Single

Engine SERVICE LETTER

SEL-57-01

REVISION TRANSMITTAL

TO: Cessna Distributors, Single Engine Authorized Service Facilities, and CPC's

SUBJECT: Cessna Service Letter SEL-57-01 Revision 1: Lower Main Spar Cap Inspection

REASON

To add model T210 serials T210-0198 thru T210-0454 to the Effectivity Section.

To add model 210 serial 21058140 to the Effectivity Section.

To list the P210 serials correctly in the Effectivity Section.

To show the aft side of the inspection area.

To reference the service manual for cleaning the areas to be inspected.

Miscellaneous changes as necessary.

Please replace any copy of SEL-57-01 with the attached copy of SEL-57-01 Revision 1 which is printed in

its entirety.

NOTE: Compliance with SEL-57-01 Revision 1 is not required for airplanes that were able to comply with

the Original Issue.

LOG OF REVISIONS

Page No. Date

1 May 9, 2012

2 May 9, 2012

3 May 9, 2012

4 May 9, 2012

5 May 9, 2012

Original Issue - April 27, 2012 SEL-57-01

Revision 1 - May 9, 2012 Page 1 of 1

Cessna Aircraft Company, Cessna Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800, Fax 1-316-517-7271,

Email: customercare@cessna.textron.com

COPYRIGHT © 2012

Single

Engine SERVICE LETTER

SEL-57-01

TITLE

WINGS - LOWER MAIN SPAR CAP INSPECTION

EFFECTIVITY

MODEL SERIAL NUMBERS

210 / T210 21058140, 21058819 thru 21065009

T210 T210-0198 thru T210-0454

P210 P21000001 thru P21000874

REASON

Reports have been received of cracks found in the wing spar caps. This service letter provides instructions

to accomplish a visual inspection of the lower main spar caps in the right and in the left wings.

Non-compliance with this service letter may result in undetected crack(s) in the spar cap, which could

result in structural failure of the wing.

DESCRIPTION

This service letter provides instructions to do a visual inspection of the left and right wing lower main

spar caps for cracks.

COMPLIANCE

Mandatory:

For airplanes/wings with 10,000 hours or more total time in service:

An external inspection must be performed before next flight.

If cracks are found during external inspection, an internal inspection must be performed before next flight.

If no cracks are found during external inspection, an internal inspection must be performed within 5 hours of

operation.

If no cracks are found during internal inspection, a recurring internal inspection must be performed every 100

hours of operation or 12 months thereafter, whichever occurs first, until spar cap, spar, or wing replacement.

For airplanes/wings with more than 5,000 hours but less than 10,000 hours total time in service:

An initial internal inspection must be performed within 25 hours of operation.

If no cracks are found, a recurring internal inspection must be performed every 100 hours of operation or 12

months thereafter, whichever occurs first, until spar cap, spar, or wing replacement.

For airplanes/wings with less than 5,000 hours total time in service:

An initial internal inspection must be performed at or before 5,000 hours.

If no cracks are found, a recurring internal inspection must be performed every 100 hours of operation or 12

months thereafter, whichever occurs first, until spar cap, spar, or wing replacement.

REFERENCES

Refer to applicable service manuals and illustrated parts catalogs

Original Issue - April 27, 2012 SEL-57-01

Revision 1 - May 9, 2012 Page 1 of 5

Cessna Aircraft Company, Cessna Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800, Fax 1-316-517-7271,

Email: customercare@cessna.textron.com

COPYRIGHT © 2012
SEL-57-01

Page 2 Revision 1 - May 9, 2012

Single

Engine SERVICE LETTER

SEL-57-01

ACCOMPLISHMENT INSTRUCTIONS

WARNING: You must do the visual inspection for cracks within the hours of operation

specified in this service letter. Cracks in the wing spar cap can cause

damage to the airplane and danger to passengers during flight.

1. Do an external visual inspection on the left and on the right wings as follows:

A. Carefully clean the skin underneath the main spar cap fitting between WS 25.25 and WS 45.00

where you will do the external inspection. No access panel removal is required for this external

inspection. (Refer to applicable sections of the applicable service manual.)

B. Do an external visual inspection for cracks of the outer skin underneath the main spar cap fitting

between WS 25.25 and WS 45.00.

(1) If you find no cracks, you must do an internal inspection within 5 hours of operation. Go

to Step 2.

(2) If you find one or more cracks, you must do an internal inspection before further flight. Go

to Step 2.

2. (Refer to Figure 1.) Do an internal visual inspection on the left and on the right wings as follows:

A. Prepare the airplane for maintenance.

(1) Make sure that the airplane is electrically grounded.

(2) Make sure that all switches are in the OFF/NORM position.

(3) Disconnect electrical power from the airplane.

(a) Disconnect the airplane battery.

(b) Disconnect external electrical power.

(4) Attach maintenance warning tags to the battery and external power receptacle that have "DO

NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them.

B. Get access to the lower main spar cap between WS 25.25 and WS 45.00. (Refer to the applicable

section of the service manual.)

C. Carefully clean the area of the lower main spar caps between WS 25.25 and WS 45.00 where you

will do the inspection. (Refer to applicable sections of the applicable service manual.)

D. Do an internal visual inspection for cracks on the lower main spar caps between WS 25.25 and WS

45.00. You must use a flashlight and a mirror or a flexible borescope for this inspection.

NOTE: On aircraft equipped with deice boots or avionics bays, you must use a flexible borescope to

see the inspection area.

(1) If you find no cracks, do as follows:

(a) A recurring internal inspection must be performed every 100 hours of operation or 12

months thereafter, whichever comes first, until spar cap, spar, or wing replacement.

(b) Install the fairings and access panels that you removed for access to do the inspection.

(c) Remove the maintenance warning tags and connect the airplane battery.

(d) Go to Step 2.D.(3).

(2) If you find one or more cracks, no further flight is permitted. You must replace the spar cap,

wing spar or wing before further flight.

NOTE: If you are not sure if what you see is a crack, do an eddy current inspection. (Refer

to the applicable service manual, Section 2A-13-01, Supplemental Inspection

Documents, Nondestructive Methods and Requirements.)
Single

Engine SERVICE LETTER

SEL-57-01

(3) Provide the results of the initial and any subsequent internal inspections to Cessna Customer

Care. Use the Wing Lower Main Spar Cap Inspection Report form and pictures as applicable.

Telephone and fax numbers are provided on the form.

NOTE: The Wing Lower Main Spar Cap Inspection Report form must be sent to Cessna

Customer Care to report both conditions - cracked or not cracked.

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

letter.

SEL-57-01

Revision 1 - May 9, 2012 Page 3
SEL-57-01

Page 4 Revision 1 - May 9, 2012

Single

Engine SERVICE LETTER

SEL-57-01

Figure 1. Lower Main Spar Cap Inspection (Sheet 1)
Single

Engine SERVICE LETTER

SEL-57-01

Figure 1. Lower Main Spar Cap Inspection (Sheet 2)

SEL-57-01

Revision 1 - May 9, 2012 Page 5
Single

Engine ATTACHMENT

SEL-57-01

WING LOWER MAIN SPAR CAP INSPECTION REPORT

To:

Cessna Aircraft Company

Customer Care Page: 1 of ___ Pages

P.O.Box 7706 Includes this cover sheet

Wichita, Kansas 67277-7706

Phone Number: 316-517-5800

Fax Number: 316-517-7271

email: customercare@cessna.textron.com

From: Registration No.:

Date: Total Time in Service (Hrs.):

Airplane Serial Number:

Owner's Name: Facility Name:

Owner's Address: Facility Address:

Owner's Phone Number: Phone Number of Facility:

Owner's Fax Number: Fax Number of Facility:

Please provide detailed and dimensioned descriptions of any crack(s). Attach pictures to this form which

indicate for left or right wing.

Comments/Notes: Cracks: Yes No (Please Circle One)
Single

Engine OWNER ADVISORY

SEL-57-01

TITLE

WINGS - WING LOWER MAIN SPAR CAP INSPECTION

TO:

Cessna 210, T210, P210 Owner

REASON

Reports have been received of cracks found in the wing spar caps. This service letter provides instructions

to accomplish a visual inspection of the lower main spar caps in the right and in the left wings.

Non-compliance with this service letter may result in undetected crack(s) in the spar caps, which could

result in structural failure of the wing.

DESCRIPTION

This service letter provides instructions to do a visual inspection of the left and right wing lower main

spar caps for cracks.

COMPLIANCE

Mandatory:

For airplanes/wings with 10,000 hours or more total time in service:

An external inspection must be performed before next flight.

If cracks are found during external inspection, an internal inspection must be performed before next flight.

If no cracks are found during external inspection, an internal inspection must be performed within 5 hours of

operation.

If no cracks are found during internal inspection, a recurring internal inspection must be performed every 100

hours of operation or 12 months thereafter, whichever occurs first, until spar cap, spar, or wing replacement.

For airplanes/wings with more than 5,000 hours but less than 10,000 hours total time in service:

An initial internal inspection must be performed within 25 hours of operation.

If no cracks are found, a recurring internal inspection must be performed every 100 hours of operation or 12

months thereafter, whichever occurs first, until spar cap, spar, or wing replacement.

For airplanes/wings with less than 5,000 hours total time in service:

An initial internal inspection must be performed at or before 5,000 hours.

If no cracks are found, a recurring internal inspection must be performed every 100 hours of operation or 12

months thereafter, whichever occurs first, until spar cap, spar, or wing replacement.

NOTE: Compliance with SEL-57-01 Revision 1 is not required for airplanes that were able to comply

with the Original Issue.

WARRANTY

Not Applicable

Please contact a Cessna Single Engine Authorized Service Facility for detailed information and arrange to

have Cessna Service Letter SEL-57-01 Revision 1 accomplished on your airplane.

NOTE: As a convenience, service documents are now available online to all our customers through a

simple, free-of-charge registration process. If you would like to sign up, please visit the "Customer

Access" link at www.cessnasupport.com to register.

Original Issue - April 27, 2012 SEL-57-01

Revision 1 - May 9, 2012 Page 1 of 1

Cessna Aircraft Company, Cessna Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800, Fax 1-316-517-7271,

Email: customercare@cessna.textron.com

COPYRIGHT © 2012