### Lake Central Aircraft Services , 

### Lake Amphibian Stabilizer Fitting LC-2200-21 Installatio n Instructions Document CI- LC-2200-2 1 , Rev B, August 26 2005, Page 1 of 3

INTRODUCTION CANADA**DEPAA~** OF TRA i "'St'OKI AIRCRAFT CER11FICA TION BRANCH**APPRO~t>** DATE: S¢'Pf {L( 

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The Lake Central Aircraft Services Lake Amph i bian stab il izer frtt i ng is an STC approved replacement part for the OEM part. The LCAS part is made from 4130**~!loy** steel. and cadmium plated and epoxy primed for corrosion protection. Its i nstall ation provid es im p roved service life , and greater fatigue and damage resistance for the horizontal stabilizer structure. INSTALLATION Complia nce wrth Revo Inc. Service Boneti n 8 -78, dated Aprn 03 1998 is necessary to ass ure an airworthy installatron. Please refer to Revo Inc. Service Bulletin B-78, dated April 03 1998 , a copy of wh i ch is supplied with th is kit. Note : Installati on of a Lake Central A i rcraft Services stabilizer fitting LC-2200-2 1 whi ch has been**~o ve~**  from another aircraft . which has been in service is proh i bited . Remove horizontal stabilizer and elevators from the a ircraft as f ollows : Disconnect elevator torque tube 

### PN 2-7207-5 from each elevator and remove outboard elevato r hing e p i n. Disconnect trim tab torque tube through lowe r access holes on u nders ide of stabilizer, just outboard of vertical fin . Adequately s u pport horizonta l t:tif. Remove bolts from forwa rd beam fitting . Remove the two AN6 bolts from frtting 2-2200-21 for each stabilizer and lift each staoifize r away from aircraft . Note the length of these two bolts, then discard them . Before drilling fitting 2 -2200-21 off, measure the clearance as per Revo Inc. Service Bulletin**~78 ,**  dated April 03 1 998 i nstructi on . also verify the origin al fittin g pos ition of 15/16" as illustrated on page 2 of Revo Inc. Service Bulletin 8-7 8. dated April 03 1998 .

## Lake Central Aircraft Services, Lake Amphibian Stabilizer Fitting LC-2200-21 Installation In structions Document CI-LC-2200-2 1 , Rev B, August 26 2005, Page 2 of 3 There must be a minimum of 5/32" clearance, as indicated in Revo In c . Service Bulletin B-78 , dated April 03 1998 . After measuring clearance , note the amount of additional clearance required . Mark the fittings " left" and " right". Drill off each origina l 2 - 2200-21 fitting, being very careful to not enlarge the holes i n old fittings , they will be required as guides later. A l so dri ll out the next two (2) rivets outboard in these rivet lines for the installation of doublers inside the stabilizer after removal drill up to 5/32". Support spa r properly from behind to prevent damage when driving out rivet shanks . With fittings removed , you can now trim the end of the stabilizer spar and sk i n back to provide necessary clearance . The trimmed edge is to be smoo. th , and free from sharp edges , or stress rais i ng f i nish marks , then re-prim e and paint t rimm ed area . Mark each of the four doublers with permanent felt tip pen, as to its final location (eg : " to p left", "top right" etc.). Pos i tion each of the four doublers LC-2200-21 D i nside the stab i l izer at i ts locati on , agai nst the i ns ide face of the spar, between the ins id e of the inboa rd end rib , and the next outboard rib . The doubler must be positioned 1/8 " away from the insi de of the upper and lower skins (use a spacer against the respective skin to set the do ubler l ocation ). Trace through all of the rivet holes so as to be able to confirm that none will be with i n Y. " of any edge of the doubler. Remove the doubler and check each of the marked holes as described . If all of the marked rivet holes are found to be located more than Y. " from a ny edge of the doubler , dri ll on ly the locator hole in the doubler as per drawing LC-2200-21, page 4 of 4 . Position the doubler back inside the stabilizer, Cleco it by the two end holes , and while s upporting the doubler with a suitable block, drill through the remaining holes . Remove the doubler to clean out any dri ll chips , and return the doubler to its position . Cleco it into place at the outboard two rivet holes , awaiting the i nstallatio n of the fitting , after which all will be riveted together. Mark the LC-2200-21 fittings as to " left" and " right" with permanent felt t i p pen . Select fitting to have part number face aft so it can be seen after i nstallation . Place an orig i nal fitting 2 -2200-21 over the new LC-2200- 21 as a drill gu i de . Use new bolts to hol d old an d new fitting together for correct alignment Using drill press , drill rivet holes i n each LC-2200-21 fitt i ng , be in g careful to keep holes square wi th a surface and centered using orig i nal fitting as a guide . Prior to installing new fittings , ensure proper clearance of the spar flange , as required by Revo Inc. Service Bulleti n B-78 , dated April 03 1998 , before riveting . Prime the new holes drilled in LC-2200-21 , and fit the rivet with wet primer. Wh i le in stall in g the fitt i ng , app ly a thin coating of Bosti k 1000 or 3M 5200 sealing compound in a thin, even coat over the entire mating surface of the fitti ng . As the fitting i s drawn into place on the 

### spar during riveting, assure that an even bead of sealant exist

### Lake Central Aircraft Services, . Lake Amphibian Stabilizer Fitting LC-2200-21 Installation Instructions Document CI-LC-2200-21 , Rev B, August 26 2005 , Page 3 of 3 around joint edges of the fitting . Add a fillet if necessary. It i s desirable to exclude all moisture from between the fitting and the spar. Rivet the fitting and doubler to spar in accordance with the standards of AC43-13-1 

### B. The rivets required are as follows: Stabilizer attach fitting , AN4 70AD6-1 0 where rivets go through fitting to original structure , AN470AD6-11 are used in holes where doubler and f itting are ri veted together. The two rivets that hold doubler only to ori ginal stab i lizer structure are AN470AD5-6 . With fi tting i nstalled on spar. apply protective matching paint prior to installing stabil izer on aircraft. Re i nstall stabilizer in reverse order of disassembly . Install fitti ngs to vert ical stab i lizer spar wi th new AN6 bolts of the same length as those removed . Prior to inserting rear fitting AN6 bolts , grease shank between head and threads only . This procedure will allow you to obtain a consistent torque value of 200 in . lbs . Torque each bolt to th is value . Comp lete the reassembly of the tail of the aircraft in accordance with prevailing Lake publications . Check the tra vels of the elevator, elevator trim and rudder following reinstallation to assure that they conform to Lake specifi cations . Complete the required documentation for the work accomplished .

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