# 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 airp lanes 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: Compli ance 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

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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 a nd 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 manufactu rer’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 d ue 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 rem ain at the current due times.
• Cockpit and/or Cabin Mounted Halon-Type Fire Extinguishers Hydrostatic Test Inspection due times will not ch ange 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 chan ge and will remain at the current due times.
• Emergency Locator Transmitter Battery Inspections required in accordance with FAR 91.207 due times wi ll 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 capaci ty 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. Compl ete 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: C ESCOM C/O, Camp Systems International, 8200 East 34th Street North, Building 1600 Suite 1607, Wichita, KS 67226, Fax: 316-462-2443.

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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

CES SNA 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 inpertinent part that,except asprovided inparagraph (c) of the sectio n 1

### noperson may operate anaircraft unless, within the preceding 12

calendar months, it has had anannual inspection inaccordance with part 43 and has been approved for return to service. Section 91.409(b), prescribes, inpertinent part, that

1Section 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

noperson may operate an aircraft carrying any person (other than a crewmember) for hire, andno person may give flight instruction for hire in anaircraft whichthat person provides, unlesswithin the preceding 1 00 hours of time inservice the aircraft has

received anannual or 100-hour inspection and been approvedfor return toservice in accordance with part 43.

Cessna petitioned for this exemption sooperatorsof itsModel CE208aircraft could use a task

-basedinspection program itdeveloped inlieu of the annual and100-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) touse 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.

Thepetitioner 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.

Thepetitioner 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:
TheFAA 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).
TheFAA 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 

# 5

**TIME LIMITS/ MAINTENANCE**  **CHECKS**

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL



## 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 MAN UAL

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 MAN UAL



## 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 MAN UAL

INSPECTION OPERATION 10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-10 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-10 Page 1 General Inspe ction Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-10 Page 1 INSPECTION OPERATION 11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-11 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-11 Page 1 General Insp ection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-11 Page 1 INSPECTION OPERATION 12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-12 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-12 Page 1 General Ins pection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-12 Pag e 1 INSPECTION OPERATION 13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-13 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-13 Page 1 General Ins pection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-13 Pag e 1 INSPECTION OPERATION 14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-14 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-14 Page 1 General In spection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-14 Page 1 INSPECTION OPERATION 15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-15 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-15 Page 1 General I nspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-15 P age 1 INSPECTION OPERATION 16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-16 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-16 Page 1 General I nspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-16 P age 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 Genera l Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-1 8 Page 1 INSPECTION OPERATION 19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-19 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-19 Page 1 Genera l Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-1 9 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 Gene ral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12 -29 Page 1 INSPECTION OPERATION 30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-30 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-30 Page 1 Gene ral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12 -30 Page 1 INSPECTION OPERATION 31 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-31 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-31 Page 1 Gen eral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 2-31 Page 1 INSPECTION OPERATION 32 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-32 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-32 Page 1 Gen eral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 2-32 Page 1 INSPECTION OPERATION 33 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-33 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-33 Page 1 Ge neral 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 MAN UAL

INSPECTION OPERATION 34 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-34 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-34 Page 1 General Inspe ction Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-34 Page 1 INSPECTION OPERATION 35 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-35 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-35 Page 1 General Insp ection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-35 Page 1 INSPECTION OPERATION 36 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-36 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-36 Page 1 General Ins pection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-36 Pag e 1 INSPECTION OPERATION 37 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-37 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-37 Page 1 General Ins pection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-37 Pag e 1 INSPECTION OPERATION 38 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-38 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-38 Page 1 General In spection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-38 Page 1 INSPECTION OPERATION 39 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-39 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-39 Page 1 General I nspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-39 P age 1 INSPECTION OPERATION 40 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-40 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-40 Page 1 General I nspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-40 P age 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 Genera l Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-M A Page 1 INSPECTION OPERATION MB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MB Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MB Page 1 Genera l Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-M B 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 Gene ral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12 -MD Page 1 INSPECTION OPERATION ME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ME Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ME Page 1 Gene ral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12 -ME Page 1 INSPECTION OPERATION MF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MF Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MF Page 1 Gen eral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 2-MF Page 1 INSPECTION OPERATION MG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MG Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MG Page 1 Gen eral Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 2-MG Page 1 INSPECTION OPERATION MI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MI Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MI Page 1 Ge neral 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 MAN UAL

INSPECTION OPERATION MJ. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MJ Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MJ Page 1 General Inspe ction Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MJ Page 1 INSPECTION OPERATION MK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MK Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MK Page 1 General Insp ection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MK Page 1 INSPECTION OPERATION ML . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ML Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ML Page 1 General Ins pection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-ML Pag e 1 INSPECTION OPERATION MH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MH Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MH Page 1 General Ins pection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12-MH Pag e 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 Inspectio n Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 5 Applicability/Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 5 PSE Details . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13-00 Page 6
LISTING O F SUPPLEMENTAL INSPECTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-00 P age 1 Supplemental Inspection Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-00 Page 1 Supplemental Inspections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-00 Page 1
SUPPLEM ENTAL INSPECTION NUMBER: 32-10-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-01 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-01 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-01 Page 1 Main Lan ding 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
SUPPL EMENTAL INSPECTION NUMBER: 53-20-07 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14- 04 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-04 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-04 Page 1 Fuse lage 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 Insp ection 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 Tit le. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 4-06 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-06 Page 1 Main Landing Gear Fitting Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-06 Page 1
SU PPLEMENTAL INSPECTION NUMBER: 53-20-05 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5- 14-07 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-07 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-07 Page 1 Ma in 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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-08 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-08 Page 1 Inspection Co mpliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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
SUPPLEMENT AL INSPECTION NUMBER: 53-20-08 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Pag e 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Page 1 Carry-Thru Root Rib Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-10 Pag e 1 SUPPLEMENTAL INSPECTION NUMBER: 53-20-09 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-11 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-11 Page 1 Inspectio n 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
SUPPLEME NTAL INSPECTION NUMBER: 53-10-07 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-13 P age 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-13 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-13 Page 1 Seat Rai ls 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 Inspect ion 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-1 5 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
SUPPL EMENTAL INSPECTION NUMBER: 53-20-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14- 16 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-16 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-16 Page 1 Fusel age 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 Insp ection 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 Titl e.. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . .. . . . . 5-14 -18 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-18 Page 1 Vertical Stabilizer Attach Points Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-18 Page 1
SUP PLEMENTAL INSPECTION NUMBER: 55-10-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 4-19 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-19 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-19 Page 1 Ho rizontal 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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 55-10-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-20 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-20 Page 1 Inspection Co mpliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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
SUPPLEMENTA L 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 Pag e 1 SUPPLEMENTAL INSPECTION NUMBER: 55-30-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-22 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-22 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-22 Pag e 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
SUPPLEMEN TAL 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 Ca rry-Thru Spar Attachment Fittings Inspection . . . . . . . . . . . . . . . . . . . . . . . . 5-14-24 P age 1 SUPPLEMENTAL INSPECTION NUMBER: 57-20-02 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-25 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-25 Page 1 Inspect ion 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
SUPPLE MENTAL INSPECTION NUMBER: 57-50-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-2 7 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 Inspe ction 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 Titl e. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14 -29 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-29 Page 1 Wing Strut Attachment to Front Spar Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-29 Page 1
SUPP LEMENTAL INSPECTION NUMBER: 71-20-01 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14 -30 Page 1 Title. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-30 Page 1 Inspection Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14-30 Page 1 Eng ine Truss and Ring Assembly Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 4-30 Page 1 SCHEDULED INSPECTION CHECKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-20-01 Page 1 Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-20-01 Page 1



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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 Preve ntion 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 P REVENTION 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 P age 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 Unsche duled Maintenance Checks Defined and Areas to be Inspected . . . . . . . . . . 5-50-0 0 Page 1



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## MODEL 208 MAINTENANCE MAN UAL

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 i nspection 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 limi ts 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 recomm ended 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 adde d because there can be no grace period for these inspections.
2. Inspection Requirements
A. Three bas ic 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 P ROGRESSIVE 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 Zon e 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 sp ecial 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 p urpose 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 Inspecti on 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, a nd 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 sched uled 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 po int 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 sect ion. 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 inspectio n 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 exam ine 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 thi s 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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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 adjacen t 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 b undles 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 o r 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 com plete 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 on e 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 b ased 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 Ho urs 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 1 0 E ve ry 2 ye a rs. J 1 1 E ve ry 3 ye a rs

. K 1 2 E ve ry 4 ye a rs

. L 1 3 E ve ry 6 ye a rs. M 14 Every 12 years.
N 1 5 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 2 1 At 10,000 hours and every 5000 hours thereafter. (Not Used)
U 2 2 At 5000 landings and every 1000 landings thereafter. (Not Used)
V 2 3 Every 400 hours or 6 calendar months, whichever occurs first.
W 2 4 At 4000 landings and every 500 landings thereafter. (Not Used)
X 2 5 At 15,000 landings and every 3000 landings thereafter. (Not Used)
Y 26 At 5000 hours and every 3600 hours thereafter. (Not Used)
Z 2 7 At 12 years i f 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 Cha pter 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.



## 5-10-00 Page 2 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 hou rs and every 3600 hours thereafter.



## 5-10-00 Page 3 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

INSPECTION TIME LIMITS
1. Inspection Ite ms

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 5 1 1
, 6 1 1

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 an d Controls - Inspect doors, cables and controls for condition and operation. C 4 2 2 0
, 2 24

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 1 2 2

Revised Mar 1/01 213002 Pressure Relief Valve - Inspect for conditi on and security of installation. C 1 1 5 1

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 1 2 2

214002 Heater System Plumbing - Inspect P3 lin e, flow control valve and heat regulating line for security of installation, condition and evidence of damag e. C 1 1 2 2

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 MAN UAL

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 w iring 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) - I nspect 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 condit ion, security of installation, and evidence of overheating. C 4 234

Revise d 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 brida l 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 spro ckets, 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

221 005 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 MAN UAL

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 brida l 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 (i f 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 Flig ht 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 62 3

Revised Mar 1/01 221017 Autopilot Computer Amplifier, Mount, Mount ing Knob and Electrical Components (Model 208 Only) - Inspect for security of installation. C 4 2 1 6

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 MAN UAL

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 p roper 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 C ontrol 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 Inspecti on - Examine the clutch torque settings and complete a GFC 700 Visual Inspection in accordance with the Garm in 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 Avion ic Operating Controls - Inspect for security of installation and proper operation of controls and switches and e nsure that all digital segments illuminate properly. C 4 223

2300 03 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 MAN UAL

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 2 1 6

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 Whee l Pushbutton Switches - Clean the transponder identification switch, microphone switch, and the interph one 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 A L L

Revised Mar 1/01 240002 Instrum ent Panel and Control Pedestal - Inspect wiring, mounting and terminals for condition and security of instal lation. C 4 220, 221, 222, 223, 224, 225, 226
Revised Mar 1/0 1 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 condi tion. 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 MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

242004 Standby Alternator Power Distribution Box - Inspect relay and associated electrical co mponents 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 Cabl e Disconnect and Cables - Inspect for condition, corrosion and security of installation. Inspect battery terminal re ceptacles 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,
corros ion 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 MAN UAL

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 in stallation. 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, se curity of connections and connector hardware. C 1 1 2 1
, 1 2 2

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 c hecks 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 Switch es - Check operation, terminals, wiring and mounting for condition, security of installation and interference. C 4 2 1 5

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 2 3 1
, 2 32

Revised Mar 1/01 251002 Pilot's and Copilot's Seats - Inspect seat b rackets, 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, bea rings 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 MAN UAL

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, cleanlines s 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 installat ion. 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, 90 6, 907, 908

Revised Mar 1/01 255004 Cargo Pod Drain Tubes (if installed) - Insp ect 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 i nstalled) - 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 MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

255007 Cargo Pod Fuel Reservoir Remote Drain (if installed) - Check drain for proper operat ion 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 attachme nt and operation of adjustment devices. C 4 2 5 1
, 2 52

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, conditi on, 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 Fi re 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 MAN UAL

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 win g cables for fraying, chafing, cleanliness, turnbuckle safetying, and proper routing. Inspect pulleys and guard p ins 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 install ation, 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

Revise d 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, 65 1

Revised Mar 1/01 271005 Fuselage and Control Column Aileron Cabl es - Inspect cables for fraying, chafing, cleanliness, turnbuckle safetying, and proper routing. Inspect pul leys 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 MAN UAL

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 55 1
, 6 5 1

Revised Mar 1/01 271011 Aileron Slot Lip Spoiler Pushrods - Lubricate. Refer to Chapter 12, Lubricants - Description and Operation. C 3 55 1
, 6 5 1

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, a nd security of installation; pushrods, pushrod bolts, bearings, and bonding jumpers for evidence of damage o r wear, failed fasteners, and security of installation. Inspect bolts on both ends of pushrods for proper safetyi ng of nuts with cotter pins. B 1, 3 521, 621

Revised Mar 1/01 271014 Aileron Trim Tab - Inspect the trim tab ski ns for cracks, loose rivets, and security of installation; and trim tab hinge for cracks, security of installation, and evi dence of damage. Inspect hinge pin for proper installation at hinge pin retainer. Inspect horn and pushrod for evi dence 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,
crac ks, 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 pus hrod ends for bearing looseness and excessive wear. C 3 65 1



## 5-10-01 Page 11 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 T ab 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 conditi on, 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 securi ty of installation. C 3 671

Revised Mar 1/0 1 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

2710 24 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 MAN UAL

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, L ubricants - Description and Operation. G 8 2 2 6

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 fo r 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 3 1 1
, 32 0

Revis ed 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, 2 53, 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 Cont rol System - Check connections for security of installation, and tightness of fasteners where applicable . Refer to Chapter 20, Torque Data - Maintenance Practices. C 3 2 1 1
, 2 1 2
, 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 require ments. 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 MAN UAL

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 pu shrod bolts for proper safetying of nuts with cotter pins. Refer to Chapter 20, Torque Data - Maintenance Practices. C 3 32 0
, 3 30

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 2 1 3
, 2 1 4

Revised Mar 1/01 273004 Elevator Cables (Tailcone) - Inspect cables for fraying, chafing, cleanliness, turnbuck le 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 fasten ers, 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 32 0
, 3 30

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 MAN UAL

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 rou ting. Inspect chains for proper safetying at all points and chains for proper alignment on sprockets. Inspect pu lleys 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 3 1 1
, 32 0

Revised Mar 1/01 273016 Elevator Trim Tab Cable Stop Blocks - Inspect for condition and security of installation. C 3 3 1 1
, 3 1 2

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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 2 2 6

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 Warn ing 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 operatio nal 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, Fligh t 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,
crac ks, 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 MAN UAL

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 cra nks 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 se curity of motors, drivescrew, and transmission. Clean drivescrew threads and lubricate with #10 weight non-d etergent oil. Inspect flap actuator assembly support structure for cracks and security of installation. Inspect fuse lage seal assemblies for condition and security of installation. C 3 252

Revi sed Mar 1/01 2750 08 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 MAN UAL

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 - Adjust ment/Test. E 6 226, 243

Revised Nov 3/03 275010 Flap bell crank Part Numbers 2622281-2, -1 2 and 2692001-2 - Inspect in accordance with the latest revision of CAB02-1. Refer to Chapter 4, Typical In spection 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 installat ion, 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 Qu antity 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) - Ins pect linkage and controls for condition, security and evidence of damage. C 4 24 3

282003 Fuel Shutoff Valve - Inspect linkage and valve for evidence of damage and operation. Inspect valve for leakage. C 4 2 0 3

282004 Fue l 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 MAN UAL

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 (R ed 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 Sele ctors 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) - Exam ine for condition and correct installation. C 3 122, 251

Revi sed Mar 1/08 3010 02 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 MAN UAL

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 2 3 1 (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 2 0800001 thru 20800221 and 208B0001 thru 208B0316 Incorporating SK208-112) (without TKS) - Do a d ischarge 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 208B00 01 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 1 00-Hour operational check. Do a check of the tank quantity indicator, tank fluid level CAS annunciator, pump fl uid delivery rate, high-pressure warning switch and CAS annunciator, low-pressure warning switch and CAS
annun ciator. 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 MAN UAL

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 A nti-ice System (without TKS) - Do an operational check of the AUTO and MANUAL systems. Make sure that th e 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 Propelle r Anti-ice Brushes (without TKS) - Examine each brush for wear, signs of damage, cleanliness, correct i nstallation 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 Propell er Anti-ice Varistor (without TKS) - Examine the firewall-mounted varistor for condition and correct instal lation. 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 co ndition 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 Landin g 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, Supplemen tal 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 MAN UAL

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 co rrosion and shot peen. If corrosion cannot be removed within the defined repair limits, install new gear compon ents. 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 sche duled 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 attac h 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 Ge ar Fork - Inspect for condition and security of installation. C 2 701

Revise d 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, elon gated 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 MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

Revised Mar 1/01 324002A Landing Gear Wheel Bearings (Airplanes 20800001 thru 20800201 and 208B0001 t hru 208B0255 Not Incorporating CAB 91-30) - Inspect for condition and repack. Refer to Chapter 12, L ubricants - 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

Revise d 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, 72 2

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 70 1



## 5-10-01 Page 25 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 - In spect 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 condi tion 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 Lig hts - 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 MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

332002 Interior Lighting - Check operation of cabin, passenger reading, no smoking/seat belt, 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 2 2 2

341001 Static System - Inspect plumbing for security of installation and evidence of damage. C 3 5 0 3
, 6 03

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 Ve rtical Speed (Rate of Climb) Test). I 10 223

341003 Alternate Static Source - Inspect for evidence of damage and security of installation. C 4 215, 21 6

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 insp ect for leaks, and presence of water in drain fittings. Drain accumulated moisture. Inspect
con dition 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 MAN UAL

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 1 0 BA T

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 operat ion, condition and security of installation. C 3 3 1 1
, 3 1 2

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 M asks 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 MAN UAL

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 visi on, dirt, buckles that are mechanically sound and secure, exhalation valve sticking, leakage and microphone o peration. H 9 231, 232

Revised Mar 1/01 371001 Vacuum System Ejector - Inspect for condition and security of installation. C 1 1 5 1

371002 Vacuum System Hoses - Inspect for hardness, deterioration, looseness or collapsed hoses. C 4 2 0 1
, 2 02

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 Ce ntral Air Filter - Servicing. C 4 2 0 1

Revised Mar 1/01 371005 Vacuum System Relief Valve - Inspect for condition and security of installation. C 4 2 0 1

371006 Low Vacu um 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 8 0 1
, 8 02

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 co ndition, 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, 8 02

521003 Crew Doors Latch Pin - Inspect for damage, cracks, wear and rigging. C 4 8 0 1
, 8 02

521004 Crew Doors Latch Pin Guide - Inspect for damage, cracks and wear. C 4 8 0 1
, 8 02



## 5-10-01 Page 29 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

Revised Mar 1/01 521007 Passenger Doors - Inspect for condition, security of installation and operation. In spect 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 t he 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, c racks, 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 BA T

Revised Mar 1/08 530001 Corros ion Prevention and Corrosion Program Inspections - Use the age of the airplane for the initial inspection. The ini tial 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 2 1 1
, 2 1 2
, 215, 2 16, 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 MAN UAL

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 2 2 6

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 Lim its. 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, Supplem ental 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 Fusela ge to Strut Attach Fitting Lugs (1/64 Inch Oversize Bolt Size) Part Number S3461-159 (NDI - Eddy Curre nt) - Inspect. Refer to Chapter 4, Severe Inspection Time Limits. Also, refer to 5-14-04, Supplemental Inspe ction 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 MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

532001 Center Section Drain Holes - Inspect for obstruction and remove any foreign mater ial 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, Suppleme ntal 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 5 3-20-11. 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 3/0 3 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 R ail Attachments at FS 143.00 and FS 158.00 - Inspect. Refer to 5-14-14, Supplemental Inspection Numb er 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 MAN UAL

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 condit ion 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, Su pplemental Inspection Number 55-10-01. AD 31 340, 341, 373, 374, 375, 376

Adde d Nov 3/03 5510 04 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 Hor izontal 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 MAN UAL

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 Nu mber 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, Suppleme ntal 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 Spa r 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 condit ion 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, 57 1, 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 MAN UAL

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 Insp ection 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, refe r 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 Attachm ent 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 MAN UAL

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 Fla p 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

Revise d 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

6110 05 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 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 1 2 1

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 MAN UAL

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 G overnor - Inspect electrical connection wiring for evidence of damage and security of installat ion. 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 S hock Mounts and Ground Straps - Inspect for condition, security of installation, and deterioration of elastom ers. C 1 121, 122

Added Nov 3/03 712003 Engine Truss and Ring Assembly - Inspe ct. 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 beari ngs 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 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 1 2 1
, 1 2 2

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 - Ins pect for security of installation, line routing, deterioration of hoses and evidence of damage. C 1 1 3 0

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 Com partment - 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 P ropeller 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 securi ty of installation, general condition and leakage. B 1, 3 121, 122

Revise d 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, chafin g, 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 Pneu matic Lines - Inspect P3/Py line heaters for operation and evidence of damage. C 1 1 2 2



## 5-10-01 Page 39 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

731004 Engine Fuel Pump - Inspect for security of installation and fuel leaks. Inspect overboard dra in 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 installati on 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 p ump inlet filter. P 17 122

Revised Mar 1/01 731009 Fuel Pump Outlet Filter - Replace fuel pump outlet filter. P 17 122

731010 Flow Divide r - 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 Ignite rs - 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 - Insp ect 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, 1 22



## 5-10-01 Page 40 © Cessna Aircraft Company Jul 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 spe ed 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 corrosio n, 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 G enerator - Inspect for security of installation and general condition. Inspect weep holes for oil leakag e. C 1 1 2 1
, 1 2 2

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 condi tion. Inspect weep holes for oil leakage. C 1 1 2 1
, 1 2 2

Revis ed Mar 1/01 771004 Ng Tach Generator Wiring - Inspect for chafing, routing and security of installation. C 1 121, 1 22

771005 T5 Terminal Block and External Wiring - Inspect for security of installation and condition. C 1 1 2 2

771006 Trim Thermocouple - Inspect for security of installation and condition. C 1 1 2 2

7730 01 Electric Torque Transmitter (if installed) - Inspect for security of installation, condition, and leakage. C 1 122



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## MODEL 208 MAINTENANCE MAN UAL

REVISION STATUS ITEM CODE NUMBER TASK INTERVAL OPERATION ZONE

Revised Mar 1/01 773002 Torque Indication System - Inspect plumbing for evidence of damage, leakage, cond ition 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. Refe r 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



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## MODEL 208 MAINTENANCE MAN UAL

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 1 2 2

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 installati on. C 4 2 2 1

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-G enerator Brush Holders - Inspect for proper spring tension (30-39 ounces) and freedom. Refer to Lear Si egler/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 Starte r-Generator Electrical Cables and Connectors - Inspect cables for routing, support, security of
connections and connector hardware. B 1, 3 122

Added Mar 1/0 8 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



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## MODEL 208 MAINTENANCE MAN UAL

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 reg ular 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 origina l 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 l andings) 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 an d 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) F l a p B e l l C ra n k ( P a rt N u m b e r 2 62 2 0 83

- 1 8)

- R e p l a ce at eve ry 2 2 5 0 l a n d i n g s

. (2) F l a p B e l l C ra n k ( P a rt N u m b e r D DA0 0 02 8

-4 )

- R e p l ace at eve ry 2 2 5 0 l a n d i n g s

. (3) F l a p B e l l C ra n k ( P a rt N u m b e rs 2 62 2 2 8 1

- 2
, - 1 2 )

- R e p l a ce at eve ry 70 0 0 l a n d i n g s

. (4) F l a p B e l l C ra n k ( P a rt N u m b e r 2 6 9 2 0 0 1

- 2 )

- R e p l a ce at eve ry 70 0 0 l a n d i n g s

. NOTE: T ota l l a n d i n g s i n c l u d e s t h e acc u m u l ate d l a n d i n g s of 2 6 2 2 2 8 1

- 2 p ri o r to m od i fi cat i o n by S K2 0 8

- 1 2 3 to t h e 2 6 92 0 0 1

-2 co n fi g u rat i o n

. (5) F l a p B e l l C ra n k ( P a rt N u m b e rs 2 6 2 2 3 1 1

- 7
, - 1 6 )

- R e p l a ce at eve ry 4 0
, 0 0 0 l a n d i n g s

. (6) F l a p B e l l C ra n k ( P a rt N u m b e r 2 62 2 3 1 1

- 7) atta ch i n g p a rts : B e a ri n g s ( P a rt N u m b e r M S2 764 1

- 5
o r S 3 95 2

- 5 ) a n d B o l t ( P a rt N u m b e r A N 5

- 7 7)

- R e p l ace at eve ry 1 0
, 0 0 0 l a n d i n g s

. (7) F l a p B e l l C ra n k ( P a rt N u m b e r 2 62 2 3 1 1

- 1 6) atta ch i n g p a rts : B e a r i n g s ( P a rt N u m b e r K P 5A

- H )
a n d Bo l t ( P a rt N u m b e r A N 5

- 77)

- R e p l ace at eve ry 1 0
, 0 0 0 l a n d i n g s

. (8) E l evato r Fo rwa rd P u s h rod P a rt N u m b e rs 2 6 1 3440

- 1
, 2 6 1 34 1 4

- 1
, a n d 2 6 6 0 034

- 1

- R e p l ace at 95 0 0 l a n d i n g s

. (9) E l evato r Fo rwa rd P u s h rod P a rt N u m b e rs 2 6 1 3440

-3
, 2 6 1 344 0

- 5
, D DA05 9 46

- 1

- R e p l ace at 40
, 0 0 0 l a n d i n g s

. (10) E l evato r Aft P u s h rod P a rt N u m b e rs 2 634 0 0 9

- 1
, 2 63402 7

- 1
, a n d 2 634 02 7

-3

- R e p l ace at 40
, 0 0 0 l a n d i n g s

. 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: Attac h i n g h a rdwa re ( bo l ts , b e a ri n g s , b u s h i n g s , a n d t r u n n i o n p i n s re l ate d to t h e i n sta l l at i o n of t h e co m po n e n ts b e l ow) i s to b e re p l a ce d w h e n eve r t h e as so c i ate d
co m p o n e n t i s re p l ace d

. (a) M a i n La n d i n g G e a r C e n te r S p ri n g ( P a rt N u m b e rs 2 64 1 0 1 4

- 2
, -3
, - 4
, - 5
, - 6

- 7
, - 8
, - 9 )

- R e p l a ce at eve ry 3 1
, 5 0 0 l a n d i n g s

.



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## MODEL 208 MAINTENANCE MAN UAL

(b) M a i n La n d i n g G e a r Tr u n n i o n As se m b l y ( P a rt N u m b e rs 2 64 1 0 1 2

- 1
, -2
, - 8
, - 9
, - 1 3

- 1 4 )

- R e p l ace at eve ry 3 1
, 5 0 0 l a n d i n g s

. (c) M a i n La n d i n g G e a r S p ri n g ( P a rt N u m b e rs 2 64 1 0 1 3

- 1
, - 2
, - 3
, - 4
, -5
, - 6
, 7
, - 8)

- R e p l ace at
eve ry 3 1
, 5 0 0 l a n d i n g s

. (d) M a i n La n d i n g G e a r Attac h P i n ( P a rt N u m b e rs 2 6 4 1 0 0 8

- 1
, - 2
, -2 0 0)

- R e p l a ce at eve ry 3 1
, 5 0 0 l a n d i n g s

. (e) M a i n La n d i n g G e a r Axl es ( P a rt N u m b e rs 2 64 1 0 1 1

- 1
, - 3
, - 4)

- R e p l ace at eve ry 1 0
, 0 0 0 l a n d i n g s

. (f) M a i n La n d i n g G e a r Ax l e s ( P a rt N u m b e rs 2 64 1 0 1 1

-5 )

- R e p l ace at eve ry 3 1
, 5 0 0 l a n d i n g s

. (g) M a i n La n d i n g G e a r Axl e F i tt i n g s ( P a rt N u m b e rs 2 6 4 1 0 1 0

- 1
, - 3
, - 7 )

- R e p l a ce at eve ry 3 1
, 5 0 0 l a n d i n g s

. (2) N os e La n d i n g G e a r

NOTE: Attac h i n g h a rd wa re ( bo l ts , b e a ri n g s , b u s h i n g s , a n d axl e co m p o n e n ts re l ate d to t h e i n sta l l at i o n of t h e co m po n e n ts b e l ow) i s to b e re p l ace d w h e n eve r t h e ass o c i ate d
co m po n e n t i s re p l ace d

. (a) N os e G e a r D rag L i n k S p ri n g ( P a rt N u m b e rs 2 6 430 62

- 1
, - 2
, - 3)

- R e p l a ce at eve ry 1 5
, 0 0 0 l a n d i n g s

. NOTE: Fo r n os e g e a r d rag l i n k s p r i n g s re p a i re d p e r CA B 9 6

- 24 o r p e r C h a pte r 32
, N o se La n d i n g G e a r
- C l e a n i n g/ P a i n t i n g w i t h d a m ag e re p a i re d b etwe e n 0

. 0 5 0 i n ch
a n d 0

. 0 62 i n c h ( 1

. 2 7 0 m m a n d 1

. 5 75 m m )
, t h e l i fe l i m i t i s a n ad d i t i o n a l 1 2
, 0 0 0 l a n d i n g s afte r re p a i r, n ot to exce e d 1 5
, 0 0 0 l a n d i n g s

. NOTE: Fo r n os e g e a r d rag l i n k s p r i n g s re p a i re d p e r CA B 9 6

- 24 o r p e r C h a pte r 32
, N o se La n d i n g G e a r
- C l e a n i n g/ P a i n t i n g w i t h d a m ag e re p a i re d b etwe e n 0

. 0 63 i n ch
a n d 0

. 0 75 i n c h ( 1

. 6 0 0 m m a n d 1

. 9 05 m m )
, t h e l i fe l i m i t i s a n ad d i t i o n a l 1 0
, 0 0 0 l a n d i n g s afte r re p a i r, n ot to exce e d 1 5
, 0 0 0 l a n d i n g s

. (b) N os e G e a r Ass e m b l y ( P a rt N u m b e rs 2 643 045
, 2 6 43 1 0 0 a n d 2 6 430 95 S e ri es P a rt N u m b e rs )

- R e p l a ce at eve ry 40
, 0 0 0 l a n d i n g s

. NOTE: Fo r a n i l l u st rat i o n of t h e n os e g e a r as se m b l y to b e re p l ace d
, refe r to C h a pte r 32
, se ct i o n 32

- 2 0

- 0 0
, N o se La n d i n g G e a r
- M a i n te n a n ce P ract i ces

. (c) S u p po rt As s e m b l y, N o se G e a r S p r i n g ( P a rt N u m b e rs 2 6 430 30
, 2 64 305 5 a n d 2 643 0 9 9 S e ri es P a rt N u m b e rs )

- R e p l a ce at eve ry 4 0
, 0 0 0 l a n d i n g s

. NOTE: Fo r a n i l l u st rat i o n of t h e n os e g e a r s p ri n g s u p p o rt as se m b l y to b e re p l ace d
, refe r to C h a pte r 32
, s e ct i o n 32

- 2 0

- 0 0
, N o se La n d i n g G e a r
- M a i n te n a n ce P ra ct i ces

. (d) Fo r k Ass e m b l y, N o se G e a r S p r i n g ( P a rt N u m b e rs 2 64 303 1

- 1
, - 7)

- R e p l a ce at eve ry 40
, 0 0 0 l a n d i n g s

. NOTE: Fo r a n i l l u st rat i o n of t h e n o se g e a r s p ri n g fo rk as s e m b l y to b e re p l ace d
, refe r to C h a pte r 32
, se ct i o n 32

-2 0

- 0 0
, N o se La n d i n g G e a r
- M a i n te n a n ce P ra ct i ces

. E. Navigatio n (Chapter 34) (1) Pitot and static hoses - Replace after 10 years in service. F. Oxygen (Chapter 35) (1) T h e a i rp l a n e m ay b e e q u i p p e d w i t h a two
- po rt oxyg e n syste m i n co rpo rat i n g a 5 0

. 6 7 c u b i c
-foot

ca p ac i ty oxyg e n cy l i n d e r ( P a rt N u m b e rs C 1 6 6 0 0 1

- 1 1 0 1 a n d C 1 6 6 0 0 1

- 1 2 0 1 ) o r a te n p o rt oxyg e n syste m i n co rpo rat i n g a 1 1 6

. 9 5 c u b i c
-foot

- ca p ac i ty oxyg e n cy l i n d e r ( P a rt N u m b e rs C 1 6 6 0 0 1

- 1 1 0 2 a n d C 1 6 6 0 0 1

- 1 1 03 )

. B ot h cyl i n d e rs h ave a l i fe l i m i t of 1 5 ye a rs

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



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## MODEL 208 MAINTENANCE MAN UAL

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 McCa uley (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 (Ch apter 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 margin al 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 retu rn 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 wit h 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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## MODEL 208 MAINTENANCE MAN UAL

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 regula r 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 in dividually 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 bellcra nk 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 bellcra nk Part Number 2622281-12 -- Replace at 5000 landings. (5) Flap bellcrank Part Number 2692001-2 -- Replace at 5000 landings.

NOTE: Total landin gs 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 g ear 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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## MODEL 208 MAINTENANCE MAN UAL

PROGRESSIVE CARE PROGRAM
1. Progressive Ca re 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 informati on 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 ho ur 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 - C overs 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 - C overs 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 - E very 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 - E very 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 th e 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 th e 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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## MODEL 208 MAINTENANCE MAN UAL

Operation 38 - Every 1200 hours. Operation 39 - At each starter generator removal. Operation 40 - E very 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 10,0 00 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 ins pection 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 in terval. 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 n ext 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 Ite ms 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 co mponents 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 specification s 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 th e 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; rubb er 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: Inspe ct 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 p arts 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 li sted 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 Rad io 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 avai lable upon request: 1 Airplane, Engine, and Propeller Logbooks.



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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 in stallation 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, conditi on 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 Pro peller - 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, conditio n 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 Engin e Propeller Shaft Seal - Inspect for leaks and security of installation. 110

30110 1 100 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, 2 20, 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 termina l 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 a nd 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 P ower 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 fo r 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 openi ng 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 cleanline ss, 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 fo r 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, distort ion, and corrosion. 121, 122

720007 Engine Accessories - Inspect for security of installation, general condition and leakage. 121, 122

731001 Fuel Li nes - 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 evide nce of fuel leaks. 121, 122

741002 Ignition Cables - Inspect for chafing, wear, routing, and security of installation. 121, 122

741003 Igni ters - 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 l eakage. 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 - S ervicing. 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 C omponents - 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 burn ing. 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 cond ition and security of installation. Disconnect plug from battery and check annunciators. Verify BATTERY HOT and BATTERY OVERHEAT
annu nciator 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 elect rolyte. 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 2 08B0317 and On, and Airplanes 20800001 thru 20800221 and 208B0001 thru 208B0316 Incorporating SK208-112) (without TKS) - Do a disc harge 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 sec urity 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

7320 02 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 Exc iter 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 Lin kages 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 Fille r 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 instal lation, condition and leakage. 122

793006 Oil Temperature Bulb Wiring - Inspect for security of installation, condition and evidence of damage. 122

801004 Starte r-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

7170 02 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 A nti-ice Varistor (without TKS) - Examine the firewall-mounted varistor for condition and correct installation. Examine the electrical connectio ns 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 Firewal l 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 sec urity 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 leve r, 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



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ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

231001 Control Wheel Pushbutton Switches - Clean the transponder identification switch, microphone switch, and th e 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 condi tion and clean. Inspect hose connection for security of installation and hose for condition. Perform operational check of pilot's mask micropho ne. 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 ma p 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 - Main tenance 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 blo ckage. 311, 312



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ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

256001 Emergency Locator Installation - Inspect for security of installation, position of function switch and condition of e lectrical 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, rud der hinges for condition, cracks, and security of installation; hinge bolts, hinge bearings, hinge attach fitting, and bonding jumper for evidence of damage o r wear, failed fasteners, and security of installation. Inspect rudder hinge bolts for proper safetying of nuts with cotter pins. Inspect balance weight fo r 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 r ivets; elevator hinges for condition, cracks, and security; and hinge bolts, hinge bearings, torque tube, horn, attach fittings, and bonding jumpers for eviden ce of damage or wear, failed fasteners, and security. Inspect elevator hinge bolts for proper safetying of nuts with cotter pins. Inspect balance weigh ts 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
57000 1 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 - Insp ect 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



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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 da mage. 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 Va lves - 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. Insp ect balance weights for looseness and their supporting structure for damage. 571, 671

2710 16 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



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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. R efer to Chapter 12, Lubricants - Description and Operation. Reinstall bolt and torque and safety wire. Refer to Chapter 32, Nose Landing Gear - Main tenance 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 - Servici ng. 701

325001 Nose Landing Gear Shimmy Damper - Inspect for condition and security of installation. 701

325002 Nose Lan ding 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 Landin g Gear Wheel Bearings (Airplanes 20800001 thru 20800201 and 208B0001 thru 208B0255 Not Incorporating CAB 91-30) - Inspect for condition and re pack. Refer to Chapter 12, Lubricants - Description and Operation. 701, 721, 722

32400 1 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

1120 01 Inte rior 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

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## MODEL 208 MAINTENANCE MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

530001 Corrosion Prevention and Corrosion Program Inspections - Use the age of the airplane for the initial inspe ction. 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 f unctional 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 ope rational check. ENG



## 5-12-01 Page 13 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 c heck. ENG

243006 NI-CAD Battery (if installed) - Perform capacity check. Check terminals for overheating or burning. LAB

*** End of Op eration 1 Inspection Items ***



## 5-12-01 Page 14 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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, depress ions, 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 MAN UAL

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 i nstallation. 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 Sp inner 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 componen ts 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 Propel ler 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

7160 02 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 MAN UAL

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 Inspect ion - 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 fo r 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 genera l 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, obstr uctions 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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

301007 Bleed Air Pressure Regulator (Airplanes 20800001 thru 20800221 and 208B0001 thru 208B0316 Not Incorporatin g 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 installati on 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 Fil ler 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 insta llation, 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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

793004 Oil Pressure Indicator Plumbing (Engine to Firewall) - Inspect for security of installation, condition, leakage and ev idence 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 accu mulated 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 install ation. 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 instal lation. 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 Prima ry 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 i nterference. 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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

231001 Control Wheel Pushbutton Switches - Clean the transponder identification switch, microphone switch, and th e 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 condi tion and clean. Inspect hose connection for security of installation and hose for condition. Perform operational check of pilot's mask micropho ne. 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 ma p 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 leakag e 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, 2 56

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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

221004 Autopilot Actuator (Elevator) - Inspect bridal cables for fraying, chafing, cleanliness, turnbuckle safetying, an d proper routing. Inspect chain for proper safetying at all points and chains for proper alignment with actuators sprockets. Inspect pulleys, dri ve 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 a nd 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 - I nspect 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 safetyi ng 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 MAN UAL

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 da mage. 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 secu rity of installation. Inspect the aileron hinge bolts for proper safetying of nuts with cotter pins. Inspect balance weights for looseness and their support ing 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 G ear 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



## 5-12-02 Page 8 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

322005 Nose Gear Spring Yoke - Inspect bearing for corrosion and freedom of rotation. Lubricate bearing. Refe r to Chapter 12, Lubricants - Description and Operation. Reinstall bolt and torque and safety wire. Refer to Chapter 32, Nose Landing Gear - Mainte nance 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 Landi ng 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 conditio n 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 Lan ding 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 se curity 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 Land ing Gear Wheel Bearings (Airplanes 20800202 and On and 208B0256 and On, and Airplanes 20800001 thru 20800201 and 208B0001 thru 208B 0255 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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

321002 Main Gear Fairings - Inspect for condition and security of installation. Check for interference between fairi ng 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 i nspection. 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 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 Warni ng 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 Runnin g) - 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 MAN UAL

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 in stallation 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, conditi on 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 MAN UAL

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 Pro peller - 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, conditio n 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 Engin e Propeller Shaft Seal - Inspect for leaks and security of installation. 110

30110 1 100 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, 2 20, 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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

242001 Standby Alternator - Inspect for condition and security of installation, belt tension and condition. Check termina l 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 installati on. 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, termin al 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 eviden ce 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, 12 2

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 MAN UAL

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 prope r 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 O n 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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

301007 Bleed Air Pressure Regulator (Airplanes 20800001 thru 20800221 and 208B0001 thru 208B0316 Not Incorporatin g 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 Fil ler 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 (with out 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 conditi on. 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 an d evidence of damage. 151

720004 Engine Fire Seals - Inspect for security of installation and general condition. 151, 152

272008 Rudder Co ntrol System - Check connections for security of installation, and tightness of fasteners where applicable. Refer to Chapter 20, Torque Data - Mainten ance Practices. 211, 212, 320

334003 Exterior Lighting - Perform operational check. 215
341007 Static System Drain Valves - Visually inspect for leaks, a nd 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,
secur ity 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 MAN UAL

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 C opilot's Seats - Inspect seat brackets, guides, stops, seat structure and seat cushions for condition and security of installation; and controls for conditio n, 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 p ressure, 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 safety ing, and proper routing. Inspect chains for proper safetying at all points and chains for proper alignment on sprockets. Inspect pulleys and guard pins fo r 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

2550 07 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 MAN UAL

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 Tailco ne 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 Rudde r Cables (Empennage) - Inspect cables for deterioration. Inspect cables for fraying, chafing, cleanliness, turnbuckles safetying, and proper rout ing. Inspect pulleys and guard pins for condition, wear, corrosion, and security of installation. 311, 320

2210 03 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
con dition 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 MAN UAL

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 p ins. 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 Stati c 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 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 d amage 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 fo r 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 Wa rning 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 andevidence 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 se curity 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



## 5-12-03 Page 10 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 Str ut - 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, 63 1

271004 Aileron/Spoiler Bell Crank and Pushrods (Both Wings) - Inspect aileron bell crank and pushrods for co ndition, security of installation, corrosion, evidence of damage to quadrant arm, stop bolts, and support bracket. Inspect aileron bell crank bolt a nd stop bolts for proper safetying. Inspect pushrod attach bolts for security of installation and proper safetying. Refer to Chapter 20, Torque Data - Mai ntenance 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



## 5-12-03 Page 11 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 prop er 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 MAN UAL

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 installati on, 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 conditio n 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 dow n. 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 La nding Gear Wheels and Tires - Check for wear, pressure and condition. Rotate tires as necessary to achieve uniform tire wear. Refer to Chapte r 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 Insp ections - 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

2120 05 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 MAN UAL

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 fun ctional 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) - D o 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 Powe r 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 MAN UAL

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 MAN UAL

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, depress ions, 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



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## MODEL 208 MAINTENANCE MAN UAL

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 i nstallation. 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 Sp inner 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 componen ts 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 Propel ler 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

7160 02 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



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## MODEL 208 MAINTENANCE MAN UAL

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 Inspect ion - Inspection/Check. 121

790004 Oil Filter - Remove, clean and inspect for damage. Filter may be electrosonically cleaned if desired. 121

261001 Fire Detecti on Control Unit - Inspect for condition and security of installation. 121, 122

261002 Heat Detecti on 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 pro per 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
corro sion, 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 chec ks in accordance with servicing placard on the side of battery. 122



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ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

301007 Bleed Air Pressure Regulator (Airplanes 20800001 thru 20800221 and 208B0001 thru 208B0316 Not Incorporatin g 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 installati on 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 Tota lizer 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 conditi on, and freedom of movement. 122

790003 Oil Filler Cap and Dipstick - Inspect for condition and security of installation. 122

215002 Compre ssor 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 insta llation, 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



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ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

793004 Oil Pressure Indicator Plumbing (Engine to Firewall) - Inspect for security of installation, condition, leakage and ev idence 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 leaka ge. 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 fasten ers 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
corro sion, 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

2730 04 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



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## MODEL 208 MAINTENANCE MAN UAL

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 interferen ce. 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 Autopil ot 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, Slavi ng Accessory and Compensator Unit, Autopilot Control Wheel Switch Cap and Power Lever Go-Around Button (Model 208 & 208B) (if installed) - Che ck for security of installation and switches for proper operation. 220, 222, 223, 226

2120 04 Instrument Panel Ventilation Air Outlets and Controls - Inspect doors, cables and controls for condition and operation. 220, 224



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## MODEL 208 MAINTENANCE MAN UAL

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 Wa rning 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 operatio n. 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 sw itches and ensure that all digital segments illuminate properly. 223

27300 6 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, 2 24

271021 Aile ron Trim Tab Control and Indicator - Inspect control and indicator for condition and security of installation. Operate trim tab control and check ail eron trim tab for freedom of movement. Inspect guide block for condition and security of installation. 226



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## MODEL 208 MAINTENANCE MAN UAL

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 installatio n. 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 Fl ap 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 cond ition and security of installation; and controls for condition, security of installation and proper operation. Service seat adjusting screws, bearings and l ocking mechanisms. 231, 232



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## MODEL 208 MAINTENANCE MAN UAL

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 m issing 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 install ation and cleanliness. 231, 232, 251, 252, 255, 256
332002 Interio r 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 dete rioration. 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



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## MODEL 208 MAINTENANCE MAN UAL

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 deteriorat ion. 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 Sele ctor 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 C ontrol 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 compon ents 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



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## MODEL 208 MAINTENANCE MAN UAL

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 sto ps 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-D own 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 Cycl e 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 secu rity 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 alignm ent 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 Eme rgency Locator Installation - Inspect for security of installation, position of function switch and condition of electrical components. Inspect structure for corrosion. 312



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## MODEL 208 MAINTENANCE MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

272007 Rudder Gust Lock (Airplanes 20800030 thru 20800236 and 208B0001 thru 208B0381) (if installed) - I nspect 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, rud der 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 secu rity; 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, 37 6 273013 Elevator Trim Tab Actuator Pushrods - Inspect for con dition 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 andevidence 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



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## MODEL 208 MAINTENANCE MAN UAL

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 pos ition of filler cap. 521, 621

281004 Drain Valves - Check operation and inspect for leakage. 521, 621

275001 Flaps - Inspe ct 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, c leanliness, 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 instal lation 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
corro sion 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

3220 06 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



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## MODEL 208 MAINTENANCE MAN UAL

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 2 08B0256 and On, and Airplanes 20800001 thru 20800201 and 208B0001 thru 208B0255 Incorporating CAB 91-30) - Inspect for condi tion 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 D oors Latch Pin Guide - Inspect for damage, cracks and wear. 801, 802

52100 8 Crew Door Entrance Steps - Inspect for condition, security of installation and folding operation. Clean. 801, 8 02

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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 an d 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 installati on, 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 install ation, 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 Wind shield 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 MAN UAL

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/Ca rgo 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 f unctional 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 MAN UAL

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 MAN UAL

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, clea nliness, 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 MAN UAL

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 MAN UAL

ITEM CODE NUMBER TASK ZONE MECH INSP REMARKS

273022 Electric Trim Clutch Torque Check - Rotate sprocket housing slowly clockwise or counterclockwise and check torq ue. 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 Autopi lot (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 1 2, 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 te nsion. 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, 67 1

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 MAN UAL

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 Fligh t 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 MAN UAL

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 - Adju stment/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 Op eration 7 Inspection Items ***



## 5-12-07 Page 2 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 Ventilatin g 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 MAN UAL

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 Ta nks - Adjustment/Test. 222



## 5-12-09 Page 1 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 Insp ection - 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 MAN UAL

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 MAN UAL

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 MAN UAL

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 O peration 12 Inspection Items ***



## 5-12-12 Page 1 © Cessna Aircraft Company Dec 1/2006

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 MAN UAL

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 O peration 14 Inspection Items ***



## 5-12-14 Page 1 © Cessna Aircraft Company Sep 4/2001

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 MAN UAL

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 MAN UAL

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 MAN UAL

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 Tr im 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 - Disasse mble, 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 MAN UAL

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 - R eplace 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 MAN UAL

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 mai n landing gear spring and center spring. Refer to Chapter 32, Main Landing Gear - Cleaning/Painting. Remove main landing gear fairings. I nspect 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 MAN UAL

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 MAN UAL

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 MAN UAL

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 E ngine 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 56-30-0 1. 240, 251, 252, 255, 256, 801, 802



## 5-12-31 Page 1 © Cessna Aircraft Company Mar 1/2008

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

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 Typi cal 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 Typica l 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 MAN UAL

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 MAN UAL

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 Attachmen ts 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 MAN UAL

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-Thr u 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-Th ru 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 MAN UAL

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, Supplemen tal 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 MAN UAL

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 MAN UAL

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 MAN UAL

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 MAN UAL

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 MAN UAL

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 O peration 40 Inspection Items ***



## 5-12-40 Page 1 © Cessna Aircraft Company Apr 1/2010

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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 O peration MB Inspection Items ***



## 5-12-MB Page 1 © Cessna Aircraft Company Jun 1/2010

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## MODEL 208 MAINTENANCE MAN UAL

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 revi sion 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

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## MODEL 208 MAINTENANCE MAN UAL

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 Ch apter 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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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 Inspecti on 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 Inspect ion 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

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## MODEL 208 MAINTENANCE MAN UAL

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 Ti me 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, T ypical 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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

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

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## MODEL 208 MAINTENANCE MAN UAL

SUPPLEMENTAL INSPECTION DOCUMENT
1. Supplemental I nspection Document
A. Introduction (1) The Supplemental Structural Inspection Program for the Cessna Models 208 and 208B airplane is a result of t he 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 Supplem ental 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 accumu lated.
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 i n this document. (a) A list is included to show the requirements for the SID program for primary and secondary airframe components. 1 The airplan e 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, rep ort 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 inspectio n 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 frequent ly. 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 ho lder(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 compo nent 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.



## 5-13-00 Page 1 © Cessna Aircraft Company Apr 1/2010

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## MODEL 208 MAINTENANCE MAN UAL

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 reinfo rcement around cutouts or discontinuities Skin-stringer combinations Spar caps Spar webs Fuselage
Circumferen tial frames and adjacent skin
Door frames Pilot window posts
Bulkheads
Skin and sin gle 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 Sup port 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 Serv ice Bulletins and Service Information Letters issued to repair common service discrepancies were examined. b FAA Service Difficulty Records were examined. 2 The data col lected 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 Spect rum (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 tai l 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 exami nation 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 approximatel y 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. Classificatio n 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 Tolera nce 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 da mage. 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 an alysis, 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 frequen tly, 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 sm all (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 "d omino" 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 location s 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 empennag e. (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 len gth at instability/failure, c crit , 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 inspectio n 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 Propel ler 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 R eporting (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 show n 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, c crit , 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 organi zations 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 d o 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/landin gs 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 Bull etins 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 met hods 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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LISTING OF SUPPLEMENTAL INSPECTIONS
1. Supplemental I nspection 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 se ction 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 t he 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 Nondestructi ve 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 SUPPLEMENTALINSPECTION 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 50 0 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 SUPPLEMENTALINSPECTION 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 Attachme nts 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 53-50-0 1 Fuselag e to Horizontal Stabilizer Attach Fittings 20,000 Hours 5000 Hou rs 31 535001

5-14-18 Typical 20,000 Hours Typical 5000 Hours 31 535002 53-50-02 Vertical Stabilizer Attach Points

Severe 16,500 Hours Seve re 500 0 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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DETAILS FOUND IN SECTION 5-14-XX SUPPLEMENTALINSPECTION NUMBER INSPECTION COMPLIANCE TITLE INITIAL REPEAT INSPECTION OPERATION ITEM CODE

5-14-20 Typical 20,000 Hours Typical 5000 Hours 31 553004 55-10-02 Horizontal Stabilizer Spars

Severe 17,500 Hours Severe 1000 Hours 36 551005

5-14-21 53-20-06 Fuselage to W ing Carry-Thru Attach Fitting and Bulkhead 12,500 Hours 2500 Hours 34 532016

5-14-22 Typical 20,000 Hours Typical 5000 Hours 31 553001 55-30-01 Vertical Stabilizer Spars

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 5000 Hours MF 570013 5-14-24 57-20-01

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 MD 575002 5-14-27 57-50-01

Flap Track (Outboard) 15,000 Landings 3000 Landings MD 575003

5-14-28 Typical 10,000 Hours Typical 5000 Hours MA 570008 57-60-0 1 Wing Strut Fittings

Severe 5000 Hours Severe 36 00 H ours ME 570009



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DETAILS FOUND IN SECTION 5-14-XX SUPPLEMENTALINSPECTION 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 Nu mber 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 - Pa rt Number S3461-164) Severe 20,000 Hours Severe 3600 Hours ML 570017

5-14-30 71-20-01 Engine Truss a nd 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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SUPPLEMENTAL INSPECTION NUMBER: 32-10-01

1. Title Main Landing Gear Axle (2641011-1, -3 and -4)
2. Inspection Com pliance

INITIAL REPEAT
TYPICAL 5000 Landings 1000 Landings u p to 10,000 Landings

3. Main Landing Gear Axle Inspection A. Examine the Main Landing Gear Axle. (1) Examine the mai n 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.



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SUPPLEMENTAL INSPECTION NUMBER: 53-10-01

1. Title Fuselage Engine Mount Fittings
2. Inspection Com pliance

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.



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SUPPLEMENTAL INSPECTION NUMBER: 53-20-01

1. Title Cargo and Passenger Door Doublers
2. Inspection Com pliance

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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SUPPLEMENTAL INSPECTION NUMBER: 53-20-07

1. Title Fuselage to Strut Attach Fitting Lugs
2. Inspection Com pliance

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 St rut 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.



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SUPPLEMENTAL INSPECTION NUMBER: 53-20-03

1. Title Lower Forward Carry-Thru Bulkhead
2. Inspection Com pliance

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.



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SUPPLEMENTAL INSPECTION NUMBER: 53-20-04

1. Title Main Landing Gear Fitting
2. Inspection Com pliance

INITIAL REPEAT
TYPICAL 25,000 Landing s 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.



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SUPPLEMENTAL INSPECTION NUMBER: 53-20-05

1. Title Main Landing Gear Attach Fittings and Aft Carry-Thru Bulkhead
2. Inspection Com pliance

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.



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SUPPLEMENTAL INSPECTION NUMBER: 53-20-02

1. Title Fuselage to Wing Attach Fitting Lugs
2. Inspection Com pliance

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.



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SUPPLEMENTAL INSPECTION NUMBER: 53-20-11

1. Title Firewall Brace and Doubler Assemblies
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-08

1. Title Carry-Thru Root Rib
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-09

1. Title Crew Door Frames
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-10

1. Title Passenger and Cargo Door Frames
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-10-07

1. Title Seat Rails and Attachment Structure
2. Inspection Com pliance

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 MAN UAL

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 Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-13

1. Title Stringers at Intersections with Forward and Aft Carry-Thru Bulkheads
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-14

1. Title Fuselage Skin Doubler at Main Landing Gear Cutout
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-50-01

1. Title Fuselage to Horizontal Stabilizer Attach Fittings
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-50-02

1. Title Vertical Stabilizer Attach Points
2. Inspection Com pliance

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 Stabi lizer 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 insp ection 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 fo und, 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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 55-10-01

1. Title Horizontal Stabilizer Forward and Aft Attach Points
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 55-10-02

1. Title Horizontal Stabilizer Spars
2. Inspection Com pliance

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 ho rizontal 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 Sta bilizer Aft Spar Inspection A. Examine the Horizontal Stabilizer Aft Spar Cap. (1) Examine the horizontal stabilizer aft spar upper cap. (a) Do a visual insp ection 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 cra cks 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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 53-20-06

1. Title Fuselage to Wing Carry-Thru Attach Fitting and Bulkhead
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 55-30-01

1. Title Vertical Stabilizer Spars
2. Inspection Com pliance

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 H oles at WL 134.38 5000 Hours Vertical Stabilizer Forward Spar, Cap and Attach H oles 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 Mod el 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 N ondestructive 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 Chapte r 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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 56-30-01

1. Title Windshield and Attachment Structure
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 57-20-01

1. Title Wing to Carry-Thru Spar Attachment Fitting
2. Inspection Com pliance

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 MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 57-20-02

1. Title Front Spar Lower Cap Inboard of WS 141.20
2. Inspection Com pliance

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.



## 5-14-25 Page 1 © Cessna Aircraft Company Nov 3/2003

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 57-20-03

1. Title Rear Spar Lower Cap Inboard of WS 141.20
2. Inspection Com pliance

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.



## 5-14-26 Page 1 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 57-50-01

1. Title Flap Tracks
2. Inspection Com pliance

INITIAL REPEAT
TYPICAL 15,000 Landing s 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.



## 5-14-27 Page 1 © Cessna Aircraft Company Nov 3/2003

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 57-60-01

1. Title Wing Strut Fittings
2. Inspection Com pliance

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 curre nt 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 win g 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 curre nt 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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## MODEL 208 MAINTENANCE MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 57-60-02

1. Title Wing Strut Attachment to Front Spar
2. Inspection Com pliance

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 win g 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 win g 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 win g 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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## MODEL 208 MAINTENANCE MAN UAL

SUPPLEMENTAL INSPECTION NUMBER: 71-20-01

1. Title Engine Truss and Ring Assembly
2. Inspection Com pliance

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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SCHEDULED INSPECTION CHECKS
1. Description A. Air Conditioning (Chapter 21). (1) Cabin Heater and Windshield Defroster Operational Check. (a) Pull out the Gro und 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 Elect ric 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 app lied 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 Cont rol 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 clutc h 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 Controlle r, 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 cabl e tension setting is 20 pounds, +5 or -5 pounds.



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C. Electrical Power (Chapter 24). (1) Standby Alternator Excitation. (a) With engine run ning, 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 Sw itch 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 th e 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 i nstalled backwards..
(c) Set the switches and circuit breakers as shown in Table 1 Step 3. 1 Make sure that th e 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 i n 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 fri ction 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 co ndition 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 fri ction 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 tri m 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 act uator 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 ch ain 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 continu e 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 annunciato r goes off. 2 Make sure that the Fuel Flow gauge indicates no fuel flow. (2) Fuel Shutoff Control. (a) Check the fuel sh utoff 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, refe r 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 propell er 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 contro l 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 6 5%, 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 annunc iator light comes on. (3) 100 Hour Operational Check without G1000 (with TKS).



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### WARNING: For health and environmental data, review the applicable Material Safety Data Sheet (MSDS). WARNING: Before you dis connect 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 th e 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 accordancewith 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 cl ean, 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 th e engine cowlings. (b) Apply power to the airplane. (c) Push the annunciator test switch. 1 Make sure th e 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 PRIMA RY 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 BACKU P 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 PRIMA RY 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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4 Set the PRIMARY switch to the OFF position.
a Make sure that the ANTI-ICE ON annunciator goes off. (g) Make sure that t he 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 t he 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 trap ped 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 accordancewith specification DDT 406B, are normally 80% to 85% monoethylene glycol, 5% isopropyl alcohol, and 10% to 20% deionized wate r. Fluid density is approximately 9.2 lbs/gal.

CAUTION: Use only clea n, 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 p ropeller 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 pro peller 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 en gine 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 t he 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 th e 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 t he 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 th e 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 temperatu res (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 ic ing 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 dis connect 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 accordancewith 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 cle an, 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 th e 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 gall on 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 gallo ns 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 t he 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 am ount 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 fl uid 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. 1 0 Set the BACKUP switch to the ON position. 1 1 Operate the system for a timed period not more than 30 minutes. 1 2 Set the BACKUP switch to the OFF position. 1 3 Measure the amo unt of fluid necessary to fill the tank again to the minimum dispatch level or the amount of fluid collected in the bucket. 1 4 Calculate the fluid delivery rate.

NOTE: The permitted limit is 33.22 ounces/minute, -0.00 or +0.34 ounces/minute.

1 5 If no additiona l 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 s ealing 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 ca p 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. 1 6 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 t ube 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 ann unciator 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 additiona l 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 ca p 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 t he 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 w ill 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 t he 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 jump er 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 jump er 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. 1 0 Connect the ta il bracket electrical connection to the proportioning unit. 1 1 Install the tail cone access panel. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. 1 2 Disconnect th e tube from the filter assembly outlet.



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### CAUTION: Do not use the seals again after you loosen or disconnect a tube couplin g. 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.

1 3 Remove the ca p and install new seals in the couplings as shown in Figure 1. 1 4 Connect the nylon tube to the filter assembly outlet. 1 5 Empty the bucket in accordance with approved procedures. (h) Do a check of t he 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 i nto 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 couplin g. 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 ma ke 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. 1 0 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 dis connect 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 th e 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 accordancewith 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 cl ean, 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 th e 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 gall on 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 - Serv icing.

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 nylo n tube fittings as necessary and connect a tube to the filter assembly outlet so it will reach into an empty bucket.

NOTE: The fluid wil l 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 l imit 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 - Servi cing. 1 0 Set the BACKUP switch to the ON position. 1 1 Operate the system for a timed period not more than 30 minutes. 1 2 Set the BACKUP switch to the OFF position. 1 3 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. 1 4 Calculate the fl uid delivery rate.

NOTE: The permitted limit is 33.22 ounces/minute, -0.00 or +0.34 ounces/minute.

1 5 If no additional checks that include the filter assembly outlet are necessary, do the steps that follow:
a Disconnect th e tube from the filter assembly outlet.


### CAUTION: Do not use the s eals 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. Thi s 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. 1 6 Empty the buc ket 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 t ube 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 ca p 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 fol low:
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 t ube 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 se al 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 n ylon 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 a nd 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 ta il 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 jum per 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 proporti oning 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 jump er 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. 1 0 Connect the tail bracket electrical connection to the proportioning unit. 1 1 Install the tail cone access panel. Refer to Chapter 6, Access Plates and Panels Identificati on - Description and Operation. 1 2 Disconnect the tube from the filter assembly outlet.


### CAUTION: Do not use the seals again after you loosen or disconnect a tube coupli ng. 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 m ake 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.

1 3 Remove the cap and install new seals in the couplings as shown in Figure 1. 1 4 Connect the nylon tube to the filter assembly outlet. 1 5 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 tu be fittings as necessary and connect a tube to the filter assembly outlet so it will reach into a bucket.

NOTE: The fluid will fl ow into the bucket during the system operation.

4 Set the momentary MAX FLOW switch to WINDSHIELD position. 5 Collect the flui d 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 an d/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 couplin g 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. 1 0 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 airpl ane, 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 ind icator 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 re ading 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 Pan el 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 (Cha pter 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 co ntrol 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 blad e individually. (c) If blades are tight, remove the propeller assembly and return to the nearest Hartzell Propeller Overhaul Facility. N. McCauley Prope ller (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 R PM. (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 Reve rse 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 pro peller 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 en gine 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 2080 0351 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 frangibl e/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 req uired 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 Emerge ncy 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 th e 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 jumpe r and then check for continuity. Q. Starting (Chapter 80). (1) Starter-Generator Brush Holders (a) Inspect for pro per 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 co ntinued 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 wi ll 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 man ual 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 inspectio n task that the operator determines to be an urgent airworthiness concern.



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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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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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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 (Chan ges 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 airpl ane 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 t he Implementation Threshold (IT).

NOTE: The corrosion inspections apply to airplanes with a calendar year age that is equal to or greater tha n 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 Baselin e Program must be started before the airplane gets to the point of IT + RI for any corrosion inspection.

NOTE: For airplan es 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. Co rrosion 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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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 Corrosio n Inspection Number consists of an ATA code, airplane zone, and the item number.
EXAMPLE: C32.701.01E
C T h e fi rst l etter 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 INT ERVAL (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 re move 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. Corrosi on 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 cha nges. (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 Technical Supp ort 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 Cess na Aircraft Company. All corrosion reports received by Cessna Aircraft Company will be reviewed to determine if the Baseline Program is adequate.

10. Corrosion Re lated 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 MAN UAL

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 ACCESS MAINTENANCE 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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## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



## 5-30-01 Page 2 © Cessna Aircraft Company Apr 1/2010

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

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 w ith supporting data to the regulatory authority.
Table 1. Corrosion Prevention and Control Program

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 © Cessna Aircraft Company Mar 1/2008

### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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 MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



## 5-30-02 Page 31 © Cessna Aircraft Company Mar 1/2008

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## MODEL 208 MAINTENANCE MAN UAL

Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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Table 1. Corrosion Prevention and Control Program (continued)

CORROSION INSPECTION

NUMBER INTERVAL (YEARS) ZONE ACCESS MAINTENANCE 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



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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 ne cessary 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. T he 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 - G uidelines 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 de sign 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 norm ally 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.



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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 a pproval 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 assign ed. 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 airwort hiness concern.

NOTE: If Level 3 corrosion is determined at the implementation threshold or any repe at 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 accord ance 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.



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WORD GENERAL DESCRIPTION Principal Stru ctural Element (PSE) A PSE is an eleme nt 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 man ual 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 disassemb ly 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 bloc kages 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 Mode l 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 Mode l 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 (C hanges the Flammability Properties)
Pitot Tubes Fuel Cap Tie Down Lugs
Chrome Item s (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 a nd 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 co rrosion 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. Als o, 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 Structura l 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 i s 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 probabi lity 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 corros ion 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 maintena nce 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 corro sion 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 deta ils 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 CPC P inspection. (4) It is recommended that you record the results of the inspection to show compliance with the program. D. If Level 3 corro sion 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 Report ing 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 recommend ed 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 corrosio n 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 da mage 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 corrosi on 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 o n 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 b eyond the allowable limits, and there is an airworthiness concern in which prompt action is required.

NOTE: The airworthi ness 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 correspondi ng 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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## MODEL 208 MAINTENANCE MAN UAL

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 Stri ke. 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 inspection s 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 accomplishe d before airplane is returned to service.
2. Unscheduled Maintenance Checks Defined and Areas to be Inspected A. Hard/Overweig ht 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 w hich 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 overwe ight landing check. (a) Landing gear. 1 Main gear struts - Inspect for security of attachment and permanent set. 2 Main gear attac hments 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 trun nion 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, an d 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 airp lane 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 equip ped 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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### CESSNA AIRCRAFT COMPANY 

## MODEL 208 MAINTENANCE MAN UAL

(b) Cowling. 1 Skins - Inspect for buckling, cracks, loose or failed fasteners, and indications of structural dam age. (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 turb ulence 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 Airp lane Flight Manual limits. (2) Severe turbulence and/or maneuvers checks. (a) Stabilizers. 1 Horizontal sta bilizer 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 fast eners, and evidence of structural damage. (b) Wing. 1 Wing to body strut fittings and supporting structure - Inspect for security, loose or failed fasten ers, and evidence of structural damage. 2 Trailing Edge - Inspect for any deformation affecting normal operation of flap and aileron. D. Lightning stri ke. (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 discharg e 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 stru cture 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 st rike 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, perfo rm functional check of affected system. (c) Navigation. 1 Radar reflector, feed horn, motor box assembly and mounting structure. Inspect for damage. If da mage 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 com pass is not within tolerance, remove, repair or replace. (d) Fuselage. 1 Skin - Inspect surface of fuselage skin for evidence of damage. 2 Tailcone - In spect tailcone and static dischargers for damage.


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## MODEL 208 MAINTENANCE MAN UAL

(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 d amage. (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 cause d 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 precauti ons 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 condition s, 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 sectio n - Inspect for dents, cracks, scratches, punctures, blood and feathers. 2 Propeller - Inspect for nicked, bent, broken, cracked, or rubbing blades.



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## MODEL 208 MAINTENANCE MAN UAL

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, secu rity, buckling, and evidence of structural damage. (b) Wings. 1 Wing to fuselage attach fittings and attaching structure - Inspect for security, loose or failed fasten ers, and evidence of structural failure.



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# 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 tas ks. • 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 © 2014NOTE: 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 reli eve 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 h our 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 conve nience, 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