Mandatory: Shall be accomplished within the next 100 hours of operation or 12 months, whichever occurs first.

Transcription

1 Single Engine SERVICE BULLETIN/SAFETY DIRECTIVE June 24, 2013 TITLE FASTENER EDGE DISTANCE INSPECTION EFFECTIVITY Model Serial Numbers thru REASON Cessna has determined that, on some airplanes, there may not be sufficient edge distance for the five rivets that attach the Rib to the aft edge of the leading edge structure in the left wing. DESCRIPTION The installation of the suspect five rivets is checked to make sure that there is sufficient edge distance. If there is not sufficient edge distance, the flange and doubler are repaired and a new rib and a repair strap are installed. COMPLIANCE Mandatory: Shall be accomplished within the next 100 hours of operation or 12 months, whichever occurs first. APPROVAL Cessna Aircraft Company approval has been obtained on technical data in this publication that affects airplane compliance to ASTM standards. TYPE OF MAINTENANCE Heavy CERTIFICATION Airframe and Powerplant Mechanic Repair Station Page1of19 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) , Facsimile (316) COPYRIGHT 2013

2 REFERENCE Model 162 Maintenance Manual Model 162 Illustrated Parts Catalog NOTE: Make sure all publications used are complete and current. Refer to NOTE: 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 required per ASTM consensus standards and, if required, 14 CFR Part OTHER PUBLICATIONS AFFECTED Model 162 Maintenance Manual Model 162 Illustrated Parts Catalog MATERIAL AVAILABILITY The following parts are available from Cessna Service Parts and Programs through an appropriate Cessna Authorized Service Facility. Part Number Description Qty/Airplane MS20470AD3-6A Rivet As Required Leading Edge Skin As Required Rib As Required Page 2 June 24, 2013

3 ACCOMPLISHMENT INSTRUCTIONS WEIGHT AND BALANCE INFORMATION Negligible MATERIAL INFORMATION The parts below may be necessary: NEW P/N QUANTITY DESCRIPTION OLD P/N DISPOSITION MS20470AD3-6A 5 Rivet Leading Edge Skin Same Discard Rib Same Discard The material below may be necessary: NAME NUMBER MANUFACTURER USE Aluminum, 2024-T3 clad sheet (0.020 inch thick, 0.70 inch wide) Instructions 1. Prepare the airplane for maintenance. S Cessna Aircraft Company Cessna Service Parts and Programs 5800 East Pawnee, PO Box 1521 Wichita, KS A. Make sure that all electrical switches are in the OFF position. B. Disconnect electrical power from the airplane. (1) Electrically ground the airplane. To make the spar reinforcement repair strap (2) If the optional ground service receptacle is installed, disconnect external electrical power. (3) Remove the engine cowl. (Refer to the Model 162 Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) (4) Disconnect the airplane battery. C. Attach the maintenance warning tags to the battery and the ground service receptacle (if installed) that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" writtenonthem. D. Disengage the SEC PWR circuit breaker, found on the instrument panel. NOTE: If you will accomplish this service bulletin in conjunction with SB Revision 2, go to Step 2 of this service bulletin. If you have already accomplished SB Original Issue, Revision 1, or Revision 2, go to Step 3 of this service bulletin. 2. (Refer to Figure 1.) For airplanes that will accomplish this service bulletin in conjunction with SB Revision 2, do as follows: A. Accomplish Step 1 through Step 9 of SB Revision 2. June 24, 2013 Page 3

4 B. (Refer to Figure 1, View A-A (Inspection).) Do an inspection for sufficient edge distance at the five suspect rivet locations shown. (1) If there is an edge distance for the five rivets of no less than 0.15 inch from all edges of the Spar Flange, do as follows: (a) Go to Step 10 of SB Revision 2 and finish the accomplishment of that bulletin. (b) Then go to Step 4 of this service bulletin. (2) If there is an edge distance for one or more of the five rivets of less than 0.15 inch, do as follows: (a) Remove and discard Rib. (b) (Refer to Figure 1, Detail B After Trim.) Trim and then smoothly blend out the five discrepant fastener holes from the Spar Flange, Waffle Doubler, and Lower Wing Skin. Do not trim more than inch from the Spar Flange, Waffle Doubler, or the Lower Wing Skin. Blend at a minimum 10 to 1 taper ratio with a 2.00-inch maximum length. The trimmed area from the outer edge of the two outermost discrepant fastener holes must not exceed 2.00 inches. Keep a minimum edge distance for all adjacent fasteners of 1.5 times the diameter of the fastener hole. Make sure that there is a 125 surface roughness finish or better on all trimmed edges. (c) Make and install a spar reinforcement repair strap as follows: 1 (Refer to Figure 1, View A-A Looking Up During Modification With Reinforcement Strap in Position and Detail B Before Trim and After Trim.) From the inch thick, 2024-T3 clad sheet Aluminum, make a spar reinforcement repair strap that is 0.70 inch wide and long enough to pick up the five adjacent fasteners on each side of the trimmed area and keep a minimum 0.20-inch edge distance for end fasteners (approximately 13.5 inches long). 2 (Refer to Figure 1, View A-A During Modification Without Reinforcement Strap in Position.) Outboard of the removed Rib, remove the three rivets shown from the spar flange and the leading edge skin. NOTE: (Refer to Figure 1, View A-A During Modification With Reinforcement Strap in Position.) You will install five MS20470AD3-6A Rivets outboard of the Rib. Three will be installed in existing holes in the spar flange, and you will drill two new holes in the spar flange. You must remove and discard the three rivets that are in the existing holes. 3 (Refer to Figure 1, View A-A During Modification Without Reinforcement Strap in Position.) From the spar flange and the leading edge skin, remove the five rivets that are inboard of the removed Rib. 4 (Refer to Figure 1, View A-A During Modification With Reinforcement Strap in Position and View B-B After Modification.) Put the spar reinforcement repair strap in position outside the wing skin and inside the leading edge skin. 5 (Refer to Figure 1, View A-A During Modification With Reinforcement Strap in Position and Detail B After Trim.) Inboard of the Rib, match drill five No. 40 (0.098-inch diameter) holes in the spar reinforcement repair strap. 6 Outboard of the Rib, use the three holes from the removed rivets to match drill three No. 40 (0.098-inch diameter) holes in the spar reinforcement repair strap. Page 4 June 24, 2013

5 (d) (e) (f) (g) 7 Outboard of the Rib, make marks for and match drill two new No. 40 (0.098-inch diameter) holes in the spar flange, spar reinforcement repair strap, and leading edge skin. 8 To replace the holes that were not drilled with sufficient edge distance, make marks for and drill five new holes for the five new rivets. Keep a minimum edge distance of 0.15 inch. 9 Deburr and apply Alodine to bare metal. Install the five outboard MS20470AD3-6A Rivets that attach the spar reinforcement repair strap to the leading edge wing skin and the spar flange. Install the Rib. Go to Step 10 of SB Revision 2 and finish the accomplishment of that bulletin. Then go to Step 4 of this service bulletin. 3. (Refer to Figure 2.) For airplanes that have already accomplished SB Original Issue, Revision 1, or Revision 2, do as follows: A. (Refer to Figure 2, View A-A Inspection.) Do an inspection for sufficient edge distance at the five suspect rivet locations as follows: (1) Remove the Access Panel that is installed in the left wing adjacent to the pitot tube. (2) On the inside of the wing, find the row of rivets installed in the Spar Flange that is inboard of the five suspect rivets. (3) Measure the distance between the line that defines the centers of the holes for this row of rivets and the forward edge of the Spar Flange. Record that distance as Distance A. (4) On the outside of the wing, measure the distance between the line that defines the centers of the holes for the five suspect rivets and the line that defines the centers of the row of rivets installed in the Spar Flange that are inboard of the five suspect rivets. Record that distance as Distance B. NOTE: Tape may be used to establish a reference line for the measurement. Install a piece of tape that picks up the centerline of the fastener row inboard and outboard of the suspect fasteners. (5) Subtract Distance B from Distance A. (a) (b) If the number is 0.18 inch or more, go to Step 4 of this service bulletin. If the number is less than 0.18 inch, go to Step 3.B of this service bulletin. B. Do a second inspection to see if there is sufficient edge distance for the row of five suspect rivets of 0.15 inch or more. (1) Remove rivets that attach the skin to the wing structure until you can move back sufficient wing skin to do a direct inspection for edge distance. (2) Measure the distance between the line that defines the centers of each of the five suspect rivets and the forward edge of the Spar Flange. (a) (b) If the edge distance is 0.15 inch or more, do as follows: 1 Use new rivets of the same type and size as the originals to install the wing skin that youremovedfromthewingstructure. 2 Install the Access Panel with the kept fasteners. 3 Go to Step 4 of this service bulletin. If the edge distance is less than 0.15 inch, go to Step 3.C of this service bulletin. June 24, 2013 Page 5

6 C. Do the wing repair as follows: (1) Remove and keep the Pitot Static Weld Assembly with the Union (or the Pitot Bond Assembly) and attachment hardware. Do not break the connection between the Pitot Static Weld Assembly and the Union. Remove the pitot line from the union and not the union from the pitot static weld assembly. (Refer to the Model 162 Maintenance Manual, Chapter 34, Pitot and Static Systems - Maintenance Practices.) (2) Move the pitot line tubing to a position in the wing where you will not do damage to the tubing during modification of the leading edge skin. (3) Move the electrical wiring in the wings to a position outboard of the modification area to make sure that you will not do damage to the wiring during removal and installation of the leading edge skin. (4) Remove and discard the Leading Edge Skin that was installed in SB Keep the four Shims. (a) As you remove the rivets that go into the rib, temporarily secure the rib to make sure that it does not move from the correct position. (b) Mark a line on the structure that shows the position of the rib to make sure that you install it in the correct position when you attach the new skin to the rib. (5) Remove and discard the Rib. (6) (Refer to Figure 2, Detail B After Trim.) Trim and then smoothly blend out the five discrepant fastener holes from the Spar Flange, Waffle Doubler, and Lower Wing Skin. Do not trim more than inch from the Spar Flange, Waffle Doubler, or the Lower Wing Skin. Blend at a minimum 10 to 1 taper ratio with a 2.00-inch maximum length. The trimmed area from the outer edge of the two outermost discrepant fastener holes must not exceed 2.00 inches. Keep a minimum edge distance for all adjacent fasteners of 1.5 times the diameter of the fastener hole. Make sure that there is a 125 surface roughness finish or better on all trimmed edges. (7) Make and install a spar reinforcement repair strap as follows: (a) (Refer to Figure 2, View A-A Looking Up During Modification With Reinforcement Strap in Position and Detail B Before Trim and After Trim.) From the inch thick, 2024-T3 clad sheet Aluminum, make a spar reinforcement repair strap that is 0.70 inch wide and long enough to pick up the five adjacent fasteners on each side of the trimmed area and wide enough to keep a minimum 0.20-inch edge distance for end fasteners (approximately 13.5 inches long). (b) (Refer to Figure 2, View A-A During Modification Without Reinforcement Strap in Position.) Outboard of the removed Rib, remove the three rivets shown from the spar flange and the leading edge skin. NOTE: (Refer to Figure 2, View A-A During Modification With Reinforcement Strap in Position.) You will install five MS20470AD3-6A Rivets outboard of the Rib. Three will be installed in existing holes in the spar flange, and you will drill two new holes in the spar flange. You must remove and discard the three rivets that are in the existing holes. (c) (Refer to Figure 2, View A-A During Modification Without Reinforcement Strap in Position.) From the spar flange and the leading edge skin, remove the five rivets that are inboard of the removed Rib. Page 6 June 24, 2013

7 (d) (Refer to Figure 2, View A-A During Modification With Reinforcement Strap in Position and View B-B After Modification.) Put the spar reinforcement repair strap in position outside the lower wing skin and inside the leading edge skin. (e) (Refer to Figure 2, View A-A During Modification With Reinforcement Strap in Position and Detail B After Trim.) Inboard of the Rib, match drill five No. 40 (0.098-inch diameter) holes in the spar reinforcement repair strap. (f) Outboard of the Rib, use the three holes from the removed rivets to match drill three No. 40 (0.098-inch diameter) holes in the spar reinforcement repair strap. (g) Outboard of the Rib, make marks for and match drill two new No. 40 (0.098-inch diameter) holes in the spar flange, spar reinforcement repair strap, and leading edge skin. (h) (Refer to Figure 2, View A-A During Modification With Reinforcement Strap in Position and Detail B After Trim.) Make marks for and drill five new holes for the five new rivets. Keep a minimum edge distance of 0.15 inch. (i) Deburr and apply Alodine to bare metal. (8) Install the five outboard MS20470AD3-6A Rivets that attach the spar reinforcement repair strap to the leading edge wing skin and the spar flange. (9) Put the new Rib, four kept Shims, and new Leading Edge Skin in position on the wing. (10) Find and backdrill fastener hole locations as necessary to replace all fasteners that you removed in the Rib, Spar Flange, Doubler, Lower Wing Skin, spar reinforcement strap, and Leading Edge Skin. Make sure that you keep the necessary edge distance for all fasteners. (11) Use new rivets of the same type and size as the originals to install the spar reinforcement repair strap, new Rib, four kept Shims, and new Leading Edge Skin. (12) Move the electrical wiring in the wing back to the correct position. (13) Move the pitot line tubing in the wing back to the correct position. (14) Install the Pitot Static Weld Assembly as follows: (Refer to the Model 162 Maintenance Manual, Chapter 34, Pitot and Static Systems - Maintenance Practices.) (a) Connect the Union to the pitot line. (Refer to the Model 162 Maintenance Manual, Chapter 34, Pitot and Static Systems - Maintenance Practices.) (b) With the kept attachment hardware, install the Pitot Static Weld Assembly to the wing structure. (Refer to the Model 162 Maintenance Manual, Chapter 34, Pitot and Static Systems - Maintenance Practices.) (c) Use vinyl tape to cover the drain hole, and make sure that the tape makes an airtight seal over the hole. (d) Connect the airplane battery. (e) Do a pitot-static system functional check. (Refer to the Model 162 Maintenance Manual, Chapter 34, Pitot and Static Systems - Maintenance Practices.) (f) Remove the tape that you used to make an airtight seal over the drain hole. (g) Disconnect the airplane battery. (15) Install the Access Panel with the kept fasteners. (16) Do a touch-up of the paint as necessary. 4. Remove the maintenance warning tags from the battery and the external power receptacle (if installed) and connect the battery. June 24, 2013 Page 7

8 5. Install the engine cowl. (Refer to the Model 162 Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) 6. Engage the SEC PWR circuit breaker. 7. Make an entry in the airplane logbook that states compliance and method of compliance with this service bulletin. NOTE: 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 required per ASTM consensus standards and, if required, 14 CFR Part Page 8 June 24, 2013

9 Figure 1. Fastener Edge Distance Inspection - Airplanes that have not Accomplished SB (Sheet 1) June 24, 2013 Page 9

10 Figure 1. Fastener Edge Distance Inspection - Airplanes that have not Accomplished SB (Sheet 2) Page 10 June 24, 2013

11 Figure 1. Fastener Edge Distance Inspection - Airplanes that have not Accomplished SB (Sheet 3) June 24, 2013 Page 11

12 Figure 1. Fastener Edge Distance Inspection - Airplanes that have not Accomplished SB (Sheet 4) Page 12 June 24, 2013

13 Figure 1. Fastener Edge Distance Inspection - Airplanes that have not Accomplished SB (Sheet 5) June 24, 2013 Page 13

14 Figure 2. Fastener Edge Distance Inspection - Airplanes that have Accomplished SB (Sheet 1) Page 14 June 24, 2013

15 Figure 2. Fastener Edge Distance Inspection - Airplanes that have Accomplished SB (Sheet 2) June 24, 2013 Page 15

16 Figure 2. Fastener Edge Distance Inspection - Airplanes that have Accomplished SB (Sheet 3) Page 16 June 24, 2013

17 Figure 2. Fastener Edge Distance Inspection - Airplanes that have Accomplished SB (Sheet 4) June 24, 2013 Page 17

18 Figure 2. Fastener Edge Distance Inspection - Airplanes that have Accomplished SB (Sheet 5) Page 18 June 24, 2013

19 * * * * * * * June 24, 2013 Page 19

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21 Owner Advisory June 24, 2013 A Dear Skycatcher Owner: REASON This owner advisory is to inform you that has been issued. Cessna has determined that, on some airplanes, there may not be sufficient edge distance for the five rivets that attach the Rib to the aft edge of the leading edge structure in the left wing. provides a check of the five suspect rivets to make sure that there is sufficient edge distance. If there is not sufficient edge distance, the flange and doubler are repaired and a new rib and a repair strap are installed. COMPLIANCE Compliance is Mandatory: Shall be accomplished within the next 100 hours of operation or 12 months, whichever occurs first. NOTE: 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 required per ASTM consensus standards and, if required, 14 CFR Part LABOR HOURS Airplanes that accomplish in conjunction with SB (Revision 2 or later revision): Time required is negligible to do the inspection. If necessary, 6.0 man-hours to do the repair. Airplanes that have accomplished SB (any revision level) and have already had a claim processed and adjudicated and now must accomplish : 0.7 man-hour to do the first inspection. If necessary, 3.0 man-hours to do the second inspection. If necessary, 2.0 man-hours to do the pitot tube removal and installation and the leak and operational checks of the pitot static system. If necessary, 10.0 man-hours to do the repair. Page1of2 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) , Facsimile (316) COPYRIGHT 2013

22 WARRANTY Airplanes that accomplish in conjunction with SB (Revision 2 or later revision): No parts credit or labor allowance credit will be provided to do the inspection. If necessary, applicable parts credit, a miscellaneous parts credit of $1.00 for rivets, and a labor allowance credit of 6.0 man-hours per airplane will be provided to do the repair. Airplanes that have accomplished SB (any revision level) and have already had a claim processed and adjudicated and now must accomplish : A labor allowance credit of 0.7 man-hour per airplane will be provided to do the first inspection. If necessary, a miscellaneous parts credit of $1.00 for rivets, and a labor allowance credit of 3.0 man-hours per airplane will be provided to do the second inspection. If necessary, 2.0 man-hours per airplane will be provided to do the pitot tube removal and installation and the leak and operational checks of the pitot static system. If necessary, applicable parts credit, a miscellaneous parts credit of $1.00 for rivets, and a labor allowance credit of 10.0 man-hours per airplane will be provided to do the repair. Freight will be credited at the most economical method unless pre-approved by Cessna. For pre-approval contact Cessna Service Parts and Programs Warranty Administration at Telephone: , Fax: or cpd2claims@cessna.textron.com. To receive credit, the work must be completed and a Warranty Claim submitted by a Cessna Single Engine Authorized Service Facility within 30 calendar days of Service Bulletin compliance before the credit expiration dates shown below. Domestic... June24,2014 International... June24,2014 Special Note to Authorized Service Facilities: When you complete the Warranty Claim, the labor allowance claimed shall be itemized for each above action completed. Please contact a Cessna Single Engine Authorized Service Facility for detailed information and arrange to have Cessna Service Bulletin accomplished on your airplane. Access the QR code for the instructional video link that follows or use the URL address: Select this link: Figure 1. Fastener Edge Distance Inspection 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 to register. A Page 2 June 24, 2013