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Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08
REVISION
TRANSMITT AL This sheet transmits Revision 1 to SEL - 57 - 08 , which:
A.
Adds additional information to the
COMPLIANCE section and clarify inspection compliance and references to SEL - 57 -
06.
NOTE:
This revision replaces the original issue of SEL - 57 - 08 in its entirety .
REVISION
COMPLIANCE NO EFFECT .
Airplanes previously modified by this service letter are not af fected by this revision.
LOG OF
REVISIONS Original Issue November 1 , 2019 Revision 1 November 19 , 2019 Original Issue - November 1 , 2019 SEL - 57 - 08 Revision 1 - November 19 , 2019 Page 1 of 1 T extron A viation Customer Service , P .O.
Box 7706 , Wichita , KS 67277 , U.S.A.
1 - 316 - 517 - 5800
COPYRIGHT © 2019
No text on this page: it may be a figure. Open the PDF to see it.
Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08 TITLE WINGS - MODEL 210 CARR Y - THRU SP AR ONE - TIME
CORROSION
INSPECTION
EFFECTIVITY MODEL SERIAL
NUMBERS 210G 21058819 thru 21058936 T210G T210 - 0198 thru T210 - 0307 210H 21058937 thru 21059061 T210H T210 - 0308 thru T210 - 0392 210J 21059062 thru 21059199 T210J 21058140 , T210 - 0393 thru T210 - 0454 210K 21059200 thru 21059502 T210K 21059200 thru 21059502 210L 21059503 thru 21061573 T210L 21059503 thru 21061573 210M 21061574 thru 21062954 T210M 21061574 thru 21062954 210N 21062955 thru 21064897 P210N P21000001 thru P21000834 T210N 21062955 thru 21064897 210R 21064898 thru 21065009 P210R P21000835 thru P21000874 T210R 21064898 thru 21065009 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 .
DESCRIPTION This service document provides instructions and repair criteria to do a detailed inspection of the carry - thru spar to inspect for corrosion and / or cracks.
Original Issue - November 1 , 2019 SEL - 57 - 08 Revision 1 - November 19 , 2019 Page 1 of 16 T extron A viation 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 1 - November 19 , 2019 Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08
COMPLIANCE W ARNING:
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 , ST OL kits , wing tips , and add - on wing fuel tanks.
Contact the STC holder for revised inspection intervals.
MANDA T OR Y .
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.
A service document published by T extron A viation may be recorded as completed in an aircraft log only when the following requirements are satisfied:
1) The mechanic must complete all of the instructions in the service document , including the intent therein.
2) The mechanic must correctly use and install all applicable parts supplied with the service document kit.
Only with written authorization from T extron A viation can substitute parts or rebuilt parts be used to replace new parts.
3) The mechanic or airplane owner must use the technical data in the service document only as approved and published.
4) The mechanic or airplane owner must apply the information in the service document only to aircraft serial numbers identified in the Effectivity section of the document.
5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations.
No individual or corporate organization other than T extron A viation is authorized to make or apply any changes to a T extron A viation - issued service document or flight manual supplement without prior written consent from T extron A viation.
T extron A viation is not responsible for the quality of maintenance performed to comply with this document , unless the maintenance is accomplished at a T extron A viation - owned Service Center .
Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08
CONSUMABLE MA TERIAL Y ou must use the consumable materials that follow , or their equivalent , to complete this service document.
NAME NUMBER MANUF
ACTURER USE Color Chemical Film T reatment U074093 (Alodine 1 132 T ouch n Prep) T extron A viation Parts Distribution 7121 Southwest Boulevard Wichita , KS 67215 T o prepare bare aluminum surface for intermediate primer .
Corrosion Resistant Primer K000574 (2oz Kit) T extron A viation Parts Distribution T ouch - up primer kit.
Cor - Ban 23 COR - BAN - 23 (U074098) (12oz aerosol) T extron A viation Parts Distribution Corrosion Inhibiting Compound coating.
Formit - 18 Fan Formit - 18 T extron A viation Parts Distribution Nozzle for Cor - Ban 23 application.
Primer , Epoxy Polyamide (Primer) K000479 (2 Gal Kit) T extron A viation Parts Distribution Large primer kit.
Aluminum oxide paper or cloth (high purity) - 180 or 220 , and 320 grit Commercially A vailable For paint / corrosion removal and surface preparation before painting.
Conversion Coating Bonderite M - CR 600R TU Commercially available Conversion Coating of bare metal before intermediate primer .
Extreme Simple Green Aircraft and Precision Cleaner Commercially A vailable Initial cleaning of soiled surface.
Isopropyl Alcohol Commercially A vailable T ype I Cleaning Solvent for surface cleaning prior to painting.
Methyl Propyl Ketone Commercially A vailable 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:
T extron A viation has tested and approved Cor - Ban 35 and ARDROX A V -
8.
These products may be used in place of Cor - Ban 23 at the owners discretion.
T OOLING NAME NUMBER MANUF
ACTURER USE 10X Magnifying Lense Commercially A vailable For detailed visual inspection of carry - thru spar .
Micrometer (depth gauge style) Commercially A vailable T o 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.
SEL - 57 - 08 Revision 1 - November 19 , 2019 Page 3
SEL - 57 - 08 Page 4 Revision 1 - November 19 , 2019 Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08
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 Cessna Model P210 Series (1985 - 1986) Service Manual Inspection T ime 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:
T o make sure all publications used are complete and current.
Refer to www .txtavsupport.com.
PUBLICA TIONS
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.
Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08
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 T able
1.)
A.
(Refer to Figure 1 , Sheets 4 and
5.)
If stress corrosion cracking or exfoliation corrosion (flaking) of the spar is found , contact T extron A viation T eam 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 T extron A viation 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 af fected region.
(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 T ABLE 1 for the specific spar feature , contact T extron A viation T eam 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 T ABLE 1 , go to Step
8.
(c) If material removed is greater than
0.010 but less than what is listed in T ABLE 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.
SEL - 57 - 08 Revision 1 - November 19 , 2019 Page 5
SEL - 57 - 08 Page 6 Revision 1 - November 19 , 2019 Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08 T ABLE 1 REP AIR
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 W eb Radius
(1) Center Line to
16.5
0.030
(2) Forward or Aft facing web radii 5 Spar W eb
(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 T extron A viation.
Example:
W eb blend and a lower spar cap blend cannot be combined at same Buttock Line location without contacting T extron A viation.
(2) The carry - thru spar must be replaced if the blend limit is exceeded in this area.
SP AR
DIMENSIONS
Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08 SP AR DET AIL 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 T extron A viation Structures.
D.
If no corrosion is found on the carry - thru spar , go to Step
8.
7.
(Refer to Figure 1 , V iew 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 F AA Certified Repair Station , an A&P Mechanic may supervise the inspection and make the appropriate logbook entry .
• T echnician must be at least Level 2 certified.
• Eddy current inspection will cover the carry - thru spar where corrosion was blended and extend 1 Inch beyond the blended area and will also cover the lower cap spar Kick Area from Buttock Line
10.0 thru
12.5.
• Eddy current inspection will be with a
0.125 Inch probe.
• T echnician 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.)
SEL - 57 - 08 Revision 1 - November 19 , 2019 Page 7
SEL - 57 - 08 Page 8 Revision 1 - November 19 , 2019 Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08 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.
If you find one or more cracks , further flight is NOT permitted.
Y ou must replace the carry - thru spar before further flight.
8.
Provide the results of the detailed visual and eddy current inspections to T extron A viation , T eam Structures.
Use the Carry - Thru Spar Inspection Report form and pictures as applicable.
T elephone number and email address are provided on the form.
NOTE:
The Carry - Thru Spar Inspection Report form must be sent to T extron A viation T eam Structures to report all conditions , cracks , corrosion , or no cracks , no corrosion.
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 600R TU) 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.
(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 T reatment (Alodine 1
132) 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.
(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 600R TU) to the entire 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.
Single Engine SER VICE LETTER MANDA T OR Y SEL - 57 - 08
(4) Go to Step
10.
D.
If there was not rework and the carry - thru spar was entirely primed before the inspection:
(1) Go to Step
10.
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.
W et 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 .
1.
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 dif fer 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.
SEL - 57 - 08 Revision 1 - November 19 , 2019 Page 9
Single Beechcraft Hawker Engine SERVICE LETTER Cessna
TEXTRON AVIATION MANDATORY SEL-57-08 B21885 Carry-Thru Spar Wing Attachment Lug
DETAIL A 1210T1036 A1210X1037 Figure 1. CARRY-THRU SPAR INSPECTION (Sheet 1) SEL-57-08 Page 10 Revision 1 - November 19, 2019