ATTACHMENT DAMAGE REPORT FORM. Page: 1 of Pages Includes this cover sheet Date: (month/day/year) This form is for the: Left Wing: Right Wing: Other:

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1 ATTACHMENT DAMAGE REPORT FORM TO: Cessna Aircraft Company Propeller Aircraft Customer Service/Dept 753 P.O. Box 7706 Wichita, Kansas Phone Number: Fax Number: Page: 1 of Pages Includes this cover sheet Date: (month/day/year) FROM: Facility: Address: Phone No. Airplane Serial No. Utilization/Year (Hrs) Total Time In Service: (Hrs) Registration No. Total Landings/Cycles: Fax No. This form is for the: Left Wing: Right Wing: Other: _ PLEASE FOLLOW THE DAMAGE REPORTING INSTRUCTIONS PROVIDED ON THE BACK OF THIS FORM. Use copies of the illustrations from the service bulletin/service kit, service/maintenance manual or illustrated parts catalog as necessary to provide detailed descriptions of any damage. Attach detailed illustrations to this form. NOTE: Facilities capable of ing digital pictures of the damage should submit them in.jpeg format in addition to the above listed information. COMMENTS: (over)

2 ATTACHMENT A. ALL DAMAGE NOTE: Complete and accurate specification of all data and information is required in order to support appropriate and timely damage assessments and repair definition(s). Please provide a detailed dimensioned drawing of the damage and surrounding structure. Describe the location of the discrepancies by using airplane coordinates (e.g., FS, BL, WL) or distances from known structure such as spars, stringers, ribs, doors, or cutouts. Reference applicable Service/Maintenance Manual section for location references. Identify all damaged and/or affected components/part numbers. Drawings and Sketches should be drawn accurately and to an appropriate scale, with fastener locations and sub-structure identified. Report and fully define any existing repairs that are in the vicinity of, or that would overlap the new repair. Indicate and provide details of any existing repairs. Take electronic photographs (if possible) of damage, external and internal (if practical). If possible, take photographs at varying distances and/or orientations from damage. Include surrounding, adjacent, and/or support structure in photographs. Include a scale, if possible. Cross reference to sketch(es). Please note that photographs are supplemental information. Providing photographs without a dimensioned sketch of the damage and surrounding structure is insufficient in most cases. B. CRACK/GOUGE/DENT, ETC. DAMAGE Provide all of the following, if applicable, on sketch(es): lengths, depths, widths and orientations of cracks, gouges, and dents; edge distances measured from fastener hole center line to edge of part; fastener/hole sizes; fastener/hole spacing within the probable repair area; and location of crack tip(s). Specify dimensions in inches. Locate crack tips using surface eddy current or fluorescent dye penetrant techniques. Specify whether damage crosses any structure (e.g., stiffeners, frames, ribs etc.) and whether that structure is damaged. Specify whether cracks were detected from gouges or dents and what method of inspection was utilized to detect crack damage. (Preferred methods are eddy current and fluorescent penetrant). C. CORROSION DAMAGE CAUTION: CONTROL CORROSION REMOVAL PROCESS TO ONLY REMOVE MINIMUM MATERIAL REQUIRED. After complete corrosion removal, measure length, width, depth, and thickness of the material remaining and, if possible, the original thickness. Also measure dimensions to nearest/adjacent details (e.g. fasteners, holes, radii, edges etc.). Specify data on detailed sketch. Non-destructive inspect for cracks using Fluorescent Penetrant or Eddy Current method as applicable.

3 Multi-engine Service Bulletin July 7, 2008 TITLE UPPER WING SKIN INSPECTION EFFECTIVITY Model Year Serial Numbers thru thru thru , A 1957 thru thru A 38029A, 38030A and 38081A 310B 1957 thru thru B 1957 thru thru B C C thru C thru C D thru E M0001 thru 310M E 35912A 310F thru F thru G G0001 thru 310G H/E310H H0001 thru 310H I I0001 thru 310I J/310J-1/ E310J J0001 thru 310J K K0001 thru 310K L L0001 thru 310L N N0001 thru 310N P/T310P P0001 thru 310P0240 Page1of9 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, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) , Facsimile (316) COPYRIGHT 2008

4 310Q/T310Q 1970 thru Q0001 thru 310Q R/T310R 1975 thru R0001 thru 310R / thru A A0001 thru 320A B B0001 thru 320B C C0001 thru 320C D D0001 thru 320D D E E0001 thru 320E F F0001 thru 320F F thru , thru thru thru thru A A0001 thru 340A A A0201 thru 340A A A0401 thru 340A A A0601 thru 340A A A0901 thru 340A A A1201 thru 340A A A1501 thru 340A A A1801 thru 340A /401A / thru A A0001 thru 401A B 1970/71 401B0001 thru 401B B B0122 thru 401B / thru A A0001 thru 402A B 1970/ B0001 thru 402B B B0201 thru 402B B B0301 thru 402B B B0501 thru 402B B B0801 thru 402B B B1001 thru 402B B B1201 thru 402B B B1301 thru 402B1384 Page 2 July 7, 2008

5 / thru A 1967/ thru P thru thru thru thru thru thru thru thru / thru A A0001 thru 421A B B0001 thru 421B B B0101 thru 421B B B0201 thru 421B B B0301 thru 421B B B0501 thru 421B B B0801 thru 421B0970 PURPOSE Reports have been received of cracks occurring in the upper wing skin in the area of the upper cap of the support rib for the side brace of the main landing gear. This Service Bulletin provides instructions for inspecting the upper wing skin for cracks, corrosion, and damage in the area described above. COMPLIANCE Mandatory: for airplanes with a total time in service greater than 2,500 hours or greater than 20 years since the date of manufacture. Initial inspection: shall be accomplished at the next scheduled 100 hour or 12 month (annual) type inspection, whichever occurs first. Repetitive inspections: the inspection shall be accomplished every 200 hours of operation or 2 years after the initial inspection. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. July 7, 2008 Page 3

6 MAN-HOURS Approximately 1.0 man-hour for inspection. Man-hours may vary depending on airplane model, airplane condition and cleanliness of the airplane. MATERIAL Not applicable ACCOMPLISHMENT INSTRUCTIONS 1. Prepare the airplane for maintenance. A. Make sure that all switches are in the OFF/NORM position. B. Disconnect electrical power from the airplane. (1) Disconnect the airplane battery. (2) Disconnect external electrical power. C. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" writtenonthem. 2. Make the airplane safe for maintenance in the main landing gear (MLG) wheel well. (Refer to applicable sections/chapters of the service/maintenance manual.) 3. (Refer to Figure 1 and Figure 2.) From the MLG wheel well, clean the skin along the upper cap of the support rib on the side brace of the MLG to make it possible to find cracks, corrosion, or damage during the inspection. (Refer to applicable sections/chapters of the service/maintenance manual.) 4. Visually examine the skin along the upper cap of the support rib on the side brace side of the MLG wheel well for signs of cracks, corrosion, and damage. A. If there are no signs of cracks, corrosion, or damage, go to Step 5. B. If you find cracks, corrosion, or damage and the applicable service/maintenance manual gives procedures for the repair of the wing skin for all of the conditions that you find, make the repairs and then go to Step 5. (Refer to applicable sections/chapters of the service/maintenance manual.) C. If you find cracks, corrosion, or damage and the applicable service/maintenance manual does not give procedures for the repair of the wing skin for one or more of the conditions that you find, do as follows: (1) Record the type and dimensions of all damage (include damage the service/maintenance manual tells you how to repair and damage the service/maintenance manual does not tell you how to repair) and send a copy of the attached Damage Report Form to Cessna Propeller Aircraft Customer Service, Dept. 753, Cessna Aircraft Company, PO Box 7706, Wichita, KS , FAX (316) , or call (316) for instructions on how to make the repairs. (2) Make the repairs and then go to Step Remove maintenance warning tags and connect the airplane battery. 6. Make applicable entries in the airplane logbook that state compliance and method of compliance with this Service Bulletin and when the next inspection is due. 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 14 CFR Part Page 4 July 7, 2008

7 Figure 1. Upper Wing Skin Inspection (Sheet 1) July 7, 2008 Page 5

8 Figure 1. Upper Wing Skin Inspection (Sheet 2) Page 6 July 7, 2008

9 Figure 2. Upper Wing Skin Inspection (Sheet 1) July 7, 2008 Page 7

10 Figure 2. Upper Wing Skin Inspection (Sheet 2) Page 8 July 7, 2008

11 CREDIT Not applicable. OWNER NOTIFICATION On July 7, 2008 the following Owner Advisory message will be sent to applicable owners of record in A. Dear Cessna Owner: This Owner Advisory is to inform you that : Upper Wing Skin Inspection has been issued. Reports have been received of cracks occurring in the upper wing skin in the area of the upper cap of the support rib for the side brace of the main landing gear. provides instructions for inspecting the upper wing skin for cracks, corrosion, and damage in the area described above. Compliance is mandatory: for airplanes with a total time in service greater than 2,500 hours or greater than 20 years since the date of manufacture. Initial inspection: shall be accomplished at the next scheduled 100 hour or 12 month (annual) type inspection, whichever occurs first. Repetitive inspections: the inspection shall be accomplished every 200 hours of operation or 2 years after the initial inspection. The information contained in the referenced Cessna Service Bulletin 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 in accordance with 14 CFR Part Please contact a Cessna Multi-engine Service Station for detailed information and arrange to have Cessna ServiceBulletinaccomplishedonyourairplane. * * * * * * * July 7, 2008 Page 9