Service Bulletin

Non-compliance with this service bulletin could result in failure of the main landing gear actuator. COMPLIANCE Mandatory; shall be accomplished as follows: For part number 1281000-1, 1281000-2, 1281006-1, 1281006-2, 9882000-1, 9882000-2, 9882015-1 and 9882015-2 actuators and 1241619-1, 1241619-2, 1281001-1, 1281001-2 or 1281001-3 actuator bodies A. Initial Inspection and Rework for actuators/bodies exceeding 3,000 hours total time in service: shall be accomplished during the next scheduled airframe inspection not to exceed 100 hours of operation. B. Subsequent Inspections shall be accomplished every 500 hours thereafter. NOTE: Compliance with the Initial Inspection and Rework of this revision is not required if in compliance with the Initial Inspection and Rework of the original issue of this service bulletin. Subsequent Inspections are required as stated. NOTE: Main landing gear actuator assembly part numbers 1280501-1, -2, -3 & -4 and 1280511-1, -2, -3, -4, -5 & -6 may have been installed on any airplane serial number listed in the Effectivity section. These part number actuators are not affected by this service bulletin. ■ SEB01-2 Revision 1 September 17, 2001 Page 3 For part number 1281000-3, 1281000-4, 9882000-4, 9882000-5 and 9882015-4 actuators and 1281001-4, 1281001-5 or 1281001-6 actuator bodies A. B. Initial Inspection for actuators/bodies exceeding 3,000 hours total time in service: shall be accomplished during the next scheduled airframe inspection not to exceed 100 hours of operation. NOTE: Rework of actuators/bodies is not required. Subsequent Inspections shall be accomplished every 500 hours thereafter. NOTE: Compliance with the Initial Inspection of this revision is not required if in compliance with the Initial Inspection of the original issue of this service bulletin. Subsequent Inspections are required as stated. NOTE: Main landing gear actuator assembly part numbers 1280501-1, -2, -3 & -4 and 1280511-1, -2, -3, -4, -5 & -6 may have been installed on any airplane serial number listed in the Effectivity section. These part number actuators are not affected by this service bulletin. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes; DGAC approval has been obtained on technical data in this publication that affects airplane type design. MAN-HOURS Approximately 8.0 man-hours per actuator for inspection. MATERIAL The following are available from Cessna Parts Distribution through an appropriate Cessna Service Station for the suggested list price shown. Part Number Description Qty/Airplane Price 1281000-3 Actuator, Left SEE NOTE 1 5,034.00 (D) ea. 1281000-4 Actuator, Right SEE NOTE 1 5,042.00 (D) ea. 9882000-4 Actuator, Left SEE NOTE 2 9,421.00 (D) ea. 9882000-5 Actuator, Right SEE NOTE 2 $ 9,417.00 (D) ea. 9882015-4 Actuator, Left or Right SEE NOTE 3 $ 7,210.00 (D) ea. 1281001-4 Actuator Body SEE NOTE 2 $ 7,750.00 (A) ea. 1281001-5 Actuator Body SEE NOTE 4 $ 5,790.00 (PD) ea. 1281001-6 Actuator Body SEE NOTE 5 $ 3,255.40 (PD) ea. Page 4 ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE SEB01-2 Revision 1 September 17, 2001 NOTES: 1. 2. 3. 4. 5. Applicable to model 210 airplane serial numbers 57001 through 2105955 Applicable to airplane serial numbers 21059551 through 21064135, 616, 618 and P21000001 through P21000150 Applicable to airplane serial numbers 172RG0001 through 172RG1191, 691, R18200001 through R18202039, FR18200001 through FR18200070, 21064136 through 21065009 and P21000151 through P21000874 Applicable to airplane serial numbers R18200001 through R18200476, FR18200001 through FR18200010, 210059200 through 2105955, 21064136 through 21065009 and P2100151 through P21000874 Applicable to airplane serial numbers 172RG0001 through 172RG1191, R18200477 through R18202039 and FR18200011 through FR18200070 ACCOMPLISHMENT INSTRUCTIONS Main Landing Gear Actuator Inspection Instructions are attached. 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 (FAR) 43.13. CREDIT Not applicable SEB01-2 Revision 1 September 17, 2001 Page 5 OWNER NOTIFICATION A. On February 19, 2001 the following Owner Advisory message was sent to applicable owners of record in SEB01-2A. Dear Cessna Owner: This letter is to provide notification that an inspection is required of the main landing gear actuators on your airplane for the presence of cracks. Cracked actuators and actuator bodies shall be replaced. If no cracks are found, the part number 1281000-1, 1281000-2, 9882000-1, 9882000-2, 9882015-1 and 9882015-2 actuators and 1281001-1, 1281001-2 or 1281001-3 actuator bodies shall be modified and subsequently reinspected as specified in Service Bulletin SEB01-2. Part number 12810000-3, 1281000-4, 9882000-4, 9882000-5 and 9882015-4 actuators and 1281001-4, 1281001-5 or 1281001-6 actuator bodies do not need to be modified but will require subsequent inspection. Non-compliance with Service Bulletin SEB01-2 could result in failure of the main landing gear actuator. Compliance is mandatory; shall be accomplished as follows: For part number 1281000-1, 1281000-2, 9882000-1, 9882000-2, 9882015-1 and 9882015-2 actuators and 1281001-1, 1281001-2 or 1281001-3 actuator bodies A. B. Initial Inspection and Rework for actuators/bodies exceeding 3,000 hours total time in service: shall be accomplished during the next scheduled airframe inspection not to exceed 100 hours of operation. Subsequent Inspections shall be accomplished every 500 hours thereafter. For part number 1281000-3, 1281000-4, 9882000-4, 9882000-5 and 9882015-4 actuators and 1281001-4, 1281001-5 or 1281001-6 actuator bodies A. B. Initial Inspection for actuators/bodies exceeding 3,000 hours total time in service: shall be accomplished during the next scheduled airframe inspection not to exceed 100 hours of operation. NOTE: Rework of actuators/bodies is not required. Subsequent Inspections shall be accomplished every 500 hours 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 FAR 43.13. Please contact a Cessna Single Engine Service Station for detailed information and make arrangements to have Service Bulletin SEB01-2 accomplished on your airplane. Page 6 SEB01-2 Revision 1 September 17, 2001 B. On September 17, 2001 the following Owner Advisory message was sent to applicable owners of record for airplane serial numbers 57001 through 21057840, 616 and 618 in SEB01-2AR1. Dear Cessna Owner: This letter is to provide notification that an inspection is required of the main landing gear actuators on your airplane for the presence of cracks. Cracked actuators and actuator bodies shall be replaced. If no cracks are found, the part number 1281000-1, 1281000-2, 1281006-1, 1281006-2, 9882000-1, 9882000-2, 9882015-1 and 9882015-2 actuators and 1241619-1, 1241619-2, 1281001-1, 1281001-2 or 1281001-3 actuator bodies shall be modified and subsequently reinspected as specified in Service Bulletin SEB01-2 Revision 1. Part number 12810000-3, 1281000-4, 9882000-4, 9882000-5 and 9882015-4 actuators and 1281001-4, 1281001-5 or 1281001-6 actuator bodies do not need to be modified but will require subsequent inspection. Non-compliance with Service Bulletin SEB01-2 Revision 1 could result in failure of the main landing gear actuator. Compliance is mandatory; shall be accomplished as follows: For part number 1281000-1, 1281000-2, 1281006-1, 1281006-2, 9882000-1, 9882000-2, 9882015-1 and 9882015-2 actuators and 1241619-1, 1241619-2, 1281001-1, 1281001-2 or 1281001-3 actuator bodies A. B. Initial Inspection and Rework for actuators/bodies exceeding 3,000 hours total time in service: shall be accomplished during the next scheduled airframe inspection not to exceed 100 hours of operation. Subsequent Inspections shall be accomplished every 500 hours thereafter. NOTE: Compliance with the Initial Inspection and Rework of this revision is not required if in compliance with the Initial Inspection and Rework of the original issue of this service bulletin. Subsequent Inspections are required as stated. NOTE: Main landing gear actuator assembly part numbers 1280501-1, -2, -3 & -4 and 1280511-1, -2, -3, -4, -5 & -6 may have been installed on any airplane serial number listed in the Effectivity section. These part number actuators are not affected by Service Bulletin SEB01-2 Revision 1. For part number 1281000-3, 1281000-4, 9882000-4, 9882000-5 and 9882015-4 actuators and 1281001-4, 1281001-5 or 1281001-6 actuator bodies A. B. Initial Inspection for actuators/bodies exceeding 3,000 hours total time in service: shall be accomplished during the next scheduled airframe inspection not to exceed 100 hours of operation. NOTE: Rework of actuators/bodies is not required. Subsequent Inspections shall be accomplished every 500 hours thereafter. NOTE: Compliance with the Initial Inspection of this revision is not required if in compliance with the Initial Inspection of the original issue of Service Bulletin SEB01-2. Subsequent Inspections are required as stated. NOTE: Main landing gear actuator assembly part numbers 1280501-1, -2, -3 & -4 and 1280511-1, -2, -3, -4, -5 & -6 may have been installed on any airplane serial number listed in the Effectivity section. These part number actuators are not affected by Service Bulletin SEB01-2 Revision 1. 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 (FAR) 43.13. Please contact a Cessna Single Engine Service Station for detailed information and make arrangements to have Service Bulletin SEB01-2 Revision 1 accomplished on your airplane. ■ SEB01-2 Revision 1 September 17, 2001 * Page 7 - Single Engine ACCOMPLISHMENT INSTRUCTIONS Cessna A Textron Company SEB01-2 Revision 1 TITLE MAIN LANDING GEAR ACTUATOR INSPECTION EFFECTIVITY MODEL SERIES 172RG 172RG R182 210 210/T210 T210 P210 FR182 NOTE: SERIAL NUMBERS 172RG0001 thru 172RG1191 691 R18200001 thru R18202039 57001 thru 57575 21057576 thru 21065009 T210-0001 thru T210-0454 P21000001 thru P21000874 FR18200001 thru FR18200070 Airplanes equipped with 1280501-1, -2, -3 and/or -4 or 1280511-1, -2, -3, -4, -5 and -6 Main Landing Gear Actuator Assemblies on both left and right main landing gear are not affected by this bulletin. It is possible to have one of these un- affected actuator assemblies installed on one side while the later style, affected actuator assembly is installed on the other side. This inspection applies only to the later style actuator. Refer to the Service Bulletin for affected actuator assembly part numbers. DESCRIPTION The following instructions explain how to check for the presence of cracks in an area of the Main Landing Gear Actuators, and how to polish that same area if no cracks are found. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes: DGAC approval has been obtained on technical data in this publication that affects airplane type design. REFERENCE SEB01-2 Revision 1 CHANGE IN WEIGHT AND BALANCE None Original Issue: February 19, 2001 Revision 1: September 17, 2001 Page 1 of 4 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©2001 ACCOMPLISHMENT INSTRUCTIONS MATERIAL INFORMATION PART NUMBER QUANTITY *ZL-22 As Required *ZP-9 As Required *ZC-7 As Required *ZB-23A 1 *8X to 10X 1 DESCRIPTION Penetrant Developer Cleaner Portable Black Light Magnifying Glass SEB01-2 Revision 1 * Product of: Magnaflux Corporation 7300 W. Lawrence Avenue Chicago, IL 60656 or equivalent inspection material, per QPL-25135 and MIL SPEC MIL-1-25135. New packings and O-rings are required for re-assembly of main landing gear actuators. Refer to applicable Parts Catalog for part number information. ACCOMPLISHMENT INSTRUCTIONS 1. Inspect Main Landing Gear Actuators. A. Jack the airplane. (Refer to applicable Service Manual.) B. (Refer to applicable Service Manual.) Remove and disassemble Main Landing Gear Actuator. (Refer to Figure 1.) Perform a fluorescent penetrant inspection in location indicated by Figure 1 on both sides of each main landing gear actuator body. C. (1) (2) (3) D. E. F. (4) (5) Clean each actuator in inspection areas with ZC-7 Cleaner using a lint free cloth. Apply ZL-22 Penetrant to the areas previously cleaned, and allow penetrant to remain on these areas for thirty minutes. Clean the penetrant from the actuator using a clean, lint free cloth dampened with ZC-7 cleaner. The inspection area is considered clean with an absence of background fluorescences. Mix ZP-9 Developer per the manufacturer's instruction on the container and apply a thin coat to the inspection area. Allow 15 minutes for developing time. Examine the areas under black light. An 8X to 10X magnifying glass should be used in the examination as some cracks are difficult to see with the naked eye. If a crack or cracks are detected, the actuator or actuator body must be replaced. If no cracks are detected on part number 1281000-1, 1281000-2, 9882000-1, 9882000-2, 9882015-1 or 9882015-2 Actuator Assemblies and 1281001-1, 1281001-2 or 1281001-3 Actuator Bodies, proceed to Step 2. If no cracks are detected on part number 1281000-3, 1281000-4, 9882000-4, 9882000-5 or 9882015-4 Actuator Assemblies and 1281001-4, 1281001-5 or 1281001-6 Actuator Bodies, proceed to Step 3. Page 2 2. A. 3. 4. ACCOMPLISHMENT INSTRUCTIONS SEB01-2 Revision 1 Polish edge of hole intersection of main landing gear actuator. (Refer to Figure 1.) Using fine grit emery cloth (600 grit), or equivalent, polish edge of hole intersection as shown in Figure 1. (1) (2) (3) Smooth continuous edge of saddle-shaped oval hole where 1.00 inch diameter bore transitions 2.28 inch diameter bore, so that no sharp edges or tool marks can be felt by finger tip. Smooth circumference of 2.28 inch diameter bore and step so that no sharp edges or tool marks can be felt by finger tip. Flush actuator body with solvent to remove any metal shavings, fluorescent penetrant solution or other foreign matter. (Refer to applicable Service Manual.) Assemble and install Main Landing Gear Actuator. NOTE: Ensure new seals are installed in actuators per Service Manual instructions. Perform an operational and leak check of the landing gear system, rig as required. (Refer to applicable Service Manual.) 5. Remove the airplane from jacks. (Refer to applicable Service Manual.) 6. Make an entry in the airplane logbook stating compliance and method of compliance with this Service Bulletin, and if applicable, when the next scheduled inspection is due. Page 3 ACCOMPLISHMENT _ INSTRUCTIONS 1.00 INCH DIAMETER BORE CONTINUOUS EDGE INSPECTION AREA NOTE: INSPECT CONTINUOUS EDGE OF SADDLE-SHAPED HOLE AND CIRCUMFERENCE OF 2.28 INCH DIAMETER BORE AND STEP. 2.28 INCH DIAMETER BORD FIGURE 1. MAIN LANDING GEAR ACTUATOR INSPECTION SEB01-2 Revision 1 Page 4