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SEB07-2

1. 0513132 6 Lower Right Stringer Shown 0513132 5 Lower Left Stringer 0513132 10 E Opposite Lower Right Reference Mounting Bracket Reference viEw C C Figure 1 Engine Mount Bracket Inspection Sheet 3 SEB07 2 April 16 2007 Page 11 CREDIT Not applicable OWNER NOTIFICATION On April 16 2007 the following Owner Advisory message will be sent to applicable owners of record in SEBO7 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 bracket s 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
2. For 172 Models Mandatory If any of the four 4 original brackets have not been replaced accomplish this inspection on the affected bracket s 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 SEBO7 2 accomplished on your airplane SEBO7 2 Page 12 April 16 2007
3. Rivet Rivet Lower Left Mounting Bracket Lower Right Mounting Bracket Upper Mounting Bracket Right and Left Alodine 1132 Marker Corrosion Resistant Primer 1 5 gal kit Qty Airplane 4 4 8 4 8 if required 8 if required 8 if required 1 if required 1 if required 2 if required as required as required AFR FHF FHF HF Price 1 30 PS ea MQ 10 0 07 PS ea MQ 100 5 20 PS ea 4 23 PS ea MQ 25 27 63 PS Ib 27 19 PS Ib S e 138 00 S ea 131 00 S ea 218 00 S ea 152 00 VR ea 339 00 VS ea ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE ACCOMPLISHMENT INSTRUCTIONS Change In Weight And Balance Negligible Page 4 SEB07 2 April 16 2007 Material Information The parts below will be necessary New P N Quantity Description Old P N Disposition AN6 See the 4 Bolt Same Discard applicable illustrated parts catalog for the correct part numbers MS21045L6 4 Nut MS20365 624C Discard NAS1149F0663P Washer AN960 616 Discard 1450 23N22 100 Washer 1450 23H16 095 Discard It is possible that the parts below will be necessary New P N Quantity Description Old P N Disposition CR3523 5 03 8 Rivet MS20470AD5 Discard MS20470AD5 6A 8 Rivet MS20470AD4 Discard MS20470AD5 8A 8 Rivet MS20470AD4 Discard 0513132 9 1 Lower Left Mounting 0513132 9 Discard Bracket 0513132 10 1 Lower Right 0513132 10 Discard Mounting Bracket 0513132 11 2 Upper Mounting 0513132 11 Dis
4. SEB07 2 April 16 2007 Page 9 B6404 view A A B AN6 Bolt an 1450 23N22 100 1 Required 1450 23N22 100 1 Required Washer NOTE Washer NOTE 1 Required 1 Required Truss Truss Reference Reference NAS1149F0663P NAS1149F0663P Washer y Washer MS21045L6 2 Required 2 Required Nut MS21045L6 1 Required Nut DETAIL 1 Required Left Side Shown Right Side Opposite DETAIL B Left Side Shown Right Side Opposite For Model 175 thru 175C and P172D Airplanes Figure 1 Engine Mount Bracket Inspection Sheet 2 SEB07 2 Page 10 April 16 2007 B6403 0513132 11 Upper Mounting Bracket Right and Left MS20470AD5 6A Rivet 2 If Required a 2 If Required D i T 7 WL MS20470AD5 8A n 7 5 59 Rivet 2 If Required 0 375 Inch L Ee ka gt Diameter Hole D 1 Required CR3523 5 03 0513132 8 0513132 11 Rivet Upper Right Stringer 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 on 1 Each If Required 14 64 CR3523 5 03 Rivet 2 If Required WL 18 25 0 375 Inch Diameter Hole 1 Required MS20470AD5 8A Rivet 2 If Required MS20470AD5 6A Rivet 2 If Required
5. 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 8 Install all of the equipment that you moved and removed 9 Install the pilot s and the copilot s seats 10 Install the upper and the lower engine cowlings 11 Remove the maintenance warning tags and connect the airplane battery 12 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 SEBO7 2 Page 8 April 16 2007 NOTE Refer to the applicable illustrated parts catalog for the correct AN6 Bolt to install NAS1149F0663P Washer 2 Required NAS1149F0663P B Washer 2 Required 1450 23N22 100 Ze Washer Truss 1 Required Reference ANG Bolt AN ai 1 Required a NOTE 1 Required NOTE Ane 23N22 100 Washer Truss Reference n 1 Required i 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
6. 50 thru F17201909 FR172E 1968 FR17200001 thru FR17200060 FR172F 1969 FR17200061 thru FR17200145 FR172G 1970 FR17200146 thru FR17200225 FR172H 1971 FR17200226 thru FR17200275 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 For 175 Models Mandatory If any of the four 4 original brackets have not been replaced accomplish this inspection on the affected bracket s 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 Mandator
7. M 172M 172M 172N 172N 172N 172N 172N 172N 175 175 175A 175A 175B 175C P172D R172K R172K R172K FP172 F172D F172E F172F F172G F172H F172H F172H F172H F172H F172H F172H F172H F172K F172L F172M F172M F172M F172M F172N F172N 1974 1975 1976 1977 1978 1978 1979 1958 1960 1961 1962 1963 1977 1978 1979 1963 1963 1964 1965 1966 1967 1967 1967 1968 1968 1968 1969 1970 1971 1972 1973 1974 1975 1976 1977 1978 thru 1959 17256493 17261899 thru 17263458 17263459 thru 17265684 17265685 thru 17267584 17267585 thru 17269309 17261445 17269310 thru 17270049 17270051 thru 17271034 17261578 17271035 thru 17272884 55001 thru 56238 28700A 626 640 56239 thru 56777 619 17556778 thru 17557002 17557003 thru 17557119 P17257120 thru P17257188 R1722000 thru R1722724 R1722725 thru R1722929 R1722930 thru R1723199 FP172 0001 thru FP172 0003 F172 0001 thru F172 0018 F172 0019 thru F172 0085 F172 0086 thru F172 0179 F172 0180 thru F172 0319 F172 0320 thru F172 0431 F172 0436 thru F172 0442 F172 0444 thru F172 0446 F172 0432 thru F172 0435 F172 0443 F172 0447 thru F172 0559 F172 0560 thru F172 0654 F17200655 thru F17200754 F17200755 thru F17200804 F17200805 thru F17200904 F17200905 thru F17201034 F17201035 thru F17201234 F17201235 thru F17201384 F17201385 thru F17201514 F17201515 thru F17201639 F17201640 thru F17201749 SEBO7 2 April 16 2007 F172N 1979 F172017
8. Single Engine al A Textron Company Service Bulletin April 16 2007 TITLE ENGINE MOUNT BRACKET INSPECTION EFFECTIVITY Model 172 172 172 172 172A 172A 172B 172B 172C 172D 172E 172E 172F 172G 172H 172H 172H 172l 172J 172K 172K 172L 172L 172M 172M 172M Year 1956 thru 1959 1956 thru 1959 1956 thru 1959 1960 1961 1962 1963 1964 1965 1966 1967 1967 1968 1969 1970 1971 1972 1973 1973 1973 Serial Numbers 28000 thru 29999 36000 thru 36999 46001 thru 46754 610 612 615 46755 thru 47746 622 625 17247747 thru 17248734 630 17248735 thru 17249544 17249545 thru 17250572 17250573 thru 17251822 639 17251823 thru 17253392 17253393 thru 17254892 17254893 thru 17256492 17256494 thru 17256512 638 17256513 thru 17257161 660 17257162 thru 17258486 17258487 thru 17259223 17259224 thru 17259903 17259904 thru 17260758 17260759 thru 17261444 17261446 thru 17261577 17261579 thru 17261898 SEBO7 2 Page 1 of 12 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 172M 172
9. 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 450 to 500 inch pounds 13 Go to Step 6 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 A 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 SEB07 2 April 16 2007 Page 7 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
10. card Bracket Right and Left The materials that follow or the equivalent may be necessary Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box 1521 Wichita KS 67218 Alodine 1132 Marker U074093 Corrosion K000912 Resistant Primer SEBO7 2 April 16 2007 Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box 1521 Wichita KS 67218 To apply to bare metal To apply to bare metal Page 5 The equipment below or equivalent will be necessary to do the inspection Borescope Commercially available To do the visual Olympus Storz or equivalent inspection for cracks e 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 0 degree angle is acceptable 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 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 s
11. ervice 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 ANE a INJURY TO PERSONNEL AND DAMAGE TO THE 4 Use an engine hoist to remove all of the engine weight from the engine truss 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 B Remove and discard the bolt washers and nut that attach the truss to the left 0513132 11 Upper Mounting Bracket 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 SEBO7 2 Page 6 April 16 2007 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 St
12. ringer 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 1 Put the left 0513132 11 Upper Mounting Bracket in position at the 0513132 7 Upper Left Stringer 2 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 4 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
13. y If any of the four 4 original brackets have not been replaced accomplish this inspection on the affected bracket s 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 APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design SEB07 2 April 16 2007 Page 3 For Reims Aviation Airplanes DGAC approval has not been obtained on technical data in this publication The affected F model and serial number airplanes are included for informational purposes Cessna considers compliance mandatory on F model airplanes regardless MAN HOURS Approximately 7 4 man hours for inspection If necessary approximately 3 0 man hours to replace each bracket MATERIAL The parts below are available from Cessna Parts Distribution through an appropriate Cessna Service Station for the suggested list price shown Part Number AN6 See the Applicable Illustrated Parts catalog for the specific part numbers MS21045L6 NAS1149F0663P 1450 23N22 100 CR3523 5 03 MS20470AD5 6A MS20470AD5 8A 0513132 9 0513132 10 0513132 114 U074093 K000912 Description Bolt Nut Washer Washer Rivet

SEB07-2

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