ATTACHMENT DAMAGE REPORT FORM TO: Cessna Aircraft Company Propeller Aircraft Customer Service/Dept 753 P.O. Box 7706 Wichita, Kansas 67277-7706 Phone Number: 316-517-5800 Fax Number: 316-942-9006 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 e-mailing digital pictures of the damage should submit them in.jpeg format in addition to the above listed information. COMMENTS: (over)
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.
Multi-engine Service Bulletin July 7, 2008 TITLE UPPER WING SKIN INSPECTION EFFECTIVITY Model Year Serial Numbers 310 1955 35000 thru 35225 310 1956 thru 1957 35226 thru 35546 310 606, 664 310A 1957 thru 1958 38000 thru 38161 310A 38029A, 38030A and 38081A 310B 1957 thru 1958 35547 thru 35549 310B 1957 thru 1958 35551 thru 35771 310B 607 310C 629 310C 1959 35772 thru 35999 310C 1959 39001 thru 39031 310C 35550 310D 1960 39032 thru 39299 310E 1960 310M0001 thru 310M0036 310E 35912A 310F 1961 310-0001 thru 310-0016 310F 1961 310-0018 thru 310-0156 310G 1962 310G0001 thru 310G0156 310H/E310H 1963 310H0001 thru 310H0148 310I 1964 310I0001 thru 310I0200 310J/310J-1/ E310J 1965 310J0001 thru 310J0200 310K 1966 310K0001 thru 310K0245 310L 1967 310L0001 thru 310L0207 310N 1968 310N0001 thru 310N0198 310P/T310P 1969 310P0001 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) 517-5800, Facsimile (316) 942-9006 COPYRIGHT 2008
310Q/T310Q 1970 thru 1974 310Q0001 thru 310Q1160 310R/T310R 1975 thru 1981 310R0001 thru 310R2140 320 635 320/320-1 1962 320-0001 thru 320-0110 320A 1963 320A0001 thru 320A0047 320B 1964 320B0001 thru 320B0062 320C 1965 320C0001 thru 320C0073 320D 1966 320D0001 thru 320D0130 320D 623 320E 1967 320E0001 thru 320E0110 320F 1968 320F0001 thru 320F0045 320F 658 335 1980 335-0001 thru 335-0065 340 672, 673 340 1972 340-0001 thru 340-0115 340 1973 340-0151 thru 340-0260 340 1974 340-0301 thru 340-0370 340 1975 340-0501 thru 340-0555 340A 1976 340A0001 thru 340A0125 340A 1977 340A0201 thru 340A0375 340A 1978 340A0401 thru 340A0562 340A 1979 340A0601 thru 340A0801 340A 1980 340A0901 thru 340A1045 340A 1981 340A1201 thru 340A1280 340A 1982 340A1501 thru 340A1543 340A 1984 340A1801 thru 340A1817 401/401A 655 401 1967/68 401-0001 thru 401-0322 401A 1969 401A0001 thru 401A0132 401B 1970/71 401B0001 thru 401B0121 401B 1972 401B0122 thru 401B0221 402 1967/68 402-0001 thru 402-0322 402A 1969 402A0001 thru 402A0129 402B 1970/1971 402B0001 thru 402B0122 402B 1972 402B0201 thru 402B0249 402B 1973 402B0301 thru 402B0455 402B 1974 402B0501 thru 402B0640 402B 1975 402B0801 thru 402B0935 402B 1976 402B1001 thru 402B1100 402B 1977 402B1201 thru 402B1250 402B 1978 402B1301 thru 402B1384 Page 2 July 7, 2008
411 642 411 1965/1966 411-0001 thru 411-0250 411A 1967/1968 411-0251 thru 411-0300 P411 657 414 667 414 1970 414-0001 thru 414-0099 414 1971 414-0151 thru 414-0175 414 1972 414-0251 thru 414-0280 414 1973 414-0351 thru 414-0437 414 1974 414-0451 thru 414-0550 414 1975 414-0601 thru 414-0655 414 1976 414-0801 thru 414-0855 414 1977 414-0901 thru 414-0965 421 693 421 1967/1968 421-0001 thru 421-0200 421A 1969 421A0001 thru 421A0158 421B 1970 421B0001 thru 421B0056 421B 1971 421B0101 thru 421B0147 421B 1972 421B0201 thru 421B0275 421B 1973 421B0301 thru 421B0486 421B 1974 421B0501 thru 421B0665 421B 1975 421B0801 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
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 67277-7706, FAX (316) 942-9006, or call (316) 517-5800 for instructions on how to make the repairs. (2) Make the repairs and then go to Step 5. 5. 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 43.13. Page 4 July 7, 2008
Figure 1. Upper Wing Skin Inspection (Sheet 1) July 7, 2008 Page 5
Figure 1. Upper Wing Skin Inspection (Sheet 2) Page 6 July 7, 2008
Figure 2. Upper Wing Skin Inspection (Sheet 1) July 7, 2008 Page 7
Figure 2. Upper Wing Skin Inspection (Sheet 2) Page 8 July 7, 2008
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 43.13. Please contact a Cessna Multi-engine Service Station for detailed information and arrange to have Cessna ServiceBulletinaccomplishedonyourairplane. * * * * * * * July 7, 2008 Page 9