Revision Transmittal

July 20, 2010

TO: Cessna Distributors and Single Engine Service Stations.

SUBJECT: Single Engine Service Bulletin SB09-27-01 Revision 3: Rudder Hinge and Bracket Inspection.

REASON FOR REVISION

To revise the Effectivity section to add Model 350 airplane serial numbers 42010, 42559, 421014, 421018,

421020, and Model 400 airplane serial numbers 41570, 411088, 411111, 411139, 411141, 411143 thru

411146, 411148 thru 411153.

To provide notification that full compliance with SB09-27-01R2 (applicable serial numbers) or SB09-27-01R3 is

an FAA-approved Alternative Method of Compliance for Airworthiness Directive AD2009-09-09.

To provide two additional rudder stop bushings.

To provide Modification Kit MK400-27-01 Revision A.

To revise the Credit Information section.

Miscellaneous changes as necessary.

REQUIRED ACTION

Compliance with SB09-27-01 Revision 3 is required for airplanes in compliance with the Original Issue or

SB09-27-01 Revision 1. Refer to the Compliance Section for detailed requirements.

Compliance with SB09-27-01 Revision 3 is also required for the airplane serial numbers that were added in

this revision.

Compliance with SB09-27-01 Revision 3 is not required for airplanes in compliance with SB09-27-01 Revision 2.

LOG OF EFFECTIVE PAGES

Page No. Date Page No. Date

1 July 20, 2010 10 July 20, 2010

2 July 20, 2010 11 July 20, 2010

3 July 20, 2010 12 July 20, 2010

4 July 20, 2010 13 July 20, 2010

5 July 20, 2010 14 July 20, 2010

6 July 20, 2010 15 July 20, 2010

7 July 20, 2010 16 July 20, 2010

8 July 20, 2010 17 July 20, 2010

9 July 20, 2010

*******

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 © 2010

Single Engine

Service Bulletin

July 20, 2010 SB09-27-01

Revision 3

TITLE

RUDDER HINGE AND BRACKET INSPECTION

EFFECTIVITY

Model Serial Numbers

300 (LC40–550FG) 40001, 40002, 40004 thru 40079

350 (LC42–550FG) 42001 thru 42569, 421001 thru 421020

400 (LC41–550FG) 41001 thru 41800, 411001 thru 411153

REASON

Two reports have been received of a crack in the lower rudder hinge.

DESCRIPTION

A visual inspection of the lower rudder hinge or bracket and the upper and middle rudder brackets shall be

accomplished for cracking, deformation, or localized discoloration. If any of these conditions are found, the

affected hinge/bracket shall be replaced as stated in this Service Bulletin.

SB09-27-01 Revision 1 provided a new design hinge and brackets for installation when replacements were

required for the previous design parts. The new hinge and brackets are made of different material, incorporate

a machined shoulder for enhanced bearing retention, and include the application of corrosion protection primer

and a top coat of white paint.

SB09-27-01 Revision 2 included a modification kit for replacement of the brackets/hinges, instructions for

rudder travel verification, an allowance for utilizing different length hardware to ensure adequate thread

engagement, and instructions to verify proper hardware thread engagement of previously installed brackets and

hinges. Additionally, Revision 2 is FAA-approved as an Alternative Method of Compliance for AD2009-09-09.

SB09-27-01 Revision 3 adds airplane serial numbers that had the new-design hinge and brackets installed

at the factory. These added airplane serial numbers are required to be inspected to verify rudder travel and

for correct hardware thread engagement. Modification Kit MK400-27-01 has been revised to include two

larger rudder travel stop bushings. Additionally, SB09-27-01 Revision 3 is FAA approved as an Alternative

Method of Compliance for AD2009-09-09.

Non-compliance with this Service Bulletin could allow any of the above described conditions to exist and if

not corrected, may result in failure of more than one hinge or bracket which could potentially result in the

loss of rudder control.

Original Issue: April 13, 2009

Revision 1: August 31, 2009

Revision 2: November 23, 2009 Page 1 of 17

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 © 2009
COMPLIANCE

A. For airplanes that have not accomplished the initial inspection:

Compliance is mandatory: Accomplish the initial inspection as soon as practical, not to exceed 10 flight

hours or 30 days, whichever occurs first.

NOTE: If the airplane must be flown before the initial inspection is accomplished, the pilot in command must

do a check of the rudder hardware for good condition and security, as directed by Area 7 of the

Preflight Inspection Checklist in Section 4 of the Pilot’s Operating Handbook and FAA Approved

Airplane Flight Manual.

If the airplane will be flown after the initial inspection, but before the installation of the new-design rudder

hinge/brackets, the rudder hinge and brackets visual inspections must be performed by maintenance personnel

using the following schedule:

Inspection Interval Required Action

Initial inspection within 10 flight hours or 30 days,

whichever occurs first

Visual 10x magnification inspection with the rudder

removed

Recurring inspection every 25 flight hours or 90 days,

whichever occurs first

Visual inspection with the rudder remaining in place

Recurring inspection every 50 flight hours or 180

days, whichever occurs first

Visual 10x magnification inspection with the rudder

removed

NOTE: Compliance with Service Bulletin SB09-27-01 Revision 2 or Revision 3 equates to full compliance, and

the recurring inspections of this Service Bulletin will no longer be required.

B. For airplanes that are in compliance with SB09-27-01 Original Issue or SB09-27-01 Revision 1:

Compliance is mandatory: SB09-27-01 Revision 3 shall be accomplished as soon as practical within the next

50 flight hours or 6 months, whichever occurs first.

C. For airplanes that are not in compliance with SB09-27-01 Revision 2

and

Model 350 Airplane serial numbers 42010, 42559, 421014, 421018, and 421020

Model 400 Airplane serial numbers 41570, 411088, 411111, 411139, 411141, 411143 thru 411146, 411148

thru 411153:

Compliance is mandatory: SB09-27-01 Revision 3 shall be accomplished within 50 flight hours or 6 months,

whichever occurs first.

These airplanes already have the new design rudder hinge and/or brackets installed. (Modification Kit

MK400-27-01A installation is not required.) Specifically the following action shall be accomplished:

• Do an inspection of the hinge/brackets attachment hardware for correct thread engagement and

accomplish the rudder travel check in accordance with Step 2 of the Accomplishment Instructions in this

Service Bulletin.

D. For airplanes in compliance with SB09-27-01 Revision 2:

Compliance with SB09-27-01 Revision 3 is not required.

SB09-27-01 Revision 3

Page 2 July 20, 2010
APPROVAL

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

This Service Bulletin is approved by the FAA Wichita Aircraft Certification Office, by letter L115W-10-632

(a copy is attached), as an Alternative Method of Compliance with FAA Airworthiness Directive number

AD2009-09-09. Compliance with Revision 2 or Revision 3 of this Service Bulletin (as applicable) by installation

of the new hinge/brackets, and subsequent verification of correct rudder travel and hardware installation, is

considered as terminating action for AD2009-09-09.

MANPOWER

Initial and recurring 50 flight hours/180 days inspections: 1.2 man-hours

Recurring 25 hours/90 days inspections: 0.5 man-hour

1.0 man-hour to install MK400-27-01A (or latest revision), and add 0.5 man-hour if rudder travel is adjusted.

For airplanes in compliance with SB09-27-01 Revision 1 only (not Revision 2) and Model 350 airplane serial

numbers 42010, 42559, 421014, 421018, 421020, and Model 400 airplane serial numbers 41570, 411088,

411111, 411139, 411141, 411143 thru 411146, 411148 thru 411153 only:

• 0.2 man-hour to inspect previously installed hardware for proper thread engagement

• 0.6 man-hour if alternate hardware must be installed

• 0.8 man-hour to inspect the rudder rigging

• 0.5 man-hour if rudder travel is adjusted

REFERENCES

Model 300 Airplane Maintenance Manual

Model 350 Airplane Maintenance Manual

Model 400 Airplane Maintenance Manual

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

This information shall be considered an amendment to the Cessna Manufacturer's Service/Maintenance

Manual or Instructions for continued airworthiness and must be accomplished for ongoing airworthiness

compliance as necessary in accordance with 14 CFR Part 43.13.

OTHER PUBLICATIONS AFFECTED

Model 300 Illustrated Parts Catalog

Model 350 Illustrated Parts Catalog

Model 400 Illustrated Parts Catalog

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

SB09-27-01 Revision 3

July 20, 2010 Page 3
MATERIAL AVAILABILITY

The parts listed below are available from Cessna Parts Distribution through an appropriate Cessna Service

Station.

NOTE: Airplane Serial Number must be provided when ordering.

Part Number Description Qty/Airplane

MK400-27-01A1

(or latest revision)

Kit, Rudder Hinge and Bracket

(Model 300 and 350 Airplanes)

(See note below)

1

MK400-27-01-2

(or latest revision)

Kit, Rudder Hinge and Bracket

(Model 400 Airplanes)

(See note below)

1

NOTE: For all serial numbers except Model 350 airplane serial numbers 42010, 42559, 421014, 421018,

421020, and Model 400 airplane serial numbers 41570, 411088, 411111, 411139, 411141, 411143 thru

411146, 411148 thru 411153. These airplanes already had the applicable new design rudder hinge and/or

brackets installed at the factory prior to delivery of the airplane.

In addition, the following parts may be required. Refer to MK400-27-01A (or latest revision) for

detail information.

LC53553000-1-G

(Alternate 2833101-15)

Rudder Stop Bushing, 0.600 inch

diameter (Model 400 only)

(if/as required)

LC53553000-2-G

(Alternate 2833101-16)

Rudder Stop Bushing, 0.636 inch

diameter (Model 400 only)

(if/as required)

LC53553000-3-G

(Alternate 2833101-17)

Rudder Stop Bushing, 0.671 inch

diameter (Model 400 only)

(if/as required)

LC53553000-4-G

(Alternate 2833101-18)

Rudder Stop Bushing, 0.564 inch

diameter (Model 400 only)

(if/as required)

LC53553000-5-G

(Alternate 2833101-19)

Rudder Stop Bushing, 0.528 inch

diameter (Model 400 only)

(if/as required)

2833102-1 Rudder Stop Bushing, 0.707-inch

diameter (Model 400 only)

(if/as required)

2833102-2 Rudder Stop Bushing, 0.743-inch

diameter (Model 400 only)

(if/as required)

AN3-7A Bolt, Hex Head 10-32 x 7/8 inch (all

models)

(if/as required)

AN3-10A Bolt, Hex Head 10-32 x 1 inch

(all models)

(if/as required)

AN4C-15A Bolt, Hex Head 1/4-28 X 1-5/8 inch

(Model 400 only)

(if/as required)

MS24693C274 Screw, Flat Head 10-32 x 3/4 inch

(Model 400 only)

(if/as required)

MS24693C275 Screw, Flat Head 10-32 x 7/8 inch

(Model 400 only)

(if/as required)

NAS1351-3-14 Screw, Socket Head 10-32 x 7/8

inch (Model 300/350 only)

(if/as required)

NAS1351-3-16 Screw, Socket Head 10-32 x 1 inch

(Model 300/350 only)

(if/as required)

SB09-27-01 Revision 3

Page 4 July 20, 2010
NAS1149F0316P Washer (Model 300/350 only) (if/as required)

NAS1149F0463P Washer (Model 400 only) (if/as required)

K000912 Corrosion Resistant Primer

(1.5 Gal Kit)

(if/as required)

CREDIT INFORMATION

A. For airplanes in warranty except those listed in B. below:

Applicable parts credit and a labor allowance credit of 1.0 man-hour will be provided to install MK400-27-01A

(or latest revision). If necessary, applicable parts credit and a labor allowance credit of 0.5 man-hour will be

provided to adjust rudder travel.

For airplanes in compliance with SB09-27-01 Revision 1 and not in compliance with SB09-27-01 Revision

2 only:

• A labor allowance credit of 0.2 man-hour will be provided to inspect previously installed hinge/bracket

hardware for proper thread engagement. If necessary, applicable parts credit and a labor allowance credit

of 0.6 man-hour will be provided to install alternate hardware.

• A labor allowance credit of 0.8 man-hour will be provided to inspect the rudder rigging per MK400-27-01A

steps 6.B(1) through 6.B(3) and if necessary, applicable parts credit and a labor allowance credit of 0.5

man-hour will be provided to adjust rudder travel per MK400-27-01A steps 6.B(4) through 6.B(6) .

Freight will be credited at the most economical method unless pre-approved by Cessna. For pre-approval

contact Cessna Parts Distribution Warranty Administration at Telephone: 316-831-4296, Fax: 316-206-2746 or

E-mail: cpd2claims@cessna.textron.com.

To receive credit, the work must be completed and a Warranty Claim submitted by a Cessna Single Engine

Service Station within 30 calendar days of Service Bulletin compliance before the credit expiration dates

shown below.

NOTE: Removed hinges or brackets shall be held for field scrap per standard procedure.

Domestic . . . . . . . . . . . . . . . . . . . . . April 13, 2010

International . . . . . . . . . . . . . . . . . . . April 13, 2010

B. For Model 350 airplane serial numbers 42010, 42559, 421014, 421018, 421020, and Model 400 airplane

serial numbers 41570, 411088, 411111, 411139, 411141, 411143 thru 411146, 411148 thru 411153 only:

• A labor allowance credit of 0.2 man-hour will be provided to inspect previously installed hinge/bracket

hardware for proper thread engagement. If necessary, applicable parts credit and a labor allowance credit

of 0.6 man-hour will be provided to install alternate hardware.

• A labor allowance credit of 0.8 man-hour will be provided to inspect the rudder rigging per MK400-27-01A

steps 6.B(1) through 6.B(3) and if necessary, applicable parts credit and a labor allowance credit of 0.5

man-hour will be provided to adjust rudder travel per MK400-27-01A steps 6.B(4) through 6.B(6) .

Freight will be credited at the most economical method unless pre-approved by Cessna. For pre-approval

contact Cessna Parts Distribution Warranty Administration at Telephone: 316-831-4296, Fax: 316-206-2746 or

E-mail: cpd2claims@cessna.textron.com.

To receive credit, the work must be completed and a Warranty Claim submitted by a Cessna Single Engine

Service Station within 30 calendar days of Service Bulletin compliance before the credit expiration dates

shown below.

Domestic . . . . . . . . . . . . . . . . . . . January 20, 2011

International . . . . . . . . . . . . . . . . . January 20, 2011

Special Note to Service Stations:

When you complete the Warranty Claim, the labor allowance claimed shall be itemized for each above action

completed as listed above.

SB09-27-01 Revision 3

July 20, 2010 Page 5
ACCOMPLISHMENT INSTRUCTIONS

Special Equipment: A 10x Magnifying glass will be required for the initial and recurring 50 flight hours/

180 days inspections.

WEIGHT AND BALANCE INFORMATION

MODEL . . . . . . . . . . . 300, 350, 400

WEIGHT CHANGE .... Negligible

Instructions

1. Model 300 airplane serial numbers 40001, 40002, 40004 thru 40079; Model 350 airplane serial numbers

42001 thru 42009, 42011 thru 42558, 42560 thru 42569, 421001 thru 421013, 421015 thru 421017,

421019; and Model 400 airplane serial numbers 41001 thru 41569, 41571 thru 41800, 411001 thru

411087, 411089 thru 411110, 411112 thru 411138, 411140, 411142, 411147, do as follows:

A. Review the airplane logbooks to determine if SB09-27-01 Revision 1 Rudder Hinge and Bracket

Inspection has been accomplished.

(1) If SB09-27-01R1 has been accomplished, the installed hinge/bracket hardware shall be

inspected for proper thread engagement in accordance with the notes in steps 3.D, 4.C, and

5.C of MK400-27-01A (or latest revision), and the rudder travel shall be checked in accordance

with steps 6.B(1) thru 6.B(6) in MK400-27-01A (or latest revision). No further action is required,

go to Step 1F.

(2) If SB09-27-01 Revision 1 has not been accomplished, go to Step 1B.

B. Remove the rudder (not required for 25 hour interval inspections) (Refer to the applicable airplane

model AMM, Chapter 27, Rudder – Removal and Installation).

NOTE: If installing Modification Kit MK400-27-01A Rudder Hinge and Bracket Installation (or latest

revision), go to Step 1D.

C. Note: It is recommended that the new hinges/brackets are replaced instead of accomplishing

the following inspection. However, the inspection method can be accomplished until the

replacement parts are available.

(Figures 1 thru 5.) Using a 10x magnifier (10x magnification not required for 25 hour interval

inspections), inspect the Lower Rudder Hinge (Model 400) or Lower Rudder Bracket (Models

300/350), and the middle and upper Rudder Brackets (all models) for evidence of cracking,

deformation, or localized discoloration along exposed surfaces as shown in Figures 4 and 5. Pay

particular attention to the inner circumference of the hinge or bracket next to the bearing. If any of

these conditions are found, go to Step 1D. If none of these conditions are found, go to Step 1E.

D. Install Modification Kit MK400-27-01A Rudder Hinge and Bracket Installation (or latest revision).

E. Make an entry in the airplane logbook that states compliance and method of compliance with this

Service Bulletin and, if applicable, the date and flight hours when the next inspection is due.

2. Model 350 airplane serial numbers 42010, 42559, 421014, 421018, 421020, and Model 400 airplane serial

numbers 41570, 411088, 411111, 411139, 411141, 411143 thru 411146, 411148 thru 411153, do as follows:

A. Do an inspection of the installed rudder hinge/bracket hardware for correct thread engagement in

accordance with the notes in Steps 3D, 4C, and 5C of MK400-27-01A (or latest revision).

B. Do a check of the rudder travel in accordance with Steps 6B(1) through 6B(6) of MK400-27-01A (or

latest revision).

C. Make an entry in the airplane logbook that states compliance and method of compliance with this

Service Bulletin.

SB09-27-01 Revision 3

Page 6 July 20, 2010
Figure 1. Locations of Lower Rudder Hinge/Bracket and Upper/Middle Rudder Brackets (Sheet 1)

SB09-27-01 Revision 3

July 20, 2010 Page 7
Figure 2. Upper Rudder Bracket (Sheet 1)

SB09-27-01 Revision 3

Page 8 July 20, 2010
Figure 3. Middle Rudder Bracket (Sheet 1)

SB09-27-01 Revision 3

July 20, 2010 Page 9
Figure 4. Upper and Middle Rudder Bracket (Sheet 1)

SB09-27-01 Revision 3

Page 10 July 20, 2010
Figure 5. Lower Rudder Hinge (Model 400 shown). Inspect similar areas on the Lower Rudder Bracket

(Model 300/350) (Sheet 1)

SB09-27-01 Revision 3

July 20, 2010 Page 11
OWNER NOTIFICATION

A. On April 13, 2009 the following Owner Advisory message was sent to applicable owners of record in

SB09-27-01A.

Dear Cessna Owner:

This Owner Advisory is to inform you that Service Bulletin SB09-27-01 Rudder Hinge and Bracket Inspection

has been issued.

SB09-27-01 provides instructions to perform a visual inspection of the lower rudder hinge or bracket and

the upper and middle rudder brackets for cracking, deformation, or localized discoloration. If any of these

conditions are found, the affected hinge/bracket shall be replaced.

Non-compliance with this Service Bulletin could allow any of the above described conditions to exist and if

not corrected, may result in failure of more than one hinge or bracket which could potentially result in the

loss of rudder control.

Compliance is mandatory: Accomplish the initial inspection as soon as practical, not to exceed 10 flight

hours or 30 days, whichever occurs first.

NOTE: If the airplane must be flown prior to the initial inspection being performed, the pilot in command should

be certain to check the rudder hardware for good condition and security, as directed by Area 7 of the

Preflight Inspection Checklist in Section 4 of the Pilot’s Operating Handbook and FAA Approved

Airplane Flight Manual.

The rudder hinge and bracket visual inspections must be performed by maintenance personnel using the

following schedule:

Inspection Interval Required Action

Initial inspection within 10 flight hours or 30 days,

whichever occurs first

Visual 10x magnification inspection with the rudder

removed

Recurring inspection every 25 flight hours or 90 days,

whichever occurs first

Visual inspection with the rudder remaining in place

Recurring inspection every 50 flight hours or 180

days, whichever occurs first

Visual 10x magnification inspection with the rudder

removed

Credit Information

For airplanes in warranty:

Initial and recurring 50 flight hours/180 days inspections: A labor allowance credit of 1.2 man-hours per airplane

will be provided to inspect the rudder hinges and brackets.

If necessary, a labor allowance credit of 0.7 man-hour and applicable parts credit will be provided to replace

each hinge or bracket exhibiting any of the conditions stated in Service Bulletin SB09-27-01.

Recurring 25 hours/90 days inspections: A labor allowance credit of 0.5 man-hour per airplane will be provided.

Freight will be credited at the most economical method unless pre-approved by Cessna.

To receive credit, the work must be completed and a Warranty Claim submitted by a Cessna Single Engine

Service Station within 30 calendar days of Service Bulletin compliance before the credit expiration dates

shown below.

NOTE: Removed hinges or brackets shall be returned with the Warranty Claim.

Domestic . . . . . . . . . . . . . . . . . . . . . April 13, 2010

International . . . . . . . . . . . . . . . . . . . April 13, 2010

SB09-27-01 Revision 3

Page 12 July 20, 2010
The information contained in the referenced Cessna Service Bulletin shall be considered an amendment to the

Cessna Manufacturer's Service/Maintenance Manual or Instructions for continued airworthiness, and must be

accomplished for ongoing airworthiness compliance as required per 14 CFR Part 43.13.

Please contact a Cessna Single Engine Service Station for detailed information and make arrangements to

have Service Bulletin SB09-27-01 accomplished on your airplane.

B. On August 31, 2009 the following Owner Advisory message was sent to applicable owners of record in

SB09-27-01R1A.

Dear Cessna Owner:

This Owner Advisory is to inform you that Service Bulletin SB09-27-01 Revision 1 Rudder Hinge and Bracket

Inspection has been issued.

SB09-27-01 provided instructions to perform a visual inspection of the lower rudder hinge or bracket and

the upper and middle rudder brackets for cracking, deformation, or localized discoloration. If any of these

conditions were found, the affected hinge/bracket was required to be replaced.

SB09-27-01 Revision 1 provides a new design hinge and brackets that shall be installed as replacements

for the previous design parts. The new hinge and brackets are made of different material, incorporate a

machined shoulder for enhanced bearing retention, and include the application of corrosion protection primer

and a top coat of white paint.

Non-compliance with SB09-27-01 Revision 1 could allow any of the above described conditions to exist and

if not corrected, may result in failure of more than one hinge or bracket which could potentially result in the

loss of rudder control.

Compliance is mandatory: Accomplish the initial inspection as soon as practical, not to exceed 10 flight

hours or 30 days, whichever occurs first.

NOTE: Compliance with SB09-27-01 Revision 1 is required for airplanes in compliance with the Original Issue.

NOTE: If the airplane must be flown prior to the initial inspection being performed, the pilot in command should

be certain to check the rudder hardware for good condition and security, as directed by Area 7 of the

Preflight Inspection Checklist in Section 4 of the Pilot’s Operating Handbook and FAA Approved

Airplane Flight Manual.

The rudder hinge and bracket visual inspections must be performed by maintenance personnel using the

following schedule:

Inspection Interval Required Action

Initial inspection within 10 flight hours or 30 days,

whichever occurs first

Visual 10x magnification inspection with the rudder

removed

Recurring inspection every 25 flight hours or 90 days,

whichever occurs first

Visual inspection with the rudder remaining in place

Recurring inspection every 50 flight hours or 180

days, whichever occurs first

Visual 10x magnification inspection with the rudder

removed

NOTE: Compliance with SB09-27-01 Revision 1 by installation of the new design hinge/brackets identified in

the Service Bulletin equates to full compliance and the recurring inspections of the Service Bulletin will

no longer be required.

SB09-27-01 Revision 3

July 20, 2010 Page 13
C. On November 23, 2009 the following message was sent to applicable owners of record in SB09-27-01AR2.

Dear Cessna Owner:

This Owner Advisory is to inform you that SB09-27-01 Revision 2 Rudder Hinge and Bracket Inspection

has been issued.

A visual inspection of the lower rudder hinge or bracket and the upper and middle rudder brackets shall be

accomplished for cracking, deformation, or localized discoloration. If any of these conditions are found, the

affected hinge/bracket shall be replaced as stated in SB09-27-01 Revision 2.

SB09-27-01 Revision 1 provided a new design hinge and brackets for installation when replacements were

required for the previous design parts. The new hinge and brackets are made of different material, incorporate

a machined shoulder for enhanced bearing retention, and include the application of corrosion protection primer

and a top coat of white paint.

SB09-27-01 Revision 2 includes a modification kit for replacement of the brackets/hinges, instructions for

rudder travel verification, an allowance for utilizing different length hardware to ensure adequate thread

engagement, and instructions to verify proper hardware thread engagement of previously installed brackets and

hinges. Additionally, Revision 2 is FAA-approved as an Alternative Method of Compliance for AD2009-09-09.

Non-compliance with SB09-27-01R2 could allow any of the above described conditions to exist and if not

corrected, may result in failure of more than one hinge or bracket which could potentially result in the loss

of rudder control.

Compliance is mandatory: Accomplish the initial inspection as soon as practical, not to exceed 10 flight

hours or 30 days, whichever occurs first. .

NOTE: Compliance with SB09-27-01 Revision 2 is required for airplanes in compliance with the Original Issue.

NOTE: Revision 1. Specifically, check for proper hinge/bracket hardware thread engagement in accordance

with the notes in steps 3.D, 4.C, and 5.C of Modification Kit MK400-27-01 Rudder Hinge and Bracket

Installation (or latest revision) and accomplish the check of the rudder travel in accordance with steps

6.B(1) through 6.B(6) of MK400-27-01 (or latest revision)

NOTE: If the airplane must be flown prior to the initial inspection being performed, the pilot in command should

be certain to check the rudder hardware for good condition and security, as directed by Area 7 of the

Preflight Inspection Checklist in Section 4 of the Pilot’s Operating Handbook and FAA Approved

Airplane Flight Manual.

The rudder hinge and bracket visual inspections must be performed by maintenance personnel using the

following schedule:

Inspection Interval Required Action

Initial inspection within 10 flight hours or 30 days,

whichever occurs first

Visual 10x magnification inspection with the rudder

removed

Recurring inspection every 25 flight hours or 90 days,

whichever occurs first

Visual inspection with the rudder remaining in place

Recurring inspection every 50 flight hours or 180

days, whichever occurs first

Visual 10x magnification inspection with the rudder

removed

NOTE: Compliance with Service Bulletin SB09-27-01 Revision 2 equates to full compliance, and the recurring

inspections of SB09-27-01 Revision 2 will no longer be required.

NOTE: SB09-27-01 Revision 2 is approved by the FAA Wichita Aircraft Certification Office, by letter

L115W-09-785 (a copy is attached), as an Alternative Method of Compliance with FAA Airworthiness

Directive number AD2009-09-09. Compliance with Revision 2 of SB09-27-01 by installation of the new

hinges/brackets, and subsequent verification of correct rudder travel and hardware installation, is

considered as terminating action for AD2009-09-09.

The information contained in the referenced Cessna Service Bulletin shall be considered an amendment to the

Cessna Manufacturer's Service/Maintenance Manual or Instructions for continued airworthiness, and must be

accomplished for ongoing airworthiness compliance as required per 14 CFR Part 43.13.

SB09-27-01 Revision 3

Page 14 July 20, 2010
D. On July 20, 2010 the following message will be sent to applicable owners of record in SB09-27-01AR3.

Dear Cessna Owner:

This Owner Advisory is to inform you that SB09-27-01 Revision 3 Rudder Hinge and Bracket Inspection

has been issued.

The paragraphs that follow give a historical summary of previously issued revisions:

A visual inspection of the lower rudder hinge or bracket and the upper and middle rudder brackets shall be

accomplished for cracking, deformation, or localized discoloration. If any of these conditions are found, the

affected hinge/bracket shall be replaced as stated in this Service Bulletin.

SB09-27-01 Revision 1 provided a new design hinge and brackets for installation when replacements were

required for the previous design parts. The new hinge and brackets are made of different material, incorporate

a machined shoulder for enhanced bearing retention, and include the application of corrosion protection primer

and a top coat of white paint.

SB09-27-01 Revision 2 included a modification kit for replacement of the brackets/hinges, instructions for

rudder travel verification, an allowance for utilizing different length hardware to ensure adequate thread

engagement, and instructions to verify proper hardware thread engagement of previously installed brackets and

hinges. Additionally, Revision 2 is FAA-approved as an Alternative Method of Compliance for AD2009-09-09.

SB09-27-01 Revision 3 adds airplane serial numbers that had the new-design hinge and brackets installed

at the factory. These added airplane serial numbers are required to be inspected to verify rudder travel and

for correct hardware thread engagement. Modification Kit MK400-27-01 has been revised to include two

larger rudder travel stop bushings. Additionally, SB09-27-01 Revision 3 is FAA approved as an Alternative

Method of Compliance for AD2009-09-09.

Non-compliance with SB09-27-01 Revision 3 could allow any of the above described conditions to exist and

if not corrected, may result in failure of more than one hinge or bracket which could potentially result in the

loss of rudder control.

COMPLIANCE REQUIREMENTS

For airplanes that have not accomplished the initial inspection:

Compliance is mandatory: Accomplish the initial inspection as soon as practical, not to exceed 10 flight

hours or 30 days, whichever occurs first.

NOTE: If the airplane must be flown before the initial inspection is accomplished, the pilot in command must

do a check of the rudder hardware for good condition and security, as directed by Area 7 of the

Preflight Inspection Checklist in Section 4 of the Pilot’s Operating Handbook and FAA Approved

Airplane Flight Manual.

If the airplane will be flown after the initial inspection, but before the installation of the new-design rudder

hinge/brackets, the rudder hinge and brackets visual inspections must be performed by maintenance personnel

using the following schedule:

Inspection Interval Required Action

Initial inspection within 10 flight hours or 30 days,

whichever occurs first

Visual 10x magnification inspection with the rudder

removed

Recurring inspection every 25 flight hours or 90 days,

whichever occurs first

Visual inspection with the rudder remaining in place

Recurring inspection every 50 flight hours or 180

days, whichever occurs first

Visual 10x magnification inspection with the rudder

removed

NOTE: Compliance with Service Bulletin SB09-27-01 Revision 2 or Revision 3 equates to full compliance, and

the recurring inspections of this Service Bulletin will no longer be required.

For airplanes that are in compliance with SB09-27-01 Original Issue or SB09-27-01 Revision 1 only:

Compliance is mandatory: SB09-27-01 Revision 3 shall be accomplished as soon as practical within the next

50 flight hours or 6 months, whichever occurs first.

SB09-27-01 Revision 3

July 20, 2010 Page 15
For airplanes that are not in compliance with SB09-27-01 Revision 2

and

Model 350 Airplane serial numbers 42010, 42559, 421014, 421018, and 421020

Model 400 Airplane serial numbers 41570, 411088, 411111,411139, 411141, 411143 thru 411146, 411148

thru 411153:

Compliance is mandatory: SB09-27-01 Revision 3 shall be accomplished within 50 flight hours or 6 months,

whichever occurs first.

These airplanes already have the new design rudder hinge and/or brackets installed. (Modification Kit

MK400-27-01A installation is not required.) Specifically the following action shall be accomplished:

• Do an inspection of the hinge/brackets attachment hardware for correct thread engagement and

accomplish the rudder travel check in accordance with Step 2 of the Accomplishment Instructions in this

Service Bulletin.

For airplanes that are in compliance with SB09-27-01 Revision 2:

Compliance with SB09-27-01 Revision 3 is not required.

The information contained in the referenced Cessna Service Bulletin shall be considered an amendment to the

Cessna Manufacturer's Service/Maintenance Manual or Instructions for continued airworthiness, and must be

accomplished for ongoing airworthiness compliance as required per 14 CFR Part 43.13.

CREDIT INFORMATION

For airplanes in warranty except for the specific airplane serials listed in the next section below:

If necessary, applicable parts credit and a labor allowance credit of 1.0 man-hour will be provided to install

MK400-27-01A (or latest revision). If necessary, applicable parts credit and a labor allowance credit of 0.5

man-hour will be provided to adjust rudder travel.

For airplanes in compliance with SB09-27-01 Revision 1 and not in compliance with SB09-27-01 Revision

2 only:

• A labor allowance credit of 0.2 man-hour will be provided to inspect previously installed hinge/bracket

hardware for proper thread engagement. If necessary, applicable parts credit and a labor allowance credit

of 0.6 man-hour will be provided to install alternate hardware.

• A labor allowance credit of 0.8 man-hour will be provided to inspect the rudder rigging.

To receive credit, the work must be completed and a Warranty Claim submitted by a Cessna Single Engine

Service Station within 30 calendar days of Service Bulletin compliance before the credit expiration dates

shown below.

Domestic . . . . . . . . . . . . . . . . . . . . . April 13, 2010

International . . . . . . . . . . . . . . . . . . . April 13, 2010

SB09-27-01 Revision 3

Page 16 July 20, 2010
For Model 350 airplane serial numbers 42010, 42559, 421014, 421018, 421020, and Model 400 airplane

serial numbers 41570, 411088, 411111, 411139, 411141, 411143 thru 411146, 411148 thru 411153 only:

• A labor allowance credit of 0.2 man-hour will be provided to inspect previously installed hinge/bracket

hardware for proper thread engagement. If necessary, applicable parts credit and a labor allowance credit

of 0.6 man-hour will be provided to install alternate hardware.

• A labor allowance credit of 0.8 man-hour will be provided to inspect the rudder rigging.

To receive credit, the work must be completed and a Warranty Claim submitted by a Cessna Single Engine

Service Station within 30 calendar days of Service Bulletin compliance before the credit expiration dates

shown below.

Domestic . . . . . . . . . . . . . . . . . . . January 20, 2011

International . . . . . . . . . . . . . . . . . January 20, 2011

Please contact a Cessna Single Engine Service Station for detailed information and if applicable arrange to

have Cessna Service Bulletin SB09-27-01 Revision 3 accomplished on your airplane.

*******

SB09-27-01 Revision 3

July 20, 2010 Page 17