by bob pastusek

Lancair 300-series and IV/IV-P/ES and Legacy aircraft were originally equipped with a nose gear strut made by ESCO. The company is no longer in business, but there are a number of units still in operation among the Lancair fleet. These units require regular inspection and servicing.

We disassembled an ESCO nose strut from an IV-P at the 2011 LOBO event in Branson, MO to observe its multiple internal components and functions. Kevin Risse at Risse Racing (kevin [at] risseracing.com/www.risseracing.com) has continued to maintain and upgrade these units for all owners but does not sell replacement components or seals for owner-servicing. Risse Racing has also developed a form/fit/function replacement strut that is superior in design to the out-of-production ESCO struts. Because of the thousands of ESCO struts still in use, I'd like to pass on some servicing/testing recommendations that can help you maintain it, and to decide whether to send your strut to Risse for overhaul or upgrade.

NOTE: Chris Zavatson has made available to LOBO an excellent write-up on overhauling the hydraulic actuators used in Lancair aircraft. This is an excellent companion document to this one. Click here to read it or download a copy for your reference library.

The ESCO struts used on both 2- and 4-seat Lancairs (after the 200-series) have received three major modifications over the years. The first was to add an internal "centering" cam to straighten a cocked nose wheel during gear retraction. This centering cam functions as the strut fully extends when the nose wheel lifts during takeoff. The second was to change the dimensions of the parts making up the shimmy damper to allow the bottom of the strut (and nose wheel) to pivot 60 degrees either side of center, as compared to 45 degrees of pivot with the unmodified parts. Fifteen degrees of additional pivot doesn't sound like much, but it's enough to allow you to lock one main wheel and pivot around it—something you can't do with a 45 degree pivot limit. The third change was to add an external bracket at the base of the strut. Two versions are in use. The original requires flange removal to install. The newer version is a two piece design that can be mounted externally.

Pivot Limit

The pivot limits in both original and modified struts are established by an internal plate that's attached to the strut piston with two very small (#4) hardened cap screws. The cap screws are durable enough to hold during normal taxi and maneuvering with a standard Lancair hand tow bar, but are easily sheared by exceeding the pivot limit using a tractor with tow bar. The pivot limit plate also serves as a shimmy damper by restricting oil flow from one side of the strut cylinder to the other when the piston rotates within the cylinder. Shearing of the screws is not visible from the outside of the strut, nor will it cause an external leak, BUT THE SHIMMY DAMPING FUNCTION OF THE STRUT IS TOTALLY LOST. Lancair can provide a pivot limit decal, or you can make your own, but this, along with a "Hand Tow Only" decal are recommended if anyone but you will move the aircraft.

Strut Testing

I recommend the following tests to: 1) determine if your strut incorporates the self-centering mechanism, 2) determine whether the shimmy damper is functional, and 3) determine the pivot limits of your nose strut. The instructions below assume you have the strut installed on an aircraft.

NOTE: You can test your strut "on the bench" by replicating the steps noted below with the strut in a vertical "normal operating" position. You can also accomplish the damper test without deflating the strut and removing the Schrader valve. You will need two flat metal plates (steel or aluminum thick enough not to flex) with grease between them. Place the greased plates under the nose gear and allow the aircraft weight to rest on them. Start at step 5 below, and adapt steps 6-11.

For the full procedure:

1. Jack the aircraft to fully extend the nose strut.
2. Remove the cap from the Schrader valve, about 1/3 down from the top, on the front of the strut.
3. Carefully release the nitrogen gas by depressing the Schrader valve, then remove the valve.
4. Centering Test:
   1. With the aircraft secured from falling, grasp the nose wheel and attempt to pivot it.
   2. If it pivots with some resistance WITHOUT rising up into the strut, your strut doesn't have a centering mechanism installed. If it rises up while pivoting, you likely have a centering mechanism installed.
   3. If it doesn't pivot, place a block under the nose wheel high enough to compress the strut at least 1½".
   4. Again, attempt to pivot the nose wheel. It should pivot with some resistance caused by the seals and dampening mechanism.
   5. Turn the nose wheel 15-20 degrees left or right, then remove the block supporting it allowing it to fully extend under gravity.
   6. The strut should pivot to straight ahead as it extends if a centering mechanism is present. You may have to give it a bit of a nudge to offset the lack of pressurization, but the extension and centering should be definite.
5. Shimmy Damper & Pivot Limit Test:
   1. Place a block under the nose wheel thick enough to fully compress the strut. If the strut is fully serviced, compressing it should eject a bit of oil from the Schrader valve opening. If no oil is visible through the Schrader valve opening with the strut vertical and fully compressed, service to the level of the opening with heavy duty motorcycle strut oil. Do not use hydraulic fluid to service the strut as it does not contain anti-foaming additive that's important for the shimmy damper function. The strut must be vertical and FULLY COMPRESSED when adding oil. Do not over-service the strut with oil! IMPORTANT NOTE: If the strut is low on oil and you have not noticed an external leak, it's likely fluid has leaked into the hollow center of the strut tube. Confirming this requires major disassembly of the strut; the fix will definitely require disassembly and specialized tools/parts. I recommend you send the strut to Risse Racing if you suspect an internal fluid leak.
   2. With the strut held compressed at least 1½", but not fully compressed, grasp the nose wheel and pivot it in either direction until it hits the internal stop.
   3. The wheel/lower strut piston should pivot with some resistance (from the shimmy damper) when twisted rapidly. You should feel resistance through the full pivot range and when reversing directions. A reduction of resistance when changing directions indicates air in the damper chamber. Extend, then fully compress the strut several times to eject the air, then return to this step. You may need to do this 2-3 times to eliminate all the air if the strut was initially low on oil. If you feel little or no resistance while pivoting, or you can pivot the strut more than 60 degrees, the internal pivot/shimmy damper plate screws are likely damaged. If this is the case the strut has no functional shimmy damping.
   4. If you hit stops in both directions, use a compass to determine if you have a strut with 45 or 60 degree pivot limits.
6. Remove the block under the nose wheel and reinstall the Schrader valve.
7. Measure the strut full extension distance and record for use below.
8. With the strut fully extended, re-inflate using nitrogen to 200 PSI for L320 & L360 nose struts, 250-300 PSI for all others.
9. Lower the jacks and set the aircraft back on the nose wheel.
10. Bounce the nose to compress the strut and measure the extension. A compression of 1" to 1 ¼" from full extension is good for the 3-series, IV series and Legacy aircraft nose struts; 1" to 2" for the Legacy main struts.
11. Add or release pressure as required to achieve this extension with weight on the strut/wheel. Removing weight from the strut/wheel is recommended when adding nitrogen. See "Method for Servicing Nose and Main Gear Struts on Lancair Legacy,ES, and IV with ESCO Struts" by the Lancair Corporation for more detailed servicing instructions.

A lot of Lancairs are flying today with no centering function and a pivot limit of 45 degrees on the nose strut. Upgrading your strut to incorporate these functions is possible, but not mandatory. If, however, your strut has been damaged and has lost its active shimmy damping you are strongly encouraged to send it to Risse Racing for repair/overhaul. Without a functioning damper you will experience a nose gear shimmy sooner or later. Significant damage, including engine mount cracks and component failure leading to nose gear collapse, have resulted from nose wheel shimmy.

I'll leave you with a couple more servicing tips. Don't try to taxi your Lancair with a flat nose strut. The prop clearance is so little that you're asking for a prop strike. Take off with a flat nose strut will require acceleration to a higher speed, and therefore more runway, before you can rotate to take off attitude. A flat strut is often accompanied by oil leaking around the wheel. This indicates seal failure in most cases and dictates removal and return to Risse Racing for overhaul/servicing in any case. A flat strut without oil present almost always indicates failure of the Schrader valve/valve base gasket. Fix this by checking the oil level per instructions above, replacing the valve (it's a special high-pressure unit; available from Aircraft Spruce), replacing the base gasket if needed, and re-inflating with nitrogen. If it goes flat again, look for a crack in the strut assembly. The only ways the nitrogen can get out of an inflated strut are 1) through the inflation valve/valve base, 2) around the seals in the lower part of the strut (always accompanied by oil), 3) around the safety-wired bolts on the front of the strut (always accompanied by oil), 4) damper key screw retainer O-rings (inside the strut), and 5) a crack in the strut piston or cylinder (4 & 5 may or may not be accompanied by oil).

NOTE: This information is provided as a courtesy and on a voluntary basis. Neither LOBO nor the providing individuals take responsibility for the accuracy, completeness, or applicability to your aircraft or situation. Assess and use this information as you think best.

Updated: 2/2024