SB E Mandatory September 19, 2008 Model 300, 350, & 400

Transcription

1 SERVICE BULLETIN Linear Bearing Inspection SB E Mandatory September 19, 2008 Model 300, 350, & 400 EFFECTIVITY Cessna Aircraft Model 300 (LC40-550FG) serial numbers ; Model 400 (LC41-550FG) serial numbers , ; Model 350 (LC42-550FG) serial numbers , REVISION HISTORY Rev Description Date N/A Initial Release (no stated revision level) March 14, 2007 A Revised to allow compliance if aircraft has aileron linear August 29, 2007 bearing inspection panels installed. B Updated to reflect company name change to Cessna December 10, 2007 C Updated to correct company name change revision February 18, 2008 D Added ending serial numbers for LC41 and LC42 models May 29, 2008 E Clerical correction to AD number September 19, 2008 PURPOSE To provide access to the aileron and elevator linear bearings for foreign object debris (FOD) inspection. COMPLIANCE Note: If this bulletin has been complied with at a previous revision no further compliance is required. MANDATORY-SECTION I-PILOT ACTION -to be complied with before further flight prior to engine start. MANDATORY-SECTION II-MAINTENANCE ACTION - Per FAA AD , compliance shall be accomplished within 35 flight hours from April 9 th, APPROVAL FAA approval has been obtained on all technical data in this Service Bulletin that affects type design. RESOURCES SECTION I-PILOT ACTION-Less than 5 minutes before every flight. SECTION II-MAINTENANCE ACTION-Four (4) hours of labor required for compliance with this Mandatory Service Bulletin. Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) , Facsimile (316) Copyright 2008 Cessna Aircraft Company cannot be responsible for the quality of work performed by others while fulfilling the requirements of this Service Bulletin. Procedures specified in this Service Bulletin must be accomplished in accordance with the standards and techniques set forth in the approved AMM and all applicable government regulations, standards and advisories. All process and material information referenced within this Service Bulletin is derived from Cessna Aircraft Company FAA approved specifications. Page 1 of 8

2 MATERIAL INFORMATION The following materials are required for compliance with this Service Bulletin. Parts can be obtained from Cessna or procured locally (P/L) as indicated. ITEM NO. DESCRIPTION P/N OR SPEC. SUPPLIER QUANTITY 1 Mandatory Service Bulletin SB E Cessna 1 2 ¾ Diameter Hole Saw n/a P/L 1 3 Anti-chafe tape 1 wide, clear LA Cessna 12 INSTRUCTIONS FOR COMPLIANCE SECTION I-PILOT ACTION Add the additional required item found in APPENDIX A: SB D, to the BEFORE STARTING ENGINE checklist. It is required to be performed prior to each flight per the FAA Mandated Service Bulletin SB D. Once this item has been added as a required additional item to the BEFORE STARTING ENGINE checklist, make a logbook entry stating the following: Pilot Name & Certificate Number Complied with SB D Section I-Pilot Action The aircraft may be operated up to the limit of 35 flight hours prior to performing SECTION II- MAINTENANCE ACTION by an appropriately licensed mechanic as described in the section titled COMPLIANCE. SB E Page 2 of 8 September 19, 2008

3 SECTION II-MAINTENANCE ACTION NOTES: Please read the Service Bulletin in its entirety prior to performing any maintenance action All instructions are to be performed on both left and right sides of aircraft. Reference AMM Section 27. The Aileron Linear Bearing inspection requirements detailed below (steps 5 thru 11) may be accomplished by installing the wing station 86 inspection hole as described in this Service Bulletin or by removal of the Linear Bearing Access Panel if the aircraft is so equipped. The Linear Bearing Access Panel is a 2.5 in x 5.0 in access panel installed in both lower wing skins at wing station 86.. AILERON If the aircraft is equipped with the newer machined flap hinges, adequate access and working space can be achieved by following steps 1 thru 3. If the aircraft is equipped with the original cast flap hinges, the flaps must per removed per Chapter 27 of the AMM. See Photo 1 New Style Machined Hinge Original Style - Cast Hinge Photo 1 1. Remove the flap final drive attachment hardware (located at WS65.5) per the Cessna AMM. Reference Photo 2. Carefully allow the flaps to hang free and ensure they do not contact the gear leg fairings and cause damage. Photo 2-View of Attachment Hardware SB E Page 3 of 8 September 19, 2008

4 2. Remove the clear flap bellcrank access panels (located near WS60). 3. Remove the clear aileron bellcrank access panels (located near WS148). 4. Using Figure 1 as a reference, locate WS86. The centerline of the flap hinge to the inboard side is WS65.5, and the centerline of flap hinge to the outboard side is WS Using these references, locate WS86, center-punch and drill a ¾ diameter hole in the flap cove as shown in Figure 2 and Photo 3. Use a vacuum while drilling to minimize any debris entering the wing. The aileron control rod is directly behind the new hole, so take care to only penetrate the skin and no deeper. Once hole is cut, ensure all material that was removed is accounted for. Figure 1 Top Down View of Wing Figure 2 Views Showing Inspection Hole in Flap Cove SB E Page 4 of 8 September 19, 2008

5 Photo 3-View of WS86 Hole in Flap Cove 5. Using a rigid borescope with a 90 head, inspect each side of the linear bearing for foreign object debris (FOD) through the new WS86 hole. A partial cross section is referenced in Figure 3. Figure 3-Bearing Cutaway-Riveted Style and Screw Style 6. While using the borescope, move aileron controls through their full range of motion and ensure there is no scarring or damage to the aluminum tube in the form of nicks or gouges on the control rod in the vicinity of the aileron linear bearing. Normal wear in the area of the bearing will show a slightly darker color than is present on the other portions of the control rod. Ensure there is no debris or adhesive attached to the aileron control rod, bearing housing, bearing race, or ball bearing. 7. If damage, attached adhesive or irretrievable FOD is noted call Cessna Product Support at Using a vacuum, clean the aft bays containing the aileron linear bearing (between aft ribs 65.5 and 105.5) 9. Using a vacuum, clean the aft bays inboard (between aft ribs 24.5 and 65.5) and outboard (between aft ribs and 151) of the bay containing the linear bearing. SB E Page 5 of 8 September 19, 2008

6 10. To confirm debris was removed, use borescope to inspect areas through the new WS86 hole, and through existing WS104.5 flap hinge hole, and both access panel holes for any additional foreign objects. Remove any debris found in these areas. 11. Move control stick throughout the full range of deflections. Full deflections should be smooth with no tactile or audible indications of grabbing, catching, or ratcheting of controls. There should be no differences between left and right roll. 12. Cover WS86 inspection hole that was created per the Service Bulletin with a small portion of clear tape. 13. Reattach the flap drive attachment hardware and install access panels per the Cessna AMM. 14. Make a final inspection of the completed installation (see Photo 4 for reference). Photo 4-View of WS86 Hole in Flap Cove Looking Inboard ELEVATOR 1. Remove interior panels as required to obtain access to the four elevator (see Figure 4) control rod linear bearings (see Figure 3) per AMM Section 25 and perform a FOD inspection before further flight. SB E Page 6 of 8 September 19, 2008

7 Figure 4 View of Linear Bearing in Fuselage for Elevator Control Rods 2. Inspect the linear bearings for any debris. Move elevator controls through their full range of motion and ensure there is no scarring or damage to the aluminum tube in the form of nicks or gouges on the control rod in the vicinity of the elevator linear bearing. Normal wear in the area of the bearing will show a slightly darker color than is present on the other portions of the control rod. Ensure there is no debris or adhesive attached to the elevator control rod, bearing housing, bearing race, or ball bearing. 3. If no damage or foreign debris is noted, reinstall parts removed per the AMM. 4. If damage, attached adhesive or other contamination is noted call Cessna Product Support at If debris is noted, remove the control rod per the AMM and thoroughly clean both the bearing and the control rod. Ensure all debris is removed. Replace parts removed per the AMM and check elevator control function. Full deflections should be smooth with no tactile or audible indications of grabbing, catching, or ratcheting of controls. There should be no differences between up or down pitch. 6. If everything is satisfactory for both aileron and elevator control systems, make a logbook entry stating compliance with Service Bulletin SB D. SB E Page 7 of 8 September 19, 2008

8 APPENDIX A: SB D The following is the addition to the BEFORE STARTING ENGINE checklist. It is required to be performed prior to each flight per the FAA Mandated Service Bulletin SB D ADDITIONAL REQUIRED ITEM TO THE BEFORE STARTING ENGINE CHECKLIST 1. Before engine start, move control stick throughout the full range of deflections to each respective control stop. Full deflections should be smooth with no tactile or audible indications of grabbing, catching, or ratcheting of controls. There should be no differences between left and right roll, or up and down pitch. 2. If discrepancies in roll or pitch axis are noted, the aircraft may not be flown prior to performing Service Bulletin SB D, SECTION II-MAINTENANCE ACTION by an appropriately licensed mechanic. SB E Page 8 of 8 September 19, 2008