Caravan SERVICE BULLETIN - Cessna

Caravan SERVICE BULLETINCAB-57-02

TITLE

WINGS - SPAR FITTING AND ATTACH BRACKET INSPECTION

EFFECTIVITY

MODEL SERIAL NUMBERS

208 20800524 thru 20800565

208B 208B2236 thru 208B2435, 208B5000 thru208B5114, 208B5116, 208B5118 thru 208B5122,208B5125, 208B5126, 208B5128 thru 208B5132,208B5134 thru 208B5143, 208B5146, 208B5148

thru 208B5151, 208B5153, 208B5154,208B5156, 208B5157

REASON

Cessna has received two reports of damage to the wing forward spar fitting and attach brackets. Thedamage was found during scheduled inspections.

DESCRIPTION

This service bulletin provides parts and instructions to do an inspection for damage on the wing forwardspar fittings and attach brackets. If damage is found to the attach bracket, the bracket must be repairedor replaced depending on the extent of damage. If damage is found to the wing forward spar fitting,the damage must be repaired.

COMPLIANCE

MANDATORY. This service bulletin must be accomplished within the next 200-hours or at the nextscheduled inspection, whichever occurs first.

CONSUMABLE MATERIAL

You must use the consumable materials that follow, or equivalent, to complete this service bulletin.

NAME NUMBER MANUFACTURER USE

Alodine U074093 Cessna Aircraft CompanyCessna Service Parts and Programs5800 East Pawnee, PO Box 1521Wichita, KS 67218

To apply to bare metal

Corrosion ResistantPrimer

K000912 Cessna Aircraft CompanyCessna Service Parts and Programs5800 East Pawnee, PO Box 1521Wichita, KS 67218

To apply to bare metal

Sealant U470642 Cessna Aircraft CompanyCessna Service Parts and Programs5800 East Pawnee, PO Box 1521Wichita, KS 67218

To fay surface seal matingsurfaces

Sealant U470638 Cessna Aircraft CompanyCessna Service Parts and Programs5800 East Pawnee, PO Box 1521Wichita, KS 67218

To wet install fasteners

CAB-57-02February 3, 2015 Page 1 of 14

Cessna Aircraft Company, Cessna 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 Statesin accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991

COPYRIGHT © 2015

CAB-57-02Page 2 February 3, 2015


APPROVAL

Cessna received FAA approval for the technical data in this publication that changes the airplane typedesign.

Cessna received EASA approval for the technical data in this publication that changes the airplanetype design.

WEIGHT AND BALANCE INFORMATION

Negligible

REFERENCES

Cessna Model 208 Maintenance Manual

Model 208 Nondestructive Testing Manual

Model 208 Structural Repair Manual

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

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 NOTCONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them.

2. Remove the fairings and panels that follow to get access to the inspection area. (Refer to the Model 208Maintenance Manual, Chapter 6, Access Plates and Panels Identification - Description and Operation.)

A. Remove the strap fairing assembly on the left and on the right wing.

B. 511AB

C. 525AB

D. 501AB

E. 611AB

F. 625AB

G. 601AB

3. (Refer to Figure 1, Detail A, Detail B, Detail C, and Detail D.) Do a visual inspection of the specifiedparts as follows:• 2622017-1 Left Aft Main Wing Spar Fitting• 2622017-3 Left Forward Main Wing Spar Fitting• 2622314-1 Left Forward Attach Bracket at WS 35.00• 2622314-3 Left Aft Attach Bracket at WS 35.00• 2622017-2 Right Aft Main Wing Spar Fitting• 2622017-4 Right Forward Main Wing Spar Fitting• 2622314-2 Right Forward Attach Bracket at WS 35.00• 2622314-4 Right Aft Attach Bracket at WS 35.00


• Four NAS464P6A35 Bolts.

A. (Refer to Figure 1, Detail C.) Look for all damage, including but not limited to drill runs and drill pits.

(1) if there is no damage, go to Step 5.

(2) If there is damage, go to Step 4.

4. (Refer to Figure 1.) Look at and do a measurement of the damage as follows:

A. (Refer to Figure 1, Detail C.) If there is a drill run or drill pit on the 2622314-1 (Left) and 2622314-2(Right) Forward Attach Bracket that is adjacent to the fastener that is common to the 2622247-7(Left) and 2622247-8 (Right) Upper Forward Spar Cap, remove the fastener that is common to the2622247-7 (Left) and 2622247-8 (Right) Upper Forward Spar Cap. You must remove it to make surethat you do the measurement for damage correctly.

B. If there is damage to the 2622314-1 (Left) or 2622314-2 (Right) Forward Attach Bracket or to the2622314-3 (Left) or 2622314-4 (Right) Aft Attach Bracket at WS 35.00, do a measurement of thedepth of the damage.

(1) If the depth of the damage does not exceed 0.020 inch, do a blending of the damage toremove it as follows:

(a) Locally blend the damage areas common to the 2622314-1 (Left) or 2622314-2 (Right)Forward Attach Bracket or to the 2622314-3 (Left) or 2622314-4 (Right) Aft AttachBracket.

(b) Use a 10 to 1 minimum width-to-depth ratio as you do the blending procedure.

(c) Blend only to the depth that is required to remove all surface damage. Do not blenddeeper than the minimum required to remove all surface damage.

(d) Make sure that the blending that you do is smooth and that there is a gradual transitionbetween the surface that has been blended and the surface that is adjacent to it.

(e) Polish the areas that you blended to a 63 μin Ra or smoother surface roughness.

(f) Polish only to the depth that is required to achieve the surface roughness that is specified.

(g) Make sure that the polishing that you do is smooth and that there is a gradual transitionbetween the surface that has been blended and the surface that is adjacent to it.

(h) Do a surface eddy current inspection of the 2622314-1 (Left) or 2622314-2 (Right)Forward Attach Bracket or to the 2622314-3 (Left) or 2622314-4 (Right) Aft AttachBracket for cracks in the blended locations. (Refer to the Model 208 NondestructiveTesting Manual, Part 6, Chapter 20, Eddy Current Surface Techniques - General.)

1 If there are no cracks or anomalies, continue with these AccomplishmentInstructions.

2 If there are cracks or anomalies, call Cessna Customer Support at 316-517-5800 forspecific instructions before you continue with these Accomplishment Instructions.

(2) If the depth of the damage exceeds 0.020 inch, you must remove and replace the 2622314-1(Left) or 2622314-2 (Right) Forward Attach Bracket or to the 2622314-3 (Left) or 2622314-4(Right) Aft Attach Bracket as follows:

(a) Defuel the airplane. (Refer to the Model 208 Maintenance Manual, Chapter 12, Fuel -Servicing.)

(b) Do the shoring of the wings. (Refer to the Model 208 Maintenance Manual, Chapter 7,Shoring - Maintenance Practices.)

CAB-57-02February 3, 2015 Page 3



(c) (Refer to Figure 1, Detail B.) Remove all fasteners that attach the 2622314-1 (Left) or2622314-2 (Right) Forward Attach Bracket or to the 2622314-3 (Left) or 2622314-4(Right) Aft Attach Bracket to the structure and discard the 2622314-1 (Left) or 2622314-2(Right) Forward Attach Bracket or to the 2622314-3 (Left) or 2622314-4 (Right) Aft AttachBracket.

(d) Match drill the holes that follow in each 2622314-1 (Left) or 2622314-2 (Right) ForwardAttach Bracket or to the 2622314-3 (Left) or 2622314-4 (Right) Aft Attach Bracket:• Two 0.374-inch diameter holes• 13 Number 21 (0.159-inch diameter) holes in 2622314-1 Left Forward Attach

Bracket.• 14 Number 21 (0.159-inch diameter) holes in 2622314-2 Right Forward Attach

Bracket.• Six Number 21 (0.159-inch diameter) holes in 2622314-3 (Left) or 2622314-4

(Right) Aft Attach Bracket• 17 Number 30 (0.128-inch diameter) holes in 2622314-3 (Left) or 2622314-4 (Right)

Aft Attach Bracket.

(e) Deburr and apply Alodine and epoxy primer to all bare metal.

(f) Put the 2622314-1 (Left) 2622314-2 (Right) Forward Attach Bracket in installationposition and install the six MS20470AD5-3.5A Rivets, 10 MS20470AD5-4.5A Rivets,and one MS20470AD5-9A Rivet wet with U470638 Sealant. (Refer to the Model 208Maintenance Manual, Chapter 20, Fuel, Weather and High-Temperature Sealing -Maintenance Practices.)

(g) Put the 2622314-3 (Left) 2622314-4 (Right) Aft Attach Bracket in installation positionand install the six MS20470AD5-3.5A Rivets, eight MS20470AD4-4.5A Rivets, andnine MS20470AD5-9A Rivets wet with U470638 Sealant. (Refer to the Model 208Maintenance Manual, Chapter 20, Fuel, Weather and High-Temperature Sealing -Maintenance Practices.)

(h) If you removed the rivet from the 2622247-1 Left Upper Forward Spar Cap, install a newMS20470AD5-9A Rivet wet with U470638 Sealant. (Refer to the Model 208 MaintenanceManual, Chapter 20, Fuel, Weather and High-Temperature Sealing - MaintenancePractices.)

(i) Install the four (two on each side of the airplane) kept or new NAS464P6A35 Bolts withthe kept washers and nuts that attach the 2622017-3 (Left) or 2622017-4 (Right) ForwardMain Wing Spar Fitting to the structure.

(j) Do a fay surface seal of all mating surfaces with U470642 Sealant. (Refer to the Model208 Maintenance Manual, Chapter 20, Fuel, Weather and High-Temperature Sealing -Maintenance Practices.)

C. (Refer to Figure 1, Detail D and View A-A.) If there is damage to the 2622017-3 (Left) or 2622017-4(Right) Forward Main Wing Spar Fitting, do a measurement of the depth of the damage.

(1) If the damage is not in the areas that you are allowed to blend in Figure 1, Detail D, callCessna Customer Support at 316-517-5800 for specific instructions before you continue withthese Accomplishment Instructions.

(2) If the depth of the damage is more than 0.100-inch, call Cessna Customer Support at316-517-5800 for specific instructions before you continue with these AccomplishmentInstructions.

(3) If the damage is in the areas where you are allowed to blend and the depth of the damagedoes not exceed 0.050 inch, do a blending of the damage to remove it as follows:

(a) Locally blend the damage areas common to the 2622017-3 (Left) 2622017-4 (Right)Forward Main Wing Spar Fitting.





(e) If the area that you blend will be installed adjacent to the head of the bolt, make sure thatthe head of the bolt will fit flat against the blended area.

(f) Polish the areas that you blended to a 63 μin Ra or smoother surface roughness.

(g) Polish only to the depth that is required to achieve the surface roughness that is specified.


(i) Make sure that the polishing that you do is smooth and that there is a gradual transitionbetween the surface that has been blended and the surface that is adjacent to it.

(j) Do a surface eddy current inspection of the 2622017-3 (Left) 2622017-4 (Right) ForwardMain Wing Spar Fitting for cracks in the blended locations. (Refer to the Model 208Nondestructive Testing Manual, Part 6, Chapter 20, Eddy Current Surface Techniques -General.)



(4) If the depth of the damage exceeds 0.050 inch but does not exceed 0.100 inch, do as follows:

NOTE: This repair requires ultrasonic inspection.

(a) Locally blend the damage areas common to the 2622017-3 (Left) 2622017-4 (Right)Forward Main Wing Spar Fitting.












(j) Do a surface eddy current inspection of the 2622017-3 (Left) 2622017-4 (Right) ForwardMain Wing Spar Fitting for cracks in the blended locations. (Refer to the Model 208Nondestructive Testing Manual, Part 6, Chapter 20, Eddy Current Surface Techniques -General.)



(k) Do an ultrasonic thickness inspection of the remaining material thickness at the damagelocations in the 2622017-3 (Left) 2622017-4 (Right) Forward Main Wing Spar Fitting.(Refer to the Model 208 Nondestructive Testing Manual, Part 4, Chapter 20, UltrasonicInspection.)

1 If the material thicknesses are no less than the values shown in Figure 1 at thespecified locations, continue with these Accomplishment Instructions.

2 If the material thicknesses are less than the values shown in Figure 1 at thespecified locations, call Cessna Customer Support at 316-517-5800 for specificinstructions before you continue with these Accomplishment Instructions.

D. If there is damage to the 2622017-1 (Left) or 2622017-2 (Right) Aft Main Wing Spar Fitting, doa measurement of the depth of the damage.

(1) If the damage is not in the areas that you are allowed to blend in Figure 1, Detail D and ViewA-A, call Cessna Customer Support at 316-517-5800 for specific instructions before youcontinue with these Accomplishment Instructions.

(2) If the depth of the damage is more than 0.100-inch, call Cessna Customer Support at316-517-5800 for specific instructions before you continue with these AccomplishmentInstructions.

(3) If the damage is in the areas where you are allowed to blend and the depth of the damagedoes not exceed 0.050 inch, do a blending of the damage to remove it as follows:

(a) Locally blend the damage areas common to the 2622017-1 (Left) 2622017-2 (Right) AftMain Wing Spar Fitting.










(j) Do a surface eddy current inspection of the 2622017-1 (Left) or 2622017-2 (Right) AftMain Wing Spar Fitting for cracks in the blended locations. (Refer to the Model 208Nondestructive Testing Manual, Part 6, Chapter 20, Eddy Current Surface Techniques -General.)



(4) If the depth of the damage exceeds 0.050 inch but does not exceed 0.100 inch, do as follows:

NOTE: This repair requires ultrasonic inspection.

(a) Locally blend the damage areas common to the 2622017-1 (Left) 2622017-2 (Right) AftMain Wing Spar Fitting.









(j) Do a surface eddy current inspection of the 2622017-1 (Left) 2622017-2 (Right) AftMain Wing Spar Fitting for cracks in the blended locations. (Refer to the Model 208Nondestructive Testing Manual, Part 6, Chapter 20, Eddy Current Surface Techniques -General.)



(k) Do an ultrasonic thickness inspection of the remaining material thickness at the damagelocations in the 2622017-1 (Left) 2622017-2 (Right) Aft Main Wing Spar Fitting. (Refer tothe Model 208 Nondestructive Testing Manual, Part 4, Chapter 20, Ultrasonic Inspection.)

1 If the material thicknesses are no less than the values shown in Figure 1 at thespecified locations, continue with these Accomplishment Instructions.

2 If the material thicknesses are less than the values shown in Figure 1 at thespecified locations, call Cessna Customer Support at 316-517-5800 for specificinstructions before you continue with these Accomplishment Instructions.

E. If you have not replaced all NAS464P6A35 Bolts that have damage, you must replace them beforesuccessful completion of this service bulletin.




5. Install the panels that follow. (Refer to the Model 208 Maintenance Manual, Chapter 6, Access Plates andPanels Identification - Description and Operation.):

A. Install the strap fairing assembly on the left and on the right wing.

B. 511AB

C. 525AB

D. 501AB

E. 611AB

F. 625AB

G. 601AB

6. If you did the shoring of the wings, remove the wing shoring. (Refer to the Model 208 MaintenanceManual, Chapter 7, Shoring - Maintenance Practices.)

7. Remove the maintenance warning tags and connect the airplane battery.

8. If you defueled the airplane, add fuel to the airplane. (Refer to the Model 208 Maintenance Manual,Chapter 12, Fuel - Servicing.)

9. Make an entry in the airplane logbook that states compliance and method of compliance with thisservice bulletin.


Figure 1. Wing Forward Spar Fitting and Attach Bracket Inspection (Sheet 1)
















MATERIAL INFORMATION

The parts below may be necessary for the repair.

NEW P/N QUANTITY KEY WORD OLD P/N INSTRUCTIONS/DISPOSITION

MS20470AD5-3.5A 24 Rivet Same Discard

MS20470AD5-4.5A 36 Rivet Same Discard

MS20470AD5-9A 23 Rivet Same Discard

NAS464P6A35 4 Bolt Same Discard

2622314-1 1 Left Forward Attach Bracket at WS35.00

Same Discard

2622314-2 1 Right Forward Attach Bracket atWS 35.00

Same Discard

2622314-3 1 Left Aft Attach Bracket at WS 35.00 Same Discard

2622314-4 1 Right Aft Attach Bracket at WS35.00

Same Discard

Caravan OWNER ADVISORYCAB-57-02

TITLEWINGS - SPAR FITTING AND ATTACH BRACKET INSPECTION

TO:Cessna 208/208B Owner

REASONThis owner advisory is to inform you that CAB-57-02 has been issued.

Cessna has received two reports of damage to the wing forward spar fitting and attach brackets. Thedamage was found during scheduled inspections.

DESCRIPTIONCAB-57-02 provides parts and instructions to do an inspection for damage on the wing forward sparfittings and attach brackets. If damage is found to the attach bracket, the bracket must be repaired orreplaced depending on the extent of damage. If damage is found to the wing forward spar fitting, thedamage must be repaired.

COMPLIANCEMANDATORY. This service bulletin must be accomplished within the next 200-hours or at the nextscheduled inspection, whichever occurs first.

LABOR HOURS1.5 man-hours are required to do the inspection.

If necessary, 0.3 man-hours are required to do a measurement of the depth of damage of the 2622017-3(Left) or 2622017-4 (Right) Forward Main Wing Spar Fitting.

If necessary, 0.3 man-hours are required to do a measurement of the depth of damage of the 2622314-1(Left) 2622314-2 (Right) Forward Attach Bracket.

If necessary, 0.3 man-hours are required to do a measurement of the depth of damage of the 2622017-1(Left) or 2622017-2 (Right) Aft Main Wing Spar Fitting.

If necessary, 8.0 man-hours are required to do a remove and replace of the 2622314-1 (Left) or2622314-2 (Right) Forward Attach Bracket.

If necessary, 0.7 man-hour are required to do a blending, NDI and paint touch-up of each drill mark on theWing Spar Fitting and/or Attach Fitting.

WARRANTYFor all airplanes identified within the serial effectivity:

1.5 man-hours will be provided to do the inspection.

If necessary, 0.3 man-hours will be provided to do a measurement of the depth of damage of the2622017-3 (Left) or 2622017-4 (Right) Forward Main Wing Spar Fitting.

If necessary, applicable parts credit and a labor allowance credit of 0.3 man-hours per airplane will beprovided to 2622314-1 (Left) 2622314-2 (Right) Forward Attach Bracket.

If necessary, 0.3 man-hours will be provided to do a measurement of the depth of damage of the2622017-1 (Left) or 2622017-2 (Right) Aft Main Wing Spar Fitting.

Original Issue - February 3, 2015 CAB-57-02Revision 2 - June 5, 2019 Page 1 of 2

Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800This 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 © 2015

CAB-57-02Page 2 Revision 2 - June 5, 2019

Caravan OWNER ADVISORYCAB-57-02

If necessary, 8.0 man-hours will be provided to do a remove and replace of the 2622314-1 (Left) or2622314-2 (Right) Forward Attach Bracket.

If necessary, 0.7 man-hour will be provided to do a blending, NDI and paint touch-up of each drill mark onthe Wing Spar Fitting and/or Attach Fitting.

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 CaravanAuthorized Service Facility within 30 calendar days of service bulletin compliance before the creditexpiration dates shown below.

Domestic ............................................... February 3, 2016International .......................................... February 3, 2016

Please contact a Cessna Authorized Service Facility for detailed information and arrange to have Cessnaservice bulletin CAB-57-02 accomplished on your airplane.

Special Note to Authorized Service Facilities:

When you complete the warranty claim, the labor allowance claimed shall be itemized for each aboveaction completed.

Access the QR code for the instructional video link that follows or use the URL address:

Please access the links that follow. They provide information that may help you in the accomplishmentof this service bulletin:

http://servicecdn.txtav.com/CAB-57-02/CAB-57-02.html

Measuring a Dent, Scratch or Gouge Using a Depth Micrometer:

https://www.youtube.com/watch?v=3GyepUSdJic

RMS Surface Roughness:

https://www.youtube.com/watch?v=lhVBJoqM_tk&feature=youtu.be

NOTE: As a convenience, service documents are now available online to all our customers through asimple, free-of-charge registration process. If you would like to sign up, please visit the "CustomerSupport Login" link at www.Cessna.com to register.

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Caravan SERVICE BULLETIN - Cessna