# Cessna Single Engine Service Bulletin SEB07-2: Revision 2 - Rights: © Textron Aviation Inc. Filed by the FAA in regulations.gov docket FAA-2016-5579; AD 2016-14-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Cessna Single Engine Service Bulletin SEB07-2](https://openairdocs.org/service-documents/cessna/seb07-2.md) - Title as filed: SEB07-2 - Pages: 12 - PDF: https://openairdocs.org/files/sha256/d0/09/d009f49a947dfde274539e32398fbedb6ead6049629af32eff4bdf033726b524 - Page: https://openairdocs.org/service-documents/cessna/seb07-2/file/d009f49a947d ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) Single Engine Cessna A Textron Company Service Bulletin June 18, 2007 SEB07-2 Revision 2 TITLE ENGINE MOUNT BRACKET INSPECTION EFFECTIVITY Model Year Serial Numbers 172B 1961 17247747 thru 17248734 172B 630 172C 1962 17248735 thru 17249544 172D 1963 17249545 thru 17250572 172E 1964 17250573 thru 17251822 172E 639 172F 1965 17251823 thru 17253392 172G 1966 17253393 thru 17254892 172H 1967 17254893 thru 17256492 172H 1967 17256494 thru 17256512 172H 638 1721 1968 17256513 thru 17257161 172J 660 172K 1969 17257162 thru 17258486 172K 1970 17258487 thru 17259223 172L 1971 17259224 thru 17259903 172L 1972 17259904 thru 17260758 172M 1973 17260759 thru 17261444 172M 1973 17261446 thru 17261577 172M 1973 17261579 thru 17261898 172M 17256493 172M 1974 17261899 thru 17263458 172M 1975 17263459 thru 17265684 172M 1976 17265685 thru 17267584 172N 1977 17267585 thru 17269309 Original Issue: April 16, 2007 Revision 1: May 14, 2007 Page 1 of 13 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 © 2007 ### Page 2 (OCR) 172N 17261445 172N 1978 17269310 thru 17270049 172N 1978 17270051 thru 17271034 172N 17261578 172N 1979 17271035 thru 17272884 175 1958 thru 1959 55001 thru 56238 175 28700A, 626, 640 175A 1960 56239 thru 56777 175A 619 175B 1961 17556778 thru 17557002 175C 1962 17557003 thru 17557119 P172D 1963 P17257120 thru P17257188 R172K 1977 R1722000 thru R1722724 R172K 1978 R1722725 thru R1722929 R172K 1979 R1722930 thru R1723199 FP172 1963 FP172-0001 thru FP172-0003 F172D 1963 F172-0001 thru F172-0018 F172E 1964 F172-0019 thru F172-0085 F172F 1965 F172-0086 thru F172-0179 F172G 1966 F172-0180 thru F172-0319 F172H 1967 F172-0320 thru F172-0431 F172H 1967 F172-0436 thru F172-0442 F172H 1967 F172-0444 thru F172-0446 F172H 1968 F172-0432 thru F172-0435 F172H 1968 F172-0443 F172H 1968 F172-0447 thru F172-0559 F172H 1969 F172-0560 thru F172-0654 F172H 1970 F17200655 thru F17200754 F172K 1971 F17200755 thru F17200804 F172L 1972 F17200805 thru F17200904 F172M 1973 F17200905 thru F17201034 F172M 1974 F17201035 thru F17201234 F172M 1975 F17201235 thru F17201384 F172M 1976 F17201385 thru F17201514 F172N 1977 F17201515 thru F17201639 F172N 1978 F17201640 thru F17201749 F172N 1979 F17201750 thru F17201909 FR172E 1968 FR17200001 thru FR17200060 FR172F 1969 FR17200061 thru FR17200145 FR172G 1970 FR17200146 thru FR17200225 FR172H 1971 FR17200226 thru FR17200275 SEB07-2 Revision 2 Page 2 June 18, 2007 ### Page 3 (OCR) FR172H 1972 FR17200276 thru FR17200350 FR172J 1973 FR17200351 thru FR17200440 FR172J 1974 FR17200441 thru FR17200530 FR172J 1975 FR17200531 thru FR17200559 FR172J 1976 FR17200560 thru FR17200590 FR172K 1977 FR17200591 thru FR17200620 FR172K 1978 FR17200621 thru FR17200630 FR172K 1979 FR17200631 thru FR17200655 PURPOSE Reports have been received of cracks being found in some upper and lower engine truss mounting brackets that are installed behind the firewall. This Service Bulletin provides instructions to do an inspection of the brackets, and if necessary, to replace the brackets. Non compliance with this Service Bulletin could result in having less than the desired structural integrity of the upper and lower engine truss mounting brackets. COMPLIANCE NOTE: Compliance with this revision is required if in compliance with the Original Issue or with Revision 1 of this Service Bulletin. The repetitive inspection requirements remain the same. For 175 Models: Mandatory: If any of the four (4) original brackets have not been replaced, accomplish this inspection on the affected brackets) at the next scheduled inspection not to exceed 25 hours of operation or 12 months/annual inspection, whichever occurs first. Repeat this inspection every 2,500 hours of operation thereafter. NOTE: This inspection shall be accomplished on any replaced bracket at 2,500 hours of operation after replacement and every 2,500 hours of operation thereafter. If either the Original Issue of SEB07-2 or SEB07-2 Revision 1 has been accomplished, removal and replacement of the engine truss to firewall mount bracket bolts and nuts shall be accomplished at the next scheduled inspection not to exceed 100 hours of operation or 12 months/annual inspection, whichever occurs first. For 172 Models: Mandatory: If any of the four (4) original brackets have not been replaced, accomplish this inspection on the affected brackets) at the next scheduled inspection not to exceed 100 hours of operation or 12 months/annual inspection, whichever occurs first. Repeat this inspection every 2,500 hours of operation thereafter. NOTE: This inspection shall be accomplished on any replaced bracket at 2,500 hours of operation after replacement and every 2,500 hours of operation thereafter. If either the Original Issue of SEB07-2 or SEB07-2 Revision 1 has been accomplished, removal and replacement of the engine truss to firewall mount bracket bolts and nuts shall be accomplished at the next scheduled inspection not to exceed 100 hours of operation or 12 months/annual inspection, whichever occurs first. SEB07-2 Revision 2 June 18, 2007 Page 3 ### Page 4 (OCR) APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. MAN-HOURS Approximately 7.4 man-hours for inspection If necessary, approximately 3.0 man-hours to replace each bracket If in compliance with the Original Issue of SEB07-2 or SEB07-2 Revision 1, approximately 7.0 man-hours to remove and replace the engine truss to firewall mount bracket bolts and nuts MATERIAL The parts below are available from Cessna Parts Distribution through an appropriate Cessna Service Station for the suggested list price shown. Part Number Description Qty/Airplane Price AN6 (See the Bolt 4 Applicable Illustrated Parts catalog for the specific part numbers) MS21045L6 Nut 4 $ 1.30 (PS) ea MQ 10 NAS1149F0663P Washer 8 $ 0.07 (PS) ea MQ 100 S1450-23N22-100 Washer 4 $ 5.20 (PS) ea CR3523-5-03 Rivet 8 (if required) 4.23 (PS) ea MQ 25 MS20470AD5-6A Rivet 8 (if required) $ 27.63 (PS) Ib MS20470AD5-8A Rivet 8 (if required) $ 27.19 (PS) Ib 0513132-9 Lower Left Mounting 1 (if required) $ 138.00 (S) ea Bracket 0513132-10 Lower Right Mounting 1 (if required) $ 131.00 (S) ea Bracket 0513132-11 Upper Mounting 2 (if required) $ 218.00 (S) ea Bracket (Right and Left) U074093 Alodine 1132 Marker (as required) 152.00 (VR) ea K000912 Corrosion Resistant (as required) 339.00 (VS) ea Primer (1.5 gal kit) ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE ACCOMPLISHMENT INSTRUCTIONS Change In Weight And Balance Negligible SEB07-2 Revision 2 Page 4 June 18, 2007 ### Page 5 (OCR) The equipment below, or equivalent, will be necessary to do the inspection. Name Number Manufacturer Use Borescope Commercially available To do the visual Olympus, Storz, or equivalent inspection for cracks • 0.125-inch (2.00 mm) diameter • 7.87-inch (200 mm) length probe • 70 to 80-degree field of view at a 30-degree fore-oblique angle. (70 to 80-degree direct field of view at a O-degree angle is acceptable.) NOTE: For airplanes not in compliance with SEB07-2 Revision 1, go to Step 1. NOTE: For airplanes in compliance with SEB07-2 or SEB07-2 Revision 1, you must remove and replace the AN6 Bolt and the MS21045L6 Nut in all positions, and torque the nut to 160 to 190 inch-pounds. Go to Step 1. 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 haveiDO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them. 2. Remove the upper and the lower engine cowlings. (Refer to the applicable sections of the service manual.) 3. Remove the pilot and the copilot seats. (Refer to the applicable sections of the service manual.) WARNING: WHILE YOU DO THIS INSPECTION, MAKE SURE THAT THE ENGINE IS SAFELY HELD IN PLACE. ONE AFTER THE OTHER, THE BOLTS THAT HOLD THE ENGINE TRUSSES TO THEIR MOUNTING BRACKET WILL BE REMOVED. IF YOU DO NOT SECURE THE ENGINE DURING THE INSPECTION, IT CAN MOVE AND CAUSE INJURY TO PERSONNEL AND DAMAGE TO THE AIRPLANE. 4. Use an engine hoist to remove all of the engine weight from the engine truss. NOTE: For airplanes in compliance with SEB07-2 or SEB07-2 Revision 1, go to Step 8. NOTE: For airplanes not in compliance with SEB07-2 or SEB07-2 Revision 1, go to Step 5. 5. Do an inspection of the left 0513132-11 Upper Mounting Bracket: A. (Refer to Figure 1, View A-A and Detail A.) From a position under the instrument panel, move the wires and the insulation away from the bolt that attaches the upper left engine truss to the left 0513132-11 Upper Mounting Bracket. SEB07-2 Revision 2 Page 6 June 18, 2007 ### Page 6 (OCR) B. Remove and discard the bolt, washers, and nut that attach the truss to the left 0513132-11 Upper Mounting Bracket. C. (Refer to Figure 1, View B-B.) Put a borescope through the slot in the 0513132-7 Upper Left Stringer. (Refer to Figure 1, View D-D.) Look carefully for a deformed or cracked left 0513132-11 Upper Mounting Bracket. (1) If you do find deformities or cracks, go to Step 5E. (2) If you do not find deformities or cracks, go to Step 6. E. (Refer to Figure 1, View B-B.) Remove the left 0513132-11 Upper Mounting Bracket from the 0513132-7 Upper Left Stringer and the airplane skin. (1) Remove the two rivets that attach the left 0513132-11 Upper Mounting Bracket to the hat section of the 0513132-7 Upper Left Stringer. (2) Remove the four rivets that attach the left 0513132-11 Upper Mounting Bracket to the flange of the 0513132-7 Upper Left Stringer and the airplane skin. (3) As necessary, remove rivets that are adjacent to the left 0513132-11 Upper Mounting Bracket until you can remove the left 0513132-11 Upper Mounting Bracket from the 0513132-7 Upper Left Stringer and the airplane. (4) Discard the left 0513132-11 Upper Mounting Bracket. F. Install the new left 0513132-11 Upper Mounting Bracket to the upper left engine truss. Put the left 0513132-11 Upper Mounting Bracket in position at the 0513132-7 Upper Left Stringer. Install the two MS20470AD5-6A Rivets and two MS20470AD5-8A Rivets that attach the left 513132-11 Upper Mounting Bracket to the 0513132-7 Upper Left Stringer and the airplane skin. (3) Drill the four existing Number 30(0.128-inch diameter) holes in the new left 0513132-11 Upper Mounting Bracket, 0513132-7 Upper Left Stringer, and airplane skin with a Number 21 (0.159-inch diameter) drill. Drill two Number 21(0.159-inch diameter) holes through the left 0513132-11 Upper Mounting Bracket and the hat of the 0513132-7 Upper Left Stringer. (5) Drill one 0.375-inch diameter hole through the left 0513132-11 Upper Mounting Bracket for the AN6 Bolt. (6) Deburr the holes and apply Alodine to bare metal. (7) Install the two CR3523-5-03 Rivets that attach the left 0513132-11 Upper Mounting Bracket to the 0513132-7 Upper Left Stringer. (8) Install rivets to replace the ones that you removed to get access to the 0513132-11 Mounting Bracket. (9) Apply Alodine to bare metal. (10) Do a touch-up of the paint as necessary. (11) (Refer to Figure 1, Detail A.) With the AN6 Bolt, S1450-23N22-100 Washer, two NAS1149F0663P Washers, and MS21045L6 Nut, attach the upper left engine truss to the left 0513132-11 Upper Mounting Bracket. (12) Torque the MS21045L6 Nut to 160 to 190 inch-pounds. (13) Go to Step 6. SEB07-2 Revision 2 June 18, 2007 Page 7 ### Page 7 (OCR) 6. Repeat Step 5 for the right 0513132-11 Upper Mounting Bracket. A. (Refer to Figure 1, Detail A.) For the installation of the upper right engine truss to the right 0513132-11 Upper Mounting Bracket, use the same hardware that is specified in Step 5F(11). 7. Do an inspection of the lower left and lower right engine truss mounting brackets as follows: Remove floorboard access panels and rudder pedal access panels as necessary to get access to the 0513132-10 Lower Right Mounting Bracket and the 0514132-9 Lower Left Mounting Bracket. CAUTION: When you remove the lower mounting bracket bolts, you must remove the two lower bolts at the same time. When you install the lower mounting bracket bolts, you must install the two lower bolts at the same time. Failure to do this can cause damage to the engine truss, the 0513132-5 Lower Left Stringer, and the 0513132-6 Lower Right Stringer. B. (Refer to all applicable details and views in Figure 1.) Do Steps 5B thru 5F again for the 0513132-10 Lower Right Mounting Bracket and the 0514132-9 Lower Left Mounting Bracket as necessary. Go to Step 9. 8. (For airplanes in compliance with the original issue of SEB07-2 or SEB07-2 Revision 1) Remove and replace the AN6 Bolts and the MS21045L6 Nuts as follows: A. (Refer to Figure 1, Detail A and Detail B.) From a position under the instrument panel, move the wires and the insulation away from the bolts that attach the upper left and the upper right engine truss to the upper mounting brackets. B. Remove floorboard access panels and rudder pedal access panels as necessary to get access to the bolts that attach the lower left and the lower right engine trusses to the lower mounting brackets. C. Remove and discard the upper left AN6 Bolt and MS21045L6 Nut that attach the engine truss to the mounting bracket, and install a new AN6 Bolt and MS21045L6 Nut. Torque the MS21045L6 Nut to 160 to 190 inch-pounds. D. Repeat Step 8C for the upper right AN6 Bolt and MS21045L6 Nut. CAUTION: When you remove the lower mounting bracket bolts, you must remove the two lower bolts at the same time. When you install the lower mounting bracket bolts, you must install the two lower bolts at the same time. Failure to do this can cause damage to the engine truss, the 0513132-5 Lower Left Stringer, and the 0513132-6 Lower E. Remove and discard the lower left and lower right AN6 Bolts and MS21045L6 Nuts that attach the engine truss to the mounting brackets, and install new AN6 Bolts and MS21045L6 Nuts. Torque the MS21045L6 Nuts to 160 to 190 inch-pounds. 9. install all of the equipment that you moved and removed. 10. Install the pilot's and the copilot's seats. 11. Install the upper and the lower engine cowlings. 12. Remove the maintenance warning tags and connect the airplane battery. 13. Make an entry in the airplane logbook that states compliance and method of compliance with this Service Bulletin, and also state 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. SEB07-2 Revision 2 Page 8 June 18, 2007 ### Page 8 (OCR) NOTE: Refer to the applicable illustrated parts catalog for the correct ANG Bolt to install. VIEW A-A NAS1149F0663P B Washer NAS1149F0663P (2 Required) Washer (2 Required) S1450-23N22-100 Washer Truss (1 Required) (Reference) AN6 AN6 Boit Bolt (1 Required) (1 Required) (NOTE) (NOTE) S1450-23N22-100 Truss Washer (Reference) MS21045L6 (1 Required) MS21045L6 Nut Nut (1 Required) (1 Required) DETAIL A DETAIL B Left Side Shown, Right Side Opposite Left Side Shown, Right Side Opposite For Model 172 thru 172N, R172K, FP172, F172D thru F172N, and FR172E thru FR172K Airplanes Figure 1. Engine Mount Bracket Inspection (Sheet 1) SEB07-2 Revision 2 June 18, 2007 Page 9 ### Page 9 (OCR) B6404 VIEW A-A B AN6 AN6 Bolt Bolt S1450-23N22-100 (1 Required) S1450-23N22-100 (1 Required) Washer (NOTE) Washer (NOTE) (1 Required) (1 Required) Truss Truss (Reference) (Reference) NAS1149F0663P NAS1149F0663P Washer Washer (2 Required) (2 Required) MS21045L6 Nut MS21045L6 Nut (1 Required) DETAIL A (1 Required) DETAIL B Left Side Shown, Right Side Opposite Left Side Shown, Right Side Opposite For Model 175 thru 175C and P172D Airplanes Figure 1. Engine Mount Bracket Inspection (Sheet 2) SEB07-2 Revision 2 Page 10 June 18, 2007 ### Page 10 (OCR) B6403 0513132-11 MS20470AD5-6A Upper Mounting Bracket Rivet (Right and Left) (2 If Required) (2 If Required) DI ф- WL MS20470AD5-8A 5.59 Rivet (2 If Required) 0.375-Inch Ф BL Diameter Hole D 19.56 (1 Required) CR3523-5-03 0513132-8 0513132-11 Rivet Upper Right Stringer VIEW D-D Upper (2 If Required) (Shown) Mounting 0513132-7 Bracket Upper Left Stringer (Reference) VIEW B-B (Opposite) (Reference) 0513132-10 Lower Right Mounting Bracket (Shown) 0513132-9 Lower Left Mounting Bracket (Opposite) (1 Each If Required) 14.61 BL CR3523-5-03 Rivet (2 If Required) WL 18.25 0.375-Inch Diameter Hole MS20470AD5-6A (1 Required) Rivet (2 If Required) 0513132-6 VIEW E-E E Lower Right Stringer (Shown) MS20470AD5-8A 0513132-5 Rivet Lower Left Stringer (2 If Required) 0513132-10 E (Opposite) Lower Right (Reference) Mounting Bracket (Reference) VIEW C-C Figure 1. Engine Mount Bracket Inspection (Sheet 3) SEB07-2 Revision 2 June 18, 2007 Page 11 ### Page 11 (OCR) CREDIT Not applicable OWNER NOTIFICATION A. On April 16, 2007 the following Owner Advisory message was sent to applicable owners of record in SEB07-2A. Dear Cessna Owner: This Owner Advisory is to inform you that SEB07-2: Engine Mount Bracket Inspection has been released. Reports have been received of cracks being found in some upper and lower engine truss mounting brackets that are installed behind the firewall. This Service Bulletin provides instructions to do an inspection of the brackets, and if necessary, to replace the brackets. Non compliance with this Service Bulletin could result in having less than the desired structural integrity of the upper and lower engine truss mounting brackets. For 175 Models: Mandatory: if any of the four (4) original brackets have not been replaced, accomplish this inspection on the affected brackets) at the next scheduled inspection not to exceed 25 hours of operation or 12 months/annual inspection, whichever occurs first. Repeat this inspection every 2,500 hours of operation thereafter. NOTE: This inspection shall be accomplished on any replaced bracket at 2,500 hours of operation after replacement and every 2,500 hours of operation thereafter. For 172 Models: Mandatory: If any of the four (4) original brackets have not been replaced, accomplish this inspection on the affected brackets) at the next scheduled inspection not to exceed 100 hours of operation or 12 months/annual inspection, whichever occurs first. Repeat this inspection every 2,500 hours of operation thereafter. NOTE: This inspection shall be accomplished on any replaced bracket at 2,500 hours of operation after replacement and every 2,500 hours of operation thereafter. 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 as required per 14 CFR Part 43.13. Please contact a Cessna Single Engine Service Station for detailed information and arrange to have Cessna Service Bulletin SEB07-2 accomplished on your airplane. B. On May 14, 2007 the following message was sent to applicable owners of record in SEB07-2AR1 for the following model 172 airplane serial numbers: 28000 thru 29999, 36000 thru 36999, 46001 thru 46754, 610, 612, 615, 46755 thru 47746, 622, and 625. Dear Cessna Owner: This Owner Advisory is to inform you that SEB07-2 Revision 1 has been issued to remove your airplane serial number from the Effectivity section of the Service Bulletin. Research of our records revealed that your airplane is not affected by Service Bulletin SEB07-2. SEB07-2 Revision 2 Page 12 June 18, 2007 ### Page 12 (OCR) C. On June 18, 2007 the following Owner Advisory will be sent to applicable owners of record in SEB07-2AR2. Dear Cessna Owner: This Owner Advisory is to inform you that Service Bulletin SEB07-2 Revision 2 has been issued to revise the torque value of the engine truss to firewall mounting bracket bolts and nuts and to require the replacement of these bolts and nuts if in compliance with the Original Issue of SEB07-2 or SEB07-2 Revision 1. SEB07-2 Revision 2 provides instructions to do an inspection of the upper and lower engine truss mounting brackets that are installed behind the firewall, and if necessary, to replace the brackets. It also provides instructions to replace the engine truss to firewall mounting bracket bolts and nuts for airplanes in compliance with the Original Issue of SEB07-2 or SEB07-2 Revision 1. Non compliance with this Service Bulletin could result in having less than the desired structural integrity of the upper and lower engine truss bolts, nuts, and mounting brackets. NOTE: Compliance with SB07-2 Revision 2 is required if in compliance with the Original Issue or Revision 1 of this Service Bulletin. The repetitive inspection requirements remain the same. For 175 Models: Mandatory: If any of the four (4) original brackets have not been replaced, accomplish this inspection on the affected brackets) at the next scheduled inspection not to exceed 25 hours of operation or 12 months/annual inspection, whichever occurs first. Repeat this inspection every 2,500 hours of operation thereafter. NOTE: This inspection shall be accomplished on any replaced bracket at 2,500 hours of operation after replacement and every 2,500 hours of operation thereafter. If either the Original Issue of SEB07-2 or SEB07-2 Revision 1 has been accomplished, removal and replacement of the engine truss to firewall mount bracket bolts and nuts shall be accomplished at the next scheduled inspection not to exceed 100 hours of operation or 12 months/annual inspection, whichever occurs first. For 172 Models: Mandatory: If any of the four (4) original brackets have not been replaced, accomplish this inspection on the affected brackets) at the next scheduled inspection not to exceed 100 hours of operation or 12 months/annual inspection, whichever occurs first. Repeat this inspection every 2,500 hours of operation thereafter. NOTE: This inspection shall be accomplished on any replaced bracket at 2,500 hours of operation after replacement and every 2,500 hours of operation thereafter. If either the Original Issue of SEB07-2 or SEB07-2 Revision 1 has been accomplished, removal and replacement of the engine truss to firewall mount bracket bolts and nuts shall be accomplished at the next scheduled inspection not to exceed 100 hours of operation or 12 months/annual inspection, whichever occurs first. 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 as required per 14 CFR Part 43.13. Please contact a Cessna Single Engine Service Station for detailed information and arrange to have Cessna Service Bulletin SEB07-2 Revision 2 accomplished on your airplane. SEB07-2 Revision 2 June 18, 2007 Page 13 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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