WINGS - MODEL 210 CARRY-THRU SPAR ONE-TIME CORROSION INSPECTION

unless the maintenance is accomplished at a Textron Aviation-owned Service Center. Single Engine SERVICE LETTER MANDATORY SEL-57-08 CONSUMABLE MATERIAL You must use the consumable materials that follow, or their equivalent, to complete this service document. NAME NUMBER MANUFACTURER USE Color Chemical Film Treatment U074093 (Alodine 1132 Touch n Prep) Textron Aviation Parts Distribution 7121 Southwest Boulevard Wichita, KS 67215 To prepare bare aluminum surface for intermediate primer. Bonderite M-CR 1132, (formerly the Alodine 1132 Touch-n-prep) are both approved for small touch up areas, generally less than 6 inches square.) Corrosion Resistant Primer K000574 (2oz Kit) Textron Aviation Parts Distribution Touch-up primer kit. Corrosion Resistant Primer K000479 (2 Gal Kit) Textron Aviation Parts Distribution Large primer kit. Alumigrip 10P8-11 Epoxy Primer Alumigrip 10P8-11 AkzoNobel 1 East Water St Waukegan, IL 60085 https://aerospace.akzonobel.com/ Corrosion Resistant Primer. Conversion Coating Bonderite M-CR 600RTU Commercially Available Conversion Coating of bare metal before intermediate primer. Cor-Ban 23 COR-BAN-23 (U074098) (12oz aerosol) Textron Aviation Parts Distribution Corrosion Inhibiting Compound coating. Formit-18 Fan Formit-18 Textron Aviation Parts Distribution Nozzle for Cor-Ban 23 application. Aluminum oxide paper or cloth (high purity) - 180 or 220, and 320 grit Commercially Available For paint/corrosion removal and surface preparation before painting. Extreme Simple Green Aircraft and Precision Cleaner Commercially Available Initial cleaning of soiled surface. Isopropyl Alcohol Commercially Available Type I Cleaning Solvent for surface cleaning prior to painting. Methyl Propyl Ketone Commercially Available Cleaning solvent of Corban Corrosion Inhibiting Compound. CAUTION: Do not use any other Simple Green products other than Extreme Simple Green as some have been found to be corrosive. NOTE: Textron Aviation has tested and approved Cor-Ban 35 and ARDROX AV-8. These products may be used in place of Cor-Ban 23 at the owners discretion. NOTE: The materials that follow are allowable alternate for the primers above and comply with standard MIL-C-8514, Type 1 Class C . SEL-57-08 Revision 2 - August 3, 2020 Page 3 SEL-57-08 Page 4 Revision 2 - August 3, 2020 Single Engine SERVICE LETTER MANDATORY SEL-57-08 NAME NUMBER MANUFACTURER USE Zinc Chromate Primer 1757B1C–P Randolph Products Co. 33 Haynes Circle Chicopee, MA 01020 Approved Zinc Chromate Primer. Zinc Chromate Primer K000484 Textron Aviation Parts Distribution 7121 Southwest Boulevard Wichita, KS 67215 Approved Zinc Chromate Primer. NOTE: As an alternate to the conversion coatings listed, the materials that follow are allowable alternate, which comply with standard MIL-DTL-81706B Class 1A. NAME NUMBER MANUFACTURER USE Oakite ChromiCoat L25 Commercially Available Approved alternate Conversion Coating. Iridite 14-2 Commercially Available Approved alternate Conversion Coating. Bonderite M-CR 1600 AERO Commercially Available Approved alternate Conversion Coating. Bonderite M-CR 1201 AERO Commercially Available Approved alternate Conversion Coating. Bonderite M-CR 1200S AERO Commercially Available Approved alternate Conversion Coating. Bonderite M-CR 1200 Commercially Available Approved alternate Conversion Coating. Bonderite M-CR 600 AERO Commercially Available Approved alternate Conversion Coating. TOOLING NAME NUMBER MANUFACTURER USE 10X Magnifying Lense Commercially Available For detailed visual inspection of carry-thru spar. Micrometer (depth gauge style) Commercially Available To measure depth of blended areas of carry thru spar. Eddy Current Inspection Equipment Nondestructive Inspection Methods and Requirements, Document 2A-13-01 found in Section 2A Supplemental Inspection Documents in the appropriate Model Service or Maintenance Manual For Eddy Current inspection of carry-thru spar lower surface. REFERENCES Cessna Model 200 Series (1966-1968) Service Manual Cessna Model 210 Centurion Series (1969) Service Manual Cessna Model 210 Centurion Series (1970-1976) Service Manual Cessna Model 210 and T210 Series (1977-1984) Service Manual Cessna Model 210 and T210 Series (1985-1986) Service Manual Cessna Model P210 Series (1978-1983) Service Manual Single Engine SERVICE LETTER MANDATORY SEL-57-08 Cessna Model P210 Series (1985-1986) Service Manual Inspection Time Limits - Structure, Section 2A-10-00 found in Section 2A Supplemental Inspection Documents in the appropriate Model Service or Maintenance Manual, Nondestructive Inspection Methods and Requirements, Document 2A-13-01 found in Section 2A Supplemental Inspection Documents in the appropriate Model Service or Maintenance Manual NOTE: To make sure all publications used are complete and current. Refer to www.txtavsupport.com. PUBLICATIONS AFFECTED None ACCOMPLISHMENT INSTRUCTIONS 1. Prepare the airplane for maintenance. A. Make sure that the airplane is electrically grounded. B. Make sure that all switches are in the OFF/NORM position. C. Disconnect electrical power from the airplane. (1) Disconnect external electrical power. (2) Disconnect the airplane battery. D. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them. 2. Remove the pilot and co-pilot seats if necessary. (Refer to the applicable Model Service or Maintenance Manual.) 3. Get access to all surfaces of the carry-thru spar by removing panels, upholstery, headliner, sealant, and installed utility or oxygen systems as necessary. (Refer to the applicable Model Service or Maintenance Manual.) 4. Remove foam from bottom of carry-thru spar as applicable. A. Clean all adhesive residue from the carry-thru spar with a non-metallic scraper tool. 5. Clean grime or debris from all interior surfaces of the carry-thru spar with special emphasis on lower cap surface. 6. (Refer to Figure 1, Sheets 1-5.) Do a detailed visual inspection of the carry-thru spar with a 10X magnification lens looking for corrosion, nicks, gouges, drill starts, or hardware damage and must include: 1. The visible surfaces of the Upper cap. 2. The Spar web (include cap to web radius). 3. The Lower cap (include upper and lower surface and cap edge). NOTE: The detailed visual inspection should pay particular attention to locations where air ducts, support wires, and upholstery pads contact the lower spar structure as well as lower spar cap lower surface Kick Area between BL 10.0 and BL 12.5. (Refer to the figure titled Spar Dimensions after Table 1.) A. (Refer to Figure 1, Sheets 4 and 5.) If stress corrosion cracking or exfoliation corrosion (flaking) of the spar is found, contact Textron Aviation Team Structures for evaluation. (Refer to the Carry-Thru Spar Inspection Report for contact information.) B. If corrosion is found on the carry-thru spar, the area can be reworked as follows: NOTE: If previous evidence of blending can be determined or is recorded in the aircraft log book for the same location corrosion has been found, contact Textron Aviation Structures. (1) Use 180 grit or finer aluminum oxide abrasive paper, cloth or pads to carefully remove corrosion and blend that area locally around the affected region. SEL-57-08 Revision 2 - August 3, 2020 Page 5 SEL-57-08 Page 6 Revision 2 - August 3, 2020 Single Engine SERVICE LETTER MANDATORY SEL-57-08 (2) Make sure to only remove the minimum material necessary to blend the corroded surface with the surrounding surface. (3) Maintain a minimum of 20:1 blend to depth ratio. (4) Leave no sharp edges after blending. (5) Finish with a 320 grit or finer grained aluminum oxide sandpaper to 63 micro RA or smoother. NOTE: When 320 grit is properly used, it will produce a 63 micro RA surface finish. (6) Use a vacuum to remove dust. (7) Use a clean cloth wet with isopropyl alcohol to clean the surface. (8) Measure the depth of the blended area mechanically; such as with a straight edge and feeler gauge or a depth gauge micrometer. (a) If material removed is greater than what is listed in the TABLE 1 for the specific spar feature, contact Textron Aviation Team Structures with the dimension of blended area for evaluation. (Refer to the Carry-Thru Spar Inspection Report for contact information.) (b) If material removed is less than 0.010 inch for the specific spar feature in TABLE 1, go to Step 8. (c) If material removed is greater than 0.010 but less than what is listed in TABLE 1 for the specific spar feature, complete the eddy current inspection of the blended areas and the Kick Area from buttock line 10.0 thru 12.5 inch (whether there is or is not presence of corrosion in the Kick Area), go to Step 7. TABLE 1 REPAIR CRITERIA Carry-thru Spar Feature Spar Buttock Line (BL) (in) Blend Limit (in) Description Center Line to 10.0 0.030 Spar Constant Cross Section 10.0 to 12.5 0.030 Lower Cap Kick Area 1 Lower Cap - Lower Surface (1) 12.5 to 21.5 0.030 Outboard of Lower Cap Kick Area 2 Lower Cap - Upper Surface (1) Center Line to 16.5 0.030 Spar Constant Cross-Section thru Cap Kick Area 3 Lower Cap Edge (1) Center Line to 16.5 0.100 Forward or Aft facing cap edges 4 Lower Cap to Web Radius (1) Center Line to 16.5 0.030 (2) Forward or Aft facing web radii 5 Spar Web (1) Center Line to 16.5 0.050 (2) Includes areas common to web holes NOTE: Dimensions shown are in Inches. (1) Limits can't be combined at the same Buttock Line location without contacting Textron Aviation. Example: Web blend and a lower spar cap blend cannot be combined at same Buttock Line location without contacting Textron Aviation. (2) The carry-thru spar must be replaced if the blend limit is exceeded in this area. Single Engine SERVICE LETTER MANDATORY SEL-57-08 SPAR DIMENSIONS SPAR DETAIL C. If no corrosion is found on the carry-thru spar but previous evidence of blending can be determined or is recorded in the aircraft log book, contact Textron Aviation Structures. D. If no corrosion is found on the carry-thru spar, go to Step 8. 7. (Refer to Figure 1, View A-A.) (If corrosion was found and blended.) Do an eddy current inspection of the blended area as follows: (Refer to 2A-13-01, Nondestructive Inspection Methods and Requirements in the appropriate Model Service or Maintenance Manual.) A. Plan out the inspection process to cover the items listed as follows: • If the eddy current inspection is performed by qualified personnel that are not representing an FAA Certified Repair Station, an A&P Mechanic may supervise the inspection and make the appropriate logbook entry. • Technician must meet the qualifications defined as being equivalent to the Cessna 210 NAS 410 Level 2 Eddy Current method as defined in the Cessna Model 210 Manuals for being qualified to accomplish the eddy current inspection required. ISO/BSI 9712, EN 4179 qualifications are considered to be equivalent to those specified in the Cessna Model 210 Manuals. SEL-57-08 Revision 2 - August 3, 2020 Page 7 SEL-57-08 Page 8 Revision 2 - August 3, 2020 Single Engine SERVICE LETTER MANDATORY SEL-57-08 • Eddy current inspection will cover the carry-thru spar where corrosion was blended and extend 1 Inch beyond the blended area. • Eddy current inspection will cover the Kick Area on the lower surface of the lower cap from Buttock Line 10.0 thru 12.5. • Eddy current inspection will be with a 0.125 Inch probe. • Technician should use an inspection approach that ensures the entire blended surface is inspected without gaps and inspection area should extend 1 Inch beyond the blended area in all directions. • Limit the inspection area to no wider than 4 square inches at a time, depending on size of blended area. Once an area is complete, move to any additional rework location and repeat the eddy current inspection. • Inspect one section at time and overlap each section by 0.25 Inch overlap between each section and identify when each section is complete. • Identify when each section is complete to help keep track of progress. B. Review the General Requirements and Eddy Current Inspection sections of 2A-13-01 Nondestructive Inspection Methods and Requirements. C. Calibrate the eddy current instrument - Impedance Plane. (Refer to 2A-13-01, Nondestructive Inspection Methods and Requirements, Section 2. Eddy Current Inspection.) D. Eddy current scan the blended surface with an 0.125 Inch diameter surface pencil probe at 200 kHz. • Scan direction must be with an inboard to outboard direction. • Use of a non-metallic straight edge as a guide will help ensure there is not a fore-aft motion of the probe. • Probe one small section of only a couple of inches at a time, recommend no wider than 4 Inches. • Move the probe in 0.125 Iinch increments. • Overlap each section by 0.25 Inch. • Extend 1 Inch beyond the blended area. (1) Look for a sharp response of 10-percent screen height or more which may indicate corrosion or fatigue cracking or both. E. Eddy current scan the Kick Area on the lower surface of the lower cap from Buttock Line 10.0 thru 12.5 with an 0.125 Inch diameter surface pencil probe at 200 kHz. (Refer to the figure titled Spar Dimensions after Table 1.) • Scan direction must be with an inboard to outboard direction. • Use of a non-metallic straight edge as a guide will help ensure there is not a fore-aft motion of the probe. • Probe one small section at a time. • Move the probe in 0.125 Iinch increments. • Overlap each section by 0.25 Inch. • Extend 1 Inch beyond the Kick Area. (1) Look for a sharp response of 10-percent screen height or more which may indicate corrosion or fatigue cracking or both. F. If you find one or more cracks, further flight is NOT permitted. You must replace the carry-thru spar before further flight. 8. Provide the results of the detailed visual and eddy current inspections to Textron Aviation, Team Structures. Use the Carry-Thru Spar Inspection Report form and pictures as applicable. Telephone number and email address are provided on the form. NOTE: The Carry-Thru Spar Inspection Report form must be sent to Textron Aviation Team Structures to report all conditions, cracks, corrosion, or no cracks, no corrosion. Single Engine SERVICE LETTER MANDATORY SEL-57-08 9. Apply protective coatings to the carry-thru spar as follows: NOTE: The steps that follow are for the carry-thru spar located inside the fuselage. Rework can be from the removal and/or blending of corrosion, nicks, gouges, drill starts, or hardware damage, anything that would result in the exposure of bare metal by removal of the coatings. A. If there has been rework and the carry-thru spar was not entirely primed before the inspection: (1) Wipe the entire surface with clean wiping cloths wet with isopropyl alcohol. (a) Let the surface dry. (2) Apply Conversion coating (Bonderite M-CR 600RTU or allowable alternate) to the entire carry-thru spar surface following the manufacture directions for application and dry time. (3) Apply a epoxy primer (primer coat) to the entire surface following the manufacture directions for application and dry time. NOTE: Zinc chromate is an acceptable alternate to epoxy prime. (4) Go to Step 10. B. If there has been rework and the carry-thru spar was entirely primed before the inspection: (1) Wipe the areas with bare metal surface with clean wiping cloths wet with isopropyl alcohol. (a) Let the parts dry. (2) Apply Chemical Film Treatment (Bonderite M-CR 1132, formerly Alodine 1132 Touch-n-prep) to the areas with bare metal surface following the manufacture directions for application and dry time. (3) Apply a epoxy primer (primer coat) to the bare metal surface following the manufacture directions for application and dry time. NOTE: Airplanes that have a zinc chromate coating, it is allowable to use zinc chromate coating or epoxy primer for the touch-up areas. It is not required to remove zinc chromate coating for the application of epoxy primer. (4) Go to Step 10. C. If there was not rework and the carry-thru spar was not entirely primed before the inspection: (1) Wipe the entire surface with clean wiping cloths wet with isopropyl alcohol. (a) Let the surface dry. (2) Apply Conversion coating (Bonderite M-CR 600RTU or allowable alternate) to the entire carry-thru spar surface following the manufacture directions for application and dry time. (3) Apply a epoxy primer (primer coat) to the entire surface following the manufacture directions for application and dry time. NOTE: Zinc chromate is an acceptable alternate to epoxy primer. (4) Go to Step 10. D. If there was not rework and the carry-thru spar was entirely primed before the inspection: NOTE: If the carry-thru spar has a zinc chromate coating, it is acceptable to keep the zinc chromate coating, it is not necessary to remove the zinc chromate coating. (1) Go to Step 10. SEL-57-08 Revision 2 - August 3, 2020 Page 9 SEL-57-08 Page 10 Revision 2 - August 3, 2020 Single Engine SERVICE LETTER MANDATORY SEL-57-08 10. Apply Corrosion Inhibiting Compound (CIC) to the entire surface of the carry-thru spar that is accessible in the fuselage as follows: (Refer to SEL-51-01 Standard Practices - Structures - Use of Corrosion Inhibiting Compounds.) NOTE: SEL-51-01 is a resource that provides additional detailed information about the application process of CIC such as equipment, facility, cleaning, masking, and application processes. A. Mask areas around the carry-thru spar areas to prevent over spray of the CIC. B. Spray aerosol with extension tube to minimize over spray. C. Apply the CIC in one full wet coat. D. Some sag/run is acceptable. A spot of significant sag/run needs to be cleaned by MPK (methyl propyl ketone) wiping and the CIC shall be reapplied. E. Wet film thickness of CIC is approximately 1 to 2 mils for Cor-Ban 23. NOTE: The coating should be tack-free after two to three hours. F. After the CIC coating is tack-free, remove the masking from around the application area. G. Let the CIC coating cure with a minimum cure temperature no less than 50 degrees F. 11. Install removed utility systems, oxygen systems, headliner and upholstery that was removed to access the carry-thru spar. (Refer to the applicable Model Service or Maintenance Manual.) NOTE: The installation of the foam padding to the bottom of the carry-thru spar is optional however; the headliner final fit may differ if the foam padding is not installed. 12. Install the pilot and co-pilot seats if removed. (Refer to the applicable Model Service or Maintenance Manual.) 13. Remove the maintenance warning tags and connect the airplane battery. 14. Make an entry in the airplane logbook that states compliance and method of compliance with this service document. Single Engine SERVICE LETTER MANDATORY SEL-57-08 Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 1) SEL-57-08 Revision 2 - August 3, 2020 Page 11 SEL-57-08 Page 12 Revision 2 - August 3, 2020 Single Engine SERVICE LETTER MANDATORY SEL-57-08 Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 2) Single Engine SERVICE LETTER MANDATORY SEL-57-08 Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 3) SEL-57-08 Revision 2 - August 3, 2020 Page 13 SEL-57-08 Page 14 Revision 2 - August 3, 2020 Single Engine SERVICE LETTER MANDATORY SEL-57-08 Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 4) Single Engine SERVICE LETTER MANDATORY SEL-57-08 Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 5) SEL-57-08 Revision 2 - August 3, 2020 Page 15 SEL-57-08 Page 16 Revision 2 - August 3, 2020 Single Engine SERVICE LETTER MANDATORY SEL-57-08 Figure 2. PROCESS FLOW CHART (REFERENCE) (Sheet 1) Single Engine SERVICE LETTER MANDATORY SEL-57-08 MATERIAL INFORMATION No parts are required to complete this service document. SEL-57-08 Revision 2 - August 3, 2020 Page 17 Single Engine ATTACHMENT MANDATORY SEL-57-08 CARRY-THRU SPAR INSPECTION REPORT To: Page: 1 of ___ Pages Wichita Citation Service Center Includes this cover sheet Attn: Textron Aviation Team Structures 2121 S. Hoover Rd Registration No.: Wichita, Kansas 67209 Total Time in Service (Hrs.): Phone Number: 316-517-6061 email: structures@txtav.com Facility Name: Facility Address: From: Date: Airplane Serial Number: Owner's Name: Phone Number of Facility: Owner's Address: Fax Number of Facility: Owner's Phone Number: Owner's Fax Number: Please provide detailed and dimensioned descriptions of any crack(s) or corrosion. Attach pictures to this form as necessary. Comments/Notes: Cracks: Yes No (Circle One) Corrosion: Yes No (Circle One) Airplane Operation: Severe: Yes No (Circle One) Typical: Yes No (Circle One) Unknown: Yes No (Circle One) Any previously known or recorded blending or material removal on the carry-thru spar? Yes No (Circle One) List any Structural Supplemental Type Certificates (STC's) Installed: Single Engine OWNER ADVISORY SEL-57-08 TITLE WINGS - MODEL 210 CARRY-THRU SPAR ONE-TIME CORROSION INSPECTION TO: Cessna Model 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, P210N, T210N, 210R, P210R, T210R Aircraft Owner REASON The carry-thru spar can develop corrosion and cracks. Corrosion can propagate and lead to crack development. A crack in the carry-thru spar can progress to a point that a structural failure of the carry-thru spar can occur, resulting in loss of airplane control and/or wing separation. Non-compliance with this service letter may result in undetected corrosion and crack(s) in the carry-thru spar, which can result in structural failure of the carry-thru spar. COMPLIANCE WARNING: The Carry-Thru spar inspection presented in this service letter applies to airplanes listed in the Effectivity Section. The compliance time is for unmodified airplanes, and represents the maximum allowable time. Airplanes that have been modified to alter the airplane design, gross weight, or airplane performance, may need to inspect sooner. Examples include but not limited to the following common supplemental type certificates (STC’s) include vortex generators, wing cuffs, STOL kits, wing tips, and add-on wing fuel tanks. Contact the STC holder for revised inspection intervals. MANDATORY. Models 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M: This service letter must be accomplished within 20 flight hours or next Annual Inspection from date of receipt, whichever occurs first. Models 210N, P210N, T210N, 210R, P210R, T210R: This service letter must be accomplished within 200 flight hours or the next Annual Inspection from date of receipt, whichever occurs first. Airplanes which have complied with SEL-57-06 but not yet with this service letter do not need to do the inspection outlined in this service letter, however; these airplanes need to complete Steps 9 and 10 of this service letter within 200 flight hours or at the next annual inspection, whichever occurs first. Airplanes which have not complied with SEL-57-06 must complete this service letter by the compliance time listed for the appropriate model. After this service letter is complied with, the inspection outlined in SEL-57-06 does not need to be complied with. If the inspection form associated with this service letter or SEL-57-06 has not been sent in, send it in whether or not cracks or corrosion were found. Refer to the Carry-Thru Spar Inspection Report for contact information. LABOR HOURS For planning purposes only: Original Issue - November 1, 2019 SEL-57-08 Revision A - November 19, 2019 Page 1 of 2 Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800 This document contains technical data and is subject to U.S. export regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991 COPYRIGHT © 2019 SEL-57-08 Page 2 Revision A - November 19, 2019 Single Engine OWNER ADVISORY SEL-57-08 WORK PHASE LABOR-HOURS Inspection As Necessary WARRANTY None 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.txtavsupport.com to register.