Service Bulletin

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 Qtv/Airp lane Price AN6 (See the Bolt 4 Applicable Illustrated Parts catalog for the specific part numbers) MS21045l6 Nut 4 $ 1.30 (PS) ea MQ 10 NAS 1149F0663P Washer 8 $ 0.07 (PS) ea MQ 100 S1450-23N22 -1 00 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) lb MS20470AD5-8A Rivet 8 (if required) $ 27.19 (PS) lb 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) s 152.00 (VR) ea K000912 Corrosion Resistant (as requ ir ed) $ 339.00 (VS) ea Primer (1.5 gal kit) ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE ACCOMPLISHMENT INSTRUCTIONS Change In Weight And Balance Negligible Page4 SEB07-2 Revision 2 June 18, 2007 The equipment below, or equivalent, will be necessary to do the inspection. Name N umbe r Manufac turer 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 0-degree angle is acceptable.) INOTE: For airplanes not in compliance with SE 80 7-2 Revision 1, go to Step 1. NOTE: For airplanes in compli2nce with SEB07-2 or S EB07-2 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. I 1. Prepare the airplane for maintenance. A. Make sure that all switches are in the OFF/NORM positio n. B. Disconnect electrical power from the airplane. (1) Disconnect the airplane batte ry. (2) Disconnect external electrical powe r. C. Attach maintenance warning tags to the battery and external power receptacle that have "D O NOT CONNECT ELECTR IC AL POWER - MAINTENANCE IN PROG RE S S" written on them. 2. Remove the upper and the lower en gi ne cowlings. (Refer to the applicable sections of the service manual.) 3. Remove the pil ot and the copilot seats. (Re fe r to the applicable sections of the service manua l. ) 4 . 5. WARNING: WHILE YOU DO THIS INSP EC TION, MAKE SU RE THAT TH E ENGINE IS SAFELY HE LD IN PLACE. ONE AFTER THE OTHE R, THE BOLTS THAT HOLD THE ENG IN E TRUSSES TO THEIR MOUNTING BRACKET WILL BE REM OVE D. IF YOU DO NOT SECURE THE EN GINE DURING TH E INSPECTION, IT CAN MOVE AND CAU SE INJURY TO PERS ONN EL AND DAMAGE TO THE AIRPLANE. Use an engine hoist to remove ali 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. 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 insu lation away from the bolt that attaches the upper left engine truss to the left 0513132-11 Upper Mounting Bracke t. SEB07-2 Revision 2 Page 6 June 18, 2007 I 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. D. (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 l eft 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 05131 32-11 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 attacr, the !eft 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 05 13132-7 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 NA S11 49F0663P Washers, and MS21 045L6 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 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 0514132-9lower 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 58 thru SF again for the 0513132-10 Lower Right Mounting Bracket and the 0514132-9 Lower Left Mounting Bracket as necessary. Goto 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 Bo lt 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 Right Stringer. 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. Page 8 SEB07-2 Revision 2 June 18, 2007 NOTE: Refer to the applicable illustrated parts catalog for the correct AN6 Bolt to install. B l A c l VIEW A- A NAS1149F0663P B NAS1149F0663P Washer (2 Required) S1450-23N22-100 p<Washer (1 Required) - AN6 < \ Bolt ~ ~ (1 Required) Truss (Reference) MS21045L6 Nut (1 Required) DETAIL B {NOTE) Left Side Shown, Right Side Opposite Truss (Reference) f~ Bolt (1 Required) ~ (NOTE) r S1450-23N22-100 Washer MS21045L6 (1 Required) Nut (1 Required) DETAIL A Left Side Shown. Right Side Opposite For Model172 thru 172N, R172K, FP172, F172D thru F172N!_<3!'d FR172E thru FR172K Airplanes SEB07-2 Revision 2 June 18, 2007 Figure 1. Engine Mount Bracket Inspection (Sheet 1) Page9 S1450-23N22-100 Washer (1 Required) Truss (Reference) VIEWA-A B AN6 Bolt (1 Required) (NOTE) S1450-23N22-100 Washer (1 Required) NAS1149F0663P Washer A N6 Bolt (1 Required} (NOTE) ~~ NAS1149F0663P Washer (2 Required) rMS21045L6 (2 Required) Nut (1 Required) Page 10 MS21045L6 Nut (1 Required) DETAIL 8 DETAIL A Left Side Shown, Right Side Opposite Left Side Shown, Right Side Opposite For Model175 thru 175C and P172D Airplanes Figure 1. Engine Mount Bracket Inspection (Sheet 2) SEB0?-2 Revision 2 June 18, 2007 0513132-11 U pper Mounting Bracket MS20470AD5-6A Rivet (Right and Left) (2 If Required) (2 If Required) WL MS20470AD5-8A .-+--+++-5.59 Rivet lkt-M---'~- Q_--- - - --- - ------ _j(2 If Required) BL 19.56 VIEW D-D 0513132-10 0.375-lnch Diameter Hole (1 Required) Lower Right Mounting Bracket (Shown) 0513132-9 Lower Left Mounting Bracket (Opposite) (1 Each If Required) Bl 14.61 D w ......._·_,_,_'!--ll- ..____t_"____ __ _ t __ CR3523-5-03 0513132-8 0513132-11 Upper Mounting Bracket (Reference) Rivet Upper Right Stringer (2 If Required) (Shown) CR3523- 5- 03 Rivet (2 If Required) 0513132-7 Upper Left Stringer VIEW B-B (Opposite) (Reference) WL __--,&.~;:------... '-t-__,11--- 18.25 0.375-lnch Diameter Hole (1 Required) SEB07-2 Revision 2 June 18, 2007 VIEW E- E MS20470AD5-8A Rivet (2 If Required) ~ 0513132- 10 E Lower Right Mounting Bracket (Reference) VIEW C- C Figure 1. Engine Mount Bracket Inspection (Sheet 3) MS20470AD5-6A 0513132-6 Lower Right Stringer (Shown) 0513132-5 Lower Left Stringer (Opposite) (Reference) Page 11 I CREDIT Not applicable OWNER NOTIFICATION A. On April16, 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 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 opera ti on thereafter. 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 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 model172 airplane serial numbers: 28000 thru 29999, 36000 thru 36999, 46001 thru 46754, 610, 61 2,615,46755 thru 47746,622. and 625. Page 12 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 June 18, 2007 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 instru ctions 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 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 replacemen,t 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 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: T hi s 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