Lake Central Aircraft Services, 

Lake Amphibian Stabilizer Fitting LC-2200-21 Installation Instructions 

Document CI-LC-2200-21, Rev B, August 26 2005, Page 1 of 3 

INTRODUCTION 

CANADA DEPAA~ OF TRAi"'St'OKI 

AIRCRAFT CER11FICA TION 

BRANCH 

APPRO~t> 

DATE: S¢'Pf {L( '2.ooS" 

~~-RT1_F_C~-r""TE~# .'S ..s.:qos-71 

ISSUE:_ • _ 

The Lake Central Aircraft Services Lake Amphibian stabilizer frtting 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 installation provides 

improved service life, and greater fatigue and damage resistance for the horizontal 

stabilizer structure. 

INSTALLATION 

Compliance wrth Revo Inc. Service Bonetin 8-78, dated Aprn 03 1998 is necessary to 

assure an airworthy installatron. Please refer to Revo Inc. Service Bulletin B-78, dated 

April 03 1998, a copy of which is supplied with this kit. 

Note: Installation of a Lake Central Aircraft Services stabilizer fitting LC-2200-21 which 

has been ~ove~ from another aircraft. which has been in service is prohibited. 

Remove horizontal stabilizer and elevators from the aircraft as follows: 

Disconnect elevator torque tube PN 2-7207-5 from each elevator and remove outboard 

elevator hinge pin. 

Disconnect trim tab torque tube through lower access holes on underside of stabilizer, 

just outboard of vertical fin. 

Adequately support horizontal t:tif. Remove bolts from forward beam fitting. 

Remove the two AN6 bolts from frtting 2-2200-21 for each stabilizer and lift each 

staoifizer 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 1998 instruction. also verify the original fitting position of 

15/16" as illustrated on page 2 of Revo Inc. Service Bulletin 8-78. dated April 03 1998. 
Lake Central Aircraft Services, 

Lake Amphibian Stabilizer Fitting LC-2200-21 Installation Instructions 

Document CI-LC-2200-21, Rev B, August 26 2005, Page 2 of 3 

There must be a minimum of 5/32" clearance, as indicated in Revo Inc. 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 original 2-2200-21 fitting, being very careful to not 

enlarge the holes in old fittings, they will be required as guides later. Also drill 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 spar 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 skin back to 

provide necessary clearance. The trimmed edge is to be smoo.th, and free from sharp 

edges, or stress raising finish marks, then re-prime and paint trimmed area. 

Mark each of the four doublers with permanent felt tip pen, as to its final location (eg: 

"top left", "top right" etc.). Position each of the four doublers LC-2200-21 D inside the 

stabilizer at its location, against the inside face of the spar, between the inside of the 

inboard end rib, and the next outboard rib. The doubler must be positioned 1/8" away 

from the inside of the upper and lower skins (use a spacer against the respective skin to 

set the doubler location). Trace through all of the rivet holes so as to be able to confirm 

that none will be within 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 any edge of the 

doubler, drill only 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 

supporting the doubler with a suitable block, drill through the remaining holes. Remove 

the doubler to clean out any drill chips, and return the doubler to its position. Cleco it into 

place at the outboard two rivet holes, awaiting the installation of the fitting, after which all 

will be riveted together. 

Mark the LC-2200-21 fittings as to "left" and "right" with permanent felt tip pen. Select 

fitting to have part number face aft so it can be seen after installation. Place an original 

fitting 2-2200-21 over the new LC-2200-21 as a drill guide. Use new bolts to hold old and 

new fitting together for correct alignment 

Using drill press, drill rivet holes in each LC-2200-21 fitting, being careful to keep holes 

square with a surface and centered using original fitting as a guide. 

Prior to installing new fittings, ensure proper clearance of the spar flange, as required by 

Revo Inc. Service Bulletin B-78, dated April 03 1998, before riveting. 

Prime the new holes drilled in LC-2200-21 , and fit the rivet with wet primer. 

While installing the fitting, apply a thin coating of Bostik 1000 or 3M 5200 sealing 

compound in a thin, even coat over the entire mating surface of the fitting. As the fitting 

is 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 is 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 fitting are riveted together. The two rivets that hold doubler only to original stabilizer 

structure are AN470AD5-6. 

With fitting installed on spar. apply protective matching paint prior to installing stabilizer 

on aircraft. Reinstall stabilizer in reverse order of disassembly. Install fittings to vertical 

stabilizer spar with 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 this value. 

Complete the reassembly of the tail of the aircraft in accordance with prevailing Lake 

publications. Check the travels of the elevator, elevator trim and rudder following 

reinstallation to assure that they conform to Lake specifications. 

Complete the required documentation for the work accomplished. 

-END-