

208B

C27.503.1I

C27.603.1I

5 2 503

603

503DB

503EB

603DB

603EB

27-00-00

27-10-01

27-10-02

Aileron and spoiler control system

installation. Make sure you examine

these areas:

01.01 Aileron Bell Crank Tubes, Aileron

Bell Crank End Rods, End Rod Bearing

and Bolts.

01.02 Spoiler End Rod, End Rod

Bearing and Bolt.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATION: WS 228.50 Models 208 and

208B

C27.525.1I

C27.625.1I

5 2 525

625

525AB

525BB

525CB

625AB

625BB

625CB

27-00-00

27-50-01

Flap control system installation. Make

sure you examine these areas:

01.01 Flap Bell Crank Tubes, Bell

Crank Bushing and Bell Crank Bearing.

01.02 Flap Bell Crank End Rods and

End Rod Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATIONS:

WS 53.00 Inboard Flap Bell Crank

WS 126.50 Center Flap Bell Crank

WS 214.30 Outboard Flap Bell Crank

Models 208 and 208B

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MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.701.01E 2 1 701 NOTE 1 12-17-01

12-21-03

32-00-00

32-20-00

Nose gear outer barrel assembly.

Make sure you examine these areas:

01.01 Outer Barrel Surface.

01.02 End Upper Strut and Lower

Collar Assembly.

NOTE: 1 Remove the nose gear

fairing to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor to

the sliding surfaces of the

oleo strut.

STATION: FS 61.78 Models 208 and

208B

C32.701.01I 2 1 701 NOTE 1 12-17-01

12-21-03

32-00-00

32-20-00

Nose gear inner barrel assembly.

Make sure you examine these areas:

01.01 Inner Barrel Surface.

01.02 Strut Tube Assembly.

NOTE: 1 Disassemble the nose

gear strut to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor to

the sliding surfaces of the

oleo strut.

STATION: FS 61.78 Models 208 and

208B

C32.701.02E 4 2 701 NOTE 12-21-03

32-00-00

32-20-00

Nose gear spring assembly and

support assembly. Make sure you

examine these areas:

02.01 Nose Gear Spring Surface.

02.02 Forward and Aft Support.

02.03 Nose Gear Spring Fork and

Attach Bolts.

NOTE: Remove the nose gear

fairing to get access.

STATION: FS 61.78 Models 208 and

208B

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MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.701.02I 4 2 701 NOTE 12-21-03

32-00-00

32-20-00

32-40-00

Nose gear support liner, support inner

bore, nose gear spring support attach

location, nose gear spring fork lug

inner bore. Make sure you examine

these areas:

02.01 Nose Gear Support Liner.

02.02 Forward and Aft Support Inner

Bore Surface.

02.03 Nose Gear Spring Surface

at Forward and Aft Support Attach

Location.

02.04 Nose Gear Spring Fork Lug Inner

Bore Surface.

NOTE: Remove the nose gear

support from the spring to

get access.

STATION: FS 61.78 Models 208 and

208B

C32.701.03E 6 3 701 NOTE 12-17-01

12-21-03

32-00-00

32-20-00

32-50-00

Nose gear trunnion steering assembly,

torque link assembly, nose gear fork.

Make sure you examine these areas:

03.01 Nose Gear Trunnion Surface.

03.02 Steering Collar and Steering

Collar Attach Bolt.

03.03 Torque Link, Torque Link Attach

Pin and Attach Bolt.

03.04 Nose Gear Fork and Shock Strut

Bearing Block.

NOTE: Remove the nose gear

fairing to get access.

STATION: FS 61.78 Models 208 and

208B

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MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.701.03I 6 3 701 NOTE 1 12-17-01

12-21-03

32-00-00

32-20-00

Nose gear trunnion upper and lower

inner bearing bore torque link bolt and

attach pin inner bore and nose gear

fork lug inner bore. Make sure you

examine these areas:

03.01 Nose Gear Trunnion Upper,

Lower Inner Bore Surface and Bearing.

03.02 Torque Link Bolt and Attach Pin

Inner Bore Surface.

03.03 Nose Gear Fork Lug Inner Bore

Surface.

NOTE: 1 Disassemble nose gear

strut to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor

on bearing.

STATION: FS 61.78 Models 208 and

208B

C32.701.04I 3 1 701 NOTE 1 12-21-03

32-00-00

32-20-00

Nose gear axle assembly. Make sure

you examine these areas:

04.01 Nose Gear Axle and Attach Bolt.

04.02 Nose Gear Axle Bucket, Spacer

and Bearing.

NOTE: 1 Disassemble the nose

gear wheel assembly to get

access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor to

the bearing.

STATION: FS 61.78 Models 208 and

208B

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MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.721.01E

C32.722.01E

1 1-2 721

722

12-21-03

32-00-00

32-10-00

32-10-02

Main gear spring assembly. Make sure

you examine these areas:

01.01 Center Spring Surface.

01.02 Right and Left Outer Spring

Surface.

01.03 Center/Outer Spring Interface.

NOTE: Refer to Inspection

Operations 29 and 30 for

Inspection Details.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.02E

C32.722.02E

5 2 721

722

NOTE 12-21-03

32-00-00

32-10-00

Main gear trunnion assembly, trunnion

fitting assembly. Make sure you

examine these areas:

02.01 Main Gear Trunnion.

02.02 Main Gear Trunnion Attach Pin

and Attach Bolt.

02.03 Main Gear Trunnion Fitting,

Fitting Cap and Attach Bolt.

NOTE: Remove the main gear

fairing to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.02I

C32.722.02I

5 2 721

722

NOTE 12-21-03

32-00-00

32-10-00

Main gear trunnion inner bore at outer

spring to center spring interface and

pin to trunnion interface. Make sure

you examine these areas:

01.01 Main Gear Trunnion Inner Bore

Surface at Outer Spring to Center

Spring Interface.

01.02 Main Gear Trunnion Inner Bore

Surface at Pin to Trunnion Interface.

NOTE: Remove the main gear

trunnion from the center

spring to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

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MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.721.03E

C32.722.03E

2 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

32-10-01

Main gear axle assembly. Make sure

you examine this area:

03.01 Main Gear Axle and Attach Bolt.

NOTE: Remove the main gear

wheel assembly to get

access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.03I

C32.722.03I

2 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

32-10-01

Main gear axle inner bore at axle, axle

fitting attach bolt location. Make sure

you examine this area:

02.01 Main Gear Axle Inner Bore

Surface at Axle and Axle Fitting Attach

Bolt Location.

NOTE: Remove the main gear

wheel assembly and attach

bolt to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.04E

C32.722.04E

5 2 721

722

NOTE 12-21-03

32-00-00

32-10-00

32-10-01

Main gear axle fitting assembly. Make

sure you examine these areas:

04.01 Main Gear Axle Fitting.

04.02 Main Gear Axle Fitting and Outer

Spring Attach Bolt.

NOTE: Remove the main gear

fairing to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.721.04I

C32.722.04I

5 2 721

722

NOTE 12-21-03

32-00-00

32-10-00

Main gear axle fitting inner bore at

axle fitting and outer spring attach bolt

location. Make sure you examine this

area:

03.01 Main Gear Axle Fitting Inner Bore

Surface at Axle Fitting and Outer Spring

Attach Bolt Location.

NOTE: Remove the main gear

fairing and attach bolt to get

access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C52.801.1E

C52.802.1E

5 2 801

802

52-00-00

52-11-00

Crew door external structure. Make

sure you examine these areas:

01.01 Crew Door External Panel

Surface, Areas Around Door Hinges

and Door Handle.

01.02 Top and Bottom Crew Door

Hinges, Hinge Pin, and Attach Screws.

01.03 Crew Door Entry Steps.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

hinge pin and chromed door

handles.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

5-30-01 Page 8

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C52.801.1I

C52.802.1I

5 2 801

802

NOTE 1 52-00-00

52-11-00

Crew door latch mechanism. Make

sure you examine these areas:

01.01 Door Handle, Roll Pin,

Escutcheon, Handle Support and Lock

Pin.

01.02 Bell Crank, Bell Crank Bushing,

Bell Crank Pin and Door Handle

Spindle.

01.03 Door Tube Assembly, Clevis,

Latch Bolt and Latch Bolt Spring.

NOTE: 1 Remove the door interior

panel to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor

on the hinge pin and

chromed door handles.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

C52.803.1E

C52.804.1E

5 2 803

804

52-00-00

52-31-00

Cargo upper door external structure.

Make sure you examine these areas:

01.01 Cargo Upper Door External

Panel Surface.

01.02 Cargo Upper Door Hinge Half

and Hinge Pin.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on the

hinge pin.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

5-30-01 Page 9

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C52.803.1I

C52.804.1I

5 2 803

804

52-00-00

52-31-00

Cargo upper door latch mechanism.

Make sure you examine these areas:

01.01 Door Handle, Roll Pin,

Escutcheon, Handle Support and Lock

Pin.

01.02 Bell Crank, Bell Crank Bushing,

Bell Crank Pin and Door Handle

Spindle.

01.03 Door Tube Assembly, Clevis,

Latch Pin and Latch Spring.

NOTE: Do not apply LPS-3

Heavy-Duty Rust Inhibitor

to the latch mechanism and

chromed door handles.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

C52.803.2E

C52.804.2E

5 2 803

804

52-00-00

52-31-00

Cargo lower door external structure.

Make sure you examine these areas:

02.01 Cargo Lower Door External

Panel Surface.

02.02 Upper and Lower Cargo Door

Hinges, Hinge Pin and Attach Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

hinge pin.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

5-30-01 Page 10

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C52.803.2I

C52.804.2I

5 2 803

804

NOTE 1 52-00-00

52-31-00

Cargo lower door latch mechanism.

Make sure you examine these areas:

02.01 Door Handle, Roll Pin,

Escutcheon and Handle Mount.

02.02 Bell Crank, Bell Crank Support,

Bushing, Bell Crank Pin and Door

Handle Spindle.

02.03 Door Tube Assembly, Clevis,

Latch Pin and Latch Spring.

NOTE: 1 Remove the interior door

panel to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor

to the latch mechanism and

chromed door handles.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

C53.211.01E

C53.212.01E

6 3 211

212

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage forward right side and left

side skin between FS 100.00 and FS

118.00. Make sure you examine this

area:

01.01 Fuselage Forward Right and Left

Side Skin Surface.

STATIONS: FS 100.00 to FS 118.00

Models 208 and 208B

5-30-01 Page 11

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.211.01I

C53.212.01I

6 3 211

212

211AL

211BL

211CL

211DL

211EL

211AC

212AR

212BR

212CR

212DR

212ER

212FR

NOTE

12-23-01

53-00-00

53-10-00

53-21-00

Fuselage forward lower internal

structure beneath the floor panel

between FS 100.00 and FS 118.00.

Make sure you examine these areas:

01.01 Right Side and Left Side

Longerons at BL 8.00 and BL 19.00

and Outboard Longerons.

01.02 Channels and Stiffeners

Common to BL 8.00 Longeron.

01.03 Bottom Bulkhead Segment at FS

118.00.

01.04 Firewall Support Structures,

Brackets Stiffeners and Doublers.

01.05 Bottom Skin Internal Surface

Between FS 100.00 and FS 118.00.

NOTE: Remove the floor panels

and access covers to get

access.

STATIONS: FS 100.00 to FS 118.00

Models 208 and 208B

C53.213.01E

C53.214.01E

6 3 213

214

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower forward skin between

FS 100.00 and FS 118.00. Make sure

you examine these areas:

01.01 Fuselage Lower Forward Skin

Surface.

01.02 Fuselage Belly Doubler and Left

and Right Side Doubler.

STATIONS: FS 100.00 to FS 118.00

Models 208 and 208B

C53.215.1E

C53.216.1E

6 3 215

216

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage forward right side and left

side skin between FS 118.00 and FS

128.00. Make sure you examine this

area:

01.01 Fuselage Forward Right and Left

Side Skin Surface.

STATIONS: FS 118.00 to FS 128.00

Models 208 and 208B

5-30-01 Page 12

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.215.1I

C53.216.1I

6 3 215

216

215AL

216AC

216AR

216BC

NOTE

12-23-01

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage forward lower internal

structure beneath the floor panel

between FS 118.00 to FS 128.00.

Make sure you examine these areas:

01.01 Right Side and Left Side

Longerons at BL 8.00 and BL 19.00

and Outboard Longerons.

01.02 Bulkhead Segment at FS 128.00.

01.03 Right Side and Left Side Inboard

Support Control Column.

01.04 Right Side and Left Side Pulley

Support Structures.

01.05 Bottom Skin Internal Surface

Between FS 118.00 and FS 128.00.

NOTE: Remove the floor panels

and access plates to get

access.

STATIONS: FS 118.00 to FS 128.00

Models 208 and 208B

C53.217.1E

C53.218.1E

6 3 217

218

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower forward skin between

FS 118.00 and FS 128.00. Make sure

you examine this area:

01.01 Fuselage Lower Forward Skin

Surface.

STATIONS: FS 118.00 to FS 128.00

Models 208 and 208B

C53.231.1E

C53.232.1E

6 3 231

232

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage top right side and top left

side skin between FS 128.00 and FS

166.45. Make sure you examine this

area:

01.01 Fuselage Top Right Side and Top

Left Side Skin Surface.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

C53.233.1E

C53.234.1E

6 3 233

234

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower forward skin center

right side and center left side skin

between FS 128.00 and FS 166.45.

Make sure you examine these areas:

01.01 Fuselage Bottom Forward Skin

Surface.

01.02 Fuselage Center Right Side and

Center Left Side Skin Surface.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

5-30-01 Page 13

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.233.1I

C53.234.1I

6 3 233

234

231AL

231BL

231CL

231DL

232AC

232AR

232BR

232BC

232CR

232DR

NOTE

12-23-01

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath the floor panel between FS

128.00 and FS 166.45. Make sure you

examine these areas:

01.01 Right Side and Left Side

Longerons at BL 8.00 and BL 19.00

and Outboard Longerons.

01.02 Bulkhead Segments at FS

143.00 and FS 158.00.

01.03 Elevator Bell Crank Support

Assembly.

01.04 Right Side and Left Side Crew

Door Sill Assembly.

01.05 Elevator, Trim, Aileron and

Rudder Pulley Brackets.

01.06 Lower Skin Internal Surface

Between FS 128.00 and FS 166.45.

NOTE: Remove the floor panels

and access covers to get

access.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

C53.251.1E

C53.252.1E

6 3 251

252

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage right side, left side, upper

forward right side and upper forward

left side skin. Make sure you examine

these areas:

01.01 Fuselage Right Side and Left

Side Skin Surface.

01.02 Fuselage Upper Forward Right

and Upper Forward Left Skin Surface.

STATIONS:

FS 166.45 to FS 208.00 Model 208

FS 166.45 to FS 228.00 Model 208B

5-30-01 Page 14

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.251.1I

C53.252.1I

6 3 251

252

251BL

251CL

251DL

251EL

251HL

251JL

251KL

251LL

252AR

252BR

252CR

252DR

252GR

252HR

252JR

252KR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath floor panel between the

forward carry-thru bulkhead assembly

and main landing gear bulkhead

assembly. Make sure you examine

these areas:

01.01 Right Side and Left Side

Longerons at BL 23.47 BL 14.00 and

BL 9.00.

01.02 Lower Carry-thru Bulkhead

Segment and Lower Main Landing

Gear Bulkhead Segment.

01.03 Lower Right Side and Lower Left

Side Attach Angle and Stiffener.

01.04 Center Stiffener Assembly and

Fuel Reservoir Support Assembly.

01.05 Belly Skin Internal Surface

between Forward Carry-Thru Bulkhead

Structure and Main Landing Gear

Bulkhead Structure.

NOTE: 1 Remove the floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 168.70 to FS 194.40 Model 208

FS 188.70 to FS 214.40 Model 208B

5-30-01 Page 15

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.251.2I

C53.252.2I

6 3 251

252

251FL

251GL

251NL

251ML

252ER

252FR

252LR

252MR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath floor panel at the main landing

gear bulkhead assembly. Make sure

you examine these areas:

02.01 Longitudinal Bulkheads at BL

0.0, BL 13.97 and BL 23.50.

02.02 Lower Forward and Lower

Aft Main Landing Gear Bulkhead

Segments.

02.03 Sealing Skin Internal Surface

Between Forward and Aft Main Landing

Gear Bulkhead.

NOTE: 1 Remove the floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 194.40 to FS 208.00 Model 208

FS 214.40 to FS 228.00 Model 208B

5-30-01 Page 16

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.251.3I

C53.252.3I

6 3 251

252

251BL

251CL

251DL

251EL

251FL

251GL

252AR

252BR

252CR

252DR

252ER

252FR

NOTE 1

12-23-01

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath floor panel forward of the

forward carry-thru bulkhead assembly.

Make sure you examine these areas:

03.01 Longerons at BL 0.00, BL 13.97

and BL 23.47.

03.02 Lower Bulkhead Segments at FS

166.45 and FS 175.95.

03.03 Lower Skin Internal Surface

Between Bulkhead at FS 166.45 and

Forward Carry-Thru Bulkhead at FS

186.45.

03.04 Seat Tracks.

NOTE: 1 Remove the floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS: FS 166.45 to FS 186.45.

Model 208B Only

C53.253.1E

C53.254.1E

6 3 253

254

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage right side lower forward, left

side lower forward, right side lower

center, left side lower center, lower

forward, lower center skin and external

doublers. Make sure you examine

these areas:

01.01 Fuselage Right and Left Side

Lower Forward Skin Surface.

01.02 Fuselage Right and Left Side

Lower Center Skin Surface.

01.03 Fuselage Lower Forward Skin

and Lower Center Skin Surface.

01.04 Fuselage Right and Left Side

Doublers.

01.05 Right and Left Main Landing

Gear Bay Stiffener.

STATIONS:

FS 166.45 to FS 208.00 Model 208

FS 166.45 to FS 228.00 Model 208B

5-30-01 Page 17

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.255.1E

C53.256.1E

6 3 255

256

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage upper aft, right side aft

and left side aft skin. Make sure you

examine these areas:

01.01 Fuselage Upper Aft Skin Surface.

01.02 Fuselage Right Side Aft and Left

Side Aft Skin Surface.

STATIONS:

FS 208.00 to FS 322.80 Model 208

FS 228.00 to FS 365.00 Model 208B

5-30-01 Page 18

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.255.1I

C53.256.1I

6 3 255

256

255AL

255BL

255CL

255DL

255EL

255FL

255GL

255HL

255JL

255KL

255LL

255ML

255NL

255PL

255QL

255RL

255SL

255TL

255UL

255VL

255WL

255XL

255YL

256AR

256BR

256CR

256DR

256ER

256FR

256GR

256HR

256JR

256KR

256LR

256MR

256NR

256PR

256QR

256RR

256SR

256TR

256UR

256VR

256WR

256XR

256YR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath the floor panel between aft

main landing gear bulkhead and aft

cargo/passenger door jamb bulkhead.

Make sure you examine these areas:

01.01 Longerons at BL 0.0, BL 13.97

and BL 23.47.

01.02 Lower Right Side and Lower Left

Side Stiffener.

01.03 Lower Bulkhead Segments

Between Aft Main Landing Gear

Bulkhead and Aft Cargo/Passenger

Door Jamb Bulkhead.

01.04 Doublers at Longeron to Door

Jamb Bulkhead Attach.

01.05 Lower Skin Internal Surface

Between Aft Main Landing Gear

Bulkhead and Aft Cargo/Passenger

Door Jamb Bulkhead.

01.06 Seat Tracks.

NOTE: 1 Remove floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 208.00 to FS 284.00 Model 208

FS 228.00 to FS 332.00 Model 208B

5-30-01 Page 19

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.255.2I

C53.256.2I

6 3 255

256

255QL

255RL

255SL

255TL

256QR

256RR

256SR

256TR

255AAL

255ZL

255ABL

255ACL

256AAR

256ZR

256ABR

256ACR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath the floor panel between aft

cargo/passenger door jamb bulkhead

and curtain attach bulkhead. Make

sure you examine these areas:

02.01 Outboard, Inboard and Center

Longerons.

02.02 Lower Bulkhead Segments

Between Aft Cargo/Passenger Door

Jamb Bulkhead and Curtain Attach

Bulkhead.

02.03 Lower Skin Internal Surface

Between Aft Cargo/Passenger Door

Jamb Bulkhead and Curtain Attach

Bulkhead.

NOTE: 1 Remove floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 284.00 to FS 308.00 Model 208

FS 332.00 to FS 356.00 Model 208B

C53.257.1E

C53.258.1E

6 3 257

258

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower center aft and lower aft

skin. Make sure you examine these

areas:

01.01 Fuselage Lower Center Aft Skin

Surface.

01.02 Fuselage Lower Aft Skin Surface.

STATIONS:

FS 208.00 to FS 322.80 Model 208

FS 228.00 to FS 365.00 Model 208B

5-30-01 Page 20

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.311.1E

C53.312.1E

6 3 311

312

12-22-01

53-00-00

53-10-00

53-23-00

Tailcone upper, right side, left side,

lower skin, and dorsal skin. Make sure

you examine these areas:

01.01 Tailcone Upper and Lower Skin

Surface.

01.02 Tailcone Right Side and Left Side

Skin Surface.

01.03 Tailcone Dorsal Skin Surface.

STATIONS:

FS 322.00 to FS 388.68 Model 208

FS 365.00 to FS 436.68 Model 208B

C53.311.1I

C53.312.1I

6 3 311

312

320A Tailcone forward canted bulkhead

assembly. Make sure you examine

these areas:

01.01 Elevator Bell Crank Bracket

Assembly including Bracket, Angles,

Doublers and Stiffeners.

01.02 Upper and Lower Canted

Bulkhead.

01.03 Right and Left Stabilizer Attach

Fitting.

STATIONS:

FS 388.68 Model 208

FS 436.68 Model 208B

C53.320.1E 6 3 320 12-22-01

53-00-00

53-10-00

53-23-00

Tailcone right side aft, left side aft, and

lower aft skin. Make sure you examine

these areas:

01.01 Tailcone Right Side Aft and Left

Side Aft Skin Surface.

01.02 Tailcone Lower Aft Skin Surface.

STATIONS:

FS 388.68 to FS 427.88 Model 208

FS 436.68 to FS 475.88 Model 208B

C53.320.1I 6 3 320 330A

NOTE

Tailcone aft canted bulkhead assembly.

Make sure you examine these areas:

01.01 Canted Bulkhead.

01.02 Right Side and Left Side Doubler.

01.03 Support Bracket and Stiffeners.

01.04 Forward and Aft Stabilizer Attach

Fitting.

NOTE: Remove stinger to get

access.

STATIONS:

FS 427.88 Model 208

FS 475.88 Model 208B

5-30-01 Page 21

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.320.01E 5 2 320 330A 55-00-00

55-30-00

Vertical stabilizer forward spar and

rear spar attachment. Make sure you

examine these areas:

01.01 Vertical Stabilizer Forward and

Rear Spar Attach Bolt.

01.02 Vertical Stabilizer Forward and

Rear Spar around Bolt Attachment

STATIONS:

WL 134.38; BL 3.18 Upper Attach

WL 126.03; BL 3.44 Lower Attach

Models 208 and 208B

C55.340.01E 5 2 340 55-00-00

55-10-01

55-30-00

Vertical stabilizer leading edge skin

and fairing. Make sure you examine

these areas:

01.01 Vertical Stabilizer Leading Edge

Skin Surface.

01.02 Vertical Stabilizer Fairing Skin

Surface around Screw Attachment.

STATIONS:

WL 135.50 to WL 207.50 Vertical

Stabilizer Leading Edge Models 208

and 208B

FS 322.80 to FS 404.60 Fairing Model

208

FS 365.00 to FS 452.60 Fairing Model

208B

C55.340.01I 3 1 340 NOTE 1 30-00-00

30-10-00

55-00-00

55-10-01

55-30-00

Vertical stabilizer deice boot at leading

edge. Make sure you examine this

area:

01.01 Vertical Stabilizer Leading Edge

Areas Under Deice Boot.

NOTE: 1 Remove the deice boot to

get access if you think there

is corrosion.

NOTE: 2 Apply this basic task if

there is an indication of

corrosion under the deice

boot.

STATIONS: WL 162.00 to WL 207.50

Models 208 and 208B

5-30-01 Page 22

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.341.01E 5 2 341 55-00-00

55-30-00

Vertical stabilizer upper and lower skin.

Make sure you examine these areas:

01.01 Vertical Stabilizer Upper and

Lower Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS:

WL 135.50 to WL 207.50 Models 208

and 208B

C55.343.01E 5 2 343 55-00-00

55-30-00

55-40-00

Rudder left side and right side skin.

Make sure you examine these areas:

01.01 Rudder Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WL 135.50 to WL 225.50

Models 208 and 208B

C55.343.01I 5 2 343 55-00-00

55-30-00

55-40-00

Rudder upper, center, and lower hinge

attachment. Make sure you examine

these areas:

01.01 Rudder Upper, Center and Lower

Hinge Bearing Plate.

01.02 Rudder Upper, Center and Lower

Hinge Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATIONS:

WL 206.28; BL 00.00 Upper Hinge Line

WL 161.78; BL 00.00 Center Hinge Line

WL 125.00; BL 00.00 Lower Hinge Line

Models 208 and 208B

C55.343.02E 5 2 343 55-00-00

55-30-00

55-40-00

Rudder upper, center, and lower

hinges. Make sure you examine these

areas:

02.01 Rudder Upper, Center and Lower

Hinge Attach Bolt.

02.02 Rudder Upper, Center and Lower

Hinge Bracket.

STATIONS:

WL 206.28; BL 00.00 Upper Hinge Line

WL 161.78; BL 00.00 Center Hinge Line

WL 125.00; BL 00.00 Lower Hinge Line

Models 208 and 208B

5-30-01 Page 23

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.343.03E 2 1 343 55-00-00

55-30-00

55-40-00

Rudder torque tube assembly. Make

sure you examine these areas:

03.01 Rudder Torque Tube around

Welded Joint at Support Plate and

Frame.

03.02 Rudder Torque Tube around Bell

Crank Welded Joint.

03.03 Rudder Torque Tube Inner

Surface at Bell Crank Welded Joint.

STATIONS: WL 124.31 to WL 142.88

Models 208 and 208B

C55.343.04E 2 1 343 55-00-00

55-30-00

55-40-00

Rudder Torque Tube bell crank. Make

sure you examine these areas:

04.01 Rudder Torque Tube Bell Crank

Surface around Welded Joint.

04.02 Rudder Torque Tube Bell Crank

Stop Block.

STATIONS: WL 124.31 Models 208 and

208B

C55.371.01E

C55.372.01E

5 2 371

372

55-00-00

55-10-00

55-10-01

Horizontal stabilizer leading edge skin

between SS 11.50 and SS 114.00.

Make sure you examine this area:

01.01 Horizontal Stabilizer Leading

Edge Skin Surface.

STATIONS: SS 11.50 to SS 114.00

Models 208 and 208B

C55.371.01I

C55.372.01I

3 1 371

372

NOTE 1 30-00-00

30-10-00

Horizontal stabilizer deice boot at

leading edge. Make sure you examine

this area:

01.01 Horizontal Stabilizer Leading

Edge Areas Under Deice Boot.

NOTE: 1 Remove deice boot to

get access if corrosion is

suspected.

NOTE: 2 Apply this basic task if

there is an indication of

corrosion under deice boot.

STATIONS: SS 11.50 to SS 114.00

Models 208 and 208B

5-30-01 Page 24

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.373.01E

C55.374.01E

5 2 373

374

55-00-00

55-10-00

Horizontal stabilizer upper and lower

skin. Make sure you examine these

areas:

01.01 Horizontal Stabilizer Upper and

Lower Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: SS 0.00 to SS 114.00

Models 208 and 208B

C55.373.02E

C55.374.02E

5 2 373

374

330A

NOTE

55-00-00

55-10-00

Horizontal stabilizer forward spar and

rear spar attachment. Make sure you

examine these areas:

02.01 Horizontal Stabilizer Forward

Spar Attach Fitting and Attach Bolt.

02.02 Horizontal Stabilizer Rear Spar

Attach Support and Attach Bolt

NOTE: Remove horizontal stabilizer

upper and lower fairing,

forward and aft inspection

covers to get access.

STATIONS:

SS 8.50 Forward Attachment

SS 5.75 Aft Attachment

Models 208 and 208B

C55.375.01E

C55.376.01E

5 2 375

376

55-00-00

55-10-00

55-20-00

Elevator skin and elevator leading

edge skin. Make sure you examine

these areas:

01.01 Elevator Upper and Lower Skin

Surface.

01.02 Elevator Leading Edge Skin

Surface.

STATIONS: SS 8.00 to SS 123.00

Models 208 and 208B

5-30-01 Page 25

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.375.01I

C55.376.01I

5 2 375

376

330A 55-00-00

55-10-00

55-20-00

Elevator inboard, center, and outboard

hinges. Make sure you examine these

areas:

01.01 Elevator Inboard, Center and

Outboard Hinge Support.

01.02 Elevator Inboard, Center, and

Outboard Bearing Plate.

01.03 Elevator Inboard, Center, and

Outboard Hinge Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATIONS:

SS 0.00 - Center Elevator Hinge

SS 55.00 - Inboard Elevator Hinge

SS 114.00 - Outboard Elevator Hinge

Models 208 and 208B

C55.375.02E

C55.376.02E

5 2 375

376

330A 55-00-00

55-10-00

55-20-00

Elevator torque tube. Make sure you

examine these areas:

02.01 Elevator Torque Tube Surface.

02.02 Elevator Torque Tube End Plate

and Adapter Plate.

02.03 Elevator Torque Tube End Plate

to Adapter Plate Attach Bolt.

STATIONS: SS 0.00 to SS 22.00

Models 208 and 208B

C56.240.1E 6 3 240 56-00-00

56-00-01

Windshield Installation. Make sure you

examine this area:

01.01 Windshield Retainers and

Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

windshield.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

C56.240.2E 6 3 240 30-00-00

30-40-00

Windshield anti-ice system installation.

Make sure you examine this area:

02.01 Windshield Anti-Ice Panel

Assembly Including Windshield Heat

Panel, Panel Frame, and Attach

Screws.

STATIONS: FS 100.00 to FS 128.00

Models 208 and 208B

5-30-01 Page 26

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C56.251.1E

C56.252.1E

6 3 251

252

255

256

56-00-00

56-00-01

56-20-00

Passenger Window Installation. Make

sure you examine this area:

01.01 Passenger Window Retainers

and Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

window.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

C56.801.1E

C56.802.1E

6 3 801

802

56-00-00

56-00-01

56-30-00

Crew Window Installation. Make sure

you examine this area:

01.01 Crew Window Retainers and

Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

window.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

C56.803.1E

C56.804.1E

6 3 803

804

56-00-00

56-00-01

56-30-00

Cargo Door Window Installation. Make

sure you examine this area:

01.01 Cargo Door Window Retainers

and Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

window.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

C57.501.01E

C57.601.01E

5 2 501

601

57-00-00

57-10-00

57-40-00

Wing leading edge skin between WS

35.0 and WS 155.9. Make sure you

examine these areas:

01.01 Wing Leading Edge Skin

Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 35.00 to WS 155.90

Models 208 and 208B

5-30-01 Page 27

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.501.01I

C57.601.01I

3 1 501

601

501AB

501BB

501CB

501DB

501EB

601AB

601BB

601CB

601DB

601EB

NOTE 1

30-00-00

30-10-00

57-00-00

57-10-00

57-40-00

Wing deice boot at leading edge

between WS 35.00 and WS 155.90.

Make sure you examine this area:

01.01 Wing Leading Edge Areas Under

Deice Boot.

NOTE: 1 Remove deice boot to

get access if corrosion is

suspected.

NOTE: 2 Apply this basic task if

there is an indication of

corrosion under deice boot.

STATIONS: WS 35.00 to WS 155.90

Models 208 and 208B

C57.503.01E

C57.603.01E

5 2 503

603

57-00-00

57-10-00

57-40-00

Wing leading edge skin between WS

155.9 and WS 308.0. Make sure you

examine these areas:

01.01 Wing Leading Edge Skin

Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 155.90 to WS 308.00

Models 208 and 208B

C57.503.01I

C57.603.01I

3 1 503

603

503AB

503BB

503CB

503DB

503EB

503FB

503GB

503HB

503JB

603AB

603BB

603CB

603DB

603EB

603FB

603GB

603HB

603JB

NOTE 1

30-00-00

30-10-00

57-00-00

57-10-00

57-40-00

Wing deice boot at leading edge

between WS 155.90 to WS 308.00.

Make sure you examine this area:

01.01 Wing Leading Edge Areas Under

Deice Boot.

NOTE: 1 Remove deice boot to

get access if corrosion is

suspected.

NOTE: 2 Apply this basic task if

there is an indication of

corrosion under deice boot.

STATIONS: WS 155.90 to WS 308.00

Models 208 and 208B

5-30-01 Page 28

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.521.01E

C57.621.01E

5 2 521

621

57-00-00

57-10-00

57-11-00

Wing upper and lower forward skin

between WS 53.0 and WS 214.3.

Make sure you examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 53.00 to WS 214.30

Models 208 and 208B

C57.521.01I

C57.621.01I

5 2 521

621

511AB

611AB

NOTE 2

57-00-00

57-10-00

Wing forward and rear spar fitting lug

inner bore. Make sure you examine

these areas:

01.01 Forward Spar Fitting Lug

Surface.

01.02 Rear Spar Fitting Lug Surface

NOTE: 1 If corrosion is found

on the lug surface, or if

the attaching hardware

(bolt, nut, or cotter pin) is

corroded, remove the attach

bolt and inspect the lug bore.

NOTE: 2 Remove wing to fuselage

fairing to get access.

STATIONS: WS 35.00 Models 208 and

208B

C57.521.02E

C57.621.02E

5 2 521

621

511AB

611AB

NOTE

57-00-00

57-10-00

Wing forward and rear spar fitting and

fitting attachment. Make sure you

examine these areas:

02.01 Forward Spar Attach Fitting and

Fitting Attach Bolt.

02.02 Rear Spar Attach Fitting and

Fitting Attach Bolt

NOTE: Remove wing to fuselage

fairing to get access.

STATIONS: WS 35.00 Models 208 and

208B

5-30-01 Page 29

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.523.01E

C57.623.01E

5 2 523

623

57-00-00

57-10-00

57-11-00

Wing upper and lower forward skin

between WS 214.3 and WS 308.0.

Make sure you examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover Around Screw

Attachment.

STATIONS: WS 214.30 to WS 308.00

Models 208 and 208B

C57.525.01E

C57.625.01E

5 2 525

625

57-00-00

57-10-00

57-11-00

Wing upper and lower aft skin between

WS 35.0 and WS 229.0. Make sure

you examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 35.00 to WS 229.00

Models 208 and 208B

C57.527.01E

C57.627.01E

5 2 527

627

57-00-00

57-10-00

57-50-00

Flap skin and flap leading edge skin

between WS 35.0 and WS 228.0.

Make sure you examine these areas:

01.01 Flap Skin Surface.

01.02 Flap Leading Edge Skin Surface.

STATIONS: WS 35.00 to WS 228.00

Models 208 and 208B

C57.527.01I

C57.627.01I

5 2 527

627

57-00-00

57-10-00

57-50-00

Flap track sliding mechanism

attachment. Make sure you examine

these areas:

01.01 Inboard and Center Flap Track

Forward Roller and Bushing.

01.02 Inboard and Center Flap Track

Aft Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATION:

WS 53.00 Inboard Flap Track

WS 126.50 Center Flap Track

Models 208 and 208B

5-30-01 Page 30

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.527.02E

C57.627.02E

5 2 527

627

57-00-00

57-10-00

57-50-00

Flap track structure including inboard,

center and outboard flap tracks. Make

sure you examine these areas:

02.01 Inboard, Center and Outboard

Flap Track.

02.02 Inboard, Center and Outboard

Flap Support Attach Bolt.

02.03 Inboard and Center Flap Bracket

and Attach Bolt.

STATION:

WS 53.00 Inboard Flap Track

WS 126.50 Center Flap Track

WS 214.30 Outboard Flap Track

Models 208 and 208B

C57.527.03E

C57.627.03E

5 2 527

627

57-00-00

57-70-00

Spoiler inboard, center, and outboard

hinges. Make sure you examine these

areas:

03.01 Spoiler Inboard, Center and

Outboard Hinge Half.

03.02 Spoiler Inboard, Center and

Outboard Hinge Pin.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on hinge

pin.

STATION:

WS 170.90 Inboard Spoiler Hinge

WS 199.80 Center Spoiler Hinge

WS 228.50 Outboard Spoiler Hinge

Models 208 and 208B

5-30-01 Page 31

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.531.01E

C57.631.01E

2 1 531

631

521CB

621CB

NOTE 1

57-00-00

57-10-00

57-10-01

Wing strut structure including upper

and lower strut attachment, and strut

attach fittings with particular attention

to the areas that follow areas:

01.01 Upper and Lower Wing Strut

Attach Bolt.

01.02 Upper and Lower Wing Strut

Fitting Lug Bore Surface at Bolt

Attachment.

01.03 Forward and Aft Strut Fairing

Skin Surface.

NOTE: 1 Remove wing strut cuffs

and strut fairing to get

access.

STATION:

FS 168.70 Model 208

FS 188.70 Model 208B

C57.531.01I

C57.631.01I

2 1 531

631

521CB

621CB

NOTE 1

57-00-00

57-10-00

57-10-01

Wing strut upper and lower attach

fitting lug inner bore, wing strut to lower

fuselage attach fitting lug inner bore,

and wing strut to wing attach fitting lug

inner bore with particular attention to

the areas that follow:

01.01 Wing Strut Upper and Lower

Attach Fitting Lug Inner Bore surface.

01.02 Wing Strut to Lower Fuselage

Attach Fitting Lug Inner Bore Surface.

01.03 Wing Strut to Wing Attach Fitting

Lug Inner Bore Surface.

NOTE: 1 Remove wing strut cuffs

and strut fairing to get

access.

STATION:

FS 168.70 Model 208

FS 188.70 Model 208B

5-30-01 Page 32

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.531.02E

C57.631.02E

2 1 531

631

521CB

621CB

NOTE 2

57-00-00

57-10-00

57-10-01

Wing strut to lower fuselage attachment

and wing strut to wing attachment.

Make sure you examine these areas:

02.01 Wing Strut to Lower Fuselage

Attach Fitting Lug Bore Surface at Bolt

Attachment.

02.02 Wing Strut to Wing Attach Fitting

Lug Bore Surface at Bolt Attachment.

NOTE: 1 If corrosion is found on the

lug surface or if the attaching

hardware (bolt, nut, or cotter

pin) is corroded, remove the

attach bolt and inspect the

lug bore.

NOTE: 2 Remove the wing strut

cuffs and strut fairing to get

access.

STATION:

FS 168.70 Model 208

FS 188.70 Model 208B

C57.531.03E

C57.631.03E

5 2 531

631

57-00-00

57-10-00

57-10-01

Wing strut fairing assembly. Make sure

you examine these areas:

03.01 Wing Strut Fairing Surface.

03.02 Upper and Lower Strut Cuff Skin

Surface.

STATION:

FS 168.70 Models 208

FS 188.70 Models 208B

C57.551.01E

C57.651.01E

5 2 551

651

57-00-00

57-10-00

57-11-00

Wing upper and lower aft skin between

WS 229.0 to WS 308.0. Make sure you

examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 229.00 to WS 308.00

Models 208 and 208B

5-30-01 Page 33

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.571.01E

C57.671.01E

5 2 571

671

57-00-00

57-10-00

57-60-00

Aileron skin, aileron leading edge skin

and aileron trim tab skin between WS

228.50 and WS 308.00. Make sure

you examine these areas:

01.01 Aileron Skin Surface

01.02 Aileron Leading Edge Skin

Surface.

01.03 Aileron Trim Tab Skin Surface.

STATIONS: WS 228.50 to WS 308.0

Models 208 and 208B

C57.571.01I

C57.671.01I

5 2 571

671

57-00-00

57-60-00

Aileron inboard and outboard hinges.

Make sure you examine these areas:

01.01 Aileron Inboard and Outboard

Hinge Bearing.

01.02 Aileron Inboard and Outboard

Hinge Support.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATIONS:

WS 229.66 Inboard Aileron Hinge

WS 304.22 Outboard Aileron Hinge

Models 208 and 208B

C57.571.02E

C57.671.02E

5 2 571

671

57-00-00

57-10-00

57-60-00

Aileron trim tab hinge. Make sure you

examine these areas:

02.01 Aileron Trim Tab Hinge Half.

02.02 Aileron Trim Tab Hinge Pin.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on hinge

pin

STATIONS: WS 276.24 to WS 308.00

Models 208 and 208B

C61.110.1E 5 2 110 12-21-04

61-00-00

61-10-00

61-11-00

Engine propeller and propeller dome.

Make sure you examine this area:

01.01 Propeller Blade Surface and

Propeller Dome Surface.

STATIONS: FS 31.50 Models 208 and

208B

5-30-01 Page 34

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C61.110.1I 5 2 110 NOTE 1 12-21-04

61-00-00

61-10-00

61-11-00

61-40-00

Propeller and spinner installation,

beta indicating system, and propeller

overspeed governor installation. Make

sure you examine these areas:

01.01 Low Stop Collar, Spinner

Bulkhead, Spinner Bulkhead Support

and Spinner Attach Bolts (Refer to

NOTE 2).

01.02 Feedback Collar, Spinner

Support, Spinner Mounting Plate,

Spinner Bulkhead and Spinner Attach

Bolts (Refer to NOTE 2).

01.03 Beta Indicating Installation

including Beta Switch, Plunger,

Bracket, Attach Plate, Spring and

Attach Screws.

01.04 Propeller Governor Linkage.

NOTE: 1 Remove the propeller

dome and nose cap to get

access.

NOTE: 2 Corrosion Inspection

Number 01.01 applies

to airplanes with Hartzel

propeller installation.

Corrosion Inspection

Number 01.02 applies to

airplanes with McCauley

propeller installation.

STATIONS: FS 31.50 Models 208 and

208B

C71.121.1E

C71.122.1E

8 4 121

122

71-10-00 Engine cowl door skin. Make sure you

examine these areas:

01.01 Engine Cowl Center Section

Surface.

01.02 Engine Upper Cowl Right and

Left Door Surfaces.

STATIONS: FS 49.47 to FS 100.00

Models 208 and 208B

5-30-01 Page 35

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C71.121.2E

C71.122.2E

4 2 121

122

71-10-00 Engine cowl door upper attach

structure. Make sure you examine

these areas:

02.01 Forward Hinge Support, Aft

Hinge Support and Attach Screws.

02.02 Upper Cowl Door Hinge, Hinge

Bearing and Hinge Attach Bolts.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on the

bearings.

STATIONS:

FS 58.30 Forward Cowl Attach

FS 95.35 Aft Cowl Attach

Models 208 and 208B

C71.121.3E

C71.122.3E

4 2 121

122

71-10-00 Engine cowl side door latch structure.

Make sure you examine these areas:

03.01 Right and Left Side Forward,

Center and Aft Latch Brackets.

03.02 Latch Hook, Bolt, Spacer and

Nut.

STATIONS:

FS 45.00 Forward Cowl Door Latch

FS 40.00 Center Cowl Door Latch

FS 95.25 Aft Cowl Door Latch

Models 208 and 208B

C71.121.4E

C71.122.4E

8 4 121

122

71-10-00 Engine nose cap and cowl bulkhead

installation. Make sure you examine

this area:

04.01 Engine Nose Cap Surface and

Cowl Bulkhead Surface.

STATION: FS 31.50 Models 208 and

208B

5-30-01 Page 36

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C71.130.1I 4 2 130 NOTE 71-20-00 Engine truss assemblies. Make sure

you examine these areas:

01.01 Engine Truss Tube Surface.

01.02 Areas around Engine Truss

Junction Weld.

01.03 Right and Left Side Landing Gear

Junctions.

01.04 Engine Truss to Firewall Attach

Bolts.

01.05 ETM Instrument Box Attach

Location at Right Side of Lower Truss

Tube.

01.06 Ignition Exciter Box Attach

Location at Right Side of Truss Tube.

NOTE: Remove the engine cowl

door to get access.

STATION: FS 61.78 to FS 100.00

Models 208 and 208B

5-30-01 Page 37

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C71.130.2I 4 2 130 NOTE 71-20-00 Engine mount assemblies. Make sure

you examine these areas:

02.01 Engine Upper, Right and Left

Side Mount Brackets.

02.02 Engine Mount and Mount Bolts.

02.03 Engine Mount to Engine Ring

Attach Bolts.

NOTE: Remove the engine cowl

door to get access.

STATION: FS 61.78 Models 208 and

208B

C71.130.3I 4 2 130 NOTE 71-20-00 Engine ring assembly. Make sure you

examine these areas:

03.01 Engine Ring Surface.

03.02 Areas Around Junction Weld.

03.03 Engine Ring to Engine Truss

Attach Bolts.

NOTE: Remove the engine cowl

door and nose cap to get

access.

STATION: FS 61.78 Models 208 and

208B

C78.130.1E 4 2 130 NOTE 78-00-00

78-10-00

Exhaust system installation. Make

sure you examine these areas:

01.01 Primary Exhaust Duct, and

Attach Bolts.

01.02 Secondary Exhaust Duct, and

Attach Screws.

01.03 Exhaust Deflector and Retainer

Screws.

01.04 Inboard, Center and Outboard

Secondary Exhaust Hanger Brackets.

NOTE: Remove the right side lower

engine cowl to get access to

secondary exhaust.

STATION: FS 49.47 to FS 100.00

Models 208 and 208B

5-30-01 Page 38

© Cessna Aircraft Company Apr 1/2010
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

CORROSION PREVENTION AND CONTROL INSPECTIONS (AIRPLANES WITH TKS ANTI-ICE SYSTEM)

1. Corrosion Prevention and Control Program Inspections

A. Corrosion Prevention and Control Program Inspection.

(1) Complete the corrosion program inspection for the corrosion prevention and control program.

(2) The initial and repeat inspection intervals are based on Model 208/208B service experience. It is

recommended that you record the results of the inspection. After the second CPCP inspection,

it is possible to shorten or lengthen the Repeat Interval (RI). Proposed changes to the RI should

be submitted with supporting data to the regulatory authority.

Table 1. Corrosion Prevention and Control Program

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C27.320.01I 3 1 320 330A

320A

27-00-00

27-30-01

Elevator control system installation.

Make sure you examine these areas:

01.01 Elevator Bell Crank and Bell

Crank Bearing.

01.02 Elevator Bell Crank Push Rod,

Push Rod Bearing and Bolt.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATION:

FS 388.68 to FS 427.88 Model 208

FS 436.68 to FS 475.88 Model 208B

C27.373.01I

C27.374.01I

3 1 373

374

373AL

374AR

27-00-00

27-30-02

27-30-03

Elevator trim tab actuator installation.

Make sure you examine these areas:

01.01 Elevator Trim Tab Actuator and

Actuator Internal Screw.

01.02 Sprocket, Attach Bolt, Spacer

and Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

sprocket and bearings.

STATION: SS 67.80 Models 208 and

208B

5-30-02 Page 1

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C27.373.02I

C27.374.02I

3 1 373

374

373AL

374AR

27-00-00

27-30-02

27-30-03

Elevator trim tab actuator control

system. Make sure you examine this

area:

02.01 Elevator Trim Tab Push Rod,

Push Rod Bearing, Bolt and Bushing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATION: SS 67.80 Models 208 and

208B

C27.503.01I

C27.603.01I

3 1 503

603

503DB

503EB

603DB

603EB

27-00-00

27-10-01

27-10-02

Aileron and spoiler control system

installation. Make sure you examine

these areas:

01.01 Aileron Bell Crank Tubes, Aileron

Bell Crank End Rods, End Rod Bearing

and Bolts.

01.02 Spoiler End Rod, End Rod

Bearing and Bolt.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATION: WS 228.50 Models 208 and

208B

C27.525.01I

C27.625.01I

3 1 525

625

525AB

525BB

525CB

625AB

625BB

625CB

27-00-00

27-50-01

Flap control system installation. Make

sure you examine these areas:

01.01 Flap Bell Crank Tubes, Bell

Crank Bushing and Bell Crank Bearing.

01.02 Flap Bell Crank End Rods and

End Rod Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

push rods and bearings.

STATIONS:

WS 53.00 Inboard Flap Bell Crank

WS 126.50 Center Flap Bell Crank

WS 214.30 Outboard Flap Bell Crank

Models 208 and 208B

5-30-02 Page 2

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.701.01E 1 1 701 NOTE 1 12-17-01

12-21-03

32-00-00

32-20-00

Nose gear outer barrel assembly.

Make sure you examine these areas:

01.01 Outer Barrel Surface.

01.02 End Upper Strut and Lower

Collar Assembly.

NOTE: 1 Remove the nose gear

fairing to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor to

the sliding surfaces of the

oleo strut.

STATION: FS 61.78 Models 208 and

208B

C32.701.01I 1 1 701 NOTE 1 12-17-01

12-21-03

32-00-00

32-20-00

Nose gear inner barrel assembly.

Make sure you examine these areas:

01.01 Inner Barrel Surface.

01.02 Strut Tube Assembly.

NOTE: 1 Disassemble the nose

gear strut to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor to

the sliding surfaces of the

oleo strut.

STATION: FS 61.78 Models 208 and

208B

C32.701.02E 2 1 701 NOTE 12-21-03

32-00-00

32-20-00

Nose gear spring assembly and

support assembly. Make sure you

examine these areas:

02.01 Nose Gear Spring Surface.

02.02 Forward and Aft Support.

02.03 Nose Gear Spring Fork and

Attach Bolts.

NOTE: Remove the nose gear

fairing to get access.

STATION: FS 61.78 Models 208 and

208B

5-30-02 Page 3

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.701.02I 2 1 701 NOTE 12-21-03

32-00-00

32-20-00

32-40-00

Nose gear support liner, support inner

bore, nose gear spring support attach

location, nose gear spring fork lug

inner bore. Make sure you examine

these areas:

02.01 Nose Gear Support Liner.

02.02 Forward and Aft Support Inner

Bore Surface.

02.03 Nose Gear Spring Surface

at Forward and Aft Support Attach

Location.

02.04 Nose Gear Spring Fork Lug Inner

Bore Surface.

NOTE: Remove the nose gear

support from the spring to

get access.

STATION: FS 61.78 Models 208 and

208B

C32.701.03E 3 1 701 NOTE 12-17-01

12-21-03

32-00-00

32-20-00

32-50-00

Nose gear trunnion steering assembly,

torque link assembly, nose gear fork.

Make sure you examine these areas:

03.01 Nose Gear Trunnion Surface.

03.02 Steering Collar and Steering

Collar Attach Bolt.

03.03 Torque Link, Torque Link Attach

Pin and Attach Bolt.

03.04 Nose Gear Fork and Shock Strut

Bearing Block.

NOTE: Remove the nose gear

fairing to get access.

STATION: FS 61.78 Models 208 and

208B

5-30-02 Page 4

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.701.03I 3 1 701 NOTE 1 12-17-01

12-21-03

32-00-00

32-20-00

Nose gear trunnion upper and lower

inner bearing bore torque link bolt and

attach pin inner bore and nose gear

fork lug inner bore. Make sure you

examine these areas:

03.01 Nose Gear Trunnion Upper,

Lower Inner Bore Surface and Bearing.

03.02 Torque Link Bolt and Attach Pin

Inner Bore Surface.

03.03 Nose Gear Fork Lug Inner Bore

Surface.

NOTE: 1 Disassemble nose gear

strut to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor

on bearing.

STATION: FS 61.78 Models 208 and

208B

C32.701.04I 2 1 701 NOTE 1 12-21-03

32-00-00

32-20-00

Nose gear axle assembly. Make sure

you examine these areas:

04.01 Nose Gear Axle and Attach Bolt.

04.02 Nose Gear Axle Bucket, Spacer

and Bearing.

NOTE: 1 Disassemble the nose

gear wheel assembly to get

access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor to

the bearing.

STATION: FS 61.78 Models 208 and

208B

5-30-02 Page 5

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.721.01E

C32.722.01E

3 1 721

722

12-21-03

32-00-00

32-10-00

32-10-02

Main gear spring assembly. Make sure

you examine these areas:

01.01 Center Spring Surface.

01.02 Right and Left Outer Spring

Surface.

01.03 Center/Outer Spring Interface.

NOTE: Refer to Inspection

Operation 30 for Inspection

Details.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.02E

C32.722.02E

3 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

Main gear trunnion assembly, trunnion

fitting assembly. Make sure you

examine these areas:

02.01 Main Gear Trunnion.

02.02 Main Gear Trunnion Attach Pin

and Attach Bolt.

02.03 Main Gear Trunnion Fitting,

Fitting Cap and Attach Bolt.

NOTE: Remove the main gear

fairing to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.02I

C32.722.02I

3 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

Main gear trunnion inner bore at outer

spring to center spring interface and

pin to trunnion interface. Make sure

you examine these areas:

01.01 Main Gear Trunnion Inner Bore

Surface at Outer Spring to Center

Spring Interface.

01.02 Main Gear Trunnion Inner Bore

Surface at Pin to Trunnion Interface.

NOTE: Remove the main gear

trunnion from the center

spring to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

5-30-02 Page 6

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.721.03E

C32.722.03E

2 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

32-10-01

Main gear axle assembly. Make sure

you examine this area:

03.01 Main Gear Axle and Attach Bolt.

NOTE: Remove the main gear

wheel assembly to get

access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.03I

C32.722.03I

2 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

32-10-01

Main gear axle inner bore at axle, axle

fitting attach bolt location. Make sure

you examine this area:

02.01 Main Gear Axle Inner Bore

Surface at Axle and Axle Fitting Attach

Bolt Location.

NOTE: Remove the main gear

wheel assembly and attach

bolt to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C32.721.04E

C32.722.04E

3 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

32-10-01

Main gear axle fitting assembly. Make

sure you examine these areas:

04.01 Main Gear Axle Fitting.

04.02 Main Gear Axle Fitting and Outer

Spring Attach Bolt.

NOTE: Remove the main gear

fairing to get access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

5-30-02 Page 7

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C32.721.04I

C32.722.04I

3 1 721

722

NOTE 12-21-03

32-00-00

32-10-00

Main gear axle fitting inner bore at

axle fitting and outer spring attach bolt

location. Make sure you examine this

area:

03.01 Main Gear Axle Fitting Inner Bore

Surface at Axle Fitting and Outer Spring

Attach Bolt Location.

NOTE: Remove the main gear

fairing and attach bolt to get

access.

STATIONS:

FS 194.40 Model 208

FS 214.40 Model 208B

C52.801.01E

C52.802.01E

5 2 801

802

52-00-00

52-11-00

Crew door external structure. Make

sure you examine these areas:

01.01 Crew Door External Panel

Surface, Areas Around Door Hinges

and Door Handle.

01.02 Top and Bottom Crew Door

Hinges, Hinge Pin, and Attach Screws.

01.03 Crew Door Entry Steps.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

hinge pin and chromed door

handles.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

5-30-02 Page 8

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C52.801.01I

C52.802.01I

5 2 801

802

NOTE 1 52-00-00

52-11-00

Crew door latch mechanism. Make

sure you examine these areas:

01.01 Door Handle, Roll Pin,

Escutcheon, Handle Support and Lock

Pin.

01.02 Bell Crank, Bell Crank Bushing,

Bell Crank Pin and Door Handle

Spindle.

01.03 Door Tube Assembly, Clevis,

Latch Bolt and Latch Bolt Spring.

NOTE: 1 Remove the door interior

panel to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor

on the hinge pin and

chromed door handles.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

C52.803.01E

C52.804.01E

3 1 803

804

52-00-00

52-31-00

Cargo upper door external structure.

Make sure you examine these areas:

01.01 Cargo Upper Door External

Panel Surface.

01.02 Cargo Upper Door Hinge Half

and Hinge Pin.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on the

hinge pin.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

5-30-02 Page 9

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C52.803.01I

C52.804.01I

5 2 803

804

52-00-00

52-31-00

Cargo upper door latch mechanism.

Make sure you examine these areas:

01.01 Door Handle, Roll Pin,

Escutcheon, Handle Support and Lock

Pin.

01.02 Bell Crank, Bell Crank Bushing,

Bell Crank Pin and Door Handle

Spindle.

01.03 Door Tube Assembly, Clevis,

Latch Pin and Latch Spring.

NOTE: Do not apply LPS-3

Heavy-Duty Rust Inhibitor

to the latch mechanism and

chromed door handles.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

C52.803.02E

C52.804.02E

3 1 803

804

52-00-00

52-31-00

Cargo lower door external structure.

Make sure you examine these areas:

02.01 Cargo Lower Door External

Panel Surface.

02.02 Upper and Lower Cargo Door

Hinges, Hinge Pin and Attach Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor to the

hinge pin.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

5-30-02 Page 10

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C52.803.02I

C52.804.02I

3 1 803

804

NOTE 1 52-00-00

52-31-00

Cargo lower door latch mechanism.

Make sure you examine these areas:

02.01 Door Handle, Roll Pin,

Escutcheon and Handle Mount.

02.02 Bell Crank, Bell Crank Support,

Bushing, Bell Crank Pin and Door

Handle Spindle.

02.03 Door Tube Assembly, Clevis,

Latch Pin and Latch Spring.

NOTE: 1 Remove the interior door

panel to get access.

NOTE: 2 Do not apply LPS-3

Heavy-Duty Rust Inhibitor

to the latch mechanism and

chromed door handles.

STATIONS:

FS 234.00 to FS 284.00 Model 208

FS 282.00 to FS 332.00 Model 208B

C53.211.01E

C53.212.01E

6 3 211

212

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage forward right side and left

side skin between FS 100.00 and FS

118.00. Make sure you examine this

area:

01.01 Fuselage Forward Right and Left

Side Skin Surface.

STATIONS: FS 100.00 to FS 118.00

Models 208 and 208B

5-30-02 Page 11

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.211.01I

C53.212.01I

3 1 211

212

211AL

211BL

211CL

211DL

211EL

211AC

212AR

212BR

212CR

212DR

212ER

212FR

NOTE

12-23-01

53-00-00

53-10-00

53-21-00

Fuselage forward lower internal

structure beneath the floor panel

between FS 100.00 and FS 118.00.

Make sure you examine these areas:

01.01 Right Side and Left Side

Longerons at BL 8.00 and BL 19.00

and Outboard Longerons.

01.02 Channels and Stiffeners

Common to BL 8.00 Longeron.

01.03 Bottom Bulkhead Segment at FS

118.00.

01.04 Firewall Support Structures,

Brackets Stiffeners and Doublers.

01.05 Bottom Skin Internal Surface

Between FS 100.00 and FS 118.00.

NOTE: Remove the floor panels

and access covers to get

access.

STATIONS: FS 100.00 to FS 118.00

Models 208 and 208B

C53.213.01E

C53.214.01E

6 3 213

214

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower forward skin between

FS 100.00 and FS 118.00. Make sure

you examine these areas:

01.01 Fuselage Lower Forward Skin

Surface.

01.02 Fuselage Belly Doubler and Left

and Right Side Doubler.

STATIONS: FS 100.00 to FS 118.00

Models 208 and 208B

C53.215.01E

C53.216.01E

6 3 215

216

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage forward right side and left

side skin between FS 118.00 and FS

128.00. Make sure you examine this

area:

01.01 Fuselage Forward Right and Left

Side Skin Surface.

STATIONS: FS 118.00 to FS 128.00

Models 208 and 208B

5-30-02 Page 12

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.215.01I

C53.216.01I

3 1 215

216

215AL

216AC

216AR

216BC

NOTE

12-23-01

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage forward lower internal

structure beneath the floor panel

between FS 118.00 to FS 128.00.

Make sure you examine these areas:

01.01 Right Side and Left Side

Longerons at BL 8.00 and BL 19.00

and Outboard Longerons.

01.02 Bulkhead Segment at FS 128.00.

01.03 Right Side and Left Side Inboard

Support Control Column.

01.04 Right Side and Left Side Pulley

Support Structures.

01.05 Bottom Skin Internal Surface

Between FS 118.00 and FS 128.00.

NOTE: Remove the floor panels

and access plates to get

access.

STATIONS: FS 118.00 to FS 128.00

Models 208 and 208B

C53.217.01E

C53.218.01E

6 3 217

218

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower forward skin between

FS 118.00 and FS 128.00. Make sure

you examine this area:

01.01 Fuselage Lower Forward Skin

Surface.

STATIONS: FS 118.00 to FS 128.00

Models 208 and 208B

C53.231.01E

C53.232.01E

6 3 231

232

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage top right side and top left

side skin between FS 128.00 and FS

166.45. Make sure you examine this

area:

01.01 Fuselage Top Right Side and Top

Left Side Skin Surface.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

C53.233.01E

C53.234.01E

3 1 233

234

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower forward skin center

right side and center left side skin

between FS 128.00 and FS 166.45.

Make sure you examine these areas:

01.01 Fuselage Bottom Forward Skin

Surface.

01.02 Fuselage Center Right Side and

Center Left Side Skin Surface.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

5-30-02 Page 13

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.233.01I

C53.234.01I

3 1 233

234

231AL

231BL

231CL

231DL

232AC

232AR

232BR

232BC

232CR

232DR

NOTE

12-23-01

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath the floor panel between FS

128.00 and FS 166.45. Make sure you

examine these areas:

01.01 Right Side and Left Side

Longerons at BL 8.00 and BL 19.00

and Outboard Longerons.

01.02 Bulkhead Segments at FS

143.00 and FS 158.00.

01.03 Elevator Bell Crank Support

Assembly.

01.04 Right Side and Left Side Crew

Door Sill Assembly.

01.05 Elevator, Trim, Aileron and

Rudder Pulley Brackets.

01.06 Lower Skin Internal Surface

Between FS 128.00 and FS 166.45.

NOTE: Remove the floor panels

and access covers to get

access.

STATIONS: FS 128.00 to FS 166.45

Models 208 and 208B

C53.251.01E

C53.252.01E

6 3 251

252

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage right side, left side, upper

forward right side and upper forward

left side skin. Make sure you examine

these areas:

01.01 Fuselage Right Side and Left

Side Skin Surface.

01.02 Fuselage Upper Forward Right

and Upper Forward Left Skin Surface.

STATIONS:

FS 166.45 to FS 208.00 Model 208

FS 166.45 to FS 228.00 Model 208B

5-30-02 Page 14

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.251.01I

C53.252.01I

3 1 251

252

251BL

251CL

251DL

251EL

251HL

251JL

251KL

251LL

252AR

252BR

252CR

252DR

252GR

252HR

252JR

252KR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath floor panel between the

forward carry-thru bulkhead assembly

and main landing gear bulkhead

assembly. Make sure you examine

these areas:

01.01 Right Side and Left Side

Longerons at BL 23.47 BL 14.00 and

BL 9.00.

01.02 Lower Carry-thru Bulkhead

Segment and Lower Main Landing

Gear Bulkhead Segment.

01.03 Lower Right Side and Lower Left

Side Attach Angle and Stiffener.

01.04 Center Stiffener Assembly and

Fuel Reservoir Support Assembly.

01.05 Belly Skin Internal Surface

between Forward Carry-Thru Bulkhead

Structure and Main Landing Gear

Bulkhead Structure.

NOTE: 1 Remove the floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 168.70 to FS 194.40 Model 208

FS 188.70 to FS 214.40 Model 208B

5-30-02 Page 15

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.251.02I

C53.252.02I

3 1 251

252

251FL

251GL

251NL

251ML

252ER

252FR

252LR

252MR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath floor panel at the main landing

gear bulkhead assembly. Make sure

you examine these areas:

02.01 Longitudinal Bulkheads at BL

0.0, BL 13.97 and BL 23.50.

02.02 Lower Forward and Lower

Aft Main Landing Gear Bulkhead

Segments.

02.03 Sealing Skin Internal Surface

Between Forward and Aft Main Landing

Gear Bulkhead.

NOTE: 1 Remove the floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 194.40 to FS 208.00 Model 208

FS 214.40 to FS 228.00 Model 208B

5-30-02 Page 16

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.251.03I

C53.252.03I

3 1 251

252

251BL

251CL

251DL

251EL

251FL

251GL

252AR

252BR

252CR

252DR

252ER

252FR

NOTE 1

12-23-01

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath floor panel forward of the

forward carry-thru bulkhead assembly.

Make sure you examine these areas:

03.01 Longerons at BL 0.00, BL 13.97

and BL 23.47.

03.02 Lower Bulkhead Segments at FS

166.45 and FS 175.95.

03.03 Lower Skin Internal Surface

Between Bulkhead at FS 166.45 and

Forward Carry-Thru Bulkhead at FS

186.45.

03.04 Seat Tracks.

NOTE: 1 Remove the floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS: FS 166.45 to FS 186.45.

Model 208B Only

C53.253.01E

C53.254.01E

3 1 253

254

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage right side lower forward, left

side lower forward, right side lower

center, left side lower center, lower

forward, lower center skin and external

doublers. Make sure you examine

these areas:

01.01 Fuselage Right and Left Side

Lower Forward Skin Surface.

01.02 Fuselage Right and Left Side

Lower Center Skin Surface.

01.03 Fuselage Lower Forward Skin

and Lower Center Skin Surface.

01.04 Fuselage Right and Left Side

Doublers.

01.05 Right and Left Main Landing

Gear Bay Stiffener.

STATIONS:

FS 166.45 to FS 208.00 Model 208

FS 166.45 to FS 228.00 Model 208B

5-30-02 Page 17

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.255.01E

C53.256.01E

6 3 255

256

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage upper aft, right side aft

and left side aft skin. Make sure you

examine these areas:

01.01 Fuselage Upper Aft Skin Surface.

01.02 Fuselage Right Side Aft and Left

Side Aft Skin Surface.

STATIONS:

FS 208.00 to FS 322.80 Model 208

FS 228.00 to FS 365.00 Model 208B

5-30-02 Page 18

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.255.01I

C53.256.01I

3 1 255

256

255AL

255BL

255CL

255DL

255EL

255FL

255GL

255HL

255JL

255KL

255LL

255ML

255NL

255PL

255QL

255RL

255SL

255TL

255UL

255VL

255WL

255XL

255YL

256AR

256BR

256CR

256DR

256ER

256FR

256GR

256HR

256JR

256KR

256LR

256MR

256NR

256PR

256QR

256RR

256SR

256TR

256UR

256VR

256WR

256XR

256YR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath the floor panel between aft

main landing gear bulkhead and aft

cargo/passenger door jamb bulkhead.

Make sure you examine these areas:

01.01 Longerons at BL 0.0, BL 13.97

and BL 23.47.

01.02 Lower Right Side and Lower Left

Side Stiffener.

01.03 Lower Bulkhead Segments

Between Aft Main Landing Gear

Bulkhead and Aft Cargo/Passenger

Door Jamb Bulkhead.

01.04 Doublers at Longeron to Door

Jamb Bulkhead Attach.

01.05 Lower Skin Internal Surface

Between Aft Main Landing Gear

Bulkhead and Aft Cargo/Passenger

Door Jamb Bulkhead.

01.06 Seat Tracks.

NOTE: 1 Remove floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 208.00 to FS 284.00 Model 208

FS 228.00 to FS 332.00 Model 208B

5-30-02 Page 19

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.255.02I

C53.256.02I

3 1 255

256

255QL

255RL

255SL

255TL

256QR

256RR

256SR

256TR

255AAL

255ZL

255ABL

255ACL

256AAR

256ZR

256ABR

256ACR

NOTE 1

12-23-01

51-12-00

53-00-00

53-10-00

53-21-00

53-25-00

Fuselage lower internal structure

beneath the floor panel between aft

cargo/passenger door jamb bulkhead

and curtain attach bulkhead. Make

sure you examine these areas:

02.01 Outboard, Inboard and Center

Longerons.

02.02 Lower Bulkhead Segments

Between Aft Cargo/Passenger Door

Jamb Bulkhead and Curtain Attach

Bulkhead.

02.03 Lower Skin Internal Surface

Between Aft Cargo/Passenger Door

Jamb Bulkhead and Curtain Attach

Bulkhead.

NOTE: 1 Remove floor panels

and access covers to get

access.

NOTE: 2 Apply additional corrosion

protection in areas that

have an increased risk for

severe corrosion. Refer

to Corrosion Program

Inspection Procedures.

STATIONS:

FS 284.00 to FS 308.00 Model 208

FS 332.00 to FS 356.00 Model 208B

C53.257.01E

C53.258.01E

6 3 257

258

12-22-01

53-00-00

53-10-00

53-23-00

Fuselage lower center aft and lower aft

skin. Make sure you examine these

areas:

01.01 Fuselage Lower Center Aft Skin

Surface.

01.02 Fuselage Lower Aft Skin Surface.

STATIONS:

FS 208.00 to FS 322.80 Model 208

FS 228.00 to FS 365.00 Model 208B

5-30-02 Page 20

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C53.311.01E

C53.312.01E

6 3 311

312

12-22-01

53-00-00

53-10-00

53-23-00

Tailcone upper, right side, left side,

lower skin, and dorsal skin. Make sure

you examine these areas:

01.01 Tailcone Upper and Lower Skin

Surface.

01.02 Tailcone Right Side and Left Side

Skin Surface.

01.03 Tailcone Dorsal Skin Surface.

STATIONS:

FS 322.00 to FS 388.68 Model 208

FS 365.00 to FS 436.68 Model 208B

C53.311.01I

C53.312.01I

3 1 311

312

320A Tailcone forward canted bulkhead

assembly. Make sure you examine

these areas:

01.01 Elevator Bell Crank Bracket

Assembly including Bracket, Angles,

Doublers and Stiffeners.

01.02 Upper and Lower Canted

Bulkhead.

01.03 Right and Left Stabilizer Attach

Fitting.

STATIONS:

FS 388.68 Model 208

FS 436.68 Model 208B

C53.320.01E 6 3 320 12-22-01

53-00-00

53-10-00

53-23-00

Tailcone right side aft, left side aft, and

lower aft skin. Make sure you examine

these areas:

01.01 Tailcone Right Side Aft and Left

Side Aft Skin Surface.

01.02 Tailcone Lower Aft Skin Surface.

STATIONS:

FS 388.68 to FS 427.88 Model 208

FS 436.68 to FS 475.88 Model 208B

C53.320.01I 3 1 320 330A

NOTE

Tailcone aft canted bulkhead assembly.

Make sure you examine these areas:

01.01 Canted Bulkhead.

01.02 Right Side and Left Side Doubler.

01.03 Support Bracket and Stiffeners.

01.04 Forward and Aft Stabilizer Attach

Fitting.

NOTE: Remove stinger to get

access.

STATIONS:

FS 427.88 Model 208

FS 475.88 Model 208B

5-30-02 Page 21

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.320.01E 3 1 320 330A 55-00-00

55-30-00

Vertical stabilizer forward spar and

rear spar attachment. Make sure you

examine these areas:

01.01 Vertical Stabilizer Forward and

Rear Spar Attach Bolt.

01.02 Vertical Stabilizer Forward and

Rear Spar around Bolt Attachment

STATIONS:

WL 134.38; BL 3.18 Upper Attach

WL 126.03; BL 3.44 Lower Attach

Models 208 and 208B

C55.340.01E 5 2 340 55-00-00

55-10-01

55-30-00

Vertical stabilizer leading edge skin

and fairing. Make sure you examine

these areas:

01.01 Vertical Stabilizer Leading Edge

Skin Surface.

01.02 Vertical Stabilizer Fairing Skin

Surface around Screw Attachment.

STATIONS:

WL 135.50 to WL 207.50 Vertical

Stabilizer Leading Edge Models 208

and 208B

FS 322.80 to FS 404.60 Fairing Model

208

FS 365.00 to FS 452.60 Fairing Model

208B

C55.341.01E 3 1 341 55-00-00

55-30-00

Vertical stabilizer upper and lower skin.

Make sure you examine these areas:

01.01 Vertical Stabilizer Upper and

Lower Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS:

WL 135.50 to WL 207.50 Models 208

and 208B

C55.343.01E 5 2 343 55-00-00

55-30-00

55-40-00

Rudder left side and right side skin.

Make sure you examine these areas:

01.01 Rudder Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WL 135.50 to WL 225.50

Models 208 and 208B

5-30-02 Page 22

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.343.01I 3 1 343 55-00-00

55-30-00

55-40-00

Rudder upper, center, and lower hinge

attachment. Make sure you examine

these areas:

01.01 Rudder Upper, Center and Lower

Hinge Bearing Plate.

01.02 Rudder Upper, Center and Lower

Hinge Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATIONS:

WL 206.28; BL 00.00 Upper Hinge Line

WL 161.78; BL 00.00 Center Hinge Line

WL 125.00; BL 00.00 Lower Hinge Line

Models 208 and 208B

C55.343.02E 3 1 343 55-00-00

55-30-00

55-40-00

Rudder upper, center, and lower

hinges. Make sure you examine these

areas:

02.01 Rudder Upper, Center and Lower

Hinge Attach Bolt.

02.02 Rudder Upper, Center and Lower

Hinge Bracket.

STATIONS:

WL 206.28; BL 00.00 Upper Hinge Line

WL 161.78; BL 00.00 Center Hinge Line

WL 125.00; BL 00.00 Lower Hinge Line

Models 208 and 208B

C55.343.03E 1 1 343 55-00-00

55-30-00

55-40-00

Rudder torque tube assembly. Make

sure you examine these areas:

03.01 Rudder Torque Tube around

Welded Joint at Support Plate and

Frame.

03.02 Rudder Torque Tube around Bell

Crank Welded Joint.

03.03 Rudder Torque Tube Inner

Surface at Bell Crank Welded Joint.

STATIONS: WL 124.31 to WL 142.88

Models 208 and 208B

5-30-02 Page 23

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.343.04E 1 1 343 55-00-00

55-30-00

55-40-00

Rudder Torque Tube bell crank. Make

sure you examine these areas:

04.01 Rudder Torque Tube Bell Crank

Surface around Welded Joint.

04.02 Rudder Torque Tube Bell Crank

Stop Block.

STATIONS: WL 124.31 Models 208 and

208B

C55.371.01E

C55.372.01E

5 2 371

372

55-00-00

55-10-00

55-10-01

Horizontal stabilizer leading edge skin

between SS 11.50 and SS 114.00.

Make sure you examine this area:

01.01 Horizontal Stabilizer Leading

Edge Skin Surface.

STATIONS: SS 11.50 to SS 114.00

Models 208 and 208B

C55.373.01E

C55.374.01E

3 1 373

374

55-00-00

55-10-00

Horizontal stabilizer upper and lower

skin. Make sure you examine these

areas:

01.01 Horizontal Stabilizer Upper and

Lower Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: SS 0.00 to SS 114.00

Models 208 and 208B

C55.373.02E

C55.374.02E

3 1 373

374

330A

NOTE

55-00-00

55-10-00

Horizontal stabilizer forward spar and

rear spar attachment. Make sure you

examine these areas:

02.01 Horizontal Stabilizer Forward

Spar Attach Fitting and Attach Bolt.

02.02 Horizontal Stabilizer Rear Spar

Attach Support and Attach Bolt

NOTE: Remove horizontal stabilizer

upper and lower fairing,

forward and aft inspection

covers to get access.

STATIONS:

SS 8.50 Forward Attachment

SS 5.75 Aft Attachment

Models 208 and 208B

5-30-02 Page 24

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C55.375.01E

C55.376.01E

5 2 375

376

55-00-00

55-10-00

55-20-00

Elevator skin and elevator leading

edge skin. Make sure you examine

these areas:

01.01 Elevator Upper and Lower Skin

Surface.

01.02 Elevator Leading Edge Skin

Surface.

STATIONS: SS 8.00 to SS 123.00

Models 208 and 208B

C55.375.01I

C55.376.01I

3 1 375

376

330A 55-00-00

55-10-00

55-20-00

Elevator inboard, center, and outboard

hinges. Make sure you examine these

areas:

01.01 Elevator Inboard, Center and

Outboard Hinge Support.

01.02 Elevator Inboard, Center, and

Outboard Bearing Plate.

01.03 Elevator Inboard, Center, and

Outboard Hinge Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATIONS:

SS 0.00 - Center Elevator Hinge

SS 55.00 - Inboard Elevator Hinge

SS 114.00 - Outboard Elevator Hinge

Models 208 and 208B

C55.375.02E

C55.376.02E

3 1 375

376

330A 55-00-00

55-10-00

55-20-00

Elevator torque tube. Make sure you

examine these areas:

02.01 Elevator Torque Tube Surface.

02.02 Elevator Torque Tube End Plate

and Adapter Plate.

02.03 Elevator Torque Tube End Plate

to Adapter Plate Attach Bolt.

STATIONS: SS 0.00 to SS 22.00

Models 208 and 208B

5-30-02 Page 25

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C56.240.01E 3 1 240 56-00-00

56-00-01

Windshield Installation. Make sure you

examine this area:

01.01 Windshield Retainers and

Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

windshield.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

C56.251.01E

C56.252.01E

6 3 251

252

255

256

56-00-00

56-00-01

56-20-00

Passenger Window Installation. Make

sure you examine this area:

01.01 Passenger Window Retainers

and Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

window.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

C56.801.01E

C56.802.01E

6 3 801

802

56-00-00

56-00-01

56-30-00

Crew Window Installation. Make sure

you examine this area:

01.01 Crew Window Retainers and

Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

window.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

C56.803.01E

C56.804.01E

6 3 803

804

56-00-00

56-00-01

56-30-00

Cargo Door Window Installation. Make

sure you examine this area:

01.01 Cargo Door Window Retainers

and Retainer Screws.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

window.

STATIONS: FS 100.00 to FS 143.00

Models 208 and 208B

5-30-02 Page 26

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.501.01E

C57.601.01E

4 2 501

601

57-00-00

57-10-00

57-40-00

Wing leading edge skin between WS

35.0 and WS 155.9. Make sure you

examine these areas:

01.01 Wing Leading Edge Skin

Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 35.00 to WS 155.90

Models 208 and 208B

C57.501.01I

C57.601.01I

3 1 501

601

501AB

501BB

501CB

501DB

501EB

601AB

601BB

601CB

601DB

601EB

NOTE 1

30-00-00

30-10-00

57-00-00

57-10-00

57-40-00

Wing deice boot at leading edge

between WS 35.00 and WS 155.90.

Make sure you examine this area:

01.01 Wing Leading Edge Areas Under

Deice Boot.

NOTE: 1 Remove deice boot to

get access if corrosion is

suspected.

NOTE: 2 Apply this basic task if

there is an indication of

corrosion under deice boot.

STATIONS: WS 35.00 to WS 155.90

Models 208 and 208B

C57.503.01E

C57.603.01E

3 1 503

603

57-00-00

57-10-00

57-40-00

Wing leading edge skin between WS

155.9 and WS 308.0. Make sure you

examine these areas:

01.01 Wing Leading Edge Skin

Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 155.90 to WS 308.00

Models 208 and 208B

5-30-02 Page 27

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.503.01I

C57.603.01I

3 1 503

603

503AB

503BB

503CB

503DB

503EB

503FB

503GB

503HB

503JB

603AB

603BB

603CB

603DB

603EB

603FB

603GB

603HB

603JB

NOTE 1

30-00-00

30-10-00

57-00-00

57-10-00

57-40-00

Wing deice boot at leading edge

between WS 155.90 to WS 308.00.

Make sure you examine this area:

01.01 Wing Leading Edge Areas Under

Deice Boot.

NOTE: 1 Remove deice boot to

get access if corrosion is

suspected.

NOTE: 2 Apply this basic task if

there is an indication of

corrosion under deice boot.

STATIONS: WS 155.90 to WS 308.00

Models 208 and 208B

C57.521.01E

C57.621.01E

3 1 521

621

57-00-00

57-10-00

57-11-00

Wing upper and lower forward skin

between WS 53.0 and WS 214.3.

Make sure you examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 53.00 to WS 214.30

Models 208 and 208B

C57.521.01I

C57.621.01I

3 1 521

621

511AB

611AB

NOTE 2

57-00-00

57-10-00

Wing forward and rear spar fitting lug

inner bore. Make sure you examine

these areas:

01.01 Forward Spar Fitting Lug

Surface.

01.02 Rear Spar Fitting Lug Surface

NOTE: 1 If corrosion is found

on the lug surface, or if

the attaching hardware

(bolt, nut, or cotter pin) is

corroded, remove the attach

bolt and inspect the lug bore.

NOTE: 2 Remove wing to fuselage

fairing to get access.

STATIONS: WS 35.00 Models 208 and

208B

5-30-02 Page 28

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.521.02E

C57.621.02E

3 1 521

621

511AB

611AB

NOTE

57-00-00

57-10-00

Wing forward and rear spar fitting and

fitting attachment. Make sure you

examine these areas:

02.01 Forward Spar Attach Fitting and

Fitting Attach Bolt.

02.02 Rear Spar Attach Fitting and

Fitting Attach Bolt

NOTE: Remove wing to fuselage

fairing to get access.

STATIONS: WS 35.00 Models 208 and

208B

C57.523.01E

C57.623.01E

3 1 523

623

57-00-00

57-10-00

57-11-00

Wing upper and lower forward skin

between WS 214.3 and WS 308.0.

Make sure you examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover Around Screw

Attachment.

STATIONS: WS 214.30 to WS 308.00

Models 208 and 208B

C57.525.01E

C57.625.01E

3 1 525

625

57-00-00

57-10-00

57-11-00

Wing upper and lower aft skin between

WS 35.0 and WS 229.0. Make sure

you examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 35.00 to WS 229.00

Models 208 and 208B

C57.527.01E

C57.627.01E

5 2 527

627

57-00-00

57-10-00

57-50-00

Flap skin and flap leading edge skin

between WS 35.0 and WS 228.0.

Make sure you examine these areas:

01.01 Flap Skin Surface.

01.02 Flap Leading Edge Skin Surface.

STATIONS: WS 35.00 to WS 228.00

Models 208 and 208B

5-30-02 Page 29

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.527.01I

C57.627.01I

1 1 527

627

57-00-00

57-10-00

57-50-00

Flap track sliding mechanism

attachment. Make sure you examine

these areas:

01.01 Inboard and Center Flap Track

Forward Roller and Bushing.

01.02 Inboard and Center Flap Track

Aft Bearing.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATION:

WS 53.00 Inboard Flap Track

WS 126.50 Center Flap Track

Models 208 and 208B

C57.527.02E

C57.627.02E

1 1 527

627

57-00-00

57-10-00

57-50-00

Flap track structure including inboard,

center and outboard flap tracks. Make

sure you examine these areas:

02.01 Inboard, Center and Outboard

Flap Track.

02.02 Inboard, Center and Outboard

Flap Support Attach Bolt.

02.03 Inboard and Center Flap Bracket

and Attach Bolt.

STATION:

WS 53.00 Inboard Flap Track

WS 126.50 Center Flap Track

WS 214.30 Outboard Flap Track

Models 208 and 208B

C57.527.03E

C57.627.03E

3 1 527

627

57-00-00

57-70-00

Spoiler inboard, center, and outboard

hinges. Make sure you examine these

areas:

03.01 Spoiler Inboard, Center and

Outboard Hinge Half.

03.02 Spoiler Inboard, Center and

Outboard Hinge Pin.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on hinge

pin.

STATION:

WS 170.90 Inboard Spoiler Hinge

WS 199.80 Center Spoiler Hinge

WS 228.50 Outboard Spoiler Hinge

Models 208 and 208B

5-30-02 Page 30

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.531.01E

C57.631.01E

1 1 531

631

521CB

621CB

NOTE 2

57-00-00

57-10-00

57-10-01

Wing strut upper and lower attach

fitting lug, wing strut to lower fuselage

attach fitting lug, and wing strut to

wing attach fitting lug. Make sure you

examine these areas:

01.01 Wing Strut Upper and Lower

Attach Fitting Lug Surface.

01.02 Wing Strut to Lower Fuselage

Attach Fitting Lug Surface.

01.03 Wing Strut to Wing Attach Fitting

Lug Surface.

NOTE: 1 If corrosion is found on the

lug surface or if the attaching

hardware (bolt, nut, or cotter

pin) is corroded, remove the

attach bolt and inspect the

lug bore.

NOTE: 2 Remove the wing strut

cuffs to get access.

STATION:

FS 168.70 Model 208

FS 188.70 Model 208B

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CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.531.01I

C57.631.01I

1 1 531

631

521CB

621CB

NOTE 2

57-00-00

57-10-00

57-10-01

Wing strut upper and lower attach

fitting lug, wing strut to lower fuselage

attach fitting lug, and wing strut to

wing attach fitting lug. Make sure you

examine these areas:

01.01 Wing Strut Upper and Lower

Attach Fitting Lug Surface.

01.02 Wing Strut to Lower Fuselage

Attach Fitting Lug Surface.

01.03 Wing Strut to Wing Attach Fitting

Lug Surface.

NOTE: 1 If corrosion is found on the

lug surface or if the attaching

hardware (bolt, nut, or cotter

pin) is corroded, remove the

attach bolt and inspect the

lug bore.

NOTE: 2 Remove the wing strut

cuffs to get access.

STATION:

FS 168.70 Model 208

FS 188.70 Model 208B

C57.531.02E

C57.631.02E

1 1 531

631

521CB

621CB

NOTE 2

57-00-00

57-10-00

57-10-01

Wing strut to lower fuselage attachment

and wing strut to wing attachment.

Make sure you examine these areas:

02.01 Wing Strut to Lower Fuselage

Attach Fitting Lug Bore Surface at Bolt

Attachment.

02.02 Wing Strut to Wing Attach Fitting

Lug Bore Surface at Bolt Attachment.

NOTE: 1 If corrosion is found on the

lug surface or if the attaching

hardware (bolt, nut, or cotter

pin) is corroded, remove the

attach bolt and inspect the

lug bore.

NOTE: 2 Remove the wing strut

cuffs and strut fairing to get

access.

STATION:

FS 168.70 Model 208

FS 188.70 Model 208B

5-30-02 Page 32

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.531.03E

C57.631.03E

5 2 531

631

57-00-00

57-10-00

57-10-01

Wing strut fairing assembly. Make sure

you examine these areas:

03.01 Wing Strut Fairing Surface.

03.02 Upper and Lower Strut Cuff Skin

Surface.

STATION:

FS 168.70 Models 208

FS 188.70 Models 208B

C57.551.01E

C57.651.01E

3 1 551

651

57-00-00

57-10-00

57-11-00

Wing upper and lower aft skin between

WS 229.0 to WS 308.0. Make sure you

examine these areas:

01.01 Wing Skin Surface.

01.02 Access Cover around Screw

Attachment.

STATIONS: WS 229.00 to WS 308.00

Models 208 and 208B

C57.571.01E

C57.671.01E

5 2 571

671

57-00-00

57-10-00

57-60-00

Aileron skin, aileron leading edge skin

and aileron trim tab skin between WS

228.50 and WS 308.00. Make sure

you examine these areas:

01.01 Aileron Skin Surface

01.02 Aileron Leading Edge Skin

Surface.

01.03 Aileron Trim Tab Skin Surface.

STATIONS: WS 228.50 to WS 308.0

Models 208 and 208B

C57.571.01I

C57.671.01I

3 1 571

671

57-00-00

57-60-00

Aileron inboard and outboard hinges.

Make sure you examine these areas:

01.01 Aileron Inboard and Outboard

Hinge Bearing.

01.02 Aileron Inboard and Outboard

Hinge Support.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on

bearings.

STATIONS:

WS 229.66 Inboard Aileron Hinge

WS 304.22 Outboard Aileron Hinge

Models 208 and 208B

5-30-02 Page 33

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C57.571.02E

C57.671.02E

3 1 571

671

57-00-00

57-10-00

57-60-00

Aileron trim tab hinge. Make sure you

examine these areas:

02.01 Aileron Trim Tab Hinge Half.

02.02 Aileron Trim Tab Hinge Pin.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on hinge

pin

STATIONS: WS 276.24 to WS 308.00

Models 208 and 208B

C61.110.01E 3 1 110 12-21-04

61-00-00

61-10-00

61-11-00

Engine propeller and propeller dome.

Make sure you examine this area:

01.01 Propeller Blade Surface and

Propeller Dome Surface.

STATIONS: FS 31.50 Models 208 and

208B

5-30-02 Page 34

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C61.110.01I 3 1 110 NOTE 1 12-21-04

61-00-00

61-10-00

61-11-00

61-40-00

Propeller and spinner installation,

beta indicating system, and propeller

overspeed governor installation. Make

sure you examine these areas:

01.01 Low Stop Collar, Spinner

Bulkhead, Spinner Bulkhead Support

and Spinner Attach Bolts (Refer to

NOTE 2).

01.02 Feedback Collar, Spinner

Support, Spinner Mounting Plate,

Spinner Bulkhead and Spinner Attach

Bolts (Refer to NOTE 2).

01.03 Beta Indicating Installation

including Beta Switch, Plunger,

Bracket, Attach Plate, Spring and

Attach Screws.

01.04 Propeller Governor Linkage.

NOTE: 1 Remove the propeller

dome and nose cap to get

access.

NOTE: 2 Corrosion Inspection

Number 01.01 applies

to airplanes with Hartzel

propeller installation.

Corrosion Inspection

Number 01.02 applies to

airplanes with McCauley

propeller installation.

STATIONS: FS 31.50 Models 208 and

208B

C71.121.01E

C71.122.01E

8 4 121

122

71-10-00 Engine cowl door skin. Make sure you

examine these areas:

01.01 Engine Cowl Center Section

Surface.

01.02 Engine Upper Cowl Right and

Left Door Surfaces.

STATIONS: FS 49.47 to FS 100.00

Models 208 and 208B

5-30-02 Page 35

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C71.121.02E

C71.122.02E

2 2 121

122

71-10-00 Engine cowl door upper attach

structure. Make sure you examine

these areas:

02.01 Forward Hinge Support, Aft

Hinge Support and Attach Screws.

02.02 Upper Cowl Door Hinge, Hinge

Bearing and Hinge Attach Bolts.

NOTE: Do not apply LPS-3 HeavyDuty Rust Inhibitor on the

bearings.

STATIONS:

FS 58.30 Forward Cowl Attach

FS 95.35 Aft Cowl Attach

Models 208 and 208B

C71.121.03E

C71.122.03E

4 2 121

122

71-10-00 Engine cowl side door latch structure.

Make sure you examine these areas:

03.01 Right and Left Side Forward,

Center and Aft Latch Brackets.

03.02 Latch Hook, Bolt, Spacer and

Nut.

STATIONS:

FS 45.00 Forward Cowl Door Latch

FS 40.00 Center Cowl Door Latch

FS 95.25 Aft Cowl Door Latch

Models 208 and 208B

C71.121.04E

C71.122.04E

8 4 121

122

71-10-00 Engine nose cap and cowl bulkhead

installation. Make sure you examine

this area:

04.01 Engine Nose Cap Surface and

Cowl Bulkhead Surface.

STATION: FS 31.50 Models 208 and

208B

5-30-02 Page 36

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C71.130.01I 2 1 130 NOTE 71-20-00 Engine truss assemblies. Make sure

you examine these areas:

01.01 Engine Truss Tube Surface.

01.02 Areas around Engine Truss

Junction Weld.

01.03 Right and Left Side Landing Gear

Junctions.

01.04 Engine Truss to Firewall Attach

Bolts.

01.05 ETM Instrument Box Attach

Location at Right Side of Lower Truss

Tube.

01.06 Ignition Exciter Box Attach

Location at Right Side of Truss Tube.

NOTE: Remove the engine cowl

door to get access.

STATION: FS 61.78 to FS 100.00

Models 208 and 208B

5-30-02 Page 37

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION

INSPECTION

NUMBER

INTERVAL

(YEARS)

ZONE ACCESSMAINTENANCE

MANUAL

REFERENCE

SECTION

CORROSION INSPECTION

DESCRIPTIONS

IT RI

C71.130.02I 2 1 130 NOTE 71-20-00 Engine mount assemblies. Make sure

you examine these areas:

02.01 Engine Upper, Right and Left

Side Mount Brackets.

02.02 Engine Mount and Mount Bolts.

02.03 Engine Mount to Engine Ring

Attach Bolts.

NOTE: Remove the engine cowl

door to get access.

STATION: FS 61.78 Models 208 and

208B

C71.130.03I 2 1 130 NOTE 71-20-00 Engine ring assembly. Make sure you

examine these areas:

03.01 Engine Ring Surface.

03.02 Areas Around Junction Weld.

03.03 Engine Ring to Engine Truss

Attach Bolts.

NOTE: Remove the engine cowl

door and nose cap to get

access.

STATION: FS 61.78 Models 208 and

208B

C78.130.01E 2 1 130 NOTE 78-00-00

78-10-00

Exhaust system installation. Make

sure you examine these areas:

01.01 Primary Exhaust Duct, and

Attach Bolts.

01.02 Secondary Exhaust Duct, and

Attach Screws.

01.03 Exhaust Deflector and Retainer

Screws.

01.04 Inboard, Center and Outboard

Secondary Exhaust Hanger Brackets.

NOTE: Remove the right side lower

engine cowl to get access to

secondary exhaust.

STATION: FS 49.47 to FS 100.00

Models 208 and 208B

5-30-02 Page 38

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

CORROSION PREVENTION AND CONTROL PROGRAM - APPENDIX

1. Appendix A - Development Of The Baseline Program

A. The Corrosion Prevention and Control Program Baseline Program.

(1) The function of the Corrosion Prevention and Control Program (CPCP) is to give the minimum

procedures necessary to prevent and control corrosion so that continued airworthiness is not

risked. The Principle Structural Elements (PSEs) are areas where the CPCP applies.

(2) The CPCP Baseline Program consists of a Corrosion Program Inspection (CPI), Implementation

Threshold (IT), and a Repeat Interval (RI). Each inspection is to be done in an airplane zone.

(3) The corrosion reports that are sent to Cessna Aircraft Company and data from the FAA Service

Difficulty Records from 1995 to 2002 were used to identify the inspection areas of the Baseline

Program. When more than one incident of corrosion was identified at a specified location, an

inspection was included for that location in the Baseline Program.

(4) When corrosion was found once, the data was examined to find if the corrosion was caused by

one specified occurrence or if other airplanes could have corrosion in the same location. If so,

this inspection was added to the Baseline Program.

(5) The inspection interval was specified by the duration and corrosion severity.

2. Appendix B - Procedures For Recording Inspection Results

A. Record the Inspection Results.

(1) It is not an FAA mandatory procedure to record the CPCP results, but Cessna Aircraft

Company recommends that records be kept to assist in program adjustments when necessary.

The inspection of records will make sure the identification, repeat, and level of corrosion is

monitored. The data can identify whether there is more or less corrosion at repeat intervals.

The data can also be used to approve increased or decreased inspection intervals.

3. Appendix C - Guidelines

A. Glossary

(1) The following additional information clarifies the previous sections of this document.

B. The Glossary of General Descriptions. Refer to Table 1, Figure 1, Figure 2, Figure 3, and Figure 4.

WORD GENERAL DESCRIPTION

Allowable Limit The allowable limit is the maximum amount of material (usually expressed in

material thickness) that may be removed or blended out without affecting the

ultimate design strength capability of the structural member. Allowable limits

may be established by the design approval holder. The FAA (or applicable

regulatory authority) may also establish allowable limits. The design approval

holder normally publishes allowable limits in the structural repair manual or in

service bulletins.

Baseline Program A Baseline Program is a CPCP developed for a specific model airplane.

The design approval holder typically develops the Baseline Program.

However, it may be developed by a group of operators who intend to use it in

developing their individual CPCP. It contains the corrosion program inspection,

an implementation threshold, and a repeat interval for the procedure

accomplishment in each area or zone.

Basic Task Refer to corrosion program inspection.

Corrosion Program

Inspection (CPI)

The corrosion program inspection (CPI) is a specific and fundamental set

of work elements that should be performed repetitively in all task areas or

zones to successfully control corrosion. The contents of the CPI may vary

depending upon the specific requirements in an airplane area or zone. The

CPI is developed to protect the primary structure of the airplane.

5-30-05 Page 1

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

WORD GENERAL DESCRIPTION

Corrosion (Metal) The physical deterioration of metals caused by reaction to an adverse

environment.

Corrosion Prevention and

Control Program (CPCP)

A Corrosion Prevention and Control Program is a comprehensive and

systematic 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 if

corrosion damage exceeds Level 1 in any area or zone.

Design Approval Holder The design approval holder is either the type certificate holder for the aircraft

or the supplemental type certificate holder.

Implementation Threshold

(IT)

The implementation threshold for a specific airplane is the date, based on

that airplane’s age, by which the initial corrosion inspection task should be

accomplished in an area or zone.

Inspection Area The inspection area is a region of airplane structure to which one or more CPIs

are assigned. The inspection area may also be referred to as a Zone.

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

1. Corrosion damage occurring between successive inspections, that is

local and can be reworked or blended out with the allowable limit.

2. 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).

3. Operator experience has demonstrated only light corrosion between

each successive corrosion task inspection; the latest corrosion

inspection task results in rework or blend out that exceeds the allowable

limit.

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.

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.

Light Corrosion Light corrosion is corrosion damage so slight that removal and blendout over

multiple repeat intervals (RI) may be accomplished before material loss

exceeds the allowable limit.

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.

5-30-05 Page 2

© Cessna Aircraft Company Mar 1/2008
CESSNA AIRCRAFT COMPANY

MODEL 208

MAINTENANCE MANUAL

WORD GENERAL DESCRIPTION

Principal Structural

Element (PSE)

A PSE is an element that contributes significantly to carrying flight, ground or

pressurization loads, and whose integrity is essential in maintaining the overall

structural integrity of the airplane.

Repeat Interval (RI) The repeat interval is the calendar time between the accomplishment of

successive corrosion inspection tasks for a Task Area or Zone.

Task Area Refer to Inspection Area.

Urgent Airworthiness

Concern

An urgent airworthiness concern is damage that could jeopardize continued

safe operation of any airplane. An urgent airworthiness concern typically

requires correction before the next flight and expeditious action to inspect the

other airplanes in the operator’s fleet.

Widespread Corrosion Widespread corrosion is corrosion of two or more adjacent skin or web bays (a

web bay is defined by frame, stringer, or stiffener spacing). Or, widespread

corrosion is corrosion of two or more adjacent frames, chords, stringers, or

stiffeners. Or, widespread corrosion is corrosion of a frame, chord, stringer, or

stiffener and an adjacent skin or web bay.

Zone Refer to Inspection Area.

4. Application Of The Corrosion Program Inspection

NOTE: In this manual the Basic Tasks are referred to as the Corrosion Program Inspection (CPI).

A. Typical Airplane Zone Corrosion Program Inspection Procedures.

(1) Remove all the equipment and airplane interior (for example the insulation, upper upholstery

panel, lower upholstery panel) as necessary to do the corrosion inspection.

(2) Clean the areas given in the corrosion inspection before you inspect them.

(3) Do a visual inspection of all of the Principal Structural Elements (PSEs) and other structure given

in the corrosion inspection for corrosion, cracking, and deformation.

(a) Carefully examine the areas that show that corrosion has occurred before.

NOTE: Areas that need a careful inspection are given in the corrosion inspection.

(b) Nondestructive testing inspections or visual inspections can be needed after some

disassembly if the inspection shows a bulge in the skin, corrosion under the splices or

corrosion under fittings.

(4) Remove all of the corrosion, examine the damage, and repair or replace the damaged structure.

(a) Apply a protective finish where it is required. Refer to Chapter 20, Interior and Exterior

Finish - Cleaning/Painting or Chapter 51, Corrosion - Description and Operation.

(b) Clean or replace the ferrous metal fasteners with oxidation.

(5) Remove blockages of foreign object debris so that the holes and clearances between parts can

drain.

(6) For bare metal on any surface of the airplane, apply fuel and corrosion resistant primer MILPRF-23377.

(a) Apply a polyurethane topcoat paint to the exterior painted surface. Refer to the

manufacturer's procedures.

(7) Cessna Aircraft Company recommends that you apply a corrosion preventive compound once

every two years to areas with a high possibility for severe corrosion identified in the corrosion

inspection.

(a) On the Model 208, apply LPS-3 Heavy-Duty Rust Inhibitor, or equivalent, in the bilge area

below the floorboards between FS 168.00 and FS 211.00. Refer to Chapter 51, Corrosion

- Description and Operation.

(b) On the Model 208B, apply LPS-3 Heavy-Duty Rust Inhibitor, or equivalent, in the bilge area

below the floorboards between FS 168.00 and FS 356.00. Refer to Chapter 51, Corrosion

- Description and Operation

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(8) Apply compounds that will replace water and prevent corrosion. Refer to Chapter 51, Corrosion

- Description and Operation.

(a) Apply one layer of LPS-3 Heavy-Duty Rust Inhibitor, or equivalent, that will soak into the

fayed surfaces to replace water and prevent corrosion.

Table 1. Areas and Items Not to Apply Compounds to Replace Water and Prevent Corrosion

AREA or ITEM

Oxygen System Lines and Components

Cables, Pulleys, and Trim Tab Pushrod

Plastics, Elastomers

Lubricated and Teflon Surfaces (Greased Joints, Sealed Bearings, and Grommets)

Adjacent to Tears and Holes in Insulation (Not Waterproof)

Areas with Electrical Arc Potential, Wiring

Interior Upholstery Panels (Changes the Flammability Properties)

Cargo Pod (Changes the Flammability Properties)

Pitot Tubes

Fuel Cap

Tie Down Lugs

Chrome Items (handles, locks)

Standard Polished Spinner

Stall Warning Detector

(9) Install the dry insulation blankets.

(10) Install the equipment and airplane interior (upper upholstery panel, lower upholstery panel) that

was removed to do the corrosion inspection.

5. Determination of the Corrosion Levels

A. Find the Corrosion Levels (Refer to Figure 5).

(1) Corrosion found on a structure when you use the Corrosion Program and Corrosion Prevention

(CPCP) Baseline Program will help find the extent of the corrosion.

(2) The second and subsequent inspections will find how well the CPCP program has been

prepared, or if there is a need to make adjustments to the Baseline Program.

(3) A good quality CPCP is one that controls corrosion to Level 1 or better.

(4) If Level 2 corrosion is found during the second or subsequent inspection, you must do something

to decrease the future corrosion to Level 1 or better.

(5) If Level 3 corrosion is found, you must also do something to decrease the future corrosion to

Level 1. Also, a plan to find or prevent Level 3 corrosion in the same area on other airplanes

must be added to the CPCP.

(6) All the corrosion that you can repair in the allowable damage limits, found in the Model 208

Structural Repair Manual, is Level 1 corrosion.

(7) If all corrosion is Level 1, the CPCP is correctly prepared.

(8) If you must reinforce or replace the part because of corrosion, the corrosion is Level 2.

(9) If the part is not airworthy because of the corrosion, you must do an analysis to find out if the

corrosion is Level 3.

(10) The chart found in this section will help find the level of the corrosion.

(11) The probability that the same problem will occur on another airplane is dependent on several

factors such as: past maintenance history, operating environment, years in service, inspectability

of the corroded area and the cause of the problem.

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B. Level 2 Corrosion Findings.

(1) All Level 2 corrosion that is more than the rework limits of the Structural Repair Manual must be

reported to Cessna Aircraft Company. Cessna Aircraft Company engineering will do an analysis

to make sure the corrosion is not a urgent airworthiness concern.

(2) When doing the analysis, Cessna Aircraft Company will consider:

(a) Can the cause of the corrosion be identified, such as a chemical spill or protective finish

breakdown?

(b) Has the same level of corrosion been found on other airplanes?

(c) Are the corrosion protection procedures applied during manufacture the same for earlier

and later models?

(d) Age of the corroded airplane compared to others checked.

(e) Is the maintenance history different than the other airplanes in the fleet?

6. Typical Actions That Follow the Determination of the Corrosion Level.

A. If corrosion is found, find the corrosion level, then do the necessary steps for a specific inspection.

B. If Level 1 corrosion is found during the first CPCP inspection.

(1) Repair the structure. Refer to the Model 208 Structural Repair Manual or a Cessna Aircraft

Company approved repair procedure.

(2) Continue with the Baseline Program.

(a) Optional: Document the results of the inspection for use in validating program compliance.

C. If Level 2 corrosion is found during the first CPCP inspection.

(1) Repair the structure. Refer to the Model 208 Structural Repair Manual or Cessna Aircraft

Company approved repair procedure.

(2) Report the details of the corrosion you see to Cessna Aircraft Company and the FAA (or

applicable regulatory authority).

(3) Continue to use the Baseline Program but check the corroded area carefully when you do a

subsequent CPCP inspection.

(4) It is recommended that you record the results of the inspection to show compliance with the

program.

D. If Level 3 corrosion is found during the first CPCP inspection.

(1) Immediately contact Cessna Aircraft Company and the FAA or regulatory authority of the

corrosion you found. Refer to Reporting System.

(2) Give sufficient information to make sure that the condition is a possible urgent airworthiness

concern for your fleet. Get assistance from Cessna Propeller Aircraft Product Support to develop

a plan of action.

(3) Apply the corrosion program inspection, which includes the repair of the structure. Refer to the

Model 208 Structural Repair Manual or a Cessna Aircraft Company approved repair procedure.

(4) Do a report that has the information of the findings. Refer to Corrosion Prevention And Control

Program Reporting System - Description And Operation.

(5) Continue with the Baseline Program and other steps of procedure required by the FAA, or

applicable regulatory authority. Examine this area carefully during future inspections.

E. If no corrosion is found during the second or subsequent CPCP inspection:

(1) Continue with the current Corrosion Prevention and Control Program. No adjustment of the

current program is required.

(2) It is recommended that you record the results of the inspection for a possible increase of the

corrosion inspection Implementation Threshold (IT) and/or Repeat Interval (RI).

F. If Level 1 corrosion is found on the second or subsequent CPCP inspection:

(1) Do the corrosion program inspection, which includes the repair of the structure. Refer to the

Model 208 Structural Repair Manual or a Cessna Aircraft Company approved repair procedure.

(2) Continue with the Baseline Program.

(3) No adjustment of the existing program is required.

(4) It is recommended that you record the corrosion inspection number and the results of the

inspection to show that the program was obeyed.

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G. If Level 2 corrosion is found on the second or subsequent CPCP inspection:

(1) Repair the structure. Refer to the Model 208 Structural Repair Manual or a Cessna Aircraft

Company approved repair procedure.

(2) Do a report that shows the information about the corrosion and send it to Cessna Aircraft

Company and the FAA (or applicable regulatory authority).

(3) If corrosion damage required the removal of material just beyond the allowable limits (within 10

percent), complete a check of the other airplanes in the fleet before you change the maintenance

program.

(a) If the corrosion is typical of Level 2, use the fleet data to find what changes are required to

control corrosion to Level 1 or better.

(b) If fleet damage is typically Level 1, examine the corroded area during subsequent

inspections on all affected airplanes.

(c) Make changes to the maintenance program if the typical corrosion becomes Level 2.

(4) Further evaluation by Cessna Aircraft Company is recommended for Level 2 corrosion findings

that are well beyond the allowable limits, and there is an airworthiness concern in which prompt

action is required.

NOTE: The airworthiness concern is because of the possibility to have similar but more

severe corrosion on any other airplane in the operator's fleet prior to the next

scheduled inspection of that area.

(5) Find the action required to control the corrosion to a Level 1 or better, between future successive

inspections. These can include the items that follow:

(a) A structural modification, such as additional drainage.

(b) Improvements to the corrosion prevention and control inspections, such as more care and

attention to corrosion removal, reapplication of protective finish, drainage path clearance.

(c) Decrease the Implementation Threshold (IT) for additional airplanes that go into the

program.

(d) Decrease the Repeat Interval (RI).

(6) Send a plan of corrective action to the FAA or applicable regulatory authority for approval and

to Cessna Aircraft Company.

(7) Use the approved plan of action.

H. If Level 3 corrosion is found on the second or subsequent CPCP inspection:

(1) contact Cessna Aircraft Company and the FAA (or applicable regulatory authority) about the

corrosion that was found.

(2) Send a plan to examine the same area on other affected airplanes in the operator's fleet.

NOTE: Circumstances can dictate the need to examine airplanes younger than the

corresponding Baseline Program Implementation Threshold.

(3) Apply the corrosion program inspection, which includes the repair of the structure. Use the

Model 208 Structural Repair Manual or a Cessna Aircraft Company approved repair procedure.

I. Find the action needed to control the corrosion finding to Level 1 or better, between future successive

inspections. These can include any or all of the following:

(1) A structural modification, such as additional drainage.

(2) Improvements to the corrosion prevention and control inspections, such as more care and

attention to corrosion removal, reapplication of protective finish, drainage path clearance.

(3) A decrease in the Implementation Threshold (IT) for additional airplanes entering the program.

(4) A decrease in the Repeat Interval (RI).

J. Send a plan of corrective action to the FAA (or applicable regulator authority for approval) as needed.

K. Use the approved plan of action.

L. It is recommended that you give the details of the findings to Cessna Aircraft Company.

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7. Factors Influencing Corrosion Occurrences

A. If you find Level 2 or Level 3 corrosion, when you think about how to change your CPCP, think about

the list that follows:

(1) Is there a presence of LPS-3 Heavy-Duty Rust Inhibitor?

(2) Is there a presence or condition of protective finish?

(3) What was the Implementation Threshold (IT) of the operator's Corrosion Control and Control

Program (CPCP)?

(4) What was the length of time since the last inspection and/or application of corrosion inhibiting

compound Repeat Interval (RI)?

(5) Was there inadequate clean-up/removal of corrosion prior to application of corrosion inhibiting

compound, during previous maintenance of the area?

(6) Are the moisture drains blocked or is there inadequate drainage?

(7) What was the environment, the time of exposure to the environment and the use of the airplane?

(a) Was the environment tropical, desert, salt water or industrial?

(b) Are there electrolytes or water and moisture, salt water or battery fluid?

(8) Was there a variation in past maintenance history and or use of the airplanes in the operator's

fleet?

(9) Were there variations in the production build standard in the operator's fleet?

8. Reporting

A. The minimum requirements to prevent or control the corrosion in the Corrosion Prevention and Control

Program (CPCP) were made on the best information, knowledge and experience available at the time.

As this experience and knowledge get better, the CPCPs will be changed at intervals as necessary.

A reporting system for this is in Section 4.0.

(1) You must contact the Cessna Aircraft Company about all Level 2 or 3 corrosion of the structure

that is on the list in the Baseline Program that is found during the second and subsequent

corrosion program inspections. Refer to Reporting System.

NOTE: You do not have to contact the Cessna Aircraft Company about corrosion that is found

on structure that is not on the list in the Baseline Program, for example the secondary

structure.

9. Program Implementation

A. When a CPCP is started it is important to do the items that follow:

(1) Start inspections where the airplane age is equal to or greater than the Baseline Program

Implementation Threshold age (IT).

(2) Once the corrosion program inspection (CPI) is started, the subsequent applications of the CPI

are given by the Repeat Interval (RI) for each CPI.

(3) You can start a CPCP on the basis of individual CPIs or groups of CPIs.

(4) Cessna Aircraft Company highly recommends to start all of the CPIs as soon as possible. This

is the most cost effective way to prevent or control corrosion.

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UNSCHEDULED MAINTENANCE CHECKS

1. General

A. During operation, the airplane may be subjected to:

(1) Hard landings.

(2) Overspeed.

(3) Severe air turbulence or severe maneuvers.

(4) Towing with a large fuel unbalance or high drag/side loads due to ground handling.

(5) Lightning Strike.

B. 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.

C. 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.

D. If foreign object damage is encountered (suspected or actual), a visual inspection of the airplane must

be accomplished before airplane is returned to service.

2. Unscheduled Maintenance Checks Defined and Areas to be Inspected

A. Hard/Overweight Landings.

(1) 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 FAA Approved

Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.

NOTE: If the hard/overweight landing is combined with high drag/side loads, additional

checks are required.

(2) Hard or overweight landing check.

(a) Landing gear.

1 Main gear struts - Inspect for security of attachment and permanent set.

2 Main gear attachments and supporting structure - Inspect for security, loose or failed

fasteners, and any evidence of structural damage.

3 Main gear spring - Inspect for gear spread or wing low.

4 Nose gear trunnion supports and attaching structure - Inspect for security, loose or

failed fasteners, and any evidence of structural damage.

5 Nose gear attachments and supporting structure - Inspect for security, loose or failed

fasteners, and any evidence of structural damage.

(b) Wings.

1 Wing surface and lift strut - Inspect for skin buckles, loose or failed fasteners, and

security of attach fittings and fuel leaks

2 Trailing edge - Inspect for any deformation affecting normal flap operation.

B. Overspeed.

(1) Any time an airplane has exceeded one or both of the following:

(a) Airplane overspeed exceeding placard speed limits of flaps.

(b) Airplane overspeed exceeding design speeds.

(2) Airplanes equipped with an airspeed exceedance device capable of recording an airspeed

exceedence with accompanying time duration:

(a) 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.

(3) Overspeed (airspeed) check.

(a) Fuselage.

1 Windshield and Windows - Inspect for buckling, dents, loose or failed fasteners, and

any evidence of structural damage.

2 All hinged doors - Inspect hinges, hinge attach points, latches and attachments, and

skins for deformation and evidence of structural damage.

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(b) Cowling.

1 Skins - Inspect for buckling, cracks, loose or failed fasteners, and indications of

structural damage.

(c) Stabilizers.

1 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.

(d) Wings.

1 Flaps - Inspect for skin buckling, cracks, loose or failed fasteners, attachments and

structure for damage.

2 Fillets and fairings - Inspect for buckling, dents, cracks, and loose or failed fasteners.

C. Severe air turbulence or severe maneuvers.

(1) May be defined as atmospheric conditions producing violent buffeting of airplane. Severe

maneuvers can be defined as any maneuvers exceeding Pilot's Operating Handbook and FAA

Approved Airplane Flight Manual limits.

(2) Severe turbulence and/or maneuvers checks.

(a) Stabilizers.

1 Horizontal stabilizer hinge fittings, actuator fittings and stabilizer center section -

Inspect for security, loose or failed fasteners, and any evidence of structural damage.

2 Vertical stabilizer - Inspect for evidence of structural damage, skin buckles and

security at primary attachments in tailcone, loose or failed fasteners, damage to

hinges and actuator fittings.

3 Elevator and rudder balance weight supporting structure - Inspect for security, loose

or failed fasteners, and evidence of structural damage.

(b) Wing.

1 Wing to body strut fittings and supporting structure - Inspect for security, loose or

failed fasteners, and evidence of structural damage.

2 Trailing Edge - Inspect for any deformation affecting normal operation of flap and

aileron.

D. Lightning strike.

(1) 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. 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.

(2) Lightning strike check.

(a) As the following checks are performed, complete Lightning Strike/Static Discharge Incident

Reporting Form. Completed form must be mailed to Cessna Contract Services, P.O. Box

7706, Wichita, KS 67277 Attn: Manager Contract Services.

(b) Communications.

1 Antennas - Inspect all antennas for evidence of burning or eroding. If damage is

noted, perform functional check of affected system.

(c) Navigation.

1 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.

2 Glideslope antenna - Inspect for burning and pitting. If damage is noted, perform a

functional check of glideslope system.

3 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.

(d) Fuselage.

1 Skin - Inspect surface of fuselage skin for evidence of damage.

2 Tailcone - Inspect tailcone and static dischargers for damage.

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(e) Stabilizers.

1 Inspect surfaces of stabilizers for evidence of damage.

(f) Wings.

1 Skins - Inspect for evidence of burning and eroding.

2 Wing tips - Inspect for evidence of burning and pitting.

3 Flight surfaces and hinging mechanisms - Inspect for burning and pitting.

4 Radome - Inspect for evidence of burning or eroding.

(g) Propeller.

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

(h) Powerplant

1 Refer to the engine manufacturer's maintenance manual, unscheduled inspection.

E. Foreign object damage.

(1) 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.

(2) 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 is wind and

dust conditions, the covers should be installed as soon as practicable following engine shutdown

and engine cooling.

(3) 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.

(4) 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.

(5) Foreign object damage check.

(a) Landing gear.

1 Fairings - Inspect for dents, cracks, misalignment, and indication of structural

damage.

(b) Fuselage.

1 Skin - Inspect forward and belly areas for dents, punctures, cracks, and any evidence

of damage.

(c) Cowling.

1 Skins - Inspect for dents, punctures, loose or failed fasteners, cracks or indications

of structural damage.

(d) Stabilizers.

1 Leading edge skins - Inspect for dents, cracks, scratches, and any evidence of

structural damage.

2 Surface de-ice boots - Inspect for cuts, punctures, or tears.

(e) Windows.

1 Windshield - Inspect for chipping, scratches, and cracks.

(f) Wings.

1 Leading edge skins - Inspect for dents, cracks, punctures, and evidence of possible

structural damage.

2 Radome - Inspect for dents, cracks, punctures, scratches, etc.

3 Surface de-ice boots - Inspect for cuts, punctures, or tears.

(g) Engine.

1 Air inlet section - Inspect for dents, cracks, scratches, punctures, blood and feathers.

2 Propeller - Inspect for nicked, bent, broken, cracked, or rubbing blades.

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F. High drag/side loads due to ground handling.

(1) 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.

(2) High drag/side loads due to ground handling check.

(a) Landing gear.

1 Main gear and fairings - Inspect for loose or failed fasteners, buckling, security,

cracks, and evidence of structural damage.

2 Nose gear and fairing - Inspect for loose or failed fasteners, cracks, steering cables

tension, security, buckling, and evidence of structural damage.

(b) Wings.

1 Wing to fuselage attach fittings and attaching structure - Inspect for security, loose or

failed fasteners, and evidence of structural failure.

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© Cessna Aircraft Company Apr 1/2010


Owner Advisory

May 16, 2014 CAB11-5A

Dear Cessna Caravan Owner:

This Owner Advisory is to inform you that CAB11-5 Revision 1 Time Limits/Maintenance Checks - New

208/208B Task-Based Inspection Program has been issued.

PURPOSE

The purpose of this Service Bulletin is to clarify the instructions provided in CAB11-5 Original Issue to

incorporate the new, task-based inspection program on the Model 208/208B presented in Revision 24 to the

maintenance manual. The task-based inspection program replaced the inspection program from Revision 23

of the maintenance manual and the phase card inspections. The maintenance manual has since revised to

Revision 27.

U.S. registered airplanes operating under CFR 14 Part 91 that have not obtained approval for the task-based

maintenance program as a progressive inspection under 91.409 paragraph d or that have not obtained an

exemption from CFR 14 Part 91.409(a) and (b) must be inspected as required by 91.409(a) and (b).

The task-based inspection program was incorporated on the Model 208/208B in order to make maintenance

procedures and inspections more efficient for operators who obtain approval for the task-based inspection

program as an approved aircraft inspection program AAIP under part 135 of the U.S. aviation regulations or for

operators who adopt the task-based program as a manufacturer’s recommended program as authorized by their

local regulatory authorities. Cessna has reviewed all item codes for efficiency, applicability, and effectiveness.

• Many item codes were incorporated into one task.

• Item codes that were found to be not applicable or not effective were eliminated.

• Many item code intervals were extended within the new tasks.

• The scheduled maintenance checks in Chapter 5-20-01 were removed from the maintenance manual.

• Chapter 5-10-00 has incorporated inspection documents to replace the progressive care program and the

inspection operations.

• Inspection time limits in Chapter 5-10-01 have tasks incorporated.

• Phase cards will no longer be sold, revised, or supported by Cessna Aircraft Company.

• The supplemental inspection documents (SIDS) were incorporated into the tasks. Refer to Chapter

5-14-00 for the conversion matrix.

• The CPCPs were incorporated into the tasks and incorporated into the task-based program.

COMPLIANCE

Optional: Conversion to the manufacturer’s recommended 208/208B Task-Based Inspection Program may be

accomplished at the owner's discretion with prior approval from your local regulatory authority.

NOTE: Compliance with CAB11-5 Revision 1 is required for airplanes that were able to comply with the

Original Issue.

Page 1 of 2

To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and

prevailing government regulations. Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the

requirements of this publication.

Cessna Aircraft Company, Customer Service, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 517-5800, Facsimile (316) 517-7271

www.cessnasupport.com

COPYRIGHT © 2014
NOTE: Cessna no longer supports the previous inspection programs. There will be no updates to the phase

cards or the maintenance program they supported.

NOTE: If you wish to continue the phase card program, you may apply to your local regulatory authority to

have the continued use of the phase cards approved for your airplanes.

NOTE: For United States operators who operate per Part 91 of Title 14, Code of Federal Regulations, the

manufacturer's recommended task-based inspection program provided in the maintenance manual

does not relieve the requirements for an annual and/or 100 hour inspection per Part 91.409(a) and

(b). It is the person with the Inspection Authorization's (or equivalent) responsibility to select the

necessary inspections to create a checklist to make sure that the scope and detail of an annual

and/or 100 hour is performed in accordance with Part 43 Appendix D of Title 14, Code of Federal

Regulations. Otherwise, the individual owner/operator may refer to Part 11 to petition the FAA for an

exemption from Part 91.409(a) and (b) in order to use the manufacturer's recommended task-based

inspection program as written.

WARRANTY

Not applicable

Please contact a Cessna Authorized Service Facility for detailed information and arrange to have Cessna

Caravan Service Bulletin CAB11-5 Revision 1 accomplished on your airplane.

NOTE: As a convenience, service documents are now available online to all our customers through a simple,

free-of-charge registration process. If you would like to sign up, please visit the "Customer Support

Login" link at www.Cessna.com to register.

CAB11-5A

Page 2 May 16, 2014