SERVICE BULLETIN. NO.: 0713 Revision C. All Garmin Aviation Service Centers and Aircraft OEM Service Centers DATE: 29 May 2007

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1 SERVICE BULLETIN NO.: 0713 Revision C TO: All Garmin Aviation Service Centers and Aircraft OEM Service Centers DATE: 29 May 2007 SUBJECT: GSM 85 Inspection Procedure REVISION B: Revision C changes some warranty times in Table 3, and makes a correction to Step 5.9 in Section 5 (all alterations are indicated by change bars). Previous revisions of Service Bulletin 0713 are superseded by this bulletin. PURPOSE All GSM 85 servo gearboxes (also referred to as servo mounts) must be inspected per the instructions in this bulletin. DESCRIPTION All GSM 85 servo gearboxes must be inspected for the presence of FOD (Foreign Object Debris) that may be inside the housing. APPROVAL LRU LRU Part Number TSO/ETSO GSM ( ) TSO-C9c, ETSO-C9c Table 1 AFMS AND PILOT S GUIDE CONSIDERATIONS There are no Pilot s Guide or Cockpit Reference Guide changes required.

2 PRODUCT AFFECTED This bulletin is applicable to all GFC 700-equipped aircraft (excluding Cessna Mustang). These aircraft include up to four GSM 85s. GSM 85s with a Mod Level marked on the serial tag as listed in Table 2 have already been inspected for FOD, and are therefore not affected by this bulletin. LRU LRU Part Number Mod Level GSM or GSM XX (where XX is other than -00 or -10) 1 Table 2 NOTE This bulletin is not applicable to GSM 85A ( XX) servo gearboxes. COMPLIANCE Mandatory: This service bulletin must be incorporated in all GFC 700-equipped aircraft (excluding Cessna Mustang) within the time specified below. Which ever of the following occurs first: o The next maintenance activity that involves removal or inspection of the GSM 85 servo gearboxes o 100 hours of time in-service from the date of this bulletin o 3 months from the date of this bulletin Garmin will request an Airworthiness Directive (AD) for this issue. If/when an AD is issued, Garmin anticipates that it will refer to this service bulletin. REFERENCES GSA 8X/GSM 85(A) Installation Manual, OEM Aircraft Maintenance Manual Garmin Service Bulletin 0607 WARRANTY INFORMATION This modification is warranty reimbursable for the hours listed in the Manpower section. When completing the Garmin warranty claim, be sure to include the following information to ensure proper reimbursement. o Aircraft Serial Number o Aircraft Registration Number o Part Number of each GSM 85 o Serial Number of each GSM 85 o Clearly indicate that this Service Bulletin has been complied with Service Bulletin 0713 Page 2 of 11 May 29, 2007 Revision C

3 MANPOWER Aircraft Axis Manpower Hours Allowed per Procedure(s) A B C Columbia 350 Pitch Roll Columbia 400 Pitch Roll Diamond DA40 Pitch Roll/PT Mooney M20M/R Pitch/Roll/PT Roll Cessna 182 (no air conditioning) Pitch Pitch Trim Roll Cessna 182 (with air conditioning) Pitch Pitch Trim Cessna 206 (no air Roll Pitch conditioning) Pitch Trim Cessna 206 (with air Roll Pitch conditioning) Pitch Trim Hawker Beechcraft Pitch/Roll/PT G36/58 Yaw Table 3 Column A These are the allowable hours for the Modification Instructions in Section 4 Borescope Inspection where completing these steps did not necessitate the removal of a GSM 85 from the aircraft. These hours may not be combined with the hours in Columns B or C. Column B - These are the allowable hours for the Modification Instructions in Section 4 Borescope Inspection or 5 FOD Inspection by GSM Removal (not both) where any of these steps necessitated removal of a GSM 85. Column C - These are the allowable hours for setting the slip-clutch breakaway torque value as per Section 6 Reinstallation, which is necessary if a GSM 85 is replaced. If applicable, these hours may be additive to the hours in Column B, but not to the hours in Column A. IDENTIFICATION PROCEDURE Check the aircraft s maintenance records to determine if the inspection procedure in this bulletin has already been performed or is not applicable. If not previously accomplished and is determined to be applicable, proceed with the inspection steps listed in this bulletin. Service Bulletin 0713 Page 3 of 11 May 29, 2007 Revision C

4 MODIFICATION INSTRUCTIONS 1 General Instructions Any GSM 85s returned from Garmin will require a Garmin Slip-Clutch Fixture, P/N T to set the slip-clutch breakaway torque before it can be installed in the aircraft. Ensure the fixture is available before returning GSM 85s to Garmin. In some cases, a preset GSM 85 may be available from the aircraft manufacturer, contact them for availability. 2 Pre-Inspection Procedure Perform all of the following instructions for all affected GSM 85 servo gearboxes in the aircraft. 2.1 Move the flight controls full travel in every axis including the pitch trim, to verify smooth operation of all GFC 700 components. 2.2 If roughness is felt in any axis, determine if the roughness is caused by an airframe component other than a GSM 85 servo gearbox. If the roughness in any axis is caused by an airframe component other than a GSM 85, then correct the condition. If the roughness in any axis is caused by a GSM 85 servo gearbox, then remove and return suspect GSM 85 servo gearbox to Garmin for exchange. After receiving the replacement GSM 85 from Garmin, proceed to Section 6 Reinstallation. 2.3 When smooth operation of every axis with a flight control servo has been verified, proceed to one of the following sections as applicable: o Section 3 Extrusion Surface Inspection for aircraft at an OEM facility o Section 4 Borescope Inspection for inspection without removal of GSM 85 o Section 5 FOD Inspection by GSM Removal for inspection by removal of GSM 85 Service Bulletin 0713 Page 4 of 11 May 29, 2007 Revision C

5 3 Extrusion Surface Inspection NOTE The Extrusion Surface Inspection is for OEM Factories only. The potential for FOD resulted from a tumbling process that is selectively used to deburr the aluminum extrusion (housing) of the GSM 85. Since not all extrusions were deburred using the tumbling process, determining which extrusions were tumbled can also identify the candidate GSM 85s that require inspection. Only extrusions that were tumbled have the possibility of FOD in the extrusion. Garmin will provide samples (work-aids) of tumbled and non-tumbled extrusions to OEM s for this inspection process. If a Garmin provided work-aid is not available, proceed to Section 4 Borescope Inspection or Section 5 FOD Inspection by GSM Removal as applicable. Perform all of the following instructions for all affected GSM 85 servo gearboxes in the aircraft. 3.1 Inspect any visible side of the GSM 85 extrusion per the Garmin supplied workaids. Only one side of the extrusion must be visible for this inspection. 3.2 If the extrusion surface matches the tumbled work-aid (a dull surface, and without the adjacent parallel vertical lines), or if no conclusive determination can be made as to a tumbled or non-tumbled status of the extrusion, further inspection is necessary, proceed to Section 4 Borescope Inspection or Section 5 FOD Inspection by GSM Removal as applicable. 3.3 If the extrusion surface matches the non-tumbled work-aid, (a shiny surface, and the presence of adjacent parallel vertical lines), no possibility of FOD exists, and no further inspection is necessary, proceed to Step 3.4. Service Bulletin 0713 Page 5 of 11 May 29, 2007 Revision C

6 3.4 For GSM 85s part number or , mark the MOD 3 circle (on the serial tag) with an indelible marker indicating compliance with this bulletin. For GSM 85s part number XX (where -XX is other than -00 or -10), mark the MOD 1 circle (on the serial tag) with an indelible marker indicating compliance with this bulletin. NOTE If the serial tag is not accessible (for marking mod status) on an installed GSM 85 servo gearbox, a Supplemental Mod Status Tag (Figure 3-1), P/N (or equivalent that provides all of the same information) can be marked Mod 1 or Mod 3 per Step 3.4 and placed on an accessible surface of the GSM 85. Figure 3-1 The serial tag shall be marked with the mod status from the Supplemental Mod Status Tag during the next regular service that allows access to the serial tag. The supplemental tag should be removed from the GSM Proceed to Step 6.6 of this bulletin. Service Bulletin 0713 Page 6 of 11 May 29, 2007 Revision C

7 4 Borescope Inspection (optional process that may be performed instead of Section 5 FOD Inspection by GSM Removal) This method of inspection requires the availability of a flexible borescope. If inspection cannot be performed using a borescope, proceed to Section 5 FOD Inspection by GSM Removal. Perform all of the following instructions for all affected GSM 85 servo gearboxes in the aircraft. 4.1 Remove the GSA 8X servo from the GSM 85 per the OEM Aircraft Maintenance Manual. 4.2 Insert the borescope into the hole on the bottom side of the GSM 85 where the actuator gear of the GSA 8X servo inserts. 4.3 Maneuver the borescope to view all potential areas where foreign objects (FOD) may be present, particularly in the corners of the extrusion (Figure 4-1). Also look closely at the gears for the presence of FOD, rotate the gears to view all potential areas for FOD. FOD may be present anywhere inside of the extrusion, not only where shown in Figure 4-1. Tumbling Media (FOD) Figure If FOD is present, remove the GSM 85 per the OEM Aircraft Maintenance Manual and return the GSM 85 servo gearbox to Garmin for exchange. After receiving the replacement GSM 85 from Garmin, proceed to Section 6 Reinstallation. Service Bulletin 0713 Page 7 of 11 May 29, 2007 Revision C

8 4.5 If the borescope inspection produces no conclusive determination regarding the absence of FOD, proceed to Section 5 FOD Inspection by GSM Removal. 4.6 If it is conclusively determined that no FOD is present: o For GSM 85s part number or only, mark the MOD 3 circle (on the serial tag) with an indelible marker indicating compliance with this bulletin. o For GSM 85s part number XX (where -XX is other than -00 or -10), mark the MOD 1 circle (on the serial tag) with an indelible marker indicating compliance with this bulletin. NOTE If the serial tag is not accessible (for marking mod status) on an installed GSM 85, a Supplemental Mod Status Tag (Figure 4-2), P/N (or equivalent that provides all of the same information) can be marked Mod 1 or Mod 3 per Step 4.7 and placed on an accessible surface of the GSM 85. Figure 4-2 The serial tag shall be marked with the mod status from the Supplemental Mod Status Tag during the next regular service that allows access to the serial tag. The supplemental tag should be removed from the GSM 85 servo gearbox. 4.7 Proceed to Step 6.3 of this bulletin. Service Bulletin 0713 Page 8 of 11 May 29, 2007 Revision C

9 5 FOD Inspection by GSM Removal This inspection is performed if Section 3 Extrusion Surface Inspection and/or Section 4 Borescope Inspection were either not performed, or were performed and did not conclusively eliminate the possibility of the presence of FOD in the GSM 85 extrusion. NOTE While the GSM 85 servo gearbox is removed from the aircraft, Garmin recommends compliance with Service Bulletin Perform all of the following instructions for all affected GSM 85 servo gearboxes in the aircraft. 5.1 Remove the GSM 85 from the aircraft per the OEM Aircraft Maintenance Manual. 5.2 As each GSM 85 is removed, make sure it is appropriately tagged to indicate the axis (pitch, roll, yaw, or pitch trim) from which it was removed in the aircraft. A Slip Clutch Setting Label, P/N (or equivalent that provides all of the same information) may be used for this purpose (Figure 5-1). This information is recorded in aircraft maintenance records for reference when the parts are reinstalled. Date Torque Axis Aircraft label p/n Figure For GSM 85 servo gearboxes part numbered and only, check the serial tag for a MOD 2 marking. If MOD 2 is marked on these GSM 85s, proceed to Step 5.5. If MOD 2 is not marked on the serial tag, return the GSM 85 to Garmin for exchange. After receiving the replacement GSM 85 from Garmin, proceed to Section 6 Reinstallation. 5.4 For all GSM 85s part numbered XX where XX is other than -00 or -10, proceed to Step Use a thin (.098 to dia.), stiff tool (such as a small screwdriver) that can go into the mounting holes in each corner to verify it can be inserted at least 1.35". This is to make sure there is not any FOD lodged in the internal corners of the extrusion. If the tool cannot be fully and smoothly inserted and removed from all four mounting holes, it is assumed that FOD is present in the extrusion. If tool cannot be fully inserted, return the GSM 85 servo gearbox to Garmin for exchange. After receiving the replacement GSM 85 from Garmin, proceed to Section 6 Reinstallation. If no FOD is found proceed to Step 5.6. Service Bulletin 0713 Page 9 of 11 May 29, 2007 Revision C

10 5.6 Shake the unit vigorously along three different axes to listen for loose FOD inside the unit. When shaking the GSM 85, hold the capstan securely so that it does not rattle and is not misinterpreted as FOD. Any rattling from within the gearbox is assumed to be FOD. If rattling occurs, return the GSM 85 to Garmin for exchange. After receiving the replacement GSM 85 from Garmin, proceed to Section 6 Reinstallation. If no FOD is found proceed to Step Rotate the capstan at least two full turns in each direction to check for rough operation or obstructions in the gear-train. Any roughness in the rotation of the capstan is assumed to be caused by the presence of FOD. If there is any roughness in the rotation of the capstan, return the GSM 85 to Garmin for exchange. After receiving the replacement GSM 85 from Garmin, proceed to Section 6 Reinstallation. If no FOD is found and the gearbox is operating smoothly, proceed to Step If the GSM 85 complies with the preceding inspection steps 5.1 through 5.7, then mark the MOD status (on the serial tag) with an indelible marker per Table 4. LRU LRU Part Number Mod Level GSM or GSM XX (where XX is other than -00 or -10) 1 Table Proceed to Step 6.3 of this bulletin. Service Bulletin 0713 Page 10 of 11 May 29, 2007 Revision C

11 6 Reinstallation Perform all of the following instructions for all affected GSM 85 servo gearboxes in the aircraft. 6.1 Verify that the Mod Status on the serial tag of the GSM 85 is marked correctly per Table 5. LRU LRU Part Number Mod Level GSM or GSM XX (where XX is other than -00 or -10) 1 Table Set the slip-clutch breakaway torque per the OEM Aircraft Maintenance Manual. This procedure requires a Garmin Slip-Clutch Fixture, P/N T If an OEM has provided a GSM 85 with the torque value already set, this step is not required. 6.3 The gear on the GSA 8X servo that mates to the GSM 85, should be thoroughly cleaned, inspected for any damage, and re-lubed with grease that conforms to MIL-G-21164D. If any gear damage is found, the GSA 8X servo must be replaced. 6.4 Reinstall the GSM 85 (and any GSA 8X servos removed in Section 4) in its original location in the aircraft per the OEM Aircraft Maintenance Manual. During reinstallation, verify the servo motor is aligned with the GSM 85 servo gearbox and both are fully seated together with less than 1/32" gap before tightening the mounting bolts. Do not use the mounting bolts to draw the assemblies together if there is a larger gap, damage may result to the GSM 85 servo gearbox, requiring replacement. 6.5 Perform the post installation checkout described in the OEM Aircraft Maintenance Manual before returning the aircraft to service. 6.6 Make appropriate entry in the aircraft s maintenance records, noting that this Service Bulletin has been complied with and the basis for returning the aircraft to service. Note the serial number and new Mod Level that was marked on each GSM 85 as it was reinstalled. MATERIAL INFORMATION Slip Clutch Setting Label, P/N Supplemental Mod Status Tag, P/N Garmin Slip-Clutch Fixture, P/N T ADDITIONAL INFORMATION NA Service Bulletin 0713 Page 11 of 11 May 29, 2007 Revision C

12 Single Engine Service Bulletin June 4, 2007 TITLE GARMIN AUTOPILOT GSM 85 SERVO GEARBOXES INSPECTION EFFECTIVITY Model Serial Numbers 182T thru , thru , , , and T182T T thru T , T , T , T , T , T , T , T , T , T , T thru T , T , and T H thru , and T206H T thru T , T thru T , T , and T REASON To transmit Garmin Service Bulletin No Revision C: GSM 85 Inspection Procedure. DESCRIPTION Cessna has been informed by Garmin that a potential exists to have foreign object debris (FOD) located inside the GSM 85 Servo Gearbox. The GSM 85 Servo Gearbox is used with the roll, pitch, and pitch trim autopilot servo assemblies. Instructions are provided to do an inspection of the GSM 85 Servo Gearbox housings for the presence of FOD. Non-compliance with this Service Bulletin could potentially result in damage to a GSM 85 Servo Gearbox if FOD is present. COMPLIANCE Mandatory: shall be accomplished within the next 15 hours of operation or 30 days, whichever occurs first. NOTE: Use of the airplane autopilot is prohibited until compliance with this Service Bulletin has been completed. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. Page 1 of 14 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) , Facsimile (316) COPYRIGHT 2007

13 MANPOWER Model 182 airplanes: NOTE: Only the use of a flexible tip style borescope is acceptable to perform the borescope inspection. Borescope Inspection man-hours are as follows: 1.9 man-hours to perform the borescope inspection on all three of the GSM 85 Servo Gearboxes (roll, pitch, and pitch trim). If necessary, add 1.5 man-hours to remove and replace the GSM 85 Roll Servo Gearbox, if the borescope inspection detects FOD. If necessary, add 1.0 man-hour to remove and replace the GSM 85 Pitch Servo Gearbox, if the borescope inspection detects FOD. If necessary, add 1.0 man-hour to remove and replace the GSM 85 Pitch Trim Servo Gearbox, if the borescope inspection detects FOD. Physical Inspection man-hours are as follows: If necessary, 5.1 man-hours to remove, perform the physical inspection (if unable to perform the borescope inspection), and install (or replace if necessary) all three of the GSM 85 Servo Gearboxes (roll, pitch, and pitch trim). Airplanes equipped with air conditioning: If applicable, add 1.0 man-hour to either the borescope inspection or physical inspection for an airplane equipped with air conditioning. Model 206 airplanes: NOTE: Only the use of a flexible tip style borescope is acceptable to perform the borescope inspection. Borescope Inspection man-hours are as follows: 2.7 man-hours to perform the borescope inspection on all three of the GSM 85 Servo Gearboxes (roll, pitch, and pitch trim). If necessary, add 1.5 man-hours to remove and replace the GSM 85 Roll Servo Gearbox, if the borescope inspection detects FOD. If necessary, add 1.2 man-hours to remove and replace the GSM 85 Pitch Servo Gearbox, if the borescope inspection detects FOD. If necessary, add 1.1 man-hours to remove and replace the GSM 85 Pitch Trim Servo Gearbox, if the borescope inspection detects FOD. Physical Inspection man-hours are as follows: If necessary, 7.2 man-hours to remove, perform the physical inspection (if unable to perform the borescope inspection), and install (or replace if necessary) all three of the GSM 85 Servo Gearboxes (roll, pitch, and pitch trim). Airplanes equipped with air conditioning: If applicable, add 2.0 man-hours to either the borescope inspection or physical inspection for an airplane equipped with air conditioning. Page 2 June 4, 2007

14 REFERENCES Model 182/T182 Series 1997 and On Maintenance Manual Model 206/T206 Series 1998 and On Maintenance Manual NOTE: Make sure all publications used are complete and current. 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 MATERIAL PRICE AND AVAILABILITY The parts below are available from Cessna Parts Distribution through an appropriate Cessna Service Station for the suggested list price shown. NOTE: The GSM 85 Servo Gearboxes must be ordered only from and returned to Cessna Parts Distribution. CAUTION: PARTICULAR ATTENTION SHOULD BE GIVEN TO THE AIRPLANE MODEL AND LOCATION OF WHERE THE GSM 85 SERVO GEARBOXES ARE INSTALLED. ORDER ONLY THE REPLACEMENT GSM 85 SERVO GEARBOX PART NUMBER BASED ON THIS INFORMATION AS EACH GSM 85 SERVO GEARBOX IS SHIPPED PRESET WITH THE SPECIFIC SLIP CLUTCH TORQUE SETTING FOR EACH OF THE GSM 85 SERVO GEARBOX LOCATIONS. Part Number Description Qty/Airplane Price MS Clips, Turnbuckle Locking(182pitch) (206 pitch trim) 2 (if required) $ 0.38 (PS) ea MQ 100 MS U N R 011-N P 011-N PT 011-N R Clips, Turnbuckle Locking (182 roll and pitch trim) (206 roll and pitch) Grease (16 oz Cartridge, alternate MIL-G-21164) GSM 85 Servo Gearbox (Model 182 roll: Slip Clutch Torque Setting 55 ±7 in-lb) GSM 85 Servo Gearbox (Model 182 pitch: Slip Clutch Torque Setting 35 ±5 in-lb) GSM 85 Servo Gearbox (Model 182 pitch trim: Slip Clutch Torque Setting 45 ±6 in-lb) GSM 85 Servo Gearbox (Model 206 roll: Slip Clutch Torque Setting 77 ±9 in-lb) 4 (if required) $ 0.41 (PS) ea MQ 100 (as required) $ (VR) ea 1 (if required) $ 3, (N) ea 1 (if required) $ 3, (N) ea 1 (if required) $ 3, (N) ea 1 (if required) $ 3, (N) ea June 4, 2007 Page 3

15 Part Number Description Qty/Airplane Price 011-N P 011-N PT GSM 85 Servo Gearbox (Model 206 pitch: Slip Clutch Torque Setting 39 ±5 in-lb) GSM 85 Servo Gearbox (Model 206 pitch trim: Slip Clutch Torque Setting 64 ±6 in-lb) Supplemental Mod Status Tag 1 (if required) $ 3, (N) ea 1 (if required) $ 3, (N) ea 3 (if required) $ 0.01 (N) ea ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE CREDIT INFORMATION Applicable parts credit (Quantity per airplane required for the GSM 85 Servo Gearboxes, Turnbuckle Locking Clips, and/or the Supplemental Mod Status Tags), a miscellaneous parts credit of $2.76, and applicable labor allowance credit, as listed in the Man-Hours section of this Service Bulletin, will be provided per airplane to perform either the borescope or the physical inspection on all three of the GSM 85 Servo Gearboxes (roll, pitch, and pitch trim). NOTE: The borescope inspection is the preferred method of compliance for all three of the GSM 85 Servo Gearboxes. If the physical inspection is performed, applicable labor allowance credit, as listed in the Man-Hours section of this Service Bulletin, will be provided per airplane only for the physical inspection, and not the borescope inspection. Cessna records indicate that the following airplanes were delivered from the factory with air conditioning installed and are eligible to receive the additional labor allowance credit as listed in the Man-Hours section of this Service Bulletin: , , , T , T , T , T , T , T , T , T , T NOTE: For those airplanes affected that have had air conditioning installed post delivery, a copy of the logbook entry must be included with the Warranty Claim to be eligible to receive the additional labor allowance credit as listed in the Man-Hours section of this Service Bulletin. Freight will be credited at the most economical method unless pre-approved by Cessna. For pre-approval contact Cessna Parts Distribution Warranty Administration at Telephone: , Fax: or cpd2claims@cessna.textron.com. To receive credit, the work must be completed and a Warranty Claim submitted by a Cessna Single Engine Service Station within 30 calendar days of Service Bulletin compliance before the credit expiration dates shown below. NOTE: Removed GSM 85 Servo Gearboxes requiring replacement based on the inspection results of these Service Bulletins must be returned with the Warranty Claim. Also note on the Warranty Claim the position/location from which the GSM 85 Servo Gearbox was removed. Domestic... June4,2008 International... June4,2008 Special Note to Service Stations: When you complete the Warranty Claim, the labor allowance claimed shall be itemized for each above action completed. Page 4 June 4, 2007

16 ACCOMPLISHMENT INSTRUCTIONS Weight And Balance Information Negligible Material Information The parts below may be necessary: NEW P/N QUANTITY DESCRIPTION OLD P/N DISPOSITION MS (182 pitch) (206 pitch trim) MS (182 roll and pitch trim) (206 roll and pitch) Clips, Turnbuckle Locking Clips, Turnbuckle Locking 011-N R 1 (Model 182 roll) GSM 85 Servo Gearbox 011-N P 1 (Model 182 pitch) GSM 85 Servo Gearbox 011-N PT 1 (Model 182 pitch trim) GSM 85 Servo Gearbox 011-N R 1 (Model 206 roll) GSM 85 Servo Gearbox 011-N P 1 (Model 206 pitch) GSM 85 Servo Gearbox 011-N PT 1 (Model 206 pitch trim) GSM 85 Servo Gearbox Supplemental Mod Status Tag Same Same Discard Discard Return to Cessna Return to Cessna Return to Cessna Return to Cessna Return to Cessna Return to Cessna Same The following material, or equivalent, may be necessary: NAME NUMBER MANUFACTURER USE Grease U (alternate MIL-G-21164) Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS To apply to the gear on the GSA 8X Servo Actuators June 4, 2007 Page 5

17 The equipment below, or equivalent, will also be necessary. Borescope Name Number Manufacturer Use Commercially available Olympus, Storz, or equivalent To do the visual inspection of servo gearbox for FOD 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.) AMSAFE Diagnostic Tool Cessna Aircraft Company Cessna Parts Distribution 5800 East Pawnee PO Box 1521 Wichita, KS *Todoafunctional test of the AMSAFE inflatable restraint *Refer to E AMSAFE SMM (Supplemental Maintenance Manual) for testing of the AMSAFE Inflatable Restraint system. 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. Put a support stand under the tail tie-down ring to support the tailcone. (Refer to the applicable Maintenance Manual, Chapter 7, Jacking - Maintenance Practices.) 3. Get access to the and Garmin GSM 85 Servo Gearboxes to do the attached Garmin Service Bulletin No Revision C or latest revision. NOTE: Do the Physical Inspection Section of the Garmin Service Bulletin No Revision C or latest revision only if you cannot comply with the Borescope Inspection. A. Model 182 airplanes (Refer to Figure 1.) (1) Remove the right wing access panels 620GB, 620FB, and 620BB to get access to the GSM 85 Roll Servo Gearbox. Keep the screws. (Refer to the Model 182/T182 Series 1997 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) Page 6 June 4, 2007

18 (2) Remove the tailcone access panel 310AR from the right side of the airplane. Keep the screws. (Refer to the Model 182/T182 Series 1997 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) (3) Do Garmin Service Bulletin No Revision C or latest revision. Refer to the Maintenance Manual for removal and installation of the gearbox if removal is necessary for physical inspection or replacement. NOTE: The Step 5 Note of Garmin Service Bulletin No Revision C is not applicable to Cessna airplanes. B. Model 206 airplanes (Refer to Figure 2.) (1) Remove the right wing access panels 610AB and 610D to get access to the GSM 85 Roll Servo Gearbox. Keep the screws. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) (2) Remove the marker beacon antenna and tailcone access panel 310AB as an assembly to get access to the GSM 85 Pitch Trim Servo Gearbox. Keep the screws. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) (3) Get access to the GSM 85 Pitch Servo Gearbox as follows: WARNING: IF THE AIRPLANE HAS AMSAFE INFLATABLE RESTRAINTS, DO NOT REMOVE SEATS WITH THE SEAT BELTS BUCKLED OR THE ELECTRONICS MODULE ASSEMBLY (EMA) CONNECTED. DAMAGE TO THE SYSTEM CAN OCCUR AND AN ACCIDENTAL DEPLOYMENT OF THE SYSTEM CAN CAUSE INJURY. (a) (b) (c) (d) (e) (f) (g) (h) (Airplanes equipped with AMSAFE Inflatable Restraints on the aft bench seat) Disarm the AMSAFE Inflatable Restraints. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 25, Inflatable Restraint System - Maintenance Practices.) Remove the rear seat. Keep the attaching hardware. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 25, Rear Seat - Maintenance Practices.) Remove the baggage curtain. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 25, Interior Upholstery - Maintenance Practices.) Remove the GIA-63 (Comm 1 and Comm 2) Integrated Avionics Units (IAU) and the GTX-33 Transponder and put them in a safe area. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 23, Communications - Maintenance Practices and Chapter 34, GTX-33 Transponder - Maintenance Practices.) Remove the Garmin Remote Avionics Rack. Keep the attaching hardware. (Refer to the Model 206H and T206H Illustrated Parts Catalog, Chapter 53, Remote Avionics Structure Installation - NAV III.) Remove the tailcone avionics fan. Keep the attaching hardware. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 21, Avionics Cooling - Maintenance Practices.) (Airplanes equipped with air conditioning) Remove the two large air conditioning ducts. Remove the aft avionics divider. Keep the attaching hardware. (4) Do Garmin Service Bulletin No Revision C or latest revision. Refer to the Maintenance Manual for removal and installation of the gearbox if removal is necessary for physical inspection or replacement. NOTE: The Step 5 Note of Garmin Service Bulletin No Revision C is not applicable to Cessna airplanes. June 4, 2007 Page 7

19 4. Install removed equipment as follows: A. Model 182 airplanes (1) Install access panel 310AR with the kept screws. (Refer to the Model 182/T182 Series 1997 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) (2) Install the right wing access panels 620GB, 620FB, and 620BB with the kept screws. (Refer to the Model 182/T182 Series 1997 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) B. Model 206 airplanes (1) Install the aft avionics divider with the kept attaching hardware. (2) (Airplanes equipped with air conditioning) Install the two large air conditioning ducts. (3) Install the tailcone avionics fan with the kept attaching hardware. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 21, Avionics Cooling - Maintenance Practices.) (4) Install the Garmin Remote Avionics Rack with the kept attaching hardware. (Refer to the Model 206H and T206H Illustrated Parts Catalog, Chapter 53, Remote Avionics Structure Installation - NAV III.) (5) Install the GIA-63 (Comm 1 and Comm 2) Integrated Avionics Units (IAU) and the GTX-33 Transponder. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 23, Communications - Maintenance Practices and Chapter 34, GTX-33 Transponder - Maintenance Practices.) (6) Install the baggage curtain. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 25, Interior Upholstery - Maintenance Practices.) (7) Install the rear seat with the kept attaching hardware. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 25, Rear Seat - Maintenance Practices.) WARNING: FOLLOW ALL SAFETY PRECAUTIONS WHEN YOU WORK ON OR NEAR THE INFLATABLE RESTRAINT SYSTEM. THE INFLATOR ASSEMBLY IS A STORED, GAS/ENERGETIC MATERIAL DEVICE AND CAN CAUSE DAMAGE TO THE SYSTEM AND/OR INJURY TO PERSONNEL IF ACCIDENTALLY DEPLOYED (8) (Airplanes equipped with AMSAFE Inflatable Restraints on the aft bench seat) Arm the AMSAFE Inflatable Restraints. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 25, Inflatable Restraint System - Maintenance Practices.) (9) (Airplanes equipped with AMSAFE Inflatable Restraints on the aft bench seat) Do an operational check of the seat belt system. (Refer to the AMSAFE Supplemental Maintenance Manual, part number E ) (10) Install the marker beacon antenna and tailcone access panel 310AB with the kept screws. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) (11) Install the right wing access panels 610AB and 610D with the kept screws. (Refer to the Model 206/T206 Series 1998 and On Maintenance Manual, Chapter 6, Access/Inspection Plates - Description and Operation.) 5. Remove maintenance warning tags from battery and external power receptacle and connect the battery. 6. Do operational checks of all of the systems that had components removed during compliance with this Service Bulletin. Page 8 June 4, 2007

20 7. Make an entry in the airplane logbook that states compliance and method of compliance with this Service Bulletin. June 4, 2007 Page 9

21 Figure Garmin GSM 85 Servo Gearbox Inspection (Sheet 1) Page 10 June 4, 2007

22 Figure Garmin GSM 85 Servo Gearbox Inspection (Sheet 2) June 4, 2007 Page 11

23 Figure Garmin GSM 85 Servo Gearbox Inspection (Sheet 1) Page 12 June 4, 2007

24 Figure Garmin GSM 85 Servo Gearbox Inspection (Sheet 2) June 4, 2007 Page 13

25 OWNER NOTIFICATION On June 4, 2007 a copy of this Service Bulletin will be sent to the affected owners of record. It is recommended that the airplane owner contact a Cessna Single Engine Service Station for detailed information and make arrangements to have Service Bulletin accomplished on their airplane. * * * * * * * Page 14 June 4, 2007